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__________ HIGHLIGHTS REVISION NO. 48 Feb 01/10 Pages which have been revised are outlined below, together with the Highlights of the Revision -------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------CHAPTER 34 __________

L.E.P. 1-24 REVISED TO REFLECT THIS REVISION INDICATING NEW,REVISED, AND/OR DELETED PAGES T. OF C. REVISED TO REFLECT THIS REVISION 1- 53 34-00-00 EFFECTIVITY UPDATED 3 EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

240-249, 251-299, 313-399, 501-509, 511-526, 528-599,

34-10-00 1, 34

EFFECTIVITY UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-10-00 201, 203204, 207208, 210, 219- 220, 223

EFFECTIVITY UPDATED CIRCUIT BREAKER(S) DATA UPDATED

34-10-00 301- 326

EFFECTIVITY UPDATED MOD.20653P1014 INCORPORATED NAVIGATION - REPLACE PITOT PROBES. LAYOUT IMPROVED/MATERIAL RELOCATED DELETION OF CALL OUT POST SB 34-1354 01 NAVIGATION - SENSORS, POWER SUPPLY AND SWITCH ING - INSTALL THALES PITOT PROBES P/N C16195B A. EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-10-00 502, 507, 513

240-249, 251-299, 313-399, 501-509, 511-526, 528-599, 062-099, 204-249, 401-499, 528-599, 001-049, 151-199, 301-399, 511-526,

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

CIRCUIT BREAKER(S) DATA UPDATED

106-149, 151-199, 251-299, 301-399, 501-509, 511-526, 051-099, 101-149, 201-249, 251-299, 401-499, 501-509, 528-599,

ALL ALL ALL

106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526,

34-HIGHLIGHTS Page REVISION NO. 48 CES

1 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------528-599, 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-11-00 01 REPRINTED 2

001-049, 101-105, 151-199, 201-203,

34-11-00 02 MOD.38480P10660 INCORPORATED 1- 31 NAVIGATION - ADIRU - INSTALL HONEYWELL ADIRU BLOCK III STANDARD L3.5 NEW TOPIC/NEW CONFIGURATION

524-526, 528-599,

34-11-00 03 EFFECTIVITY UPDATED 1- 15, REPRINTED 17- 26, 28- 29, 31- 37 EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

524-526, 528-599,

34-11-00 508- 509, 512, 514, 516- 517, 526- 529

EFFECTIVITY UPDATED CIRCUIT BREAKER(S) DATA UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-11-15 401- 403, 406, 408412

MOD.20446P1579 REMOVED ICE AND RAIN PROTECTION - PROBE HEAT COMPUTER - REPLACE POWER SUPPLY COMPUTERS. CORRECTION/ADDITION/AMPLIFICATION ADDED WARNING 3439 IN PARA. 4.A.(12). CIRCUIT BREAKER(S) DATA UPDATED WARNING/NOTE/REASON FOR THE JOB AMENDED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

051-099, 251-299, 501-509, 051-099, 251-299, 501-509,

106-149, 301-399, 511-523, 106-149, 301-399, 511-523,

204-249, 401-499,

240-249, 251-299, 313-399, 501-509, 511-526, 528-599, ALL ALL

EFFECTIVITY UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-11-16 401- 407, 410- 415

EFFECTIVITY UPDATED MOD.20446P1579 REMOVED ICE AND RAIN PROTECTION - PROBE HEAT COMPUTER - REPLACE POWER SUPPLY COMPUTERS.

ALL ALL 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599,

34-11-15 602, 604608

106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, ALL

34-HIGHLIGHTS Page REVISION NO. 48 CES

204-249, 401-499,

2 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------CORRECTION/ADDITION/AMPLIFICATION ADDED WARNING RELATED TO SPECIFIED SEQUENCE FOR CIRCUIT BREAKER OPENING. REPRINTED CIRCUIT BREAKER(S) DATA UPDATED WARNING/NOTE/REASON FOR THE JOB AMENDED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

ALL

34-11-17 401, 403404, 408410, 412413

EFFECTIVITY UPDATED CIRCUIT BREAKER(S) DATA UPDATED

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-11-17 503

CIRCUIT BREAKER(S) DATA UPDATED

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-11-18 401- 404, 406, 408410, 413414

34-11-18 502- 503, 505

EFFECTIVITY UPDATED MOD.20446P1579 REMOVED ICE AND RAIN PROTECTION - PROBE HEAT COMPUTER - REPLACE POWER SUPPLY COMPUTERS. CORRECTION/ADDITION/AMPLIFICATION ADDED WARNING RELATED TO SPECIFIED SEQUENCE FOR CIRCUIT BREAKER OPENING. CIRCUIT BREAKER(S) DATA UPDATED WARNING/NOTE/REASON FOR THE JOB AMENDED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

EFFECTIVITY UPDATED CIRCUIT BREAKER(S) DATA UPDATED

001-049, 151-199, ALL ALL 051-099, 211-249, 401-499, 528-599,

051-099, 101-105, 201-220, 236-238,

062-099, 204-249, 401-499, 528-599, 062-099, 203-249, 401-499, 528-599,

106-149, 151-199, 251-299, 301-399, 501-509, 511-526,

062-099, 204-249, 401-499, 528-599, 062-099, 204-249, 401-499, 528-599,

106-149, 151-199, 251-299, 301-399, 501-509, 511-526,

106-149, 159-199, 251-299, 301-399, 501-509, 511-526,

103-149, 151-199, 251-299, 301-399, 501-509, 511-526,

106-149, 151-199, 251-299, 301-399, 501-509, 511-526,

ALL ALL ALL ALL 051-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 34-HIGHLIGHTS Page REVISION NO. 48

CES

3 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------401-499, 528-599, 062-099, 204-249, 401-499, 528-599,

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-11-18 602- 603

34-11-19 401- 413

MOD.20446P1579 REMOVED ICE AND RAIN PROTECTION - PROBE HEAT COMPUTER - REPLACE POWER SUPPLY COMPUTERS. CIRCUIT BREAKER(S) DATA UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

ALL

MOD.20446P1579 REMOVED ICE AND RAIN PROTECTION - PROBE HEAT COMPUTER - REPLACE POWER SUPPLY COMPUTERS. CORRECTION/ADDITION/AMPLIFICATION ADDED WARNING W34/44 RELATED TO THE DRAIN HOL E. CIRCUIT BREAKER(S) DATA UPDATED WARNING/NOTE/REASON FOR THE JOB AMENDED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

ALL

34-12-00 02 MOD.30368P6578 INCORPORATED 1- 29 INDICATING RECORDING SYSTEMSEIS-INSTALL DMC, DU AND DISKETTES FOR EIS2 MOD.38480P10660 INCORPORATED NAVIGATION - ADIRU - INSTALL HONEYWELL ADIRU BLOCK III STANDARD L3.5 NEW TOPIC/NEW CONFIGURATION 34-12-00 03 EFFECTIVITY UPDATED 1, 3, EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) 57, 9- 10, 14- 19, 21- 24, 28- 31, 33, 3536, 3841

501-509, 511-526, 106-149, 151-199, 251-299, 301-399, 501-509, 511-526,

ALL 051-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

ALL ALL ALL 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 524-526, 528-599,

524-526, 528-599, 524-526, 528-599, 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523,

34-HIGHLIGHTS Page REVISION NO. 48 CES

4 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------34-12-34 402- 403, 406- 407

CIRCUIT BREAKER(S) DATA UPDATED

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-12-34 606

EFFECTIVITY UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-12-51 402, 405, 407, 411413

CORRECTION/ADDITION/AMPLIFICATION MODIFIED TOLERANCE VALUES FOR X AND Y. TOOL DESIGNATION(S) DATA UPDATED CIRCUIT BREAKER(S) DATA UPDATED

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-13-00 02 MOD.38480P10660 INCORPORATED 1- 55 NAVIGATION - ADIRU - INSTALL HONEYWELL ADIRU BLOCK III STANDARD L3.5 NEW TOPIC/NEW CONFIGURATION 34-13-00 03 EFFECTIVITY UPDATED 1, 3- EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) 17, 1930, 3877 34-13-00 404- 405

EFFECTIVITY UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-13-00 502, 505, 510, 516520, 528, 531, 533534, 536, 540- 541,

EFFECTIVITY UPDATED CORRECTION/ADDITION/AMPLIFICATION MODIFIED NOTE IN PARA.4 CIRCUIT BREAKER(S) DATA UPDATED

062-099, 204-249, 401-499, 528-599, 062-099, 204-249, 401-499, 528-599,

106-149, 151-199, 251-299, 301-399, 501-509, 511-526, 106-149, 151-199, 251-299, 301-399, 501-509, 511-526,

240-249, 251-299, 313-399, 501-509, 511-526, 528-599, ALL ALL 062-099, 204-249, 401-499, 528-599, 062-099, 204-249, 401-499, 528-599,

106-149, 151-199, 251-299, 301-399, 501-509, 511-526, 106-149, 151-199, 251-299, 301-399, 501-509, 511-526,

524-526, 528-599, 524-526, 528-599, 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523,

240-249, 251-299, 501-509, 511-526, 528-599, 151-199, 301-399, 401-499, 001-049, 151-199, 301-399, 511-526,

051-099, 101-149, 201-249, 251-299, 401-499, 501-509, 528-599,

34-HIGHLIGHTS Page REVISION NO. 48 CES

5 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------543- 546, 554- 555, 557, 567570, 574577, 597, A502-A505, A507-A509, A513-A514, A521-A524, A531-A532, A539-A543

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

001-049, 151-199, 301-399, 511-526,

34-13-00 603

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

34-14-00 02 MOD.33240P8194 INCORPORATED 1- 68 NAVIGATION - ADIRS ACTIVATE ALIGNMENT IMPROVEMENT FUNCTION ON ADIRU MOD.38480P10660 INCORPORATED NAVIGATION - ADIRU - INSTALL HONEYWELL ADIRU BLOCK III STANDARD L3.5 NEW TOPIC/NEW CONFIGURATION 34-14-00 03 EFFECTIVITY UPDATED 13, EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) 57, 11- 14, 16- 19, 21, 2325, 2831, 3439, 5465, 6872, 75, 78-A041 34-14-00 502- 503, 505, 509510, 513, 515, 517, 519- 520, 522- 549

EFFECTIVITY UPDATED MOD.38480P10660 INCORPORATED NAVIGATION - ADIRU - INSTALL HONEYWELL ADIRU BLOCK III STANDARD L3.5 CORRECTION/ADDITION/AMPLIFICATION MODIFIED STEP (5). ADDED (IR2) (IR3). CIRCUIT BREAKER(S) DATA UPDATED

051-099, 101-149, 201-249, 251-299, 401-499, 501-509, 528-599,

524-526, 528-599,

524-526, 528-599, 524-526, 528-599, 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523,

524-526, 528-599, 001-049, 151-199, 301-399, 511-523, 001-049, 151-199,

051-099, 101-149, 201-249, 251-299, 401-499, 501-509, 051-099, 101-149, 201-249, 251-299,

34-HIGHLIGHTS Page REVISION NO. 48 CES

6 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES --------------------------------------------------------------------------------------

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-15-21 401

EFFECTIVITY UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-18-00 02 MOD.38480P10660 INCORPORATED 1- 50 NAVIGATION - ADIRU - INSTALL HONEYWELL ADIRU BLOCK III STANDARD L3.5 NEW TOPIC/NEW CONFIGURATION 34-18-00 03 EFFECTIVITY UPDATED 1, 3- EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) 8, 10, 12- 13, 15, 17, 19, 2123, 26, 28- 29, 32, 34, 36, 38, 41- 42, 44- 74, 76 34-20-00 501

EFFECTIVITY UPDATED CIRCUIT BREAKER(S) DATA UPDATED

301-399, 511-526, 001-049, 151-199, 301-399, 511-526,

401-499, 528-599, 051-099, 201-249, 401-499, 528-599,

501-509, 101-149, 251-299, 501-509,

240-249, 251-299, 313-399, 501-509, 511-526, 528-599, 524-526, 528-599, 524-526, 528-599, 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523,

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

106-149, 251-299, 501-509, 106-149, 251-299, 501-509,

221-235, 301-399, 511-526, 221-235, 301-399, 511-526,

34-21-00 505, 507508, 523

CORRECTION/ADDITION/AMPLIFICATION ADDED NOTE IN PARA.4A.

001-049, 051-099, 101-105, 151-199, 201-220, 236-238,

34-21-22 401- 402, 405- 406

CORRECTION/ADDITION/AMPLIFICATION ADDED EXTRACTING TOOL REFERENCE F1402369.

001-049, 051-099, 101-105, 151-199, 201-220, 236-238,

34-21-25 401- 402

CORRECTION/ADDITION/AMPLIFICATION ADDED EXTRACTING TOOL REFERENCE F1402369.

001-049, 051-099, 101-105, 34-HIGHLIGHTS Page REVISION NO. 48

CES

239-249, 401-499, 528-599, 239-249, 401-499, 528-599,

7 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------34-21-26 401- 402

CORRECTION/ADDITION/AMPLIFICATION ADDED EXTRACTING TOOL REFERENCE F1402369.

34-22-00 02 EFFECTIVITY UPDATED 1- 27, CIRCUIT BREAKER(S) DATA UPDATED 29- 44 EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-22-00 503, 507508, 511533, 535536

EFFECTIVITY UPDATED LAYOUT IMPROVED/MATERIAL RELOCATED CIRCUIT BREAKER(S) DATA UPDATED

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-22-23 401- 402, 404- 406

EFFECTIVITY UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-22-24 401- 404, 407- 408

CORRECTION/ADDITION/AMPLIFICATION ADDED EXTRACTING TOOL REFERENCE F1402369.

34-22-25 301- 307

EFFECTIVITY UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-22-25 401- 402, 404- 411

EFFECTIVITY UPDATED CORRECTION/ADDITION/AMPLIFICATION ADDED EXTRACTING TOOL REFERENCE F1402369. CIRCUIT BREAKER(S) DATA UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

001-049, 051-099, 101-105, 151-199, 201-220, 236-238, 106-149, 251-299, 501-509, 106-149, 251-299, 501-509,

221-235, 301-399, 511-526, 221-235, 301-399, 511-526,

001-049, 151-199, 401-499, 001-049, 151-199, 301-399, 511-526, 001-049, 151-199, 301-399, 511-526,

051-099, 101-149, 201-239, 301-312, 051-099, 201-249, 401-499, 528-599, 051-099, 201-249, 401-499, 528-599,

101-149, 251-299, 501-509, 101-149, 251-299, 501-509,

062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 001-049, 051-099, 101-105, 151-199, 201-220, 236-238,

106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 106-149, 251-299, 501-509, 106-149, 251-299, 501-509, 106-149,

221-235, 301-399, 511-526, 221-235, 301-399, 511-526, 221-235,

34-HIGHLIGHTS Page REVISION NO. 48 CES

239-249, 401-499, 528-599, 239-249, 401-499, 528-599,

239-249, 401-499, 528-599, 239-249, 401-499, 528-599, 239-249,

8 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-22-25 501- 510, 515- 523

EFFECTIVITY UPDATED CIRCUIT BREAKER(S) DATA UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-22-25 601- 603

EFFECTIVITY UPDATED CIRCUIT BREAKER(S) DATA UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-22-25 701- 703

EFFECTIVITY UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-36-00 03 EFFECTIVITY UPDATED 1- 51 CIRCUIT BREAKER(S) DATA UPDATED

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-36-00 03 EFFECTIVITY UPDATED 501- 519 CIRCUIT BREAKER(S) DATA UPDATED

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-36-11 402, 407, 409- 410

CIRCUIT BREAKER(S) DATA UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

106-149, 251-299, 501-509, 106-149, 251-299, 501-509,

221-235, 301-399, 511-526, 221-235, 301-399, 511-526,

239-249, 401-499, 528-599, 239-249, 401-499, 528-599,

106-149, 251-299, 501-509, 106-149, 251-299, 501-509,

221-235, 301-399, 511-526, 221-235, 301-399, 511-526,

239-249, 401-499, 528-599, 239-249, 401-499, 528-599,

106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 001-049, 201-234, 301-307, 501-509, 001-049, 201-234, 301-307, 501-509,

101-149, 236-249, 312-399, 511-526, 101-149, 236-249, 312-399, 511-526,

151-199, 251-299, 401-499, 528-599, 151-199, 251-299, 401-499, 528-599,

001-049, 201-234, 301-307, 501-509, 001-049, 201-234, 301-307, 501-509,

101-149, 236-249, 312-399, 511-526, 101-149, 236-249, 312-399, 511-526,

151-199, 251-299, 401-499, 528-599, 151-199, 251-299, 401-499, 528-599,

051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 001-049, 051-099, 101-149, 34-HIGHLIGHTS Page REVISION NO. 48

CES

9 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------151-199, 201-234, 236-249, 251-299, 301-307, 311-399, 401-499, 501-509, 511-526, 528-599, 34-36-16 402- 403, 405, 408, 410, 414, 417- 418

EFFECTIVITY UPDATED CIRCUIT BREAKER(S) DATA UPDATED

062-099, 204-249, 401-499, 528-599, 001-049, 151-199, 301-399, 511-526,

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-36-18 402, 406407, 409410

LAYOUT IMPROVED/MATERIAL RELOCATED CIRCUIT BREAKER(S) DATA UPDATED

ALL 051-099, 311-399, 528-599, 001-049, 151-199, 251-299, 401-499, 528-599,

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-36-31 01 MOD.26377P4789 INCORPORATED 407- 430 NAVIGATION - ILS - INSTALL ADDITIONAL WIRING PROVISIONS FOR MMR INSTALLATION MOD.28655P6042 INCORPORATED ELECTRICAL AND ELECTRONIC COMMON INSTALLATION - STANDARDIZE CIRCUIT BREAKERS FUNCTIONAL DESIGNATION PLACARDS MOD.37446P10134 INCORPORATED NAVIGATION - ILS (MMR)- INSTALL THALES MMR STANDARD P/N TLS755-01-0102A SB 34-1147 21 INCORPORATED NAVIGATION - ILS - REMOVE ILS COMPUTER AND IN STALL ADDITIONAL WIRING PROVISIONS FOR MMR IN STALLATION SB 34-1373 INCORPORATED NAVIGATION - ILS (MMR) - INSTALL THALES MMR S TANDARD P/N TLS755-01-0102A. LAYOUT IMPROVED/MATERIAL RELOCATED 34-41-00 03 EFFECTIVITY UPDATED 1, 7, CIRCUIT BREAKER(S) DATA UPDATED

106-149, 151-199, 251-299, 301-399, 501-509, 511-526, 051-099, 101-149, 201-249, 251-299, 401-499, 501-509, 528-599, 239-249, 251-299, 501-509, 511-526, 051-099, 201-234, 301-307, 501-509,

101-149, 236-249, 311-399, 511-526,

001-049, 201-234, 301-307, 501-509, ALL

101-149, 236-249, 312-399, 511-526,

151-199, 251-299, 401-499, 528-599,

001-049, 201-234, 301-307, 501-509, ALL

101-149, 236-249, 312-399, 511-526,

151-199, 251-299, 401-499, 528-599,

ALL ALL

051-099, 239-249, 251-299, 34-HIGHLIGHTS Page REVISION NO. 48

CES

10 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------14- 16, 21, 23, 27, 29, 31- 33, 38- 39, 45, 5053, 5764, 6668, 7172, 7475, 7879, 81, 85- 86, 93, 97, A001-A004, A008,A012, A025-A027, A030,A032A033,A039A044,A049A050,A054, A058,A063, A065,A067, A072,A079A083 34-41-00 503- 504, 509- 512, 520, 528530, 533, 536, 539, 543

EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

EFFECTIVITY UPDATED CIRCUIT BREAKER(S) DATA UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-41-11 03 EFFECTIVITY UPDATED 402- 403, CORRECTION/ADDITION/AMPLIFICATION 406, 408- ADDED TORQUE VALUES. 415 CIRCUIT BREAKER(S) DATA UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-41-12

311-399, 528-599, 001-049, 151-199, 301-399, 511-526,

501-509, 511-526,

051-099, 311-399, 528-599, 051-099, 201-249, 401-499, 528-599,

239-249, 251-299, 501-509, 511-526,

001-049, 151-199, 301-399, 511-526, 051-099, 311-399, 528-599, 051-099, 251-299, 501-509,

051-099, 201-249, 401-499, 528-599, 239-249, 501-509,

051-099, 101-149, 201-249, 251-299, 401-499, 501-509, 528-599,

106-149, 151-199, 251-299, 301-399, 501-509, 511-526,

251-299, 511-526,

106-149, 201-249, 301-399, 401-499, 511-526, 528-599,

EFFECTIVITY UPDATED 34-HIGHLIGHTS Page REVISION NO. 48

CES

101-149, 251-299, 501-509,

11 of 16 Feb 01/10

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------401- 402, 404, 406409

MOD.34315P8614 INCORPORATED NAVIGATION - WEATHER RADAR SYSTEM DEACTIVATE THE LINK BETWEEN WXR2-EGPWS (2ND PART: DEACTIVATION OF THE DISCRET) CIRCUIT BREAKER(S) DATA UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-41-33 401- 403, 405- 407

EFFECTIVITY UPDATED CIRCUIT BREAKER(S) DATA UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-41-37 401- 402, 404, 406407, 409, 413- 414

EFFECTIVITY UPDATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

34-41-41 401, 408

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EFFECTIVITY UPDATED MOD.150716P11728 INCORPORATED NAVIGATION - RADIO ALTIMETER - INSTALL A NEW GASKET BETWEEN RADIO ALTI ANTENNA AND A/C SKIN SIL34-0069 01 REMOVED/REJECTED NAVIGATION - NEW TEFLON SEAL FOR LLRA MICROSTRIP ANTENNAS LAYOUT IMPROVED/MATERIAL RELOCATED EFFECTIVITY UPDATED (THROUGHOUT THE TEXT)

106-149, 229-235, 239-249, 251-299, 302-399, 401-499, 501-509, 511-526, 528-599, 051-099, 311-399, 528-599, 001-049, 151-199, 301-399, 511-526,

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051-099, 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 051-099, 311-399, 528-599, 051-099, 311-399, 528-599,

239-249, 251-299, 501-509, 511-526, 239-249, 251-299, 501-509, 511-526,

001-049, 051-099, 101-149, 201-249, 251-299, 501-509, 511-526, 528-599, 001-049, 151-199, 301-399, 511-526, ALL

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001-049, 151-199, 401-499, 528-599, 001-049, 151-199, 301-399,

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001-049, 151-199, 401-499, 528-599, 001-049, 151-199, 301-399, 511-526,

051-099, 101-149, 201-249, 301-399, 501-509, 511-526,

001-049, 151-199, 401-499, 528-599, 001-049, 151-199, 401-499, 528-599,

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051-099, 101-149, 201-249, 251-299, 401-499, 501-509, 528-599,

051-099, 101-149, 201-249, 301-399, 501-509, 511-526,

001-049, 051-099, 101-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

001-049, 051-099, 101-105, 151-199, 251-299, 501-509, 511-526, 528-599,

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CHAPTER 34 __________ NAVIGATION LIST OF EFFECTIVE PAGES _______________________ N, R or D indicates pages which are New, Revised or Deleted respectively Remove and insert the affected pages and complete the Record of Revisions and the Record of Temporary Revisions as necessary CH/SE/SU

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DATE Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10

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401 Feb01/10 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49

May01/08 May01/05 Feb01/08 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 Aug01/06 May01/05 May01/05 May01/05 May01/05 Feb01/08 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 Feb01/08 Feb01/08 Feb01/08 May01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/08

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34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00 34-18-00

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DATE Feb01/08 Feb01/08 Feb01/08 Feb01/07 Feb01/07 Feb01/07 Feb01/07 Feb01/07 Feb01/07 Feb01/07 Feb01/07 Feb01/07 Feb01/07 Feb01/07 Feb01/08 Feb01/07 Feb01/07 Feb01/08 Feb01/08 Feb01/08 Feb01/08 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10

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DATE Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/08 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/08 Feb01/10 Feb01/08 Feb01/10 Feb01/10 Feb01/08 Feb01/10 Feb01/08 Feb01/10 Feb01/08 Feb01/10 Feb01/08 Feb01/10 Feb01/10 Feb01/10 Aug01/09 Feb01/08 Feb01/10 Feb01/08 Feb01/10 Feb01/10 Nov01/09 Nov01/09

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32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76

DATE Feb01/10 Feb01/08 Feb01/10 Feb01/08 Feb01/10 Feb01/08 Feb01/10 Nov01/09 Nov01/09 Feb01/10 Feb01/10 Feb01/08 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/08 Feb01/10

501 Feb01/10 1 Aug01/09 2 May01/05 3 Feb01/08

CH/SE/SU 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-00 34-21-22 34-21-22 34-21-22 34-21-22 34-21-22 34-21-22 34-21-22 34-21-22 34-21-22 34-21-22 34-21-22 34-21-22 34-21-25 34-21-25 34-21-25 34-21-25 34-21-25 34-21-25 34-21-25

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DATE Aug01/09 May01/05 Feb01/08 May01/05 Feb01/08 May01/05 Feb01/08 Aug01/09 Aug01/09 May01/08 Aug01/09 Aug01/09 Aug01/09 Feb01/10 Aug01/08 Feb01/10 Feb01/10 Aug01/08 Aug01/09 Aug01/09 Aug01/09 Feb01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/07 Feb01/08 Feb01/10 Feb01/10 Aug01/09 Aug01/09 Feb01/08 Aug01/09 Aug01/09 Aug01/09 Feb01/10 Feb01/10 Feb01/07 Feb01/07 Feb01/07 Feb01/07 Feb01/07

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34-21-26 34-21-26 34-21-26 34-21-26 34-21-26 34-21-26 34-21-26 34-21-26 34-21-26 34-21-26 34-21-26 34-21-26 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00

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401 402 403 404 405 406 407 408 409 410 501 502

Feb01/10 Feb01/10 Feb01/07 Feb01/08 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Feb01/08 Aug01/09 Aug01/09 Aug01/09

1 2 3 4 5 6 7 8 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30

Feb01/08 May01/05 Feb01/08 Feb01/08 Feb01/08 May01/05 Feb01/08 Feb01/08 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Aug01/09 Feb01/10 Feb01/10

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31 32 33 34 35 36 37 38 39 40 41 42 43 44 1 2 3 4 5 501 502 503 504 505 506 507 508 509 510 511 512 513 514 515 516 517 518 519 520 521 522 523 524 525 526 527 528 529 530 531 532

DATE Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Aug01/09 Nov01/03 Nov01/03 Nov01/03 Nov01/03 Nov01/06 Feb01/08 Feb01/10 Feb01/08 Feb01/09 Feb01/09 Feb01/10 Feb01/10 Feb01/09 Feb01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10

CH/SE/SU 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-00 34-22-23 34-22-23 34-22-23 34-22-23 34-22-23 34-22-23 34-22-23 34-22-23 34-22-23 34-22-24 34-22-24 34-22-24 34-22-24 34-22-24 34-22-24 34-22-24 34-22-24 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25

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533 534 535 536 537 538 401 402 403 404 405 406 407 601 602 401 402 403 404 405 406 407 408 301 302 303 304 305 306 307 401 402 403 404 405 406 407 408 409 410 411 501 502 503 504 505 506 507 508 509 510

DATE Feb01/10 Nov01/09 Feb01/10 Feb01/10 Nov01/09 Nov01/09 Feb01/10 Feb01/10 May01/05 Feb01/10 Feb01/10 Feb01/10 May01/00 May01/05 Feb01/98 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Aug01/09 Aug01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Aug01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10

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34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-22-25 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00 34-36-00

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Aug01/09 Aug01/08 Aug01/08 Aug01/08 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10

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32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15

DATE May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 May01/05 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09

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DATE May01/09 May01/09 May01/09 May01/09 Feb01/10 Feb01/10 May01/09 Feb01/10 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 Feb01/10 Feb01/10 May01/09 Feb01/10 Feb01/10 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09

CH/SE/SU 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00

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A A A A A A A A A A A A A A A A A

66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16

DATE Feb01/10 May01/09 May01/09 May01/09 Nov01/07 Nov01/07 Nov01/07 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 May01/09 May01/09 Feb01/10 May01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10

34-L.E.P. Page 21 Feb 01/10 CES

CH/SE/SU 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00

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17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 201 202 203 501 502 503 504 505 506 507 508 509 510 511 512 513 514 515

DATE Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Aug01/07 Aug01/07 Aug01/07 May01/08 Feb01/10 Feb01/10 Feb01/04 Feb01/04 May01/04 Nov01/07 Nov01/07 Nov01/07 Nov01/07 May01/07 Feb01/10 May01/07 May01/07 May01/07

CH/SE/SU 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-00 34-52-11 34-52-11 34-52-11 34-52-11 34-52-11 34-52-11 34-52-11 34-52-11 34-52-11 34-52-12 34-52-12 34-52-12 34-52-12 34-52-12 34-52-33 34-52-33 34-52-33 34-52-33 34-52-33 34-52-33 34-52-33 34-52-33 34-52-33

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516 517 518 519 520 521 522 523 524 525 526 527 528 529 530 531 532 533 534 535 536 537 538 539 540 541 542 543 401 402 403 404 405 406 407 408 409 401 402 403 404 405 401 402 403 404 405 406 407 408 409

DATE May01/07 May01/07 May01/07 May01/07 Feb01/10 May01/07 May01/07 May01/07 Aug01/07 May01/07 May01/07 May01/07 May01/07 Aug01/09 Feb01/10 May01/07 May01/07 Aug01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 May01/07 May01/07 May01/07 May01/07 Feb01/98 Feb01/03 Feb01/98 Feb01/98 Feb01/09 Feb01/09 Feb01/09 Feb01/09 Feb01/09 Feb01/03 Nov01/01 Feb01/98 Feb01/03 Feb01/98 Feb01/10 Feb01/10 Feb01/10 Aug01/02 Feb01/99 Feb01/10 Feb01/10 Feb01/99 Feb01/02

CH/SE/SU 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00

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1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51

DATE Feb01/10 Feb01/10 Aug01/05 Feb01/10 May01/09 May01/09 Feb01/10 May01/09 May01/09 May01/09 Feb01/10 Feb01/10 May01/09 Feb01/10 Feb01/10 May01/09 Feb01/10 May01/09 Feb01/10 Feb01/10 Feb01/10 Nov01/09 Feb01/10 Nov01/09 Nov01/09 Feb01/10 Nov01/09 Aug01/09 Nov01/09 Nov01/09 Nov01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Aug01/09 Aug01/09 Feb01/10 Aug01/09 Feb01/10 Aug01/09 Aug01/09 Feb01/10 Feb01/10 Aug01/09 Feb01/10 Nov01/09 Feb01/10 Feb01/10 Nov01/09

34-L.E.P. Page 22 Feb 01/10 CES

CH/SE/SU 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-00 34-53-11 34-53-11 34-53-11 34-53-11 34-53-11 34-53-11 34-53-11 34-53-11 34-53-11 34-53-11 34-53-11 34-53-11 34-53-11 34-53-31 34-53-31 34-53-31 34-53-31 34-53-31 34-53-31 34-53-31 34-53-31

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R R R R R R R R R

52 53 54 55 56 57 58 59 60 61 501 502 503 504 505 506 507 508 509 510 511 512 513 514 515 516 517 518 519 520 401 402 403 404 405 406 407 408 409 410 411 412 413 401 402 403 404 405 406 407 408

DATE Feb01/10 Feb01/10 Nov01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/98 Nov01/08 May01/09 Feb01/10 Feb01/10 May01/09 May01/09 May01/09 May01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 May01/09 May01/09 Feb01/10 May01/09 Feb01/10 Feb01/10 Feb01/10 Aug01/09 May01/09 May01/04 Feb01/10 Aug01/08 Feb01/10 Feb01/10 Feb01/10 May01/09 May01/04 Feb01/10 Feb01/10 Feb01/10 May01/09 May01/09 Feb01/10 Feb01/10 May01/09

CH/SE/SU 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00

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1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51

DATE May01/05 Feb01/10 Feb01/10 Aug01/05 May01/04 May01/05 May01/05 May01/05 Nov01/08 Feb01/10 May01/05 May01/05 Nov01/08 Nov01/08 Feb01/10 Nov01/07 Nov01/07 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Nov01/07 Feb01/10 Nov01/09 Feb01/10 Feb01/10 Nov01/09 Feb01/10 Nov01/09 Nov01/09 Nov01/09 Feb01/10 Nov01/09 Nov01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Nov01/07 Nov01/07 Nov01/07 Feb01/10 Nov01/07 Nov01/09 Nov01/07

CH/SE/SU 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-00 34-55-11 34-55-11 34-55-11 34-55-11 34-55-11 34-55-11 34-55-11 34-55-11

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52 53 54 55 56 57 58 59 60 61 62 63 64 65 501 502 503 504 505 506 507 508 509 510 511 512 513 514 515 516 517 518 519 520 521 522 523 524 525 526 527 528 529 401 402 403 404 405 406 407 408

DATE Feb01/10 Nov01/07 Nov01/09 Feb01/10 Nov01/07 Feb01/10 Nov01/07 Nov01/07 Feb01/10 Nov01/07 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/98 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Feb01/10 Nov01/08 Nov01/07 Nov01/08 Nov01/07 Feb01/10 Feb01/10 Feb01/10 Nov01/07 Nov01/07 Nov01/07 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Feb01/10 Feb01/10 Nov01/07 Nov01/07 Nov01/07 May01/05 May01/05 Feb01/98 Feb01/98 May01/05 May01/07 May01/00 May01/00

34-L.E.P. Page 23 Feb 01/10 CES

CH/SE/SU

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34-55-11 34-55-18 34-55-18 34-55-18 34-55-18 34-55-18 34-55-18 34-55-18 34-55-18 34-55-31 34-55-31 34-55-31 34-55-31 34-55-31 34-55-31 34-57-22 34-57-22 34-57-22 34-57-22 34-57-22 34-57-22 34-57-22 34-57-22 34-57-22 34-57-22 34-58-00

PAGE R R R R

01 01 01 01 01 02 02 02 02 02

DATE

409 401 402 403 404 405 406 407 408 401 402 403 404 405 406

Feb01/98 Feb01/10 Feb01/10 Feb01/10 Aug01/05 Feb01/09 Feb01/10 May01/07 Aug01/07 Feb01/98 Feb01/98 Feb01/98 Feb01/02 Feb01/98 Feb01/02

401 402 403 404 405 401 402 403 404 405

May01/05 May01/05 May01/07 May01/05 May01/05 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08

CH/SE/SU

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1 May01/05

34-L.E.P. Page 24 Feb 01/10 CES

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT NAVIGATION - GENERAL ____________________ DESCRIPTION AND OPERATION General System Description ADIRS Integrated Standby Instrument System (ISIS) (optional system) Landing and Taxiing Aids Independent Position Determining Dependent Position Determining

________ CH/SE/SU 34-00-00

__________________________________ AIR DATA/INERTIAL REFERENCE SYSTEM _______ (ADIRS) DESCRIPTION AND OPERATION General

34-10-00

___________________________________ AIR DATA/INERTIAL REFERENCE SYSTEM ________ (ADIRS) MAINTENANCE PRACTICES ADIRS Start Procedure IR Alignment Procedure ADIRS Stop Procedure

34-10-00

___________________________________ AIR DATA/INERTIAL REFERENCE SYSTEM ________ (ADIRS) SERVICING Cleaning of the Pitot Probe Drain-Holes Flushing of the Principal Total Pressure Lines Flushing of the Principal Static Pressure Lines Draining and Flushing of Standby Pneumatic Circuits

34-10-00

___________________________________ AIR DATA/INERTIAL REFERENCE SYSTEM ________ (ADIRS) DEACTIVATION/REACTIVATION ADIRS - Check of all Flight Control Accelerometers for Correct Operation Refer to the MMEL TASK: 34-10-01

34-10-00

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ALL ALL ALL ALL ALL

4 6 8

ALL ALL ALL

1 1

ALL ALL

201 201 206 222

ALL ALL ALL ALL

301 301

ALL ALL

305

ALL

312

ALL

315

001-049, 051-099 101-105, 151-199 201-220, 236-238

401 401

ALL ALL

401

ALL

34-CONTENTS R CES

Page 1 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

___________________________________ AIR DATA/INERTIAL REFERENCE SYSTEM ________ (ADIRS) ADJUSTMENT/TEST Check of the ADIRS CDU Brightness and Display Test of the Angle of Attack Warning Operational Test of the 5-minute Time Delay of ADIRU 2 and 3 Power Disconnection in Emergency Configuration SENSORS, POWER SUPPLY AND SWITCHING DESCRIPTION AND OPERATION

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34-10-00 501 501

ALL ALL

505

ALL

511

ALL

34-11-00 1

1

General

1

Component Location

2

Power Supply

5

General

5

ADIRS Power Supply Distribution in Normal Configuration ADIRS Power Supply Distribution after Loss of Main Electrical Generation Circuit Breakers

7

Component Description

9 11 12

Static Probes

12

Pitot Probes

12

Air Data Modules (ADM)

15

Total Air Temperature (TAT) Sensor Angle Of Attack (AOA) Sensor

25

Selector Switches

32

27

001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199,

101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203

001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199,

101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105

34-CONTENTS R CES

Page 2 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

Selector Switches DESCRIPTION AND OPERATION General Component Location Power Supply General ADIRS Power Supply Distribution in Normal Configuration ADIRS Power Supply Distribution after Loss of Main Electrical Generation Circuit Breakers Component Description Static Probes Pitot Probes Air Data Modules (ADM) Total Air Temperature (TAT) Sensor Angle Of Attack (AOA) Sensor Selector Switches DESCRIPTION AND OPERATION

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3

524-526, 528-599

11 12 12 12 12 23

524-526, 524-526, 524-526, 524-526, 524-526, 524-526,

528-599 528-599 528-599 528-599 528-599 528-599

26 30 1

524-526, 524-526, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249,

528-599 528-599 106-149 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 251-299

General

1

Component Location

2

Power Supply

5

General

5

ADIRS Power Supply Distribution in Normal Configuration

7

ADIRS Power Supply Distribution after Loss of Main Electrical

10

34-CONTENTS R CES

Page 3 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ Generation Circuit Breakers

Component Description

Static Probes

Pitot Probes

Air Data Modules (ADM)

Total Air Temperature (TAT) Sensor Angle Of Attack (AOA) Sensor

Selector Switches Selector Switches

SENSORS, POWER SUPPLY AND SWITCHING ADJUSTMENT/TEST Functional Test of the ADM Test of the Monitoring of the ADR/AOA 26VAC Power Supply Test of the Monitoring of the ADIRS Power Supply (115VAC-28VDC) PROBE - PITOT REMOVAL/INSTALLATION

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34-11-00 501 501 507

ALL ALL ALL

515

ALL

401

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34-11-15 34-CONTENTS

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT Removal of the Pitot Probe (9DA1, 9DA2, 9DA3) Installation of the Pitot Probe (9DA1, 9DA2, 9DA3) PROBE - PITOT ADJUSTMENT/TEST Test of the Pitot Probe (9DA1, 9DA2, 9DA3) without the CFDS PROBE - PITOT INSPECTION/CHECK Inspection/Check of the Pitot Probe (9DA1, 9DA2, 9DA3) PROBE - STATIC REMOVAL/INSTALLATION Removal of the Static Probe (7DA1, 7DA2, 7DA3, 8DA1, 8DA2, 8DA3) Installation of the Static Probe (7DA1, 7DA2, 7DA3, 8DA1, 8DA2, 8DA3) PROBE - STATIC ADJUSTMENT/TEST Test of the Static Probe (7DA1, 8DA1, 7DA2, 8DA2, 7DA3, 8DA3) without the CFDS. PROBE - STATIC INSPECTION/CHECK Inspection of the Static Probe (7DA1, 7DA2, 7DA3, 8DA1, 8DA2, 8DA3) MODULE - AIR DATA REMOVAL/INSTALLATION Removal of the Air Data Module (19FP1, 19FP2, 19FP3, 19FP4, 19FP5, 19FP6, 19FP7, 19FP8) Installation of the Air Data Module (19FP1, 19FP2, 19FP3, 19FP4, 19FP5, 19FP6, 19FP7, 19FP8) MODULE - AIR DATA ADJUSTMENT/TEST Test of the Air Data Module without the CFDS SENSOR - TOTAL AIR TEMPERATURE REMOVAL/INSTALLATION Removal of the TAT Sensor (11FP1, 11FP2) Installation of the TAT Sensor

CH/SE/SU ________

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ALL ALL

601 601

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408

ALL

501 501

ALL ALL

601 601

ALL ALL

401 401

ALL ALL

410

ALL

501 501

ALL ALL

401 401

ALL ALL

407

ALL

34-11-15

34-11-15

34-11-16

34-11-16

34-11-16

34-11-17

34-11-17

34-11-18

34-CONTENTS R CES

Page 5 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT (11FP1, 11FP2) SENSOR - TOTAL AIR TEMPERATURE ADJUSTMENT/TEST Test of the TAT Sensor (11FP1, 11FP2) without the CFDS SENSOR - TOTAL AIR TEMPERATURE INSPECTION/CHECK Inspection/Check of the TAT Sensor (11FP1, 11FP2) SENSOR - ANGLE OF ATTACK REMOVAL/INSTALLATION Removal of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3) Installation of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3) SENSOR - ANGLE OF ATTACK INSPECTION/CHECK

CH/SE/SU ________

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ALL ALL

601 601

ALL ALL

401 401

ALL ALL

405

ALL

601

001-049, 151-158, 001-049, 151-158,

101-105 201-209 101-105 201-209

001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199,

101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203

34-11-18

34-11-19

34-11-19

Inspection of the Angle-Of-Attack Sensor (3FP1, 3FP2, 3FP3) AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRU & CDU OR MSU) DESCRIPTION AND OPERATION

PAGE ___________ ____ EFFECTIVITY

601 34-12-00 1

1

General

1

Component Location

1

Interface

4

Mechanical Interface

4

Electrical Interface

4

Component Description

23

ADIRS CDU

23

ADIRU

25

AIR DATA, INERTIAL REFERENCE SYSTEM (ADIRU & CDU OR MSU) DESCRIPTION AND OPERATION General

34-12-00 2

1 1

524-526, 528-599 524-526, 528-599

34-CONTENTS R CES

Page 6 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT Component Location Interface Mechanical Interface Electrical Interface Component Description ADIRS CDU ADIRU AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRU & CDU OR MSU) DESCRIPTION AND OPERATION

CH/SE/SU ________

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34-12-00 3

1

General

1

Component Location

1

Interface

7

Mechanical Interface

7

Electrical Interface

7

Electrical Interface

9

Component Description

31

ADIRS CDU

31

ADIRS MSU

35

001-049, 101-149, 201-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-239, 401-499, 240-249, 313-399, 511-523, 051-099, 204-249, 301-399, 501-509, 051-099, 204-239, 401-499, 240-249, 313-399,

34-CONTENTS R CES

051-099 151-199 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 301-312 251-299 501-509 106-149 251-299 401-499 511-523 106-149 301-312 251-299 501-509 Page 7 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

ADIRU

CONTROL AND DISPLAY UNIT (CDU) - ADIRS REMOVAL/INSTALLATION

PAGE EFFECTIVITY ____ ___________ 511-523, 38 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523

34-12-12 401

Removal of the ADIRS CDU (2FP)

401

Installation of the ADIRS CDU (2FP)

405

REFERENCE UNIT - AIR DATA/INERTIAL (ADIRU) REMOVAL/INSTALLATION Removal of the ADIRU (1FP1, 1FP2, 1FP3) Installation of the ADIRU (1FP1, 1FP2, 1FP3) REFERENCE UNIT - AIR DATA/INERTIAL (ADIRU) INSPECTION/CHECK ADIRU Removal Criteria MOUNT - ADIRU REMOVAL/INSTALLATION Removal of the ADIRU Mount Installation of the ADIRU Mount AIR DATA DESCRIPTION AND OPERATION

401 401

ALL ALL

405

ALL

601 601

ALL ALL

CES

051-099 151-199 301-312

401 401 405

ALL ALL ALL

34-12-51

34-13-00 1

1

System Description

1

ADR Operation

1 38 38

001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049,

34-CONTENTS R

051-099 151-199 301-312

34-12-34

1

Control

051-099 151-199 301-312

34-12-34

General

Operation/Control and Indicating

001-049, 101-149, 201-239, 401-499, 001-049, 101-149, 201-239, 401-499, 001-049, 101-149, 201-239, 401-499,

101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 Page 8 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

Indicating Warnings DESCRIPTION AND OPERATION General System Description ADR Operation Operation/Control and Indicating Control Indicating Warnings DESCRIPTION AND OPERATION

General

System Description

ADR Operation

Operation/Control and Indicating

Control Control Indicating

Warnings

2

3

PAGE EFFECTIVITY ____ ___________ 151-199, 201-203 38 001-049, 101-105 151-199, 201-203 47 001-049, 101-105 151-199, 201-203 1 524-526, 528-599 1 524-526, 528-599 1 524-526, 528-599 1 524-526, 528-599 38 524-526, 528-599 38 524-526, 528-599 38 524-526, 528-599 47 524-526, 528-599 1 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 1 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 1 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 1 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 56 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 56 051-099, 106-149 204-239, 301-312 401-499, 56 240-249, 251-299 313-399, 501-509 511-523, 59 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 67 051-099, 106-149 204-239, 301-312 401-499, 34-CONTENTS

R CES

Page 9 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ Warnings

AIR DATA REMOVAL/INSTALLATION PFD Mach Number - Overspeed Check Reactivation of PFD Mach Number Overspeed Check

34-13-00

AIR DATA ADJUSTMENT/TEST Operational Test of the AIR DATA Switching Function Operational Test of the VMO/MMO Overspeed Warnings Operational Test of the ALT Comparison Warning Operational Test of the ALT DYNAMIC SLEW TEST Operational Test of the CAS DYNAMIC SLEW TEST Operational Test of the AOA SENSOR TEST Operational Test of the Overspeed Warnings in the Slats/Flaps and Landing Gear Extended (VFE/VLE) Configuration Functional Test of the Altitude and Airspeed Data

34-13-00

C _

____ EFFECTIVITY PAGE ___________ 67 240-249, 251-299 313-399, 501-509 511-523,

401 401 407

ALL ALL ALL

501 501

ALL ALL

508

ALL

522

ALL

527

ALL

532

ALL

537

ALL

538

ALL

558

001-049, 101-105, 201-209, 001-049, 151-199, 251-299, 401-499, 511-526, ALL

Functional Test of the Altitude and Airspeed Data (A/C with RVSM capability on three ADIRUs)

567

Leak Test of the Principal Static and Total Air Data System INTERFACE TEST of the ADR SYSTEM TEST of the ADR Read the CFDIU for the ADR CURRENT STATUS Read the CFDIU for the ADR INPUT STATUS

599 A511 A529 A534 A539

CES

101-149 201-249 301-399 501-509 528-599

ALL ALL 001-049, 151-199, 051-099, 204-249,

34-CONTENTS R

051-099 151-158

101-105 201-203 106-149 251-299 Page 10 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

AIR DATA INSPECTION/CHECK Visual Check of Pitot probes, Static ports and AOA sensors ATTITUDE, HEADING AND POSITION DESCRIPTION AND OPERATION

C _

PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 501-509, 511-526 528-599,

34-13-00 601 601 34-14-00 1

1

General

1

System Description

1

General

1

Inputs Inputs

2 3

Inputs

5

Software Computation

10

IR, GPS and GPIRS Output Data IR, GPS and GPIRS Output Data

15 24

Operation/Control and Indicating

46

Control

46

Indicating

55

Indicating Warnings

55 67

ADIRUs Performance Criteria

74

DESCRIPTION AND OPERATION General System Description General Inputs Software Computation

ALL ALL

2

1 1 1 1 2 7

001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-004, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-004, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 201-203, 001-049, 151-199, 001-049, 151-199, 524-526, 524-526, 524-526, 524-526, 524-526, 524-526,

34-CONTENTS R CES

101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 101-105 201-203 101-105 201-203 528-599 528-599 528-599 528-599 528-599 528-599 Page 11 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

IR, GPS, and GPIRS Output Data Operation/Control and Indicating Control Indicating Warnings ADIRUs Performance Criteria DESCRIPTION AND OPERATION

General

System Description

General

Inputs

General

Inputs

Software Computation

C _

3

____ EFFECTIVITY PAGE ___________ 17 524-526, 528-599 42 524-526, 528-599 42 524-526, 528-599 50 524-526, 528-599 59 524-526, 528-599 59 524-526, 528-599 1 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 1 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 1 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 1 051-057, 059-060 062-099, 106-149 204-215, 217-217 219-219, 221-225 227-233, 236-238 301-304, 2 051-057, 059-060 062-099, 106-149 204-215, 217-217 219-219, 221-225 227-233, 236-238 301-304, 2 058-058, 061-061 216-216, 218-218 220-220, 226-226 234-235, 239-249 251-299, 305-399 401-499, 501-509 511-523, 3 058-058, 061-061 216-216, 218-218 220-220, 226-226 234-235, 239-249 251-299, 305-399 401-499, 501-509 511-523, 19 051-099, 106-149 204-249, 251-299 34-CONTENTS

R CES

Page 12 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ Software Computation IR Output Data

IR, GPS, and GPIRS Output Data

Operation/Control and Indicating

Control Control Indicating Indicating Warnings Warnings ADIRUs Performance Criteria

ATTITUDE, HEADING AND POSITION ADJUSTMENT/TEST

C _

PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 501-509, 511-514 24 515-523, 42 051-057, 059-060 062-099, 106-149 204-215, 217-217 219-219, 221-225 227-233, 236-238 301-304, 54 058-058, 061-061 216-216, 218-218 220-220, 226-226 234-235, 239-249 251-299, 305-399 401-499, 501-509 511-523, 99 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 99 051-099, 106-149 204-239, 301-312 401-499, A 3 240-249, 251-299 313-399, 501-509 511-523, A 15 051-099, 106-149 204-239, 301-312 401-499, A 16 240-249, 251-299 313-399, 501-509 511-523, A 30 051-099, 106-149 204-239, 301-312 401-499, A 36 240-249, 251-299 313-399, 501-509 511-523, A 38 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523

34-14-00 501

ALL

34-CONTENTS R CES

Page 13 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT Operational Test of the Attitude/Heading (ATT/HDG) Switching Function Operational Test of the Attitude/Heading (ATT/HDG) Comparison Warning Interface Test of the IR Read CFDIU for IR CURRENT STATUS

CH/SE/SU ________

C _

Read CFDIU for IR INPUT STATUS

SYSTEM TEST of the Inertial Reference (IR) INDICATOR - ANGLE OF ATTACK REMOVAL/INSTALLATION

507

ALL

516 536

ALL 001-049, 151-199, 051-099, 204-249, 301-399, 501-509, 528-599, ALL

101-105 201-203 106-149 251-299 401-499 511-526

240-249, 313-399, 511-526, 240-249, 313-399, 511-526,

251-299 501-509 528-599 251-299 501-509 528-599

001-049, 101-149, 201-233, 301-304, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049, 151-199, 001-049,

051-099 151-199 236-238 401-402 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105 201-203 101-105

540

545 34-15-21 401

Installation of the AOA Indicator (17FN1, 17FN2) ADIRS - BITE DESCRIPTION AND OPERATION

____ ___________ PAGE EFFECTIVITY 501 ALL

401

34-18-00 1

1

General

1

Component Location

3

Computers Directly Linked to the CFDS ADIRS Control Panel

3

Other LRUs of the System

4

System Description Reporting Function

3

5 5

Interactive Function

33

Power-up Test Initialization and

64

34-CONTENTS R CES

Page 14 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

Cockpit Repercussions AIR DATA, INERTIAL REFERENCE SYSTEM (ADIRS) BUILT-IN TEST EQUIPMENT (BITE) DESCRIPTION AND OPERATION General Component Location Computers Directly Linked to the CFDS ADIRS Control Panel Computers Directly Linked to the CFDS Other LRUs of the System System Description Reporting Function Interactive Function Power-up Test Initialization and Cockpit Repercussions

34-18-00

ADIRS - BITE DESCRIPTION AND OPERATION

34-18-00

2

3

PAGE EFFECTIVITY ____ ___________ 151-199, 201-203

1 1 3 3

524-526, 524-526, 524-526, 524-526,

3 3

524-526, 528-599 524-526, 528-599

3 5 5 23 50

524-526, 524-526, 524-526, 524-526, 524-526,

528-599 528-599 528-599 528-599 528-599

1

001-049, 101-149, 201-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-249, 301-399, 501-509, 051-099, 204-239, 401-499, 240-249, 313-399, 511-523, 051-099, 204-249, 301-399,

051-099 151-199 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 251-299 401-499 511-523 106-149 301-312

General

1

Component Location

5

Computers Directly Linked to the CFDS

5

ADIRS Control Panel

5

ADIRS Control Panel

6

Other LRUs of the System

7

34-CONTENTS R CES

528-599 528-599 528-599 528-599

251-299 501-509 106-149 251-299 401-499 Page 15 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

System Description

Reporting Function

Interactive Function

Power-up Test Initialization and Cockpit Repercussions Power-up Test Initialization and Cockpit Repercussions __________________________ STANDBY NAVIGATION SYSTEMS ADJUSTMENT/TEST

PAGE EFFECTIVITY ____ ___________ 501-509, 511-523 8 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 8 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 47 051-099, 106-149 204-249, 251-299 301-399, 401-499 501-509, 511-523 75 051-099, 106-149 204-239, 301-312 401-499, 76 240-249, 251-299 313-399, 501-509 511-523,

34-20-00 501

ISIS Reset

STANDBY DATA : ALTITUDE AND AIRSPEED DESCRIPTION AND OPERATION

C _

501

221-235 251-299 401-499 511-526

001-049, 101-105, 201-220, 001-049, 101-105, 201-220, 001-049, 101-105, 201-220, 001-049, 101-105, 201-220, 001-049,

051-099 151-199 236-238 051-099 151-199 236-238 051-099 151-199 236-238 051-099 151-199 236-238 051-099

1 1

Component Location

1

System Description

4 11

34-CONTENTS R CES

221-235 251-299 401-499 511-526

34-21-00

General

Standby Altimeter

106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599,

Page 16 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ Standby Airspeed Indicator Metric Altimeter Metric Altimeter

STANDBY DATA : ALTITUDE AND AIRSPEED ADJUSTMENT/TEST

C _

PAGE EFFECTIVITY ____ ___________ 101-105, 151-199 201-220, 236-238 11 001-049, 051-099 101-105, 151-199 201-220, 236-238 12 001-049, 051-099 101-105, 12 213-213,

34-21-00 501

Low-Range Leak Test of the Standby Pneumatic Circuits

501

Functional Test of the Standby Airspeed Indicator

512

Functional Test of the Standby Altimeter

518

ALTIMETER - STANDBY REMOVAL/INSTALLATION

401 401

Installation of the Standby Altimeter (3FN)

406

Removal of the Metric Altimeter (15FN) Installation of the Metric

001-049, 101-105, 201-220, 001-049, 101-105, 201-220, 001-049, 101-105, 201-220,

051-099 151-199 236-238 051-099 151-199 236-238 051-099 151-199 236-238

001-049, 101-105, 201-220, 001-049, 101-105, 201-220,

051-099 151-199 236-238 051-099 151-199 236-238

34-21-22 501

ADJUSTING/ALIGNING/CALIBRATING of the Standby Altimeter ALTIMETER - METRIC REMOVAL/INSTALLATION

051-099 151-199 236-238 051-099 151-199 236-238 051-099 151-199 236-238 051-099 151-199 236-238

34-21-22

Removal of the Standby Altimeter (3FN)

ALTIMETER - STANDBY ADJUSTMENT/TEST

001-049, 101-105, 201-220, 001-049, 101-105, 201-220, 001-049, 101-105, 201-220, 001-049, 101-105, 201-220,

501 34-21-25 401 401 404

001-049, 051-099 101-105, 001-049, 051-099 101-105, 001-049, 051-099

34-CONTENTS R CES

Page 17 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT Altimeter (15FN) INDICATOR - STANDBY AIRSPEED REMOVAL/INSTALLATION

CH/SE/SU ________

C _

PAGE EFFECTIVITY ____ ___________ 101-105,

34-21-26 401

Removal of the Standby Airspeed Indicator (9FN)

401

Installation of the Standby Airspeed Indicator (9FN)

406

INDICATOR - STANDBY AIRSPEED ADJUSTMENT/TEST

General

051-099 151-199 236-238 051-099 151-199 236-238 051-099 151-199 236-238

001-049, 101-105, 201-220, 001-049, 101-105, 201-220,

051-099 151-199 236-238 051-099 151-199 236-238

001-049, 101-105, 201-212, 236-238, 001-049, 101-105, 201-212, 236-238, 001-049, 101-105, 201-212, 236-238, 001-049, 101-105, 201-212, 236-238, 001-049, 101-105, 201-212, 236-238, 001-049, 101-105, 201-212, 236-238, 001-049, 101-105,

051-099 151-199 214-220

34-21-26 501

ADJUSTING/ALIGNING/CALIBRATING of the Standby Airspeed Indicator STANDBY DATA : ATTITUDE AND HEADING DESCRIPTION AND OPERATION

001-049, 101-105, 201-220, 001-049, 101-105, 201-220, 001-049, 101-105, 201-220,

501

34-22-00 1

1

1

Standby Heading

1

Standby Attitude

1

Component Location

1

System Description

1

Standby Compass

4

34-CONTENTS R CES

051-099 151-199 214-220 051-099 151-199 214-220 051-099 151-199 214-220 051-099 151-199 214-220 051-099 151-199 214-220 051-061 201-203 Page 18 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

Standby Compass Standby Horizon Indicator

STANDBY DATA : INTEGRATED STANDBY INSTRUMENT SYSTEM (ISIS) DESCRIPTION AND OPERATION

General

____ EFFECTIVITY PAGE ___________ 4 062-099, 151-199 204-212, 214-220 236-238, 4 001-049, 051-099 101-105, 151-199 201-212, 214-220 236-238,

34-22-00 2

1

1

ISIS Indicator

1

Standby Compass

1

Component Location

1

System Description

1

ISIS Indicator

1

Standby Compass

16

106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599, 106-149,

34-CONTENTS R CES

221-235 251-299 401-499 511-526 221-235 251-299 401-499 511-526 221-235 251-299 401-499 511-526 221-235 251-299 401-499 511-526 221-235 251-299 401-499 511-526 221-235 251-299 401-499 511-526 221-235 251-299 401-499 511-526 221-235 Page 19 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

Power Supply

ISIS Indicator

Standby Compass

Interface

Mechanical Interface

Peripherals

Component Description

External Description

Internal Description

C _

PAGE EFFECTIVITY ____ ___________ 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 16 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 16 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 21 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 21 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 21 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 21 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 27 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 27 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 27 106-149, 221-235 239-249, 251-299 34-CONTENTS

R CES

Page 20 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

Operation

System Performance

Control and Indicating

Test

BITE Description

STANDBY DATA : ATTITUDE AND HEADING DESCRIPTION AND OPERATION General Standby Heading Standby Attitude Component Location System Description Standby Compass Standby Horizon Indicator

34-22-00

STANDBY DATA : ATTITUDE AND HEADING ADJUSTMENT/TEST Operational Check of the standby compass including light test and visual check Compensation Adjustment/Test of

34-22-00

3

PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 501-509, 511-526 528-599, 33 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 33 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 36 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 39 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 39 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 1 1 1 1 1 1 1 2

213-213, 213-213, 213-213, 213-213, 213-213, 213-213, 213-213, 213-213,

501 501

ALL ALL

505

ALL

34-CONTENTS R CES

Page 21 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT the Standby Compass Compensation Adjustment/Test of the Standby Compass with the Standby Compass Calibrator COMPASS - STANDBY REMOVAL/INSTALLATION Removal of the Standby Compass (2FN) Installation of the Standby Compass (2FN) COMPASS - STANDBY INSPECTION/CHECK Detailed Visual Inspection of the Standby Compass Damping Fluid INDICATOR - STANDBY HORIZON REMOVAL/INSTALLATION

CH/SE/SU ________

C _

PAGE ___________ ____ EFFECTIVITY 524

ALL

401 401

ALL ALL

405

ALL

601 601

ALL ALL

401

001-049, 101-105, 201-220, 001-049, 101-105, 201-220, 001-049, 101-105, 201-220,

051-099 151-199 236-238 051-099 151-199 236-238 051-099 151-199 236-238

106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599,

221-235 251-299 401-499 511-526

106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399,

221-235 251-299 401-499 511-526

34-22-23

34-22-23

34-22-24

Removal of the Standby Horizon Indicator (7FN)

401

Installation of the Standby Horizon Indicator (7FN)

405

INDICATOR - ISIS (INTEGRATED STANDBY INSTRUMENT SYSTEM) SERVICING

34-22-25 301

Draining and Flushing of the Standby Static and Standby Total Pressure lines (ISIS) INDICATOR - ISIS (INTEGRATED STANDBY INSTRUMENT SYSTEM) REMOVAL/INSTALLATION

Removal of the ISIS Indicator (22FN)

301

34-22-25 401

401

34-CONTENTS R CES

221-235 251-299 401-499 511-526

221-235 251-299 401-499 Page 22 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

Installation of the ISIS Indicator (22FN)

INDICATOR - ISIS (INTEGRATED STANDBY INSTRUMENT SYSTEM) ADJUSTMENT/TEST

C _

PAGE EFFECTIVITY ____ ___________ 501-509, 511-526 528-599, 406 106-149, 221-235 239-249, 251-299 301-399, 401-499 501-509, 511-526 528-599,

34-22-25 501

Operational Check of ISIS DC HOT Bus SUPPLY

501

BITE Test of the ISIS Indicator with the pushbutton switches on the Face of the Indicator.

504

Low range Leak Test of the Standby Pneumatic circuits

507

Functional Test of the ISIS Indicator

518

INDICATOR - ISIS (INTEGRATED STANDBY INSTRUMENT SYSTEM) INSPECTION/CHECK

ISIS Inspection for Legibility

106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599,

221-235 251-299 401-499 511-526

106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599,

221-235 251-299 401-499 511-526

CES

221-235 251-299 401-499 511-526 221-235 251-299 401-499 511-526 221-235 251-299 401-499 511-526

34-22-25 601

601

34-CONTENTS R

221-235 251-299 401-499 511-526

221-235 251-299 401-499 511-526 Page 23 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT INDICATOR - ISIS (INTEGRATED STANDBY INSTRUMENT SYSTEM) CLEANING/PAINTING

________ CH/SE/SU 34-22-25

C _

701

Cleaning of the ISIS Indicator

ILS

PAGE ___________ ____ EFFECTIVITY 221-235 251-299 401-499 511-526

701

106-149, 239-249, 301-399, 501-509, 528-599, 106-149, 239-249, 301-399, 501-509, 528-599,

1 1 1 3 3 3 7 14 14 14 14 16 40 40 40 42 42 44 44 44

001-004, 001-004, 001-004, 001-004, 001-004, 001-004, 001-004, 001-004, 001-004, 001-004, 001-004, 051-060, 001-004, 001-004, 001-004, 001-004, 001-004, 001-004, 001-004, 001-004,

051-060 051-060 051-060 051-060 051-060 051-060 051-060 051-060 051-060 051-060

50 50

051-060, 051-060,

51

051-060,

51

001-004, 051-060

53

001-004, 051-060

1

001-049, 051-099

34-36-00 DESCRIPTION AND OPERATION General Component Location System Description Principle System Architecture Utilization Technical Data Warnings Power Supply Interface Receiver Receiver Antennas Component Description Control Reconfiguration Switching Operation Access to ILS Sub-Menu Functions Activation of the Self-Test Activation of the Functional Test Access to ILS Sub-Menu Functions Activation of the Receiver Face Test Activation of the Functional Test Power-up Tests Initialization and Cockpit Repercussions CFDIU Interface

ILS ((MMR)) DESCRIPTION AND OPERATION

1

CES

051-060 051-060 051-060 051-060 051-060

34-36-00 2

34-CONTENTS R

221-235 251-299 401-499 511-526

Page 24 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

General

ILS Receiver

GPS Receiver

Component Location

System Description

ILS Operation

GPS Operation

Maintenance Operation

Power Supply

Interface

ILS Interface

C _

PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-238, 301-311 401-499, 1 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 1 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 1 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 1 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 3 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 3 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 3 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 6 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 6 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 7 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 7 001-049, 051-099 101-149, 151-199 201-238, 301-311 34-CONTENTS

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Page 25 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ GPS Interface

Component Description

MMR MMR GPS Antenna

Localizer Antenna

Glide Slope Antenna

Operation

ILS Operation

GPS Function

BITE Function

CFDIU Interface CFDIU Interface BITE Implementation

C _

PAGE EFFECTIVITY ____ ___________ 401-499, 9 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 13 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 13 051-099, 19 001-049, 101-149 151-199, 201-238 301-311, 401-499 23 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 23 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 23 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 26 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 26 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 34 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 43 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 43 051-099, 58 001-049, 101-149 151-199, 201-238 301-311, 401-499 62 051-099, 34-CONTENTS

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Page 26 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT DESCRIPTION AND OPERATION

General

ILS Receiver

GPS Receiver

Component Location

System Description

ILS Operation

GPS Operation

CH/SE/SU ________

_ C 3

____ EFFECTIVITY PAGE ___________ 1 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 1 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 1 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 1 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 1 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 3 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 3 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 3 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 34-CONTENTS

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Page 27 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ Maintenance Operation

Power Supply

Interface

ILS Interface

GPS Interface

Component Description

MMR

GPS Antenna

C _

PAGE EFFECTIVITY ____ ___________ 401-499, 501-509 511-526, 528-599 6 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 6 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 7 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 7 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 9 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 13 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 13 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 18 001-049, 101-149 151-199, 201-234 34-CONTENTS

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Page 28 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

Localizer Antenna

Glide Slope Antenna

Operation

ILS Operation

GPS Function

BITE Function

CFDIU Interface

C _

PAGE EFFECTIVITY ____ ___________ 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 20 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 20 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 22 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 22 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 30 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 39 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 39 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 34-CONTENTS

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Page 29 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

ILS ADJUSTMENT/TEST BITE Test of the ILS Operational Test of the ILS Functional Test of the ILS

34-36-00

ILS ((MMR)) ADJUSTMENT/TEST

34-36-00

C _

PAGE ___________ ____ EFFECTIVITY

1

501 501 507 510

001-004, 001-004, 001-004, 001-004,

051-060 051-060 051-060 051-060

2

501

001-049, 101-149, 201-238, 401-499, 001-049, 101-149, 201-238, 401-499, 001-049, 101-149, 201-238, 401-499, 001-049, 101-149, 201-238, 401-499, 001-049, 101-149, 201-238, 401-499, 001-049, 151-199, 236-249, 301-307, 401-499, 511-526, 001-049, 151-199, 236-249, 301-307, 401-499, 511-526, 001-049, 151-199, 236-249, 301-307, 401-499,

051-099 151-199 301-311

BITE Test of the MMR

501

Operational Test of the GPS

507

Operational Test of the ILS

513

Functional Test of the ILS

516

ADJUSTMENT/TEST

3

501

BITE Test of the MMR

501

Operational Test of the GPS

506

34-CONTENTS R CES

051-099 151-199 301-311 051-099 151-199 301-311 051-099 151-199 301-311 051-099 151-199 301-311 101-149 201-234 251-299 312-399 501-509 528-599 101-149 201-234 251-299 312-399 501-509 528-599 101-149 201-234 251-299 312-399 501-509 Page 30 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

Operational Test of the MMR

Functional Test of the MMR

ANTENNA - LOCALIZER REMOVAL/INSTALLATION Removal of the Localizer Antenna (3RT) Installation of the Localizer Antenna (3RT) ANTENNA - GPS ACTIVE REMOVAL/INSTALLATION Removal of the GPS Active Antenna (43RT1, 43RT2) Installation of the GPS Active Antenna (43RT1, 43RT2) with Teflon Seal Installation of the GPS Active Antenna (43RT1, 43RT2) without Teflon Seal ANTENNA - GLIDE/SLOPE REMOVAL/INSTALLATION Removal of the Glide/Slope Antenna (4RT) Installation of the Glide/Slope Antenna (4RT) RECEIVER - ILS REMOVAL/INSTALLATION Removal of the ILS Receiver (2RT1, 2RT2) Installation of the ILS Receiver (2RT1, 2RT2) Installation of the ILS Receiver (2RT1, 2RT2) Removal of the Multi Mode Receiver (40RT1, 40RT2)

PAGE EFFECTIVITY ____ ___________ 511-526, 528-599 512 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599 515 001-049, 101-149 151-199, 201-234 236-249, 251-299 301-307, 312-399 401-499, 501-509 511-526, 528-599

34-36-11 401 401

ALL ALL

405

ALL

401 401

ALL ALL

406

ALL

412

ALL

401 401

ALL ALL

405

ALL

401 401

ALL 001-004, 051-060

404

001-004, 051-060

407

ALL

411

001-049, 051-099 101-149, 151-199 201-238, 301-311

34-36-16

34-36-18

34-36-31 1

34-CONTENTS R CES

Page 31 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

Installation of the Multi Mode Receiver (40RT1, 40RT2) Installation of the Multi Mode Receiver (40RT1, 40RT2) Removal of the Multi Mode Receiver (40RT1, 40RT2)

423

Installation of the Multi Mode Receiver (40RT1, 40RT2)

WEATHER RADAR SYSTEM DESCRIPTION AND OPERATION General Component Location System Description General

PAGE EFFECTIVITY ____ ___________ 401-499, 415 001-049, 051-099 101-149, 151-199 201-238, 301-311 401-499, 419 ALL

427

3

1 1 5 16 25

37

ALL ALL ALL ALL 001-049, 151-199, 301-310, 051-099, 251-299, 501-509, 528-599, 001-049, 101-149, 201-233, 501-509, 528-599, 234-235, 251-299, 401-499, ALL

38 39 39

ALL ALL ALL

27

Peripherals

31

Peripherals

33

34-CONTENTS R CES

101-149 201-234 251-299 312-399 501-509 528-599 101-149 201-234 251-299 312-399 501-509 528-599

34-41-00

General

General Technical Characteristics Power Supply Interface Digital Interface Special for Weather Radar

001-049, 151-199, 236-249, 301-307, 401-499, 511-526, 001-049, 151-199, 236-249, 301-307, 401-499, 511-526,

101-149 201-238 401-499 239-249 311-399 511-526 051-099 151-199 236-238 511-526 239-249 301-399

Page 32 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT Component Description Transceiver Transceiver Weather Radar System Weather Radar Antenna Weather Radar Antenna Weather Radar Control Unit

Weather Radar Control Unit Weather Radar Wave Guide and Wave Guide Switch Operation Operation

CH/SE/SU ________

C _

____ EFFECTIVITY PAGE ___________ 45 ALL 45 001-049, 101-105 151-199, 501-509 511-526, 528-599 53 051-099, 106-149 201-249, 251-299 301-399, 401-499 58 001-049, 101-105 151-199, 501-509 511-526, 528-599 67 001-049, 101-105 151-199, 501-509 511-526, 528-599 67 051-099, 106-149 201-249, 251-299 301-399, 401-499 71 001-049, 051-099 101-149, 151-199 201-233, 236-238 501-509, 511-526 528-599, 71 234-235, 239-249 251-299, 301-399 401-499, 71 ALL 72 72

Operation

73

Timing of Transmitted Pulses in WX/MAP Mode and in Doppler Mode (Turbulence) and W/S Mode Timing of Transmitted Pulses in WX/MAP Mode, in Doppler Mode (Turbulence) and in W/S Mode Pulse Duration and Range Timing

85

Controls and Indicating Utilization of Controls and Indicating

87 87

A

92 0

ALL 001-049, 151-199, 511-526, 051-099, 201-249, 301-399, 001-049, 151-199, 511-526, 051-099, 201-233, 234-235, 251-299, 401-499, ALL 001-049, 151-199, 301-310,

34-CONTENTS R CES

101-105 501-509 528-599 106-149 251-299 401-499 101-105 501-509 528-599 106-149 236-238 239-249 301-399 101-149 201-238 401-499 Page 33 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

Utilization of Controls and Indicating Reconfiguration switching Reconfiguration switching

Test BITE Description BITE Description Self-Test

WEATHER RADAR SYSTEM ADJUSTMENT/TEST Functional test of the Tilt Control of the Weather-Radar Antenna Drive-Unit BITE Test of the Weather Radar System Test of the Weather Radar ANTENNA ASSEMBLY - WEATHER RADAR REMOVAL/INSTALLATION Removal of the Weather Radar Antenna Assembly (7SQ, 11SQ) Installation of the Weather Radar Antenna Assembly (7SQ, 11SQ) CONTROL UNIT - WEATHER RADAR REMOVAL/INSTALLATION Removal of the Weather Radar Control Unit (3SQ) Installation of the Weather Radar Control Unit (3SQ) TRANSCEIVER - WEATHER RADAR REMOVAL/INSTALLATION Removal of the Weather Radar Transceiver (1SQ1, 1SQ2)

____ EFFECTIVITY PAGE ___________ A 1 051-099, 239-249 251-299, 311-399 501-509, 511-526 528-599, A 48 001-049, 101-149 151-199, 201-238 301-310, 401-499 A 49 051-099, 239-249 251-299, 311-399 501-509, 511-526 528-599, A 50 ALL A 50 001-049, 101-105 151-199, 501-509 511-526, 528-599 A 50 051-099, 106-149 201-249, 251-299 301-399, 401-499 A 82 001-049, 101-105 151-199, 501-509 511-526, 528-599

34-41-00 501 501

ALL ALL

508 532

ALL ALL

401 401

ALL ALL

409

ALL

401 401

ALL ALL

406

ALL

401 401

ALL ALL

34-41-11 3

34-41-12

34-41-33

34-CONTENTS R CES

Page 34 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT Installation of the Weather Radar Transceiver (1SQ1, 1SQ2) MOUNTING TRAY - WEATHER RADAR TRANSCEIVER REMOVAL/INSTALLATION Removal of the Weather Radar Transceiver Mounting Tray (9SQ) Installation of the Weather Radar Transceiver Mounting Tray (9SQ) WAVE GUIDE ASSEMBLY REMOVAL/INSTALLATION Removal of the Wave Guide Assembly Installation of the Wave Guide Assembly

CH/SE/SU ________

RADIO ALTIMETER DESCRIPTION AND OPERATION General Component Location System Description Principle System Architecture Utilization Technical Data Warnings Power Supply Component Description Transceiver Antennas Fans Operation Control Reconfiguration Switching Test Access to Radio Altimeter Sub-menu Functions Activation of the Test Function Activation of the Test Function Power-up Tests Initialization and Cockpit Repercussions CFDIU Interface

34-42-00

RADIO ALTIMETER ADJUSTMENT/TEST BITE Test of the Radio Altimeter Operational Check and Detailed

34-42-00

C _

____ ___________ PAGE EFFECTIVITY 406 ALL

34-41-37 401 401

ALL ALL

409

ALL

401 401 406

ALL ALL ALL

1 1 1 5 5 5 5 9 9 9 9 20 20 22 22 22 22 22

ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL

25 26 27

ALL 001-004, ALL

31

001-004,

34-41-41

501 501 505

ALL ALL ALL

34-CONTENTS R CES

Page 35 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT Inspection for Contamination of the Radio Altimeter Fan Ramp Test of the Radio Altimeter Warning Test of the Radio Altimeter ANTENNA - RADIO ALTIMETER REMOVAL/INSTALLATION Removal of the Radio Altimeter Antennas 5SA1, 5SA2, 6SA1, 6SA2 Installation of the Radio Altimeter Antennas 5SA1, 5SA2, 6SA1, 6SA2 TRANSCEIVER - RADIO ALTIMETER REMOVAL/INSTALLATION Removal of the Radio Altimeter Transceiver 2SA1 and 2SA2 Installation of the Radio Altimeter Transceiver 2SA1 and 2SA2 FAN - RADIO ALTIMETER TRANSCEIVER REMOVAL/INSTALLATION Removal of the Radio Altimeter-Transceiver Fan 3SA1 (3SA2) Installation of the Radio Altimeter-Transceiver Fan 3SA1 (3SA2) FAN - RADIO ALTIMETER TRANSCEIVER CLEANING/PAINTING Cleaning of the Radio Altimeter Transceiver Fan

CH/SE/SU ________

TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS) DESCRIPTION AND OPERATION General Presentation

34-43-00

C _

PAGE ___________ ____ EFFECTIVITY 510 515

ALL ALL

401 401

ALL ALL

414

ALL

401 401

ALL ALL

404

ALL

401 401

ALL ALL

405

ALL

701 701

ALL ALL

34-42-11

34-42-33

34-42-45

34-42-45

1

1 1 1

Presentation Presentation Presentation

3 4 6

Presentation

8

Principle

9

ALL ALL 001-049, 151-199, 051-099, 201-207, 501-509, 528-599, 106-149, 210-249, 401-499, ALL

34-CONTENTS R CES

101-105 208-209 251-299 511-526 201-207 301-399

Page 36 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

Advisories Display Coordination Component Location System Description TCAS Computer Directional Antennas ATC/TCAS Control Unit Associated Items Peripherals Associated Items Peripherals Associated Items Peripherals Power Supply Component Description TCAS Computer TCAS Computer TCAS Computer TCAS Computer ATC/TCAS Control Unit TCAS Antennas TCAS Antennas TCAS Antennas Operation Intruder Detection Intruder Detection Measurement of Intruder Parameters

C _

____ EFFECTIVITY PAGE ___________ 9 ALL 11 ALL 11 ALL 11 ALL 14 ALL 14 ALL 19 ALL 19 ALL 19 001-049, 101-149 151-199, 201-249 301-399, 401-499 20 001-049, 101-149 151-199, 201-249 301-399, 401-499 21 051-099, 251-299 22 051-099, 251-299 23 501-509, 511-526 528-599, 24 501-509, 511-526 528-599, 26 ALL 26 ALL 26 001-049, 101-105 151-199, 501-509 511-526, 528-599 34 051-099, 251-299 37 201-209, 40 106-149, 201-207 210-249, 301-399 401-499, 49 ALL 50 001-049, 101-105 151-199, 501-509 511-526, 528-599 50 051-099, 251-299 50 106-149, 201-249 301-399, 401-499 54 ALL 54 001-049, 101-149 151-199, 201-249 301-399, 401-499 58 051-099, 251-299 501-509, 511-526 528-599, 70 001-049, 101-105 151-199, 501-509 34-CONTENTS

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Page 37 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

Measurement of Intruder Parameters Measurement of Intruder Parameters Coordination Principles of Computation Definition of Target Aircraft

74 76 81 90

Definition of Target Aircraft Definition of Target Aircraft

Sensitivity Sensitivity Sensitivity Sensitivity

PAGE EFFECTIVITY ____ ___________ 511-526, 528-599 73 051-099, 251-299

93 95

Level Level Level Level

A 9 A 12 A 16 A 18

Information Display ATC/TCAS Control Unit Operational Use Test Self-Test

A 20 A 29 A 33 A 33

Self-Test Self-Test

A 36 A 38

Self-Test

A 41

CFDS

A 43

TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS) SERVICING Uploading Procedure with Portable Data Loader (SFIM or equivalent) to Load the Operational Software of the TCAS Uploading Procedure to Load the Operational Software of the TCAS

106-149, 301-399, ALL ALL 001-049, 101-149, 301-399, 062-099, 001-049, 101-105, 251-299, 511-526, 001-049, 051-099, 201-207, 001-049, 151-199, 301-399, 501-509, 528-599, ALL ALL

CES

051-061 201-249 401-499 051-061 151-199 501-509 528-599 101-105 251-299 101-149 201-249 401-499 511-526

ALL 001-049, 151-199, 051-099, 106-149, 301-399, 501-509, 528-599, ALL

101-105 251-299 201-249 401-499 511-526

34-43-00 1

301 301

ALL 001-049, 051-061 101-105,

307

106-149, 151-199 201-249, 251-299

34-CONTENTS R

201-249 401-499

Page 38 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

Uploading Procedure with Portable Data Loader (SFIM or equivalent) to Load the Operational Software of the TCAS TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS) DEACTIVATION/REACTIVATION Deactivation of the TCAS Refer to the MMEL TASK: 34-43-01 Reactivation of the TCAS Refer to the MMEL TASK: 34-43-01

34-43-00

TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS) ADJUSTMENT/TEST BITE Test of the TCAS Functional Test of the TCAS Antennas Read the TCAS CONFIGURATION Data of the TCAS ANTENNA - TCAS REMOVAL/INSTALLATION Removal of the TCAS Antenna (7SG1, 7SG2) Installation of the TCAS Antenna (7SG1, 7SG2) COMPUTER - TCAS REMOVAL/INSTALLATION Removal of the TCAS Computer (1SG) Installation of the TCAS Computer (1SG)

34-43-00

ENHANCED GROUND PROXIMITY WARNING SYSTEM (GPWS) DESCRIPTION AND OPERATION General Basic GPWS Modes Enhanced Features Component Location System Description

34-48-00

PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 501-509, 511-526 528-599, 312 062-099,

1

401 401 401 403 403

ALL ALL ALL ALL ALL

1

501 501 507

ALL ALL ALL

512

501-509, 511-526 528-599,

401 401

ALL ALL

409

ALL

1

401 401 404

ALL ALL ALL

1

1 1 3 5 7 14

ALL ALL ALL ALL ALL ALL

34-43-11 1

34-43-34

34-CONTENTS R CES

Page 39 Feb 01/10

CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ General Warnings Digital Data Inputs Digital Data Inputs

Digital Data Inputs

Digital Data Inputs Digital Data Inputs Discrete Data Inputs Discrete Data Inputs Discrete Data Inputs

Warning Outputs Warning Outputs Warning Outputs

Monitor Outputs

Monitor Outputs Bus Output Bus Output

C _

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ Bus Output

Audio Output Power Supply Interface Digital Outputs Digital Outputs

Digital Outputs Component Description Enhanced GPWC Enhanced GPWC Enhanced GPWC

Enhanced GPWC

Enhanced GPWC Pushbutton Switches

Pushbutton Switches Operation General Detailed Operation - Modes 1 through 5 Envelope Modulation

Envelope Modulation Enhanced Features Warning Generation and Inhibition Warning Generation and

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A 61 A 68 B 25 B 32

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

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Inhibition Warning Generation and Inhibition

PAGE ___________ ____ EFFECTIVITY B 35

Warning Generation and Inhibition Enhanced GPWC Maintenance Output

B 42 B 54

Test Self-Tests

B 54 B 56

Self-Tests

B 59

Self-Tests CFDS Interface

B 61 B 66

CFDS Interface BITE Implementation Power-up Test Initialization and Cockpit Repercussions

B 75 B 88 B 89

GROUND PROXIMITY WARNING SYSTEM (GPWS) DESCRIPTION AND OPERATION

001-049, 051-099 101-105, 151-199 201-214, ALL 001-049, 101-102, 201-202, 251-299, 401-499, 511-526, ALL 106-149, 236-238, 001-049, 101-105, 201-214, ALL 001-049, 101-149, 201-233, 301-304, ALL ALL 061-099, 151-199, 251-299, 401-499, 511-526,

051-099 106-149 211-249 301-399 501-509 528-599

001-049, 101-104, 001-049, 101-104, 001-049, 101-104, 001-049, 101-104, 001-049, 101-104, 001-049, 101-104, 001-004, 001-049,

051-060

CES

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34-48-00 2

1

General

1

Component Location

4

System Description

5

General

5

Warnings

5

Digital Data Inputs Digital Data Inputs

5 5

34-CONTENTS R

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ Discrete Data Inputs Discrete Data Inputs Warning Outputs Warning Outputs Monitor Output Bus Output Audio Output

Power Supply Component Description GPWC (1WZ) Pushbutton Switches SYS Pushbutton Switch 9WZ Operation General Detailed Operation - Modes 1 through 5 Envelope Modulation Envelope Modulation Warning Generation and Inhibition GPWC Maintenance Output Test Airborne Self-test Ground Self-Test Airborne Self-test

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ Ground Self-Test Ground Vocabulary Test Status History Test CFDS Interface Power-up Tests Initialization and Cockpit Repercussions

GROUND PROXIMITY WARNING SYSTEM (GPWS) SERVICING Uploading of the Enhanced GPWC Database

34-48-00

GROUND PROXIMITY WARNING SYSTEM (GPWS) ADJUSTMENT/TEST Operational Test of the Enhanced GPWS Ground Self-Test Function Operational Test of the Enhanced GPWS with Stall Warning Test and Activation of the GPWS/SYS Pushbutton Switch and EMER CANC Key BITE Test of the Enhanced GPWS COMPUTER - GROUND PROXIMITY WARNING (GPWC) REMOVAL/INSTALLATION Removal of the GPWC (1WZ) Installation of the GPWC (1WZ)

34-48-00

DME

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301 301

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501 501

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527

ALL

534

ALL

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34-51-00 DESCRIPTION AND OPERATION General Component Location System Description Principle

1 1 1 1 1

System Architecture

3

Utilization Technical Data

3

Principle

13

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ System Architecture Utilization Technical Data Principle System Architecture Utilization Technical Data Principle System Architecture Utilization Technical Data Principle System Architecture Utilization Technical Data

Power Supply Component Description DME Interrogator DME Interrogator

DME Antenna Operation Control Reconfiguration Switching BITE Function Access to DME Sub-menu Functions Activation of the Test Function Access to DME Sub-menu Functions

Activation of the Test Function

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____ EFFECTIVITY PAGE ___________ 13 051-099, 14 051-099, 15 106-149, 201-233 236-238, 301-304 15 106-149, 201-233 236-238, 301-304 16 106-149, 201-233 236-238, 301-304 18 234-235, 239-249 305-399, 401-499 18 234-235, 239-249 305-399, 401-499 19 234-235, 239-249 305-399, 401-499 20 251-299, 501-509 511-526, 528-599 20 251-299, 501-509 511-526, 528-599 21 251-299, 501-509 511-526, 528-599 21 ALL 23 ALL 23 001-049, 101-105 151-199, 25 051-099, 106-149 201-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 37 ALL 39 ALL 39 ALL 41 ALL 41 ALL 41 001-049, 101-105 151-199, 41 001-049, 101-105 151-199, 43 051-099, 106-149 201-249, 251-299 301-399, 401-499 501-509, 511-526 528-599, 43 051-099, 106-149 201-249, 251-299 301-399, 401-499 34-CONTENTS

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ CFDIU Interface BITE Implementation BITE Implementation BITE Implementation Power-up Tests Initialization and Cockpit Repercussions Power-up Tests Initialization and Cockpit Repercussions

DME ADJUSTMENT/TEST BITE Test of the DME Operational Test of the DME Functional Test of the DME ANTENNA - DME REMOVAL/INSTALLATION Removal of the DME Antenna (3SD1, 3SD2) Installation of the DME Antenna (3SD1, 3SD2) INTERROGATOR - DME REMOVAL/INSTALLATION Removal of the DME Interrogator (2SD1, 2SD2) Installation of the DME Interrogator (2SD1, 2SD2) ATC/MODE S (SELECT) DESCRIPTION AND OPERATION General Component Location System Description Principle

Principle

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9

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ Principle

System Architecture Warning Power Supply Interface

Control Panel Buses Transponder Buses Transponder Input Data

Transponder output buses

Component Description ATC Transponder ATC Transponder ATC Transponder ATC Transponder ATC Transponder ATC Transponder ATC/TCAS Control Unit Antenna Operation Control Reconfiguration Switching Test Maintenance Test CFDIU Interface CFDIU Interface CFDIU CFDIU CFDIU CFDIU

Interface Interface Interface Interface

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ BITE Implementation BITE Implementation Power-up Tests Initialization and Cockpit Repercussions

ATC/MODE S (SELECT) MAINTENANCE PRACTICES Change of ICAO Address (after a Change of Aircraft Registration Number)

34-52-00

ATC ADJUSTMENT/TEST BITE Test of the ATC Operational Test of the ATC Functional Test of the Altitude Reporting Function Functional Test of the ATC/Mode S Transponder Functional Test of the ATC/Mode S Transponder Functional Test of the ATC/Mode S Transponder Functional Test of the ATC Antennas ANTENNA - ATC REMOVAL/INSTALLATION Removal of the ATC Antenna (7SH1, 7SH2, 7SH3, 7SH4) Installation of the ATC Antenna (7SH1, 7SH2, 7SH3, 7SH4) CONTROL UNIT - ATC/TCAS REMOVAL/INSTALLATION Removal of the ATC/TCAS Control Unit (3SH) Installation of the ATC/TCAS Control Unit (3SH) TRANSPONDER - ATC/MODE S REMOVAL/INSTALLATION Removal of the ATC/Mode S

34-52-00

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ALL

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ALL

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401 401

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34-52-12

34-52-33

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT Transponder (1SH1, 1SH2) Installation of the ATC/Mode S Transponder (1SH1, 1SH2)

CH/SE/SU ________

ADF

34-53-00

C _

PAGE ___________ ____ EFFECTIVITY 406

DESCRIPTION AND OPERATION General Component Location System Description Principle System Architecture Utilisation Technical Data

1 1 1 4 4 7 14

Utilisation Technical Data Warning

17 20

Warning Power Supply Component Description ADF Receiver ADF Receiver

ADF Receiver Loop and Sense Antenna Operation Test Maintenance Test

21 21 22 22 23

27 39 39 41 41

Maintenance Test

44

Maintenance Test CFDIU Interface

47 47

ALL

ALL ALL ALL ALL ALL ALL 001-049, 101-149, 201-249, 401-499, 511-526, 251-299, 001-049, 101-149, 201-249, 401-499, 511-526, 251-299, ALL ALL 001-049, 151-199, 051-051, 106-149, 251-299, 401-499, 511-526, 052-052, ALL ALL ALL 001-049, 101-105, 501-509, 528-599, 106-149, 301-399, 251-299, 001-049, 053-099, 151-199,

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051-099 151-199 301-399 501-509 528-599 051-099 151-199 301-399 501-509 528-599

101-105 053-099 201-249 301-399 501-509 528-599

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

Power-up Tests Initialization and Cockpit Repercussions

Power-up Tests Initialization and Cockpit Repercussions ADF ADJUSTMENT/TEST BITE Test of the ADF Operational Test of the ADF ANTENNA - ADF LOOP AND SENSE REMOVAL/INSTALLATION Removal of the ADF Loop and Sense Antenna Installation of the ADF Loop and Sense Antenna RECEIVER - ADF REMOVAL/INSTALLATION Removal of the ADF Receiver (2RP1, 2RP2) Installation of the ADF Receiver (2RP1, 2RP2) VOR/MARKER DESCRIPTION AND OPERATION General Foreword VOR System MARKER System Foreword VOR System MARKER System Component Location System Description Principle

C _

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34-55-00 1 1 1 1 1 1 2 2 2 6 6

System Architecture

6

Utilization Technical Data

8

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________ Warning Principle System Architecture Utilization Technical Data Warning Principle System Architecture Utilization Technical Data

Power Supply Component Description VOR/MKR Receiver VOR/MKR Receiver

Antennas Operation Control Reconfiguration Switching BITE Function Access to the VOR/MKR Sub-menu Functions Activation of the Test Function Access to the VOR/MKR Sub-menu Functions

Activation of the Test Function

BITE Test

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ SUBJECT _______

CH/SE/SU ________

C _

CFDIU Interface BITE Test

CFDIU Interface

Power-up Tests Initialization and Cockpit Repercussions VOR/MARKER ADJUSTMENT/TEST BITE Test of the VOR/MKR Operational Test of the VOR/MKR Functional Test of the VOR/MKR ANTENNA - VOR REMOVAL/INSTALLATION Removal of the VOR Antenna 4RS Installation of the VOR Antenna 4RS ANTENNA - MARKER REMOVAL/INSTALLATION Removal of the Marker Antenna (1RS) Installation of the Marker Antenna (1RS) RECEIVER - VOR/MARKER REMOVAL/INSTALLATION Removal of the VOR/MKR Receiver (3RS1, 3RS2) Installation of the VOR/MKR Receiver (3RS1, 3RS2) RMI - VOR/DME REMOVAL/INSTALLATION

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ALL

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ALL

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34-55-11

34-55-18

34-55-31

34-57-22 1

Removal of the VOR/DME RMI (11FN) Installation of the VOR/DME RMI (11FN) RMI - VOR/ADF/DME

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CHAPTER 34 __________ NAVIGATION TABLE OF CONTENTS _________________ _______ SUBJECT REMOVAL/INSTALLATION

CH/SE/SU ________

Removal of the VOR/ADF/DME RMI (21FN) Installation of the VOR/ADF/DME RMI (21FN) SATELLITE NAVIGATION DESCRIPTION AND OPERATION General

_ C 2

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NAVIGATION - GENERAL - DESCRIPTION AND OPERATION ________________________________________________ 1. _______ General (Ref. Fig. 001) The aircraft navigation systems provide the crew with the data required for flight within the most appropriate safety requirements. These data can be divided into four groups : - Air Data/Inertial Reference System (ADIRS) - Landing and taxing aids - Independent position determining - Dependent position determining. 2. __________________ System Description A. ADIRS This part of the navigation system comprises : - three Air Data/Inertial Reference Units (ADIRU) - standby systems. Each ADIRU performs : - the air data function through its Air Data Reference (ADR) portion. - the attitude, heading and position function through its Inertial Reference (IR) portion. (1) Air data function Air data are provided by four independent sources : (a) Three main systems Each of the three main systems includes static probes, pitot probes and their associated Air Data Modules (ADM), Total Air Temperature (TAT) sensors and Angle of Attack (AOA) sensors. They provide the ADR portion of the ADIRU with the necessary data for the generation of parameters which are transmitted to the Primary Flight Displays (PFD) and Navigation Displays (ND) and the Angle of Attack (AOA) indicator (optional) and to the various aircraft systems. (b) A standby system 1 _ R R R R

The standby system includes a standby altimeter, a standby airspeed indicator and a metric altimeter (optional) (Ref. 34-21) and the optional system ISIS (Ref. 34-22). They are provided with pressure by static probes and pitot probe linked to the ADIRU 3. More explanations are given in the ADIRU system (Ref. 34-13).

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Navigation - Systems Overvieww Figure 001

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**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, (2) Attitude, heading and position function Attitude, heading and position data are provided by four independent sources: (a) Three main systems The three main systems are made up of the following components : - three IR portions - a Control and Display Unit (CDU). They provide inertial reference information, attitude (pitch, roll and yaw), heading, ground speed and present position. The primary information of rotation rates and linear acceleration measured by the IR portions are directly used by the Auto Flight System (AFS), by the Flight Augmentation Computer (FAC) and the Flight Management and Guidance Computer (FMGC). The IR data are transmitted to the indicators (PFD, ND and RMI) and to the various aircraft systems. (b) A standby system 1 _

R

The standby system includes a standby horizon indicator and a standby compass (Ref. 34-22). More explanations are given in the ADIRU system (Ref. 34-14).

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, (2) Attitude, heading and position function Four sources that operate independently supply the attitude, heading and position data. (a) Three primary systems The three primary systems have the components that follow: - Three IR portions - A Mode Selector Unit (MSU). They supply inertial reference, attitude (pitch, roll and yaw), heading, ground speed and position data. The Auto Flight System (AFS), the Flight Augmentation Computer (FAC) and the Flight Management and Guidance Computer (FMGC) directly use the primary data related to the rotation rates and linear acceleration measured by the IR parts. The IR data is transmitted to the indicators (PFD, ND and RMI) and to the different aircraft systems.

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(b) A standby system

R R R R

1 _

The standby system includes a standby horizon indicator and a standby compass (Ref. 34-22). More data is given in the ADIRU system chapter (Ref. 34-14).

**ON A/C ALL B. Integrated Standby Instrument System (ISIS) (optional system) The Integrated Standby Instrument System (ISIS) indicator replaces the three conventional standby instruments i.e.: - the standby altimeter (and standby altimeter in meters -optional-) - the standby airspeed indicator - the standby horizon indicator. The standby heading is given by a magnetic compass, which is an independent instrument. (1) The ISIS indicator, provides the following standby data on a Liquid Crystal Display (LCD) installed in place of the standby horizon: - Attitude, - Standard or baro-corrected altitude and related barometric pressure - Indicated airspeed and Mach number - Lateral acceleration and the following optional parameters: - ILS deviation - V-bar aircraft symbol - Barometric pressure in hPa or in hPa and in.Hg - Altitude in meters. In addition, two specific functions are available: - Display and adjustment of four airspeed bugs and four airspeed altitude bugs - Automatic test procedure. More explanations are given in the ISIS system (Ref. 34-22). C. Landing and Taxiing Aids This part of the navigation system comprises : (1) Paravisual Indicator (PVI) (optional system) The aircraft is equipped with one PVI installed on the glareshield panel 131VU, Captains side. This system provides the Captain with an image which serves as a piloting aid for take-off and landing in reduced visibility conditions. The system receives parameters from the DMC1 which can be switched to the DMC3, and generates the image. More explanations are given in the PVI system (Ref. 34-34).

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(2) Head Up Display (HUD) (optional system) The aircraft is equipped with : - a HUDC (Head Up Display Computer) - a OHU (Optical Head Unit). This system provides the Captain with an image superimposed on the outside world in his field of view. This image gives the guidance information in take-off, landing or approach configurations. The HUDC processes the input parameters received from the Display Management Computer 1 (DMC1), which can be switched to the DMC3, and sends them to the OHU after transformation. More explanations are given in the HUD system (Ref. 34-35). (3) Instrument Landing System (ILS) or Multi-Mode (optional system) Both ILS or MMR receivers are controlled from Management Panels (RMPs) featuring two output output and one dialog output. All data are shown on the EFIS displays. More explanations are given in the ILS system

Receiver (MMR) FMGCs and Radio channels, one command (Ref. 34-36).

(a) The ILS system enables to know the aircraft position during the landing phase with respect to a predetermined descent path. This system is composed of: - two ILS receivers - a Localizer antenna - a Glide/Slope antenna. (b) The MMR system is a navigation system with two internal receivers, the Instrument Landing System (ILS) and the Global Positioning System (GPS). 1 _

The ILS function is to provide the crew and the airborne system users with lateral (LOC) and vertical (Glide/Slope) deviations signals, with respect to the approach ILS radio beam transmitted by a ground station.

2 _

The GPS function is a radio aid to worldwide navigation which provides: - the crew with a readout of accurate navigation information, e.g. position, track and speed. - the Flight Management and Guidance Computer (FMGC) with position information, for accurate position fixing. The MMR system is composed of: - two MMR receivers - a Localizer antenna - a Glide/Slope antenna - two GPS ACTIVE antennas.

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Page 5 Feb 01/08

D. Independent Position Determining This part of the navigation system, which is basically independent of ground installations, provides data on the position of the aircraft. It comprises : (1) Weather radar system The weather radar system is a X-band system which can be capable of the Predictive Windshear function. This system enables: - detection and localization of the atmospheric disturbances in the area defined by the antenna scanning with visual display of their intensity - presentation of terrain mapping information by the combination of the orientation of the radar beam and of the receiver gain - detection and presentation of windshear events in the area defined by the antenna scanning (if the Predictive Windshear function is operative). NOTE : The Electronic Flight Instrumental System (EFIS) controls the ____ operation and superimposes the weather picture on the Navigation Display. This system is made up of the following components : - one or two transceivers (transceiver 2 is optional) - a control unit - a flat plate antenna and its drive unit. More explanations are given in the W/R system (Ref. 34-41). (2) Radio altimeter The function of the radio altimeter is to determine precisely and continuously, the height of the aircraft from 0 to 2500 ft above the terrain independently of the atmospheric pressure. The Height and Decision Height data are displayed on the PFD. The selection and reading of Decision Height are performed on the Multipurpose Control and Display unit (MCDU). The radio altimeter system is composed of: - two transceivers - four identical antennas, one for transmission and one for reception for each transceiver. More explanations are given in the RA system (Ref. 34-42). (3) Traffic Collision Avoidance System (TCAS) (optional system) The TCAS is designed to protect a volume of airspace around the TCAS equipped aircraft. The function of the TCAS II is to determine the range, altitude and bearing of other aircraft equipped with ATC transponders. The system monitors the trajectory of the other aircraft for the purpose of determining if any of them constitute a potential collision hazard. If a potential conflict exists, the

  EFF : ALL  34-00-00   R  CES

 

Page 6 Feb 01/08

system provides the pilots with aural and visual advisories which indicate the vertical avoidance maneuvers. The aircraft is equipped with : - a TCAS computer unit - two TCAS antennas. The system exchanges data with the Air Traffic Control (ATC) System. Traffic advisories are shown on the EFIS displays. More explanations are given in the TCAS system (Ref. 34-43). (4) Gound Proximity Warning System (GPWS) This system is used to inform the crew if the aircraft is in a dangerous configuration when approaching the ground in a non-predetermined manner. (a) The GPWS generates aural and visual warnings if the aircraft adopts a potentially hazardous condition with respect to: - Mode 1 - Excessive rate of descent - Mode 2 - Excessive closure rate with terrain - Mode 3 - Descent after takeoff and minimum terrain clearance - Mode 4 - Unsafe terrain clearance - Mode 5 - Descent below glide slope. The system is operative between 30ft and 2450ft radio altitude. (b) Enhanced Ground Proximity Warning System (Enhanced GPWS) (optional system) The purpose of the Enhanced GPWS is to alert the flight crew of potentially hazardous conditions with respect to the terrain. The following Enhanced features have been added to existing basic Ground Proximity Warning Modes 1 to 5 which are the backbone of the system: - Terrain Clearance Floor (TCF) function. It creates an increasing terrain clearance envelope around the intended airport runway directly related to the distance from the runway. The TCF function generates aural and visual alerts. - Terrain Awareness alerting and Display (TAD) function. This function uses aircraft geographic position, aircraft altitude and a terrain data base to predict potential conflicts between the aircraft flight path and the terrain, and to provide graphic displays of the conflicting terrain on the NDs. The terrain awareness alerting algorithms continuously compute terrain clearance envelopes ahead of the aircraft. More explanations are given in the GPWS system (Ref. 34-48).

  EFF : ALL  34-00-00   R  CES

 

Page 7 Feb 01/08

E. Dependent Position Determining This part of the navigation system comprises : (1) Distance Measuring Equipment (DME) The DME enables the distance separating the aircraft from one or two DME station being received to be known. The DME is made up of two systems comprising respectively : - a DME interrogator - a transmission/reception antenna. The system receives frequency information from FMGCs or RMPs. The slant range distance is displayed on NDs and PFDs. More explanations are given in the DME system (Ref. 34-51). The slant range distance is displayed also on a VOR/DME Radio Magnetic Indicator (RMI) or a VOR/ADF/DME RMI (optional) (Ref. 34-57). (2) Air Traffic Control (ATC) The ATC allows an operator of the corresponding equipment on the ground to locate and identify the aircraft in flight without having to communicate with the crew. The system is made up of the following components : - two ATC transponders - a ATC/TCAS control unit - four ATC antennas: two bottom antennas and two top antennas (optional). More explanations are given in the ATC system (Ref. 34-52). (3) Automatic Direction Finder (ADF) The ADF enables the bearings of one or two ADF ground transmitter stations to be permanently indicated with respect to the aircraft heading. The system is made up of the following components : - one or two transceivers (transceiver 2 is optional) - two ADF loop and sense antennas. The system receives frequency information from FMGCs or RMPs. The ADF bearings are displayed on: - two EFIS Navigation Displays (in Rose mode). - a Radio Magnetic Indicator (RMI) (optional) (Ref. 34-57). More explanations are given in the ADF system (Ref. 34-53). (4) VHF Omni-Range (VOR) The VOR firstly enables the bearings of one or two VOR ground transmitter stations to be permanently indicated with respect to the aircraft heading, and secondly it indicates the aircraft course deviation with respect to a preselected course. The system is made up of the following components : - two VOR/MKR receivers

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Page 8 Feb 01/08

- a VOR antenna to supply the two VOR/MKR receivers - a MARKER antenna to supply the VOR/MKR receiver 1 which is the only one to ensure the MARKER function. The system receives frequency information from FMGCs or RMPs. VOR data are displayed on: - two EFIS PFDs - two EFIS NDs - a VOR/DME Radio magnetic Indicator (RMI) or a VOR/ADF/DME RMI (optional) (Ref. 34-57). Marker data are displayed on CAPT and F/O PFDs and NDs. More explanations are given in the VOR/MARKER system (Ref. 34-55). (5) Global Positioning System (GPS) (optional system) The GPS system is a radio aid to worldwide navigation which provides: - the crew with a readout of accurate navigation information, e.g. position, track and speed. - the Flight Management and Guidance Computer (FMGC) with position information for accurate position fixing. To this end, the GPS system uses signals broadcast by a constellation of 24 satellites at a frequency of 1575.42 MHz. The GPS system is composed of: - two GPS Sensor Units (GPSSUs) - two GPS antennas. More explanations are given in the GPS system (Ref. 34-58).

  EFF : ALL  34-00-00    CES

 

Page 9 Feb 01/08

AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - DESCRIPTION AND OPERATION ______________________________________________________________________ 1. General _______ **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, (Ref. Fig. 001) The main air data and heading/attitude data are provided by a three-channel Air Data Inertial Reference System (ADIRS). This configuration provides for triple redundant information for all inertial and air data functions. Each channel is isolated from the others and provides independent information as defined by ARINC Characteristic 738. The ADIRS comprises: - Three Air Data/Inertial Reference Units (ADIRU) (ATA 34-12) - A control and Display Unit (CDU) (ATA 34-12) - Three pitot probes (ATA 34-11) - Six static probes (ATA 34-11) - Eight Air Data Modules (ADM) Linked to the pitot and static probes (ATA 34-11) - Two Total Air Temperature (TAT) sensors (ATA 34-11) - Three Angle of Attack (AOA) sensors (ATA 34-11) Each of the ADIRUs contains two portions: - The Air Data Reference (ADR) portion which supplies air data parameters (ATA 34-13) - The Inertial Reference (IR) portion which supplies attitude and navigation parameters (ATA 34-14). The parameters are transmitted to the user systems on ARINC 429 buses. The Built-In Test Equipment (BITE) is included in the ADIRUs and the ADMs. It detects and identifies a failure related to the ADIRS and reports it to the Centralized Fault Display System (CFDS) (ATA 34-18). R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, (Ref. Fig. 001A) A three-channel Air Data Inertial Reference System (ADIRS) supplies the primary air data and heading/attitude data. This configuration has triple redundant data for all the inertial and air data functions. Each channel is isolated from the other channels and supplies data independently as given in the ARINC Characteristic 738. The ADIRS has: - Three Air Data/Inertial Reference Units (ADIRU) (ATA 34-12) - A Mode Selector Unit (MSU) (ATA 34-12) - Three pitot probes (ATA 34-11)

  EFF : ALL  34-10-00    CES

 

Page 1 Feb 01/10

ADIRU - Block Diagram Figure 001   R EFF : 001-049, 051-099, 101-149, 151-199,  34-10-00 201-239, 301-312, 401-499,   CES

 

Page 2 Feb 01/08

ADIRU - Block Diagram Figure 001A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-10-00 511-526, 528-599,   CES

 

Page 3 Feb 01/10

- Six static probes (ATA 34-11) - Eight Air Data Modules (ADM) connected to the pitot and static probes (ATA 34-11) - Two Total Air Temperature (TAT) sensors (ATA 34-11) - Three Angle of Attack (AOA) sensors (ATA 34-11) Each of the ADIRUs has two parts: - The Air Data Reference (ADR) part which supplies air data parameters (ATA 34-13) - The Inertial Reference (IR) portion which supplies attitude and navigation parameters (ATA 34-14). The parameters are transmitted to the user systems through the ARINC 429 buses. The Built-In Test Equipment (BITE) is included in the ADIRUs and the ADMs. It senses and identifies a failure related to the ADIRS and sends it to the Centralized Fault Display System (CFDS) (ATA 34-18).

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-10-00 511-526, 528-599,   CES

 

Page 4 Feb 01/10

AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - MAINTENANCE PRACTICES __________________________________________________________________ TASK 34-10-00-860-002 ADIRS Start Procedure 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 31-60-00-860-001

Energize the Aircraft Electrical Circuits from the External Power EIS Start Procedure

3. __________ Job Set-up R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 501-509, 511-526, 528-599, Subtask 34-10-00-860-061 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (PFDs and NDs only) (Ref. TASK 31-60-00860-001).

  EFF : ALL  34-10-00    CES

 

Page 201 Feb 01/10

R

**ON A/C 401-499,

R

Subtask 34-10-00-860-061-A

R

A. Aircraft Maintenance Configuration

R R R R

WARNING : MAKE SURE THAT ALL PERSONS ARE AWAY FROM THE SATCOM ANTENNAS _______ (MORE THAN 3 METERS) WHEN YOU DO THIS TEST. THE SATCOM ANTENNAS USE HIGH POWER WHEN THEY TRANSMIT AND CAN CAUSE INJURY TO PERSONS.

R R

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002).

R R

(2) Do the EIS start procedure (PFDs and NDs only) (Ref. TASK 31-60-00860-001).

R

**ON A/C ALL Subtask 34-10-00-010-065 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822 (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover

  EFF : ALL  34-10-00    CES

 

Page 202 Nov 01/05

Subtask 34-10-00-865-070 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU R R

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

  EFF : ALL  34-10-00    CES

 

N10 N09 N08 N07 N06 N05 N04 N03

Page 203 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-10-00-710-065 A. ADIRS Start Procedure. (1) On the overhead panel, on the ADIRS CDU: (a) Set the three OFF/NAV/ATT selector switches to NAV. (b) Make sure that the ON BAT light comes on for 5 seconds and the ALIGN legend of the IR1, IR2 and IR3 annunciators comes on. (c) Make sure that the FAULT and OFF legends of the ADR1, ADR2 and ADR3 pushbutton switches are off. (2) On the CAPT and F/O main instrument panels, on the PFDs : - make sure that the CAS, ALT and V/S come into view. - make sure that the attitude data come into view 40 seconds approximetaly after the three selector switches are at NAV. (3) On the ADIRS CDU, set the SYS DISPLAY selector switch to 1 and the DATA DISPLAY selector switch to PPOS, and make sure that dashes are shown on the CDU display. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-10-00-710-065-A A. ADIRS Start Procedure. (1) On the overhead panel, on the ADIRS MSU: (a) Set the three OFF/NAV/ATT selector switches to NAV. (b) Make sure that the ON BAT light comes on for 5 seconds and then goes off. (c) Make sure that the FAULT and OFF legends of the ADR1, ADR2 and ADR3 pushbutton switches are off.

  EFF : ALL  34-10-00    CES

 

Page 204 Feb 01/10

(d) Make sure that the FAULT and OFF legends of the IR1, IR2 and IR3 pushbutton switches are off. (2) On the CAPT and F/O main instrument panels, on the PFDs : - Make sure that the CAS, ALT and V/S come into view. - Make sure that the attitude data come into view 40 seconds approximetaly after the three selector switches are at NAV. **ON A/C ALL 5. Close-up ________ Subtask 34-10-00-410-065 A. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

  EFF : ALL  34-10-00   R  CES

 

Page 205 Aug 01/08

TASK 34-10-00-860-004 IR Alignment Procedure 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 31-60-00-860-001

Energize the Aircraft Electrical Circuits from the External Power EIS Start Procedure

3. __________ Job Set-up R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, Subtask 34-10-00-860-057 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

  EFF : ALL  34-10-00    CES

 

Page 206 Feb 01/08

(3) On the overhead panel: - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (the OFF legends are on). - on the ADIRS CDU, make sure that the three OFF/NAV/ATT selector switches are at OFF. (4) On the glareshield, on the CAPT and F/O EFIS control sections of the FCU, set the mode selector switches to ROSE/NAV. NOTE : (1) During the alignment phase until the NAV mode is got, the ____ aircraft must not move. NOTE : (2) During the alignment phase necessary to get the NAV mode, ____ the time for alignment is shown: - in the right part of the display of the ADIRS CDU, if the DATA DISPLAY selector switch is at HDG. The indication is as follows: TTN5 - on the upper ECAM display unit, minute after minute (from 6 MN to 1 MN) as follows: IRS IN ALIGN 6 MN. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-10-00-860-057-B A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) On the overhead panel: - On the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (the OFF legends are on). - On the ADIRS MSU, make sure that the three OFF/NAV/ATT selector switches are at OFF. (4) On the glareshield, on the CAPT and F/O EFIS control sections of the FCU, set the mode selector switches to ROSE/NAV. NOTE : (1) During the alignment phase until the NAV mode is got, the ____ aircraft must not move.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-10-00 201-249, 251-299, 301-399, 501-509, 511-526,  528-599, CES

 

Page 207 Feb 01/10

NOTE : (2) During the alignment phase necessary to get the NAV mode, ____ the time for alignment is shown: - On the upper ECAM display unit, minute after minute (from 6 MN to 1 MN) as follows: IRS IN ALIGN 6 MN. **ON A/C 401-499, Subtask 34-10-00-860-057-A A. Aircraft Maintenance Configuration WARNING : MAKE SURE THAT ALL PERSONS ARE AWAY FROM THE SATCOM ANTENNAS _______ (MORE THAN 3 METERS) WHEN YOU DO THIS TEST. THE SATCOM ANTENNAS USE HIGH POWER WHEN THEY TRANSMIT AND CAN CAUSE INJURY TO PERSONS. (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) On the overhead panel: - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - on the ADIRS CDU, make sure that the three OFF/NAV/ATT selector switches are at OFF. (4) On the glareshield, on the CAPT and F/O EFIS control sections of the FCU, set the mode selector switches to ROSE/NAV. NOTE : (1) During the alignment phase until the NAV mode is got, the ____ aircraft must not move. NOTE : (2) During the alignment phase necessary to get the NAV mode, ____ the time for alignment is shown: - in the right part of the display of the ADIRS CDU, if the DATA DISPLAY selector switch is at HDG. The indication is as follows: TTN5 - on the upper ECAM display unit, minute after minute (from 6 MN to 1 MN) as follows: IRS IN ALIGN 6 MN.

  R EFF : 240-249, 251-299, 313-399, 401-499,  34-10-00 501-509, 511-526, 528-599,   CES

 

Page 208 Feb 01/10

**ON A/C ALL Subtask 34-10-00-010-062 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-10-00-865-079 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FCU/1 9CA1 B05 49VU AUTO FLT/FMGC/1 10CA1 B02 49VU AUTO FLT/MCDU/1 11CA1 B01 49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

2TW 9CA2

J18 M21

**ON A/C ALL 121VU CFDS/CFDIU/SPLY 121VU AUTO FLT/FCU/2

  EFF : ALL  34-10-00   R  CES

 

Page 209 Feb 01/08

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU AUTO FLT/FMGC/2 10CA2 M17 121VU AUTO FLT/MCDU/2 11CA2 N20 121VU HYDRAULIC/LGCIU/SYS2 2GA Q35 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34 R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N10 N09 N08 N07 N06 N05 N04 N03

8TW

J17

**ON A/C ALL Post SB

31-1163 For A/C 155-156,208-209,

121VU CFDS/CFDIU/BACK/UP

  EFF : ALL  34-10-00    CES

 

Page 210 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-10-00-860-058 A. IR Alignment from the ADIRS CDU ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU: - set the three OFF/NAV/ATT selector switches to NAV

On the ADIRS CDU: - the OFF legend of the ADR1, ADR2 and ADR3 pushbutton switches stays off. - the ON BAT light stays on for 5 seconds. - the ALIGN legend comes on. After approximately 40 seconds: - on the CAPT and F/O PFDs: . the ATT warning flags go out of view. . the attitude data come into view. - on the upper ECAM display unit, the memo section shows IRS IN ALIGN > 7 MN.

- set the DATA DISPLAY selector switch to PPOS - set the SYS DISPLAY selector switch to 1 - on the CDU keyboard, enter the present position (example for Toulouse): N 43⁰ 36 8 then push the ENT key, E 1⁰ 21 9 then push the ENT key.

The ADIRS CDU shows the coordinates N 43-36-8 (in the left part of the display) and E 1-21-9 (in the right part of the display).

NOTE : If the coordinates are ____ incorrect, push the CLR key and enter new data as above. NOTE : If an incorrect longitude ____ is entered two times in sequence during PPOS   EFF : ALL  34-10-00   R  CES

 

Page 211 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------entry, the ADIRUs will accept this position until the subsequent alignment. - set the SYS DISPLAY selector switch to 2, then to 3 and make sure that the coordinates shown are the same for the three ADIRUs. Set the SYS DISPLAY selector switch to 1.

R R R R R R R R R R R R R R R R R R R R R R R

After a time delay of approximately 5 minutes: - on the CAPT and F/O NDs , the HDG warning flags go out of view and the heading dial comes into view. After a time delay of approximately 10 minutes: - on the ADIRS CDU, the ALIGN legend of the IR1, IR2 and IR3 annunciators goes off - on the upper ECAM display unit, the IRS IN ALIGN 1 MN indication goes out of view (the ADIRUs are in the NAV mode).

------------------------------------------------------------------------------| MAINTENANCE INDICATION | DESCRIPTION | | ON THE CDU | | ------------------------------------------------------------------------------| STS - IRU FAULT | Critical failure. Remove the IRU for | | | maintenance. | ------------------------------------------------------------------------------| STS - DELAYED MAINT | Non critical failure. Remove the IRU | | | if necessary. | ------------------------------------------------------------------------------| STS - ENTER P POS | Enter the present position. | ------------------------------------------------------------------------------| STS - SELECT ATT | Non critical failure. Set the ATT mode | ------------------------------------------------------------------------------| STS - XCESS MOTION | Excessive movements of the aircraft | | | during the alignment. | ------------------------------------------------------------------------------| STS - ADR FAULT | ADR non valid. | ------------------------------------------------------------------------------| STS - CHECK CK/BK | Do the check of the circuit breaker. | ------------------------------------------------------------------------------| STS - CDU FAULT | Remove the CDU for maintenance. | ------------------------------------------------------------------------------| STS - ENT MAG HDG | Enter the magnetic heading in | | | attitude mode. | -------------------------------------------------------------------------------

  EFF : 001-049, 051-099, 101-149, 151-199,  34-10-00 201-239, 301-312, 401-499,   CES

 

Page 212 Aug 01/08

NOTE : These status indications are given to help you. They come into ____ view only when the DATA DISPLAY selector switch on the ADIRS CDU is at STS, after a fault detection. R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-499, Subtask 34-10-00-860-059 B. IR Alignment from the MCDU: ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the circuit breaker panel 121VU: - open the circuit breaker 10CA2.

R R R R R R R

2. On the ADIRS CDU: - set the three OFF/NAV/ATT selector switches to NAV.

R

On the ADIRS CDU: - The OFF legend of the ADR pushbutton switches flashes two times, then goes off. - The ON BAT light comes on for 5 seconds. - The ALIGN legend of the IR1, IR2 and IR3 annunciators comes on. On the upper ECAM display unit the memo section shows IRS IN ALIGN > 7 MN (only if one FMGC (1 or 2) is energized) On the CAPT and F/O PFDs: - CAS, V/S and ALT data come into view. - after approximately 40 seconds the ATT warning flags go out of view and the attitude data come into view.

- set the SYS DISPLAY selector switch to 1 (2 or 3) and the DATA DISPLAY selector switch to PPOS. 3. On the MCDU1 or 2:

On the MCDU1 or 2:

- turn the BRT knob (or push the BRT key) R

- Push the MCDU MENU mode key.

The MCDU MENU page comes into view.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-10-00 201-239, 301-312, 401-499,   CES

 

Page 213 Feb 01/08

R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Push the line key adjacent to the FMGC indication.

R

- Push the INIT mode key.

The INIT A page comes into view.

R R R

- Enter an airline code route with the keyboard.

The code number is shown in the scratchpad line (bottom part of the MCDU).

R R

- Push the line key adjacent to the CO RTE indication

- The code number comes into view below the CO RTE indication. - The latitude and longitude are shown below the LAT and LONG indications. The slew prompts (up and down arrow) adjacent to the LAT indication are shown. - The ALIGN IRS indication is shown on the line above the LONG coordinates.

R R R

NOTE : You can increase or decrease the ____ LAT or/and LONG magnitude as indicated in para. 4 and 5. If no LAT or LONG change is necessary, go to the para. 6. NOTE : If an incorrect longitude is ____ entered two times in sequence during PPOS entry, the ADIRU will accept this position until the subsequent alignment.

R R R 4. For the LAT change: - on the MCDU keyboard, push one of the two slew keys.

The LAT coordinates increase or decrease: - by 1 minute, each time you push the slew key - by 1 minute/second, if you push and hold the slew key.

5. For the LONG change:

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-10-00 201-233, 236-238, 301-304, 401-499,   CES

 

Page 214 Feb 01/08

R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- on the MCDU, push the line key The slew prompts (up and down arrow) adjacent to the LONG move to the LONG indication. coordinates. - on the MCDU keyboard, push one of the two slew keys.

R

6. On the MCDU, push the line key adjacent to the ALIGN IRS indication.

On the MCDU, the ALIGN IRS indication goes out of view.

7. On the ADIRS CDU, set the SYS DISPLAY selector switch to 2, then to 3 and make sure that the coordinates shown are the same for the three ADIRUs. Set the SYS DISPLAY selector switch to 1

The coordinates which are in view on the ADIRS CDU are the same as the coordinates shown on the MCDU After approximately 5 minutes: - on the CAPT and F/O NDs, the HDG warning flags go out of view and the heading dial comes into view. After approximately 10 minutes: - on the ADIRS CDU, the ALIGN legend of the IR1, IR2 and IR3 goes off. - on the upper ECAM display unit, the IRS IN ALIGN 1 MN indication goes out of view.

R

R R

The LONG coordinates increase or decrease as for the LAT.

8. On the related circuit breaker panel: - open the circuit breaker 10CA1 (49VU). - close the circuit breaker 10CA2 (121VU). 9. Do the same test from the para. 2.

Same results.

10. On the related circuit breaker panel, close the circuit breaker 10CA1.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-10-00 201-233, 236-238, 301-304, 401-499,   CES

 

Page 215 Feb 01/08

R

**ON A/C 234-235, 239-239, 305-312, Subtask 34-10-00-860-059-A B. IR Alignment from the MCDU: ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the circuit breaker panel 121VU: - open the circuit breaker 10CA2.

R R R R R R R

2. On the ADIRS CDU: - Set the three OFF/NAV/ATT selector switches to NAV.

On the ADIRS CDU: - The OFF legend of the ADR pushbutton switches flashes two times, then goes off. - The ON BAT light comes on for 5 seconds. - The ALIGN legend of the IR1, IR2 and IR3 annunciators comes on. On the upper ECAM display unit the memo section shows IRS IN ALIGN > 7 MN (only if the FMGC 1 and 2 energized) On the CAPT and F/O PFDs: - CAS, V/S and ALT data come into view. - after approximately 40 seconds the ATT warning flags go out of view and the attitude data come into view.

- set the SYS DISPLAY selector switch to 1 (2 or 3) and the DATA DISPLAY selector switch to PPOS. 3. On the MCDU:

On the MCDU:

R R

- Turn the BRT knob. - Push the MCDU MENU mode key.

The MCDU MENU page comes into view.

R R

- Push the line key adjacent to the FMGC indication.

The A/C status page comes into view.

R

- Push the INIT mode key.

The INIT page comes into view.

  R EFF : 234-235, 239-239, 305-312,  34-10-00    CES

 

Page 216 Feb 01/08

R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Enter an airline code route (or The code number is shown in the FROM/TO destination). scratchpad line (bottom part of the MCDU).

R R R

- Push the line key adjacent to the CO RTE indication (or FROM/TO indication).

- The code number comes into view below the CO RTE indication (or FROM/TO indication).

- Push the line key adjacent to the IRS INIT indication.

- The IRS INIT page comes into view. - The latitude and longitude are shown below the LAT and LONG indications. The slew prompts (up and down arrow) adjacent to the LAT indication are shown. - The ALIGN IRS indication is shown on the line above the LONG coordinates.

R R R

NOTE : You can increase or decrease the ____ LAT or/and LONG magnitude as indicated in para. 4 and 5. If no LAT or LONG change is necessary, go to the para. 6. NOTE : If an incorrect longitude is ____ entered two times in sequence during PPOS entry, the ADIRU will accept this position until the subsequent alignment.

R R R 4. For the LAT change: - on the MCDU keyboard, push one of the two slew keys.

The LAT coordinates increase or decrease: - by 1 minute, each time you push the slew key - by 1 minute/second, if you push and hold the slew key.

5. For the LONG change: R R

- on the MCDU, push the line key adjacent to the LONG coordinates.

The slew prompts (up and down arrow) move to the LONG indication.

  R EFF : 234-235, 239-239, 305-312,  34-10-00    CES

 

Page 217 Feb 01/08

R R

R R R R R R R R R R R R R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- On the MCDU keyboard, push one The LONG coordinates increase or of the two slew keys. decrease as for the LAT. 6. On the MCDU, push the line key adjacent to the ALIGN IRS indication.

On the MCDU, the ALIGN IRS indication goes out of view.

7. On the ADIRS CDU, set the SYS DISPLAY selector switch to 2, then to 3 and make sure that the coordinates shown are the same for the three ADIRUs. Set the SYS DISPLAY selector switch to 1

The coordinates which are in view on the ADIRS CDU are the same as the coordinates shown on the MCDU After approximately 5 minutes: - On the CAPT and F/O NDs, the HDG warning flags go out of view and the heading dial comes into view. After approximately 10 minutes: - On the ADIRS CDU, the ALIGN legend of the IR1, IR2 and IR3 goes off. - On the upper ECAM display unit, the IRS IN ALIGN 1 MN indication goes out of view.

8. On the related circuit breaker panel: - Open the circuit breaker 10CA1. - Close the circuit breaker 10CA2. 9. Do the same test from the para. 2.

Same results.

10. On the related circuit breaker panel, close the circuit breaker 10CA1.

  R EFF : 234-235, 239-239, 305-312,  34-10-00    CES

 

Page 218 Feb 01/08

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-10-00-860-059-B B. IR Alignment from the MCDU: ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the circuit breaker panel 121VU: - Open the circuit breaker 10CA2. 2. On the ADIRS MSU: - Set the three OFF/NAV/ATT selector switches to NAV.

On the ADIRS MSU: - The OFF legend of the ADR1, ADR2 and ADR3 pushbutton switches flashes two times,then goes off. - The FAULT legend of the IR1, IR2 and IR3 pushbutton switches is off. - The ON BAT light comes on for 5 seconds. On the upper ECAM display unit the memo section shows IRS IN ALIGN > 7 MN (only if the FMGC 1 and 2 are energized) On the CAPT and F/O PFDs: - CAS, V/S and ALT data come into view. - After approximately 40 seconds the ATT warning flags go out of view and the attitude data come into view.

3. On the MCDU:

On the MCDU:

- Turn the BRT knob. - Push the MCDU MENU mode key.

The MCDU MENU page comes into view.

- Push the line key adjacent to the FMGC indication.

The A/C status page comes into view.

- Push the INIT mode key.

The INIT page comes into view.

- Enter an airline code route (or FROM/TO destination).

The code number is shown in the scratchpad line (bottom part of the MCDU).

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-10-00 511-526, 528-599,   CES

 

Page 219 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Push the line key adjacent to - The code number comes into view below the CO RTE indication (or the CO RTE indication (or FROM/TO FROM/TO indication). indication). - Push the line key adjacent to the IRS INIT indication.

- The IRS INIT page comes into view. - The latitude and longitude are shown below the LAT and LONG indications. The slew prompts (up and down arrow) adjacent to the LAT indication are shown. - The ALIGN IRS indication is shown on the line above the LONG coordinates. NOTE : You can increase or decrease the ____ LAT or/and LONG magnitude as indicated in para. 4 and 5. If no LAT or LONG change is necessary, go to the para. 6. NOTE : If an incorrect longitude is ____ entered two times in sequence during PPOS entry, the ADIRU will accept this position until the subsequent alignment.

4. For the LAT change: - On the MCDU keyboard, push one of the two slew keys.

The LAT coordinates increase or decrease: - By 1 minute, each time you push the slew key - By 1 minute/second, if you push and hold the slew key.

5. For the LONG change: - On the MCDU, push the line key adjacent to the LONG coordinates.

The slew prompts (up and down arrow) move to the LONG indication.

- On the MCDU keyboard, push one of the two slew keys.

The LONG coordinates increase or decrease as for the LAT.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-10-00 511-526, 528-599,   CES

 

Page 220 Feb 01/10

R R R R R R R R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------6. On the MCDU, push the line key On the MCDU, the ALIGN IRS indication adjacent to the ALIGN IRS goes out of view. indication. After approximately 5 minutes: - On the CAPT and F/O NDs, the HDG warning flags go out of view and the heading dial comes into view. After approximately 10 minutes: - On the upper ECAM display unit, the IRS IN ALIGN 1 MN indication goes out of view.

R R R R R

7. On the related circuit breaker panel: - Open the circuit breaker 10CA1. - Close the circuit breaker 10CA2.

R R

8. Do the same test from the para. 2.

R R R

9. On the related circuit breaker panel, close the circuit breaker 10CA1.

Same results.

**ON A/C ALL 5. Close-up ________ Subtask 34-10-00-410-062 A. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

  EFF : ALL  34-10-00    CES

 

Page 221 Feb 01/08

TASK 34-10-00-860-005 ADIRS Stop Procedure 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-862-002

De-energize the Aircraft Electrical Circuits Supplied from the External Power

3. __________ Job Set-up Subtask 34-10-00-860-069 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the SWITCHING control panel 8VU: - set the AIR DATA selector switch to NORM - set the ATT HDG selector switch to NORM. 4. Procedure _________ R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-10-00-860-070 A. ADIRS Stop Procedure (1) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF.

  EFF : ALL  34-10-00    CES

 

Page 222 Feb 01/08

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-10-00-860-070-A A. ADIRS Stop Procedure (1) On the ADIRS MSU, set the OFF/NAV/ATT selector switches to OFF. **ON A/C ALL 5. Close-up ________ Subtask 34-10-00-860-071 A. Put the aircraft back to its initial configuration. (1) On the panels 301VU and 500VU, set the PFD and ND potentiometers to OFF. (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  EFF : ALL  34-10-00    CES

 

Page 223 Feb 01/10

AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - SERVICING ______________________________________________________ R

TASK 34-10-00-170-004

R

Cleaning of the Pitot Probe Drain-Holes

R

1. __________________ Reason for the Job

R R

- To remove dust and particles from the pitot probes. 2. ______________________ Job Set-up Information

R

A. Fixtures, Tools, Test and Support Equipment

R R R

------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R R R R R R

No specific No specific No specific No specific 98D34103004001 98F34103003000

R

dry nitrogen source of 2 bars (29 psi) WIRE-NYLON, dia. 0.7mm (0.027in.) 0.8mm (0.031in.) 1 ACCESS PLATFORM 2M (6 FT) 1 CLEANER-PITOT PROBE 1 TBD

B. Referenced Information

R R R

------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------

R R R R R R

24-42-00-861-001

R

3. __________ Job Set-up

R

Subtask 34-10-00-861-063

24-42-00-862-001 34-13-00-790-002

R R

Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Leak Test of the Principal Static and Total Air Data System

A. Energize the ground service network (Ref. TASK 24-42-00-861-001).

  EFF : ALL  34-10-00    CES

 

Page 301 Feb 01/10

R

Subtask 34-10-00-010-067

R

B. Get access to the Avionics Compartment

R R R

(1) Put the ACCESS PLATFORM 2M (6 FT) in position : - At zone 125 to get access to pitot probes 1 (9DA1) and 3 (9DA3) - At zone 126 to get access to pitot probe 2 (9DA2).

R R R R R

(2) Open the applicable access door: FOR 9DA1, 9DA3 812 FOR 9DA2 822.

R

Subtask 34-10-00-860-079

R

C. Connection of the Dry Nitrogen Source

R R

(1) Disconnect the quick-disconnect coupling from the total Pitot probe 1 (2 or 3).

R R R

(2) Connect TBD (98F34103003000) to a 3-pin adapter (98D34103002100) and to the quick-disconnect coupling of the pitot probe 1 (2 or 3). Then connect it to a dry nitrogen source of 2 bars (29 psi).

R

(3) Attach the hose to prevent movement.

R

4. Procedure _________

R

Subtask 34-10-00-170-057

R

A. Cleaning of the Pitot Probe Drain-Holes

R R R R R

(1) Blow the gas into the hose at a pressure of 2 bars (29 psi) for approximately 3 minutes, and at the same time: - clean draining hole of the pitot probe 1 (2 or 3) with a CLEANERPITOT PROBE (98D34103004001) and a WIRE-NYLON, dia. 0.7mm (0.027in.) and 0.8mm (0.031in.).

R R R

NOTE : The WIRE-NYLON must have a length of 5 mm (0.1968 in.) to ____ prevent contact between the metal tool element and the pitot probe.

R R

(2) Make sure that there is no contamination in the pressurized gas at the outlet of the pitot probe 1 (2 or 3).

R

(3) Stop the flow of gas.

  EFF : ALL  34-10-00    CES

 

Page 302 Feb 01/10

R

(4) Disconnect the dry nitrogen source.

R

(5) Remove the 3-pin adapter.

R

(6) Connect the quick-disconnect coupling to the Pitot probe 1 (2 or 3).

R R

(7) Make sure that you can see the blue ring on the quick-disconnect coupling.

R R

(8) Pull the quick-disconnect coupling to make sure that it is correctly attached.

R

Subtask 34-10-00-170-058

R

B. After the Cleaning Procedure

R R R R R R R R R

WARNING : IF ONE QUICK DISCONNECT COUPLING IS DISCONNECTED IN ONE SYSTEM, _______ MAKE SURE THAT A SECOND QUALIFIED MECHANIC DOES A VISUAL INSPECTION OF THE QUICK-DISCONNECT COUPLING CONNECTION. THE TWO MECHANICS MUST SIGN OFF THE JOB. IF TWO OR MORE QUICK DISCONNECT COUPLINGS ARE DISCONNECTED IN TWO OR MORE SYSTEMS, MAKE SURE THAT A SECOND QUALIFIED MECHANIC DOES A VISUAL INSPECTION OF THE QUICK-DISCONNECT COUPLING CONNECTIONS AND DOES THE LEAK TEST. THE TWO MECHANICS MUST SIGN OFF THE JOB.

R

(1) Release the hose.

R R

(2) If one quick-disconnect coupling is disconnected in one total pressure line:

R R

(a) A second qualified mechanic must do a visual inspection of the quick-disconnect coupling connection.

R R

(3) If two (or more) quick-disconnect coupling are disconnected in two (or more) total pressure lines:

R R

(a) A second qualified mechanic must do a visual inspection of the quick-disconnect coupling connections.

R R

(b) Do the leak test of the principal static and total air-data system (Ref. TASK 34-13-00-790-002).

R

(4) The two mechanics must sign off the job.

  EFF : ALL  34-10-00    CES

 

Page 303 Feb 01/10

R

5. Close-up ________

R

Subtask 34-10-00-410-067

R

A. Close Access

R R

(1) Make sure that the work area is clean and clear of tool(s) and other items.

R R R R R

(2) Close the applicable access door: FOR 9DA1, 9DA3 - 812 FOR 9DA2 - 822.

R

(3) Remove the access platform(s).

R

Subtask 34-10-00-862-064

R R

B. De-energize the ground service network (Ref. TASK 24-42-00-862-001).

  EFF : ALL  34-10-00    CES

 

Page 304 Feb 01/10

TASK 34-10-00-170-001 Flushing of the Principal Total Pressure Lines 1. __________________ Reason for the Job Refer to the MPD TASK: 341300-07 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific 98D34103002000

dry nitrogen source - 2 bars (29 psi) WIRE-NYLON dia. 0,7 and 0,8mm WIRE-NYLON, dia. 0.6mm access platform 1.6 m (5 ft. 3 in.) 1 ADAPTERS - AIR DATA SYSTEM FLUSHING

98D34103004001

1 CLEANER-PITOT PROBE

R B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-13-00-790-002 34-10-00-991-001 R R R

Leak Test of the Principal Static and Total Air Data System Fig. 301

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-10-00-991-003

Fig. 302

  EFF : ALL  34-10-00    CES

 

Page 305 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up (Ref. Fig. 301/TASK 34-10-00-991-001) NOTE : The hose couplings are self-sealing. ____ Subtask 34-10-00-010-059 A. Get access to the Avionics Compartment (1) Put the access platform in position in the zone 123 at the access door 812 (in the zone 122 at the access door 822). (2) Open the access door: for ADM 19FP1 (19FP2): 812 (822). R Subtask 34-10-00-860-051-A B. Connect the Dry Nitrogen Source (1) Disconnect the quick-disconnect coupling from the ADM 19FP1 (19FP2). (2) Connect an ADAPTERS - AIR DATA SYSTEM FLUSHING 3-pin adapter (98D34103002100) to the total pressure hose. Then connect it to the dry nitrogen source - 2 bars (29 psi). (3) Attach the hose to prevent movement.

  R EFF : ALL  34-10-00    CES

 

Page 306 Feb 01/10

Routing of Pressure Lines Figure 301/TASK 34-10-00-991-001   R EFF : ALL  34-10-00    CES

 

Page 307 Feb 01/10

R 4. Procedure _________ R **ON A/C 001-049, 051-099, 101-105, 151-199, R Subtask 34-10-00-170-050-B A. Flushing of the Total Pressure Line (1) Blow the gas into the hose at a pressure of 2 bars (29 psi) for approximately 3 minutes. (2) Clean draining hole of the pitot probe 1(2) with CLEANER-PITOT PROBE and a WIRE-NYLON, dia. 0.6mm. NOTE : The WIRE-NYLON must have a length of 5mm (0.196in) to prevent ____ contact between the metallic tool element and the pitot probe. (3) Make sure that there is no contamination in the pressurized gas at the outlet of the pitot probe 1(2). (4) Stop the flow of gas. (5) Disconnect the dry nitrogen source. (6) Remove the 3-pin adapter. (7) Release the hose. (8) Connect the quick-disconnect coupling to the ADM 19FP1 (19FP2). (Ref. Fig. 302/TASK 34-10-00-991-003) (9) Make sure that you can see the blue ring on the quick-disconnect coupling. (10) Pull the quick-disconnect coupling to be sure that it is correctly attached.

  EFF : ALL  34-10-00    CES

 

Page 308 Feb 01/10

Illustration of the Quick-Disconnect coupling Figure 302/TASK 34-10-00-991-003   EFF : ALL  34-10-00   R  CES

 

Page 309 Feb 01/10

R R

**ON A/C 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

R

Subtask 34-10-00-170-050-A

R

A. Flushing of the Total Pressure Line

R R

(1) Blow the gas into the hose at a pressure of 2 bars (29 psi) for approximately 3 minutes.

R R

(2) Clean draining hole of the pitot probe 1(2) with CLEANER-PITOT PROBE and WIRE-NYLON dia. 0,7 and 0,8mm.

R R

(3) Make sure that there is no contamination in the pressurized gas at the outlet of the pitot probe 1(2).

R

(4) Stop the flow of gas.

R

(5) Disconnect the dry nitrogen source.

R

(6) Remove the 3-pin adapter.

R

(7) Release the hose.

R R

(8) Connect the quick-disconnect coupling to the ADM 19FP1 (19FP2). (Ref. Fig. 302/TASK 34-10-00-991-003)

R R

(9) Make sure that you can see the blue ring on the quick-disconnect coupling.

R R

(10) Pull the quick-disconnect coupling to be sure that it is correctly attached.

  R EFF : 106-149, 201-249, 251-299, 301-399,  34-10-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 310 Feb 01/10

**ON A/C ALL Subtask 34-10-00-170-053 B. After the flushing. WARNING : IF ONE QUICK DISCONNECT COUPLING IS DISCONNECTED IN ONE SYSTEM, _______ MAKE SURE THAT A SECOND QUALIFIED MECHANIC DOES A VISUAL INSPECTION OF THE QUICK-DISCONNECT COUPLING CONNECTION. THE TWO MECHANICS MUST SIGN OFF THE JOB. IF TWO OR MORE QUICK DISCONNECT COUPLINGS ARE DISCONNECTED IN TWO OR MORE SYSTEMS, MAKE SURE THAT A SECOND QUALIFIED MECHANIC DOES A VISUAL INSPECTION OF THE QUICK-DISCONNECT COUPLING CONNECTIONS AND DOES THE LEAK TEST. THE TWO MECHANICS MUST SIGN OFF THE JOB. (1) If one quick disconnect coupling is disconnected in one total pressure line does a visual inspection of the quick disconnect coupling by a second qualified mechanic. (2) If two (or more) quick disconnect coupling are disconnected in two (or more) total pressure lines: (a) Do a visual inspection of the quick disconnect coupling connections by a second qualified mechanic. (b) Do the leak test of the Principal Static and Total Air Data System (Ref. TASK 34-13-00-790-002). (c) The two mechanics must sign off the job. 5. Close-up ________ Subtask 34-10-00-410-059 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the access door 812 (822). (3) Remove the access platform(s).

  EFF : ALL  34-10-00   R  CES

 

Page 311 Feb 01/10

TASK 34-10-00-170-002 Flushing of the Principal Static Pressure Lines 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 98D34103002000

dry nitrogen source - 2 bars (29 psi) access platform 1.6 m (5 ft. 3 in.) 1 ADAPTERS - AIR DATA SYSTEM FLUSHING

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-13-00-790-002 52-41-00-410-002 34-10-00-991-001 34-10-00-991-003

Leak Test of the Principal Static and Total Air Data System Close the Avionics Compartment Doors after Access Fig. 301 Fig. 302

3. __________ Job Set-up (Ref. Fig. 301/TASK 34-10-00-991-001) NOTE : The hose couplings are self-sealing. ____ Subtask 34-10-00-010-060 A. Get access to the Avionics Compartment (1) Put the access platform in position in the zone 128 at the access door 824. (2) Open the access door 824.

  R EFF : ALL  34-10-00    CES

 

Page 312 Feb 01/10

Subtask 34-10-00-860-052 B. Connect the Dry Nitrogen Source (1) Disconnect the quick-disconnect coupling from the ADM 19FP4 or 19FP5 (19FP6 or 19FP7). (2) Connect a ADAPTERS - AIR DATA SYSTEM FLUSHING (98D34103002000) 3-pin adapter (98D34103002100) to the static pressure hose. Then connect it to the dry nitrogen source - 2 bars (29 psi). (3) Attach the hose to prevent movement. 4. Procedure _________ Subtask 34-10-00-170-051 A. Flushing of the Static Pressure Line (1) Blow the gas into the hose at a pressure of 2 bars (29 psi) for approximately 1 minute. (2) Make sure that there is no contamination in the pressurized gas at the outlet of the L or R static probe 1 (L or R static probe 2). (3) Stop the flow of gas. (4) Disconnect the dry nitrogen source. (5) Remove the 3-pin adapter . (6) Release the hose. (7) Connect the quick-disconnect coupling to the ADM 19FP4 or 19FP5 (19FP6 or 19FP7). (Ref. Fig. 302/TASK 34-10-00-991-003) (8) Make sure that you can see the blue ring on the quick-disconnect coupling. (9) Pull the quick-disconnect coupling to be sure that it is correctly attached.

  R EFF : ALL  34-10-00    CES

 

Page 313 Feb 01/10

Subtask 34-10-00-170-054 B. After the flushing. WARNING : IF ONE QUICK DISCONNECT COUPLING IS DISCONNECTED IN ONE SYSTEM, _______ MAKE SURE THAT A SECOND QUALIFIED MECHANIC DOES A VISUAL INSPECTION OF THE QUICK-DISCONNECT COUPLING CONNECTION. THE TWO MECHANICS MUST SIGN OFF THE JOB. IF TWO OR MORE QUICK DISCONNECT COUPLINGS ARE DISCONNECTED IN TWO OR MORE SYSTEMS, MAKE SURE THAT A SECOND QUALIFIED MECHANIC DOES A VISUAL INSPECTION OF THE QUICK-DISCONNECT COUPLING CONNECTIONS AND DOES THE LEAK TEST. THE TWO MECHANICS MUST SIGN OFF THE JOB. (1) If one quick disconnect coupling is disconnected in one static pressure line does a visual inspection of the quick disconnect coupling by a second qualified mechanic. (2) If two (or more) Quick Disconnect coupling are disconnected on the two (or more) Static Pressure Lines: (a) Do a visual inspection of the Quick Disconnect coupling connections by a second qualified mechanic. (b) Do the leak test of the Principal Static and Total Air Data System (Ref. TASK 34-13-00-790-002). (c) The two mechanics must sign off the job. 5. Close-up ________ Subtask 34-10-00-410-060 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the access door 824 (Ref. TASK 52-41-00-410-002). (3) Remove the access platform(s).

  R EFF : ALL  34-10-00    CES

 

Page 314 Feb 01/10

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, TASK 34-10-00-170-003 Draining and Flushing of Standby Pneumatic Circuits 1. __________________ Reason for the Job Refer to the MPD TASK: 342100-02 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific No specific 98D34003500000 98D34103002000 98D34103003000 98D34103004001

2 1 1 1

blanking cap dry nitrogen source - 2 bars (29 psi) WIRE-NYLON 0,7 and 0,8mm WIRE-NYLON, dia. 0.6mm access platform 1.6 m (5 ft. 3 in.) ADAPTER COVER-STATIC PORT ADAPTERS - AIR DATA SYSTEM FLUSHING ADAPTER, PITOT - PNEUMATIC CLEANER CLEANER-PITOT PROBE

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-24-34-600-001 34-21-00-790-001 34-21-22-000-001 34-21-22-400-001 34-21-25-000-001 34-21-25-400-001 34-21-26-000-001 34-21-26-400-001

Bleeding of the Standby Air Data System Low-Range Leak Test of the Standby Pneumatic Circuits Removal of the Standby Altimeter (3FN) Installation of the Standby Altimeter (3FN) Removal of the Metric Altimeter (15FN) Installation of the Metric Altimeter (15FN) Removal of the Standby Airspeed Indicator (9FN) Installation of the Standby Airspeed Indicator (9FN)

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-10-00 201-220, 236-238,   CES

 

Page 315 Feb 01/10

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-099, 101-105, 34-10-00-991-002

Fig. 303

**ON A/C 151-199, 201-220, 236-238, 34-10-00-991-002-A

Fig. 303A

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, 34-10-00-991-004

Fig. 304

3. __________ Job Set-up **ON A/C 001-049, 051-099, 101-105, (Ref. Fig. 303/TASK 34-10-00-991-002) **ON A/C 151-199, 201-220, 236-238, (Ref. Fig. 303A/TASK 34-10-00-991-002-A) **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, NOTE : The hose couplings are self-sealing. ____ Subtask 34-10-00-010-061 A. Get Access (1) Put the access platform in position in the zone 110 at the access door 811. (2) Open the access door 811.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-10-00 201-220, 236-238,  R  CES

 

Page 316 Feb 01/10

Location of Components Related to the Standby Pressure Lines-Schematic Figure 303/TASK 34-10-00-991-002   R EFF : 001-049, 051-099, 101-105,  34-10-00    CES

 

Page 317 Feb 01/10

Location of Components Related to the Standby Pressure Lines-Schematic Figure 303A/TASK 34-10-00-991-002-A   R EFF : 151-199, 201-220, 236-238,  34-10-00    CES

 

Page 318 Feb 01/10

**ON A/C 001-049, 051-099, 101-105, Subtask 34-10-00-860-053 B. Aircraft Maintenance Configuration (1) Drain the standby air data system (Ref. TASK 12-24-34-600-001). (2) Disconnect the quick-disconnect coupling (4) from the ADM 19FP8 and the quick-disconnect coupling (8) from the ADM 19FP3. (3) Disconnect the cabin-pressure detection pressure-switch 14WN (3) from the static pipe. Put a blanking cap on the pressure switch. (4) Remove the water drain plug (2) from the water drain (1). (5) In the cockpit, on the center instrument panel: - remove the standby altimeter 3FN (Ref. TASK 34-21-22-000-001) - remove the standby airspeed indicator (6) 9FN (Ref. TASK 34-21-26000-001) - remove the metric altimeter (15FN) (Ref. TASK 34-21-25-000-001). (6) Disconnect the quick-disconnect coupling (7) from the red 2-pin coupling of the standby airspeed indicator (6) and disconnect the quick-disconnect couplings (5) from the yellow 3-pin couplings of the standby instruments 3FN, 9FN and 15FN. (7) Connect a ADAPTERS - AIR DATA SYSTEM FLUSHING 3-pin adapter (98D34103002100) to the hose of the standby altimeter and a ADAPTERSAIR DATA SYSTEM FLUSHING 2-pin adapter (98D34103002102) to the hose (7). Then connect them to the dry nitrogen source - 2 bars (29 psi). (8) Connect the ADAPTER, PITOT - PNEUMATIC CLEANER to the dry nitrogen source - 2 bars (29 psi). (9) Attach the hoses to prevent movement.

  R EFF : 001-049, 051-099, 101-105,  34-10-00    CES

 

Page 319 Feb 01/10

**ON A/C 151-199, Subtask 34-10-00-860-053-A B. Aircraft Maintenance Configuration (1) Drain the standby air data system (Ref. TASK 12-24-34-600-001). (2) Disconnect the quick-disconnect coupling (4) from the ADM 19FP8 and the quick-disconnect coupling (8) from the ADM 19FP3. (3) Disconnect the cabin-pressure detection pressure-switch 14WN (3) from the static pipe. Put a blanking cap on the pressure switch. (4) Remove the water drain plug (2) from the water drain (1). (5) In the cockpit, on the center instrument panel: - remove the standby altimeter 3FN (Ref. TASK 34-21-22-000-001) - remove the standby airspeed indicator (6) 9FN (Ref. TASK 34-21-26000-001). (6) Disconnect the quick-disconnect coupling (7) from the red 2-pin coupling of the standby airspeed indicator (6) and disconnect the quick-disconnect couplings (5) from the yellow 3-pin couplings of the standby instruments 3FN and 9FN. (7) Connect a ADAPTERS - AIR DATA SYSTEM FLUSHING 3-pin adapter (98D34103002100) ) to the hose of the standby altimeter and a ADAPTERS - AIR DATA SYSTEM FLUSHING 2-pin adapter (98D34103002102) to the hose (7). Then connect to the dry nitrogen source - 2 bars (29 psi). (8) Connect the ADAPTER, PITOT - PNEUMATIC CLEANER to the dry nitrogen source - 2 bars (29 psi). (9) Attach the hoses to prevent movement.

  R EFF : 151-199,  34-10-00    CES

 

Page 320 Feb 01/10

**ON A/C 201-220, 236-238, Subtask 34-10-00-860-053-B B. Aircraft Maintenance Configuration (1) Drain the standby air data system (Ref. TASK 12-24-34-600-001). (2) Disconnect the quick-disconnect coupling (4) from the ADM 19FP8 and the quick-disconnect coupling (8) from the ADM 19FP3. (3) Disconnect the cabin-pressure detection pressure-switch 14WN (3) from the static pipe. Put a blanking cap on the pressure switch. (4) Remove the water drain plug (2) from the water drain (1). (5) In the cockpit, on the center instrument panel: - remove the standby altimeter 3FN (Ref. TASK 34-21-22-000-001) - remove the standby airspeed indicator (6) 9FN (Ref. TASK 34-21-26000-001). (6) Disconnect the quick-disconnect coupling (7) from the red 2-pin coupling of the standby airspeed indicator (6) and disconnect the quick-disconnect couplings (5) from the yellow 3-pin couplings of the standby instruments 3FN and 9FN. (7) Connect a ADAPTERS - AIR DATA SYSTEM FLUSHING 3-pin adapter (98D34103002100) to the hose of the standby altimeter and a ADAPTERSAIR DATA SYSTEM FLUSHING 2-pin adapter (98D34103002102) to the hose (7). Then connect to the dry nitrogen source - 2 bars (29 psi). (8) Attach the hoses to prevent movement.

  R EFF : 201-220, 236-238,  34-10-00    CES

 

Page 321 Feb 01/10

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, 4. Procedure _________ R **ON A/C 001-049, 051-099, 101-105, 151-199, R Subtask 34-10-00-170-052-B A. Draining and Flushing of the Standby Static and the Standby Total Pressure Lines (1) Blow the gas into each of the instrument hoses (5) and into the hose (7), from one to the other, at a pressure of 2 bars (29 psi). Do this for approximately 5 minutes. (2) Clean draining hole of the pitot probe 3 with CLEANER-PITOT PROBE and a WIRE-NYLON, dia. 0.6mm. NOTE : The WYRE-NYLON must have a length of 5mm (0.196inch) to ____ prevent contact between the metallic tool element and the pitot probe. (3) Make sure that there is no contamination in the pressurized gas at these outlets: - L static probe 3 and R static probe 3 - Pitot probe 3 - Water drain - Pipe of the cabin-pressure detection pressure-switch. (4) Put an ADAPTER COVER-STATIC PORT on the L static probe 3 then on the R static probe 3. (5) Make sure that the flow of gas is correct at : - the pipe of the pressure switch - the water drain. (6) Stop the flow of gas.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-10-00 201-220, 236-238,   CES

 

Page 322 Feb 01/10

R

**ON A/C 201-220, 236-238,

R

Subtask 34-10-00-170-052-A

R R

A. Draining and Flushing of the Standby Static and the Standby Total Pressure Lines

R R R

(1) Blow the gas into each of the instrument hoses (5) and into the hose (7), from one to the other, at a pressure of 2 bars (29 psi). Do this for approximately 5 minutes.

R R

(2) Clean draining hole of the pitot probe 3 with CLEANER-PITOT PROBE and WIRE-NYLON 0,7 and 0,8mm.

R R R R R R

(3) Make sure that there is no contamination in the pressurized gas at these outlets: - L static probe 3 and R static probe 3 - Pitot probe 3 - Water drain - Pipe of the cabin-pressure detection pressure-switch.

R R

(4) Put an ADAPTER COVER-STATIC PORT on the L static probe 3 then on the R static probe 3.

R R R

(5) Make sure that the flow of gas is correct at : - the pipe of the pressure switch - the water drain.

R

(6) Stop the flow of gas. **ON A/C 001-049, 051-099, 101-105, Subtask 34-10-00-860-054 B. Put the aircraft back to its initial configuration. (1) Disconnect the dry nitrogen source. (2) Remove the adapters. (3) Install the water drain plug (2) on the water drain (1). (4) Remove the blanking cap from the pressure switch 14WN (3). (5) Connect the static pipe to the pressure switch 14WN (3).

  R EFF : 001-049, 051-099, 101-105, 201-220,  34-10-00 236-238,   CES

 

Page 323 Feb 01/10

(6) Connect the quick-disconnect coupling (8) to the ADM 19FP3 and the quick-disconnect coupling (4) to the ADM 19FP8. (Ref. Fig. 304/TASK 34-10-00-991-004) (7) Make sure that you can see the blue ring on the quick-disconnect couplings (4) and (8). (8) Pull the quick-disconnect couplings connectors to be sure that they are correctly attached. (9) Install the standby airspeed indicator (Ref. TASK 34-21-26-400-001) the standby altimeter (Ref. TASK 34-21-22-400-001) and the metric altimeter (15FN) (Ref. TASK 34-21-25-400-001) on the center instrument panel. (10) Release the hoses. (11) Do a visual inspection only, of the quick-disconnect fitting connection, by a second qualified mechanic, with a sign off by both mechanics. **ON A/C 151-199, 201-220, 236-238, Subtask 34-10-00-860-054-A B. Put the aircraft back to its initial configuration. (1) Disconnect the dry nitrogen source. (2) Remove the adapters. (3) Install the water drain plug (2) on the water drain (1). (4) Remove the blanking cap from the pressure switch 14WN (3). (5) Connect the static pipe to the pressure switch 14WN (3). (6) Connect the quick-disconnect coupling (8) to the ADM 19FP3 and the quick-disconnect coupling (4) to the ADM 19FP8. (Ref. Fig. 304/TASK 34-10-00-991-004) (7) Make sure that you can see the blue ring on the quick-disconnect couplings (4) and (8). (8) Pull the quick-disconnect couplings to be sure that they are correctly attached.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-10-00 201-220, 236-238,  R  CES

 

Page 324 Feb 01/10

Illustration of the Quick-Disconnect coupling Figure 304/TASK 34-10-00-991-004   EFF : 001-049, 051-099, 101-105, 151-199,  34-10-00 201-220, 236-238,   CES

 

Page 325 Feb 01/10

(9) Install the standby airspeed indicator (Ref. TASK 34-21-26-400-001) and the standby altimeter (Ref. TASK 34-21-22-400-001) on the center instrument panel. (10) Release the hoses. (11) Do a visual inspection only, of the quick-disconnect fitting connection, by a second qualified mechanic, with a sign off by both mechanics. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, Subtask 34-10-00-790-052 C. Leak test (1) Make sure that all the hoses are connected correctly. (2) Do a leak test of the standby air data system (Ref. TASK 34-21-00-790-001). 5. Close-up ________ Subtask 34-10-00-410-061 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (3) Close the access door 811. (4) Remove the access platform(s).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-10-00 201-220, 236-238,   CES

 

Page 326 Feb 01/10

AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - DEACTIVATION/REACTIVATION ______________________________________________________________________ R TASK 34-10-00-040-002 ADIRS - Check of all Flight Control Accelerometers for Correct Operation 1. __________________ Reason for the Job Refer to the MMEL TASK: 34-10-01 Air data inertial reference ADIRS ADIRS (FAA Only) 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 27-96-00-740-001 31-60-00-860-001 31-60-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power BITE Test of the EFCS (Ground Scanning) EIS Start Procedure EIS Stop Procedure

3. __________ Job Set-up Subtask 34-10-00-860-077 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001). (3) On the center pedestal, on the ECAM control panel, push the STS key (on the lower ECAM DU, the STATUS page comes into view).

  EFF : ALL  34-10-00    CES

 

Page 401 May 01/04

4. Procedure _________ Subtask 34-10-00-040-050 A. Make sure that there is no F/CTL maintenance status on the STATUS page. If there is the F/CTL maintenance status: (1) Do the BITE test of the EFCS (Ground Scanning) (Ref. TASK 27-96-00740-001). (2) Make sure that there are no maintenance messages related to the flight control accelerometers 12CE1, 12CE2, 12CE3 and 12CE4. 5. Close-up ________ Subtask 34-10-00-860-078 A. Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2) Make an entry in the logbook. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  EFF : ALL  34-10-00   R  CES

 

Page 402 May 01/04

AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - ADJUSTMENT/TEST ____________________________________________________________ TASK 34-10-00-710-001 Check of the ADIRS CDU Brightness and Display WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power

3. __________ Job Set-up Subtask 34-10-00-860-063 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits. (Ref. TASK 24-41-00-861002) (2) on the panel 20VU, on the ADIRS CDU, make sure that the three OFF/NAV/ATT selector switches are at OFF.

  EFF : ALL  34-10-00    CES

 

Page 501 Feb 01/98

Subtask 34-10-00-010-063 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-10-00-865-050 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU R R

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

  EFF : ALL  34-10-00    CES

 

N10 N09 N08 N07 N06 N05 N04 N03

Page 502 Feb 01/10

R

**ON A/C ALL 4. Procedure _________ Subtask 34-10-00-710-050 A. Check from the ADIRS CDU: ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU: - set the three OFF/NAV/ATT selector switches to NAV - set the DATA DISPLAY selector switch to TEST and keep it in this position.

- the display (LCD) segments come on - the ENT and CLR keys come on green.

2. Release the DATA DISPLAY selector switch. Subtask 34-10-00-710-051 B. Check from the INT LT ANN LT switch: ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the panel 25VU, set the INT LT ANN LT switch to TEST.

On the ADIRS CDU: - the display (LCD) segments come on - the ENT and CLR keys come on green - the ON BAT light comes on - the FAULT/OFF legends of the ADR pushbutton switches come on. The FAULT/ALIGN legends of the IR annunciators come on.

2. Set the INT LT ANN LT switch to BRT or DIM.

  EFF : ALL  34-10-00    CES

 

Page 503 Feb 01/00

5. Close-up ________ Subtask 34-10-00-860-064 A. De-energize the aircraft electrical circuits. (Ref. TASK 24-41-00-862002) Subtask 34-10-00-410-063 B. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

  EFF : ALL  34-10-00   R  CES

 

Page 504 Feb 01/00

TASK 34-10-00-710-007 Test of the Angle of Attack Warning 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 27-50-00-866-009 31-32-00-860-010 31-60-00-860-001 31-60-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Retraction of the Flaps on the Ground Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure

  EFF : ALL  34-10-00    CES

 

Page 505 Feb 01/98

3. __________ Job Set-up R R

CAUTION : MAKE SURE THAT THE AOA SENSOR CAN MOVE FREELY DURING THE TEST (IT _______ WILL MOVE FROM THE STANDBY POSITION TO THE TEST POSITION). Subtask 34-10-00-860-065 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) On the overhead panel: - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - On the panel 20VU, on the ADIRS CDU, make sure that the three OFF/NAV/ATT selector switches are at OFF. (3) Fully retract the flaps (Ref. TASK 27-50-00-866-009) NOTE : This test is for the system 1. For the systems 2 and 3, use ____ the indications between the parentheses. (4) Do the EIS start procedure (PFD only) (Ref. TASK 31-60-00-860-001). (5) On the MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). Subtask 34-10-00-010-064 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover.

  EFF : ALL  34-10-00    CES

 

Page 506 Feb 01/01

Subtask 34-10-00-865-064 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

2WC 2GA 52GA

P09 Q35 Q34

**ON A/C ALL 121VU EIS/HORN/SPLY 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

  EFF : ALL  34-10-00    CES

 

N10 N09 N08 N07 N06 N05 N04 N03

Page 507 Feb 01/10

**ON A/C ALL Subtask 34-10-00-865-076 D. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 4. Procedure _________ Subtask 34-10-00-710-062 A. Test of the Angle of Attack Warning ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU: - set the three OFF/NAV/ATT selector switches to NAV.

On the CAPT and F/O PFDs: - make sure that the CAS, ALT, V/S data are shown. - make sure that the attitude data is shown 40 seconds after start up.

2. On one MCDU, on the NAV page:

On the MCDU:

- push the line key adjacent to the ADR1 (ADR2) (ADR3) indication.

- the ADIRS ADR1 (ADR2) (ADR3) page comes into view.

- push the line key adjacent to the OUTPUT TESTS indication.

- the OUTPUT TESTS page comes into view.

- push the line key adjacent to the AOA SENSOR TEST indication.

- the AOA SENSOR TEST page comes into view with these indications: AOA SENSOR COMMANDED TO FIXED POSITION MAKE SURE THAT THE AURAL STALL WARNING IS GENERATED. On the L (R) side of the fuselage, in the zone 231 (232) (127), the angle of

  EFF : ALL  34-10-00   R  CES

 

Page 508 May 01/04

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------attack sensor 3FP1 (3FP2) (3FP3) under test moves to the test position. On the panels 130VU and 131VU, the MASTER WARN lights flash. You can hear the cricket aural warning and the STALL voice. - Push the line key adjacent to the YES indication.

On the MCDU: - the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication until the CFDS menu page comes into view.

The test procedure stops. The warning goes out of view. On the MCDU: - the CFDS menu page comes into view.

R 5. Close-up ________ Subtask 34-10-00-860-066 A. Put the aircraft back to its initial configuration. (1) On the ADIRS CDU, set the three OFF/NAV/ATT selector switches to OFF. (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002) (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Remove the access platform(s). Subtask 34-10-00-865-077 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2

  EFF : ALL  34-10-00    CES

 

Page 509 Nov 01/00

Subtask 34-10-00-410-064 C. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

  R EFF : ALL  34-10-00    CES

 

Page 510 Nov 01/00

TASK 34-10-00-710-009 Operational Test of the 5-minute Time Delay of ADIRU 2 and 3 Power Disconnection in Emergency Configuration 1. __________________ Reason for the Job Refer to the MPD TASK: 341300-05 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 31-60-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure

3. __________ Job Set-up Subtask 34-10-00-860-067 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

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Page 511 Nov 01/00

(3) On the overhead panel: - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - on the panel 20VU, on the ADIRS CDU, make sure that the three OFF/NAV/ATT selector switches are at OFF. - on the ELEC panel 35VU, make sure that the battery voltage is correct, between 26VDC and 30VDC. R R

(4) On the SWICHING panel 8VU, make sure that the AIR DATA and ATT HDG selector switches are at NORMAL position. Subtask 34-10-00-010-057 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-10-00-865-068 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

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N11 N10 N09 N08 N07 N06 N05 N04

Page 512 May 01/08

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C ALL 121VU EIS/HORN/SPLY 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY R R

2WC 2GA 52GA

P09 Q35 Q34

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N10 N09 N08 N07 N06 N05 N04 N03

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 101-105, 151-199, 201-203, Subtask 34-10-00-710-064-A A. Operational Test of the 5-minute Time Delay of ADIRU 2 and 3 Power Disconnection in Emergency Configuration NOTE : Ignore the ECAM warnings that can occur when you open the circuit ____ breakers 9FP, 10FP, 4FP2, 4FP3 and 2WC.

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Page 513 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU:

On the ADIRS CDU:

- set the OFF/NAV/ATT selector switches related to the IR 2 and IR 3 to NAV.

- the ALIGN legend comes on. - the ON BAT light comes on for 5 seconds.

- push the ADR 2 and ADR 3 pushbutton switches.

- the OFF legends come on. On the F/O PFD: - after approximately 35 seconds, the attitude is shown.

2. On the circuit breaker panel 121VU: - open the circuit breakers 2WC, 10FP and 4FP2.

3. On the circuit breaker panel 121VU: - close the circuit breakers 4FP2 and 10FP.

4. On the circuit breaker panel 121VU: - open the circuit breakers 9FP and 4FP3.

On the ADIRS CDU: - the ADR OFF legend goes off. - the ON BAT light comes on. - the ALIGN legend of the IR 2 annunciator stays on. After 5 minutes - the ALIGN legend of the IR 2 annunciator and the ON BAT light go off. On the F/O PFD: - the ATT warning flag is shown. On the ADIRS CDU: - the ALIGN legend of the IR 2 annunciator comes on. - the ON BAT light comes on for 5 seconds. On the ADIRS CDU: - the ON BAT light comes on. After 5 minutes: - the ALIGN legend of the IR 3 annunciator and the ON BAT light go off.

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Page 514 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------5. On the circuit breaker panel 121VU: - close the circuit breakers 2WC, 9FP and 4FP3.

- the ON BAT light comes on for 5 seconds. - the ALIGN legend of the IR 3 annunciator comes on.

6. On the ADIRS CDU: - set the two OFF/NAV/ATT selector switches to OFF. R

**ON A/C ALL

R

Post SB

34-1249 For A/C 001-049,101-105,151-199,201-203,

Subtask 34-10-00-710-064 A. Operational Test of the 5-minute Time Delay of ADIRU 2 and 3 Power Disconnection in Emergency Configuration NOTE : Ignore the ECAM warnings that can occur when you open the circuit ____ breakers 9FP, 10FP, 4FP2, 4FP3 and 2WC. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU:

On the ADIRS CDU:

R - set the OFF/NAV/ATT selector switches related to the IR 2 and IR 3 to NAV.

- the ALIGN legend comes on. - the ON BAT light comes on for 5 seconds.

- push the ADR 2 and ADR 3 pushbutton switches.

- the OFF legend comes on. On the F/O PFD: - after approximately 35 seconds, the attitude is shown.

R R

2. On the circuit breaker panel 121VU: R

- open the circuit breakers 2WC,

On the ADIRS CDU: - the ON BAT light comes on.

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Page 515 May 01/08

R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------4FP2 and 10FP. - the ALIGN legend of the IR 2 annunciator stays on. - the OFF legend ADR2 p/b sw goes off. After 5 minutes - the ALIGN legend of the IR 2 annunciator and the ON BAT light go off. On the F/O PFD: - the ATT warning flag is shown. 3. On the circuit breaker panel 121VU:

R R R R R R

- close the circuit breakers 10FP and 4FP2.

4. On the circuit breaker panel 121VU: - open the circuit breakers 9FP and 4FP3.

On the ADIRS CDU: - the ON BAT light can flash for 5 seconds, - the ALIGN legend of the IR 2 annunciator comes on, - the OFF/FAULT legend ADR 2 p/bsw can flash for 3 seconds. On the ADIRS CDU: - the ON BAT light comes on. After 5 minutes: - the ALIGN legend of the IR 3 annunciator, the OFF legend ADR3 p/b sw and the ON BAT light go off.

5. On the circuit breaker panel 121VU: R R R R R

- close the circuit breakers 2WC, 4FP3 and 9FP.

- the ON BAT light stays off, - the ALIGN legend of the IR 3 annunciator comes on, - the OFF/FAULT legend ADR 3 p/bsw can flash for 3 seconds.

6. On the ADIRS CDU: - set the two OFF/NAV/ATT selector switches to OFF.

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Page 516 May 01/08

**ON A/C ALL 5. Close-up ________ Subtask 34-10-00-860-068 A. Put the aircraft back to its initial configuration. Do the EIS stop procedure (Ref. TASK 31-60-00-860-002) (1) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). Subtask 34-10-00-410-057 B. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

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Page 517 May 01/04

SENSORS, POWER SUPPLY AND SWITCHING - DESCRIPTION AND OPERATION _______________________________________________________________ 1. _______ General The aircraft is equipped with three Air Data/Inertial Reference Units (ADIRUs). Each ADIRU receives data from the four types of sensors after: - three pitot probes which provide total pressure data, - six static probes which provide static pressure data, - two Total Air Temperature (TAT) sensors which provide air temperature data, - three Angle Of Attack (AOA) sensors which provide angle of attack data of the aircraft. The TAT sensors and the angle of attack sensors are directly connected to the ADIRUs. The pitot probes and the static probes are connected to eight Air Data Modules (ADM) which convert pressure data before they send them to the ADIRUs. The sensors, the probes, the ADMs and the ADIRUs are power supplied as follows: ------------------------------------------| EQUIPMENT | 28VDC | 115VAC | 26VAC | ------------------------------------------| ADIRU | X | X | X | |----------------|-------|--------|-------| | AOA Sensor | | X | X | |----------------|-------|--------|-------| | PITOT Probe | | X | | |----------------|-------|--------|-------| | TAT Sensor | | X | | |----------------|-------|--------|-------| | STATIC Probe | X | | | |----------------|-------|--------|-------| | ADM |13.5VAC from ADIRU | ------------------------------------------In normal configuration, the Captain Primary Flight Display (PFD) and Navigation Display (ND) show the data computed by the ADIRU 1. The First Officer PFD and ND show the data computed by the ADIRU 2. The data from the ADIRU 3 can be displayed by action on the AIR DATA selector switch or on the ATT HDG selector switch located on the SWITCHING panel. These selector switches which define a priority order for the ADIRUs are also used by several other aircraft systems (Ref. Para. 4.F.).

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2. Component __________________ Location (Ref. Fig. 001) The sensors, probes and ADMs are located on the aircraft as follows: ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------R R R R

3FP1 3FP2

SENSOR-ANGLE OF ATTACK, 1 SENSOR-ANGLE OF ATTACK, 2

231 232

3FP3 11FP1 11FP2 19FP1 19FP2 19FP3 19FP4 19FP5 19FP6 19FP7 19FP8 7DA1 7DA2 7DA3 8DA1 8DA2 8DA3 9DA1 9DA2 9DA3

SENSOR-ANGLE OF ATTACK, 3 SENSOR-TAT, 1 SENSOR-TAT, 2 ADM-L TOTAL PRESSURE ADM-R TOTAL PRESSURE ADM-STBY TOTAL PRESSURE ADM-R STATIC PRESSURE ADM-L STATIC PRESSURE ADM-R STATIC PRESSURE ADM-L STATIC PRESSURE ADM-STBY STATIC PRESSURE PROBE-L STATIC, 1 PROBE-L STATIC, 2 PROBE-L STATIC, 3 PROBE-R STATIC, 1 PROBE-R STATIC, 2 PROBE-R STATIC, 3 PROBE-PITOT, 1 PROBE-PITOT, 2 PROBE-PITOT, 3

127 121 122 NONE 125 126 125 128 127 128 127 121 127 127 121 128 128 122 125 126 125

34-11-19 34-11-19 824 812 822 812 824 824 824 824 811 824 824 811 824 824 811 812 822 812

34-11-19 34-11-18 34-11-18 34-11-17 34-11-17 34-11-17 34-11-17 34-11-17 34-11-17 34-11-17 34-11-17 34-11-16 34-11-16 34-11-16 34-11-16 34-11-16 34-11-16 34-11-15 34-11-15 34-11-15

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ADIRS - Probe and Sensor Location Figure 001   R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00 Page 3   Config-1 May 01/05  CES

 

The different ADIRS switching devices are located on the aircraft as follows: ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------12FP RELAY-ADIRS ON BAT/GROUND WARN 103VU 126 34-11-00 13FP SEL SW-ATT HDG 8VU 210 34-11-00 14FP RELAY-ADIRS 3 PWR SHEDDING 103VU 126 34-11-00 15FP SEL SW-AIR DATA 8VU 210 34-11-00 16FP RELAY-ADIRS 3 28VDC CONTROL 103VU 126 34-11-00 17FP RELAY-ADIRS 2 PWR SHEDDING 103VU 126 34-11-00 21FP1 RELAY-AOA1 TEST 103VU 126 34-11-00 21FP2 RELAY-AOA2 TEST 103VU 126 34-11-00 21FP3 RELAY-AOA3 TEST 103VU 126 34-11-00 22FP SW-L/G DOWN VMO/MMO SELECTION 188VU 128 34-11-00 23FP RELAY-ADIRS LGCIU GND POS 103VU 126 34-11-00 -----------------------------------------------------------------------------NOTE : The function of the switch (22FP) is described in 34-12-00. ____

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3. ____________ Power Supply A. General (Ref. Fig. 002) The ADIRU is normally supplied with 115VAC, 400 Hz power for the ADR and IR functions. However its AOA resolver converter module is supplied with 26VAC, 400 Hz. The 28VDC back-up generation is provided by batteries and is automatically used when the main power exceeds its normal limits. At the beginning of each power cycle, the ADIRU switches from the main to the back-up power to test the electrical generation. The table below gives the power consumption of each unit of the ADIRS: -----------------------------------------------------------------| EQUIPMENT | 28VDC | 115VAC | 26VAC | | |-------------------|-------------------| | | | Typical | Maximum | Typical | Maximum | | -----------------------------------------------------------------| ADIRU | 57 W | 71 W | 61 VA | 76 VA | 1 VA | |----------------|---------|---------|---------|---------|-------| | AOA Sensor | | | 250 VA | 320 VA |3.5 VA | |----------------|---------|---------|---------|---------|-------| | PITOT Probe | | | 281 VA | 360 VA | | |----------------|---------|---------|---------|---------|-------| | TAT Sensor | | | 200 VA | 350 VA | | |----------------|---------|---------|---------|---------|-------| | STATIC Probe | | 2X75 W | | | | |----------------|---------|---------|---------|---------|-------| | PHC | | 14 W | | | | -----------------------------------------------------------------(1) ADIRU power consumption includes the supply of three ADMs. With ON BAT annunciator, add 0.6 W. With IR FAULT annunciator at I = 250 mA, add 1.3 W. Other annunciators are open/ground discretes and so they are energized by a power which is different from the ADIRU power. When the ADIRU is in the OFF mode, all the circuitry in the ADIRU is de-energized except for any logic associated with the power off function. Power consumption does not exceed 3.0 W on 115VAC and 0.3 W on 28VDC. Each ADIRU supplies the power for the ADM of its side (CAPT, F/O, STBY). The ADIRU also supplies the CDU with a 28VDC signal. The consumption of the CDU is 4.1 W (typical) and 19.1 W (maximum with additional 11.2 W for the first 2 minutes of turn-on at -15⁰ for LCD heaters).

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ADIRS - Power Supply Distribution Figure 002   R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00 Page 6   Config-1 May 01/05  CES

 

B. ADIRS Power Supply Distribution in Normal Configuration (1) Captain side The ADIRU 1 is supplied with 115VAC by the 115VAC SHED ESS BUS 801XP-A. The back-up 28VDC is provided by the 28VDC HOT BUS 701PP. The resolvers of the AOA sensor 1 and the AOA resolver converter module of the ADIRU 1 are supplied with 26VAC by the 26VAC ESS BUS 431XP-A. The sensors and probes (static, TAT, pitot, AOA) are supplied for heating through the Probe Heat Computer 1: - the heating element of the AOA sensor 1 receives 115VAC from the 115VAC SHED ESS BUS 801XP - the heating element of the TAT sensor 1 receives 115VAC from the 115VAC BUS 1 101XP-A - the heating element of the L and R static probes 1 receives 28VDC from the 28VDC BUS 1 101PP - the heating element of the pitot probe 1 receives 115VAC from the 115VAC ESS BUS 401XP. (Ref. Fig. 003) NOTE : the ADIRS/PHC Interface figure is a principle diagram and does ____ not show the interface between the PHC and the sensors. (Ref. 30-31-00 for more details on probe ice protection). (2) First Officer side The ADIRU 2 is supplied with 115VAC by the 115VAC BUS 2 204XP-C. The back-up 28VDC is provided by the 28VDC HOT BUS 702PP. The resolvers of the AOA sensor 2 and the AOA resolver converter module of the ADIRU 2 are supplied with 26VAC by the 26VAC BUS 2 231XP-A. The sensors and probes are supplied for heating through the PHC 2: - the heating element of the AOA sensor 2 receives 115VAC from the 115VAC BUS 2 202XP-B - the heating element of the TAT sensor 2 receives 115VAC from the 115VAC BUS 2 202XP-C - the heating element of the L and R static probes 2 receives 28VDC from the 28VDC BUS 2 206PP - the heating element of the pitot probe 2 receives 115VAC from the 115VAC BUS 2 202XP-B. (3) Standby side The ADIRU 3 is supplied with 115VAC by the 115VAC BUS 1 101XP-C. The back-up 28VDC is provided by the 28VDC HOT BUS 701PP. The resolvers of the AOA sensor 3 and the AOA resolver converter module of the ADIRU 3 are supplied with 26VAC by the 26VAC BUS 1 131XP-A. The sensors and probes are supplied for heating through the PHC 3: - the heating element of the AOA sensor 3 receives 115VAC from the 115VAC BUS 1 103XP

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ADIRS/PHC Interface Figure 003   R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00 Page 8   Config-1 May 01/05  CES

 

- the heating element of the L and R static probes 3 receives 28VDC from the 28VDC BUS 1 103PP - the heating element of the pitot probe 3 receives 115VAC from the 115VAC BUS 1 103XP. In normal configuration of the aircraft electrical generation, the distribution described before is independent of the switching selector switches. C. ADIRS Power Supply Distribution after Loss of Main Electrical Generation (1) Loss of the main generation and ATT HDG selector switch in NORM position (a) Captain side The ADIRU 1 is supplied as in normal configuration. (Ref.Para B.(1)). (b) First Officer side The ADIRU 2 is no more supplied with 115VAC and 26VAC. When the 26VAC is lost, the ADR detects a fault and flags the output parameters. The ADIRU is still powered with 28VDC from the 28VDC HOT BUS 702PP but the Time Delay Opening (TDO) relay 17FP will cut this supply after 5 minutes in emergency configuration. The ADR 2 function is lost immediately. The IR 2 function is lost after 5 minutes. (c) Standby side The ADIRU 3 is no more supplied with 115VAC and 26VAC. When the 26VAC is lost, the ADR detects a fault and flags the output parameters. The ADIRU is still powered with 28VDC from the 28VDC HOT BUS 701PP but the Time Delay Opening (TDO) relay 14FP will cut this supply after 5 minutes in emergency configuration. The ADR3 function is lost immediately. The IR 3 function is lost after 5 minutes. (2) Loss of the main generation and ATT HDG selector switch in CAPT/3 position The CAPT/3 position of the ATT HDG selector switch corresponds to the selection of the ADR 3 in place of the ADR 1. The power supply distribution must then be modified to keep the ADR 3 in emergency configuration. (a) Captain side The ADIRU 1 is supplied as in normal configuration (Ref. Para. B.(1)).

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(b) First Officer side ADIRU 2 supply: Ref. Para. (1)(b). (c) Standby side The ADIRU 3 is no more supplied with 115VAC. The ADIRU 3 is still powered with 28VDC from the 28VDC HOT BUS 701PP. The ADR 3 function is lost immediately. The IR 3 function is available.

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D. Circuit Breakers The system is supplied through these circuit breakers: ----------------------------------------------------------------------------FIN PANEL/ DESIGNATION BUS ATA. REF. AMM LOCATION P. BLOCK 001 ----------------------------------------------------------------------------4FP1 49VU NAV AND PROBES/ADIRU1/115VAC 801XP-A 34-11-00 4FP2 121VU ADIRS/ADIRU/2/115VAC 204XP-C 34-11-00 4FP3 121VU ADIRS/ADIRU/3/115VAC 101XP-C 34-11-00 5FP1 49VU NAV AND PROBES/ADIRU1 & 431XP-A 34-11-00 AOA/26VAC 5FP2 121VU ADIRS/ADIRU/2/26VAC AND AOA 231XP-A 34-11-00 5FP3 121VU ADIRS/ADIRU/3/26VAC AND AOA 131XP-A 34-11-00 6FP1 105VU ADIRS/ADIRU1/28VDC 704PP 34-11-00 6FP2 121VU ADIRS/ADIRU/2/28VDC 702PP 34-11-00 6FP3 121VU ADIRS/ADIRU/3/28VDC 701PP 34-11-00 8FP 49VU NAV AND PROBES/ADIRU 3/ 401PP 34-11-00 SWTG/SPLY 9FP 121VU ADIRS/ADIRU/3 SWTG/SPLY 301PP 34-11-00 10FP 121VU ADIRS/ADIRU/2 PWR/SHED 206PP 34-11-00 1DA1 122VU ANTI ICE/PROBES/1/TAT 101XP-A 30-31-00 1DA2 122VU ANTI ICE/PROBES/2/TAT 202XP-C 30-31-00 2DA1 49VU ANTI ICE/PROBES/PHC/1 401PP 30-31-00 2DA2 122VU ANTI ICE/PROBES/2/PHC 206PP 30-31-00 2DA3 122VU ANTI ICE/PROBES/PHC/3 101PP 30-31-00 3DA1 49VU ANTI ICE/PROBES/PITOT/1 401XP-B 30-31-00 3DA2 122VU ANTI ICE/PROBES/2/PITOT 202XP-B 30-31-00 3DA3 122VU ANTI ICE/PROBES/3/PITOT 103XP-C 30-31-00 4DA1 49VU ANTI ICE/PROBES/1/AOA 801XP-C 30-31-00 4DA2 122VU ANTI ICE/PROBES/2/AOA 202XP-B 30-31-00 4DA3 122VU ANTI ICE/PROBES/3/AOA 103XP-C 30-31-00 5DA1 122VU ANTI ICE/PROBES/1/STATIC 101PP 30-31-00 5DA2 122VU ANTI ICE/PROBES/2/STATIC 206PP 30-31-00 5DA3 122VU ANTI ICE/PROBES/3/STATIC 103PP 34-11-00

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4. _____________________ Component Description A. Static Probes (Ref. Fig. 004) Each of the three systems (CAPT (1), F/O (2), STBY (3)) comprises two static probes which are linked to each ADR portion of the ADIRUs through five ADMs. The probe is protected from icing with a 28VDC heater circuit. The static probes linked to ADIRU 1 and ADIRU 2 are set at 48.64 deg. below the fuselage datum line (Z=0). The static probes linked to ADIRU 3 are set at 29.5 deg. below the fuselage datum line. B. Pitot Probes (Ref. Fig. 005) Each system comprises one pitot probe (CAPT (1), F/O (2), STBY (3)) which is linked to each ADR portion of the ADIRUs through one ADM. The probe is protected from icing with a 115VAC - 400 Hz heater circuit.

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ADIRS - Static Probe Figure 004   R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00 Page 13   Config-1 May 01/05  CES

 

ADIRS - Pitot Probe Figure 005   R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00 Page 14   Config-1 May 01/05  CES

 

C. Air Data Modules (ADM) (Ref. Fig. 006) The term Air Data Module (ADM) refers to any remotely located LRU which senses pressure information and transmits it to the ADIRU in ARINC 429 format. The ADMs are remotely mounted near and above the level of the pitot and static probes, this in order to make the ADM pneumatic plumbing self draining when the aircraft is stationary on the ground. (1) Internal description The ADM comprises the following components (Ref. Fig. 007) (a) Pressure sensor The sensor delivers a pressure frequency (Fp) signal and a temperature frequency (Ft) signal corresponding to the measured pressure. (b) Processor board The electronic card comprises the following circuits: - a micro-controller 80C31 - two memories: ROM (storage of software program and pressure sensor modelling coefficients) and RAM (temporary storage of data) - an ARINC 429 transmitter. The processor board uses the Ft and Fp signals sent by the pressure sensor and the sensor modelling coefficients stored in the EEPROM to compute the pressure. (c) EMI/lightning board This board comprises the following devices: - power supply: the ADM is supplied by the associated ADIRU with +/- 13.5VAC. Power consumption is less than 200 mA on the +13.5VDC input and less than 40 mA on the -13.5VDC input. - EMI filters - lightning protection - input discretes filtering. (2) Modes of operation The ADM has two modes of operation: - power-up - normal operation. (a) Power-up Two types of reset are available depending on the following conditions :

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Air Data Module Figure 006   R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00 Page 16   Config-1 May 01/05  CES

 

ADM - Block Diagram Figure 007   R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00 Page 17   Config-1 May 01/05  CES

 

1 _

Complete reset The equipment performs a complete hardware and software reset cycle whenever the equipment is switched on or after a power cut greater than 100 ms. In this case, the equipment is fully operational after 2 seconds. The complete reset includes all that is necessary to initialize the operation of the equipment : - initialize the RAM, variables, counters. - tests : * discrete input parity : After the 5 SDI discretes have been acquired, and position identification and parity checks have been made, the parity bits are checked to ensure that there is an odd number of logic 1s. * ARINC output : Two additionnal configurations are looped back, and the words thus received are checked bit by bit. * An algorithm requiring a significant number of instructions is run for the Arithmetic and Logic Unit test. * The internal RAM is checked by means of a write-read sequence. - wait for sensor periods to be set and initialization of the pressure filter. - transmission on ARINC : * no transmission during the reset hard (0.1 s) * transmission of discrete words with bits set to the pass condition * transmission of pressure parameter : the Status Sign Matrix is set to Functional Test and the data is set to zero.

2 _

Modified reset The equipment performs a modified reset after a power cut equal or less than 10 ms. In this case, the equipment is fully operational within 100 ms +/- 5 ms. The modified reset includes the following initializations : - initialize the RAM, variables, counters. - initialize the pressure filter after 2 calculated pressure (30 ms). - no transmission on ARINC during this reset.

3 _

The equipment performs either type of reset after a power cut greater than 10 ms and less than 100 ms.

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(b) Normal operation mode The ADM enters the Normal Operation Mode after the completion of the Power-up Mode. It remains in the Normal Operation Mode until either power is removed from the ADM, or an internal failure activates the Watchdog Timer, or an internal BITE detects an unsafe condition at which time a failure warning is annunciated or ARINC 429 transmissions cease. The ADM performs the following functions in the Normal Operation Mode: - measures the pressure and temperature outputs from the pressure sensor - uses filtering or averaging techniques consistent with the noise, resolution, and dynamic frequency response requirements - computes the Applied Pressure based upon the pressure and temperature signals - filters the Computed Pressure - formats the ARINC 429 word to be transmitted - transmits the ARINC 429 Computed Pressure Word - formats and transmits two ADM discrete words (labels 270, 271) - performs the BITE functions - formats and transmits ADM software and equipment I.D. words (labels 040,377).

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(3) Discrete inputs Table 1 gives the identification of the ADM discrete inputs: -------------------------------------------| ADM Pin | Identification | -------------------------------------------| K | SDI 1 (LSB) (2) | | L | SDI 2 (MSB) (2) | | M | Configuration code 1 (3) | | N | Configuration code 2 (3) | | P | Parity (1) | -------------------------------------------Table 1 = Discrete Inputs NOTE : (1) An odd number of pins K, L, M, N and P must be grounded to ____ signify a valid installation. After the desired Source Data Identifier (SDI) and the configuration pins have been selected, the parity pin P must be selectively left open or grounded to ensure that an odd number of pins K through P inclusive have been grounded. NOTE : (2) Program pins used for identification of the installation ____ position on the aircraft and the corresponding SDI code to be transmitted. The code definition is provided in table 2. NOTE : (3) The ADM transmits the measured pressure with a label ____ depending on the configuration code input discretes. The configuration code definition is provided in table 3. -----------------------------------------------------------------------|Input discrete SDI output |Input discrete SDI output |Installation| | pin L Bit 10 state| pin K Bit 09 state| | |----------------------------------------------------------------------| | open 0 | open 0 | Invalid | | open 0 | ground 1 | 1 | | ground 1 | open 0 | 2 | | ground 1 | ground 1 | 3 | -----------------------------------------------------------------------Table 2 = SDI Code

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--------------------------------------------------------------------| Installation function | Config. code 1 | Config. code 2 | Label | | | Pin N | Pin M | | |-------------------------------------------------------------------| | Total pressure | open | open | 242 | | Left static pressure | open | ground | 176 | | Right static pressure | ground | open | 177 | | Averaged static | ground | ground | 245 | | pressure (uncorrected)| | | | --------------------------------------------------------------------Table 3 = Configuration Code (4) Output bus All data are transmitted via a single ARINC 429 low-speed serial digital output bus. The outputs from the ADM are a single pressure word having an installation selectable label, two discrete data words, and two identification words. The following table gives: - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds - CODE : BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code parameters are given in the table 4 below: - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. All these parameters are given in the table 4 below:

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 242 |TOTAL |100-1400 |hPa | | 18 |29- |BNR | | | | |PRESSURE |+/- 0.25 | | | |31 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 176 |LEFT STAT |100-1100 |hPa | | 18 |29- |BNR | | | | |PRESSURE |+/- 0.25 | | | |31 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 177 |RIGHT STAT|100-1100 |hPa | | 18 |29- |BNR | | | | |PRESSURE |+/- 0.25 | | | |31 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 245 |AVERAGED |100-1100 |hPa | | 18 |29- |BNR | | | | |STATIC |+/- 0.25 | | | |31 | | | | | |PRESSURE | | | | | | | | | | |(UNCORRTD)| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DISCRETE |Table 5 | | | |250-|BCD | | | | |WORD 1 | | | | |500 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 271 |DISCRETE |Table 6 | | | |250-|BCD | | | | |WORD 2 | | | | |500 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQUIPMENT |Table 7 | | | |250-|BCD | | | | |IDENT | | | | |500 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 040 |SOFTWARE |Table 8 | | | |250-|BCD | | | | |IDENT | | | | |500 | | | | ------------------------------------------------------------------------------Table 4 = Digital Outputs

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--------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 270 | | 9-10 |SDI | | 11-20 |P/N coded in binary (currently 329) | | 21-27 |Version number coded in binary | | 28-29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to NO for a maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 5 = Discrete Word 1 (Label 270) --------------------------------------------------------------------| Bit |Data | Bit Status | | Position | | 0 | 1 | |-------------------------------------------------------------------| | 1-8 |Octal Label 271 | | | | 9-10 |SDI | | | | 11-13 |Logic 0 | 0 | | | 14 |EEPROM program memory | Failure | OK | | 15 |Discrete input parity | Failure | OK | | 16 |CPU | Failure | OK | | 17 |ARINC output | Failure | OK | | 18-20 |Logic 1 | | 1 | | 21 |Pressure period range |off.range | OK | | 22 |Temperature period range |off.range | OK | | 23 |Absolute pressure range |off.range | OK | | 24-26 |Logic 1 | | 1 | | 27 |Pressure counter | Failure | OK | | 28 |Temperature counter | Failure | OK | | 29 |Logic 1 | | 1 | | 30-31 |Logic 0. Set the SSM to NO for a | 0 | | | |maintenance word | | | | 32 |Odd parity | | | --------------------------------------------------------------------Table 6 = Discrete Word 2 (Label 271)

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--------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 377 | | 9-10 |SDI | | 11-24 |Serial Number coded in binary | | 25-29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to NO for a maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 7 = Hardware Identification word (Label 377) --------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 040 | | 9-10 |SDI | | 11-12 |Logic 0 | | 13-16 |LSD software version number | | 17-20 |MSD software version number | | 21-24 |LSD manufacturer ident number | | 25-28 |MSD manufacturer ident number | | 29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to NO for a maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 8 = Software Ident (Label 040)

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D. Total Air Temperature (TAT) Sensor (Ref. Fig. 008) The aircraft is equipped with two TAT sensors with two sensing elements each. The sensing elements of the sensor have variable resistances. The TAT sensor 1 is linked to the ADR portion of ADIRUs 1 and 3, the TAT sensor 2 is linked to the ADR portion of ADIRU 2. The TAT sensors are set at 2.33 m from the nose and at 0.60 m of the aircraft axis below the fuselage. The TAT sensor 1 is located on the left side and the TAT sensor 2 on the right side. The air flow enters the scoop of the sensor, goes through a calibrated choke and flows over the hermetically sealed platinum resistance sensing element where the temperature is measured. The speed of the flow over the element is controlled by the choke in the element tube. The ADR portion is designed to operate with 500 ohms (at 0 deg. C) temperature sensor unit corresponding to the basic Callender - Van Dusen equation. To improve the accuracy of the sensor, a network of precision resistors is used. This technique is identified by the term Precision Calibration Interchangeability (PCI). These sensors are heated with 115VAC through the probe heating system. The heating element must not be energized on the ground. The heating element is implanted in the scoop and strut and keeps the probe free of ice under the most severe icing conditions. NOTE : Probe ice protection is described in 30-31-00. ____

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ADIRS - TAT Sensor Figure 008   R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00 Page 26   Config-1 May 01/05  CES

 

E. Angle Of Attack (AOA) Sensor R

**ON A/C 001-049, 101-102, 201-203, (Ref. Fig. 009)

R

**ON A/C 103-105, 151-199, (Ref. Fig. 009A)

R

**ON A/C 001-049, 101-105, 151-199, 201-203, The aircraft is equipped with three AOA sensors. Two are located on the left side and one on the right side of the fuselage. Each of these AOA sensors is respectively linked to each ADR portion of the ADIRUs. The AOA sensors 1 and 3 are set at 6.08 deg. and 31 deg. below the fuselage datum line (Z = 0) on the left side. The AOA sensor 2 is set at 6.08 deg. below the fuselage datum line (Z = 0) on the right side. The angle of attack sensor is of the wind vane type. Its sensing element is a small wing which is positioned in the direction of airflow. The small wing is mechanically linked to a free turn-shaft which drives the devices transmitting the local angle of attack signal. These transmitting devices are made up of resolver transformers which convert the angular information into proportional electrical information (angle sine and cosine). The resolvers are supplied with a 26VAC signal. The same signal is also received by the ADIRU as a reference for the decoding of AOA values. Each sensor has three resolver outputs but only two are wired to the ADIRU. The whole mechanism is stabilized around the rotation axis. In addition, a damping device enables a satisfactory dynamic response to be obtained (filtering of mechanical oscillation). A self-regulated heating element (CTP resistances: positive coefficient of temperature) inserted into the vane eliminates or avoids icing. It is supplied with 115VAC through the PHC (Ref. 30-31-00). The AOA sensor is equipped with a self-test device which is activated by a 28VDC signal, from the ADR (through the relay 21FP1, 21FP2 or 21FP3) when the test is entered via the maintenance system (CFDIU and MCDU). The self-test positions the vane at a resolver angle of +15 deg. (left side test) or -15 deg. (right side test). The mounting and wing of AOA resolvers determine the relationship between the measured resolver angle and indicated angle of attack. This relationship for each resolver input is as follows: (Ref. Fig. 010)

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ADIRS - AOA Sensor Figure 009   R EFF : 001-049, 101-102, 201-203,  34-11-00 Page 28   Config-1 May 01/05  CES

 

ADIRS - AOA Sensor Figure 009A   R EFF : 103-105, 151-199,  34-11-00 Page 29   Config-1 May 01/05  CES

 

AOA Sensors - Installation Definition Figure 010   R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00 Page 30   Config-1 May 01/05  CES

 

-----------------------------------------------------------------------| | Indicated AOA: | +85 | +60 | +25 | 0 | -35 | | AOA 1 and AOA 3 |----------------------------------------------------| | in degrees | Resolver angle: | -60 | -35 | 0 | +25 | +60 | -----------------------------------------------------------------------| | Indicated AOA: | +85 | +60 | +25 | 0 | -35 | | AOA 2 |----------------------------------------------------| in degrees | Resolver angle: | +60 | +35 | 0 | -25 | -60 | -----------------------------------------------------------------------The ADRs receive the same 26VAC, 400 Hz reference as the AOA resolvers. This reference is common to both AOA resolver inputs 1 and 2. Characteristics: Excitation : 26 V 400 Hz Phase shift : 18 deg. to 30 deg. Resolver transformer : ratio RT : 0.4029 to 0.4629 Rotor impedance : Zro = 125 + j175 ohms +/-20% Stator impedance : Zso = 115 + j90 ohms +/-30% Range : +/-60 deg. Scale factor : 1 deg. resolver/1 deg. local AOA The accuracy of the AOA sensor, at 100 knots, is +/-0.3 deg.

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**ON A/C 001-049, 101-105, 151-199, F. Selector Switches (Ref. Fig. 011) The two selector switches AIR DATA and ATT HDG are rotary selector switches with 3 positions: CAPT/3, NORM and F/O/3. These selector switches are used for the functions listed below (Ref. the respective section for more details): - AIR DATA SEL SW (15FP): 34-14-00 Selection of the ADR used by the IR3 34-52-00 ATC mode S 31-68-00 DMC 22-85-00 FMGC - ATT HDG SEL SW (13FP): 34-11-00 Power Supply 34-14-00 Selection of the ADR used by the IR3 34-41-00 Weather Radar R 31-68-00 DMC 22-85-00 FMGC.

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ADIRS Switching Figure 011   R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00 Page 33   Config-1 Aug 01/07  CES

 

**ON A/C 201-203, F. Selector Switches (Ref. Fig. 011) The two selector switches AIR DATA and ATT HDG are rotary selector switches with 3 positions: CAPT/3, NORM and F/O/3. These selector switches are used for the functions listed below (Ref. the respective section for more details): - AIR DATA SEL SW 15FP = 34-14-00 Selection of the ADR used by IR3 34-52-00 ATC mode S 31-68-00 DMC 22-85-00 FMGC - ATT HDG SEL SW 13FP = 34-11-00 Power Supply 34-14-00 Selection of the ADR used by IR3 34-41-00 Weather Radar R 31-68-00 DMC 22-85-00 FMGC.

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SENSORS, POWER SUPPLY AND SWITCHING - DESCRIPTION AND OPERATION _______________________________________________________________ 1. _______ General The aircraft is equipped with three Air Data/Inertial Reference Units (ADIRUs). Each ADIRU receives data from four types of sensors: - three pitot probes which provide total pressure data, - six static probes which provide static pressure data, - two Total Air Temperature (TAT) sensors which provide air temperature data, - three Angle Of Attack (AOA) sensors which provide angle of attack data of the aircraft. The TAT sensors and the angle of attack sensors are directly connected to the ADIRUs. The pitot probes and the static probes are connected to eight Air Data Modules (ADM) which convert pressure data before sending them to the ADIRUs. The sensors, the probes, the ADMs and the ADIRUs are power supplied as follows: ------------------------------------------| EQUIPMENT | 28VDC | 115VAC | 26VAC | ------------------------------------------| ADIRU | X | X | X | |----------------|-------|--------|-------| | AOA Sensor | | X | X | |----------------|-------|--------|-------| | PITOT Probe | | X | | |----------------|-------|--------|-------| | TAT Sensor | | X | | |----------------|-------|--------|-------| | STATIC Probe | X | | | |----------------|-------|--------|-------| | ADM |13.5VAC from ADIRU | ------------------------------------------In normal configuration, the Captain Primary Flight Display (PFD) and the Navigation Display (ND) show the data computed by the ADIRU 1. The First Officer PFD and ND show the data computed by the ADIRU 2. The data from the ADIRU 3 can be displayed by action on the AIR DATA selector switch or on the ATT HDG selector switch located on the SWITCHING panel. These selector switches, which define a priority order for the ADIRUs, are also used by several other aircraft systems (Ref. Para. 4.F.).

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2. Component __________________ Location (Ref. Fig. 001) The sensors, probes and ADMs are located on the aircraft as follows: ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------3FP1 SENSOR-ANGLE OF ATTACK, 1 231 34-11-19 3FP2 SENSOR-ANGLE OF ATTACK, 2 232 34-11-19 3FP3 SENSOR-ANGLE OF ATTACK, 3 127 824 34-11-19 11FP1 SENSOR-TAT, 1 121 34-11-18 11FP2 SENSOR-TAT, 2 122 34-11-18 19FP1 ADM-L TOTAL PRESSURE NONE 125 812 34-11-17 19FP2 ADM-R TOTAL PRESSURE 126 822 34-11-17 19FP3 ADM-STBY TOTAL PRESSURE 125 812 34-11-17 19FP4 ADM-R STATIC PRESSURE 128 824 34-11-17 19FP5 ADM-L STATIC PRESSURE 127 824 34-11-17 19FP6 ADM-R STATIC PRESSURE 128 824 34-11-17 19FP7 ADM-L STATIC PRESSURE 127 824 34-11-17 19FP8 ADM-STBY STATIC PRESSURE 121 811 34-11-17 7DA1 PROBE-L STATIC, 1 127 824 34-11-16 7DA2 PROBE-L STATIC, 2 127 824 34-11-16 7DA3 PROBE-L STATIC, 3 121 811 34-11-16 8DA1 PROBE-R STATIC, 1 128 824 34-11-16 8DA2 PROBE-R STATIC, 2 128 824 34-11-16 8DA3 PROBE-R STATIC, 3 122 811 34-11-16 9DA1 PROBE-PITOT, 1 125 812 34-11-15 9DA2 PROBE-PITOT, 2 126 822 34-11-15 9DA3 PROBE-PITOT, 3 125 812 34-11-15

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ADIRS - Probe and Sensor Location Figure 001   EFF : 524-526, 528-599,  34-11-00 Page 3   Config-2 Feb 01/10  CES

 

The different ADIRS switching devices are located on the aircraft as follows: ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------12FP RELAY-ADIRS ON BAT/GROUND WARN 103VU 126 34-11-00 13FP SEL SW-ATT HDG 8VU 210 34-11-00 14FP RELAY-ADIRS 3 PWR SHEDDING 103VU 126 34-11-00 15FP SEL SW-AIR DATA 8VU 210 34-11-00 16FP RELAY-ADIRS 3 28VDC CONTROL 103VU 126 34-11-00 17FP RELAY-ADIRS 2 PWR SHEDDING 103VU 126 34-11-00 21FP1 RELAY-AOA1 TEST 103VU 126 34-11-00 21FP2 RELAY-AOA2 TEST 103VU 126 34-11-00 21FP3 RELAY-AOA3 TEST 103VU 126 34-11-00 22FP SW-L/G DOWN VMO/MMO SELECTION 188VU 128 34-11-00 23FP RELAY-ADIRS LGCIU GND POS 103VU 126 34-11-00 -----------------------------------------------------------------------------NOTE : The function of the switch (22FP) is described in 34-12-00. ____

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3. ____________ Power Supply A. General (Ref. Fig. 002) The ADIRU is normally supplied with 115 VAC, 400 Hz power for the ADR and IR functions. However, its AOA resolver converter module is supplied with 26 VAC, 400 Hz. The 28 VDC back-up generation is provided by batteries and is automatically used when the main power exceeds its normal limits. At the beginning of each power cycle, the ADIRU switches from the main to the back-up power to test the electrical generation. The table below gives the power consumption of each unit of the ADIRS: -----------------------------------------------------------------| EQUIPMENT | 28VDC | 115VAC | 26VAC | | |-------------------|-------------------| | | | Typical | Maximum | Typical | Maximum | | -----------------------------------------------------------------| ADIRU | 48 W | 61 W | 79 VA | 98 VA | 1 VA | |----------------|---------|---------|---------|---------|-------| | AOA Sensor | | | 250 VA | 320 VA |3.5 VA | |----------------|---------|---------|---------|---------|-------| | PITOT Probe | | | 281 VA | 360 VA | | |----------------|---------|---------|---------|---------|-------| | TAT Sensor | | | 200 VA | 350 VA | | |----------------|---------|---------|---------|---------|-------| | STATIC Probe | | 2X75 W | | | | |----------------|---------|---------|---------|---------|-------| | PHC | | 14 W | | | | -----------------------------------------------------------------(1) The ADIRU power consumption includes the supply of three ADMs. With the ON BAT annunciator, add 5 W. With the IR FAULT annunciator at I = 250 mA, add 10.5 W. Other annunciators are open/ground discretes and so they are energized by a power which is different from the ADIRU power. When the ADIRU is in the OFF mode, all the circuitry in the ADIRU is de-energized except for any logic associated with the power-off function. The current does not exceed 10 mA DC. Each ADIRU supplies power for the ADM of its side (CAPT, F/O, STBY). The ADIRU also supplies the CDU with a 28 VDC signal. The consumption of the CDU is 6 W (typical) and 10 W (maximum).

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ADIRS - Power Supply Distribution Figure 002   EFF : 524-526, 528-599,  34-11-00 Page 6   Config-2 Feb 01/10  CES

 

B. ADIRS Power Supply Distribution in Normal Configuration (1) Captain side The ADIRU 1 is supplied with 115 VAC by the 115 VAC SHED ESS BUS 801XP-A. The back-up 28 VDC is provided by the 28 VDC HOT BUS 702PP. The resolvers of the AOA sensor 1 and the AOA resolver converter module of the ADIRU 1 are supplied with 26 VAC by the 26 VAC ESS BUS 431XP-A. The sensors and probes (static, TAT, pitot, AOA) are supplied for heating through the PHC 1: - the heating element of the AOA sensor 1 receives 115 VAC from the 115 VAC SHED ESS BUS 801XP, - the heating element of the TAT sensor 1 receives 115 VAC from the 115 VAC BUS 1 101XP-A, - the heating element of the L and R static probes 1 receives 28 VDC from the 28 VDC BUS 1 101PP, - the heating element of the pitot probe 1 receives 115 VAC from the 115VAC ESS BUS 401XP. (Ref. Fig. 003) NOTE : The ADIRS/PHC Interface figure is a principle diagram and does ____ not show the interface between the PHC and the sensors. (Ref. 30-31-00 for more details on probe ice protection). (2) First Officer side The ADIRU 2 is supplied with 115 VAC by the 115 VAC BUS 2 204XP. The back-up 28 VDC is provided by the 28 VDC HOT BUS 702PP. The resolvers of the AOA sensor 2 and the AOA resolver converter module of the ADIRU 2 are supplied with 26 VAC by the 26 VAC BUS 2 231XP-A. The sensors and probes are supplied for heating through the PHC 2: - the heating element of the AOA sensor 2 receives 115 VAC from the 115 VAC BUS 2 202XP-B, - the heating element of the TAT sensor 2 receives 115 VAC from the 115 VAC BUS 2 202XP-C, - the heating element of the L and R static probes 2 receives 28 VDC from the 28 VDC BUS 2 206PP, - the heating element of the pitot probe 2 receives 115 VAC from the 115 VAC BUS 2 202XP-B. (3) Standby side The ADIRU 3 is supplied with 115 VAC by the 115 VAC BUS 1 101XP-C. The back-up 28 VDC is provided by the 28 VDC HOT BUS 701PP. The resolvers of the AOA sensor 3 and the AOA resolver converter module of the ADIRU 3 are supplied with 26 VAC by the 26 VAC BUS 1 131XP-A. The sensors and probes are supplied for heating through the PHC 3: - the heating element of the AOA sensor 3 receives 115 VAC from the 115 VAC BUS 1 103XP,

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ADIRS/PHC Interface Figure 003   EFF : 524-526, 528-599,  34-11-00 Page 8   Config-2 Feb 01/10  CES

 

- the heating element of the L and R static probes 3 receives 28 VDC from the 28 VDC BUS 1 103PP - the heating element of the pitot probe 3 receives 115 VAC from the 115 VAC BUS 1 103XP. In normal configuration of the aircraft electrical generation, the distribution described before is independent of the switching selector switches. C. ADIRS Power Supply Distribution after Loss of Main Electrical Generation (1) Loss of the main generation and ATT HDG selector switch in NORM position (a) Captain side The ADIRU 1 is supplied as in normal configuration. (Ref. Para B.(1)). (b) First Officer side The ADIRU 2 is no more supplied with 115 VAC and 26 VAC. When the 26 VAC is lost, the ADR detects a fault and flags the output parameters. The ADIRU is still powered with 28 VDC from the 28 VDC HOT BUS 702PP but the Time Delay Opening (TDO) relay 17FP will cut this supply after 5 minutes in emergency configuration. The ADR 2 function is lost immediately. The IR 2 function is lost after 5 minutes. (c) Standby side The ADIRU 3 is no more supplied with 115 VAC and 26 VAC. When the 26 VAC is lost, the ADR detects a fault and flags the output parameters. The ADIRU is still powered with 28 VDC from the 28 VDC HOT BUS 701PP but the Time Delay Opening (TDO) relay 14FP will cut this supply after 5 minutes in emergency configuration. The ADR3 function is lost immediately. The IR 3 function is lost after 5 minutes. (2) Loss of the main generation and ATT HDG selector switch in CAPT/3 position The CAPT/3 position of the ATT HDG selector switch corresponds to the selection of the IR 3 in place of the IR 1. The power supply distribution must then be modified to keep the IR 3 in emergency configuration. (a) Captain side The ADIRU 1 is supplied as in normal configuration (Ref. Para. B.(1)).

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(b) First Officer side ADIRU 2 supply: Ref. Para. (1)(b). (c) Standby side The ADIRU 3 is no more supplied with 115 VAC. The ADIRU 3 is still powered with 28 VDC from the 28 VDC HOT BUS 701PP. The ADR 3 function is lost immediately. The IR 3 function is available.

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D. Circuit Breakers The system is supplied through these circuit breakers: ----------------------------------------------------------------------------FIN PANEL/ DESIGNATION BUS ATA. REF. AMM LOCATION P. BLOCK 001 ----------------------------------------------------------------------------4FP1 49VU NAV AND PROBES/ADIRU1/115VAC 801XP-A 34-11-00 4FP2 121VU ADIRS/ADIRU/2/115VAC 204XP-C 34-11-00 4FP3 121VU ADIRS/ADIRU/3/115VAC 101XP-C 34-11-00 5FP1 49VU NAV AND PROBES/ADIRU1 & 431XP-A 34-11-00 AOA/26VAC 5FP2 121VU ADIRS/ADIRU/2/26VAC AND AOA 231XP-A 34-11-00 5FP3 121VU ADIRS/ADIRU/3/26VAC AND AOA 131XP-A 34-11-00 6FP1 105VU ADIRS/ADIRU/1/28VDC 702PP 34-11-00 6FP2 121VU ADIRS/ADIRU/2/28VDC 702PP 34-11-00 6FP3 121VU ADIRS/ADIRU/3/28VDC 701PP 34-11-00 8FP 49VU NAV AND PROBES/ADIRU 3/ 401PP 34-11-00 SWTG/SPLY 9FP 121VU ADIRS/ADIRU/3 SWTG/SPLY 301PP 34-11-00 10FP 121VU ADIRS/ADIRU/2 PWR/SHED 206PP 34-11-00 1DA1 122VU ANTI ICE/PROBES/1/TAT 101XP-A 30-31-00 1DA2 122VU ANTI ICE/PROBES/2/TAT 202XP-C 30-31-00 2DA1 49VU ANTI ICE/PROBES/PHC/1 401PP 30-31-00 2DA2 122VU ANTI ICE/PROBES/2/PHC 206PP 30-31-00 2DA3 122VU ANTI ICE/PROBES/PHC/3 101PP 30-31-00 3DA1 49VU ANTI ICE/PROBES/PITOT/1 401XP-B 30-31-00 3DA2 122VU ANTI ICE/PROBES/2/PITOT 202XP-B 30-31-00 3DA3 122VU ANTI ICE/PROBES/3/PITOT 103XP-C 30-31-00 4DA1 49VU ANTI ICE/PROBES/1/AOA 801XP-C 30-31-00 4DA2 122VU ANTI ICE/PROBES/2/AOA 202XP-B 30-31-00 4DA3 122VU ANTI ICE/PROBES/3/AOA 103XP-C 30-31-00 5DA1 122VU ANTI ICE/PROBES/1/STATIC 101PP 30-31-00 5DA2 122VU ANTI ICE/PROBES/2/STATIC 206PP 30-31-00 5DA3 122VU ANTI ICE/PROBES/3/STATIC 103PP 34-11-00

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4. _____________________ Component Description A. Static Probes (Ref. Fig. 004) Each of the three systems (CAPT (1), F/O (2), STBY (3)) comprises two static probes which are linked to each ADR portion of the ADIRUs through five ADMs. The probe is protected from icing with a 28 VDC heater circuit. The static probes linked to the ADIRU 1 and ADIRU 2 are set at 48.64 deg. below the fuselage datum line (Z=0). The static probes linked to ADIRU 3 are set at 29.5 deg. below the fuselage datum line. The pitot probe comprises a three-pin connector defined as follows: B. Pitot Probes (Ref. Fig. 005) Each system comprises one pitot probe (CAPT (1), F/O (2), STBY (3)) which is linked to each ADR portion of the ADIRUs through one ADM. The probe is protected from icing with a 115 VAC - 400 Hz heater circuit. The pitot probes 1 and 2 are set at 40.08 deg. below the fuselage datum line (Z=0). The pitot probe 3 is set at 59.56 deg. below the fuselage datum line (Z=0). C. Air Data Modules (ADM) (Ref. Fig. 006) The term Air Data Module (ADM) refers to any remotely-located LRU which senses pressure information and transmits it to the ADIRU in ARINC 429 format. The ADMs are remotely mounted near and above the level of the pitot and static probes, this in order to make the ADM pneumatic plumbing self draining when the aircraft is stationary on the ground. (1) Internal description The ADM comprises the following components: (Ref. Fig. 007) (a) Transducer board This device provides two signals (Pressure Time Pulse (PTP) and Temperature Time Pulse (TTP)) used by the processor board. (b) Processor board The microcomputer comprises the following circuits: - a micro-controller 80C31, - two memories: ROM (storage of software program) and RAM (temporary storage of data),

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Air Data Module Figure 006   EFF : 524-526, 528-599,  34-11-00 Page 15   Config-2 Feb 01/10  CES

 

ADM - Block Diagram Figure 007   EFF : 524-526, 528-599,  34-11-00 Page 16   Config-2 Feb 01/10  CES

 

- a Non Volatile Memory (NVM) (Storage of transducer modeling coefficients and failure information), - a RS-232C Serial Digital Input/Output (used for bench test and calibration purposes), - an ARINC 429 transmitter. The processor board uses the PTP and TTP signals sent by the transducer board and the transducer modeling coefficients stored in the NVM to compute the pressure. (c) EMI/lightning board This board comprises the following devices: - power supply: the ADM is supplied by the associated ADIRU with +/- 13.5 VAC. The power consumption is less than 200 mA on the +13.5 VDC input and less than 50 mA on the -13.5 VDC input. - EMI filters - lightning protection - filtering of input discretes. (2) Modes of operation The ADM has three modes of operation: - initialization - normal operation - Memory Access/Calibration (MA/C). (a) Initialization mode The ADM automatically enters the initialization mode immediately after power is applied to the device or after a Watchdog Timer is activated due to an ADM failure. The ADM performs several tasks while in the initialization mode: - initializes software variables and hardware interfaces, - performs various self-monitoring tests to determine if the ADM operates properly, - reads the fixed Program Pin discretes. The ARINC 429 bus is disabled during the initialization mode. The ADM does not output any data on the ARINC 429 bus. The initialization mode is completed within 900 ms (maximum) after valid power is applied to the ADM. Upon completion of the initialization mode, the ADM automatically enters the normal operation mode. (b) Normal operation mode The ADM enters the normal operation mode after the completion of the initialization mode. It remains in the normal operation mode until either power is removed from the ADM, or an internal failure activates the Watchdog Timer, or an internal BITE detects an unsafe condition, at which time a failure warning is annunciated or ARINC 429 transmissions cease.

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The ADM performs the following functions in the normal operation mode: - measures the pressure and temperature outputs from the transducer, - uses filtering or averaging techniques consistent with the noise, resolution, and dynamic frequency response requirements - computes the Applied Pressure based upon the pressure and temperature signals, - filters the Computed Pressure, - formats the ARINC 429 word to be transmitted, - transmits the ARINC 429 Computed Pressure word, - formats and transmits two ADM discrete words (labels 270, 271), - reads and debounces the MA/C discretes, - performs the BITE functions, - formats and transmits ADM software and equipment I.D. words (labels 040,377). (c) Memory access/calibration mode The Memory access/calibration (MA/C) mode is used for purposes of transducer calibration and fault analysis. The MA/C mode requires external test equipment which interfaces to the ADM via a RS-232C bus. This mode can be considered as an auxiliary mode which is accessible in a repair shop environment only.

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(3) Discrete inputs Table 1 gives the identification of the ADM discrete inputs: -------------------------------------------| ADM Pin | Identification | -------------------------------------------| K | SDI 1 (LSB) (2) | | L | SDI 2 (MSB) (2) | | M | Configuration code 1 (3) | | N | Configuration code 2 (3) | | P | Parity (1) | | a | Memory Access/Calibration 1 | | b | NVM reset discrete | | c | Memory Access/Calibration 2 | -------------------------------------------Table 1 = Discrete Inputs NOTE : (1) An odd number of pins K, L, M, N and P must be grounded to ____ signify a valid installation. After the desired Source Data Identifier (SDI) and the configuration pins have been selected, the parity pin P must be selectively left open or grounded to ensure that an odd number of pins K through P inclusive have been grounded. NOTE : (2) Program pins used for identification of the installation ____ position on the aircraft and the corresponding SDI code to be transmitted. The code definition is provided in table 2. NOTE : (3) The ADM transmits the measured pressure with a label ____ depending on the configuration code input discretes. The configuration code definition is provided in table 3. -----------------------------------------------------------------------|Input discrete SDI output |Input discrete SDI output |Installation| | pin L Bit 10 state| pin K Bit 09 state| | |----------------------------------------------------------------------| | open 0 | open 0 | Invalid | | open 0 | ground 1 | 1 | | ground 1 | open 0 | 2 | | ground 1 | ground 1 | 3 | -----------------------------------------------------------------------Table 2 = SDI Code

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--------------------------------------------------------------------| Installation function | Config. code 2 | Config. code 1 | Label | | | Pin N | Pin M | | |-------------------------------------------------------------------| | Total pressure | open | open | 242 | | Left static pressure | open | ground | 176 | | Right static pressure | ground | open | 177 | | Averaged static | ground | ground | 245 | | pressure (uncorrected)| | | | --------------------------------------------------------------------Table 3 = Configuration Code (4) Output bus All data are transmitted via a single ARINC 429 low-speed serial digital output bus. The outputs from the ADM are a single pressure word having an installation selectable label, two discrete data words and two identification words. The following table gives: - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds - CODE : BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code parameters are given in the table 4 below: - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. All these parameters are given in the table 4 below:

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 242 |TOTAL |100-1400 |hPa | | 18 |29- |BNR | | | | |PRESSURE |+/- 0.25 | | | |31 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 176 |LEFT STAT |100-1100 |hPa | | 18 |29- |BNR | | | | |PRESSURE |+/- 0.25 | | | |31 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 177 |RIGHT STAT|100-1100 |hPa | | 18 |29- |BNR | | | | |PRESSURE |+/- 0.25 | | | |31 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 245 |AVERAGED |100-1100 |hPa | | 18 |29- |BNR | | | | |STATIC |+/- 0.25 | | | |31 | | | | | |PRESSURE | | | | | | | | | | |(UNCORRTD)| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DISCRETE |Table 5 | | | |460-|BCD | | | | |WORD 1 | | | | |500 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 271 |DISCRETE |Table 6 | | | |460-|BCD | | | | |WORD 2 | | | | |500 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQUIPMENT |Table 7 | | | |460-|BCD | | | | |IDENT | | | | |500 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 040 |SOFTWARE |Table 8 | | | |460-|BCD | | | | |IDENT | | | | |500 | | | | ------------------------------------------------------------------------------Table 4 = Digital Outputs NOTE : - the survival range of the ADM is 0 - 1900 hPa ____ - accuracy = three sigma tolerance at time of delivery over -15 deg. C to +85 deg. C range at thermal steady state. (It does not include long-term drift).

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--------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 270 | | 9-10 |SDI | | 11-12 |Logic 0 | | 13-16 |LSD device revision number (currently 4H) | | 17-20 |MSD device revision number (currently 0H) | | 21-24 |LS device revision letter (currently CH) | | 25-28 |MS device revision letter (currently AH) | | 29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete | | |maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 5 = Discrete Word 1 (Label 270) --------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 271 | | 9-10 |SDI | | 11-13 |Logic 0 | | 14 |ADM LRU Status | | 15 |Pin configuration status | | 16 |Environment status | | 17-24 |Current fault byte matrix | | 25-28 |Word counter | | 29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete | | |maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 6 = Discrete Word 2 (Label 271)

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--------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 377 | | 9-10 |SDI | | 11-14 |LSD equipment identification (8H) | | 15-18 |MSD equipment identification (3H) | | 19-29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete | | |maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 7 = Equipment Ident (Label 377) --------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 040 | | 9-10 |SDI | | 11-12 |Logic 0 | | 13-16 |LSD software revision number | | 17-20 |MSD software revision number | | 21-24 |LSD manufacturer ident number (1H) | | 25-28 |MSD manufacturer ident number (0H) | | 29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete | | |maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 8 = Software Ident. (Label 040) D. Total Air Temperature (TAT) Sensor (Ref. Fig. 008) The aircraft is equipped with two TAT sensors with two sensing elements each. The sensing elements of the sensor have variable resistances. The TAT sensor 1 is linked to the ADR portion of the ADIRUs 1 and 3, the TAT sensor 2 is linked to the ADR portion of the ADIRU 2. The TAT sensors are set at 2.33 m from the nose and at 0.60 m of the aircraft axis below the fuselage. The TAT sensor 1 is located on the left side and the TAT sensor 2 on the right side.

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ADIRS - TAT Sensor Figure 008   EFF : 524-526, 528-599,  34-11-00 Page 24   Config-2 Feb 01/10  CES

 

The air flow enters the scoop of the sensor, goes through a calibrated choke and flows over the hermetically-sealed platinum resistance sensing element where the temperature is measured. The speed of the flow over the element is controlled by the choke in the element tube. The ADR portion is designed to operate with 500 ohms (at 0 deg. C) temperature sensor unit corresponding to the basic Callender - Van Dusen equation. To improve the accuracy of the sensor, a network of precision resistors is used. This technique is identified by the term Precision Calibration Interchangeability (PCI). These sensors are heated with 115 VAC through the probe heating system. The heating element must not be energized on the ground. The heating element is implanted in the scoop and strut and keeps the probe free of ice under the most severe icing conditions. NOTE : Probe ice protection is described in 30-31-00. ____

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E. Angle Of Attack (AOA) Sensor (Ref. Fig. 009) The aircraft is equipped with three AOA sensors. Two are located on the left side and one on the right side of the fuselage. Each of these AOA sensors is respectively linked to each ADR portion of the ADIRUs. The AOA sensors 1 and 3 are set at 6.08 deg. and 31 deg. below the fuselage datum line (Z = 0) on the left side. The AOA sensor 2 is set at 6.08 deg. below the fuselage datum line (Z = 0) on the right side. The angle of attack sensor is of the wind vane type. Its sensing element is a small wing which is positioned in the direction of the airflow. The small wing is mechanically linked to a free-turn shaft which drives the devices transmitting the local angle of attack signal. These transmitting devices are made up of resolver transformers which convert the angular information into proportional electrical information (angle sine and cosine). The resolvers are supplied with a 26 VAC signal. The same signal is also received by the ADIRU as a reference for the decoding of AOA values. Each sensor has three resolver outputs but only two are wired to the ADIRU. The whole mechanism is stabilized around the rotation axis. In addition, a damping device enables a satisfactory dynamic response to be obtained (filtering of mechanical oscillation). A self-regulated heating element (PTC resistors: positive coefficient of temperature) inserted into the vane eliminates or avoids icing. It is supplied with 115 VAC through the PHC (Ref. 30-31-00). The AOA sensor is equipped with a self-test device which is activated by a 28 VDC signal, from the ADR (through the relay 21FP1, 21FP2 or 21FP3) when the test is entered via the maintenance system (CFDIU and MCDU). The self-test positions the vane at a resolver angle of +15 deg. (left side test) or -15 deg. (right side test). The mounting and wing of AOA resolvers determine the relationship between the measured resolver angle and the indicated angle of attack. This relationship for each resolver input is as follows: (Ref. Fig. 010) -----------------------------------------------------------------------| | Indicated AOA: | +85 | +60 | +25 | 0 | -35 | | AOA 1 and AOA 3 |----------------------------------------------------| | in degrees | Resolver angle: | -60 | -35 | 0 | +25 | +60 | -----------------------------------------------------------------------| | Indicated AOA: | +85 | +60 | +25 | 0 | -35 | | AOA 2 |----------------------------------------------------| | in degrees | Resolver angle: | +60 | +35 | 0 | -25 | -60 | -----------------------------------------------------------------------The ADRs receive the same 26 VAC, 400 Hz reference as the AOA resolvers. This reference is common to both AOA resolver inputs 1 and 2. Characteristics:

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ADIRS - AOA Sensor Figure 009   EFF : 524-526, 528-599,  34-11-00 Page 27   Config-2 Feb 01/10  CES

 

AOA Sensor - Installation Definition Figure 010   EFF : 524-526, 528-599,  34-11-00 Page 28   Config-2 Feb 01/10  CES

 

Excitation : Phase shift : Resolver transformer ratio RT : Rotor impedance : Stator impedance : Range : Scale factor : The accuracy of the AOA sensor,

26 V 400 Hz 18 deg. to 30 deg. 0.4029 to 0.4629 Zro = 125 + j175 ohms +/-20% Zso = 115 + j90 ohms +/-30% +/-60 deg. 1 deg. resolver/1 deg. local AOA at 100 knots, is +/-0.3 deg.

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F. Selector Switches (Ref. Fig. 011) The two selector switches AIR DATA and ATT HDG are rotary selector switches with three positions: CAPT/3, NORM and F/O/3. These selector switches are used for the functions listed below (Ref. the respective section for more details): - AIR DATA SEL SW (15FP): 34-14-00 Selection of the ADR used by the IR3 34-52-00 ATC mode S 31-68-00 DMC 22-85-00 FMGC - ATT HDG SEL SW (13FP): 34-11-00 Power Supply 34-14-00 Selection of the ADR used by the IR3 34-41-00 Weather Radar 31-68-00 DMC 22-85-00 FMGC.

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ADIRS Switching Figure 011   EFF : 524-526, 528-599,  34-11-00 Page 31   Config-2 Feb 01/10  CES

 

SENSORS, POWER SUPPLY AND SWITCHING - DESCRIPTION AND OPERATION _______________________________________________________________ 1. _______ General The aircraft is equipped with three Air Data/Inertial Reference Units (ADIRUs). Each ADIRU receives data from the four types of sensors after: - three pitot probes which provide total pressure data, - six static probes which provide static pressure data, - two Total Air Temperature (TAT) sensors which provide air temperature data, - three Angle Of Attack (AOA) sensors which provide angle of attack data of the aircraft. The TAT sensors and the angle of attack sensors are directly connected to the ADIRUs. The pitot probes and the static probes are connected to eight Air Data Modules (ADM) which convert pressure data before they send them to the ADIRUs. The sensors, the probes, the ADMs and the ADIRUs are power supplied as follows: ------------------------------------------| EQUIPMENT | 28VDC | 115VAC | 26VAC | ------------------------------------------| ADIRU | X | X | X | |----------------|-------|--------|-------| | AOA Sensor | | X | X | |----------------|-------|--------|-------| | PITOT Probe | | X | | |----------------|-------|--------|-------| | TAT Sensor | | X | | |----------------|-------|--------|-------| | STATIC Probe | X | | | |----------------|-------|--------|-------| | ADM |13.5VAC from ADIRU | ------------------------------------------In normal configuration, the Captain Primary Flight Display (PFD) and Navigation Display (ND) show the data computed by the ADIRU 1. The First Officer PFD and ND show the data computed by the ADIRU 2. The data from the ADIRU 3 can be displayed by action on the AIR DATA selector switch or on the ATT HDG selector switch located on the SWITCHING panel. These selector switches which define a priority order for the ADIRUs are also used by several other aircraft systems (Ref. Para. 4.F.).

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2. Component __________________ Location (Ref. Fig. 001) The sensors, probes and ADMs are located on the aircraft as follows: ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------R R R R

3FP1 3FP2

SENSOR-ANGLE OF ATTACK, 1 SENSOR-ANGLE OF ATTACK, 2

231 232

3FP3 11FP1 11FP2 19FP1 19FP2 19FP3 19FP4 19FP5 19FP6 19FP7 19FP8 7DA1 7DA2 7DA3 8DA1 8DA2 8DA3 9DA1 9DA2 9DA3

SENSOR-ANGLE OF ATTACK, 3 SENSOR-TAT, 1 SENSOR-TAT, 2 ADM-L TOTAL PRESSURE ADM-R TOTAL PRESSURE ADM-STBY TOTAL PRESSURE ADM-R STATIC PRESSURE ADM-L STATIC PRESSURE ADM-R STATIC PRESSURE ADM-L STATIC PRESSURE ADM-STBY STATIC PRESSURE PROBE-L STATIC, 1 PROBE-L STATIC, 2 PROBE-L STATIC, 3 PROBE-R STATIC, 1 PROBE-R STATIC, 2 PROBE-R STATIC, 3 PROBE-PITOT, 1 PROBE-PITOT, 2 PROBE-PITOT, 3

127 121 122 NONE 125 126 125 128 127 128 127 121 127 127 121 128 128 122 125 126 125

34-11-19 34-11-19 824 812 822 812 824 824 824 824 811 824 824 811 824 824 811 812 822 812

34-11-19 34-11-18 34-11-18 34-11-17 34-11-17 34-11-17 34-11-17 34-11-17 34-11-17 34-11-17 34-11-17 34-11-16 34-11-16 34-11-16 34-11-16 34-11-16 34-11-16 34-11-15 34-11-15 34-11-15

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The different ADIRS switching devices are located on the aircraft as follows: ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------12FP RELAY-ADIRS ON BAT/GROUND WARN 103VU 126 34-11-00 13FP SEL SW-ATT HDG 8VU 210 34-11-00 14FP RELAY-ADIRS 3 PWR SHEDDING 103VU 126 34-11-00 15FP SEL SW-AIR DATA 8VU 210 34-11-00 16FP RELAY-ADIRS 3 28VDC CONTROL 103VU 126 34-11-00 17FP RELAY-ADIRS 2 PWR SHEDDING 103VU 126 34-11-00 21FP1 RELAY-AOA1 TEST 103VU 126 34-11-00 21FP2 RELAY-AOA2 TEST 103VU 126 34-11-00 21FP3 RELAY-AOA3 TEST 103VU 126 34-11-00 22FP SW-L/G DOWN VMO/MMO SELECTION 188VU 128 34-11-00 23FP RELAY-ADIRS LGCIU GND POS 103VU 126 34-11-00 -----------------------------------------------------------------------------NOTE : The function of the switch (22FP) is described in 34-12-00. ____

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3. ____________ Power Supply A. General (Ref. Fig. 002) The ADIRU is normally supplied with 115VAC, 400 Hz power for the ADR and IR functions. However its AOA resolver converter module is supplied with 26VAC, 400 Hz. The 28VDC back-up generation is provided by batteries and is automatically used when the main power exceeds its normal limits. At the beginning of each power cycle the ADIRU switches from the main to the back-up power to test the electrical generation. **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, The table below gives the power consumption of each unit of the ADIRS: -----------------------------------------------------------------| EQUIPMENT | 28VDC | 115VAC | 26VAC | | |-------------------|-------------------| | | | Typical | Maximum | Typical | Maximum | | -----------------------------------------------------------------| ADIRU (1) | 67 W | 84 W | 79 VA | 98 VA | 1 VA | |----------------|---------|---------|---------|---------|-------| | AOA Sensor | | | 250 VA | 320 VA |3.5 VA | |----------------|---------|---------|---------|---------|-------| | PITOT Probe | | | 281 VA | 360 VA | | |----------------|---------|---------|---------|---------|-------| | TAT Sensor | | | 200 VA | 350 VA | | |----------------|---------|---------|---------|---------|-------| | STATIC Probe | | 2X75 W | | | | |----------------|---------|---------|---------|---------|-------| | PHC | | 14 W | | | | -----------------------------------------------------------------(1) ADIRU power consumption includes the supply of three ADMs. With ON BAT annunciator, add 5 W. With IR FAULT annunciator at I = 250 mA, add 10.5 W. Other annunciators are open/ground discretes and so they are energized by a power which is different from the ADIRU power. When the ADIRU is in the OFF mode, all the circuitry in the ADIRU is de-energized except for any logic associated with the power off function. Current does not exceed 10 mA DC. Each ADIRU supplies the power for the ADM of its side (CAPT, F/O, STBY). The ADIRU also supplies the CDU with a 28VDC signal. The consumption of the CDU is 6 W (typical) and 10 W (maximum).

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ADIRS - Power Supply Distribution Figure 002   R EFF : 051-099, 106-149, 204-249, 251-299,  34-11-00 Page 6 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, The table below gives the power consumption of each unit of the ADIRS: -----------------------------------------------------------------| EQUIPMENT | 28 VDC | 115 VAC |26 VAC | | |-------------------|-------------------|-------| | Typical | Maximum | Typical | Maximum | | -----------------------------------------------------------------| ADIRU (1) | 67 W | 84 W | 79 VA | 98 VA | 1 VA | |----------------|---------|---------|---------|---------|-------| | AOA Sensor | | | 250 VA | 320 VA |3.5 VA | |----------------|---------|---------|---------|---------|-------| | PITOT Probe | | | 281 VA | 360 VA | | |----------------|---------|---------|---------|---------|-------| | TAT Sensor | | | 200 VA | 350 VA | | |----------------|---------|---------|---------|---------|-------| | STATIC Probe | | 2X75 W | | | | |----------------|---------|---------|---------|---------|-------| | PHC | | 14 W | | | | -----------------------------------------------------------------(1) The ADIRU power consumption includes the supply of three ADMs. With the ON BAT annunciator, add 5 W. With the IR FAULT annunciator at I = 250 mA, add 10.5 W. Other annunciators are open/ground discretes and so they are energized by a power which is different from the ADIRU power. When the ADIRU is in the OFF mode, all the circuitry in the ADIRU is de-energized except for any logic associated with the power-off function. The current does not exceed 10 mA DC. Each ADIRU supplies the power for the ADM of its side (CAPT, F/O, STBY).

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, B. ADIRS Power Supply Distribution in Normal Configuration (1) Captain side The ADIRU 1 is supplied with 115VAC by the 115VAC SHED ESS BUS 801XP-A. The back-up 28VDC is provided by the 28VDC HOT BUS 701PP. The resolvers of the AOA sensor 1 and the AOA resolver converter module of the ADIRU 1 are supplied with 26VAC by the 26VAC ESS BUS 431XP-A.

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The sensors and probes (static, TAT, pitot, AOA) are supplied for heating through the Probe Heat Computer 1: - the heating element of the AOA sensor 1 receives 115VAC from the 115VAC SHED ESS BUS 801XP - the heating element of the TAT sensor 1 receives 115VAC from the 115VAC BUS 1 101XP-A - the heating element of the L and R static probes 1 receives 28VDC from the 28VDC BUS 1 101PP - the heating element of the pitot probe 1 receives 115VAC from the 115VAC ESS BUS 401XP. (Ref. Fig. 003) NOTE : Figure ADIRS/PHC Interface, is a principle diagram which does ____ not show the interface between the PHC and the sensors. (Ref. 30-31-00 for more details on probe ice protection). (2) First Officer side The ADIRU 2 is supplied with 115VAC by the 115VAC BUS 2 204XP. The back-up 28VDC is provided by the 28VDC HOT BUS 702PP. The resolvers of the AOA sensor 2 and the AOA resolver converter module of the ADIRU 2 are supplied with 26VAC by the 26VAC BUS 2 231XP-A. The sensors and probes are supplied for heating through the PHC 2: - the heating element of the AOA sensor 2 receives 115VAC from the 115VAC BUS 2 202XP-B - the heating element of the TAT sensor 2 receives 115VAC from the 115VAC BUS 2 202XP-C - the heating element of the L and R static probes 2 receives 28VDC from the 28VDC BUS 2 206PP - the heating element of the pitot probe 2 receives 115VAC from the 115VAC BUS 2 202XP-B. (3) Standby side The ADIRU 3 is supplied with 115VAC by the 115VAC BUS 1 101XP-C. The back-up 28VDC is provided by the 28VDC HOT BUS 701PP. The resolvers of the AOA sensor 3 and the AOA resolver converter module of the ADIRU 3 are supplied with 26VAC by the 26VAC BUS 1 131XP-A. The sensors and probes are supplied for heating through the PHC 3: - the heating element of the AOA sensor 3 receives 115VAC from the 115VAC BUS 1 103XP - the heating element of the L and R static probes 3 receives 28VDC from the 28VDC BUS 1 103PP - the heating element of the pitot probe 3 receives 115VAC from the 115VAC BUS 1 103XP. In normal configuration of the aircraft electrical generation, the distribution described before is independent of the switching selector switches.

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ADIRS/PHC Interface Figure 003   R EFF : 051-099, 106-149, 204-249, 251-299,  34-11-00 Page 9 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

C. ADIRS Power Supply Distribution after Loss of Main Electrical Generation (1) Loss of the main generation and ATT HDG selector switch in NORM position (a) Captain side The ADIRU 1 is supplied as in normal configuration. (Ref.Para B.(1)). (b) First Officer side The ADIRU 2 is no more supplied with 115VAC and 26VAC. When the 26VAC is lost, the ADR detects a fault and flags the output parameters. The ADIRU is still powered with 28VDC from the 28VDC HOT BUS 702PP but the Time Delay Opening (TDO) relay 17FP will cut this supply after 5 minutes in emergency configuration. The ADR 2 function is lost immediately. The IR 2 function is lost after 5 minutes. (c) Standby side The ADIRU 3 is no more supplied with 115VAC and 26VAC. When the 26VAC is lost, the ADR detects a fault and flags the output parameters. The ADIRU is still powered with 28VDC from the 28VDC HOT BUS 701PP but the Time Delay Opening (TDO) relay 14FP will cut this supply after 5 minutes in emergency configuration. The ADR3 function is lost immediately. The IR 3 function is lost after 5 minutes. (2) Loss of the main generation and ATT HDG selector switch in CAPT/3 position The CAPT/3 position of the ATT HDG selector switch corresponds to the selection of the IR 3 in place of the IR 1. The power supply distribution must then be modified to keep the IR 3 in emergency configuration. (a) Captain side The ADIRU 1 is supplied as in normal configuration (Ref. Para. B.(1)). (b) First Officer side ADIRU 2 supply: Ref. Para. (1)(b). (c) Standby side The ADIRU 3 is no more supplied with 115VAC. The ADIRU 3 is still powered with 28VDC from the 28VDC HOT BUS 701PP. The ADR 3 function is lost immediately. The IR 3 function is available.

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D. Circuit Breakers The system is supplied through these circuit breakers: ----------------------------------------------------------------------------FIN PANEL/ DESIGNATION BUS ATA. REF. AMM LOCATION P. BLOCK 001 ----------------------------------------------------------------------------4FP1 49VU NAV AND PROBES/ADIRU1/115VAC 801XP-A 34-11-00 4FP2 121VU ADIRS/ADIRU/2/115VAC 204XP-C 34-11-00 4FP3 121VU ADIRS/ADIRU/3/115VAC 101XP-C 34-11-00 5FP1 49VU NAV AND PROBES/ADIRU1 & 431XP-A 34-11-00 AOA/26VAC 5FP2 121VU ADIRS/ADIRU/2/26VAC AND AOA 231XP-A 34-11-00 5FP3 121VU ADIRS/ADIRU/3/26VAC AND AOA 131XP-A 34-11-00 6FP1 105VU ADIRS/ADIRU1/28VDC 704PP 34-11-00 6FP2 121VU ADIRS/ADIRU/2/28VDC 702PP 34-11-00 6FP3 121VU ADIRS/ADIRU/3/28VDC 701PP 34-11-00 8FP 49VU NAV AND PROBES/ADIRU 3/ 401PP 34-11-00 SWTG/SPLY 9FP 121VU ADIRS/ADIRU/3 SWTG/SPLY 301PP 34-11-00 10FP 121VU ADIRS/ADIRU/2 PWR/SHED 206PP 34-11-00 1DA1 122VU ANTI ICE/PROBES/1/TAT 101XP-A 30-31-00 1DA2 122VU ANTI ICE/PROBES/2/TAT 202XP-C 30-31-00 2DA1 49VU ANTI ICE/PROBES/PHC/1 401PP 30-31-00 2DA2 122VU ANTI ICE/PROBES/2/PHC 206PP 30-31-00 2DA3 122VU ANTI ICE/PROBES/PHC/3 101PP 30-31-00 3DA1 49VU ANTI ICE/PROBES/PITOT/1 401XP-B 30-31-00 3DA2 122VU ANTI ICE/PROBES/2/PITOT 202XP-B 30-31-00 3DA3 122VU ANTI ICE/PROBES/3/PITOT 103XP-C 30-31-00 4DA1 49VU ANTI ICE/PROBES/1/AOA 801XP-C 30-31-00 4DA2 122VU ANTI ICE/PROBES/2/AOA 202XP-B 30-31-00 4DA3 122VU ANTI ICE/PROBES/3/AOA 103XP-C 30-31-00 5DA1 122VU ANTI ICE/PROBES/1/STATIC 101PP 30-31-00 5DA2 122VU ANTI ICE/PROBES/2/STATIC 206PP 30-31-00 5DA3 122VU ANTI ICE/PROBES/3/STATIC 103PP 34-11-00

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4. _____________________ Component Description A. Static Probes (Ref. Fig. 004) Each of the three systems (CAPT (1), F/O (2), STBY (3)) comprises two static probes which are linked to each ADR portion of the ADIRUs through five ADMs. The probe is protected from icing with a 28VDC heater circuit. The static probes linked to ADIRU 1 and ADIRU 2 are set at 48.64 deg. below the fuselage datum line (Z=0). The static probes linked to ADIRU 3 are set at 29.5 deg. below the fuselage datum line. B. Pitot Probes (Ref. Fig. 005) Each system comprises one pitot probe (CAPT (1), F/O (2), STBY (3)) which is linked to each ADR portion of the ADIRUs through one ADM. The probe is protected from icing with a 115VAC - 400 Hz heater circuit. The pitot probes 1 and 2 are set at 40.08 deg. below the fuselage datum line (Z=0). The pitot probe 3 is set at 59.56 deg. below the fuselage datum line (Z=0).

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ADIRS - Static Probe Figure 004   R EFF : 051-099, 106-149, 204-249, 251-299,  34-11-00 Page 13 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS - Pitot Probe Figure 005   R EFF : 051-099, 106-149, 204-249, 251-299,  34-11-00 Page 14 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

C. Air Data Modules (ADM) **ON A/C 051-061, (Ref. Fig. 006) R R

**ON A/C 062-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (Ref. Fig. 006A)

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, The term Air Data Module (ADM) refers to any remotely located LRU which senses pressure information and transmits it to the ADIRU in ARINC 429 format. The ADMs are remotely mounted near and above the level of the pitot and static probes, this in order to make the ADM pneumatic plumbing self draining when the aircraft is stationary on the ground. (1) Internal description The ADM comprises the following components (Ref. Fig. 007) (a) Transducer board This device provides two signals (Pressure Time Pulse (PTP) and Temperature Time Pulse (TTP)) used by the processor board. (b) Processor board The microcomputer comprises the following circuits: - a micro-controller 80C31 - two memories: ROM (storage of software program) and RAM (temporary storage of data) - a Non Volatile Memory (NVM) (Storage of transducer modelling coefficients and failure information) - a RS-232C Serial Digital Input/Output (used for bench test and calibration purposes) - an ARINC 429 transmitter. The processor board uses the PTP and TTP signals sent by the transducer board and the transducer modelling coefficients stored in the NVM to compute the pressure.

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Air Data Module Figure 006   R EFF : 051-061,  34-11-00 Page 16   Config-3 Nov 01/06  CES

 

Air Data Module Figure 006A   R EFF : 062-099, 106-149, 204-249, 251-299,  34-11-00 Page 17 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADM - Block Diagram Figure 007   R EFF : 051-099, 106-149, 204-249, 251-299,  34-11-00 Page 18 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

(c) EMI/lightning board This board comprises the following devices: - power supply: the ADM is supplied by the associated ADIRU with +/- 13.5VAC. Power consumption is less than 200 mA on the +13.5VDC input and less than 50 mA on the -13.5VDC input. - EMI filters - lightning protection - input discretes filtering. (2) Modes of operation The ADM has three modes of operation: - initialization - normal operation - Memory Access/Calibration (MA/C). (a) Initialization mode The ADM automatically enters the initialization mode immediately after power is applied to the device or after a Watchdog Timer is activated due to an ADM failure. The ADM performs several tasks while in the initialization mode. It: - initializes software variables and hardware interfaces - performs various self-monitoring tests to determine if the ADM operates properly - reads the fixed Program Pin discretes. The ARINC 429 bus is disabled during the initialization mode. The ADM does not output any data on the ARINC 429 bus. The initialization mode is completed within 900 ms (maximum) after valid power is applied to the ADM. Upon completion of the initialization mode, the ADM automatically enters the normal operation mode. (b) Normal operation mode The ADM enters the normal operation mode after the completion of the initialization mode. It remains in the normal operation mode until either power is removed from the ADM, or an internal failure activates the Watchdog Timer, or an internal BITE detects an unsafe condition at which time a failure warning is annunciated or ARINC 429 transmissions cease. The ADM performs the following functions in the normal operation mode. It: - measures the pressure and temperature outputs from the transducer - uses filtering or averaging techniques consistent with the noise, resolution, and dynamic frequency response requirements

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- computes the Applied Pressure based upon the pressure and temperature signals - filters the Computed Pressure - formats the ARINC 429 word to be transmitted - transmits the ARINC 429 Computed Pressure word - formats and transmits two ADM discrete words (labels 270, 271) - reads and debounces the MA/C discretes - performs the BITE functions - formats and transmits ADM software and equipment I.D. words (labels 040,377). (c) Memory Access/Calibration mode The Memory Access/Calibration (MA/C) mode is used for purposes of transducer calibration and fault analysis. The MA/C mode requires external test equipment which interfaces to the ADM via a RS-232C bus. This mode can be considered as an auxiliary mode which is accessible in a repair shop environment only.

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(3) Discrete inputs Table 1 gives the identification of the ADM discrete inputs: -------------------------------------------| ADM Pin | Identification | -------------------------------------------| K | SDI 1 (LSB) (2) | | L | SDI 2 (MSB) (2) | | M | Configuration code 1 (3) | | N | Configuration code 2 (3) | | P | Parity (1) | | a | Memory Access/Calibration 1 | | b | NVM reset discrete | | c | Memory Access/Calibration 2 | -------------------------------------------Table 1 = Discrete Inputs NOTE : (1) An odd number of pins K, L, M, N and P must be grounded to ____ signify a valid installation. After the desired Source Data Identifier (SDI) and the configuration pins have been selected, the parity pin P must be selectively left open or grounded to ensure that an odd number of pins K through P inclusive have been grounded. NOTE : (2) Program pins used for identification of the installation ____ position on the aircraft and the corresponding SDI code to be transmitted. The code definition is provided in table 2. NOTE : (3) The ADM transmits the measured pressure with a label ____ depending on the configuration code input discretes. The configuration code definition is provided in table 3. -----------------------------------------------------------------------|Input discrete SDI output |Input discrete SDI output |Installation| | pin L Bit 10 state| pin K Bit 09 state| | |----------------------------------------------------------------------| | open 0 | open 0 | Invalid | | open 0 | ground 1 | 1 | | ground 1 | open 0 | 2 | | ground 1 | ground 1 | 3 | -----------------------------------------------------------------------Table 2 = SDI Code

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--------------------------------------------------------------------| Installation function | Config. code 1 | Config. code 2 | Label | | | Pin N | Pin M | | |-------------------------------------------------------------------| | Total pressure | open | open | 242 | | Left static pressure | open | ground | 176 | | Right static pressure | ground | open | 177 | | Averaged static | ground | ground | 245 | | pressure (uncorrected)| | | | --------------------------------------------------------------------Table 3 = Configuration Code (4) Output bus All data are transmitted via a single ARINC 429 low-speed serial digital output bus. The outputs from the ADM are a single pressure word having an installation selectable label, two discrete data words, and two identification words. The following table gives: - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds - CODE : BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code parameters are given in the table 4 below: - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. All these parameters are given in the table 4 below:

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 242 |TOTAL |100-1400 |hPa | | 18 |29- |BNR | | | | |PRESSURE |+/- 0.25 | | | |31 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 176 |LEFT STAT |100-1100 |hPa | | 18 |29- |BNR | | | | |PRESSURE |+/- 0.25 | | | |31 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 177 |RIGHT STAT|100-1100 |hPa | | 18 |29- |BNR | | | | |PRESSURE |+/- 0.25 | | | |31 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 245 |AVERAGED |100-1100 |hPa | | 18 |29- |BNR | | | | |STATIC |+/- 0.25 | | | |31 | | | | | |PRESSURE | | | | | | | | | | |(UNCORRTD)| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DISCRETE |Table 5 | | | |460-|BCD | | | | |WORD 1 | | | | |500 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 271 |DISCRETE |Table 6 | | | |460-|BCD | | | | |WORD 2 | | | | |500 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQUIPMENT |Table 7 | | | |460-|BCD | | | | |IDENT | | | | |500 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 040 |SOFTWARE |Table 8 | | | |460-|BCD | | | | |IDENT | | | | |500 | | | | ------------------------------------------------------------------------------Table 4 = Digital Outputs

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--------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 270 | | 9-10 |SDI | | 11-12 |Logic 0 | | 13-16 |LSD device revision number (currently 4H) | | 17-20 |MSD device revision number (currently 0H) | | 21-24 |LS device revision letter (currently CH) | | 25-28 |MS device revision letter (currently AH) | | 29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete | | |maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 5 = Discrete Word 1 (Label 270) --------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 271 | | 9-10 |SDI | | 11-13 |Logic 0 | | 14 |ADM LRU Status | | 15 |Pin configuration status | | 16 |Environment status | | 17-24 |Current fault byte matrix | | 25-28 |Word counter | | 29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete | | |maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 6 = Discrete Word 2 (Label 271)

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--------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 377 | | 9-10 |SDI | | 11-14 |LSD equipment identification (8H) | | 15-18 |MSD equipment identification (3H) | | 19-29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete | | |maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 7 = Equipment Ident (Label 377) --------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 040 | | 9-10 |SDI | | 11-12 |Logic 0 | | 13-16 |LSD software revision number | | 17-20 |MSD software revision number | | 21-24 |LSD manufacturer ident number (1H) | | 25-28 |MSD manufacturer ident number (0H) | | 29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete | | |maintenance word | | 32 |Odd parity | --------------------------------------------------------------------Table 8 = Software Ident (Label 040)

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D. Total Air Temperature (TAT) Sensor **ON A/C 051-099, 106-149, 204-238, 301-310, 401-499, (Ref. Fig. 008) R

**ON A/C 239-249, 251-299, 311-399, 501-509, 511-523, (Ref. Fig. 008A)

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, The aircraft is equipped with two TAT sensors with two sensing elements each. The sensing elements of the sensor have variable resistances. The TAT sensor 1 is linked to the ADR portion of ADIRUs 1 and 3, the TAT sensor 2 is linked to the ADR portion of ADIRU 2. The TAT sensors are set at 2.33 m from the nose and at 0.60 m of the aircraft axis below the fuselage. The TAT sensor 1 is located on the left side and the TAT sensor 2 on the right side. The air flow enters the scoop of the sensor, goes through a calibrated choke and flows over the hermetically sealed platinum resistance sensing element where the temperature is measured. The speed of the flow over the element is controlled by the choke in the element tube. The ADR portion is designed to operate with 500 ohms (at 0 deg. C ) temperature sensor unit corresponding to the basic Callender - Van Dusen equation. To improve the accuracy of the sensor, a network of precision resistors is used. This technique is identified by the term Precision Calibration Interchangeability (PCI). These sensors are heated with 115VAC through the probe heating system. The heating element must not be energized on the ground. The heating element is implanted in the scoop and strut and keeps the probe free of ice under the most severe icing conditions. NOTE : Probe ice protection is described in 30-31-00. ____

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ADIRS - TAT Sensor Figure 008   R EFF : 051-099, 106-149, 204-238, 301-310,  34-11-00 Page 27 401-499,  Config-3 Feb 01/08  CES

 

ADIRS - TAT Sensor Figure 008A   R EFF : 239-249, 251-299, 311-399, 501-509,  34-11-00 Page 28 511-523,  Config-3 Feb 01/10  CES

 

E. Angle Of Attack (AOA) Sensor **ON A/C 051-061, (Ref. Fig. 009) R R

**ON A/C 062-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (Ref. Fig. 009A)

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, The aircraft is equipped with three AOA sensors. Two are located on the left side and one on the right side of the fuselage. Each of these AOA sensors is respectively linked to each ADR portion of the ADIRUs. The AOA sensors 1 and 3 are set at 6.08 deg. and 31 deg. below the fuselage datum line (Z = 0) on the left side. The AOA sensor 2 is set at 6.08 deg. below the fuselage datum line (Z = 0) on the right side. The angle of attack sensor is of the wind vane type. Its sensing element is a small wing which is positioned in the direction of airflow. The small wing is mechanically linked to a free turn-shaft which drives the devices transmitting the local angle of attack signal. These transmitting devices are made up of resolver transformers which convert the angular information into proportional electrical information (angle sine and cosine). The resolvers are supplied with a 26VAC signal. The same signal is also received by the ADIRU as a reference for the decoding of AOA values. Each sensor has three resolver outputs but only two are wired to the ADIRU. The whole mechanism is stabilized around the rotation axis. In addition, a damping device enables a satisfactory dynamic response to be obtained (filtering of mechanical oscillation). A self-regulated heating element (CTP resistances: positive coefficient of temperature) inserted into the vane eliminates or avoids icing. It is supplied with 115VAC through the PHC (Ref. 30-31-00). The AOA sensor is equipped with a self-test device which is activated by a 28VDC signal, from the ADR (through the relay 21FP1, 21FP2 or 21FP3) when the test is entered via the maintenance system (CFDIU and MCDU). The self-test positions the vane at a resolver angle of +15 deg. (left side test) or -15 deg. (right side test). The mounting and wing of AOA resolvers determine the relationship between the measured resolver angle and indicated angle of attack. This relationship for each resolver input is as follows: (Ref. Fig. 010)

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ADIRS - AOA Sensor Figure 009   R EFF : 051-061,  34-11-00 Page 30   Config-3 Nov 01/07  CES

 

ADIRS - AOA Sensor Figure 009A   R EFF : 062-099, 106-149, 204-249, 251-299,  34-11-00 Page 31 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

AOA Sensor - Installation Definition Figure 010   R EFF : 051-099, 106-149, 204-249, 251-299,  34-11-00 Page 32 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

-----------------------------------------------------------------------| | Indicated AOA: | +85 | +60 | +25 | 0 | -35 | | AOA 1 and AOA 3 |----------------------------------------------------| | in degrees | Resolver angle: | -60 | -35 | 0 | +25 | +60 | -----------------------------------------------------------------------| | Indicated AOA: | +85 | +60 | +25 | 0 | -35 | | AOA 2 |----------------------------------------------------| | in degrees | Resolver angle: | +60 | +35 | 0 | -25 | -60 | -----------------------------------------------------------------------The ADRs receive the same 26VAC, 400 Hz reference as the AOA resolvers. This reference is common to both AOA resolver inputs 1 and 2. Characteristics: Excitation : 26 V 400 Hz Phase shift : 18 deg. to 30 deg. Resolver transformer ratio RT : 0.4029 to 0.4629 Rotor impedance : Zro = 125 + j175 ohms +/-20% Stator impedance : Zso = 115 + j90 ohms +/-30% Range : +/-60 deg. Scale factor : 1 deg. resolver/1 deg. local AOA The accuracy of the AOA sensor, at 100 knots, is +/-0.3 deg.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-11-00 Page 33 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

R

**ON A/C 051-099, 251-299, 401-499, 501-509, 511-523, F. Selector Switches (Ref. Fig. 011) The two selector switches AIR DATA and ATT HDG are rotary selector switches with 3 positions: CAPT/3, NORM and F/O/3. These selector switches are used for the functions listed below (Ref. the respective section for more details): - AIR DATA SEL SW (15FP): 34-14-00 Selection of the ADR used by the IR3 34-52-00 ATC mode S 31-68-00 DMC 22-85-00 FMGC - ATT HDG SEL SW (13FP): 34-11-00 Power Supply 34-14-00 Selection of the ADR used by the IR3 34-41-00 Weather Radar 31-68-00 DMC 22-85-00 FMGC.

  R EFF : 051-099, 251-299, 401-499, 501-509,  34-11-00 Page 34 511-523,  Config-3 Feb 01/10  CES

 

INTENTIONALLY BLANK

  R   34-11-00 Page 35   Config-3 Feb 01/10  CES

 

ADIRS Switching Figure 011   R EFF : 051-099, 106-149, 204-249, 251-299,  34-11-00 Page 36 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

**ON A/C 106-149, 204-249, 301-399, F. Selector Switches (Ref. Fig. 011) The two selector switches AIR DATA and ATT HDG are rotary selector switches with 3 positions: CAPT/3, NORM and F/O/3. These selector switches are used for the functions listed below (Ref. the respective section for more details): - AIR DATA SEL SW (15FP): 34-14-00 Selection of the ADR used by the IR3 34-52-00 ATC mode S 31-68-00 DMC 22-85-00 FMGC - ATT HDG SEL SW (13FP): 34-11-00 Power Supply 34-14-00 Selection of the ADR used by the IR3 34-41-00 Weather Radar 31-68-00 DMC 22-85-00 FMGC.

  EFF : 106-149, 204-249, 301-399,  34-11-00 Page 37   Config-3 Feb 01/10  CES

 

SENSORS, POWER SUPPLY AND SWITCHING - ADJUSTMENT/TEST _____________________________________________________ TASK 34-11-00-720-001 Functional Test of the ADM CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO _______ INSTRUMENTS: - THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg) - CHANGES IN STATIC PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE - DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED. CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE _______ STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg). 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R

No specific No specific No specific No specific No specific 36122 98D34003500000

circuit breaker(s) safety clip(s) colored adhesive tape ARINC reader access platform 1.6 m (5 ft. 3 in.) 1 GENERATOR - GROUND PRESSURE MINI. 100 MB 3 ADAPTOR-CHARGING,PITOT PROBE 1 ADAPTER COVER-STATIC PORT

  EFF : ALL  34-11-00    CES

 

Page 501 Aug 01/09

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

R

31-60-00-860-001 31-60-00-860-002 34-10-00-860-002 34-10-00-860-005 52-41-00-410-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure ADIRS Stop Procedure Close the Avionics Compartment Doors after Access

3. __________ Job Set-up Subtask 34-11-00-010-050 A. Get Access to the Avionics Compartment (1) Put the access platform in position and open the access door 824. Subtask 34-11-00-860-056 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (PFDs only) (Ref. TASK 31-60-00-860-001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) On the center pedestral, on the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is at NORM.

  EFF : ALL  34-11-00    CES

 

Page 502 Feb 01/02

Subtask 34-11-00-865-050 C. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 Subtask 34-11-00-480-050 D. Install the Ground Pressure Generator and the ARINC Reader. (1) Remove the slip on covers from the static probes and the pitot probes. (2) Connect the static port of the GENERATOR - GROUND PRESSURE MINI. 100 MB to the static and/or total probes on which you do the test : (a) the static probes with the ADAPTER COVER-STATIC PORT (98D34003500102) For CAPT circuit (ADIRU 1) and F/O circuit (ADIRU 2): - 7DA1 ZONE 127 STA 8750 for the LH static pressure ADM - 7DA2 ZONE 127 STA 8700 for the LH static pressure ADM and - 8DA1 ZONE 128 STA 9300 for the RH static pressure ADM - 8DA2 ZONE 128 STA 9350 for the RH static pressure ADM

(19FP5) (19FP7) (19FP4) (19FP6)

(b) the static probes with the ADAPTER COVER-STATIC PORT (98D34003500100) For the standby circuit (ADIRU 3) : - 7DA3 ZONE 121 STA 4250 for the static pressure ADM (19FP8) or - 8DA3 ZONE 122 STA 4250 for the static pressure ADM (19FP8) R

(c) the pitot probes with the ADAPTOR-CHARGING,PITOT PROBE or equivalent For CAPT circuit (ADIRU 1) : - 9DA1 ZONE 125 STA 5500 for the total pressure ADM (19FP1) For F/O circuit (ADIRU 2) : - 9DA2 ZONE 126 STA 5500 for the total pressure ADM (19FP2) For the standby circuit (ADIRU 3) : - 9DA3 ZONE 125 STA 5500 for the total pressure ADM (19FP3)

  EFF : ALL  34-11-00    CES

 

Page 503 Aug 01/09

(3) seal the Stby probes: CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT _______ SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE. ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE FIRST AND USE THE COLORED ADHESIVE TAPE TO ATTACH THE PLASTIC. IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE, THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE PROBE. (a) Seal the drain holes of the pitot probes with a piece of plastic and colored adhesive tape of very bright color. (b) Seal the opposite static probe of the standby ADM with the ADAPTER COVER-STATIC PORT (98D34003500103). (4) Start the ground pressure generator. (5) Connect the ARINC reader to - the connector 199VC (pins - the connector 198VC (pins - the connector 199VC (pins

: GG/HH) for the CAPT circuit (ADIRU 1) GG/HH) for the F/O circuit (ADIRU 2)
(6) Start the ARINC reader. 4. Procedure _________ Subtask 34-11-00-720-050 A. Functional Test of the ADM ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ground pressure generator, set a static pressure as given in the table below. NOTE : You can also set an other ____ pressure value. The tolerance for the values read on the ARINC reader

On the ARINC reader, compare the pressure values of the static and total ADM read on the following labels : ADIRU 1 - Label 242 (ADM 19FP1) - Label 176 (ADM 19FP5) - Label 177 (ADM 19FP4) ADIRU 2

  EFF : ALL  34-11-00   R  CES

 

Page 504 Feb 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------is the same as these - Label 242 (ADM 19FP2) indicated in the table - Label 176 (ADM 19FP7) below. - Label 177 (ADM 19FP6) ADIRU 3 - Label 242 (ADM 19FP3) - Label 245 (ADM 19FP8) 2. On the ground pressure generator, slowly decrease the pressure.

The rate of descent must not be more than 6000 ft/mn.

3. Stop the ground pressure generator.

The test procedure stops.

----------------------------------------------------| PT | Altitude | Pressure value from | | | (approx.) | the ADM | |----------|--------------|-------------------------| | 836 hPa | 5000 ft | 836 +/- 0.3 hPa | |----------|--------------|-------------------------| | 690 hPa | 10000 ft | 690 +/- 0.3 hPa | |----------|--------------|-------------------------| | 460 hPa | 20000 ft | 460 +/- 0.3 hPa | |----------|--------------|-------------------------| | 300 hPa | 30000 ft | 300 +/- 0.3 hPa | |----------|--------------|-------------------------| | 196 hPa | 39000 ft | 196 +/- 0.3 hPa | -----------------------------------------------------

R R R R R 5. Close-up ________

Subtask 34-11-00-080-050 A. Remove the Ground Pressure Generator (1) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (2) Make sure that there is no remaining piece of plastic and/or adhesive tape on the pitot probes. Make sure that the pitot drain holes are serviceable.

  EFF : ALL  34-11-00    CES

 

Page 505 Aug 01/08

Subtask 34-11-00-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 Subtask 34-11-00-410-050 C. Close Access R

(1) Close the access door 824 (Ref. TASK 52-41-00-410-002). (2) Remove the access platform(s). Subtask 34-11-00-860-051 D. Put the aircraft back to its initial configuration. (1) Install the slip on covers on the static probes and on the pitot probes. (2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005). (3) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  EFF : ALL  34-11-00    CES

 

Page 506 Feb 01/02

TASK 34-11-00-710-001 Test of the Monitoring of the ADR/AOA 26VAC Power Supply 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 31-60-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure

3. __________ Job Set-up Subtask 34-11-00-010-051 A. Get Access (1) Put the access platform in position in zone 126 at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover.

  EFF : ALL  34-11-00    CES

 

Page 507 Feb 01/98

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-11-00-860-052 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) On the overhead panel: - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - on the ELEC panel 35VU, make sure that the battery voltage is correct, between 26VDC and 30VDC. - on the ADIRS CDU, make sure that the 3 OFF/NAV/ATT selector switches are at OFF. NOTE : This test is for the system 1. For the systems 2 and 3, use ____ the indications between the parentheses. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-11-00-860-052-A B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) On the overhead panel: - On the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - On the ELEC panel 35VU, make sure that the battery voltage is correct, between 26VDC and 30VDC. - On the ADIRS MSU, make sure that the three OFF/NAV/ATT selector switches are at OFF. NOTE : This test is for the system 1. For the systems 2 and 3, use ____ the indications between the parentheses.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 508 Feb 01/10

**ON A/C ALL Subtask 34-11-00-865-053 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

2WC 2GA 52GA

P09 Q35 Q34

**ON A/C ALL 121VU EIS/HORN/SPLY 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

  EFF : ALL  34-11-00    CES

 

N10 N09 N08 N07 N06 N05 N04 N03

Page 509 Feb 01/10

**ON A/C ALL 4. Procedure _________ R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-11-00-710-050 A. Test of the Monitoring of the ADR/AOA 26VAC Power Supply ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR1, IR2 and IR3 to NAV.

- the CAPT and F/O PFDs show the speed and altitude indications.

2. On the panel 49VU (121VU): - open the circuit breaker 5FP1 (5FP2).

- on the ADIRS CDU, the FAULT legend of the ADR1 (ADR2) pushbutton switch comes on. - on the CAPT (F/O) PFD, the SPD and ALT warning flags come into view. - on the lower ECAM DU, on the status page, in the INOP SYST section, the ADR1 indication comes into view.

3. On the panel 8VU: - set the AIR DATA selector switch to CAPT/3 (F/O/3).

- on the CAPT (F/O) PFD, the speed and altitude indications come into view.

4. On the panel 121VU: - open the circuit breaker 5PF3.

- on the CAPT (F/O) PFD, the SPD and ALT warning flags come into view. - on the lower ECAM display unit, in the INOP SYST section, the ADR 1 + 3 (ADR 2 + 3) indication comes into view.

  EFF : ALL  34-11-00    CES

 

Page 510 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- on the ADIRS CDU, the FAULT legend of the ADR3 pushbutton switch comes on. 5. On the panel 49VU (121VU): - close the circuit breaker 5FP1 (5FP2).

- on the lower ECAM display unit, in the INOP SYST section, the ADR3 indication comes into view. - on the ADIRS CDU, the FAULT legend of the ADR1 (ADR2) pushbutton switch goes off.

6. On the panel 8VU: - set the AIR DATA selector switch to NORM.

- on the CAPT (F/O) PFD, the speed and altitude indications come into view.

7. On the panel 121VU: - close the circuit breaker 5FP3.

8. Refer to the indications in the parentheses specified in the para. 1 to 5 and do the ADR2 test.

- on the lower ECAM display unit, in the INOP SYST section, the ADR3 indication goes out of view. - on the ADIRS CDU, the FAULT legend of the ADR3 pushbutton switch goes off. You must get the same results on the F/O side.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-00 201-239, 301-312, 401-499,   CES

 

Page 511 Feb 01/08

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-11-00-710-050-A A. Test of the Monitoring of the ADR/AOA 26VAC Power Supply ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS MSU: - Set the OFF/NAV/ATT selector switch related to the IR1, IR2 and IR3 to NAV.

- The CAPT and F/O PFDs show the speed and altitude indications.

2. On the overhead C/B panel 49VU (121VU): - Open the circuit breaker 5FP1 (5FP2).

- On the ADIRS MSU, the FAULT legend of the ADR1 (ADR2) pushbutton switch comes on. - On the CAPT (F/O) PFD, the SPD and ALT warning flags come into view. - On the lower ECAM DU, on the status page, in the INOP SYST section, the ADR1 indication comes into view.

3. On the SWITCHING panel 8VU: - Set the AIR DATA selector switch to CAPT/3 (F/O/3).

- On the CAPT (F/O) PFD, the speed and altitude indications come into view.

4. On the rear C/B panel 121VU: - Open the circuit breaker 5PF3.

- On the CAPT (F/O) PFD, the SPD and ALT warning flags come into view. - On the lower ECAM display unit, in the INOP SYST section, the ADR 1 + 3 (ADR 2 + 3) indication comes into view. - On the ADIRS MSU, the FAULT legend of the ADR3 pushbutton switch comes on.

5. On the overhead C/B panel 49VU (121VU):

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-11-00 511-526, 528-599,   CES

 

Page 512 Feb 01/10

R R R R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Close the circuit breaker 5FP1 - On the lower ECAM display unit, in (5FP2). the INOP SYST section, the ADR3 indication comes into view. - On the ADIRS MSU, the FAULT legend of the ADR1 (ADR2) pushbutton switch goes off.

R

6. On the SWITCHING panel 8VU:

R R

- Set the AIR DATA selector switch to NORM.

R

- On the CAPT (F/O) PFD, the speed and altitude indications come into view.

7. On the rear C/B panel 121VU:

R R R R R

- Close the circuit breaker 5FP3.

R R R R

8. Refer to the indications in the parentheses specified in the para. 1 to 5 and do the ADR2 test.

R

**ON A/C ALL

- On the lower ECAM display unit, in the INOP SYST section, the ADR3 indication goes out of view. - On the ADIRS MSU, the FAULT legend of the ADR3 pushbutton switch goes off. You must get the same results on the F/O side.

5. Close-up ________ R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-11-00-860-053 A. Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2) On the ADIRS CDU, set the 3 OFF/NAV/ATT selector switches to OFF. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  EFF : ALL  34-11-00    CES

 

Page 513 Feb 01/08

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-11-00-860-053-A A. Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2) On the ADIRS MSU, set the three OFF/NAV/ATT selector switches to OFF. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). **ON A/C ALL Subtask 34-11-00-410-051 B. Close Access (1) Install the protective cover of the 105VU with two bolts. (2) Close the access door 822. (3) Remove the access platform(s).

  EFF : ALL  34-11-00    CES

 

Page 514 Feb 01/10

TASK 34-11-00-710-002 Test of the Monitoring of the ADIRS Power Supply (115VAC-28VDC) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 31-60-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure

3. __________ Job Set-up Subtask 34-11-00-010-052 A. Get Access (1) Put the access platform in position in zone 126 at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover.

  EFF : ALL  34-11-00   R  CES

 

Page 515 Feb 01/08

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-11-00-860-054 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) On the overhead panel: - On the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - On the ADIRS CDU, on the panel 20VU, make sure that the 3 OFF/NAV/ATT selector switches are at OFF. - On the ELEC panel 35VU, make sure that the battery voltage is correct, between 26VDC and 30VDC. NOTE : This test is for the system 1. For the systems 2 and 3, use ____ the indications between the parentheses. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-11-00-860-054-A B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) On the overhead panel: - On the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - On the ADIRS MSU, on the overhead panel 20VU, make sure that the three OFF/NAV/ATT selector switches are at OFF. - On the ELEC panel 35VU, make sure that the battery voltage is correct, between 26VDC and 30VDC. NOTE : This test is for the system 1. For the systems 2 and 3, use ____ the indications between the parentheses.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 516 Feb 01/10

**ON A/C ALL Subtask 34-11-00-865-054 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

2WC 2GA 52GA

P09 Q35 Q34

**ON A/C ALL 121VU EIS/HORN/SPLY 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

  EFF : ALL  34-11-00    CES

 

N10 N09 N08 N07 N06 N05 N04 N03

Page 517 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 101-105, 151-199, 201-203, Subtask 34-11-00-710-051-A A. Test of the Monitoring of the ADIRS Power Supply (115VAC-28VDC) NOTE : Ignore all warnings / indications which are not related to this ____ test. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the panel 49VU (121VU): - open the circuit breaker 4FP1 (4FP2). 2. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 1 (IR 2) to NAV. - set the SYS DISPLAY selector switch to 1 (2).

- on the ADIRS CDU: * the ON BAT light is on, * the related ALIGN legend is on, * the related FAULT legend flashes. - on the upper ECAM display unit, the IR 1 FAULT (IR 2 FAULT) warning comes into view. - on the GLARESHIELD panels 130VU and 131VU, the MASTER CAUT lights are on. - you can hear the single chime. - after a time delay of 15 s, you can hear the horn.

3. On the panel 49VU (121VU): - close the circuit breaker 4FP1 (4FP2).

- on the ADIRS CDU: * the related FAULT legend goes off, * the ON BAT light goes off, * the related ALIGN legend stays on.

  R EFF : ALL  34-11-00    CES

 

Page 518 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- on the upper ECAM display unit, the IR1 FAULT (IR2 FAULT) warning goes out of view. - the horn stops. 4. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 1 (IR 2) to OFF.

- on the ADIRS CDU, the related ALIGN legend goes off.

5. On the GLARESHIELD panels 130VU and 131VU: - push and release the MASTER CAUT lights. 6. Do the IR 2 test as specified in para. 1 to 5.

- on the GLARESHIELD panels 130VU and 131VU, the MASTER CAUT lights go off. You must get the same results on the F/O side.

7. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 1 (IR 2) to NAV.

- on the ADIRS CDU: * the related ALIGN legend comes on, * then, the ON BAT light comes on during 5 s.

8. On the panel 49VU (121VU): - open the circuit breaker 4FP1 (4FP2).

- on the ADIRS CDU, the ON BAT light comes on. - in the nose gear well: * after a time delay of 15 s approx you can hear the horn, * on the door 121AL, on the EXT PWR panel 108VU, the ADIRU & AVNCS VENT light comes on. - on the CAPT (F/O) PFD, the attitude indications are shown.

9. On the panel 49VU (121VU): - close the circuit breaker 4FP1 (4FP2).

- on the ADIRS CDU, the ON BAT light goes off.

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00    CES

 

Page 519 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the horn stops. 10. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 1 (IR 2) to OFF. 11. Do the IR 2 test as specified in para. 7 to 10.

- on the ADIRS CDU, the related ALIGN legend goes off. - on the CAPT (F/O) PFD, the attitude indications go off. You must get the same results on the F/O side.

12. On the panel 121VU: - open the circuit breaker 4FP3. 13. On the SWITCHING panel 8VU: - set the ATT HDG selector switch to CAPT/3.

- on the CAPT PFD and ND the attitude and heading indications from the IR 1 are not shown.

14. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 3 to NAV. - set the SYS DISPLAY selector switch to 3.

- on the ADIRS CDU: * the ON BAT light is on, * the related ALIGN legend is on, * the related FAULT legend flashes. - on the upper ECAM display unit, the IR 3 FAULT warning comes into view. - on the GLARESHIELD panels 130VU and 131VU, the MASTER CAUT lights are on. - you can hear the single chime. - after a time delay of 15 s, you can hear the horn.

15. On the panel 121VU: - close the circuit breaker 4FP3.

- on the ADIRS CDU: * the related FAULT legend goes off, * the ON BAT light goes off, * the related ALIGN legend stays on.

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00    CES

 

Page 520 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- on the upper ECAM display unit, the IR 3 FAULT warning goes off. 16. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 3 to OFF.

- on the ADIRS CDU, the ALIGN legend goes off.

17. On the GLARESHIELD panels 130VU and 131VU: - push and release the MASTER CAUT lights.

- on the GLARESHIELD panels 130VU and 131VU, the MASTER CAUT lights go off.

18. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 3 to NAV.

- on the ADIRS CDU: * the related ALIGN legend comes on, * then, the ON BAT light comes on during 5 s.

19. On the panel 121VU: - open the circuit breaker 4FP3.

- on the ADIRS CDU, the ON BAT light comes on. - in the nose gear well: * after a time delay of 15 s approx you can hear the horn, * on the door 121AL, on the EXT PWR panel 108VU, the ADIRU & AVNCS VENT light comes on. - on the CAPT (F/O) PFD, the attitude indications stay in view.

20. On the panel 121VU: - close the circuit breaker 4FP3.

- on the ADIRS CDU, the ON BAT light goes off. - the horn stops.

21. On the ADIRS CDU:

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-11-00    CES

 

Page 521 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set the 3 OFF/NAV/ATT selector - on the ADIRS CDU, the related ALIGN switches to OFF. legend goes off. 22. On the SWITCHING panel 8VU: - set the ATT HDG selector switch to NORM. 23. On the ADIRS CDU: - set the SYS DISPLAY selector switch to OFF. R

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, Subtask 34-11-00-710-051 A. Test of the Monitoring of the ADIRS Power Supply (115VAC-28VDC) NOTE : Ignore all warnings / indications which are not related to this ____ test. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the panel 49VU (121VU): - open the circuit breaker 4FP1 (4FP2). 2. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 1 (IR 2) to NAV. - set the SYS DISPLAY selector switch to 1 (2).

- on the ADIRS CDU: * the related ALIGN legend is on, * the ON BAT light is on, * the related FAULT legend flashes. - On the upper ECAM display unit, the IR 1 FAULT (IR 2 FAULT) warning comes into view. - on the panels 130VU and 131VU, the MASTER CAUT lights are on. - you can hear the single chime.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-00 201-239, 301-312, 401-499,   CES

 

Page 522 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- after a time delay of 15 s, you can hear the horn. 3. On the panel 49VU (121VU), close the circuit breaker 4FP1 (4FP2).

- on the ADIRS CDU, The related FAULT legend continues to flash. The ON BAT light goes off. The ALIGN legend stays on. - The horn stops.

4. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 1 (IR 2) to OFF.

- on the ADIRS CDU, the related FAULT legend continues to flash then goes off after a short time, - on the upper ECAM display unit, the IR1 FAULT (IR2 FAULT) warning goes out of view. - on the panels 130VU and 131VU the MASTER CAUT lights go off, - on the ADIRS CDU, the related ALIGN legend goes off.

5. Do the IR 2 test as specified in para. 1 to 4.

You must get the same results on the F/O side.

6. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 1 (IR 2) to NAV.

On the ADIRS CDU: - the related ALIGN legend comes on, - then, the ON BAT light comes on during 5 s.

7. On the panel 49VU (121VU): - open the circuit breaker 4FP1 (4FP2).

- on the ADIRS CDU, the ON BAT light comes on. - in the nose gear wheel: * after a time delay of 15 s approx you can hear the horn. * on the door 121AL, on the panel 108VU, the ADIRU & AVNCS VENT light comes on. - on the CAPT (F/O) PFD and ND, the attitude indications are shown.

8. On the panel 49VU (121VU):

  R EFF : 051-099, 106-149, 204-239, 301-312,  34-11-00 401-499,   CES

 

Page 523 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- close the circuit breaker 4FP1 - on the ADIRS CDU, the ON BAT light (4FP2). goes off. - the horn stops. 9. On the ADIRS CDU: set the OFF/NAV/ATT selector switch related to the IR1 (IR2) to OFF.

On the ADIRS CDU: the ALIGN legend goes off.

10. Do the IR 2 test as specified in para. 6 to 8.

You must get the same results on the F/O side.

11. On the panel 121VU: - open the circuit breaker 4FP3. 12. On the panel 8VU: - set the ATT HDG selector switch to CAPT/3.

- on the CAPT PFD and ND the attitude and heading indications from the IR 1 are not shown.

13. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 3 to NAV. - set the SYS DISPLAY selector switch to 3.

- on the ADIRS CDU: * the related ALIGN legend is on, * the ON BAT light is on. * the related FAULT legend flashes. - on the upper ECAM display unit, the IR 3 FAULT warning comes into view. - on the panels 130VU and 131VU, the MASTER CAUT lights are on. - you can hear the single chime. - after a time delay of 15 s, you can hear the horn.

14. On the panel 121VU: - close the circuit breaker 4FP3.

- on the ADIRS CDU: * the related FAULT legend goes off. * the ON BAT light goes off. * the ALIGN legend stays on.

  EFF : 051-099, 106-149, 204-239, 301-312,  34-11-00 401-499,   CES

 

Page 524 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------15. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 3 to OFF.

- on the ADIRS CDU: * the related FAULT legend continues to flash then goes off after a short time, * the ALIGN legend goes off.

16. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch related to the IR 3 to NAV.

- on the ADIRS CDU: * the ON BAT light comes on during 5 s. * then, the ALIGN legend comes on.

17. On the panel 121VU: - open the circuit breaker 4FP3.

18. On the panel 121VU: - close the circuit breaker 4FP3.

- on the ADIRS CDU, the ON BAT light comes on. - in the nose gear well: * after a time delay of 15 s approx you can hear the horn. * on the door 121AL, on the panel 108VU, the ADIRU & AVNCS VENT light comes on. - on the CAPT (F/O) PFD , the attitude indications stay in view. - on the ADIRS CDU, the ON BAT light goes off. - the horn stops.

19. On the ADIRS CDU: - set the 3 OFF/NAV/ATT selector switches to OFF.

- The related ALIGN legend goes off.

20. On the panel 8VU: - set the ATT HDG selector switch to NORM.

  EFF : 051-099, 106-149, 204-239, 301-312,  34-11-00 401-499,   CES

 

Page 525 Feb 01/08

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-11-00-710-051-B A. Test of the Monitoring of the ADIRS Power Supply (115VAC-28VDC) NOTE : Ignore all warnings / indications which are not related to this ____ test. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead C/B panel 49VU (121VU): - Open the circuit breaker 4FP1 (4FP2).

- On the ADIRS MSU: * The ON BAT light is on. * The related FAULT legend flashes. - On the upper ECAM display unit, the

2. On the ADIRS MSU: - Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) to NAV.

IR1 FAULT (IR2 FAULT) warning comes into view. - On the F/O and CAPT glareshield panels 130VU and 131VU, the MASTER CAUT lights are on. - You can hear the single chime. - After a time delay of 15 s, you can hear the horn.

3. On the overhead C/B panel 49VU (121VU), close the circuit breaker 4FP1 (4FP2).

- On the ADIRS MSU: The related FAULT legend continues to flash. The ON BAT light goes off. - The horn stops.

4. On the ADIRS MSU: - Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) to OFF.

- On the ADIRS MSU, the related FAULT legend continues to flash then goes off after a short time. - On the upper ECAM display unit, the IR1 FAULT (IR2 FAULT) warning goes out of view. - On the F/O and CAPT glareshield panels 130VU and 131VU the MASTER CAUT lights go off.

5. Do the IR2 test as specified in para. 1 to 4.

You must get the same results on the F/O side.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-11-00 511-526, 528-599,   CES

 

Page 526 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------6. On the ADIRS MSU: On the ADIRS MSU: - Set the OFF/NAV/ATT selector - The ON BAT light comes on during 5 s. switch related to the IR1 (IR2) to NAV. 7. On the overhead C/B panel 49VU (121VU): - Open the circuit breaker 4FP1 (4FP2).

- On the ADIRS MSU, the ON BAT light comes on. - In the nose gear wheel: * After a time delay of 15 s approx you can hear the horn. * On the door 121AL, on the external power panel 108VU, the ADIRU & AVNCS VENT light comes on. - On the CAPT (F/O) PFD and ND, the attitude indications are shown.

8. On the overhead C/B panel 49VU (121VU): - Close the circuit breaker 4FP1 (4FP2).

- On the ADIRS MSU, the ON BAT light goes off. - The horn stops.

9. On the ADIRS MSU: Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) to OFF. 10. Do the IR2 test as specified in para. 6 to 8.

You must get the same results on the F/O side.

11. On the rear C/B panel 121VU: - Open the circuit breaker 4FP3. 12. On the SWITCHING panel 8VU: - Set the ATT HDG selector switch to CAPT/3. 13. On the ADIRS MSU:

- On the CAPT PFD and ND the attitude and heading indications from the IR1 are not shown. - On the ADIRS MSU:

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-11-00 511-526, 528-599,   CES

 

Page 527 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Set the OFF/NAV/ATT selector * The ON BAT light is on. switch related to the IR3 to * The related FAULT legend flashes. NAV. - On the upper ECAM display unit, the IR3 FAULT warning comes into view. - On the F/O and CAPT glareshield panels 130VU and 131VU, the MASTER CAUT lights are on. - You can hear the single chime. - After a time delay of 15 s, you can hear the horn. 14. On the rear C/B panel 121VU: - Close the circuit breaker 4FP3.

- On the ADIRS MSU: * The related FAULT legend goes off. * The ON BAT light goes off.

15. On the ADIRS MSU: - Set the OFF/NAV/ATT selector switch related to the IR3 to OFF.

- On the ADIRS MSU: * The related FAULT legend continues to flash then goes off after a short time.

16. On the ADIRS MSU: - Set the OFF/NAV/ATT selector switch related to the IR3 to NAV.

- On the ADIRS MSU: * The ON BAT light comes on during 5 s.

17. On the rear C/B panel 121VU: - Open the circuit breaker 4FP3.

- On the ADIRS MSU, the ON BAT light comes on. - In the nose gear well: * After a time delay of 15 s approx you can hear the horn. * On the door 121AL, on the external power panel 108VU, the ADIRU & AVNCS VENT light comes on. - On the CAPT (F/O) PFD, the attitude indications stay in view.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-11-00 511-526, 528-599,   CES

 

Page 528 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------18. On the rear C/B panel 121VU: - On the ADIRS MSU, the ON BAT light - Close the circuit breaker goes off. 4FP3. - The horn stops. 19. On the ADIRS MSU: - Set the three OFF/NAV/ATT selector switches to OFF. 20. On the SWITCHING panel 8VU: - Set the ATT HDG selector switch to NORM. **ON A/C ALL 5. Close-up ________ Subtask 34-11-00-860-055 A. Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2) On the overhead panel: - On the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are pushed. The off legends are off. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-11-00-410-052 B. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

  EFF : ALL  34-11-00   R  CES

 

Page 529 Feb 01/10

PROBE - PITOT (9DA1,9DA2,9DA3) - REMOVAL/INSTALLATION _____________________________________________________ TASK 34-11-15-000-001 Removal of the Pitot Probe (9DA1, 9DA2, 9DA3) WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE _______ OPENED, SAFETIED AND TAGGED. R R R R R R

WARNING : OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) _______ AND 5DA1(2,3) BEFORE YOU OPEN THE PHC CIRCUIT BREAKERS 2DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

blanking cap blanking plug circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-11-15-991-001

Fig. 401

  EFF : ALL  34-11-15    CES

 

Page 401 Feb 01/10

3. __________ Job Set-up Subtask 34-11-15-860-058 A. Aircraft Maintenance Configuration (1) Remove the protective covers from the sensors and the probes (AOA, Static, Pitot and TAT). Subtask 34-11-15-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

ICE/PROBES/AOA/1 ICE/PROBES/PITOT/1 ICE/PROBES/1/STATIC ICE/PROBES/1/TAT

4DA1 3DA1 5DA1 1DA1

D04 D02 Z13 Z12

ICE/PROBES/2/TAT ICE/PROBES/2/PITOT ICE/PROBES/2/AOA ICE/PROBES/2/STATIC

1DA2 3DA2 4DA2 5DA2

Y15 Y14 Y13 Y11

ICE/PROBES/3/PITOT ICE/PROBES/3/AOA ICE/PROBES/3/STATIC

3DA3 4DA3 5DA3

Z16 Z15 Z14

**ON A/C ALL FOR 9DA1 49VU ANTI 49VU ANTI 122VU ANTI 122VU ANTI FOR 9DA2 122VU ANTI 122VU ANTI 122VU ANTI 122VU ANTI FOR 9DA3 122VU ANTI 122VU ANTI 122VU ANTI

  EFF : ALL  34-11-15    CES

 

Page 402 Feb 01/10

Subtask 34-11-15-865-061 C. Open, safety and tag this(these) circuit breaker(s):

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 9DA1 49VU ANTI ICE/PROBES/PHC/1 2DA1 D03 FOR 9DA2 122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12 FOR 9DA3 122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16 Subtask 34-11-15-010-050 D. Get Access (1) Put the access platform in position at zone 125 to get access to pitot probes 1 and 3 and at zone 126 to get access to pitot probe 2. (2) Open the access door: FOR 9DA1, 9DA3 812 FOR 9DA2 822 4. Procedure _________ (Ref. Fig. 401/TASK 34-11-15-991-001) Subtask 34-11-15-020-050 A. Removal of the Pitot Probe (9DA1, 9DA2, 9DA3) CAUTION : BE VERY CAREFUL WITH THE PITOT PROBES: _______ - DO NOT LET THEM FALL - DO NOT BEND THEM - DO NOT CAUSE SCRATCHES. (1) Disconnect the electrical connector (2). (2) Disconnect the quick-disconnect coupling (1). (3) Put a blanking cap on the disconnected electrical connector (2). (4) Put a blanking plug on the quick-disconnect coupling (1).

  EFF : ALL  34-11-15    CES

 

Page 403 Feb 01/10

R R

Pitot Probe Figure 401/TASK 34-11-15-991-001

  EFF : ALL  34-11-15    CES

 

Page 404 Nov 01/01

(5) Loosen the two nuts (3) from the inner side of the aircraft. NOTE : A second person is necessary to hold the pitot probe from the ____ outer side of the aircraft. (6) Carefully remove the pitot probe (5) from the fuselage. (7) Remove and discard the gasket (4).

  EFF : ALL  34-11-15   R  CES

 

Page 405 Nov 01/09

TASK 34-11-15-400-001 Installation of the Pitot Probe (9DA1, 9DA2, 9DA3) WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE _______ OPENED, SAFETIED AND TAGGED. CAUTION : MAKE SURE THAT: _______ - THERE IS NO SIGN OF CORROSION OR DAMAGE ON THE EQUIPMENT - THERE IS NO FOREIGN OBJECT IN THE EQUIPMENT TO PREVENT ANY DAMAGE IN THE SYSTEM. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R

No specific No specific

access platform 1.6 m (5 ft. 3 in.) Torque Wrench : range 0.00 to 1.20 m.daN (0.00 to 9.00 lbf.ft)

B. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------4 4

gasket gasket

34-11-01 03 -040 34-11-01 03 -040A

R

  EFF : ALL  34-11-15    CES

 

Page 406 Feb 01/10

C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-720-005 30-31-00-710-001 34-11-15-200-001 34-11-15-710-001 52-41-00-010-002 52-41-00-410-002 34-11-15-991-001 34-11-15-991-003

Check of the Electrical Bonding of the Different Components (But not the Fluid Systems and the Components Installed on Composite materials) Operational Test of the Probe Ice Protection Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3) Test of the Pitot Probe (9DA1, 9DA2, 9DA3) without the CFDS Open the Avionics Compartment Doors for Access Close the Avionics Compartment Doors after Access Fig. 401 Fig. 402

3. __________ Job Set-up Subtask 34-11-15-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at zone 125 to get access to pitot probes 1 and 3 and at zone 126 to get access to pitot probe 2. (2) Make sure that the access door are open (Ref. TASK 52-41-00-010-002): FOR 9DA1, 9DA3 812 FOR 9DA2 822 R R

(3) Make sure that the protective covers of the sensors and probes (AOA, static, Pitot and TAT) are removed.

  EFF : ALL  34-11-15    CES

 

Page 407 Nov 01/09

Subtask 34-11-15-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

ICE/PROBES/AOA/1 ICE/PROBES/PITOT/1 ICE/PROBES/1/STATIC ICE/PROBES/1/TAT

4DA1 3DA1 5DA1 1DA1

D04 D02 Z13 Z12

ICE/PROBES/2/TAT ICE/PROBES/2/PITOT ICE/PROBES/2/AOA ICE/PROBES/2/STATIC

1DA2 3DA2 4DA2 5DA2

Y15 Y14 Y13 Y11

ICE/PROBES/3/PITOT ICE/PROBES/3/AOA ICE/PROBES/3/STATIC

3DA3 4DA3 5DA3

Z16 Z15 Z14

**ON A/C ALL FOR 9DA1 49VU ANTI 49VU ANTI 122VU ANTI 122VU ANTI FOR 9DA2 122VU ANTI 122VU ANTI 122VU ANTI 122VU ANTI FOR 9DA3 122VU ANTI 122VU ANTI 122VU ANTI

Subtask 34-11-15-865-062 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 9DA1 49VU ANTI ICE/PROBES/PHC/1 2DA1 D03 FOR 9DA2 122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12 FOR 9DA3 122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16

  EFF : ALL  34-11-15    CES

 

Page 408 Feb 01/10

4. Procedure _________ (Ref. Fig. 401/TASK 34-11-15-991-001) Subtask 34-11-15-420-050 A. Installation of the Pitot Probe (9DA1, 9DA2, 9DA3) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. R

(3) Install the new gasket (4). NOTE : A second person is necessary to hold the pitot probe from the ____ outer side of the aircraft. (4) Carefully install the pitot probe (5). NOTE : You must turn the sensor element (6) to the front of the ____ aircraft.

R R

(5) TORQUE the two nuts (3) to 0.85 m.daN (75.22 lbf.in) from the inner side of the fuselage. (6) Remove the blanking cap from the electrical connector (2). (7) Make sure that the electrical connectors are clean and in the correct condition. (8) Connect the electrical connector (2) to the pitot probe (5). (9) Remove the blanking plug from the quick-disconnect coupling (1). (10) Connect the quick-disconnect coupling (1) to the pitot probe (5). (Ref. Fig. 402/TASK 34-11-15-991-003) (11) Make sure that you can see the blue ring on the quick-disconnect coupling.

  EFF : ALL  34-11-15    CES

 

Page 409 Feb 01/10

Illustration of the Quick-Disconnect coupling Figure 402/TASK 34-11-15-991-003   EFF : ALL  34-11-15   R  CES

 

Page 410 Feb 01/10

(12) Pull the quick-disconnect coupling to be sure that it is correctly attached. WARNING : IF YOU REPLACE PITOT PROBE 3 (9DA3), OR IF YOU REPLACE MORE _______ THAN ONE PITOT PROBE, MAKE SURE THAT A SECOND QUALIFIED MECHANIC DOES A VISUAL INSPECTION OF THE QUICK-DISCONNECT COUPLING CONNECTION. THE TWO MECHANICS MUST SIGN OFF THE JOB. (13) Check the bonding contact resistance between the pitot probe (5) and the fuselage structure (Ref. TASK 20-28-00-720-005). Subtask 34-11-15-865-052 B. Remove the safety breaker(s): 5SQ1, 5SQ2 FOR 9DA1 1DA1, 2DA1, 3DA1, FOR 9DA2 1DA2, 2DA2, 3DA2, FOR 9DA3 2DA3, 3DA3, 4DA3,

clip(s) and the tag(s) and close this(these) circuit

4DA1, 5DA1 4DA2, 5DA2 5DA3

Subtask 34-11-15-710-050 C. Do the tests that follow: (1) Do the operational test of the Probe Ice Protection. (Ref. TASK 30-31-00-710-001). NOTE : As an alternative procedure, you can do this operational test ____ without the CFDS (Ref. TASK 34-11-15-710-001). 5. Close-up ________ Subtask 34-11-15-410-050 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Make sure that the drain holes on the pitot probes are not blocked by unwanted materials. (Ref. TASK 34-11-15-200-001)

  EFF : ALL  34-11-15   R  CES

 

Page 411 Feb 01/10

(3) Close the access door (Ref. TASK 52-41-00-410-002) : FOR 9DA1, 9DA3 812 FOR 9DA2 822 (4) Install the protective covers on the sensors and probes (AOA, static, Pitot and TAT). (5) Remove the access platform(s).

  EFF : ALL  34-11-15   R  CES

 

Page 412 Feb 01/10

PROBE - PITOT (9DA1,9DA2,9DA3) - ADJUSTMENT/TEST ________________________________________________ TASK 34-11-15-710-001 Test of the Pitot Probe (9DA1, 9DA2, 9DA3) without the CFDS CAUTION : REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THE TEST. _______ CAUTION : DO NOT CONTINUE THE TEST FOR MORE THAN ONE MINUTE TO PREVENT DAMAGE _______ TO THE PROBES. WARNING : DO NOT TOUCH THE PROBES IMMEDIATELY AFTER THE TEST. _______ THEY ARE HOT AND CAN BURN YOU. 1. __________________ Reason for the Job Do this test after the removal/installation of the Pitot Probe (9DA1,9DA2,9DA3) when the CFDS is unserviceable. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-11-15-860-051 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure ECAM only(Ref. TASK 31-60-00-860-001).

  EFF : ALL  34-11-15    CES

 

Page 501 Feb 01/98

(3) Do the ADIRS start procedure for the related system: For 9DA1 ADIRU1 For 9DA2 ADIRU2 For 9DA3 ADIRU3 (Ref. TASK 34-10-00-860-002). Subtask 34-11-15-865-056 B. Make sure that this(these) circuit breaker(s) is(are) closed:

R R R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 9DA1 49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 FOR 9DA2 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 FOR 9DA3 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 4. Procedure _________ Subtask 34-11-15-710-051 A. Heating Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead panel on the PROBE/WINDOW HEAT section of the panel 25VU: - push the AUTO pushbutton switch

the ON legend comes on.

2. On the circuit breaker panel : - on the panel 49VU, open the circuit breaker 3DA1

- on the panels 131VU and 132VU, the MASTER CAUT lights come on - you can hear the single chime - on the upper ECAM display unit the ANTI ICE CAPT PITOT indication comes into view.

  EFF : ALL  34-11-15    CES

 

Page 502 May 01/00

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- or on the panel 122VU, open the - on the panels 131VU and 132VU, the circuit breaker 3DA2 MASTER CAUT lights come on - you can hear the single chime - on the upper ECAM display unit the ANTI ICE F/O PITOT indication comes into view. - or on the panel 122VU, open the circuit breaker 3DA3.

3. Close the circuit breaker(s) that you opened before.

- on the panels 131VU and 132VU, the MASTER CAUT lights come on - you can hear the single chime - on the upper ECAM display unit the ANTI ICE STBY PITOT indication comes into view. - on the panels 131VU and 132VU, the MASTER CAUT lights go off. - on the upper ECAM display unit, the indication given above goes out of view. - on the upper ECAM display unit, the MEMO page comes into view.

4. On the overhead panel, on the PROBE/WINDOW HEAT section of the panel 25VU: - release the AUTO pushbutton switch

The ON legend goes off.

5. Close-up ________ Subtask 34-11-15-860-052 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF. (2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  EFF : ALL  34-11-15    CES

 

Page 503 Feb 01/98

PROBE - PITOT (9DA1,9DA2,9DA3) - INSPECTION/CHECK _________________________________________________ TASK 34-11-15-200-001 Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3) 1. __________________ Reason for the Job The purpose of this Task is to do a Visual inspection of the Pitot probe. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-10-00-170-001 34-10-00-170-003 34-11-15-000-001 34-11-15-400-001 34-22-25-170-001

R

Flushing of the Principal Total Pressure Lines (for corrective action) Draining and Flushing of Standby Pneumatic Circuits (for corrective action) Removal of the Pitot Probe (9DA1, 9DA2, 9DA3) (for corrective action) Installation of the Pitot Probe (9DA1, 9DA2, 9DA3) (for corrective action) Draining and Flushing of the Standby Static and Standby Total Pressure lines (ISIS) (for corrective action)

**ON A/C 001-049, 051-099, 101-105, 151-199, 34-11-15-991-002

Fig. 601

  EFF : ALL  34-11-15    CES

 

Page 601 Nov 01/09

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R R

**ON A/C 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-11-15-991-002-B

Fig. 601A

**ON A/C ALL 3. __________ Job Set-up Subtask 34-11-15-865-053 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 9DA1 49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 FOR 9DA2 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 FOR 9DA3 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 Subtask 34-11-15-860-054 B. Aircraft Maintenance Configuration (1) Put the access platform in position in Zone 125 to get access to the pitot probes 1 and 3 and in Zone 126 to get access to the pitot probe 2. (2) Remove the cover of the pitot probe. 4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, 151-199, (Ref. Fig. 601/TASK 34-11-15-991-002)

  EFF : ALL  34-11-15    CES

 

Page 602 Feb 01/10

Pitot Probe Tip Configuration Figure 601/TASK 34-11-15-991-002   R EFF : 001-049, 051-099, 101-105, 151-199,  34-11-15    CES

 

Page 603 Nov 01/09

R R

**ON A/C 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 601A/TASK 34-11-15-991-002-B) **ON A/C 001-049, 051-099, 101-105, 151-199, Subtask 34-11-15-220-050 A. Inspection/Check of the Pitot probe (9DA1,9DA2,9DA3) (1) Do a general visual inspection of the Pitot probe. (a) Color During the ageing of the probe, the color of the tube becomes brownish and/or blackish. This coloration has no effect on the operation of the probe. (b) Internal obstruction CAUTION : DO NOT USE SHARP AND/OR METAL TOOLS OR OBJECTS TO CLEAN _______ THE PITOT PROBE. SUCH TOOLS OR OBJECTS CAN CAUSE DAMAGE TO THE PITOT PROBE. Make sure that Pitot probe is clean, without obstruction. If not, remove the Pitot probe (Ref. TASK 34-11-15-000-001), blow compressed air into the Pitot tube at the pneumatic connector and out of the tube entrance. Maximum air pressure: 57 psi (3.9300 bar). NOTE : The compressed air line must have an oil trap to make sure ____ that no oil gets into the Pitot probe. Install the Pitot probe (Ref. TASK 34-11-15-400-001). (c) External condition. Make sure that the Pitot probe tube is not bent and has no holes or cracks. If you find damage, replace the Pitot probe (Ref. TASK 34-11-15-000-001) and (Ref. TASK 34-11-15-400-001). (d) Make sure that the drain holes are not blocked. If they are blocked, do the flushing of the total pressure lines: - for Pitot probe 1 and/or 2 (Ref. TASK 34-10-00-170-001) - for Pitot probe 3 (Ref. TASK 34-10-00-170-003) (only standby total pressure line part).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-15 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 604 Feb 01/10

Pitot Probe Tip Configuration Figure 601A/TASK 34-11-15-991-002-B   R EFF : 106-149, 201-249, 251-299, 301-399,  34-11-15 401-499, 501-509, 511-526, 528-599,   CES

 

Page 605 Feb 01/10

(e) If the inspection/check is not satisfactory, you must reject the Pitot probe (Ref. TASK 34-11-15-000-001) and (Ref. TASK 34-11-15400-001). If the protective cover melted on the probe and the other criteria are correct, you must reject the Pitot probe. NOTE : If the Pitot probe is not in correct condition, you can do ____ a check of the probe in workshop during scheduled maintenance procedures (A or C Checks, etc.). Refer to the Inspection part of the CMM 341153. R R

**ON A/C 106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-11-15-220-050-B A. Inspection/Check of the Pitot probe (9DA1,9DA2,9DA3) (1) Do a general visual inspection of the Pitot probe. (a) Color During the ageing of the probe, the color of the tube becomes brownish and/or blackish. This coloration has no effect on the operation of the probe. (b) Internal obstruction (b) CAUTION : DO NOT USE SHARP AND/OR METAL TOOLS OR OBJECTS TO CLEAN _______ THE PITOT PROBE. SUCH TOOLS OR OBJECTS CAN CAUSE DAMAGE TO THE PITOT PROBE. Make sure that Pitot probe is clean, without obstruction. If not, remove the Pitot probe (Ref. TASK 34-11-15-000-001), blow compressed air into the Pitot tube at the pneumatic connector and out of the tube entrance. Maximum air pressure: 57 psi (3.9300 bar). NOTE : The compressed air line must have an oil trap to make sure ____ that no oil gets into the Pitot probe. Install the Pitot probe (Ref. TASK 34-11-15-400-001). (c) External condition Make sure that the Pitot probe tube is not bent and has no holes or cracks. If you find damage, replace the Pitot probe.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-15 221-235, 239-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 606 Feb 01/10

(d) Make sure that the drain holes are not blocked. If they are blocked, do the flushing of the total pressure lines: - for Pitot probe 1 and/or 2 (Ref. TASK 34-10-00-170-001) - for Pitot 3 (Ref. TASK 34-22-25-170-001) (only standby total pressure line part). (e) If the inspection/check is not satisfactory, you must reject the Pitot probe (Ref. TASK 34-11-15-000-001) and (Ref. TASK 34-11-15400-001). If the protective cover melted on the probe and the other criteria are correct, you must reject the Pitot probe. NOTE : If the Pitot probe is not in correct condition, you can do ____ a check of the probe in workshop during scheduled maintenance procedures (A or C Checks, etc.). Refer to the Inspection part of the CMM 341109. **ON A/C 201-220, 236-238, Subtask 34-11-15-220-050-A A. Inspection/Check of the Pitot probe (9DA1,9DA2,9DA3) (1) Do a general visual inspection of the Pitot probe. (a) Color During the ageing of the probe, the color of the tube becomes brownish and/or blackish. This coloration has no effect on the operation of the probe. (b) Internal obstruction (b) CAUTION : DO NOT USE SHARP AND/OR METAL TOOLS OR OBJECTS TO CLEAN _______ THE PITOT PROBE. SUCH TOOLS OR OBJECTS CAN CAUSE DAMAGE TO THE PITOT PROBE. Make sure that Pitot probe is clean, without obstruction. If not, remove the Pitot probe (Ref. TASK 34-11-15-000-001), blow compressed air into the Pitot tube at the pneumatic connector and out of the tube entrance. Maximum air pressure: 57 psi (3.9300 bar). NOTE : The compressed air line must have an oil trap to make sure ____ that no oil gets into the Pitot probe. Install the Pitot probe (Ref. TASK 34-11-15-400-001).

  R EFF : 106-149, 201-249, 251-299, 301-399,  34-11-15 401-499, 501-509, 511-526, 528-599,   CES

 

Page 607 Feb 01/10

(c) External condition Make sure that the Pitot probe tube is not bent and has no holes or cracks. If you find damage, replace the Pitot probe. (d) Make sure that the drain holes are not blocked. If they are blocked, do the flushing of the total pressure lines: - for Pitot probe 1 and/or 2 (Ref. TASK 34-10-00-170-001) - for Pitot probe 3 (Ref. TASK 34-10-00-170-003) (only the standby total-pressure line part). (e) If the inspection/check is not satisfactory, replace the Pitot probe (Ref. TASK 34-11-15-000-001) and (Ref. TASK 34-11-15-400001). If the protective cover melted on the probe and the other criteria are correct, you must reject the Pitot probe. NOTE : If the Pitot probe is not in correct condition, you can do ____ a check of the probe in workshop during scheduled maintenance procedures (A or C Checks, etc.). Refer to the Inspection part of the CMM 341109. **ON A/C ALL 5. Close-up ________ Subtask 34-11-15-860-053 A. Put the aircraft back to its initial configuration. (1) Install the cover on the Pitot probe. (2) Make sure that the work area is clean and clear of tool(s) and other items. (3) Remove the access platform. Subtask 34-11-15-865-054 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 9DA1 3DA1 FOR 9DA2 3DA2

  EFF : ALL  34-11-15   R  CES

 

Page 608 Feb 01/10

FOR 9DA3 3DA3

  EFF : ALL  34-11-15   R  CES

 

Page 609 Nov 01/09

PROBE - STATIC (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3) - REMOVAL/INSTALLATION _____________________________________________________________________ TASK 34-11-16-000-001 Removal of the Static Probe (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3) WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE _______ OPENED, SAFETIED AND TAGGED. WARNING : MAKE SURE THAT: _______ - THE STATIC PROBE IS NOT HOT - THE ELECTRICAL SUPPLY TO THE HEATING ELEMENT OF THE PROBE IS ISOLATED BEFORE YOU START THE TASK. R R R R R R

WARNING : OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) _______ AND 5DA1(2,3) BEFORE YOU OPEN THE PHC CIRCUIT BREAKERS 2DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking plug circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

  EFF : ALL  34-11-16    CES

 

Page 401 Feb 01/10

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-099, 101-105, 151-158, 201-210, 34-11-16-991-001 R R

Fig. 401

**ON A/C 106-149, 159-199, 211-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-11-16-991-001-A

Fig. 401A

**ON A/C ALL 3. __________ Job Set-up Subtask 34-11-16-860-054 A. Aircraft Maintenance Configuration (1) Remove the protective covers from the sensors and the probes (AOA, static, Pitot and TAT). Subtask 34-11-16-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL FOR 7DA1, 8DA1

  EFF : ALL  34-11-16    CES

 

Page 402 Feb 01/10

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/AOA/1 4DA1 D04 49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12 FOR 7DA2, 8DA2 122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 FOR 7DA3, 8DA3 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 Subtask 34-11-16-865-061 C. Open, safety and tag this(these) circuit breaker(s):

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 7DA1, 8DA1 49VU ANTI ICE/PROBES/PHC/1 2DA1 D03 FOR 7DA2, 8DA2 122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12 FOR 7DA3, 8DA3 122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16 Subtask 34-11-16-010-050 D. Get Access (1) Put the access platform in position at the zone 128 for the static probes 7DA1, 8DA1, 7DA2 and 8DA2. (2) Put the access platform in position at the zone 120 for static probes 7DA3 and 8DA3. (3) Open the access door : FOR 7DA1, 8DA1, 7DA2, 8DA2 824 FOR 7DA3, 8DA3 811

  EFF : ALL  34-11-16    CES

 

Page 403 Feb 01/10

4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, 151-158, 201-210, (Ref. Fig. 401/TASK 34-11-16-991-001) R R

**ON A/C 106-149, 159-199, 211-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-11-16-991-001-A) **ON A/C 001-049, 051-099, 101-105, 151-158, 201-210, Subtask 34-11-16-020-050 A. Removal of the Static Probe NOTE : This procedure is the same for the six static probes. ____ (1) Remove the covers (12). (2) Remove the two nuts (8), the washers (10) and the bolts (11). (3) Disconnect the nut (1) and remove the static line (13). (4) Put a blanking plug on the nut (1). (5) Remove the union (2). (6) Remove the packing (4) and discard it. (7) Remove the four nuts (3). (8) Remove the static probe (5). (9) Remove the packing (6) and discard it. (10) Keep the bolts (7).

  R EFF : ALL  34-11-16    CES

 

Page 404 Feb 01/10

Static Probe Figure 401/TASK 34-11-16-991-001   R EFF : 001-049, 051-099, 101-105, 151-158,  34-11-16 201-210,   CES

 

Page 405 Feb 01/10

Static Probe Figure 401A/TASK 34-11-16-991-001-A   R EFF : 106-149, 159-199, 211-249, 251-299,  34-11-16 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 406 Feb 01/10

R R

**ON A/C 106-149, 159-199, 211-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-11-16-020-050-A A. Removal of the Static Probe NOTE : This procedure is the same for the six static probes. ____ (1) Remove the covers (12). (2) Remove the two nuts (8), the washers (10) and the bolts (11). (3) Disconnect the nut (1) and remove the static line (13). (4) Put a blanking plug on the nut (1). (5) Remove the union (2). (6) Remove the packing (4) and discard it. (7) Remove the four nuts (3). (8) Remove the washer (16) and the bonding strip (15). (9) Remove the static probe (5). (10) Remove the packing (6) and discard it. (11) Keep the bolts (7).

  R EFF : 106-149, 159-199, 211-249, 251-299,  34-11-16 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 407 Feb 01/10

**ON A/C ALL TASK 34-11-16-400-002 Installation of the Static Probe (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3) WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE _______ OPENED, SAFETIED AND TAGGED. CAUTION : MAKE SURE THAT: _______ - THERE IS NO SIGN OF CORROSION OR DAMAGE ON THE EQUIPMENT - THERE IS NO FOREIGN OBJECT IN THE EQUIPMENT TO PREVENT ANY DAMAGE IN THE SYSTEM. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

access platform 1.6 m (5 ft. 3 in.) Torque Wrench : range 0.00 to 1.20 m.daN (0.00 to 9.00 lbf.ft)

B. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------4 4 6 6

packing packing packing packing

34-11-01 34-11-01 34-11-01 34-11-01

  EFF : ALL  34-11-16   R  CES

 

02 -060 02A-060 02 -030 02A-030

Page 408 Nov 01/09

C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-912-004

Electrical Bonding of Components With Conductive Bolts and Screws and Bonding Straps in the Fuselage and in the Wings (this does not include the tanks)30-31-00-710-001 Operational Test of the Probe Ice Protection 34-11-16-710-001 Test of the Static Probe (7DA1,8DA1,7DA2,8DA2,7DA3,8DA3) without the CFDS. 34-13-00-790-002 Leak Test of the Principal Static and Total Air Data System 34-21-00-790-001 Low-Range Leak Test of the Standby Pneumatic Circuits 34-22-25-790-001 Low range Leak Test of the Standby Pneumatic circuits FOR FIN 7DA1, 8DA1, 7DA2, 8DA2 52-41-00-410-002 Close the Avionics Compartment Doors after Access 3. __________ Job Set-up Subtask 34-11-16-860-052 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at the zone 128 for the static probes 7DA1, 8DA1, 7DA2 and 8DA2. (2) Make sure that the access platform is in position at the zone 120 for the static probes 7DA3 and 8DA3. (3) Open the access door: FOR 7DA1, 8DA1, 7DA2, 8DA2 824 FOR 7DA3, 8DA3 811 R R

(4) Make sure that the protective covers of the sensors and probes (AOA, static Pitot and TAT) are removed.

  EFF : ALL  34-11-16    CES

 

Page 409 Nov 01/09

Subtask 34-11-16-865-055 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

4DA1 3DA1 5DA1 1DA1

D04 D02 Z13 Z12

1DA2 3DA2 4DA2 5DA2

Y15 Y14 Y13 Y11

3DA3 4DA3 5DA3

Z16 Z15 Z14

**ON A/C ALL FOR 7DA1, 8DA1 49VU ANTI ICE/PROBES/AOA/1 49VU ANTI ICE/PROBES/PITOT/1 122VU ANTI ICE/PROBES/1/STATIC 122VU ANTI ICE/PROBES/1/TAT FOR 7DA2, 8DA2 122VU ANTI ICE/PROBES/2/TAT 122VU ANTI ICE/PROBES/2/PITOT 122VU ANTI ICE/PROBES/2/AOA 122VU ANTI ICE/PROBES/2/STATIC FOR 7DA3, 8DA3 122VU ANTI ICE/PROBES/3/PITOT 122VU ANTI ICE/PROBES/3/AOA 122VU ANTI ICE/PROBES/3/STATIC Subtask 34-11-16-865-062 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 7DA1, 8DA1 49VU ANTI ICE/PROBES/PHC/1 2DA1 D03 FOR 7DA2, 8DA2 122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12 FOR 7DA3, 8DA3 122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16

  EFF : ALL  34-11-16    CES

 

Page 410 Feb 01/10

4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, 151-158, 201-210, Subtask 34-11-16-420-051 A. Installation of the Static Probe WARNING : IF YOU REPLACE STATIC PROBE 3 (7DA3 OR 8DA3), OR IF YOU REPLACE _______ MORE THAN ONE STATIC PROBE, YOU MUST DO A LEAK TEST ON THE RELATED CIRCUITS. NOTE : This procedure is the same for the six static probes. ____ (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Install a new packing (6). (4) Carefully engage the static probe (5) on the bolts (7). NOTE : The heating element must point to the nose of the aircraft for ____ static probes 7DA1, 8DA1, 7DA2 and 8DA2. It must point down for static probes 7DA3 and 8DA3. (5) Install the four nuts (3). (6) Tighten the nuts which are diagonally opposite (X sequence) and TORQUE them to 0.1 m.daN (8.84 lbf.in). (7) Install a new packing (4). (8) Install the union (2). (9) Remove the blanking plug from the nut (1). (10) Install the static line (13). (11) Connect the nut (1).

  EFF : ALL  34-11-16   R  CES

 

Page 411 Feb 01/10

(12) Install the lugs (9) on the terminals (14) with the bolts (11), the washers (10) and the nuts (8). NOTE : The covers (12) of the static probe (8DA2) must not touch the ____ static line. Thus, make sure that the lugs (9) connected to the terminals (14) are correctly installed as shown in the figure given in this procedure. (13) Install the covers (12). R R

**ON A/C 106-149, 159-199, 211-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-11-16-420-051-A A. Installation of the Static Probe WARNING : IF YOU REPLACE STATIC PROBE 3 (7DA3 OR 8DA3), OR IF YOU REPLACE _______ MORE THAN ONE STATIC PROBE, YOU MUST DO A LEAK TEST ON THE RELATED CIRCUITS. NOTE : This procedure is the same for the six static probes. ____ (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Install a new packing (6). (4) Carefully engage the static probe (5) on the bolts (7). NOTE : The heating element must point to the nose of the aircraft for ____ static probes 7DA1, 8DA1, 7DA2 and 8DA2. It must point down for static probes 7DA3 and 8DA3. (5) Install the bonding strip (15) and the washer (16) (Ref. TASK 20-2800-912-004). (6) Install the four nuts (3). (7) Tighten the nuts which are diagonally opposite (X sequence) and TORQUE them to 0.1 m.daN (8.84 lbf.in). (8) Install a new packing (4). (9) Install the union (2).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-16 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 412 Feb 01/10

(10) Remove the blanking plug from the nut (1). (11) Install the static line (13). (12) Connect the nut (1). (13) Install the lugs (9) on the terminals (14) with the bolts (11), the washers (10) and the nuts (8). NOTE : The covers (12) of the static probe (8DA2) must not touch the ____ static line. Thus, make sure that the lugs (9) connected to the terminals (14) are correctly installed as shown in the figure given in this procedure. (14) Install the covers (12). **ON A/C ALL Subtask 34-11-16-865-056 B. Remove the safety breaker(s): 5SQ1, 5SQ2 FOR 7DA1, 8DA1 1DA1, 2DA1, 3DA1, FOR 7DA2, 8DA2 1DA2, 2DA2, 3DA2, FOR 7DA3, 8DA3 2DA3, 3DA3, 4DA3,

clip(s) and the tag(s) and close this(these) circuit

4DA1, 5DA1 4DA2, 5DA2 5DA3

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, Subtask 34-11-16-790-051 C. Leak Test NOTE : The leak test is mandatory if you installed one static probe 3 ____ (7DA3 or 8DA3) or more than two static probes.

R

(1) Do a leak test of the main static system (Ref. TASK 34-13-00-790002). (2) Do a leak test of the standby static system (Ref. TASK 34-21-00-790-001).

  EFF : ALL  34-11-16    CES

 

Page 413 Feb 01/10

R R

**ON A/C 106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-11-16-790-051-A C. Leak Test NOTE : The leak test is mandatory if you installed one static probe 3 ____ (7DA3 or 8DA3) or more than two static probes. (1) Do a leak test of the main static system (Ref. TASK 34-13-00-790002). (2) Do a leak test of the standby air data system (Ref. TASK 34-22-25-790-001). **ON A/C ALL Subtask 34-11-16-710-052 D. Do an operational test of the Static Probe with the CFDS: Do the operational test of the Probe Ice Protection (Ref. TASK 30-31-00-710-001). NOTE : As an alternative procedure, you can do this operational test ____ without the CFDS (Ref. TASK 34-11-16-710-001). 5. Close-up ________ Subtask 34-11-16-410-051 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the FOR 7DA1, 824 (Ref. FOR 7DA3, 811

access door : 8DA1, 7DA2, 8DA2 TASK 52-41-00-410-002). 8DA3

(3) Install the protective covers on the sensors and probes (AOA, static, Pitot and TAT).

  EFF : ALL  34-11-16    CES

 

Page 414 Feb 01/10

(4) Remove the access platform(s).

  EFF : ALL  34-11-16   R  CES

 

Page 415 Feb 01/10

PROBE - STATIC (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3) - ADJUSTMENT/TEST ________________________________________________________________ TASK 34-11-16-710-001 Test of the Static Probe (7DA1,8DA1,7DA2,8DA2,7DA3,8DA3) without the CFDS. CAUTION : REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THE TEST. _______ CAUTION : DO NOT CONTINUE THE TEST FOR MORE THAN ONE MINUTE TO PREVENT DAMAGE _______ TO THE PROBES. WARNING : DO NOT TOUCH THE PROBES IMMEDIATELY AFTER THE TEST. _______ THEY ARE HOT AND CAN BURN YOU. 1. __________________ Reason for the Job Do this test after the removal/installation of the Static Probe (7DA1,8DA1,7DA2,8DA2,7DA3,8DA3) when the CFDS is unserviceable. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-11-16-860-050 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (ECAM only) (Ref. TASK 31-60-00-860-001).

  EFF : ALL  34-11-16    CES

 

Page 501 Feb 01/98

(3) Do the ADIRS start procedure for the related system: For 7DA1,8DA1 ADIRU1 For 7DA2,8DA2 ADIRU2 For 7DA3,8DA3 ADIRU3 (Ref. TASK 34-10-00-860-002). Subtask 34-11-16-865-054 B. Make sure that this(these) circuit breaker(s) is(are) closed:

R R R R R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 7DA1, 8DA1 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 FOR 7DA2, 8DA2 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 FOR 7DA3, 8DA3 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 4. Procedure _________ Subtask 34-11-16-710-051 A. Heating test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead panel, on the PROBE/WINDOW HEAT section of the panel 25VU : - push the AUTO pushbutton switch.

- the ON legend comes on.

2. On the circuit breaker panel 122VU : - Open the circuit breaker ANTI-ICE PROBES 1 STATIC-5DA1 or

- on the panels 131VU and 132VU, the MASTER CAUT lights come on. - you can hear the single chime.

  EFF : ALL  34-11-16    CES

 

Page 502 May 01/00

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------ANTI-ICE PROBES 2 STATIC-5DA2 - on the upper ECAM display unit, this or indication comes into view: ANTI-ICE PROBES 3 STATIC-5DA3. ANTI ICE CAPT L STAT (R STAT) or, ANTI ICE F/O L STAT (R STAT) or, ANTI ICE STBY L STAT (R STAT). 3. Close the circuit breaker(s) that you opened before.

- on the panels 131VU and 132VU, the MASTER CAUT lights go off. - on the upper ECAM display unit, the MEMO page comes into view.

4. On the overhead panel, on the PROBE/WINDOW HEAT section of the panel 25VU : - release the AUTO pushbutton switch.

- the ON legend goes off.

5. Close-up ________ Subtask 34-11-16-860-051 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF. (2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  EFF : ALL  34-11-16    CES

 

Page 503 Feb 01/98

PROBE - STATIC (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3) - INSPECTION/CHECK _________________________________________________________________ TASK 34-11-16-200-001 Inspection of the Static Probe (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3) WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE _______ OPENED, SAFETIED AND TAGGED. WARNING : MAKE SURE THAT: _______ - THE STATIC PROBE IS NOT HOT - THE ELECTRICAL SUPPLY TO THE HEATING ELEMENT OF THE PROBE IS ISOLATED BEFORE YOU START THE TASK. 1. __________________ Reason for the Job To do a visual inspection of the static probe. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific circuit breaker(s) safety clip(s) FOR FIN 7DA3, 8DA3 No specific access platform 1.6 m (5 ft. 3 in.) FOR FIN 7DA1, 7DA2, 8DA1, 8DA2 No specific access platform 1.6 m (5 ft. 3 in.) B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-11-16-000-001 34-11-16-400-002

Removal of the Static Probe (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3) Installation of the Static Probe (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3)

  EFF : ALL  34-11-16    CES

 

Page 601 Nov 01/07

3. __________ Job Set-up Subtask 34-11-16-865-059 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 7DA1, 8DA1 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 FOR 7DA2, 8DA2 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 FOR 7DA3, 8DA3 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 Subtask 34-11-16-010-051 B. Get Access (1) FOR 7DA1, 7DA2, 8DA1, 8DA2 - Put an access platform in position at the zone 128. (2) FOR 7DA3, 8DA3 - Put an access platform in position at the zone 120. 4. Procedure _________ Subtask 34-11-16-220-050 A. Inspection of the Static Probe ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Do the inspection of the static probes. A. For lightning strike damage.

Two marks are permitted.

If there are more than two marks, replace the static probe (Ref. TASK 34-11-16000-001) and (Ref. TASK 34-11-16-400-002).

A damage diameter or length of 1.5 mm (0.06

If the diameter or length of damage is more than 1.5

  EFF : ALL  34-11-16    CES

 

Page 602 Nov 01/07

------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------in.) is permitted. mm (0.06 in.), replace the static probe (Ref. TASK 34-11-16-000-001) and (Ref. TASK 34-11-16-400002). A damage depth of 0.15 mm (0.006 in.) is permitted.

If the depth of damage is more than 0.15 mm (0.006 in.), replace the static probe (Ref. TASK 34-11-16000-001) and (Ref. TASK 34-11-16-400-002).

The surface of the static probe is smooth.

If the surface of the static probe is not smooth, replace the static probe (Ref. TASK 34-11-16000-001) and (Ref. TASK 34-11-16-400-002).

5. Close-up ________ Subtask 34-11-16-410-053 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the access platform(s). Subtask 34-11-16-865-060 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 7DA1, 8DA1 5DA1. FOR 7DA2, 8DA2 5DA2. FOR 7DA3, 8DA3 5DA3.

  EFF : ALL  34-11-16    CES

 

Page 603 Nov 01/07

___________________________________________________________________ MODULE - AIR DATA (19FP1,19FP2,19FP3,19FP4,19FP5,19FP6,19FP7,19FP8) ____________________ REMOVAL/INSTALLATION TASK 34-11-17-000-001 Removal of the Air Data Module (19FP1,19FP2,19FP3,19FP4,19FP5,19FP6, 19FP7,19FP8) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No No

specific specific specific specific specific

blanking caps blanking plugs circuit breaker(s) safety clip(s) warning notice access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-061, 101-102, 151-199, 201-202, 34-11-17-991-001 R R

Fig. 401

**ON A/C 062-099, 103-149, 203-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-11-17-991-001-A

Fig. 401A

  EFF : ALL  34-11-17    CES

 

Page 401 Feb 01/10

R

**ON A/C ALL 3. __________ Job Set-up Subtask 34-11-17-010-050 A. Get Access (1) Put the access platform in position : (a) In the zone 123 for the Total Pressure ADM 19FP1 and 19FP3. (b) In the zone 122 for the Total Pressure ADM 19FP2. (c) In the zone 128 for the Static Pressure ADM 19FP4, 19FP5, 19FP6 and 19FP7. (d) In zone 110 for the Static Pressure ADM 19FP8. (e) At the access door 822. (2) Open the access door : FOR 19FP1, 19FP3 812 FOR 19FP2 822 FOR 19FP5, 19FP7 824 FOR 19FP8 811 FOR 19FP4, 19FP6 824 (3) Open the access door 822. (4) On the battery power center 105VU: -loosen the two screws and remove the protective cover.

  EFF : ALL  34-11-17    CES

 

Page 402 May 01/99

Subtask 34-11-17-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 19FP1, 19FP4, 19FP5 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 FOR 19FP2, 19FP6, 19FP7 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/2/115VAC 121VU ADIRS/ADIRU/2/28VDC R R

4FP2 6FP2

N07 N05

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/2/115VAC 121VU ADIRS/ADIRU/2/28VDC

4FP2 6FP2

N06 N04

4FP3 6FP3

N06 N04

**ON A/C ALL FOR 19FP3, 19FP8 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/3/115VAC 121VU ADIRS/ADIRU/3/28VDC R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/3/115VAC 121VU ADIRS/ADIRU/3/28VDC

4FP3 6FP3

  EFF : ALL  34-11-17    CES

 

N05 N03

Page 403 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 051-061, 101-102, 151-199, 201-202, (Ref. Fig. 401/TASK 34-11-17-991-001) R R

**ON A/C 062-099, 103-149, 203-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-11-17-991-001-A) **ON A/C ALL Subtask 34-11-17-020-050 A. Removal of the ADM (1) Precaution : NOTE : During the removal of the Static Pressure ADM 19FP4 and 19FP6, ____ you must close the door 824. Before you close, put a warning notice in position to tell persons not to open the door. (2) Disconnect the electrical connector (7). (3) Disconnect the quick-disconnect coupling (6). (4) Put blanking caps on the disconnected electrical connectors (7) and (8). (5) Put blanking plugs on the disconnected quick-disconnect couplings (5) and (6). (6) Remove the four screws (3) and the washers (4); when you do this, hold the ADM (2). (7) Remove the ADM (2).

  EFF : ALL  34-11-17    CES

 

Page 404 Feb 01/10

INTENTIONALLY BLANK

  R   34-11-17    CES

 

Page 405 Feb 01/00

Pressure ADM Figure 401/TASK 34-11-17-991-001- 12 (SHEET 1)   R EFF : 001-049, 051-061, 101-102, 151-199,  34-11-17 201-202,   CES

 

Page 406 Nov 01/06

Pressure ADM Figure 401/TASK 34-11-17-991-001- 22 (SHEET 2)   R EFF : 001-049, 051-061, 101-102, 151-199,  34-11-17 201-202,   CES

 

Page 407 Nov 01/06

Pressure ADM Figure 401A/TASK 34-11-17-991-001-A12 (SHEET 1)   R EFF : 062-099, 103-149, 203-249, 251-299,  34-11-17 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 408 Feb 01/10

Pressure ADM Figure 401A/TASK 34-11-17-991-001-A22 (SHEET 2)   R EFF : 062-099, 103-149, 203-249, 251-299,  34-11-17 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 409 Feb 01/10

TASK 34-11-17-400-001 Installation of the Air Data Module (19FP1,19FP2,19FP3,19FP4,19FP5,19FP6, 19FP7,19FP8) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

warning notice access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-11-17-710-001 34-13-00-740-003 52-41-00-010-002 52-41-00-410-002

Test of the Air Data Module without the CFDS SYSTEM TEST of the ADR Open the Avionics Compartment Doors for Access Close the Avionics Compartment Doors after Access

**ON A/C 001-049, 051-061, 101-102, 151-199, 201-202, 34-11-17-991-001 R R

Fig. 401

**ON A/C 062-099, 103-149, 203-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-11-17-991-001-A

Fig. 401A

**ON A/C ALL 34-11-17-991-002 Fig. 402 FOR FIN 19FP4, 19FP5, 19FP6, 19FP7 52-41-00-410-002 Close the Avionics Compartment Doors after Access

  EFF : ALL  34-11-17    CES

 

Page 410 Feb 01/10

3. __________ Job Set-up Subtask 34-11-17-860-050 A. Get Access NOTE : During the installation of the Static Pressure ADM 19FP4 and ____ 19FP6, you must close the door 824. Before you close it, put a warning notice in position to tell persons not to open the door.

R R

(1) Make sure that the access platform are in position: (a) In the zone 123 for the Total Pressure ADM 19FP1 and 19FP3. (b) In the zone 122 for the Total Pressure ADM 19FP2. (c) In the zone 128 for the Static Pressure ADM 19FP4, 19FP5, 19FP6 and 19FP7. (d) In zone 110 for the Static Pressure ADM 19FP8. (e) At the access door 822. R

(2) Make sure that the access door are open (Ref. TASK 52-41-00-010-002): FOR 19FP1, 19FP3 812 FOR 19FP2 822 FOR 19FP5, 19FP7 824 FOR 19FP8 811 FOR 19FP4, 19FP6 824 (3) Make sure that the protective cover is removed from the battery power center 105VU. (4) Clean the component interface and/or the adjacent area. (5) Do an inspection of the component interface and/or the adjacent area.

  EFF : ALL  34-11-17    CES

 

Page 411 Aug 01/07

Subtask 34-11-17-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 19FP1, 19FP4, 19FP5 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 FOR 19FP2, 19FP6, 19FP7 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/2/115VAC 121VU ADIRS/ADIRU/2/28VDC R R

4FP2 6FP2

N07 N05

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/2/115VAC 121VU ADIRS/ADIRU/2/28VDC

4FP2 6FP2

N06 N04

4FP3 6FP3

N06 N04

**ON A/C ALL FOR 19FP3, 19FP8 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/3/115VAC 121VU ADIRS/ADIRU/3/28VDC R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/3/115VAC 121VU ADIRS/ADIRU/3/28VDC

4FP3 6FP3

  EFF : ALL  34-11-17    CES

 

N05 N03

Page 412 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 051-061, 101-102, 151-199, 201-202, (Ref. Fig. 401/TASK 34-11-17-991-001) R R

**ON A/C 062-099, 103-149, 203-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-11-17-991-001-A) **ON A/C ALL Subtask 34-11-17-420-050 A. Installation of the ADM (1) Put the ADM (2) in position on its support and hold it in this position. (2) Attach the ADM (2) with the four screws (3) and the washers (4). (3) Remove the blanking caps from the disconnected electrical connectors (7) and (8). (4) Make sure that the electrical connectors are in the correct condition. (5) Connect the electrical connector (7). (6) Remove the blanking plugs from the disconnected quick-disconnect couplings (5) and (6). (7) Make sure that the quick-disconnect coupling are in the correct condition. (8) Connect the quick-disconnect coupling (6). (Ref. Fig. 402/TASK 34-11-17-991-002) (9) Make sure that you can see the blue ring on the quick-disconnect coupling.

  EFF : ALL  34-11-17    CES

 

Page 413 Feb 01/10

R R

Illustration of the Quick-Disconnect coupling Figure 402/TASK 34-11-17-991-002

  EFF : ALL  34-11-17    CES

 

Page 414 Feb 01/07

(10) Pull the quick-disconnect coupling to be sure that it is correctly attached. R R R R

WARNING : IF YOU REPLACE MORE THAN ONE ADM, MAKE SURE THAT A SECOND _______ QUALIFIED MECHANIC DOES A VISUAL INSPECTION OF THE QUICKDISCONNECT COUPLING CONNECTION. THE TWO MECHANICS MUST SIGN OFF THE JOB. Subtask 34-11-17-710-050 B. Do the SYSTEM TEST of the ADR with the CFDS (Ref. TASK 34-13-00-740-003). NOTE : As an alternative procedure, you can do this operational test ____ without the CFDS (Ref. TASK 34-11-17-710-001). 5. Close-up ________ Subtask 34-11-17-410-050 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the access door (Ref. TASK 52-41-00-410-002): FOR 19FP1, 19FP3 812 FOR 19FP2 822 FOR 19FP4, 19FP5, 19FP6, 19FP7 824 (Ref. TASK 52-41-00-410-002) FOR 19FP8 811 (3) Remove the warning notice(s). (4) Install the protective cover on the battery power center 105VU. (5) Tighten the two screws. (6) Close the access door 822. (7) Remove the access platform(s).

  EFF : ALL  34-11-17    CES

 

Page 415 Feb 01/09

___________________________________________________________________ MODULE - AIR DATA (19FP1,19FP2,19FP3,19FP4,19FP5,19FP6,19FP7,19FP8) _______________ ADJUSTMENT/TEST TASK 34-11-17-710-001 Test of the Air Data Module without the CFDS 1. __________________ Reason for the Job Do this test after the removal/installation of the Air Data Module when the CFDS is unserviceable. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure ADIRS Start Procedure ADIRS Stop Procedure

  EFF : ALL  34-11-17    CES

 

Page 501 Feb 01/98

3. __________ Job Set-up Subtask 34-11-17-860-051 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (ADIRU related to the installed ADM only) (Ref. TASK 34-10-00-860-002) (3) Do the EIS start procedure (PFD only). (Ref. TASK 31-60-00-860-001) Subtask 34-11-17-010-051 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-11-17-865-053 C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 R

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

4FP2 4FP3 6FP2 6FP3

  EFF : ALL  34-11-17    CES

 

N07 N06 N05 N04

Page 502 May 01/05

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

4FP2 4FP3 6FP2 6FP3

N06 N05 N04 N03

**ON A/C ALL 4. Procedure _________ Subtask 34-11-17-710-051 A. Make sure that the PFD of the onside ADIRU related to the installed ADM shows the correct altitude (the ALT flag goes out of view and the SPD flag goes out of view on the speed scale). NOTE : To do the check of the altitude display with the ADIRU3 set the ____ AIR DATA selector switch to CAPT/3 (F/O/3) on the SWITCHING panel 8VU. 5. Close-up ________ Subtask 34-11-17-860-052 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005). (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-11-17-410-051 B. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822.

  EFF : ALL  34-11-17    CES

 

Page 503 Feb 01/10

(4) Remove the access platform(s).

  EFF : ALL  34-11-17    CES

 

Page 504 Feb 01/00

SENSOR - TOTAL AIR TEMPERATURE (11FP1,11FP2) - REMOVAL/INSTALLATION ___________________________________________________________________ TASK 34-11-18-000-001 Removal of the TAT Sensor (11FP1, 11FP2) WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE _______ OPENED, SAFETIED AND TAGGED. R R R R R R

WARNING : OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) _______ AND 5DA1(2,3) BEFORE YOU OPEN THE PHC CIRCUIT BREAKERS 2DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 1 m (3 ft. 3 in.)

  EFF : ALL  34-11-18    CES

 

Page 401 Feb 01/10

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-310, 401-499, 34-11-18-991-001 R

Fig. 401

**ON A/C 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 34-11-18-991-001-A

Fig. 401A

**ON A/C ALL 3. __________ Job Set-up Subtask 34-11-18-860-058 A. Aircraft Maintenance Configuration (1) Remove the protective covers from the sensors and the probes (AOA, static, Pitot and AOA). Subtask 34-11-18-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL FOR 11FP1

  EFF : ALL  34-11-18    CES

 

Page 402 Feb 01/10

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/AOA/1 4DA1 D04 49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/3/115VAC R R

4FP3

N06

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/3/115VAC

4FP3

N05

5DA1 1DA1

Z13 Z12

4FP2

N07

**ON A/C ALL 122VU ANTI ICE/PROBES/1/STATIC 122VU ANTI ICE/PROBES/1/TAT FOR 11FP2 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/2/115VAC R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/2/115VAC

4FP2

N06

1DA2 3DA2 4DA2 5DA2

Y15 Y14 Y13 Y11

**ON A/C ALL 122VU 122VU 122VU 122VU

ANTI ANTI ANTI ANTI

ICE/PROBES/2/TAT ICE/PROBES/2/PITOT ICE/PROBES/2/AOA ICE/PROBES/2/STATIC

  EFF : ALL  34-11-18    CES

 

Page 403 Feb 01/10

Subtask 34-11-18-865-056 C. Open, safety and tag this(these) circuit breaker(s):

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 11FP1 49VU ANTI ICE/PROBES/PHC/1 2DA1 D03 FOR 11FP2 122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12 Subtask 34-11-18-860-052 D. Put the access platform in position at zone 120. 4. Procedure _________ **ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-310, 401-499, (Ref. Fig. 401/TASK 34-11-18-991-001)

R

**ON A/C 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-11-18-991-001-A) **ON A/C ALL Subtask 34-11-18-020-051 A. Removal of the TAT Sensor (11FP1, 11FP2) (1) Loosen the six screws (6). (2) Pull the sensor (5) from its housing (2). (3) Hold the sensor (5) and disconnect the connector (1). (4) Put blanking caps on the disconnected electrical connectors (1) and (4). (5) Remove the sensor (5). (6) Remove and discard the seal (3).

  EFF : ALL  34-11-18    CES

 

Page 404 Feb 01/10

Total Air Temperature (TAT) Sensor Figure 401/TASK 34-11-18-991-001   R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-18 201-238, 301-310, 401-499,   CES

 

Page 405 Nov 01/09

Total Air Temperature (TAT) Sensor Figure 401A/TASK 34-11-18-991-001-A   R EFF : 239-249, 251-299, 311-399, 501-509,  34-11-18 511-526, 528-599,   CES

 

Page 406 Feb 01/10

TASK 34-11-18-400-001 Installation of the TAT Sensor (11FP1, 11FP2) WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE _______ OPENED, SAFETIED AND TAGGED. CAUTION : MAKE SURE THAT: _______ - THERE IS NO SIGN OF CORROSION OR DAMAGE ON THE EQUIPMENT - THERE IS NO FOREIGN OBJECT IN THE EQUIPMENT TO PREVENT ANY DAMAGE IN THE SYSTEM. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------3

seal

34-11-01 01 -040

R

  EFF : ALL  34-11-18    CES

 

Page 407 May 01/08

C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-720-005 24-41-00-861-002 24-41-00-862-002 30-31-00-710-001 34-11-18-710-001

Check of the Electrical Bonding of the Different Components (But not the Fluid Systems and the Components Installed on Composite materials) Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Operational Test of the Probe Ice Protection Test of the TAT Sensor (11FP1, 11FP2) without the CFDS

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-310, 401-499, 34-11-18-991-001 R

Fig. 401

**ON A/C 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 34-11-18-991-001-A

Fig. 401A

**ON A/C ALL 3. __________ Job Set-up Subtask 34-11-18-860-054 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at zone 120. (2) Make sure that the protective covers of the sensors and probes (AOA, static Pitot and TAT) are removed.

  EFF : ALL  34-11-18    CES

 

Page 408 Feb 01/10

Subtask 34-11-18-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

4DA1 3DA1 4FP1

D04 D02 F06

4FP3

N06

**ON A/C ALL FOR 11FP1 49VU ANTI ICE/PROBES/AOA/1 49VU ANTI ICE/PROBES/PITOT/1 49VU NAV PROBES/ADIRU1/115VAC **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/3/115VAC R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/3/115VAC

4FP3

N05

5DA1 1DA1

Z13 Z12

4FP2

N07

**ON A/C ALL 122VU ANTI ICE/PROBES/1/STATIC 122VU ANTI ICE/PROBES/1/TAT FOR 11FP2 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/2/115VAC

  EFF : ALL  34-11-18    CES

 

Page 409 Feb 01/10

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/2/115VAC

4FP2

N06

1DA2 3DA2 4DA2 5DA2

Y15 Y14 Y13 Y11

**ON A/C ALL 122VU 122VU 122VU 122VU

ANTI ANTI ANTI ANTI

ICE/PROBES/2/TAT ICE/PROBES/2/PITOT ICE/PROBES/2/AOA ICE/PROBES/2/STATIC

Subtask 34-11-18-865-057 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 11FP1 49VU ANTI ICE/PROBES/PHC/1 2DA1 D03 FOR 11FP2 122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12 4. Procedure _________ **ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-310, 401-499, (Ref. Fig. 401/TASK 34-11-18-991-001)

R

**ON A/C 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-11-18-991-001-A)

  EFF : ALL  34-11-18    CES

 

Page 410 Feb 01/10

**ON A/C ALL Subtask 34-11-18-420-051 A. Installation of the TAT Sensor (11FP1, 11FP2) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Install the new seal (3) on the sensor (5). (4) Remove the blanking caps from the connectors (1) and (4). (5) Make sure that the electrical connectors are clean and in the correct condition. (6) Connect the connector (1) to the sensor (5) out of the housing (2). (7) Install the sensor (5) in its housing (2) and hold it. NOTE : Make sure that the seal (3) is in the correct position. ____ (8) Tighten the six screws (6). (9) Check the bonding contact resistance between the TAT Sensor (5) and the fuselage structure (2) (Ref. TASK 20-28-00-720-005). Subtask 34-11-18-860-053 B. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 34-11-18-865-052 C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5SQ1, 5SQ2 FOR 11FP1 4FP1, 4FP3, 1DA1, 2DA1, 3DA1, 4DA1, 5DA1 FOR 11FP2 4FP2, 1DA2, 2DA2, 3DA2, 4DA2, 5DA2

  EFF : ALL  34-11-18   R  CES

 

Page 411 Nov 01/09

R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 401-499, Subtask 34-11-18-710-050-A D. Do the operational test of the TAT sensor with the CFDS. (1) Do the operational test of the Probe Ice Protection. (Ref. TASK 30-31-00-710-001) (2) Do the operational test of the CURRENT STATUS: NOTE : The TAT sensor 1 is related to the ADIRU 1 and 3. The TAT ____ sensor 2 is related to the ADIRU 2. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center pedestal, on one MCDU:

On the MCDU:

- push the MCDU MENU mode key.

- the MCDU MENU page comes into view.

- push the line key adjacent to the CFDS indication.

- the CFDS MENU page comes into view.

- push the line key adjacent to the SYSTEM REPORT/TEST indication.

- the SYSTEM REPORT/TEST page comes into view.

- push the line key adjacent to the NAV indication.

- the SYSTEM REPORT/TEST NAV page comes into view.

- push the line key adjacent to the ADR1 (ADR2) (ADR3) indication (related to the removed TAT sensor).

- the ADR1 (ADR2) (ADR3) page comes into view.

- push the line key adjacent to the CURRENT STATUS indication.

- the CURRENT STATUS page comes into view.

- push NEXT PAGE key until you get ADR1 (ADR2) (ADR3)/CURRENT STATUS pages 5/8 and 7/8.

- CURRENT STATUS pages 5/8 and 7/8 come into view: do a check of the TAT data (OPEN, XXX DEGC).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-18 201-233, 236-238, 401-499,   CES

 

Page 412 Nov 01/09

NOTE : As an alternative procedure, you can do this operational test ____ without the CFDS (Ref. TASK 34-11-18-710-001). R

**ON A/C 234-235, 239-249, 251-299, 501-509, 511-526, 528-599, Subtask 34-11-18-710-050-B D. Do the operational test of the TAT sensor with the CFDS. (1) Do the operational test of the Probe Ice Protection. (Ref. TASK 30-31-00-710-001) (2) Do the operational test of the INPUT STATUS: NOTE : The TAT sensor 1 is related to the ADIRU 1 and 3. The TAT ____ sensor 2 is related to the ADIRU 2. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center pedestal, on one MCDU:

On the MCDU:

- push the MCDU MENU mode key.

- the MCDU MENU page comes into view.

- push the line key adjacent to the CFDS indication.

- the CFDS MENU page comes into view.

- push the line key adjacent to the SYSTEM REPORT/TEST indication.

- the SYSTEM REPORT/TEST page comes into view.

- push the line key adjacent to the NAV indication.

- the SYSTEM REPORT/TEST NAV page comes into view.

- push the line key adjacent to the ADR1 (ADR2) (ADR3) indication (related to the removed TAT sensor).

- the ADR1 (ADR2) (ADR3) page comes into view.

- push the line key adjacent to the INPUT STATUS indication.

- the INPUT STATUS page comes into view.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-18 201-249, 251-299, 401-499, 501-509, 511-526,  528-599, CES

 

Page 413 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push NEXT PAGE key until you - INPUT STATUS pages 3/8 and 7/8 come get ADR1 (ADR2) (ADR3)/INPUT into view: STATUS pages 3/8 and 7/8. do a check of the TAT data (OPEN, XXX ⁰ C). NOTE : As an alternative procedure, you can do this operational test ____ without the CFDS (Ref. TASK 34-11-18-710-001). **ON A/C 301-399, Subtask 34-11-18-710-050 D. Do the operational test of the TAT sensor with the CFDS. (1) Do the operational test of the Probe Ice Protection. (Ref. TASK 30-31-00-710-001) (2) Do the operational test of the CURRENT STATUS: NOTE : The TAT sensor 1 is related to the ADIRU 1 and 3. The TAT ____ sensor 2 is related to the ADIRU 2. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center pedestal, on one MCDU:

On the MCDU:

- push the MCDU MENU mode key.

- the MCDU MENU page comes into view.

- push the line key adjacent to the CFDS indication.

- the CFDS MENU page comes into view.

- push the line key adjacent to the SYSTEM REPORT/TEST indication.

- the SYSTEM REPORT/TEST page comes into view.

- push the line key adjacent to the NAV indication.

- the SYSTEM REPORT/TEST NAV page comes into view.

  R EFF : 234-235, 239-249, 251-299, 301-399,  34-11-18 501-509, 511-526, 528-599,   CES

 

Page 414 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the ADIRS ADR1 (ADR2) (ADR3) 1/2 page the ADR1 (ADR2) (ADR3) comes into view. indication (related to the removed TAT sensor). - push the line key adjacent to the CURRENT STATUS indication.

- the CURRENT STATUS page comes into view. - if you found no defect after the installation of the new sensor, the NO FAULTS indication comes into view.

NOTE : As an alternative procedure, you can do this operational test ____ without the CFDS (Ref. TASK 34-11-18-710-001). **ON A/C ALL 5. Close-up ________ Subtask 34-11-18-860-055 A. Put the aircraft back to its initial configuration. (1) On the MCDU , push the MCDU MENU mode key. (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). (3) Make sure that the work area is clean and clear of tool(s) and other items. R R

(4) Install the protective covers on the sensors and probes (AOA, static, Pitot and TAT).

R

(5) Remove the access platform(s).

  EFF : ALL  34-11-18    CES

 

Page 415 Nov 01/09

SENSOR - TOTAL AIR TEMPERATURE (11FP1,11FP2) - ADJUSTMENT/TEST ______________________________________________________________ TASK 34-11-18-710-001 Test of the TAT Sensor (11FP1, 11FP2) without the CFDS 1. __________________ Reason for the Job Do this test after the removal/installation of the TAT Sensor (11FP1,11FP2) when the CFDS is unserviceable. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power ADIRS Stop Procedure

24-41-00-862-002 34-10-00-860-005 FOR FIN 11FP2 31-60-00-860-001 34-10-00-860-002

EIS Start Procedure ADIRS Start Procedure

3. __________ Job Set-up R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, Subtask 34-11-18-860-051 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS FOR 11FP1 Lower ECAM FOR 11FP2 Lower ECAM (Ref. TASK

start procedure DU and CAPT ND only DU only 31-60-00-860-001).

  EFF : ALL  34-11-18    CES

 

Page 501 Feb 01/09

(3) Do the ADIRS start procedure FOR 11FP1 ADIRU 1 and 3 only FOR 11FP2 ADIRU 2 only (Ref. TASK 34-10-00-860-002). R R

**ON A/C 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-11-18-860-051-A A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure FOR 11FP1 Lower ECAM DU and CAPT ND only FOR 11FP2 F/O ND only (Ref. TASK 31-60-00-860-001). (3) Do the ADIRS start procedure FOR 11FP1 ADIRU 1 and 3 only FOR 11FP2 ADIRU 2 only (Ref. TASK 34-10-00-860-002).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-11-18 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 502 Feb 01/10

**ON A/C ALL Subtask 34-11-18-865-053 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 11FP1 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/3/115VAC R R

4FP3

N06

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/3/115VAC

4FP3

N05

1DA1

Z12

4FP2

N07

**ON A/C ALL 122VU ANTI ICE/PROBES/1/TAT FOR 11FP2 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/2/115VAC R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/2/115VAC

4FP2

N06

1DA2

Y15

**ON A/C ALL 122VU ANTI ICE/PROBES/2/TAT

  EFF : ALL  34-11-18    CES

 

Page 503 Feb 01/10

4. Procedure _________ R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, Subtask 34-11-18-710-051 A. Test of the TAT Sensor (1) Operational test of the TAT sensor 11FP1: ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the SWITCHING panel 8VU: - set the ECAM/ND XFR selector switch to CAPT.

- the display of the lower ECAM DU moves to the CAPT ND. - make sure that the SAT and TAT indications are shown at the bottom of the CAPT ND, on the left side.

- set the AIR DATA selector switch to CAPT/3.

- make sure that the SAT and TAT indications stay in view on the CAPT ND.

- set the ECAM/ND XFR and AIR DATA selector switches to NORM. (2) Operational test of the TAT sensor 11FP2: - Make sure that the SAT and TAT indications are shown at the bottom section of the lower ECAM DU, on the left side.

  EFF : ALL  34-11-18    CES

 

Page 504 Feb 01/09

R R

**ON A/C 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-11-18-710-051-A A. Test of the TAT Sensor (1) Operational test of the TAT sensor 11FP1: ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the SWITCHING panel 8VU: - make sure that the selector switches are at the NORM position.

On the lower ECAM DU: - the TAT indication is shown at the bottom section of the lower ECAM DU, on the left side.

- set the ECAM/ND XFR selector switch to CAPT.

- the display of the lower ECAM DU moves to the CAPT ND. - make sure that the SAT and TAT indications are shown at the bottom of the CAPT ND, on the left side.

- set the ECAM/ND XFR selector switch to NORM. - set the AIR DATA selector switch to CAPT/3.

- make sure that the SAT and TAT indications are shown at the bottom section of the lower ECAM DU, on the left side (from ADIRU 3).

- set the ECAM/ND XFR selector switch to F/O. - set the AIR DATA selector switches to F/O/3.

- make sure that the SAT and TAT indications are shown at the bottom of the F/O ND, on the left side (from ADIRU 3).

- set the ECAM/ND XFR selector switch to NORM. - set the AIR DATA selector switches to NORM.. (2) Operational test of the TAT sensor 11FP2: (a) set the ECAM/ND XFR selector switch to F/O. - make sure that the SAT and TAT indications are shown at the bottom of the F/O ND, on the left side.

  R EFF : 234-235, 239-249, 251-299, 305-399,  34-11-18 401-499, 501-509, 511-526, 528-599,   CES

 

Page 505 Feb 01/10

(b) set the ECAM/ND XFR selector switch to NORM. **ON A/C ALL 5. Close-up ________ Subtask 34-11-18-860-050 A. Put the aircraft back to its initial configuration. R

(1) Do the ADIRS Stop Procedure (Ref. TASK 34-10-00-860-005).

R R

(2) On the center pedestal, on the ECAM control panel, set the LOWER DISPLAY potentiometer to OFF. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-11-18    CES

 

Page 506 May 01/09

SENSOR - TOTAL AIR TEMPERATURE (11FP1,11FP2) - INSPECTION/CHECK _______________________________________________________________ TASK 34-11-18-200-002 Inspection/Check of the TAT Sensor (11FP1, 11FP2) 1. __________________ Reason for the Job The purpose of this Task is to do a Visual Inspection of the TAT sensor 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 0.30 m (12 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-11-18-000-001 34-11-18-400-001

Removal of the TAT Sensor (11FP1, 11FP2) (for corrective action) Installation of the TAT Sensor (11FP1, 11FP2) (for corrective action)

  EFF : ALL  34-11-18    CES

 

Page 601 Nov 01/06

3. __________ Job Set-up Subtask 34-11-18-865-054 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

4DA1 2DA1 3DA1 4FP1

D04 D03 D02 F06

4FP3

N06

**ON A/C ALL FOR 11FP1 49VU ANTI ICE/PROBES/AOA/1 49VU ANTI ICE/PROBES/PHC/1 49VU ANTI ICE/PROBES/PITOT/1 49VU NAV PROBES/ADIRU1/115VAC **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/3/115VAC R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/3/115VAC

4FP3

N05

5DA1 1DA1

Z13 Z12

4FP2

N07

**ON A/C ALL 122VU ANTI ICE/PROBES/1/STATIC 122VU ANTI ICE/PROBES/1/TAT FOR 11FP2 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/2/115VAC

  EFF : ALL  34-11-18    CES

 

Page 602 Feb 01/10

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/2/115VAC

4FP2

N06

1DA2 3DA2 4DA2 2DA2 5DA2

Y15 Y14 Y13 Y12 Y11

**ON A/C ALL

R

122VU 122VU 122VU 122VU 122VU

ANTI ANTI ANTI ANTI ANTI

ICE/PROBES/2/TAT ICE/PROBES/2/PITOT ICE/PROBES/2/AOA ICE/PROBES/PHC/2 ICE/PROBES/2/STATIC

Subtask 34-11-18-860-056 B. Get Access (1) Put an access platform in position in zone 120. (2) Remove the TAT sensor slip-on cover. 4. Procedure _________ Subtask 34-11-18-220-050 A. Inspection/Check of the TAT sensors (11FP1, 11FP2) (1) Do a general visual inspection of the TAT sensors. (a) Color During the ageing of the sensor, the color of the sensor becomes brownish and/or blackish. This coloration has no effect on the operation of the sensor. (b) Internal Obstruction CAUTION : DO NOT USE SHARP AND/OR METAL TOOLS OR OBJECTS TO CLEAN _______ THE TAT SENSOR. SUCH TOOLS OR OBJECTS CAN CAUSE DAMAGE TO THE TAT SENSOR. Make sure that the TAT sensor is not clogged. If the TAT sensor is clogged, remove it (Ref. TASK 34-11-18-000001).

  EFF : ALL  34-11-18    CES

 

Page 603 Feb 01/10

- Clean the TAT sensor as described in CMM 341863. - Reinstall the TAT sensor (Ref. TASK 34-11-18-400-001). NOTE : If the TAT sensor is not in correct condition (oxidation, ____ impact mark, crack, ...), refer to the visual inspection part of the CMM 341863. 5. Close-up ________ Subtask 34-11-18-865-055 A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5SQ1, 5SQ2 FOR 11FP1 4FP1, 4FP3, 1DA1, 2DA1, 3DA1, 4DA1, 5DA1 FOR 11FP2 4FP2, 1DA2, 2DA2, 3DA2, 4DA2, 5DA2 Subtask 34-11-18-860-057 B. Put the aircraft back to its initial configuration. (1) Install the TAT sensor slip-on cover. (2) Make sure that the work area is clean and clear of tool(s) and other items. (3) Remove the access platform(s).

  EFF : ALL  34-11-18   R  CES

 

Page 604 Aug 01/09

SENSOR - ANGLE OF ATTACK (3FP1,3FP2,3FP3) - REMOVAL/INSTALLATION ________________________________________________________________ TASK 34-11-19-000-001 Removal of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3) R R R R R R

WARNING : OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) _______ AND 5DA1(2,3) BEFORE YOU OPEN THE PHC CIRCUIT BREAKERS 2DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 3.4 m (11 ft. 2 in.)

3. __________ Job Set-up Subtask 34-11-19-860-056 A. Aircraft Maintenance Configuration (1) Remove the protective covers from the sensors and the probes (AOA, static, Pitot and TAT).

  EFF : ALL  34-11-19    CES

 

Page 401 Feb 01/10

Subtask 34-11-19-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3FP1 49VU ANTI ICE/PROBES/AOA/1 4DA1 D04 49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/3PWR/SWTG R R

9FP

N10

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/3PWR/SWTG

9FP

N09

5DA1 1DA1

Z13 Z12

10FP 5FP2 4FP2

N11 N09 N07

**ON A/C ALL 122VU ANTI ICE/PROBES/1/STATIC 122VU ANTI ICE/PROBES/1/TAT FOR 3FP2 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/2PWR/SHED 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/2PWR/SHED 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC

10FP 5FP2 4FP2

  EFF : ALL  34-11-19    CES

 

N10 N08 N06

Page 402 Feb 01/10

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C ALL 122VU ANTI 122VU ANTI 122VU ANTI 122VU ANTI FOR 3FP3

ICE/PROBES/2/TAT ICE/PROBES/2/PITOT ICE/PROBES/2/AOA ICE/PROBES/2/STATIC

1DA2 3DA2 4DA2 5DA2

Y15 Y14 Y13 Y11

9FP 5FP3 4FP3

N10 N08 N06

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/3/115VAC R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/3/115VAC

9FP 5FP3 4FP3

N09 N07 N05

3DA3 4DA3 5DA3

Z16 Z15 Z14

**ON A/C ALL 122VU ANTI ICE/PROBES/3/PITOT 122VU ANTI ICE/PROBES/3/AOA 122VU ANTI ICE/PROBES/3/STATIC Subtask 34-11-19-865-055 C. Open, safety and tag this(these) circuit breaker(s):

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3FP1 49VU ANTI ICE/PROBES/PHC/1 2DA1 D03 FOR 3FP2 122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12 FOR 3FP3 122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16

  EFF : ALL  34-11-19    CES

 

Page 403 Feb 01/10

Subtask 34-11-19-860-050 D. Put an access platform in position in zone 231 for 3FP1 (232 for 3FP2) (127 for 3FP3). 4. Procedure _________ Subtask 34-11-19-020-050 A. Removal of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3) CAUTION : DO NOT HOLD THE AOA SENSOR BY THE VANE WHEN YOU MOVE IT. IF YOU _______ DO, YOU CAN CAUSE DAMAGE TO THE AOA SENSOR. NOTE : The procedure is the same for angle of attack sensors 3FP1, 3FP2 ____ and 3FP3. (1) Remove the potting compound from the screw (6). (2) Loosen the seven screws (8). (3) Remove the blanking plate (7). (4) Remove the screw (6). NOTE : Carefully remove the plate so as not to cause damage to the ____ sensor (5). (5) Disengage and hold the sensor (5). (6) Disconnect the connector (1). (7) Remove the angle of attack sensor (5). (8) Remove and discard the seal (3). (9) Put blanking caps on the disconnected electrical connectors (1) and (9).

  EFF : ALL  34-11-19   R  CES

 

Page 404 Feb 01/10

TASK 34-11-19-400-001 Installation of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3) CAUTION : DO NOT HOLD THE AOA SENSOR BY THE VANE WHEN YOU MOVE IT. IF YOU DO, _______ YOU CAN CAUSE DAMAGE TO THE AOA SENSOR. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 09-008 Material No. 09-016 R R

Material No. 11-003

USA MIL-S-8802 CLASS A NO LONGER AVAILABLE (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) USA ASTM D 740 METHYL-ETHYL-KETONE (Ref. 20-31-00)

C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------3 3

seal seal

34-11-02 01 -070 34-11-02 01A-070

  EFF : ALL  34-11-19    CES

 

Page 405 Feb 01/10

D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-720-005 30-31-00-710-001 34-10-00-710-007 34-11-00-710-001 34-11-19-991-002

Check of the Electrical Bonding of the Different Components (But not the Fluid Systems and the Components Installed on Composite materials) Operational Test of the Probe Ice Protection Test of the Angle of Attack Warning Test of the Monitoring of the ADR/AOA 26VAC Power Supply Fig. 401

3. __________ Job Set-up Subtask 34-11-19-860-051 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position in zone 231 for 3FP1 (232 for 3FP2) (127 for 3FP3). (2) Make sure that the protective covers of the sensors and probes (AOA, static Pitot and TAT) are removed. Subtask 34-11-19-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3FP1 49VU ANTI ICE/PROBES/AOA/1 4DA1 D04 49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/3PWR/SWTG

9FP

  EFF : ALL  34-11-19   R  CES

 

N10

Page 406 Feb 01/10

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/3PWR/SWTG

9FP

N09

5DA1 1DA1

Z13 Z12

10FP 5FP2 4FP2

N11 N09 N07

**ON A/C ALL 122VU ANTI ICE/PROBES/1/STATIC 122VU ANTI ICE/PROBES/1/TAT FOR 3FP2 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/2PWR/SHED 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/2PWR/SHED 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC

10FP 5FP2 4FP2

N10 N08 N06

1DA2 3DA2 4DA2 5DA2

Y15 Y14 Y13 Y11

9FP 5FP3 4FP3

N10 N08 N06

**ON A/C ALL 122VU ANTI 122VU ANTI 122VU ANTI 122VU ANTI FOR 3FP3

ICE/PROBES/2/TAT ICE/PROBES/2/PITOT ICE/PROBES/2/AOA ICE/PROBES/2/STATIC

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/3/115VAC

  EFF : ALL  34-11-19    CES

 

Page 407 Feb 01/10

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/3/115VAC

9FP 5FP3 4FP3

N09 N07 N05

3DA3 4DA3 5DA3

Z16 Z15 Z14

**ON A/C ALL 122VU ANTI ICE/PROBES/3/PITOT 122VU ANTI ICE/PROBES/3/AOA 122VU ANTI ICE/PROBES/3/STATIC Subtask 34-11-19-865-057 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3FP1 49VU ANTI ICE/PROBES/PHC/1 2DA1 D03 FOR 3FP2 122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12 FOR 3FP3 122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16 4. Procedure _________ Subtask 34-11-19-420-050 A. Installation of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3) (1) Angle of Attack Sensor without drain hole. NOTE : The procedure is the same for angle of attack sensors 3FP1, ____ 3FP2 and 3FP3. (a) Clean the component interface and/or the adjacent area. (b) Do an inspection of the component interface and/or the adjacent area.

  EFF : ALL  34-11-19    CES

 

Page 408 Feb 01/10

(c) Remove the blanking caps from the connectors (1) and (9). (d) Make sure that the connectors (1) and (9) are clean and in the correct condition. (e) Put the seal (3) in its housing (2). (f) Connect the connector (1). (g) Push the connector (1) into the fuselage. (h) Put the angle of attack sensor (5) in position with the stud (4) and hold it. (i) Tighten the screw (6). NOTE : During installation, the screw (6) must be inserted in the ____ only c-sink hole of the AOA sensor (5).As the other holes have no c-sink, mounting the screw (6) in one of them may create non-flush surface. (j) Install and hold the blanking plate (7). NOTE : The AOA blanking plate (7) is manufactured with a radius ____ that corresponds to the fuselage curve.The rotation of this plate around the AOA sensor may also create non-flush surface. The blanking plate (7) contains 8 attaching holes.Out of these 8 holes, 7 have a c-sink, 1 has not. Whilst mounting the blanking plate (7), it must be ensured that the only hole without the c-sink is aligned with the screw (6). NOTE : The 7 remaining screws (8) must all be inserted in each of ____ the 7 c-sink holes of the blanking plate (7). NOTE : Carefully install plate so as not to cause damage to the ____ sensor (5). (k) Tighten the seven screws (8). (l) Check the bonding contact resistance between the AOA Sensor (7) and the fuselage struture (2) (Ref. TASK 20-28-00-720-005). (m) Apply SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008) (better curing time) on the screw (6) head and around the blanking plate (7).

  EFF : ALL  34-11-19   R  CES

 

Page 409 Feb 01/10

NOTE : If the cure time of the sealant will cause a flight delay, ____ the aircraft can operate without the sealant for a maximum period of 48 hours from installation of the sensor. Before application of the sealant, it is necessary to make sure that the surfaces are clean and in the correct condition (no moisture, dust, insects, sand etc...). - If not, clean the area with CLEANING AGENTS (Material No. 11-003).

R R R R

(2) Angle of Attack Sensor with drain hole. NOTE : The procedure is the same for angle of attack sensors 3FP1, ____ 3FP2 and 3FP3. (a) Clean the component interface and/or the adjacent area. (b) Do an inspection of the component interface and/or the adjacent area. (c) Remove the blanking caps from the connectors (1) and (9). (d) Make sure that the connectors (1) and (9) are clean and in the correct condition. (e) Put the seal (3) in its housing (2). (f) Connect the connector (1). (g) Push the connector (1) into the fuselage. (h) Put the angle of attack sensor (5) in position with the stud (4) and hold it. (i) Tighten the screw (6). NOTE : During installation, the screw (6) must be inserted in the ____ only c-sink hole of the AOA sensor (5). As the other holes have no c-sink, mounting the screw (6) in one of them may create non-flush surface. illustration. (Ref. Fig. 401/TASK 34-11-19-991-002) (j) Install and hold the blanking plate (7). NOTE : The AOA blanking plate (7) is manufactured with a radius ____ that corresponds to the fuselage curve.The rotation of this plate around the AOA sensor may also create non-flush surface.

  EFF : ALL  34-11-19    CES

 

Page 410 Feb 01/10

Angle of Attack Sensor. Figure 401/TASK 34-11-19-991-002   EFF : ALL  34-11-19   R  CES

 

Page 411 Feb 01/10

The blanking plate (7) contains 8 attaching holes. Out of these 8 holes, 7 have a c-sink, 1 has not. Whilst mounting the blanking plate (7), it must be ensured that the only hole without the c-sink is aligned with the screw (6). Make sure that the drain hole (10) is at 6 Oclock position. NOTE : The 7 remaining screws (8) must all be inserted in each of ____ the 7 c-sink holes of the blanking plate (7). NOTE : Carefully install plate so as not to cause damage to the ____ sensor (5). (k) Tighten the seven screws (8). (l) Check the bonding contact resistance between the AOA Sensor (7) and the fuselage struture (2) (Ref. TASK 20-28-00-720-005). (m) Apply SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008) (better curing time) on the screw (6) head and around the blanking plate (7). NOTE : If the cure time of the sealant will cause a flight delay, ____ the aircraft can operate without the sealant for a maximum period of 48 hours from installation of the sensor. Before application of the sealant, it is necessary to make sure that the surfaces are clean and in the correct condition (no moisture, dust, insects, sand etc.).

R R R R

(n) Check the drain hole (10).

R R

WARNING : MAKE SURE THAT THE DRAIN HOLE (10) IS CLEAR AFTER YOU _______ INSTALL AND SEAL THE AOA BLANKING PLATE (7). Subtask 34-11-19-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 3FP1 4FP1, 5FP1, 9FP, 1DA1, 2DA1, 3DA1, 4DA1, 5DA1 FOR 3FP2 4FP2, 5FP2, 10FP, 1DA2, 2DA2, 3DA2, 4DA2, 5DA2 FOR 3FP3 4FP3, 5FP3, 9FP, 2DA3, 3DA3, 4DA3, 5DA3

  EFF : ALL  34-11-19    CES

 

Page 412 Feb 01/10

Subtask 34-11-19-710-050 C. Test (1) Do the operational test of the Probe Ice Protection (Ref. TASK 30-31-00-710-001). (2) Do the test of the angle of attack warning. (Ref. TASK 34-10-00-710-007). NOTE : As an alternative procedure, you can do an operational test ____ without the CFDS. (Ref. TASK 34-11-00-710-001). 5. Close-up ________ Subtask 34-11-19-860-052 A. Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the protective covers on the sensors and probes (AOA, static, Pitot and TAT). (3) Remove the access platform(s).

  EFF : ALL  34-11-19   R  CES

 

Page 413 Feb 01/10

SENSOR - ANGLE OF ATTACK (3FP1,3FP2,3FP3) - INSPECTION/CHECK ____________________________________________________________ TASK 34-11-19-200-001 R

Inspection of the Angle-Of-Attack Sensor (3FP1, 3FP2, 3FP3) 1. __________________ Reason for the Job Make sure that there is no paint on the vane and on the movable part of the three AOA sensors. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

circuit breaker(s) safety clip(s) lint-free cloth access platform 3.40 m (11 ft. 2 in.)

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 12-005B

USA MIL-R-25134 CHLORINATED,NON PHENOLIC STRIPPERS (Ref. 20-31-00)

3. __________ Job Set-up R

**ON A/C 001-049, 101-105, 151-158, 201-209,

R

Post SB

34-1222 For A/C 001-049,101-105,151-158,201-209,

Subtask 34-11-19-860-053 A. Get Access (1) Put an access platform in position in zone 231 for AOA sensor 3FP1 (232 for 3FP2) (127 for 3FP3). R

(2) Remove the AOA sensor slip-on cover.

  R EFF : 001-049, 101-105, 151-158, 201-209,  34-11-19    CES

 

Page 601 May 01/07

Subtask 34-11-19-865-053 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3FP1 49VU ANTI ICE/PROBES/AOA/1 4DA1 D04 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 **ON A/C 001-049, 101-105, 201-203, 121VU ADIRS/ADIRU/3PWR/SWTG R

9FP

N10

9FP

N09

10FP 5FP2 4FP2

N11 N09 N07

10FP 5FP2 4FP2

N10 N08 N06

4DA2

Y13

**ON A/C 151-158, 204-209, 121VU ADIRS/ADIRU/3PWR/SWTG

R

**ON A/C 001-049, 101-105, 151-158, 201-209,

R

Post SB

34-1222 For A/C 001-049,101-105,151-158,201-209,

FOR 3FP2 **ON A/C 001-049, 101-105, 201-203, 121VU ADIRS/ADIRU/2PWR/SHED 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC R

**ON A/C 151-158, 204-209, 121VU ADIRS/ADIRU/2PWR/SHED 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC

R

**ON A/C 001-049, 101-105, 151-158, 201-209, 122VU ANTI ICE/PROBES/2/AOA

  R EFF : 001-049, 101-105, 151-158, 201-209,  34-11-19    CES

 

Page 602 May 01/07

R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-049, 101-105, 151-158, 201-209,

R

Post SB

34-1222 For A/C 001-049,101-105,151-158,201-209,

FOR 3FP3 **ON A/C 001-049, 101-105, 201-203, 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/3/115VAC R

N10 N08 N06

9FP 5FP3 4FP3

N09 N07 N05

4DA3

Z15

**ON A/C 151-158, 204-209, 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/3/115VAC

R

9FP 5FP3 4FP3

**ON A/C 001-049, 101-105, 151-158, 201-209, 122VU ANTI ICE/PROBES/3/AOA 4. Procedure _________ CAUTION : DO NOT TOUCH THE AOA VANE IMMEDIATELY AFTER POWER-OFF BECAUSE IT _______ IS VERY HOT AND CAN BURN YOU. LET THE TEMPERATURE OF THE AOA VANE DECREASE FOR A FEW MINUTES BEFORE YOU TOUCH IT.

R

**ON A/C 001-049, 101-105, 151-158, 201-209,

R

Post SB

34-1222 For A/C 001-049,101-105,151-158,201-209,

Subtask 34-11-19-210-051 A. Make sure that there is no paint on the vane and mounting base of the three AOA sensors.

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Page 603 May 01/07

Subtask 34-11-19-210-052 B. If there is paint, remove it very carefully with STRIPPERS (Material No. 12-005B) and a lint-free cloth. CAUTION : MAKE SURE THAT NO LIQUID GOES INTO THE BEARING THROUGH THE _______ SPACE BETWEEN THE AOA VANE AND BODY. LIQUID IN THE AOA SENSOR CAN CAUSE CORROSION AND DAMAGE. Subtask 34-11-19-210-053 C. Manually turn the AOA sensor from the maximum to the minimum mechanical stops (+ 85⁰ to - 35⁰) and make sure that there is no hard point. R

**ON A/C 001-049, 101-105, 151-158, 201-209, 5. Close-up ________

R

**ON A/C 001-049, 101-105, 151-158, 201-209,

R

Post SB

34-1222 For A/C 001-049,101-105,151-158,201-209,

Subtask 34-11-19-860-054 A. Put the aircraft back to its initial configuration. (1) Install the AOA sensor slip-on cover. (2) Make sure that the work area is clean and clear of tool(s) and other items. (3) Remove the access platform(s).

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Page 604 May 01/07

Subtask 34-11-19-865-054 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3FP1 49VU ANTI ICE/PROBES/AOA/1 4DA1 D04 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 **ON A/C 001-049, 101-105, 201-203, 121VU ADIRS/ADIRU/3PWR/SWTG R

9FP

N10

9FP

N09

10FP 5FP2 4FP2

N11 N09 N07

10FP 5FP2 4FP2

N10 N08 N06

4DA2

Y13

**ON A/C 151-158, 204-209, 121VU ADIRS/ADIRU/3PWR/SWTG

R

**ON A/C 001-049, 101-105, 151-158, 201-209,

R

Post SB

34-1222 For A/C 001-049,101-105,151-158,201-209,

FOR 3FP2 **ON A/C 001-049, 101-105, 201-203, 121VU ADIRS/ADIRU/2PWR/SHED 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC R

**ON A/C 151-158, 204-209, 121VU ADIRS/ADIRU/2PWR/SHED 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC

R

**ON A/C 001-049, 101-105, 151-158, 201-209, 122VU ANTI ICE/PROBES/2/AOA

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Page 605 May 01/07

R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-049, 101-105, 151-158, 201-209,

R

Post SB

34-1222 For A/C 001-049,101-105,151-158,201-209,

FOR 3FP3 **ON A/C 001-049, 101-105, 201-203, 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/3/115VAC R

N10 N08 N06

9FP 5FP3 4FP3

N09 N07 N05

4DA3

Z15

**ON A/C 151-158, 204-209, 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/3/115VAC

R

9FP 5FP3 4FP3

**ON A/C 001-049, 101-105, 151-158, 201-209, 122VU ANTI ICE/PROBES/3/AOA

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Page 606 May 01/07

R R

_______________________________________________________ AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRU & CDU OR MSU) DESCRIPTION AND OPERATION _________________________ 1. General _______

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The Air Data/Inertial Reference System (ADIRS) provides the main air data and heading/attitude/navigation data to the aircraft systems. The main computers of the ADIRS are the three Air Data/Inertial Reference Units (ADIRU) which are controlled by the ADIRS Control and Display Unit (CDU). The ADIRS is a three channel system. Each channel is isolated from the others and provides independent information as defined in ARINC 738. Each ADIRU contains: - an Air Data Reference (ADR) portion. Its operation is described in 34-13 - an Inertial Reference (IR) portion. Its operation is described in 34-14. Power supply is common for ADR and IR and described in 34-11. 2. __________________ Component Location

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(Ref. Fig. 001, 002) The three ADIRUs are installed in the avionics compartment. The ADIRS CDU is installed in the cockpit. ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1FP1 ADIRU-1 127 824 34-12-34 1FP2 ADIRU-2 128 824 34-12-34 1FP3 ADIRU-3 127 824 34-12-34 2FP CDU-ADIRS 20VU 211 831 34-12-12

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ADIRS - Component Location Figure 001   R EFF : 001-049, 101-105, 151-199, 201-203,  34-12-00 Page 2   Config-1 May 01/05  CES

 

ADIRS CDU - Component Location Figure 002   R EFF : 001-049, 101-105, 151-199, 201-203,  34-12-00 Page 3   Config-1 May 01/05  CES

 

3. Interface _________ A. Mechanical Interface The ADIRUs are installed and aligned on a specific mounting tray in the avionics compartment in accordance with the installation design defined in ARINC 738. The ADIRU is to 4 MCU size. In order to ensure attitude and azimuth accuracy, the mounting tray orientation complies with the following tolerances: - pitch and roll: plus or minus 12 minutes - azimuth: plus or minus 12 minutes. B. Electrical Interface (1) ADIRS CDU (Ref. Fig. 003) The ADIRS CDU contains three identical connectors. Each connector is linked to one ADIRU. The four annunciator discretes ADR OFF, ADR FAULT, IR ALIGN and IR FAULT are linked to the ADIRS CDU from the ADIRU, through the annunciator light test and interface boards. The CDU panel lighting and LCD backlighting are provided by bulbs supplied with 5VAC (from the A/C electrical generation). The CDU exchanges data with the ADIRU. The data sent by the CDU can be used for the initialization of the IR portion. The data received by the CDU are displayed on the Liquid Crystal Display (LCD). R R R

(2) ADIRU The ADIRU receives data and computes outputs in accordance with ARINC 738. It uses an ARINC 600 type 2 floating-connector.

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(a) Digital inputs - Air Data Module (ADM) inputs The ADR provides up to five ADM input buses. Only three of them are used to receive air mass data from remotely mounted ADM (Ref. 34-11), two linked to the static probe and one linked to the pitot probe.

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NOTE : For the ADIRU 3, only two ADM input buses are used: one ____ for the total pressure data and the other for the averaged static pressure data.

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- digital baro-correction inputs The ADR provides two baro-correction digital data input ports. The incoming data from the Flight Control Unit (FCU) are in ARINC 429 low speed format.

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The ADR receives data from baro-correction bus A. The baro-correction is used to compensate baro-corrected altitude output. - initialization data inputs The IR portion of the ADIRU receives data from either ARINC 702 Flight Management and Guidance Computer (FMGC). The data are in ARINC 429 low speed format. The initialization parameters are latitude and longitude or magnetic heading. - CFDIU input The ADIRU provides one Centralized Fault Display Interface Unit (CFDIU) input bus. The data are in ARINC 429 low speed format. The CFDIU continuously transmits data to all systems. The ADIRU uses these data to accept commands from the CFDIU. - Air Data Reference inputs The IR portion of the ADIRU provides two digital data input ports for receiving data from the other ADIRUs. The incoming data are in ARINC 429 low speed format and include altitude and true airspeed. **ON A/C 001-004,

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- CDU inputs The IR portion of the ADIRU receives data from one ARINC 738 CDU. The data are in ARINC 429 low speed format. These data are initialization parameters (latitude and longitude or magnetic heading) and CDU status. - GPS inputs The IR portion of the ADIRU receives data from two ARINC 743 GPS receivers. The data are in ARINC 429 high speed format. These data concern various parameters such as position, velocity, integrity,... - the ADIRU provides provision for digital input buses. (b) Analog inputs - analog AOA input The ADR portion of the ADIRU accepts two resolver inputs of indicated angle of attack. The characteristics of the resolvers, as seen by the ADR, are as follows: . scale factor: 1⁰/Degree of AOA . index reference: 0⁰ resolver input = 25⁰ AOA - Total Air Temperature (TAT) sensor The ADR portion of the ADIRU accepts a standard 500 ohm platinum sensing element input from the TAT sensor. The ADR derives the measured temperature from the TAT sensor input using the Callender-Van Dusen equation from ARINC 738.

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- GPS Time Mark inputs These two inputs (one for each GPS sensor) allow the ADIRU to be synchronized with the GPS receivers. - 115VAC The ADIRU operates from the 115VAC/400 Hz primary power. - 28VDC back-up The ADIRU can operate from the 28VDC back-up power. - 26VAC reference The ADIRU accepts up to three 26VAC resolver reference inputs. Only one is used for the AOA resolver. The ADIRU provides provisions for analog inputs (two 26VAC reference inputs and three analog baro-correction inputs are reserved). R R

**ON A/C 001-049, 101-105, 151-199, 201-203,

R

Post SB

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34-1147 For A/C 001-004, - CDU inputs The IR portion of the ADIRU receives data from one ARINC 738 CDU. The data are in ARINC 429 low speed format. These data are initialization parameters (latitude and longitude or magnetic heading) and CDU status. - GPS inputs The IR portion of the ADIRU receives data from the GPS portion of the Multi-Mode Receivers (MMRs). The data are in ARINC 429 high speed format. These data concern various parameters such as position, velocity, integrity,... - the ADIRU provides provision for digital input buses. (b) Analog inputs - analog AOA input The ADR portion of the ADIRU accepts two resolver inputs of indicated angle of attack. The characteristics of the resolvers, as seen by the ADR, are as follows: . scale factor: 1⁰/Degree of AOA . index reference: 0⁰ resolver input = 25⁰ AOA - Total Air Temperature (TAT) sensor The ADR portion of the ADIRU accepts a standard 500 ohm platinum sensing element input from the TAT sensor. The ADR derives the measured temperature from the TAT sensor input using the Callender-Van Dusen equation from ARINC 738. - GPS Time Mark inputs These two inputs (one for each Multi-Mode Receiver) allow the ADIRU to be synchronized with the GPS portion of the MMRs. - 115VAC The ADIRU operates from the 115VAC/400 Hz primary power. - 28VDC back-up The ADIRU can operate from the 28VDC back-up power. - 26VAC reference

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The ADIRU accepts up to three 26VAC resolver reference inputs. Only one is used for the AOA resolver. The ADIRU provides provisions for analog inputs (two 26VAC reference inputs and three analog baro-correction inputs are reserved). R

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**ON A/C 001-049, 101-105, 151-199, 201-203, (c) Discrete inputs These inputs are generally pin programs except for: - Static Source Error Correction (SSEC) and AOA correction and selection discretes which come from the Slat and Flap Control Computers (SFCC) and are linked to flap position (Ref. Fig. 004) - heat discretes which come from the associated Probe Heat Computer (PHC) - VMO/MMO discrete provided by the position of the L/G DOWN VMO/MMO SELECTION switch (22FP). - ADR selection: It indicates, to the IR, the air data source to be used. - CDU ON/OFF : It indicates, to the ADIRU, whether the ADIRU data are currently displayed on CDU. - ADR OFF: It indicates, to the ADIRU, that the crew has pushed the ADR pushbutton switch on the ADIRS CDU. This commands the ADIRU to stop the transmission of the ADR output buses. - IR MODE SELECT: It indicates, to the ADIRU, the position of the associated selector switch on the CDU. Three positions can be coded: OFF, NAV, ATT. This gives the computer operating mode. The functions of the pin program discretes are: - aircraft identification: nine discretes provide the ADIRU with the identification of the aircraft. They are used by the ADR to select the appropriate SSEC and AOA correction laws and by the IR to select the appropriate filtering (bandwidth) of the output labels. - baro-correction source selection: This discrete provides the ADIRU with the following: . the form (digital or analog) in which the baro-correction transmission is made . the number of sources (2 or 3) . the type of transmission used by the digital sources (single bus or various buses). On the A/C the FCU transmits the CAPT and F/O baro-correction in digital form on separate buses. - AOA average/unique: The ADIRU receives the AOA on two resolvers.

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INTENTIONALLY BLANK

  R   34-12-00 Page 10   Config-1 Feb 01/08  CES

 

ADIRS - ADIRUs/SFCCs Interface Figure 004   EFF : 001-049, 101-105, 151-199, 201-203,  34-12-00 Page 11   Config-1 Nov 01/05 R  CES

 

-

-

This discrete indicates whether the computation must use an average value from the two resolvers or the value of resolver 1 in priority with the second as a back-up in case of failure. This last solution is chosen on the A/C. ADR ARINC filter select: This permits to choose between two sets of filter characteristics for the ADR outputs. mounting position: This indicates the orientation of the unit to the IR portion. It is used to know where are the longitudinal and lateral axes of the aircraft and the sign of motion measured. SDI: This indicates on which side (CAPT, F/O, Standby) the ADIRU is installed. CMC-CFDS message select: The ADIRU could be installed on the Long Range. In this case, the ADIRU selects a table of maintenance messages different from the Standart Bodies one, with a different vocabulary.

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**ON A/C 001-049, 101-102, (d) Digital outputs - The ADR portion of the ADIRU provides eight identical ARINC 429 Low Speed buses. Two of these buses are dedicated to the interface with the Electronic Engine Control (EEC). The number of these buses is 5 and 6. The system users are described in the table below: ---------------------------------------------------------------------------| | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | USERS |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |ADIRU 1 | | | | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 2 | |* | | | | | | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 3 | | |* | | | | | | |* | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 1 |* | | | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 2 | | | | | | |* | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 3 | | |* | | | | | |* | | | |* | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |WR 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 2 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CFDIU | | | |* | | | | | |* | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ECU ENG 1 | | | | |* | | | | | |* | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ECU ENG 2 | | | | | |* | | | | | |* | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|

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---------------------------------------------------------------------------| | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | USERS |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |SFCC 1 | | |* | | | | | |* | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SFCC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 1 | | |* | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 3 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |GPWC | | | |* | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMU | |* | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN | | | | | | | | | | | | | | | | | | | |PRESSURE | | |* | | | | | | |* | | | | |* | | | | |CONTROLLER1 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN PRESSURE | | | |* | | | |* | | | | | | | |* | | | |CONTROLLER2 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ZONE TEMRERATURE | | | | | | | | | | | | | | | |* | | | |CONTROLLER | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |TEST 1 CONNECTORS | | | |* | | | | | |* | | | | | |* | | | ---------------------------------------------------------------------------Table 11 : ADR Data Users

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**ON A/C 103-105, (d) Digital outputs - The ADR portion of the ADIRU provides eight identical ARINC 429 Low Speed buses. Two of these buses are dedicated to the interface with the Electronic Engine Control (EEC). The number of these buses is 5 and 6. The system users are described in the table below: ---------------------------------------------------------------------------| | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | USERS |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |ADIRU 1 | | | | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 2 | |* | | | | | | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 3 | | |* | | | | | | |* | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 1 |* | | | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 2 | | | | | | |* | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 3 | | |* | | | | | |* | | | |* | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |WR 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 2 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CFDIU | | | |* | | | | | |* | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ECU ENG 1 | | | | |* | | | | | |* | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ECU ENG 2 | | | | | |* | | | | | |* | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|

  EFF : 103-105,  34-12-00 Page 15   Config-1 Nov 01/05 R  CES

 

---------------------------------------------------------------------------| | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | USERS |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |SFCC 1 | | |* | | | | | |* | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SFCC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 1 | | |* | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 3 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |GPWC | | | |* | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN | | | | | | | | | | | | | | | | | | | |PRESSURE | | |* | | | | | | |* | | | | |* | | | | |CONTROLLER1 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN PRESSURE | | | |* | | | |* | | | | | | | |* | | | |CONTROLLER2 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ZONE TEMRERATURE | | | | | | | | | | | | | | | |* | | | |CONTROLLER | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |TEST 1 CONNECTORS | | | |* | | | | | |* | | | | | |* | | | ---------------------------------------------------------------------------Table 11 : ADR Data Users

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**ON A/C 151-199, 203-203, (d) Digital outputs - The ADR portion of the ADIRU provides eight identical ARINC 429 Low Speed buses. Two of these buses are dedicated to the interface with the Electronic Engine Control (EEC). The number of these buses is 5 and 6. The system users are described in the table below: ---------------------------------------------------------------------------| | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | USERS |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |ADIRU 1 | | | | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 2 | |* | | | | | | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 3 | | |* | | | | | | |* | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 1 |* | | | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 2 | | | | | | |* | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 3 | | |* | | | | | |* | | | |* | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |WR 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |WR 2 | | | | | | | | | |* | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 2 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CFDIU | | | |* | | | | | |* | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ECU ENG 1 | | | | |* | | | | | |* | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|

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---------------------------------------------------------------------------| | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | USERS |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |ECU ENG 2 | | | | | |* | | | | | |* | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SFCC 1 | | |* | | | | | |* | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SFCC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 1 | | |* | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 3 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |GPWC | | | |* | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN | | | | | | | | | | | | | | | | | | | |PRESSURE | | |* | | | | | | |* | | | | |* | | | | |CONTROLLER1 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN PRESSURE | | | |* | | | |* | | | | | | | |* | | | |CONTROLLER2 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ZONE TEMRERATURE | | | | | | | | | | | | | | | |* | | | |CONTROLLER | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |TEST 1 CONNECTORS | | | |* | | | | | |* | | | | | |* | | | ---------------------------------------------------------------------------Table 11 : ADR Data Users

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**ON A/C 201-202, (d) Digital outputs - The ADR portion of the ADIRU provides eight identical ARINC 429 Low Speed buses. Two of these buses are dedicated to the interface with the Electronic Engine Control (EEC). The number of these buses is 5 and 6. The system users are described in the table below: ---------------------------------------------------------------------------| | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | USERS |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |ADIRU 1 | | | | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 2 | |* | | | | | | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 3 | | |* | | | | | | |* | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 1 |* | | | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 2 | | | | | | |* | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 3 | | |* | | | | | |* | | | |* | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |WR 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |WR 2 | | | | | | | | | |* | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 2 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CFDIU | | | |* | | | | | |* | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ECU ENG 1 | | | | |* | | | | | |* | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|

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---------------------------------------------------------------------------| | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | USERS |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |ECU ENG 2 | | | | | |* | | | | | |* | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SFCC 1 | | |* | | | | | |* | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SFCC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 1 | | |* | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 3 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |GPWC | | | |* | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMU | |* | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN | | | | | | | | | | | | | | | | | | | |PRESSURE | | |* | | | | | | |* | | | | |* | | | | |CONTROLLER1 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN PRESSURE | | | |* | | | |* | | | | | | | |* | | | |CONTROLLER2 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ZONE TEMRERATURE | | | | | | | | | | | | | | | |* | | | |CONTROLLER | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |TEST 1 CONNECTORS | | | |* | | | | | |* | | | | | |* | | | ---------------------------------------------------------------------------Table 11 : ADR Data Users

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**ON A/C 001-049, 101-105, 151-199, 201-203, - The IR portion of the ADIRU provides four identical ARINC 429 High Speed buses. The system users are described in the table below: ------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |-----------------------------------------------------------------------| |FAC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FAC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |ELAC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |ELAC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 1 | | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 2 | | * | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 3 | | | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 1 | * | | | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 2 | | | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|--- | |DMC 3 | | | * | | | | * | | * | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |CDU | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FMGC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FMGC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FQIC | | * | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |BSCU | | * | | | | | * | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |CFDIU | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPWC (1)| | | * | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |WR 1 | | | * | | | | | | | | * | |

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------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |-----------------------------------------------------------------------| |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |WR 2 (1)| | | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |TCAS (1)| | | * | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMU (1)| | * | | | | | * | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPS 1 (1)| | * | | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPS 2 (1)| | | | | | * | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |MMR 1 (1)| | * | | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |MMR 2 (1)| | | * | | | * | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |RMI-VOR/DME| | * | | | | | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |RMI (1)| | * | | | | | | | | * | | | |VOR/ADF/DME| | | | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |RMI-ADF (1)| | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |TEST PLUG | | | * | | | * | | | | | * | | ------------------------------------------------------------------------(1) Optional system Table 12 : IR Data Users - Basic version (e) Analog outputs The ADIRUs, through analog outputs, supply the ADMs with +13.5/-13.5VDC and the CDU with 28VDC.

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**ON A/C 151-199, (f) Discrete outputs The discrete outputs are either open/ground or open/28VDC discretes (for ON BAT, IR FAILURE WARNING and ALIGN NOT READY discretes). The LOW SPEED WARNING discretes are set according to a speed threshold (with an hysteresis of 4 knots). These thresholds are respectively: --------------------------------|Lower threshold|Upper threshold| | value | value | --------------------------|---------------|---------------| | LOW SPEED WARNING 1 | 100 | 104 | | LOW SPEED WARNING 2 | 50 | 54 | | LOW SPEED WARNING 3 | 155 | 159 | | LOW SPEED WARNING 4 | 260 | 264 | ----------------------------------------------------------The LOW SPEED WARNING 1 discrete is used in the Ram Air Turbine extension logic and in the power generation logic. The LOW SPEED WARNING 2 discrete is used in the power generation logic. The following discretes are used to control the CDU annunciators: - ON BAT - ADR OFF - ADR FAILURE WARNING - IR FAILURE WARNING - IR ALIGN. **ON A/C 001-049, 101-105, 151-199, 201-203, 4. _____________________ Component Description R R R R R R R R R R R R

A. ADIRS CDU (Ref. Fig. 005) The CDU is a three-channel unit. Each CDU channel is dedicated to one separate ADIRU and includes the following features: - a three-position mode selector switch. The modes are: . power off (OFF) . navigation (NAV) . reversionary attitude (ATT) - an indicator announcing when the IR is aligning (ALIGN legend of IR annunciator) - an IR fault indicator (FAULT legend of IR annunciator)

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ADIRS CDU Figure 005   EFF : 001-049, 101-105, 151-199, 201-203,  34-12-00 Page 24   Config-1 Nov 01/05 R  CES

 

R R R R R R R R R R R R R R R R R R R R R R R

- a pushbutton switch to disable ADR output buses. It is a momentary action pushbutton switch - an indicator announcing when the ADR output buses are turned off (OFF legend of ADR pushbutton switch) - an ADR fault indicator (FAULT legend of ADR pushbutton switch). The following items of equipment are shaped between the three channels : - a keyboard to enter the initial position in degrees, minutes and tenth of minutes or magnetic heading in the attitude mode - two data pushbutton switches (ENT and CLR) with cue lights - a liquid crystal display for selected parameters. The LCD has 16 digits and each digit has 14 segments - a DATA DISPLAY selector switch to select parameters for display on the LCD: * wind (WIND) * present position (PPOS) * true heading (HDG) * status of selected system (STS) * track and ground speed (TK/GS) * test values (TEST) - a SYS DISPLAY selector switch with four positions: OFF, 1, 2, 3. The OFF position disables the display of the CDU but the mode control of the ADIRUs remains active - an ON BAT annunciator. The CDU contains three identical connectors referenced J1, J2 and J3. (Ref. Fig. 006) No cooling air is provided to the CDU. The CDU is supplied with 28VDC from the selected ADIRU to drive internal circuits and the data display. The 28VDC inputs are isolated from each other. The aircraft supplies 5VAC power for panel lighting/LCD backlighting and for annunciator lighting. B. ADIRU (Ref. Fig. 007) (1) General The ADIRU is contained in a 4 MCU case as defined in ARINC 600. The ADIRU has to be aligned on a special shelf in the avionics compartment in accordance with the installation design described in ARINC 738. This installation involves modification of the ARINC 600 standard to include three alignment pins and a floating connector. Pins 12 and 13 of the bottom plug have been modified with a reducer to accept power input instead of coax input as defined in ARINC 738. All input discretes are electrically isolated by an in-line diode or an equivalent device. The discrete outputs are protected by means of diodes to permit a wired OR circuit with other outputs.

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ADIRS CDU - Internal Block Diagram Figure 006   EFF : 001-049, 101-105, 151-199, 201-203,  34-12-00 Page 26   Config-1 Nov 01/05 R  CES

 

ADIRU - General View Figure 007   EFF : 001-049, 101-105, 151-199, 201-203,  34-12-00 Page 27   Config-1 Nov 01/05 R  CES

 

As each ADIRU is a common point to all engines installed on the aircraft, special care is taken to make impossible any electrical disturbance to propagate through the ADIRU/engine interface to other inputs/outputs dedicated to engines. The ADIRU is designed to reach a high level of protection for lightning and Electromagnetic Interference (EMI). The lightning protection circuitry is made up of high-powered Zener diode type semiconductors called Transzorbs on I/O connector pins. Power supply inputs are protected by Mov or by Zener type suppressor mounted adjacent to I/O connector. A 80960 microprocessor is shared between the ADR and IR functions to perform computations, BITE and input/output. The ADIRU contains an ADR and an IR portion supplied by a common power (115VAC, 28VDC). (2) ADR portion (Ref. Fig. 008) Five resolvers can be used for the analog baro-correction and the AOA inputs. The ADR provides eight ARINC 429 low-speed output buses (buses 5 to 8 are reserved for engine control). Each bus can drive twenty ARINC bus loads. (3) IR portion (Ref. Fig. 008) A DSP (Digital Signal Processing) C25 microprocessor is used to interface between the sensor block and the 80960 microprocessor. The gyros/accel sensors block contains three accels and three gyros mounted along each axis. This sensor block is supplied by a high voltage power supply provided by the IR portion. The IR provides four ARINC 429 High-Speed output buses. Each bus can drive twenty loads.

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ADIRU - Block Diagram Figure 008   EFF : 001-049, 101-105, 151-199, 201-203,  34-12-00 Page 29   Config-1 Nov 01/05  CES

 

________________________________________________________ AIR DATA, INERTIAL REFERENCE SYSTEM (ADIRU & CDU OR MSU) DESCRIPTION AND OPERATION _________________________ 1. _______ General The Air Data/Inertial Reference System (ADIRS) provides the main air data and heading/attitude/navigation data to the aircraft systems. The main computers of the ADIRS are the three Air Data/Inertial Reference Units (ADIRU) which are controlled by the ADIRS Control and Display Unit (CDU). The ADIRS is a three channel system. Each channel is isolated from the others and provides independent information as defined in ARINC 738. Each ADIRU contains: - An Air Data Reference (ADR) portion. Its operation is described in 34-13. - An Inertial Reference (IR) portion. Its operation is described in 34-14. The power supply is common for the ADR and IR portions and described in 34-11. 2. Component __________________ Location L (Ref. Fig. 001, 002) The three ADIRUs are installed in the avionics compartment. The ADIRS CDU is installed in the cockpit. ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1FP1 ADIRU-1 127 824 34-12-34 1FP2 ADIRU-2 128 824 34-12-34 1FP3 ADIRU-3 127 824 34-12-34 2FP CDU-ADIRS 20VU 211 831 34-12-12

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ADIRS - Component Location Figure 001   EFF : 524-526, 528-599,  34-12-00 Page 2   Config-2 Feb 01/10  CES

 

ADIRS CDU - Component Location Figure 002   EFF : 524-526, 528-599,  34-12-00 Page 3   Config-2 Feb 01/10  CES

 

3. Interface _________ A. Mechanical Interface The ADIRUs are installed and aligned on a specific mounting tray in the avionics compartment in accordance with the installation design defined in ARINC 738. The ADIRU is to 4 MCU size. In order to ensure attitude and azimuth accuracy, the mounting tray orientation complies with the following tolerances: - pitch and roll: plus or minus 12 minutes - azimuth: plus or minus 12 minutes. B. Electrical Interface (1) ADIRS CDU (a) General (Ref. Fig. 003) The ADIRS CDU contains three identical connectors. Each connector is linked to one ADIRU by means of an insert position keying. The four annunciator discretes ADR OFF, ADR FAULT, IR ALIGN and IR FAULT are linked to the ADIRS CDU from the ADIRU, through the annunciator light test and interface boards. The CDU panel lighting and LCD backlighting are provided by bulbs supplied with 5 VAC (from the A/C electrical generation). The CDU exchanges data with the ADIRU. The data sent by the CDU can be used for the initialization of the IR portion. The data received by the CDU is displayed on the Liquid Crystal Display (LCD). (b) CDU digital form The tables below contain all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following tables give: - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds. - CODE:

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ADIRS CDU - Electrical Interface Figure 003   EFF : 524-526, 528-599,  34-12-00 Page 5   Config-2 Feb 01/10  CES

 

BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code. - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system.

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1 _

CDU bus inputs The CDU receives an ARINC 429 High-Speed bus from the IR portion of each ADIRU.

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 010 |PRESENT |90S-90N |DEG | | 6 | | BCD| | | |POS LAT-D |(POSITIVE: |& | | | | | | | | |NORTH FROM |MIN | | | | | | | | |0 DEG) | | | | | | | | | |RESOL = .1 | | | | | | | |-----------------------------------------------------------------------------| | 011 |PRESENT |180E-180W |DEG | | 6 | | BCD| | | |POS LONG-D |(POSITIVE: |& | | | | | | | | |EAST FROM |MIN | | | | | | | | |0 DEG) | | | | | | | | | |RESOL = .1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 012 |GROUND |0-2000 |Kt | | 4 | | BCD| | | |SPEED-D |(ALWAYS | | | | | | | | | |POSITIVE) | | | | | | | | | |RESOL = 1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 013 |TRACK |0-359.9 |DEG | | 4 | | BCD| | | |ANGLE TRUE |(POSITIVE: | | | | | | | | | |CW FROM | | | | | | | | | |NORTH) | | | | | | | | | |RESOL = .1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 014 |MAGNETIC |0-359.9 |DEG | | 4 | | BCD| | | |HEADING |(POSITIVE: | | | | | | | | | |CW FROM | | | | | | | | | |NORTH) | | | | | | | | | |RESOL = .1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 015 |WIND SPEED |0-256 |Kt | | 3 | | BCD| | | | |(ALWAYS | | | | | | | | | |POSITIVE) | | | | | | | | | |RESOL = 1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 016 |WIND DIR |0-359 |DEG | | 3 | | BCD| | | |TRUE |(POSITIVE: | | | | | | | | | |CW FROM | | | | | | | | | |NORTH) | | | | | | | | | |RESOL = 1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 044 |TRUE |0-359.9 |DEG | | 4 | | BCD| | | |HEADING |(POSITIVE: | | | | | | | | | |CW FROM | | | | | | | | | |NORTH) | | | | | | | | | |RESOL = .1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 270 |IR DISCRETE| | | | 19 | | DIS| | | |(1) | | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 277 |CDU TEST | | | | 18 | | DIS| | | |WORD (1) | | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 350 |ACTION | | | | 19 | | DIS| | | |CODE (1) | | | | | | | | ------------------------------------------------------------------------------CDU IR Input Labels NOTE : (1) The complete definition of labels 270, 277 and 350 ____ is detailed in 34-14-00 Para. 2.D.(1). 2 _

CDU bus outputs The CDU sends the parameters detailed in the following table to the IR portion of each ADIRU:

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 041 |SET | 90S-90N |DEG | | 6 | | BCD| | | |LATITUDE | (POSITIVE: |& | | | | | | | | | NORTH) |MIN | | | | | | | | | RESOL = 0.1| | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 042 |SET | 180E-180W |DEG | | 6 | | BCD| | | |LONGITUDE | (POSITIVE: |& | | | | | | | | | EAST) |MIN | | | | | | | | | RESOL = 0.1| | | | | | | |--------------|----------| -----------|----|----|----|----|----|-------------| | 043 |SET | 0-359 |DEG | | 3 | | BCD| | | |MAGNETIC | (POSITIVE: | | | | | | | | |HDG | CW FROM N) | | | | | | | | | | RESOL = 1 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 277 |CDU TEST | | | | 19 | | DIS| | ------------------------------------------------------------------------------CDU Output Labels (2) ADIRU The ADIRU receives data and computes outputs in accordance with ARINC 738. It uses an ARINC 600 type 2 floating-connector. (a) Digital inputs - Air Data Module (ADM) inputs The ADR provides up to five ADM input buses. Only three of them are used to receive air mass data from remotely mounted ADM (Ref. 34-11), two linked to the static probe and one linked to the pitot probe. NOTE : For the ADIRU 3, only two ADM input buses are used: one ____ for the total pressure data and the other for the averaged static pressure data. - digital baro-correction inputs The ADR provides two baro-correction digital data input ports. The incoming data from the Flight Control Unit (FCU) is in ARINC 429 low-speed format.

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The ADR receives data from baro-correction bus A. The baro-correction is used to compensate baro-corrected altitude output. initialization data inputs The IR portion of the ADIRU receives data from either ARINC 702 Flight Management and Guidance Computer (FMGC). The data is in ARINC 429 low-speed format. The initialization parameters are latitude and longitude or magnetic heading. CFDIU input The ADIRU provides one Centralized Fault Display Interface Unit (CFDIU) input bus. The data is in ARINC 429 low-speed format. The CFDIU continuously transmits data to all systems. The ADIRU uses this data to accept commands from the CFDIU. Air Data Reference inputs The IR portion of the ADIRU provides two digital data input ports for receiving data from the other ADIRUs. The incoming data is in ARINC 429 low-speed format and includes altitude and true airspeed. the ADIRU provides provision for digital input buses (two buses are reserved for the Global Positioning System (GPS)). CDU inputs The IR portion of the ADIRU receives data from one ARINC 738 CDU. The data is in ARINC 429 low-speed format. These items of data are initialization parameters (latitude and longitude or magnetic heading) and CDU status.

(b) Analog inputs - analog AOA input The ADR portion of the ADIRU accepts two resolver inputs of indicated angle of attack. The characteristics of the resolvers, as seen by the ADR, are as follows: . scale factor: 1⁰/Degree of AOA . index reference: 0⁰ resolver input = 25⁰ AOA - Total Air Temperature (TAT) sensor The ADR portion of the ADIRU accepts a standard 500 ohm platinum sensing element input from the TAT sensor. The ADR derives the measured temperature from the TAT sensor input using the Callender-Van Dusen equation from ARINC 738. - GPS Time Mark inputs This allows the ADIRU to be synchronized with the GPS portion of the MMRs. - 115 VAC The ADIRU operates from the 115 VAC/400 Hz primary power. - 28 VDC back-up The ADIRU can operate from the 28 VDC back-up power. - 26 VAC reference

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The ADIRU accepts up to three 26 VAC resolver reference inputs. Only one is used for the AOA resolver. The ADIRU provides provisions for analog inputs (two 26 VAC reference inputs, and three analog baro-correction inputs are reserved). (c) Analog inputs - analog AOA input The ADR portion of the ADIRU accepts two resolver inputs of indicated angle of attack. The characteristics of the resolvers, as seen by the ADR, are as follows: . scale factor: 1⁰/Degree of AOA . index reference: 0⁰ resolver input = 25⁰ AOA - Total Air Temperature (TAT) sensor The ADR portion of the ADIRU accepts a standard 500 ohm platinum sensing element input from the TAT sensor. The ADR derives the measured temperature from the TAT sensor input using the Callender-Van Dusen equation from ARINC 738. - 115 VAC The ADIRU operates from the 115 VAC/400 Hz primary power. - 28 VDC back-up The ADIRU can operate from the 28 VDC back-up power. - 26 VAC reference The ADIRU accepts up to three 26 VAC resolver reference inputs. Only one is used for the AOA resolver. The ADIRU provides provisions for analog inputs (two 26 VAC reference inputs and three analog baro-correction inputs are reserved).

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(d) Discrete inputs These inputs are generally pin programs except for: - Static Source Error Correction (SSEC) and AOA correction and selection discretes which come from the Slat and Flap Control Computers (SFCC) and are linked to flap position, (Ref. Fig. 004) - heat discretes which come from the associated Probe Heat Computer (PHC), - VMO/MMO discrete provided by the position of the L/G DOWN VMO/MMO SELECTION switch (22FP). - ADR selection: It indicates, to the IR, the air data source to be used. - CDU ON/OFF: It indicates, to the ADIRU, whether the ADIRU data is currently displayed on the CDU. - ADR OFF: It indicates, to the ADIRU, that the crew has pushed the ADR pushbutton switch on the ADIRS CDU. This commands the ADIRU to stop the transmission of the ADR output buses. - IR MODE SELECT: It indicates, to the ADIRU, the position of the associated selector switch on the CDU. Three positions can be coded: OFF, NAV, ATT. This gives the computer operating mode. The functions of the pin program discretes are: - aircraft identification: seven discretes provide the ADIRU with the identification of the aircraft. They are used by the ADR to select the appropriate SSEC and AOA correction laws and by the IR to select the appropriate filtering (bandwidth) of the output labels. - baro-correction source selection: This discrete provides the ADIRU with the following: . the form (digital or analog) in which the baro-correction transmission is made. . the number of sources (2 or 3) . the type of transmission used by the digital sources (single bus or various buses). On the A/C, the FCU transmits the CAPT and F/O baro-correction in digital form on separate buses. - AOA average/unique: The ADIRU receives the AOA on two resolvers. This discrete indicates whether the computation must use an average value from the two resolvers, or the value of resolver 1 in priority with the second as a back-up in case of failure. This last solution is chosen on the A/C. - ADR ARINC filter select:

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ADIRS - ADIRUs/SFCCs Interface Figure 004   EFF : 524-526, 528-599,  34-12-00 Page 13   Config-2 Feb 01/10  CES

 

-

-

This permits to choose between two sets of filter characteristics for the ADR outputs. mounting position: This indicates the orientation of the unit to the IR portion. It is used to know where are the longitudinal and lateral axes of the aircraft and the sign of motion measured. SDI: This indicates on which side (CAPT, F/O, Standby) the ADIRU is installed. CFDS message select: The ADIRU selects a table of maintenance messages. GPS sensor present: This indicates, to the ADIRU, the presence on-board the aircraft of one or two MMRs (GPS portion). GPS priority select: This indicates, to the ADIRU, the priority for using the MMRs (GPS portion). Mag. Var. select: This discrete is not used anymore. In previous standards, it selected between two different magnetic variation tables.

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(e) Digital outputs - The ADR portion of the ADIRU provides eight identical ARINC 429 Low-Speed buses. Two of these buses are dedicated to the interface with the Electronic Control Units (ECU). The number of these buses is 5 and 6. The system users are described in the table below: ---------------------------------------------------------------------------| USERS | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |ADIRU 1 | | | | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 2 | |* | | | | | | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 3 | | |* | | | | | | |* | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 1 |* | | | | | | |* | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 2 | |* | | | | |* | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 3 | | |* | | | | | |* | | | |* | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 2 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CFDIU | | | |* | | | | | |* | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ECU or EEC ENG 1 | | | | |* | | | | | |* | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |PVIS (1) | | | | | | | | | |* | | | | | | | | | |Passenger Visual | | | | | | | | | | | | | | | | | | | |Information | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |Landscape Camera (1)| | | | | | | | | |* | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |AINS (1)| | | | | | | | | |* | | | | | | | | |

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---------------------------------------------------------------------------| USERS | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |Aircraft Information| | | | | | | | | | | | | | | | | | | |Network System | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ECU or EEC ENG 2 | | | | | |* | | | | | |* | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SFCC 1 | | |* | | | | | |* | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SFCC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 1 | | |* | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 3 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |WR 1 (option PWS) | | |* | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |WR 2 (option PWS) | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMU (option) | |* | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |AOA CAPT INDICATOR | | | |* | | | | | | | | | | | | | | | |(option) | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |AOA F/O INDICATOR | | | | | | | | | |* | | | | | | | | | |(option) | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |GPWC (option) | | | |* | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMU (option) | |* | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN PRESSURE | | |* | | | | | | |* | | | | |* | | | | |CONTROLLER1 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|

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---------------------------------------------------------------------------| USERS | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |CABIN PRESSURE | | | |* | | | |* | | | | | | | |* | | | |CONTROLLER2 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ZONE TEMPERATURE | | | | | | | | | | | | | | | |* | | | |CONTROLLER | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |TEST 1 CONNECTORS | | | |* | | | | | |* | | | | | |* | | | ---------------------------------------------------------------------------Table 11: ADR Data Users - The IR portion of the ADIRU provides four identical ARINC 429 High-Speed buses. The system users are described in the table below: ------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |-----------------------------------------------------------------------| |FAC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FAC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |ELAC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |ELAC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 1 | | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 2 | | * | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 3 | | | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 1 | * | | | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 3 | | | * | | | | * | | * | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |CDU | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FMGC 1 | | | * | | | | * | | | | * | |

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------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |-----------------------------------------------------------------------| |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FMGC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FQIC | | * | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |BSCU | | * | | | | | * | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |CFDIU | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPWC (1)| | | * | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |WR 1 | | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |WR 2 (1)| | | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |TCAS | | | * | | | | | | | | | | |/T2CAS(1) | | | | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMU (1)| | * | | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPS 1 (1)| | * | | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPS 2 (1)| | | | | * | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |MMR 1 (1)| | * | | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |MMR 2 (1)| | | * | | | * | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |RMI-VOR/DME| | * | | | | | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |RMI-ADF (1)| | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |TEST PLUG | | | * | | | * | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |ISIS | | * | | | | | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |MCDU 1 | | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |MCDU 2 | | | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |ATC 1 | | * | | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----|

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------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |-----------------------------------------------------------------------| |ATC 2 | | | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |PVIS (1)| | | | | | | * | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SATCOM (1)| | * | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |HFDR 1 (1)| | | * | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |HFDR 2 (1)| | | | | | * | | | | | | | ------------------------------------------------------------------------(1) Optional system Table 12 : IR Data Users - Basic version - The IR portion of the ADIRU provides four identical ARINC 429 High-Speed buses. The system users are described in the table below: ----------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |---------------------------------------------------------------------------| |FAC 1 | | | * | | | | * | | | | * | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |FAC 2 | | * | | | | * | | | | * | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |ELAC 1 | | | * | | | | * | | | | * | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |ELAC 2 | | * | | | | * | | | | * | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 1 | | | * | | | | | | | | * | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 2 | | * | | | | * | | | | | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 3 | | | | | | * | | | | * | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 1 | * | | | | | | | | | | * | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 2 | | | | | | * | | | | * | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 3 | | | * | | | | * | | * | | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----|

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----------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |---------------------------------------------------------------------------| |CDU | | * | | | | * | | | | * | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |FMGC 1 | | | * | | | | * | | | | * | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |FMGC 2 | | * | | | | * | | | | * | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |FQIC | | * | | | | * | | | | | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |BSCU | | * | | | | | * | | | * | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |CFDIU | | | * | | | | * | | | | * | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |GPWC | | | * | | | | | | | | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |WR 1 | | | * | | | | | | | | * | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |WX 2 | | | | | | * | | | | * | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |DMU | | * | | | | | * | | | | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |RMI-VOR/DME | | * | | | | | | | | * | | | |---------------|----|----|----|----|----|----|----|----|----|----|----|----| |TEST PLUG | | | * | | | * | | | | | * | | ----------------------------------------------------------------------------Table 12 : IR Data Users - Basic version

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(f) Analog outputs The ADIRUs, through analog outputs, supply the ADMs with +13.5/-13.5 VDC and the CDU with 28 VDC. (g) Discrete outputs The discrete outputs are either open/ground or open/28 VDC discretes (for ON BAT, IR FAILURE WARNING and ALIGN NOT READY discretes). The LOW SPEED WARNING discretes are set according to a speed threshold (with a hysteresis of 4 knots). These thresholds are respectively: --------------------------------|Lower threshold|Upper threshold| | value | value | --------------------------|---------------|---------------| | LOW SPEED WARNING 1 | 100 | 104 | | LOW SPEED WARNING 2 | 50 | 54 | | LOW SPEED WARNING 3 | 155 | 159 | | LOW SPEED WARNING 4 | 260 | 264 | ----------------------------------------------------------The LOW SPEED WARNING 1 discrete is used in the Ram Air Turbine extension logic and in the power generation logic. The LOW SPEED WARNING 2 discrete is used in the power generation logic. The following discretes are used to control the CDU annunciators: - ON BAT - ADR OFF - ADR FAILURE WARNING - IR FAILURE WARNING - IR ALIGN.

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4. _____________________ Component Description A. ADIRS CDU (Ref. Fig. 005) The CDU is a three-channel unit. Each CDU channel has the following features: - a three-position mode selector switch. The modes are: . power off (OFF) . navigation (NAV) . reversionary attitude (ATT) - an indicator announcing when the IR is aligning (ALIGN legend of IR annunciator) - an IR fault indicator (FAULT legend of the IR annunciator) - a pushbutton switch to disable ADR output buses. It is a momentary action pushbutton switch - an indicator announcing when the ADR output buses are turned off (OFF legend of the ADR pushbutton switch) - an ADR fault indicator (FAULT legend of the ADR pushbutton switch). The following items of equipment are shaped between the three channels: - a keyboard to enter the initial position in degrees, minutes and tenth of minutes or magnetic heading in the attitude mode - two data pushbutton switches (ENT and CLR) with cue lights - a liquid crystal display for selected parameters. The LCD has 16 digits and each digit has 14 segments - a DATA DISPLAY selector switch to select parameters for display on the LCD: * wind (WIND) * present position (PPOS) * true heading (HDG) * status of selected system (STS) * track and ground speed (TK/GS) * test values (TEST) - a SYS DISPLAY selector switch with four positions: OFF, 1, 2, 3. The OFF position disables the display of the CDU but the mode control of the ADIRUs remains active - an ON BAT annunciator. The CDU contains three identical connectors referenced J1, J2 and J3. (Ref. Fig. 006) This LRU uses an Intel 8031 microprocessor. The CDU receives an IR bus from each ADIRU to display navigation data. It provides one bus per ADIRU to permit IR initialization. (Ref. Fig. 007) No cooling air is provided to the CDU. The CDU is supplied with 28 VDC from the selected ADIRU to drive internal circuits and the data display. The 28 VDC inputs are isolated from each other. The aircraft supplies 5 VAC power for panel lighting/LCD backlighting and for annunciator lighting.

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ADIRS CDU - Internal Block Diagram Figure 007   EFF : 524-526, 528-599,  34-12-00 Page 25   Config-2 Feb 01/10  CES

 

B. ADIRU (Ref. Fig. 008) (1) General The ADIRU is contained in a 4 MCU case as defined in ARINC 600. The ADIRU has to be aligned on a special shelf in the avionics compartment in accordance with the installation design described in ARINC 738. This installation involves modification of the ARINC 600 standard to include three alignment pins and a floating connector. Pins 12 and 13 of the bottom plug have been modified with a reducer to accept power input instead of coax input as defined in ARINC 738. All input discretes are electrically isolated by an in-line diode or an equivalent device. The discrete outputs are protected by means of diodes to permit a wired OR circuit with other outputs. The ADIRU is designed to reach a high level of protection for lightning and Electromagnetic Interference (EMI). The lightning protection circuitry is made up of discrete components which consist of high-powered Zener diode type semiconductors called Transzorbs. Varistors are used on the power supply input lines. Varistors are voltage-controlled resistors that go to a low impedance state when a voltage above their clamp voltage is applied, thus shunting the lightning current. As each ADIRU is a common point to all engines installed on the aircraft, special care is taken to make impossible any electrical disturbance to propagate through the ADIRU/engine interface to other inputs/outputs dedicated to engines. The ADIRU contains an ADR and an IR portion supplied by a common power (115 VAC,28 VDC). (2) ADR portion (Ref. Fig. 009) This portion uses a 68000 microprocessor. Five resolvers can be used for the analog baro-correction and the AOA inputs. The ADR provides eight ARINC 429 Low-Speed output buses (buses 5 to 8 are reserved for engine control). A bus isolation is provided using in-line fuses in all ADR buses 5-8 reserved to the engine control. Each bus can drive twenty ARINC bus loads. (3) IR portion (Ref. Fig. 010) This portion uses a 80960 microprocessor. It provides a high-voltage power supply used by the gyros. The gyros/accel sensor block contains three accels and three gyros mounted along each axis. The IR provides four ARINC 429 High-Speed output buses. Each bus can drive twenty loads.

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ADIRU - Block Diagram Figure 010   EFF : 524-526, 528-599,  34-12-00 Page 29   Config-2 Feb 01/10  CES

 

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**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-523, Post SB 34-1249 For A/C 001-049,101-105,151-199,201-203, _______________________________________________________ AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRU & CDU OR MSU) DESCRIPTION AND OPERATION _________________________

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**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, 1. General _______ **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, The Air Data/Inertial Reference System (ADIRS) provides the main air data and heading/attitude/navigation data to the aircraft systems. The main computers of the ADIRS are the three Air Data/Inertial Reference Units (ADIRU) which are controlled by the ADIRS Control and Display Unit (CDU). The ADIRS is a three channel system. Each channel is isolated from the others and provides independent information as defined in ARINC 738. Each ADIRU contains: - an Air Data Reference (ADR) portion. Its operation is described in 34-13 - an Inertial Reference (IR) portion. Its operation is described in 34-14. Power supply is common for ADR and IR and described in 34-11.

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, The Air Data/Inertial Reference System (ADIRS) provides the main air data and heading/attitude/navigation data to the aircraft systems. The main computers of the ADIRS are the three Air Data/Inertial Reference Units (ADIRU) which are controlled by the ADIRS Mode Selector Unit (MSU). The ADIRS is a three-channel system. Each channel is isolated from the others and provides independent information as defined in ARINC 738. Each ADIRU contains: - An Air Data Reference (ADR) portion. Its operation is described in 34-13. - An Inertial Reference (IR) portion. Its operation is described in 34-14. The power supply is common for the ADR and IR and described in 34-11.

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**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, 2. __________________ Component Location

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**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 001, 002) The three ADIRUs are installed in the avionics compartment. The ADIRS CDU is installed in the cockpit. ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1FP1 ADIRU-1 127 824 34-12-34 1FP2 ADIRU-2 128 824 34-12-34 1FP3 ADIRU-3 127 824 34-12-34 2FP CDU-ADIRS 20VU 211 831 34-12-12

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ADIRS - Component Location Figure 001   R EFF : 051-099, 106-149, 204-249, 251-299,  34-12-00 Page 3 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS CDU - Component Location Figure 002   R EFF : 051-099, 106-149, 204-239, 301-312,  34-12-00 Page 4 401-499,  Config-3 Feb 01/08  CES

 

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, L (Ref. Fig. 001, 002A) The three ADIRUs are installed in the avionics compartment. The ADIRS MSU is installed in the cockpit. ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1FP1 ADIRU-1 127 824 34-12-34 1FP2 ADIRU-2 128 824 34-12-34 1FP3 ADIRU-3 127 824 34-12-34 3. ______________ Not Applicable

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ADIRS MSU - Component Location Figure 002A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-12-00 Page 6 511-523,  Config-3 Feb 01/10  CES

 

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**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, 3. Interface _________ A. Mechanical Interface The ADIRUs are installed and aligned on a specific mounting tray in the avionics compartment in accordance with the installation design defined in ARINC 738. The ADIRU is to 4 MCU size. In order to ensure attitude and azimuth accuracy, the mounting tray orientation complies with the following tolerances: - pitch and roll: plus or minus 12 minutes - azimuth: plus or minus 12 minutes. **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, B. Electrical Interface (1) ADIRS CDU (a) General (Ref. Fig. 003) The ADIRS CDU contains three identical connectors. Each connector is linked to one ADIRU by means of an insert position keying. The four annunciator discretes ADR OFF, ADR FAULT, IR ALIGN and IR FAULT are linked to the ADIRS CDU from the ADIRU, through the annunciator light test and interface boards. The CDU panel lighting and LCD backlighting are provided by bulbs supplied with 5VAC (from the A/C electrical generation). The CDU exchanges data with the ADIRU. The data sent by the CDU can be used for the initialization of the IR portion. The data received by the CDU are displayed on the Liquid Crystal Display (LCD).

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ADIRS CDU - Electrical Interface Figure 003   R EFF : 051-099, 106-149, 204-239, 301-312,  34-12-00 Page 8 401-499,  Config-3 Feb 01/08  CES

 

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, B. Electrical Interface (1) ADIRS MSU (a) General (Ref. Fig. 003A) The ADIRS MSU contains three identical connectors. Each connector is linked to one ADIRU by means of an insert position keying. The four annunciator discretes ADR OFF, ADR FAULT, IR OFF and IR FAULT are linked to the ADIRS MSU from the ADIRU, through the annunciator light test and interface boards. **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (b) CDU Digital Form The tables below contain all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following tables give: - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds. - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code. - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system.

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CDU bus inputs The CDU receives an ARINC 429 High Speed bus from the IR portion of each ADIRU.

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 010 |PRESENT |90S-90N |DEG | | 6 | | BCD| | | |POS LAT-D |(POSITIVE: |& | | | | | | | | |NORTH FROM |MIN | | | | | | | | |0 DEG) | | | | | | | | | |RESOL = .1 | | | | | | | |-----------------------------------------------------------------------------| | 011 |PRESENT |180E-180W |DEG | | 6 | | BCD| | | |POS LONG-D |(POSITIVE: |& | | | | | | | | |EAST FROM |MIN | | | | | | | | |0 DEG) | | | | | | | | | |RESOL = .1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 012 |GROUND |0-2000 |Kt | | 4 | | BCD| | | |SPEED-D |(ALWAYS | | | | | | | | | |POSITIVE) | | | | | | | | | |RESOL = 1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 013 |TRACK |0-359.9 |DEG | | 4 | | BCD| | | |ANGLE TRUE |(POSITIVE: | | | | | | | | | |CW FROM | | | | | | | | | |NORTH) | | | | | | | | | |RESOL = .1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 014 |MAGNETIC |0-359.9 |DEG | | 4 | | BCD| | | |HEADING |(POSITIVE: | | | | | | | | | |CW FROM | | | | | | | | | |NORTH) | | | | | | | | | |RESOL = .1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 015 |WIND SPEED |0-256 |Kt | | 3 | | BCD| | | | |(ALWAYS | | | | | | | | | |POSITIVE) | | | | | | | | | |RESOL = 1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 016 |WIND DIR |0-359 |DEG | | 3 | | BCD| | | |TRUE |(POSITIVE: | | | | | | | | | |CW FROM | | | | | | | | | |NORTH) | | | | | | | | | |RESOL = 1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 044 |TRUE |0-359.9 |DEG | | 4 | | BCD| | | |HEADING |(POSITIVE: | | | | | | | | | |CW FROM | | | | | | | | | |NORTH) | | | | | | | | | |RESOL = .1 | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 270 |IR DISCRETE| | | | 19 | | DIS| | | |(1) | | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 277 |CDU TEST | | | | 18 | | DIS| | | |WORD (1) | | | | | | | | |--------------|-----------|-----------|----|---|----|----|----|--------------| | 350 |ACTION | | | | 19 | | DIS| | | |CODE (1) | | | | | | | | ------------------------------------------------------------------------------CDU IR Input Labels NOTE : (1) The complete definition of the labels 270, 277 and ____ 350 is detailed in 34-14-00 Para. 2.D.(1).

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CDU bus outputs The CDU sends the parameters detailed in the following table to the IR portion of each ADIRU:

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 041 |SET | 90S-90N |DEG | | 6 | | BCD| | | |LATITUDE | (POSITIVE: |& | | | | | | | | | NORTH) |MIN | | | | | | | | | RESOL = 0.1| | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 042 |SET | 180E-180W |DEG | | 6 | | BCD| | | |LONGITUDE | (POSITIVE: |& | | | | | | | | | EAST) |MIN | | | | | | | | | RESOL = 0.1| | | | | | | |--------------|----------| -----------|----|----|----|----|----|-------------| | 043 |SET | 0-359 |DEG | | 3 | | BCD| | | |MAGNETIC | (POSITIVE: | | | | | | | | |HDG | CW FROM N) | | | | | | | | | | RESOL = 1 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 277 |CDU TEST | | | | 19 | | DIS| | ------------------------------------------------------------------------------CDU Output Labels (2) ADIRU The ADIRU receives data and computes outputs in accordance with ARINC 738. It uses an ARINC 600 type 2 floating-connector. (a) Digital inputs - Air Data Module (ADM) inputs The ADR provides up to five ADM input buses. Only three of them are used to receive air mass data from remotely mounted ADM (Ref. 34-11), two linked to the static probe and one linked to the pitot probe. NOTE : For the ADIRU 3, only two ADM input buses are used: one ____ for the total pressure data and the other for the averaged static pressure data.

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- digital baro-correction inputs The ADR provides two baro-correction digital data input ports. The incoming data from the Flight Control Unit (FCU) are in ARINC 429 low speed format. The ADR receives data from baro-correction bus A. The baro-correction is used to compensate baro-corrected altitude output. - initialization data inputs The IR portion of the ADIRU receives data from either ARINC 702 Flight Management and Guidance Computer (FMGC). The data are in ARINC 429 low speed format. The initialization parameters are latitude and longitude or magnetic heading. - CFDIU input The ADIRU provides one Centralized Fault Display Interface Unit (CFDIU) input bus. The data are in ARINC 429 low speed format. The CFDIU continuously transmits data to all systems. The ADIRU uses these data to accept commands from the CFDIU. - Air Data Reference inputs The IR portion of the ADIRU provides two digital data input ports for receiving data from the other ADIRUs. The incoming data are in ARINC 429 low speed format and include altitude and true airspeed. - CDU inputs The IR portion of the ADIRU receives data from one ARINC 738 CDU. The data are in ARINC 429 low speed format. These data are initialization parameters (latitude and longitude or magnetic heading) and CDU status. - GPS inputs The IR portion of the ADIRU receives data from the GPS portion of the Multi-Mode Receivers (MMRs). The data are in ARINC 429 high speed format. These data concern various parameters such as position, velocity, and integrity. - the ADIRU provides provision for digital input buses. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (2) ADIRU The ADIRU receives data and computes outputs in accordance with ARINC 738. It uses an ARINC 600 type-2 floating-connector. (a) Digital inputs - Air Data Module (ADM) inputs The ADR provides up to five ADM input buses. Only three of them are used to receive air mass data from remotely-mounted ADM (Ref. 34-11), two linked to the static probe and one linked to the pitot probe.

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NOTE : For the ADIRU 3, only two ADM input buses are used: one ____ for the total pressure data and the other one for the averaged static pressure data. - Digital baro-correction inputs The ADR provides two baro-correction digital data input ports. The data incoming from the Flight Control Unit (FCU) is in ARINC 429 low-speed format. The ADR receives data from baro-correction bus A. The baro-correction is used to compensate baro-corrected altitude output. - Initialization data inputs The IR portion of the ADIRU receives data from either ARINC 702 Flight Management and Guidance Computer (FMGC). The data is in ARINC 429 low-speed format. The initialization parameters are latitude and longitude or magnetic heading. - CFDIU input The ADIRU provides one Centralized Fault Display Interface Unit (CFDIU) input bus. The data is in ARINC 429 low-speed format. The CFDIU continuously transmits data to all systems. The ADIRU uses this data to accept commands from the CFDIU. - Air Data Reference inputs The IR portion of the ADIRU provides two digital data input ports for receiving data from the other ADIRUs. The incoming data are in ARINC 429 low-speed format and includes altitude and true airspeed. - GPS inputs The IR portion of the ADIRU receives data from the GPS portion of the Multi-Mode Receivers (MMRs). The data is in ARINC 429 high-speed format. This data is related to various parameters such as position, velocity and integrity. - The ADIRU has provision for digital input buses. R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (b) Analog inputs - analog AOA input The ADR portion of the ADIRU accepts two resolver inputs of indicated angle of attack. The characteristics of the resolvers, as seen by the ADR, are as follows: . scale factor: 1⁰/Degree of AOA . index reference: 0⁰ resolver input = 25⁰ AOA - Total Air Temperature (TAT) sensor The ADR portion of the ADIRU accepts a standard 500 ohm platinum sensing element input from the TAT sensor. The ADR derives the measured temperature from the TAT sensor input using the Callender-Van Dusen equation from ARINC 738. - GPS Time Mark inputs

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This allows the ADIRU to be synchronized with the GPS portion of the MMRs. - 115VAC The ADIRU operates from the 115VAC/400 Hz primary power. - 28VDC back-up The ADIRU can operate from the 28VDC back-up power. - 26VAC reference The ADIRU accepts up to three 26VAC resolver reference inputs. Only one is used for the AOA resolver. The ADIRU provides provisions for analog inputs (two 26VAC reference inputs, and three analog baro-correction inputs are reserved).

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INTENTIONALLY BLANK

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**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (c) Discrete inputs These inputs are generally pin programs except for: - Static Source Error Correction (SSEC) and AOA correction and selection discretes which come from the Slat and Flap Control Computers (SFCC) and are linked to flap position (Ref. Fig. 004) - heat discretes which come from the associated Probe Heat Computer (PHC) - VMO/MMO discrete provided by the position of the L/G DOWN VMO/MMO SELECTION switch (22FP). - ADR selection: It indicates, to the IR, the air data source to be used. - CDU ON/OFF: It indicates, to the ADIRU, whether the ADIRU data are currently displayed on the CDU. - ADR OFF: It indicates, to the ADIRU, that the crew has pushed the ADR pushbutton switch on the ADIRS CDU. This commands the ADIRU to stop the transmission of the ADR output buses. - IR MODE SELECT: It indicates, to the ADIRU, the position of the associated selector switch on the CDU. Three positions can be coded: OFF, NAV, ATT. This gives the computer operating mode. The functions of the pin program discretes are: - aircraft identification: seven discretes provide the ADIRU with the identification of the aircraft. They are used by the ADR to select the appropriate SSEC and AOA correction laws and by the IR to select the appropriate filtering (bandwidth) of the output labels. - baro-correction source selection: This discrete provides the ADIRU with the following: . the form (digital or analog) in which the baro-correction transmission is made . the number of sources (2 or 3) . the type of transmission used by the digital sources (single bus or various buses). On the A/C, the FCU transmits the CAPT and F/O baro-correction in digital form on separate buses. - AOA average/unique: The ADIRU receives the AOA on two resolvers.

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This discrete indicates whether the computation must use an average value from the two resolvers or the value of resolver 1 in priority with the second as a back-up in case of failure. This last solution is chosen on the A/C. ADR ARINC the filter select: Unused (the selection of the ADR outputs filtering is done by the A/C ident pin programming). mounting position: This indicates the orientation of the unit to the IR portion. It is used to know where are the longitudinal and lateral axes of the aircraft and the sign of motion measured. SDI: This indicates on which side (CAPT, F/O, Standby) the ADIRU is installed. CMC-CFDS message select: The ADIRU could be installed on other A/C version. In this case, the ADIRU selects a table of maintenance messages with a different syntax.

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (c) Discrete inputs These inputs are generally pin programs except for: - Static Source Error Correction (SSEC) and AOA correction and selection discretes which come from the Slat and Flap Control Computers (SFCC) and are linked to flap position (Ref. Fig. 004) - heat discretes which come from the associated Probe Heat Computer (PHC) - VMO/MMO discrete provided by the position of the L/G DOWN VMO/MMO SELECTION switch (22FP). - ADR selection: It indicates, to the IR, the air data source to be used. - ADR OFF, IR OFF: It indicates, to the ADIRU, that the crew has pushed the ADR pushbutton switch on the ADIRS MSU. This commands the ADIRU to stop the transmission of the ADR output buses. - IR MODE SELECT: It indicates, to the ADIRU, the position of the associated selector switch on the MSU. Three positions can be coded: OFF, NAV, ATT. This gives the computer operating mode. The functions of the pin program discretes are: - aircraft identification: seven discretes provide the ADIRU with the identification of the aircraft. They are used by the ADR to select the appropriate SSEC and AOA correction laws and by the IR to select the appropriate filtering (bandwidth) of the output labels. - baro-correction source selection: This discrete provides the ADIRU with the following: . the form (digital or analog) in which the baro-correction transmission is made . the number of sources (2 or 3) . the type of transmission used by the digital sources (single bus or various buses). On the A/C, the FCU transmits the CAPT and F/O baro-correction in digital form on separate buses. - AOA average/unique: The ADIRU receives the AOA on two resolvers. This discrete indicates whether the computation must use an average value from the two resolvers or the value of resolver 1 in priority with the second as a back-up in case of failure. This last solution is chosen on the A/C. - ADR ARINC the filter select:

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Unused (the selection of the ADR outputs filtering is done by the A/C ident pin programming). - mounting position: This indicates the orientation of the unit to the IR portion. It is used to know where are the longitudinal and lateral axes of the aircraft and the sign of motion measured. - SDI: This indicates on which side (CAPT, F/O, Standby) the ADIRU is installed. - CMC-CFDS message select: The ADIRU could be installed on other A/C version. In this case, the ADIRU selects a table of maintenance messages with a different syntax. R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, - GPS sensor present: This indicates, to the ADIRU, the presence on-board the aircraft of one or two MMRs (GPS portion). - GPS priority select: This indicates, to the ADIRU, the priority for using the MMRs (GPS portion).

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**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-523, - Mag. Var. select: This discrete selects between two different magnetic variation tables: * one standard coverage model optimized for year 2010 and one expanded coverage model optimized for year 2015. **ON A/C 001-049, 052-052, 101-149, 151-199, 201-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, - Mag. Var. select: This discrete selects between two different magnetic variation tables: * one standard coverage model optimized for year 2005 and one expanded coverage model optimized for year 2010.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-12-00 Page 22 201-249, 251-299, 301-399, 401-499, 501-509,  Config-3 Feb 01/10 511-523, CES

 

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**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (d) Digital outputs - The ADR portion of the ADIRU provides eight identical ARINC 429 Low Speed buses. Two of these buses are dedicated to the interface with the Electronic Control Units (ECU). The number of these buses is 5 and 6. The system users are described in the table below: ---------------------------------------------------------------------------| USERS | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |ADIRU 1 | | | | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 2 | |* | | | | | | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ADIRU 3 | | |* | | | | | | |* | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FMGC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 1 |* | | | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 2 | | | | | | |* | | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMC 3 | | |* | | | | | |* | | | |* | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |WR 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |WR 2 (1)| | | | | | | | | |* | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 1 | | | |* | | | | | | | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ATC 2 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FWC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CFDIU | | | |* | | | | | |* | | | | | |* | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ECU or EEC ENG 1 | | | | |* | | | | | |* | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|

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---------------------------------------------------------------------------| USERS | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS | | |-----------------|-----------------|-----------------| | |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 | |--------------------------------------------------------------------------| |ECU or EEC ENG 2 | | | | | |* | | | | | |* | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SFCC 1 | | |* | | | | | |* | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SFCC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |FAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 1 | | |* | | | | | |* | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ELAC 2 | |* | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 1 | | |* | | | | | | | | | | | |* | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 2 | |* | | | | | |* | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |SEC 3 | | | | | | | |* | | | | | |* | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |AOA CAPT INDIC. (1)| | | |* | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |AOA F/O INDIC. (1)| | | | | | | | | |* | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |GPWC (1)| | | |* | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |DMU (1)| |* | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN PRESSURE | | |* | | | | | | |* | | | | |* | | | | |CONTROLLER1 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |CABIN PRESSURE | | | |* | | | |* | | | | | | | |* | | | |CONTROLLER2 | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |ZONE TEMPERATURE | | | | | | | | | | | | | | | |* | | | |CONTROLLER | | | | | | | | | | | | | | | | | | | |--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--| |TEST 1 CONNECTORS | | | |* | | | | | |* | | | | | |* | | | ---------------------------------------------------------------------------(1) Optional system Table 11 : ADR Data Users

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**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, - The IR portion of the ADIRU provides four identical ARINC 429 High Speed buses. The system users are described in the table below: ------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |-----------------------------------------------------------------------| |FAC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FAC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |ELAC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |ELAC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 1 | | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 2 | | * | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 3 | | | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 1 | * | | | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 2 | | | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 3 | | | * | | | | * | | * | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |CDU | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FMGC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FMGC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FQIC | | * | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |BSCU | | * | | | | | * | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |CFDIU | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPWC (1)| | | * | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |WR 1 | | | * | | | | | | | | * | |

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------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |-----------------------------------------------------------------------| |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |WR 2 (1)| | | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |TCAS (1)| | | | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMU (1)| | * | | | | | * | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPS 1 (1)| | * | | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPS 2 (1)| | | | | * | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |MMR 1 (1)| | * | | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |MMR 2 (1)| | | * | | | * | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SDU | | | | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |RMI-VOR/DME| | * | | | | | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |RMI-ADF (1)| | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |TEST PLUG | | | * | | | * | | | | | * | | ------------------------------------------------------------------------(1) Optional system Table 12 : IR Data Users - Basic version

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(e) Analog outputs The ADIRUs, through analog outputs, supply the ADMs with +13.5/-13.5VDC and the CDU with 28VDC. (f) Discrete outputs The discrete outputs are either open/ground or open/28VDC discretes (for ON BAT, IR FAILURE WARNING and ALIGN NOT READY discretes). The LOW SPEED WARNING discretes are set according to a speed threshold (with an hysteresis of 4 knots). These thresholds are respectively: --------------------------------|Lower threshold|Upper threshold| | value | value | --------------------------|---------------|---------------| | LOW SPEED WARNING 1 | 100 | 104 | | LOW SPEED WARNING 2 | 50 | 54 | | LOW SPEED WARNING 3 | 155 | 159 | | LOW SPEED WARNING 4 | 260 | 264 | ----------------------------------------------------------The LOW SPEED WARNING 1 discrete is used in the Ram Air Turbine extension logic and in the power generation logic. The LOW SPEED WARNING 2 discrete is used in the power generation logic. The following discretes are used to control the CDU annunciators: - ON BAT - ADR OFF - ADR FAILURE WARNING - IR FAILURE WARNING - IR ALIGN.

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, - The IR portion of the ADIRU provides four identical ARINC 429 high-speed buses. The system users are described in the table below: ------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |-----------------------------------------------------------------------| |FAC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FAC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |ELAC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |ELAC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 1 | | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 2 | | * | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SEC 3 | | | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 1 | * | | | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 2 | | | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMC 3 | | | * | | | | * | | * | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FMGC 1 | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FMGC 2 | | * | | | | * | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |FQIC | | * | | | | * | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |BSCU | | * | | | | | * | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |CFDIU | | | * | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPWC (1)| | | * | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |WR 1 | | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |WR 2 (1)| | | | | | * | | | | | | |

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------------------------------------------------------------------------| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS | | |-------------------|-------------------|-------------------| | | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | |-----------------------------------------------------------------------| |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |TCAS (1)| | | | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |DMU (1)| | * | | | | | * | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPS 1 (1)| | * | | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |GPS 2 (1)| | | | | * | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |MMR 1 (1)| | * | | | | | * | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |MMR 2 (1)| | | * | | | * | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |SDU | | | | | | | | | | | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |RMI-VOR/DME| | * | | | | | | | | * | | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |RMI-ADF (1)| | | * | | | | | | | | * | | |-----------|----|----|----|----|----|----|----|----|----|----|----|----| |TEST PLUG | | | * | | | * | | | | | * | | ------------------------------------------------------------------------(1) Optional system Table 12 : IR Data Users - Basic version

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(e) Analog outputs The ADIRUs, through analog outputs, supply the ADMs with +13.5/-13.5 VDC. (f) Discrete outputs The discrete outputs are either open/ground or open/28 VDC discretes (for ON BAT, IR FAILURE WARNING and IR OFF discretes). The LOW SPEED WARNING discretes are set according to a speed threshold (with a hysteresis of 4 knots). These thresholds are respectively: --------------------------------|Lower threshold|Upper threshold| | value | value | --------------------------|---------------|---------------| | LOW SPEED WARNING 1 | 100 | 104 | | LOW SPEED WARNING 2 | 50 | 54 | | LOW SPEED WARNING 3 | 155 | 159 | | LOW SPEED WARNING 4 | 260 | 264 | ----------------------------------------------------------The LOW SPEED WARNING 1 discrete is used in the Ram Air Turbine extension logic and in the power generation logic. The LOW SPEED WARNING 2 discrete is used in the power generation logic. The following discretes are used to control the MSU annunciators: - ON BAT - ADR OFF - IR OFF - ADR FAILURE WARNING - IR FAILURE WARNING.

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**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, 4. _____________________ Component Description **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, A. ADIRS CDU (Ref. Fig. 005) The CDU is a three-channel unit. Each CDU channel includes the following features: - a three-position mode selector switch. The modes are: . power off (OFF) . navigation (NAV) . reversionary attitude (ATT) - an indicator announcing when the IR is aligning (ALIGN legend of IR annunciator) - an IR fault indicator (FAULT legend of IR annunciator) - a pushbutton switch to disable ADR output buses. It is a momentary action pushbutton switch - an indicator announcing when the ADR output buses are turned off (OFF legend of ADR pushbutton switch) - an ADR fault indicator (FAULT legend of ADR pushbutton switch). The following items of equipment are shaped between the three channels : - a keyboard to enter the initial position in degrees, minutes and tenth of minutes or magnetic heading in the attitude mode - two data pushbutton switches (ENT and CLR) with cue lights - a liquid crystal display for selected parameters. The LCD has 16 digits and each digit has 14 segments - a DATA DISPLAY selector switch to select parameters for display on the LCD: * wind (WIND) * present position (PPOS) * true heading (HDG) * status of selected system (STS) * track and ground speed (TK/GS) * test values (TEST) - a SYS DISPLAY selector switch with four positions: OFF, 1, 2, 3. The OFF position disables the display of the CDU but the mode control of the ADIRUs remains active - an ON BAT annunciator. The CDU contains three identical connectors referenced J1, J2 and J3. (Ref. Fig. 006) This LRU uses an Intel 8031 microprocessor. The CDU receives an IR bus from each ADIRU to display navigation data. It provides one bus per ADIRU to permit IR initialization.

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ADIRS CDU Figure 005   R EFF : 051-099, 106-149, 204-239, 301-312,  34-12-00 Page 32 401-499,  Config-3 Aug 01/08  CES

 

ADIRS MSU Figure 005A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-12-00 Page 33 511-523,  Config-3 Feb 01/10  CES

 

ADIRS CDU - Identical Connectors Figure 006   R EFF : 051-099, 106-149, 204-239, 301-312,  34-12-00 Page 34 401-499,  Config-3 Aug 01/08  CES

 

(Ref. Fig. 007) R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, A. ADIRS MSU (Ref. Fig. 005A) The MSU is a three-channel unit. Each MSU channel is dedicated to one separate ADIRU and includes the following features: - a three-position mode selector switch. The modes are: . power off (OFF) . navigation (NAV) . reversionary attitude (ATT) - a pushbutton switch to disable IR output buses. It is a momentary action pushbutton switch - an indicator announcing when the IR output buses are turned off (OFF legend IR pushbutton switch) - an IR fault indicator (FAULT legend of IR annunciator) - a pushbutton switch to disable ADR output buses. It is a momentary action pushbutton switch - an indicator announcing when the ADR output buses are turned off (OFF legend of ADR pushbutton switch) - an ADR fault indicator (FAULT legend of ADR pushbutton switch). An ON BAT annunciator is shared by the three channels. The MSU contains three identical connectors referenced J1, J2 and J3. (Ref. Fig. 006A) **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, No cooling air is provided to the CDU. The CDU is supplied with 28VDC from the selected ADIRU to drive internal circuits and the data display. The 28VDC inputs are isolated from each other. The aircraft supplies 5VAC power for panel lighting/LCD backlighting and for annunciator lighting.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-12-00 Page 35 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS MSU - Identical Connectors Figure 006A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-12-00 Page 36 511-523,  Config-3 Feb 01/10  CES

 

ADIRS CDU - Internal Block Diagram Figure 007   R EFF : 051-099, 106-149, 204-239, 301-312,  34-12-00 Page 37 401-499,  Config-3 Aug 01/08  CES

 

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, B. ADIRU (Ref. Fig. 008) (1) General The ADIRU is contained in a 4 MCU case as defined in ARINC 600. The ADIRU has to be aligned on a special shelf in the avionics compartment in accordance with the installation design described in ARINC 738. This installation involves modification of the ARINC 600 standard to include three alignment pins and a floating connector. Pins 12 and 13 of the bottom plug have been modified with a reducer to accept power input instead of coax input as defined in ARINC 738. All input discretes are electrically isolated by an in-line diode or an equivalent device. The discrete outputs are protected by means of diodes to permit a wired OR circuit with other outputs. The ADIRU is designed to reach a high level of protection for lightning and Electromagnetic Interference (EMI). The lightning protection circuitry is made up of discrete components which consist of high-powered Zener diode type semiconductors called Transzorbs. Varistors are used on the power supply input lines. Varistors are voltage-controlled resistors that go to a low impedance state when a voltage above their clamp voltage is applied, thus shunting the lightning current. As each ADIRU is a common point to all engines installed on the aircraft, special care is taken to make impossible any electrical disturbance to propagate through the ADIRU/engine interface to other inputs/outputs dedicated to engines. The ADIRU contains an ADR and an IR portion supplied by a common power (115VAC, 28VDC). (2) ADR portion (Ref. Fig. 009) This portion uses a 68000 microprocessor. Five resolvers can be used for the analog baro-correction and the AOA inputs. The ADR provides eight ARINC 429 Low-Speed output buses (buses 5 to 8 are reserved for engine control). A bus isolation is provided using in-line fuses in all ADR buses 5-8 reserved to the engine control. Each bus can drive twenty ARINC bus loads.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-12-00 Page 38 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS - General View Figure 008   R EFF : 051-099, 106-149, 204-249, 251-299,  34-12-00 Page 39 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRU - Block Diagram Figure 009   R EFF : 051-099, 106-149, 204-249, 251-299,  34-12-00 Page 40 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

(3) IR portion (Ref. Fig. 009) This portion uses a 80960 microprocessor. It provides a high-voltage power supply used by the gyros. The gyros/accel sensors block contains three accels and three gyros mounted along each axis. The IR provides four ARINC 429 High-Speed output buses. Each bus can drive twenty loads.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-12-00 Page 41 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

CONTROL AND DISPLAY UNIT (CDU) - ADIRS (2FP) - REMOVAL/INSTALLATION ___________________________________________________________________ TASK 34-12-12-000-001 Removal of the ADIRS CDU (2FP) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-12-12-991-001

Fig. 401

3. __________ Job Set-up Subtask 34-12-12-010-050 A. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105 VU: - loosen the two screws and remove the protective cover.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-12-12 201-239, 301-312, 401-499,   CES

 

Page 401 Feb 01/08

Subtask 34-12-12-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU R

ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

N07 N06 N05 N04

4FP2 4FP3 6FP2 6FP3

N06 N05 N04 N03

**ON A/C 062-099, 106-149, 151-199, 204-239, 301-312, 401-499, 121VU 121VU 121VU 121VU

R

4FP2 4FP3 6FP2 6FP3

ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, 122VU 122VU 122VU 122VU

LIGHTING/TST/BOARD/SPLY LIGHTING/ANN LT SPLY/XFMR/BUS 2 LIGHTING/ANN LT SPLY/XFMR/BUS 1 LIGHTING/INSTL LT/OVHD/PNL

30LP 27LP 26LP 3LF

X06 X05 X04 Y03

4. Procedure _________ (Ref. Fig. 401/TASK 34-12-12-991-001) Subtask 34-12-12-020-050 A. Removal of the ADIRS CDU (2FP) (1) Hold the CDU (4) and loosen the four quarter turn fasteners (5). (2) Disengage the CDU (4) from its housing (1). (3) Disconnect the three electrical connectors (2).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-12-12 201-239, 301-312, 401-499,   CES

 

Page 402 Feb 01/08

ADIRS - Control and Display Unit (CDU) Figure 401/TASK 34-12-12-991-001   R EFF : 001-049, 051-099, 101-149, 151-199,  34-12-12 201-239, 301-312, 401-499,   CES

 

Page 403 Feb 01/08

(4) Remove the CDU (4). (5) Put blanking caps on the disconnected electrical connectors (2) and (3).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-12-12 201-239, 301-312, 401-499,   CES

 

Page 404 Feb 01/08

TASK 34-12-12-400-001 Installation of the ADIRS CDU (2FP) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-10-00-710-001 34-12-12-991-001

Check of the ADIRS CDU Brightness and Display Fig. 401

3. __________ Job Set-up Subtask 34-12-12-010-051 A. Get Access (1) Make sure that the access platform is in position at the access door 822. (2) Make sure that the access door 822 is open. (3) Make sure that the protective cover is removed from the battery power center 105VU.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-12-12 201-239, 301-312, 401-499,   CES

 

Page 405 Feb 01/08

Subtask 34-12-12-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU R

ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

N07 N06 N05 N04

4FP2 4FP3 6FP2 6FP3

N06 N05 N04 N03

**ON A/C 062-099, 106-149, 151-199, 204-239, 301-312, 401-499, 121VU 121VU 121VU 121VU

R

4FP2 4FP3 6FP2 6FP3

ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, 122VU 122VU 122VU 122VU

LIGHTING/TST/BOARD/SPLY LIGHTING/ANN LT SPLY/XFMR/BUS 2 LIGHTING/ANN LT SPLY/XFMR/BUS 1 LIGHTING/INSTL LT/OVHD/PNL

30LP 27LP 26LP 3LF

X06 X05 X04 Y03

4. Procedure _________ (Ref. Fig. 401/TASK 34-12-12-991-001) Subtask 34-12-12-420-050 A. Installation of the ADIRS CDU (2FP) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-12-12 201-239, 301-312, 401-499,   CES

 

Page 406 Feb 01/08

(3) Remove the blanking caps from the electrical connectors (2) and (3). (4) Make sure that the electrical connectors are clean and in the correct condition. (5) Connect the electrical connectors (2) to the related receptacles (3). (6) Install the CDU (4) in its housing (1). (7) Tighten the four quarter turn fasteners (5). Subtask 34-12-12-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 4FP1, 4FP2, 4FP3, 6FP1, 6FP2, 6FP3, 3LF, 26LP, 27LP, 30LP Subtask 34-12-12-710-050 C. Do the test of the ADIRS CDU brightness and display. (Ref. TASK 34-10-00-710-001) 5. Close-up ________ Subtask 34-12-12-860-050 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 34-12-12-410-050 B. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822 (4) Remove the access platform(s).

  EFF : 001-049, 051-099, 101-149, 151-199,  34-12-12 201-239, 301-312, 401-499,   CES

 

Page 407 Feb 01/08

___________________________________________________________ REFERENCE UNIT - AIR DATA/INERTIAL (ADIRU) (1FP1,1FP2,1FP3) ____________________ REMOVAL/INSTALLATION TASK 34-12-34-000-001 Removal of the ADIRU (1FP1, 1FP2, 1FP3) CAUTION : DO NOT REMOVE THE RACK OF THIS UNIT. _______ PRECISION ADJUSTMENT IS NECESSARY TO INSTALL THE RACK CORRECTLY. THE MANUFACTURER DOES THIS ADJUSTMENT BEFORE DELIVERY OF THE AIRCRAFT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-12-34-991-002

Fig. 401

3. __________ Job Set-up Subtask 34-12-34-010-050 A. Get Access (1) Put the access platform in position at the access door 822 (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover.

  EFF : ALL  34-12-34   R  CES

 

Page 401 May 01/04

(4) Put the access platform in position in the zone 128 at the acces door 824 (5) Open the access door 824 Subtask 34-12-34-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 1FP1 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 FOR 1FP2 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU R R

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/2/28VDC

10FP 5FP2 4FP2 6FP2

N11 N09 N07 N05

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/2/28VDC

10FP 5FP2 4FP2 6FP2

N10 N08 N06 N04

8FP

F09

9FP 5FP3 4FP3 6FP3

N10 N08 N06 N04

**ON A/C ALL FOR 1FP3 49VU NAV PROBES/ADIRU3/PWR/SWTG **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU

ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/3/28VDC

  EFF : ALL  34-12-34    CES

 

Page 402 Feb 01/10

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU

ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/3/28VDC

9FP 5FP3 4FP3 6FP3

N09 N07 N05 N03

**ON A/C ALL 4. Procedure _________ (Ref. Fig. 401/TASK 34-12-34-991-002) Subtask 34-12-34-020-050 A. Removal of the ADIRU (1FP1, 1FP2, 1FP3) NOTE : The procedure is the same for the three ADIRUs 1FP1, 1FP2 and ____ 1FP3. (1) Loosen the nuts (4). (2) Lower the nuts (4). (3) Pull the ADIRU (6) on its rack (3) to disconnected the electrical connectors (1). (4) Remove the ADIRU (6) from its rack (3). (5) Put blanking caps on the disconnected electrical connectors (1).

  EFF : ALL  34-12-34    CES

 

Page 403 Feb 01/10

R

Air Data/Inertial Reference Unit (ADIRU) Figure 401/TASK 34-12-34-991-002

  EFF : ALL  34-12-34    CES

 

Page 404 Feb 01/05

TASK 34-12-34-400-001 Installation of the ADIRU (1FP1, 1FP2, 1FP3) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------

R

22-97-00-710-001 34-13-00-740-002 34-14-00-740-001 52-41-00-410-002 34-12-34-991-002

Operational Test of the LAND CAT III Capability INTERFACE TEST of the ADR Interface Test of the IR Close the Avionics Compartment Doors after Access Fig. 401

3. __________ Job Set-up Subtask 34-12-34-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at the access door 824. (2) Make sure that the access door 824 is open.

  EFF : ALL  34-12-34    CES

 

Page 405 Feb 01/02

Subtask 34-12-34-010-051 B. Get Access (1) Make sure that the access platform is in position at the access door 822. (2) Make sure that the access door is open. (3) Make sure that the protective cover is removed from the battery power center 105VU. Subtask 34-12-34-865-051 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 1FP1 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 FOR 1FP2 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU R R

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/2/28VDC

10FP 5FP2 4FP2 6FP2

N11 N09 N07 N05

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/2/28VDC

10FP 5FP2 4FP2 6FP2

N10 N08 N06 N04

8FP

F09

**ON A/C ALL FOR 1FP3 49VU NAV PROBES/ADIRU3/PWR/SWTG

  EFF : ALL  34-12-34    CES

 

Page 406 Feb 01/10

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU R R

ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/3/28VDC

9FP 5FP3 4FP3 6FP3

N10 N08 N06 N04

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU

ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/3/28VDC

9FP 5FP3 4FP3 6FP3

N09 N07 N05 N03

**ON A/C ALL 4. Procedure _________ (Ref. Fig. 401/TASK 34-12-34-991-002) Subtask 34-12-34-420-050 A. Installation of the ADIRU (1FP1, 1FP2, 1FP3) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (1). (4) Make sure that the electrical connectors (1) are clean and in the correct condition. (5) Push the ADIRU (6) on its rack (3) to connect the electrical connectors (1). NOTE : Make sure that the ADIRU (6) correctly engages in the ____ centering pins (2). (6) Engage the nuts (4) on the lugs (5) and tighten.

  EFF : ALL  34-12-34    CES

 

Page 407 Feb 01/10

Subtask 34-12-34-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 1FP1 4FP1, 5FP1, 6FP1 FOR 1FP2 4FP2, 5FP2, 6FP2, 10FP FOR 1FP3 4FP3, 5FP3, 6FP3, 8FP, 9FP Subtask 34-12-34-740-050 C. BITE Test (1) Do the BITE Test of the ADIRS (Ref. TASK 34-13-00-740-002) (Ref. TASK 34-14-00-740-001). NOTE : If the airline operates the aircraft in CAT 3 conditions, do ____ the LAND CAT III capability test (Ref. TASK 22-97-00-710-001). (2) As an alternative procedure, you can do an operational test without the CFDS (installed ADIRU only) 5. Close-up ________ Subtask 34-12-34-860-051 A. Put the aircraft back to its initial configuration. (1) On the overhead panel 23VU, release and push the FLT CTL/ELAC1 and FLT CTL/SEC1 pushbutton switches (the OFF legend comes on and goes off). (2) On the overhead panel 24VU, release and push the FLT CTL/ELAC2, FLT CTL/SEC2 and FLT CTL/SEC3 pushbutton switches (the OFF legend comes on and goes off). (3) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-12-34   R  CES

 

Page 408 May 01/04

Subtask 34-12-34-410-050 B. Close Access R

(1) Close the access door 824 (Ref. TASK 52-41-00-410-002). (2) Install the protective cover on the battery power center 105VU. (3) Tighten the two screws. (4) Close the access door 822. (5) Remove the access platform(s).

  EFF : ALL  34-12-34    CES

 

Page 409 Feb 01/02

REFERENCE UNIT - AIR DATA/INERTIAL (ADIRU) (1FP1,1FP2,1FP3) - INSPECTION/CHECK ______________________________________________________________________________ TASK 34-12-34-200-001 ADIRU Removal Criteria 1. __________________ Reason for the Job To make sure that the performance parameters of the ADIRUs are satisfactory for operation in Class II navigation airspace in the range specified in the FAR drift rate requirement. To do this, do a check of the ADIRUs for: - Radial position errors - Residual ground speed errors. This procedure gives accurate removal criteria. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

R R

31-60-00-860-001 31-60-00-860-002 34-10-00-860-002 34-10-00-860-005 34-12-34-000-001 34-12-34-400-001 34-12-34-991-008 34-12-34-991-011 34-12-34-991-009

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure ADIRS Stop Procedure Removal of the ADIRU (1FP1, 1FP2, 1FP3) Installation of the ADIRU (1FP1, 1FP2, 1FP3) Fig. 601 Fig. 602 Fig. 603

  EFF : ALL  34-12-34    CES

 

Page 601 Aug 01/09

3. __________ Job Set-up Subtask 34-12-34-860-052 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) On the center pedestal, on the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is at NORM. 4. Procedure _________ Subtask 34-12-34-740-051 A. Radial Position Error (RPE) (Ref. Fig. 601/TASK 34-12-34-991-008, 602/TASK 34-12-34-991-011)

R

NOTE : At the end of the flight, the pilot must make an entry of the RPE ____ in the logbook. NOTE : Do this procedure only at the end of a flight: ____ - before the ADIRUs are off and - before you start a new alignment and - before you load a new flight plan into the FMGC. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the center pedestal, on one MCDU:

On the MCDU:

1. Push the line key adjacent to the FMGC indication

The FMGC page comes into view.

2. On the keyboard, push the DATA mode key

The DATA INDEX page comes into view.

3. Push the line key adjacent to the POSITION MONITOR indication

The POSITION MONITOR page comes into view.

  EFF : ALL  34-12-34    CES

 

Page 602 Aug 01/09

ADIRU - Radial Position Error - Removal Criteria Figure 601/TASK 34-12-34-991-008   EFF : ALL  34-12-34    CES

 

Page 603 May 01/03

R R

ADIRU Figure 602/TASK 34-12-34-991-011

  EFF : ALL  34-12-34    CES

 

Page 604 Aug 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------4. Record each IRS position error shown on line 5. (1) Calculate the NAV time of the ADIRU as follows: - record the flight time of the previous flight given in the logbook and add 30 minutes to this time. NOTE : This 30-minute period is the assumed time interval from the ____ end point of the ADIRU alignment and aircraft door closing before pushback. (2) Compare the recorded values with the curve at the time value calculated. (a) If the RPE is below the grey band (refer to AREA 1): - the ADIRU is serviceable and no action is necessary. (b) If the RPE is in the grey band (refer to AREA 2): - it is not necessary to replace the ADIRU but you must do a second check of the RPE immediately after the subsequent flight. If the RPE is again in the grey band, replace the ADIRU (Ref. TASK 34-12-34-000-001) and (Ref. TASK 34-12-34-400-001). (c) If the RPE is above the grey band (refer to AREA 3): - replace the ADIRU (Ref. TASK 34-12-34-000-001) and (Ref. TASK 34-12-34-400-001). **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-12-34-740-052 B. Residual Ground Speed Error NOTE : Do this procedure only at the end of a flight: ____ - before the ADIRUs are off and - before you start a new alignment. Record the residual ground speed for each IR at the end of the flight when the aircraft is fully stopped.

  R EFF : ALL  34-12-34    CES

 

Page 605 Aug 01/09

(1) Record the residual ground speed on the ADIRS CDU on the overhead panel (20VU): - set the DATA DISPLAY selector switch to TK/GS - set the SYS DISPLAY selector switch to 1, 2 and 3 - read the related ground speed on the ADIRS CDU display. NOTE : You can also read the ground speed on the CAPT ND (IR1) and ____ F/O ND (IR2). To read the residual ground speed for IR3 on the CAPT (F/O) ND, set the ATT HDG selector switch on the SWITCHING panel (8VU) to CAPT/3 (F/O/3). But, because of DMC processing, the ground speed value shown on the ND can be different from the value on the ADIRS CDU by 1 Kt. (2) Compare the recorded ground speed values with these limits: (a) If the residual ground speed error is less than 15 Kts: - the ADIRU is serviceable and no action is necessary. (b) If the residual ground speed error is equal to 15 Kts or is between 15 and 21 Kts: - it is not necessary to replace the ADIRU but you must do a second check of the residual ground speed error immediately after the subsequent flight. If the value is again equal to 15 Kts or is between 15 and 21 Kts, replace the ADIRU (Ref. TASK 34-12-34-000-001) and (Ref. TASK 34-12-34-400-001); (c) If the residual ground speed error is equal to or more than 21 Kts: - replace the ADIRU (Ref. TASK 34-12-34-000-001) and (Ref. TASK 34-12-34-400-001). R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-12-34-740-052-A B. Residual Ground Speed Error NOTE : Do this procedure only at the end of a flight: ____ - Before the ADIRUs are off and - Before you start a new alignment. Record the residual ground speed for each IR at the end of the flight when the aircraft is fully stopped.

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Page 606 Feb 01/10

(1) Record the ground speed on the CAPT ND (IR1) and F/O ND (IR2). To read the residual ground speed for IR3 on the CAPT (F/O) ND, set the ATT HDG selector switch on the SWITCHING panel (8VU) to CAPT/3 (F/O/3). (2) Compare the recorded ground speed values with these limits: (a) If the residual ground speed error is less than 15 Kts: - The ADIRU is serviceable and no action is necessary. (b) If the residual ground speed error is equal to 15 Kts or is between 15 and 21 Kts: - It is not necessary to replace the ADIRU but you must do a second check of the residual ground speed error immediately after the subsequent flight. If the value is again equal to 15 Kts or is between 15 and 21 Kts, replace the ADIRU (Ref. TASK 34-12-34-000-001) and (Ref. TASK 34-12-34-400-001); (c) If the residual ground speed error is equal to or more than 21 Kts: - Replace the ADIRU (Ref. TASK 34-12-34-000-001) and (Ref. TASK 34-12-34-400-001). **ON A/C ALL Subtask 34-12-34-740-053 C. Drift Rate The Drift Rate criteria are directly derived from the RPE removal criteria, divided by the NAV TIME (T). (Ref. Fig. 603/TASK 34-12-34-991-009)

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NOTE : Do this procedure only at the end of a flight: ____ - before the ADIRUs are off and - before you start a new alignment and - before you load a new flight plan into the FMGC.

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Page 607 Aug 01/09

ADIRU - Drift Rate - Removal Criteria Figure 603/TASK 34-12-34-991-009

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Page 608 Aug 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the center pedestal, on one MCDU:

On the MCDU:

1. Push the line key adjacent to the FMGC indication

The FMGC page comes into view.

2. On the keyboard, push the DATA mode key

The DATA INDEX page comes into view.

3. Push the line key adjacent to the IRS MONITOR indication

The IRS MONITOR page comes into view.

4. Record each IRS NAV DRIFT. 5. Close-up ________ Subtask 34-12-34-860-053 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

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Page 609 Aug 01/09

MOUNT - ADIRU - REMOVAL/INSTALLATION ____________________________________ TASK 34-12-51-000-001 Removal of the ADIRU Mount 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

blanking caps

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------

R R

08-22-00-200-001 21-26-41-000-001 21-26-42-000-001 21-26-43-000-006 34-12-34-000-001 34-12-51-991-001

Precise Leveling Removal of the Check Valve (2140HM) Removal of the Avionics Equipment Ventilation Duct Removal of the Filter Assembly (2081HM, 2082HM, 2083HM) Removal of the ADIRU (1FP1, 1FP2, 1FP3) Fig. 401

3. __________ Job Set-up Subtask 34-12-51-210-050 A. Do the aircraft precise leveling (Ref. TASK 08-22-00-200-001) to put the aircraft in position to have a 0 degree pitch, 0 degree roll. Use the standard reference marks of the aircraft (tolerance +/- 5 minutes). NOTE : You must keep the aircraft in this position during the removal and ____ installation procedures.

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Page 401 Feb 01/09

Subtask 34-12-51-020-050 B. Remove the ADIRUs 1FP1, 1FP2 and 1FP3 (Ref. TASK 34-12-34-000-001). 4. Procedure _________ Subtask 34-12-51-020-051 A. Removal of the ADIRU Mount (Ref. Fig. 401/TASK 34-12-51-991-001) (1) Remove the nuts (4), the washers (8) and the screws (7) which attach the bonding leads (5) to the mount (13). (2) Remove the nuts (14) from the screws (11). (3) Remove the electrical connectors (12) from the mount (13). Use some straps to attach the electrical connectors (12). R

(4) Put blanking caps on the disconnected electrical connector(s). (5) Remove the nuts (1), the washers (2) and the screws (6). (6) Lift the mount (13) off its support. Be careful not to cause damage to the peel shims (3) and the air conditioning pipe (9). (7) Put marks on the peel shims (3) with a felt-tip pen or equivalent, to make sure that you put them back in their initial positions when you install the mount (13). (8) Remove the nuts (10). (9) Remove the air conditioning pipe (9). (10) Remove the mount (13). Subtask 34-12-51-020-052 B. Removal of the Air Conditioning Pipes (1) Remove the check valve (2140HM) (Ref. TASK 21-26-41-000-001). (2) Remove the filter assembly (2081HM, 2082HM, 2083HM) (Ref. TASK 21-2643-000-006).

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Page 402 Feb 01/10

ADIRU Mount Figure 401/TASK 34-12-51-991-001   R EFF : ALL  34-12-51    CES

 

Page 403 Aug 01/08

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(3) Remove the avionics equipment ventilation-duct (Ref. TASK 21-26-42000-001).

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Page 404 Feb 01/09

TASK 34-12-51-400-001 Installation of the ADIRU Mount 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R

No specific 3028000 950-315 98D34103000000 98D34203000000

1 1 1 1

access platform 1.8 m (5 ft. 11 in.) CLINOMETER - REPLACED BY P/N 3028011001 DIGITAL PROTRACTOR ALIGNMENT,TOOL-IRU PLATFORM BRACKETS ALIGNMENT,TOOL-MOUNT,ADIRU

B. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------2 2 2 5 7

peel shims peel shims peel shims cotter pins packings

34-11-01 34-11-01 34-11-01 32-21-01 32-21-01

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11B-130 11C-130 11D-130 01 -010 01 -075

Page 405 Feb 01/10

C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------07-11-00-586-002 08-22-00-200-001 21-26-41-400-001 21-26-42-400-001 R R

21-26-43-400-006 34-12-34-400-001 34-12-51-991-001 34-12-51-991-002 34-12-51-991-003

Lowering of the Aircraft for Maintenance Operations Precise Leveling Installation of the Check Valve (2140HM) Installation of the Avionics Equipment Ventilation Duct Installation of the Filter Assembly (2081HM, 2082HM, 2083HM) Installation of the ADIRU (1FP1, 1FP2, 1FP3) Fig. 401 Fig. 402 Fig. 403

3. __________ Job Set-up Subtask 34-12-51-210-051 A. Make sure that the aircraft is in precise leveling (Ref. TASK 08-22-00200-001). Do this procedure to put the aircraft in position to have a 0 degree pitch and a 0 degree roll. Use the standard reference marks of the aircraft (tolerance +/- 5 minutes). Subtask 34-12-51-010-050 B. Get Access (1) Make sure that the access platform is in position in the zone 126 at the access door 822. (2) Make sure that the access door 822 is open. (3) Make sure that the two screws and the protective cover are removed from the battery power center 105VU. (4) Make sure that the access platform is in position in the zone 128 at the access door 824. (5) Make sure that the access door 824 is open.

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Page 406 Feb 01/09

Subtask 34-12-51-865-050 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU R R

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

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N10 N09 N08 N07 N06 N05 N04 N03

Page 407 Feb 01/10

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**ON A/C ALL 4. Procedure _________ Subtask 34-12-51-210-052 A. Heading Check CAUTION : IF YOU MUST MOVE THE TOOL IN THE AIRCRAFT, BE CAREFUL NOT TO _______ DAMAGE THE PEEL SHIMS OF THE SUPPORTS OF THE ADIRU MOUNT. NOTE : Assemble the tool in the aircraft avionics compartment. The ____ assembled tool is too large to go through the access door of the zone. (Ref. Fig. 402/TASK 34-12-51-991-002) (1) Installation of the ALIGNMENT,TOOL-IRU PLATFORM BRACKETS (98D34103000000) (a) Remove and discard the cotter pins (5). (b) Remove the nuts (4) and the washers (3). (c) Remove the flanges (6) from the pintles (1) of the nose gear. (d) Remove and discard the packings (7) and (2). (e) Install the support shafts (8) on the pintles (1) of the nose gear. (f) Install the washers (3) and the nuts (4). (g) Install the new cotter pins (5). (h) Assemble the three parts of the tool (11) with the bolts (9). NOTE : The left and right parts of the tool are not ____ interchangeable. Make sure that they are installed on the correct side. (i) Install the tool (11) on the support shafts (8). To do this: - tilt the top of the tool (11) forward to engage it on the support shafts (8). - let the tool (11) turn down until it touches the surfaces of the ADIRU mount support.

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Page 408 Aug 01/08

Installation Platform - IRU Brackets Figure 402/TASK 34-12-51-991-002   R EFF : ALL  34-12-51    CES

 

Page 409 Aug 01/08

(j) Install the shim (13) between the tool (11) and the right support shaft (8) to prevent movement in the Y-axis (Roll) direction. (k) Install and tighten the knurled nuts (12) on each support shaft (8). (2) Heading Check (a) Manually push the four pins (10) into the inspection bushes of the tool (11). The pins (10) must go easily in the attachment holes of the ADIRU mount support. NOTE : If it is not easy manually to push the four pins (10) into ____ the attachment holes for the ADIRU mount support, there is a heading angle mismatch. You must get more information from the Airbus Customer Service. (3) Removal of the ALIGNMENT,TOOL-IRU PLATFORM BRACKETS (98D34103000000) (a) Remove the four pins (10). (b) Remove the knurled nuts (12). (c) Remove the tool (11) and the shim (13) from the support shafts (8). (d) Remove the bolts (9) and disassemble the three parts of the tool (11). (e) Remove and discard the cotter pins (5). (f) Remove the nuts (4) and the washers (3). (g) Remove the support shafts (8) from the pintles (1) of the nose gear. (h) Install the new packings (7) (7) and (2) and the flanges (6) on the pintles (1) of the nose gear. (i) Install the washers (3) and the nuts (4). (j) TORQUE the nuts (4) to between 1.2 and 1.35 m.daN (106.19 and 119.46 Ibf.in). (k) Install the new cotter pins (5).

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Page 410 Aug 01/08

Subtask 34-12-51-210-053 B. Flatness Check (Ref. Fig. 403/TASK 34-12-51-991-003) (1) If necessary, replace the damaged peel shims (2). Carefully clean the sealing bearing on the support surfaces of the ADIRU mount. Remove the unwanted thickness from the peel shims (2). (2) Put the ALIGNMENT,TOOL-MOUNT,ADIRU (98D34203000000) (1) in position on the three peel shims (2) with the right angle of the tool (1) at position 2. R R

(3) Put a CLINOMETER - REPLACED BY P/N 3028011001 (3028000) or DIGITAL PROTRACTOR (950-315) on the two perpendicular arms of the tool (1). (4) Adjust the assembly until it is horizontal. To do this, remove the unwanted thickness from the peel shims (2). Tolerance for X (pitch)= +/-530 (+/-0.09⁰). Tolerance for Y (roll)= +/-3.30 (+/-0.06⁰). (5) Turn the tool (1) 180 degrees until its right angle is at position 4. (6) Adjust the assembly until it is horizontal. To do this, remove the unwanted thickness from the peel shims (2). (7) Do a check to make sure that all the assembly is horizontal. If not, go back to step (2). (8) Remove the CLINOMETER - REPLACED BY P/N 3028011001 (3028000) or DIGITAL PROTRACTOR (950-315) and the tool (1).

R

Subtask 34-12-51-420-050 C. Installation of the Air Conditioning Pipes (1) Install the avionics equipment ventilation-duct (Ref. TASK 21-26-42400-001). (2) Install the filter assembly (2081HM, 2082HM, 2083HM) (Ref. TASK 2126-43-400-006). (3) Install the check valve (2140HM) (Ref. TASK 21-26-41-400-001).

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Page 411 Feb 01/10

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Alignment Tool - ADIRU Mount Figure 403/TASK 34-12-51-991-003

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Page 412 Feb 01/10

Subtask 34-12-51-420-051 D. Installation of the ADIRU Mount (Ref. Fig. 401/TASK 34-12-51-991-001) (1) Install the air conditioning pipe (9). (2) Install the nuts (10). R

(3) Remove the blanking caps from the electrical connector(s). (4) Install the electrical connectors (12) on the mount (13). (5) Install the nuts (14). (6) Install the mount (13) on the peel shims (3). Be careful not to cause damage to the peel shims (3). (7) Install the screws (6), the washers (2) and the nuts (1). (8) Install the bonding leads (5), the screws (7) and the washers (8). (9) Install the nuts (4). 5. Close-up ________ Subtask 34-12-51-420-052 A. Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the ADIRUs 1FP1, 1FP2 and 1FP3 (Ref. TASK 34-12-34-400-001). (3) Lower the aircraft (Ref. TASK 07-11-00-586-002).

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Page 413 Feb 01/10

AIR DATA - DESCRIPTION AND OPERATION ____________________________________ 1. _______ General The Air Data Reference (ADR) portion of the Air Data/Inertial Reference Unit (ADIRU) provides main data sources which are air data references for the aircraft avionics systems. The ADR receives and processes the outputs of the Air Data Modules (ADM) and other sensors (Ref. 34-11-00). It computes the aerodynamic parameters in the form of ARINC 429 low speed buses. For more details concerning the user systems, ref. 34-12-00. 2. __________________ System Description A. ADR Operation (1) General The ADR software performs five basic computational elements which are under the air data calculations as follows: - pressure altitude functions (ALT/ALT rate) - Mach calculation (M) - airspeed calculation (CAS/TAS) - temperature calculation (SAT/TAT) - output signal processing. Aircraft-dependent calculations are also included in the operational software: - static source error correction - angle of attack (AOA) - maximum operating speed (MMO/VMO). The system tests include continuous in-flight monitoring and manually-activated test modes. The in-flight monitoring includes test of: - input signal integrity - input interface integrity - memory integrity - computational integrity - output signal integrity. The continuous monitoring detects and annunciates faults in the ADR during normal operation. Faults are stored in BITE history EEROM and sent to the Centralized Fault Display System (CFDS) via digital words (ref. 34-18-00).

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(2) Inputs (a) Digital inputs 1 _

Air Data Modules (ADM) inputs The ADR receives three input buses from its corresponding ADM. These buses transmit the following input data words depending on the ADM installation: Label 242 : Total Pressure Label 176 : Left Static Pressure Label 177 : Right Static Pressure Label 245 : Averaged Static Pressure. Each of these words is a 32-bit word with the following format: ---------------------------------------------------------| BIT POSITION | DATA | ---------------------------------------------------------| 1 - 8 | Label | | 9 - 10 | SDI | | 11 - 28 | Pressure Value | | 29 | Sign bit (0 = positive) | | 30 - 31 | Status matrix | | 32 | Parity bit | ---------------------------------------------------------Table 1 - ADM Input Label These data words are output on all eight Air Data output data buses and used for calculation of corrected pressure data.

2 _

Flight Control Unit (FCU) inputs The ADR receives one input bus from the FCU, for digital baro corrections. The FCU output bus sends: BCD label 234 Baro Correction 1(hPa) for CAPT side BCD label 236 Baro Correction 2(hPa) for F/O side. Each ADR receives the two FCU output bus according to the discrete selection as explained in Para. 2.A.(2)(c) (discrete inputs). Each of these words is a 32-bit BCD word with the following format:

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----------------------------------------------------------| BIT POSITION | DATA | ----------------------------------------------------------| 1 - 8 | Label | | 9 - 10 | SDI | | 11 - 28 | Value | | 29 | Sign bit | | 30 - 31 | Status matrix | | 32 | Parity | ----------------------------------------------------------Table 2 - FCU Input Label 3 _

Centralized Fault Display Interface Unit (CFDIU) input For maintenance purposes, the ADR receives one input bus from the CFDIU. For more details, ref. 34-18-00.

4 _

Air Data Reference (ADR) input Each ADR receives two intercommunication buses from the other ADRs for cross channel comparison purpose.

(b) Analog inputs 1 _

Total Air Temperature (TAT) input The ADR measures the resistance of the sensing element of the TAT sensor (Ref. 34-11-00). The ADR subtracts a fixed value function of system number from the measured input resistance to compensate for aircraft wiring resistance.

2 _

Angle of Attack (AOA) inputs (Ref. Fig. 001) The ADR receives two resolver inputs for angle of attack computation. The following requirements apply to the analog resolver inputs: - load: 15 kilohms minimum - reference: 26V, 400 Hz (same as AOA) - transformer ratio: 0.415 nominal plus or minus 10 % - phase shift: 24 deg. leading - source impedance: Zro = A + jB A less than 315, B less than 725 Zso = C + jD C less than 150, D less than 165 - electrical range input: plus or minus 60 deg.

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AOA/ADR Wiring Figure 001   R EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 4   Config-1 May 01/05  CES

 

3 _

Analog baro correction inputs The ADR receives three resolver inputs for analog baro correction (from the altimeter for example). These inputs are not used.

(c) Discrete inputs (Ref. Table 3) For pin assignment, Ref. 34-12-00. The ADR is provided with the following input discretes: ---------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT DEFINITION | ---------------------------------------------------------------| ADR ARINC Filter Select | Open/GND | Type A/Type B | | CFDS Message Select | Open/GND | Active/ Not Active | | SDI LSB (Middle Insert) | Open/GND | 0/1 | | SDI MSB (Middle Insert) | Open/GND | 0/1 | | Pitot Probe Ht Disc | Open/GND | No Fault/Fault | | Right Static Ht Disc | Open/GND | No Fault/Fault | | Left Static Ht Disc | Open/GND | No Fault/Fault | | TAT Ht Disc | Open/GND | Off/On | | AOA 1 Ht Disc | Open/GND | No Fault/Fault | | AOA Average/Unique | Open/GND | Average/Unique | | VMO/MMO Disc 1 | Open/GND | No/Yes | | VMO/MMO Disc 2 | Open/GND | No/Yes | | VMO/MMO Disc 3 | Open/GND | No/Yes | | VMO/MMO Disc 4 | Open/GND | No/Yes | | SSEC Alternate Disc A | Open/GND | No/Yes | | SSEC Alternate Disc B | Open/GND | N0/Yes | | AOA Alternate Disc 1A | Open/GND | Off/On | | AOA Alternate Disc 1B | Open/GND | Off/On | | AOA Alternate Disc 2A | Open/GND | Off/On | | AOA Alternate Disc 2B | Open/GND | Off/On | | Baro Port A | Open/GND | Port B/Port A | | Zero MACH SSEC | Open/GND | Use SSEC/Ignore SSEC | | Zero AOA SSEC | Open/GND | Use SSEC/Ignore SSEC | | AIR FRM ID Code 1/0 | Open/GND | No/Yes | | AIR FRM ID Code 2/0 | Open/GND | No/Yes | | AIR FRM ID Code 4/0 | Open/GND | No/Yes | | AIR FRM ID Code 8/0 | Open/GND | No/Yes | | AIR FRM ID Code 16/0 | Open/GND | No/Yes | | AIR FRM ID Code 32/0 | Open/GND | No/Yes | | AIR FRM ID Code 64/0 | Open/GND | No/Yes | | AIR FRM ID Code Parity | Open/GND | No/Yes | | ADR Remote Test | Open/GND | No Test/Test | | ADR OFF DISCR Input | Open/GND | Released/Pressed | | Dual Baro | Open/GND | Sgl Port/Dual Port | | Baro Analog/Digital Sel.| Open/GND | Digital/Analog |

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---------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT DEFINITION | ---------------------------------------------------------------| Baro Corr. 3 Active | Open/GND | Not Active/Active | ---------------------------------------------------------------Table 3 - Discrete Input Signal NOTE : Open means either a high logic voltage level or the ____ binary zero state. GND means either a low logic voltage level or the binary one state. 1 _

ADR ARINC Filter Select discrete This discrete is used to select the characteristics of the ADR output filter. Two sets of characteristics are available: Open/Ground = Type A/Type B Type A : No filtering except for the Altitude Rate (3dB filter bandwidth : 0.17 Hz) The A/C is defined with the ADR ARINC filter select discrete open.

2 _

CFDS Message Select discrete Open = CFDS message. When open, this discrete is used to select and display fault messages.

3 _

Source Data Identifier (SDI) program pins These discretes code the installation side of the ADIRU. This item of information is used to choose the appropriate correction laws (for Static Source Error Correction (SSEC) and corrected angle of attack). The following table gives the ADR side according to the SDI: -------------------------------------------------------| DEBOUNCED STATUS | | | |-----------------------------| SDI | ADIRU | | SDI-MSB | SDI-LSB | CODE | NUMBER | |------------------------------------------------------| | OPEN | GND | 01 | 1 | | GND | OPEN | 10 | 2 | | GND | GND | 11 | 3 | -------------------------------------------------------Table 4 - ADR SDI Code

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4 _

sensor heat status discretes These discrete inputs are used to provide the sensors heat status to the ADR. These discretes are of the open/ground type. When the TAT HEAT DISC is grounded, the TAT sensor is heated. When one of the STATIC, PITOT or AOA HEAT discretes is grounded, it means that the output of the Probe Heat Computer (PHC) heating power supply is faulty and that the concerned probe is no longer heated. In this case, the ADR operates as a relay which sends these information signals to the FWC for warning purposes.

5 _

AOA Average/Unique program pin The ADR uses the AOA Average/Unique program pin to determine whether one or two angle of attack resolver inputs are used for angle of attack computations. When this program pin indicates Unique, the ADR uses only a single angle of attack input. If this first AOA input fails, the ADR uses the opposite AOA input, as shown in table 5 below. When this program pin indicates Average, the ADR calculates angle of attack based on the average of the angle of attack inputs 1 and 2. ------------------------------------------------------| SYSTEM | INITIAL NON-FAULT | INPUT TO ADR | | NUMBER | INPUT TO ADR | AFTER FAULT | ------------------------------------------------------| 1 | input number 1 | input number 2 | | 2 | input number 2 | input number 1 | | 3 | input number 1 | input number 2 | ------------------------------------------------------Table 5 - AOA Resolver Input The characteristics of these discretes are OPEN/GROUND = AVERAGE/UNIQUE. The A/C is defined with the AOA average/unique discrete grounded.

6 _

VMO/MMO Program Discretes 1 through 4 These discretes are used to select alternate VMO/MMO levels. There are four alternates and a basic VMO/MMO for each aircraft type. Table 6 below defines VMO/MMO versus state of the VMO/MMO program discretes. With no VMO/MMO discretes in the ground state (yes) the ADR defaults to the BASIC LAW values for VMO/MMO. Only one of the four VMO/MMO program discretes can be in the ground state at any one time.

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If more than one VMO/MMO program discrete is in the ground state at any one time, the ADR defaults to the lowest available alternate condition. 7 _

on the A/C only the VMO/MMO DISC 2 is available and is provided by the L/G DOWN VMO/MMO SELECTION switch 22FP. The normal position of this switch is open and it is grounded after crew action for particular flights (ferry flight for example). Table 6 below defines VMO/MMO state according to the position of the switch 22FP. ---------------------------------------------------------| | VMO | MMO | SWITCH | | LAW | (kts) | (Mach) | 22FP | ---------------------------------------------------------| BASIC | 350 | 0.82 | OPEN | | ALT 1 * | 235 | 0.60 | N/A | | ALT 2 | 235 | 0.60 | GROUND | | ALT 3 * | 235 | 0.60 | N/A | | ALT 4 * | 235 | 0.60 | N/A | ---------------------------------------------------------* Spare. Default value included for safety and BITE purpose. Table 6 - VMO/MMO Selection

8 _

SSEC Alternate discrete The ADR is provided with two Static Source Error Correction (SSEC) data sets to be stored in the computer, for each SDI and each aircraft type, one for use in normal conditions and one for use in alternate conditions. With the two SSEC selection discretes open (no), the ADR employs the normal SSEC curve for the aircraft type in which it is installed. With the two SSEC selection discretes grounded (yes), the ADR employs the alternate condition curve.

9 _

AOA Alternate discrete The ADR uses the alternate discrete inputs from the two redundant SFCCs to select the angle of attack correction which is appropriate for the current slat and flap settings. Three laws are available for each aircraft type and SDI: - the normal law is activated when all the discretes are open, - the alternate 1 law is activated when discretes 1A and 2A are grounded, - the alternate 2 law is activated when discretes 1A, 2A, 1B and 2B are grounded.

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10 __

Baro Port A discrete The ADR uses this discrete to select which ARINC 429 port is used as a source for all baro-correction input data. If this discrete is grounded, the baro port A is selected. If this discrete is open, the baro port B is selected. The A/c is wired with this discrete grounded (Ref. Dual Baro discrete).

11 __

Dual Baro discrete The ADR uses this discrete to select which ARINC 429 port is used as a source for all baro-correction input data. If this discrete is grounded, the baro port A and the baro port B are selected and the baro port A discrete selection is overriden. If this discrete is open, the baro port A or the baro port B is selected depending on the baro port A discrete selection. The A/C is wired with this discrete open.

12 __

Zero MACH SSEC discrete The ADR uses this discrete to select the SSEC as a function of Mach. When this program pin indicates Use SSEC (open), the SSEC as a function of Mach is computed. When this program pin indicates Ignore SSEC (ground), the ADR uses zero correction. The A/C is wired with this discrete open.

13 __

Zero AOA SSEC discrete The ADR uses this discrete to select the SSEC as a function of angle of attack. When this program pin indicates Use SSEC (open), the SSEC as a function of AOA is computed. When this program pin indicates Ignore SSEC (ground), the ADR uses zero correction. The A/C is wired with this discrete open.

14 __

AIR FRM ID Code discrete The ADR uses input discretes to identify the aircraft (type, engine model) on which the ADIRU is fitted, and to select the appropriate set of correction laws for Static Source Error Correction (SSEC) and AOA corrections. The ADIRU memory has the capacity to store 128 different sets of laws. To perform this coding, the ADR wires seven input discretes and one discrete for parity to a common.

15 __

ADR Remote Test discrete The ADR uses one discrete to select the remote test by external control. When this discrete is open, the test is not activated. When this discrete is grounded, the test is activated.

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The A/C is wired with this discrete open (unused). The test is activated via the CFDIU (Ref. 34-18-00). 16 __

ADR OFF DISCR input discrete The ADR uses this discrete input to toggle its state between ON and OFF at each press on the momentary contact switch. When the ADR is OFF, the output buses are disabled and the ADR FAULT annunciator is inhibited (reset if already set).

17 __

Baro Analog/Digital Sel discrete The ADR uses this discrete to select either the analog or digital baro correction. When this discrete is grounded, the analog baro correction is selected. When this discrete is open, the digital baro correction is selected. The A/C is wired with this discrete open.

18 __

Baro Corr 3 Active discrete The ADR uses this discrete to determine for BITE purposes whether the baro correction 3 is connected or not. When the discrete is grounded, the baro correction 3 is connected. When the discrete is open, the baro correction 3 is not connected. The A/C is wired with this discrete open.

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(3) Acquisition and processing of the sensor inputs (Ref. Fig. 002, 003) (a) Pressure computation Based on pressure data received from the ADM (Ref. para. 2.A.(2)(a)1), the software converts the pressure inputs into corrected pressure data. From the average static pressure (Psm), the software calculates the corrected static pressure based on the SSEC factor: ( G1 G2 ) Psc = Psm (1 + ---- + ----) ( 1000 1000) - G1 depends on flaps and Mach is interpolated in a table (2 flaps position and 19 Mach values are considered) - G2 depends on Mach and AOA corrected and is interpolated in a table (6 AOA values and 19 Mach values are considered). The correct SSEC factor depends on the sensor location and on the aircraft configuration. The ADR memory contains several tables and the appropriate one is selected according to the following input discretes: . SDI . aircraft Ident . SSEC Alternate. Two input discretes can be used to force the SSEC factor to be independent from AOA or Mach: . zero MACH SSEC . zero AOA SSEC. Ref. Para. 2.A.(2)(c) for more details. During correction of total pressure, the software calculates the limited total pressure in a range of 100 to 1400hPa from the ADM inputs. From the measured total pressure (Ptm) and the measured static pressure (Psm), the software calculates a corrected total pressure: (Ptm + Psm) Pt = Ptm + --------------- X 0.38 Psm The results of the above computation is available on these output labels: . label 176 Left Static Pressure . label 177 Right Static Pressure . label 242 Total Pressure . label 245 Averaged Static Pressure . label 246 Corrected Static Pressure

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Pressure Computation - Block Diagram Figure 002   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 12   Config-1 Feb 01/08 R  CES

 

CAS/Mach Computation - Block Diagram Figure 003   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 13   Config-1 Feb 01/08 R  CES

 

(b) Temperature computation The resistance measured by the ADR and compensated for aircraft wiring is then converted into a temperature value (TAT) according to the Callender-Van Dusen equation given for a 500 ohm platinum sensing element: | 3| Rt | (TAT ) (TAT ) (TAT ) (TAT) | -- = 1 + a | TAT - d (--- -1) (--- ) - b (--- -1) (---) | Ro | (100 ) (100 ) (100 ) (100) | TAT = temperature in deg.C Rt = Resistance at temperature TAT Ro = Resistance at 0 deg.C = 500 ohm a = 0.003832 d = 1.81 b = 0.1 for temperature below 0 deg.C b = 0 for temperature above 0 deg.C The computation also compensates the TAT value for heating effect. The ADR knows when the sensor is heated by the state of the TAT Heat input discrete from the PHC. The heating compensation law is provided by the TAT sensor supplier and is function of Mach and air density. The PHC 1 controls the heating of the TAT sensor 1 and the PHC 2 controls the heating of the TAT sensor 2. On the ground, the sensors are not heated (Ref. 30-31-00 for more details). The result of the above computation is available on the following output labels: - label 211 Total Air Temperature (BNR) - label 231 Total Air Temperature (BCD).

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(c) AOA computation The A/C is wired in the AOA unique selection, so the ADR computes the AOA with the reading of one resolver. The second resolver is used as a back-up. The monitoring function is described in 34-18. The ADR determines the corrected angle of attack value which depends on the system number and the slat/flap position. For a CAS less than 60 kts: AOAc is still computed but coded NCD. The corrected angle of attack is calculated as follows: AOA ind AOAc = ------- + I K where: AOA ind = Indicated Angle of Attack (Ref. 34-11-00 for the relation between resolver and AOA indication) K, I = Correction coefficients which depend on system number, slat and flap configuration and magnitude AOA indication. The configuration is defined by the status of four input discretes (Ref. 2.A.(2)(c)). The results of the above computation is available on the labels: - label 221 = Indicated Angle of Attack - label 241 = Corrected Angle of Attack

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(4) Parameter computation (a) General The operational software of the ADR performs the following computations: - pressure altitude and pressure altitude rate function (ALT) - Mach function (M) - airspeed function (CAS/TAS) - temperature function (SAT/TAT) - maximum operating speed function (VMO/MMO). (b) Altitude computation The ADR software computes these different parameters: label 203 Altitude label 212 Altitude Rate (BNR) label 204 Baro Corrected Altitude 1 (CAPT) label 220 Baro Corrected Altitude 2 (F/O) label 232 Altitude rate (BCD) 1 _

Altitude and altitude rate computation The altitude is derived from the corrected static pressure. Standard altitude is computed as : * For Ps graeter or equal to 226,323 hPa 0,190263 Altitude = 145442,156 * (1- (Ps / Po) ) * For Ps < 226,323 hPa Altitude = 148897,4 - 47907,18 * Log (Ps) with Ps = Corrected Static Pressure Po = Standard day sea level pressure (1013,25 hPa) The accepted range is (-2000 ft, +50.000 ft). The altitude rate is calculated by multiplying the rate of change of the corrected static pressure by the derivative of altitude with respect to corrected static pressure: dH d Ps dH -- = ---- x ---dt dt d Ps

2 _

Corrected altitude computation The ADR receives the baro correction introduced on the FCU by each crew member. The ADR uses the values in hPa (labels 234 and 236 from the FCU). The corrected altitude is calculated by a shift of the pressure altitude to a value corresponding to the entered baro correction. The result is sent on label 204 for CAPT baro

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corrected altitude and label 220 for F/O baro corrected altitude.

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(c) CAS/Mach computation The ADR software computes these different parameters: label 206 Computed Airspeed label 205 Mach label 207 Maximum Allowable Airspeed. The CAS and Mach computation is based on the conversion of the impact pressure: impact pressure = Pt - Ps. - the CAS computation converts input of impact pressure to output corresponding to computed airspeed with: _______________________ / Qc 2/7 CAS = Cso X V 5 X ((-- + 1) - 1) Po CAS = Computed Airspeed in knots Cso = Speed of sound under standard day sea level conditions = 661.4746 kts Qc = Impact pressure in hPa Po = Standard day sea level pressure = 1013.25 hPa For accuracy reason, the CAS is output with a valid (NO) SSM only after 30 kts. If the CAS is below 30 kts, the label 206 indicates 0 kt with SSM = NCD. - the Mach computation converts Qc/Ps to Mach, with: _______________________ / Qc 2/7 MACH = V 5 ((-- + 1) - 1) Ps MACH = Mach number Qc/Ps = Ratio of impact pressure to static pressure If Mach is below 0.1, the label 205 indicates 0 with SSM = NCD.

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(d) SAT/TAS computation The ADR software calculates these different parameters: label 213 BNR Static Air Temperature (SAT) label 233 BCD Static Air Temperature (SAT) label 210 BNR True Airspeed (TAS) label 230 BCD True Airspeed (TAS). - the calculation of the BNR SAT converts TAT to SAT with: TAT SAT = --------- 273.15 2 1 + 0.2M SAT = Static Air Temperature (in deg. C) TAT = Total Air Temperature (in deg. Kelvin) M = Mach number (corrected for static source error) - the calculation converts Static Air Temperature from BNR to BCD format. - the calculation of the BNR TAS converts Mach and SAT to TAS with: ___ / TAS = 38.96695 x M x V SAT TAS = True Airspeed (in knots) M = Mach Number (corrected for Static Source Error) SAT = Static Air Temperature (in deg. Kelvin) - the calculation converts True Airspeed from BNR to BCD format. For accuracy reason, the TAS is output with a valid (NO) SSM only after 60 kts. If TAS is below 60 kts, the label 210 indicates 0 kt with SSM = NCD. (e) VMO/MM0 computation The software determines the normal or alternate VMO/MMO law selected by the VM0/MM0 input 2 discrete state; then it computes the label 207 Maximum Allowable Airspeed. This airspeed is based on the Maximum Allowable Airspeed under a certain altitude and on the Maximum Allowable Mach above this altitude. It is always indicated in knots and decreases when the altitude increases. NOTE : At a constant Mach, the Vc value decreases when the ____ altitude increases.

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(5) ADR data outputs The ADR data outputs are transmitted in two forms: digital and discrete. (a) Digital form The table below contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI : (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - RANGE ACCURACY : measurement range maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT : unit in which the digital value is transmitted - SIG BIT : indicates whether a sign bit is available - BITS : number of bits used by the parameter in the label - UPD/MSEC : output transmission interval. The refresh rate is given in milliseconds. - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code. - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. R

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 047 |S/W IDENT | | | | |1000|BCD | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 176 |L STATIC |W2048 |hPa | | 18 |125 |BNR | | | | |PRESSURE |100 to 1100 | | | | | | | | | | |R 0.0078 | | | | | | | | | | |+/- 0.30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 177 |R STATIC |W2048 |hPa | | 18 |125 |BNR | | | | |PRESSURE |100 to 1100 | | | | | | | | | | |R 0.0078 | | | | | | | | | | |+/- 0.30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 203 |STANDARD |W+/- 131072 | ft | 29 | 17 | 62 |BNR | ALT | | | |ALTITUDE |-2000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 | | | | | | | | | | |+/-40 | | | | | | | | | | |(30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 204 |BARO CORR |W+/- 131072 | ft | 29 | 17 | 62 |BNR | | | | |ALT 1 |-2000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 | | | | | | | | | | |+/-47 | | | | | | | | | | |(30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 205 |MACH |W4096 |Mach| | 16 |125 |BNR | MN | | | | |0.1 to 1.00 | | | | | | | | | | |R 6.25 E-5 | | | | | | | | | | |+/-0.015 | | | | | | | | | | |(0.1) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 206 |COMPUTED |W1024 |Kts | | 14 |125 |BNR | CAS | | | |AIRSPEED |30 to 450 | | | | | | | | | | |R 0.0625 | | | | | | | | | | |2 (100) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 207 |MAXIMUM |W1024 |Kts | | 12 |125 |BNR | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |ALLOWABLE |150 to 450 | | | | | | | | | |AIRSPEED |R 0.25 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 210 |TRUE |W2048 |Kts | | 15 |125 |BNR | | | | |AIRSPEED |60 to 599 | | | | | | | | | | |R 0.0625 | | | | | | | | | | |+/- 4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 211 |TOTAL AIR |W +/- 512 |Deg.| 29 | 11 |500 |BNR | TAT | | | |TEMP |-60 to +100 |C | | | | | | | | | |R 0.25 | | | | | | | | | | |+/- 0.5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 212 |ALTITUDE |W+/- 32768 |ft/ | 29 | 11 | 62 |BNR | | | | |RATE |+/- 20000 |mn | | | | | | | | | |R 2 | | | | | | | | | | |+/- 30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 213 |STATIC AIR|W+/- 512 |Deg.| 29 | 11 |500 |BNR | SAT | | | |TEMP |-99 to +80 |C | | | | | | | | | |R 0.25 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 215 |IMPACT |W512 |hPa | | 16 |125 |BNR | | | | |PRESSURE |0 to 372.5 | | | | | | | | | | |R 0.0078 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 220 |BARO CORR |W +/- 131072| ft | 29 | 17 | 62 |BNR | | | | |ALT 2 |-2000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 | | | | | | | | | | |47 (30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 221 |IND ANGLE |W +/- 180 |Deg.| 29 | 12 | 62 |BNR | | | | |OF ATTACK |-40 to +90 | | | | | | | | | | |R 0.0439 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 230 |TRUE |W +/- 799 |Kts | | 3 |500 |BCD | | | | |AIRSPEED |60 to 599 | | | | | | | | | | |R 1 | | | | | | | | | | |+/- 4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 231 |TOTAL AIR |W +/- 799 |Deg.| | 2 |500 |BCD | | | | |TEMP |-60 to +100 |C | | | | | | | | | |R 1 | | | | | | | | | | |+/- 0.5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 232 |ALTITUDE |W +/- 79999 |ft/ | | 5 |500 |BCD | | | | |RATE |0 TO |mn | | | | | | | | | |+/- 20,000 | | | | | | | | | | |R 1 | | | | | | | | | | |+/- 30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 233 |STATIC AIR|W +/- 799 |Deg.| | 2 |500 |BCD | | | | |TEMP |-99 to +80 |C | | | | | | | | | |R 1 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 234 |BARO |W +/- 7999.9|hPa | | 5 |500 |BCD | | | | |CORRECT 1 |745 to 1100 | | | | | | | | | | |R 0.1 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 235 |BARO |W +/- 79.999|inHg| | 5 |500 |BCD | | | | |CORRECT 1 |22.0 to 32.5| | | | | | | | | | |R 0.001 | | | | | | | | | | |+/- 0.0074 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 236 |BARO |W +/- 7999.9|hPa | | 5 |500 |BCD | | | | |CORRECT 2 |745 to 1100 | | | | | | | | | | |R 0.1 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 237 |BARO |W +/- 79.999|inHg| | 5 |500 |BCD | | | | |CORRECT 2 |22.0 to 32.5| | | | | | | | | | |R 0.001 | | | | | | | | | | |+/- 0.0074 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 240 |VMO/MMO | | | | |500 |BCD | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 241 |CORRECTED |W +/- 180 |Deg.| 29 | 12 | 62 |BNR | AOA | | | |ANGLE OF |-40 to +90 | | | | | | | | | |ATTACK |R 0.0439 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 242 |TOTAL |W2048 |hPa | | 18 |125 |BNR | | | | |PRESSURE |100 to 1400 | | | | | | | | | | |R 0.0078 | | | | | | | | | | |+/- 0.30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 245 |UNCRCTD |W2048 |hPa | | 18 |125 |BNR | | | | |AVG STAT |100 to 1100 | | | | | | | | | |PRESSURE |R 0.0078 | | | | | | | | | | |+/- 0.30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 246 |CORCTD |W2048 |hPa | | 18 |125 |BNR | | | | |AVG STAT |100 to 1100 | | | | | | | | | |PRESSURE |R 0.0078 | | | | | | | | | | |+/- 0.30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DSCT WORD | | | | |500 |DIS | | | | | 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 271 |DSCT WORD | | | | |500 |DIS | | | | | 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 272 |DSCT WORD | | | | |500 |DIS | | | | | 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 277 |ADR TEST | | | | |1000|DIS | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 352 |DSCT WORD | | | | |1000|DIS | | | | | 4 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 354 |LRU IDENT | | | | |500 |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 356 | CFDIU | | | | | |ISO | | | | |INTFC WORD| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQPT IDENT| | | | |1000|HEX | | | ------------------------------------------------------------------------------Table 7 - Output Label

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------------------------------------------------------------------------| BIT N⁰ | FUNCTION | ------------------------------------------------------------------------| 11 |--| | 12 | | LSD --| | 13 | | | | | 14 |--| Program Modification xx | | 15 |--| | | 16 | | MSD --| | 17 | | | | 18 |--| | 19 |--| | 20 | | LSD ----| | 21 | | | | | 22 |--| | | 23 |--| | | 24 | | MSD --| Program Version xx | | 25 | | | | 26 |--| | 27 | 0 | | 28 | 0 | | 29 | 0 | ------------------------------------------------------------------------Table 8 :

Label 047 - S/W Ident

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------------------------------------------------------------------------| BIT N⁰ | FUNCTION | ------------------------------------------------------------------------| 11 |--| | 12 | | Least significant (Hundredths) digit of MMO | | 13 | | | | 14 |--| | 15 |--| | 16 | | Most significant (Tenths) digit of MMO | | 17 | | | | 18 |--| | 19 |--| | 20 | | Least significant (Units) BCD digit of VMO | | 21 | | | | 22 |--| | 23 |--| | 24 | | Middle (Tens) BCD digit of VMO | | 25 | | | | 26 |--| | 27-28 |--- Most significant (Hundreds) BCD digit of VMO | ------------------------------------------------------------------------Table 9 :

Label 240 - VMO/MMO

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-------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | Icing Detector Heat | NO FAULT | FAULT | | 12 | Pitot Probe Heat | NO FAULT | FAULT | | 13 | ADR FAULT | FAULT | NO FAULT | | 14 | Right Static Heat | NO FAULT | FAULT | | 15 | Left Static Heat | NO FAULT | FAULT | | 16 | TAT Heat | HEAT | NO HEAT | | 17 | AOA 1 Heat | NO FAULT | FAULT | | 18 | AOA 2 Heat | NO FAULT | FAULT | | 19 | Overspeed Warning | WARN | NO WARN | | 20 | Spare (Primary AOA Fault) | | | | 21 | AOA Average/Unique | UNIQUE | AVERAGE | | 22 | VMO/MMO 1 | YES | NO | | 23 | VMO/MMO 2 | YES | NO | | 24 | VMO/MMO 3 | YES | NO | | 25 | VMO/MMO 4 | YES | NO | | 26 | SSEC Alternate Select 1 | YES | NO | | 27 | SSEC Alternate Select 2 | YES | NO | | 28 | Baro Port A Select | Port A | Port B | | 29 | Zero Mach SSEC Select | YES | NO | -------------------------------------------------------------------------Table 10 : Label 270 - Discrete Word 1 -------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | Zero AOA SSEC Select | YES | NO | | 12 | AOA Test Active | ACTIVE | NOT | | 13 | Low Speed Warning 1 | FAST | SLOW | | 14 | Low Speed Warning 2 | FAST | SLOW | | 15 | Low Speed Warning 3 | FAST | SLOW | | 16 | Low Speed Warning 4 | SLOW | FAST | | 17 | Spare | | | | 18 | Spare | | | | 19 | Spare | | | | 20 | AOA Correction 1A | YES | NO | | 21 | AOA Correction 1B | YES | NO | | 22 | AOA Correction 2A | YES | NO | | 23 | AOA Correction 2B | YES | NO | |24 to 29| Spare | | | -------------------------------------------------------------------------Table 11 :

Label 271 - Discrete Word 2

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-------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | SDI 2 | GROUND | OPEN | | 12 | SDI 1 | GROUND | OPEN | | 13 | Dual Baro Select | INPUT A | INPUT B | | 14 | Analog Baro Select | YES | NO | | 15 | Spare IDSC 1 | GROUND | OPEN | | 16 | Spare IDSC 2 | GROUND | OPEN | | 17 | Spare IDSC 3 | GROUND | OPEN | | 18 | Baro 3 Present | PRESENT | ABSENT | | 19 | Spare IDSC 4 | GROUND | OPEN | | 20 | CFDS Select | NOT ACTI.| ACTIVE | | 21 | ADR Filter Select | FILTERED | NOT | | 22 | BITE Memory Clear Enable | ENABLE | DISABLE | | 23 | BITE Write Inhibit | INHIBIT | ENABLE | | 24 | ADR Interface Test | TEST | NORMAL | | 25 | ADR Off Command | GROUND | OPEN | | 26 | Reserved | | | | 27 | ADR On/Off Status | On | Off | | 28 | Spare | | | | 29 | Spare | | | -------------------------------------------------------------------------Table 12 : Label 272 - Discrete Word 3

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------------------------------------------------------------------------| | Test Pattern | | | BIT N⁰ | 0 | 1 | FT | | ------------------------------------------------------------------------| 11 | 0 | 1 | 1 | | | 12 | 1 | 0 | 1 | | | 13 | 0 | 1 | 1 | | | 14 | 1 | 0 | 1 | | | 15 | 0 | 1 | 1 | | | 16 | 1 | 0 | 1 | | | 17 | 0 | 1 | 1 | | | 18 | 1 | 0 | 1 | | | 19 | 0 | 1 | 1 | | | 20 | 1 | 0 | 1 | Test patterns 0 and 1 alternate | | 21 | 0 | 1 | 1 | every other transmission. The FT | | 22 | 1 | 0 | 1 | test pattern is used when the | | 23 | 0 | 1 | 1 | interface test discrete is set. | | 24 | 1 | 0 | 1 | | | 25 | 0 | 1 | 1 | | | 26 | 1 | 0 | 1 | | | 27 | 0 | 1 | 1 | | | 28 | 1 | 0 | 1 | | | 29 | 0 | 1 | 1 | | | 30 | 0 | 1 | 0 | | | 31 | 0 | 1 | 1 | | | 32 | P | | | | ------------------------------------------------------------------------Table 13 : Label 277 - ADR test word

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------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | ------------------------------------------------------------------------| 11 | A/C ID Code 32/0 | GROUND | OPEN | | 12 | A/C ID Code 64/0 | GROUND | OPEN | |13 to 23| Spare | | | | 24 | A/C ID Code 1/0 | GROUND | OPEN | | 25 | A/C ID Code 2/0 | GROUND | OPEN | | 26 | A/C ID Code 4/0 | GROUND | OPEN | | 27 | A/C ID Code 8/0 | GROUND | OPEN | | 28 | A/C ID Code 16/0 | GROUND | OPEN | | 29 | A/C ID Parity | GROUND | OPEN | ------------------------------------------------------------------------Table 14 : Label 352 - Discrete Word 4 ------------------------------------------------------------------------| BIT N⁰ | FUNCTION | ------------------------------------------------------------------------| 11 | = 0 -| | 12 | = 1 | LSD = 6 | | 13 | = 1 | | | 14 | = 0 -| | 15 | = 0 -| | 16 | = 0 | MSD = 0 | | 17 | = 0 | | | 18 | = 0 -| |19 to 29| Spare | ------------------------------------------------------------------------Table 15 : Label 377 - Equipment Ident

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- On the ground the output labels are in the following state: -----------------------------------------------------------------------------| LABEL | PARAMETER DEFINITION | SSM | ON GND CRITERION | -----------------------------------------------------------------------------| 047 | S/W Ident | NO | | | 203 | Altitude | NO | | | 204 | Baro Corr Alt 1 | NO | | | 220 | Baro Corr Alt 2 | NO | | | 251 | Baro Corr Alt 3 | NO | | | 205 | Mach | NCD | 0 Mach less than 0.1 | | 206 | Computed Airspeed | NCD | 0 kt CAS less than 30 kts | | 207 | Max Allowable Airspeed | NO | | | 210 | True Airspeed | NCD | 0 kt CAS less than 60 kts | | 211 | Total Air Temp | NO | | | 212 | Altitude Rate | NO | | | 213 | Static Air Temp | NO | | | 215 | Impact Pressure | NO | | | 221 | Indicated AOA | NCD | NOTE CAS less than 60 kts | | 230 | True Airspeed | NCD | 0 kt CAS less than 60 kts | | 231 | Total Air Temp | NO | | | 232 | Altitude Rate | NO | | | 233 | Static Air Temp | NO | | | 234 | Baro Corr (hPa) 1 | NO | | | 236 | Baro Corr (hPa) 2 | NO | | | 235 | Baro Corr (in.Hg) 1 | NO | | | 237 | Baro Corr (in.Hg) 2 | NO | | | 240 | VMO/MMO | NO | | | 241 | Corrected AOA | NCD | Cmptd value CAS less than 60Kts | | 242 | Total Pressure | NO | | | 176 | L. Static Pressure | NO | | | 177 | R. Static Pressure | NO | | | 245 | Uncrctd Avg Stat Pressure| NO | | | 246 | Corctd Avg Stat Pressure | NO | | | 270 | Discrete word 1 | NO | | | 271 | Discrete word 2 | NO | | | 272 | Discrete word 3 | NO | | | 277 | ADR test | NO | | | 352 | Discrete word 4 | NO | | | 354 | LRU ident | NO | | | 377 | Equipement ident | NO | | | 356 | CFDIU interface word | N/A | N/A | -----------------------------------------------------------------------------Table 16 - Output Label Value on Ground

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(b) Discrete form The ADR provides seven standard OPEN/GROUND output discretes (Ref. table 17). -------------------------------------------------------------------------| SIGNAL | PIN | OUTPUT | DEFINITION | |------------------------------|------------|-------------|--------------| | ADR OFF Status | TP- 4E | OPEN/GROUND | ON/OFF | | ADR FAULT | TP- 4D | OPEN/GROUND | NO/FAULT | | Low Speed Warning Discrete 1 | TP- 2F | OPEN/GROUND | SLOW/FAST | | Low Speed Warning Discrete 2 | TP- 2G | OPEN/GROUND | SLOW/FAST | | Low Speed Warning Discrete 3 | TP- 6F | OPEN/GROUND | SLOW/FAST | | Low Speed Warning Discrete 4 | TP-13H | OPEN/GROUND | FAST/SLOW | | AOA Special Test | TP-12G | OPEN/28VDC | NO/TEST | -------------------------------------------------------------------------Table 17 - ADR - Discrete Output Signals 1 _

ADR OFF Status When the ADR is commanded OFF, it issues a ground state to the ADR OFF light discrete to enable the legend to come on.

2 _

ADR FAULT When an ADR FAULT is detected, the ADR issues a ground state to the ADR FAULT discrete to enable the legend to come on.

3 _

Low speed warning discretes 1, 2, 3, 4 The ADR provides four standard Open/Ground low speed-warning output discretes. - Airspeed conditions Airspeed decreasing Discrete 1 = OPEN for Airspeed less than or equal to 100 knots Discrete 2 = OPEN for Airspeed less than or equal to 50 knots Discrete 3 = OPEN for Airspeed less than or equal to 155 knots Discrete 4 = GROUND for Airspeed less than or equal to 260 knots Airspeed increasing Discrete 1 = GROUND for Airspeed greater than 104 knots Discrete 2 = GROUND for Airspeed greater than 54 knots Discrete 3 = GROUND for Airspeed greater than 159 knots Discrete 4 = OPEN for Airspeed greater than 264 knots - Power off conditions Discrete 1 = OPEN Discrete 2 = OPEN Discrete 3 = OPEN

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Discrete 4 = - CAS detected Discrete 1 = Discrete 2 = Discrete 3 = Discrete 4 = 4 _

OPEN failure condition previous state previous state previous state OPEN

AOA special test The ADR provides an OPEN/GROUND output discrete to drive the AOA self-test. The AOA self-test is commanded via the CFDS interface bus. When the AOA test is active, the AOA sensor is offset to +15 deg. (plus or minus 1 deg.). All AOA dependent parameters reflect this offset and their SSMs indicate Functional Test (FT). The RETURN command from the MCDU results in the discrete output set to OPEN. Ref. 34-18-00 for more details.

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3. ________________________________ Operation/Control and Indicating A. Control (1) ADIRS Control and Display Unit (CDU) (Ref. Fig. 004) The ADIRS CDU provides the control and warning of the three ADRs by means of three ADR illuminated pushbutton switches: - the pushbutton switch is used to disable the ADR output buses. It is a momentary action pushbutton switch - when the ADR output buses are disabled, the ADR controls the activation of the ADR OFF legend by its output discrete: ADR OFF status - when an ADR failure is detected, the ADR controls the activation of the ADR FAULT legend by its output discrete: ADR FAULT - each ADR is de-energized when the associated OFF/NAV/ATT selector switch is set to OFF - when the associated OFF/NAV/ATT selector switch is set to NAV or ATT, each ADR is switched on independently of the previous selection on the ADR pushbutton switch. B. Indicating Altitude (ALT), Computed Airspeed (CAS), Mach number (M) and Vertical Speed (V/S) are computed by the ADIRU (ADR portion), processed by the associated DMC and displayed on the PFDs. True Airspeed (TAS) is supplied in the same way but is displayed on the NDs. In normal configuration, with the AIR DATA selector switch in NORM position, the ADR 1 displays information on CAPT PFD and ND. The ADR 2 displays information on F/O PFD and ND. Static Air Temperature (SAT) and Total Air Temperature (TAT) are also supplied in the same way but are permanently displayed on the lower part of the lower ECAM DU. These items of information are displayed by the ADR 2 when EIS 1 is installed, by ADR 1 when EIS 2 is installed. (1) PFD display For further details concerning speed, altitude or vertical speed scale, Ref. 31-64-00. (a) Computed Airspeed (CAS) (Ref. Fig. 005) The CAS indication is displayed in analog form by means of a white tape with graduations every 10 kts and digital values every 20 kts. This tape moves up and down so as to indicate the A/C actual speed value in front of a fixed yellow reference line.

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ADR Control on CDU Figure 004   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 39   Config-1 Feb 01/08 R  CES

 

Computed Airspeed and Mach Indication Display Figure 005   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 40   Config-1 Feb 01/08 R  CES

 

The displayed part of the scale represents an 84 kts range. The scale is graduated from 30 kts to 520 kts and the digital values from 40 to 520 kts (item A). In no case can the displayed CAS be lower than 30 kts. In case of computed airspeed failure, the speed scale goes out of view and is replaced by a red SPD flag (item B). (b) Mach number (M) When the Mach number is above 0.5, it is displayed just below the speed scale. In case of failure, a red MACH flag is presented. (c) Altitude (ALT) (Ref. Fig. 006) The baro altitude indication is provided by means of a tape which moves up and down behind a window within which the A/C actual altitude is displayed. The tape of the scale is graduated every 100 ft and digital values are displayed every 500 ft in hundreds. The A/C actual altitude is provided by a counter located at the middle of the scale in which the actual value is displayed in green digits. The hundreds of feet are written in a large size whereas the tens and units are displayed by a drum operating as a classical mechanical altimeter. Small white marks are positioned in front of each number on the tape (item A). If the altitude is negative, a NEG white indication is added at the left of the digital value. The digital value is limited to minus 1500 ft (item B). Different displays are presented depending on the baro setting reference (standard or baro corrected), Ref. 31-64-00. In case of baro altitude failure, the scale goes out of view and a red ALT flag flashes for a few seconds in the altitude window then remains steady (item C). In case of discrepancy between the altitude given by the CAPT air data source and the altitude given by the F/O air data source, a CHECK ALT amber flag is presented on the right side of the altitude scale (item D). (d) Vertical Speed (V/S) (Ref. Fig. 007) The baro vertical speed is automatically displayed in the right side of the PFD when the inertial vertical speed is not available (item A). It is a degraded mode. The vertical speed scale consists of:

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Altitude Indication Display Figure 006   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 42   Config-1 Feb 01/08 R  CES

 

Vertical Speed Indication Display Figure 007   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 43   Config-1 Feb 01/08 R  CES

 

- a trapezoidal grey background colored surface - a fixed white scale with 500 ft/mn spaced marks from -2000 ft/mn to +2000 ft/mn - a needle giving in analog form the actual vertical speed value - a number in a moving amber window. This window accompanies the needle (above the needle if V/S > 0, below if V/S < 0). The number gives the V/S value in hundreds of ft/mn. Between -200 ft/mn and +200 ft/mn, both the window and the number disappear. - above +6000 ft/mn (or below -6000 ft/mn), the needle remains stopped where it is. When the vertical speed exceeds +6000 ft/mn or -6000 ft/mn, the digital indication and the analog needle change from green to amber. In addition, those indications change to amber in approach, in the following cases: - V/S less than -2000 ft/mn below 2500 ft RA - V/S less than -1200 ft/mn below 1000 ft RA. In case of a failure warning, the vertical speed scale is removed and replaced by a red V/S flag which flashes for a few seconds then remains steady (item B). (2) ND display (Ref. Fig. 008) The true airspeed (TAS) is displayed on the ND in ROSE, ARC and PLAN mode (item A). The TAS information is displayed by a numerical indication of three digits preceded by TAS indication. This information is displayed in the left upper corner of the ND for speed higher than 100 kts. Below this value TAS indication remains visible but is followed by three dashes (item B). (3) Display on the lower ECAM DU (Ref. Fig. 009) The Static Air Temperature (SAT) and the Total Air Temperature (TAT) are permanently displayed on the lower part of the lower ECAM DU by a numerical indication of two digits preceded by the plus or minus sign (item A). These data are delivered by the ADR 2 when EIS 1 is installed, by ADR 1 when EIS 2 is installed. In case of failure or when NCD information is received from the ADR 2, these data are replaced by crosses (item B).

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True Airspeed Indication Display Figure 008   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 45   Config-1 Feb 01/08 R  CES

 

TAT/SAT Indication Display Figure 009   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 46   Config-1 Feb 01/08 R  CES

 

(4) Reconfiguration display In case of loss of AIR DATA parameters on CAPT or F/O PFD and ND, the ADR 3 can be used as a back up source by placing the AIR DATA selector switch in CAPT/3 position for EFIS 1 and F/O/3 position for EFIS 2. In case of loss of TAT/SAT parameters on the lower ECAM DU, the ADR 3 can be used as a back up source by placing the AIR DATA selector switch in F/O/3 position when EIS 1 is installed, in CAPT/3 position when EIS 2 is installed.

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C. Warnings In addition to the AIR DATA flags displayed on the PFDs and NDs and on the CDU, warning messages are displayed on the lower part of the upper ECAM DU. Two kinds of warning messages can be displayed: - failure warning messages in case of loss of AIR DATA parameters - configuration warning messages in case of dangerous configuration of the aircraft. When the CLR key is pushed on the ECAM control panel, a STATUS page is displayed on the lower ECAM DU and indicates the STATUS and INOP SYS (systems). (1) Failure warning messages (Ref. Fig. 010, 011, 012) (a) NAV ADR 1(2)(3) FAULT NAV ADR 1(2) + 2(3) FAULT When these messages are displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the FAULT legend of the ADR pushbutton switch on the CDU comes on. (b) NAV ALTI DISCREPANCY (Ref. Fig. 013) This message is displayed when a difference higher than plus or minus 250 ft is detected by the external comparison inside the FWCs between the baro-corrected altitude (or plus or minus 500 ft for the standard altitude) provided by two ADRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK ALT message appears on the PFD.

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NAV ADR 1(2)(3) FAULT Message Figure 010   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 48   Config-1 Feb 01/08 R  CES

 

NAV ADR 1+3(2+3) FAULT Message Figure 011   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 49   Config-1 Feb 01/08 R  CES

 

NAV ADR 1 + 2 FAULT Message Figure 012   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 50   Config-1 Feb 01/08 R  CES

 

NAV ALTI DISCREPANCY Message Figure 013   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 51   Config-1 Feb 01/08 R  CES

 

(2) Configuration warning messages (Ref. Fig. 014, 015) (a) OVERSPEED VM0/MM0 OVERSPEED VFE/VLE When these messages are displayed: - the MASTER WARN lights on the glareshield flash - the Continuous Repetitive Chime (CRC) sounds. OVERSPEED VMO/MMO warning processed by the FWC is triggered when the CAS/Mach calculated by the ADR exceed the VMO/MMO threshold by more than 4 kts/0.006 Mach. OVERSPEED VFE/VLE processed by the FWC is a function of CAS and depends on slat/flap position for the VFE and landing gear position for the VLE. For overspeed VLE, the warning is triggered at 284 knots. (b) Stall warning (Ref. Fig. 016) When this warning is activated: - the MASTER WARN lights on the glareshield flash - the cricket and the voice STALL sound. This warning is processed by the FWC and is a function of angle of attack value and slat position following these conditions: - normal law: if corrected angle of attack exceeds 23⁰ or if corrected angle of attack exceeds 15⁰ and slat < 15⁰ and aircraft in clean configuration - alternate law if corrected angle of attack exceeds 13⁰ or if corrected angle of attack exceeds 8⁰ and slat < 15⁰.

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OVERSPEED VMO/MMO Message Figure 014   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 53   Config-1 Feb 01/08 R  CES

 

OVERSPEED VFE/VLE Message Figure 015   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 54   Config-1 Feb 01/08 R  CES

 

Stall Warning Message Figure 016   EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00 Page 55   Config-1 Feb 01/08 R  CES

 

AIR DATA - DESCRIPTION AND OPERATION ____________________________________ 1. _______ General The Air Data Reference (ADR) portion of the Air Data/Inertial Reference Unit (ADIRU) provides main data sources which are air data references for the aircraft avionics systems. The ADR receives and processes the outputs of the Air Data Modules (ADM) and other sensors (Ref. 34-11-00). It computes the aerodynamic parameters in the form of ARINC 429 low-speed buses. For more details concerning the user systems, ref. 34-12-00. 2. __________________ System Description A. ADR Operation (1) General The ADR software performs five basic computational elements which are under the air data calculations as follows: - pressure altitude functions (ALT/ALT rate) - Mach calculation (M) - airspeed calculation (CAS/TAS) - temperature calculation (SAT/TAT) - output signal processing. Aircraft-dependent calculations are also included in the operational software: - static source error correction - angle of attack (AOA) - maximum operating speed (MMO/VMO). The system tests include continuous in-flight monitoring and manually-activated test modes. The in-flight monitoring includes test of: - input signal integrity - input interface integrity - memory integrity - computational integrity - output signal integrity. The continuous monitoring detects and annunciates faults in the ADR during normal operation. Faults are stored in BITE history in Non Volatile Memory (NVM) and sent to the Centralized Fault Display System (CFDS) via digital words.

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(2) Inputs (a) Digital inputs 1 _

Air Data Modules (ADM) inputs The ADR receives three input bus from its corresponding ADM. These buses transmit the following input data words depending on the ADM installation: Label 242: Total Pressure Label 176: Left Static Pressure Label 177: Right Static Pressure Label 245: Averaged Static Pressure Each of these words is a 32-bit word with the following format: ---------------------------------------------------------| BIT POSITION | DATA | ---------------------------------------------------------| 1 - 8 | Label | | 9 - 10 | SDI | | 11 - 28 | Pressure Value | | 29 | Sign bit (0 = positive) | | 30 - 31 | Status matrix | | 32 | Parity bit | ---------------------------------------------------------ADM Input Label These data words are output on all eight Air Data output data buses and used for calculation of corrected pressure data.

2 _

Flight Control Unit (FCU) inputs The ADR receives one input bus from the FCU, for digital baro corrections. The FCU output bus sends: BCD label 234 Baro Correction 1(hPa) for CAPT side BCD label 236 Baro Correction 2(hPa) for F/O side. Each ADR receives the two FCU output buses according to the discrete selection as explained in Para. 2.A.(2)(c) (discrete inputs). Each of these words is a 32-bit BCD word with the following format:

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----------------------------------------------------------| BIT POSITION | DATA | ----------------------------------------------------------| 1 - 8 | Label | | 9 - 10 | SDI | | 11 - 28 | Value | | 29 | Sign bit | | 30 - 31 | Status matrix | | 32 | Parity | ----------------------------------------------------------FCU Input Label 3 _

Centralized Fault Display Interface Unit (CFDIU) input For maintenance purposes, the ADR receives one input bus from the CFDIU. For more details, ref. 34-18-00.

4 _

Air Data Reference (ADR) input Each ADR receives two intercommunication buses from the other ADRs for cross channel comparison purpose.

(b) Analog inputs 1 _

Total Air Temperature (TAT) input The ADR measures the resistance of the sensing element of the TAT sensor (Ref. 34-11-00). The ADR subtracts a fixed value (1.04 ohm) from the measured input resistance to compensate for aircraft wiring resistance.

2 _

Angle of Attack (AOA) inputs (Ref. Fig. 001) The ADR receives two resolver inputs for angle of attack computation. The following requirements apply to the analog resolver inputs: - load: 15 kilohms minimum - reference: 26 V, 400 Hz (same as AOA) - transformer ratio: 0.415 nominal plus or minus 10 % - phase shift: 8.8 to 30 deg. leading - source impedance: Zro = A + jB A less than 315, B less than 725 Zso = C + jD C less than 150, D less than 165 - voltage range: 23 to 31.7 VRMS - peak factor: 1.31 to 1.51 - electrical range input: plus or minus 60 deg.

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AOA/ADR Wiring Figure 001   EFF : 524-526, 528-599,  34-13-00 Page 4   Config-2 Feb 01/10  CES

 

3 _

Analog baro correction inputs The ADR receives three resolver inputs for analog baro correction (from the altimeter for example). These inputs are not used.

(c) Discrete inputs For pin assignment, Ref. 34-12-00. The ADR is provided with the following input discretes: ---------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT DEFINITION | ---------------------------------------------------------------| ADR ARINC Filter Select | Open/GND | Type A/Type B | | CFDS Message Select | Open/GND | Active/Not Active | | SDI LSB (Middle Insert) | Open/GND | 0/1 | | SDI MSB (Middle Insert) | Open/GND | 0/1 | | Pitot Probe Ht Disc | Open/GND | No Fault/Fault | | Right Static Ht Disc | Open/GND | No Fault/Fault | | Left Static Ht Disc | Open/GND | No Fault/Fault | | TAT Ht Disc | Open/GND | Off/On | | AOA 1 Ht Disc | Open/GND | No Fault/Fault | | AOA Average/Unique | Open/GND | Average/Unique | | VMO/MMO Disc 1 | Open/GND | No/Yes | | VMO/MMO Disc 2 | Open/GND | No/Yes | | VMO/MMO Disc 3 | Open/GND | No/Yes | | VMO/MMO Disc 4 | Open/GND | No/Yes | | SSEC Alternate Disc A | Open/GND | No/Yes | | SSEC Alternate Disc B | Open/GND | N0/Yes | | AOA Alternate Disc 1A | Open/GND | Off/On | | AOA Alternate Disc 1B | Open/GND | Off/On | | AOA Alternate Disc 2A | Open/GND | Off/On | | AOA Alternate Disc 2B | Open/GND | Off/On | | Baro Port A | Open/GND | Port B/Port A | | Zero MACH SSEC | Open/GND | Use SSEC/Ignore SSEC | | Zero AOA SSEC | Open/GND | Use SSEC/Ignore SSEC | | AIR FRM ID Code 1/0 |Open/A.I.Com | No/Yes | | AIR FRM ID Code 2/0 |Open/A.I.Com | No/Yes | | AIR FRM ID Code 4/0 |Open/A.I.Com | No/Yes | | AIR FRM ID Code 8/0 |Open/A.I.Com | No/Yes | | AIR FRM ID Code 16/0 |Open/A.I.Com | No/Yes | | AIR FRM ID Code Parity |Open/A.I.Com | No/Yes | | ADR Remote Test | Open/GND | No Test/Test | | ADR OFF DISCR Input | Open/GND | Released/Pressed | | Dual Baro | Open/GND | Sgl Port/Dual Port | | Baro Analog/Digital Sel.| Open/GND | Digital/Analog | | Baro Corr. 3 Active | Open/GND | Not Active/Active | ----------------------------------------------------------------

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---------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT DEFINITION | ---------------------------------------------------------------Discrete Input Signal NOTE : Open means either a high logic voltage level or the ____ binary zero state. GND means either a low logic voltage level or the binary one state. A.I. Com means grounded to the Aircraft Ident Common pin through a resistance of 10 ohms or less. For program pin inputs other than Aircraft I.D., GND means grounded to the Program Pin Common pin through a resistance of 10 ohms or less. 1 _

ADR ARINC Filter Select discrete This discrete is used to select the characteristics of the ADR output filter. Two sets of characteristics are available: Open/Ground = Type A/Type B The A/C is defined with the ADR ARINC filter select discrete open. -------------------------------------------------------------| | | TYPE A | TYPE B | | OCTAL | | MAXIMUM | MAXIMUM | | LABEL | SIGNAL | 3db FILTER | 3db FILTER | | | | BANDWIDTH | BANDWIDTH | | | | (HZ)(1) | (HZ) | -------------------------------------------------------------| 203 |Altitude | 8 | 3 | | 204 |Baro Cor. Alt. 1 | 8 | 3 | | 205 |Mach | 8 | 3 | | 206 |Computed Airspeed | 8 | 3 | | 207 |Max Allow. Airspeed | 8 | 8 | | 210 |True Airspeed | 8 | 3 | | 211 |Total Air Temp | 4 | 3 | | 212 |Altitude Rate | 1.8 | 1.8 | | 213 |Static Air Temp | 4 | 3 | | 215 |Impact Pressure | 8 | 3 | | 220 |Baro Cor. Alt. 2 | 8 | 3 | | 221 |Ind. Angle of Attack | 8 | 3 | | 241 |Cor. Angle of Attack | 8 | 3 | | 242 |Total Pressure | N/A (2) | N/A (2) | | 176 |Left Static Pressure | N/A (2) | N/A (2) | | 177 |Right Static Pressure | N/A (2) | N/A (2) | | 245 |Uncorr Avg Static Pressure| N/A (2) | N/A (2) |

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-------------------------------------------------------------| | | TYPE A | TYPE B | | OCTAL | | MAXIMUM | MAXIMUM | | LABEL | SIGNAL | 3db FILTER | 3db FILTER | | | | BANDWIDTH | BANDWIDTH | | | | (HZ)(1) | (HZ) | -------------------------------------------------------------| 246 |Corr Avg Static Pressure | N/A (2) | N/A (2) | | 251 |Baro Cor. Alt. 3 | 8 | 3 | -------------------------------------------------------------ADR Output Filter Characteristics NOTE : (1) Filters present only as provisions, except for ____ Altitude Rate. (2) Filtering of pressure data is performed by the ADM. 2 _

CFDS Message Select discrete When open, this discrete is used to select and display fault messages.

3 _

Source Data Identifier (SDI) program pins These discretes code the installation side of the ADIRU. This item of information is used to choose the appropriate correction laws (for Static Source Error Correction (SSEC) and corrected angle of attack). The following table gives the ADR side according to the SDI: -------------------------------------------------------| DEBOUNCED STATUS | | | |-----------------------------| SDI | ADIRU | | SDI-MSB | SDI-LSB | CODE | NUMBER | |------------------------------------------------------| | OPEN | GND | 01 | 1 | | GND | OPEN | 10 | 2 | | GND | GND | 11 | 3 | -------------------------------------------------------ADR SDI Code

4 _

Sensor heat status discretes These discrete inputs are used to provide the sensors heat status to the ADR. These discretes are of the open/ground type. When the TAT HEAT DISC is grounded, the TAT sensor is heated. When one of the STATIC, PITOT or AOA HEAT discretes is grounded, it means that the output of the Probe Heat Computer (PHC) heating power supply is faulty and that the concerned probe is no longer heated.

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In this case the ADR operates as a relay which sends these information signals to the FWC for warning purposes. 5 _

AOA Average/Unique program pin The ADR uses the AOA Average/Unique program pin to determine whether one or two angle of attack resolver inputs are used for angle of attack computations. When this program pin indicates Unique, the ADR uses only a single angle of attack input. If this first AOA input fails, the ADR uses the opposite AOA input, as shown in the table below. When this program pin indicates Average, the ADR calculates the angle of attack based on the average of the angle of attack inputs 1 and 2. ------------------------------------------------------| SYSTEM | INITIAL NON-FAULT | INPUT TO ADR | | NUMBER | INPUT TO ADR | AFTER FAULT | ------------------------------------------------------| 1 | input number 1 | input number 2 | | 2 | input number 2 | input number 1 | | 3 | input number 1 | input number 2 | ------------------------------------------------------AOA Resolver Input The characteristics of these discretes are OPEN/GROUND = AVERAGE/UNIQUE. The A/C is defined with the AOA average/unique discrete grounded.

6 _

VMO/MMO Program Discretes 1 through 4 These discretes are used to select alternate VMO/MMO levels. There are four alternates and a basic VMO/MMO for each aircraft type. The table below defines VMO/MMO versus state of the VMO/MMO program discretes. With no VMO/MMO discretes in the ground state (yes), the ADR defaults to the BASIC LAW values for VMO/MMO. Only one of the four VMO/MMO program discretes can be in the ground state at any one time. If more than one VMO/MMO program discrete is in the ground state at any one time, the ADR defaults to the lowest available alternate condition.

7 _

On the A/C, only the VMO/MMO DISC 2 is available and is provided by the L/G DOWN VMO/MMO SELECTION switch (22FP). The normal position of this switch is open and it is grounded after crew action for particular flights (ferry flight for example).

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The table below defines VMO/MMO state according to the switch (22FP) position. ---------------------------------------------------------| | VMO | MMO | SWITCH | | LAW | (kts) | (Mach) | 22FP | ---------------------------------------------------------| BASIC | 350 | 0.82 | OPEN | | ALT 1 | | | | | ALT 2 | 235 | 0.60 | GROUND | | ALT 3 | | | | | ALT 4 | | | | ---------------------------------------------------------VMO/MMO Selection 8 _

SSEC Alternate discrete The ADR is provided with two Static Source Error Correction (SSEC) data sets stored in the computer for each SDI and for each of sixteen aircraft types, one for use in normal conditions and the other for use in alternate conditions. With the two SSEC selection discretes open (no), the ADR uses the normal SSEC curve for the aircraft type in which it is installed. With the two SSEC selection discretes grounded (yes), the ADR uses the alternate condition curve.

9 _

AOA Alternate discrete The ADR uses the alternate discrete inputs from the two redundant SFCCs to select the angle of attack correction which is appropriate for the current slat and flap settings. Three laws are available for each aircraft type and SDI: - the normal law is activated when all the discretes are open - the alternate 1 law is activated when discretes 1A and 2A are grounded - the alternate 2 law is activated when discretes 1A, 2A, 1B and 2B are grounded.

10 __

Baro Port A discrete The ADR uses this discrete to select which ARINC 429 port is used as a source for all baro-correction input data. If this discrete is grounded, the baro port A is selected. If this discrete is open, the baro port B is selected. The A/C is wired with this discrete grounded (Ref. Dual Baro discrete).

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11 __

Dual Baro discrete The ADR uses this discrete to select which ARINC 429 port is used as a source for all baro-correction input data. If this discrete is grounded, the baro port A and the baro port B are selected and the baro port A discrete selection is overridden. If this discrete is open, the baro port A or the baro port B is selected depending on the baro port A discrete selection. The A/C is wired with this discrete open.

12 __

Zero MACH SSEC discrete The ADR uses this discrete to select the SSEC as a function of Mach. When this program pin indicates Use SSEC (open), the SSEC as a function of Mach is computed. When this program pin indicates Ignore SSEC (ground), the ADR uses zero correction. The A/C is wired with this discrete open.

13 __

Zero AOA SSEC discrete The ADR uses this discrete to select the SSEC as a function of the angle of attack. When this program pin indicates Use SSEC (open), the SSEC as a function of AOA is computed. When this program pin indicates Ignore SSEC (ground), the ADR uses zero correction. The A/C is wired with this discrete open.

14 __

AIR FRM ID Code discrete The ADR uses input discretes to identify the aircraft (type, engine model) on which the ADIRU is fitted, and to select the appropriate set of correction laws for Static Source Error Correction (SSEC) and AOA corrections. The ADIRU memory has the capacity to store 128 different sets of laws. To perform this coding, the ADR wires seven input discretes and one discrete for parity to a common.

15 __

ADR Remote Test discrete The ADR uses one discrete to select the remote test by external control. When this discrete is open, the test is not activated. When this discrete is grounded, the test is activated. The A/C is wired with this discrete open (unused). The test is activated via the CFDS (Ref. 34-18-00).

16 __

ADR OFF DISCR input discrete The ADR uses this discrete input to toggle its state between ON and OFF. When the ADR is OFF, the output buses are disabled and the ADR FAULT legend is inhibited whenever the momentary action ADR pushbutton switch is pushed. When the ADR is ON,

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the output bus output data and the ADR FAULT legend operate normally. The ADR OFF DISCR input does not modify Air Data computation. 17 __

Baro Analog/Digital Sel discrete The ADR uses this discrete to select either the analog or digital baro correction. When this discrete is grounded, the analog baro correction is selected. When this discrete is open, the digital baro correction is selected. The A/C is wired with this discrete open.

18 __

Baro Corr 3 Active discrete The ADR uses this discrete to determine for BITE purposes whether the baro correction 3 is connected or not. When the discrete is grounded, the baro correction 3 is connected. When the discrete is open, the baro correction 3 is not connected. The A/C is wired with this discrete open.

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(3) Acquisition and processing of the sensor inputs (a) Pressure computation (Ref. Fig. 002) Based on pressure raw data received from the ADM (Ref. para. 2.A.(2)(a)1), the software converts the asynchronous pressure inputs into regularly-scheduled pressure data. During correction of static pressure, the software calculates the limited left, right and average static pressure in a range of 100 to 1100 hPa from the ADM inputs. From the average static pressure (Psm), the software calculates the corrected static pressure based on the SSEC factor: ( G1 G2 ) Psc = Psm (1 + ---- + ----) ( 1000 1000) - G1 depends on flaps and Mach is interpolated in a table (2 flaps position and 19 Mach values are considered) - G2 depends on Mach and AOA corrected and is interpolated in a table (6 AOA values and 18 Mach values are considered). The correct SSEC factor depends on the sensor location and on the aircraft configuration. The ADR memory contains several tables and the appropriate one is selected according to the following input discretes: . SDI . aircraft Ident . SSEC Alternate. Two input discretes can be used to force the SSEC factor to be independent from AOA or Mach: . zero MACH SSEC . zero AOA SSEC. Ref. Para. 2.A.(2)(c) for more details. No correction is needed for the total pressure received from the ADM. The results of the above computation is available on these output labels: . label 176 Left Static Pressure . label 177 Right Static Pressure . label 242 Total Pressure . label 245 Averaged Static Pressure . label 246 Corrected Static Pressure

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Pressure Computation - Block Diagram Figure 002   EFF : 524-526, 528-599,  34-13-00 Page 13   Config-2 Feb 01/10  CES

 

(b) Temperature computation (Ref. Fig. 003) The resistance measured by the ADR and compensated for aircraft wiring is then converted into a temperature value (TAT) according to the Callender-Van Dusen equation given for a 500 ohm platinum sensing element: | 3| Rt | (TAT ) (TAT ) (TAT ) (TAT) | -- = 1 + a | TAT - d (--- -1) (--- ) - b (--- -1) (---) | Ro | (100 ) (100 ) (100 ) (100) | TAT = temperature in deg.C (TAT) Rt = Resistance at temperature TAT Ro = Resistance at 0 deg.C = 500 ohm a = 0.003832 d = 1.81 b = 0.1 for temperature below 0 deg.C b = 0 for temperature above 0 deg.C The computation also compensates the TAT value for heating effect. The ADR knows when the sensor is heated by the state of the TAT Heat input discrete from the PHC. The heating compensation law is provided by the TAT sensor supplier and is a function of Mach and air density. The PHC 1 controls the heating of the TAT sensor 1 and the PHC 2 controls the heating of the TAT sensor 2. On the ground, the sensors are not heated (Ref. 30-31-00 for more details). The result of the above computation is available on the following output labels: - label 211 Total Air Temperature (BNR) - label 231 Total Air Temperature (BCD).

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Temperature (TAT) Computation - Block Diagram Figure 003   EFF : 524-526, 528-599,  34-13-00 Page 15   Config-2 Feb 01/10  CES

 

(c) AOA computation (Ref. Fig. 004) The A/C is wired in the AOA unique selection, so the ADR computes the AOA with the reading of one resolver. The second resolver is used as a back-up. The monitoring function is described in 34.18 The ADR determines the corrected angle of attack value which depends on the system number and the slat/flap position. For a CAS less than 60 kts: AOAc = 0 and status matrix is coded NCD. For a CAS more than or equal to 60 kts, the corrected angle of attack is calculated as follows: AOA ind AOAc = ------- + I K where: AOA ind = Indicated Angle of Attack (Ref. 34-11-00 for the relation between resolver and AOA indication) K, I = Correction coefficients which depend on system number, slat and flap configuration and magnitude AOA indication. The configuration is defined by the status of four input discretes (Ref. 2.A.(2)(c)). The results of the above computation is available on the labels: - label 221 = Indicated Angle of Attack - label 241 = Corrected Angle of Attack

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SFCC/AOA - AOA Alternate Discrete Signals Figure 004   EFF : 524-526, 528-599,  34-13-00 Page 17   Config-2 Feb 01/10  CES

 

(4) Parameter computation (a) General The operational software of the ADR performs the following computations: - pressure altitude and pressure altitude rate function (ALT) - Mach function (M) - airspeed function (CAS/TAS) - temperature function (SAT/TAT) - maximum operating speed function (VMO/MMO). (b) Altitude computation The ADR software computes these different parameters: label 203 Pressure Altitude label 212 Altitude Rate label 204 Baro Corrected Altitude 1 (CAPT) label 220 Baro Corrected Altitude 2 (F/O) label 235 Baro Correction In Hg 1 (CAPT) label 237 Baro Correction In Hg 2 (F/O) 1 _

Altitude pressure and altitude rate computation (Ref. Fig. 005) The altitude is derived from the corrected static pressure. The conversion from pressure to altitude is based on the geopotential altitude tables of the US Standard Atmosphere, 1962. The accepted range is (-2000 ft, +50,000 ft). The altitude rate is calculated by multiplying the rate of change of the corrected static pressure by the derivative of altitude with respect to corrected static pressure: dH d Ps dH -- = ---- x ---dt dt d Ps

2 _

Corrected altitude computation (Ref. Fig. 006) The ADR receives the baro correction introduced on the FCU by each crew member. The ADR uses the values in hPa (labels 234 and 236 from the FCU). The ADR also converts these values into inches of mercury (in. Hg) and the result is sent on the output labels 235, 237. The corrected altitude is calculated by a shift of the pressure altitude to a value corresponding to the entered baro correction. The result is sent on label 204 for CAPT baro corrected altitude and label 220 for F/O baro corrected altitude.

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Altitude and Altitude Rate Computation - Block Diagram Figure 005   EFF : 524-526, 528-599,  34-13-00 Page 19   Config-2 Feb 01/10  CES

 

Corrected Altitude Computation - Block Diagram Figure 006   EFF : 524-526, 528-599,  34-13-00 Page 20   Config-2 Feb 01/10  CES

 

(c) CAS/Mach computation (Ref. Fig. 007) The ADR software computes these different parameters: label 206 Computed Airspeed label 205 Mach label 207 Maximum Allowable Airspeed. The CAS and Mach computation is based on the conversion of the impact pressure: impact pressure = Pt - Ps. - the CAS computation converts input of impact pressure to output corresponding to computed airspeed with: ______________________ / Qc 2/7 CAS = Cso X V 5 X ((-- + 1) - 1) Po CAS = Computed Airspeed in knots Cso = Speed of sound under standard day sea level conditions = 661.4746 kts Qc = Impact pressure in hPa Po = Standard day sea level pressure = 1013.25 hPa For accuracy reason, the CAS is output with a valid (NO) SSM only after 30 kts. If the CAS is below 30 kts, label 206 indicates 0 kt with SSM = NCD. - the Mach computation converts Qc/Ps to Mach, with: _______________________ / Qc 2/7 MACH = V 5 ((-- + 1) - 1) Ps MACH = Mach number Qc/Ps = Ratio of impact pressure to static pressure If Mach is below 0.1, label 205 indicates 0 with SSM = NCD.

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CAS/Mach Computation - Block Diagram Figure 007   EFF : 524-526, 528-599,  34-13-00 Page 22   Config-2 Feb 01/10  CES

 

(d) SAT/TAS computation (Ref. Fig. 008) The ADR software calculates these different parameters: label 213 BNR Static Air Temperature (SAT) label 233 BCD Static Air Temperature (SAT) label 210 BNR True Airspeed (TAS) label 230 BCD True Airspeed (TAS). - the calculation of the BNR SAT converts TAT to SAT with: TAT SAT = --------- 273.15 2 1 + 0.2M SAT = Static Air Temperature (in deg. C) TAT = Total Air Temperature (in deg. Kelvin) M = Mach number (corrected for static source error) - the calculation converts Static Air Temperature from BNR to BCD format. - the calculation of the BNR TAS converts Mach and SAT to TAS with: ___ / TAS = 38.96695 x M x V SAT TAS = True Airspeed (in knots) M = Mach Number (corrected for Static Source Error) SAT = Static Air Temperature (in deg. Kelvin) - the calculation converts True Airspeed from BNR to BCD format. For accuracy reason, the TAS is output with a valid (NO) SSM only after 60 kts. If TAS is below 60 kts, label 210 indicates 0 kt with SSM = NCD. (e) VMO/MM0 computation (Ref. Fig. 009) The software determines the normal or alternate VMO/MMO law selected by the VM0/MM0 input 2 discrete state; then it computes the label 207 Maximum Allowable Airspeed. This airspeed is based on the Maximum Allowable Airspeed under a certain altitude and on the Maximum Allowable Mach above this altitude. It is always indicated in knots and decreases when the altitude increases. NOTE : At a constant Mach, the Vc value decreases when the ____ altitude increases.

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SAT/TAS Computation - Block Diagram Figure 008   EFF : 524-526, 528-599,  34-13-00 Page 24   Config-2 Feb 01/10  CES

 

VMO/MMO Computation - Block Diagram Figure 009   EFF : 524-526, 528-599,  34-13-00 Page 25   Config-2 Feb 01/10  CES

 

(5) ADR data outputs The ADR data outputs are transmitted in two forms: digital and discrete. (a) Digital form The table below contains all the output parameters in the digital form. They are sorted in numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds. - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code. - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system.

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 176 |L STATIC |W2048 |hPa | | 16 |125 |BNR | | | | |PRESSURE |100 to 1100 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 177 |R STATIC |W2048 |hPa | | 16 |125 |BNR | | | | |PRESSURE |100 to 1100 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 203 |ALTITUDE |W+/- 131072 | ft | 29 | 17 | 62 |BNR | ALT | | | |1013.25mb |-2000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 +/-30 | | | | | | | | | | |(30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 204 |BARO CORR |W+/- 131072 | ft | 29 | 17 | 62 |BNR | | | | |ALT 1 |-1000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 +/-30 | | | | | | | | | | |(30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 205 |MACH |W4096 |Mach| | 16 |125 |BNR | MN | | | | |0.1 to 1.00 | | | | | | | | | | |R 6.25 E-5 | | | | | | | | | | |+/-0.010 | | | | | | | | | | |(0.1) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 206 |COMPUTED |W1024 |Kts | | 14 |125 |BNR | CAS | | | |AIRSPEED |30 to 450 | | | | | | | | | | |R 0.0625 | | | | | | | | | | |+1.5 (100) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 207 |MAXIMUM |W1024 |Kts | | 12 |125 |BNR | | | | |ALLOWABLE |150 to 450 | | | | | | | | | |AIRSPEED |R 0.25 +/- 1| | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 210 |TRUE |W2048 |Kts | | 15 |125 |BNR | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |AIRSPEED |60 to 599 | | | | | | | | | | |R 0.0625 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 211 |TOTAL AIR |W +/- 512 |Deg.| 29 | 11 |500 |BNR | TAT | | | |TEMP |-60 to 99 |C | | | | | | | | | |R 0.25 | | | | | | | | | | |+/- 0.5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 212 |ALTITUDE |W+/- 32768 |ft/ | 29 | 11 | 62 |BNR | | | | |RATE |-20,000 to |mn | | | | | | | | | | 20,000 | | | | | | | | | | |R 16.0 | | | | | | | | | | |+/-30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 213 |STATIC AIR|W+/- 512 |Deg.| 29 | 11 |500 |BNR | SAT | | | |TEMP |-99 to +80 |C | | | | | | | | | |R 0.25 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 215 |IMPACT |W512 |hPa | | 14 |125 |BNR | | | | |PRESSURE |0 to 372.5 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 220 |BARO CORR |W +/- 131072| ft | 29 | 17 | 62 |BNR | | | | |ALT 2 |-1000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 +/- 30 | | | | | | | | | | | (30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 221 |IND ANGLE |W +/- 180 |Deg.| 29 | 12 | 62 |BNR | | | | |OF ATTACK |-35 to +85 | | | | | | | | | | |R 0.0439 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 230 |TRUE |W +/- 799 |Kts | | 3 |500 |BCD | | | | |AIRSPEED |60 to 599 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |R 1 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 231 |TOTAL AIR |W +/- 799 |Deg.| | 2 |500 |BCD | | | | |TEMP |-60 to 99 |C | | | | | | | | | |R 1 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 233 |STATIC AIR|W +/- 799 |Deg.| | 2 |500 |BCD | | | | |TEMP |-99 to +80 |C | | | | | | | | | |R 1 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 234 |BARO |W +/- 7999.9|hPa | | 5 |500 |BCD | | | | |CORRECT 1 |745 to 1100 | | | | | | | | | |mb |R 0.1 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 235 |BARO |W +/- 79.999|inHg| | 5 |500 |BCD | | | | |CORRECT 1 |22.0 to 32.5| | | | | | | | | |in.Hg |R 0.001 | | | | | | | | | | |+/- 0.0074 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 236 |BARO |W +/- 7999.9|hPa | | 5 |500 |BCD | | | | |CORRECT 2 |745 to 1100 | | | | | | | | | |mb |R 0.1 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 237 |BARO |W +/- 79.999|inHg| | 5 |500 |BCD | | | | |CORRECT 2 |22.0 to 32.5| | | | | | | | | |in.Hg |R 0.001 | | | | | | | | | | |+/- 0.0074 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 240 |VMO/MMO |W 399/0.99 |Kts/| |3/2 |1000|BCD | | | | |STATUS |0 to 399 / |Mach| | | | | | | | | |0 to 0.99 | | | | | | | | | | |R 1 /0.01 | | | | | | | | | | |1 / 0.01 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 241 |CORRECTED |W +/- 180 |Deg.| 29 | 12 | 62 |BNR | AOA | | | |ANGLE OF |-35 to +85 | | | | | | | | | |ATTACK |R 0.0439 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 242 |TOTAL |W2048 |hPa | | 16 |125 |BNR | | | | |PRESSURE |100 to 1400 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 245 |UNCRCTD |W2048 |hPa | | 16 |125 |BNR | | | | |AVG STAT |100 to 1100 | | | | | | | | | |PRESSURE |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 246 |CORCTD |W2048 |hPa | | 16 |125 |BNR | | | | |AVG STAT |100 to 1100 | | | | | | | | | |PRESSURE |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DSCT WORD | | | | |500 |DIS | | | | | 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 271 |DSCT WORD | | | | |500 |DIS | | | | | 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 272 |DSCT WORD | | | | |500 |DIS | | | | | 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 350 |MAINT WORD| | | | |500 |DIS | | | | | 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 351 |MAINT WORD| | | | |500 |DIS | | | | | 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 352 |MAINT WORD| | | | |500 |DIS | | | | | 3 | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 155 |MAINT WORD| | | | |500 |DIS | | | | | 4 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 354 |LRU ID | | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 356 |FAULT STAT| | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQPT IDENT| | | | |500 |HEX | | | ------------------------------------------------------------------------------Output Label -------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | Icing Detector Heat | NO FAULT | FAULT | | 12 | Pitot Probe Heat | NO FAULT | FAULT | | 13 | ADR FAULT | FAULT | NO FAULT | | 14 | Right Static Heat | NO FAULT | FAULT | | 15 | Left Static Heat | NO FAULT | FAULT | | 16 | TAT Heat | HEAT | NO HEAT | | 17 | AOA 1 Heat | NO FAULT | FAULT | | 18 | AOA 2 Heat | NO FAULT | FAULT | | 19 | Overspeed Warning | WARN | NO WARN | | 20 | Spare (Primary AOA Fault) | | | | 21 | AOA Average/Unique | UNIQUE | AVERAGE | | 22 | VMO/MMO 1 | YES | NO | | 23 | VMO/MMO 2 | YES | NO | | 24 | VMO/MMO 3 | YES | NO | | 25 | VMO/MMO 4 | YES | NO | | 26 | SSEC Alternate Select 1 | YES | NO | | 27 | SSEC Alternate Select 2 | YES | NO | | 28 | Baro Port A Select | Port A | Port B | | 29 | Zero Mach SSEC Select | YES | NO | -------------------------------------------------------------------------Label 270 - Discrete Word 1

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-------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | Zero AOA SSEC Select | YES | NO | | 12 | AOA Test Active | ACTIVE | NOT ACTIVE | | 13 | Low Speed Warning 1 | FAST | SLOW | | 14 | Low Speed Warning 2 | FAST | SLOW | | 15 | Low Speed Warning 3 | FAST | SLOW | | 16 | Low Speed Warning 4 | SLOW | FAST | | 17 | Spare | | | | 18 | Spare | | | | 19 | Spare | | | | 20 | AOA Correction 1A | YES | NO | | 21 | AOA Correction 1B | YES | NO | | 22 | AOA Correction 2A | YES | NO | | 23 | AOA Correction 2B | YES | NO | |24 to 29| Spare | | | -------------------------------------------------------------------------Label 271 - Discrete Word 2 -------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | SDI 2 | GROUND | OPEN | | 12 | SDI 1 | GROUND | OPEN | | 13 | Dual Baro Select | DUAL PORT | SINGLE PORT| | 14 | Analog Baro Select | ANALOG | DIGITAL | | 15 | Spare IDSC 1 | GROUND | OPEN | | 16 | Spare IDSC 2 | GROUND | OPEN | | 17 | Spare IDSC 3 | GROUND | OPEN | | 18 | Baro 3 Present | PRESENT | ABSENT | | 19 | Spare IDSC 4 | GROUND | OPEN | | 20 | CFDS Select | NOT ACTIVE| ACTIVE | | 21 | Spare | | | | 22 | BITE Memory Clear Enable | ENABLE | DISABLE | | 23 | BITE Write Inhibit | INHIBIT | ENABLE | | 24 | ADR Interface Test | TEST | NORMAL | | 25 | ADR Off Command | GROUND | OPEN | | 26 | Reserved | | | | 27 | ADR On/Off Status | OFF | ON | | 28 | Spare | | | | 29 | Spare | | | -------------------------------------------------------------------------Label 272 - Discrete Word 3

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------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | ------------------------------------------------------------------------| 11 | A/C ID Code 32/0 | GROUND | OPEN | | 12 | A/C ID Code 64/0 | GROUND | OPEN | |13 to 23| Spare | | | | 24 | A/C ID Code 1/0 | GROUND | OPEN | | 25 | A/C ID Code 2/0 | GROUND | OPEN | | 26 | A/C ID Code 4/0 | GROUND | OPEN | | 27 | A/C ID Code 8/0 | GROUND | OPEN | | 28 | A/C ID Code 16/0 | GROUND | OPEN | | 29 | A/C ID Parity | GROUND | OPEN | ------------------------------------------------------------------------Label 352 - Discrete Word 4 ------------------------------------------------------------------------| BIT N⁰ | FUNCTION | ------------------------------------------------------------------------| 11 | = 0 -| | 12 | = 1 | LSD = 6 | | 13 | = 1 | | | 14 | = 0 -| | 15 | = 0 -| | 16 | = 0 | MSD = 0 | | 17 | = 0 | | | 18 | = 0 -| |19 to 29| Spare | ------------------------------------------------------------------------Label 377 - Equipment Ident.

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- On the ground the output labels are in the following state: -------------------------------------------------------------------------| LABEL | PARAMETER DEFINITION | SSM | ON GND CRITERION | |------------------------------------------------------------------------| 203 | Altitude | NO | | | 204 | Baro Corr Alt 1 | NO | | | 220 | Baro Corr Alt 2 | NO | | | 251 | Baro Corr Alt 3 | NO | | | 205 | Mach | NCD | 0 Mach less than 0.1 | | 206 | Computed Airspeed | NCD | 0 kt CAS less than 30 kts | | 207 | Max Allowable Airspeed | NO | | | 210 | True Airspeed | NCD | 0 kt CAS less than 60 kts | | 211 | Total Air Temp | NO | | | 212 | Altitude Rate | NO | | | 213 | Static Air Temp | NO | | | 215 | Impact Pressure | NO | | | 221 | Indicated AOA | NCD | NOTE CAS less than 60 kts | | 230 | True Airspeed | NCD | 0 kt CAS less than 60 kts | | 231 | Total Air Temp | NO | | | 233 | Static Air Temp | NO | | | 234 | Baro Corr (hPa) 1 & 2 & 3| NO | | | 236 | Baro Corr (hPa) 2 | NO | | | 034 | Baro Corr (hPa) 3 | NO | | | 235 | Baro Corr (in.Hg) 1 | NO | | | 237 | Baro Corr (in.Hg) 2 | NO | | | 035 | Baro corr (in.Hg) 3 | NO | | | 240 | VMO/MMO status | NO | | | 241 | Corrected AOA | NCD | 0⁰ CAS less than 60 kts | | 242 | Total Pressure | NO | | | 176 | L. Static Pressure | NO | | | 177 | R. Static Pressure | NO | | | 245 | Uncrctd Avg Stat Pressure| NO | | | 246 | Corctd Avg Stat Pressure | NO | | | 270 | Discrete words | NO | | | 271 | Discrete words | NO | | | 272 | Discrete words | NO | | | 350 | Discrete words | NO | | | 351 | Discrete words | NO | | | 352 | Discrete words | NO | | | 377 | Discrete words | NO | | | 354 | LRU ID | N/A | N/A | | 356 | Fault Status | N/A | N/A | -------------------------------------------------------------------------Output Label Value on Ground

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- On the ground the output labels are in the following state:

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(b) Discrete form The ADR provides seven standard OPEN/GROUND output discretes. -------------------------------------------------------------------------| SIGNAL | PIN | OUTPUT | DEFINITION | |------------------------------|------------|-------------|--------------| | ADR OFF Light | TP- 4E | OPEN/GROUND | ON/OFF | | ADR FAULT | TP- 4D | OPEN/GROUND | NO/FAULT | | Low Speed Warning Discrete 1 | TP- 2F | OPEN/GROUND | SLOW/FAST | | Low Speed Warning Discrete 2 | TP- 2G | OPEN/GROUND | SLOW/FAST | | Low Speed Warning Discrete 3 | TP- 6F | OPEN/GROUND | SLOW/FAST | | Low Speed Warning Discrete 4 | TP-13H | OPEN/GROUND | FAST/SLOW | | AOA Special Test | TP-12G | OPEN/28VDC | NO/TEST | -------------------------------------------------------------------------ADR - Discrete Output Signals NOTE : The ADR OFF light, the low speed warning 4 and ADR FAULT ____ discretes are forced to the ground state when the watchdog timer (WDT) has timed out. 1 _

ADR OFF Light When the ADR is commanded OFF, it issues a ground state to the ADR OFF light discrete to enable the legend to come on.

2 _

ADR FAULT When an ADR FAULT is detected, the ADR issues a ground state to the ADR FAULT discrete to enable the legend to come on.

3 _

Low speed warning discretes 1, 2, 3, 4 The ADR provides four standard Open/Ground low speed warning output discretes. - Airspeed conditions Airspeed decreasing Discrete 1 = OPEN for Airspeed less than or equal to 100 knots Discrete 2 = OPEN for Airspeed less than or equal to 50 knots Discrete 3 = OPEN for Airspeed less than or equal to 155 knots Discrete 4 = GROUND for Airspeed less than or equal to 260 knots Airspeed increasing Discrete 1 = GROUND for Airspeed greater than 104 knots Discrete 2 = GROUND for Airspeed greater than 54 knots Discrete 3 = GROUND for Airspeed greater than 159 knots Discrete 4 = OPEN for Airspeed greater than 264 knots - Power off conditions

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Discrete 1 = Discrete 2 = Discrete 3 = Discrete 4 = - CAS detected Discrete 1 = Discrete 2 = Discrete 3 = Discrete 4 = 4 _

OPEN OPEN OPEN OPEN failure condition previous state previous state previous state OPEN

AOA special test The ADR provides an OPEN/GROUND output discrete to drive the AOA self-test. The AOA self-test is commanded via the CFDIU interface bus. When the AOA test is active, the AOA sensor is offset to +15 deg. (plus or minus 1 deg.). All AOA dependent parameters reflect this offset and their SSMs indicate Functional Test (FT). The RETURN command from the MCDU results in the discrete output set to OPEN. Ref. 34-18-00 for more details.

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3. ________________________________ Operation/Control and Indicating A. Control (1) ADIRS Control and Display Unit (CDU) (Ref. Fig. 010) The ADIRS CDU provides the control and warning of the three ADRs by means of three ADR illuminated pushbutton switches: - The pushbutton switch is used to disable the ADR output buses. It is a momentary action pushbutton switch. - When the ADR output buses are disabled, the ADR controls the activation of the ADR OFF legend by its output discrete: ADR OFF status. - When an ADR failure is detected, the ADR controls the activation of the ADR FAULT legend by its output discrete: ADR FAULT. - Each ADR is de-energized when the associated OFF/NAV/ATT selector switch is set to OFF. - When the associated OFF/NAV/ATT selector switch is set to NAV or ATT, each ADR is switched on independently of the previous selection on the ADR pushbutton switch. B. Indicating Altitude (ALT), Computed Airspeed (CAS), Mach number (M) and Vertical Speed (V/S) are computed by the ADIRU (ADR portion), processed by the associated DMC and displayed on the PFDs. True Airspeed (TAS) is supplied in the same way but is displayed on the NDs. In normal configuration, with the AIR DATA selector switch in NORM position, the ADR 1 displays information on CAPT PFD and ND. The ADR 2 displays information on F/O PFD and ND. Static Air Temperature (SAT) and Total Air Temperature (TAT) are also supplied in the same way but are permanently displayed on the lower part of the lower ECAM DU. These items of information are displayed by the ADR 2 when EIS 1 is installed, and by ADR 1 when the EIS 2 is installed. (1) PFD display For further details concerning speed, altitude or vertical speed scale, Ref. 31-64-00. (a) Computed Airspeed (CAS) (Ref. Fig. 011) The CAS indication is displayed in analog form by means of a white tape with graduations every 10 kts and digital values every 20 kts. This tape moves up and down so as to indicate the A/C actual speed value in front of a fixed yellow reference line.

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ADR Control on CDU Figure 010   EFF : 524-526, 528-599,  34-13-00 Page 39   Config-2 Feb 01/10  CES

 

Computed Airspeed and Mach Indication Display Figure 011   EFF : 524-526, 528-599,  34-13-00 Page 40   Config-2 Feb 01/10  CES

 

The displayed part of the scale represents an 84 kt range. The scale is graduated from 30 kts to 520 kts and the digital values from 40 to 520 kts (item A). In no case can the displayed CAS be lower than 30 kts. In case of computed airspeed failure, the speed scale goes out of view and is replaced by a red SPD flag (item B). (b) Mach number (M) When the Mach number is above 0.5, it is displayed just below the speed scale. In case of failure, a red MACH flag is presented. (c) Altitude (ALT) (Ref. Fig. 012) The baro altitude indication is provided by means of a tape which moves up and down behind a window within which the A/C actual altitude is displayed. The tape of the scale is graduated every 100 ft and digital values are displayed every 500 ft in hundreds. The A/C actual altitude is provided by a counter located at the middle of the scale in which the actual value is displayed in green digits. The hundreds of feet are written in a large size whereas the tens and units are displayed by a drum operating as a classical mechanical altimeter. Small white marks are positioned in front of each number on the tape (item A). If the altitude is negative, a NEG white indication is added at the left of the digital value. The digital value is limited to minus 1500 ft (item B). Different displays are presented depending on the baro setting reference (standard or baro corrected), Ref. 31-64-00. In case of baro altitude failure, the scale goes out of view and a red ALT flag flashes for a few seconds in the altitude window, then remains steady (item C). In case of discrepancy between the altitude given by the CAPT air data source and the altitude given by the F/O air data source, a CHECK ALT amber flag is presented on the right side of the altitude scale (item D). (d) Vertical Speed (V/S) (Ref. Fig. 013) The baro vertical speed is automatically displayed on the right side of the PFD when the inertial vertical speed is not available (item A). It is a degraded mode. The vertical speed scale consists of: - a trapezoidal grey background colored surface

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Altitude Indication Display Figure 012   EFF : 524-526, 528-599,  34-13-00 Page 42   Config-2 Feb 01/10  CES

 

Vertical Speed Indication Display Figure 013   EFF : 524-526, 528-599,  34-13-00 Page 43   Config-2 Feb 01/10  CES

 

- a fixed white scale with 500 ft/min spaced marks from -2000 ft/min to +2000 - ft/min a needle giving, in analog form, the actual vertical speed value - a number in a moving amber window. This window accompanies the needle (above the needle if V/S > 0, below if V/S < 0). The number gives the V/S value in hundreds of ft/min. Between -200 ft/min and +200 ft/min, both the window and the number disappear. - above +6000 ft/min (or below -6000 ft/min), the needle remains stopped where it is. When the vertical speed exceeds +6000 ft/min or -6000 ft/min, the digital indication and the analog needle change from green to amber. In addition, those indications change to amber in approach, in the following cases: - V/S less than -2000 ft/min below 2500 ft RA - V/S less than -1200 ft/min below 1000 ft RA. In case of a failure warning, the vertical speed scale is removed and replaced by a red V/S flag which flashes for a few seconds, then remains steady (item B). (2) ND display (Ref. Fig. 014) The true airspeed (TAS) is displayed on the ND in ROSE, ARC and PLAN mode (item A). The TAS information is displayed by a numerical indication of three digits preceded by TAS indication. This information is displayed in the left upper corner of the ND for a speed higher than 100 kts. Below this value the TAS indication remains visible but is followed by three dashes (item B). (3) Display on the lower ECAM DU (Ref. Fig. 015) The Static Air Temperature (SAT) and the Total Air Temperature (TAT) are permanently displayed on the lower part of the lower ECAM DU by a numerical indication of two digits preceded by the plus or minus sign (item A). This data is delivered by the ADR 2 when EIS 1 is installed, and by ADR 1 when EIS 2 is installed. In case of failure or when NCD information is received from the ADR 2, this data is replaced by crosses (item B).

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True Airspeed Indication Display Figure 014   EFF : 524-526, 528-599,  34-13-00 Page 45   Config-2 Feb 01/10  CES

 

TAT/SAT Indication Display Figure 015   EFF : 524-526, 528-599,  34-13-00 Page 46   Config-2 Feb 01/10  CES

 

(4) Reconfiguration display In case of loss of AIR DATA parameters on CAPT or F/O PFD and ND, the ADR 3 can be used as a back-up source by placing the AIR DATA selector switch in CAPT/3 position for EFIS 1 and in F/O/3 position for EFIS 2. In case of loss of TAT/SAT parameters on the lower ECAM DU, the ADR 3 can be used as a back- up source by placing the AIR DATA selector switch in F/O/3 position when EIS 1 is installed, and in CAPT/3 position when EIS 2 is installed. C. Warnings In addition to the AIR DATA flags displayed on the PFDs and NDs and on the CDU, warning messages are displayed on the lower part of the upper ECAM DU. Two kinds of warning messages can be displayed: - failure warning messages in case of loss of AIR DATA parameters - configuration warning messages in case of dangerous configuration of the aircraft. When the CLR key is pushed on the ECAM control panel, a STATUS page is displayed on the lower ECAM DU and indicates the STATUS and INOP SYS (systems). (1) Failure warning messages (Ref. Fig. 016, 017, 018) (a) NAV ADR 1(2)(3) FAULT NAV ADR 1(2) + 2(3) FAULT When these messages are displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the FAULT legend of the ADR pushbutton switch on the CDU comes on. (b) NAV ALTI DISCREPANCY (Ref. Fig. 019) This message is displayed when a difference higher than plus or minus 250 ft is detected by the external comparison inside the FWCs between the baro-corrected altitude (or plus or minus 500 ft for the standard altitude) provided by two ADRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK ALT message appears on the PFD.

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NAV ADR 1(2)(3) FAULT Message Figure 016   EFF : 524-526, 528-599,  34-13-00 Page 48   Config-2 Feb 01/10  CES

 

NAV ADR 1+3 (2+3) FAULT Message Figure 017   EFF : 524-526, 528-599,  34-13-00 Page 49   Config-2 Feb 01/10  CES

 

NAV ADR 1 + 2 FAULT Message Figure 018   EFF : 524-526, 528-599,  34-13-00 Page 50   Config-2 Feb 01/10  CES

 

NAV ALTI DISCREPANCY Message Figure 019   EFF : 524-526, 528-599,  34-13-00 Page 51   Config-2 Feb 01/10  CES

 

(c) NAV ALTI DISCREPANCY (Ref. Fig. 019) This message is displayed when a difference higher than plus or minus 250 ft is detected by the external comparison inside the FWCs between the baro-corrected altitude (or plus or minus 500 ft for the standard altitude) provided by two ADRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK ALT message appears on the PFD. (2) Configuration warning messages (Ref. Fig. 020, 021) (a) OVERSPEED VM0/MM0 OVERSPEED VFE/VLE When these messages are displayed: - the MASTER WARN lights on the glareshield flash - the Continuous Repetitive Chime (CRC) sounds. OVERSPEED VMO/MMO warning processed by the FWC is triggered when the CAS/Mach calculated by the ADR exceeds the VMO/MMO threshold by more than 4 kts/0.006 Mach. OVERSPEED VFE/VLE processed by the FWC is a function of Vc and depends on slat/flap position for the VFE and landing gear position for the VLE. For overspeed VLE, the warning is triggered at 284 knots. (b) Stall warning (Ref. Fig. 022) When this warning is activated: - the MASTER WARN lights on the glareshield flash - the cricket and the voice STALL sound. This warning is processed by the FWC and is a function of the angle of attack value and slat position following these conditions: - normal law: if the corrected angle of attack exceeds 23⁰ or if the corrected angle of attack exceeds 15⁰ and slat < 15⁰. - alternate law if the corrected angle of attack exceeds 13⁰ or if the corrected angle of attack exceeds 8⁰ and slat < 15⁰.

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OVERSPEED VMO/MMO Message Figure 020   EFF : 524-526, 528-599,  34-13-00 Page 53   Config-2 Feb 01/10  CES

 

OVERSPEED VFE/VLE Message Figure 021   EFF : 524-526, 528-599,  34-13-00 Page 54   Config-2 Feb 01/10  CES

 

Stall Warning Message Figure 022   EFF : 524-526, 528-599,  34-13-00 Page 55   Config-2 Feb 01/10  CES

 

AIR DATA - DESCRIPTION AND OPERATION ____________________________________ 1. _______ General The Air Data Reference (ADR) portion of the Air Data/Inertial Reference Unit (ADIRU) provides main data sources which are air data references for the aircraft avionics systems. The ADR receives and processes the outputs of the Air Data Modules (ADM) and other sensors (Ref. 34-11-00). It computes the aerodynamic parameters in the form of ARINC 429 low speed buses. For more details concerning the user systems, ref. 34-12-00. 2. __________________ System Description A. ADR Operation (1) General The ADR software performs five basic computational elements which are under the air data calculations as follows: - pressure altitude functions (ALT/ALT rate) - Mach calculation (M) - airspeed calculation (CAS/TAS) - temperature calculation (SAT/TAT) - output signal processing. Aircraft-dependent calculations are also included in the operational software: - static source error correction - angle of attack (AOA) - maximum operating speed (MMO/VMO). The system tests include continuous in-flight monitoring and manually-activated test modes. The in-flight monitoring includes test of: - input signal integrity - input interface integrity - memory integrity - computational integrity - output signal integrity. The continuous monitoring detects and annunciates faults in the ADR during normal operation. Faults are stored in BITE history in Non Volatile Memory (NVM) and sent to the Centralized Fault Display System (CFDS) via digital words.

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R R

**ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, (2) Inputs (a) Digital inputs 1 _

Air Data Modules (ADM) inputs The ADR receives three input buses from its corresponding ADM. These buses transmit the following input data words depending on the ADM installation: Label 242 : Total Pressure Label 176 : Left Static Pressure Label 177 : Right Static Pressure Label 245 : Averaged Static Pressure Each of these words is a 32-bit word with the following format: ---------------------------------------------------------| BIT POSITION | DATA | ---------------------------------------------------------| 1 - 8 | Label | | 9 - 10 | SDI | | 11 - 28 | Pressure Value | | 29 | Sign bit (0 = positive) | | 30 - 31 | Status matrix | | 32 | Parity bit | ---------------------------------------------------------ADM Input Label These data words are output on all eight Air Data output data buses and used for calculation of corrected pressure data.

2 _

Flight Control Unit (FCU) inputs The ADR receives one input bus from the FCU, for digital baro corrections. The FCU output bus sends: BCD label 234 Baro Correction 1(hPa) for CAPT side BCD label 236 Baro Correction 2(hPa) for F/O side. Each ADR receives the two FCU output bus according to the discrete selection as explained in Para. 2.A.(2)(c) (discrete inputs). Each of these words is a 32-bit BCD word with the following format:

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----------------------------------------------------------| BIT POSITION | DATA | ----------------------------------------------------------| 1 - 8 | Label | | 9 - 10 | SDI | | 11 - 28 | Value | | 29 | Sign bit | | 30 - 31 | Status matrix | | 32 | Parity | ----------------------------------------------------------FCU Input Label

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3 _

Centralized Fault Display Interface Unit (CFDIU) input For maintenance purposes, the ADR receives one input bus from the CFDIU. For more details, ref. 34-18-00.

4 _

Air Data Reference (ADR) input Each ADR receives two intercommunication buses from the other ADRs for cross channel comparison purpose.

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-523, (2) Inputs (a) Digital inputs 1 _

Air Data Modules (ADM) inputs The ADR receives three input bus from its corresponding ADM. These buses transmit the following input data words depending on the ADM installation: Label 242 : Total Pressure Label 176 : Left Static Pressure Label 177 : Right Static Pressure Label 245 : Averaged Static Pressure Each of these words is a 32-bit word with the following format:

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---------------------------------------------------------| BIT POSITION | DATA | ---------------------------------------------------------| 1 - 8 | Label | | 9 - 10 | SDI | | 11 - 28 | Pressure Value | | 29 | Sign bit (0 = positive) | | 30 - 31 | Status matrix | | 32 | Parity bit | ---------------------------------------------------------ADM Input Label These data words are output on all eight Air Data output data buses and used for calculation of corrected pressure data. 2 _

Flight Control Unit (FCU) inputs The ADR receives two input buses from the FCU; one for digital baro corrections and one for altimeter modes. The FCU output bus which corresponds to the CAPT side is only connected to ADIRU1 and ADIRU3, and it sends: * BCD label 234 Baro Correction 1(hPa) * Discrete label 272 Altimeter mode from Barometric Bus B, FCU EIS Disc 1. The FCU output bus which corresponds to the F/O side is only connected to ADIRU2, and it sends: * BCD label 236 Baro Correction 2(hPa) * Discrete label 272 Altimeter mode from Barometric Bus A, FCU EIS Disc 1. Each ADR receives the two FCU output bus according to the discrete selection as explained in Para. 2.A.(2)(c) (discrete inputs). Each of these words is a 32-bit BCD word with the following format: ----------------------------------------------------------| BIT POSITION | DATA | ----------------------------------------------------------| 1 - 8 | Label | | 9 - 10 | SDI | | 11 - 28 | Value | | 29 | Sign bit | | 30 - 31 | Status matrix | | 32 | Parity | ----------------------------------------------------------FCU Input Label

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The Altimeter mode is coded on the label 272 according to the following format: ----------------------------------------| Altimeter Mode | Label 272 Bits | | | 29 28 | |------------------|--------------------| | STD | 0 1 | | QNH | 1 0 | | QFE | 0 0 | | INVALID | 1 1 | -----------------------------------------

R R

3 _

Centralized Fault Display Interface Unit (CFDIU) input For maintenance purposes, the ADR receives one input bus from the CFDIU. For more details, ref. 34-18-00.

4 _

Air Data Reference (ADR) input Each ADR receives two intercommunication buses from the other ADRs for cross channel comparison purpose.

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (b) Analog inputs 1 _

Total Air Temperature (TAT) input The ADR measures the resistance of the sensing element of the TAT sensor (Ref. 34-11-00). The ADR subtracts a fixed value (1.04 ohm) from the measured input resistance to compensate for aircraft wiring resistance.

2 _

Angle of Attack (AOA) inputs (Ref. Fig. 001) The ADR receives two resolver inputs for angle of attack computation. The following requirements apply to the analog resolver inputs: - load: 15 kilohms minimum - reference: 26V, 400 Hz (same as AOA) - transformer ratio: 0.415 nominal plus or minus 10 % - phase shift: 8.8 to 30 deg. leading - source impedance: Zro = A + jB A less than 315, B less than 725 Zso = C + jD C less than 150, D less than 165 - voltage range: 23 to 31.7 VRMS

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AOA/ADR Wiring Figure 001   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 6 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

- peak factor: 1.31 to 1.51 - electrical range input: plus or minus 60 deg. 3 _

Analog baro correction inputs The ADR receives three resolver inputs for analog baro correction (from the altimeter for example). These inputs are not used.

(c) Discrete inputs For pin assignment, Ref. 34-12-00. The ADR is provided with the following input discretes: ---------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT DEFINITION | ---------------------------------------------------------------| ADR ARINC Filter Select | Open/GND | Type A/Type B | | CFDS Message Select | Open/GND | Active/Not Active | | SDI LSB (Middle Insert) | Open/GND | 0/1 | | SDI MSB (Middle Insert) | Open/GND | 0/1 | | Pitot Probe Ht Disc | Open/GND | No Fault/Fault | | Right Static Ht Disc | Open/GND | No Fault/Fault | | Left Static Ht Disc | Open/GND | No Fault/Fault | | TAT Ht Disc | Open/GND | Off/On | | AOA 1 Ht Disc | Open/GND | No Fault/Fault | | AOA Average/Unique | Open/GND | Average/Unique | | VMO/MMO Disc 1 | Open/GND | No/Yes | | VMO/MMO Disc 2 | Open/GND | No/Yes | | VMO/MMO Disc 3 | Open/GND | No/Yes | | VMO/MMO Disc 4 | Open/GND | No/Yes | | SSEC Alternate Disc A | Open/GND | No/Yes | | SSEC Alternate Disc B | Open/GND | N0/Yes | | AOA Alternate Disc 1A | Open/GND | Off/On | | AOA Alternate Disc 1B | Open/GND | Off/On | | AOA Alternate Disc 2A | Open/GND | Off/On | | AOA Alternate Disc 2B | Open/GND | Off/On | | Baro Port A | Open/GND | Port B/Port A | | Zero MACH SSEC | Open/GND | Use SSEC/Ignore SSEC | | Zero AOA SSEC | Open/GND | Use SSEC/Ignore SSEC | | AIR FRM ID Code 1/0 |Open/A.I.Com | No/Yes | | AIR FRM ID Code 2/0 |Open/A.I.Com | No/Yes | | AIR FRM ID Code 4/0 |Open/A.I.Com | No/Yes | | AIR FRM ID Code 8/0 |Open/A.I.Com | No/Yes | | AIR FRM ID Code 16/0 |Open/A.I.Com | No/Yes | | AIR FRM ID Code Parity |Open/A.I.Com | No/Yes | | ADR Remote Test | Open/GND | No Test/Test | | ADR OFF DISCR Input | Open/GND | Released/Pressed | | Dual Baro | Open/GND | Sgl Port/Dual Port |

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---------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT DEFINITION | ---------------------------------------------------------------| Baro Analog/Digital Sel.| Open/GND | Digital/Analog | | Baro Corr. 3 Active | Open/GND | Not Active/Active | ---------------------------------------------------------------Discrete Input Signal NOTE : Open means either a high logic voltage level or the ____ binary zero state. GND means either a low logic voltage level or the binary one state. A.I. Com means grounded to the Aircraft Ident Common pin through a resistance of 10 ohms or less. For program pin inputs other than Aircraft I.D., GND means grounded to the Program Pin Common pin through a resistance of 10 ohms or less. 1 _

ADR ARINC Filter Select discrete This discrete is used to select the characteristics of the ADR output filter. Two sets of characteristics are available: Open/Ground = Type A/Type B The A/C is defined with the ADR ARINC filter select discrete open. -------------------------------------------------------------| | | TYPE A | TYPE B | | OCTAL | | MAXIMUM | MAXIMUM | | LABEL | SIGNAL | 3db FILTER | 3db FILTER | | | | BANDWIDTH | BANDWIDTH | | | | (HZ)(1) | (HZ) | -------------------------------------------------------------| 203 |Altitude | 8 | 3 | | 204 |Baro Cor. Alt. 1 | 8 | 3 | | 205 |Mach | 8 | 3 | | 206 |Computed Airspeed | 8 | 3 | | 207 |Max Allow. Airspeed | 8 | 8 | | 210 |True Airspeed | 8 | 3 | | 211 |Total Air Temp | 4 | 3 | | 212 |Altitude Rate | 1.8 | 1.8 | | 213 |Static Air Temp | 4 | 3 | | 215 |Impact Pressure | 8 | 3 | | 220 |Baro Cor. Alt. 2 | 8 | 3 | | 221 |Ind. Angle of Attack | 8 | 3 | | 241 |Cor. Angle of Attack | 8 | 3 | | 242 |Total Pressure | N/A (2) | N/A (2) |

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-------------------------------------------------------------| | | TYPE A | TYPE B | | OCTAL | | MAXIMUM | MAXIMUM | | LABEL | SIGNAL | 3db FILTER | 3db FILTER | | | | BANDWIDTH | BANDWIDTH | | | | (HZ)(1) | (HZ) | -------------------------------------------------------------| 176 |Left Static Pressure | N/A (2) | N/A (2) | | 177 |Right Static Pressure | N/A (2) | N/A (2) | | 245 |Uncorr Avg Static Pressure| N/A (2) | N/A (2) | | 246 |Corr Avg Static Pressure | N/A (2) | N/A (2) | | 251 |Baro Cor. Alt. 3 | 8 | 3 | -------------------------------------------------------------ADR Output Filter Characteristics NOTE : (1) Filters present only as provisions, except for ____ Altitude Rate. (2) Filtering of pressure data is performed by the ADM. 2 _

CFDS Message Select discrete When open, this discrete is used to select and display fault messages.

3 _

Source Data Identifier (SDI) program pins These discretes code the installation side of the ADIRU. This item of information is used to choose the appropriate correction laws (for Static Source Error Correction (SSEC) and corrected angle of attack). The following table gives the ADR side according to the SDI: -------------------------------------------------------| DEBOUNCED STATUS | | | |-----------------------------| SDI | ADIRU | | SDI-MSB | SDI-LSB | CODE | NUMBER | |------------------------------------------------------| | OPEN | GND | 01 | 1 | | GND | OPEN | 10 | 2 | | GND | GND | 11 | 3 | -------------------------------------------------------ADR SDI Code

4 _

sensor heat status discretes These discrete inputs are used to provide the sensors heat status to the ADR. These discretes are of the open/ground type. When the TAT HEAT DISC is grounded, the TAT sensor is heated.

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When one of the STATIC, PITOT or AOA HEAT discretes is grounded, it means that the output of the Probe Heat Computer (PHC) heating power supply is faulty and that the concerned probe is no longer heated. In this case the ADR operates as a relay which sends these information signals to the FWC for warning purposes. 5 _

AOA Average/Unique program pin The ADR uses the AOA Average/Unique program pin to determine whether one or two angle of attack resolver inputs are used for angle of attack computations. When this program pin indicates Unique, the ADR uses only a single angle of attack input. If this first AOA input fails, the ADR uses the opposite AOA input, as shown in table below. When this program pin indicates Average, the ADR calculates angle of attack based on the average of the angle of attack inputs 1 and 2. ------------------------------------------------------| SYSTEM | INITIAL NON-FAULT | INPUT TO ADR | | NUMBER | INPUT TO ADR | AFTER FAULT | ------------------------------------------------------| 1 | input number 1 | input number 2 | | 2 | input number 2 | input number 1 | | 3 | input number 1 | input number 2 | ------------------------------------------------------AOA Resolver Input The characteristics of these discretes are OPEN/GROUND = AVERAGE/UNIQUE. The A/C is defined with the AOA average/unique discrete grounded.

6 _

VMO/MMO Program Discretes 1 through 4 These discretes are used to select alternate VMO/MMO levels. There are four alternates and a basic VMO/MMO for each aircraft type. Table below defines VMO/MMO versus state of the VMO/MMO program discretes. With no VMO/MMO discretes in the ground state (yes) the ADR defaults to the BASIC LAW values for VMO/MMO. Only one of the four VMO/MMO program discretes can be in the ground state at any one time. If more than one VMO/MMO program discrete is in the ground state at any one time, the ADR defaults to the lowest available alternate condition.

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7 _

on the A/C only the VMO/MMO DISC 2 is available and is provided by the L/G DOWN VMO/MMO SELECTION switch (22FP). The normal position of this switch is open and it is grounded after crew action for particular flights (ferry flight for example). Table below defines VMO/MMO state according to the switch (22FP) position. ---------------------------------------------------------| | VMO | MMO | SWITCH | | LAW | (kts) | (Mach) | 22FP | ---------------------------------------------------------| BASIC | 350 | 0.82 | OPEN | | ALT 1 | | | | | ALT 2 | 235 | 0.60 | GROUND | | ALT 3 | | | | | ALT 4 | | | | ---------------------------------------------------------VMO/MMO Selection

8 _

SSEC Alternate discrete The ADR is provided with two Static Source Error Correction (SSEC) data sets stored in the computer for each SDI and for each of sixteen aircraft types, one for use in normal conditions and the other for use in alternate conditions. With the two SSEC selection discretes open (no), the ADR employs the normal SSEC curve for the aircraft type in which it is installed. With the two SSEC selection discretes grounded (yes), the ADR employs the alternate condition curve.

9 _

AOA Alternate discrete The ADR uses the alternate discrete inputs from the two redundant SFCCs to select the angle of attack correction which is appropriate for the current slat and flap settings. Three laws are available for each aircraft type and SDI: - the normal law is activated when all the discretes are open - the alternate 1 law is activated when discretes 1A and 2A are grounded - the alternate 2 law is activated when discretes 1A, 2A, 1B and 2B are grounded.

10 __

Baro Port A discrete The ADR uses this discrete to select which ARINC 429 port is used as a source for all baro-correction input data. If this discrete is grounded, the baro port A is selected.

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If this discrete is open, the baro port B is selected. The A/C is wired with this discrete grounded (Ref. Dual Baro discrete). 11 __

Dual Baro discrete The ADR uses this discrete to select which ARINC 429 port is used as a source for all baro-correction input data. If this discrete is grounded, the baro port A and the baro port B are selected and the baro port A discrete selection is overriden. If this discrete is open, the baro port A or the baro port B is selected depending on the baro port A discrete selection. The A/C is wired with this discrete open.

12 __

Zero MACH SSEC discrete The ADR uses this discrete to select the SSEC as a function of Mach. When this program pin indicates Use SSEC (open), the SSEC as a function of Mach is computed. When this program pin indicates Ignore SSEC (ground), the ADR uses zero correction. The A/C is wired with this discrete open.

13 __

Zero AOA SSEC discrete The ADR uses this discrete to select the SSEC as a function of angle of attack. When this program pin indicates Use SSEC (open), the SSEC as a function of AOA is computed. When this program pin indicates Ignore SSEC (ground), the ADR uses zero correction. The A/C is wired with this discrete open.

14 __

AIR FRM ID Code discrete The ADR uses input discretes to identify the aircraft (type, engine model) on which the ADIRU is fitted, and to select the appropriate set of correction laws for Static Source Error Correction (SSEC) and AOA corrections. The ADIRU memory has the capacity to store 128 different sets of laws. To perform this coding, the ADR wires seven input discretes and one discrete for parity to a common.

15 __

ADR Remote Test discrete The ADR uses one discrete to select the remote test by external control. When this discrete is open, the test is not activated. When this discrete is grounded, the test is activated. The A/C is wired with this discrete open (unused). The test is activated via the CFDS (Ref. 34-18-00).

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16 __

ADR OFF DISCR input discrete The ADR uses this discrete input to toggle its state between ON and OFF. When the ADR is OFF, the output buses are disabled and the ADR FAULT legend is inhibited whenever the momentary action ADR pusbutton switch is pushed. When the ADR is ON, the output buses output data and the ADR FAULT legend operates normally. The ADR OFF DISCR input does not modify Air Data computation.

17 __

Baro Analog/Digital Sel discrete The ADR uses this discrete to select either the analog or digital baro correction. When this discrete is grounded, the analog baro correction is selected. When this discrete is open, the digital baro correction is selected. The A/C is wired with this discrete open.

18 __

Baro Corr 3 Active discrete The ADR uses this discrete to determine for BITE purposes whether the baro correction 3 is connected or not. When the discrete is grounded, the baro correction 3 is connected. When the discrete is open, the baro correction 3 is not connected. The A/C is wired with this discrete open.

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(3) Acquisition and processing of the sensor inputs (a) Pressure computation (Ref. Fig. 002) Based on pressure raw data received from the ADM (Ref. para. 2.A.(2)(a)1), the software converts the asynchronous pressure inputs into regularly-scheduled pressure data. During correction of static pressure, the software calculates the limited left, right and average static pressure in a range of 100 to 1100 hPa from the ADM inputs. From the average static pressure (Psm), the software calculates the corrected static pressure based on the SSEC factor: ( G1 G2 ) Psc = Psm (1 + ---- + ----) ( 1000 1000) - G1 depends on flaps and Mach is interpolated in a table (2 flaps position and 19 Mach values are considered) - G2 depends on Mach and AOA corrected and is interpolated in a table (6 AOA values and 18 Mach values are considered). The correct SSEC factor depends on the sensor location and on the aircraft configuration. The ADR memory contains several tables and the appropriate one is selected according to the following input discretes: . SDI . aircraft Ident . SSEC Alternate. Two input discretes can be used to force the SSEC factor to be independent from AOA or Mach: . zero MACH SSEC . zero AOA SSEC. Ref. Para. 2.A.(2)(c) for more details. No correction is needed for the total pressure received from the ADM. The results of the above computation is available on these output labels: . label 176 Left Static Pressure . label 177 Right Static Pressure . label 242 Total Pressure . label 245 Averaged Static Pressure . label 246 Corrected Static Pressure

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Pressure Computation - Block Diagram Figure 002   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 15 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

(b) Temperature computation (Ref. Fig. 003) The resistance measured by the ADR and compensated for aircraft wiring is then converted into a temperature value (TAT) according to the Callender-Van Dusen equation given for a 500 ohm platinum sensing element: | 3| Rt | (TAT ) (TAT ) (TAT ) (TAT) | -- = 1 + a | TAT - d (--- -1) (--- ) - b (--- -1) (---) | Ro | (100 ) (100 ) (100 ) (100) | TAT = temperature in deg.C (TAT) Rt = Resistance at temperature TAT Ro = Resistance at 0 deg.C = 500 ohm a = 0.003832 d = 1.81 b = 0.1 for temperature below 0 deg.C b = 0 for temperature above 0 deg.C The computation also compensates the TAT value for heating effect. The ADR knows when the sensor is heated by the state of the TAT Heat input discrete from the PHC. The heating compensation law is provided by the TAT sensor supplier and is function of Mach and air density. The PHC 1 controls the heating of the TAT sensor 1 and the PHC 2 controls the heating of the TAT sensor 2. On the ground, the sensors are not heated (Ref. 30-31-00 for more details). The result of the above computation is available on the following output labels: - label 211 Total Air Temperature (BNR) - label 231 Total Air Temperature (BCD).

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Temperature (TAT) Computation - Block Diagram Figure 003   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 17 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

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**ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, (c) AOA computation (Ref. Fig. 004) The A/C is wired in the AOA unique selection, so the ADR computes the AOA with the reading of one resolver. The second resolver is used as a back-up. The monitoring function is described in 34.18 The ADR determines the corrected angle of attack value which depends on the system number and the slat/flap position. For a CAS less than 60 kts: AOAc = 0 and status matrix is coded NCD. For a CAS more than or equal to 60 kts, the corrected angle of attack is calculated as follows: AOA ind AOAc = ------- + I K where: AOA ind = Indicated Angle of Attack (Ref. 34-11-00 for the relation between resolver and AOA indication) K, I = Correction coefficients which depend on system number, slat and flap configuration and magnitude AOA indication. The configuration is defined by the status of four input discretes (Ref. 2.A.(2)(c)). The results of the above computation is available on the labels: - label 221 = Indicated Angle of Attack - label 241 = Corrected Angle of Attack

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SFCC/AOA Alternate Discrete Signals Figure 004   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 19 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-523, (c) AOA computation (Ref. Fig. 004) The A/C is wired in the AOA unique selection, so the ADR computes the AOA with the reading of one resolver. The second resolver is used as a back-up. The monitoring function is described in 34.18 The ADR determines the corrected angle of attack value which depends on the system number and the slat/flap position. For a CAS less than 60 kts: AOAc is still computed , and status matrix is coded NCD. The corrected angle of attack is calculated as follows: AOA ind AOAc = ------- + I K where: AOA ind = Indicated Angle of Attack (Ref. 34-11-00 for the relation between resolver and AOA indication) K, I = Correction coefficients which depend on system number, slat and flap configuration and magnitude AOA indication. The configuration is defined by the status of four input discretes (Ref. 2.A.(2)(c)). The results of the above computation is available on the labels: - label 221 = Indicated Angle of Attack - label 241 = Corrected Angle of Attack

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**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (4) Parameter computation (a) General The operational software of the ADR performs the following computations: - pressure altitude and pressure altitude rate function (ALT) - Mach function (M) - airspeed function (CAS/TAS) - temperature function (SAT/TAT) - maximum operating speed function (VMO/MMO). (b) Altitude computation The ADR software computes these different parameters: label 203 Pressure Altitude label 212 Altitude Rate label 204 Baro Corrected Altitude 1 (CAPT) label 220 Baro Corrected Altitude 2 (F/O) label 235 Baro Correction In Hg 1 (CAPT) label 237 Baro Correction In Hg 2 (F/O) 1 _

Altitude pressure and altitude rate computation (Ref. Fig. 005) The altitude is derived from the corrected static pressure. The conversion from pressure to altitude is based on the geopotential altitude tables of the US Standard Atmosphere, 1962. The accepted range is (-2000 ft, +50,000 ft). The altitude rate is calculated by multiplying the rate of change of the corrected static pressure by the derivative of altitude with respect to corrected static pressure: dH d Ps dH -- = ---- x ---dt dt d Ps

2 _

Corrected altitude computation (Ref. Fig. 006) The ADR receives the baro correction introduced on the FCU by each crew member. The ADR uses the values in hPa (labels 234 and 236 from the FCU). The ADR also converts these values into inches of mercury (in. Hg) and the result is sent on the output labels 235, 237.

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Altitude and Altitude Rate Computation - Block Diagram Figure 005   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 22 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

Corrected Altitude Computation - Block Diagram Figure 006   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 23 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

The corrected altitude pressure altitude to a correction. The result corrected altitude and altitude.

is calculated by a shift of the value corresponding to the entered baro is sent on label 204 for CAPT baro label 220 for F/O baro corrected

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(c) CAS/Mach computation (Ref. Fig. 007) The ADR software computes these different parameters: label 206 Computed Airspeed label 205 Mach label 207 Maximum Allowable Airspeed. The CAS and Mach computation is based on the conversion of the impact pressure: impact pressure = Pt - Ps. - the CAS computation converts input of impact pressure to output corresponding to computed airspeed with: ______________________ / Qc 2/7 CAS = Cso X V 5 X ((-- + 1) - 1) Po CAS = Computed Airspeed in knots Cso = Speed of sound under standard day sea level conditions = 661.4746 kts Qc = Impact pressure in hPa Po = Standard day sea level pressure = 1013.25 hPa For accuracy reason, the CAS is output with a valid (NO) SSM only after 30 kts. If the CAS is below 30 kts, the label 206 indicates 0 kt with SSM = NCD. - the Mach computation converts Qc/Ps to Mach, with: _______________________ / Qc 2/7 MACH = V 5 ((-- + 1) - 1) Ps MACH = Mach number Qc/Ps = Ratio of impact pressure to static pressure If Mach is below 0.1, the label 205 indicates 0 with SSM = NCD.

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CAS/Mach Computation - Block Diagram Figure 007   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 26 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

(d) SAT/TAS computation (Ref. Fig. 008) The ADR software calculates these different parameters: label 213 BNR Static Air Temperature (SAT) label 233 BCD Static Air Temperature (SAT) label 210 BNR True Airspeed (TAS) label 230 BCD True Airspeed (TAS). - the calculation of the BNR SAT converts TAT to SAT with: TAT SAT = --------- 273.15 2 1 + 0.2M SAT = Static Air Temperature (in deg. C) TAT = Total Air Temperature (in deg. Kelvin) M = Mach number (corrected for static source error) - the calculation converts Static Air Temperature from BNR to BCD format. - the calculation of the BNR TAS converts Mach and SAT to TAS with: ___ / TAS = 38.96695 x M x V SAT TAS = True Airspeed (in knots) M = Mach Number (corrected for Static Source Error) SAT = Static Air Temperature (in deg. Kelvin) - the calculation converts True Airspeed from BNR to BCD format. For accuracy reason, the TAS is output with a valid (NO) SSM only after 60 kts. If TAS is below 60 kts, the label 210 indicates 0 kt with SSM = NCD. (e) VMO/MM0 computation (Ref. Fig. 009) The software determines the normal or alternate VMO/MMO law selected by the VM0/MM0 input 2 discrete state; then it computes the label 207 Maximum Allowable Airspeed. This airspeed is based on the Maximum Allowable Airspeed under a certain altitude and on the Maximum Allowable Mach above this altitude. It is always indicated in knots and decreases when the altitude increases. NOTE : At a constant Mach, the Vc value decreases when the ____ altitude increases.

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SAT/TAS Computation - Block Diagram Figure 008   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 28 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

VMO/MMO Computation - Block Diagram Figure 009   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 29 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

(5) ADR data outputs The ADR data outputs are transmitted in two forms: digital and discrete. (a) Digital form The table below contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds. - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code. - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system.

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**ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 176 |L STATIC |W2048 |hPa | | 16 |125 |BNR | | | | |PRESSURE |100 to 1100 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 177 |R STATIC |W2048 |hPa | | 16 |125 |BNR | | | | |PRESSURE |100 to 1100 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 203 |ALTITUDE |W+/- 131072 | ft | 29 | 17 | 62 |BNR | ALT | | | |1013.25mb |-2000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 +/-30 | | | | | | | | | | |(30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 204 |BARO CORR |W+/- 131072 | ft | 29 | 17 | 62 |BNR | | | | |ALT 1 |-1000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 +/-30 | | | | | | | | | | |(30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 205 |MACH |W4096 |Mach| | 16 |125 |BNR | MN | | | | |0.1 to 1.00 | | | | | | | | | | |R 6.25 E-5 | | | | | | | | | | |+/-0.010 | | | | | | | | | | |(0.1) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 206 |COMPUTED |W1024 |Kts | | 14 |125 |BNR | CAS | | | |AIRSPEED |30 to 450 | | | | | | | | | | |R 0.0625 | | | | | | | | | | |+1.5 (100) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 207 |MAXIMUM |W1024 |Kts | | 12 |125 |BNR | | | | |ALLOWABLE |150 to 450 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |AIRSPEED |R 0.25 +/- 1| | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 210 |TRUE |W2048 |Kts | | 15 |125 |BNR | | | | |AIRSPEED |60 to 599 | | | | | | | | | | |R 0.0625 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 211 |TOTAL AIR |W +/- 512 |Deg.| 29 | 11 |500 |BNR | TAT | | | |TEMP |-60 to 99 |C | | | | | | | | | |R 0.25 | | | | | | | | | | |+/- 0.5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 212 |ALTITUDE |W+/- 32768 |ft/ | 29 | 11 | 62 |BNR | | | | |RATE |-20,000 to |mn | | | | | | | | | | 20,000 | | | | | | | | | | |R 16.0 | | | | | | | | | | |+/-30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 213 |STATIC AIR|W+/- 512 |Deg.| 29 | 11 |500 |BNR | SAT | | | |TEMP |-99 to +80 |C | | | | | | | | | |R 0.25 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 215 |IMPACT |W512 |hPa | | 14 |125 |BNR | | | | |PRESSURE |0 to 372.5 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 220 |BARO CORR |W +/- 131072| ft | 29 | 17 | 62 |BNR | | | | |ALT 2 |-1000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 +/- 30 | | | | | | | | | | | (30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 221 |IND ANGLE |W +/- 180 |Deg.| 29 | 12 | 62 |BNR | | | | |OF ATTACK |-35 to +85 | | | | | | | | | | |R 0.0439 | | | | | | | | | | |+/- 0.25 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 230 |TRUE |W +/- 799 |Kts | | 3 |500 |BCD | | | | |AIRSPEED |60 to 599 | | | | | | | | | | |R 1 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 231 |TOTAL AIR |W +/- 799 |Deg.| | 2 |500 |BCD | | | | |TEMP |-60 to 99 |C | | | | | | | | | |R 1 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 233 |STATIC AIR|W +/- 799 |Deg.| | 2 |500 |BCD | | | | |TEMP |-99 to +80 |C | | | | | | | | | |R 1 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 234 |BARO |W +/- 7999.9|hPa | | 5 |500 |BCD | | | | |CORRECT 1 |745 to 1100 | | | | | | | | | |mb |R 0.1 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 235 |BARO |W +/- 79.999|inHg| | 5 |500 |BCD | | | | |CORRECT 1 |22.0 to 32.5| | | | | | | | | |in.Hg |R 0.001 | | | | | | | | | | |+/- 0.0074 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 236 |BARO |W +/- 7999.9|hPa | | 5 |500 |BCD | | | | |CORRECT 2 |745 to 1100 | | | | | | | | | |mb |R 0.1 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 237 |BARO |W +/- 79.999|inHg| | 5 |500 |BCD | | | | |CORRECT 2 |22.0 to 32.5| | | | | | | | | |in.Hg |R 0.001 | | | | | | | | | | |+/- 0.0074 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 240 |VMO/MMO |W 399/0.99 |Kts/| |3/2 |1000|BCD | | | | |STATUS |0 to 399 / |Mach| | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |0 to 0.99 | | | | | | | | | | |R 1 /0.01 | | | | | | | | | | |1 / 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 241 |CORRECTED |W +/- 180 |Deg.| 29 | 12 | 62 |BNR | AOA | | | |ANGLE OF |-35 to +85 | | | | | | | | | |ATTACK |R 0.0439 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 242 |TOTAL |W2048 |hPa | | 16 |125 |BNR | | | | |PRESSURE |100 to 1400 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 245 |UNCRCTD |W2048 |hPa | | 16 |125 |BNR | | | | |AVG STAT |100 to 1100 | | | | | | | | | |PRESSURE |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 246 |CORCTD |W2048 |hPa | | 16 |125 |BNR | | | | |AVG STAT |100 to 1100 | | | | | | | | | |PRESSURE |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DSCT WORD | | | | |500 |DIS | | | | | 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 271 |DSCT WORD | | | | |500 |DIS | | | | | 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 272 |DSCT WORD | | | | |500 |DIS | | | | | 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 350 |MAINT WORD| | | | |500 |DIS | | | | | 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 351 |MAINT WORD| | | | |500 |DIS | | | | | 2 | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 352 |MAINT WORD| | | | |500 |DIS | | | | | 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 155 |MAINT WORD| | | | |500 |DIS | | | | | 4 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 354 |LRU ID | | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 356 |FAULT STAT| | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQPT IDENT| | | | |500 |HEX | | | ------------------------------------------------------------------------------Output Label -------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | Icing Detector Heat | NO FAULT | FAULT | | 12 | Pitot Probe Heat | NO FAULT | FAULT | | 13 | ADR FAULT | FAULT | NO FAULT | | 14 | Right Static Heat | NO FAULT | FAULT | | 15 | Left Static Heat | NO FAULT | FAULT | | 16 | TAT Heat | HEAT | NO HEAT | | 17 | AOA 1 Heat | NO FAULT | FAULT | | 18 | AOA 2 Heat | NO FAULT | FAULT | | 19 | Overspeed Warning | WARN | NO WARN | | 20 | Spare (Primary AOA Fault) | | | | 21 | AOA Average/Unique | UNIQUE | AVERAGE | | 22 | VMO/MMO 1 | YES | NO | | 23 | VMO/MMO 2 | YES | NO | | 24 | VMO/MMO 3 | YES | NO | | 25 | VMO/MMO 4 | YES | NO | | 26 | SSEC Alternate Select 1 | YES | NO | | 27 | SSEC Alternate Select 2 | YES | NO | | 28 | Baro Port A Select | Port A | Port B | | 29 | Zero Mach SSEC Select | YES | NO | --------------------------------------------------------------------------

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-------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------Label 270 - Discrete Word 1

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-------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | Zero AOA SSEC Select | YES | NO | | 12 | AOA Test Active | ACTIVE | NOT ACTIVE | | 13 | Low Speed Warning 1 | FAST | SLOW | | 14 | Low Speed Warning 2 | FAST | SLOW | | 15 | Low Speed Warning 3 | FAST | SLOW | | 16 | Low Speed Warning 4 | SLOW | FAST | | 17 | Spare | | | | 18 | Spare | | | | 19 | Spare | | | | 20 | AOA Correction 1A | YES | NO | | 21 | AOA Correction 1B | YES | NO | | 22 | AOA Correction 2A | YES | NO | | 23 | AOA Correction 2B | YES | NO | |24 to 29| Spare | | | -------------------------------------------------------------------------Label 271 - Discrete Word 2 -------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | SDI 2 | GROUND | OPEN | | 12 | SDI 1 | GROUND | OPEN | | 13 | Dual Baro Select | DUAL PORT | SINGLE PORT| | 14 | Analog Baro Select | ANALOG | DIGITAL | | 15 | Spare IDSC 1 | GROUND | OPEN | | 16 | Spare IDSC 2 | GROUND | OPEN | | 17 | Spare IDSC 3 | GROUND | OPEN | | 18 | Baro 3 Present | PRESENT | ABSENT | | 19 | Spare IDSC 4 | GROUND | OPEN | | 20 | CFDS Select | NOT ACTIVE| ACTIVE | | 21 | Spare | | | | 22 | BITE Memory Clear Enable | ENABLE | DISABLE | | 23 | BITE Write Inhibit | INHIBIT | ENABLE | | 24 | ADR Interface Test | TEST | NORMAL | | 25 | ADR Off Command | GROUND | OPEN | | 26 | Reserved | | | | 27 | ADR On/Off Status | OFF | ON | | 28 | Spare | | | | 29 | Spare | | | -------------------------------------------------------------------------Label 272 - Discrete Word 3

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R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-523, ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 176 |L STATIC |W2048 |hPa | | 16 |125 |BNR | | | | |PRESSURE |100 to 1100 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 177 |R STATIC |W2048 |hPa | | 16 |125 |BNR | | | | |PRESSURE |100 to 1100 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 203 |ALTITUDE |W+/- 131072 | ft | 29 | 17 | 62 |BNR | ALT | | | |1013.25mb |-2000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 +/-30 | | | | | | | | | | |(30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 204 |BARO CORR |W+/- 131072 | ft | 29 | 17 | 62 |BNR | | | | |ALT 1 |-1000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 +/-30 | | | | | | | | | | |(30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 205 |MACH |W4096 |Mach| | 16 |125 |BNR | MN | | | | |0.1 to 1.00 | | | | | | | | | | |R 6.25 E-5 | | | | | | | | | | |+/-0.010 | | | | | | | | | | |(0.1) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 206 |COMPUTED |W1024 |Kts | | 14 |125 |BNR | CAS | | | |AIRSPEED |30 to 450 | | | | | | | | | | |R 0.0625 | | | | | | | | | | |+1.5 (100) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 207 |MAXIMUM |W1024 |Kts | | 12 |125 |BNR | | | | |ALLOWABLE |150 to 450 | | | | | | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 38 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |AIRSPEED |R 0.25 +/- 1| | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 210 |TRUE |W2048 |Kts | | 15 |125 |BNR | | | | |AIRSPEED |60 to 599 | | | | | | | | | | |R 0.0625 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 211 |TOTAL AIR |W +/- 512 |Deg.| 29 | 11 |500 |BNR | TAT | | | |TEMP |-60 to 99 |C | | | | | | | | | |R 0.25 | | | | | | | | | | |+/- 0.5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 212 |ALTITUDE |W+/- 32768 |ft/ | 29 | 11 | 62 |BNR | | | | |RATE |-20,000 to |mn | | | | | | | | | | 20,000 | | | | | | | | | | |R 16.0 | | | | | | | | | | |+/-30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 213 |STATIC AIR|W+/- 512 |Deg.| 29 | 11 |500 |BNR | SAT | | | |TEMP |-99 to +80 |C | | | | | | | | | |R 0.25 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 215 |IMPACT |W512 |hPa | | 14 |125 |BNR | | | | |PRESSURE |0 to 372.5 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 220 |BARO CORR |W +/- 131072| ft | 29 | 17 | 62 |BNR | | | | |ALT 2 |-1000 to | | | | | | | | | | | 50000 | | | | | | | | | | |R 1 +/- 30 | | | | | | | | | | | (30,000) | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 221 |IND ANGLE |W +/- 180 |Deg.| 29 | 12 | 62 |BNR | | | | |OF ATTACK |-35 to +85 | | | | | | | | | | |R 0.0439 | | | | | | | | | | |+/- 0.25 | | | | | | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 39 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 230 |TRUE |W +/- 799 |Kts | | 3 |500 |BCD | | | | |AIRSPEED |60 to 599 | | | | | | | | | | |R 1 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 231 |TOTAL AIR |W +/- 799 |Deg.| | 3 |500 |BCD | | | | |TEMP |-60 to 99 |C | | | | | | | | | |R 1 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 233 |STATIC AIR|W +/- 799 |Deg.| | 3 |500 |BCD | | | | |TEMP |-99 to +80 |C | | | | | | | | | |R 1 | | | | | | | | | | |+/- 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 234 |BARO |W +/- 7999.9|hPa | | 5 |500 |BCD | | | | |CORRECT 1 |745 to 1100 | | | | | | | | | |mb |R 0.1 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 235 |BARO |W +/- 79.999|inHg| | 5 |500 |BCD | | | | |CORRECT 1 |22.0 to 32.5| | | | | | | | | |in.Hg |R 0.001 | | | | | | | | | | |+/- 0.0074 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 236 |BARO |W +/- 7999.9|hPa | | 5 |500 |BCD | | | | |CORRECT 2 |745 to 1100 | | | | | | | | | |mb |R 0.1 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 237 |BARO |W +/- 79.999|inHg| | 5 |500 |BCD | | | | |CORRECT 2 |22.0 to 32.5| | | | | | | | | |in.Hg |R 0.001 | | | | | | | | | | |+/- 0.0074 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 240 |VMO/MMO |W 399/0.99 |Kts/| |3/2 |1000|BCD | | | | |STATUS |0 to 399 / |Mach| | | | | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 40 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |0 to 0.99 | | | | | | | | | | |R 1 /0.01 | | | | | | | | | | |1 / 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 241 |CORRECTED |W +/- 180 |Deg.| 29 | 12 | 62 |BNR | AOA | | | |ANGLE OF |-35 to +85 | | | | | | | | | |ATTACK |R 0.0439 | | | | | | | | | | |+/- 0.25 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 242 |TOTAL |W2048 |hPa | | 16 |125 |BNR | | | | |PRESSURE |100 to 1400 | | | | | | | | | | |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 245 |UNCRCTD |W2048 |hPa | | 16 |125 |BNR | | | | |AVG STAT |100 to 1100 | | | | | | | | | |PRESSURE |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 246 |CORCTD |W2048 |hPa | | 16 |125 |BNR | | | | |AVG STAT |100 to 1100 | | | | | | | | | |PRESSURE |R 0.03125 | | | | | | | | | | |+/- 0.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DSCT WORD | | | | |500 |DIS | | | | | 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 271 |DSCT WORD | | | | |500 |DIS | | | | | 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 272 |DSCT WORD | | | | |500 |DIS | | | | | 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 350 |MAINT WORD| | | | |500 |DIS | | | | | 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 351 |MAINT WORD| | | | |500 |DIS | | | | | 2 | | | | | | | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 41 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 352 |MAINT WORD| | | | |500 |DIS | | | | | 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 155 |MAINT WORD| | | | |500 |DIS | | | | | 4 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 354 |LRU ID | | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 356 |FAULT STAT| | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQPT IDENT| | | | |500 |HEX | | | ------------------------------------------------------------------------------Output Label -------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | Icing Detector Heat | NO FAULT | FAULT | | 12 | Pitot Probe Heat | NO FAULT | FAULT | | 13 | ADR FAULT | FAULT | NO FAULT | | 14 | Right Static Heat | NO FAULT | FAULT | | 15 | Left Static Heat | NO FAULT | FAULT | | 16 | TAT Heat | HEAT | NO HEAT | | 17 | AOA 1 Heat | NO FAULT | FAULT | | 18 | AOA 2 Heat | NO FAULT | FAULT | | 19 | Overspeed Warning | WARN | NO WARN | | 20 | Spare (Primary AOA Fault) | | | | 21 | AOA Average/Unique | UNIQUE | AVERAGE | | 22 | VMO/MMO 1 | YES | NO | | 23 | VMO/MMO 2 | YES | NO | | 24 | VMO/MMO 3 | YES | NO | | 25 | VMO/MMO 4 | YES | NO | | 26 | SSEC Alternate Select 1 | YES | NO | | 27 | SSEC Alternate Select 2 | YES | NO | | 28 | Baro Port A Select | Port A | Port B | | 29 | Zero Mach SSEC Select | YES | NO | --------------------------------------------------------------------------

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 42 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

-------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------Label 270 - Discrete Word 1

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 43 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

-------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | Zero AOA SSEC Select | YES | NO | | 12 | AOA Test Active | ACTIVE | NOT ACTIVE | | 13 | Low Speed Warning 1 | FAST | SLOW | | 14 | Low Speed Warning 2 | FAST | SLOW | | 15 | Low Speed Warning 3 | FAST | SLOW | | 16 | Low Speed Warning 4 | SLOW | FAST | | 17 | Spare | | | | 18 | Spare | | | | 19 | Spare | | | | 20 | AOA Correction 1A | YES | NO | | 21 | AOA Correction 1B | YES | NO | | 22 | AOA Correction 2A | YES | NO | | 23 | AOA Correction 2B | YES | NO | | 24-25 | Bus A Altimeter Mode | refer to Table 11A | | 26-27 | Bus B Altimeter Mode | refer to Table 11A | | 28 | Spare | | | | 29 | Spare | | | -------------------------------------------------------------------------Label 271 - Discrete Word 2 -----------------------------------------------------------------------------| Altimeter Mode | FCU Input | Label 271 Bus A - Bits 25 & 24 | | | Label 272 - Bits 15 & 13 | Bus B - Bits 27 & 26 | |----------------------------------------------------------------------------| | STD | 01 | 01 | |----------------|--------------------------|--------------------------------| | QNH | 10 | 10 | |----------------|--------------------------|--------------------------------| | QFE | 00 | 00 | |----------------|--------------------------|--------------------------------| | INVALID | 11 | 11 | -----------------------------------------------------------------------------Altimeter Mode Conversion

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 44 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

-------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | -------------------------------------------------------------------------| 11 | SDI 2 | GROUND | OPEN | | 12 | SDI 1 | GROUND | OPEN | | 13 | Dual Baro Select | DUAL PORT | SINGLE PORT| | 14 | Analog Baro Select | ANALOG | DIGITAL | | 15 | Spare IDSC 1 | GROUND | OPEN | | 16 | Spare IDSC 2 | GROUND | OPEN | | 17 | Spare IDSC 3 | GROUND | OPEN | | 18 | Baro 3 Present | PRESENT | ABSENT | | 19 | Spare IDSC 4 | GROUND | OPEN | | 20 | CFDS Select | NOT ACTIVE| ACTIVE | | 21 | Spare | | | | 22 | BITE Memory Clear Enable | ENABLE | DISABLE | | 23 | BITE Write Inhibit | INHIBIT | ENABLE | | 24 | ADR Interface Test | TEST | NORMAL | | 25 | ADR Off Command | GROUND | OPEN | | 26 | Reserved | | | | 27 | ADR On/Off Status | OFF | ON | | 28 | Spare | | | | 29 | Spare | | | -------------------------------------------------------------------------Label 272 - Discrete Word 3

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 45 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, ------------------------------------------------------------------------| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN | ------------------------------------------------------------------------| 11 | A/C ID Code 32/0 | GROUND | OPEN | | 12 | A/C ID Code 64/0 | GROUND | OPEN | |13 to 23| Spare | | | | 24 | A/C ID Code 1/0 | GROUND | OPEN | | 25 | A/C ID Code 2/0 | GROUND | OPEN | | 26 | A/C ID Code 4/0 | GROUND | OPEN | | 27 | A/C ID Code 8/0 | GROUND | OPEN | | 28 | A/C ID Code 16/0 | GROUND | OPEN | | 29 | A/C ID Parity | GROUND | OPEN | ------------------------------------------------------------------------Label 352 - Discrete Word 4 ------------------------------------------------------------------------| BIT N⁰ | FUNCTION | ------------------------------------------------------------------------| 11 | = 0 -| | 12 | = 1 | LSD = 6 | | 13 | = 1 | | | 14 | = 0 -| | 15 | = 0 -| | 16 | = 0 | MSD = 0 | | 17 | = 0 | | | 18 | = 0 -| |19 to 29| Spare | ------------------------------------------------------------------------Label 377 - Equipment Ident

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 46 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

INTENTIONALLY BLANK

  R   34-13-00 Page 47   Config-3 Feb 01/10  CES

 

**ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, - On the ground the output labels are in the following state: -------------------------------------------------------------------------| LABEL | PARAMETER DEFINITION | SSM | ON GND CRITERION | |------------------------------------------------------------------------| 203 | Altitude | NO | | | 204 | Baro Corr Alt 1 | NO | | | 220 | Baro Corr Alt 2 | NO | | | 251 | Baro Corr Alt 3 | NO | | | 205 | Mach | NCD | 0 Mach less than 0.1 | | 206 | Computed Airspeed | NCD | 0 kt CAS less than 30 kts | | 207 | Max Allowable Airspeed | NO | | | 210 | True Airspeed | NCD | 0 kt CAS less than 60 kts | | 211 | Total Air Temp | NO | | | 212 | Altitude Rate | NO | | | 213 | Static Air Temp | NO | | | 215 | Impact Pressure | NO | | | 221 | Indicated AOA | NCD | NOTE CAS less than 60 kts | | 230 | True Airspeed | NCD | 0 kt CAS less than 60 kts | | 231 | Total Air Temp | NO | | | 233 | Static Air Temp | NO | | | 234 | Baro Corr (hPa) 1 & 2 & 3| NO | | | 236 | Baro Corr (hPa) 2 | NO | | | 034 | Baro Corr (hPa) 3 | NO | | | 235 | Baro Corr (in.Hg) 1 | NO | | | 237 | Baro Corr (in.Hg) 2 | NO | | | 035 | Baro corr (in.Hg) 3 | NO | | | 240 | VMO/MMO status | NO | | | 241 | Corrected AOA | NCD | 0⁰ CAS less than 60 kts | | 242 | Total Pressure | NO | | | 176 | L. Static Pressure | NO | | | 177 | R. Static Pressure | NO | | | 245 | Uncrctd Avg Stat Pressure| NO | | | 246 | Corctd Avg Stat Pressure | NO | | | 270 | Discrete words | NO | | | 271 | Discrete words | NO | | | 272 | Discrete words | NO | | | 350 | Discrete words | NO | | | 351 | Discrete words | NO | | | 352 | Discrete words | NO | | | 377 | Discrete words | NO | | | 354 | LRU ID | N/A | N/A | | 356 | Fault Status | N/A | N/A | --------------------------------------------------------------------------

  EFF : 051-057, 059-060, 062-099, 106-149,  34-13-00 Page 48 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Feb 01/10 R 236-238, 301-304, CES

 

-------------------------------------------------------------------------| LABEL | PARAMETER DEFINITION | SSM | ON GND CRITERION | |------------------------------------------------------------------------Output Label Value on Ground

  R EFF : 051-057, 059-060, 062-099, 106-149,  34-13-00 Page 49 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Feb 01/10 236-238, 301-304, CES

 

R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-523, - On the ground the output labels are in the following state: -------------------------------------------------------------------------| LABEL | PARAMETER DEFINITION | SSM | ON GND CRITERION | |-----------------------------------------------------------------------------| 203 | Altitude | NO | | | 204 | Baro Corr Alt 1 | NO | | | 220 | Baro Corr Alt 2 | NO | | | 251 | Baro Corr Alt 3 | NO | | | 205 | Mach | NCD | 0 Mach less than 0.1 | | 206 | Computed Airspeed | NCD | 0 kt CAS less than 30 kts | | 207 | Max Allowable Airspeed | NO | | | 210 | True Airspeed | NCD | 0 kt CAS less than 60 kts | | 211 | Total Air Temp | NO | | | 212 | Altitude Rate | NO | | | 213 | Static Air Temp | NO | | | 215 | Impact Pressure | NO | | | 221 | Indicated AOA | NCD | NOTE CAS less than 60 kts | | 230 | True Airspeed | NCD | 0 kt CAS less than 60 kts | | 231 | Total Air Temp | NO | | | 233 | Static Air Temp | NO | | | 234 | Baro Corr (hPa) 1 & 2 & 3| NO | | | 236 | Baro Corr (hPa) 2 | NO | | | 034 | Baro Corr (hPa) 3 | NO | | | 235 | Baro Corr (in.Hg) 1 | NO | | | 237 | Baro Corr (in.Hg) 2 | NO | | | 035 | Baro corr (in.Hg) 3 | NO | | | 240 | VMO/MMO status | NO | | | 241 | Corrected AOA | NCD | Cmptd value CAS less than 60 kts | | 242 | Total Pressure | NO | | | 176 | L. Static Pressure | NO | | | 177 | R. Static Pressure | NO | | | 245 | Uncrctd Avg Stat Pressure| NO | | | 246 | Corctd Avg Stat Pressure | NO | | | 270 | Discrete words | NO | | | 271 | Discrete words | NO | | | 272 | Discrete words | NO | | | 350 | Discrete words | NO | | | 351 | Discrete words | NO | | | 352 | Discrete words | NO | | | 377 | Discrete words | NO | | | 354 | LRU ID | N/A | N/A | | 356 | Fault Status | N/A | N/A | -------------------------------------------------------------------------------

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 50 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

-------------------------------------------------------------------------| LABEL | PARAMETER DEFINITION | SSM | ON GND CRITERION | |-----------------------------------------------------------------------------Output Label Value on Ground

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 51 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

-------------------------------------------------------------------------| | | TYPE A | TYPE B | | | |-------------------|-------------------| |OCTAL| | MAXIMUM | MAXIMUM | MAXIMUM | MAXIMUM | |LABEL| SIGNAL | FILTER |TRANSPORT| FILTER |TRANSPORT| | | |BANDWIDTH|DELAY****|BANDWIDTH|DELAY****| | | | (HZ) | (MSEC) | (HZ) | (MSEC) | -------------------------------------------------------------------------| 034 |Baro Corr mb 3 | N/A | 220 | N/A | 220 | | 035 |Baro Corr ins hg 3 | N/A | 220 | N/A | 220 | | 176 |Left Static Pressure | N/A *** | 119 | N/A *** | 119 | | 177 |Right Static Pressure | N/A *** | 119 | N/A *** | 119 | | 203 |Altitude | 8 | 86 | 3 | 120 | | 204 |Baro Corr Alt 1 | 8 | 94 | 3 | 128 | | 205 |Mach | 8 | 86 | 3 | 120 | | 206 |Computed Airspeed | 8 | 86 | 3 | 120 | | 207 |Max Allow. Aispeed | 8 | 219 | 8 | 219 | | 210 |True Airspeed | 8 | 219 | 3 | 253 | | 211 |Total Air Temp. | 4 | 1019 | 3 | 1049 | | 212 |Altitude Rate | 1.8 | 415 | 1,8 | 415 | | 213 |Static Air Temp. | 4 | 1019 | 3 | 1049 | | 215 |Impact Pressure | 8 | 219 | 3 | 253 | | 220 |Baro Corr Alt 2 | 8 | 94 | 3 | 128 | | 221 |Ind. Angle of Attack | 8 | 167 | 3 | 220 | | 230 |True Airspeed | 8 | 370 | 3 | 404 | | 231 |Total Air Temp | 4 | 1019 | 3 | 1049 | | 233 |Static Air Temp | 4 | 1019 | 3 | 1049 | | 234 |Baro Corr mb 1 | N/A | 169 | N/A | 169 | | 235 |Baro Corr ins hg 1 | N/A | 169 | N/A | 169 | | 236 |Baro Corr mb 2 | N/A | 169 | N/A | 169 | | 237 |Baro Corr ins hg 2 | N/A | 169 | N/A | 169 | | 241 |Corr Angle of Attack | 8 | 167 | 3 | 220 | | 242 |Total Pressure | N/A *** | 219 | N/A *** | 219 | | 245 |Uncorr Avg Static Pressure| N/A *** | 119 | N/A *** | 119 | | 246 |Corr Avg Static Pressure | N/A *** | 119 | N/A *** | 119 | | 251 |Baro Corr Alt 3 | 8 | 94 | 3 | 128 | -------------------------------------------------------------------------Table 15 A - ADR output filter data characteristics. NOTE : Type A refers to A318/A319/A320/A321 and type B refers to ____ A330/A340. * Maximum filter bandwidth and maximum transport delay are not applicable to the following labels: - 155 Maintenance Word 4, - 270 Discrete Word 1, - 271 Discrete Word 2, - 272 Discrete Word 3,

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-

350 351 356 377

Maintenance Word 1, Maintenance Word 2, Fault Status, Equipment ID.

** Filters present only as provisions, except for Altitude Rate. *** Filtering of pressure data is performed by ADM. **** The Transport Delay does not include the Transmit Interval of the digital outputs. For ADR digital outputs based on the digital inputs (such as from the ADM), the Transport Delay is the delay between the digital input and the corresponding digital output. It is determined by plotting data updates vs. time for the digital inputs and outputs, and converting these discrete data points into continuous curves by appropriate smoothing between points. The Transport Delay is defined as the time delay between the input and output continuous curves. For parameters in which wide band and narrow band data are combined in the calculation, the transport delay requirement applies to the wide band portion of the computation.

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-13-00 Page 53 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (b) Discrete form The ADR provides seven standard OPEN/GROUND output discretes. -------------------------------------------------------------------------| SIGNAL | PIN | OUTPUT | DEFINITION | |------------------------------|------------|-------------|--------------| | ADR OFF Light | TP- 4E | OPEN/GROUND | ON/OFF | | ADR FAULT | TP- 4D | OPEN/GROUND | NO/FAULT | | Low Speed Warning Discrete 1 | TP- 2F | OPEN/GROUND | SLOW/FAST | | Low Speed Warning Discrete 2 | TP- 2G | OPEN/GROUND | SLOW/FAST | | Low Speed Warning Discrete 3 | TP- 6F | OPEN/GROUND | SLOW/FAST | | Low Speed Warning Discrete 4 | TP-13H | OPEN/GROUND | FAST/SLOW | | AOA Special Test | TP-12G | OPEN/28VDC | NO/TEST | -------------------------------------------------------------------------ADR - Discrete Output Signals NOTE : The ADR OFF light, the low speed warning 4 and ADR FAULT ____ discretes are forced to the ground state when the watchdog timer (WDT) has timed out. 1 _

ADR OFF Light When the ADR is commanded OFF, it issues a ground state to the ADR OFF light discrete to enable the legend to come on.

2 _

ADR FAULT When an ADR FAULT is detected, the ADR issues a ground state to the ADR FAULT discrete to enable the legend to come on.

3 _

Low speed warning discretes 1, 2, 3, 4 The ADR provides four standard Open/Ground low speed warning output discretes. - Airspeed conditions Airspeed decreasing Discrete 1 = OPEN for Airspeed less than or equal to 100 knots Discrete 2 = OPEN for Airspeed less than or equal to 50 knots Discrete 3 = OPEN for Airspeed less than or equal to 155 knots Discrete 4 = GROUND for Airspeed less than or equal to 260 knots Airspeed increasing Discrete 1 = GROUND for Airspeed greater than 104 knots Discrete 2 = GROUND for Airspeed greater than 54 knots

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Discrete 3 = GROUND for Airspeed greater than 159 knots Discrete 4 = OPEN for Airspeed greater than 264 knots - Power off conditions Discrete 1 = OPEN Discrete 2 = OPEN Discrete 3 = OPEN Discrete 4 = OPEN - CAS detected failure condition Discrete 1 = previous state Discrete 2 = previous state Discrete 3 = previous state Discrete 4 = OPEN 4 _

AOA special test The ADR provides an OPEN/GROUND output discrete to drive the AOA self-test. The AOA self-test is commanded via the CFDIU interface bus. When the AOA test is active, the AOA sensor is offset to +15 deg. (plus or minus 1 deg.). All AOA dependent parameters reflect this offset and their SSMs indicate Functional Test (FT). The RETURN command from the MCDU results in the discrete output set to OPEN. Ref. 34-18-00 for more details.

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3. ________________________________ Operation/Control and Indicating **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, A. Control (1) ADIRS Control and Display Unit (CDU) (Ref. Fig. 010) The ADIRS CDU provides the control and warning of the three ADRs by means of three ADR illuminated pushbutton switches: - the pushbutton switch is used to disable the ADR output buses. It is a momentary action pushbutton switch - when the ADR output buses are disabled, the ADR controls the activation of the ADR OFF legend by its output discrete: ADR OFF status - when an ADR failure is detected, the ADR controls the activation of the ADR FAULT legend by its output discrete: ADR FAULT - each ADR is de-energized when the associated OFF/NAV/ATT selector switch is set to OFF - when the associated OFF/NAV/ATT selector switch is set to NAV or ATT, each ADR is switched on independently of the previous selection on the ADR pushbutton switch. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, A. Control (1) ADIRS Mode Selector Unit (MSU) (Ref. Fig. 010A) The ADIRS MSU provides the control and warning of the three ADRs by means of three ADR illuminated pushbutton switches: - The pushbutton switch is used to disable the ADR output buses. It is a momentary action pushbutton switch. - When the ADR output buses are disabled, the ADR controls the activation of the ADR OFF legend by its output discrete: ADR OFF status. - When an ADR failure is detected, the ADR controls the activation of the ADR FAULT legend by its output discrete: ADR FAULT. - Each ADR is de-energized when the associated OFF/NAV/ATT selector switch is set to OFF. - When the associated OFF/NAV/ATT selector switch is set to NAV or ATT, each ADR is switched on independently of the previous selection on the ADR pushbutton switch.

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ADR Control on CDU Figure 010   R EFF : 051-099, 106-149, 204-239, 301-312,  34-13-00 Page 57 401-499,  Config-3 Feb 01/10  CES

 

ADR Control on MSU Figure 010A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-13-00 Page 58 511-523,  Config-3 Feb 01/10  CES

 

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, B. Indicating Altitude (ALT), Computed Airspeed (CAS), Mach number (M) and Vertical Speed (V/S) are computed by the ADIRU (ADR portion), processed by the associated DMC and displayed on the PFDs. True Airspeed (TAS) is supplied in the same way but is displayed on the NDs. In normal configuration, with the AIR DATA selector switch in NORM position, the ADR 1 displays information on CAPT PFD and ND. The ADR 2 displays information on F/O PFD and ND. Static Air Temperature (SAT) and Total Air Temperature (TAT) are also supplied in the same way but are permanently displayed on the lower part of the lower ECAM DU. These items of information are displayed by the ADR 2 when EIS1 is installed, by ADR1 when EIS2 is installed. (1) PFD display For further details concerning speed, altitude or vertical speed scale, Ref. 31-64-00. (a) Computed Airspeed (CAS) (Ref. Fig. 011) The CAS indication is displayed in analog form by means of a white tape with graduations every 10 kts and digital values every 20 kts. This tape moves up and down so as to indicate the A/C actual speed value in front of a fixed yellow reference line. The displayed part of the scale represents an 84 kts range. The scale is graduated from 30 kts to 520 kts and the digital values from 40 to 520 kts (item A). In no case can the displayed CAS be lower than 30 kts. In case of computed airspeed failure, the speed scale goes out of view and is replaced by a red SPD flag (item B). (b) Mach number (M) When the Mach number is above 0.5, it is displayed just below the speed scale. In case of failure, a red MACH flag is presented. (c) Altitude (ALT) (Ref. Fig. 012) The baro altitude indication is provided by means of a tape which moves up and down behind a window within which the A/C actual altitude is displayed. The tape of the scale is graduated every 100 ft and digital values are displayed every 500 ft in hundreds.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 59 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

Computed Airspeed and Mach Indication Display Figure 011   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 60 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

Altitude Indication Display Figure 012   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 61 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

The A/C actual altitude is provided by a counter located at the middle of the scale in which the actual value is displayed in green digits. The hundreds of feet are written in a large size whereas the tens and units are displayed by a drum operating as a classical mechanical altimeter. Small white marks are positioned in front of each number on the tape (item A). If the altitude is negative, a NEG white indication is added at the left of the digital value. The digital value is limited to minus 1500 ft (item B). Different displays are presented depending on the baro setting reference (standard or baro corrected), Ref. 31-64-00. In case of baro altitude failure, the scale goes out of view and a red ALT flag flashes for a few seconds in the altitude window, then remains steady (item C). In case of discrepancy between the altitude given by the CAPT air data source and the altitude given by the F/O air data source, a CHECK ALT amber flag is presented on the right side of the altitude scale (item D). (d) Vertical Speed (V/S) (Ref. Fig. 013) The baro vertical speed is automatically displayed in the right side of the PFD when the inertial vertical speed is not available (item A). It is a degraded mode. The vertical speed scale consists of: - a trapezoidal grey background colored surface - a fixed white scale with 500 ft/mn spaced marks from -2000 ft/mn to +2000 ft/mn - a needle giving, in analog form, the actual vertical speed value - a number in a moving amber window. This window accompanies the needle (above the needle if V/S > 0, below if V/S < 0). The number gives the V/S value in hundreds of ft/mn. Between -200 ft/mn and +200 ft/mn, both the window and the number disappear. - above +6000 ft/mn (or below -6000 ft/mn), the needle remains stopped where it is. When the vertical speed exceeds +6000 ft/mn or -6000 ft/mn, the digital indication and the analog needle change from green to amber. In addition, those indications change to amber in approach, in the following cases: - V/S less than -2000 ft/mn below 2500 ft RA - V/S less than -1200 ft/mn below 1000 ft RA.

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Vertical Speed Indication Display Figure 013   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 63 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

In case of a failure warning, the vertical speed scale is removed and replaced by a red V/S flag which flashes for a few seconds, then remains steady (item B). (2) ND display (Ref. Fig. 014) The true airspeed (TAS) is displayed on the ND in ROSE, ARC and PLAN mode (item A). The TAS information is displayed by a numerical indication of three digits preceded by TAS indication. This information is displayed in the left upper corner of the ND for speed higher than 100 kts. Below this value TAS indication remains visible but is followed by three dashes (item B). **ON A/C 051-099, 204-233, 236-238, 301-302, (3) Display on the lower ECAM DU (Ref. Fig. 015) The Static Air Temperature (SAT) and the Total Air Temperature (TAT) are permanently displayed on the lower part of the lower ECAM DU by a numerical indication of two digits preceded by the plus or minus sign (item A). These data are delivered by the ADR 2 when EIS 1 is installed, by ADR 1 when EIS 2 is installed. In case of failure or when NCD information is received from the ADR 2, these data are replaced by crosses (item B). R R

**ON A/C 106-149, 234-235, 239-249, 251-299, 303-399, 401-499, 501-509, 511-523, (3) Display on the lower ECAM DU (Ref. Fig. 015) The Static Air Temperature (SAT) and the Total Air Temperature (TAT) are permanently displayed on the lower part of the lower ECAM DU by a numerical indication of two digits preceded by the plus or minus sign (item A). These data are delivered by the ADR 2 when EIS 1 is installed, by ADR 1 when EIS 2 is installed. In case of failure or when NCD information is received from the ADR 1, these data are replaced by crosses (item B).

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True Airspeed Indication Display Figure 014   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 65 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

TAT/SAT Indication Display Figure 015   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 66 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (4) Reconfiguration display In case of loss of AIR DATA parameters on CAPT or F/O PFD and ND, the ADR 3 can be used as a back up source by placing the AIR DATA selector switch in CAPT/3 position for EFIS 1 and F/O/3 position for EFIS 2. In case of loss of TAT/SAT parameters on the lower ECAM DU, the ADR 3 can be used as a back up source by placing the AIR DATA selector switch in F/O/3 position when EIS 1 is installed, in CAPT/3 position when EIS 2 is installed. **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, C. Warnings In addition to the AIR DATA flags displayed on the PFDs and NDs and on the CDU, warning messages are displayed on the lower part of the upper ECAM DU. Two kinds of warning messages can be displayed: - failure warning messages in case of loss of AIR DATA parameters - configuration warning messages in case of dangerous configuration of the aircraft. When the CLR key is pushed on the ECAM control panel, a STATUS page is displayed on the lower ECAM DU and indicates the STATUS and INOP SYS (systems). (1) Failure warning messages (Ref. Fig. 016, 017, 018) (a) NAV ADR 1(2)(3) FAULT NAV ADR 1(2) + 2(3) FAULT When these messages are displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the FAULT legend of the ADR pushbutton switch on the CDU comes on.

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, C. Warnings In addition to the AIR DATA flags displayed on the PFDs and NDs, warning messages are displayed on the lower part of the upper ECAM DU. Two kinds of warning messages can be displayed: - failure warning messages in case of loss of AIR DATA parameters

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NAV ADR 1(2)(3) FAULT Message Figure 016   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 68 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

NAV ADR 1+3 (2+3) FAULT Message Figure 017   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 69 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

NAV ADR 1 + 2 FAULT Message Figure 018   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 70 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

- configuration warning messages in case of dangerous configuration of the aircraft. When the CLR key is pushed on the ECAM control panel, a STATUS page is displayed on the lower ECAM DU and indicates the STATUS and INOP SYS (systems). (1) Failure warning messages (Ref. Fig. 016, 017, 018) (a) NAV ADR 1(2)(3) FAULT NAV ADR 1(2) + 2(3) FAULT When these messages are displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the FAULT legend of the ADR pushbutton switch on the MSU comes on. R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (b) NAV ALTI DISCREPANCY (Ref. Fig. 019) This message is displayed when a difference higher than plus or minus 250 ft is detected by the external comparison inside the FWCs between the baro-corrected altitude (or plus or minus 500 ft for the standard altitude) provided by two ADRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK ALT message appears on the PFD. (2) Configuration warning messages (Ref. Fig. 020)

R

**ON A/C 051-099, 106-149, 204-249, 251-299, 401-499, 501-509, 511-523, (Ref. Fig. 021) **ON A/C 301-399, (Ref. Fig. 021A)

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NAV ALTI DISCREPANCY Message Figure 019   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 72 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

OVERSPEED VMO/MMO Message Figure 020   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 73 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

OVERSPEED VFE/VLE Message Figure 021   R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 74 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

OVERSPEED VFE/VLE Message Figure 021A   R EFF : 301-399,  34-13-00 Page 75   Config-3 Feb 01/10  CES

 

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (a) OVERSPEED VM0/MM0 OVERSPEED VFE/VLE When these messages are displayed: - the MASTER WARN lights on the glareshield flash - the Continuous Repetitive Chime (CRC) sounds. OVERSPEED VMO/MMO warning processed by the FWC is triggered when the CAS/Mach calculated by the ADR exceed the VMO/MMO threshold by more than 4 kts/0.006 Mach. OVERSPEED VFE/VLE processed by the FWC is a function of Vc and depends on slat/flap position for the VFE and landing gear position for the VLE. For overspeed VLE, the warning is triggered at 284 knots. (b) Stall warning (Ref. Fig. 022) When this warning is activated: - the MASTER WARN lights on the glareshield flash - the cricket and the voice STALL sound. This warning is processed by the FWC and is a function of angle of attack value and slat position following these conditions: - normal law: if corrected angle of attack exceeds 23⁰ or if corrected angle of attack exceeds 15⁰ and slat < 15⁰. - alternate law if corrected angle of attack exceeds 13⁰ or if corrected angle of attack exceeds 8⁰ and slat < 15⁰.

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Stall Warning Message Figure 022   EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 Page 77 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

AIR DATA - REMOVAL/INSTALLATION _______________________________ TASK 34-13-00-040-001 PFD Mach Number - Overspeed Check WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job R

NOTE : This deactivation task is not related to an AFM-CDL/MMEL item. ____ 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 34-10-00-860-002 34-10-00-860-005 34-13-00-740-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure ADIRS Start Procedure ADIRS Stop Procedure INTERFACE TEST of the ADR

3. __________ Job Set-up Subtask 34-13-00-865-070 A. On the circuit breaker panels 49VU, 121VU and 122VU, close the circuit breakers related to the NAVIGATION, EIS, FCU, CFDS and LGCIU systems. Subtask 34-13-00-860-081 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

  EFF : ALL  34-13-00    CES

 

Page 401 Feb 01/08

(3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) On the MCDU, get the SYSTEM REPORT/TEST NAV menu page (Ref. TASK 31-32-00-860-010) (5) On the overhead panel : - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - on the ELEC panel 35VU, make sure that the battery voltage is correct, between 26VDC and 30VDC. 4. Procedure _________ R

**ON A/C 001-049, 101-105, 151-199, 201-210, 301-312, 401-499, Subtask 34-13-00-710-056 A. Overspeed Check ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead panel, on the ADIRS CDU: - set the 3 OFF/NAV/ATT selector switches to NAV.

The OFF legend of the 3 ADR pushbutton switches must be off.

- push the ADR3 pushbutton switch.

The related OFF legend comes on.

2. On the MCDU, on the NAV menu page: - push the line key adjacent to the ADC1 (ADC2) indication.

The ADR1 (ADR2) page comes into view.

- push the line key adjacent to the OUTPUT TESTS indication.

The ADR1 (ADR2) OUTPUT TESTS page comes into view.

- push the line key adjacent to the INTERFACE TEST indication.

The ADR1 (ADR2) INTERFACE TEST 1/2 page comes into view.

  EFF : ALL  34-13-00    CES

 

Page 402 May 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- on the keyboard push the NEXT The ADR1 (ADR2) INTERFACE TEST 2/2 page PAGE function key. comes into view.

R

- push the line key adjacent to the START TEST indication. (Ref. TASK 34-13-00-740-002).

From 0 to 10 seconds ignore the warnings and indications. From 10 seconds: - the black and red strip comes into view on the speedscale on the CAPT (F/O) PFD - ignore the related warnings.

- push the line key adjacent to the RETURN indication.

The test procedure stops, the warnings above stop.

**ON A/C 051-099, 106-149, 211-239, Subtask 34-13-00-710-056-A A. Overspeed Check ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead panel, on the ADIRS CDU: - set the 3 OFF/NAV/ATT selector switches to NAV.

The OFF legend of the 3 ADR pushbutton switches must be off.

- push the ADR3 pushbutton switch.

The related OFF legend comes on.

2. On the MCDU, on the NAV menu page: - push the line key adjacent to the ADC1 (ADC2) indication.

The ADIRS ADR1 (ADR2) 1/2 page comes into view.

- push the line key adjacent to the INTERFACE TEST indication.

The ADIRS ADR1 (ADR2) INTERFACE TEST page comes into view.

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Page 403 May 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to From 0 to 10 seconds ignore the the TEST START indication warnings and indications. (Ref. TASK 34-13-00-740-002). From 10 seconds: - the black and red strip comes into view on the speedscale on the CAPT (F/O) PFD - ignore the related warnings. - Push the line key adjacent to the RETURN/TEST STOP indication. R

The test procedure stops, the warnings above stop.

**ON A/C 240-249, 251-299, 501-509, 511-526, 528-599, Subtask 34-13-00-710-056-B A. Overspeed Check ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead panel, on the ADIRS MSU: - Set the three OFF/NAV/ATT selector switches to NAV.

The OFF legend of the three ADR pushbutton switches must be off.

- Push the ADR3 pushbutton switch.

The related OFF legend comes on.

2. On the MCDU, on the NAV menu page: - Push the line key adjacent to the ADC1 (ADC2) indication.

The ADIRS ADR1 (ADR2) 1/2 page comes into view.

- Push the line key adjacent to the INTERFACE TEST indication.

The ADIRS ADR1 (ADR2) INTERFACE TEST page comes into view.

- Push the line key adjacent to the TEST START indication (Ref. TASK 34-13-00-740-002).

From 0 to 10 seconds ignore the warnings and indications. From 10 seconds:

  R EFF : 051-099, 106-149, 211-249, 251-299,  34-13-00 501-509, 511-526, 528-599,   CES

 

Page 404 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- The black and red strip comes into view on the speedscale on the CAPT (F/O) PFD. - Ignore the related warnings. - Push the line key adjacent to the RETURN/TEST STOP indication.

The test procedure stops, the warnings above stop.

**ON A/C 313-399, Subtask 34-13-00-710-056-C A. Overspeed Check ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead panel, on the ADIRS MSU: - Set the three OFF/NAV/ATT selector switches to NAV.

The OFF legend of the three ADR pushbutton switches must be off.

- Push the ADR3 pushbutton switch.

The related OFF legend comes on.

2. On the MCDU, on the NAV menu page: - Push the line key adjacent to the ADC1 (ADC2) indication.

The ADR1 (ADR2) page comes into view.

- Push the line key adjacent to the OUTPUT TESTS indication.

The ADR1 (ADR2) OUTPUT TESTS page comes into view.

- Push the line key adjacent to the INTERFACE TEST indication.

The ADR1 (ADR2) INTERFACE TEST 1/2 page comes into view.

- On the keyboard push the NEXT PAGE function key.

The ADR1 (ADR2) INTERFACE TEST 2/2 page comes into view.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-13-00 511-526, 528-599,   CES

 

Page 405 Feb 01/10

R R R R R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Push the line key adjacent to From 0 to 10 seconds ignore the the START TEST indication. warnings and indications. (Ref. TASK 34-13-00-740-002). From 10 seconds: - The black and red strip comes into view on the speedscale on the CAPT (F/O) PFD. - Ignore the related warnings.

R R

- Push the line key adjacent to the RETURN indication.

The test procedure stops, the warnings above stop.

**ON A/C ALL 5. Close-up ________ Subtask 34-13-00-860-082 A. Put the aircraft back to its initial configuration. (1) On the ECAM control panel, set the LOWER DISPLAY and the UPPER DISPLAY potentiometers to OFF. (2) On the MCDU, push the MCDU MENU mode key. (3) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005). (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  EFF : ALL  34-13-00    CES

 

Page 406 May 01/08

TASK 34-13-00-440-001 Reactivation of PFD Mach Number - Overspeed Check 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information R

Not Applicable 3. __________ Job Set-up Subtask 34-13-00-869-085 A. Not Applicable 4. Procedure _________ Subtask 34-13-00-810-050 A. Do the trouble-shooting of the auto-flight function.

R R R

(1) Refer to the trouble shooting procedure relative to the triggered message.

  EFF : ALL  34-13-00    CES

 

Page 407 May 01/08

AIR DATA - ADJUSTMENT/TEST __________________________ TASK 34-13-00-710-001 Operational Test of the AIR DATA Switching Function WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Refer to the MPD TASK: 341300-02 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

R R

31-60-00-860-001 31-60-00-860-002 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-13-00-860-056 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

  EFF : ALL  34-13-00    CES

 

Page 501 May 01/05

Subtask 34-13-00-010-057 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-13-00-865-063 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

2GA 52GA

Q35 Q34

**ON A/C ALL 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/2PWR/SHED 121VU ADIRS/ADIRU/3PWR/SWTG

10FP 9FP

  EFF : ALL  34-13-00    CES

 

N10 N09

Page 502 Feb 01/10

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03 **ON A/C ALL Subtask 34-13-00-860-057 D. Aircraft Maintenance Configuration (1) Do the EIS start procedure (PFDs and NDs only) (Ref. TASK 31-60-00860-001). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) On the overhead panel: - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. (4) On the CAPT and F/O main instrument panels, on the PFDs: - make sure that the altitude and airspeed data come into view.

  EFF : ALL  34-13-00   R  CES

 

Page 503 Feb 01/08

4. Procedure _________ R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-13-00-710-050 A. BITE Test of the AIR DATA Switching Function ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU: - push the ADR1 pushbutton switch.

2. On the center pedestal, on the SWITCHING panel 8VU:

On the ADIRS CDU, the OFF legend of the ADR1 pushbutton switch comes on On the CAPT PFD, the speed and altitude indications go out of view (ignore the related flag warnings). On the CAPT PFD:

- set the AIR DATA selector switch to CAPT/3

- the speed and altitude indications from the ADR3 come into view.

- set the AIR DATA selector switch to NORM.

- the speed and altitude indications go out of view (ignore the related flag warnings).

3. On the ADIRS CDU: - push the ADR2 pushbutton switch.

On the ADIRS CDU, the OFF legend of the ADR2 pushbutton switch comes on On the F/O PFD, the speed and altitude indications go out of view (ignore the related flag warnings).

4. On the center pedestal, on the SWITCHING panel 8VU:

On the F/O PFD:

- set the AIR DATA selector switch to F/O/3

- the speed and altitude indications from the ADR3 come into view

- set the AIR DATA selector switch to NORM.

- the speed and altitude indications go out of view (ignore the related flag warnings).

  EFF : ALL  34-13-00    CES

 

Page 504 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------5. On the ADIRS CDU: - push the ADR1 and ADR2 pushbutton switches again

On the ADIRS CDU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off On the CAPT and F/O PFDs, the speed and altitude indications come into view.

- set the three OFF/NAV/ATT selector switches to OFF. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-13-00-710-050-A A. BITE Test of the AIR DATA Switching Function ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS MSU: - Push the ADR1 pushbutton switch.

2. On the center pedestal, on the SWITCHING panel 8VU:

On the ADIRS MSU, the OFF legend of the ADR1 pushbutton switch comes on. On the CAPT PFD, the speed and altitude indications go out of view (ignore the related flag warnings). On the CAPT PFD:

- Set the AIR DATA selector switch to CAPT/3.

- The speed and altitude indications from the ADR3 come into view.

- Set the AIR DATA selector switch to NORM.

- The speed and altitude indications go out of view (ignore the related flag warnings).

3. On the ADIRS MSU: - Push the ADR2 pushbutton

On the ADIRS MSU, the OFF legend of the ADR2 pushbutton switch comes on.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 505 Feb 01/10

R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------switch. On the F/O PFD, the speed and altitude indications go out of view (ignore the related flag warnings).

R R

4. On the center pedestal, on the SWITCHING panel 8VU:

R R

- Set the AIR DATA selector switch to F/O/3.

- The speed and altitude indications from the ADR3 come into view.

R R R

- Set the AIR DATA selector switch to NORM.

- The speed and altitude indications go out of view (ignore the related flag warnings).

R

5. On the ADIRS MSU:

R R R R R

- Push the ADR1 and ADR2 pushbutton switches again.

R R

- Set the three OFF/NAV/ATT selector switches to OFF.

R

On the F/O PFD:

On the ADIRS MSU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off. On the CAPT and F/O PFDs, the speed and altitude indications come into view.

**ON A/C ALL 5. Close-up ________ Subtask 34-13-00-860-058 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).

  EFF : ALL  34-13-00    CES

 

Page 506 Feb 01/08

Subtask 34-13-00-410-057 B. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

  EFF : ALL  34-13-00   R  CES

 

Page 507 Feb 01/08

TASK 34-13-00-710-002 Operational Test of the VMO/MMO Overspeed Warnings WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Refer to the MPD TASK: 341300-01 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 31-60-00-860-002 34-10-00-860-002 34-10-00-860-005 34-13-00-740-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure ADIRS Stop Procedure INTERFACE TEST of the ADR

  EFF : ALL  34-13-00   R  CES

 

Page 508 Feb 01/08

3. __________ Job Set-up Subtask 34-13-00-010-052 A. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-13-00-860-059 B. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 34-13-00-865-064 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 121VU HYDRAULIC/LGCIU/SYS2 2GA Q35 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34 Subtask 34-13-00-865-069 D. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 121VU AUTO FLT/FAC2/28VDC 5CC2 M19

  EFF : ALL  34-13-00   R  CES

 

Page 509 Feb 01/08

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-13-00-860-061 E. Aircraft Maintenance Configuration (1) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002), (3) On the overhead panel : - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - on the ADIRS CDU, on the panel 20VU, make sure that the 3 OFF/NAV/ATT selector switches are at NAV, - on the ELEC panel 35VU, make sure that the battery voltage is correct, between 26VDC and 30VDC. (4) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). (5) Make sure that the L/G doors are closed and the slats/flaps are fully retracted. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-13-00-860-061-A E. Aircraft Maintenance Configuration (1) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002), (3) On the overhead panel: - On the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - On the ADIRS MSU, on the overhead panel 20VU, make sure that the three OFF/NAV/ATT selector switches are at NAV. - On the ELEC panel 35VU, make sure that the battery voltage is correct, between 26VDC and 30VDC.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 510 Feb 01/10

R R

(4) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010).

R R

(5) Make sure that the L/G doors are closed and the slats/flaps are fully retracted.

R

**ON A/C ALL 4. Procedure _________

R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-13-00-710-051 A. OVERSPEED Warning VMO/MMO 1 (L/G DOWN VMO/MMO SELECTION Switch 22FP at NORM) NOTE : This test is for the VMO/MMO overspeed warning only. Ignore the ____ warnings and indications (VLE, ...) which are not related to this test. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead panel, on the ADIRS CDU: - push the ADR2 and ADR3 pushbutton switches. 2. On the MCDU:

On the ADIRS DCU: - the OFF legend of the ADR2 and ADR3 pushbutton switches comes on. On the MCDU:

- push the line key adjacent to the ADR1 indication.

- the ADR1 page comes into view.

- push the line key adjacent to the OUTPUT TESTS indication.

- the ADR1 OUTPUT TESTS page comes into view.

- push the line key adjacent to the INTERFACE TEST indication.

- the ADR1 INTERFACE TEST 1/2 page comes into view.

- on the keyboard push the NEXT PAGE function key.

- the ADR1 INTERFACE TEST 2/2 page comes into view.

  EFF : ALL  34-13-00    CES

 

Page 511 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to From 0 to 10 seconds, ignore the the START TEST indication. warnings and indications. From 10 seconds and more, on the CAPT(F/O) PFD, the speed increases to 367.7 Kts. When the value is 354 Kts: - on the upper ECAM display unit, this indication is shown: OVERSPEED VMO/MMO 350/.82 - On the panels 130VU and 131VU, the MASTER WARN lights flash. - You can hear the continuous repetitive chime aural warning. - push the line key adjacent to the RETURN indication.

The test procedure stops. The warnings above stop.

- push the line key adjacent to the RETURN indication.

The SYSTEM REPORT/TEST/NAV page comes into view.

3. On the ADIRS CDU: - push the ADR2 pushbutton switch.

- the OFF legend of the ADR2 pushbutton switch goes off.

- push the ADR1 pushbutton switch.

- the OFF legend of the ADR1 pushbutton switch comes on.

4. On the MCDU: - push the line key adjacent to the ADR2 indication. Do the same test as specified in the para 2 and 3.

Same results on the F/O PFD.

5. On the ADIRS CDU: - push the ADR3 pushbutton switch. 6. On the SWITCHING panel 8VU: - set the AIR DATA selector switch to CAPT/3.

On the ADIRS CDU, the OFF legend of the ADR3 pushbutton switch goes off. On the CAPT PFD, the speed and altitude indications from the ADR3 come into view.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-239, 301-312, 401-499,   CES

 

Page 512 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------7. On the ADIRS CDU: - push the ADR2 pushbutton switch.

On the ADIRS CDU, the OFF legend of the ADR2 pushbutton switch comes on.

8. On the MCDU: - push the line key adjacent to the ADR3 indication. Do the same test as specified in the para 2 and 3.

Same results on the CAPT PFD.

9. On the ADIRS CDU: - push the ADR1 and ADR2 pushbutton switches

On the ADIRS CDU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off.

10. On the SWITCHING panel 8VU: - set the AIR DATA selector switch to NORM. Subtask 34-13-00-710-052 B. OVERSPEED Warning VMO/MMO 2 (L/G DOWN VMO/MMO SELECTION Switch 22FP at L/G DOWN) ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. In the avionics compartment, on the panel 188VU: - remove the lockwire from the safety cover of the L/G DOWN VMO/MMO SELECTION switch. - set the switch to L/G DOWN. 2. In the cockpit on the overhead panel, on the ADIRS CDU: - push the ADR2 and ADR3 pushbutton switches.

On the ADIRS CDU: - the OFF legend of the ADR2 and ADR3 pushbutton switches comes on.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-239, 301-312, 401-499,   CES

 

Page 513 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------3. On the MCDU: On the MCDU: - push the line key adjacent to the ADR1 indication.

- the ADR1 page comes into view.

- push the line key adjacent to the OUTPUT TESTS indication.

- the ADR1 OUTPUT TESTS page comes into view.

- push the line key adjacent to the INTERFACE TEST indication.

- the ADR1 INTERFACE TEST 1/2 page comes into view.

- on the keyboard push the NEXT PAGE function key.

- the ADR1 INTERFACE TEST 2/2 page comes into view.

- push the line key adjacent to the START TEST indication. (Ref. TASK 34-13-00-740-002).

From 0 to 10 seconds, ignore the warnings and indications. From 10 seconds and more, on the CAPT(F/O) PFD, the speed increases to 367.7 Kts. When the value is 239Kts: - on the upper ECAM display unit, this indication is shown: OVERSPEED VMO/MMO 235/.60 - on the panels 130VU and 131VU, the MASTER WARN lights flash. - you can hear the continuous repetitive chime aural warning.

- push the line key adjacent to the RETURN indication.

The test procedure stops. The warnings above stop.

- push the line key adjacent to the RETURN indication.

The SYSTEM REPORT/TEST/NAV page comes into view.

4. On the ADIRS CDU:

On the ADIRS CDU:

- push the ADR2 pushbutton switch

- the OFF legend of the ADR2 pushbutton switch goes off.

- push the ADR1 pushbutton switch.

- the OFF legend of the ADR1 pushbutton switch comes on.

5. On the MCDU:

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-239, 301-312, 401-499,   CES

 

Page 514 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to Same results on the F/O PFD. the ADR2 indication. Do the same test as specified in the para 3 and 4. 6. On the ADIRS CDU: - push the ADR3 pushbutton switch. 7. On the SWITCHING panel 8VU: - set the AIR DATA selector switch to CAPT/3.

On the ADIRS CDU, the OFF legend of the ADR3 pushbutton switch goes off. On the CAPT PFD, the speed and altitude indications from the ADR3 come into view.

8. On the ADIRS CDU: - push the ADR2 pushbutton switch.

On the ADIRS CDU, the OFF legend of the ADR2 pushbutton switch comes on.

9. On the MCDU: - push the line key adjacent to the ADR3 indication. Do the same test as specified in the para 3 and 4.

Same results on the CAPT PFD.

10. ON the ADIRS CDU: - push the ADR1 and ADR2 pushbutton switches.

On the ADIRS CDU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off.

11. On the SWITCHING panel 8VU: - set the AIR DATA selector switch to NORM. 12. In the avionics compartment, on the panel 188VU: - set the L/G DOWN VMO/MMO SELECTION switch to NORM. - lock the safety cover and secure it with lockwire.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-239, 301-312, 401-499,   CES

 

Page 515 Feb 01/08

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-13-00-710-051-B A. OVERSPEED Warning VMO/MMO 1 (L/G DOWN VMO/MMO SELECTION Switch 22FP at NORM) NOTE : This test is for the VMO/MMO overspeed warning only. Ignore the ____ warnings and indications (VLE, ...) which are not related to this test. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead panel, on the ADIRS MSU: - Push the ADR2 and ADR3 pushbutton switches. 2. On the MCDU:

On the ADIRS MSU: - The OFF legend of the ADR2 and ADR3 pushbutton switches comes on. On the MCDU:

- Push the line key adjacent to the ADR1 indication.

- The ADR1 page comes into view.

- Push the line key adjacent to the OUTPUT TESTS indication.

- The ADR1 OUTPUT TESTS page comes into view.

- Push the line key adjacent to the INTERFACE TEST indication.

- The ADR1 INTERFACE TEST 1/2 page comes into view.

- On the keyboard push the NEXT PAGE function key.

- The ADR1 INTERFACE TEST 2/2 page comes into view.

- Push the line key adjacent to the START TEST indication.

From 0 to 10 seconds, ignore the warnings and indications. From 10 seconds and more, on the CAPT(F/O) PFD, the speed increases to 367.7 Kts. When the value is 354 Kts: - On the upper ECAM display unit, this indication is shown: OVERSPEED VMO/MMO 350/.82

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-13-00 511-526, 528-599,   CES

 

Page 516 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- On the F/O and CAPT glareshield panels 130VU and 131VU, the MASTER WARN lights flash. - You can hear the continuous repetitive chime aural warning. - Push the line key adjacent to the RETURN indication.

The test procedure stops. The warnings above stop.

- Push the line key adjacent to the RETURN indication.

The SYSTEM REPORT/TEST/NAV page comes into view.

3. On the ADIRS MSU: - Push the ADR2 pushbutton switch.

- The OFF legend of the ADR2 pushbutton switch goes off.

- Push the ADR1 pushbutton switch.

- The OFF legend of the ADR1 pushbutton switch comes on.

4. On the MCDU: - Push the line key adjacent to the ADR2 indication. Do the same test as specified in the para 2 and 3.

Same results on the F/O PFD.

5. On the ADIRS CDU: - Push the ADR3 pushbutton switch. 6. On the SWITCHING panel 8VU: - Set the AIR DATA selector switch to CAPT/3.

On the ADIRS CDU, the OFF legend of the ADR3 pushbutton switch goes off. On the CAPT PFD, the speed and altitude indications from the ADR3 come into view.

7. On the ADIRS MSU: - Push the ADR2 pushbutton switch.

On the ADIRS MSU, the OFF legend of the ADR2 pushbutton switch comes on.

8. On the MCDU:

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-13-00 511-526, 528-599,   CES

 

Page 517 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Push the line key adjacent to Same results on the CAPT PFD. the ADR3 indication. Do the same test as specified in the para 2 and 3. 9. On the ADIRS MSU: - Push the ADR1 and ADR2 pushbutton switches

On the ADIRS MSU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off.

10. On the SWITCHING panel 8VU: - Set the AIR DATA selector switch to NORM. Subtask 34-13-00-710-052-B B. OVERSPEED Warning VMO/MMO 2 (L/G DOWN VMO/MMO SELECTION Switch 22FP at L/G DOWN) ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. In the avionics compartment, on the panel 188VU: - Remove the lockwire from the safety cover of the L/G DOWN VMO/MMO SELECTION switch. - Set the switch to L/G DOWN. 2. In the cockpit on the overhead panel, on the ADIRS MSU: - Push the ADR2 and ADR3 pushbutton switches. 3. On the MCDU:

On the ADIRS MSU: - The OFF legend of the ADR2 and ADR3 pushbutton switches comes on. On the MCDU:

- Push the line key adjacent to the ADR1 indication.

- The ADR1 page comes into view.

- Push the line key adjacent to the OUTPUT TESTS indication.

- The ADR1 OUTPUT TESTS page comes into view.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-13-00 511-526, 528-599,   CES

 

Page 518 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Push the line key adjacent to - The ADR1 INTERFACE TEST 1/2 page the INTERFACE TEST indication. comes into view. - On the keyboard push the NEXT PAGE function key.

- The ADR1 INTERFACE TEST 2/2 page comes into view.

- Push the line key adjacent to the START TEST indication. (Ref. TASK 34-13-00-740-002).

From 0 to 10 seconds, ignore the warnings and indications. From 10 seconds and more, on the CAPT(F/O) PFD, the speed increases to 367.7 Kts. When the value is 239Kts: - On the upper ECAM display unit, this indication is shown: OVERSPEED VMO/MMO 235/.60 - On the F/O and CAPT glareshield panels 130VU and 131VU, the MASTER WARN lights flash. - You can hear the continuous repetitive chime aural warning.

- Push the line key adjacent to the RETURN indication.

The test procedure stops. The warnings above stop.

- Push the line key adjacent to the RETURN indication.

The SYSTEM REPORT/TEST/NAV page comes into view.

4. On the ADIRS MSU:

On the ADIRS MSU:

- Push the ADR2 pushbutton switch.

- The OFF legend of the ADR2 pushbutton switch goes off.

- Push the ADR1 pushbutton switch.

- The OFF legend of the ADR1 pushbutton switch comes on.

5. On the MCDU: - Push the line key adjacent to the ADR2 indication. Do the same test as specified in the para 3 and 4.

Same results on the F/O PFD.

6. On the ADIRS MSU:

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-13-00 511-526, 528-599,   CES

 

Page 519 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Push the ADR3 pushbutton On the ADIRS MSU, the OFF legend of the switch. ADR3 pushbutton switch goes off. 7. On the SWITCHING panel 8VU: - Set the AIR DATA selector switch to CAPT/3.

On the CAPT PFD, the speed and altitude indications from the ADR3 come into view.

8. On the ADIRS MSU: - Push the ADR2 pushbutton switch.

On the ADIRS MSU, the OFF legend of the ADR2 pushbutton switch comes on.

9. On the MCDU: - Push the line key adjacent to the ADR3 indication. Do the same test as specified in the para 3 and 4.

Same results on the CAPT PFD.

10. ON the ADIRS MSU: - Push the ADR1 and ADR2 pushbutton switches.

On the ADIRS MSU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off.

11. On the SWITCHING panel 8VU: - Set the AIR DATA selector switch to NORM. 12. In the avionics compartment, on the panel 188VU: - Set the L/G DOWN VMO/MMO SELECTION switch to NORM. - Lock the safety cover and secure it with lockwire.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-13-00 511-526, 528-599,   CES

 

Page 520 Feb 01/10

**ON A/C ALL 5. Close-up ________ Subtask 34-13-00-860-062 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). R R R R

(2) On the overhead panel : - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are pushed (on). The OFF legends are of.

R

(3) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

R

(4) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. Subtask 34-13-00-865-065 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 7XE, 5CC1, 5CC2 Subtask 34-13-00-860-060 C. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-13-00-410-052 D. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the protective cover on the battery power center 105VU. (3) Tighten the two screws. (4) Close the access door 822. (5) Remove the access platform(s).

  EFF : ALL  34-13-00    CES

 

Page 521 Aug 01/08

TASK 34-13-00-710-003 Operational Test of the ALT Comparison Warning WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Refer to the MPD TASK: 341300-04 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

circuit breaker(s) safety clip(s)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 31-60-00-860-002 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-13-00-860-063 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

  EFF : ALL  34-13-00   R  CES

 

Page 522 Feb 01/08

Subtask 34-13-00-865-066 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 121VU HYDRAULIC/LGCIU/SYS2 2GA Q35 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34 R Subtask 34-13-00-865-071 C. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 R Subtask 34-13-00-860-065 D. Aircraft Maintenance Configuration (1) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) When the circuit breakers 5CC1 and 5CC2 are open: - - the AUTO FLT FAC 1+2 FAULT message and the MASTER CAUT light come on - - you can hear the single chime. (4) Before the test, on the ECAM Control Panel, push the CLR key to clear the message. (5) On the glareshield 13VU, on the CAPT and F/O EFIS control sections of the FCU, set the mode selector switch to ROSE/NAV. (6) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV menu page. (Ref. TASK 31-32-00-860-010).

  EFF : ALL  34-13-00    CES

 

Page 523 May 01/09

4. Procedure _________ Subtask 34-13-00-710-053 A. Operational Test of the ALT Comparison Warning NOTE : This test is for the system 1. For the systems 2 and 3, use the ____ indications between parentheses. NOTE : For system 3, on the center pedestal, set the SWITCHING/AIR DATA ____ selector switch 15FP to CAPT (F/O) position; the CAPT (F/O) PFD shows the ADR3 indications. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the glareshield 13VU, on the CAPT and F/O EFIS control sections of the FCU: - pull the baro reference selector knob.

2. On the MCDU:

The baro display (above the baro reference selector knob) shows STD. The CAPT and F/O PFDs show the altitude related to the standard barometric pressure. Below this indication the PFDs show STD. On the MCDU:

- push the line key adjacent to the ADR1 (ADR2) (ADR3) indication.

- the ADR1 (ADR2) (ADR3) page comes into view.

- push the line key adjacent to the OUTPUT TESTS indication.

- the ADR1 (ADR2) (ADR3) OUTPUT TESTS page comes into view.

- push the line key adjacent to the SLEW TESTS indication.

- the ADR1 (ADR2) (ADR3) SLEW TESTS page comes into view.

- push the line key adjacent to the ALT DYNAMIC SLEW indication.

- the ADR1 (ADR2) (ADR3) ALT DYNAMIC SLEW page comes into view.

- on the keyboard, enter:

- the display shows:

  EFF : ALL  34-13-00   R  CES

 

Page 524 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------*the airfield altitude value / *the airfield altitude value / (airfield altitude value plus (airfield altitude value plus 1500) 1500) *(Example: for an airfield altitude value of 1800ft enter: 1800 / 3300). and push the line key adjacent to the ALT LIMITS (FT) indication. - on the keyboard, enter 1000 and push the line key adjacent to the ALT SLEW RATE (FT/MIN) indication.

- the display shows 1000.

- push the line key adjacent to The test starts: the UP (START SLEW) indication. - the ADR1 ALT DYNAMIC SLEW TEST page with SLEWING IN PROGRESS 90 S information comes into view. - On the CAPT (F/O) PFD the altitude increase. When the difference of altitude between the CAPT PFD and the F/O PFD is 650 ft approximately: - the vertical CHECK ALT indication comes into view on the two PFDs. - the upper ECAM DU shows this warning: NAV ALTI DISCREPANCY - on the glareshield panels 130VU and 131VU, the MASTER CAUT light comes on. - you can hear the single chime. On the MCDU: - at the end of the test, the END OF SLEWING indication comes into view. - push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. NOTE : After the ADR3 test, set ____ the AIR DATA selector switch 15FP to NORMAL.

  EFF : ALL  34-13-00   R  CES

 

Page 525 May 01/09

5. Close-up ________ Subtask 34-13-00-860-066 A. Put the aircraft back to its initial configuration. (1) On the CAPT and F/O EFIS control sections of the FCU, push the baro reference selector knob. (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). R Subtask 34-13-00-865-072 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2 R Subtask 34-13-00-860-064 C. Close Access (1) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (2) Make sure that the work area is clean and clear of tool(s) and other items. (3) Put the aircraft back to the serviceable condition.

  EFF : ALL  34-13-00    CES

 

Page 526 Aug 01/09

TASK 34-13-00-710-004 Operational Test of the ALT DYNAMIC SLEW TEST WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job This test simulates a change in altitude. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-13-00-860-067 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

  EFF : ALL  34-13-00   R  CES

 

Page 527 Feb 01/08

Subtask 34-13-00-010-058 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822 (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover Subtask 34-13-00-865-067 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU R R

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

  EFF : ALL  34-13-00    CES

 

N10 N09 N08 N07 N06 N05 N04 N03

Page 528 Feb 01/10

R

**ON A/C ALL Subtask 34-13-00-865-073 D. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 121VU AUTO FLT/FAC2/28VDC 5CC2 M19

R Subtask 34-13-00-860-069 E. Aircraft Maintenance Configuration (1) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (2) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). 4. Procedure _________ Subtask 34-13-00-710-054 A. Operational Test of the ALT DYNAMIC SLEW TEST NOTE : This test is for the system 1. For the other system(s), use the ____ indications between the parentheses. NOTE : This test is an example of the altitude ramp test. Ignore the ____ warnings which are the result of a difference in altitude between the CAPT and F/O PFD.

  EFF : ALL  34-13-00    CES

 

Page 529 Nov 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the glareshield 13VU, on the CAPT and F/O EFIS control sections of the FCU: - pull the baro reference selector knob.

2. On the MCDU:

the baro display (above the baro reference selector knob) shows STD. the CAPT and F/O PFDs show the altitude related to the standard barometric pressure and the STD indication. On the MCDU:

- push the line key adjacent to the ADR1 (ADR2) (ADR3) indication.

- the ADR1 (ADR2) (ADR3) page comes into view.

- push the line key adjacent to the OUTPUT TESTS indication.

- the ADR1 (ADR2) (ADR3) OUTPUT TESTS page comes into view.

- push the line key adjacent to the SLEW TESTS indication.

- the ADR1 (ADR2) (ADR3) SLEW TESTS page comes into view.

- push the line key adjacent to the ALT DYNAMIC SLEW indication.

- the ADR1 (ADR2) (ADR3) ALT DYNAMIC SLEW page comes into view.

- on the keyboard, enter 0/1500 and push the line key adjacent to the ALT LIMITS (FT) indication.

- the display shows 0/1500.

- on the keyboard, enter 1000 and push the line key adjacent to the ALT SLEW RATE (FT/MIN) indication.

- the display shows 1000.

- push the line key adjacent to the UP (START SLEW) indication.

The test starts: - the CAPT (F/O) PFD shows 0 ft and the altitude increases to 1500 ft in approximately 90 seconds.

  EFF : ALL  34-13-00   R  CES

 

Page 530 Feb 01/08

5. Close-up ________ Subtask 34-13-00-410-058 A. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s). R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-13-00-865-074 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2 **ON A/C ALL Subtask 34-13-00-860-068 C. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) On the CAPT and F/O EFIS control sections of the FCU, push the baro reference selector knob. (3) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-13-00    CES

 

Page 531 Feb 01/10

TASK 34-13-00-710-005 Operational Test of the CAS DYNAMIC SLEW TEST WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job This test simulates a change in airspeed. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

circuit breaker(s) safety clip(s) safety barriers access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-13-00-860-070 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

  EFF : ALL  34-13-00   R  CES

 

Page 532 Feb 01/08

Subtask 34-13-00-010-059 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822 (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover Subtask 34-13-00-865-068 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU R R

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

  EFF : ALL  34-13-00    CES

 

N10 N09 N08 N07 N06 N05 N04 N03

Page 533 Feb 01/10

R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-13-00-865-075 D. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 **ON A/C ALL Subtask 34-13-00-860-072 E. Aircraft Maintenance Configuration (1) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (2) on the center pedestal, on the MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). (3) Put the safety barriers in position around the RAT area. 4. Procedure _________ Subtask 34-13-00-710-055 A. Operational Test of the CAS DYNAMIC SLEW TEST NOTE : This test is for the system 1. For the other system(s), use the ____ indications between the parentheses. NOTE : This test is an example of the CAS ramp test. Ignore the warnings ____ which are the result of an overspeed.

  EFF : ALL  34-13-00    CES

 

Page 534 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On one MCDU:

On the MCDU:

- push the line key adjacent to the ADR1 (ADR2) (ADR3) indication.

- the ADR1 (ADR2) (ADR3) page comes into view.

- push the line key adjacent to OUTPUT TESTS indication.

- the ADR1 (ADR2) (ADR3) OUTPUT TESTS page comes into view.

- push the line key adjacent to SLEW TESTS indication.

- the ADR1 (ADR2) (ADR3) SLEW TESTS page comes into view.

- push the line key adjacent to the CAS DYNAMIC SLEW indication.

- the ADR1 (ADR2) (ADR3) CAS DYNAMIC SLEW page comes into view.

- on the keyboard, enter these limits: 175/225 and push the line key adjacent to the CAS LIMITS (FT) indication.

- the slew limits set come into view below the related indication.

- on the keyboard, enter this slew rate: 0020 and push the line key adjacent to the CAS SLEW RATE (FT/MIN) indication.

- the slew rate comes into view below the related indication.

- push the line key adjacent to the UP-START SLEW indication.

On the CAPT and F/O PFDs: - the speed scale moves from 175 Kts to 225 Kts. The warnings above stop.

5. Close-up ________ Subtask 34-13-00-410-059 A. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822.

  EFF : ALL  34-13-00   R  CES

 

Page 535 Feb 01/08

(4) Remove the access platform(s). R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-13-00-865-076 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2, 7XE **ON A/C ALL Subtask 34-13-00-860-071 C. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) Do a reset of each ELAC: - on the panel 49VU, open then close the ELAC1 C/B, - on the panel 121VU, open then close the ELAC2 C/B. (3) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-13-00    CES

 

Page 536 Feb 01/10

TASK 34-13-00-710-006 Operational Test of the AOA SENSOR TEST WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job This test controls the angle of attack (AOA) sensors to the special test position. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-10-00-710-007

Test of the Angle of Attack Warning

3. __________ Job Set-up Subtask 34-13-00-860-073 A. Not Applicable 4. Procedure _________ Subtask 34-13-00-710-060 A. Refer to the operational test of the angle of attack warning. (Ref. TASK 34-10-00-710-007)

  EFF : ALL  34-13-00   R  CES

 

Page 537 Feb 01/08

TASK 34-13-00-710-007 Operational Test of the Overspeed Warnings in the Slats/Flaps and Landing Gear Extended (VFE/VLE) Configuration NOTE : This test is for the system 1. For the systems 2 and 3, use the ____ indications between parentheses. 1. __________________ Reason for the Job Refer to the MPD TASK: 341300-03 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 29-10-00-863-001 29-10-00-863-002 29-10-00-863-003 29-10-00-864-001 29-10-00-864-002 29-10-00-864-003 31-32-00-860-010 31-60-00-860-001 31-60-00-860-002 32-22-00-010-001 32-22-00-410-001 34-10-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Pressurize the Green Hydraulic System Pressurize the Yellow Hydraulic System Pressurize the Blue Hydraulic System with a Ground Power Supply Depressurize the Green Hydraulic System Depressurize the Yellow Hydraulic System Depressurize the Blue Hydraulic System Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure Nose Gear Doors - Ground Doors Opening Nose Gear Doors - Ground Doors Closing ADIRS Start Procedure

  R EFF : ALL  34-13-00    CES

 

Page 538 Feb 01/08

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-10-00-860-005

ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-13-00-860-050 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Make sure that the nose landing gear doors are closed (Ref. TASK 32-22-00-410-001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) Pressurize (Ref. TASK (Ref. TASK (Ref. TASK

the aircraft hydraulic systems 29-10-00-863-001) 29-10-00-863-002) 29-10-00-863-003) (NOTE : You can use the electric pumps).

Subtask 34-13-00-860-052 B. Aircraft Maintenance Configuration (1) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (2) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). (3) On the overhead panel, on the FLT CTL panels 23VU and 24VU: - make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. (4) On the center pedestal (panel 114VU), set the flap and slat control lever to the FULL position. (5) On the panel 50VU, release the ENG/FADEC GND PWR/1 and ENG/FADEC GND PWR/2 pushbutton switches. The ON legends come on.

  R EFF : ALL  34-13-00    CES

 

Page 539 Feb 01/08

Subtask 34-13-00-010-060 C. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822 (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover Subtask 34-13-00-865-082 D. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

2GA

Q35

**ON A/C ALL 121VU HYDRAULIC/LGCIU/SYS2 R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU ADIRS/ADIRU/2PWR/SHED 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/2/26VAC AND AOA

10FP 9FP 5FP2

  EFF : ALL  34-13-00    CES

 

N10 N09 N08

Page 540 Feb 01/10

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03 R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-13-00-865-085 E. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 **ON A/C ALL Subtask 34-13-00-860-090 F. Aircraft Maintenance Configuration (1) On the center pedestal, on the ECAM control panel: - push the CLR key until the MASTER CAUT and MASTER WARN lights go off on the panels 131VU and 130VU. - push the CLR key until the memo section comes into view in the lower part of the upper ECAM display unit.

  EFF : ALL  34-13-00    CES

 

Page 541 Feb 01/10

4. Procedure _________ R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-13-00-710-057 A. Test of the VFE Overspeed Warning ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead panel 20VU, on the ADIRS CDU: - push the ADR2 and ADR3 pushbutton switches. 2. On the MCDU:

On the ADIRS CDU, the OFF legend of the ADR2 and ADR3 pushbutton switches comes on. On the MCDU:

- push the line key adjacent to the NAV indication

- the SYSTEM REPORT/TEST page which contains the three ADR comes into view.

- push the line key adjacent to the ADR1 (ADR2) (ADR3) indication

- the ADR1 (ADR2) (ADR3) page comes into view.

- push the line key adjacent to the OUTPUT TESTS indication

- the ADR1 (ADR2) (ADR3) OUTPUT TESTS page comes into view.

- push the line key adjacent to the SLEW TESTS indication

- the ADR1 (ADR2) (ADR3) SLEW TESTS page comes into view.

- push the line key adjacent to the CAS DYNAMIC SLEW indication

- the ADR1 (ADR2) (ADR3) CAS DYNAMIC SLEW page comes into view.

- on the keyboard, enter these limits: 175/260 - push the line key adjacent to the CAS LIMITS (KT) indication

The slew limits set come into view below the related indication.

- on the keyboard, enter this slew rate: 020

  EFF : ALL  34-13-00    CES

 

Page 542 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to The slew rate set comes into view below the CAS SLEW RATE (KTs/MIN) the related indication. indication - push the line key adjacent to the UP-START SLEW indication

R

On the CAPT (F/O) PFD, the speed scale moves from 175 kts to 260 kts as specified in the following table On the upper ECAM display unit, make sure that all the indications given in the table below come into view On the panels 130VU and 131VU, the MASTER WARN lights flash when the speeds set come into view The continuous repetitive chime sounds On the panels 130VU and 131VU, the MASTER WARN lights go off when you set the flap and slat control lever to a lower position.

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-13-00-710-057-B A. Test of the VFE Overspeed Warning ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the overhead panel, on the ADIRS MSU: - Push the ADR2 and ADR3 pushbutton switches. 2. On the MCDU: - Push the line key adjacent to the NAV indication.

On the ADIRS MSU, the OFF legend of the ADR2 and ADR3 pushbutton switches comes on. On the MCDU: - The SYSTEM REPORT/TEST page which contains the three ADR comes into view.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 543 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Push the line key adjacent to - The ADR1 (ADR2) (ADR3) page comes the ADR1 (ADR2) (ADR3) into view. indication. - Push the line key adjacent to the OUTPUT TESTS indication.

- The ADR1 (ADR2) (ADR3) OUTPUT TESTS page comes into view.

- Push the line key adjacent to the SLEW TESTS indication.

- The ADR1 (ADR2) (ADR3) SLEW TESTS page comes into view.

- Push the line key adjacent to the CAS DYNAMIC SLEW indication.

- The ADR1 (ADR2) (ADR3) CAS DYNAMIC SLEW page comes into view.

- On the keyboard, enter these limits: 175/260 - Push the line key adjacent to the CAS LIMITS (KT) indication.

The slew limits set come into view below the related indication.

- On the keyboard, enter this slew rate: 020 - Push the line key adjacent to the CAS SLEW RATE (KTs/MIN) indication.

The slew rate set comes into view below the related indication.

- Push the line key adjacent to the UP-START SLEW indication.

On the CAPT (F/O) PFD, the speed scale moves from 175 kts to 260 kts as specified in the following table. On the upper ECAM display unit, make sure that all the indications given in the table below come into view. On the F/O and CAPT glareshield panels 130VU and 131VU, the MASTER WARN lights flash when the speeds set come into view. The continuous repetitive chime sounds. On the F/O and CAPT glareshield panels 130VU and 131VU, the MASTER WARN lights go off when you set the flap and slat control lever to a lower position.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-13-00 511-526, 528-599,   CES

 

Page 544 Feb 01/10

R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-13-00-710-061 B. Speed values NOTE : Make sure that speed values are reached before you move the ____ flaps/slats control lever.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-249, 251-299, 401-499, 501-509, 511-526,  528-599, CES

 

Page 545 Feb 01/10

------------------------------------------------------------------------------| SLATS AND FLAPS | |---------------------------------| | | | SPEED | Position | Indication | INDICATION IS MORE | of CTL LEVER | on the upper | ON THE UPPER ECAM THAN | | ECAM DU | DISPLAY UNIT | | | ---------|----------------|----------------|----------------------------------181 Kts | FULL | FULL | OVERSPEED | | | - VFE 177 |----------------|----------------|----------------------------------| 3 | 3 | The indication goes out of view ---------|----------------|----------------|----------------------------------189 Kts | 3 | 3 | OVERSPEED | | | - VFE 185 |----------------|----------------|----------------------------------| 2 | 2 | The indication goes out of view ---------|----------------|----------------|----------------------------------204 Kts | 2 | 2 | OVERSPEED | | | - VFE 200 |----------------|----------------|----------------------------------| 1 | 1+F | The indication goes out of view ---------|----------------|----------------|----------------------------------219 Kts | 1 | 1+F | OVERSPEED | | | - VFE 215 ---------|----------------|----------------|----------------------------------234 Kts | 1 | 1+F | OVERSPEED (or equal) | | - VFE 215 |----------------|----------------|----------------------------------| | | When OVERSPEED | 0 | 0 | - VFE 215 | | | indication goes out of view: | | | OVERSPEED | | | - VFE 230 | | |this indication can come into view | | |for some seconds then goes out of | | |view. -------------------------------------------------------------------------------

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-249, 251-299, 401-499, 501-509, 511-526,  528-599, CES

 

Page 546 Feb 01/10

**ON A/C 301-399, Subtask 34-13-00-710-061-A B. Speed values NOTE : Make sure that speed values are reached before you move the ____ flaps/slats control lever.

  R EFF : 301-399,  34-13-00    CES

 

Page 547 Feb 01/08

R R

------------------------------------------------------------------------------| SLATS AND FLAPS | |---------------------------------| | | | SPEED | Position | Indication | INDICATION IS MORE | of CTL LEVER | on the upper | ON THE UPPER ECAM THAN | | ECAM DU | DISPLAY UNIT | | | ---------|----------------|----------------|----------------------------------194 Kts | FULL | FULL | OVERSPEED | | | - VFE 190 |----------------|----------------|----------------------------------| 3 | 3 | The indication goes out of view ---------|----------------|----------------|----------------------------------199 Kts | 3 | 3 | OVERSPEED | | | - VFE 195 |----------------|----------------|----------------------------------| 2 | 2 | The indication goes out of view ---------|----------------|----------------|----------------------------------219 Kts | 2 | 2 | OVERSPEED | | | - VFE 215 |----------------|----------------|----------------------------------| 1 | 1+F | The indication goes out of view | | | (215 be shown while some seconds | | | before the following indication.) ---------|----------------|----------------|----------------------------------229 Kts | 1 | 1+F | The indication | | | - VFE 225 | | | comes into view | | | ---------|----------------|----------------|----------------------------------239 Kts | 1 | 1+F | The indication | | | | | | - VFE 225 |----------------|----------------| goes out of view if the indication | | |

R R R R R R

| | | OVERSPEED | 0 | 0 | -VFE 235 | | | comes into view (for approximately ---------|----------------|----------------| 1 second) then goes out of view. When the OVERSPEED VFE 235 goes out of | view or if the OVERSPEED VFE 225 remained | displayed, move the control lever to the | position 1 before you reach CAS 254 Kts. | ---------|----------------|----------------|----------------------------------254 Kts | 1 | 1+F | OVERSPEED | | | -VFE 225 |----------------|----------------|-----------------------------------

  EFF : 301-399,  34-13-00    CES

 

Page 548 Feb 01/09

------------------------------------------------------------------------------| SLATS AND FLAPS | |---------------------------------| | | | SPEED | Position | Indication | INDICATION IS MORE | of CTL LEVER | on the upper | ON THE UPPER ECAM THAN | | ECAM DU | DISPLAY UNIT | | | ---------|----------------|----------------|----------------------------------| | | The indication goes out of view |----------------|----------------|----------------------------------| | | OVERSPEED | | | -VFE 235 | 0 | 0 |The indication comes into view for | | |some seconds then goes out of view. ------------------------------------------------------------------------------**ON A/C ALL Subtask 34-13-00-860-053 C. Depressurize the aircraft hydraulic systems (Ref. TASK 29-10-00-864-001) (Ref. TASK 29-10-00-864-002) (Ref. TASK 29-10-00-864-003). R

**ON A/C 001-049, 101-105, 151-199, 201-210, 301-312, 401-499, Subtask 34-13-00-710-059 D. Test of the VLE Overspeed Warning ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Open the nose landing gear doors (Ref. TASK 32-22-00-010-001). 2. On the overhead panel 20VU, on the ADIRS CDU: - push the ADR2 and ADR3 pushbutton switches. 3. On the MCDU:

On the ADIRS CDU, the OFF legend of the ADR2 and ADR3 pushbutton switches comes on. On the MCDU:

  EFF : ALL  34-13-00    CES

 

Page 549 May 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the ADR1 (ADR2) (ADR3) page comes the ADR1 (ADR2) (ADR3) into view. indication - push the line key adjacent to the OUTPUT TESTS indication

- the ADR1 (ADR2) (ADR3) OUTPUT TESTS page comes into view.

- push the line key adjacent to the SLEW TESTS indication

- the ADR1 (ADR2) (ADR3) SLEW TESTS page comes into view.

- push the line key adjacent to the CAS DYNAMIC SLEW indication

- the ADR1 (ADR2) (ADR3) CAS DYNAMIC SLEW page comes into view.

- on the keyboard, enter these limits: 275/290

- the slew limits come into view on the bottom line (scratch pad) of the MCDU.

- push the line key adjacent to the CAS LIMITS (FT) indication.

- the slew limits set come into view below the related indication.

- on the keyboard, enter this slew rate: 025

- the slew rate comes into view on the bottom line (scratch pad) of the MCDU.

- push the line key adjacent to the CAS SLEW RATE (FT/MIN) indication.

- the slew rate set comes into view below the related indication.

- push the line key adjacent to the UP-START SLEW indication

On the CAPT (F/O) PFD, the speed scale moves from 275 kts to 290 kts. On the upper ECAM display unit, when the CAS reaches 284 kts, make sure that this indication comes into view: OVERSPEED VLE...............280/.67 On the panels 130VU and 131VU, the MASTER WARN lights flash The continuous repetitive chime sounds.

- push the line key adjacent to the RETURN/STOP indication.

On the CAPT (F/O) PFD, the speed scale moves down On the panels 130VU and 131VU, the MASTER WARN lights do not flash The continuous repetitive chime stops.

  R EFF : 001-049, 101-105, 151-199, 201-210,  34-13-00 301-312, 401-499,   CES

 

Page 550 May 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------4. On the ADIRS CDU: On the ADIRS CDU: - push the ADR1 and ADR2 pushbutton switches.

- the OFF legend of the ADR1 pushbutton switch comes on - the OFF legend of the ADR2 pushbutton switch goes off.

5. Do the ADR2 test as specified in step 3.

Same results on the F/O side.

6. On the ADIRS CDU:

On the ADIRS CDU:

- push the ADR2 and ADR3 pushbutton switches.

- the OFF legend of the ADR2 pushbutton switch comes on - the OFF legend of the ADR3 pushbutton switch goes off.

7. On the SWITCHING panel 8VU: - set the AIR DATA selector switch to CAPT/3.

On the CAPT PFD, the speed and altitude indications from the ADR3 come into view.

8. Do the ADR3 test as specified in the step 3.

Same results on the CAPT side.

9. On the ADIRS CDU: - push the ADR1 and ADR2 pushbutton switches again

On the ADIRS CDU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off.

  R EFF : 001-049, 101-105, 151-199, 201-210,  34-13-00 301-312, 401-499,   CES

 

Page 551 May 01/08

R

**ON A/C 051-099, 106-149, 211-239,

R

Subtask 34-13-00-710-059-A

R

D. Test of the VLE Overspeed Warning

R R R

------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------

R R

1. Open the nose landing gear doors (Ref. TASK 32-22-00-010-001).

R R

2. On the overhead panel 20VU, on the ADIRS CDU:

R R R R

- push the ADR2 and ADR3 pushbutton switches. 3. On the MCDU:

On the ADIRS CDU, the OFF legend of the ADR2 and ADR3 pushbutton switches comes on. On the MCDU:

R R R

- push the line key adjacent to the ADR1 (ADR2) (ADR3) indication

- the ADIRS ADR1 (ADR2) (ADR3) 1/2 page comes into view.

R R

- on the keyboard, push the NEXT PAGE function key

- the ADIRS ADR1 (ADR2) (ADR3) 2/2 page comes into view.

R R R

- push the line key adjacent to the CAS DYNAMIC SLEW TEST indication

- the ADR1 (ADR2) (ADR3) SLEW TEST page comes into view.

R R R

- on the keyboard, enter these limits: 275/290

- the slew limits come into view on the bottom line (scratch pad) of the MCDU.

R R R

- push the line key adjacent to the SET CAS SLEW LIMITS indication

- the slew limits set come into view below the related indication.

R R R

- on the keyboard, enter this slew rate: 025

- the slew rate comes into view on the bottom line (scratch pad) of the MCDU.

  R EFF : 051-099, 106-149, 211-239,  34-13-00    CES

 

Page 552 May 01/08

R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the slew rate set comes into view the SET CAS SLEW RATE below the related indication. indication

R R R R R R R R R R

- push the line key adjacent to the UP-START SLEW indication

On the CAPT (F/O) PFD, the speed scale moves from 275 kts to 290 kts. On the upper ECAM display unit, when the CAS reaches 284 kts, make sure that this indication comes into view: OVERSPEED VLE...............280/.67 On the panels 130VU and 131VU, the MASTER WARN lights flash The continuous repetitive chime sounds.

R R R R R

- push the line key adjacent to the RETURN/STOP indication.

On the CAPT (F/O) PFD, the speed scale moves down On the panels 130VU and 131VU, the MASTER WARN lights do not flash The continuous repetitive chime stops.

R

4. On the ADIRS CDU:

R R R R

- push the ADR1 and ADR2 pushbutton switches.

On the ADIRS CDU: - the OFF legend of the ADR1 pushbutton switch comes on - the OFF legend of the ADR2 pushbutton switch goes off.

R R

5. Do the ADR2 test as specified in step 3.

Same results on the F/O side.

R

6. On the ADIRS CDU:

On the ADIRS CDU:

R R R R

- push the ADR2 and ADR3 pushbutton switches.

- the OFF legend of the ADR2 pushbutton switch comes on - the OFF legend of the ADR3 pushbutton switch goes off.

R R R

7. On the SWITCHING panel 8VU: - set the AIR DATA selector switch to CAPT/3.

On the CAPT PFD, the speed and altitude indications from the ADR3 come into view.

R R

8. Do the ADR3 test as specified in the step 3.

Same results on the CAPT side.

  R EFF : 051-099, 106-149, 211-239,  34-13-00    CES

 

Page 553 May 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------9. On the ADIRS CDU: - push the ADR1 and ADR2 pushbutton switches again R

On the ADIRS CDU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off.

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-13-00-710-059-B D. Test of the VLE Overspeed Warning ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Open the nose landing-gear doors (Ref. TASK 32-22-00-010-001). 2. On the overhead panel 20VU, on the ADIRS MSU: - Push the ADR2 and ADR3 pushbutton switches. 3. On the MCDU:

On the ADIRS MSU, the OFF legend of the ADR2 and ADR3 pushbutton switches comes on. On the MCDU:

- Push the line key adjacent to the ADR1 (ADR2) (ADR3) indication

- The ADR1 (ADR2) (ADR3) page comes into view.

- Push the line key adjacent to the OUTPUT TESTS indication

- The ADR1 (ADR2) (ADR3) OUTPUT TESTS page comes into view.

- Push the line key adjacent to the SLEW TESTS indication

- The ADR1 (ADR2) (ADR3) SLEW TESTS page comes into view.

- Push the line key adjacent to the CAS DYNAMIC SLEW indication

- The ADR1 (ADR2) (ADR3) CAS DYNAMIC SLEW page comes into view.

  R EFF : 051-099, 106-149, 211-249, 251-299,  34-13-00 313-399, 501-509, 511-526, 528-599,   CES

 

Page 554 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- On the keyboard, enter these - The slew limits come into view on the limits: 275/290 bottom line (scratch pad) of the MCDU. - Push the line key adjacent to the CAS LIMITS (FT) indication.

- The slew limits set come into view below the related indication.

- On the keyboard, enter this slew rate: 025

- The slew rate comes into view on the bottom line (scratch pad) of the MCDU.

- Push the line key adjacent to the CAS SLEW RATE (FT/MIN) indication.

- The slew rate set comes into view below the related indication.

- Push the line key adjacent to the UP-START SLEW indication

On the CAPT (F/O) PFD, the speed scale moves from 275 kts to 290 kts. On the upper ECAM display unit, when the CAS reaches 284 kts, make sure that this indication comes into view: OVERSPEED VLE...............280/.67 On the F/O and CAPT glareshield panels 130VU and 131VU, the MASTER WARN lights flash. The continuous repetitive chime sounds.

- Push the line key adjacent to the RETURN/STOP indication.

On the CAPT (F/O) PFD, the speed scale moves down. On the F/O and CAPT glareshield panels 130VU and 131VU, the MASTER WARN lights do not flash. The continuous repetitive chime stops.

4. On the ADIRS MSU: - Push the ADR1 and ADR2 pushbutton switches.

5. Do the ADR2 test as specified in step 3.

On the ADIRS MSU: - The OFF legend of the ADR1 pushbutton switch comes on. - The OFF legend of the ADR2 pushbutton switch goes off. Same results on the F/O side.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-13-00 511-526, 528-599,   CES

 

Page 555 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------6. On the ADIRS MSU: On the ADIRS MSU: - Push the ADR2 and ADR3 pushbutton switches.

- The OFF legend of the ADR2 pushbutton switch comes on. - The OFF legend of the ADR3 pushbutton switch goes off.

7. On the SWITCHING panel 8VU: - Set the AIR DATA selector switch to CAPT/3.

On the CAPT PFD, the speed and altitude indications from the ADR3 come into view.

8. Do the ADR3 test as specified in the step 3.

Same results on the CAPT side.

9. On the ADIRS MSU: - Push the ADR1 and ADR2 pushbutton switches again.

On the ADIRS MSU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off.

**ON A/C ALL 5. Close-up ________ Subtask 34-13-00-410-060 A. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

  R EFF : ALL  34-13-00    CES

 

Page 556 May 01/08

R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-13-00-865-083 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2, 7XE **ON A/C ALL Subtask 34-13-00-860-051 C. Put the aircraft back to its initial configuration. (1) Do the EIS STOP procedure (Ref. TASK 31-60-00-860-002). (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (4) De-energize the aircraft electrical circuit (Ref. TASK 24-41-00-862-002). (5) Close the nose landing gear doors (Ref. TASK 32-22-00-410-001).

  EFF : ALL  34-13-00    CES

 

Page 557 Feb 01/10

**ON A/C 001-049, 051-099, 101-105, 151-158, 201-209, TASK 34-13-00-720-009 Functional Test of the Altitude and Airspeed Data CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO _______ INSTRUMENTS: - THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg) - CHANGES IN STATIC PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE - DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED. CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE _______ STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg). 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R

No specific No specific No specific 36122 98D34003500000

circuit breaker(s) safety clip(s) colored adhesive tape 1 GENERATOR - GROUND PRESSURE MINI. 100 MB 3 ADAPTOR-CHARGING,PITOT PROBE 1 ADAPTER COVER-STATIC PORT

  EFF : 001-049, 051-099, 101-105, 151-158,  34-13-00 201-209,   CES

 

Page 558 Aug 01/09

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 27-50-00-866-009 31-60-00-860-001 34-10-00-860-002 34-10-00-860-005 34-11-15-200-001 34-13-00-790-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Retraction of the Flaps on the Ground EIS Start Procedure ADIRS Start Procedure ADIRS Stop Procedure Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3) Leak Test of the Principal Static and Total Air Data System

3. __________ Job Set-up Subtask 34-13-00-860-054 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (PFD DUs only) (Ref. TASK 31-60-00-860001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) On the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is at NORM. (5) Make sure that the flaps are fully retracted (Ref. TASK 27-50-00-866009). (6) On the FCU, set the CAPT (F/O) Baro-Correction to display STD below the altitude scale on the CAPT (F/O) PFD . (7) Do the Leak Test of the main Air Data System (Ref. TASK 34-13-00-790002).

  EFF : 001-049, 051-099, 101-105, 151-158,  34-13-00 201-209,  R  CES

 

Page 559 May 01/08

Subtask 34-13-00-865-086 B. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 Subtask 34-13-00-480-050 C. Install the Ground Pressure Generator NOTE : For this test, use a ground pressure generator with these minimum ____ requirement: - Static (altitude): -1000ft to 50,000ft (accuracy +/-0,31mb (0,00453psi)), - Pitot (speed): 0 to 500kts, - Mach Nbr: 0 to 1.000, - Climb Rate: 0 to +/- 6000ft/mn (accuracy +/- 7%). (1) Remove the slip on covers from the static probes and the pitot probes. R

(2) Connect the GENERATOR - GROUND PRESSURE MINI. 100 MB to the static and pitot probes of the aircraft: NOTE : For the CAPT and F/O circuits, it is necessary to connect the ____ ground pressure generator to the two static probes (L and R). For CAPT circuit (ADIRU 1) and F/O circuit (ADIRU 2), connect the ground pressure generator to the static probes with the ADAPTER COVER-STATIC PORT (98D34003500102): - L static probe 1 7DA1, zone 127, STA 8750, for the L static pressure ADM (19FP5) - L static probe 2 7DA2, zone 127, STA 8700, for the L static pressure ADM (19FP7) and

  EFF : 001-049, 051-099, 101-105, 151-158,  34-13-00 201-209,   CES

 

Page 560 Feb 01/09

- R static probe 1 8DA1, zone 128, STA 9300, for the R static pressure ADM (19FP4) - R static probe 2 8DA2, zone 128, STA 9350, for the R static pressure ADM (19FP6) For the standby circuit (ADIRU 3), connect the ground pressure generator to the static probes with the ADAPTER COVER-STATIC PORT (98D34003500100): - L static probe 3 7DA3, zone 121, STA 4250, for the static pressure ADM (19FP8) or - R static probe 3 8DA3, zone 122, STA 4250, for the static pressure ADM (19FP8). Connect the ground pressure generator to the pitot probes with the ADAPTOR-CHARGING,PITOT PROBE or equivalent: For CAPT circuit: - pitot probe 1 9DA1, zone 125, for the L total pressure ADM (19FP1).

R

For F/O circuit: - pitot probe 2 9DA2, zone 126, for the R total pressure ADM (19FP2). For the standby circuit: - pitot probe 3 9DA3, zone 125, for the standby total pressure ADM (19FP3). (3) Seal the drain holes of the pitot probes with a piece of platic and colored adhesive tape. CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT _______ SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE. ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE FIRST AND USE THE COLORED ADHESIVE TAPE TO ATTACH THE PLASTIC. IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE, THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE PROBE. (a) Seal the opposite static probe of the standby ADM with the ADAPTER COVER-STATIC PORT (98D34003500103). (4) Move the vane of the three AOA sensors to the upper position. Keep the AOA sensors in position with colored adhesive tape. (5) Start the ground pressure generator.

  EFF : 001-049, 051-099, 101-105, 151-158,  34-13-00 201-209,   CES

 

Page 561 Aug 01/09

4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, 201-209, Subtask 34-13-00-720-065 A. Functional Test of the Altitude and Airspeed Data ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ground pressure generator, set a static pressure and a total pressure as given in the table below.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 2.

2. On the SWITCHING panel 8VU: - set the AIR DATA selector to CAPT/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 and 2.

- set the AIR DATA selector to F/O/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 3.

3. At the end of the test, on the ground pressure generator: - slowly balance the pressure in the static and total pressure lines. - open the lines to get the atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

4. Stop the pressure generator.

  R EFF : 001-049, 051-099, 101-105, 151-158,  34-13-00 201-209,   CES

 

Page 562 May 01/08

R R R R R R

------------------------------------------------------------------------------Pressure | CAPT PFD and F/O PFD generator | AIR DATA switch at | AIR DATA switch | NORM | at CAPT/3 or F/O/3 ------------------------------|-----------------------|-----------------------Ps | Pt | QC |Hp 1/2|Vc 1/2 |Mach 1/2| Hp 3 | Vc 3 | Mach 3 (ft)|(hpa)| (ft)|(hpa)|Pt-Ps | (ft) | (Kts) | | (ft) |(Kts) | | | | | (hpa)| | +/- 2 | | | +/-2 | | | | | (Kts)| | | | | | -----|-----|-----|-----|------|------|-------|--------|------|------|---------5308|833.4| 1829|948,1|114.7 | 5000 | 250 |0.413(*)| 5406 | 264 | 0.439 (*) | | | |260.9 |+/-12 | |+/-0.004|+/- 12| |+/-0.004 -----|-----|-----|-----|------|------|-------|--------|------|------|---------10345|687.5| 6335|801.8|114.3 |10000 | 250 |0.452(*)| 10485| 264 | 0.482 (*) | | | |260.46|+/-15 | |+/-0.004|+/- 15| |+/-0.004 -----|-----|-----|-----|------|------|-------|--------|------|------|---------20498|456.0|13010|619.2|163.5 |20000 | 300 | 0.651 | 21135| 319 | 0.706 | | | |308.82|+/- 22| |+/-0.004|+/- 22| |+/-0.004 -----|-----|-----|-----|------|------|-------|--------|------|------|---------30517|293.9|20579|454.4|160.5 |30000 | 300 | 0.790 | 31847| 322 | 0.873 | | | |306.38|+/- 30| |+/-0.003|+/- 30| |+/-0.003 -----|-----|-----|-----|------|------|-------|--------|------|------|---------40489|183.2|30618|292.5|109.3 |40000 | 250 | 0.823 | 41764| 267 | 0.904 | | | |254.91|+/- 42| |+/-0.003|+/- 42| |+/-0.003 ------------------------------------------------------------------------------(*) These indications are not shown when the Mach value is less than 0.5. **ON A/C 151-158, Subtask 34-13-00-720-065-A A. Functional Test of the Altitude and Airspeed Data ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ground pressure generator, set a static pressure and a total pressure as given in the table below.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 2.

2. On the SWITCHING panel 8VU:

  EFF : 001-049, 051-099, 101-105, 151-158,  34-13-00 201-209,   CES

 

Page 563 Nov 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set the AIR DATA selector to On the CAPT and F/O PFDs, compare and CAPT/3. write the altitude and airspeed values for the ADIRU 3 and 2. - set the AIR DATA selector to F/O/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 3.

3. At the end of the test, on the ground pressure generator: - slowly balance the pressure in the static and total pressure lines. - open the lines to get the atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

4. Stop the pressure generator.

  R EFF : 151-158,  34-13-00    CES

 

Page 564 May 01/08

R R R R R R

------------------------------------------------------------------------------Pressure | CAPT PFD and F/O PFD generator | AIR DATA switch at | AIR DATA switch | NORM | at CAPT/3 or F/O/3 ------------------------------|-----------------------|-----------------------Ps | Pt | QC |Hp 1/2|Vc 1/2 |Mach 1/2| Hp 3 | Vc 3 | Mach 3 (ft)|(hpa)| (ft)|(hpa)|Pt-Ps | (ft) | (Kts) | | (ft) |(Kts) | | | | | (hpa)| | +/- 2 | | | +/-2 | | | | | (Kts)| | | | | | -----|-----|-----|-----|------|------|-------|--------|------|------|---------5257|835.0| 1829|948,1|113.1 | 5000 | 250 |0.413(*)| 5305 | 261 | 0.433 (*) | | | |259.14|+/-12 | |+/-0.004|+/- 12| |+/-0.004 -----|-----|-----|-----|------|------|-------|--------|------|------|---------10254|690.0| 6335|801.8|111.8 |10000 | 250 |0.452(*)| 10371| 261 | 0.475 (*) | | | |257.7 |+/-15 | |+/-0.004|+/- 15| |+/-0.004 -----|-----|-----|-----|------|------|-------|--------|------|------|---------20189|462.0|13010|619.2|157.2 |20000 | 300 | 0.651 | 20789| 314 | 0.690 | | | |303.7 |+/- 22| |+/-0.004|+/- 22| |+/-0.004 -----|-----|-----|-----|------|------|-------|--------|------|------|---------30055|300.1|20579|454.4|154.3 |30000 | 300 | 0.790 | 31363| 316 | 0.852 | | | |300.7 |+/- 30| |+/-0.003|+/- 30| |+/-0.003 -----|-----|-----|-----|------|------|-------|--------|------|------|---------40003|187.5|30618|292.5|105.0 |40000 | 250 | 0.823 | 41319| 263 | 0.884 | | | |250.02|+/- 42| |+/-0.003|+/- 42| |+/-0.003 ------------------------------------------------------------------------------(*) These indications are not shown when the Mach value is less than 0.5. **ON A/C 001-049, 051-099, 101-105, 151-158, 201-209, 5. Close-up ________ Subtask 34-13-00-080-050 A. Remove the ground support and maintenance equipment, the special and standard tools and all other items. Make sure that there is no remaining piece of plastic and/or adhesive tape on the pitot probes and AOA sensors. Make sure the pitot drain holes are operational and that the AOA sensors move freely.

  EFF : 001-049, 051-099, 101-105, 151-158,  34-13-00 201-209,   CES

 

Page 565 Nov 01/09

Subtask 34-13-00-865-088 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 Subtask 34-13-00-860-055 C. Put the aircraft back to its initial configuration. (1) Do a reset of each ELAC: - on the panel 49VU, open then close the ELAC1 C/B, - on the panel 121VU, open then close the ELAC2 C/B. (2) Install the slip on covers on the static probes and on the pitot probes. (3) Make sure that the drain holes on the pitot probes are not blocked by unwanted materials. (Ref. TASK 34-11-15-200-001) (4) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  R EFF : 001-049, 051-099, 101-105, 151-158,  34-13-00 201-209,   CES

 

Page 566 May 01/08

R R

**ON A/C 501-509, Post SB Post SB

001-049, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 511-526, 528-599, 34-1222 For A/C 001-049,101-105,151-158,201-209, 34-1252 For A/C 154-158,207-209,

TASK 34-13-00-720-009-A Functional Test of the Altitude and Airspeed Data (A/C with RVSM capability on three ADIRUs) CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO _______ INSTRUMENTS: - THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg) - CHANGES IN STATIC PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE - DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED. CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE _______ STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg). 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 36122 98D34003500000

circuit breaker(s) safety clip(s) colored adhesive tape 1 GENERATOR - GROUND PRESSURE MINI. 100 MB 3 ADAPTOR-CHARGING,PITOT PROBE 1 ADAPTER COVER-STATIC PORT

  R EFF : 001-049, 101-149, 151-199, 201-249,  34-13-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 567 Feb 01/10

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 27-50-00-866-009 31-60-00-860-001 34-10-00-860-002 34-10-00-860-005 34-11-15-200-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Retraction of the Flaps on the Ground EIS Start Procedure ADIRS Start Procedure ADIRS Stop Procedure Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3)

3. __________ Job Set-up Subtask 34-13-00-860-092 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (PFD DUs only) (Ref. TASK 31-60-00-860001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) On the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is at NORM. (5) Make sure that the flaps are fully retracted (Ref. TASK 27-50-00-866009). (6) On the FCU, set the CAPT (F/O) Baro-Correction to display STD below the altitude scale on the CAPT (F/O) PFD . Subtask 34-13-00-865-101 B. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED.

  R EFF : 001-049, 101-149, 151-199, 201-249,  34-13-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 568 Feb 01/10

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 Subtask 34-13-00-480-052 C. Install the Ground Pressure Generator NOTE : For this test, use a ground pressure generator with these minimum ____ requirements: - Static (altitude): -1000ft to 50,000ft (accuracy +/-0,1mb (0.00145psi) in positive t⁰), - Pitot (speed) : 0 to 500Kts, - Mach Nbr : 0 to 1.000, - Climb Rate : 0 to +/- 6000ft/mn (accuracy +/- 7%). (1) Remove the slip on covers from the static probes and the pitot probes. (2) Connect the GENERATOR - GROUND PRESSURE MINI. 100 MB to the static and pitot probes of the aircraft: NOTE : For the CAPT and F/O circuits, it is necessary to connect the ____ ground pressure generator to the two static probes (L and R). For CAPT circuit (ADIRU 1) and F/O circuit (ADIRU 2), connect the ground pressure generator to the static probes with the ADAPTER COVER-STATIC PORT (98D34003500102): - L static probe 1 7DA1, zone 127, STA 8750, for the L static pressure ADM (19FP5) - L static probe 2 7DA2, zone 127, STA 8700, for the L static pressure ADM (19FP7) and - R static probe 1 8DA1, zone 128, STA 9300, for the R static pressure ADM (19FP4) - R static probe 2 8DA2, zone 128, STA 9350, for the R static pressure ADM (19FP6) For the standby circuit (ADIRU 3), connect the ground pressure generator to the static probes with the ADAPTER COVER-STATIC PORT (98D34003500100):

  R EFF : 001-049, 101-149, 151-199, 201-249,  34-13-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 569 Feb 01/10

- L static pressure - R static pressure

probe 3 7DA3, zone 121, STA 4250, for the static ADM (19FP8) or probe 3 8DA3, zone 122, STA 4250, for the static ADM (19FP8).

Connect the ground pressure generator to the pitot probes with the ADAPTOR-CHARGING,PITOT PROBE or equivalent: For CAPT circuit: - pitot probe 1 9DA1, zone 125, for the L total pressure ADM (19FP1). For F/O circuit: - pitot probe 2 9DA2, zone 126, for the R total pressure ADM (19FP2). For the standby circuit: - pitot probe 3 9DA3, zone 125, for the standby total pressure ADM (19FP3). (3) Seal the drain holes of the pitot probes with a piece of plastic and colored adhesive tape. CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT _______ SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE. ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE FIRST AND USE THE COLORED ADHESIVE TAPE TO ATTACH THE PLASTIC. IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE, THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE PROBE. (a) Seal the opposite static probe of the standby ADM with the ADAPTER COVER-STATIC PORT (98D34003500103). (4) Move the vane of the three AOA sensors to the upper position. Keep the AOA sensors in position with colored adhesive tape. (5) Start the ground pressure generator.

  R EFF : 001-049, 101-149, 151-199, 201-249,  34-13-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 570 Feb 01/10

4. Procedure _________ **ON A/C 301-399, Subtask 34-13-00-720-063-C A. Functional Test of the Altitude and Airspeed Data ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ground pressure generator, set a static pressure and a total pressure as given in the tables below.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 2.

2. On the SWITCHING panel 8VU: - set the AIR DATA selector to CAPT/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the Trim 0) and the ADIRU 2.

- set the AIR DATA selector to F/O/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the Trim 0) and the ADIRU 1.

3. At the end of the test, on the ground pressure generator: - slowly balance the pressure in the static and total pressure lines. - open the lines to get the atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

4. Stop the pressure generator.

  R EFF : 001-049, 101-149, 151-199, 201-249,  34-13-00 251-299, 301-399, 401-499, 501-509, 511-522,  524-599, CES

 

Page 571 Nov 01/09

(1) ADIRUs 1 and 2

R R R R R R R R

-----------------------------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch at | AIR DATA switch | | | NORM | at CAPT/3 or F/O/3 | |------------------------------|-----------------------|---------------------| | Ps | Pt | QC |Hp 1/2| Vc 1/2|Mach 1/2| | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) | (Kts) | | For ADIRU 3 to get | | | | | | (hPa)| | +/- 2 | | | | | | | | (Kts)| | | | | |-----|-----|-----|-----|------|------|-------|--------| the correct values: | | 5392|830.8| 1828|948.1|117.3 | 5000 | 250 |0.412(*)| | | | | | |263.73|+/-12 | |+/-0.004| - use the placard | |-----|-----|-----|-----|------|------|-------|--------| | |10450|684.7| 6335|801.8|117.1 |10000 | 250 |0.452(*)| near the ADIRU3 and | | | | | |263.51|+/-15 | |+/-0.004| | |-----|-----|-----|-----|------|------|-------|--------| refer to the tables | |20822|449.8|13009|619.2|169.4 |20000 | 300 | 0.651 | | | | | | |314.32|+/- 22| |+/-0.004| that follow. | |-----|-----|-----|-----|------|------|-------|--------| | |31067|286,6|20579|454.4|167.8 |30000 | 300 | 0.790 | | | | | | |312.91|+/- 30| |+/-0.003| (in relation to the | |-----|-----|-----|-----|------|------|-------|--------| | |41086| 178 |30618|292.5|114.5 |40000 | 250 | 0.823 | Trim 0ft) | | | | | |260.68|+/- 42| |+/-0.003| | ------------------------------------------------------------------------------

  EFF : 301-399,  34-13-00    CES

 

Page 572 Nov 01/09

(2) ADIRU 3 (a) Aircraft with Trim = 0ft -------------------------------------------------------| Pressure | CAPT PFD and F/O PFD | | generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5392|830.8| 1828|948.1|117.3 | 5445 | 265 |0.442 (*)| | | | | |263.73|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10450|684.7| 6335|801.8|117.1 | 10565| 266 |0.487 (*)| | | | | |263.51|+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20822|449.8|13009|619.2|169.4 | 21535| 326 | 0.725 | | | | | |314.32|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |31067|286.6|20579|454.4|167.8 | 32455| 328 | 0.899 | | | | | |312.91|+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |41086| 178 |30618|292.5|114.5 | 42430| 272 | 0.932 | | | | | |260.68|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

  EFF : 301-399,  34-13-00    CES

 

Page 573 Nov 01/09

(*) These indications are not shown when the Mach value is less than 0.5. R

**ON A/C 501-509, 511-526, 528-599, Subtask 34-13-00-720-063-E A. Functional Test of the Altitude and Airspeed Data ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ground pressure generator, set a static pressure and a total pressure as given in the tables below.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 2.

2. On the SWITCHING panel 8VU: - set the AIR DATA selector to CAPT/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the Trim 0) and the ADIRU 2.

- set the AIR DATA selector to F/O/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the Trim 0) and the ADIRU 1.

3. At the end of the test, on the ground pressure generator: - slowly balance the pressure in the static and total pressure lines. - open the lines to get the atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

4. Stop the pressure generator.

  R EFF : 301-399, 501-509, 511-526, 528-599,  34-13-00    CES

 

Page 574 Feb 01/10

(1) ADIRUs 1 and 2 -----------------------------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch at | AIR DATA switch | | | NORM | at CAPT/3 or F/O/3 | |------------------------------|-----------------------|---------------------| | Ps | Pt | QC |Hp 1/2| Vc 1/2|Mach 1/2| | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | For ADIRU 3 to get | | | | | |(hPa) | | +/- 2| | | | | | | |(Kts) | | | | | |-----|-----|-----|-----|------|------|-------|--------| the correct value: | | 5308|833.4| 1828|948.1|114.7 | 5000 | 250 |0.413(*)| | | | | | |260.90|+/-12 | |+/-0.004| - use the placard | |-----|-----|-----|-----|------|------|-------|--------| | |10343|687.6| 6335|801.8|114.2 |10000 | 250 |0.452(*)| near the ADIRU3 and | | | | | |260.35|+/-15 | |+/-0.004| | |-----|-----|-----|-----|------|------|-------|--------| refer to the tables | |20461|456.7|13009|619.2|162.5 |20000 | 300 | 0.651 | | | | | | |308.19|+/- 22| |+/-0.004| that follow. | |-----|-----|-----|-----|------|------|-------|--------| | |30515|293.9|20581|454.4|160.5 |30000 | 300 | 0.790 | | | | | | |306.38|+/- 30| |+/-0.003| (in relation to the | |-----|-----|-----|-----|------|------|-------|--------| | |40487|183.2|30618|292.5|109.3 |40000 | 250 | 0.823 | Trim 0ft) | | | | | |254.91|+/- 42| |+/-0.003| | ------------------------------------------------------------------------------

  R EFF : 501-509, 511-526, 528-599,  34-13-00    CES

 

Page 575 Feb 01/10

(2) ADIRU 3 (a) Aircraft with Trim = 0ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5308|833.4| 1828| 948 |114.6 | 5406 | 264 |0.439 (*)| | | | | |260.90|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10343|687.6| 6335|801.8|114.2 | 10483| 264 |0.482 (*)| | | | | |260.35|+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20461|456.7|13009|619.2|162.5 | 21092| 319 | 0.706 | | | | | |308.19|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30515|293.9|20581|454.4|160.5 | 31845| 322 | 0.873 | | | | | |306.38|+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40487|183.2|30618|292.5|109.3 | 41761| 267 | 0.903 | | | | | | |+/- 42| |+/-0.003 | --------------------------------------------------------

  R EFF : 501-509, 511-526, 528-599,  34-13-00    CES

 

Page 576 Feb 01/10

(*) These indications are not shown when the Mach value is less than 0.5. **ON A/C 001-049, 101-105, 201-206, Subtask 34-13-00-720-063 A. Functional Test of the Altitude and Airspeed Data ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ground pressure generator, set a static pressure and a total pressure as given in the tables below.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 2.

2. On the SWITCHING panel 8VU: - set the AIR DATA selector to CAPT/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the applicable Trim) and the ADIRU 2.

- set the AIR DATA selector to F/O/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the applicable Trim) and the ADIRU 1.

3. At the end of the test, on the ground pressure generator: - slowly balance the pressure in the static and total pressure lines. - open the lines to get the atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

4. Stop the pressure generator.

  R EFF : 001-049, 101-105, 201-206, 501-509,  34-13-00 511-526, 528-599,   CES

 

Page 577 Feb 01/10

(1) ADIRUs 1 and 2

R R R R R R R R R R

-----------------------------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch at | AIR DATA switch | | | NORM | at CAPT/3 or F/O/3 | |------------------------------|-----------------------|---------------------| | Ps | Pt | QC |Hp 1/2| Vc 1/2|Mach 1/2| | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | For ADIRU 3 to get | | | | | |(hPa) | | +/- 2| | | | | | | |(Kts) | | | | | |-----|-----|-----|-----|------|------|-------|--------| the correct value: | | 5308|833.4| 1828|948.1|114.7 | 5000 | 250 |0.413(*)| | | | | | |260.9 |+/-12 | |+/-0.004| - use the placard | |-----|-----|-----|-----|------|------|-------|--------| | |10345|687.6| 6335|801.8|114.2 |10000 | 250 |0.452(*)|near the ADIRU 3 and | | | | | |260.35|+/-15 | |+/-0.004| | |-----|-----|-----|-----|------|------|-------|--------| refer to the tables | |20498| 456 |13009|619.2|163.2 |20000 | 300 | 0.651 | | | | | | |308.82|+/- 22| |+/-0.004| that follow. | |-----|-----|-----|-----|------|------|-------|--------| | |30515|293.9|20579|454.4|160.5 |30000 | 300 | 0.790 | | | | | | |306.38|+/- 30| |+/-0.003| (in relation to the | |-----|-----|-----|-----|------|------|-------|--------| | |40489|183.2|30618|292.5|109.3 |40000 | 250 | 0.823 | applicable Trim) | | | | | |254.91|+/- 42| |+/-0.003| | ------------------------------------------------------------------------------

  EFF : 001-049, 101-105, 201-206,  34-13-00    CES

 

Page 578 Nov 01/09

(2) ADIRU 3 (a) Aircraft with Trim = +250ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5308|833.4| 1828| 948 |114.6 | 5405 | 264 |0.439 (*)| | | | | |260.79|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10345|687.5| 6335|801.8|114.3 | 10485| 264 |0.482 (*)| | | | | |260.46|+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20498|456.0|13009|619.2|163.2 | 21291| 322 | 0.740 | | | | | |308.82|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30515|293.9|20579|454.4|160.5 | 32125| 325 | 0.885 | | | | | |306.38|+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40489|183.2|30618|292.5|109.3 | 42040| 269 | 0.915 | | | | | |254.91|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

  EFF : 001-049, 101-105, 201-206,  34-13-00    CES

 

Page 579 Nov 01/09

(b) Aircraft with Trim = +150ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5308|833.4| 1828| 948 |114.6 | 5405 | 264 |0.439 (*)| | | | | |260.79|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10345|687.5| 6335|801.8|114.3 | 10485| 264 |0.482 (*)| | | | | |260.46|+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20498|456.0|13009|619.2|163.2 | 21230| 321 | 0.711 | | | | | |308.82|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30515|293.9|20579|454.4|160.5 | 32010| 324 | 0.881 | | | | | |306.38|+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40489|183.2|30618|292.5|109.3 | 41930| 268 | 0.911 | | | | | |254.91|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

  EFF : 001-049, 101-105, 201-206,  34-13-00    CES

 

Page 580 Nov 01/09

(c) Aircraft with Trim = 0ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5308|833.4| 1828|948.1|114.7 | 5406 | 265 |0.439 (*)| | | | | |260.9 |+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10345|687.6| 6335|801.8|114.2 | 10483| 264 |0.482 (*)| | | | | |260.35|+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20498| 456 |13009|619.2|163.2 | 21135| 319 | 0.706 | | | | | |308.82|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30515|293.9|20579|454.4|160.5 | 31845| 322 | 0.873 | | | | | |306.38|+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40489|183.2|30618|292.5|109.3 | 41761| 267 | 0.903 | | | | | |254.91|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

  EFF : 001-049, 101-105, 201-206,  34-13-00    CES

 

Page 581 Nov 01/09

(d) Aircraft with Trim = -150ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5308|833.4| 1828| 948 |114.6 | 5405 | 264 |0.439 (*)| | | | | |260.79|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10345|687.5| 6335|801.8|114.3 | 10485| 265 |0.462 (*)| | | | | |260.46|+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20498|456.0|13009|619.2|163.2 | 21050| 318 | 0.702 | | | | | |308.82|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30515|293.9|20579|454.4|160.5 | 31685| 320 | 0.866 | | | | | |306.38|+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40489|183.2|30618|292.5|109.3 | 41600| 265 | 0.896 | | | | | |254.91|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

  EFF : 001-049, 101-105, 201-206,  34-13-00    CES

 

Page 582 Nov 01/09

(e) Aircraft with Trim = -250ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hpa)| (ft)|(hpa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5308|833.4| 1828| 948 |114.6 | 5405 | 264 |0.439 (*)| | | | | |260.79|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10345|687.5| 6335|801.8|114.3 | 10485| 265 |0.482 (*)| | | | | |260.46|+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20498|456.0|13009|619.2|163.2 | 21005| 317 | 0.7 | | | | | |308.82|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30515|293.9|20579|454.4|160.5 | 31580| 319 | 0.862 | | | | | |306.38|+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40489|183.2|30618|292.5|109.3 | 41500| 264 | 0.892 | | | | | |254.91|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R

(*) These indications are not shown when the Mach value is less than 0.5.

  R EFF : 001-049, 101-105, 201-206,  34-13-00    CES

 

Page 583 Nov 01/09

**ON A/C 106-149, 207-249, 251-299, Subtask 34-13-00-720-063-B A. Functional Test of the Altitude and Airspeed Data ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ground pressure generator, set a static pressure and a total pressure as given in the tables below.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 2.

2. On the SWITCHING panel 8VU: - set the AIR DATA selector to CAPT/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the Trim 0) and the ADIRU 2.

- set the AIR DATA selector to F/O/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the Trim 0) and the ADIRU 1.

3. At the end of the test, on the ground pressure generator: - slowly balance the pressure in the static and total pressure lines. - open the lines to get the atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

4. Stop the pressure generator.

  EFF : 106-149, 207-249, 251-299,  34-13-00   R  CES

 

Page 584 Nov 01/09

(1) ADIRUs 1 and 2

R R R R R R R R

-----------------------------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch at | AIR DATA switch | | | NORM | at CAPT/3 or F/O/3 | |------------------------------|-----------------------|---------------------| | Ps | Pt | QC |Hp 1/2| Vc 1/2|Mach 1/2| | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | For ADIRU 3 to get | | | | | |(hPa) | | +/- 2| | | | | | | | | | | | | |-----|-----|-----|-----|------|------|-------|--------| the correct value: | | 5308|833.4| 1828|948.1|114.7 | 5000 | 250 |0.413(*)| | | | | | |260.90|+/-12 | |+/-0.004| - use the placard | |-----|-----|-----|-----|------|------|-------|--------| | |10345|687.6| 6335|801.8|114.2 |10000 | 250 |0.452(*)| near the ADIRU3 and | | | | | |260.35|+/-15 | |+/-0.004| | |-----|-----|-----|-----|------|------|-------|--------| refer to the tables | |20498| 456 |13009|619.2|163.2 |20000 | 300 | 0.651 | | | | | | |308.82|+/- 22| |+/-0.004| that follow. | |-----|-----|-----|-----|------|------|-------|--------| | |30515|293.9|20579|454.4|160.5 |30000 | 300 | 0.790 | | | | | | |306.38|+/- 30| |+/-0.003| (in relation to the | |-----|-----|-----|-----|------|------|-------|--------| | |40489|183.2|30618|292.5|109.3 |40000 | 250 | 0.823 | Trim 0ft) | | | | | |254.91|+/- 42| |+/-0.003| | ------------------------------------------------------------------------------

  EFF : 106-149, 207-249, 251-299,  34-13-00    CES

 

Page 585 Nov 01/09

(2) ADIRU 3 (a) Aircraft with Trim = 0ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5308|833.4| 1828|948.1|114.7 | 5406 | 265 |0.439 (*)| | | | | |260.9 |+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10345|687.6| 6335|801.8|114.2 | 10483| 265 |0.482 (*)| | | | | |260.35|+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20498| 456 |13009|619.2|163.2 | 21135| 319 | 0.706 | | | | | |308.82|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30515|293.9|20579|454.4|160.5 | 31845| 322 | 0.873 | | | | | |306.38|+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40489|183.2|30618|292.5|109.3 | 41761| 267 | 0.903 | | | | | |254.91|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

  EFF : 106-149, 207-249, 251-299,  34-13-00    CES

 

Page 586 Nov 01/09

(*) These indications are not shown when the Mach value is less than 0.5. **ON A/C 151-153, Subtask 34-13-00-720-063-A A. Functional Test of the Altitude and Airspeed Data ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ground pressure generator, set a static pressure and a total pressure as given in the tables below.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 2.

2. On the SWITCHING panel 8VU: - set the AIR DATA selector to CAPT/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the applicable Trim) and the ADIRU 2.

- set the AIR DATA selector to F/O/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the applicable Trim) and the ADIRU 1.

3. At the end of the test, on the ground pressure generator: - slowly balance the pressure in the static and total pressure lines. - open the lines to get the atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

4. Stop the pressure generator.

  R EFF : 106-149, 151-153, 207-249, 251-299,  34-13-00    CES

 

Page 587 Nov 01/08

(1) ADIRUs 1 and 2

R R R R R R R R

-----------------------------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch at | AIR DATA switch | | | NORM |at CAPT/3 or F/O/3 | |------------------------------|-----------------------|---------------------| | Ps | Pt | QC |Hp 1/2| Vc 1/2|Mach 1/2| | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | For ADIRU 3 to get | | | | | | (hPa)| | +/- 2| | | | | | | | (Kts)| | | | | |-----|-----|-----|-----|------|------|-------|--------| the correct value: | | 5257| 835 | 1827|948.1|113.1 |5000 | 250 |0.413(*)| | | | | | |259.14|+/-12 | |+/-0.004| - use the placard | |-----|-----|-----|-----|------|------|-------|--------| | |10253| 690 | 6335|801.8|111.8 |10000 | 250 |0.452(*)| near the ADIRU3 and | | | | | |257.7 |+/-15 | |+/-0.004| | |-----|-----|-----|-----|------|------|-------|--------| refer to the tables | |20192|461.9|13009|619.2|157.3 |20000 | 300 | 0.651 | | | | | | |303.46|+/- 22| |+/-0.004| that follow. | |-----|-----|-----|-----|------|------|-------|--------| | |30058|300.1|20576|454.5|154.4 |30000 | 300 | 0.791 | | | | | | |300.7 |+/- 30| |+/-0.003| (in relation to the | |-----|-----|-----|-----|------|------|-------|--------| | |40004|187.5|30620|292.5| 105 |39995 | 250 | 0.823 | applicable Trim) | | | | | |250.02|+/- 42| |+/-0.003| | ------------------------------------------------------------------------------

  EFF : 151-153,  34-13-00    CES

 

Page 588 Nov 01/09

(2) ADIRU 3 (a) Aircraft with Trim = +250ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5257| 835 | 1827|948.1|113.1 | 5305 | 261 |0.433 (*)| | | | | |259.14|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10253| 690 | 6335|801.8|111.8 | 10370| 261 |0.475 (*)| | | | | |257.7 |+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20192|461.9|13009|619.2|157.3 | 20940| 316 | 0.697 | | | | | |303.46|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30058|300.1|20583|454.5|154.4 | 31630| 319 | 0.863 | | | | | |300.7 |+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40004|187.5|30618|292.5| 105 | 41595| 265 | 0.896 | | | | | |250.02|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

  EFF : 151-153,  34-13-00    CES

 

Page 589 Nov 01/09

(b) Aircraft with Trim = +150ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | |-----|-----|-----|-----|------|------|------|---------| | 5257| 835 | 1827|948.1|113.1 | 5305 | 261 |0.433 (*)| | | | | |259.14|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10253| 690 | 6335|801.8|111.8 | 10370| 261 |0.475 (*)| | | | | |257.7 |+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20192|461.9|13009|619.2|157.3 | 20860| 315 | 0.694 | | | | | |303.46|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30058|300.1|20583|454.5|154.4 | 31520| 318 | 0.859 | | | | | |300.7 |+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40004|187.5|30618|292.5| 105 | 41485| 264 | 0.891 | | | | | |250.02|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R

  EFF : 151-153,  34-13-00    CES

 

Page 590 Nov 01/09

(c) Aircraft with Trim = 0ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5257| 835 | 1827|948.1|113.1 | 5305 | 261 |0.433 (*)| | | | | |259.14|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10253| 690 | 6335|801.8|111.8 |10370 | 261 |0.475 (*)| | | | | |257.7 |+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20192|461.9|13009|619.2|157.3 |20790 | 314 | 0.690 | | | | | |303.46|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30058|300.1|20583|454.5|154.4 |31340 | 316 | 0.851 | | | | | |300.7 |+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40004|187.5|30618|292.5| 105 |41320 | 263 | 0.883 | | | | | |250.02|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

  EFF : 151-153,  34-13-00    CES

 

Page 591 Nov 01/09

(d) Aircraft with Trim = -150ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5257| 835 | 1827|948.1|113.1 | 5305 | 261 |0.433 (*)| | | | | |259.14|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10253| 690 | 6335|801.8|111.8 | 10370| 261 |0.475 (*)| | | | | |257.7 |+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20192|461.9|13009|619.2|157.3 | 20720| 313 | 0.686 | | | | | |303.46|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30058|300.1|20583|454.5|154.4 | 31210| 314 | 0.845 | | | | | |300.7 |+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40004|187.5|30618|292.5| 105 | 41160| 261 | 0.877 | | | | | |250.02|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

  EFF : 151-153,  34-13-00    CES

 

Page 592 Nov 01/09

(e) Aircraft with Trim = -250ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5257| 835 | 1827|948.1|113.1 | 5305 | 261 |0.433 (*)| | | | | |259.14|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10253| 690 | 6335|801.8|111.8 | 10370| 261 |0.475 (*)| | | | | |257.7 |+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20192|461.9|13009|619.2|157.3 | 20680| 312 | 0.685 | | | | | |303.46|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30058|300.1|20583|454.5|154.4 | 31110| 313 | 0.840 | | | | | |300.7 |+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40004|187.5|30618|292.5| 105 | 41060| 260 | 0.872 | | | | | |250.02|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

(*) These indications are not shown when the Mach value is less than 0.5.

  R EFF : 151-153,  34-13-00    CES

 

Page 593 Nov 01/09

**ON A/C 154-199, 401-499, Subtask 34-13-00-720-063-D A. Functional Test of the Altitude and Airspeed Data ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ground pressure generator, set a static pressure and a total pressure as given in the tables below.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 1 and 2.

2. On the SWITCHING panel 8VU: - set the AIR DATA selector to CAPT/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the Trim 0ft) and the ADIRU 2.

- set the AIR DATA selector to F/O/3.

On the CAPT and F/O PFDs, compare and write the altitude and airspeed values for the ADIRU 3 (in relation to the Trim 0ft) and the ADIRU 1.

3. At the end of the test, on the ground pressure generator: - slowly balance the pressure in the static and total pressure lines. - open the lines to get the atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

4. Stop the pressure generator.

  EFF : 154-199, 401-499,  34-13-00   R  CES

 

Page 594 Nov 01/09

(1) ADIRUs 1 and 2

R R R R R R R R

-----------------------------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch at | AIR DATA switch | | | NORM |at CAPT/3 or F/O/3 | |------------------------------|-----------------------|---------------------| | Ps | Pt | QC |Hp 1/2| Vc 1/2|Mach 1/2| | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | For ADIRU 3 to get | | | | | | (hPa)| | +/- 2| | | | | | | | (Kts)| | | | | |-----|-----|-----|-----|------|------|-------|--------| the correct values: | | 5257| 835 | 1827|948.1|113.1 |5000 | 250 |0.413(*)| | | | | | |259.14|+/-12 | |+/-0.004| - use the placard | |-----|-----|-----|-----|------|------|-------|--------| | |10253| 690 | 6335|801.8|111.8 |10000 | 250 |0.452(*)| near the ADIRU3 and | | | | | |257.7 |+/-15 | |+/-0.004| | |-----|-----|-----|-----|------|------|-------|--------| refer to the tables | |20192|461.9|13009|619.2|157.3 |20000 | 300 | 0.651 | | | | | | |303.46|+/- 22| |+/-0.004| that follow. | |-----|-----|-----|-----|------|------|-------|--------| | |30058|300.1|20576|454.5|154.4 |30000 | 300 | 0.791 | | | | | | |300.7 |+/- 30| |+/-0.003| (in relation to the | |-----|-----|-----|-----|------|------|-------|--------| | |40004|187.5|30620|292.5| 105 |39995 | 250 | 0.823 | Trim 0ft) | | | | | |250.02|+/- 42| |+/-0.003| | ------------------------------------------------------------------------------

  EFF : 154-199, 401-499,  34-13-00    CES

 

Page 595 Nov 01/09

(2) ADIRU 3 (a) Aircraft with Trim = 0ft -------------------------------------------------------| | CAPT PFD and F/O PFD | | Pressure generator | AIR DATA switch | | | at CAPT/3 or F/O/3 | |------------------------------|-----------------------| | Ps | Pt | QC | Hp 3 | Vc 3 | Mach 3 | | (ft)|(hPa)| (ft)|(hPa)|Pt-Ps | (ft) |(Kts) | | | | | | | (hPa)| | +/-2 | | | | | | | (Kts)| | | | |-----|-----|-----|-----|------|------|------|---------| | 5257| 835 | 1827|948.1|113.1 | 5305 | 261 |0.433 (*)| | | | | |259.14|+/- 12| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |10253| 690 | 6335|801.8|111.8 |10370 | 261 |0.475 (*)| | | | | |257.7 |+/- 15| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |20192|461.9|13009|619.2|157.3 |20790 | 314 | 0.690 | | | | | |303.46|+/- 22| |+/-0.004 | |-----|-----|-----|-----|------|------|------|---------| |30058|300.1|20583|454.5|154.4 |31340 | 316 | 0.851 | | | | | |300.7 |+/- 30| |+/-0.003 | |-----|-----|-----|-----|------|------|------|---------| |40004|187.5|30618|292.5| 105 |41320 | 263 | 0.883 | | | | | |250.02|+/- 42| |+/-0.003 | --------------------------------------------------------

R R R R R R R R

  EFF : 154-199, 401-499,  34-13-00    CES

 

Page 596 Nov 01/09

(*) These indications are not shown when the Mach value is less than 0.5. R R

**ON A/C 001-049, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 5. Close-up ________ Subtask 34-13-00-080-052 A. Remove the ground support and maintenance equipment, the special and standard tools and all other items. Make sure that there is no remaining piece of plastic and/or adhesive tape on the pitot probes and AOA sensors. Make sure the pitot drain holes are operational and that the AOA sensors move freely. Subtask 34-13-00-865-102 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 Subtask 34-13-00-860-093 C. Put the aircraft back to its initial configuration. (1) Do a reset of each ELAC: - on the panel 49VU, open then close the ELAC1 C/B, - on the panel 121VU, open then close the ELAC2 C/B. (2) Install the slip on covers on the static probes and on the pitot probes. (3) Make sure that the drain holes on the pitot probes are not blocked by unwanted materials. (Ref. TASK 34-11-15-200-001) (4) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  R EFF : 001-049, 101-149, 151-199, 201-249,  34-13-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 597 Feb 01/10

INTENTIONALLY BLANK

  R   34-13-00    CES

 

Page 598 Nov 01/09

**ON A/C ALL TASK 34-13-00-790-002 Leak Test of the Principal Static and Total Air Data System WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU _______ START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE _______ CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM. AUTOMATIC MOVEMENT OF THE FLIGHT CONTROL SURFACES CAN BE DANGEROUS AND/OR CAUSE DAMAGE. CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO _______ INSTRUMENTS: - THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg) - CHANGES IN STATIC PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE - DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED. CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE _______ STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg). 1. __________________ Reason for the Job To make sure that there are no leaks in the Captain and the First Officer pitot and static circuits.

  EFF : ALL  34-13-00   R  CES

 

Page 599 Aug 01/08

2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R

No specific No specific No specific 36122 98D34003500000

circuit breaker(s) safety clip(s) colored adhesive tape 1 GENERATOR - GROUND PRESSURE MINI. 100 MB 2 ADAPTOR-CHARGING,PITOT PROBE 1 ADAPTER COVER-STATIC PORT

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 27-50-00-866-009 31-60-00-860-001 34-10-00-860-005 34-11-15-200-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Retraction of the Flaps on the Ground EIS Start Procedure ADIRS Stop Procedure Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3)

3. __________ Job Set-up Subtask 34-13-00-860-074 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 34-13-00-865-061 B. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED.

  EFF : ALL  34-13-00    CES

 

Page A500 Aug 01/09

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 R

**ON A/C 001-049, 051-099, 101-105, 151-199, Subtask 34-13-00-480-051 C. Installation of the Main Air Data System (1) Remove the slip on covers from the static probes and the pitot probes of the main system. (2) Connect the static port of the GENERATOR - GROUND PRESSURE MINI. 100 MB to the static probes with the ADAPTER COVER-STATIC PORT (98D34003500102). For CAPT circuit (ADIRU 1) and F/O circuit (ADIRU 2): - L static probe 1 7DA1, zone 127, STA 8750, for the LH static pressure ADM (19FP5) - L static probe 2 7DA2, zone 127, STA 8700, for the LH static pressure ADM (19FP7) and - R static probe 1 8DA1, zone 128, STA 9300, for the RH static pressure ADM (19FP4) - R static probe 2 8DA2, zone 128, STA 9350, for the RH static pressure ADM (19FP6). (3) Connect the ground pressure generator to the pitot probe with the ADAPTOR-CHARGING,PITOT PROBE. For CAPT circuit: - pitot probe 1 9DA1, zone 125 For F/O circuit: - pitot probe 2 9DA2, zone 126.

  EFF : ALL  34-13-00    CES

 

Page A501 Nov 01/09

(4) Seal the drain holes: CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT _______ SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE. ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE FIRST AND USE THE COLORED ADHESIVE TAPE TO ATTACH THE PLASTIC. IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE, THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE PROBE. Seal the drain holes of the pitot probes with a piece of plastic and/or colored adhesive tape of very bright color. (5) Move the vane of the AOA sensors 1 and 2 to the upper position. Maintain the vane in position with colored adhesive tape. R R

**ON A/C 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-13-00-480-051-A C. Installation of the Main Air Data System (1) Remove the slip on covers from the static probes and the pitot probes of the main system. (2) Connect the static port of the GENERATOR - GROUND PRESSURE MINI. 100 MB to the static probes with the ADAPTER COVER-STATIC PORT (98D34003500102). For CAPT circuit (ADIRU 1) and F/O circuit (ADIRU 2): - L static probe 1 7DA1, zone 127, STA 8750, for the LH static pressure ADM (19FP5) - L static probe 2 7DA2, zone 127, STA 8700, for the LH static pressure ADM (19FP7) and - R static probe 1 8DA1, zone 128, STA 9300, for the RH static pressure ADM (19FP4) - R static probe 2 8DA2, zone 128, STA 9350, for the RH static pressure ADM (19FP6). (3) Connect the ground pressure generator to the pitot probe with the ADAPTOR-CHARGING,PITOT PROBE. For CAPT circuit: - pitot probe 1 9DA1, zone 125 For F/O circuit:

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page A502 Feb 01/10

- pitot probe 2 9DA2, zone 126. (4) Move the vane of the AOA sensors 1 and 2 to the upper position. Maintain the vane in position with colored adhesive tape. **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-13-00-860-076 D. Aircraft Maintenance Configuration (1) Do the EIS start procedure (PFD only) (Ref. TASK 31-60-00-860-001). (2) Make sure that the flaps are in the fully retracted position (Ref. TASK 27-50-00-866-009). (3) On the ADIRS CDU ,set the OFF/NAV/ATT selector switches to NAV. (4) Start the ground pressure generator. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-13-00-860-076-A D. Aircraft Maintenance Configuration (1) Do the EIS start procedure (PFD only) (Ref. TASK 31-60-00-860-001). (2) Make sure that the flaps are in the fully retracted position (Ref. TASK 27-50-00-866-009). (3) On the ADIRS MSU ,set the OFF/NAV/ATT selector switches to NAV. (4) Start the ground pressure generator.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page A503 Feb 01/10

**ON A/C ALL 4. Procedure _________ R R

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 501-509, 511-526, 528-599, Subtask 34-13-00-790-050 A. Leak Test of the Main Air Data System NOTE : You can do the test below for a static pressure of 691.4 hPa and ____ an impact pressure of 59 hPa (or a total pressure of 750.4 hPa) but it is less accurate. Make sure that: - the CAPT (or F/O) PFD shows the altitude value 10,000ft +/-30ft and the airspeed value 180kts +/-3kts. After 5 min: - the change of altitude must not be more than 275 ft. - the change of speed must not be more than 10 Kts. NOTE : The input parameters for the ground test (speed and altitude) and ____ the values shown on the cockpit displays are different because of the sum of the tolerances of the air data circuit (ground test unit, ADMs, ADIRUs). ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the glareshield 13VU ,on the EFIS control section of the FCU, set a barometric pressure of 1013 hPa. 2. On the ground pressure generator: - set a static pressure of 455.4 hPa. - set an impact pressure of 186.4 hPa (or a total pressure of 641.8 hPa). 3. Close the electrovalves to isolate the static and total

- Make sure that: the CAPT (or F/O) PFD shows the

  EFF : ALL  34-13-00    CES

 

Page A504 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------pressure lines of the aircraft altitude value 20,000ft +/-40ft and from the pressure generator. the airspeed value 320kts +/-3kts. After 5 minutes, on the CAPT (or F/O) PFD: - make sure that the change of altitude is not more than 320 ft. After 10 minutes, on the CAPT (or F/O) PFD: - make sure that the change of speed is not more than 10 Kts. 4. On the pressure generator: - slowly balance the pressure in the main static and total pressure lines - open the electrovalves to get atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

5. Stop the pressure generator. **ON A/C 151-199, 401-499, Subtask 34-13-00-790-050-B A. Leak Test of the Main Air Data System NOTE : You can do the test below for a static pressure of 691 hPa and an ____ impact pressure of 59.3 hPa (or a total pressure of 750.3 hPa) but it is less accurate. Make sure that: - the CAPT (or F/O) PFD shows the altitude value 10,000ft +/-30ft and the airspeed value 180kts +/-3kts. After 5 min: - the change of altitude must not be more than 275 ft. - the change of speed must not be more than 10 Kts. R R R R

NOTE : The input parameters for the ground test (speed and altitude) and ____ the values shown on the cockpit displays are different because of the sum of the tolerances of the air data circuit (ground test unit, ADMs, ADIRUs).

R

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-249, 251-299, 401-499, 501-509, 511-526,  528-599, CES

 

Page A505 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the glareshield 13VU ,on the EFIS control section of the FCU, set a barometric pressure of 1013 hPa. R R

2. On the ground pressure generator: - set a static pressure of 462.4 hPa.

R R R

- set an impact pressure of 179.1 hPa (or a total pressure of 641.5 hPa).

R R R

3. Close the electrovalves to isolate the static and total pressure lines of the aircraft from the pressure generator.

- Make sure that: the CAPT (or F/O) PFD shows the altitude value 20,000ft +/-40ft and the airspeed value 320kts +/-3kts. After 5 minutes, on the CAPT (or F/O) PFD: - make sure that the change of altitude is not more than 320 ft. After 10 minutes, on the CAPT (F/O) PFD: - make sure that the change of speed is not more than 10 Kts.

4. On the pressure generator: - slowly balance the pressure in the main static and total pressure lines - open the electrovalves to get atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

5. Stop the pressure generator.

  R EFF : 151-199, 401-499,  34-13-00    CES

 

Page A506 Aug 01/08

**ON A/C 301-399, Subtask 34-13-00-790-050-A A. Leak Test of the Main Air Data System NOTE : You can do the test below for a static pressure of 690 hPa and an ____ impact pressure of 60.4 hPa (or a total pressure of 750.4 hPa) but it is less accurate. Make sure that: the CAPT (or F/O) PFD shows the altitude value 10,000ft +/- 30 ft and the airspeed value 180kts +/-3 kts. After 5 min: - the change of altitude must not be more than 275 ft. - the change of speed must not be more than 10 Kts. R R R R

NOTE : The input parameters for the ground test (speed and altitude) and ____ the values shown on the cockpit displays are different because of the sum of the tolerances of the air data circuit (ground test unit, ADMs, ADIRUs).

R ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the glareshield 13VU ,on the EFIS control section of the FCU, set a barometric pressure of 1013 hPa. 2. On the ground pressure generator: - set a static pressure of 447.9 hPa. - set an impact pressure of 193.9 hPa (or a total pressure of 641.8 hPa). 3. Close the electrovalves to isolate the static and total pressure lines of the aircraft from the pressure generator.

- Make sure that: the CAPT (or F/O) PFD shows the altitude value 20,000ft +/- 40ft and the airspeed value 320 kts +/- 3kts. After 5 minutes, on the CAPT (or F/O) PFD:

  EFF : 301-399,  34-13-00    CES

 

Page A507 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- make sure that the change of altitude is not more than 320 ft. After 10 minutes, on the CAPT (or F/O) PFD: - make sure that the change of speed is not more than 10 Kts. 4. On the pressure generator: - slowly balance the pressure in the main static and total pressure lines - open the electrovalves to get atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

5. Stop the pressure generator. **ON A/C ALL 5. Close-up ________ **ON A/C 001-049, 051-099, 101-105, 151-199, Subtask 34-13-00-080-051 A. Disconnect the ground pressure generator. (1) Remove the adapters from the static probes and the pitot probes. (2) Remove the piece of plastic and the colored adhesive tape from the drain holes of the pitot probe. (3) Remove the adhesive tape from the vane of the AOA. (4) Install the slip on covers on the static probes and the pitot probes.

  EFF : ALL  34-13-00   R  CES

 

Page A508 Feb 01/10

R R

**ON A/C 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-13-00-080-051-A A. Disconnect the ground pressure generator. (1) Remove the adapters from the static probes and the pitot probes. (2) Remove the adhesive tape from the vane of the AOA. (3) Install the slip on covers on the static probes and the pitot probes. **ON A/C ALL Subtask 34-13-00-865-062 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 Subtask 34-13-00-860-075 C. Put the aircraft back to its initial configuration. (1) Do a reset of each ELAC: - on the panel 49VU, open then close the ELAC1 C/B, - on the panel 121VU, open then close the ELAC2 C/B. (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Make sure that the work area is clean and clear of tool(s) and other items. (5) Make sure that the drain holes on the pitot probes are not blocked by unwanted materials. (Ref. TASK 34-11-15-200-001)

  EFF : ALL  34-13-00    CES

 

Page A509 Feb 01/10

INTENTIONALLY BLANK

  R   34-13-00    CES

 

Page A510 Nov 01/08

TASK 34-13-00-740-002 INTERFACE TEST of the ADR 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

circuit breaker(s) safety clip(s) safety barriers access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 31-60-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure

  EFF : ALL  34-13-00   R  CES

 

Page A511 Aug 01/08

3. __________ Job Set-up **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-13-00-860-077 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) On the center pedestal, on the MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). (3) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (4) On the overhead panel: - on the FLT CTL panels 23VU and 24VU, release the FAC,ELAC and SEC pushbutton switches. The OFF legends are on. - on the ADIRS CDU, make sure that the 3 OFF/NAV/ATT selectors are at off - on the ELEC panel 35VU, make sure that the battery voltage is correct, between 26VDC and 30VDC. (5) On the center pedestal, on the ECAM control panel, push the STS key. (6) On the glareshield 13VU, on the CAPT and F/O EFIS control sections of the FCU, set the mode selector switch to ROSE/NAV. (7) Put the safety barriers in position around the RAT area. NOTE : This test is for the system 1. For the systems 2 and 3, use ____ the indications between parentheses.

  EFF : ALL  34-13-00   R  CES

 

Page A512 Aug 01/08

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-13-00-860-077-A A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) On the center pedestal, on the MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). (3) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (4) On the overhead panel: - On the FLT CTL panels 23VU and 24VU, release the FAC, ELAC and SEC pushbutton switches. The OFF legends are on. - On the ADIRS MSU, make sure that the three OFF/NAV/ATT selectors are at off. - On the ELEC panel 35VU, make sure that the battery voltage is correct, between 26VDC and 30VDC. (5) On the center pedestal, on the ECAM control panel, push the STS key. (6) On the glareshield 13VU, on the CAPT and F/O EFIS control sections of the FCU, set the mode selector switch to ROSE/NAV. (7) Put the safety barriers in position around the RAT area. NOTE : This test is for the system 1. For the systems 2 and 3, use ____ the indications between parentheses. **ON A/C ALL Subtask 34-13-00-010-055 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover.

  EFF : ALL  34-13-00    CES

 

Page A513 Feb 01/10

Subtask 34-13-00-865-089 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FCU/1 9CA1 B05 49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

9CA2 2GA 52GA

M21 Q35 Q34

**ON A/C ALL 121VU AUTO FLT/FCU/2 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

  EFF : ALL  34-13-00    CES

 

N10 N09 N08 N07 N06 N05 N04 N03

Page A514 Feb 01/10

**ON A/C ALL Subtask 34-13-00-865-091 D. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, 151-199, 201-233, 236-238, 301-302, Subtask 34-13-00-740-050 A. INTERFACE TEST of the ADR NOTE : - Ignore the warnings and indications (VLE, ...) which are not ____ related to this interface test. - When you test the ADR3, set the AIR DATA selector switch 15FP, on the SWITCHING panel 8VU, to CAPT/3. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU: - Set the three OFF/NAV/ATT selector switches to NAV - push the ADR1, ADR2 and ADR3 pushbutton switches

The OFF legend of the ADR1, ADR2 and ADR3 pushbutton switches comes on.

- push the ADR1 (ADR2) (ADR3), only if the AIR DATA selector switch is to CAPT/3 or F/O/3) pushbutton switch again.

On the ADIRS CDU, the OFF legend of the ADR pushbutton switch goes off On the CAPT (F/O) PFD, the SPD and ALT flags go out of view. The speed and altitude indications (30 Kts and local altitude) are shown

  R EFF : ALL  34-13-00    CES

 

Page A515 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the lower ECAM display unit, the local temperature values SAT and TAT are shown (only with ADR2 set). 2. On the MCDU: - push the line key adjacent to the ADR1 (ADR2) (ADR3) indication

- the ADR1 (ADR2) (ADR3) page comes into view.

- push the line key adjacent to the OUTPUT TESTS indication.

- the ADR1 (ADR2) (ADR3) OUTPUT TESTS page comes into view.

- push the line key adjacent to the INTERFACE TEST indication

- the ADR1 (ADR2) (ADR3) INTERFACE TEST 1/2 page comes into view.

- on the keyboard push the NEXT PAGE function key.

- the ADR1 (ADR2) (ADR3) INTERFACE TEST 2/2 page comes into view.

- push the line key adjacent to the START TEST indication

From 0 to 5 seconds: - on the ADIRS CDU, the FAULT and OFF legends of the ADR1 (ADR2) (ADR3) pushbutton switch come on then go off - on the CAPT (F/O) PFD, the symbols on the speed and altitude scale go out of view. The SPD and ALT warning flags flash for some seconds - on the CAPT (F/O) ND, the TAS indication goes out of view From 5 to 10 seconds: - on the CAPT (F/O) PFD, the warnings go out of view - on the CAPT (F/O) PFD, the altitude increases. After 10 seconds: - on the CAPT (F/O) PFD, these values are shown: CAS: 367.7 Kts MACH: 0.66 M ALTITUDE: 10000 Ft - on the CAPT (F/O) ND, this value is shown: TAS: 433 Kts

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-13-00 201-233, 236-238, 301-302,   CES

 

Page A516 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- on the lower ECAM display unit, (if ADR2 set) these values are shown: TAT: + 35 deg. C SAT: + 10 deg. C - on the upper ECAM display unit, this indication is shown: OVERSPEED VMO/MMO 350/.82 - push the line key adjacent to the RETURN indication.

The test procedure stops: - on the upper ECAM display unit, the OVERSPEED warning indication goes out of view - on the CAPT (F/O) PFD, the speed and altitude indications go back to their initial value - on the lower ECAM display unit, the TAT and SAT values show the local temperature (only with ADR2 set).

3. On the ADIRS CDU, push the ADR2 pushbutton switch.

On the ADIRS CDU, the OFF legend of the ADR2 pushbutton switch goes off

4. Do the ADR2 test as specified in the para. 1 and 2.

Same results on the F/O side.

5. On the ADIRS CDU: - push the ADR3 pushbutton switch

On the ADIRS CDU, the OFF legend of the ADR3 pushbutton switch goes off

- push the ADR1 pushbutton switch.

On the ADIRS CDU, the OFF legend of the ADR1 pushbutton switch comes on On the CAPT PFD, the speed and altitude indications go out of view.

6. On the SWITCHING panel 8VU: - set the AIR DATA selector switch to CAPT/3.

On the CAPT PFD, the speed and altitude indications from the ADR3 are shown.

7. Do the ADR3 test as specified in the para. 1 and 2.

Same results on the CAPT side.

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-13-00 201-233, 236-238, 301-302,   CES

 

Page A517 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------8. On the ADIRS CDU, push the ADR1 On the ADIRS CDU, the OFF legend of the pushbutton switch. ADR1 pushbutton switch goes off 9. On the SWITCHING panel 8VU: - set the AIR DATA selector switch to NORM.

On the CAPT PFD, the speed and altitude indications stay in view.

10. On the ADIRS CDU, set the three OFF/NAV/ATT selector switches to OFF. After the ADR3 test, set the AIR DATA selector switch 15FP to NORMAL. **ON A/C 106-149, 234-235, 239-239, 303-312, 401-499, Subtask 34-13-00-740-050-B A. INTERFACE TEST of the ADR NOTE : - Ignore the warnings and indications (VLE, ...) which are not ____ related to this interface test. - When you test the ADR3, set the AIR DATA selector switch 15FP, on the SWITCHING panel 8VU, to CAPT/3. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU: - Set the three OFF/NAV/ATT selector switches to NAV - push the ADR1, ADR2 and ADR3 pushbutton switches

The OFF legend of the ADR1, ADR2 and ADR3 pushbutton switches comes on.

- push the ADR1 (ADR2) (ADR3), only if the AIR DATA selector switch is to CAPT/3 or F/O/3) pushbutton switch again.

On the ADIRS CDU, the OFF legend of the related ADR pushbutton switch goes off On the CAPT (F/O) PFD, the SPD and ALT flags go out of view. The speed and

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-239, 301-312, 401-499,   CES

 

Page A518 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------altitude indications (30 Kts and local altitude) are shown On the lower ECAM display unit, the local temperature values SAT and TAT are shown (only with ADR1 and/or ADR3 is set). 2. On the MCDU: - push the line key adjacent to the ADR1 (ADR2) (ADR3) indication

- the ADR1 (ADR2) (ADR3) page comes into view.

- push the line key adjacent to the OUTPUT TESTS indication.

- the ADR1 (ADR2) (ADR3) OUTPUT TESTS page comes into view.

- push the line key adjacent to the INTERFACE TEST indication

- the ADR1 (ADR2) (ADR3) INTERFACE TEST 1/2 page comes into view.

- on the keyboard push the NEXT PAGE function key.

- the ADR1 (ADR2) (ADR3) INTERFACE TEST 2/2 page comes into view.

- push the line key adjacent to the START TEST indication

From 0 to 5 seconds: - on the ADIRS CDU, the FAULT and OFF legends of the ADR1 (ADR2) (ADR3) pushbutton switch come on then go off - on the CAPT (F/O) PFD, the symbols on the speed and altitude scale go out of view. The SPD and ALT warning flags flash for some seconds - on the CAPT (F/O) ND, the TAS indication goes out of view From 5 to 10 seconds: - on the CAPT (F/O) PFD, the warnings go out of view - on the CAPT (F/O) PFD, the altitude increases. After 10 seconds: - on the CAPT (F/O) PFD, these values are shown: CAS: 367.7 Kts MACH: 0.66 M ALTITUDE: 10000 Ft

  R EFF : 106-149, 234-235, 239-239, 303-312,  34-13-00 401-499,   CES

 

Page A519 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- on the CAPT (F/O) ND, this value is shown: TAS: 433 Kts - on the lower ECAM display unit, (if ADR1 and/or ADR3 is set) these values are shown: TAT: + 35 deg. C SAT: + 10 deg. C - on the upper ECAM display unit, this indication is shown: OVERSPEED VMO/MMO 350/.82 - push the line key adjacent to the RETURN indication.

The test procedure stops: - on the upper ECAM display unit, the OVERSPEED warning indication goes out of view, - on the CAPT (F/O) PFD, the speed and altitude indications go back to their initial value, - on the lower ECAM display unit, the TAT and SAT values show the local temperature (only with ADR1 and/or ADR3 is set).

3. On the ADIRS CDU, push the ADR2 pushbutton switch.

On the ADIRS CDU, the OFF legend of the ADR2 pushbutton switch goes off

4. Do the ADR2 test as specified in the para. 1 and 2.

Same results on the F/O side. - on the lower ECAM display unit, the TAT and SAT values are not shown (only with ADR1 and/or ADR3 is set).

5. On the ADIRS CDU: - push the ADR3 pushbutton switch

On the ADIRS CDU, the OFF legend of the ADR3 pushbutton switch goes off

- push the ADR1 pushbutton switch.

On the ADIRS CDU, the OFF legend of the ADR1 pushbutton switch comes on On the CAPT PFD, the speed and altitude indications go out of view.

  R EFF : 106-149, 234-235, 239-239, 303-312,  34-13-00 401-499,   CES

 

Page A520 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------6. On the SWITCHING panel 8VU: On the CAPT PFD, the speed and altitude - set the AIR DATA selector indications from the ADR3 are shown. switch to CAPT/3. 7. Do the ADR3 test as specified in the para. 1 and 2.

Same results on the CAPT side.

8. On the ADIRS CDU, push the ADR1 pushbutton switch.

On the ADIRS CDU, the OFF legend of the ADR1 pushbutton switch goes off

9. On the SWITCHING panel 8VU: - set the AIR DATA selector switch to NORM.

On the CAPT PFD, the speed and altitude indications stay in view.

10. On the ADIRS CDU, set the three OFF/NAV/ATT selector switches to OFF. After the ADR3 test, set the AIR DATA selector switch 15FP to NORMAL. R

**ON A/C 240-249, 251-299, 501-509, 511-526, 528-599, Subtask 34-13-00-740-050-C A. INTERFACE TEST of the ADR NOTE : - Ignore the warnings and indications (VLE, ...) which are not ____ related to this interface test. - When you test the ADR3, set the AIR DATA selector switch 15FP, on the SWITCHING panel 8VU, to CAPT/3.

  R EFF : 106-149, 234-235, 239-249, 251-299,  34-13-00 303-312, 401-499, 501-509, 511-526, 528-599,   CES

 

Page A521 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS MSU: - Set the three OFF/NAV/ATT selector switches to NAV. - Push the ADR1, ADR2 and ADR3 pushbutton switches.

The OFF legend of the ADR1, ADR2 and ADR3 pushbutton switches comes on.

- Push the ADR1 (ADR2) (ADR3, only if the AIR DATA selector switch is to CAPT/3 or F/O/3) pushbutton switch again.

On the ADIRS MSU, the OFF legend of the ADR pushbutton switch goes off. On the CAPT (F/O) PFD, the SPD and ALT flags go out of view. The speed and altitude indications (30 Kts and local altitude) are shown. On the lower ECAM display unit, the local temperature values SAT and TAT are shown (only with ADR1 and/or ADR3 is set).

2. On the MCDU: - Push the line key adjacent to the ADR1 (ADR2) (ADR3) indication.

- The ADR1 (ADR2) (ADR3) page comes into view.

- Push the line key adjacent to the OUTPUT TESTS indication.

- The ADR1 (ADR2) (ADR3) OUTPUT TESTS page comes into view.

- Push the line key adjacent to the INTERFACE TEST indication.

- The ADR1 (ADR2) (ADR3) INTERFACE TEST 1/2 page comes into view.

- On the keyboard push the NEXT PAGE function key.

- The ADR1 (ADR2) (ADR3) INTERFACE TEST 2/2 page comes into view.

- Push the line key adjacent to the START TEST indication.

From 0 to 5 seconds: - On the ADIRS MSU, the FAULT and OFF legends of the ADR1 (ADR2) (ADR3) pushbutton switch come on then go off. - On the CAPT (F/O) PFD, the symbols on the speed and altitude scale go out of view. The SPD and ALT warning flags flash for some seconds.

  R EFF : 240-249, 251-299, 501-509, 511-526,  34-13-00 528-599,   CES

 

Page A522 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- On the CAPT (F/O) ND, the TAS indication goes out of view. From 5 to 10 seconds: - On the CAPT (F/O) PFD, the warnings go out of view. - On the CAPT (F/O) PFD, the altitude increases. After 10 seconds: - On the CAPT (F/O) PFD, these values are shown: CAS: 367.7 Kts MACH: 0.66 M ALTITUDE: 10000 Ft - On the CAPT (F/O) ND, this value is shown: TAS: 433 Kts - On the lower ECAM display unit, (if ADR1 and/or ADR3 is set) these values are shown: TAT: + 35 deg. C SAT: + 10 deg. C - On the upper ECAM display unit, this indication is shown: OVERSPEED VMO/MMO 350/.82 - Push the line key adjacent to the RETURN indication.

The test procedure stops: - On the upper ECAM display unit, the OVERSPEED warning indication goes out of view. - On the CAPT (F/O) PFD, the speed and altitude indications go back to their initial value. - On the lower ECAM display unit, the TAT and SAT values show the local temperature (only with ADR1 and/or ADR3 is set).

3. On the ADIRS MSU, push the ADR2 pushbutton switch.

On the ADIRS MSU, the OFF legend of the ADR2 pushbutton switch goes off.

4. Do the ADR2 test as specified in

Same results on the F/O side.

  R EFF : 240-249, 251-299, 501-509, 511-526,  34-13-00 528-599,   CES

 

Page A523 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------the para. 1 and 2. - On the lower ECAM display unit, the TAT and SAT values are not shown (only with ADR1 and/or ADR3 is set). 5. On the ADIRS MSU: - Push the ADR3 pushbutton switch.

On the ADIRS MSU, the OFF legend of the ADR3 pushbutton switch goes off.

- Push the ADR1 pushbutton switch.

On the ADIRS MSU, the OFF legend of the ADR1 pushbutton switch comes on. On the CAPT PFD, the speed and altitude indications go out of view.

6. On the SWITCHING panel 8VU: - Set the AIR DATA selector switch to CAPT/3.

On the CAPT PFD, the speed and altitude indications from the ADR3 are shown.

7. Do the ADR3 test as specified in the para. 1 and 2.

Same results on the CAPT side.

8. On the ADIRS MSU, push the ADR1 pushbutton switch.

On the ADIRS MSU, the OFF legend of the ADR1 pushbutton switch goes off.

9. On the SWITCHING panel 8VU: - Set the AIR DATA selector switch to NORM.

On the CAPT PFD, the speed and altitude indications stay in view.

10. On the ADIRS MSU, set the three OFF/NAV/ATT selector switches to OFF. After the ADR3 test, set the AIR DATA selector switch 15FP to NORMAL.

  R EFF : 240-249, 251-299, 501-509, 511-526,  34-13-00 528-599,   CES

 

Page A524 Feb 01/10

R

**ON A/C 313-399, Subtask 34-13-00-740-050-D A. INTERFACE TEST of the ADR NOTE : - Ignore the warnings and indications (VLE, ...) which are not ____ related to this interface test. - When you test the ADR3, set the AIR DATA selector switch 15FP, on the SWITCHING panel 8VU, to CAPT/3. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS MSU: - Set the three OFF/NAV/ATT selector switches to NAV. - Push the ADR1, ADR2 and ADR3 pushbutton switches.

The OFF legend of the three pushbutton switches comes on.

- Push the ADR1 (ADR2) (ADR3, only if the AIR DATA selector switch is at CAPT/3 or F/O/3) pushbutton switch again.

On the ADIRS MSU, the OFF legend of the ADR pushbutton switch goes off. On the CAPT (F/O) PFD, the SPD and ALT flags go out view. The speed and altitude indications (30 Kts and local altitude) are shown. - On the lower ECAM display unit, the local temperature values SAT and TAT are shown (only with ADR1 and/or ADR3 is set).

2. On the MCDU:

On the MCDU:

- Push the line key adjacent to the ADR1 (ADR2) (ADR3) indication.

- The ADIRS ADR1 (ADR2) (ADR3) 1/2 page comes into view.

- Push the line key adjacent to the INTERFACE TEST indication.

- The ADIRS ADR1 (ADR2) (ADR3) INTERFACE TEST page comes into view.

- Push the line key adjacent to the TEST START indication.

From 0 to 5 seconds: - On the ADIRS MSU, the FAULT and OFF legends of the ADR1 (ADR2) (ADR3)

  R EFF : 313-399,  34-13-00    CES

 

Page A525 Nov 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------pushbutton switch come on then go off. - On the CAPT (F/O) PFD, the symbols on the speed and altitude scale go out view. The SPD and ALT warning flags flash for some seconds. - On the CAPT (F/O) ND, the TAS indication goes out view. From 5 to 10 seconds: - On the CAPT (F/O) PFD, the warnings go out of view. - On the CAPT (F/O) PFD, the altitude increases. After 10 seconds: - On the CAPT (F/O) PFD, these values are shown: CAS: 367.7 Kts MACH: 0.66 M ALTITUDE: 10000 Ft - On the CAPT (F/O) ND, this value is shown: TAS: 433 Kts - On the lower ECAM display unit, (if ADR1 and/or ADR3 is set) these values are shown: TAT: + 35 deg. C SAT: + 10 deg. C - On the upper ECAM display unit, this indication is shown: OVERSPEED VMO/MMO 350/.82 - Push the line key adjacent to the RETURN/TEST STOP indication.

The test procedure stops: - On the upper ECAM display unit, the OVERSPEED warning indication goes out of view. - On the CAPT (F/O) PFD, the speed and altitude indications go back to their initial value. - On the lower ECAM display unit, the TAT and SAT values show the local temperature (only with ADR1 and/or ADR3 is set).

  R EFF : 313-399,  34-13-00    CES

 

Page A526 Nov 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------3. On the ADIRS MSU, push the ADR2 On the ADIRS MSU, the OFF legend of the pushbutton switch. ADR2 pushbutton switch goes off. 4. Do the ADR2 test as specified in the para. 1 and 2.

Same results on the F/O side. - On the lower ECAM display unit, the TAT and SAT values are not shown (only with ADR1 and/or ADR3 is set).

5. On the ADIRS MSU: - Push the ADR3 pushbutton switch.

On the ADIRS MSU, the OFF legend of the ADR3 pushbutton switch goes off.

- Push the ADR1 pushbutton switch.

On the ADIRS MSU, the OFF legend of the ADR1 pushbutton switch comes on. On the CAPT PFD, the speed and altitude indications go out of view.

6. On the SWITCHING panel 8VU: - Set the AIR DATA selector switch to CAPT/3.

On the CAPT PFD, the speed and altitude indications from the ADR3 are shown.

7. Do the ADR3 test as specified in the para. 1 and 2.

Same results on the CAPT side.

8. On the ADIRS MSU, push the ADR1 pushbutton switch.

On the ADIRS MSU, the OFF legend of the ADR1 pushbutton switch goes off.

9. On the SWITCHING panel 8VU: - Set the AIR DATA selector switch to NORM.

On the CAPT PFD, the speed and altitude indications stay in view.

10. On the ADIRS MSU, set the three OFF/NAV/ATT selector switches to OFF. After the ADR3 test, set the AIR DATA selector switch 15FP to NORMAL.

  R EFF : 313-399,  34-13-00    CES

 

Page A527 Nov 01/09

**ON A/C ALL 5. Close-up ________ Subtask 34-13-00-860-078 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (3) On the FLT CTL panels 23VU and 24VU, push the FAC, ELAC and SEC pushbutton switches. The related OFF legend goes off. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-13-00-410-055 B. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s). Subtask 34-13-00-865-092 C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 7XE, 5CC1, 5CC2

  EFF : ALL  34-13-00   R  CES

 

Page A528 Aug 01/08

TASK 34-13-00-740-003 SYSTEM TEST of the ADR 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-13-00-860-079 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) On the center pedestal, on the MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010).

  EFF : ALL  34-13-00   R  CES

 

Page A529 Aug 01/08

(4) On the overhead panel, on the ADIRS CDU, make sure that the OFF legend of the ADR pushbutton switches is off). Subtask 34-13-00-010-056 B. Get Access (1) Put the access platformin position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-13-00-865-093 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FCU/1 9CA1 B05 49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

9CA2 2GA 52GA

M21 Q35 Q34

**ON A/C ALL 121VU AUTO FLT/FCU/2 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY

  EFF : ALL  34-13-00   R  CES

 

Page A530 Aug 01/08

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N10 N09 N08 N07 N06 N05 N04 N03

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, 151-199, 201-207, Subtask 34-13-00-740-051 A. SYSTEM TEST of the ADR NOTE : - The actions and the results of this procedure occur on the MCDU ____ used. - It is not necessary to do an IR alignment procedure before you start the ADR SYSTEM TEST. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Push the line key adjacent to the ADR 1(ADR 2)(ADR 3) indication

The ADR 1(ADR 2)(ADR 3) page comes into view.

2. Push the line key adjacent to the SYSTEM TEST indication

The SYSTEM TEST page comes into view.

3. Push the line key adjacent to the START TEST indication

The TEST IN PROGRESS indication comes into view. At the end of the test, the TEST OK indication comes into view.

  EFF : ALL  34-13-00    CES

 

Page A531 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------4. Push the line key adjacent to the These indications come into view: TEST CLOSE UP indication - TEST CLOSE UP . IR RE-ALIGNMENT - ENTER PPOS WITH AN UNUSED MCDU (Refer to the NOTE given above) 5. Push the line key adjacent to the RETURN indication R R

The test procedure stops.

**ON A/C 001-049, 052-052, 058-058, 061-061, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1249 For A/C 001-049,052-052,058-058,061-061,101-105,151-199, 201-207, Subtask 34-13-00-740-051-A A. SYSTEM TEST of the ADR NOTE : - The actions and the results of this procedure occur on the MCDU ____ used. - It is not necessary to do an IR alignment procedure before you start the ADR SYSTEM TEST. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Push the line key adjacent to the ADR 1(ADR 2)(ADR 3) indication

The ADR 1(ADR 2)(ADR 3) page comes into view.

2. Push the line key adjacent to the SYSTEM TEST indication

The TEST IN PROGRESS indication comes into view. At the end of the test, the TEST OK indication comes into view.

3. Push the line key adjacent to the RETURN indication

The test procedure stops.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-13-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page A532 Feb 01/10

**ON A/C ALL 5. Close-up ________ Subtask 34-13-00-860-080 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-13-00-410-056 B. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

  R EFF : ALL  34-13-00    CES

 

Page A533 Aug 01/08

**ON A/C 001-049, 101-105, 151-199, 201-203, TASK 34-13-00-740-004 Read the CFDIU for the ADR CURRENT STATUS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure ADIRS Stop Procedure

  EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00   R  CES

 

Page A534 Aug 01/08

3. __________ Job Set-up Subtask 34-13-00-860-083 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (ADIRU related to the installed ADM only) (Ref. TASK 34-10-00-860-002). Subtask 34-13-00-010-061 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-13-00-865-094 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FCU/1 9CA1 B05 49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 121VU AUTO FLT/FCU/2 9CA2 M21 **ON A/C 001-049, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC

10FP 9FP 5FP2 5FP3 4FP2 4FP3

  EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00   R  CES

 

N11 N10 N09 N08 N07 N06

Page A535 Aug 01/08

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU ADIRS/ADIRU/2/28VDC 6FP2 N05 121VU ADIRS/ADIRU/3/28VDC 6FP3 N04 **ON A/C 001-049, 101-105, 151-199, 201-203, 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY

2GA 52GA

Q35 Q34

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N10 N09 N08 N07 N06 N05 N04 N03

**ON A/C 151-199, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

**ON A/C 001-049, 101-105, 151-199, 201-203, Subtask 34-13-00-865-095 D. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 121VU AUTO FLT/FAC2/28VDC 5CC2 M19

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00    CES

 

Page A536 Aug 01/08

4. Procedure _________ Subtask 34-13-00-740-052 A. Do the Operational Test of the CURRENT STATUS ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the center pedestal, on one MCDU:

On the MCDU:

1. Get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010).

- the SYSTEM REPORT/TEST/NAV page comes into view.

2. On the NAV page: - push the line key adjacent to the ADR1 (ADR2) (ADR3) indication (related to the removed ADM)

- the ADR1 (ADR2) (ADR3) page comes into view.

- push the line key adjacent to the CURRENT STATUS indication.

- the ADR1 (ADR2) (ADR3) CURRENT STATUS 1/8 page comes into view. - if there is no defect detected after the new ADM is installed, the NO FAULTS indication comes into view.

5. Close-up ________ Subtask 34-13-00-410-061 A. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00    CES

 

Page A537 Aug 01/08

Subtask 34-13-00-860-084 B. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the MCDU, push the line key adjacent to the RETURN indication until the MCDU MENU page comes into view. (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-13-00-865-096 C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2, 7XE

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-13-00    CES

 

Page A538 Aug 01/08

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, TASK 34-13-00-740-005 Read the CFDIU for the ADR INPUT STATUS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure ADIRS Stop Procedure

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page A539 Feb 01/10

3. __________ Job Set-up Subtask 34-13-00-860-085 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (ADIRU related to the installed ADM only) (Ref. TASK 34-10-00-860-002). (3) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). Subtask 34-13-00-010-062 B. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-13-00-865-097 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FCU/1 9CA1 B05 49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 051-061, 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA

10FP 9FP 5FP2 5FP3

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

N11 N10 N09 N08

Page A540 Feb 01/10

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU ADIRS/ADIRU/2/115VAC 4FP2 N07 121VU ADIRS/ADIRU/3/115VAC 4FP3 N06 121VU ADIRS/ADIRU/2/28VDC 6FP2 N05 121VU ADIRS/ADIRU/3/28VDC 6FP3 N04 R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU AUTO FLT/FCU/2 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY

R R

M21 Q35 Q34

**ON A/C 062-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

R R

9CA2 2GA 52GA

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N10 N09 N08 N07 N06 N05 N04 N03

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-13-00-865-098 D. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 121VU AUTO FLT/FAC2/28VDC 5CC2 M19

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page A541 Feb 01/10

4. Procedure _________ Subtask 34-13-00-740-053 A. Read the CFDIU for the ADR INPUT STATUS NOTE : This test is for the system 1. For the systems 2 and 3, use the ____ indications between the parentheses. The actions and the results of this procedure occur on the MCDU used. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Push the line key adjacent to the ADR 1(ADR 2)(ADR 3) indication.

- the ADR 1(ADR 2)(ADR 3) page comes into view.

2. Push the line key adjacent to the INPUT STATUS indication.

- the INPUT STATUS page 1/8 comes into view with the current on-the-ground status of the ADR1 (ADR2) (ADR3) parameters.

3. Push the down arrow function key to set the INPUT STATUS page 2/8 to 8/8.

- the related pages come into view.

4. Push the line key adjacent to the RETURN indication.

- the test procedure stops.

5. Close-up ________ Subtask 34-13-00-410-062 A. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page A542 Feb 01/10

Subtask 34-13-00-860-086 B. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the MCDU, push the line key adjacent to the RETURN indication until the MCDU MENU page comes into view. (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-13-00-865-099 C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2, 7XE

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-13-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page A543 Feb 01/10

AIR DATA - INSPECTION/CHECK ___________________________ TASK 34-13-00-200-001 Visual Check of Pitot probes, Static ports and AOA sensors 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

1 ACCESS PLATFORM 2M (6 FT) 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-10-00-170-001 34-10-00-170-002 34-10-00-170-003 34-11-19-000-001 R R

34-11-19-200-001 34-11-19-400-001 34-22-25-170-001

Flushing of the Principal Total Pressure Lines Flushing of the Principal Static Pressure Lines Draining and Flushing of Standby Pneumatic Circuits Removal of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3) Inspection of the Angle-Of-Attack Sensor (3FP1, 3FP2, 3FP3) Installation of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3) Draining and Flushing of the Standby Static and Standby Total Pressure lines (ISIS)

  EFF : ALL  34-13-00    CES

 

Page 601 Feb 01/07

3. __________ Job Set-up Subtask 34-13-00-860-094 A. Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) in position in zone 125 to get access to the pitot probes 1 and 3 and in zone 126 to get access to the pitot probe 2. (2) Remove the cover from the pitot probe. (3) Put the ACCESS PLATFORM 2M (6 FT) in position in zone 128 to get acces to the static probes 7DA1, 7DA2, 8DA1 and 8DA2. (4) Remove the cover from the static probe. (5) Put the ACCESS PLATFORM 2M (6 FT) in zone 120 to get acces to the static probes 7DA3 and 8DA3. (6) Remove the cover from the static probe. (7) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position in zone 231 to get acces to the AOA sensor 3FP1 (232 for 3FP2) (127 for 3FP3). (8) Remove the slip-on cover from the AOA sensor. 4. Procedure _________ Subtask 34-13-00-220-050 A. Inspection/Check of the Pitot Probes (9DA1, 9DA2, 9DA3) (1) Do a general visual inspection of the pitot probes. (a) Color During the ageing of the probe, the color of the tube becomes brownish and/or blackish. This coloration has no effect on the operation of the probe. (b) Make sure that the drain holes are not blocked. - If a drain hole is blocked, do the flushing (Ref. TASK 34-1000-170-001) of the main system, or (Ref. TASK 34-10-00-170-003) for the standby system.

  EFF : ALL  34-13-00   R  CES

 

Page 602 May 01/06

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, Subtask 34-13-00-220-051 B. Inspection/Check of the Static Probes (7DA1, 7DA2, 7DA3, 8DA1, 8DA2, 8DA3) (1) Do a visual check of the static probes: (a) If there is contamination, do the (Ref. TASK 34-10-00-170-002) of the main static circuit, or/and the (Ref. TASK 34-10-00-170-003) of the standby static circuit. (2) Do a visual check of the structure around the static probes, - if there is impact, refer to SRM 53-00-11 Pb101. R R

**ON A/C 106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-13-00-220-051-A B. Inspection/Check of the Static Probes (7DA1, 7DA2, 7DA3, 8DA1, 8DA2, 8DA3) (1) Do a visual check of the static probes: (a) If there is contamination, do the (Ref. TASK 34-10-00-170-002) of the main static circuit, or/and the (Ref. TASK 34-22-25-170-001) of the standby static circuit. (2) Do a visual check of the structure around the static probes, - if there is impact, refer to SRM 53-00-11 Pb101. **ON A/C ALL Subtask 34-13-00-220-052 C. Inspection/Check of the AOA Sensors (3FP1, 3FP2, 3FP3) (1) Do a visual check of the AOA sensors: (a) Make sure that there is no paint on the vane and on the mounting base of the three AOA sensors. - if not, do the (Ref. TASK 34-11-19-200-001).

  EFF : ALL  34-13-00    CES

 

Page 603 Feb 01/10

(2) Manually turn the vane of the AOA sensors very carefully from the maximum to the minimum mechanical stops (+85⁰ to -35⁰) and make sure that there is no hard point. (a) if one vane has a hard point, replace the related AOA sensor (Ref. TASK 34-11-19-000-001) and (Ref. TASK 34-11-19-400-001) 5. Close-up ________ Subtask 34-13-00-860-095 A. Put the aircraft back to its initial configuration. (1) Install the slip-on cover on the AOA sensor. (2) Install the static cover. (3) Install the pitot cover. (4) Make sure that the work area is clean and clear of tool(s) and other items. (5) Remove the access platform(s).

  EFF : ALL  34-13-00   R  CES

 

Page 604 Nov 01/09

ATTITUDE, HEADING AND POSITION - DESCRIPTION AND OPERATION __________________________________________________________ 1. General _______ R

**ON A/C 001-049, 101-105, 151-199, The Inertial Reference (IR) portion of the Air Data/Inertial Reference Unit (ADIRU) provides main data sources which are precision attitude, magnetic heading references and navigation data to the aircraft avionics systems. The IR portion also provides selected Global Positioning System (GPS) data and accurate GPIR hybrid position. Attitude, heading and navigation data are displayed on the Electronic Flight Instrument System (EFIS) displays Primary Flight Display (PFD); Navigation Display (ND)) and on the VOR/DME RMI which recopies the heading data.

R

**ON A/C 201-203,

R R R R R R R R R

The Inertial Reference (IR) portion of the Air Data/Inertial Reference Unit (ADIRU) provides main data sources which are precision attitude, magnetic heading references and navigation data to the aircraft avionics systems. The IR portion also provides selected GPS data and accurate GPIR hybrid position. Attitude, heading and navigation data are displayed on the Electronic Flight Instrument System (EFIS) displays Primary Flight Display (PFD); Navigation Display (ND)) and on the VOR/ADF/DME RMI which recopies the heading data. **ON A/C 001-049, 101-105, 151-199, 201-203, 2. __________________ System Description A. General The IR portion is a strapdown inertial system which provides a quality reference for attitude, heading (true and magnetic), angular rates and accelerations. The IR software also computes: - the inertial position - the ground velocities - the baro inertial vertical speed - the drift angle - the wind data - the flight path data.

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 1   Config-1 Aug 01/06  CES

 

R

**ON A/C 001-004, B. Inputs (1) Digital inputs (a) FMGC inputs The IR portion is provided with two ARINC 429 low speed buses from the two ARINC 702 Flight Management and Guidance Computers (FMGCs). These buses transmit the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 270: FMGC DISCRETES. These data words are used for initialization and BITE purposes. (b) CDU input The IR portion is provided with one ARINC 429 low speed bus from the CDU. This bus transmits the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 043: SET MAGNETIC HEADING - label 277: CDU TEST. These data words are used for initialization and BITE purpose. (c) ADR inputs The IR portion is provided with three ARINC 429 low speed buses from the other two ADIRUs (ADR portion) and from its associated ADR. These buses transmit the following data words: - label 203: ALTITUDE - label 210: TRUE AIRSPEED. (d) GPS inputs The IR portion is provided with two ARINC 429 high speed buses from the two ARINC 743 Global Positioning System Sensor Units (GPSSU) which are part of the Global Positioning System (GPS). These buses transmit the following data words: - label 060: MEASUREMENT STATUS - label 061: PSEUDO RANGE - label 062: PSEUDO RANGE FINE 4 - label 063: RANGE RATE - label 064: DELTA RANGE - label 065: SV POSITION X - label 066: SV POSITION X FINE 4 - label 070: SV POSITION Y - label 071: SV POSITION Y FINE 4 - label 072: SV POSITION Z

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label label label label label label label label label label label label label label label label label label label label label label label label

073: 074: 076: 101: 102: 103: 110: 111: 112: 120: 121: 125: 130: 136: 140: 141: 150: 165: 166: 174: 247: 260: 273: 377:

SV POSITION Z FINE 4 UTC MEASURE TIME GPS ALTITUDE (MSL) HDOP VDOP GPS TRACK ANGLE TRUE GPS LATITUDE 2 GPS LONGITUDE GPS GROUND SPEED GPS LATITUDE LSBS 2 GPS LONGITUDE LSBS GPS UTC BCD GPS INTEGRITY LIMIT VERTICAL FIGURE OF MERIT UTC BIN FINE 4 UTC BIN FRACTION 4 GPS UTC BIN GPS VERTICAL VELOCITY GPS NORTH VELOCITY GPS EAST VELOCITY HORIZ FIGURE OF MERIT GPS DATE GPS SENSOR STATUS EQUIPMENT IDENT

(2) Analog inputs The IR portion is provided with analog inputs for power supply AND GPS/IRS synchronization purposes. For more details Ref. 34-12-00. R

**ON A/C 001-049, 101-105, 151-199, 201-203, Post SB

34-1147 For A/C 001-004,

B. Inputs (1) Digital inputs (a) FMGC inputs The IR portion is provided with two ARINC 429 low speed buses from the two ARINC 702 Flight Management and Guidance Computers (FMGCs). These buses transmit the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 270: FMGC DISCRETES. These data words are used for initialization and BITE purposes.

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(b) CDU input The IR portion is provided with one ARINC 429 low speed bus from the CDU. This bus transmits the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 043: SET MAGNETIC HEADING - label 277: CDU TEST. These data words are used for initialization and BITE purpose. (c) ADR inputs The IR portion is provided with three ARINC 429 low speed buses from the other two ADIRUs (ADR portion) and from its associated ADR. These buses transmit the following data words: - label 203: ALTITUDE - label 210: TRUE AIRSPEED. (d) GPS inputs The IR portion is provided with two ARINC 429 high speed buses from the GPS portion of the Multi-Mode Receivers (MMRs). These buses transmit the following data words: - label 060: MEASUREMENT STATUS - label 061: PSEUDO RANGE - label 062: PSEUDO RANGE FINE 4 - label 063: RANGE RATE - label 064: DELTA RANGE - label 065: SV POSITION X - label 066: SV POSITION X FINE 4 - label 070: SV POSITION Y - label 071: SV POSITION Y FINE 4 - label 072: SV POSITION Z - label 073: SV POSITION Z FINE 4 - label 074: UTC MEASURE TIME - label 076: GPS ALTITUDE (MSL) - label 101: HDOP - label 102: VDOP - label 103: GPS TRACK ANGLE TRUE - label 110: GPS LATITUDE 2 - label 111: GPS LONGITUDE - label 112: GPS GROUND SPEED - label 120: GPS LATITUDE LSBS 2 - label 121: GPS LONGITUDE LSBS - label 125: GPS UTC BCD - label 130: GPS INTEGRITY LIMIT - label 136: VERTICAL FIGURE OF MERIT - label 140: UTC BIN FINE 4 - label 141: UTC BIN FRACTION 4 - label 150: GPS UTC BIN

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label label label label label label label

165: 166: 174: 247: 260: 273: 377:

GPS VERTICAL VELOCITY GPS NORTH VELOCITY GPS EAST VELOCITY HORIZ FIGURE OF MERIT GPS DATE GPS SENSOR STATUS EQUIPMENT IDENT

(2) Analog inputs The IR portion is provided with analog inputs for power supply and GPS/IRS synchronization purposes. For more details Ref. 34-12-00. R B. Inputs (1) Digital inputs (a) FMGC inputs The IR portion is provided with two ARINC 429 low speed buses from the two ARINC 702 Flight Management and Guidance Computers (FMGCs). These buses transmit the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 270: FMGC DISCRETES. These data words are used for initialization and BITE purposes. (b) CDU input The IR portion is provided with one ARINC 429 low speed bus from the CDU. This bus transmits the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 043: SET MAGNETIC HEADING - label 277: CDU TEST. These data words are used for initialization and BITE purpose. (c) ADR inputs The IR portion is provided with three ARINC 429 low speed buses from the other two ADIRUs (ADR portion) and from its associated ADR. These buses transmit the following data words: - label 203: ALTITUDE - label 210: TRUE AIRSPEED. - label 241: CORRECTED AOA (only from internal ADR bus).

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R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R

(d) GPS inputs The IR portion is provided with two ARINC 429 high speed buses from the GPS portion of the Multi-Mode Receivers (MMRs). These buses transmit the following data words: - label 060: MEASUREMENT STATUS - label 061: PSEUDO RANGE - label 062: PSEUDO RANGE FINE 4 - label 063: RANGE RATE - label 064: DELTA RANGE - label 065: SV POSITION X - label 066: SV POSITION X FINE 4 - label 070: SV POSITION Y - label 071: SV POSITION Y FINE 4 - label 072: SV POSITION Z - label 073: SV POSITION Z FINE 4 - label 074: UTC MEASURE TIME - label 076: GPS ALTITUDE (MSL) - label 101: HDOP - label 102: VDOP - label 103: GPS TRACK ANGLE TRUE - label 110: GPS LATITUDE 2 - label 111: GPS LONGITUDE - label 112: GPS GROUND SPEED - label 120: GPS LATITUDE LSBS 2 - label 121: GPS LONGITUDE LSBS - label 125: GPS UTC BCD - label 130: GPS INTEGRITY LIMIT - label 136: VERTICAL FIGURE OF MERIT - label 140: UTC BIN FINE 4 - label 141: UTC BIN FRACTION 4 - label 150: GPS UTC BIN - label 165: GPS VERTICAL VELOCITY - label 166: GPS NORTH VELOCITY - label 174: GPS EAST VELOCITY - label 247: HORIZ FIGURE OF MERIT - label 260: GPS DATE - label 273: GPS SENSOR STATUS - label 377: EQUIPMENT IDENT

R R R R

(2) Analog inputs The IR portion is provided with analog inputs for power supply and GPS/IRS synchronization purposes. For more details Ref. 34-12-00.

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**ON A/C 001-049, 101-105, 151-199, 201-203, (3) Discrete inputs The IR portion is provided with the following discrete inputs: --------------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT | | | | DEFINITION | --------------------------------------------------------------------| Mounting position 1 | Open/GND | see table 2 | | Mounting position 2 | Open/GND | see table 2 | | SDI MSB (Middle insert) | Open/GND | 0/1 | | SDI LSB (Middle insert) | Open/GND | 0/1 | | IR OFF | Open/GND | Momentary action | | IR mode select M1 | Open/GND | see table 3 | | IR mode select M2 | Open/GND | see table 3 | | Auto ADR.DADS select | Open/GND | see table 4 | | Manual ADR.DADS select | Open/GND | see table 4 | | Aircraft Ident Code 1/0 | Open/GND | 0/1 | | Aircraft Ident Code 2/0 | Open/GND | 0/1 | | Aircraft Ident Code 4/0 | Open/GND | 0/1 | | Aircraft Ident Code 8/0 | Open/GND | 0/1 | | Aircraft Ident Code 16/0 | Open/GND | 0/1 | | Aircraft Ident Code 32/0 | Open/GND | 0/1 | | Aircraft Ident Code 64/0 | Open/GND | 0/1 | | Aircraft Ident Code Parity | Open/GND | 0/1 | | IR remote test | Open/GND | No test/test | | GPSSU 1 present | Open/GND | GND = present | | GPSSU 2 present | Open/GND | GND = present | | GPS priority select | Open/GND | Normal priority/ | | | | Reserved priority | --------------------------------------------------------------------Table 1 : IR Discrete Inputs (a) Mounting positions 1 and 2 These discrete inputs provide the IR with the unit orientation data which give the longitudinal and lateral axis of the aircraft. Table 2 below gives the unit position according to the discrete selection.

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--------------------------------------------------------------| Mounting | Mounting | Connector Position/Aircraft | | Position 1 | Position 2 | | --------------------------------------------------------------| Open * | Open * | FWD * | | Ground | Open | AFT | | Open | Ground | RIGHT | | Ground | Ground | LEFT | --------------------------------------------------------------Table 2 : Mounting Position Discretes *These discretes are wired in FWD position. (b) IR mode select The IR portion uses these discrete inputs to know the position of the OFF/NAV/ATT selector switch as follows: ---------------------------------------------| M1 | M2 | OFF/NAV/ATT | | | | Selector Switch Position | |--------------------------------------------| | Open | Open | OFF | | Ground | Open | NAV | | Open | Ground | ATT | ---------------------------------------------Table 3 : IR Mode Select (c) ADR DADS select The IR portion uses these discrete inputs to know which air data source to use: -------------------------------------------------------------------| Auto | Manual | IR Selection | | ADR DADS | ADR DADS | | -------------------------------------------------------------------| Open | Open | The IR uses the air data received | | | | on port 1 | |-------------|----------------|-----------------------------------| | Open | Ground | The IR uses the air data received | | | | on port 2 | |-------------|----------------|-----------------------------------| | Ground | Not applicable | The IR goes automatically from one| | | | air data source to the others | | | | according to their validity and | | | | priority. | -------------------------------------------------------------------Table 4 : ADR DADS Select

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The A/C is wired in the automatic ADR selection mode with the following priority: 1: its own ADR unit 2: ADR received on port 1 3: ADR received on port 2. (d) SDI program pins These discretes code the installation side of the ADIRU. The following table gives the IR side according to the SDI. -------------------------------------------| SDI-MSB | SDI-LSB | ADIRU NUMBER | -------------------------------------------| OPEN | GROUND | 1 | | GROUND | OPEN | 2 | | GROUND | GROUND | 3 | -------------------------------------------Table 5 : IR SDI Code (e) Aircraft ident The IR portion uses input discretes to identify the aircraft (type, engine model) on which the ADIRU is installed, and to select the appropriate set of filters for inertial data. To perform this coding, the IR wires seven input discretes and one discrete for parity to a common. **ON A/C 001-049, 101-105, 151-199, 201-203, Post SB

34-1147 For A/C 001-004, (f) IR remote test The IR portion uses one discrete to select the remote test by external control. When this discrete is open, the test is not activated. When this discrete is grounded, the test is activated. In normal operation this discrete is open (unused), but can be also activated via the CFDIU (on ground). (g) GPS present These discretes are used to activate the GPS/IRS hybridization function (computation, BITE output). (h) GPS priority select The GPIRS function uses this discrete to modify the GPS priority. Each ADIRU receives data from the GPS portion of the two MMRs on the primary and secondary inputs.

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For each ADIRU, the primary and secondary GPS inputs are defined as follows: ---------------------------------------------------------| ADIRU SDI | PRIMARY INPUT | SECONDARY INPUT | |--------------------------------------------------------| 1 | GPS 1 (MMR1) | GPS 2 (MMR2) | | 2 | GPS 2 (MMR2) | GPS 1 (MMR1) | | 3 | GPS 1 (MMR1) | GPS 2 (MMR2) | ---------------------------------------------------------Depending on the GPS validity and GPS priority select input discrete status, the GPS source is defined as follows: ------------------------------------------------------------------------------| Priority | Primary | Secondary | GPS source | | Status | GPS | GPS |--------------------------------------| | | | | GPS priority | GPS priority | | | | | select : open | select : GND | ------------------------------------------------------------------------------| 1 | Valid | Valid | Primary | Secondary | | 2 | Valid | Fail | Primary | Primary | | 3 | Fail | Valid | Secondary | Secondary | | 4 | Fail | Fail | Primary | Secondary | ------------------------------------------------------------------------------**ON A/C 001-049, 101-105, 151-199, 201-203, C. Software Computation (Ref. Fig. 001) The software contains the program memory and provides the following basic functions: - real-time executive - attitude integration - velocity integration - position integration - GPS/IRS hybridization - output computation - built-in test (Ref. 34-18-00). The IR architecture utilizes two processors: - DSP C25 for interface with sensors - INTEL 80960 for I/O and maintenance functions. The IR software operates in one of three basic modes: alignment, navigation, or a reversionary attitude mode. These modes include various portions of the major functions. The real-time executive and built-in test functions interface with each function in each mode.

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The GPIR function computes a hybrid GPS/IRS solution utilizing inputs received from the IR function and GPSSUs. The GPIR function has two operating modes: GPIR NAV mode and GPIR ATT mode, as indicated by IR mode command. In GPIR NAV mode, all the system state transitions are slaved to the IR function (Align, NAV). (1) Alignment mode The alignment is the initialization mode for the IR. Its primary function is to initialize the attitude, velocity and position integration functions implemented in the navigation mode. This mode operates on the ground only. The IR alignment mode is divided into three parts: - coarse level processing The coarse level processing is engaged during the first 30 seconds of the IR alignment mode. This processing estimates the local vertical using the three accelerometers and the measured gravity. During coarse level processing of the alignment mode, the software computes the level coordinate frame, pitch and roll, and associated rates and accelerations. - gyro-compass (or azimuth) processing and level processing Gyro-compass processing is engaged after the 30 seconds of the IR alignment mode (coarse level complete) and runs for a minimum of 9.5 minutes. Gyro-compass processing is used to orient body frame to North (using earth rotation detection by gyros). During this alignment submode, an estimated latitude is computed using local vertical component of the earth rotation. During this submode, the results of the coarse level processing are sharpened to have a better knowledge of the coordinate frame. - position entry data processing This position initialization can take place in coarse level processing or gyro-compass processing. The latitude and longitude pair processed for position initialization is received from the same source (FMGC 1, FMGC 2 or CDU). As soon as a valid position initialization pair is received, the software performs three BITE tests to check if the entered latitude and longitude are within the following limits versus the position recorded at the end of the last power-up cycle: 3+3T test: the entered position and the position from the previous navigation mode must not differ by more than 3NM+(3NM/HR)*T, where T is the duration in hours of the previous navigation mode. Abs val( lat entered - lat recorded ) less than or equal to 1 deg.

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Abs val( long entered - long recorded ) less than or equal to 1 deg/cos(latitude) (Ref. 34-18-00). A third BITE test is performed on the entered latitude when an estimated latitude is available during the gyro-compass processing: Abs val(lat est) - (lat ent) less than or equal to 0.5⁰. The alignment is completed after 10 minutes if a valid position data has been received and verified by the IR. If not, the automatic sequencing to the NAV mode will be delayed after position data is received. The operations to enter position and the warnings associated to the tests performed in alignment mode are described in para. 3 (operation/control and indicating). The IR also offers the possibility to enter into a variant of the alignment mode called rapid realign or 30-second realign. This mode is selected by moving the CDU selector switch from NAV to OFF, then to NAV within five seconds, when the aircraft is on the ground (ground speed less than 20 knots). Valid position data must be received. During the rapid realign mode, all computed velocities are set to zero and a fine tuning of the alignment is performed using the attitude reference vertical and the heading data available from the last NAV phase as initial conditions. During the alignment mode, the IR outputs on the ARINC 429 bus may not be available. Position initialization of the ADIRU is transmitted to the GPSSU for its own initialization . In addition to position, the GPSSU requires initialization data of date and UTC. The IR portion receives date and UTC from the FMGC and transmits the data to the GPSSUs. The GPIR NAV mode alignment performs coarse level and ground align processing. All the system state transitions are slaved to the IR functions. The coarse level processing of the GPIR NAV mode initializes a parallel virtual platform to provide hybrid navigation data. The GPIR NAV mode ground align processing duplicates to the IR gyro-compass processing. The chronology of the validation of the outputs during the alignment is given in para. 2-D (IR output data). (2) Attitude mode The attitude mode is a reversionary mode which can be activated only by manual selection of the ATT mode on the CDU. The mode can be activated on the ground or in flight and is intended to provide a rapid attitude/heading restart capability if the IR has experienced total power shutdown or failures which do not disable the mechanization of the attitude computation. The necessity of selecting ATT is indicated by the IR on its action code (label 350 - code 04 =

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select ATT) and this data is used by the FWC to display a message on the ECAM displays and by the FMGC to display a message on the MCDU. This mode needs a 30-second initialization phase with the aircraft in level flight. During this phase, all the ARINC bus outputs are sent with their status matrix coded NCD (No Computed Data). At the end of the initialization phase, the IR sends valid outputs: - body axis accelerations and angular rates - pitch and roll attitude and rate - vertical acceleration - vertical velocity - baro-inertial altitude and vertical speed. The magnetic heading may also be valid if an initialization value has been sent by the FMGC (through the MCDU) or the CDU (Ref. para. D - IR output data for the complete list of valid outputs). The GPIR ATT mode is activated when the IR is in ATT mode after manual selection on the ADIRS CDU. A GPIR ATT mode alignment processing is performed before Pseudo Range or Delta Range measurement are used to update the 21-state Kalman filter. The measurements and measurement matrices used for updating are the same as those used in the GPIR NAV processing. (3) Hybrid partition The ADIRU receives Global Position System Sensor data as defined by ARINC 743 and integrates it with the inertial reference data to produce a hybrid navigation solution. The Northrop Grumman ADIRU ensures the integrity of the hybrid solution using a unique GPS/IRS integration technique called Autonomous Integrity Monitored Extrapolation (AIME). The key to this mechanization is the ability to detect and isolate slowly drifting satellite clock drifts with as few as four satellites. AIME accomplishes this through a set of Kalman filter operations and a Failure Detection and Exclusion (FDE) mechanization. The ADIRS operational modes are slaved to the IR operational modes of Align, Navigate and Attitude Reference. The AIME function is not available if the IR is in the Attitude Reference Mode. When two MMR are installed on the aircraft, the ADIRU will select the primary input unless a fault is detected. In the case of a primary MMR fault, the secondary MMR will be selected for the hybrid solution. If both MMR are fault, the AIME may be able to extrapolate the GPIRS data depending on the flight phase.

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**ON A/C 001-004, D. IR, GPS and GPIRS Output Data (1) Digital output characteristics The IRs have four independently buffered high-speed ARINC 429 digital output buses, designated bus output 1, 2, 3 and 4 - digital output table: This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI : (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - RANGE ACCURACY : measurement range maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT : unit in which the digital value is transmitted - SIG BIT : indicates whether a sign bit is available - BITS : number of bits used by the parameter in the label - UPD/MSEC : output transmission interval. The refresh rate is given in milliseconds. - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code. - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. When the GPS PRESENT programming pins input discretes are grounded (indicating GPS present), both the GPSSU outputs and the GPIRS integrated navigation solution outputs are transmitted on the IR output buses with the IR output data.

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 010 |PPOS LAT |W +/- 180 |Deg | | 6 |500 |BCD |LATP | | | | |90S-90N |& | | | | | | | | | |0.1 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 011 |PPOS LONG |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |180E-180W |& | | | | | | | | | |0.1 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 012 |GROUND |W 0 to 4096 |Kts | | 4 |500 |BCD | GS | | | |SPEED |0 to 1000 | | | | | | | | | | |R 1 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 013 |TRK ANGLE |W 0 to 359 |Deg | | 4 |500 |BCD | | | | |TRUE |R 0.1 | | | | | | | | | | |+/- 2.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 014 |MAG HDG |W 0 to 359.9|Deg | | 4 |500 |BCD | MH | | | | |R 0.1 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 015 |WIND SPEED|W 0 to 256 |Kts | | 3 |500 |BCD | WS | | | | |R 1 | | | | | | | | | | |+/- 9 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 016 |WIND DIR |W 0 to 359 |Deg | | 3 |500 |BCD | WD | | | |TRUE |R 1 | | | | | | | | | | |+/- 10 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 041 |SET LAT |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |90S-90N |& | | | | | | | | | |R 0.1 min |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 042 |SET LONG |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |R 0.1 min |& | | | | | | | | | | |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 043 |SET MAG |W 0 to 359 |Deg | | 3 |500 |BCD | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |HDG |R 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 044 |TRUE HDG |W 0 to 359.9|Deg | | 4 |500 |BCD |THDG | | | | |R 0.1 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 046 |SOFTWARE | | | | 19 |1000|DIS | | | | |IDENT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 052 |PITCH |W +/- 64 |Deg/| 29 | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 053 |ROLL |W +/- 64 |Deg/| 29 | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 054 |YAW |W +/- 64 |Deg/| 29 | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 310 |PPOS LAT |W +/- 180 |Deg | 29 | 20 |200 |BNR | | | | | |+/- 90 |& | | | | | | | | | |R 0.00017 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 311 |PPOS LONG |W +/- 180 |Deg | 29 | 20 |200 |BNR |LONP | | | | |R 0.00017 |& | | | | | | | | | | |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 312 |GROUND |W 0 to 4096 |Kts | | 15 | 40 |BNR | | | | |SPEED |0 to 1000 | | | | | | | | | | |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 313 |TRK - TRUE|W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 2.3⁰ | | | | | | | | | | |at 200 Kts | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 314 |TRUE HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 315 |WIND |W +/- 256 |Kts | | 15 |100 |BNR | | | | |SPEED |0 to 256 | | | | | | | | | | |R 0.0078 | | | | | | | | | | |+/- 9 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 316 |WIND DIR |W +/- 180 |Deg | 29 | 15 |100 |BNR | | | | |- TRUE |+/- 180 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 10 with | | | | | | | | | | |50 Knots | | | | | | | | | | |wind | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 317 |TRK - MAG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 3 at | | | | | | | | | | |200 Kts | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 320 |MAG HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |82 N to 60 S| | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 321 |DRIFT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | DA | | | |ANGLE |+/- 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 3⁰ at | | | | | | | | | | |200 Kts | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 322 |FLIGHT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | FPA | | | |PATH |+/- 90 | | | | | | | | | |ANGLE |R 0.0055 | | | | | | | | | | |+/- 0.24 at | | | | | | | | | | |200 Kts | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 323 |FLT PATH |W +/- 4 | g | 29 | 15 | 20 |BNR |FPAC | | | |ACCEL |R 0.0001 | | | | | | | | | | |+/- 10 % of | | | | | | | | | | |outp over | | | | | | | | | | |0.5 g | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 324 |PITCH |W +/- 180 |Deg | 29 | 15 | 20 |BNR |PTCH | | | |ANGLE |-90 to + 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 325 |ROLL |W +/- 180 |Deg | 29 | 15 | 20 |BNR |ROLL | | | |ANGLE |-90 to + 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 326 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |PTCR | | | |PITCH RATE|+/- 128 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 327 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |ROLR | | | |ROLL RATE |+/- 128 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 330 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |YAW | | | |YAW RATE |+/- 128 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 331 |BODY LONG |W +/- 4 | g | 29 | 15 | 20 |BNR |LONG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 332 |BODY LAT |W +/- 4 | g | 29 | 15 | 20 |BNR |LATG | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 333 |BODY NORM |W +/- 4 | g | 29 | 15 | 20 |BNR |VRTG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 334 |PLATFORM |W +/- 180 |Deg | 29 | 15 |100 |BNR | | | | |HEADING |R 0.0055 | | | | | | | | | | |+/- 0.40 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 335 |TRK ANGLE |W +/- 32 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.001 |s | | | | | | | | | |+/- 0.15 at | | | | | | | | | | |200 Knots | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 336 |PITCH ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.0039 |s | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 337 |ROLL ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.0039 |s | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 340 |TRACK |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |ANGLE |R 0.0055 | | | | | | | | | |GRID |+/- 2.3 at | | | | | | | | | | |200 Kts | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 341 |GRID |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |HEADING |R 0.0055 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 360 |POTENTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR | | | | |V/S |R 1.0 | min| | | | | | | | | |+/- 30 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 361 |INERTIAL |W +/- 131072|ft | 29 | 20 | 40 |BNR | | | | |ALT |R 0.125 | | | | | | | | | | |+/- 5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 362 |ALONG TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | | | |HORIZ |R 0.00012 | | | | | | | | | |ACCEL |+/- 10 % | | | | | | | | | | |of outp | | | | | | | | | | |over 0.5 g | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 363 |CROSS TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | | | |HORIZ |R 0.00012 | | | | | | | | | |ACCEL |+/- 10 % | | | | | | | | | | |of outp | | | | | | | | | | |over 0.5 g | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 364 |VERTICAL |W +/- 4 | g | 29 | 15 | 20 |BNR |VACC | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.00012 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 365 |INERTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR |IVV | | | |V/S |R 1.0 |min | | | | | | | | | |+/- 30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 366 |N - S |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 367 |E - W |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 275 |DSCRT DATA| | | | |500 |DIS | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |WORD 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 276 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 277 |IRS TEST | | | | | |HYB | | | | |WORD | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 350 |ACTION | | | | |500 |HYB | | | | |CODE | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 354 |LRU IDENT | | | | |500 |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 356 |FAULT STAT| | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQUIP | | | | |1000|HEX | | | | |IDENT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 076 |GPS ALT - |W +/- 131072| ft | | 20 |1000|BNR | | | | |MSL |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 101 |HDOP |W 0 to 1024 | | | 15 |1000|BNR | | | | | |R 0.031 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 102 |VDOP |W 0 to 1024 | | | 15 |1000|BNR | | | | | |R 0.031 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 103 |GPS TRACK |W +/- 180 |DEG | | 15 |1000|BNR | | | | |ANGLE TRUE|R 0.005493 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 110 |GPS PRES |W +/- 180 |DEG | | 20 |1000|BNR | | | | |POS - LAT |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 111 |GPS PRES |W +/- 180 |DEG | | 20 |1000|BNR | | | | |POS - LON |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 112 |GPS GROUND|W +/- 4096 |Kts | | 15 |1000|BNR | | | | |SPEED |R 0.125 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 120 |GPS PRES |W +/- 000172|Deg | | 11 |1000|BNR | | | | |POS - LAT |R 8.38E-8 | | | | | | | | | |FRAC |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 121 |GPS PRES |W +/- 000172|Deg | | 11 |1000|BNR | | | | |POS - LON |R 8.38E-8 | | | | | | | | | |FRAC |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 125 |GPS |W 0.23:59:9 |H / | | 5 |1000|BCD | | | | |UTC-BCD |R 0.1 min |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 130 |GPS INTEG |W 0 - 16 |NM | | 18 |1000|BNR | | | | |LIMIT HORI|R 6.1E-5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 133 |GPS INTEG |W 0 - 32768 |ft | | 18 |1000|BNR | | | | |LIMIT VERT|R 0,125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 136 |VERT |w 0 - 32678 |M | | 18 |1000|BNR | | | | |FOM-GPS |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 150 |GPS |W 0-23:59:59|H / | | 17 |1000|BNR | | | | |UTC-BNR |R 1 sec |min/| | | | | | | | | | |sec | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 165 |GPS VERT |w +/- 32768 |Ft/ | | 15 |1000|BNR | | | | |SPEED |R 1.00 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 166 |GPS N-S |W +/- 4096 |Kts | | 15 |1000|BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 174 |GPS E-W |w +/- 4096 |Kts | | 15 |1000|BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 247 |HORIZ FIG |W 0 - 16 |Nm | | 18 |1000|BNR | | | | |OF |R 6.1E-5 | | | | | | | | | |MERIT-GPS | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 260 |GPS DATE |R 1 DAY |D:M:| | 6 |1000|BCD | | | | | | |Y | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 273 |GPS SENSOR|W N/A | | | |1000|DIS | | | | |STATUS |R N/A | | | | | | | | ------------------------------------------------------------------------------Table 6 :IR Digital Output Characteristics **ON A/C 001-049, 101-105, 151-199, 201-203, Post SB

34-1147 For A/C 001-004,

D. IR, GPS and GPIRS Output Data (1) Digital output characteristics The IRs have four independently buffered high-speed ARINC 429 digital output buses, designated bus output 1, 2, 3 and 4 - digital output table: This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI : (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - RANGE ACCURACY : measurement range maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT : unit in which the digital value is transmitted - SIG BIT : indicates whether a sign bit is available - BITS : number of bits used by the parameter in the label - UPD/MSEC : output transmission interval. The refresh rate is given in milliseconds. - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code.

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- ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. When the GPS PRESENT programming pins input discretes are grounded (indicating GPS present), both the GPSSU outputs and the GPIRS integrated navigation solution outputs are transmitted on the IR output buses with the IR output data.

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 010 |PPOS LAT |W +/- 180 |Deg | | 6 |500 |BCD |LATP | | | | |90S-90N |& | | | | | | | | | |0.1 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 011 |PPOS LONG |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |180E-180W |& | | | | | | | | | |0.1 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 012 |GROUND |W 0 to 4096 |Kts | | 4 |500 |BCD | GS | | | |SPEED |0 to 1000 | | | | | | | | | | |R 1 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 013 |TRK ANGLE |W 0 to 359 |Deg | | 4 |500 |BCD | | | | |TRUE |R 0.1 | | | | | | | | | | |+/- 2.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 014 |MAG HDG |W 0 to 359.9|Deg | | 4 |500 |BCD | MH | | | | |R 0.1 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 015 |WIND SPEED|W 0 to 256 |Kts | | 3 |500 |BCD | WS | | | | |R 1 | | | | | | | | | | |+/- 9 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 016 |WIND DIR |W 0 to 359 |Deg | | 3 |500 |BCD | WD | | | |TRUE |R 1 | | | | | | | | | | |+/- 10 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 041 |SET LAT |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |90S-90N |& | | | | | | | | | |R 0.1 min |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 042 |SET LONG |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |R 0.1 min |& | | | | | | | | | | |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 043 |SET MAG |W 0 to 359 |Deg | | 3 |500 |BCD | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |HDG |R 1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 044 |TRUE HDG |W 0 to 359.9|Deg | | 4 |500 |BCD |THDG | | | | |R 0.1 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 046 |SOFTWARE | | | | 19 |1000|DIS | | | | |IDENT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 052 |PITCH |W +/- 64 |Deg/| 29 | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 053 |ROLL |W +/- 64 |Deg/| 29 | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 054 |YAW |W +/- 64 |Deg/| 29 | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 310 |PPOS LAT |W +/- 180 |Deg | 29 | 20 |200 |BNR | | | | | |+/- 90 |& | | | | | | | | | |R 0.00017 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 311 |PPOS LONG |W +/- 180 |Deg | 29 | 20 |200 |BNR |LONP | | | | |R 0.00017 |& | | | | | | | | | | |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 312 |GROUND |W 0 to 4096 |Kts | | 15 | 40 |BNR | | | | |SPEED |0 to 1000 | | | | | | | | | | |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 313 |TRK - TRUE|W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 2.3⁰ | | | | | | | | | | |at 200 Kts | | | | | | | |

  EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 27   Config-1 Feb 01/07 R  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 314 |TRUE HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 315 |WIND |W +/- 256 |Kts | | 15 |100 |BNR | | | | |SPEED |0 to 256 | | | | | | | | | | |R 0.0078 | | | | | | | | | | |+/- 9 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 316 |WIND DIR |W +/- 180 |Deg | 29 | 15 |100 |BNR | | | | |- TRUE |+/- 180 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 10 with | | | | | | | | | | |50 Knots | | | | | | | | | | |wind | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 317 |TRK - MAG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 3 at | | | | | | | | | | |200 Kts | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 320 |MAG HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |82 N to 60 S| | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 321 |DRIFT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | DA | | | |ANGLE |+/- 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 3⁰ at | | | | | | | | | | |200 Kts | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 322 |FLIGHT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | FPA | | | |PATH |+/- 90 | | | | | | | | | |ANGLE |R 0.0055 | | | | | | | | | | |+/- 0.24 at | | | | | | | | | | |200 Kts | | | | | | | |

  EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 28   Config-1 Feb 01/07 R  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 323 |FLT PATH |W +/- 4 | g | 29 | 15 | 20 |BNR |FPAC | | | |ACCEL |R 0.0001 | | | | | | | | | | |+/- 10 % of | | | | | | | | | | |outp over | | | | | | | | | | |0.5 g | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 324 |PITCH |W +/- 180 |Deg | 29 | 15 | 20 |BNR |PTCH | | | |ANGLE |-90 to + 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 325 |ROLL |W +/- 180 |Deg | 29 | 15 | 20 |BNR |ROLL | | | |ANGLE |-90 to + 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 326 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |PTCR | | | |PITCH RATE|+/- 128 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 327 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |ROLR | | | |ROLL RATE |+/- 128 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 330 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |YAW | | | |YAW RATE |+/- 128 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 331 |BODY LONG |W +/- 4 | g | 29 | 15 | 20 |BNR |LONG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 332 |BODY LAT |W +/- 4 | g | 29 | 15 | 20 |BNR |LATG | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 333 |BODY NORM |W +/- 4 | g | 29 | 15 | 20 |BNR |VRTG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 334 |PLATFORM |W +/- 180 |Deg | 29 | 15 |100 |BNR | | | | |HEADING |R 0.0055 | | | | | | | | | | |+/- 0.40 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 335 |TRK ANGLE |W +/- 32 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.001 |s | | | | | | | | | |+/- 0.15 at | | | | | | | | | | |200 Knots | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 336 |PITCH ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.0039 |s | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 337 |ROLL ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.0039 |s | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 340 |TRACK |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |ANGLE |R 0.0055 | | | | | | | | | |GRID |+/- 2.3 at | | | | | | | | | | |200 Kts | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 341 |GRID |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |HEADING |R 0.0055 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 360 |POTENTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR | | | | |V/S |R 1.0 | min| | | | | | | | | |+/- 30 | | | | | | | |

  EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 30   Config-1 Feb 01/07 R  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 361 |INERTIAL |W +/- 131072|ft | 29 | 20 | 40 |BNR | | | | |ALT |R 0.125 | | | | | | | | | | |+/- 5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 362 |ALONG TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | | | |HORIZ |R 0.00012 | | | | | | | | | |ACCEL |+/- 10 % | | | | | | | | | | |of outp | | | | | | | | | | |over 0.5 g | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 363 |CROSS TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | | | |HORIZ |R 0.00012 | | | | | | | | | |ACCEL |+/- 10 % | | | | | | | | | | |of outp | | | | | | | | | | |over 0.5 g | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 364 |VERTICAL |W +/- 4 | g | 29 | 15 | 20 |BNR |VACC | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.00012 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 365 |INERTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR |IVV | | | |V/S |R 1.0 |min | | | | | | | | | |+/- 30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 366 |N - S |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 367 |E - W |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 275 |DSCRT DATA| | | | |500 |DIS | | |

  EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 31   Config-1 Feb 01/07 R  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |WORD 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 276 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 277 |IRS TEST | | | | | |HYB | | | | |WORD | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 350 |ACTION | | | | |500 |HYB | | | | |CODE | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 354 |LRU IDENT | | | | |500 |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 356 |FAULT STAT| | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQUIP | | | | |1000|HEX | | | | |IDENT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 076 |GPS ALT - |W +/- 131072| ft | | 20 |1000|BNR | | | | |MSL |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 101 |HDOP |W 0 to 1024 | | | 15 |1000|BNR | | | | | |R 0.031 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 102 |VDOP |W 0 to 1024 | | | 15 |1000|BNR | | | | | |R 0.031 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 103 |GPS TRACK |W +/- 180 |DEG | | 15 |1000|BNR | | | | |ANGLE TRUE|R 0.005493 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 110 |GPS PRES |W +/- 180 |DEG | | 20 |1000|BNR | | | | |POS - LAT |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 111 |GPS PRES |W +/- 180 |DEG | | 20 |1000|BNR | | | | |POS - LON |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 112 |GPS GROUND|W +/- 4096 |Kts | | 15 |1000|BNR | | | | |SPEED |R 0.125 | | | | | | | |

  EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 32   Config-1 Feb 01/07 R  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 120 |GPS PRES |W +/- 000172|Deg | | 11 |1000|BNR | | | | |POS - LAT |R 8.38E-8 | | | | | | | | | |FRAC |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 121 |GPS PRES |W +/- 000172|Deg | | 11 |1000|BNR | | | | |POS - LON |R 8.38E-8 | | | | | | | | | |FRAC |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 125 |GPS |W 0.23:59:9 |H / | | 5 |1000|BCD | | | | |UTC-BCD |R 0.1 min |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 130 |GPS INTEG |W 0 - 16 |NM | | 18 |1000|BNR | | | | |LIMIT HORI|R 6.1E-5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 131 |HYB INTEG |W 0 - 16 |NM | | 17 |1000|BNR | | | | |LIMIT HORI|R 1,22 E-4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 132 |HYB TRUE |W +/- 180 |Deg | | 15 | 40 |BNR | | | | |HEADING |R 5,5 E-3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 133 |GPS INTEG |W 0 - 32768 | ft | | 18 |1000|BNR | | | | |LIMIT VERT|R 0,125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 135 |HYB VERT |W 0 - 32768 | ft | | 18 |1000|BNR | | | | |FOM |R 0,125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 136 |GPS VERT |W 0 - 32678 | ft | | 18 |1000|BNR | | | | |FOM |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 137 |HYB TRACK |W +/- 180 |Deg | | 15 | 40 |BNR | | | | |ANGLE TRUE|R 5,5E-3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 150 |GPS |W 0-23:59:59|H / | | 17 |1000|BNR | | | | |UTC-BNR |R 1 sec |min/| | | | | | | | | | |sec | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 165 |GPS VERT |w +/- 32768 |Ft/ | | 15 |1000|BNR | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |SPEED |R 1.00 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 166 |GPS N-S |W +/- 4096 |Kts | | 15 |1000|BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 174 |GPS E-W |w +/- 4096 |Kts | | 15 |1000|BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 175 |HYBRID |W +/- 4096 |Kts | | 15 | 40 |BNR | | | | |GROUND-SPD|R 0,125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 247 |HORIZ FIG |W 0 - 16 |Nm | | 18 |1000|BNR | | | | |OF |R 6.1E-5 | | | | | | | | | |MERIT-GPS | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 254 |HYB PRES |W +/- 180 |Deg | | 20 | 100|BNR | | | | |POS - LAT |R 1.72E-4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 255 |HYB PRES |W +/- 180 |Deg | | 20 | 100|BNR | | | | |POS - LON |R 1.72E-4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 256 |HYB PRES |W+/-0,000172|Deg | | 11 | 100|BNR | | | | |POS-LAT FR|R 8,38E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 257 |HYB PRES |W+/-0,000172|Deg | | 11 | 100|BNR | | | | |POS-LON FR|R 8,38E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 260 |GPS DATE |R 1 DAY |D:M:| | 6 |1000|BCD | | | | | | |Y | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 261 |HYBRID |W +/- 131072| ft | | 20 | 40 |BNR | | | | |ALTITUDE |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 263 |HYB FLIGHT|W +/- 180 |Deg | | 12 | 40 |BNR | | | | |PATH ANGLE|R 0.044 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 264 |HYB HORIZ |W 0 - 16 |NM | | 18 |1000|BNR | | | | |FOM |R 6,1e-5 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 266 |HYB N - S |W +/- 4096 |Kts | | 15 | 100|BNR | | | | |VELOCITY |R 0,125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 267 |HYB E - W |W +/- 4096 |Kts | | 15 | 100|BNR | | | | |VELOCITY |R 0,125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 273 |GPS SENSOR|W N/A | | | 19 |1000|DIS | | | | |STATUS |R N/A | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 274 |GPADIRS |W N/A | | | 19 |1000|DIS | | | | |STATUS |R N/A | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 345 |HYBRID |W +/- 32768 |ft/ | | 15 | 40 |BNR | | | | |VERT SPEED|R 1 | mn | | | | | | | ------------------------------------------------------------------------------Table 6 :IR Digital Output Characteristics ----------------------------------------------------------| BIT | FUNCTION | | No. | | ----------------------------------------------------------| 9 | SDI | | 10 | SDI | | 11 | Reserved | | 12 | DADS Status* Present=0 , Not Present=1 | | 13 | DADS Source* Primary=0 , Secondary=1 | | 14 | IR/FMS Status Present=0 , Not Present=1 | | 15 | IR/FMS Source Primary=0 , Secondary=1 | | 16 | -| | 17 | | - NUMBER OF SATELLITES | | 18 | | VISIBLE (0 - 15) | | 19 | -| | 20 | -| | 21 | | - NUMBER OF SATELLITES | | 22 | | TRACKED (0 - 15) | | 23 | -| | 24 | SPARE |

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----------------------------------------------------------| BIT | FUNCTION | | No. | | ----------------------------------------------------------| 25 | SPARE | | 26 | -| | 27 | | - GPSSU OPERATIONAL | | 28 | -MODE (Ref. Table Below) | | 29 | RESERVED | | 30 | SSM | | 31 | SSM | | 32 | PARITY (Odd) | ----------------------------------------------------------Table 7 : GPS Discrete Word 273 Output Format * DADS input not required if altitude is received from IR/FMS inputs. -----------------------------------------------------| GPSSU MODE | BIT 28 | BIT 27 | BIT 26 | |-------------------|----------|----------|----------| | SELF TEST | 0 | 0 | 0 | | INITIALIZATION | 0 | 0 | 1 | | ACQUISITION | 0 | 1 | 0 | | NAVIGATION | 0 | 1 | 1 | | ALTITUDE AIDING | 1 | 0 | 0 | | SPARE | 1 | 0 | 1 | | SPARE | 1 | 1 | 0 | | FAULT | 1 | 1 | 1 | -----------------------------------------------------------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 131 |HYBRID |W 0 - 16 |Nm | | 18 |1000| | | | | |INTEG |R 6.1E-5 | | | | | | | | | |LIMIT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 132 |HYBRID |W +/- 180 |Deg | | 15 |1000| | | | | |TRUE HDG |R 5.5e-3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 132 |HYBRID |W +/- 180 |Deg | | 15 | 40 | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |TRUE HDG |R 5.5E-3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 135 |VERT |W 0-32,678 |M | | 18 |1000| | | | | |FOM-HYBRID|R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 137 |HYBRID |W +/- 180 |Deg | | 15 | 40 | | | | | |TRACK |R 5.5E-3 | | | | | | | | | |ANGLE TRUE| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 175 |HYBRID |W +/- 4096 |Kts | | 15 | 40 | | | | | |GND SPEED |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 254 |HYBRID |W +/- 180 |Deg | | 20 | 100| | | | | |PRES |R 1.72E-4 | | | | | | | | | |POS - LAT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 255 |HYBRID |W +/- 180 |Deg | | 20 | 100| | | | | |PRES |R 1.72E-4 | | | | | | | | | |POS - LON | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 256 |HYBRID |W +/-.000172|Deg | | 11 | 100| | | | | |LAT |R 8.38E-8 | | | | | | | | | |FRACTIONS | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 257 |HYBRID |W +/-.000172|Deg | | 11 | 100| | | | | |LON |R 8.38E-8 | | | | | | | | | |FRACTIONS | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 261 |HYBRID |W +/- 131072|Ft | | 20 | 40 | | | | | |ALTITUDE |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 263 |HYBRID |W +/- 180 |Deg | | 12 | 40 | | | | | |FLIGHT |R 0.044 | | | | | | | | | |PATH ANGLE| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 264 |HORIZ FIG |W 0 - 16 |Nm | | 18 |1000| | | | | |OF MERIT -|R 6.1E-5 | | | | | | | | | |HYBRID | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 266 |HYBRID N-S|W +/- 4096 |Kts | | 15 | 100| | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 267 |HYBRID E-W|W +/- 4096 |Kts | | 15 | 100| | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 345 |HYBRID |W +/- 32768 |Ft/ | | 15 | 40 | | | | | |VERT |R 1.00 |mn | | | | | | | | |VELOCITY | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 274 |GPADIRS | | | | |1000| | | | | |STATUS | | | | | | | | | ------------------------------------------------------------------------------Table 8 : GPIRS Digital Output Characteristics -----------------------------------------------------------------------------| BIT | FUNCTION | | No. | | |-------|--------------------------------------------------------------------| | 9 | SPARE | | 10 | SPARE | | 11 | SPARE | | 12 | SPARE | | 13 | SPARE | | 14 | SPARE | | | _ | | 15 | | SECONDARY GPSSU VALIDITY (See Table Below) | | 16 | _| | | | _ | | 17 | | PRIMARY GPSSU VALIDITY (See Table Below) | | 18 | _| | | 19 | GPSSU SOURCE (SECONDARY = 1, PRIMARY = 0) | | 20 | -- LSB | | 21 | | - No. OF SATELLITES TRACKED (0-15) | | 22 | | | | 23 | -- MSB | | 24 | SPARE |

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-----------------------------------------------------------------------------| BIT | FUNCTION | | No. | | |-------|--------------------------------------------------------------------| | 25 | SPARE | | 26 | -| | 27 | | -GPIRS OPERATIONAL MODE (See Table Below) | | 28 | -| | 29 | RESERVED | | 30 | SSM | | 31 | SSM | | 32 | PARITY (ODD) | -----------------------------------------------------------------------------Table 9 : GPIRS Status - Label 274 ------------------------------------------| SECONDARY GPSSU | BIT 16 | BIT 15 | | VALIDITY | | | |-------------------|----------|----------| | VALID | 0 | 0 | | INACTIVE | 0 | 1 | | FUNCTIONAL TEST | 1 | 0 | | FAIL | 1 | 1 | ------------------------------------------------------------------------------------| PRIMARY GPSSU | BIT 18 | BIT 17 | | VALIDITY | | | |-------------------|----------|----------| | VALID | 0 | 0 | | INACTIVE | 0 | 1 | | FUNCTIONAL TEST | 1 | 0 | | FAIL | 1 | 1 | -----------------------------------------------------------------------------------------------| GPIRS | BIT 28 | BIT 27 | BIT 26 | | OPERATIONAL MODE | | | | |-------------------|----------|----------|----------| | SELF TEST MODE | 0 | 0 | 0 | | INITIALIZATION | 0 | 0 | 1 | | ACQUISITION | 0 | 1 | 0 | | NAVIGATION | 0 | 1 | 1 | | ALT/CLK AIDING | 1 | 0 | 0 | | SPARE | 1 | 0 | 1 | | SPARE | 1 | 1 | 0 | | FAULT MODE | 1 | 1 | 1 |

  EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 39   Config-1 Feb 01/07 R  CES

 

-----------------------------------------------------| GPIRS | BIT 28 | BIT 27 | BIT 26 | | OPERATIONAL MODE | | | | |-------------------|----------|----------|----------| -----------------------------------------------------(Ref. Fig. 002) **ON A/C 001-049, 101-105, 151-199, 201-203, (Ref. Fig. 003, 004, 005)

  EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 40   Config-1 Feb 01/07 R  CES

 

GPIRS Hybrid Parameter Sign Status Matrix Requirements Figure 002   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 41   Config-1 Feb 01/07 R  CES

 

IR - Binary Output Word 1/2 Figure 003   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 42   Config-1 Feb 01/07 R  CES

 

IR - Binary Output Word 2/2 Figure 004   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 43   Config-1 Feb 01/07 R  CES

 

IR - BCD and Special Output Words Figure 005   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 44   Config-1 Feb 01/07 R  CES

 

(2) Discrete outputs The IR provides three discrete outputs. Table below defines the characteristics of these discretes. --------------------------------------| SIGNAL | OUTPUT | DEFINITION | |----------|-------------|------------| | ON BAT | OPEN/+28VDC | NO/YES | | IR FAULT | OPEN/+28VDC | NO/YES | | IR ALIGN | OPEN/GROUND | NO/YES | --------------------------------------- ON BAT When the IR is powered with batteries, this discrete delivers a 28VDC state and sets the ON BAT light to on. - IR FAULT When a failure is detected by the IR, this discrete delivers a 28VDC state and sets the FAULT legend to on. - IR ALIGN When the IR is aligning, this discrete delivers a ground and sets the ALIGN legend to on.

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 45   Config-1 Feb 01/07  CES

 

3. ________________________________ Operation/Control and Indicating R R R

A. Control **ON A/C 001-049, 101-105, 151-199,

R R

(Ref. Fig. 006) **ON A/C 201-203,

R R

(Ref. Fig. 006A) **ON A/C 001-049, 101-105, 151-199, 201-203,

R R R R R R R R R R R

(1) Modes of operation Operation interface with the IR is performed through the Multipurpose Control and Display Unit 1(2) (MCDU) or the CDU. The MCDU 1(2) is used for entering initialization data and displaying IR data. (Ref. Fig. 007) The CDU is used for mode selection, IR annunciation (FAULT, ALIGN), for entering initialization data and displaying IR data. The IR has three selectable modes: OFF, NAV and ATT. The relation between the mode selection and system response is shown in the figure. (Ref. Fig. 008)

R R R R R R R R R

(2) OFF mode When the OFF/NAV/ATT selector switch on the CDU is in the OFF position, all circuitry in the ADIRU is de-energized except for any logic associated with the power-off function. When the ADIRU has turned off, it consumes less than 10 milliamps (needed for power supply turn-on control). The power supply of the ADMs is switched off. A period is required between switching to OFF and actual power-off. During this sequence, the last position computed is stored. (3) NAV (Navigation) mode After selection of the NAV mode on the ground, the IR automatically enters the NAV mode if a self-determined satisfactory alignment has been completed. If alignment is not completed, the IR remains in the Align submode. No updating of the IR present position latitude and longitude is allowed once the IR has completed the Align submode.

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IR - Operation/Control and Indicating Figure 006   R EFF : 001-049, 101-105, 151-199,  34-14-00 Page 47   Config-1 Feb 01/07  CES

 

IR - Operation/Control and Indicating Figure 006A   R EFF : 201-203,  34-14-00 Page 48   Config-1 Feb 01/07  CES

 

IR - Alignment Procedure from the MCDU Figure 007   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 49   Config-1 Feb 01/07 R  CES

 

IR - Mode State Diagram Figure 008   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 50   Config-1 Feb 01/07 R  CES

 

The IR latitude and longitude entered during alignment is the starting point for its computation. The following logical processes are mechanized: - OFF to NAV provides automatic alignment in 10 minutes for latitudes between 73⁰N and 60⁰S, with automatic entry to NAV mode. Requires initial position data to be entered. NOTE : The automatic alignment requires 15 mn delay for latitudes ____ between 73⁰N and 82⁰N. For high latitudes, the alignment is provided by an operational procedure which delays the entering of the initial position by the crew. Accuracies of the system are slightly degraded. - a message on the UPPER ECAM DU indicates that the IRs are in ALIGN submode with the maximum time until NAV - in the NAV mode, rapid realignment of the IR is initiated by switching the OFF/NAV/ATT selector switch from NAV to OFF and back to NAV within 5 seconds. The IR starts a 30-second realignment submode with existing attitude and heading angles and rezeroed velocities - the system does not enter the rapid realignment sequence if the ground speed is greater than 20 knots. The CDU permits to observe some particular parameters (Ref. 34-12-00). (a) Initialization data (Ref. Fig. 009) IR alignment is carried out on the ground before takeoff and after the entry of the current aircraft coordinates on the INIT page of the MCDU 1(2) (Ref. 22-72-00) or on the CDU (DATA DISPLAY selector switch in PPOS position). Valid initial position data must be received and verified by the IR during the 10-minute alignment or automatic sequencing to the NAV mode will be delayed after position data is received. Initial position data are verified by the IR (Ref. Para. 2.C.(1)-Position entry data processing). If a miscompare exists then: - on the ADIRS CDU, the ALIGN light flashes. - a message ENTER PPOS is displayed on the CDU (DATA DISPLAY selector switch in STS position). The miscompare is removed and the position data verified by the IR when: - the last two Set Latitudes received by the IR are identical and the last two Set Longitudes received by the IR are identical, or

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MCDU - INIT Page Figure 009   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 52   Config-1 Feb 01/07 R  CES

 

- the last Set Latitude and Set Longitude received by the IR compare within one degree (or one degree divided by cos(latitude)) of the latitude and longitude from the previous flight. (b) Latitude comparison The IR compares Set Latitude with a self-computed gyro-compass latitude after 10 minutes into alignment or any subsequent time when a valid Set Latitude is available. In case of discrepancy, on the ADIRS CDU the ALIGN light flashes. The message ENTER PPOS is displayed on the CDU (DATA DISPLAY selector switch in STS position). The discrepancy exists when: - the entered latitude differs from the computed latitude by more than 0.5⁰. The miscompare is removed if a subsequent entry of Set Latitude passes the test. If latitude test fails two times with identical set latitude inputs then: - the IR FAULT legend flashes on the CDU - the message IR FAULT appears on the CDU liquid crystal display (DATA DISPLAY selector switch in STS position) - a warning message appears on the upper ECAM DU: NAV IR 1(2)(3) FAULT. (c) Excessive motion The IR performs an excessive motion test during the Align submode. If taxiing or towing causes a step input which exceeds 0.2 ft/s in the X or Y velocity, then: - the EXCESS MOTION message is displayed on the CDU (DATA DISPLAY selector switch in STS position) - the following message is displayed on the upper ECAM DU: NAV IR 1(2)(3) NOT ALIGN EXCESS MOTION IR 1(2)(3) IN ALIGN - the attitude information is flagged on the PFD. Thirty seconds after motion detection, the system reverts to a full alignment (time to the end of alignment will revert to 9 min 30 s). It is not necessary to re-enter the position.

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(d) Thirty-second rapid realignment A thirty-second rapid realignment is provided by moving the OFF/NAV/ATT selector switch on the CDU from NAV to OFF and back to NAV within five seconds. A subsequent switching on the selector switch from NAV to OFF and back to NAV within 5 seconds during the 30-second realignment causes the system to start the 30-second realignment again. The realignment is initialized with existing attitude and heading angles. Velocities are zeroed. Valid position data must be received and verified by the IR during the 30-second realignment. (4) ATT (Attitude) mode The IR has a reversionary mode which can be activated only by manual selection of ATT mode on the CDU. The mode can be activated on the ground or in flight and is intended to provide a rapid attitude/heading restart capability in the event that the IR has experienced a total power shutdown or a failure has occurred resulting in the following: - IR FAULT legend flashing on the CDU - IR 1(2)(3) FAULT message displayed on the upper ECAM DU: IR x MODE SEL...ATT - SELECT ATT message displayed on the CDU (DATA DISPLAY selector switch in STS position). The IR is designed so that the ATT mode can be used after BITE has detected failures which will cause excessive NAV mode data errors but does not disable the ATT mode mechanization. However, it is recommended to stay in NAV mode even with excessive navigation errors because of higher accuracy of attitude signals and a more complete signal processing. The ATT mode must always be used after loss of power or a similar situation in flight where a new alignment/leveling is required. The ENTER HEADING message is displayed on the CDU (DATA DISPLAY selector switch in STS position) when the ATT mode is selected until valid heading initialization is received from the MCDU or the CDU. The ATT mode is normally engaged with the aircraft in level flight. A 30-second period is needed with the aircraft in level flight to perform an attitude erection to initialize a level attitude. During this period, the data normally computed in ATT mode have SSMs set to NCD.

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**ON A/C 001-049, 101-105, 151-199, B. Indicating Attitude and heading information is computed by the ADIRU (IR portion) and processed by the associated DMC. The attitude data are displayed on the PFD and the heading data are displayed on the PFD, the ND and the VOR/DME RMI. In addition, vertical speed (V/S) is displayed on the PFD and Ground Speed and wind indications are displayed on the ND. In normal configuration, with the ATT/HDG selector switch in NORM position, the IR1 data are displayed on the CAPT PFD, ND and the VOR/DME RMI (Ref. ATA 34-57-00). The IR2 data are displayed on the F/O PFD and ND. The following parameters can be displayed on the CDU liquid crystal display according to the position of the DATA DISPLAY selector switch on the CDU: - wind (WIND) - present position (PPOS) - true heading (HDG) - status of selected system conditions (STS) - track and ground speed (TK/GS) - test values (TEST). The sources of the data displayed are controlled by the SYS DISPLAY selector switch on the CDU. **ON A/C 201-203, B. Indicating Attitude and heading information is computed by the ADIRU (IR portion) and processed by the associated DMC. The attitude data are displayed on the PFD and the heading data are displayed on the PFD, the ND and the VOR/ADF/DME RMI. In addition, vertical speed (V/S) is displayed on the PFD and Ground Speed and wind indications are displayed on the ND. In normal configuration, with the ATT/HDG selector switch in NORM position, the IR1 data are displayed on the CAPT PFD, ND and the VOR/ADF/DME RMI (Ref. ATA 34-57-00). The IR2 data are displayed on the F/O PFD and ND. The following parameters can be displayed on the CDU liquid crystal display according to the position of the DATA DISPLAY selector switch on the CDU: - wind (WIND) - present position (PPOS) - true heading (HDG) - status of selected system conditions (STS)

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- track and ground speed (TK/GS) - test values (TEST). The sources of the data displayed are controlled by the SYS DISPLAY selector switch on the CDU. **ON A/C 001-049, 101-105, 151-199, 201-203, (1) Attitude information (Ref. Fig. 010) The aircraft roll and pitch attitude is indicated in the center part of the PFD by a sphere representing a conventional ADI drum. (Ref. 31-64-00 for sphere definition and display). (a) Pitch angle information (item A) The A/C present pitch angle is given by the vertical displacements of the pitch attitude scale with respect to the center of the A/C reference. The scale moves behind the cut-sphere shaped window, limited by the lines of an upper and a lower sector. The scale rotates around the center of the A/C reference in accordance with the A/C present roll angle. The pitch scale comprises white reference lines and associated pitch angle values. The lines are given every 2.5 degrees from 0 to 30 degrees, then for the 50 degrees and 80 degrees values for positive pitch angles. For negative pitch angles, the lines are given every 2.5 degrees from 0 to 10 degrees, then for the 15 degrees, 20 degrees, 30 degrees, 50 degrees and 80 degrees values. Beyond 30 degrees, red large arrow heads (V-shaped) indicate an excessive attitude and the direction to follow in order to reduce it (item B). (b) Roll angle information (item A) A yellow triangle which remains on the line going through the center of the A/C reference and which is perpendicular to the horizon line, moves against the fixed roll scale on the upper contour of the attitude sphere. This fixed roll scale comprises white marks for the 10 degrees, 20 degrees, 30 degrees and 45 degrees significant values, on either side of the zero position (horizontal wings) which is indicated by a small fixed triangle. The 60 degrees roll indication corresponds to the limits of the upper contour of the cut-sphere shaped window.

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IR - Attitude Information Display Figure 010   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 57   Config-1 Feb 01/07 R  CES

 

(c) Attitude failure In case of attitude failure concerning the pitch and/or roll information, the attitude sphere goes out of view and is replaced by a red ATT flag which flashes for a few seconds then remains steady (item C). In case of discrepancy detected by the FWC between the pitch or roll attitude information presented on the CAPT and F/O PFDs, a CHECK ATT amber message flashes for a few seconds on both PFDs, then remains steady (item D). **ON A/C 001-049, 101-105, 151-199, (2) Heading information (Ref. Fig. 011) The aircraft magnetic or true heading is displayed on the PFD, the ND and the VOR/DME RMI. The true heading can be displayed on the CDU. **ON A/C 201-203, (2) Heading information (Ref. Fig. 011) The aircraft magnetic or true heading is displayed on the PFD, the ND and the VOR/ADF/DME RMI. The true heading can be displayed on the CDU. **ON A/C 001-049, 101-105, 151-199, 201-203, (a) On the PFD When true heading is displayed, a TRUE white message appears above the heading scale (item A). A blank heading scale (with 10 deg. spaced marks without any indicated value) is provided on the horizon line. The marks are just under this line. This scale moves as the aircraft heading varies. For important nose-up or nose- down the heading graduations remain at the lower or upper sector limit. Below the sphere, a heading scale provides the pilot with the aircraft actual track and relative selection. This heading scale is graduated every 5 deg. (item A). In case of failure, the heading graduation disappears on the two scales and a red HDG flag appears on the lower heading scale (item B). It flashes for a few seconds, then remains steady.

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IR - Heading Information Display on the PFD Figure 011   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 59   Config-1 Feb 01/07 R  CES

 

Furthermore, in case of discrepancy detected by the FWC between CAPT and F/O heading indications, with the heading signal valid, a CHECK HDG amber message is displayed at the center of the heading scale (item C). (b) On the ND (Ref. Fig. 012) The heading data is displayed on the ND in the three following operating modes: ROSE, ARC and PLAN. The ROSE mode and the ARC mode are oriented with respect to the aircraft heading, while the PLAN mode is oriented with respect to the true north. 1 _

True heading display In ROSE or ARC mode, when true heading is displayed, a cyan TRUE message appears at the top of the ND.

2 _

ROSE mode (item A) In this mode, each pilot has three different sub-modes of presentation on his ND: ROSE-ILS/ROSE-VOR/ROSE-NAV. In the three ROSE sub-modes, the ND provides a display which is similar to that of a conventional HSI, i.e. a rotating heading dial orientated to the North and giving to the pilot the aircraft actual magnetic or true heading with as reference the fixed yellow lubber line at the top of the dial.

3 _

ARC mode (item B) In this mode, the ND displays a 90 deg. heading sector ahead of the aircraft giving the aircraft actual magnetic or true heading with respect to the fixed yellow lubber line at the top of the scale.

4 _

PLAN mode The ND displays a static map orientated with respect to the true North.

5 _

Heading failure (items C and D) In case of heading failure, the scale and all symbols positioned on the ROSE and ARC scales go out of view; a red HDG flag comes into view below the scale after flashing for a few seconds, when the DMC has detected an anomaly concerning the heading parameter. In addition, if a discrepancy between CAPT and F/O sides is detected by the comparison inside the FWCs, the CHECK HDG message is displayed in amber on both NDs (item E).

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IR - Heading Information Display on the ND Figure 012   R EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 61   Config-1 Feb 01/07  CES

 

**ON A/C 001-049, 101-105, 151-199, (c) On the VOR/DME RMI (Ref. Fig. 013) The heading indication is given by a dial which rotates in front of a fixed index (item A). In case of heading failure, the fire orange warning flag with the black HDG inscription comes into view at the top of the compass card (item B). For more details ref. 34-57-00. (d) On the CDU The time heading can be displayed on the CDU if the DATA DISPLAY selector switch is placed in the HDG position. **ON A/C 201-203, (c) On the VOR/ADF/DME RMI (Ref. Fig. 013A) The heading indication is given by a dial which rotates in front of a fixed index (item A). In case of heading failure, the fire orange warning flag with the black HDG inscription comes into view at the top of the compass card (item B). For more details ref. 34-57-00. (d) On the CDU The time heading can be displayed on the CDU if the DATA DISPLAY selector switch is placed in the HDG position. **ON A/C 001-049, 101-105, 151-199, 201-203, (3) Ground speed (Ref. Fig. 014) The ground speed is displayed in the left upper corner of the ROSE, ARC or PLAN mode (item A). The GS title is displayed in white color and the ground speed in green. In case of failure or NCD, the ground speed value is replaced three dashed lines (item B). The ground speed can also be displayed on the CDU if the DATA selector switch is placed in the TK/GS position.

ND for value by DISPLAY

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IR - Heading Information Display on the VOR/DME RMI Figure 013   R EFF : 001-049, 101-105, 151-199,  34-14-00 Page 63   Config-1 Feb 01/07  CES

 

IR - Heading Information Display on the VOR/ADF/DME RMI Figure 013A   R EFF : 201-203,  34-14-00 Page 64   Config-1 Feb 01/07  CES

 

IR - GS, Wind, vertical Speed Information Display Figure 014   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 65   Config-1 Feb 01/07 R  CES

 

(4) Wind indications (Ref. Fig. 014) The wind origin, force and direction is displayed in the left upper corner of the ND, for ROSE, ARC and PLAN mode (item A): - the wind origin is displayed in green color in degrees with respect to the true North - the wind force is displayed in green color in knots - the wind direction, in analog form, is represented by means of a green arrow orientated with respect to the north reference in use. This arrow is displayed only if the wind force is greater than 2 knots. In case of failure or NCD, the digital data are replaced by three dashed lines and the wind direction arrow disappears (item B). The wind indications can also be displayed on the CDU if the DATA DISPLAY selector switch is placed in the WIND position. (5) Vertical speed (Ref. Fig. 014) The inertial vertical speed is displayed in the right side of the PFD (item C). The vertical speed scale consists of: - a trapezoidal grey background colored surface - a fixed white scale with 500 ft/mn spaced marks from -2000 ft/mn to +2000 ft/mn - a needle giving in analog form the actual vertical speed value - a number in a moving blanking window. This window accompanies the needle (above the needle if V/S > 0, below if V/S < 0). The number gives the V/S value in hundreds of ft/mn. Between -200 ft/mn and +200 ft/mn, both the window and the number disappear. - above +6000 ft/mn (or below -6000 ft/mn), the needle remains stopped where it is. When the vertical speed exceeds +6000 ft/mn or -6000 ft/mn, the digital indication and the analog needle change from green to amber. In addition, those indications change to amber in approach, in the following cases: - V/S less than -2000 ft/mn below 2500 ft RA. - V/S less than -1200 ft/mn below 1000 ft RA. In case of failure, the inertial vertical speed display is automatically replaced by the baro vertical speed display (Ref. 34-13-00). (6) Reconfiguration display In case of loss of inertial parameters on the CAPT or F/O PFD and ND, the IR3 can be used as a back up source by placing the ATT HDG selector switch in CAPT/3 position for the CAPT PFD and ND or in F/O/3 position for the F/O PFD and ND.

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C. Warnings (Ref. Fig. 015, 016, 017, 018, 019) (1) In addition to the ATT or HDG flags displayed on the PFDs, NDs and on the CDU, warning messages are displayed on the lower part of the upper ECAM DU. (a) NAV IR 1(2)(3) FAULT NAV IR 1(2) + 2(3) FAULT When these messages are displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the IR FAULT legend flashes on the CDU. (b) NAV ATT DISCREPANCY This message is displayed when a difference higher than 5 deg. is detected by comparison inside the FWCs between the roll angle or the pitch angle provided by two IRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK ATT message appears on the PFD. (c) NAV HDG DISCREPANCY This message is displayed when a difference higher than 7 deg. (or 5 deg. in true heading) is detected by comparison inside the FWCs between the heading value provided by two IRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK HDG message appears on the PFDs and NDs. (d) NAV GPS 1(2) FAULT (Ref. Fig. 020) The GPSSUs are monitored by the three ADIRUs using the status word sent by the GPSSU and the BITE of the IR partion. This message is accompanied by: - activation of the MASTER CAUT lights on the glareshield panel - aural warning: single chime (SC). (2) When the CLR key is pushed on the ECAM control panel, a STATUS page is displayed on the lower ECAM DU and indicates the STATUS and INOP SYS (systems).

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NAV IR 1 (2) (3) FAULT Message Figure 015   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 68   Config-1 Feb 01/07 R  CES

 

NAV IR 1+2 FAULT Message Figure 016   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 69   Config-1 Feb 01/07 R  CES

 

NAV IR 1+3 (2+3) FAULT Message Figure 017   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 70   Config-1 Feb 01/07 R  CES

 

NAV ATT DISCREPANCY Message Figure 018   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 71   Config-1 Feb 01/07 R  CES

 

NAV HDG DISCREPANCY Message Figure 019   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 72   Config-1 Feb 01/07 R  CES

 

NAV GPS - Fault Messages Figure 020   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 73   Config-1 Feb 01/07 R  CES

 

D. ADIRUs Performance Criteria (1) History The inertial parameters to be considered to evaluate the level of performance of an inertial system after flight completion are: - the radial position error (in NM) - the residual ground speed error (in kts). Depending on their magnitude noticed at the end of the flight, the concerned inertial system(s) shall or shall not be removed from the aircraft. (2) Radial position error In order to address the statistical term of this requirement with the most relevant approximation, the removal criteria use a limit based on the recording of the radial position error on two consecutive flights. The use of a two-strike method presents the advantage to decrease the removal rate of healthy units that have shown, by chance, or by an inaccurate position entry at alignment, a radial position error beyond the specified criterion. The removal boundaries described on the figure present three different areas: (Ref. Fig. 021) - Area 1 - ADIRU OK all the time - Area 2 - ADIRU to be checked after second flight - Area 3 - ADIRU to be replaced. NOTE : Area 2 is applicable when the residual radial position error ____ ranges within the limits described in following Para. (a) Lower limit for removal criteria The integration of the drift rate results in a lower limit for the radial position error: Radial position error (NM) = (2 (NM/h) * T (h)) + Offset (NM) The presence of an offset is necessary to avoid the unjustified removal of healthy units subject to the natural Schuler effects and to the Present Position inaccuracies entered during initialization. It should be pointed out that the adverse impacts of such inaccuracies over the radial position error will reveal stronger for short flight durations (below 1.5 hour). - Flight duration < 1.5 FH: The lower limit of the grey band is fixed at 5 NM. - 1.5 FH < Flight duration < 10 FH: The lower limit of the grey band is fixed at 2T + 2. - Flight duration > 10 FH: The lower limit of the grey band is fixed at 22 NM.

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ADIRU RPE Removal Criteria Figure 021   EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00 Page 75   Config-1 Feb 01/07  CES

 

(b) Upper limit for removal criteria - Flight duration < 1.5 FH: The upper limit of the grey band is fixed at 7.5 NM. - 1.5 FH < Flight duration < 10 FH: The upper limit of the grey band is fixed at 3T + 3. - Flight duration > 10 FH: The upper limit of the grey band is fixed at 33 NM. (3) Residual Ground Speed Error The residual ground speed for each IR is determined at the end of the flight when the aircraft has come to a complete stop. (a) Check of the residual ground speed can be made: - On the CAPT (IR1) and F/O (IR2) Navigation Displays (ND): The residual ground speed of the IR3 can be read on the CAPT ND by setting the ATT HDG selector switch to CAPT/3. - On the ADIRS CDU: . set the DATA DISPLAY selector switch to TK/GS . set the SYS DISPLAY selector switch to 1, 2, 3 . read the respective ground speed in the CDU display. (b) Compare the recorded ground speed values with the following limits: - if the residual ground speed error is 15 kts or greater after each of two consecutive flights, replace the ADIRU - if the residual ground speed error is 21 kts or greater at the end of any one flight, replace the ADIRU.

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ATTITUDE, HEADING AND POSITION - DESCRIPTION AND OPERATION __________________________________________________________ 1. _______ General The Inertial Reference (IR) portion of the Air Data/Inertial Reference Unit (ADIRU) supplies the primary data that follows to the aircraft avionic systems: - Precision attitude - Magnetic heading references - Navigation data. The attitude, heading and navigation data is shown on the displays of the Electronic Flight Instrument System (EFIS): - Primary Flight Display (PFD) - Navigation Display (ND). The IR portion also supplies data from the selected MMR and the accurate GPIR hybrid position. 2. __________________ System Description A. General The IR portion is a strapdown inertial system which provides a quality reference for attitude, heading (true and magnetic), angular rates and accelerations. The IR software also computes: - the inertial position - the ground velocities - the baro inertial vertical speed - the drift angle - the wind data - the flight path data. The GPS partition integrated in the IR portion provides both the GPS autonomous and hybrid navigation solutions. The term hybrid is used to indicate that the navigation solution is a result of combining the GPS, Inertial, and Air Data altitude data. The autonomous navigation solution denotes a solution derived solely by the MMR using only satellite data. For each type of data, hybrid and autonomous, the software provides: - the position - the velocities (Ground, N/S, E/W) - the accuracy parameters - the integrity parameters.

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B. Inputs (1) Digital inputs (a) FMGC inputs The IR portion is provided with two ARINC 429 low-speed buses from the two ARINC 702 Flight Management and Guidance Computers (FMGCs). These buses transmit the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 043: SET MAGNETIC HEADING - label 256: FIELD ELEVATION - label 270: FMGC DISCRETES - label 271: ADR discrete word 2. These data words are used for initialization and BITE purposes, and barometric data setting. (b) CDU inputs The IR portion is provided with one ARINC 429 low-speed buses from the CDU. This bus transmits the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 043: SET MAGNETIC HEADING - label 277: CDU TEST. These data words are used for initialization and BITE purposes. (c) ADR inputs The IR portion is provided with three ARINC 429 low-speed buses from the two other ADIRUs (ADR portion) and from its associated ADR. These buses transmit the following data words: - label 203: ALTITUDE - label 204: BAROMETRIC CORRECTED ALTITUDE 1 - label 210: TRUE AIRSPEED - label 212: ALTITUDE RATE - label 220: BAROMETRIC CORRECTED ALTITUDE 2 - label 241: CORRECTED AOA. (d) CFDS input The IR portion is provided with one ARINC 429 low-speed bus from the Centralized Fault Display System (CFDS). This bus transmits the following data words: - label 125: UTC - label 126: FLIGHT PHASE - label 155: AIRCRAFT CONFIG - label 227: CFDS COMMAND - label 260: DATE

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- labels 233 to 236: FLIGHT NUMBER - labels 301 to 303: AIRCRAFT TAIL NUMBER For more details Ref. 34-18-00. (e) GPS inputs The IR portion is provided with two ARINC 429 high-speed buses from the GPS portion of the Multi-Mode Receivers (MMRs). These buses transmit the following data words: - label 057: USER RANGE ACCURACY - label 060: MEASUREMENT STATUS - label 061: PSEUDO RANGE - label 062: PSEUDO RANGE FINE - label 063: RANGE RATE - label 064: DELTA RANGE - label 065: SV POSITION X - label 066: SV POSITION X FINE - label 070: SV POSITION Y - label 071: SV POSITION Y FINE - label 072: SV POSITION Z - label 073: SV POSITION Z FINE - label 074: UTC MEASURE TIME - label 076: GPS ALTITUDE (MSL) - label 101: GPS HDOP - label 102: GPS VDOP - label 103: GPS TRACK ANGLE - label 110: GPS LATITUDE - label 111: GPS LONGITUDE - label 112: GPS GROUND SPEED - label 120: GPS LATITUDE FINE - label 121: GPS LONGITUDE FINE - label 125: GPS UTC BCD - label 126: SAT DE-SELECT 1 - label 127: SAT DE-SELECT 2 - label 130: GPS HORIZONTAL INTEGRITY LIMIT - label 136: GPS VERTICAL FOM - label 140: GPS UTC FINE - label 141: GPS UTC FINE FRACTIONS - label 143: TERMINAL AREA HIL - label 144: APPROACH AREA HIL - label 150: GPS UTC BIN - label 162: DESTINATION ETA - label 163: ALT WAYPOINT ETA - label 165: GPS VERTICAL VELOCITY - label 166: GPS N/S VELOCITY - label 174: GPS E/W VELOCITY - label 226: GPS DATA LOADER - label 247: GPS HORIZONTAL FOM

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-

label label label label label

260: 273: 343: 347: 377:

GPS DATE GPS SENSOR STATUS DESTINATION HIL ALT WAYPOINT HIL EQUIPMENT IDENT

(2) Analog inputs The IR portion is provided with analog inputs for power supply and GPS/IRS synchronization purposes (Time Mark). For more details Ref. 34-12-00. (3) Discrete inputs The IR portion is provided with the following discrete inputs: --------------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT | | | | DEFINITION | --------------------------------------------------------------------| Mounting position 1 | Open/GND | see table 2 | | Mounting position 2 | Open/GND | see table 2 | | SDI MSB (Middle insert) | Open/GND | 0/1 | | SDI LSB (Middle insert) | Open/GND | 0/1 | | CDU ON/OFF | Open/GND |Not displayed/displayed| | IR mode select M1 | Open/GND | see table 3 | | IR mode select M2 | Open/GND | see table 3 | | Auto ADR.DADS select | Open/GND | see table 4 | | Manual ADR.DADS select | Open/GND | see table 4 | | Aircraft Ident Code 1/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 2/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 4/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 8/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 16/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 32/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 64/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code Parity |Open/A.I. Com| 0/1 | | IR remote test | Open/GND | No test/test | | MAGVAR select | Open/GND |Reserved/expended model| | GPS sensor 1 present | Open/GND | GND = present | | GPS sensor 2 present | Open/GND | GND = present | | GPS priority select | Open/GND |Normal priority/ | | | |Reserved priority | --------------------------------------------------------------------Table 1 : IR Discrete Inputs

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(a) Mounting positions 1 and 2 These discrete inputs are used to indicate to the IR the orientation of the unit. It is needed to know the longitudinal and lateral axes of the aircraft. Table 2 below gives the unit position as a function of the discrete selection. --------------------------------------------------------------| Mounting | Mounting | Connector Position/Aircraft | | Position 1 | Position 2 | | --------------------------------------------------------------| Open * | Open * | FWD * | | Ground | Open | AFT | | Open | Ground | RIGHT | | Ground | Ground | LEFT | --------------------------------------------------------------Table 2 : Mounting Position Discretes * The discretes are wired in FWD position. (b) IR mode select The IR portion uses these discrete inputs to know the position of the OFF/NAV/ATT selector switch as follows: ---------------------------------------------| M1 | M2 | OFF/NAV/ATT | | | | Selector Switch Position | |--------------------------------------------| | Open | Open | OFF | | Ground | Open | NAV | | Open | Ground | ATT | ---------------------------------------------Table 3 : IR Mode Select (c) ADR DADS select The IR portion uses these discrete inputs to know which air data source to use:

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-------------------------------------------------------------------| Auto | Manual | IR Selection | | ADR DADS | ADR DADS | | -------------------------------------------------------------------| Open | Open | The IR uses the air data received | | | | on port 1 | |-------------|----------------|-----------------------------------| | Open | Ground | The IR uses the air data received | | | | on port 2 | |-------------|----------------|-----------------------------------| | Ground * | Open | The IR goes automatically from one| | | | air data source to the others | | | | according to their validity and | | | | priority. * | -------------------------------------------------------------------Table 4 : ADR DADS Select * The discretes are wired in the automatic ADR selection mode with the following priority: 1: its own ADR unit 2: ADR received on port 1 3: ADR received on port 2. (d) SDI program pins These discretes code the installation side of the ADIRU. The following table gives the IR side according to the SDI. -------------------------------------------| SDI-MSB | SDI-LSB | ADIRU NUMBER | -------------------------------------------| OPEN | GROUND | 1 | | GROUND | OPEN | 2 | | GROUND | GROUND | 3 | -------------------------------------------Table 5 : IR SDI Code (e) IR remote test The IR portion uses one discrete to select the remote test by external control. When this discrete is open, the test is not activated. When this discrete is grounded, the test is activated. On the A/C, this discrete is open. In normal operation this discrete is open (unused) but can also be activated via the CFDIU on the ground (Ref. 34-18-00). (f) CFDS message select On the A/C, this discrete is open.

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(g) GPS present These discretes are used to activate GPS/IRS hybridization (computation, BITE function). (h) GPS priority select The GPIRS function uses this discrete to modify the GPS priority. Each ADIRU receives data from the two GPS portions of the MMRs on the primary and secondary inputs. For each ADIRU, the primary and secondary GPS inputs are defined as follows: --------------------------------------------| ADIRU | PRIMARY | SECONDARY | | SDI | INPUT | INPUT | --------------------------------------------| 1 | GPSSU 1 (MMR 1) | GPSSU 2 (MMR 2) | | 2 | GPSSU 2 (MMR 2) | GPSSU 1 (MMR 1) | | 3 | GPSSU 1 (MMR 1) | GPSSU 2 (MMR 2) | --------------------------------------------Depending on the GPS validity and GPS priority select input discrete status, the GPS source is defined as follows: --------------------------------------------------------------------| PRIORITY | PRIMARY | SECONDARY | GPSSU SOURCE | | STATUS | GPSSU | GPSSU |----------------------------------| | | | GPS PRIORITY | GPS PRIORITY | | | | | SELECT = OPEN | SELECT = GROUND | --------------------------------------------------------------------| 1 | Valid | Valid | Primary | Secondary | | 2 | Valid | Fail | Primary | Primary | | 3 | Fail | Valid | Secondary | Secondary | | 4 | Fail | Fail | Primary | Secondary | --------------------------------------------------------------------C. Software Computation (Ref. Fig. 001, 002) The software contains the program memory and provides the following basic functions: - real-time executive - attitude integration - velocity integration - position integration - output computation - built-in test (Ref. 34-18-00).

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ADIRU - IR Block Diagram Figure 001   EFF : 524-526, 528-599,  34-14-00 Page 8   Config-2 Feb 01/10  CES

 

ADIRU - IR Signal Flow Diagram Figure 002   EFF : 524-526, 528-599,  34-14-00 Page 9   Config-2 Feb 01/10  CES

 

The IR software operates in one of three basic modes: alignment, navigation, or reversionary attitude mode. These modes include various portions of the major functions. The real-time executive and built-in test functions interface with each function in each mode. (1) Alignment mode The alignment is the initialization mode for the IR. Its primary function is to initialize the attitude, velocity and position integration functions implemented in the navigation mode. This mode operates on the ground only. The IR alignment mode is divided into three parts: - coarse level processing The coarse level processing is engaged during the first 30 seconds of the IR alignment mode. This processing estimates the local vertical using the three accelerometers and the measured gravity. During coarse level processing of the alignment mode, the software computes the level coordinate frame, pitch and roll, and associated rates and accelerations. - gyro-compass (or azimuth) processing and level processing Gyro-compass processing is engaged after the 30 seconds of the IR alignment mode (coarse level complete) and runs for a minimum of 9.5 minutes. Gyro-compass processing is used to point body frame to North (using earth rotation detection by gyros). During this alignment submode, an estimated latitude is computed using the local vertical component of the earth rotation. During this submode, the results of coarse level processing are sharpened to have a better knowledge of the coordinate frame. - position entry data processing This position initialization can take place in coarse level processing or gyro-compass processing. The latitude and longitude pair processed for position initialization is received from the same source (FMGC 1, FMGC 2 or CDU). As soon as a valid position initialization pair is received, the software performs a BITE test to check if the entered latitude and longitude are within the following limits versus the position recorded at the end of the last power-up cycle: Abs val(lat entered - lat recorded) less than or equal to 1 deg. Abs val(long entered - long recorded) less than or equal to 1 deg (Ref. 34-18-00). A second BITE test is performed on the entered latitude when an estimated latitude is available during the gyro-compass processing:

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Abs val(cos (lat est) - cos (lat ent)) less than or equal to 0.01234. Abs val(sin (lat est) - sin (lat ent)) less than or equal to 0.01234. The alignment is completed if a valid position data has been received and verified by the IR. The typical alignment time will be calculated for a given latitude as follows: - ABS (5 minutes/cosine (latitude)) for latitude between 60 deg. South and 60 deg. North - 10 minutes at 73 deg. South < latitude < 60 deg. South - 10 minutes at 60 deg. North < latitude < 73 deg. North - 17 minutes at latitude < 73 deg. South - 17 minutes at 73 deg. North < latitude. If not, the automatic sequencing to the NAV mode will be delayed (up to 1 minute) after the position data is received. The operations to enter position and the warnings associated to the tests performed in alignment mode are described in para. 3 (operation/control and indicating). The IR also offers the possibility to enter into a variant of the alignment mode called rapid realign or 30-second realign. This mode is selected by moving the CDU selector switch from NAV to OFF, then to NAV within five seconds, when the aircraft is on the ground (ground speed less than 20 knots). A valid position data must be received. During the rapid realign mode, all computed velocities are set to zero and a fine tuning of the alignment is performed using the attitude reference vertical and the heading data available from the last NAV phase as initial conditions. During the alignment mode, the IR outputs on the ARINC 429 bus may not be available. Position initialization of the ADIRU is transmitted to the MMR for its own initialization. In addition to this position, the MMR requires initialization data of date and UTC. The IR portion receives the date and UTC from the CMC and transmits the data to the MMRs. The chronology of the validation of the outputs during the alignment is given in para. 2-D (IR output data).

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(2) Navigation (NAV) mode (Ref. Fig. 003) The NAV mode is the primary operating mode for the IR and is implemented in software as unaided strapdown inertial navigation computation. The basic operating elements consist of three integration functions (attitude, velocity and position) driven by input gyro and accelerometer strapdown sensor data. The following equations are used to compute the main parameters: - body pitch, roll, yaw rates (labels 326, 327, 330): they are representative of the aircraft body rotations relative to the aircraft body axes and are directly measured by the laser gyros. - body longitudinal, lateral, normal accelerations (labels 331, 332, 333): they are directly measured by the accelerometers but with the gravity effect subtracted to have 0 g on the normal acceleration when in level. - pitch and roll attitude rate (labels 336, 337) Pitch Att rate = Q. cos (Ra) - R. sin (Ra) Q. sin (Ra) + R. cos (Ra) Roll Att rate = P + ------------------------cos (Pa)/sin (Pa) where: Ra = Roll angle Pa = Pitch angle P = Body roll rate Q = Body pitch rate R = Body yaw rate - flight path angle (label 322) = angle between the aircraft velocity vector and the horizontal plane (VZ) FPA = Arc tan (--) (VG) where: VZ = inertial vertical speed (label 365) VG = ground speed (label 312)

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ADIRU - Navigation Mode Functions Figure 003   EFF : 524-526, 528-599,  34-14-00 Page 13   Config-2 Feb 01/10  CES

 

- flight path acceleration (label 323) = aircraft acceleration along the total velocity vector Vx.Ax + Vy.Ay + Vz.Az Flt Path Accel = --------------------______________ / 2 2 2 V Vx + Vy + Vz where: Ax, Ay, Az, Vx, Vy, Vz: accelerations and velocities in the earth frame. - wind speed and direction computation (labels 315 and 316) ___________________ / 2 2 Wind speed = V Vwind N + Vwind E (Vwind E) Wind direction = Arc tan (-------) + 180 deg. (Vwind N) Vwind E = Veast - cos (Pa). sin (Hdg). TAS Vwind N = Vnorth - cos (Pa). cos (Hdg). TAS where : Veast = east velocity = label 367 Vnorth = north velocity = label 366 Pa = pitch angle = label 324 Hdg = heading = label 314 TAS = true airspeed. The TAS is received from the ADR. The ADR source to be used is selected according to the configuration of the discretes described in para. 2.B.(3)(d). The IR does not compute the wind if the TAS is less than 100 knots or if the air data sources are no more available. In this case, the wind labels are sent with their status matrix coded NCD (No Computed Data). - inertial vertical speed and inertial altitude computation (labels 365 and 361) The IR software contains a baro-inertial loop to compute the Inertial Vertical Speed and Inertial Altitude. This loop permits to take advantage of the different qualities of the inertial and air data systems. The IR brings its better behaviour in dynamic maneuvers while the ADR brings its stability in time (no drift of the outputs like in IR). The principle of the baro-inertial loop is given in the figure (Ref. Fig. 004)

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IR - Baro Inertial Altitude Filter Figure 004   EFF : 524-526, 528-599,  34-14-00 Page 15   Config-2 Feb 01/10  CES

 

The ADR source to be used is selected according to the configuration of the discretes described in para. 2.B.(3)(d). When no ADR source is available, labels 361 and 365 are sent with their status matrix coded NCD (No Computed Data). - magnetic deviation computation The principle of the inertial system is based on geographic referenced measurements and computation. To create the labels which are magnetic references (magnetic heading, magnetic track angle, labels 320, 317), the IR computes a magnetic variation which is added to the true values (labels 314, 313). The magnetic variation is computed as a function of the present position (latitude and longitude) within the range of 82⁰N to 60⁰S excluding the magnetic polar region (latitude exceeds 73⁰N and longitude between 120⁰W and 92⁰W). The magnetic variation at any given point is calculated by using four grid intersection data values and a two-dimensional linear interpolation. The grid data comes from the National Oceanic and Atmospheric Administration and must be updated every 10 years in order to meet the accuracy requirements. Normally the computation and display of navigation data by the FMGS and the EIS are in magnetic references (using magnetic referenced labels from the IR). - GPS/IRS hybridization computation At the end of GPIR NAV mode ground align processing, an 18-state PR/DR (Pseudo Range / Delta Range) mechanized Kalman filter is engaged to estimate the system error states. The hybrid solution is then corrected by removing its errors estimated from the Kalman filter. (3) Attitude mode The attitude mode is a reversionary mode which can be activated only by manual selection of the ATT mode on the CDU. The mode can be activated on the ground or in flight and is intended to provide a rapid attitude/heading restart capability if the IR has experienced total power shutdown or failures which do not disable the mechanization of the attitude computation. The necessity of selecting ATT is indicated by the IR in its action code (label 350 - code 04 = select ATT) and this data is used by the FWC to display a message on the ECAM displays. On the CDU, the STS-SELECT ATT indication comes into view if the DISPLAY/DATA selector switch is in STS (status) position. This mode needs a 20-second initialization phase with the aircraft in level flight. During this phase, all the ARINC bus outputs are sent with their status matrix coded NCD (No Computed Data). At the end of the initialization phase the IR sends valid outputs of: - body axis accelerations and angular rates

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-

pitch and roll attitude and rate vertical acceleration vertical velocity baro-inertial altitude and vertical speed (Ref. para. D - IR output data, list of valid labels). The magnetic heading may also be valid if an initialization value has been sent by the FMGC (through the MCDU) or the CDU. (Ref. para. D - IR output data for the complete list of valid outputs).

D. IR, GPS, and GPIRS Output Data (1) Digital output characteristics The IRs have 4 independently-buffered high-speed ARINC 429 digital output buses, designated bus output 1, 2, 3 and 4 - digital output table: This table contains all the output parameters in the digital form. They are sorted in numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available. - PARAMETER DEFINITION: parameter name. - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy. - UNIT: unit in which the digital value is transmitted. - SIG BIT: indicates whether a sign bit is available. - BITS: number of bits used by the parameter in the label. - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds. - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code. - ALPHA CODE: indicates the parameter mnemonic code. - SOURCE ORIGIN: parameter source computer or system. When the input discretes of THE GPS PRESENT programming pins are grounded (indicating GPS present), both the MMR outputs and the GPIRS integrated navigation solution outputs are transmitted on the IR output buses with the IR output data.

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 010 |PPOS LAT |W |Deg | | 6 |500 |BCD |LATP | | | | |90S-90N |& | | | | | | | | | |0.1 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 011 |PPOS LONG |W |Deg | | 6 |500 |BCD | | | | | |180E-180W |& | | | | | | | | | |0.1 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 012 |GROUND |W 0 to 2000 |Kts | | 4 |500 |BCD | GS | | | |SPEED |0 to 1000 | | | | | | | | | | |R 1 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 013 |TRK ANGLE |W 0 to 359.9|Deg | | 4 |500 |BCD | | | | |TRUE |R 0.1 | | | | | | | | | | |+/- 2.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 014 |MAG HDG |W 0 to 359.9|Deg | | 4 |500 |BCD | MH | | | | |R 0.1 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 015 |WIND SPEED|W 0 to 256 |Kts | | 3 |500 |BCD | WS | | | | |R 1 | | | | | | | | | | |+/- 9 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 016 |WIND DIR |W 0 to 359 |Deg | | 3 |500 |BCD | WD | | | |TRUE |R 1 | | | | | | | | | | |+/- 10 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 041 |SET LAT |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |90S-90N |& | | | | | | | | | |R 0.1 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 042 |SET LONG |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |R 0.1 |& | | | | | | | | | | |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 043 |SET MAG |W 0 to 359.9|Deg | | 4 |500 |BCD | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |HDG |R 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 044 |TRUE HDG |W 0 to 359.9|Deg | | 4 |500 |BCD |THDG | | | | |R 0.1 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 052 |PITCH |W +/- 64 |Deg/| | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 053 |ROLL |W +/- 64 |Deg/| | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 054 |YAW |W +/- 64 |Deg/| | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 310 |PPOS LAT |W +/- 180 |Deg | 29 | 20 |200 |BNR | | | | | |+/- 90 |& | | | | | | | | | |R 0.00017 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 311 |PPOS LONG |W +/- 180 |Deg | 29 | 20 |200 |BNR |LONP | | | | |R 0.00017 |& | | | | | | | | | | |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 312 |GROUND |W 0 to 4096 |Kts | | 15 | 40 |BNR | | | | |SPEED |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 313 |TRK - TRUE|W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.23 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 314 |TRUE HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 315 |WIND |W 0 to 256 |Kts | | 15 |100 |BNR | | | | |SPEED |0 to 100 | | | | | | | | | | |R 0.0078 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 316 |WIND DIR |W +/- 180 |Deg | 29 | 15 |100 |BNR | | | | |- TRUE |+/- 180 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 10 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 317 |TRK - MAG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 320 |MAG HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |82 N to 60 S| | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 321 |DRIFT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | DA | | | |ANGLE |+/- 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 2.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 322 |FLIGHT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | FPA | | | |PATH |+/- 90 | | | | | | | | | |ANGLE |R 0.0055 | | | | | | | | | | |+/- 0.28 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 323 |FLT PATH |W +/- 4 | g | 29 | 15 | 20 |BNR |FPAC | | | |ACCEL |R 0.0001 | | | | | | | | | | |+/- 10 % of | | | | | | | | | | |outp | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 324 |PITCH |W +/- 180 |Deg | 29 | 15 | 20 |BNR |PTCH | | | |ANGLE |-90 to + 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.05 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 325 |ROLL |W +/- 180 |Deg | 29 | 15 | 20 |BNR |ROLL | | | |ANGLE |-90 to + 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.05 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 326 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |PTCR | | | |PITCH RATE|+/- 45 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 327 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |ROLR | | | |ROLL RATE |+/- 45 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 330 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |YAW | | | |YAW RATE |+/- 45 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 331 |BODY LONG |W +/- 4 | g | 29 | 15 | 20 |BNR |LONG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 332 |BODY LAT |W +/- 4 | g | 29 | 15 | 20 |BNR |LATG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 333 |BODY NORM |W +/- 4 | g | 29 | 15 | 20 |BNR |VRTG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 334 |PLATFORM |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |HEADING |R 0.0055 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |+/- 0.23 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 335 |TRK ANGLE |W +/- 32 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.001 |s | | | | | | | | | |+/- 0.17 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 336 |PITCH ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.0039 |s | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 337 |ROLL ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.0039 |s | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 340 |TRACK |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |ANGLE |R 0.0055 | | | | | | | | | |GRID |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 341 |GRID |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |HEADING |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 360 |POTENTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR | | | | |V/S |R 1.0 | min| | | | | | | | | |+/- 30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 361 |INERTIAL |W +/- 131072|ft | 29 | 20 | 40 |BNR | | | | |ALT |R 0.125 | | | | | | | | | | |+/- 5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 362 |ALONG TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | | | |HORIZ |R 0.00012 | | | | | | | | | |ACCEL |+/- 10 % | | | | | | | | | | |of outp | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 363 |CROSS TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | | | |HORIZ |R 0.00012 | | | | | | | | | |ACCEL |+/- 10 % | | | | | | | |

  EFF : 524-526, 528-599,  34-14-00 Page 22   Config-2 Feb 01/10  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |of outp | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 364 |VERTICAL |W +/- 4 | g | 29 | 15 | 20 |BNR |VACC | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.00012 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 365 |INERTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR |IVV | | | |V/S |R 1.0 |min | | | | | | | | | |+/- 30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 366 |N - S |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 367 |E - W |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 275 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 276 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 277 |IRS TEST | | | | |500 |HYB | | | | |WORD | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 350 |ACTION | | | | |500 |HYB | | | | |CODE | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 351 |IR MAINT | | | | |500 |DIS | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 354 |LRU IDENT | | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

  EFF : 524-526, 528-599,  34-14-00 Page 23   Config-2 Feb 01/10  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 356 |FAULT | | | | | |ISO | | | | |STAT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQUIP | | | | |500 |HEX | | | | |IDENT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 242 |BODY PITCH|W +/-128 |Deg/| 29 | 15 | 20 |BNR |PTCR | | | |RATE |+/-128 |s | | | | | | | | |(unfiltrd)|R 0,0039 | | | | | | | | | | |+/- 0,1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 342 |BODY ROLL |W +/-128 |Deg/| 29 | 15 | 20 |BNR |ROLR | | | |RATE |+/-45 |s | | | | | | | | |(unfiltrd)|R 0,0039 | | | | | | | | | | |+/- 0,1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 344 |BODY YAW |W +/-128 |Deg/| 29 | 15 | 20 |BNR | YAW | | | |RATE |+/- 45 |s | | | | | | | | |(unfiltrd)|R 0,0039 | | | | | | | | | | |+/- 0,1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 346 |PITCH ATT |W +/-128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0,0039 |s | | | | | | | | |(unfiltrd)|+/- 0,1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 173 |PITCH |W +/-180 |Deg | 29 | 15 | 20 |BNR |PITCH| | | |ANGLE |-90 to +90 | | | | | | | | | |(unfiltrd)|R 0,0055 | | | | | | | | | | |+/- 0,05 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 202 |ROLL |W +/-180 |Deg | 29 | 15 | 20 |BNR |ROLL | | | |ANGLE |-90 to +90 | | | | | | | | | |(unfiltrd)|R 0,0055 | | | | | | | | | | |+/- 0,05 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 372 |BODY LONG |W +/- 4 | g | 29 | 15 | 20 |BNR |LONG | | | |ACCEL |+/- 4,000 | | | | | | | | | |(unfiltrd)|R 0,0001 | | | | | | | |

  EFF : 524-526, 528-599,  34-14-00 Page 24   Config-2 Feb 01/10  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |+/- 0,01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 373 |BODY LAT |W +/- 4 | g | 29 | 15 | 20 |BNR |LATG | | | |ACCEL |+/- 4,000 | | | | | | | | | |(unfiltrd)|R 0,0001 | | | | | | | | | | |+/- 0,01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 374 |BODY NORM |W +/- 4 | g | 29 | 15 | 20 |BNR |VRTG | | | |ACCEL |+/- 4,000 | | | | | | | | | |(unfiltrd)|R 0,0001 | | | | | | | | | | |+/- 0,01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 076 |GPS ALT |W +/- 131072|ft | | 20 |666 |BNR | | | | |(MLS) |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 101 |HDOP |W 0 to 1024 | | | 15 |666 |BNR | | | | | |R 0.031 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 102 |VDOP |W 0 to 1024 | | | 15 |666 |BNR | | | | | |R 0.031 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 103 |GPS TRACK |W +/- 180 |DEG | | 15 |666 |BNR | | | | |ANGLE TRUE|R 0.0055 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 110 |GPS PRES |W +/- 90 |DEG | | 20 |666 |BNR | | | | |POS-LAT |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 111 |GPS PRES |W +/- 180 |DEG | | 20 |666 |BNR | | | | |POS-LONG |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 112 |GPS GROUND|W 0 to 4096 |KTS | | 15 |666 |BNR | | | | |SPEED |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 120 |GPS PRES |W +/|DEG | | 11 |666 |BNR | | | | |POS-LAT |0.000172 | | | | | | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 121 |GPS PRES |W +/|DEG | | 11 |666 |BNR | | |

  EFF : 524-526, 528-599,  34-14-00 Page 25   Config-2 Feb 01/10  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |POS-LONG |0.000172 | | | | | | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 125 |GPS UTC |W 23:59.9 |H/ | | 5 |666 |BCD | | | | | |R 0.1 min |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 130 |GPS INTEG |W 0 to 16 |NM | | 18 |666 |BNR | | | | |LIMIT |R 1.2 E-4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 131 |HYB INTEG |W 0 to 16 |NM | | 18 |666 |BNR | | | | |LIMIT |R 6.1 E-5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 132 |HYB TRUE |W +/- 180 |DEG | | 15 | 40|BNR | | | | |HEADING |R 0.0055 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 135 |HYB VERT |W 0 to 32768|ft | | 18 |666 |BNR | | | | |FOM |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 136 |GPS VERT |W 0 to 32768|ft | | 18 |666 |BNR | | | | |FOM |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 137 |HYB TRACK |W +/- 180 |DEG | | 15 | 40|BNR | | | | |ANGLE TRUE|R 0.0055 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 143 |TERMINAL |W 0 to 16 |NM | | 17 |666 |BNR | | | | |AREA HIL |R 1.22 E-4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 150 |GPS UTC |W 23:59:59 |H:M | | 17 |666 |BNR | | | | | |R 1.0 |:S | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 162 |DESTINA- |W 23:59 |H:M | | 11 |333 |BNR | | | | |TION ETA |R 1 |M | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 163 |ALT |W 23:59 |H:M | | 11 |333 |BNR | | | | |WAYPOINT |R 1 |M | | | | | | | | |ETA | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 165 |GPS VERT |W +/- 32768 |ft/ | | 15 |666 |BNR | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |SPEED |R 1.0 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 166 |GPS N/S |W +/- 4096 |kts | | 15 |666 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 174 |GPS E/W |W +/- 4096 |kts | | 15 |666 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 175 |HYB GROUND|W 0 TO 4096 |kts | | 15 | 40|BNR | | | | |SPEED |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 247 |GPS HORIZ |W 0 TO 16 |NM | | 18 |666 |BNR | | | | |FOM |R 6.1 E-5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 254 |HYB LAT |W +/- 90 |DEG | | 20 |80 |BNR | | | | | |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 255 |HYB LONG |W +/- 180 |DEG | | 20 |80 |BNR | | | | | |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 256 |HYB LAT |W 0.000172 |DEG | | 11 |80 |BNR | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 257 |HYB LONG |W 0.000172 |DEG | | 11 |80 |BNR | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 260 |GPS DATE |W 31:12:99 |D:M | | 6 |666 |BCD | | | | | |R 1 |:D | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 261 |HYB ALT |W +/- 131072|ft | | 20 | 40|BNR | | | | |(MSL) |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 263 |HYB FLIGHT|W +/- 90 |DEG | | 12 | 40|BNR | | | | |PATH ANGLE|R 0.044 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 264 |HYB HORIZ |W 0 to 16 |NM | | 18 |666 |BNR | | | | |FOM |R 6.1 E-S | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

  EFF : 524-526, 528-599,  34-14-00 Page 27   Config-2 Feb 01/10  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 266 |HYB N/S |W 0 TO 4096 |kts | | 15 |80 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 267 |HYB E/W |W 0 TO 4096 |kts | | 15 |80 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 273 |GPS SENSOR| N/A | | | |666 |DIS | | | | |STATUS | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 274 |GPIRS | | | | |666 |DIS | | | | |SENSOR | N/A | | | | | | | | | |STATUS | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 343 |DESTINA- |W 0 to 16 |NM | | 13 |333 |BNR | | | | |TION HIL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 345 |HYB VERT |W +/- 32768 |ft/ | | 15 | 40|BNR | | | | |VELOCITY |R 1.0 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 347 |ALT |W 0 to 16 |NM | | 13 | 333|BNR | | | | |WAYPOINT | | | | | | | | | | |HIL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 352 |GPSSU RCVR| N/A | | | |666 |DIS | | | | |MAINT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 353 |GPIRS | N/A | | | |666 |DIS | | | | |MAINT WORD| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 355 |GPSSU NAV | N/A | | | |666 |DIS | | | | |MAINT | | | | | | | | | ------------------------------------------------------------------------------Table 7A :IR Digital Output Characteristics

  EFF : 524-526, 528-599,  34-14-00 Page 28   Config-2 Feb 01/10  CES

 

---------------------------------------------------------------------------| BIT | SIGNAL | 1 CONDITION | |-----|--------------------|-----------------------------------------------| | 1 | 1 | | | 2 | 0 | | | | 3 | 1 | | | | 4 | 1 | LABEL 270 | | | 5 | 1 | | | | 6 | 0 | | | | 7 | 0 | | | | 8 | 0 | | | 9 | SDI - LSB | | | 10 | SDI - MSB | | | 11 | Alignment Not Ready| In Align Submode | | 12 | Rev Att Mode | In Attitude Mode | | 13 | Nav Mode | In Nav Mode | | 14 | Valid Set Heading | A valid set heading has to be input to the | | | | IR. Magnetic heading outputs are no longer | | | | being computed, but have the characteristics | | | | of a Free Direction Gyro. | | 15 | Attitude Invalid | Attitude Critical Fault | | 16 | DC Fail | DC Power Less Than 18 V | | 17 | On DC | On DC Power | | 18 | ADR Fault | The IR has detected an ADR input (TAS, ALT | | | | and ALT RATE) as FW or NCD. Note functional | | | | test data is ignored by the IR and last valid | | | | input is used. | | 19 | IR Failure | Navigation (Non Critical) Fault | | 20 | DC Fail - On DC | The IR has detected that a DC fail occurred | | | | while on DC from last turn on. | | 21 | Align Fault | The IR has detected a position miscompare | | | | or a Quality of Align fault. | | 22 | No IR Initial | IR does not have position data or data | | | | received is invalid. | | 23 | Excess Motion Error| X or Y velocity greater than 0.011 ft/s | | | | during align. | | 24 | ADR/IR Fault | No data has been received from the ADR or | | | | was received with a parity error. | | 25 | Extreme Latitude | Latitude exceeds 73⁰N (+/-0.5⁰ hysteresis) | | | | while Longitude is between 120⁰W and 90⁰W | | | | (+/-2.5⁰ hysteresis) or Latitude exceeds | | | | 82⁰N (+/-0.5⁰ hysteresis) or Latitude | | | | exceeds 60⁰S (+/-0.5⁰ hysteresis). | | | | Magnetic Deviation is set to zero. | | 26 | Align Time Status | Bits 28 27 26 Time Until Nav | | 27 | | 1 1 1 7 - 10 minutes | | 28 | | 1 1 0 6 minutes |

  EFF : 524-526, 528-599,  34-14-00 Page 29   Config-2 Feb 01/10  CES

 

---------------------------------------------------------------------------| BIT | SIGNAL | 1 CONDITION | |-----|--------------------|-----------------------------------------------| | | | 1 0 1 5 minutes | | | | 1 0 0 4 minutes | | | | 0 1 1 3 minutes | | | | 0 1 0 2 minutes | | | | 0 0 1 1 minute | | | | 0 0 0 IN NAV MODE ONLY | | 29 | COMPUT LAT MISCOMP | SIN/COS OF LATITUDE TEST FAILED | | 30 | SSM | | | 31 | SSM | | | 32 | Parity | | ---------------------------------------------------------------------------Digital Word 270 (IR Discretes) (Ref. Fig. 005, 006, 007, 008) The data field of the test word 277 (21 bits) alternates between the four first patterns shown in the table below, except during the REALIGN DECISION submode and the POWER OFF submode. During these submodes, the data field shall be as shown in pattern 5. ---------------------------------------------------------------------------| BIT | DEFINITION | |--------------------------------------------------------------------------| | 1 | 1 | | 2 | 0 | | | 3 | 1 | | | 4 | 1 | LABEL 277 | | 5 | 1 | | | 6 | 1 | | | 7 | 1 | | | 8 | 1 | |--------------------------------------------------------------------------| | 9 | SDI | | 10 | SDI | |---------|----------------------------------------------------------------| | |PATTERN 1 |PATTERN 2|PATTERN 3|PATTERN 4| PATTERN 5 | |---------|----------|---------|---------|---------|-----------------------| | 11 | 0 | 0 | 1 | 1 | BCD MODE TIMER | | 12 | 1 | 1 | 0 | 0 | (LSD) | | 13 | 0 | 1 | 1 | 0 | (REALIGN AND | | 14 | 1 | 1 | 0 | 0 | POWER OFF) | |---------|----------|---------|---------|---------------------------------| | 15 | 0 | 0 | 1 | 1 | BCD MODE TIMER | | 16 | 1 | 1 | 0 | 0 | (MSD) | | 17 | 0 | 1 | 1 | 0 | (REALIGN AND |

  EFF : 524-526, 528-599,  34-14-00 Page 30   Config-2 Feb 01/10  CES

 

Digital Word 275 IR Discrete 2 Figure 005   EFF : 524-526, 528-599,  34-14-00 Page 31   Config-2 Feb 01/10  CES

 

Digital Word 276 IR Discrete 3 Figure 006   EFF : 524-526, 528-599,  34-14-00 Page 32   Config-2 Feb 01/10  CES

 

Digital Word 351 IR Maintenance Figure 007   EFF : 524-526, 528-599,  34-14-00 Page 33   Config-2 Feb 01/10  CES

 

IR - BCD and Special Output Words Figure 008   EFF : 524-526, 528-599,  34-14-00 Page 34   Config-2 Feb 01/10  CES

 

---------------------------------------------------------------------------| BIT | DEFINITION | |--------------------------------------------------------------------------| | 18 | 1 | 1 | 0 | 0 | POWER OFF) | |---------|----------|---------|---------|---------------------------------| | | | | | | MODE FLAG: | | 19 | 0 | 0 | 1 | 1 | 00 = PWR OFF SUBMODE | | 20 | 1 | 1 | 0 | 0 | 11 = REALIGN DECISION | | | | | | | SUBMODE | |---------|----------|---------|---------|---------|-----------------------| | 21 | 0 | 1 | 1 | 0 | 0 | | 22 | 1 | 1 | 0 | 0 | 0 | | 23 | 0 | 0 | 1 | 1 | 0 | | 24 | 1 | 1 | 0 | 0 | 0 | | 25 | 0 | 1 | 1 | 0 | 0 | | 26 | 1 | 1 | 0 | 0 | 0 | | 27 | 0 | 0 | 1 | 1 | 0 | | 28 | 1 | 1 | 0 | 0 | 0 | | 29 | 0 | 1 | 1 | 0 | 0 | | 30 | 0 | 0 | 1 | 0 | 0 | | 31 | 0 | 0 | 1 | 1 | 0 | |---------|----------|---------|---------|---------|-----------------------| | 32 | Parity | ---------------------------------------------------------------------------Digital Word 277 (CDU Test Word) NOTE : Time (seconds) remaining in the POWER OFF submode and the time ____ (seconds) remaining in the REALIGN DECISION submode are transmitted with the BCD data (bits 11-18). ---------------------------------------------------------------------------| BIT | DEFINITION | |--------------------------------------------------------------------------| | 1 | 1 | | 2 | 1 | | | 3 | 1 | | | 4 | 0 | LABEL 350 | | 5 | 1 | | | 6 | 0 | | | 7 | 0 | | | 8 | 0 | |--------------------------------------------------------------------------| | 9 | SDI - LSB | | 10 | SDI - MSB | |--------------------------------------------------------------------------| | 11 TO 14 | SPARE | |----------|---------------------------------------------------------------|

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---------------------------------------------------------------------------| BIT | DEFINITION | |--------------------------------------------------------------------------| | 15 | TIME UNTIL NAV LEAST | | 16 | TIME UNTIL NAV SIGNIFICANT | | 17 | TIME UNTIL NAV DIGIT | | 18 | TIME UNTIL NAV (BCD) | |----------|---------------------------------------------------------------| | 19 | TIME UNTIL NAV MOST | | 20 | TIME UNTIL NAV SIGNIFICANT | | 21 | TIME UNTIL NAV DIGIT | | 22 | TIME UNTIL NAV (BCD) | |----------|---------------------------------------------------------------| | 23 | Action Code (1) Least | | 24 | Action Code (1) Significant | | 25 | Action Code (1) Digit | | 26 | Action Code (1) | |----------|---------------------------------------------------------------| | 27 | Action Code (1) Most | | 28 | Action Code (1) Significant | | 29 | Action Code (1) Digit | |----------|---------------------------------------------------------------| | 30 | SSM | | 31 | SSM | | 32 | Parity | ---------------------------------------------------------------------------Digital Word 350 (Action Code) NOTE : (1) The action codes corresponding to the maintenance messages ____ are listed in the following table. --------------------------------------------------------------------------| ACTION CODE | MAINTENANCE MESSAGE | DESCRIPTION | |-------------|---------------------|-------------------------------------| | 01 | IR FAULT | Critical failure; Remove ADIRU for | | | | maintenance | | 02 | DELAYED MAINT | Non-Critical failure; Service ADIRU | | | | when convenient | | 03 | ENTER PPOS | Enter present position | | 04 | SELECT ATT | Hard failure; Select ATTITUDE MODE | | 05 | EXCESS MOTION | Excess motion detected during ALIGN | | 06 | SWITCH ADR | Air Data Reference invalid | | 07 | CHK C/B | Check circuit breakers | | 08 | CDU FAULT | Remove CDU for maintenance | | 09 | ENTER HEADING | Enter heading for ATTITUDE MODE | | 10 | | Unassigned TBD | ----------------------------------------------------------------------------

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--------------------------------------------------------------------------| ACTION CODE | MAINTENANCE MESSAGE | DESCRIPTION | |-------------|---------------------|-------------------------------------| Action Code - Maintenance Messages (Ref. Fig. 005, 006, 009) ------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 9 | SDI | | 10 | SDI | | 11 | MSB OF SATELLITES VISIBLE (16) | | 12 | DADS STATUS Present = 0 Not present = 1 | | 13 | DADS SOURCE Primary = 0 Secondary = 1 | | 14 | IRS/FMS STATUS Present = 0 Not present = 1 | | 15 | IRS/FMS SOURCE Primary = 0 Secondary = 1 | | 16 | | | 17 | | NUMBER OF SATELLITES VISIBLE (0-15) | | 18 | | | | 19 | | | 20 | | | 21 | | NUMBER OF SATELLITES TRACKED (0-15) | | 22 | | | | 23 | | | 24 | 00 = GPS | | | | SYSTEM DESIGNATOR 01 = GLONASS | | | | 10 = GPS GLONASS | | 25 | 11 = Spare | | 26 | | | 27 | | MMR OPERATIONAL MODE (Ref table below) | | 28 | | | 29 | MSB OF TRACKED SATELLITES | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------Discrete Word 273 Output Format

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IR - Binary Output Words Figure 009   EFF : 524-526, 528-599,  34-14-00 Page 38   Config-2 Feb 01/10  CES

 

----------------------------------------------------------| MMR MODE | BIT 28 | BIT 27 | BIT 26 | ----------------------------------------------------------| SELF TEST | 0 | 0 | 0 | | INITIALIZATION | 0 | 0 | 1 | | ACQUISITION | 0 | 1 | 0 | | NAVIGATION | 0 | 1 | 1 | | ALTITUDE AIDING | 1 | 0 | 0 | | DIFFERENTIAL MODE | 1 | 0 | 1 | | DIR/SPEED AIDING MODE | 1 | 1 | 0 | | FAULT | 1 | 1 | 1 | ----------------------------------------------------------------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 9 | | | | | SDI | | 10 | | | 11 | - SA STATUS AS DETERMINED BY THE ADIRU 0 = sa off | | | 1 = sa on | | 12 | | | 13 | | POSITION DATA SOURCE/POSITION COMPARISON FAILURE MODE | | 14 | | | 15 | | | | | SECONDARY MMR VALIDITY 00 = Valid | | 16 | 01 = Inactive | | 17 | 10 = Functional Test | | | | PRIMARY MMR VALIDITY 11 = Fail | | 18 | | | 19 | MMR SOURCE Primary = 0 Secondary = 1 | | 20 | | | 21 | | NUMBER OF SATELLITES TRACKED (0-15) | | 22 | | | | 23 | | | 24 | | | | | SPARE | | 25 | | | 26 | | | 27 | | GPIRS SENSOR OPERATIONAL MODE (Ref table below) | | 28 | | | 29 | MSB OF TRACKED SATELLITES (16) | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------Discrete Word 274 Output Format

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----------------------------------------------------------| GPIRS MODE | BIT 28 | BIT 27 | BIT 26 | ----------------------------------------------------------| SELF TEST | 0 | 0 | 0 | | INITIALIZATION | 0 | 0 | 1 | | ACQUISITION | 0 | 1 | 0 | | NAVIGATION | 0 | 1 | 1 | | ALTITUDE AIDING | 1 | 0 | 0 | | SPARE | 1 | 0 | 1 | | SPARE | 1 | 1 | 0 | | FAULT | 1 | 1 | 1 | ----------------------------------------------------------------------------------------------------------------------------------------| BIT N⁰ | FUNCTION | |--------|--------------------------------------------------------------------| | 9 | SDI (LSB) | | 10 | SDI (LSB) | | 11 | | | 12 | | | | 13 | | | | 14 | | | | 15 | | | | 16 | | | | 17 | | | | 18 | | | | 19 | | | | 20 | | RESERVED | | 21 | | | | 22 | | | | 23 | | | | 24 | | | | 25 | | | | 26 | | | | 27 | | | | 28 | | | | 29 | | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------MMR Maintenance Word (Label 352) | 9 | GPS SYSTEM FAILURE | | 10 | DUAL GPS CHANNEL FAIL | | 11 | NO IR DATA | | 12 | INVALID IR DATA | | 13 | TM MISSING ON PRIMARY |

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------------------------------------------------------------------------------| BIT N⁰ | FUNCTION | |--------|--------------------------------------------------------------------| | 14 | TM MISSING ON SECONDARY | | 15 | ARINC TRANSMISSION FAULT | | 16 | NO AUTONOMOUS DATA FROM PRIMARY | | 17 | NO AUTONOMOUS DATA FROM SECONDARY | | 18 | AUTONOMOUS/IRS LATITUDE MISCOMPARE | | 19 | SPARE | | 20 | AUTONOMOUS/IRS LONGITUDE MISCOMPARE | | 21 | SPARE | | 22 | CLOCK PHASE MISCOMPARE ON PRIMARY | | 23 | CLOCK PHASE MISCOMPARE ON SECONDARY | | 24 | TM TIMING/UTC MISCOMPARE ON PRIMARY | | 25 | TM TIMING/UTC MISCOMPARE ON SECONDARY | | 26 | | | 27 | | RESERVED | | 28 | | | | 29 | | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------ADIRU Maintenance Word 353 ------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 9 | SDI (LSB) | | 10 | SDI (MSB) | | 11 | | | 12 | | | | 13 | | | | 14 | | RESERVED | | 15 | | | | 16 | | | | 17 | | | 18 | CMC INPUT BUS (OMS) No activity = 1 | | 19 | DIFF BUS No. 2 No activity = 1 | | 20 | DIFF BUS No. 2 No activity = 1 | | 21 | DADS BUS 2 No activity = 1 | | 22 | DADS BUS 1 No activity = 1 | | 23 | IRS INPUT BUS 2 No activity = 1 | | 24 | IRS INPUT BUS 1 No activity = 1 | | 25 | GPS Fail = 1 | | 26 | RF INPUT Fail = 1 | | 27 | SENSOR UNIT Fail = 1 |

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------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 28 | TEST INHIBIT Inhibit = 1 | | 29 | COMMAND WORD ACKNOWLEDGE Forced = 0 | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------GPSSU Navigation Maintenance Word (Label 355) (2) Discrete outputs The IR provides 3 discrete outputs. The following table defines the characteristics of these discretes. --------------------------------------| SIGNAL | OUTPUT | DEFINITION | |----------|-------------|------------| | ON BAT | OPEN/+28VDC | NO/YES | | IR FAULT | OPEN/+28VDC | NO/YES | | IR ALIGN | OPEN/GROUND | NO/YES | --------------------------------------Discrete Outputs - ON BAT When the IR is powered with batteries, this discrete delivers a 28 VDC state and sets the ON BAT light to on. - IR FAULT When a failure is detected by the IR, this discrete delivers a 28 VDC state and sets the FAULT legend to on. - IR ALIGN When the IR is aligning, this discrete delivers a ground and sets the ALIGN legend to on. 3. Operation/Control ________________________________ and Indicating (Ref. Fig. 010) A. Control (1) Modes of operation The operation interface with the IR is performed through the Multipurpose Control and Display Unit 1(2) or the CDU. The MCDU 1(2) is used for entering initialization data and displaying IR data. (Ref. Fig. 011) The CDU is used for mode selection, IR annunciation (FAULT, ALIGN), for entering initialization data and displaying IR data. The IR has three selectable modes: OFF, NAV and ATT.

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IR - Operation/Control and Indicating Figure 010   EFF : 524-526, 528-599,  34-14-00 Page 43   Config-2 Feb 01/10  CES

 

IR - Alignment Procedure from the MCDU Figure 011   EFF : 524-526, 528-599,  34-14-00 Page 44   Config-2 Feb 01/10  CES

 

The relation between the mode selection and system response is shown in the figure (Ref. Fig. 012) (2) OFF mode When the OFF/NAV/ATT selector switch on the CDU is in the OFF position, all circuitry in the ADIRU is de-energized except for any logic associated with the power-off function. When the ADIRU has turned off, it consumes less than 10 milliamps (needed for power supply turn-on control). The power supply of the ADMs is switched off. A period of 15 seconds is required between switching to OFF and actual power-off. During this sequence, the last position computed is stored in the NVM. (3) NAV (Navigation) mode After selection of the NAV mode on the ground, the IR automatically enters the NAV mode if a self-determined satisfactory alignment has been completed. If alignment is not completed, the IR remains in the Align submode. No updating of the IR present position latitude and longitude is allowed once the IR has completed the Align submode. The IR latitude and longitude entered during the alignment is the starting point for its computation. The following logical processes are mechanized: - OFF to NAV provides automatic alignment in 10 minutes for latitudes between 73⁰N and 60⁰S, with automatic entry to the NAV mode. Requires initial position data to be entered. NOTE : The automatic alignment requires a 15 min delay for latitudes ____ between 73⁰N and 82⁰N. For high latitudes, the alignment is provided by an operational procedure which delays the entering of the initial position by the crew. Accuracies of the system are slightly degraded. - A message on the UPPER ECAM DU indicates that the IRs are in ALIGN submode with the maximum time until NAV. - In the NAV mode, rapid realignment of the IR is initiated by switching the OFF/NAV/ATT selector switch from NAV to OFF and back to NAV within 5 seconds. The IR starts a 30-second realignment submode with existing attitude and heading angles and rezeroed velocities. - The system does not enter the rapid realignment sequence if the ground speed is greater than 20 knots. The CDU permits to observe some particular parameters (Ref. 34-12-00).

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IR - Mode State Diagram Figure 012   EFF : 524-526, 528-599,  34-14-00 Page 46   Config-2 Feb 01/10  CES

 

(a) Initialization data (Ref. Fig. 013) IR alignment is carried out on the ground before takeoff and after the acquisition of valid position data (either GPS data or pilot entry on the INIT page of the MCDU 1(2) (Ref. 22-72-00) or on the CDU (DATA DISPLAY selector switch in PPOS position)). A valid initial position data must be received and verified by the IR during the alignment, or automatic sequencing to the NAV mode will be delayed after position data is received. Initial position data is verified by the IR if Set Latitude and Set Longitude compare within one degree of the last latitude and longitude from the previous flight. If a miscompare exists then: - on the ADIRS CDU, the ALIGN light flashes. - a message ENTER PPOS is displayed on the CDU (DATA DISPLAY selector switch in STS position). The miscompare is removed and the position data verified by the IR when: - the last two Set Latitudes received by the IR are identical and the last two Set Longitudes received by the IR are identical, or - the last Set Latitude and Set Longitude received by the IR compare within one degree of the latitude and longitude from the previous flight. (b) Latitude comparison The IR compares Set Latitude with a self-computed gyro-compass latitude after 10 minutes into alignment or any subsequent time when a valid Set Latitude is available. In case of discrepancy, on the ADIRS CDU the ALIGN light flashes. The message ENTER PPOS is displayed on the CDU (DATA DISPLAY selector switch in STS position). The discrepancy exists when: - the cosine of entered latitude differs from the computed cosine of latitude by more than 0.01234, or - the sine of entered latitude differs from the computed sine of latitude by more than 0.01234. The miscompare is removed if a subsequent entry of Set Latitude passes the test. If the sin/cos test fails two times with identical set latitude inputs then: - the IR FAULT legend flashes on the CDU - a warning message appears on the upper ECAM DU: NAV IR 1(2)(3) FAULT.

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MCDU - INIT Page Figure 013   EFF : 524-526, 528-599,  34-14-00 Page 48   Config-2 Feb 01/10  CES

 

(c) Excessive motion The IR performs an excessive motion test during the Align submode. If taxiing or towing causes a step input which exceeds 0.5 ft/s in the X or Y velocity, then: - the EXCESS MOTION message is displayed on the CDU (DATA DISPLAY selector switch in STS position) - the following message is displayed on the upper ECAM DU: NAV IR 1(2)(3) NOT ALIGN EXCESS MOTION IR 1(2)(3) IN ALIGN - the attitude information is flagged on the PFD. Thirty seconds after motion detection, the system reverts to a full alignment (time to the end of alignment will revert to 9 min 30 s). It is not necessary to re-enter the position. (d) Thirty-second rapid realignment A thirty-second rapid realignment is provided by moving the OFF/NAV/ATT selector switch on the CDU from NAV to OFF and back to NAV within five seconds. A subsequent switching on the selector switch from NAV to OFF and back to NAV within 5 seconds during the 30-second realignment causes the system to start the 30-second realignment again. The realignment is initialized with existing attitude and heading angles. The velocities are zeroed. Valid position data must be received and verified by the IR during the 30-second realignment. (4) ATT (Attitude) mode The IR has a reversionary mode which can be activated only by manual selection of the ATT mode on the CDU. The mode can be activated on the ground or in flight and is intended to provide a rapid attitude/heading restart capability in the event that the IR has experienced a total power shutdown or a failure has occurred resulting in the following: - IR FAULT legend flashing on the CDU - IR 1(2)(3) FAULT message displayed on the upper ECAM DU: IR x MODE SEL...ATT - SELECT ATT message displayed on the CDU (DATA DISPLAY selector switch in STS position). The IR is designed so that the ATT mode can be used after the BITE has detected failures which will cause excessive NAV mode data errors but does not disable the ATT mode mechanization. However, it is recommended to stay in the NAV mode even with excessive navigation

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errors because of higher accuracy of attitude signals and a more complete signal processing. The ATT mode must always be used after loss of power or a similar situation in flight where a new alignment/leveling is required. The ENTER HEADING message is displayed on the CDU (DATA DISPLAY selector switch in STS position) when the ATT mode is selected until valid heading initialization is received from the MCDU or the CDU. The ATT mode is normally engaged with the aircraft in level flight. A 20-second period is needed with the aircraft in level flight to perform an attitude erection to initialize a level attitude. During this period, the data normally computed in the ATT mode have SSMs set to NCD. In the event the ATT mode is engaged with the aircraft not in level flight, an erection cut-out function delays erection when the yaw rate exceeds 0.5 deg/s and permits erection to continue when the yaw rate drops below 0.25 deg/s. Twenty seconds of flight with the erection cut-out switch disengaged is required to erect the attitude. B. Indicating The attitude and heading information is computed by the ADIRU (IR portion) and processed by the associated DMC. The attitude data is displayed on the PFD and the heading data is displayed on the PFD, the ND and the RMI. In addition, the vertical speed (V/S) is displayed on the PFD and the Ground Speed and wind indications are displayed on the ND. In normal configuration, with the ATT/HDG selector switch in the NORM position, the IR1 data is displayed on the CAPT PFD, ND and the RMI (Ref. ATA 34-57-00). The IR2 data is displayed on the F/O PFD and ND. The following parameters can be displayed on the CDU liquid crystal display according to the position of the DATA DISPLAY selector switch on the CDU: - wind (WIND) - present position (PPOS) - true heading (HDG) - status of selected system conditions (STS) - track and ground speed (TK/GS) - test values (TEST). The sources of the data displayed are controlled by the SYS DISPLAY selector switch on the CDU. (1) Attitude information (Ref. Fig. 014) The aircraft roll and pitch attitude is indicated in the center part of the PFD by a sphere representing a conventional ADI drum (Ref. 31-64-00 for sphere definition and display).

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IR - Attitude Information Display Figure 014   EFF : 524-526, 528-599,  34-14-00 Page 51   Config-2 Feb 01/10  CES

 

(a) Pitch angle information (item A) The A/C present pitch angle is given by the vertical displacements of the pitch attitude scale with respect to the center of the A/C reference. The scale moves behind the cut-sphere shaped window, limited by the lines of an upper and a lower sector. The scale rotates around the center of the A/C reference in accordance with the A/C present roll angle. The pitch scale comprises white reference lines and associated pitch angle values. The lines are given every 2.5 degrees from 0 to 10 degrees, then for the 15 degrees, 20 degrees, 30 degrees, 50 degrees and 80 degrees values. Beyond 30 degrees, red large arrow heads (V-shaped) indicate an excessive attitude and the direction to follow in order to reduce it (item B). (b) Roll angle information (item A) A yellow triangle which remains on the line going through the center of the A/C reference and which is perpendicular to the horizon line, moves against the fixed roll scale on the upper contour of the attitude sphere. This fixed roll scale comprises white marks for the 10 degrees, 20 degrees, 30 degrees and 45 degrees significant values, on either side of the zero position (horizontal wings) which is indicated by a small fixed triangle. The 60 degrees roll indication corresponds to the limits of the upper contour of the cut-sphere shaped window. (c) Attitude failure In case of attitude failure concerning the pitch and/or roll information the attitude sphere goes out of view and is replaced by a red ATT flag which flashes for a few seconds then remains steady (item C). In case of discrepancy detected by the FWC between the pitch or roll attitude information presented on the CAPT and F/O PFDs, a CHECK ATT amber message flashes for a few seconds on both PFDs, then remains steady (item D). (2) Heading information (Ref. Fig. 015) The aircraft magnetic or true heading is displayed on the PFD, the ND and the RMI. The true heading can be displayed on the CDU.

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IR - Heading Information Display on the PFD Figure 015   EFF : 524-526, 528-599,  34-14-00 Page 53   Config-2 Feb 01/10  CES

 

(a) On the PFD When the true heading is displayed, a TRUE white message appears above the heading scale (item A). A blank heading scale (with 10 deg. spaced marks without any indicated value) is provided on the horizon line. The marks are just under this line. This scale moves as the aircraft heading varies. For important nose-up or nose-down, the heading graduations remain at the lower or upper sector limit. Below the sphere, a heading scale provides the pilot with the aircraft actual track and relative selection. This heading scale is graduated every 5 deg. (item A). In case of failure, the heading graduation disappears on the two scales and a red HDG flag appears on the lower heading scale (item B). It flashes for a few seconds, then remains steady. Furthermore, in case of discrepancy detected by the FWC between CAPT and F/O heading indications, with the heading signal valid, a CHECK HDG amber message is displayed at the center of the heading scale (item C). (b) On the ND (Ref. Fig. 016) The heading data is displayed on the ND in the three following operating modes: ROSE, ARC and PLAN. The ROSE mode and the ARC mode are oriented with respect to the aircraft heading, while the PLAN mode is oriented with respect to the true North. 1 _

True heading display In ROSE or ARC mode, when the true heading is displayed, a cyan TRUE message appears at the top of the ND.

2 _

ROSE mode (item A) In this mode each pilot has three different sub-modes of presentation on his ND: ROSE-ILS/ROSE-VOR/ROSE-NAV. In the three ROSE sub-modes, the ND provides a display which is similar to that of a conventional HSI, i.e. a rotating heading dial oriented to the North and giving to the pilot the aircraft actual magnetic or true heading with, as reference, the fixed yellow lubber line at the top of the dial.

3 _

ARC mode (item B) In this mode, the ND displays a 90 deg. heading sector ahead of the aircraft giving the aircraft actual magnetic or true heading with respect to the fixed yellow lubber line at the top of the scale.

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IR - Heading Information Display on the ND Figure 016   EFF : 524-526, 528-599,  34-14-00 Page 55   Config-2 Feb 01/10  CES

 

4 _

PLAN mode The ND displays a static map oriented with respect to the true North.

5 _

Heading failure (items C and D) In case of heading failure, the scale and all symbols positioned on the ROSE and ARC scales go out of view; a red HDG flag comes into view below the scale after flashing for a few seconds, when the DMC has detected an anomaly concerning the heading parameter. In addition, if a discrepancy between CAPT and F/O sides is detected by the comparison inside the FWCs, the CHECK HDG message is displayed in amber on both NDs (item E).

(c) On the CDU The time heading can be displayed on the CDU if the DATA DISPLAY selector switch is placed in the HDG position. (3) Ground speed (Ref. Fig. 017) The ground speed is displayed in the left upper corner of the the ROSE, ARC or PLAN mode (item A). The GS title is displayed in white color and the ground speed in green. In case of failure or NCD, the ground speed value is replaced three dashed lines (item B). The ground speed can also be displayed on the CDU if the DATA selector switch is placed in the TK/GS position.

ND for value by DISPLAY

(4) Wind indications (Ref. Fig. 017) The wind origin, force and direction are displayed in the left upper corner of the ND, for the ROSE, ARC and PLAN mode (item A): - the wind origin is displayed in green color in degrees with respect to the true North - the wind force is displayed in green color in knots - the wind direction, in analog form, is represented by means of a green arrow oriented with respect to the north reference in use. This arrow is displayed only if the wind force is greater than 2 knots. In case of failure or NCD, the digital data is replaced by three dashed lines and the wind direction arrow disappears (item B). The wind indications can also be displayed on the CDU if the DATA DISPLAY selector switch is placed in the WIND position.

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IR - GS, Wind, Vertical Speed Information Display Figure 017   EFF : 524-526, 528-599,  34-14-00 Page 57   Config-2 Feb 01/10  CES

 

(5) Vertical speed (Ref. Fig. 017) The inertial vertical speed is displayed on the right side of the PFD (item C). The vertical speed scale consists of: (a) A trapezoidal grey background colored surface. (b) A fixed white scale with 500 ft/min spaced marks from -2000 ft/min to +2000 ft/min. (c) A needle giving in analog form the actual vertical speed value. (d) A number in a moving blanking window. This window accompanies the needle (above) if V/S > 0, below if V/S < 0). The number gives the V/S value in hundreds of ft/min. Between -200 ft/min and +200 ft/min, both the window and the number disappear. (e) Above +6000 ft/min (or below -6000 ft/min), the needle remains stopped where it is. When the vertical speed exceeds +6000 ft/mn or -6000 ft/mn, the digital indication and the analog needle change from green to amber. (f) In addition, those indications change to amber in approach, in the following cases: - V/S less than -2000 ft/min below 2500 ft RA. - V/S less than -1200 ft/min below 1000 ft RA. In case of failure, the inertial vertical speed display is automatically replaced by the baro vertical speed display (Ref. 34-13-00). (6) Reconfiguration display In case of loss of inertial parameters on the CAPT or F/O PFD and ND, the IR3 can be used as a back-up source by placing the ATT HDG selector switch in the CAPT/3 position for the CAPT PFD and ND or in the F/O/3 position for the F/O PFD and ND.

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C. Warnings (Ref. Fig. 018, 019, 020, 021, 022) (1) In addition to the ATT or HDG flags displayed on the PFDs, NDs and on the CDU, warning messages are displayed on the lower part of the upper ECAM DU. (a) NAV IR 1(2)(3) FAULT NAV IR 1(2) + 2(3) FAULT When these messages are displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the IR FAULT legend flashes on the CDU. (b) NAV ATT DISCREPANCY This message is displayed when a difference higher than 5 deg. is detected by comparison inside the FWCs between the roll angle or the pitch angle provided by two IRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK ATT message appears on the PFD. (c) NAV HDG DISCREPANCY this message is displayed when a difference higher than 7 deg. (or 5 deg. in true heading) is detected by comparison inside the FWCs between the heading value provided by two IRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK HDG message appears on the PFDs and NDs. (d) NAV GPS 1(2) FAULT (Ref. Fig. 023) The GPSSUs are monitored by the three ADIRUs using the status word sent by the GPSSU and the BITE of the IR portion. This message is accompanied by: - activation of the MASTER CAUT lights on the glareshield panel - aural warning: single chime (SC). D. ADIRUs Performance Criteria (1) History The inertial parameters to be considered to evaluate the level of performance of an inertial system after flight completion are: - the radial position error (in NM) - the residual ground speed error (in kts).

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NAV IR 1(2)(3) FAULT Message Figure 018   EFF : 524-526, 528-599,  34-14-00 Page 60   Config-2 Feb 01/10  CES

 

NAV IR 1+2 FAULT Message Figure 019   EFF : 524-526, 528-599,  34-14-00 Page 61   Config-2 Feb 01/10  CES

 

NAV IR 1+3 (2+3) FAULT Message Figure 020   EFF : 524-526, 528-599,  34-14-00 Page 62   Config-2 Feb 01/10  CES

 

NAV ATT DISCREPANCY Message Figure 021   EFF : 524-526, 528-599,  34-14-00 Page 63   Config-2 Feb 01/10  CES

 

NAV HDG DISCREPANCY Message Figure 022   EFF : 524-526, 528-599,  34-14-00 Page 64   Config-2 Feb 01/10  CES

 

NAV GPS - Fault Messages Figure 023   EFF : 524-526, 528-599,  34-14-00 Page 65   Config-2 Feb 01/10  CES

 

Depending on their magnitude noticed at the end of the flight, the concerned inertial system(s) shall or shall not be removed from the aircraft. (2) Radial position error In order to address the statistical term of this requirement with the most relevant approximation, the removal criteria use a limit based on the recording of the radial position error on two consecutive flights. The use of a two-strike method presents the advantage to decrease the removal rate of healthy units that have shown, by chance, or by an inaccurate position entry at alignment, a radial position error beyond the specified criterion. The removal boundaries described on the figure present three different areas: (Ref. Fig. 024) - Area 1 - ADIRU OK all the time - Area 2 - ADIRU to be checked after second flight - Area 3 - ADIRU to be replaced. NOTE : Area 2 is applicable when the residual radial position error ____ ranges within the limits described in following paragraphs. (a) Lower limit for removal criteria The integration of the drift rate results in a lower limit for the radial position error: Radial position error (NM) = (2 (NM/h) * T (h)) + Offset (NM) The presence of an offset is necessary to avoid the unjustified removal of healthy units subject to the natural Schuler effects and to the Present Position inaccuracies entered during initialization. It should be pointed out that the adverse impacts of such inaccuracies over the radial position error will reveal stronger for short flight durations (below 1.5 hour). - Flight duration < 1.5 FH: The lower limit of the grey band is fixed at 5 NM. - 1.5 FH < Flight duration < 10 FH: The lower limit of the grey band is fixed at 2T + 2. - Flight duration > 10 FH: The lower limit of the grey band is fixed at 22 NM. (b) Upper limit for removal criteria - Flight duration < 1.5 FH: The upper limit of the grey band is fixed at 7.5 NM. - 1.5 FH < Flight duration < 10 FH: The upper limit of the grey band is fixed at 3T + 3. - Flight duration > 10 FH:

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ADIRU RPE Removal Criteria Figure 024   EFF : 524-526, 528-599,  34-14-00 Page 67   Config-2 Feb 01/10  CES

 

The upper limit of the grey band is fixed at 33 NM. (3) Residual Ground Speed Error The residual ground speed for each IR is determined at the end of the flight when the aircraft has come to a complete stop. (a) Check of the residual ground speed can be made: - On the CAPT (IR1) and F/O (IR2) Navigation Displays (ND): The residual ground speed of the IR3 can be read on the CAPT ND by setting the ATT HDG selector switch to CAPT/3. - On the ADIRS CDU: . set the DATA DISPLAY selector switch to TK/GS . set the SYS DISPLAY selector switch to 1, 2, 3 . read the respective ground speed on the CDU display. (b) Compare the recorded ground speed values with the following limits: - If the residual ground speed error is 15 kts or greater after each of two consecutive flights, replace the ADIRU. - If the residual ground speed error is 21 kts or greater at the end of any one flight, replace the ADIRU.

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ATTITUDE, HEADING AND POSITION - DESCRIPTION AND OPERATION __________________________________________________________ 1. General _______ **ON A/C 051-099, 106-149, 204-249, 301-399, 401-499, The Inertial Reference (IR) portion of the Air Data/Inertial Reference Unit (ADIRU) provides main data sources which are precision attitude, magnetic heading references and navigation data to the aircraft avionics systems. Attitude, heading and navigation data are displayed on the Electronic Flight Instrument System (EFIS) displays (Primary Flight Display (PFD); Navigation Display (ND)) and on the Digital Distance and Radio Magnetic Indicator (DDRMI) with recopies the heading data. The IR portion also provides data from the selected MMR and accurate GPIR hybrid position. R

**ON A/C 251-299, 501-509, 511-523, The Inertial Reference (IR) part of the Air Data/Inertial Reference Unit (ADIRU) supplies the primary data that follows to the aircraft avionic systems: - Precision attitude - Magnetic heading references - Navigation data. The attitude, heading and navigation data is shown on the displays of the Electronic Flight Instrument System (EFIS): - Primary Flight Display (PFD) - Navigation Display (ND). The IR part also supplies data from the selected MMR and the accurate GPIR hybrid position.

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, 2. __________________ System Description **ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, A. General The IR portion is a strapdown inertial system which provides a quality reference for attitude, heading (true and magnetic), angular rates and accelerations. The IR software also computes: - the inertial position

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the the the the the

ground velocities baro inertial vertical speed drift angle wind data flight path data.

B. Inputs (1) Digital inputs (a) FMGC inputs The IR portion is provided with two ARINC 429 low speed buses from the two ARINC 702 Flight Management and Guidance Computers (FMGCs). These buses transmit the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 270: FMGC DISCRETES. R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-523, A. General The IR portion is a strapdown inertial system which provides a quality reference for attitude, heading (true and magnetic), angular rates and accelerations. The IR software also computes: - the inertial position - the ground velocities - the baro inertial vertical speed - the drift angle - the wind data - the flight path data. The GPS partition integrated in the IR portion provides both the GPS autonomous and hybrid navigation solutions. The term hybrid is used to indicate that the navigation solution is a result of combining the GPS, Inertial, and Air Data altitude data. The autonomous navigation solution denotes a solution derived solely by the MMR using only satellite data. For each type of data, hybrid and autonomous, the software provides: - the position - the velocities (Ground, N/S, E/W) - the accuracy parameters - the integrity parameters.

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B. Inputs (1) Digital inputs (a) FMGC inputs The IR portion is provided with two ARINC 429 low speed buses from the two ARINC 702 Flight Management and Guidance Computers (FMGCs). These buses transmit the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 043: SET MAGNETIC HEADING - label 256: FIELD ELEVATION - label 270: FMGC DISCRETES - label 271: ADR discrete word 2. **ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, These data words are used for initialization and BITE purposes. (b) CDU inputs The IR portion is provided with one ARINC 429 low speed buses from the CDU. This bus transmits the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 043: SET MAGNETIC HEADING - label 277: CDU TEST. These data words are used for initialization and BITE purposes. (c) ADR inputs The IR portion is provided with three ARINC 429 low speed buses from the other two ADIRUs (ADR portion) and from its associated ADR. These buses transmit the following data words: - label 203: ALTITUDE - label 210: TRUE AIRSPEED. (d) CFDS input The IR portion is provided with one ARINC 429 low speed bus from the Centralized Fault Display System (CFDS). This bus transmits the following data words: - label 125: UTC - label 126: FLIGHT PHASE - label 155: AIRCRAFT CONFIG - label 227: CFDS COMMAND - label 260: DATE - labels 233 to 236: FLIGHT NUMBER

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- labels 301 to 303: AIRCRAFT TAIL NUMBER For more details, Ref. 34-18-00. R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-239, 305-312, 401-499, These data words are used for initialization and BITE purposes, and barometric data setting. (b) CDU inputs The IR portion is provided with one ARINC 429 low speed buses from the CDU. This bus transmits the following data words: - label 041: SET LATITUDE - label 042: SET LONGITUDE - label 043: SET MAGNETIC HEADING - label 277: CDU TEST. These data words are used for initialization and BITE purposes. (c) ADR inputs The IR portion is provided with three ARINC 429 low speed buses from the two other ADIRUs (ADR portion) and from its associated ADR. These buses transmit the following data words: - label 203: ALTITUDE - label 204: BAROMETRIC CORRECTED ALTITUDE 1 - label 210: TRUE AIRSPEED - label 212: ALTITUDE RATE - label 220: BAROMETRIC CORRECTED ALTITUDE 2 - label 241: CORRECTED AOA. (d) CFDS input The IR portion is provided with one ARINC 429 low speed bus from the Centralized Fault Display System (CFDS). This bus transmits the following data words: - label 125: UTC - label 126: FLIGHT PHASE - label 155: AIRCRAFT CONFIG - label 227: CFDS COMMAND - label 260: DATE - labels 233 to 236: FLIGHT NUMBER - labels 301 to 303: AIRCRAFT TAIL NUMBER For more details Ref. 34-18-00.

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R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, These data words are used for initialization and BITE purposes and barometric data setting. (b) ADR inputs The IR portion is provided with three ARINC 429 low-speed buses from the other two ADIRUs (ADR portion) and from its associated ADR. These buses transmit the following data words: - label 203: ALTITUDE - label 204: BAROMETRIC CORRECTED ALTITUDE 1 - label 210: TRUE AIRSPEED - label 212: ALTITUDE RATE - label 220: BAROMETRIC CORRECTED ALTITUDE 2 - label 241: CORRECTED AOA. (c) CFDS input The IR portion is provided with one ARINC 429 low-speed bus from the Centralized Fault Display System (CFDS). This bus transmits the following data words: - label 125: UTC - label 126: FLIGHT PHASE - label 155: AIRCRAFT CONFIG - label 227: CFDS COMMAND - label 260: DATE - labels 233 to 236: FLIGHT NUMBER - labels 301 to 303: AIRCRAFT TAIL NUMBER For more details Ref. 34-18-00. (d) Not Applicable **ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, (e) GPS inputs The IR portion is provided with two ARINC 429 high speed buses from the GPS portion of the Multi-Mode Receivers (MMRs). These buses transmit the following data words: - label 060: MEASUREMENT STATUS - label 061: PSEUDO RANGE - label 062: PSEUDO RANGE FINE - label 063: RANGE RATE - label 064: DELTA RANGE - label 065: SV POSITION X - label 066: SV POSITION X FINE - label 070: SV POSITION Y

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label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label

071: 072: 073: 074: 076: 101: 102: 103: 110: 111: 112: 120: 121: 125: 130: 136: 140: 141: 143: 150: 162: 163: 165: 166: 174: 247: 260: 273: 343: 347: 377:

SV POSITION Y FINE SV POSITION Z SV POSITION Z FINE UTC MEASURE TIME GPS ALTITUDE (MSL) GPS HDOP GPS VDOP GPS TRACK ANGLE GPS LATITUDE GPS LONGITUDE GPS GROUND SPEED GPS LATITUDE FINE GPS LONGITUDE FINE GPS UTC BCD GPS HORIZONTAL INTEGRITY LIMIT GPS VERTICAL FOM GPS UTC FINE GPS UTC FINE FRACTIONS TERMINAL AREA HIL GPS UTC BIN DESTINATION ETA ALT WAYPOINT ETA GPS VERTICAL VELOCITY GPS N/S VELOCITY GPS E/W VELOCITY GPS HORIZONTAL FOM GPS DATE GPS SENSOR STATUS DESTINATION HIL ALT WAYPOINT HIL EQUIPMENT IDENT

(2) Analog inputs The IR portion is provided with analog inputs for power supply purposes. For more details Ref. 34-12-00. R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-523, (e) GPS inputs The IR portion is provided with two ARINC 429 high speed buses from the GPS portion of the Multi-Mode Receivers (MMRs). These buses transmit the following data words: - label 057: USER RANGE ACCURACY - label 060: MEASUREMENT STATUS - label 061: PSEUDO RANGE

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label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label label

062: 063: 064: 065: 066: 070: 071: 072: 073: 074: 076: 101: 102: 103: 110: 111: 112: 120: 121: 125: 126: 127: 130: 136: 140: 141: 143: 144: 150: 162: 163: 165: 166: 174: 226: 247: 260: 273: 343: 347: 377:

PSEUDO RANGE FINE RANGE RATE DELTA RANGE SV POSITION X SV POSITION X FINE SV POSITION Y SV POSITION Y FINE SV POSITION Z SV POSITION Z FINE UTC MEASURE TIME GPS ALTITUDE (MSL) GPS HDOP GPS VDOP GPS TRACK ANGLE GPS LATITUDE GPS LONGITUDE GPS GROUND SPEED GPS LATITUDE FINE GPS LONGITUDE FINE GPS UTC BCD SAT DE-SELECT 1 SAT DE-SELECT 2 GPS HORIZONTAL INTEGRITY LIMIT GPS VERTICAL FOM GPS UTC FINE GPS UTC FINE FRACTIONS TERMINAL AREA HIL APPROACH AREA HIL GPS UTC BIN DESTINATION ETA ALT WAYPOINT ETA GPS VERTICAL VELOCITY GPS N/S VELOCITY GPS E/W VELOCITY GPS DATA LOADER GPS HORIZONTAL FOM GPS DATE GPS SENSOR STATUS DESTINATION HIL ALT WAYPOINT HIL EQUIPMENT IDENT

(2) Analog inputs The IR portion is provided with analog inputs for power supply and GPS/IRS synchronization purposes (Time Mark). For more details Ref. 34-12-00.

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R R

**ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-312, 401-499, (3) Discrete inputs The IR portion is provided with the following discrete inputs: --------------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT | | | | DEFINITION | --------------------------------------------------------------------| Mounting position 1 | Open/GND | see table 2 | | Mounting position 2 | Open/GND | see table 2 | | SDI MSB (Middle insert) | Open/GND | 0/1 | | SDI LSB (Middle insert) | Open/GND | 0/1 | | CDU ON/OFF | Open/GND |Not displayed/displayed| | IR mode select M1 | Open/GND | see table 3 | | IR mode select M2 | Open/GND | see table 3 | | Auto ADR.DADS select | Open/GND | see table 4 | | Manual ADR.DADS select | Open/GND | see table 4 | | Aircraft Ident Code 1/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 2/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 4/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 8/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 16/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 32/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 64/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code Parity |Open/A.I. Com| 0/1 | | IR remote test | Open/GND | No test/test | | MAGVAR select | Open/GND |Standard/expended model| | GPS sensor 1 present | Open/GND | GND = present | | GPS sensor 2 present | Open/GND | GND = present | | GPS priority select | Open/GND |Normal priority/ | | | |Reserved priority | --------------------------------------------------------------------Table 1 : IR Discrete Inputs (a) Mounting positions 1 and 2 These discrete inputs are used to indicate to the IR the orientation of the unit. It is needed to know the longitudinal and lateral axis of the aircraft. Table 2 below gives the unit position in function of the discrete selection.

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--------------------------------------------------------------| Mounting | Mounting | Connector Position/Aircraft | | Position 1 | Position 2 | | --------------------------------------------------------------| Open * | Open * | FWD * | | Ground | Open | AFT | | Open | Ground | RIGHT | | Ground | Ground | LEFT | --------------------------------------------------------------Table 2 : Mounting Position Discretes * The discretes are wired in FWD position. (b) IR mode select The IR portion uses these discrete inputs to know the position of the OFF/NAV/ATT selector switch as follows: ---------------------------------------------| M1 | M2 | OFF/NAV/ATT | | | | Selector Switch Position | |--------------------------------------------| | Open | Open | OFF | | Ground | Open | NAV | | Open | Ground | ATT | ---------------------------------------------Table 3 : IR Mode Select (4) Not Applicable R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-239, (3) Discrete inputs The IR portion is provided with the following discrete inputs: --------------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT | | | | DEFINITION | --------------------------------------------------------------------| Mounting position 1 | Open/GND | see table 2 | | Mounting position 2 | Open/GND | see table 2 | | SDI MSB (Middle insert) | Open/GND | 0/1 | | SDI LSB (Middle insert) | Open/GND | 0/1 | | CDU ON/OFF | Open/GND |Not displayed/displayed| | IR mode select M1 | Open/GND | see table 3 | | IR mode select M2 | Open/GND | see table 3 | | Auto ADR.DADS select | Open/GND | see table 4 |

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--------------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT | | | | DEFINITION | --------------------------------------------------------------------| Manual ADR.DADS select | Open/GND | see table 4 | | Aircraft Ident Code 1/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 2/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 4/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 8/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 16/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 32/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 64/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code Parity |Open/A.I. Com| 0/1 | | IR remote test | Open/GND | No test/test | | MAGVAR select | Open/GND |Reserved/expended model| | GPS sensor 1 present | Open/GND | GND = present | | GPS sensor 2 present | Open/GND | GND = present | | GPS priority select | Open/GND |Normal priority/ | | | |Reserved priority | --------------------------------------------------------------------Table 1 : IR Discrete Inputs (a) Mounting positions 1 and 2 These discrete inputs are used to indicate to the IR the orientation of the unit. It is needed to know the longitudinal and lateral axis of the aircraft. Table 2 below gives the unit position in function of the discrete selection. --------------------------------------------------------------| Mounting | Mounting | Connector Position/Aircraft | | Position 1 | Position 2 | | --------------------------------------------------------------| Open * | Open * | FWD * | | Ground | Open | AFT | | Open | Ground | RIGHT | | Ground | Ground | LEFT | --------------------------------------------------------------Table 2 : Mounting Position Discretes * The discretes are wired in FWD position. (b) IR mode select The IR portion uses these discrete inputs to know the position of the OFF/NAV/ATT selector switch as follows:

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---------------------------------------------| M1 | M2 | OFF/NAV/ATT | | | | Selector Switch Position | |--------------------------------------------| | Open | Open | OFF | | Ground | Open | NAV | | Open | Ground | ATT | ---------------------------------------------Table 3 : IR Mode Select (4) Not Applicable R

**ON A/C 240-249, 251-299, 501-509, 511-523, (3) Discrete inputs The IR portion is provided with the following discrete inputs: --------------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT | | | | DEFINITION | --------------------------------------------------------------------| Mounting position 1 | Open/GND | see table 2 | | Mounting position 2 | Open/GND | see table 2 | | SDI MSB (Middle insert) | Open/GND | 0/1 | | SDI LSB (Middle insert) | Open/GND | 0/1 | | IR OFF | Open/GND |Momentary action | | IR mode select M1 | Open/GND | see table 3 | | IR mode select M2 | Open/GND | see table 3 | | Auto ADR.DADS select | Open/GND | see table 4 | | Manual ADR.DADS select | Open/GND | see table 4 | | Aircraft Ident Code 1/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 2/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 4/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 8/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 16/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 32/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 64/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code Parity |Open/A.I. Com| 0/1 | | IR remote test | Open/GND | No test/test | | MAGVAR select | Open/GND |Reserved/expended model| | GPS sensor 1 present | Open/GND | GND = present | | GPS sensor 2 present | Open/GND | GND = present | | GPS priority select | Open/GND |Normal priority/ | | | |Reserved priority | --------------------------------------------------------------------Table 1 : IR Discrete Inputs

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(a) Mounting positions 1 and 2 These discrete inputs are used to indicate to the IR the orientation of the unit. It is needed to know the longitudinal and lateral axes of the aircraft. Table 2 below gives the unit position according to discrete selection. --------------------------------------------------------------| Mounting | Mounting | Connector Position/Aircraft | | Position 1 | Position 2 | | --------------------------------------------------------------| Open * | Open * | FWD * | | Ground | Open | AFT | | Open | Ground | RIGHT | | Ground | Ground | LEFT | --------------------------------------------------------------Table 2 : Mounting Position Discretes * The discretes are wired in FWD position. (b) IR mode select The IR portion uses these discrete inputs to know the position of the OFF/NAV/ATT selector switch as follows: ---------------------------------------------| M1 | M2 | OFF/NAV/ATT | | | | Selector Switch Position | |--------------------------------------------| | Open | Open | OFF | | Ground | Open | NAV | | Open | Ground | ATT | ---------------------------------------------Table 3 : IR Mode Select

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(4) Discrete inputs The IR portion is provided with the following discrete inputs: --------------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT | | | | DEFINITION | --------------------------------------------------------------------| Mounting position 1 | Open/GND | see table 2 | | Mounting position 2 | Open/GND | see table 2 | | SDI MSB (Middle insert) | Open/GND | 0/1 | | SDI LSB (Middle insert) | Open/GND | 0/1 | | IR mode select M1 | Open/GND | see table 3 | | IR mode select M2 | Open/GND | see table 3 | | Auto ADR.DADS select | Open/GND | see table 4 | | Manual ADR.DADS select | Open/GND | see table 4 | | Aircraft Ident Code 1/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 2/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 4/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 8/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 16/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 32/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 64/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code Parity |Open/A.I. Com| 0/1 | | IR remote test | Open/GND | No test/test | | MAGVAR select | Open/GND |Reserved/expended model| | GPS sensor 1 present | Open/GND | GND = present | | GPS sensor 2 present | Open/GND | GND = present | | GPS priority select | Open/GND |Normal priority/ | | | |Reserved priority | --------------------------------------------------------------------Table 1 : IR Discrete Inputs (a) Mounting positions 1 and 2 These discrete inputs are used to indicate to the IR the orientation of the unit. It is needed to know the longitudinal and lateral axes of the aircraft. Table 2 below gives the unit position according to discrete selection.

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--------------------------------------------------------------| Mounting | Mounting | Connector Position/Aircraft | | Position 1 | Position 2 | | --------------------------------------------------------------| Open * | Open * | FWD * | | Ground | Open | AFT | | Open | Ground | RIGHT | | Ground | Ground | LEFT | --------------------------------------------------------------Table 2 : Mounting Position Discretes * The discretes are wired in FWD position. (b) IR mode select The IR portion uses these discrete inputs to know the position of the OFF/NAV/ATT selector switch as follows: ---------------------------------------------| M1 | M2 | OFF/NAV/ATT | | | | Selector Switch Position | |--------------------------------------------| | Open | Open | OFF | | Ground | Open | NAV | | Open | Ground | ATT | ---------------------------------------------Table 3 : IR Mode Select **ON A/C 313-399, (3) Discrete inputs The IR portion is provided with the following discrete inputs: --------------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT | | | | DEFINITION | --------------------------------------------------------------------| Mounting position 1 | Open/GND | see table 2 | | Mounting position 2 | Open/GND | see table 2 | | SDI MSB (Middle insert) | Open/GND | 0/1 | | SDI LSB (Middle insert) | Open/GND | 0/1 | | IR OFF | Open/GND |Momentary action | | IR mode select M1 | Open/GND | see table 3 | | IR mode select M2 | Open/GND | see table 3 | | Auto ADR.DADS select | Open/GND | see table 4 | | Manual ADR.DADS select | Open/GND | see table 4 | | Aircraft Ident Code 1/0 |Open/A.I. Com| 0/1 |

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R R R R R R R R R R R R R R R

--------------------------------------------------------------------| INPUT SIGNAL | INPUT | INPUT | | | | DEFINITION | --------------------------------------------------------------------| Aircraft Ident Code 2/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 4/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 8/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 16/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 32/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code 64/0 |Open/A.I. Com| 0/1 | | Aircraft Ident Code Parity |Open/A.I. Com| 0/1 | | IR remote test | Open/GND | No test/test | | MAGVAR select | Open/GND |Standard/expended model| | GPS sensor 1 present | Open/GND | GND = present | | GPS sensor 2 present | Open/GND | GND = present | | GPS priority select | Open/GND |Normal priority/ | | | |Reserved priority | --------------------------------------------------------------------Table 1 : IR Discrete Inputs

R R R R R R

(a) Mounting positions 1 and 2 These discrete inputs are used to indicate to the IR the orientation of the unit. It is needed to know the longitudinal and lateral axes of the aircraft. Table 2 below gives the unit position according to discrete selection.

R R R R R R R R R R

--------------------------------------------------------------| Mounting | Mounting | Connector Position/Aircraft | | Position 1 | Position 2 | | --------------------------------------------------------------| Open * | Open * | FWD * | | Ground | Open | AFT | | Open | Ground | RIGHT | | Ground | Ground | LEFT | --------------------------------------------------------------Table 2 : Mounting Position Discretes

R

* The discretes are wired in FWD position.

R R R

(b) IR mode select The IR portion uses these discrete inputs to know the position of the OFF/NAV/ATT selector switch as follows:

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---------------------------------------------| M1 | M2 | OFF/NAV/ATT | | | | Selector Switch Position | |--------------------------------------------| | Open | Open | OFF | | Ground | Open | NAV | | Open | Ground | ATT | ---------------------------------------------Table 3 : IR Mode Select (4) Not Applicable R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (c) ADR DADS select The IR portion uses these discrete inputs to know which air data source to use: -------------------------------------------------------------------| Auto | Manual | IR Selection | | ADR DADS | ADR DADS | | -------------------------------------------------------------------| Open | Open | The IR uses the air data received | | | | on port 1 | |-------------|----------------|-----------------------------------| | Open | Ground | The IR uses the air data received | | | | on port 2 | |-------------|----------------|-----------------------------------| | Ground * | Open | The IR goes automatically from one| | | | air data source to the others | | | | according to their validity and | | | | priority. * | -------------------------------------------------------------------Table 4 : ADR DADS Select * The discretes are wired in the automatic ADR selection mode with the following priority: 1: its own ADR unit 2: ADR received on port 1 3: ADR received on port 2. (d) SDI program pins These discretes code the installation side of the ADIRU. The following table gives the IR side according to the SDI.

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-------------------------------------------| SDI-MSB | SDI-LSB | ADIRU NUMBER | -------------------------------------------| OPEN | GROUND | 1 | | GROUND | OPEN | 2 | | GROUND | GROUND | 3 | -------------------------------------------Table 5 : IR SDI Code **ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-399, 401-499, (e) IR remote test The IR portion uses one discrete to select the remote test by external control. When this discrete is open, the test is not activated. When this discrete is grounded, the test is activated. In normal operation this discrete is open (unused) but can be also activated via the CFDIU on ground (Ref. 34-18-00). (f) CFDS message select On the A/C, this discrete is open. (g) GPS present These discretes are used to activate GPS/IRS hybridization (computation, BITE function). (h) GPS priority select The GPIRS function uses this discrete to modify the GPS priority. Each ADIRU receives data from the two GPS portions of the MMRs on the primary and secondary inputs. For each ADIRU, the primary and secondary GPS inputs are defined as follows: --------------------------------------------| ADIRU | PRIMARY | SECONDARY | | SDI | INPUT | INPUT | --------------------------------------------| 1 | GPSSU 1 (MMR 1) | GPSSU 2 (MMR 2) | | 2 | GPSSU 2 (MMR 2) | GPSSU 1 (MMR 1) | | 3 | GPSSU 1 (MMR 1) | GPSSU 2 (MMR 2) | --------------------------------------------Depending on the GPS validity and GPS priority select input discrete status, the GPS source is defined as follows:

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--------------------------------------------------------------------| PRIORITY | PRIMARY | SECONDARY | GPSSU SOURCE | | STATUS | GPSSU | GPSSU |----------------------------------| | | | GPS PRIORITY | GPS PRIORITY | | | | | SELECT = OPEN | SELECT = GROUND | --------------------------------------------------------------------| 1 | Valid | Valid | Primary | Secondary | | 2 | Valid | Fail | Primary | Primary | | 3 | Fail | Valid | Secondary | Secondary | | 4 | Fail | Fail | Primary | Secondary | --------------------------------------------------------------------R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 501-509, 511-523, (e) IR remote test The IR portion uses one discrete to select the remote test by external control. When this discrete is open, the test is not activated. When this discrete is grounded, the test is activated. On the A/C, this discrete is opened. In normal operation this discrete is open (unused) but can be also activated via the CFDIU on ground (Ref. 34-18-00). (f) CFDS message select On the A/C, this discrete is open. (g) GPS present These discretes are used to activate GPS/IRS hybridization (computation, BITE function). (h) GPS priority select The GPIRS function uses this discrete to modify the GPS priority. Each ADIRU receives data from the two GPS portions of the MMRs on the primary and secondary inputs. For each ADIRU, the primary and secondary GPS inputs are defined as follows: --------------------------------------------| ADIRU | PRIMARY | SECONDARY | | SDI | INPUT | INPUT | --------------------------------------------| 1 | GPSSU 1 (MMR 1) | GPSSU 2 (MMR 2) | | 2 | GPSSU 2 (MMR 2) | GPSSU 1 (MMR 1) | | 3 | GPSSU 1 (MMR 1) | GPSSU 2 (MMR 2) | ---------------------------------------------

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Depending on the GPS validity and GPS priority select input discrete status, the GPS source is defined as follows: --------------------------------------------------------------------| PRIORITY | PRIMARY | SECONDARY | GPSSU SOURCE | | STATUS | GPSSU | GPSSU |----------------------------------| | | | GPS PRIORITY | GPS PRIORITY | | | | | SELECT = OPEN | SELECT = GROUND | --------------------------------------------------------------------| 1 | Valid | Valid | Primary | Secondary | | 2 | Valid | Fail | Primary | Primary | | 3 | Fail | Valid | Secondary | Secondary | | 4 | Fail | Fail | Primary | Secondary | --------------------------------------------------------------------**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-514, C. Software Computation **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 001) **ON A/C 240-249, 251-299, 313-399, 501-509, 511-514, (Ref. Fig. 001A) **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 002) **ON A/C 240-249, 251-299, 313-399, 501-509, 511-514, (Ref. Fig. 002A) **ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-514, The software contains the program memory and provides the following basic functions: - real-time executive - attitude integration

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ADIRU - IR Block Diagram Figure 001   R EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page 20 401-499,  Config-3 Feb 01/08  CES

 

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ADIRU - IR Signal Flow Diagram Figure 002   R EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page 22 401-499,  Config-3 Feb 01/08  CES

 

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- velocity integration - position integration - output computation - built-in test (Ref. 34-18-00). The IR software operates in one of three basic modes: alignment, navigation, or a reversionary attitude mode. These modes include various portions of the major functions. The real-time executive and built-in test functions interface with each function in each mode. (1) Alignment mode The alignment is the initialization mode for the IR. Its primary function is to initialize the attitude, velocity and position integration functions implemented in the navigation mode. This mode operates on the ground only. The IR alignment mode is divided into three parts: - coarse level processing The coarse level processing is engaged during the first 30 seconds of the IR alignment mode. This processing estimates the local vertical using the three accelerometers and the measured gravity. During coarse level processing of the alignment mode, the software computes the level coordinate frame, pitch and roll, and associated rates and accelerations. - gyro-compass (or azimuth) processing and level processing Gyro-compass processing is engaged after the 30 seconds of the IR alignment mode (coarse level complete) and runs for a minimum of 9.5 minutes. Gyro-compass processing is used to orient body frame to North (using earth rotation detection by gyros). During this alignment submode, an estimated latitude is computed using local vertical component of the earth rotation. During this submode, the results of the coarse level processing are sharpened to have a better knowledge of the coordinate frame. R

**ON A/C 515-523, C. Software Computation (Ref. Fig. 001A, 002A) The software contains the program memory and provides the following basic functions: - real-time executive - attitude integration - velocity integration - position integration - output computation - built-in test (Ref. 34-18-00).

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The IR software operates in one of three basic modes: alignment, navigation, or a reversionary attitude mode. These modes include various portions of the major functions. The real-time executive and built-in test functions interface with each function in each mode. (1) Alignment mode The alignment is the initialization mode for the IR. Its primary function is to initialize the attitude, velocity and position integration functions implemented in the navigation mode. This mode operates on the ground only. The IR alignment mode is divided into three parts: - coarse level processing The coarse level processing is engaged during the first 30 seconds of the IR alignment mode. This processing estimates the local vertical using the three accelerometers and the measured gravity. During coarse level processing of the alignment mode, the software computes the level coordinate frame, pitch and roll, and associated rates and accelerations. - gyro-compass (or azimuth) processing and level processing Gyro-compass processing is engaged after the 30 seconds of the IR alignment mode (coarse level complete) and run for a minimum of 5 minutes. The ADIRU alignment time will be reduced from 10 minutes fixed alignment time to a variable time based on aircraft latitude. Gyro-compass processing is used to orient body frame to North (using earth rotation detection by gyros). During this alignment submode, an estimated latitude is computed using local vertical component of the earth rotation. During this submode, the results of the coarse level processing are sharpened to have a better knowledge of the coordinate frame. **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, - position entry data processing This position initialization can take place in coarse level processing or gyro-compass processing. The latitude and longitude pair processed for position initialization is received from the same source (FMGC 1, FMGC 2 or CDU). As soon as a valid position initialization pair is received, the software performs a BITE test to check if the entered latitude and longitude are within the following limits versus the position recorded at the end of the last power- up cycle: Abs val( lat entered - lat recorded ) less than or equal to 1 deg.

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Abs val( long entered - long recorded ) less than or equal to 1 deg (Ref. 34-18-00). A second BITE test is performed on the entered latitude when an estimated latitude is available during the gyro-compass processing: Abs val(cos (lat est) - cos (lat ent)) less than or equal to 0.01234. Abs val(sin (lat est) - sin (lat ent)) less than or equal to 0.01234. The alignment is completed after 10 minutes if a valid position data has been received and verified by the IR. If not, the automatic sequencing to the NAV mode will be delayed (up to 1 minute) after position data is received. The operations to enter position and the warnings associated to the tests performed in alignment mode are described in para. 3 (operation/control and indicating). The IR also offers the possibility to enter into a variant of the alignment mode called rapid realign or 30-second realign. This mode is selected by moving the CDU selector switch from NAV to OFF, then to NAV within five seconds, when the aircraft is on ground (ground speed less than 20 knots). Valid position data must be received. During the rapid realign mode, all computed velocities are set to zero and a fine tuning of the alignment is performed using the attitude reference vertical and the heading data available from the last NAV phase as initial conditions. During the alignment mode, the IR outputs on the ARINC 429 bus may not be available. Position initialization of the ADIRU is transmitted to the MMR for its own initialization. In addition to this position, the MMR requires initialization data of date and UTC. The IR portion receives date and UTC from the CMC and transmits the data to the MMRs. The chronology of the validation of the outputs during the alignment is given in para. 2-D (IR output data).

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R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-514, - position entry data processing This position initialization can take place in coarse level processing or gyro-compass processing. The latitude and longitude pair processed for position initialization is received from the same source (FMGC 1 or FMGC 2). As soon as a valid position initialization pair is received, the software performs a BITE test to check if the entered latitude and longitude are within the following limits versus the position recorded at the end of the last power- up cycle: Abs val( lat entered - lat recorded ) less than or equal to 1 deg. Abs val( long entered - long recorded ) less than or equal to 1 deg (Ref. 34-18-00). A second BITE test is performed on the entered latitude when an estimated latitude is available during the gyro-compass processing: Abs val(cos (lat est) - cos (lat ent)) less than or equal to 0.01234. Abs val(sin (lat est) - sin (lat ent)) less than or equal to 0.01234. The alignment is completed after 10 minutes if a valid position data has been received and verified by the IR. If not, the automatic sequencing to the NAV mode will be delayed (up to 1 minute) after position data is received. The operations to enter position and the warnings associated to the tests performed in alignment mode are described in para. 3 (operation/control and indicating). The IR also offers the possibility to enter into a variant of the alignment mode called rapid realign or 30-second realign. This mode is selected by moving the MSU selector switch from NAV to OFF, then to NAV within five seconds, when the aircraft is on ground (ground speed less than 20 knots). Valid position data must be received. During the rapid realign mode, all computed velocities are set to zero and a fine tuning of the alignment is performed using the attitude reference vertical and the heading data available from the last NAV phase as initial conditions. During the alignment mode, the IR outputs on the ARINC 429 bus may not be available. Position initialization of the ADIRU is transmitted to the MMR for its own initialization. In addition to this position, the MMR requires initialization data of date and

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UTC. The IR portion receives date and UTC from the CMC and transmits the data to the MMRs. The chronology of the validation of the outputs during the alignment is given in para. 2-D (IR output data). R

**ON A/C 515-523, - position entry data processing This position initialization can take place in coarse level processing or gyro-compass processing. The latitude and longitude pair processed for position initialization is received from the same source (FMGC 1, FMGC 2, GPSSU1/MMR1 or GPSSU2/MMR2). .If a GPS position data is available and if there is no pilot entry, the GPS data is used to perform the alignment. .If a GPS position data is available and if there is a pilot entry, the pilot entry is compared with the GPS position. The discrepancies between the two latitudes and the two longitudes must be within 5Nm. If the discrepancies exceed 5Nm, the ALIGN annunciator flashes. . If no GPS position data is available, the software performs a BITE test to check if the entered latitude and longitude are within the following limits versus the position recorded at the end of the last power-up cycle: Abs val( lat entered - lat recorded ) less than or equal to 1 deg. Abs val( long entered - long recorded ) less than or equal to 1 deg (Ref. 34-18-00). A second BITE test is performed on the entered latitude when an estimated latitude is available during the gyro-compass processing: Abs val(cos (lat est) - cos (lat ent)) less than or equal to 0.01234. Abs val(sin (lat est) - sin (lat ent)) less than or equal to 0.01234. The alignment is completed if a valid position data has been received and verified by the IR. The typical alignment time will be calculated for a given latitude as follows:

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ABS (5.0 minutes/cosine (latitude)) for latitudes between 60S and 60N 10.0 minutes at a latitude more than or equal to 73.0S and less than 60S 10.0 minutes at a latitude more than 60N and less than or equal to 73.0N 17 minutes at latitude less than 73.0S 17 minutes at latitude more than 73.0N (Ref. Fig. 003) If not, the automatic sequencing to the NAV mode will be delayed (up to 1 minute) after position data is received. The operations to enter position and the warnings associated to the tests performed in alignment mode are described in para. 3 (operation/control and indicating). The IR also offers the possibility to enter into a variant of the alignment mode called rapid realign or 30-second realign. This mode is selected by moving the MSU selector switch from NAV to OFF, then to NAV within five seconds, when the aircraft is on ground (ground speed less than 20 knots). Valid position data must be received. During the rapid realign mode, all computed velocities are set to zero and a fine tuning of the alignment is performed using the attitude reference vertical and the heading data available from the last NAV phase as initial conditions. During the alignment mode, the IR outputs on the ARINC 429 bus may not be available. Position initialization of the ADIRU is transmitted to the MMR for its own initialization. In addition to this position, the MMR requires initialization data of date and UTC. The IR portion receives date and UTC from the CMC and transmits the data to the MMRs. The chronology of the validation of the outputs during the alignment is given in para. 2-D (IR output data). **ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-399, 401-499, (2) Navigation (NAV) mode (Ref. Fig. 004) The NAV mode is the primary operating mode for the IR and is implemented in software as unaided strapdown inertial navigation computation. The basic operating elements consist of three integration functions (attitude, velocity and position) driven by input gyro and accelerometer strapdown sensor data. The equations used to compute the main parameters are the following: - body pitch, roll, yaw rates (labels 326, 327, 330): they are representative of the aircraft body rotations relative to the aircraft body axes and are directly measured by the laser gyros.

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ADIRU - Alignment Time in North Hemisphere Figure 003   R EFF : 515-523,  34-14-00 Page 30   Config-3 Feb 01/10  CES

 

ADIRU - Navigation Mode Functions Figure 004   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page 31 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

- body longitudinal, lateral, normal accelerations (labels 331, 332, 333): they are directly measured by the accelerometers but with the gravity effect substracted to have 0g on the normal acceleration when in level. - pitch and roll attitude rate (labels 336, 337) Pitch Att rate = Q. cos (Ra) - R. sin (Ra) Q. sin (Ra) + R. cos (Ra) Roll Att rate = P + ------------------------cos (Pa)/sin (Pa) where : Ra = Roll angle Pa = Pitch angle P = Body roll rate Q = Body pitch rate R = Body yaw rate - flight path angle (label 322) = angle between the aircraft velocity vector and the horizontal plane (VZ) FPA = Arc tan (--) (VG) where : VZ = inertial vertical speed (label 365) VG = ground speed (label 312)

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- flight path acceleration (label 323) = aircraft acceleration along the total velocity vector Vx.Ax + Vy.Ay + Vz.Az Flt Path Accel = --------------------______________ / 2 2 2 V Vx + Vy + Vz where : Ax, Ay, Az, Vx, Vy, Vz: accelerations and velocities in the earth frame. - wind speed and direction computation (labels 315 and 316) ___________________ / 2 2 Wind speed = V Vwind N + Vwind E (Vwind E) Wind direction = Arc tan (-------) + 180 deg. (Vwind N) Vwind E = Veast - cos (Pa). sin (Hdg). TAS Vwind N = Vnorth - cos (Pa). cos (Hdg). TAS where : Veast = east velocity = label 367 Vnorth = north velocity = label 366 Pa = pitch angle = label 324 Hdg = heading = label 314 TAS = true airspeed. The TAS is received from the ADR. The ADR source to be used is selected according to the configuration of the discretes described in para. 2.B.(3)(d). The IR does not compute the wind if the TAS is less than 100 knots or if the air data sources are no more available. In this case, the wind labels are sent with their status matrix coded NCD (No Computed Data). - Inertial vertical speed and inertial altitude computation (labels 365 and 361) The IR software contains a baro-inertial loop to compute the Inertial Vertical Speed and Inertial Altitude. This loop permits to take advantage of the different qualities of the inertial and air data systems. The IR brings its better behaviour in dynamic maneuvers while the ADR brings its stability in time (no drift of the outputs like in IR). The principle of the baro-inertial loop is given in: the figure (Ref. Fig. 005)

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IR - Baro Inertial Altitude Filter Figure 005   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page 34 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

The ADR source to be used is selected according to the configuration of the discretes described in para. 2.B.(3)(d). When no ADR source is available, the labels 361 and 365 are sent with their status matrix coded NCD (No Computed Data). - Magnetic deviation computation The principle of the inertial system is based on geographic referenced measurements and computation. To create the labels which are magnetic referenced (magnetic heading, magnetic track angle ; labels 320, 317) the IR computes a magnetic variation which is added to the true values (labels 314, 313). The magnetic variation is computed as a function of the present position (latitude and longitude) within the range of 73⁰N to 60⁰S. The magnetic variation at any given point is calculated by using four grid intersection data values and a two-dimensional linear interpolation. The grid data comes from the National Oceanic and Atmospheric Administration and must be updated every 10 years in order to meet the accuracy requirements. The computation and display of navigation data by the FMGS and the EIS are in magnetic references (using magnetic referenced labels from the IR). R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 501-509, 511-523, (2) Navigation (NAV) mode (Ref. Fig. 004) The NAV mode is the primary operating mode for the IR and is implemented in software as unaided strapdown inertial navigation computation. The basic operating elements consist of three integration functions (attitude, velocity and position) driven by input gyro and accelerometer strapdown sensor data. The equations used to compute the main parameters are the following: - body pitch, roll, yaw rates (labels 326, 327, 330): they are representative of the aircraft body rotations relative to the aircraft body axes and are directly measured by the laser gyros. - body longitudinal, lateral, normal accelerations (labels 331, 332, 333): they are directly measured by the accelerometers but with the gravity effect substracted to have 0g on the normal acceleration when in level. - pitch and roll attitude rate (labels 336, 337)

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Pitch Att rate = Q. cos (Ra) - R. sin (Ra) Q. sin (Ra) + R. cos (Ra) Roll Att rate = P + ------------------------cos (Pa)/sin (Pa) where : Ra = Roll angle Pa = Pitch angle P = Body roll rate Q = Body pitch rate R = Body yaw rate - flight path angle (label 322) = angle between the aircraft velocity vector and the horizontal plane (VZ) FPA = Arc tan (--) (VG) where : VZ = inertial vertical speed (label 365) VG = ground speed (label 312)

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- flight path acceleration (label 323) = aircraft acceleration along the total velocity vector Vx.Ax + Vy.Ay + Vz.Az Flt Path Accel = --------------------______________ / 2 2 2 V Vx + Vy + Vz where : Ax, Ay, Az, Vx, Vy, Vz: accelerations and velocities in the earth frame. - wind speed and direction computation (labels 315 and 316) ___________________ / 2 2 Wind speed = V Vwind N + Vwind E (Vwind E) Wind direction = Arc tan (-------) + 180 deg. (Vwind N) Vwind E = Veast - cos (Pa). sin (Hdg). TAS Vwind N = Vnorth - cos (Pa). cos (Hdg). TAS where : Veast = east velocity = label 367 Vnorth = north velocity = label 366 Pa = pitch angle = label 324 Hdg = heading = label 314 TAS = true airspeed. The TAS is received from the ADR. The ADR source to be used is selected according to the configuration of the discretes described in para. 2.B.(3)(d). The IR does not compute the wind if the TAS is less than 100 knots or if the air data sources are no more available. In this case, the wind labels are sent with their status matrix coded NCD (No Computed Data). - inertial vertical speed and inertial altitude computation (labels 365 and 361) The IR software contains a baro-inertial loop to compute the Inertial Vertical Speed and Inertial Altitude. This loop permits to take advantage of the different qualities of the inertial and air data systems. The IR brings its better behaviour in dynamic maneuvers while the ADR brings its stability in time (no drift of the outputs like in IR). The principle of the baro-inertial loop is given in: the figure (Ref. Fig. 005) The ADR source to be used is selected according to the configuration of the discretes described in para. 2.B.(3)(d). When

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no ADR source is available, the labels 361 and 365 are sent with their status matrix coded NCD (No Computed Data). - magnetic deviation computation The principle of the inertial system is based on geographic referenced measurements and computation. To create the labels which are magnetic referenced (magnetic heading, magnetic track angle ; labels 320, 317) the IR computes a magnetic variation which is added to the true values (labels 314, 313). The magnetic variation is computed as a function of the present position (latitude and longitude) within the range of 73⁰N to 60⁰S excluding the magnetic polar region (latitude exceeds 73⁰N and longitude between 120⁰W and 90⁰W). The magnetic variation at any given point is calculated by using four grid intersection data values and a two-dimensional linear interpolation. The grid data comes from the National Oceanic and Atmospheric Administration and must be updated every 10 years in order to meet the accuracy requirements. The computation and display of navigation data by the FMGS and the EIS are in magnetic references (using magnetic referenced labels from the IR). R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, - GPS/IRS hybridization computation At the end of GPIR NAV mode ground align processing, an 18-state PR/DR (Pseudo Range / Delta Range) mechanized Kalman filter is engaged to estimate the system error states. The hybrid solution is then corrected by removing its errors estimated from the Kalman filter. **ON A/C 051-099, 106-149, 204-239, 301-304, 401-499, (3) Attitude mode The attitude mode is a reversionary mode which can be activated only by manual selection of the ATT mode on the CDU. The mode can be activated on the ground or in flight and is intended to provide a rapid attitude/heading restart capability if the IR has experienced total power shutdown or failures which do not disable the mechanization of the attitude computation. The necessity of selecting ATT is indicated by the IR on its action code (label 350 - code 04 = select ATT) and this data is used by the FWC to display a message on the ECAM displays. On the CDU, the STS-SELECT ATT indication comes into view if the DISPLAY/DATA selector switch is in STS (status) position.

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This mode needs a 20-second initialization phase with the aircraft in level flight. During this phase, all the ARINC bus outputs are sent with their status matrix coded NCD (No Computed Data). At the end of the initialization phase the IR sends valid outputs of: - body axis accelerations and angular rates - pitch and roll attitude and rate - vertical acceleration - vertical velocity - baro-inertial altitude and vertical speed (Ref. para. D - IR output data, list of valid labels). The magnetic heading may also be valid if an initialization value has been sent by the FMGC (through the MCDU) or the CDU. (Ref. para. D - IR output data for the complete list of valid outputs). R

**ON A/C 240-249, 251-299, 501-509, 511-523, (3) Attitude mode The attitude mode is a reversionary mode that can be activated only by manual selection of the ATT mode on the MSU. The mode can be activated on the ground or in flight and is intended to provide a rapid attitude/heading restart capability if the IR has experienced total power shutdown or failures which do not disable the mechanization of the attitude computation. The necessity of selecting ATT is indicated by the IR in its action code (label 350 - code 04 = select ATT) and this data is used by the FWC to display a message on the ECAM displays. This mode needs a 20-second initialization phase with the aircraft in level flight. During this phase, all the ARINC bus outputs are sent with their status matrix coded NCD (No Computed Data). At the end of the initialization phase the IR sends valid outputs of: - body axis accelerations and angular rates - pitch and roll attitude and rate - vertical acceleration - vertical velocity - baro-inertial altitude and vertical speed (Ref. para. D - IR output data, list of valid labels). The magnetic heading may also be valid if an initialization value has been sent by the FMGC (through the MCDU) (Ref. para. D - IR output data for the complete list of valid outputs).

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**ON A/C 305-312, (3) Attitude mode The attitude mode is a reversionary mode which can be activated only by manual selection of the ATT mode on the CDU. The mode can be activated on the ground or in flight and is intended to provide a rapid attitude/heading restart capability if the IR has experienced total power shutdown or failures which do not disable the mechanization of the attitude computation. The necessity of selecting ATT is indicated by the IR on its action code (label 350 - code 04 = select ATT) and this data is used by the FWC to display a message on the ECAM displays. On the CDU, the STS-SELECT ATT indication comes into view if the DISPLAY/DATA selector switch is in STS (status) position. This mode needs a 20-second initialization phase with the aircraft in level flight. During this phase, all the ARINC bus outputs are sent with their status matrix coded NCD (No Computed Data). At the end of the initialization phase the IR sends valid outputs of: - body axis accelerations and angular rates - pitch and roll attitude and rate - vertical acceleration - vertical velocity - baro-inertial altitude and vertical speed (Ref. para. D - IR output data, list of valid labels). The magnetic heading may also be valid if an initialization value has been sent by the FMGC (through the MCDU) or the CDU. (Ref. para. D - IR output data for the complete list of valid outputs). (4) Hybrid partition The hybrid filter function of this partition utilizes an 18 state Kalman filter using MMR pseudo-range measurements, Air Data altitude measurements, and inertial sensor data inputs to provide the hybrid navigation solution. To assure integrity of the hybrid navigation solution, the GPS partition executes a Receiver Autonomous Integrity Monitor (RAIM) algorithm. In addition to determining the validity of the solution, the RAIM function also performs satellite failure detection and isolation so erroneous satellite measurements can be removed from the navigation solution. The integrity limit for the hybrid solution is computed from either the MMR autonomous or integrity monitor based data and provided as output. In contrast to the hybrid solution, the autonomous solution is provided by each MMR via the GPS ARINC input buses. The autonomous data from one MMR is then relayed and retransmitted on the output buses. Also, predictive RAIM labels can be received from the MMR, and relayed to the output fonctions for retransmission.

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The GPS partition remains operating in the Navigation mode unless the hybrid filter must be restarted or less than 4 unique satellites are being used by the filter - the hybrid filter is restarted if the IR partition transitions to a mode other than NAV after transitioning to NAV, and also if True Heading or position data from the IR partition becomes invalid prior to the IR partition transitioning to NAV. This restart condition will then initiate a transition back to the Acquisition mode of operation. Also when less than 4 satellites are being used by the filter, the GPS partition transitions to the Altitude Aiding/Clock Coasting mode. However the software performs the same operational tasks as performed in the GPS Navigation mode, except for the mode indication in the GPIRS status word of the outputs. It remains in this mode until four or more satellite measurements are received again when its transitioned back to the Navigation mode. **ON A/C 313-399, (3) Attitude mode The attitude mode is a reversionary mode that can be activated only by manual selection of the ATT mode on the MSU. The mode can be activated on the ground or in flight and is intended to provide a rapid attitude/heading restart capability if the IR has experienced total power shutdown or failures which do not disable the mechanization of the attitude computation. The necessity of selecting ATT is indicated by the IR in its action code (label 350 - code 04 = select ATT) and this data is used by the FWC to display a message on the ECAM displays. This mode needs a 20-second initialization phase with the aircraft in level flight. During this phase, all the ARINC bus outputs are sent with their status matrix coded NCD (No Computed Data). At the end of the initialization phase, the IR sends valid outputs of: - body axis accelerations and angular rates - pitch and roll attitude and rate - vertical acceleration - vertical velocity - baro-inertial altitude and vertical speed (Ref. para. D - IR output data, list of valid labels). The magnetic heading may also be valid if an initialization value has been sent by the FMGC (through the MCDU) (Ref. para. D - IR output data for the complete list of valid outputs).

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(4) Hybrid partition The hybrid filter function of this partition uses an 18-state Kalman filter using MMR pseudo-range measurements, Air Data altitude measurements, and inertial sensor data inputs to provide the hybrid navigation solution. To assure integrity of the hybrid navigation solution, the GPS partition executes a Receiver Autonomous Integrity Monitor (RAIM) algorithm. In addition to determining the validity of the solution, the RAIM function also performs satellite failure detection and isolation so erroneous satellite measurements can be removed from the navigation solution. The integrity limit for the hybrid solution is computed from either the MMR autonomous or integrity monitor based data and provided as output. In contrast to the hybrid solution, the autonomous solution is provided by each MMR via the GPS ARINC input buses. The autonomous data from one MMR is then relayed and retransmitted on the output buses. Also, predictive RAIM labels can be received from the MMR, and relayed to the output functions for retransmission. The GPS partition remains operating in the Navigation mode unless the hybrid filter must be restarted or less than four unique satellites are being used by the filter - the hybrid filter is restarted if the IR partition transitions to a mode other than NAV after transitioning to NAV, and also if True Heading or position data from the IR partition becomes invalid prior to the IR partition transitioning to NAV. This restart condition will then initiate a transition back to the Acquisition mode of operation. Also when less than four satellites are being used by the filter, the GPS partition transitions to the Altitude Aiding/Clock Coasting mode. However, the software performs the same operational tasks as performed in the GPS Navigation mode, except for the mode indication in the GPIRS status word of the outputs. It remains in this mode until four or more satellite measurements are received again when its transitioned back to the Navigation mode. R R

**ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, D. IR Output Data (1) Digital output characteristics The IRs have 4 independently buffered high-speed ARINC 429 digital output buses, designated bus output 1, 2, 3 and 4 - digital output table: This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI : (SDAC, FWC, DMC...) output label for which the parameter is available

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- PARAMETER DEFINITION: parameter name - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT : unit in which the digital value is transmitted - SIG BIT : indicates whether a sign bit is available - BITS : number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds. - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code. - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. When the input discretes of THE GPS PRESENT programming pins are grounded (indicating GPS present), both the GPSSU outputs and the GPIRS integrated navigation solution outputs are transmitted on the IR output buses with the IR output data.

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 010 |PPOS LAT |W |Deg | | 6 |500 |BCD |LATP | | | | |90S-90N |& | | | | | | | | | |0.1 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 011 |PPOS LONG |W |Deg | | 6 |500 |BCD | | | | | |180E-180W |& | | | | | | | | | |0.1 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 012 |GROUND |W 0 to 2000 |Kts | | 4 |500 |BCD | GS | | | |SPEED |0 to 1000 | | | | | | | | | | |R 1 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 013 |TRK ANGLE |W 0 to 359.9|Deg | | 4 |500 |BCD | | | | |TRUE |R 0.1 | | | | | | | | | | |+/- 2.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 014 |MAG HDG |W 0 to 359.9|Deg | | 4 |500 |BCD | MH | | | | |R 0.1 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 015 |WIND SPEED|W 0 to 256 |Kts | | 3 |500 |BCD | WS | | | | |R 1 | | | | | | | | | | |+/- 9 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 016 |WIND DIR |W 0 to 359 |Deg | | 3 |500 |BCD | WD | | | |TRUE |R 1 | | | | | | | | | | |+/- 10 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 041 |SET LAT |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |90S-90N |& | | | | | | | | | |R 0.1 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 042 |SET LONG |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |R 0.1 |& | | | | | | | | | | |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 043 |SET MAG |W 0 to 359.9|Deg | | 4 |500 |BCD | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |HDG |R 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 044 |TRUE HDG |W 0 to 359.9|Deg | | 4 |500 |BCD |THDG | | | | |R 0.1 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 052 |PITCH |W +/- 64 |Deg/| | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 053 |ROLL |W +/- 64 |Deg/| | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 054 |YAW |W +/- 64 |Deg/| | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 310 |PPOS LAT |W +/- 180 |Deg | 29 | 20 |200 |BNR | | | | | |+/- 90 |& | | | | | | | | | |R 0.00017 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 311 |PPOS LONG |W +/- 180 |Deg | 29 | 20 |200 |BNR |LONP | | | | |R 0.00017 |& | | | | | | | | | | |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 312 |GROUND |W 0 to 4096 |Kts | | 15 | 40 |BNR | | | | |SPEED |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 313 |TRK - TRUE|W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.23 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 314 |TRUE HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 315 |WIND |W 0 to 256 |Kts | | 15 |100 |BNR | | | | |SPEED |0 to 100 | | | | | | | | | | |R 0.0078 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 316 |WIND DIR |W +/- 180 |Deg | 29 | 15 |100 |BNR | | | | |- TRUE |+/- 180 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 10 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 317 |TRK - MAG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 320 |MAG HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |82 N to 60 S| | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 321 |DRIFT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | DA | | | |ANGLE |+/- 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 2.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 322 |FLIGHT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | FPA | | | |PATH |+/- 90 | | | | | | | | | |ANGLE |R 0.0055 | | | | | | | | | | |+/- 0.28 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 323 |FLT PATH |W +/- 4 | g | 29 | 15 | 20 |BNR |FPAC | | | |ACCEL |R 0.0001 | | | | | | | | | | |+/- 10 % of | | | | | | | | | | |outp | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 324 |PITCH |W +/- 180 |Deg | 29 | 15 | 20 |BNR |PTCH | | | |ANGLE |-90 to + 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.05 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 325 |ROLL |W +/- 180 |Deg | 29 | 15 | 20 |BNR |ROLL | | | |ANGLE |-90 to + 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.05 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 326 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |PTCR | | | |PITCH RATE|+/- 45 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 327 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |ROLR | | | |ROLL RATE |+/- 45 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 330 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |YAW | | | |YAW RATE |+/- 45 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 331 |BODY LONG |W +/- 4 | g | 29 | 15 | 20 |BNR |LONG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 332 |BODY LAT |W +/- 4 | g | 29 | 15 | 20 |BNR |LATG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 333 |BODY NORM |W +/- 4 | g | 29 | 15 | 20 |BNR |VRTG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 334 |PLATFORM |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |HEADING |R 0.0055 | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |+/- 0.23 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 335 |TRK ANGLE |W +/- 32 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.001 |s | | | | | | | | | |+/- 0.17 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 336 |PITCH ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.0039 |s | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 337 |ROLL ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.0039 |s | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 340 |TRACK |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |ANGLE |R 0.0055 | | | | | | | | | |GRID |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 341 |GRID |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |HEADING |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 360 |POTENTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR | | | | |V/S |R 1.0 | min| | | | | | | | | |+/- 30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 361 |INERTIAL |W +/- 131072|ft | 29 | 20 | 40 |BNR | | | | |ALT |R 0.125 | | | | | | | | | | |+/- 5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 362 |ALONG TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | | | |HORIZ |R 0.00012 | | | | | | | | | |ACCEL |+/- 10 % | | | | | | | | | | |of outp | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 363 |CROSS TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | | | |HORIZ |R 0.00012 | | | | | | | | | |ACCEL |+/- 10 % | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |of outp | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 364 |VERTICAL |W +/- 4 | g | 29 | 15 | 20 |BNR |VACC | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.00012 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 365 |INERTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR |IVV | | | |V/S |R 1.0 |min | | | | | | | | | |+/- 30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 366 |N - S |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 367 |E - W |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 275 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 276 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 277 |IRS TEST | | | | |500 |HYB | | | | |WORD | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 350 |ACTION | | | | |500 |HYB | | | | |CODE | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 351 |IR MAINT | | | | |500 |DIS | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 354 |LRU IDENT | | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 356 |FAULT | | | | | |ISO | | | | |STAT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQUIP | | | | |500 |HEX | | | | |IDENT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 076 |GPS ALT |W +/- 131072|ft | | 20 |666 |BNR | | | | |(MLS) |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 101 |HDOP |W 0 to 1024 | | | 15 |666 |BNR | | | | | |R 0.031 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 102 |VDOP |W 0 to 1024 | | | 15 |666 |BNR | | | | | |R 0.031 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 103 |GPS TRACK |W +/- 180 |DEG | | 15 |666 |BNR | | | | |ANGLE TRUE|R 0.0055 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 110 |GPS PRES |W +/- 90 |DEG | | 20 |666 |BNR | | | | |POS-LAT |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 111 |GPS PRES |W +/- 180 |DEG | | 20 |666 |BNR | | | | |POS-LONG |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 112 |GPS GROUND|W 0 to 4096 |KTS | | 15 |666 |BNR | | | | |SPEED |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 120 |GPS PRES |W +/|DEG | | 11 |666 |BNR | | | | |POS-LAT |0.000172 | | | | | | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 121 |GPS PRES |W +/|DEG | | 11 |666 |BNR | | | | |POS-LONG |0.000172 | | | | | | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 125 |GPS UTC |W 23:59.9 |H/ | | 5 |666 |BCD | | | | | |R 0.1 min |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 130 |GPS INTEG |W 0 to 16 |NM | | 18 |666 |BNR | | | | |LIMIT |R 1.2 E-4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 131 |HYB INTEG |W 0 to 16 |NM | | 18 |666 |BNR | | | | |LIMIT |R 6.1 E-5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 132 |HYB TRUE |W +/- 180 |DEG | | 15 | 40|BNR | | | | |HEADING |R 0.0055 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 135 |HYB VERT |W 0 to 32768|ft | | 18 |666 |BNR | | | | |FOM |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 136 |GPS VERT |W 0 to 32768|ft | | 18 |666 |BNR | | | | |FOM |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 137 |HYB TRACK |W +/- 180 |DEG | | 15 | 40|BNR | | | | |ANGLE TRUE|R 0.0055 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 143 |TERMINAL |W 0 to 16 |NM | | 17 |666 |BNR | | | | |AREA HIL |R 1.22 E-4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 150 |GPS UTC |W 23:59:59 |H:M | | 17 |666 |BNR | | | | | |R 1.0 |:S | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 162 |DESTINA- |W 23:59 |H:M | | 11 |333 |BNR | | | | |TION ETA |R 1 |M | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 163 |ALT |W 23:59 |H:M | | 11 |333 |BNR | | | | |WAYPOINT |R 1 |M | | | | | | | | |ETA | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 165 |GPS VERT |W +/- 32768 |ft/ | | 15 |666 |BNR | | | | |SPEED |R 1.0 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 166 |GPS N/S |W +/- 4096 |kts | | 15 |666 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 174 |GPS E/W |W +/- 4096 |kts | | 15 |666 |BNR | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 175 |HYB GROUND|W 0 TO 4096 |kts | | 15 | 40|BNR | | | | |SPEED |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 247 |GPS HORIZ |W 0 TO 16 |NM | | 18 |666 |BNR | | | | |FOM |R 6.1 E-5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 254 |HYB LAT |W +/- 90 |DEG | | 20 |80 |BNR | | | | | |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 255 |HYB LONG |W +/- 180 |DEG | | 20 |80 |BNR | | | | | |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 256 |HYB LAT |W 0.000172 |DEG | | 11 |80 |BNR | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 257 |HYB LONG |W 0.000172 |DEG | | 11 |80 |BNR | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 260 |GPS DATE |W 31:12:99 |D:M | | 6 |666 |BCD | | | | | |R 1 |:D | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 261 |HYB ALT |W +/- 131072|ft | | 20 | 40|BNR | | | | |(MSL) |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 263 |HYB FLIGHT|W +/- 90 |DEG | | 12 | 40|BNR | | | | |PATH ANGLE|R 0.044 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 264 |HYB HORIZ |W 0 to 16 |NM | | 18 |666 |BNR | | | | |FOM |R 6.1 E-S | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 266 |HYB N/S |W 0 TO 4096 |kts | | 15 |80 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 267 |HYB E/W |W 0 TO 4096 |kts | | 15 |80 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 273 |GPS SENSOR| N/A | | | |666 |DIS | | | | |STATUS | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 274 |GPIRS | | | | |666 |DIS | | | | |SENSOR | N/A | | | | | | | | | |STATUS | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 343 |DESTINA- |W 0 to 16 |NM | | 13 |333 |BNR | | | | |TION HIL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 345 |HYB VERT |W +/- 32768 |ft/ | | 15 | 40|BNR | | | | |VELOCITY |R 1.0 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 347 |ALT |W 0 to 16 |NM | | 13 | 333|BNR | | | | |WAYPOINT | | | | | | | | | | |HIL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 352 |GPSSU RCVR| N/A | | | |666 |DIS | | | | |MAINT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 353 |GPIRS | N/A | | | |666 |DIS | | | | |MAINT WORD| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 355 |GPSSU NAV | N/A | | | |666 |DIS | | | | |MAINT | | | | | | | | | ------------------------------------------------------------------------------Table 7A :IR Digital Output Characteristics

  R EFF : 051-057, 059-060, 062-099, 106-149,  34-14-00 Page 53 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Nov 01/09 236-238, 301-304, CES

 

R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-523, D. IR, GPS, and GPIRS Output Data (1) Digital output characteristics The IRs have 4 independently buffered high-speed ARINC 429 digital output buses, designated bus output 1, 2, 3 and 4 - digital output table: This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI : (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT : unit in which the digital value is transmitted - SIG BIT : indicates whether a sign bit is available - BITS : number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds. - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code. - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. When the input discretes of THE GPS PRESENT programming pins are grounded (indicating GPS present), both the MMR outputs and the GPIRS integrated navigation solution outputs are transmitted on the IR output buses with the IR output data.

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 54 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 010 |PPOS LAT |W |Deg | | 6 |500 |BCD |LATP | | | | |90S-90N |& | | | | | | | | | |0.1 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 011 |PPOS LONG |W |Deg | | 6 |500 |BCD | | | | | |180E-180W |& | | | | | | | | | |0.1 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 012 |GROUND |W 0 to 2000 |Kts | | 4 |500 |BCD | GS | | | |SPEED |0 to 1000 | | | | | | | | | | |R 1 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 013 |TRK ANGLE |W 0 to 359.9|Deg | | 4 |500 |BCD | | | | |TRUE |R 0.1 | | | | | | | | | | |+/- 2.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 014 |MAG HDG |W 0 to 359.9|Deg | | 4 |500 |BCD | MH | | | | |R 0.1 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 015 |WIND SPEED|W 0 to 256 |Kts | | 3 |500 |BCD | WS | | | | |R 1 | | | | | | | | | | |+/- 9 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 016 |WIND DIR |W 0 to 359 |Deg | | 3 |500 |BCD | WD | | | |TRUE |R 1 | | | | | | | | | | |+/- 10 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 041 |SET LAT |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |90S-90N |& | | | | | | | | | |R 0.1 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 042 |SET LONG |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |R 0.1 |& | | | | | | | | | | |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 043 |SET MAG |W 0 to 359.9|Deg | | 4 |500 |BCD | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |HDG |R 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 044 |TRUE HDG |W 0 to 359.9|Deg | | 4 |500 |BCD |THDG | | | | |R 0.1 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 052 |PITCH |W +/- 64 |Deg/| | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 053 |ROLL |W +/- 64 |Deg/| | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 054 |YAW |W +/- 64 |Deg/| | 15 | 20 |BNR | | | | |ANGULAR |R 0.002 |sec2| | | | | | | | |ACCEL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 310 |PPOS LAT |W +/- 180 |Deg | 29 | 20 |200 |BNR | | | | | |+/- 90 |& | | | | | | | | | |R 0.00017 |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 311 |PPOS LONG |W +/- 180 |Deg | 29 | 20 |200 |BNR |LONP | | | | |R 0.00017 |& | | | | | | | | | | |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 312 |GROUND |W 0 to 4096 |Kts | | 15 | 40 |BNR | | | | |SPEED |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 313 |TRK - TRUE|W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.23 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 314 |TRUE HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 315 |WIND |W 0 to 256 |Kts | | 15 |100 |BNR | | | | |SPEED |0 to 100 | | | | | | | | | | |R 0.0078 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 316 |WIND DIR |W +/- 180 |Deg | 29 | 15 |100 |BNR | | | | |- TRUE |+/- 180 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 10 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 317 |TRK - MAG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 320 |MAG HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | | |82 N to 60 S| | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 321 |DRIFT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | DA | | | |ANGLE |+/- 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 2.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 322 |FLIGHT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | FPA | | | |PATH |+/- 90 | | | | | | | | | |ANGLE |R 0.0055 | | | | | | | | | | |+/- 0.28 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 323 |FLT PATH |W +/- 4 | g | 29 | 15 | 20 |BNR |FPAC | | | |ACCEL |R 0.0001 | | | | | | | | | | |+/- 10 % of | | | | | | | | | | |outp | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 324 |PITCH |W +/- 180 |Deg | 29 | 15 | 20 |BNR |PTCH | | | |ANGLE |-90 to + 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.05 | | | | | | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 57 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | 325 |ROLL |W +/- 180 |Deg | 29 | 15 | 20 |BNR |ROLL | | | |ANGLE |-90 to + 90 | | | | | | | | | | |R 0.0055 | | | | | | | | | | |+/- 0.05 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 326 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |PTCR | | | |PITCH RATE|+/- 45 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 327 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |ROLR | | | |ROLL RATE |+/- 45 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 330 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |YAW | | | |YAW RATE |+/- 45 |s | | | | | | | | | |R 0.0039 | | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 331 |BODY LONG |W +/- 4 | g | 29 | 15 | 20 |BNR |LONG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 332 |BODY LAT |W +/- 4 | g | 29 | 15 | 20 |BNR |LATG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 333 |BODY NORM |W +/- 4 | g | 29 | 15 | 20 |BNR |VRTG | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.0001 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 334 |PLATFORM |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |HEADING |R 0.0055 | | | | | | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 58 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |+/- 0.23 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 335 |TRK ANGLE |W +/- 32 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.001 |s | | | | | | | | | |+/- 0.17 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 336 |PITCH ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.0039 |s | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 337 |ROLL ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0.0039 |s | | | | | | | | | |+/- 0.1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 340 |TRACK |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |ANGLE |R 0.0055 | | | | | | | | | |GRID |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 341 |GRID |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | | | |HEADING |R 0.0055 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 360 |POTENTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR | | | | |V/S |R 1.0 | min| | | | | | | | | |+/- 30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 361 |INERTIAL |W +/- 131072|ft | 29 | 20 | 40 |BNR | | | | |ALT |R 0.125 | | | | | | | | | | |+/- 5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 362 |ALONG TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | | | |HORIZ |R 0.00012 | | | | | | | | | |ACCEL |+/- 10 % | | | | | | | | | | |of outp | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 363 |CROSS TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | | | |HORIZ |R 0.00012 | | | | | | | | | |ACCEL |+/- 10 % | | | | | | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 59 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |of outp | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 364 |VERTICAL |W +/- 4 | g | 29 | 15 | 20 |BNR |VACC | | | |ACCEL |+/- 4.000 | | | | | | | | | | |R 0.00012 | | | | | | | | | | |+/- 0.01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 365 |INERTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR |IVV | | | |V/S |R 1.0 |min | | | | | | | | | |+/- 30 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 366 |N - S |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 367 |E - W |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 275 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 276 |DSCRT DATA| | | | |500 |DIS | | | | |WORD 3 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 277 |IRS TEST | | | | |500 |HYB | | | | |WORD | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 350 |ACTION | | | | |500 |HYB | | | | |CODE | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 351 |IR MAINT | | | | |500 |DIS | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 354 |LRU IDENT | | | | | |ISO | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 60 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 356 |FAULT | | | | | |ISO | | | | |STAT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 377 |EQUIP | | | | |500 |HEX | | | | |IDENT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 242 |BODY PITCH|W +/-128 |Deg/| 29 | 15 | 20 |BNR |PTCR | | | |RATE |+/-128 |s | | | | | | | | |(unfiltrd)|R 0,0039 | | | | | | | | | | |+/- 0,1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 342 |BODY ROLL |W +/-128 |Deg/| 29 | 15 | 20 |BNR |ROLR | | | |RATE |+/-45 |s | | | | | | | | |(unfiltrd)|R 0,0039 | | | | | | | | | | |+/- 0,1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 344 |BODY YAW |W +/-128 |Deg/| 29 | 15 | 20 |BNR | YAW | | | |RATE |+/- 45 |s | | | | | | | | |(unfiltrd)|R 0,0039 | | | | | | | | | | |+/- 0,1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 346 |PITCH ATT |W +/-128 |Deg/| 29 | 15 | 20 |BNR | | | | |RATE |R 0,0039 |s | | | | | | | | |(unfiltrd)|+/- 0,1 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 173 |PITCH |W +/-180 |Deg | 29 | 15 | 20 |BNR |PITCH| | | |ANGLE |-90 to +90 | | | | | | | | | |(unfiltrd)|R 0,0055 | | | | | | | | | | |+/- 0,05 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 202 |ROLL |W +/-180 |Deg | 29 | 15 | 20 |BNR |ROLL | | | |ANGLE |-90 to +90 | | | | | | | | | |(unfiltrd)|R 0,0055 | | | | | | | | | | |+/- 0,05 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 372 |BODY LONG |W +/- 4 | g | 29 | 15 | 20 |BNR |LONG | | | |ACCEL |+/- 4,000 | | | | | | | | | |(unfiltrd)|R 0,0001 | | | | | | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 61 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | |+/- 0,01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 373 |BODY LAT |W +/- 4 | g | 29 | 15 | 20 |BNR |LATG | | | |ACCEL |+/- 4,000 | | | | | | | | | |(unfiltrd)|R 0,0001 | | | | | | | | | | |+/- 0,01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 374 |BODY NORM |W +/- 4 | g | 29 | 15 | 20 |BNR |VRTG | | | |ACCEL |+/- 4,000 | | | | | | | | | |(unfiltrd)|R 0,0001 | | | | | | | | | | |+/- 0,01 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 076 |GPS ALT |W +/- 131072|ft | | 20 |666 |BNR | | | | |(MLS) |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 101 |HDOP |W 0 to 1024 | | | 15 |666 |BNR | | | | | |R 0.031 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 102 |VDOP |W 0 to 1024 | | | 15 |666 |BNR | | | | | |R 0.031 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 103 |GPS TRACK |W +/- 180 |DEG | | 15 |666 |BNR | | | | |ANGLE TRUE|R 0.0055 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 110 |GPS PRES |W +/- 90 |DEG | | 20 |666 |BNR | | | | |POS-LAT |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 111 |GPS PRES |W +/- 180 |DEG | | 20 |666 |BNR | | | | |POS-LONG |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 112 |GPS GROUND|W 0 to 4096 |KTS | | 15 |666 |BNR | | | | |SPEED |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 120 |GPS PRES |W +/|DEG | | 11 |666 |BNR | | | | |POS-LAT |0.000172 | | | | | | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 121 |GPS PRES |W +/|DEG | | 11 |666 |BNR | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 62 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |POS-LONG |0.000172 | | | | | | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 125 |GPS UTC |W 23:59.9 |H/ | | 5 |666 |BCD | | | | | |R 0.1 min |min | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 130 |GPS INTEG |W 0 to 16 |NM | | 18 |666 |BNR | | | | |LIMIT |R 1.2 E-4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 131 |HYB INTEG |W 0 to 16 |NM | | 18 |666 |BNR | | | | |LIMIT |R 6.1 E-5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 132 |HYB TRUE |W +/- 180 |DEG | | 15 | 40|BNR | | | | |HEADING |R 0.0055 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 135 |HYB VERT |W 0 to 32768|ft | | 18 |666 |BNR | | | | |FOM |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 136 |GPS VERT |W 0 to 32768|ft | | 18 |666 |BNR | | | | |FOM |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 137 |HYB TRACK |W +/- 180 |DEG | | 15 | 40|BNR | | | | |ANGLE TRUE|R 0.0055 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 143 |TERMINAL |W 0 to 16 |NM | | 17 |666 |BNR | | | | |AREA HIL |R 1.22 E-4 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 150 |GPS UTC |W 23:59:59 |H:M | | 17 |666 |BNR | | | | | |R 1.0 |:S | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 162 |DESTINA- |W 23:59 |H:M | | 11 |333 |BNR | | | | |TION ETA |R 1 |M | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 163 |ALT |W 23:59 |H:M | | 11 |333 |BNR | | | | |WAYPOINT |R 1 |M | | | | | | | | |ETA | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 165 |GPS VERT |W +/- 32768 |ft/ | | 15 |666 |BNR | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 63 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |SPEED |R 1.0 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 166 |GPS N/S |W +/- 4096 |kts | | 15 |666 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 174 |GPS E/W |W +/- 4096 |kts | | 15 |666 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 175 |HYB GROUND|W 0 TO 4096 |kts | | 15 | 40|BNR | | | | |SPEED |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 247 |GPS HORIZ |W 0 TO 16 |NM | | 18 |666 |BNR | | | | |FOM |R 6.1 E-5 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 254 |HYB LAT |W +/- 90 |DEG | | 20 |80 |BNR | | | | | |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 255 |HYB LONG |W +/- 180 |DEG | | 20 |80 |BNR | | | | | |R 0.000172 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 256 |HYB LAT |W 0.000172 |DEG | | 11 |80 |BNR | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 257 |HYB LONG |W 0.000172 |DEG | | 11 |80 |BNR | | | | |FINE |R 8.38 E-8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 260 |GPS DATE |W 31:12:99 |D:M | | 6 |666 |BCD | | | | | |R 1 |:D | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 261 |HYB ALT |W +/- 131072|ft | | 20 | 40|BNR | | | | |(MSL) |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 263 |HYB FLIGHT|W +/- 90 |DEG | | 12 | 40|BNR | | | | |PATH ANGLE|R 0.044 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 264 |HYB HORIZ |W 0 to 16 |NM | | 18 |666 |BNR | | | | |FOM |R 6.1 E-S | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------|

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 64 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 266 |HYB N/S |W 0 TO 4096 |kts | | 15 |80 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 267 |HYB E/W |W 0 TO 4096 |kts | | 15 |80 |BNR | | | | |VELOCITY |R 0.125 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 273 |GPS SENSOR| N/A | | | |666 |DIS | | | | |STATUS | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 274 |GPIRS | | | | |666 |DIS | | | | |SENSOR | N/A | | | | | | | | | |STATUS | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 343 |DESTINA- |W 0 to 16 |NM | | 13 |333 |BNR | | | | |TION HIL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 345 |HYB VERT |W +/- 32768 |ft/ | | 15 | 40|BNR | | | | |VELOCITY |R 1.0 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 347 |ALT |W 0 to 16 |NM | | 13 | 333|BNR | | | | |WAYPOINT | | | | | | | | | | |HIL | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 352 |GPSSU RCVR| N/A | | | |666 |DIS | | | | |MAINT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 353 |GPIRS | N/A | | | |666 |DIS | | | | |MAINT WORD| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 355 |GPSSU NAV | N/A | | | |666 |DIS | | | | |MAINT | | | | | | | | | ------------------------------------------------------------------------------Table 7A :IR Digital Output Characteristics

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 65 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

R R

**ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-399, 401-499, ---------------------------------------------------------------------------| BIT | SIGNAL | 1 CONDITION | |-----|--------------------|-----------------------------------------------| | 1 | 1 | | | 2 | 0 | | | | 3 | 1 | | | | 4 | 1 | LABEL 270 | | | 5 | 1 | | | | 6 | 0 | | | | 7 | 0 | | | | 8 | 0 | | | 9 | SDI - LSB | | | 10 | SDI - MSB | | | 11 | Alignment Not Ready| In Align Submode | | 12 | Rev Att Mode | In Attitude Mode | | 13 | Nav Mode | In Nav Mode | | 14 | Valid Set Heading | A valid set heading has to be input to the | | | | IR. Magnetic heading outputs are no longer | | | | being computed, but have the characteristics | | | | of a Free Direction Gyro. | | 15 | Attitude Invalid | Attitude Critical Fault | | 16 | DC Fail | DC Power Less Than 18V | | 17 | On DC | On DC Power | | 18 | ADR Fault | The IR has detected an ADR input (TAS, ALT | | | | and ALT RATE) as FW or NCD. Note functional | | | | test data is ignored by the IR and last valid | | | | input is used. | | 19 | IR Failure | Navigation (Non Critical) Fault | | 20 | DC Fail - On DC | The IR has detected that a DC fail occurred | | | | while on DC from last turn on. | | 21 | Align Fault | The IR has detected a position miscompare | | | | or a Quality of Align fault. | | 22 | No IR Initial | IR does not have position data or data | | | | received is invalid. | | 23 | Excess Motion Error| X or Y velocity greater than 0.011 ft/s | | | | during align. | | 24 | ADR/IR Fault | No data has been received from the ADR or | | | | was received with a parity error. | | 25 | Extreme Latitude | Latitude exceeds 73⁰N (+/-0.5⁰ hysteresis) | | | | or Latitude exceeds 60⁰S (+/-0.5⁰ hysteresis).| | | | Magnetic Deviation is set to zero. | | 26 | Align Time Status | Bits 28 27 26 Time Until Nav | | 27 | | 1 1 1 7 - 10 minutes | | 28 | | 1 1 0 6 minutes |

  R EFF : 051-057, 059-060, 062-099, 106-149,  34-14-00 Page 66 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Nov 01/09 236-238, 301-399, 401-499, CES

 

---------------------------------------------------------------------------| BIT | SIGNAL | 1 CONDITION | |-----|--------------------|-----------------------------------------------| | | | 1 0 1 5 minutes | | | | 1 0 0 4 minutes | | | | 0 1 1 3 minutes | | | | 0 1 0 2 minutes | | | | 0 0 1 1 minute | | | | 0 0 0 IN NAV MODE ONLY | | 29 | COMPUT LAT MISCOMP | SIN/COS OF LATITUDE TEST FAILED | | 30 | SSM | | | 31 | SSM | | | 32 | Parity | | ---------------------------------------------------------------------------Digital Word 270 (IR Discretes) (Ref. Fig. 006, 007, 008)

  R EFF : 051-057, 059-060, 062-099, 106-149,  34-14-00 Page 67 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Nov 01/09 236-238, 301-399, 401-499, CES

 

Digital Word 275 IR Discrete 2 Figure 006   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page 68 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

Digital Word 276 IR Discrete 3 Figure 007   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page 69 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

Digital Word 351 IR Maintenance Figure 008   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page 70 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

R R

**ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 501-509, 511-523, ---------------------------------------------------------------------------| BIT | SIGNAL | 1 CONDITION | |-----|--------------------|-----------------------------------------------| | 1 | 1 | | | 2 | 0 | | | | 3 | 1 | | | | 4 | 1 | LABEL 270 | | | 5 | 1 | | | | 6 | 0 | | | | 7 | 0 | | | | 8 | 0 | | | 9 | SDI - LSB | | | 10 | SDI - MSB | | | 11 | Alignment Not Ready| In Align Submode | | 12 | Rev Att Mode | In Attitude Mode | | 13 | Nav Mode | In Nav Mode | | 14 | Valid Set Heading | A valid set heading has to be input to the | | | | IR. Magnetic heading outputs are no longer | | | | being computed, but have the characteristics | | | | of a Free Direction Gyro. | | 15 | Attitude Invalid | Attitude Critical Fault | | 16 | DC Fail | DC Power Less Than 18V | | 17 | On DC | On DC Power | | 18 | ADR Fault | The IR has detected an ADR input (TAS, ALT | | | | and ALT RATE) as FW or NCD. Note functional | | | | test data is ignored by the IR and last valid | | | | input is used. | | 19 | IR Failure | Navigation (Non Critical) Fault | | 20 | DC Fail - On DC | The IR has detected that a DC fail occurred | | | | while on DC from last turn on. | | 21 | Align Fault | The IR has detected a position miscompare | | | | or a Quality of Align fault. | | 22 | No IR Initial | IR does not have position data or data | | | | received is invalid. | | 23 | Excess Motion Error| X or Y velocity greater than 0.011 ft/s | | | | during align. | | 24 | ADR/IR Fault | No data has been received from the ADR or | | | | was received with a parity error. | | 25 | Extreme Latitude | Latitude exceeds 73⁰N (+/-0.5⁰ hysteresis) | | | | while Longitude is between 120⁰W and 90⁰W | | | | (+/-2.5⁰ hysteresis) or Latitude exceeds | | | | 82⁰N (+/-0.5⁰ hysteresis) or Latitude | | | | exceeds 60⁰S (+/-0.5⁰ hysteresis). | | | | Magnetic Deviation is set to zero. | | 26 | Align Time Status | Bits 28 27 26 Time Until Nav | | 27 | | 1 1 1 7 - 10 minutes | | 28 | | 1 1 0 6 minutes | | | | 1 0 1 5 minutes | | | | 1 0 0 4 minutes |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 71 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 501-509, 511-523, CES

 

---------------------------------------------------------------------------| BIT | SIGNAL | 1 CONDITION | |-----|--------------------|-----------------------------------------------| | | | 0 1 1 3 minutes | | | | 0 1 0 2 minutes | | | | 0 0 1 1 minute | | | | 0 0 0 IN NAV MODE ONLY | | 29 | COMPUT LAT MISCOMP | SIN/COS OF LATITUDE TEST FAILED | | 30 | SSM | | | 31 | SSM | | | 32 | Parity | | ---------------------------------------------------------------------------Digital Word 270 (IR Discretes) (Ref. Fig. 006, 007, 008) **ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-239, (Ref. Fig. 009A) R

**ON A/C 240-249, 251-299, 501-509, 511-523, (Ref. Fig. 009B)

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 72 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 501-509, 511-523, CES

 

IR - BCD and Special Output Words Figure 009   R EFF : 051-057, 059-060, 062-099, 106-149,  34-14-00 Page 73 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Nov 01/09 236-238, 301-312, 401-499, CES

 

IR - BCD and Special Output Words Figure 009A   R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 74 220-220, 226-226, 234-235, 239-239,  Config-3 Nov 01/09  CES

 

IR - BCD and Special Output Words Figure 009B   R EFF : 240-249, 251-299, 501-509, 511-523,  34-14-00 Page 75   Config-3 Feb 01/10  CES

 

INTENTIONALLY BLANK

  R   34-14-00 Page 76   Config-3 Nov 01/09  CES

 

INTENTIONALLY BLANK

  R   34-14-00 Page 77   Config-3 Nov 01/09  CES

 

INTENTIONALLY BLANK

  R   34-14-00 Page 78   Config-3 Feb 01/10  CES

 

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, The data field of the test word 277 (21 bits) alternates between the four first patterns shown in the following table below, except during the REALIGN DECISION submode and the POWER OFF submode. During these submodes the data field shall be as shown in pattern 5. ---------------------------------------------------------------------------| BIT | DEFINITION | |--------------------------------------------------------------------------| | 1 | 1 | | 2 | 0 | | | 3 | 1 | | | 4 | 1 | LABEL 277 | | 5 | 1 | | | 6 | 1 | | | 7 | 1 | | | 8 | 1 | |--------------------------------------------------------------------------| | 9 | SDI | | 10 | SDI | |---------|----------------------------------------------------------------| | |PATTERN 1 |PATTERN 2|PATTERN 3|PATTERN 4| PATTERN 5 | |---------|----------|---------|---------|---------|-----------------------| | 11 | 0 | 0 | 1 | 1 | BCD MODE TIMER | | 12 | 1 | 1 | 0 | 0 | (LSD) | | 13 | 0 | 1 | 1 | 0 | (REALIGN AND | | 14 | 1 | 1 | 0 | 0 | POWER OFF) | |---------|----------|---------|---------|---------------------------------| | 15 | 0 | 0 | 1 | 1 | BCD MODE TIMER | | 16 | 1 | 1 | 0 | 0 | (MSD) | | 17 | 0 | 1 | 1 | 0 | (REALIGN AND | | 18 | 1 | 1 | 0 | 0 | POWER OFF) | |---------|----------|---------|---------|---------------------------------| | | | | | | MODE FLAG: | | 19 | 0 | 0 | 1 | 1 | 00 = PWR OFF SUBMODE | | 20 | 1 | 1 | 0 | 0 | 11 = REALIGN DECISION | | | | | | | SUBMODE | |---------|----------|---------|---------|---------|-----------------------| | 21 | 0 | 1 | 1 | 0 | 0 | | 22 | 1 | 1 | 0 | 0 | 0 | | 23 | 0 | 0 | 1 | 1 | 0 | | 24 | 1 | 1 | 0 | 0 | 0 | | 25 | 0 | 1 | 1 | 0 | 0 | | 26 | 1 | 1 | 0 | 0 | 0 | | 27 | 0 | 0 | 1 | 1 | 0 |

  EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page 79 401-499,  Config-3 Feb 01/10 R  CES

 

---------------------------------------------------------------------------| BIT | DEFINITION | |--------------------------------------------------------------------------| | 28 | 1 | 1 | 0 | 0 | 0 | | 29 | 0 | 1 | 1 | 0 | 0 | | 30 | 0 | 0 | 1 | 0 | 0 | | 31 | 0 | 0 | 1 | 1 | 0 | |---------|----------|---------|---------|---------|-----------------------| | 32 | Parity | ---------------------------------------------------------------------------Digital Word 277 (CDU Test Word) NOTE : Time (seconds) remaining in the POWER OFF submode and the time ____ (seconds) remaining in the REALIGN DECISION submode are transmitted with the BCD data (bits 11-18). ---------------------------------------------------------------------------| BIT | DEFINITION | |--------------------------------------------------------------------------| | 1 | 1 | | 2 | 1 | | | 3 | 1 | | | 4 | 0 | LABEL 350 | | 5 | 1 | | | 6 | 0 | | | 7 | 0 | | | 8 | 0 | |--------------------------------------------------------------------------| | 9 | SDI - LSB | | 10 | SDI - MSB | |--------------------------------------------------------------------------| | 11 TO 14 | SPARE | |----------|---------------------------------------------------------------| | 15 | TIME UNTIL NAV LEAST | | 16 | TIME UNTIL NAV SIGNIFICANT | | 17 | TIME UNTIL NAV DIGIT | | 18 | TIME UNTIL NAV (BCD) | |----------|---------------------------------------------------------------| | 19 | TIME UNTIL NAV MOST | | 20 | TIME UNTIL NAV SIGNIFICANT | | 21 | TIME UNTIL NAV DIGIT | | 22 | TIME UNTIL NAV (BCD) | |----------|---------------------------------------------------------------| | 23 | Action Code (1) Least | | 24 | Action Code (1) Significant | | 25 | Action Code (1) Digit | | 26 | Action Code (1) |

  EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page 80 401-499,  Config-3 Feb 01/10 R  CES

 

---------------------------------------------------------------------------| BIT | DEFINITION | |--------------------------------------------------------------------------| |----------|---------------------------------------------------------------| | 27 | Action Code (1) Most | | 28 | Action Code (1) Significant | | 29 | Action Code (1) Digit | |----------|---------------------------------------------------------------| | 30 | SSM | | 31 | SSM | | 32 | Parity | ---------------------------------------------------------------------------Digital Word 350 (Action Code) NOTE : (1) The action codes corresponding to the maintenance messages ____ are listed in the following table. --------------------------------------------------------------------------| ACTION CODE | MAINTENANCE MESSAGE | DESCRIPTION | |-------------|---------------------|-------------------------------------| | 01 | IR FAULT | Critical failure; Remove ADIRU for | | | | maintenance | | 02 | DELAYED MAINT | Non-Critical failure; Service ADIRU | | | | when convenient | | 03 | ENTER PPOS | Enter present position | | 04 | SELECT ATT | Hard failure; Select ATTITUDE MODE | | 05 | EXCESS MOTION | Excess motion detected during ALIGN | | 06 | SWITCH ADR | Air Data Reference invalid | | 07 | CHK C/B | Check circuit breakers | | 08 | CDU FAULT | Remove CDU for maintenance | | 09 | ENTER HEADING | Enter heading for ATTITUDE MODE | | 10 | | Unassigned TBD | ---------------------------------------------------------------------------Action Code - Maintenance Messages (Ref. Fig. 006, 007) **ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-312, 401-499, (Ref. Fig. 010) **ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-239, (Ref. Fig. 010A)

  R EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page 81 401-499,  Config-3 Feb 01/10  CES

 

IR - BCD and Special Output Words Figure 009C   R EFF : 313-399,  34-14-00 Page 82   Config-3 Feb 01/10  CES

 

IR - Binary Output Words Figure 010   R EFF : 051-057, 059-060, 062-099, 106-149,  34-14-00 Page 83 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Feb 01/10 236-238, 301-399, 401-499, CES

 

IR - Binary Output Words Figure 010A   R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 84 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 501-509, 511-523, CES

 

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, ------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 9 | SDI | | 10 | SDI | | 11 | MSB OF SATELLITES VISIBLE (16) | | 12 | DADS STATUS Present = 0 Not present = 1 | | 13 | DADS SOURCE Primary = 0 Secondary = 1 | | 14 | IRS/FMS STATUS Present = 0 Not present = 1 | | 15 | IRS/FMS SOURCE Primary = 0 Secondary = 1 | | 16 | | | 17 | | NUMBER OF SATELLITES VISIBLE (0-15) | | 18 | | | | 19 | | | 20 | | | 21 | | NUMBER OF SATELLITES TRACKED (0-15) | | 22 | | | | 23 | | | 24 | 00 = GPS | | | | SYSTEM DESIGNATOR 01 = GLONASS | | | | 10 = GPS GLONASS | | 25 | 11 = Spare | | 26 | | | 27 | | MMR OPERATIONAL MODE (Ref table below) | | 28 | | | 29 | MSB OF TRACKED SATELLITES | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------Discrete Word 273 Output Format ----------------------------------------------------------| MMR MODE | BIT 28 | BIT 27 | BIT 26 | ----------------------------------------------------------| SELF TEST | 0 | 0 | 0 | | INITIALIZATION | 0 | 0 | 1 | | ACQUISITION | 0 | 1 | 0 | | NAVIGATION | 0 | 1 | 1 | | ALTITUDE AIDING | 1 | 0 | 0 | | DIFFERENTIAL MODE | 1 | 0 | 1 | | DIR/SPEED AIDING MODE | 1 | 1 | 0 | | FAULT | 1 | 1 | 1 | -----------------------------------------------------------

  R EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page 85 401-499,  Config-3 Feb 01/10  CES

 

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, ---------------------------------------------------------------------------| BIT | DEFINITION | |--------------------------------------------------------------------------| | 1 | 1 | | 2 | 1 | | | 3 | 1 | | | 4 | 0 | LABEL 350 | | 5 | 1 | | | 6 | 0 | | | 7 | 0 | | | 8 | 0 | |--------------------------------------------------------------------------| | 9 | SDI - LSB | | 10 | SDI - MSB | |--------------------------------------------------------------------------| | 11 TO 14 | SPARE | |----------|---------------------------------------------------------------| | 15 | TIME UNTIL NAV LEAST | | 16 | TIME UNTIL NAV SIGNIFICANT | | 17 | TIME UNTIL NAV DIGIT | | 18 | TIME UNTIL NAV (BCD) | |----------|---------------------------------------------------------------| | 19 | TIME UNTIL NAV MOST | | 20 | TIME UNTIL NAV SIGNIFICANT | | 21 | TIME UNTIL NAV DIGIT | | 22 | TIME UNTIL NAV (BCD) | |----------|---------------------------------------------------------------| | 23 | Action Code (1) Least | | 24 | Action Code (1) Significant | | 25 | Action Code (1) Digit | | 26 | Action Code (1) | |----------|---------------------------------------------------------------| | 27 | Action Code (1) Most | | 28 | Action Code (1) Significant | | 29 | Action Code (1) Digit | |----------|---------------------------------------------------------------| | 30 | SSM | | 31 | SSM | | 32 | Parity | ---------------------------------------------------------------------------Digital Word 350 (Action Code) NOTE : (1) The action codes corresponding to the maintenance messages ____ are listed in the following table.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-14-00 Page 86 511-523,  Config-3 Feb 01/10  CES

 

--------------------------------------------------------------------------| ACTION CODE | MAINTENANCE MESSAGE | DESCRIPTION | |-------------|---------------------|-------------------------------------| | 01 | IR FAULT | Critical failure; Remove ADIRU for | | | | maintenance | | 02 | DELAYED MAINT | Non-Critical failure; Service ADIRU | | | | when convenient | | 03 | ENTER PPOS | Enter present position | | 04 | SELECT ATT | Hard failure; Select ATTITUDE MODE | | 05 | EXCESS MOTION | Excess motion detected during ALIGN | | 06 | SWITCH ADR | Air Data Reference invalid | | 07 | CHK C/B | Check circuit breakers | | 08 | MSU FAULT | Remove MSU for maintenance | | 09 | ENTER HEADING | Enter heading for ATTITUDE MODE | | 10 | | Unassigned TBD | ---------------------------------------------------------------------------Action Code - Maintenance Messages (Ref. Fig. 006, 007) **ON A/C 313-399, (Ref. Fig. 010) R

**ON A/C 240-249, 251-299, 501-509, 511-523, (Ref. Fig. 010A)

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, ------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 9 | SDI | | 10 | SDI | | 11 | MSB OF SATELLITES VISIBLE (16) | | 12 | DADS STATUS Present = 0 Not present = 1 | | 13 | DADS SOURCE Primary = 0 Secondary = 1 | | 14 | IRS/FMS STATUS Present = 0 Not present = 1 | | 15 | IRS/FMS SOURCE Primary = 0 Secondary = 1 | | 16 | | | 17 | | NUMBER OF SATELLITES VISIBLE (0-15) | | 18 | | | | 19 | |

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-14-00 Page 87 511-523,  Config-3 Feb 01/10  CES

 

------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 20 | | | 21 | | NUMBER OF SATELLITES TRACKED (0-15) | | 22 | | | | 23 | | | 24 | 00 = GPS | | | | SYSTEM DESIGNATOR 01 = GLONASS | | | | 10 = GPS GLONASS | | 25 | 11 = Spare | | 26 | | | 27 | | MMR OPERATIONAL MODE (Ref table below) | | 28 | | | 29 | MSB OF TRACKED SATELLITES | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------Discrete Word 273 Output Format ----------------------------------------------------------| MMR MODE | BIT 28 | BIT 27 | BIT 26 | ----------------------------------------------------------| SELF TEST | 0 | 0 | 0 | | INITIALIZATION | 0 | 0 | 1 | | ACQUISITION | 0 | 1 | 0 | | NAVIGATION | 0 | 1 | 1 | | ALTITUDE AIDING | 1 | 0 | 0 | | DIFFERENTIAL MODE | 1 | 0 | 1 | | DIR/SPEED AIDING MODE | 1 | 1 | 0 | | FAULT | 1 | 1 | 1 | -----------------------------------------------------------

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-14-00 Page 88 511-523,  Config-3 Feb 01/10  CES

 

**ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, ------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 9 | | | 10 | | | | 11 | | | | 12 | | SPARE | | 13 | | | | 14 | | | 15 | | | | | SECONDARY MMR VALIDITY 00 = Valid | | 16 | 01 = Inactive | | 17 | 10 = Functional Test | | | | PRIMARY MMR VALIDITY 11 = Fail | | 18 | | | 19 | MMR SOURCE Primary = 0 Secondary = 1 | | 20 | | | 21 | | NUMBER OF SATELLITES TRACKED (0-15) | | 22 | | | | 23 | | | 24 | | | | | SPARE | | 25 | | | 26 | | | 27 | | GPIRS SENSOR OPERATIONAL MODE (Ref table below) | | 28 | | | 29 | MSB OF TRACKED SATELLITES (16) | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------Discrete Word 274 Output Format ----------------------------------------------------------| GPIRS MODE | BIT 28 | BIT 27 | BIT 26 | ----------------------------------------------------------| SELF TEST | 0 | 0 | 0 | | INITIALIZATION | 0 | 0 | 1 | | ACQUISITION | 0 | 1 | 0 | | NAVIGATION | 0 | 1 | 1 | | ALTITUDE AIDING | 1 | 0 | 0 | | SPARE | 1 | 0 | 1 | | SPARE | 1 | 1 | 0 | | FAULT | 1 | 1 | 1 |

  EFF : 051-057, 059-060, 062-099, 106-149,  34-14-00 Page 89 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Feb 01/10 R 236-238, 301-304, CES

 

----------------------------------------------------------| GPIRS MODE | BIT 28 | BIT 27 | BIT 26 | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------| BIT N⁰ | FUNCTION | |--------|--------------------------------------------------------------------| | 9 | MMR SYSTEM FAILURE | | 10 | DUAL MMR CHANNEL FAIL | | 11 | NO IR DATA | | 12 | INVALID IR DATA | | 13 | TM MISSING ON PRIMARY | | 14 | TM MISSING ON SECONDARY | | 15 | ARINC TRANSMISSION FAULT | | 16 | NO AUTONOMOUS DATA FROM PRIMARY | | 17 | NO AUTONOMOUS DATA FROM SECONDARY | | 18 | AUTONOMOUS/IRS LATITUDE MISCOMPARE | | 19 | SPARE | | 20 | AUTONOMOUS/IRS LONGITUDE MISCOMPARE | | 21 | SPARE | | 22 | CLOCK PHASE MISCOMPARE ON PRIMARY | | 23 | CLOCK PHASE MISCOMPARE ON SECONDARY | | 24 | TM TIMING/UTC MISCOMPARE ON PRIMARY | | 25 | TM TIMING/UTC MISCOMPARE ON SECONDARY | | 26 | | | 27 | | RESERVED | | 28 | | | | 29 | | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------ADIRU Maintenance Word 353 ------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 9 | SDI (LSB) | | 10 | SDI (MSB) | | 11 | | | 12 | | | | 13 | | | | 14 | | RESERVED | | 15 | | | | 16 | | | | 17 | |

  R EFF : 051-057, 059-060, 062-099, 106-149,  34-14-00 Page 90 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Feb 01/10 236-238, 301-304, CES

 

------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 18 | CMC INPUT BUS (OMS) No activity = 1 | | 19 | DIFF BUS No. 2 No activity = 1 | | 20 | DIFF BUS No. 2 No activity = 1 | | 21 | DADS BUS 2 No activity = 1 | | 22 | DADS BUS 1 No activity = 1 | | 23 | IRS INPUT BUS 2 No activity = 1 | | 24 | IRS INPUT BUS 1 No activity = 1 | | 25 | MMR Fail = 1 | | 26 | RF INPUT Fail = 1 | | 27 | SENSOR UNIT Fail = 1 | | 28 | TEST INHIBIT Inhibit = 1 | | 29 | COMMAND WORD ACKNOWLEDGE Forced = 0 | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------MMR Navigation Maintenance Word (Label 355) **ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-514, | | | | | | | | | | | | | | | | | | | | | | |

9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26

| | | | | | | | | | | | | | | | | | | | | | |

| SDI -

SA STATUS AS DETERMINED BY THE ADIRU 0 = sa off 1 = sa on

| POSITION DATA SOURCE/POSITION COMPARISON FAILURE MODE | SECONDARY MMR VALIDITY | PRIMARY MMR VALIDITY

00 01 10 11

= = = =

Valid Inactive Functional Test Fail

MMR SOURCE

Primary = 0

Secondary = 1

| NUMBER OF SATELLITES TRACKED (0-15) | | SPARE -

| | | | | | | | | | | | | | | | | | | | | | |

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page 91 301-399, 401-499, 501-509, 511-514,  Config-3 Feb 01/10  CES

 

------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 27 | | GPIRS SENSOR OPERATIONAL MODE (Ref table below) | | 28 | | | 29 | MSB OF TRACKED SATELLITES (16) | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------Discrete Word 274 Output Format ----------------------------------------------------------| GPIRS MODE | BIT 28 | BIT 27 | BIT 26 | ----------------------------------------------------------| SELF TEST | 0 | 0 | 0 | | INITIALIZATION | 0 | 0 | 1 | | ACQUISITION | 0 | 1 | 0 | | NAVIGATION | 0 | 1 | 1 | | ALTITUDE AIDING | 1 | 0 | 0 | | SPARE | 1 | 0 | 1 | | SPARE | 1 | 1 | 0 | | FAULT | 1 | 1 | 1 | ----------------------------------------------------------------------------------------------------------------------------------------| BIT N⁰ | FUNCTION | |--------|--------------------------------------------------------------------| | 9 | SDI (LSB) | | 10 | SDI (LSB) | | 11 | | | 12 | | | | 13 | | | | 14 | | | | 15 | | | | 16 | | | | 17 | | | | 18 | | | | 19 | | | | 20 | | RESERVED | | 21 | | | | 22 | | | | 23 | | | | 24 | | | | 25 | | | | 26 | | | | 27 | | |

  EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 92 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 R 305-399, 401-499, 501-509, 511-514, CES

 

------------------------------------------------------------------------------| BIT N⁰ | FUNCTION | |--------|--------------------------------------------------------------------| | 28 | | | | 29 | | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------MMR Maintenance Word (Label 352) | 9 | GPS SYSTEM FAILURE | | 10 | DUAL GPS CHANNEL FAIL | | 11 | NO IR DATA | | 12 | INVALID IR DATA | | 13 | TM MISSING ON PRIMARY | | 14 | TM MISSING ON SECONDARY | | 15 | ARINC TRANSMISSION FAULT | | 16 | NO AUTONOMOUS DATA FROM PRIMARY | | 17 | NO AUTONOMOUS DATA FROM SECONDARY | | 18 | AUTONOMOUS/IRS LATITUDE MISCOMPARE | | 19 | SPARE | | 20 | AUTONOMOUS/IRS LONGITUDE MISCOMPARE | | 21 | SPARE | | 22 | CLOCK PHASE MISCOMPARE ON PRIMARY | | 23 | CLOCK PHASE MISCOMPARE ON SECONDARY | | 24 | TM TIMING/UTC MISCOMPARE ON PRIMARY | | 25 | TM TIMING/UTC MISCOMPARE ON SECONDARY | | 26 | | | 27 | | RESERVED | | 28 | | | | 29 | | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------ADIRU Maintenance Word 353

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 93 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-514, CES

 

------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 9 | SDI (LSB) | | 10 | SDI (MSB) | | 11 | | | 12 | | | | 13 | | | | 14 | | RESERVED | | 15 | | | | 16 | | | | 17 | | | 18 | CMC INPUT BUS (OMS) No activity = 1 | | 19 | DIFF BUS No. 2 No activity = 1 | | 20 | DIFF BUS No. 2 No activity = 1 | | 21 | DADS BUS 2 No activity = 1 | | 22 | DADS BUS 1 No activity = 1 | | 23 | IRS INPUT BUS 2 No activity = 1 | | 24 | IRS INPUT BUS 1 No activity = 1 | | 25 | GPS Fail = 1 | | 26 | RF INPUT Fail = 1 | | 27 | SENSOR UNIT Fail = 1 | | 28 | TEST INHIBIT Inhibit = 1 | | 29 | COMMAND WORD ACKNOWLEDGE Forced = 0 | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------GPSSU Navigation Maintenance Word (Label 355) R

**ON A/C 515-523, | | | | | | | | | | | | | |

9 10 11 12 13 14 15 16 17 18

| | | | | | | | | | | | | |

| SDI -

SPARE

| POSITION DATA SOURCE/POSITION COMPARISON FAILURE MODE | SECONDARY MMR VALIDITY | PRIMARY MMR VALIDITY

00 01 10 11

= = = =

-

Valid Inactive Functional Test Fail

| | | | | | | | | | | | | |

  R EFF : 058-058, 061-061, 216-216, 218-218,  34-14-00 Page 94 220-220, 226-226, 234-235, 239-249, 251-299,  Config-3 Feb 01/10 305-399, 401-499, 501-509, 511-523, CES

 

------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 19 | MMR SOURCE Primary = 0 Secondary = 1 | | 20 | | | 21 | | NUMBER OF SATELLITES TRACKED (0-15) | | 22 | | | | 23 | | | 24 | | | | | SPARE | | 25 | | | 26 | | | 27 | | GPIRS SENSOR OPERATIONAL MODE (Ref table below) | | 28 | | | 29 | MSB OF TRACKED SATELLITES (16) | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------Discrete Word 274 Output Format ----------------------------------------------------------| GPIRS MODE | BIT 28 | BIT 27 | BIT 26 | ----------------------------------------------------------| SELF TEST | 0 | 0 | 0 | | INITIALIZATION | 0 | 0 | 1 | | ACQUISITION | 0 | 1 | 0 | | NAVIGATION | 0 | 1 | 1 | | ALTITUDE AIDING | 1 | 0 | 0 | | SPARE | 1 | 0 | 1 | | SPARE | 1 | 1 | 0 | | FAULT | 1 | 1 | 1 | ----------------------------------------------------------------------------------------------------------------------------------------| BIT N⁰ | FUNCTION | |--------|--------------------------------------------------------------------| | 9 | SDI (LSB) | | 10 | SDI (LSB) | | 11 | | | 12 | | | | 13 | | | | 14 | | | | 15 | | | | 16 | | | | 17 | | | | 18 | | |

  R EFF : 515-523,  34-14-00 Page 95   Config-3 Feb 01/10  CES

 

------------------------------------------------------------------------------| BIT N⁰ | FUNCTION | |--------|--------------------------------------------------------------------| | 19 | | | | 20 | | RESERVED | | 21 | | | | 22 | | | | 23 | | | | 24 | | | | 25 | | | | 26 | | | | 27 | | | | 28 | | | | 29 | | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------MMR Maintenance Word (Label 352) | 9 | GPS SYSTEM FAILURE | | 10 | DUAL GPS CHANNEL FAIL | | 11 | NO IR DATA | | 12 | INVALID IR DATA | | 13 | TM MISSING ON PRIMARY | | 14 | TM MISSING ON SECONDARY | | 15 | ARINC TRANSMISSION FAULT | | 16 | NO AUTONOMOUS DATA FROM PRIMARY | | 17 | NO AUTONOMOUS DATA FROM SECONDARY | | 18 | AUTONOMOUS/IRS LATITUDE MISCOMPARE | | 19 | SPARE | | 20 | AUTONOMOUS/IRS LONGITUDE MISCOMPARE | | 21 | SPARE | | 22 | CLOCK PHASE MISCOMPARE ON PRIMARY | | 23 | CLOCK PHASE MISCOMPARE ON SECONDARY | | 24 | TM TIMING/UTC MISCOMPARE ON PRIMARY | | 25 | TM TIMING/UTC MISCOMPARE ON SECONDARY | | 26 | | | 27 | | RESERVED | | 28 | | | | 29 | | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------ADIRU Maintenance Word 353

  R EFF : 515-523,  34-14-00 Page 96   Config-3 Feb 01/10  CES

 

------------------------------------------------------------------------------| BIT No.| FUNCTION | |--------|--------------------------------------------------------------------| | 9 | SDI (LSB) | | 10 | SDI (MSB) | | 11 | | | 12 | | | | 13 | | | | 14 | | RESERVED | | 15 | | | | 16 | | | | 17 | | | 18 | CMC INPUT BUS (OMS) No activity = 1 | | 19 | DIFF BUS No. 2 No activity = 1 | | 20 | DIFF BUS No. 2 No activity = 1 | | 21 | DADS BUS 2 No activity = 1 | | 22 | DADS BUS 1 No activity = 1 | | 23 | IRS INPUT BUS 2 No activity = 1 | | 24 | IRS INPUT BUS 1 No activity = 1 | | 25 | GPS Fail = 1 | | 26 | RF INPUT Fail = 1 | | 27 | SENSOR UNIT Fail = 1 | | 28 | TEST INHIBIT Inhibit = 1 | | 29 | COMMAND WORD ACKNOWLEDGE Forced = 0 | | 30 | SSM | | 31 | SSM | | 32 | PARITY | ------------------------------------------------------------------------------GPSSU Navigation Maintenance Word (Label 355)

  R EFF : 515-523,  34-14-00 Page 97   Config-3 Feb 01/10  CES

 

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (2) Discrete outputs The IR provides 3 discrete outputs. The following table defines the characteristics of these discretes. --------------------------------------| SIGNAL | OUTPUT | DEFINITION | |----------|-------------|------------| | ON BAT | OPEN/+28VDC | NO/YES | | IR FAULT | OPEN/+28VDC | NO/YES | | IR ALIGN | OPEN/GROUND | NO/YES | --------------------------------------Discrete Outputs - ON BAT When the IR is powered with batteries, this discrete delivers a 28VDC state and sets the ON BAT light to on. - IR FAULT When a failure is detected by the IR, this discrete delivers a 28VDC state and sets the FAULT legend to on. - IR ALIGN When the IR is aligning, this discrete delivers a ground and sets the ALIGN legend to on.

  R EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page 98 401-499,  Config-3 Feb 01/10  CES

 

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (2) Discrete outputs The IR provides 3 discrete outputs. The following table defines the characteristics of these discretes. --------------------------------------| SIGNAL | OUTPUT | DEFINITION | |----------|-------------|------------| | ON BAT | OPEN/+28VDC | NO/YES | | IR FAULT | OPEN/+28VDC | NO/YES | | IR OFF | OPEN/GROUND | NO/YES | --------------------------------------Discrete Outputs - ON BAT When the IR is powered with batteries, this discrete delivers a 28VDC state and sets the ON BAT light to on. - IR FAULT When a failure is detected by the IR, this discrete delivers a 28VDC state and sets the FAULT legend to on. - IR OFF When the IR is set to off, this discrete delivers a ground and sets the OFF legend to on.

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, 3. ________________________________ Operation/Control and Indicating **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 011) A. Control (1) Modes of operation Operation interface with the IR is performed through the Multipurpose Control and Display Unit 1(2) or the CDU. The MCDU 1(2) is used for entering initialization data and displaying IR data. (Ref. Fig. 012) The CDU is used for mode selection, IR annunciation (FAULT, ALIGN), for entering initialization data and displaying IR data. The IR has three selectable modes: OFF, NAV and ATT.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page 99 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

IR - Operation/Control and Indicating Figure 011   R EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page A0 401-499,  Config-3 Feb 01/10  CES

 

IR - Operation/Control and Indicating Figure 011A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-14-00 Page A1 511-523,  Config-3 Feb 01/10  CES

 

IR - Alignment Procedure from the MCDU Figure 012   R EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page A2 401-499,  Config-3 Feb 01/10  CES

 

The relation between the mode selection and system response is shown in the figure (Ref. Fig. 013) (2) OFF mode When the OFF/NAV/ATT selector switch on the CDU is in the OFF position, all circuitry in ADIRU is de-energized except for any logic associated with the power-off function. When the ADIRU has turned off, it consumes less than 10 milliamps (needed for power supply turn-on control). The power supply of the ADMs is switched off. A period of 15 seconds is required between switching to OFF and actual power off. During this sequence, the last position computed is stored in NVM. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (Ref. Fig. 011A) A. Control (1) Modes of operation The operation interface with the IR is performed through the Multipurpose Control and Display Unit 1(2) and the MSU. The MCDU 1(2) is used for entering initialization data and displaying IR data. (Ref. Fig. 012A) The MSU is used for mode selection and IR annunciation (FAULT, OFF). The IR has three selectable modes: OFF, NAV and ATT. The relation between the mode selection and system response is shown in the figure. (Ref. Fig. 013) (2) OFF mode When the OFF/NAV/ATT selector switch on the MSU is in the OFF position, all circuitry in the ADIRU is de-energized except for any logic associated with the power-off function. When the ADIRU is turned off, its consumption is less than 10 milliamps (needed for power supply switch-on control). The power supply of the ADMs is switched off. A period of 15 seconds is required between switching to OFF and actual power-off. During this sequence, the last position computed is stored in NVM.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A3 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

IR - Alignment Procedure from the MCDU Figure 012A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-14-00 Page A4 511-523,  Config-3 Feb 01/10  CES

 

IR - Mode State Diagram Figure 013   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A5 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (3) NAV (Navigation) mode After selection of the NAV mode on the ground, the IR automatically enters the NAV mode if a self-determined satisfactory alignment has been completed. If alignment is not completed, the IR remains in the Align submode. No updating of the IR present position latitude and longitude is allowed once the IR has completed the Align submode. The IR latitude and longitude entered during alignment is the starting point for its computation. The following logical processes are mechanized: - OFF to NAV provides automatic alignment in 10 minutes for latitudes between 73⁰N and 60⁰S, with automatic entry to NAV mode. Requires initial position data to be entered. NOTE : The automatic alignment requires 15 min delay for latitudes ____ between 73⁰N and 82⁰N. For high latitudes, the alignment is provided by an operational procedure which delays the entering of the initial position by the crew. Accuracies of the system are slightly degraded. - a message on the UPPER ECAM DU indicates that the IRs are in ALIGN submode with the maximum time until NAV - in the NAV mode, rapid realignment of the IR is initiated by switching the OFF/NAV/ATT selector switch from NAV to OFF and back to NAV within 5 seconds. The IR starts a 30-second realignment submode with existing attitude and heading angles and rezeroed velocities - the system does not enter the rapid realignment sequence if the ground speed is greater than 20 knots. The CDU permits to observe some particular parameters (Ref. 34-12-00). (a) Initialization data **ON A/C 051-099, 106-149, 204-233, 236-238, 301-304, 401-499, (Ref. Fig. 014) **ON A/C 234-235, 239-239, 305-312, (Ref. Fig. 014A)

  R EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page A6 401-499,  Config-3 Feb 01/10  CES

 

MCDU - INIT Page Figure 014   R EFF : 051-099, 106-149, 204-233, 236-238,  34-14-00 Page A7 301-304, 401-499,  Config-3 Feb 01/10  CES

 

MCDU - INIT Page Figure 014A   R EFF : 234-235, 239-249, 251-299, 305-399,  34-14-00 Page A8 501-509, 511-523,  Config-3 Feb 01/10  CES

 

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, IR alignment is carried out on the ground before takeoff and after the entry of the current aircraft coordinates on the INIT page of the MCDU 1(2) (Ref. 22-72-00) or on the CDU (DATA DISPLAY selector switch in PPOS position). Valid initial position data must be received and verified by the IR during the 10-minute alignment or automatic sequencing to the NAV mode will be delayed after position data is received. Initial position data are verified by the IR if Set Latitude and Set Longitude compare within one degree of the last latitude and longitude from the previous flight. If a miscompare exists then: - on the ADIRS CDU, the ALIGN light flashes. - a message ENTER PPOS is displayed on the CDU (DATA DISPLAY selector switch in STS position). The miscompare is removed and the position data verified by the IR when: - the last two Set Latitudes received by the IR are identical and the last two Set Longitudes received by the IR are identical, or - the last Set Latitude and Set Longitude received by the IR compare within one degree of the latitude and longitude from the previous flight. (b) Latitude comparison The IR compares Set Latitude with a self-computed gyro-compass latitude after 10 minutes into alignment or any subsequent time when a valid Set Latitude is available. In case of discrepancy, on the ADIRS CDU the ALIGN light flashes. The message ENTER PPOS is displayed on the CDU (DATA DISPLAY selector switch in STS position). The discrepancy exists when: - the cosine of entered latitude differs from the computed cosine of latitude by more than 0.01234, or - the sine of entered latitude differs from the computed sine of latitude by more than 0.01234. The miscompare is removed if a subsequent entry of Set Latitude passes the test. If sin/cos test fails two times with identical set latitude inputs then: - the IR FAULT legend flashes on the CDU - a warning message appears on the upper ECAM DU: NAV IR 1(2)(3) FAULT.

  R EFF : 051-099, 106-149, 204-239, 301-312,  34-14-00 Page A9 401-499,  Config-3 Feb 01/10  CES

 

(c) Excessive motion The IR performs an excessive motion test during the Align submode. If taxiing or towing causes a step input which exceeds 0.5 ft/s in the X or Y velocity, then: - the EXCESS MOTION message is displayed on the CDU (DATA DISPLAY selector switch in STS position) - the following message is displayed on the upper ECAM DU: NAV IR 1(2)(3) NOT ALIGN EXCESS MOTION IR 1(2)(3) IN ALIGN - the attitude information is flagged on the PFD. Thirty seconds after motion detection, the system reverts to a full alignment (time to the end of alignment will revert to 9 min 30 s). It is not necessary to re-enter the position. (d) Thirty-second rapid realignment A thirty-second rapid realignment is provided by moving the OFF/NAV/ATT selector switch on the CDU from NAV to OFF and back to NAV within five seconds. A subsequent switching on the selector switch from NAV to OFF and back to NAV within 5 seconds during the 30-second realignment causes the system to start the 30-second realignment again. The realignment is initialized with existing attitude and heading angles. Velocities are zeroed. Valid position data must be received and verified by the IR during the 30-second realignment. **ON A/C 240-249, 251-299, 313-399, 501-509, 511-514, (3) NAV (Navigation) mode After selection of the NAV mode on the ground, the IR automatically enters the NAV mode if a self-determined satisfactory alignment has been completed. If alignment is not completed, the IR remains in the Align submode. No updating of the IR present position latitude and longitude is allowed once the IR has completed the Align submode. The IR latitude and longitude entered during alignment is the starting point for its computation. The following logical processes are mechanized: - OFF to NAV provides automatic alignment in 10 minutes for latitudes between 73⁰N and 60⁰S, with automatic entry to NAV mode. Requires initial position data to be entered.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A10 301-399, 401-499, 501-509, 511-514,  Config-3 Feb 01/10  CES

 

NOTE : The automatic alignment requires a delay of 15 min for ____ latitudes between 73⁰N and 82⁰N. For high latitudes, the alignment is provided by an operational procedure which delays the entry of the initial position by the crew. Accuracies of the system are slightly degraded. - A message on the UPPER ECAM DU indicates that the IRs are in ALIGN submode with the maximum time until NAV. - In the NAV mode, rapid realignment of the IR is initiated by switching the OFF/NAV/ATT selector switch from NAV to OFF and back to NAV within 5 seconds. The IR starts a 30-second realignment submode with existing attitude and heading angles and rezeroed velocities. - The system does not enter the rapid realignment sequence if the ground speed is greater than 20 knots. (a) Initialization data (Ref. Fig. 014A) IR alignment is carried out on the ground before takeoff and after the entry of the current aircraft coordinates on the INIT page of the MCDU 1(2) (Ref. 22-72-00). Valid initial position data must be received and verified by the IR during the 10-minute alignment or automatic sequencing to the NAV mode will be delayed after position data is received. The initial position data is verified by the IR if the Set Latitude and Set Longitude compare within one degree of the last latitude and longitude from the previous flight. The position data is verified by the IR when: - the last two Set Latitudes received by the IR are identical and the last two Set Longitudes received by the IR are identical, or - the last Set Latitude and Set Longitude received by the IR compare within one degree of the latitude and longitude from the previous flight. (b) Latitude comparison The IR compares the Set Latitude with a self-computed gyro-compass latitude after 10 minutes into alignment or any subsequent time when a valid Set Latitude is available. The discrepancy exists when: - the cosine of the entered latitude differs from the computed cosine of latitude by more than 0.01234, or - the sine of the entered latitude differs from the computed sine of latitude by more than 0.01234. The miscompare is removed if a subsequent entry of Set Latitude passes the test.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-14-00 Page A11 511-514,  Config-3 Feb 01/10  CES

 

If sin/cos test fails two times with identical set latitude inputs then: - a warning message appears on the upper ECAM DU: NAV IR 1(2)(3) FAULT. (c) Excessive motion The IR performs an excessive motion test during the Align submode. If taxiing or towing causes a step input which exceeds 0.5 ft/s in the X or Y velocity, then: - the following message is displayed on the upper ECAM DU: NAV IR 1(2)(3) NOT ALIGN EXCESS MOTION IR 1(2)(3) IN ALIGN - the attitude information is flagged on the PFD. Thirty seconds after motion detection, the system reverts to a full alignment (time to the end of alignment will revert to 9 min 30 s). It is not necessary to re-enter the position. (d) Thirty-second rapid realignment A thirty-second rapid realignment is provided by moving the OFF/NAV/ATT selector switch on the MSU from NAV to OFF and back to NAV within five seconds. A subsequent switching on the selector switch from NAV to OFF and back to NAV within 5 seconds during the 30-second realignment causes the system to start the 30-second realignment again. The realignment is initialized with existing attitude and heading angles. Velocities are zeroed. Valid position data must be received and verified by the IR during the 30-second realignment. R

**ON A/C 515-523, (3) NAV (Navigation) mode After selection of the NAV mode on the ground, the IR automatically enters the NAV mode if a self-determined satisfactory alignment has been completed. If alignment is not completed, the IR remains in the Align submode. No updating of the IR present position latitude and longitude is allowed once the IR has completed the Align submode. The IR latitude and longitude entered during alignment is the starting point for its computation. The following logical processes are mechanized:

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-14-00 Page A12 511-523,  Config-3 Feb 01/10  CES

 

- OFF to NAV provides automatic alignment with automatic entry to the NAV mode. Requires either initial position data to be entered, or GPS data to be valid. NOTE : The automatic alignment requires a delay 17 min for latitudes ____ between 73⁰N and 82⁰N. For high latitudes, the alignment is provided by an operational procedure which delays the entry of the initial position by the crew. Accuracies of the system are slightly degraded. - A message on the UPPER ECAM DU indicates that the IRs are in ALIGN submode with the maximum time until NAV. - In the NAV mode, rapid realignment of the IR is initiated by switching the OFF/NAV/ATT selector switch from NAV to OFF and back to NAV within 5 seconds. The IR starts a 30-second realignment submode with existing attitude and heading angles and rezeroed velocities. - The system does not enter the rapid realignment sequence if the ground speed is greater than 20 knots. (a) Initialization data (Ref. Fig. 014A) IR alignment is carried out on the ground before takeoff and after the acquisition of valid position data (either GPS data or pilot entry). Valid initial position data must be received and verified by the IR during the 10-minute alignment or automatic sequencing to the NAV mode will be delayed after a position data is received. The initial position data is verified by the IR if the Set Latitude and Set Longitude compare within one degree of the last latitude and longitude from the previous flight. The position data is verified by the IR when: - The last two Set Latitudes received by the IR are identical and the last two Set Longitudes received by the IR are identical, or - The last Set Latitude and Set Longitude received by the IR compare within one degree of the latitude and longitude from the previous flight. (b) Latitude comparison The IR compares the selected Latitude with a self-computed gyro-compass latitude at the end of the alignment into alignment or any subsequent time when a valid Set Latitude is available. The discrepancy exists when: - The cosine of the entered latitude differs from the computed cosine of latitude by more than 0.01234, or

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- The sine of the entered latitude differs from the computed sine of latitude by more than 0.01234. The miscompare is removed if a subsequent entry of the Set Latitude passes the test. If the sin/cos test fails two times with identical set latitude inputs then: - a warning message appears on the upper ECAM DU: NAV IR 1(2)(3) FAULT. (c) Excessive motion The IR performs an excessive motion test during the Align submode. If taxiing or towing causes a step input which exceeds 0.5 ft/s in the X or Y velocity, then: - The following message is displayed on the upper ECAM DU: NAV IR NOT ALIGNED EXCESS MOTION IR 1(2)(3) IN ALIGN - the attitude information is flagged on the PFD. Thirty seconds after motion detection, the system reverts to a full alignment (time to the end of alignment will revert to 9 min 30 s). It is not necessary to re-enter the position. (d) Thirty-second rapid realignment A thirty-second rapid realignment is provided by moving the OFF/NAV/ATT selector switch on the MSU from NAV to OFF and back to NAV within five seconds. A subsequent switching of the selector switch from NAV to OFF and back to NAV within 5 seconds during the 30-second realignment causes the system to start the 30-second realignment again. The realignment is initialized with existing attitude and heading angles. Velocities are zeroed. Valid position data must be received and verified by the IR during the 30-second realignment. **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (4) ATT (Attitude) mode The IR has a reversionary mode which can be activated only by manual selection of ATT mode on the CDU. The mode can be activated on the ground or in the flight and is intended to provide a rapid attitude/heading restart capability in the event that the IR has

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experienced a total power shutdown or a failure has occurred resulting in the following: - IR FAULT legend flashing on the CDU - IR 1(2)(3) FAULT message displayed on the upper ECAM DU: IR x MODE SEL...ATT - SELECT ATT message displayed on the CDU (DATA DISPLAY selector switch in STS position). The IR is designed so that the ATT mode can be used after BITE has detected failures which will cause excessive NAV mode data errors but does not disable the ATT mode mechanization. However, it is recommended to stay in NAV mode even with excessive navigation errors because of higher accuracy of attitude signals and a more complete signal processing. The ATT mode must always be used after loss of power or a similar situation in flight where a new alignment/leveling is required. The ENTER HEADING message is displayed on the CDU (DATA DISPLAY selector switch in STS position) when the ATT mode is selected until valid heading initialization is received from the MCDU or the CDU. The ATT mode is normally engaged with the aircraft in level flight. A 20-second period is needed with the aircraft in level flight to perform an attitude erection to initialize a level attitude. During this period, the data normally computed in ATT mode have SSMs set to NCD. In the event the ATT mode is engaged with the aircraft not in level flight, an erection cut-out function delays erection when yaw rate exceeds 0.5 deg/s and permits erection to continue when yaw rate drops below 0.25 deg/s. Twenty seconds of flight with the erection cut-out switch disengaged is required to erect the attitude. B. Indicating Attitude and heading information is computed by the ADIRU (IR portion) and processed by the associated DMC. The attitude data are displayed on the PFD and the heading data are displayed on the PFD, the ND and the RMI. In addition, vertical speed (V/S) is displayed on the PFD and Ground Speed and wind indications are displayed on the ND. In normal configuration, with the ATT/HDG selector switch in NORM position, the IR1 data are displayed on the CAPT PFD, ND and the RMI (Ref. ATA 34-57-00). The IR2 data are displayed on the F/O PFD and ND. The following parameters can be displayed on the CDU liquid crystal display according to the position of the DATA DISPLAY selector switch on the CDU: - wind (WIND) - present position (PPOS) - true heading (HDG) - status of selected system conditions (STS) - track and ground speed (TK/GS)

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- test values (TEST). The sources of the data displayed are controlled by the SYS DISPLAY selector switch on the CDU. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (4) ATT (Attitude) mode The IR has a reversionary mode that can be activated only by manual selection of the ATT mode on the MSU. The mode can be activated on the ground or in flight and is intended to provide a rapid attitude/heading restart capability in the event that the IR has experienced a total power shutdown or a failure has occurred resulting in the following: - IR FAULT legend flashing on the MSU - IR 1(2)(3) FAULT message displayed on the upper ECAM DU: IR x MODE SEL...ATT The IR is designed so that the ATT mode can be used after the BITE has detected failures which will cause excessive NAV mode data errors but do not disable the ATT mode mechanization. However, it is recommended to stay in the NAV mode even with excessive navigation errors because of higher accuracy of attitude signals and more complete signal processing. The ATT mode must always be used after loss of power or a similar situation in flight where a new alignment/leveling is required. The ATT mode is normally engaged with the aircraft in level flight. A 20-second period is needed with the aircraft in level flight to perform an attitude erection to initialize a level attitude. During this period, the data normally computed in ATT mode has SSMs set to NCD. In the event the ATT mode is engaged with the aircraft not in level flight, an erection cut-out function delays erection when the yaw rate exceeds 0.5 deg/s and permits erection to continue when yaw rate drops below 0.25 deg/s. Twenty seconds of flight with the erection cut-out switch disengaged is required to erect the attitude. B. Indicating Attitude and heading information is computed by the ADIRU (IR portion) and processed by the associated DMC. The attitude data is displayed on the PFD and the heading data is displayed on the PFD, the ND and the RMI. In addition, the vertical speed (V/S) is displayed on the PFD and Ground Speed and wind indications are displayed on the ND. In normal configuration, with the ATT/HDG selector switch in NORM position, the IR1 data is displayed on the CAPT PFD, ND and the RMI (Ref. ATA 34-57-00). The IR2 data is displayed on the F/O PFD and ND.

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R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (1) Attitude information (Ref. Fig. 015) The aircraft roll and pitch attitude is indicated in the center part of the PFD by a sphere representing a conventional ADI drum. (Ref. 31-64-00 for sphere definition and display). (a) Pitch angle information (item A) The A/C present pitch angle is given by the vertical displacements of the pitch attitude scale with respect to the center of the A/C reference. The scale moves behind the cut-sphere shaped window, limited by the lines of an upper and a lower sector. The scale rotates around the center of the A/C reference in accordance with the A/C present roll angle. The pitch scale comprises white reference lines and associated pitch angle values. The lines are given every 2.5 degrees from 0 to 10 degrees, then for the 15 degrees, 20 degrees, 30 degrees, 50 degrees and 80 degrees values. Beyond 30 degrees, red large arrow heads (V-shaped) indicate an excessive attitude and the direction to follow in order to reduce it (item B). (b) Roll angle information (item A) A yellow triangle which remains on the line going through the center of the A/C reference and which is perpendicular to the horizon line, moves against the fixed roll scale on the upper contour of the attitude sphere. This fixed roll scale comprises white marks for the 10 degrees, 20 degrees, 30 degrees and 45 degrees significant values, on either side of the zero position (horizontal wings) which is indicated by a small fixed triangle. The 60 degrees roll indication corresponds to the limits of the upper contour of the cut-sphere shaped window. (c) Attitude failure In case of attitude failure concerning the pitch and/or roll information the attitude sphere goes out of view and is replaced by a red ATT flag which flashes for a few seconds then remains steady (item C). In case of discrepancy detected by the FWC between the pitch or roll attitude information presented on the CAPT and F/O PFDs, a CHECK ATT amber message flashes for a few seconds on both PFDs, then remains steady (item D).

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IR - Attitude Information Display Figure 015   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A18 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (2) Heading information (Ref. Fig. 016) The aircraft magnetic or true heading is displayed on the PFD, the ND and the RMI. The true heading can be displayed on the CDU. (a) On the PFD When true heading is displayed, a TRUE white message appears above the heading scale (item A). A blank heading scale (with 10 deg. spaced marks without any indicated value) is provided on the horizon line. The marks are just under this line. This scale moves as the aircraft heading varies. For important nose-up or nose- down, the heading graduations remain at the lower or upper sector limit. Below the sphere, a heading scale provides the pilot with the aircraft actual track and relative selection. This heading scale is graduated every 5 deg. (item A). In case of failure, the heading graduation disappears on the two scales and a red HDG flag appears on the lower heading scale (item B). It flashes for a few seconds, then remains steady. Furthermore, in case of discrepancy detected by the FWC between CAPT and F/O heading indications, with the heading signal valid, a CHECK HDG amber message is displayed at the center of the heading scale (item C). (b) On the ND (Ref. Fig. 017) The heading data is displayed on the ND in the three following operating modes: ROSE, ARC and PLAN. The ROSE mode and the ARC mode are oriented with respect to the aircraft heading, while the PLAN mode is oriented with respect to the true north. 1 _

True heading display In ROSE or ARC mode, when true heading is displayed, a cyan TRUE message appears at the top of the ND.

2 _

ROSE mode (item A) In this mode each pilot has three different sub-modes of presentation on his ND: ROSE-ILS/ROSE-VOR/ROSE-NAV.

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IR - Heading Information Display on the PFD Figure 016   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A20 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

IR - Heading Information Display on the ND Figure 017   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A21 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

In the three ROSE sub-modes, the ND provides a display which is similar to that of a conventional HSI, i.e. a rotating heading dial orientated to the North and giving to the pilot the aircraft actual magnetic or true heading with as reference the fixed yellow lubber line at the top of the dial. 3 _

ARC mode (item B) In this mode, the ND displays a 90 deg. heading sector ahead of the aircraft giving the aircraft actual magnetic or true heading with respect to the fixed yellow lubber line at the top of the scale.

4 _

PLAN mode The ND displays a static map orientated with respect to the true North.

5 _

Heading failure (items C and D) In case of heading failure, the scale and all symbols positioned on the ROSE and ARC scales go out of view; a red HDG flag comes into view below the scale after flashing for a few seconds, when the DMC has detected an anomaly concerning the heading parameter. In addition, if a discrepancy between CAPT and F/O sides is detected by the comparison inside the FWCs, the CHECK HDG message is displayed in amber on both NDs (item E).

(c) On the RMI **ON A/C 051-099, (Ref. Fig. 018) **ON A/C 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 018A) **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, The heading indication is given by a dial which rotates in front of a fixed index (item A). In case of heading failure, the fire orange warning flag with the black HDG inscription comes into view at the top of the compass card (item B). For more details, ref. 34-57-00.

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IR - Heading Information Display on the VOR/DME RMI Figure 018   R EFF : 051-099,  34-14-00 Page A23   Config-3 Feb 01/10  CES

 

IR - Heading Information Display on the VOR/ADF/DME RMI Figure 018A   R EFF : 106-149, 204-249, 301-399, 401-499,  34-14-00 Page A24   Config-3 Feb 01/10  CES

 

(d) On the CDU The time heading can be displayed on the CDU if the DATA DISPLAY selector switch is placed in the HDG position. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (2) Heading information (Ref. Fig. 016) The aircraft magnetic or true heading is displayed on the PFD, the ND and the RMI. (a) On the PFD When the true heading is displayed, a TRUE white message appears above the heading scale (item A). A blank heading scale (with 10 deg. spaced marks without any indicated value) is provided on the horizon line. The marks are just under this line. This scale moves as the aircraft heading varies. For important nose-up or nose-down, the heading graduations remain at the lower or upper sector limit. Below the sphere, a heading scale provides the pilot with the aircraft actual track and relative selection. This heading scale is graduated every 5 deg. (item A). In case of failure, the heading graduation disappears on the two scales and a red HDG flag appears on the lower heading scale (item B). It flashes for a few seconds, then remains steady. Furthermore, in case of discrepancy detected by the FWC between CAPT and F/O heading indications, with the heading signal valid, a CHECK HDG amber message is displayed at the center of the heading scale (item C). (b) On the ND (Ref. Fig. 017) The heading data is displayed on the ND in the following three operating modes: ROSE, ARC and PLAN. The ROSE mode and the ARC mode are oriented with respect to the aircraft heading, while the PLAN mode is oriented with respect to the true north. 1 _

True heading display In ROSE or ARC mode, when the true heading is displayed, a cyan TRUE message appears at the top of the ND.

2 _

ROSE mode (item A) In this mode, each pilot has three different sub-modes of presentation on his ND: ROSE-ILS/ROSE-VOR/ROSE-NAV.

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In the three ROSE sub-modes, the ND provides a display which is similar to that of a conventional HSI, i.e. a rotating heading dial orientated to the North and giving to the pilot the aircraft actual magnetic or true heading with, as reference, the fixed yellow lubber line at the top of the dial. 3 _

ARC mode (item B) In this mode, the ND displays a 90 deg. heading sector ahead of the aircraft giving the aircraft actual magnetic or true heading with respect to the fixed yellow lubber line at the top of the scale.

4 _

PLAN mode The ND displays a static map orientated with respect to the true North.

5 _

Heading failure (items C and D) In case of heading failure, the scale and all symbols positioned on the ROSE and ARC scales go out of view; a red HDG flag comes into view below the scale after flashing for a few seconds, when the DMC has detected an anomaly concerning the heading parameter. In addition, if a discrepancy between the CAPT and F/O sides is detected by the comparison inside the FWCs, the CHECK HDG message is displayed in amber on both NDs (item E).

(c) On the RMI **ON A/C 240-249, 313-399, (Ref. Fig. 018A) R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, The heading indication is given by a dial which rotates in front of a fixed index (item A). In case of heading failure, the fire orange warning flag with the black HDG inscription comes into view at the top of the compass card (item B). For more details, ref. 34-57-00. (d) Not Applicable

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**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (3) Ground speed (Ref. Fig. 019) The ground speed is displayed in the left upper corner of the ROSE, ARC or PLAN mode (item A). The GS title is displayed in white color and the ground speed in green. In case of failure or NCD, the ground speed value is replaced three dashed lines (item B). The ground speed can also be displayed on the CDU if the DATA selector switch is placed in the TK/GS position. R

ND for value by DISPLAY

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (3) Ground speed (Ref. Fig. 019) The ground speed is displayed in the left upper corner of the ND for the ROSE, ARC or PLAN mode (item A). The GS title is displayed in white color and the ground speed value in green. In case of failure or NCD, the ground speed value is replaced by three dashed lines (item B). **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (4) Wind indications (Ref. Fig. 019) The wind origin, force and direction is displayed in the left upper corner of the ND, for ROSE, ARC and PLAN mode (item A): - the wind origin is displayed in green color in degrees with respect to the true North - the wind force is displayed in green color in knots - the wind direction, in analog form, is represented by means of a green arrow orientated with respect to the north reference in use. This arrow is displayed only if the wind force is greater than 2 knots. In case of failure or NCD, the digital data are replaced by three dashed lines and the wind direction arrow disappears (item B). The wind indications can also be displayed on the CDU if the DATA DISPLAY selector switch is placed in the WIND position.

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IR - GS, Wind, Vertical Speed Information Display Figure 019   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A28 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (4) Wind indications (Ref. Fig. 019) The wind origin, force and direction is displayed in the left upper corner of the ND, for the ROSE, ARC and PLAN modes (item A): - the wind origin is displayed in green color in degrees with respect to the true North - the wind force is displayed in green color in knots - the wind direction, in analog form, is represented by means of a green arrow orientated with respect to the north reference in use. This arrow is displayed only if the wind force is greater than 2 knots. In case of failure or NCD, the digital data is replaced by three dashed lines and the wind direction arrow disappears (item B).

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (5) Vertical speed (Ref. Fig. 019) The inertial vertical speed is displayed in the right side of the PFD (item C). The vertical speed scale consists of: (a) a trapezoidal grey background colored surface (b) a fixed white scale with 500 ft/mn spaced marks from -2000 ft/mn to +2000 ft/mn (c) a needle giving in analog form the actual vertical speed value (d) a number in a moving blanking window. This window accompanies the needle (above) the needle if V/S > 0, below if V/S < 0). The number gives the V/S value in hundreds of ft/mn. Between -200 ft/mn and +200 ft/mn, both the window and the number disappear. (e) above +6000 ft/mn (or below -6000 ft/mn), the needle remains stopped where it is. When the vertical speed exceeds +6000 ft/mn or -6000 ft/mn, the digital indication and the analog needle change from green to amber.

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(f) In addition, those indications change to amber in approach, in the following cases: - V/S less than -2000 ft/mn below 2500 ft RA. - V/S less than -1200 ft/mn below 1000 ft RA. In case of failure, the inertial vertical speed display is automatically replaced by the baro vertical speed display. (Ref. 34-13-00). (6) Reconfiguration display In case of loss of inertial parameters on the CAPT or F/O PFD and ND, the IR3 can be used as a back up source by placing the ATT HDG selector switch in CAPT/3 position for the CAPT PFD and ND or in F/O/3 position for the F/O PFD and ND. **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, C. Warnings (Ref. Fig. 020, 021, 022, 023, 024) (1) In addition to the ATT or HDG flags displayed on the PFDs, NDs and on the CDU, warning messages are displayed on the lower part of the upper ECAM DU. (a) NAV IR 1(2)(3) FAULT NAV IR 1(2) + 2(3) FAULT When these messages are displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the IR FAULT legend flashes on the CDU. (b) NAV ATT DISCREPANCY This message is displayed when a difference higher than 5 deg. is detected by comparison inside the FWCs between the roll angle or the pitch angle provided by two IRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK ATT message appears on the PFD. (c) NAV HDG DISCREPANCY this message is displayed when a difference higher than 7 deg. (or 5 deg. in true heading) is detected by comparison inside the FWCs between the heading value provided by two IRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK HDG message appears on the PFDs and NDs.

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NAV IR 1(2)(3) fault message Figure 020   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A31 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

NAV IR 1+2 FAULT Message Figure 021   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A32 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

NAV IR 1+3 (2+3) FAULT Message Figure 022   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A33 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

NAV ATT DISCREPANCY Message Figure 023   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A34 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

NAV HDG DISCREPANCY Message Figure 024   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A35 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

(d) NAV GPS 1(2) FAULT (Ref. Fig. 025) The GPSSUs are monitored by the three ADIRUs using the status word sent by the GPSSU and the BITE of the IR partion. This message is accompanied by: - activation of the MASTER CAUT lights on the glareshield panel - aural warning: single chime (SC). R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, C. Warnings (Ref. Fig. 020, 021, 022, 023, 024) (1) In addition to the ATT or HDG flags displayed on the PFDs and the NDs, warning messages are displayed on the lower part of the upper ECAM DU. (a) NAV IR 1(2)(3) FAULT NAV IR 1(2) + 2(3) FAULT When these messages are displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the IR FAULT legend flashes on the MSU. (b) NAV ATT DISCREPANCY This message is displayed when a difference higher than 5 deg. is detected by comparison inside the FWCs between the roll angle or the pitch angle provided by two IRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK ATT message appears on the PFD. (c) NAV HDG DISCREPANCY This message is displayed when a difference higher than 7 deg. (or 5 deg. in true heading) is detected by comparison inside the FWCs between the heading value provided by two IRs. When it is displayed: - the MASTER CAUT lights on the glareshield come on - the Single Chime (SC) sounds - the CHECK HDG message appears on the PFDs and NDs. (d) Not Applicable

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NAV GPS - Fault Messages Figure 025   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A37 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, D. ADIRUs Performance Criteria (1) History The inertial parameters to be considered to evaluate the level of performance of an inertial system after flight completion are: - the radial position error (in NM) - the residual ground speed error (in kts). Depending on their magnitude noticed at the end of the flight, the concerned inertial system(s) shall or shall not be removed from the aircraft. (2) Radial position error In order to address the statistical term of this requirement with the most relevant approximation, the removal criteria use a limit based on the recording of the radial position error on two consecutive flights. The use of a two-strike method presents the advantage to decrease the removal rate of healthy units that have shown, by chance, or by an inaccurate position entry at alignment, a radial position error beyond the specified criterion. The removal boundaries described on the figure present three different areas: (Ref. Fig. 026) - Area 1 - ADIRU OK all the time - Area 2 - ADIRU to be checked after second flight - Area 3 - ADIRU to be replaced. NOTE : Area 2 is applicable when the residual radial position error ____ ranges within the limits described in following Para. (a) Lower limit for removal criteria The integration of the drift rate results in a lower limit for the radial position error: Radial position error (NM) = (2 (NM/h) * T (h)) + Offset (NM) The presence of an offset is necessary to avoid the unjustified removal of healthy units subject to the natural Schuler effects and to the Present Position inaccuracies entered during initialization. It should be pointed out that the adverse impacts of such inaccuracies over the radial position error will reveal stronger for short flight durations (below 1.5 hour). - Flight duration < 1.5 FH: The lower limit of the grey band is fixed at 5 NM. - 1.5 FH < Flight duration < 10 FH:

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A38 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRU RPE removal criteria Figure 026   R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A39 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

The lower limit of the grey band is fixed at 2T + 2. - Flight duration > 10 FH: The lower limit of the grey band is fixed at 22 NM. (b) Upper limit for removal criteria - Flight duration < 1.5 FH: The upper limit of the grey band is fixed at 7.5 NM. - 1.5 FH < Flight duration < 10 FH: The upper limit of the grey band is fixed at 3T + 3. - Flight duration > 10 FH: The upper limit of the grey band is fixed at 33 NM. **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (3) Residual Ground Speed Error The residual ground speed for each IR is determined at the end of the flight when the aircraft has come to a complete stop. (a) Check of the residual ground speed can be made: - On the CAPT (IR1) and F/O (IR2) Navigation Displays (ND): The residual ground speed of the IR3 can be read on the CAPT ND by setting the ATT HDG selector switch to CAPT/3. - On the ADIRS CDU: . set the DATA DISPLAY selector switch to TK/GS . set the SYS DISPLAY selector switch to 1, 2, 3 . read the respective ground speed in the CDU display. (b) Compare the recorded ground speed values with the following limits: - if the residual ground speed error is 15 kts or greater after each of two consecutive flights, replace the ADIRU - if the residual ground speed error is 21 kts or greater at the end of any one flight, replace the ADIRU. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (3) Residual Ground Speed Error The residual ground speed for each IR is determined at the end of the flight when the aircraft has come to a complete stop. (a) A check of the residual ground speed can be made on the CAPT (IR1) and F/O (IR2) Navigation Displays (ND). The residual ground speed of the IR3 can be read on the CAPT ND by setting the ATT HDG selector switch to CAPT/3.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 Page A40 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

(b) Compare the recorded ground speed values with the following limits: - if the residual ground speed error is 15 kts or greater after each of two consecutive flights, replace the ADIRU - if the residual ground speed error is 21 kts or greater at the end of any one flight, replace the ADIRU.

  EFF : 240-249, 251-299, 313-399, 501-509,  34-14-00 Page A41 511-523,  Config-3 Feb 01/10  CES

 

ATTITUDE, HEADING AND POSITION - ADJUSTMENT/TEST ________________________________________________ TASK 34-14-00-710-003 Operational Test of the Attitude/Heading (ATT/HDG) Switching Function WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Refer to the MPD TASK: 341400-01 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 31-60-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure

3. __________ Job Set-up Subtask 34-14-00-010-050 A. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822.

  EFF : ALL  34-14-00    CES

 

Page 501 Feb 01/98

(3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-14-00-865-054 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

2GA 52GA

Q35 Q34

**ON A/C ALL 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

  EFF : ALL  34-14-00    CES

 

N10 N09 N08 N07 N06 N05 N04 N03

Page 502 Feb 01/10

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-14-00-860-055 C. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) On the overhead panel : - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - on the ADIRS CDU, make sure that the three OFF/NAV/ATT selector switches are at OFF. (3) Do the EIS start procedure (PFD and ND only) (Ref. TASK 31-60-00-860001). R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-14-00-860-055-A C. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) On the overhead panel : - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - on the ADIRS MSU, make sure that the three OFF/NAV/ATT selector switches are at OFF. (3) Do the EIS start procedure (PFD and ND only) (Ref. TASK 31-60-00-860001).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-14-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 503 Feb 01/10

R

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-14-00-710-054 A. Operational Test of the Attitude/Heading (ATT/HDG) Switching Function ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU : - set the three OFF/NAV/ATT selector switches to NAV.

- push the ADR1, ADR2 and ADR3 pushbutton switches.

On the ADIRS CDU : - the ON BAT light comes on for 5 seconds - the three ALIGN legends come on. On the Captain and First Officer PFD : - the ATT flags go out of view after approximately 30 seconds - the pitch and roll attitudes are shown. - make sure that the OFF legends of the ADR1, ADR2 and ADR3 pushbutton switches are on.

2. On the center pedestal, on the SWITCHING panel 8VU, set the ATT HDG selector switch to CAPT/3. 3. On the ADIRS CDU, set the OFF/NAV/ATT selector switch related to the IR1 to OFF.

On the ADIRS CDU, the ALIGN legend of the IR1 annunciatior goes off On the Captain PFD, the pitch and roll attitudes stay in view.

4. On the center pedestal, on the SWITCHING panel 8VU, set the ATT HDG selector switch to NORM then to F/O/3.

On the Captain PFD, the ATT flag is shown (ignore the related warnings).

5. On the ADIRS CDU, set the OFF/NAV/ATT selector switch

- On the ADIRS CDU, the ALIGN legend of the IR2 annunciator goes off

  R EFF : ALL  34-14-00    CES

 

Page 504 May 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------related to the IR2 to OFF. - On the First Officer PFD, the pitch and roll attitudes stay in view. 6. On the center pedestal, on the SWITCHING panel 8VU, set the ATT HDG selector switch to NORM.

On the First Officer PFD, the ATT flag is shown (ignore the related warnings).

7. On the ADIRS CDU : - set the OFF/NAV/ATT selector switch related to the IR3 to OFF R

On the ADIRS CDU, the ALIGN legend of the IR3 annunciator goes off.

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-14-00-710-054-A A. Operational Test of the Attitude/Heading (ATT/HDG) Switching Function ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS MSU : - Set the three OFF/NAV/ATT selector switches to NAV.

- Push the ADR1, ADR2 and ADR3 pushbutton switches.

On the ADIRS MSU : - The ON BAT light comes on for 5 seconds. On the Captain and First Officer PFD : - The ATT flags go out of view after approximately 30 seconds. - The pitch and roll attitudes are shown. - Make sure that the OFF legends of the ADR1, ADR2 and ADR3 pushbutton switches are on.

2. On the center pedestal, on the SWITCHING panel 8VU, set the ATT HDG selector switch to CAPT/3. 3. On the ADIRS MSU, set the OFF/NAV/ATT selector switch related to the IR1 to OFF.

On the Captain PFD, the pitch and roll attitudes stay in view.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-14-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 505 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------4. On the center pedestal, on the On the Captain PFD, the ATT flag is SWITCHING panel 8VU, set the ATT shown (ignore the related warnings). HDG selector switch to NORM then to F/O/3. 5. On the ADIRS MSU, set the OFF/NAV/ATT selector switch related to the IR2 to OFF.

On the First Officer PFD, the pitch and roll attitudes stay in view.

6. On the center pedestal, on the SWITCHING panel 8VU, set the ATT HDG selector switch to NORM.

On the First Officer PFD, the ATT flag is shown (ignore the related warnings).

**ON A/C ALL 5. Close-up ________ Subtask 34-14-00-860-056 A. Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (3) Make sure that the work area is clean and clear of tool(s) and other items. (4) Put the aircraft back to the serviceable condition. Subtask 34-14-00-410-050 B. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform.

  EFF : ALL  34-14-00   R  CES

 

Page 506 May 01/08

TASK 34-14-00-710-004 Operational Test of the Attitude/Heading (ATT/HDG) Comparison Warning WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Refer to the MPD TASK: 341400-02 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

circuit breaker(s) safety clip(s) safety barriers access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 31-60-00-860-002 34-10-00-860-004

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure IR Alignment Procedure

  EFF : ALL  34-14-00   R  CES

 

Page 507 Feb 01/08

3. __________ Job Set-up Subtask 34-14-00-010-051 A. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-14-00-865-055 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

2GA 52GA

Q35 Q34

**ON A/C ALL 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY

  EFF : ALL  34-14-00   R  CES

 

Page 508 Feb 01/08

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

R R

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N10 N09 N08 N07 N06 N05 N04 N03

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-14-00-865-056 C. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-14-00-860-057 D. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) On the ADIRS CDU, make sure that the three OFF/NAV/ATT selector switches are at OFF.

  EFF : ALL  34-14-00    CES

 

Page 509 Feb 01/10

(4) On the FCU, on the CAPT and F/O EFIS control sections, set the mode selector switch to the ROSE-NAV . (5) On one MCDU, get the SYSTEM REPORT/TEST/NAV page. (Ref. TASK 31-32-00-860-010) (6) Put thesafety barriers in position around the RAT area. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-14-00-860-057-A D. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) On the ADIRS MSU, make sure that the three OFF/NAV/ATT selector switches are at OFF. (4) On the FCU, on the CAPT and F/O EFIS control sections, set the mode selector switch to the ROSE-NAV . (5) On one MCDU, get the SYSTEM REPORT/TEST/NAV page. (Ref. TASK 31-32-00-860-010) (6) Put the safety barriers in position around the RAT area.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-14-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 510 Feb 01/10

R

**ON A/C ALL 4. Procedure _________

R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-14-00-710-055 A. Operational Test of the Attitude/Heading (ATT/HDG) Comparison Warning ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU, set the OFF/NAV/ATT selector switches related to the IR1 and IR2 to NAV. 2. Align the two ADIRUs (IR) (Ref. TASK 34-10-00-860-004). After approximately 5 minutes, the CAPT and F/O NDs show the heading dial. 3. On the MCDU, on the NAV page:

On the MCDU:

- push the line key adjacent to the IR1 indication

The IR1 page comes into view.

- push the line key adjacent to the INTERFACE TEST indication

The IR1 INTERFACE TEST 1/2 page comes into view.

- on the keyboard push the NEXT PAGE function key.

The IR1 INTERFACE TEST 2/2 page comes into view.

- push the line key adjacent to the START TEST indication

After two seconds : - the CAPT PFD shows this position : ROLL 45⁰ Right. PITCH 5⁰ Up. - the CAPT ND shows this position : HDG 15⁰. NOTE : Only the test values used for ____ comparison in the FWC are shown.

  EFF : ALL  34-14-00    CES

 

Page 511 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT and F/O PFDs, the CHECK ATT indication flashes during a short time then stays stable On the CAPT and F/O NDs, the CHECK HDG indication comes into view On the upper ECAM display unit, these indications come into view : NAV HDG DISCREPANCY - HDG.............X CHECK - ATT HDG SWTG....AS RQRD NAV ATT DISCREPANCY - ATT.............X CHECK - ATT HDG SWTG....AS RQRD On the panels 130VU and 131VU, the MASTER CAUT lights come on You can hear the single chime. NOTE : If the aircraft heading is equal to 15 degrees, plus or minus 5 ____ degrees, the CHECK HDG and HDG DISCREPANCY indications do not come into view. - push the line key adjacent to the RETURN indication.

The test stops. The indications above go out of view. The attitude and heading indications come into view.

4. On the ADIRS CDU, set the OFF/NAV/ATT selector switches related to the IR1 and IR2 to OFF.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-14-00 201-239, 301-312, 401-499,   CES

 

Page 512 Feb 01/08

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-14-00-710-055-B A. Operational Test of the Attitude/Heading (ATT/HDG) Comparison Warning ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS MSU, set the OFF/NAV/ATT selector switches related to the IR1 and IR2 to NAV. 2. Align the two ADIRUs (IR) (Ref. TASK 34-10-00-860-004). After approximately 5 minutes, the CAPT and F/O NDs show the heading dial. 3. On the MCDU, on the NAV page:

On the MCDU:

- Push the line key adjacent to the IR1 indication.

The IR1 page comes into view.

- Push the line key adjacent to the INTERFACE TEST indication.

The IR1 INTERFACE TEST 1/2 page comes into view.

- On the keyboard push the NEXT PAGE function key.

The IR1 INTERFACE TEST 2/2 page comes into view.

- Push the line key adjacent to the START TEST indication.

After two seconds: - The CAPT PFD shows this position: ROLL 45⁰ Right. PITCH 5⁰ Up. - The CAPT ND shows this position : HDG 15⁰. NOTE : Only the test values used for ____ comparison in the FWC are shown. On the CAPT and F/O PFDs, the CHECK ATT indication flashes during a short time then stays stable.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-14-00 511-526, 528-599,   CES

 

Page 513 Feb 01/10

R R R R R R R R R R R R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT and F/O NDs, the CHECK HDG indication comes into view. On the upper ECAM display unit, these indications come into view: NAV HDG DISCREPANCY - HDG.............X CHECK - ATT HDG SWTG....AS RQRD NAV ATT DISCREPANCY - ATT.............X CHECK - ATT HDG SWTG....AS RQRD On the F/O and CAPT glareshield panels 130VU and 131VU, the MASTER CAUT lights come on. You can hear the single chime.

R R R

NOTE : If the aircraft heading is equal to 15 degrees, plus or minus 5 ____ degrees, the CHECK HDG and HDG DISCREPANCY indications do not come into view.

R R R R

- Push the line key adjacent to the RETURN indication.

R R R R

4. On the ADIRS MSU, set the OFF/NAV/ATT selector switches related to the IR1 and IR2 to OFF.

R

**ON A/C ALL

The test stops. The indications above go out of view. The attitude and heading indications come into view.

5. Close-up ________ Subtask 34-14-00-860-058 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the MCDU MENU mode key. (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002) potentiometers to OFF.

  EFF : ALL  34-14-00    CES

 

Page 514 Feb 01/08

(3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Make sure that the work area is clean and clear of tool(s) and other items. (5) Put the aircraft back to the serviceable condition. R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-14-00-865-057 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 7XE, 5CC1, 5CC2 **ON A/C ALL Subtask 34-14-00-410-051 C. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform.

  EFF : ALL  34-14-00    CES

 

Page 515 Feb 01/10

TASK 34-14-00-740-001 Interface Test of the IR 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 31-60-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure

3. __________ Job Set-up Subtask 34-14-00-010-052 A. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: - loosen the two screws and remove the protective cover.

  R EFF : ALL  34-14-00    CES

 

Page 516 Feb 01/08

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-14-00-860-050 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (PFD and ND only) (Ref. TASK 31-60-00-860001). (3) On the overhead panel : - on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - on the panel 20VU, on the ADIRS CDU, make sure that the three OFF/NAV/ATT selector switches are at OFF. (4) On the panel 13VU, on the CAPT and F/O EFIS control sections of the FCU, set the mode selector switch to ROSE-NAV . (5) On the MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). NOTE : This test is for the system 1. For the systems 2 and 3, use ____ the indications between the parentheses. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-14-00-860-050-A B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (PFD and ND only) (Ref. TASK 31-60-00-860001).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-14-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 517 Feb 01/10

R R R R R R

(3) On the overhead panel: - On the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC and SEC pushbutton switches are not pushed (in). The OFF legends are on. - On the overhead panel 20VU, on the ADIRS MSU, make sure that the three OFF/NAV/ATT selector switches are at OFF.

R R

(4) On the glareshield panel 13VU, on the CAPT and F/O EFIS control sections of the FCU, set the mode selector switch to ROSE-NAV .

R R

(5) On the MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010).

R R R

NOTE : This test is for the system 1. For the systems 2 and 3, use ____ the indications between the parentheses. **ON A/C ALL Subtask 34-14-00-865-058 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FCU/1 9CA1 B05 49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 051-061, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

  R EFF : ALL  34-14-00    CES

 

N11 N10 N09 N08 N07 N06 N05 N04

Page 518 Feb 01/08

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C ALL 121VU AUTO FLT/FCU/2 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY R R

M21 Q35 Q34

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

R R

9CA2 2GA 52GA

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N10 N09 N08 N07 N06 N05 N04 N03

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-14-00-865-059 D. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 121VU AUTO FLT/FAC2/28VDC 5CC2 M19

  EFF : ALL  34-14-00    CES

 

Page 519 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, Subtask 34-14-00-869-072 A. General NOTE : In the test that follows, we use the name DDRMI for the VOR/DME ____ RMI and the VOR/ADF/DME RMI (refer to the equipment on your aircraft). **ON A/C 001-049, 101-105, 151-199, 201-210, 308-312, Subtask 34-14-00-740-068-A B. BITE Test of the IR System ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU: R R R

- set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to NAV.

On the ADIRS CDU: - the ON BAT light comes on for 5 seconds, - the ALIGN legend of the IR1 (IR2) (IR3) annunciator comes on.

- set the DATA DISPLAY selector switch to TK/GS, - set the SYS DISPLAY selector switch to 1 (2) (3). 2. On one MCDU, on the NAV page:

On the MCDU:

- push the line key adjacent to the IR1 (IR2) (IR3) indication.

The IR1 (IR2) (IR3) page comes into view.

- push the line key adjacent to the INTERFACE TEST indication.

The IR1 (IR2) (IR3) INTERFACE TEST 1/2 page comes into view.

  EFF : ALL  34-14-00    CES

 

Page 520 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- on the keyboard, push the The IR1 (IR2) (IR3) INTERFACE TEST 2/2 function key to get to the page comes into view. INTERFACE TEST 2/2 page. - push the line key adjacent to the START TEST indication.

- from 0 to 2 seconds: * on the ADIRS CDU, the ON BAT light, the ALIGN (if the IRs are aligned) and FAULT legends come on then go off, - from 2 seconds and more: * on the CAPT (F/O) PFD, the HDG warning flag is no more shown and these values come into view: ROLL 45 deg. Right PITCH 5 deg. Up. SLIP Left IVS -600 ft/mn. * on the CAPT (F/O) ND, the HDG warning flag is no more shown, * on the DDRMI, the HDG warning flag is no more shown, * the CAPT (F/O) ND shows these values: G/S 200 Kts WIND 030/100 HDG 15 deg. * the DDRMI shows this value: HDG 15 deg. * on the ADIRS CDU, the left part of the display window shows this track angle true value: 00.0 The right part of the display window shows this ground speed value: 0200

3. On the ADIRS CDU, set the DATA DISPLAY selector switch to HDG.

On the ADIRS CDU, the left part of the display window shows this true HDG value: 010.0

4. On the MCDU, push the line key adjacent to the RETURN indication.

The test procedure stops.

  R EFF : 001-049, 101-105, 151-199, 201-210,  34-14-00 308-312,   CES

 

Page 521 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------5. On the ADIRS CDU: On the ADIRS CDU: R R R

- set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to OFF, - set the OFF/NAV/ATT selector switch related to the IR2 to NAV.

- the ON BAT light comes on for 5 seconds, - the related ALIGN legend comes on.

6. Do the IR2 test as written in para. 2.

You must get the same results only on the F/O PFD and ND and on the ADIRS CDU (no indication on the DDRMI).

7. On the ADIRS CDU:

On the ADIRS CDU:

- set the OFF/NAV/ATT selector switch related to the IR2 to OFF, - set the OFF/NAV/ATT selector switch related to the IR3 to NAV.

- the ON BAT light comes on for 5 seconds, - the related ALIGN legend comes on.

8. On the center pedestal, on the SWITCHING panel 8VU, set the ATT/HDG selector switch to CAPT/3. 9. Do the IR3 test as written in para. 2.

You must get the same results as for the IR1 on the CAPT PFD and ND, the ADIRS CDU and the DDRMI.

10. On the ADIRS CDU, set the OFF/NAV/ATT selector switch related to the IR3 to OFF.

  EFF : 001-049, 101-105, 151-199, 201-210,  34-14-00 308-312,   CES

 

Page 522 Feb 01/10

**ON A/C 051-099, 106-149, 211-239, 301-307, 401-499, Subtask 34-14-00-740-068-B B. BITE Test of the IR System ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS CDU: R R R

- set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to NAV.

On the ADIRS CDU: - the ON BAT light comes on for 5 seconds, - the ALIGN legend of the IR1 (IR2) (IR3) annunciator comes on.

- set the DATA DISPLAY selector switch to TK/GS, - set the SYS DISPLAY selector switch to 1 (2) (3). 2. On one MCDU, on the NAV page:

On the MCDU:

- push the line key adjacent to the IR1 (IR2) (IR3) indication.

The IR1 (IR2) (IR3) page comes into view.

- push the line key adjacent to the INTERFACE TEST indication.

The IR1 (IR2) (IR3) INTERFACE TEST 1/2 page comes into view.

- on the keyboard, push the function key to get the INTERFACE TEST 2/2 page.

The IR1 (IR2) (IR3) INTERFACE TEST 2/2 page comes into view.

- push the line key adjacent to the START TEST indication.

- from 0 to 2 seconds: * on the ADIRS CDU, the ON BAT light, the ALIGN (if the IRs are aligned) and FAULT legends and the ENT and CLR keys come on then go off, - from 2 seconds and more: * on the CAPT (F/O) PFD, the HDG warning flag is no more shown and these values come into view: ROLL 45 deg. Right PITCH 5 deg. Up. SLIP Left

  EFF : 051-099, 106-149, 211-239, 301-307,  34-14-00 401-499,   CES

 

Page 523 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------IVS -600 ft/mn. * on the CAPT (F/O) ND, the HDG warning flag is no more shown, * on the DDRMI, the HDG warning flag is no more shown, * the CAPT (F/O) ND shows these values: G/S 200 Kts WIND 030/100 HDG 15 deg. * the DDRMI shows this value: HDG 15 deg. * on the ADIRS CDU, the left part of the display window shows this track angle true value: 00.0 The right part of the display window shows this ground speed value: 0200 3. On the ADIRS CDU, set the DATA DISPLAY selector switch to HDG.

On the ADIRS CDU, the left part of the display window shows this true HDG value: 010.0

4. On the MCDU, push the line key adjacent to the RETURN indication.

The test procedure stops.

5. On the ADIRS CDU:

On the ADIRS CDU:

R R R

- set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to OFF, - set the OFF/NAV/ATT selector switch related to the IR2 to NAV.

- the ON BAT light comes on for 5 seconds, - the related ALIGN legend comes on.

6. Do the IR2 test as written in para. 2.

You must get the same results only on the F/O PFD and ND and on the ADIRS CDU (no indication on the DDRMI).

7. On the ADIRS CDU:

On the ADIRS CDU:

  EFF : 051-099, 106-149, 211-239, 301-307,  34-14-00 401-499,   CES

 

Page 524 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set the OFF/NAV/ATT selector switch related to the IR2 to OFF, - set the OFF/NAV/ATT selector switch related to the IR3 to NAV.

- the ON BAT light comes on for 5 seconds, - the related ALIGN legend comes on.

8. On the center pedestal, on the SWITCHING panel 8VU, set the ATT/HDG selector switch to CAPT/3. 9. Do the IR3 test as written in para. 2.

You must get the same results as for the IR1 on the CAPT PFD and ND, the ADIRS CDU and the DDRMI.

10. On the ADIRS CDU, set the OFF/NAV/ATT selector switch related to the IR3 to OFF. **ON A/C 240-249, Subtask 34-14-00-740-068-D B. BITE Test of the IR System ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS MSU:

On the ADIRS MSU:

R R R R

- Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to NAV.

- The ON BAT light comes on for 5 seconds. - The FAULT legend of the IR1 (IR2) (IR3) pushbutton switch is off.

R R

- Push the IR1, IR2 and IR3 pushbutton switches.

- The OFF legend of the IR1, IR2 and IR3 pushbutton switches comes on.

  EFF : 051-099, 106-149, 211-249, 301-307,  34-14-00 401-499,   CES

 

Page 525 Feb 01/10

R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the IR1, IR2 and IR3 pushbutton switches again. 2. On one MCDU, on the NAV page:

On the MCDU:

- Push the line key adjacent to the IR1 (IR2) (IR3) indication.

The IR1 (IR2) (IR3) page comes into view.

- Push the line key adjacent to the INTERFACE TEST indication.

The IR1 (IR2) (IR3) INTERFACE TEST 1/2 page comes into view.

- On the keyboard, push the function key to get the INTERFACE TEST 2/2 page.

The IR1 (IR2) (IR3) INTERFACE TEST 2/2 page comes into view.

- Push the line key adjacent to the START TEST indication.

- After 0 to 2 seconds: * On the ADIRS MSU, the ON BAT light and FAULT legends come on then go off. - After 2 seconds and more: * On the CAPT (F/O) PFD, the HDG warning flag is no more shown and these values come into view: ROLL 45 deg. Right PITCH 5 deg. Up. SLIP Left IVS -600 ft/mn. * On the CAPT (F/O) ND, the HDG warning flag is no more shown. * On the DDRMI, the HDG warning flag is no more shown. * The CAPT (F/O) ND shows these values: G/S 200 Kts WIND 030/100 HDG 15 deg. * the DDRMI shows this value: HDG 15 deg.

3. On the MCDU, push the line key adjacent to the RETURN indication.

The test procedure stops.

4. On the ADIRS MSU:

On the ADIRS MSU:

  EFF : 240-249,  34-14-00    CES

 

Page 526 Feb 01/10

R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to OFF. - Set the OFF/NAV/ATT selector switch related to the IR2 to NAV.

- The ON BAT light comes on for 5 seconds.

5. Do the IR2 test as written in para. 2.

You must get the same results only on the F/O PFD and ND and on the ADIRS MSU (no indication on the DDRMI).

6. On the ADIRS MSU:

On the ADIRS MSU:

- Set the OFF/NAV/ATT selector switch related to the IR2 to OFF. - Set the OFF/NAV/ATT selector switch related to the IR3 to NAV.

- The ON BAT light comes on for 5 seconds.

7. On the center pedestal, on the SWITCHING panel 8VU, set the ATT/HDG selector switch to CAPT/3. 8. Do the IR3 test as written in para. 2.

You must get the same results as for the IR1 on the CAPT PFD and ND, the ADIRS MSU and the DDRMI.

9. On the ADIRS MSU, set the OFF/NAV/ATT selector switch related to the IR3 to OFF.

  R EFF : 240-249,  34-14-00    CES

 

Page 527 Feb 01/10

R

**ON A/C 251-299, 501-509, 511-523, Subtask 34-14-00-740-068-E B. BITE Test of the IR System ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS MSU:

On the ADIRS MSU:

R R R

- Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to NAV.

- The ON BAT light comes on during 5 seconds. - The FAULT legend of the IR1 (IR2) (IR3) pushbutton switch is off.

R R

- Push the IR1, IR2 and IR3 pushbutton switches.

- The OFF legend of the IR1, IR2 and IR3 pushbutton switches comes on.

R R

- Push the IR1, IR2 and IR3 pushbutton switches again. 2. On one MCDU, on the NAV page:

On the MCDU:

- Push the line key adjacent to the IR1 (IR2) (IR3) indication.

The IR1 (IR2) (IR3) page comes into view.

- Push the line key adjacent to the INTERFACE TEST indication.

The IR1 (IR2) (IR3) INTERFACE TEST 1/2 page comes into view.

- On the keyboard, push the function key to get the INTERFACE TEST 2/2 page.

The IR1 (IR2) (IR3) INTERFACE TEST 2/2 page comes into view.

- Push the line key adjacent to the START TEST indication.

- After 0 to 2 seconds: * On the ADIRS MSU, the ON BAT light and FAULT legends come on then go off. - After 2 seconds: * On the CAPT (F/O) PFD, the HDG warning flag is no more shown and the values that follow come into view: ROLL 45 deg. Right PITCH 5 deg. Up. SLIP Left

  R EFF : 251-299, 501-509, 511-523,  34-14-00    CES

 

Page 528 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------IVS -600 ft/mn. * On the CAPT (F/O) ND, the HDG warning flag is no more shown. * The CAPT (F/O) ND shows the values that follow: G/S 200 Kts WIND 030/100 HDG 15 deg. 3. On the MCDU, push the line key adjacent to the RETURN indication.

The test procedure stops.

4. On the ADIRS MSU:

On the ADIRS MSU:

R R R

- Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to OFF. - Set the OFF/NAV/ATT selector switch related to the IR2 to NAV.

- The ON BAT light comes on during 5 seconds.

5. Do the IR2 test given in Para. 2.

You must get the same results only on the F/O PFD and ND, and on the ADIRS MSU.

6. On the ADIRS MSU:

On the ADIRS MSU:

- Set the OFF/NAV/ATT selector switch related to the IR2 to OFF. - Set the OFF/NAV/ATT selector switch related to the IR3 to NAV.

- The ON BAT light comes on during 5 seconds.

7. On the center pedestal, on the SWITCHING panel 8VU, set the ATT/HDG selector switch to CAPT/3.

  R EFF : 251-299, 501-509, 511-523,  34-14-00    CES

 

Page 529 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------8. Do the IR3 test given in Para. 2. You must get the same results as for the IR1 on the CAPT PFD and ND, and on the ADIRS MSU. 9. On the ADIRS MSU, set the OFF/NAV/ATT selector switch related to the IR3 to OFF. **ON A/C 313-399, Subtask 34-14-00-740-068-F B. BITE Test of the IR System ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ADIRS MSU:

On the ADIRS MSU:

R R R

- Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to NAV.

- The ON BAT light comes on for 5 seconds. - The FAULT legend of the IR1 (IR2) (IR3) pushbutton switch is off.

R R

- Push the IR1, IR2 and IR3 pushbutton switches.

- The OFF legend of the IR1, IR2 and IR3 pushbutton switches comes on.

R R

- Push the IR1, IR2 and IR3 pushbutton switches again. 2. On one MCDU, on the NAV page:

On the MCDU:

- Push the line key adjacent to the IR1 (IR2) (IR3) indication.

The IR1 (IR2) (IR3) page comes into view.

- Push the line key adjacent to the INTERFACE TEST indication.

The IR1 (IR2) (IR3) INTERFACE TEST 1/2 page comes into view.

- On the keyboard, push the function key to get to the INTERFACE TEST 2/2 page.

The IR1 (IR2) (IR3) INTERFACE TEST 2/2 page comes into view.

  R EFF : 251-299, 313-399, 501-509, 511-523,  34-14-00    CES

 

Page 530 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Push the line key adjacent to - After 0 to 2 seconds: the START TEST indication. * On the ADIRS MSU, the ON BAT light and FAULT legends come on then go off. - After 2 seconds and more: * On the CAPT (F/O) PFD, the HDG warning flag is no more shown and these values come into view: ROLL 45 deg. Right PITCH 5 deg. Up. SLIP Left IVS -600 ft/mn. * On the CAPT (F/O) ND, the HDG warning flag is no more shown. * On the DDRMI, the HDG warning flag is no more shown. * The CAPT (F/O) ND shows these values: G/S 200 Kts WIND 030/100 HDG 15 deg. * The DDRMI shows this value: HDG 15 deg. 3. On the MCDU, push the line key adjacent to the RETURN indication.

The test procedure stops.

4. On the ADIRS MSU:

On the ADIRS MSU:

R R R

- Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to OFF. - Set the OFF/NAV/ATT selector switch related to the IR2 to NAV.

- The ON BAT light comes on for 5 seconds.

5. Do the IR2 test as written in para. 2.

You must get the same results only on the F/O PFD and ND and on the ADIRS MSU (no indication on the DDRMI).

6. On the ADIRS MSU:

On the ADIRS MSU:

  EFF : 313-399,  34-14-00    CES

 

Page 531 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set the OFF/NAV/ATT selector switch related to the IR2 to OFF. - set the OFF/NAV/ATT selector switch related to the IR3 to NAV.

- The ON BAT light comes on for 5 seconds.

7. On the center pedestal, on the SWITCHING panel 8VU, set the ATT/HDG selector switch to CAPT/3. 8. Do the IR3 test as written in para. 2.

You must get the same results as for the IR1 on the CAPT PFD and ND, the ADIRS MSU and the DDRMI.

9. On the ADIRS MSU, set the OFF/NAV/ATT selector switch related to the IR3 to OFF. R

**ON A/C 524-526, 528-599,

R

Subtask 34-14-00-740-068-G

R

B. BITE Test of the IR System

R R R

------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------

R

1. On the ADIRS MSU:

On the ADIRS MSU:

R R R R

- Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to NAV.

- The ON BAT light comes on for 5 seconds. - The FAULT legend of the IR1 (IR2) (IR3) pushbutton switch is off.

R R

- Push the IR1, IR2 and IR3 pushbutton switches.

- The OFF legend of the IR1, IR2 and IR3 pushbutton switches comes on.

R R

- Push the IR1, IR2 and IR3 pushbutton switches again.

  R EFF : 313-399, 524-526, 528-599,  34-14-00    CES

 

Page 532 Feb 01/10

R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------2. On one MCDU, on the NAV page: On the MCDU:

R R

- Push the line key adjacent to the IR1 (IR2) (IR3) indication.

The IR1 (IR2) (IR3) page comes into view.

R R

- Push the line key adjacent to the INTERFACE TEST indication.

The IR1 (IR2) (IR3) INTERFACE TEST 1/2 page comes into view.

R R R

- On the keyboard, push the function key to get the INTERFACE TEST 2/2 page.

The IR1 (IR2) (IR3) INTERFACE TEST 2/2 page comes into view.

R R R R R R R R R R R R R R R R R R R R R

- Push the line key adjacent to the START TEST indication.

- After 0 to 2 seconds: * On the ADIRS MSU, the ON BAT light and FAULT legends come on then go off. - After 2 seconds and for around 20 seconds: * On the CAPT (F/O) PFD, the HDG warning flag is no more shown and these values that follow come into view: ROLL 45 deg. Right PITCH 5 deg. Up. SLIP Left IVS -600 ft/mn. * On the CAPT (F/O) ND, the HDG warning flag is no more shown. * The CAPT (F/O) ND shows these values: G/S 200 Kts WIND 030/100 HDG 15 deg.

R R R R R R R R

NOTE : If all cheks have not been ____ performed when the interface test automatically exits, then IR interface test again as described in (2) and resume the procedure where it was stopped. 3. On the MCDU, push the line key adjacent to the RETURN indication

The test procedure stops.

  R EFF : 524-526, 528-599,  34-14-00    CES

 

Page 533 Feb 01/10

R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------or wait until the test automatically exits.

R

4. On the ADIRS MSU:

R R R

- Set the OFF/NAV/ATT selector switch related to the IR1 (IR2) (IR3) to OFF.

R R R

- Set the OFF/NAV/ATT selector switch related to the IR2 to NAV.

On the ADIRS MSU:

- The ON BAT light comes on for 5 seconds.

R R R

5. Do the IR2 test as written in para. 2.

You must get the same results only on the F/O PFD and ND and on the ADIRS MSU.

R

6. On the ADIRS MSU:

On the ADIRS MSU:

R R R

- Set the OFF/NAV/ATT selector switch related to the IR2 to OFF.

R R R

- Set the OFF/NAV/ATT selector switch related to the IR3 to NAV.

R R R R

7. On the center pedestal, on the SWITCHING panel 8VU, set the ATT/HDG selector switch to CAPT/3.

R R R

8. Do the IR3 test as written in para. 2.

R R R

9. On the ADIRS MSU, set the OFF/NAV/ATT selector switch related to the IR3 to OFF.

- The ON BAT light comes on for 5 seconds.

You must get the same results as for the IR1 on the CAPT PFD and ND, the ADIRS MSU.

  R EFF : 524-526, 528-599,  34-14-00    CES

 

Page 534 Feb 01/10

**ON A/C ALL 5. Close-up ________ Subtask 34-14-00-860-051 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002) (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-14-00-865-060 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2 **ON A/C ALL Subtask 34-14-00-410-052 C. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform.

  R EFF : ALL  34-14-00    CES

 

Page 535 Feb 01/10

**ON A/C 001-049, 101-105, 151-199, 201-203, TASK 34-14-00-740-002 Read CFDIU for IR CURRENT STATUS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-14-00-010-053 A. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822.

  EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00   R  CES

 

Page 536 Feb 01/10

(3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-14-00-860-053 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (ADIRU related to the installed ADM only) (Ref. TASK 34-10-00-860-002) Subtask 34-14-00-865-061 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FCU/1 9CA1 B05 49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 121VU AUTO FLT/FCU/2 9CA2 M21 **ON A/C 001-049, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

2GA 52GA

Q35 Q34

**ON A/C 001-049, 101-105, 151-199, 201-203, 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY

  EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00   R  CES

 

Page 537 Feb 01/10

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 151-199, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N10 N09 N08 N07 N06 N05 N04 N03

**ON A/C 001-049, 101-105, 151-199, 201-203, Subtask 34-14-00-865-062 D. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 4. Procedure _________ Subtask 34-14-00-740-064 A. Do the Operational Test of the CURRENT STATUS ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the center pedestal, on one MCDU: 1. Get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010).

The SYSTEM REPORT/TEST/NAV page comes into view.

2. On the NAV page

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00    CES

 

Page 538 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the IR1 (IR2) (IR3) page comes into the IR1 (IR2) (IR3) indication view. (related to the removed ADM) - push the line key adjacent to the CURRENT STATUS indication.

- the IR1 (IR2) (IR3) CURRENT STATUS 1/8 page comes into view. - if there is no defect found after the new ADM is installed, the NO FAULTS indication comes into view.

5. Close-up ________ Subtask 34-14-00-860-054 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the MCDU, push the line key adjacent to the RETURN indication until the MCDU MENU page comes into view. (2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-14-00-865-063 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2 Subtask 34-14-00-410-053 C. Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform.

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-14-00    CES

 

Page 539 Feb 01/10

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, TASK 34-14-00-740-003 Read CFDIU for IR INPUT STATUS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-001 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST Menu Page ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-14-00-010-054 A. Get Access (1) Put the access platform in position at the access door 822. (2) Open the access door 822.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 540 Feb 01/10

(3) On the battery power center 105VU: - loosen the two screws and remove the protective cover. Subtask 34-14-00-860-059 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (ADIRU related to the installed ADM only) (Ref. TASK 34-10-00-860-002) Subtask 34-14-00-865-064 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FCU/1 9CA1 B05 49VU L/G/LGCIU/SYS1/NORM 1GA C09 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 051-061, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU R R

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU AUTO FLT/FCU/2 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY

9CA2 2GA 52GA

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

M21 Q35 Q34

Page 541 Feb 01/10

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 062-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

R R

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N10 N09 N08 N07 N06 N05 N04 N03

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-14-00-865-065 D. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 4. Procedure _________ Subtask 34-14-00-740-065 A. Read the CFDIU for the IR INPUT STATUS NOTE : This test is for the system 1. For the systems 2 and 3, use the ____ indications between the parentheses. The actions and the results of this procedure occur on the MCDU used.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 542 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the center pedestral, on one MCDU: 1. Get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860001).

The SYSTEM REPORT/TEST/NAV page comes into view.

2. On the NAV page - Push the line key adjacent to the IR1 (IR2) (IR3) indication

- the IR1 (IR2) (IR3) page comes into view.

3. Push the line key adjacent to the INPUT STATUS indication

- the INPUT STATUS page 1/6 comes into view with the current on-the-ground status of the IR1 (IR2) (IR3) inputs.

4. Push the NEXT PAGE function key to get the INPUT STATUS page 2/6 to 6/6

- the related pages come into view.

5. Push the line key adjacent to the RETURN indication

- the test procedure stops.

5. Close-up ________ Subtask 34-14-00-860-060 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the MCDU, push the line key adjacent to the RETURN indication until the MCDU MENU page comes into view. (2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-14-00-865-066 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 543 Feb 01/10

Subtask 34-14-00-410-054 C. Close Access (1) Install the protective cover on the battery power center 105VU: (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-14-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 544 Feb 01/10

**ON A/C ALL TASK 34-14-00-740-004 SYSTEM TEST of the Inertial Reference (IR) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up **ON A/C 001-049, 101-105, 151-199, 201-210, 301-399, 401-499, Subtask 34-14-00-860-061 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002) (2) Do the Air Data/Inertial Reference System (ADIRS) start procedure (Ref. TASK 34-10-00-860-002). (3) Get the SYSTEM REPORT/TEST NAV menu page (Ref. TASK 31-32-00-860010).

  EFF : ALL  34-14-00   R  CES

 

Page 545 Feb 01/10

Subtask 34-14-00-865-067 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07 49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06 105VU ADIRS/ADIRU1/28VDC 6FP1 C02 **ON A/C 001-049, 101-105, 201-203, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N11 N10 N09 N08 N07 N06 N05 N04

10FP 9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N10 N09 N08 N07 N06 N05 N04 N03

**ON A/C 151-199, 204-210, 301-399, 401-499, 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU/2PWR/SHED ADIRS/ADIRU/3PWR/SWTG ADIRS/ADIRU/2/26VAC AND AOA ADIRS/ADIRU/3/26VAC AND AOA ADIRS/ADIRU/2/115VAC ADIRS/ADIRU/3/115VAC ADIRS/ADIRU/2/28VDC ADIRS/ADIRU/3/28VDC

  R EFF : 001-049, 101-105, 151-199, 201-210,  34-14-00 301-399, 401-499,   CES

 

Page 546 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 101-105, 151-199, 201-210, Subtask 34-14-00-740-069 A. SYSTEM TEST of the Inertial Reference (IR) NOTE : - This test is for the system 1. For the systems 2 and 3, use the ____ indications between the parentheses. The actions and the results of this procedure occur on the Multipurpose Control and Display Unit (MCDU) used. - It is not necessary to do an IR alignment procedure before you start the IR SYSTEM TEST. - If the IRs are aligned before you start the IR SYSTEM TEST, a new alignment is necessary after the IR SYSTEM TEST (only if the ADIRUs must be operative, if not set the ADIRUs to off). ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Push the line key adjacent to the IR 1 (IR 2)(IR 3) indication

- the IR 1 (IR 2)(IR 3) page comes into view.

2. Push the line key adjacent to the SYSTEM TEST indication

- the IR 1 (IR 2)(IR 3) SYSTEM TEST page comes into view.

3. Push the line key adjacent to the START TEST indication

- the TEST IN PROGRESS 95 s indication comes into view - at the end of the test, the TEST OK indication comes into view.

4. Push the line key adjacent to the TEST CLOSE UP indication

- these indications come into view : * TEST CLOSE UP. IR RE-ALIGNMENT * ENTER PPOS WITH AN UNUSED MCDU - (Refer to the NOTE given above)

5. Push the line key adjacent to the RETURN indication

- the test procedure stops.

  EFF : ALL  34-14-00   R  CES

 

Page 547 Feb 01/10

R R

**ON A/C 051-099, 106-149, 211-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-14-00-740-069-A A. SYSTEM TEST of the Inertial Reference (IR) NOTE : - This test is for the system 1. For the systems 2 and 3, use the ____ indications between the parentheses. The actions and the results of this procedure occur on the Multipurpose Control and Display Unit (MCDU) used. - It is not necessary to do an IR alignment procedure before you start the IR SYSTEM TEST. - If the IRs are aligned before you start the IR SYSTEM TEST, a new alignment is necessary after the IR SYSTEM TEST (only if the ADIRUs must be operative, if not set the ADIRUs to off). ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the SYSTEM REPORT/TEST ATA 34 page, push the line key adjacent to the ATTITUDE indication

- the SYSTEM REPORT/TEST NAV:ATTITUDE page comes into view.

2. Push the line key adjacent to the IR 1 (IR 2)(IR 3) indication

- the IR 1 (IR 2)(IR 3) page comes into view.

3. Push the line key adjacent to the SYSTEM TEST indication

- the IR 1 (IR 2)(IR 3) SYSTEM TEST page comes into view.

4. Push the line key adjacent to the START TEST indication

- the TEST IN PROGRESS 40 s indication comes into view - at the end of the test, the TEST OK indication comes into view.

5. Push the line key adjacent to the TEST CLOSE UP indication

- these indications come into view : * TEST CLOSE UP. IR RE-ALIGNMENT * ENTER PPOS WITH THE OTHER MCDU - (Refer to the NOTE given above)

6. Push the line key adjacent to the RETURN indication

- the test procedure stops.

  EFF : 051-099, 106-149, 211-249, 251-299,  34-14-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 548 Feb 01/10

**ON A/C ALL 5. Close-up ________ **ON A/C 001-049, 101-105, 151-199, 201-210, 301-399, 401-499, Subtask 34-14-00-860-062 A. Put the Aircraft back to its Initial Configuration (1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (2) On the MCDU, push the line key adjacent to the RETURN indication until the MAINTENANCE MENU 1/2 page comes into view. (3) On the MCDU, set the BRT knob to OFF. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).

  EFF : ALL  34-14-00    CES

 

Page 549 Feb 01/10

INDICATOR - ANGLE OF ATTACK - REMOVAL/INSTALLATION __________________________________________________ TASK 34-15-21-400-001 Installation of the AOA Indicator (17FN1, 17FN2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information Not Applicable 3. __________ Job Set-up 4. Procedure _________ Subtask 34-15-21-860-051 A. Aircraft Maintenance Configuration (1) On the ADIRS MSU, set the OFF/NAV/ATT selector switch to NAV to start the ADIRU related to the AOA indicator. (2) Make sure that the flag goes out of view and that the angle of attack indication is 0 deg. 5. Close-up ________

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-15-21 511-526, 528-599,   CES

 

Page 401 Feb 01/10

R ADIRS - BITE - DESCRIPTION AND OPERATION ________________________________________ **ON A/C 001-049, 101-105, 151-199, 201-203, 1. _______ General The Built In Test Equipment facilitates maintenance on in-service aircraft. It detects and identifies faults related to the Air Data/Inertial Reference System (ADIRS) and reports them to the Centralized Fault Display Interface Unit (CFDIU). The BITE is included in the following LRUs: - Air Data/Inertial Reference Unit (ADIRU) - Air Data Module (ADM) - Control and Display Unit (CDU). It is linked to the CFDIU through the ADIRU (ADR and IR portions) which summarizes the BITE results for its own channel. (Ref. Fig. 001) The ADM performs various tests to detect its own faults (watchdog timer, RAM addressing, ROM, CPU, RAM, NVM etc.) and failed input signals (check of programming pins). Faults are annunciated to the ADR by omission or labeling of a faulty output word (pressure label) and through the use of a discrete fault-code word output on the ARINC bus. Fault reports are also stored in a non-volatile memory inside the ADM. The IR BITE monitors: the performance of the Digital Signal Processor C25 and the outputs of the INTEL 80960, external inputs (both digital and discrete), the functionality of other IR internal hardware including the power supply and the inertial sensors (gyro, accelerometers). These BITE tests are performed either at power up or continuously (Ref. Para. 3.A.(2)). Some of them enable to monitor operation errors. These tests are: Align in air, Excessive Motion, Latitude comparison test. They result in IR warnings but without fault message sent to the CFDIU. Tests and fault reactions are described in Para. 3.B. The ADR BITE monitors: the ADR outputs of the INTEL 80960 processor, the functionality of other ADR internal hardware, the status of analog, digital and discrete inputs and cross-channel comparisons with the other ADRs. These BITE tests are performed either at power-up or continuously (Ref. Para. 3.A.(3)) with the exception of cross-channel comparisons which are run once at takeoff. The common BITE monitors the computer performances: (INTEL 80960 processor and memories) with the following tests : watchdog timer, checksum, RAM pattern monitor.

  EFF : 001-049, 051-099, 101-149, 151-199,  34-18-00 Page 1 201-233, 236-238, 301-304, 401-402,  Config-1 May 01/08  CES

 

ADIRU - Architecture and Interface with CFDIU Figure 001   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 2   Config-1 May 01/05  CES

 

R R R R R R

The ADR and IR BITEs send reports to the CFDIU through the ARINC output bus, on label 356. These reports memorize the faults which occurred during the last 63 flight legs with their context. They operate in two modes: - NORMAL mode: fault reporting to the CFDIU during the flight - INTERACTIVE mode: on the ground. Access by the MCDU MENU pages (Ref. Para. 3.B.). 2. __________________ Component Location A. Computers Directly Linked to the CFDS ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1FP1 ADIRU-1 127 824 34-12-34 1FP2 ADIRU-2 128 824 34-12-34 1FP3 ADIRU-3 127 824 34-12-34 B. ADIRS Control Panel ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2FP CDU-ADIRS 20VU 211 831 34-12-12

  EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 3   Config-1 Feb 01/08  CES

 

C. Other LRUs of the System ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------3FP1 SENSOR-ANGLE OF ATTACK, 1 127 824 34-11-19 3FP2 SENSOR-ANGLE OF ATTACK, 2 128 824 34-11-19 3FP3 SENSOR-ANGLE OF ATTACK, 3 127 824 34-11-19 11FP1 SENSOR-TAT, 1 121 34-11-18 11FP2 SENSOR-TAT, 2 122 34-11-18 9DA1 PROBE-PITOT, 1 125 812 34-11-15 9DA2 PROBE-PITOT, 2 126 822 34-11-15 9DA3 PROBE-PITOT, 3 125 812 34-11-15 7DA1 PROBE-L STATIC, 1 127 824 34-11-16 7DA2 PROBE-L STATIC, 2 127 824 34-11-16 7DA3 PROBE-L STATIC, 3 121 811 34-11-16 8DA1 PROBE-R STATIC, 1 128 824 34-11-16 8DA2 PROBE-R STATIC, 2 128 824 34-11-16 8DA3 PROBE-R STATIC, 3 122 811 34-11-16 19FP1 ADM-L TOTAL PRESSURE NONE 125 812 34-11-17 19FP2 ADM-R TOTAL PRESSURE 126 822 34-11-17 19FP3 ADM-STBY TOTAL PRESSURE 125 812 34-11-17 19FP4 ADM-R STATIC PRESSURE 128 824 34-11-17 19FP5 ADM-L STATIC PRESSURE 127 824 34-11-17 19FP6 ADM-R STATIC PRESSURE 128 824 34-11-17 19FP7 ADM-L STATIC PRESSURE 127 824 34-11-17 19FP8 ADM-STBY STATIC PRESSURE 121 811 34-11-17

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 4   Config-1 May 01/05  CES

 

3. __________________ System Description A. Reporting Function Each ADIRS BITE message is described in the following pages, with the corresponding fault description and the consequences on the system and in the cockpit. (1) General - IR faults are classified as follows: . class 1 faults . class 2 faults . class 3 faults. - ADR faults: . class 1 faults . class 2 faults . class 3 faults. - Common faults (IR + ADR) . class 1 faults . class 2 faults . class 3 faults. NOTE : Bit 13 of ADR label 270 indicates an ADR fault (bit 13 = 1) ____ - use of i, j, k indexes in BITE messages: . barring explicit restriction, ADIRUi stands for ADIRU 1, ADIRU 2 or ADIRU 3 . ADMi, ADMj, or ADMk: i, j, and k values are specified below the message. - ECAM messages: . xxx stands for CAPT or F/O, depending on the ADIRU side (1 or 2) . the letter in parentheses indicates the color used to display the text: (A) Amber, (C) Cyan and (W) White. (2) Inertial reference faults -Class 1 External Faults (Ref. Fig. 002, 003) -Class 1 Internal Faults (Ref. Fig. 004, 005, 006, 007, 008, 009) -Class 2 External Faults R

**ON A/C 001-049, 101-105, 151-199, 201-203, Post SB

34-1147 For A/C 001-004, (Ref. Fig. 010)

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 5   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 1 External Faults 1/2 Figure 002   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 6   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 1 External Faults 2/2 Figure 003   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 7   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 1 Internal Faults 1/6 Figure 004   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 8   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 1 Internal Faults 2/6 Figure 005   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 9   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 1 Internal Faults 3/6 Figure 006   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 10   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 1 Internal Faults 4/6 Figure 007   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 11   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 1 Internal Faults 5/6 Figure 008   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 12   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 1 Internal Faults 6/6 Figure 009   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 13   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 2 External Faults Figure 010   R EFF : 001-049, 051-060, 101-105, 151-199,  34-18-00 Page 14 201-203,  Config-1 Aug 01/06  CES

 

R

**ON A/C 001-049, 101-105, 151-199, 201-203, -Class 2 Internal Faults (Ref. Fig. 011) -Class 3 External Faults (Ref. Fig. 012) -Class 3 Internal Faults (Ref. Fig. 013) The IR portion performs tests which result in warnings (fault annunciation, invalid outputs). But, for these warnings, no message is sent to the CFDIU as these faults are due to an incorrect operational use of the system and not to a system fault. These tests are: - align in air - position-entry test (comparison with the last stored position and computed latitude). - Test on motion (a) Align in air The test fails if, with the OFF/NAV/ATT selector switch on the CDU in NAV position, the aircraft is detected in flight (TAS greater than 100 kts) at power-up or during the ALIGN phase. The following occurs: - the NAV IRi FAULT message is displayed on the upper ECAM DU. - the FAULT legend of the IR annunciator, on the CDU, flashes. - all BNR output labels are coded Failure Warning (F/W) and all BCD labels are not transmitted. - the SELECT ATT indication is displayed on the CDU (DATA DISPLAY selector switch in STS position) The IR portion can be recovered by setting the OFF/NAV/ATT selector switch on the CDU to ATT and by applying the procedure (level flight) to initialize the ATT mode. (b) Position-entry test - Initial position (latitude, longitude) must compare within one degree of the last computed latitude and longitude from the previous flight. If a miscompare exists, then the NOT ALIGN message is displayed on the upper ECAM display unit with a text indicating to enter again the initial position (Ref. 34-14 Para. 3.). The miscompare is removed if the new entered position is identical to the previous one or is within the one-degree threshold. If not, the system waits for other position entry.

  R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 15   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 2 Internal Faults Figure 011   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 16   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 3 External Faults Figure 012   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 17   Config-1 May 01/05  CES

 

ADIRS BITE - IR System - Class 3 Internal Faults Figure 013   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 18   Config-1 May 01/05  CES

 

- At the end of the alignment submode, the IR portion compares the initial latitude to a self-computed latitude. The test fails and the NOT ALIGN message is displayed on the upper ECAM DU with action to enter again the position, when: . The difference between the entered latitude and the computed latitude is greater than 0,5⁰. The miscompare is removed if a subsequent entry of latitude passes the test. If the sin/cos test fails two times with identical initial latitude entries, the IR system goes in a fault reaction: IR FAULT warning message on the upper ECAM DU and FAULT legend on the CDU on, invalid outputs. (c) Test on motion If taxiing or towing causes a step input which exceeds 0.2 ft/s in the X or Y velocity, or 2⁰/s for the azimuth rate, the align process is stopped with a message on the upper ECAM DU indicating IR NOT ALIGN and excessive motion (Ref. 34-14) with the code NCD on the status matrix of the attitude (pitch, roll, heading) which implies a flag on the PFD. When the motion is no more detected, the IR reverts to the beginning of the align submode. It is not necessary to re-initialize the position. (3) Air Data Reference Faults .Class 1 External Faults (Ref. Fig. 014, 015) .Class 1 Internal Faults (Ref. Fig. 016, 017, 018, 019, 020, 021, 022, 023) .Class 2 Internal Faults (Ref. Fig. 024) .Class 3 Faults (Ref. Fig. 025) .Class 2 and 3 External Faults (Ref. Fig. 026)

R R R

(a) Cross-channel comparison tests A cross-channel comparison of pressures, angle-of-attack, and temperature parameters is performed to identify drifted air data input sensors. These tests are done for maintenance purpose only and they have no operational effects (no fault warning, output parameters are always valid, class 3 failures). To run these tests each ADR portion receives one ADR output bus of the other side, computers (Ref. Fig. 001) As the air data sensors are installed per design in different zones and measure different values, the comparison can only be done in an identified flight phase.

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ADIRS BITE - ADR System - Class 1 External Faults 1/2 Figure 014   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 20   Config-1 May 01/05  CES

 

ADIRS BITE - ADR System - Class 1 External Faults 2/2 Figure 015   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 21   Config-1 May 01/05  CES

 

ADIRS BITE - ADR System - Class 1 Internal Faults 1/8 Figure 016   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 22   Config-1 May 01/05  CES

 

ADIRS BITE - ADR System - Class 1 Internal Faults 2/8 Figure 017   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 23   Config-1 May 01/05  CES

 

ADIRS BITE - ADR System - Class 1 Internal Faults 3/8 Figure 018   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 24   Config-1 May 01/05  CES

 

ADIRS BITE - ADR System - Class 1 Internal Faults 4/8 Figure 019   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 25   Config-1 May 01/05  CES

 

ADIRS BITE - ADR System - Class 1 Internal Faults 5/8 Figure 020   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 26   Config-1 May 01/05  CES

 

ADIRS BITE - ADR System - Class 1 Internal Faults 6/8 Figure 021   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 27   Config-1 May 01/05  CES

 

ADIRS BITE - ADR System - Class 1 Internal Faults 7/8 Figure 022

R

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ADIRS BITE - ADR System - Class 1 Internal Faults 8/8 Figure 023   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 29   Config-1 Feb 01/08  CES

 

ADIRS BITE - ADR System - Class 2 Internal Faults Figure 024

R

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-18-00 Page 30 201-233, 236-238, 301-304, 401-402,  Config-1 Feb 01/08  CES

 

ADIRS BITE - ADR System - Class 3 Faults Figure 025   R EFF : 001-049, 051-099, 101-149, 151-199,  34-18-00 Page 31 201-233, 236-238, 301-304,  Config-1 May 01/08  CES

 

ADIRS BITE - ADR System - Class 2 and 3 External Faults Figure 026   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 32   Config-1 Feb 01/08  CES

 

The tests are performed at takeoff with a CAS between 90 and 200 kts and only if the received ADR data are valid. The thresholds used in the comparison are: -----------------------------------------------| Parameter | Threshold | |----------------------------------------------| | Total pressure | 5 hPa | | Averaged static pressure | 5 hPa | | Left static pressure | 2 hPa | | Right static pressure | 2 hPa | | Angle-of-attack | 4⁰ | | Total air temperature | 3⁰C | -----------------------------------------------Table 1 : Comparison Thresholds The messages resulting from a miscompare between parameters point the faulty sensor if it can be identified (one data differs from the two others which are identical) or the sensors which disagree. They are sent to the CFDIU in normal mode through label 356 of the ADR output and can be accessed by Class 3 Faults page on the MCDU menu. (4) Air Data and Inertial Reference Faults .Class 1 Internal Faults (Ref. Fig. 027) .Class 2 Internal Faults (Ref. Fig. 028) .Class 3 Faults (Ref. Fig. 029) .Faults without any message (Ref. Fig. 030, 031) B. Interactive Function (1) General The interactive mode is activated via the SYSTEM REPORT/TEST page ATA 34 chapter (Navigation) including Air Data and Inertial Reference System (ADIRS). As this system includes two parts (Air Data Reference and Inertial Reference), two interactive functions are available : (a) ADR interactive function : select NAV from the SYSTEM REPORT/TEST page and then the selected ADR (1 to 3) to activate the ADR interactive mode and display the main menu (Ref. Fig. 032)

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ADIRS BITE - ADR and IR Systems - Class 1 Internal Faults Figure 027   R EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 34   Config-1 Feb 01/08  CES

 

ADIRS BITE - ADR and IR Systems - Class 2 Internal Faults Figure 028   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 35   Config-1 Feb 01/08 R  CES

 

ADIRS BITE - ADR and IR Systems - Class 3 Faults Figure 029   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 36   Config-1 Feb 01/08 R  CES

 

ADIRS BITE - ADR and IR Systems - Faults without any Message 1/2 Figure 030   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 37   Config-1 Feb 01/08 R  CES

 

ADIRS BITE - ADR and IR Systems - Faults without any Message 2/2 Figure 031   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 38   Config-1 Feb 01/08 R  CES

 

ADIRS BITE - Activation of ADR Interactive Function Figure 032   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 39   Config-1 Feb 01/08 R  CES

 

(b) IR interactive function : select NAV from the SYSTEM REPORT/TEST page and then the selected IR (1 to 3) to activate the IR interactive mode and display the main menu (Ref. Fig. 033) NOTE : The figures enclosed in this document are provided for the ____ layout of the different pages. Fault messages, trouble shooting data and input discrete status are provided for information. (2) Air Data Interactive function description (a) Last Leg Report (Ref. Fig. 034) (b) Previous Legs Reports (Ref. Fig. 034) (c) LRU Ident (Ref. Fig. 034) On page 1/2, the Part Numbers and the Serial Numbers of the ADIRU and the total pressure ADM are displayed. On page 2/2, the associated data to the remaining ADM are displayed. (d) Ground Scanning (Ref. Fig. 035) The Ground Scanning function performs most of the continuous tests. All tests with an important time delay (temperature ...) are not performed within this function. (e) Trouble Shooting Data (Ref. Fig. 036) A maximum of sixteen 16-bit words can be recorded for the Trouble Shooting Data. (f) Class 3 Faults (Ref. Fig. 034) (g) System test (Ref. Fig. 037) The system test function performs power-up tests and various continuous tests to provide a complete status of the ADR part of the ADIRS. It is necessary to re-initialize the system for IR part because the navigation data are erased by the test of the RAM performed at the power-up.

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ADIRS BITE - Activation of IR Interactive Function Figure 033   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 41   Config-1 Feb 01/08 R  CES

 

ADIRS BITE - ADR Main Menu 1/2 Figure 034   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 42   Config-1 Feb 01/08 R  CES

 

ADIRS BITE - ADR Ground Scanning Figure 035   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 43   Config-1 Feb 01/08 R  CES

 

ADIRS BITE - ADR Main Menu 2/2 Figure 036   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 44   Config-1 Feb 01/08 R  CES

 

ADIRS BITE - ADR System Test Figure 037   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 45   Config-1 Feb 01/08 R  CES

 

(h) Output Tests The output tests are divided in three parts : - Slew tests - Interface test - AOA test. 1 _

Slew tests (Ref. Fig. 038) The Slew tests are divided in two parts : - Altitude dynamic slew This function slews the altitude (label 203) between the lower limit and the upper limit (up or down)) at the altitude slew rate. These data are entered by the operator. The altitude limit values are tested to be within -2000 and +50000 feet. The altitude lower limit is tested to be less than the altitude upper limit. The altitude slew rate is tested to be within 1 to +20000 ft/mn. - CAS dynamic slew This function slews the Computed Air Speed (label 206) between the lower limit and the upper limit (up or down) at the CAS slew rate. These data are entered by the operator. The CAS limit values are tested to be within 0 and +450 knots. The CAS lower limit is tested to be less than the CAS upper limit. The CAS slew rate is tested to be within 1 to +100 Kts/mn. When the upper (or lower) limit is reached at the end of the ramp (END OF SLEWING page), the limit value is maintained till the operator pushes the key adjacent to the RETURN or the ALT DYNAMIC SLEW indication.

2 _

Interface test (Ref. Fig. 039) Initiation of the ADR Interface Test causes the following sequence to occur : - 0-5 seconds (Failure Warning Test) For 0-5 seconds after initiation of the test mode, the ADR outputs are transmitted per tables as follows. Since this is the failure warning test period, the BCD output parameters are not transmitted and the SSM of the BNR parameters are set to F/W. Timing tolerance is plus or minus 0.5 second. - 5-10 seconds (Altitude Ramp Test)

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ADIRS BITE - ADR Slew Tests Figure 038   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 47   Config-1 Feb 01/08 R  CES

 

ADIRS BITE - ADR Interface Test Figure 039   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 48   Config-1 Feb 01/08 R  CES

 

For 5-10 seconds after initiation of the test mode the ADR outputs are transmitted per tables as follows. Since this is the altitude ramp test period, the altitude outputs are slewed in a positive direction for the entire 5-second period at a rate of 600 ft/min, starting at the ambient computed altitude. Timing tolerance is plus or minus 0.5 second. - 10 second until test completion (Fixed Output Test) From 10 seconds after initialization of the test mode until the test completion is commanded, the ADR outputs are transmitted per tables as follows, outputting the fixed values specified by these tables. Timing tolerance is +/0.5 second.

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ADR Interface test values are shown in the following tables: -----------------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |--------------------------------------| | | | 0 to 5 s | 5 to 10 s | Over 10 s | |----------------------------------------------------------------------| | 176 | LEFT STATIC PRESSURE | Last Valid | Last Valid | 696.8 hPa | | 177 | RIGHT STATIC PRESSURE | Last Valid | Last Valid | 696.8 hPa | | 203 | STANDARD ALTITUDE | Last Valid | Slewed | 10,000 ft | | 204 | BARO COR ALT 1 | Last Valid | Slewed | 10,000 ft | | 205 | MACH | 0 | 0 | 0.66 | | 206 | COMPUTED AIRSPEED | 0 Kts | 0 Kts | 367.7 Kts | | 207 | MAX ALLOWABLE AIRSPEED| Last Valid | Last Valid | Last Valid | | 210 | TRUE AIRSPEED | 0 Kts | 0 Kts | 433 Kts | | 211 | TOTAL AIR TEMP | Last Valid | Last Valid | 35⁰C | | 212 | ALTITUDE RATE | Last Valid | 600 ft/mn | 0 ft/mn | | 213 | STATIC AIR TEMP | Last Valid | Last Valid | 10.3 ⁰C | | 215 | IMPACT PRESSURE | Last Valid | Last Valid | 236.6 hPa | | 220 | BARO COR ALT 2 | Last Valid | Slewed | 10,000 ft | | 221 | IND ANGLE OF ATTACK | See note | See note | 5 ⁰ | | 241 | CORCTD ANGLE OF ATTACK| See note | See note | 5 ⁰ | | 242 | TOTAL PRESSURE | Last Valid | Last Valid | 933.4 hPa | | 245 | UNCRCTD AVG STAT PRESS| Last Valid | Last Valid | 696.8 hPa | | 246 | CORCTD AVG STAT PRESS | Last Valid | Last Valid | 696.8 hPa | | 251 | BARO CORR ALT 3 | Last Valid | Slewed | 10,000 ft | -----------------------------------------------------------------------NOTE : Indicated AOA is a function of the AOA sensor position. Corrected AOA is function of AOA alternate discrete inputs and indicated AOA. Table 2 : Output Binary Words

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-------------------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |----------------------------------------| | | | 0 to 5 s | 5 to 10 s | Over 10 s. | |------------------------------------------------------------------------| | 034 | BARO CORR (hPa) 3 |Not Transmit.| Last Valid | 1013.3 hPa | | 035 | BARO CORR (in.Hg) 3 |Not Transmit.| Last Valid | 29.92 in.Hg | | 230 | TRUE AIRSPEED |Not Transmit.| 0 Kts | 433 Kts | | 231 | TOTAL AIR TEMP |Not Transmit.| Last Valid | 35⁰C | | 232 | ALTITUDE RATE |Not Transmit.| 600 ft/min | 0 ft/min | | 233 | STATIC AIR TEMP |Not Transmit.| Last Valid | 10⁰C | | 234 | BARO CORR (hPa) 1 |Not Transmit.| Last Valid | 1013.3 hPa | | 235 | BARO CORR (in.Hg) 1 |Not Transmit.| Last Valid | 29.92 in.Hg | | 236 | BARO CORR (hPa) 2 |Not Transmit.| Last Valid | 1013.3 hPa | | 237 | BARO CORR (in.Hg) 2 |Not Transmit.| Last Valid | 29.92 in.HG | -------------------------------------------------------------------------Table 3 : Output BCD Words -------------------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | BIT - PARAMETER |----------------------------------------| | | | 0 to 5 s | 5 to 10 s | Over 10 s | |------------------------------------------------------------------------| | 270 | 13 - ADR FAULT | 1 | 0 | 0 | | 270 | 19 - OVERSPEED WARNING| 0 | 0 | 1 | | 271 | 13 - LOW SPD WARN 1 | 0 | 0 | 1 | | 271 | 14 - LOW SPD WARN 2 | 0 | 0 | 1 | | 271 | 15 - LOW SPD WARN 3 | 0 | 0 | 0 | | 271 | 16 - LOW SPD WARN 4 | 1 | 1 | 0 | -------------------------------------------------------------------------Table 4 : Output Discrete Words -------------------------------------------------------------------------| | SELF TEST VALUE | | PARAMETER |----------------------------------------| | | 0 to 5 s | 5 to 10 s | Over 10 s | |------------------------------------------------------------------------| | LOW SPEED WARNING 1 | OPEN | OPEN | GROUND | | LOW SPEED WARNING 2 | OPEN | OPEN | GROUND | | LOW SPEED WARNING 3 | OPEN | OPEN | OPEN | | LOW SPEED WARNING 4 | GROUND | GROUND | OPEN | | OVERSPEED WARNING | OPEN | OPEN | GROUND | | ADR FAULT | GROUND | OPEN | OPEN | | ADR OFF | GROUND | OPEN | OPEN | -------------------------------------------------------------------------Table 5 : Discrete Outputs

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3 _

AOA Test (Ref. Fig. 040) The AOA test function set the AOA test output discrete to command the AOA sensor to fixed position greater than the stall warning threshold. So, the Flight Warning Computer activates the aural stall warning.

(i) Ground Report (Ref. Fig. 035) (j) Current Status (Ref. Fig. 041) The Current Status function displays on 8 pages the state (as read by the computer) of the discrete inputs, digital inputs (ADM and baro-correction), analog inputs and power condition. (3) Inertial Interactive function description (a) Last Leg Report (Ref. Fig. 042) (b) Previous Legs Report (Ref. Fig. 042) (c) LRU Ident (Ref. Fig. 042) The Part Numbers and the Serial Numbers of the ADIRU are displayed. (d) Ground Scanning (Ref. Fig. 043) The Ground Scanning function performs most of the continuous tests .All tests with an important time delay (temperature ...) are not performed within this function. (e) Trouble Shooting Data (Ref. Fig. 043) A maximum of sixteen 16-bit words can be recorded for the Trouble Shooting Data. (f) Class 3 Fault (Ref. Fig. 042)

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ADIRS BITE - ADR AOA Test Figure 040   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 56   Config-1 Feb 01/07 R  CES

 

ADIRS BITE - ADR Current Status Figure 041   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 57   Config-1 Feb 01/07 R  CES

 

ADIRS BITE - IR Main Menu 1/3 Figure 042   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 58   Config-1 Feb 01/07 R  CES

 

ADIRS BITE - IR Main Menu 2/3 Figure 043   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 59   Config-1 Feb 01/07 R  CES

 

(g) System Test (Ref. Fig. 037) The system test function performs power-up tests and various continuous tests to provide a complete status of the IR part of the ADIRS. The layout of the System test pages of the ADR and IR parts are equivalent except of the title ADR which is replaced by IR. It is necessary to re-initialize the system because the navigation data are erased by the test of the RAM performed at the power-up. (h) Interface Test (Ref. Fig. 044) Initiation of the IR Interface Test shall cause the following sequence to occur: - 0-2 seconds BCD, BNR and Discrete Words - output with SSM set to Functional Test and data set as shown in next tables. Annunciator discretes shall be energized. - Over 2 seconds BCD, BNR and Discrete Words - output with SSM set to Functionnal Test and data set as shown in next tables. Annunciator discretes released to indicated status.

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ADIRS BITE - IR Interface Test Figure 044   EFF : 001-049, 101-105, 151-199, 201-203,  34-18-00 Page 61   Config-1 Feb 01/07 R  CES

 

----------------------------------------------------------------------| LABEL | PARAMETER | SELF TEST VALUE | |---------------------------------------------------------------------| 052 | PITCH ANGULAR ACCEL | 5.0⁰ /s/s | | 053 | ROLL ANGULAR ACCEL | 5.0⁰ /s/s | | 054 | YAW ANGULAR ACCEL | 5.0⁰ /s/s | | 310 | PRESENT POSITION LAT | N 22.50⁰ | | 311 | PRESENT POSITION LONG | E 22.50⁰ | | 312 | GROUND SPEED | 200 Kts | | 313 | TRACK ANGLE-TRUE | 00.0⁰ | | 314 | TRUE HEADING | 10.0⁰ | | 315 | WIND SPEED | 100 Kts | | 316 | WIND DIRECTION-TRUE | 30⁰ | | 317 | TRACK ANGLE-MAG | 5⁰ | | 320 | MAGNETIC HEADING | 15⁰ | | 321 | DRIFT ANGLE | -10⁰ (Left) | | 322 | FLIGHT PATH ANGLE | -5⁰ | | 323 | FLIGHT PATH ACCEL | 0.2g | | 324 | PITCH ANGLE | 5⁰ | | 325 | ROLL ANGLE | 45⁰ (Right) | | 326 | BODY AXIS PITCH RATE | 10⁰/s | | 327 | BODY AXIS ROLL RATE | 10⁰/s | | 330 | BODY AXIS YAW RATE | 10⁰/s | | 331 | BODY LONGIT ACCEL | 0.02g | | 332 | BODY LATERAL ACCEL | 0.10g | | 333 | BODY NORMAL ACCEL | 0.10g | | 334 | PLATFORM HEADING | 22.50⁰ | | 335 | TRACK ANGLE RATE | 4.0⁰/s | | 336 | PITCH ATT RATE | 10⁰/s | | 337 | ROLL ATT RATE | 10⁰/s | | 340 | TRACK ANGLE GRID | 10⁰/s | | 341 | GRID HEADING | 20⁰/s | | 360 | POTENTIAL VERT SPEED | -600 ft/mn | | 361 | INERTIAL ALTITUDE | 10,000 ft | | 362 | ALONG TRACK HORIZ ACCEL | 0.02g | | 363 | CROSS TRACK HORIZ ACCEL | 0.02g | | 364 | VERTICAL ACCEL | 0.1g | | 365 | INERTIAL VERT SPEED | -600 ft/mn | | 366 | N-S VELOCITY | 200 Kts (N) | | 367 | E-W VELOCITY | 200 Kts (E) | | 076 | GPS ALTITUDE | 10,000 FT | | 101 | HDOP | 500 | | 102 | VDOP | 500 | | 103 | GPS TRACK ANGLE TRUE-BNR | 00.0⁰ | | 110 | GPS PRES POS-LAT | N22.50⁰ | | 111 | GPS PRES POS-LONG | E22.50⁰ | | 112 | GPS GROUND SPEED-BNR | 200 KTS |

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----------------------------------------------------------------------| LABEL | PARAMETER | SELF TEST VALUE | |---------------------------------------------------------------------| 120 | GPS PRES POS-LAT FRAC | N00.00⁰ | | 121 | GPS PRES POS-LONG FRAC | E00.00⁰ | | 130 | GPS INTEGRITY LIMIT | 8 | | 131 | HYBRID INTEGRITY LIMIT | 8 | | 132 | HYBRID TRUE HEADING | 10⁰ | | 135 | HYBRID VERT FIGURE OF MERIT | 512 | | 136 | GPS VERT FIGURE OF MERIT | 512 | | 137 | HYBRID TRACK ANGLE TRUE-BNR | 00.0⁰ | | 150 | UTC-BNR | 12:00:00 | | 165 | GPS VERT SPEED | -600 FT/MIN | | 166 | GPS N-S VELOCITY | 200 KTS | | 174 | GPS E-W VELOCITY | 200 KTS | | 175 | HYBRID GROUND SPEED-BNR | 200 KTS | | 247 | GPS HORIZ FIGURE OF MERIT | 1.0 | | 254 | HYBRID PRES POS-LAT | N22.50⁰ | | 255 | HYBRID PRES POS-LONG | E22.50⁰ | | 256 | HYBRID PRES POS-LAT FRAC | N00.00⁰ | | 257 | HYBRID PRES POS-LONG FRAC | E00.00⁰ | | 261 | HYBRID ALTITUDE | 10,000 FT | | 263 | HYBRID FLIGHT PATH ANGLE | -5.0⁰ | | 264 | HYBRID HORIZ FIGURE OF MERIT | 1.0 | | 266 | HYBRID N-S VELOCITY | 200 KTS | | 267 | HYBRID E-W VELOCITY | 200 KTS | | 273 | GPS SENSOR STATUS | Not Applicable | | 274 | GPADIRS STATUS | Not Applicable | | 345 | HYBRID VERT SPEED | -600 FT/MIN | ----------------------------------------------------------------------Table 6 : Binary Output Labels ---------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |--------------------------| | | | 0 to 2 s. | Over 2 s. | |--------------------------------------------------------------| | 010 | PRESENT POSITION LAT | 188⁰88.8 | N 22⁰30.0 | | 011 | PRESENT POSITION LONG | 188⁰88.8 | E 22⁰30.0 | | 012 | GROUND SPEED | 6888 Kts | 200 Kts | | 013 | TRACK ANGLE TRUE | 688.8⁰ | 00.0⁰ | | 014 | MAGNETIC HEADING | 688.8⁰ | 15⁰ | | 015 | WIND SPEED | 688 Kts | 100 Kts | | 016 | WIND DIRECTION TRUE | 688⁰ | 30⁰ | | 041 | SET LATITUDE | 188⁰88.8 | N 22⁰30.0 | | 042 | SET LONGITUDE | 188⁰88.8 | E 22⁰30.0 | | 043 | SET MAGNETIC HEADING | 688⁰ | 15⁰ |

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---------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |--------------------------| | | | 0 to 2 s. | Over 2 s. | |--------------------------------------------------------------| | 044 | TRUE HEADING | 688.8⁰ | 10⁰ | | 125 | GPS UTC | 78:88.8 | 12:00:00 | | 260 | GPS DATE | 38/18/88 | 01/01/88 | ---------------------------------------------------------------Table 8 : Output BCD Words (i) Ground Report (Ref. Fig. 043) (j) Current Status (Ref. Fig. 045) The Current Status function displays on 8 pages the state (as read by the computer) of the discrete inputs, digital inputs (Set Lat and Long from FMGC), power condition. (k) GPIRS REPORT (Ref. Fig. 046) The GPIRS Report function displays GPS primary (AIME) parameters which are stored either in case of GPS primary failure or routinely at the end of each flight (historic on several flights). (l) GPIRS HISTORY (Ref. Fig. 047) R The GPIRS HISTORY function displays the number of events stored in memory and their accumulated durations. - CNT: Number of produced events (approximately 10). - HRS: Total event durations. C. Power-up Test Initialization and Cockpit Repercussions (1) Conditions of power-up test initialization - How long the computer must be de-energized: >20 s. - A/C configuration: - A/C on ground and OFF/NAV/ATT selector switch related to IR 1 (2) (3) (located on the ADIRS panel) set to OFF for 20 s at least then to NAV.

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ADIRS BITE - IR Main Menu 3/3 Figure 047 (SHEET 1)

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ADIRS BITE - IR Main Menu 3/3 Figure 047 (SHEET 2)

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(2) Progress of power-up tests (a) Duration: 5 s (b) Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - ADIRS panel: - ON BAT legend annunciator on for 5 s, 2 s after power-up test initialization. (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). (a) Test pass: - ALIGN legend of the IR 1 (2) (3) annunciator on. NOTE : It means that the system is in align mode. ____ (b) Test failed: - ECAM warning - NAV IR 1 (2) (3) FAULT or - NAV ADR 1 (2) (3) FAULT depending on the faulty part. - ADIRS panel: - FAULT legend of the IR 1 (2) (3) annunciator on or FAULT/OFF of the ADR 1 (2) (3) pushbutton switch on. depending on the faulty part. NOTE : In case of failure, set the DISPLAY/DATA selector switch ____ to STS then do the troubleshooting procedure on the system according to the error code displayed on the ADIRS panel.

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__________________________________________________________________________ AIR DATA, INERTIAL REFERENCE SYSTEM (ADIRS) BUILT-IN TEST EQUIPMENT (BITE) DESCRIPTION AND OPERATION _________________________ 1. _______ General The Built-in Test Equipment (BITE) facilitates maintenance on in-service aircraft. It detects and identifies faults related to the Air Data/Inertial Reference System (ADIRS) and reports them to the Centralized Fault Display Interface Unit (CFDIU). The BITE is included in the following LRUs: - Air Data/Inertial Reference Unit (ADIRU) - Air Data Module (ADM) - Control and Display Unit (CDU). It is linked to the CFDIU through the ADIRU (ADR and IR portions) which summarizes the BITE results for its own channel. (Ref. Fig. 001) The ADM performs various tests to detect its own faults (watchdog timer, RAM addressing, ROM, CPU, RAM, NVM, etc.) and failed input signals (check of programming pins). Faults are annunciated to the ADR by omission or labeling of a faulty output word (pressure label) and through the use of a discrete fault-code word output on the ARINC bus. Fault reports are also stored in a non-volatile memory inside the ADM. The IR BITE monitors: - the performance of both IR NAV and IR I/O processors - external inputs (both digital and discrete) - the functionality of the other internal hardware including the power supply and the inertial sensors (gyro, accelerometers). These BITE tests are performed either at power-up or continuously (Ref. Para. 3.A.(2)). Some tests enable to monitor operation errors: - Align in air - Excessive Motion - Latitude Sin/Cos test. They result in IR warnings but without fault message sent to the CFDIU. Tests and fault reactions are described in Para. 3.B. The ADR BITE monitors: - the performance of the ADR processor - the functionality of other ADR internal hardware - the status of analog, digital and discrete inputs - cross-channel comparisons with the other ADRs. These BITE tests are performed either at power-up or continuously (Ref. Para. 3.A.(3)) with the exception of cross-channel comparisons which are run once at takeoff. The common BITE monitors the computer performances (INTEL 80960 processor and memories) with the following tests: watchdog timer, checksum, RAM pattern monitor.

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The ADR and IR BITEs send reports to the CFDIU through the ARINC output bus, on label 356. These reports memorize the faults which occurred during the last 63 flight legs with their context. They operate in two modes: - NORMAL mode: fault reporting to the CFDIU during the flight - INTERACTIVE mode: on the ground. Access by the MCDU MENU pages (Ref. Para. 3.B.). 2. __________________ Component Location A. Computers Directly Linked to the CFDS ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1FP1 ADIRU-1 127 824 34-12-34 1FP2 ADIRU-2 128 824 34-12-34 1FP3 ADIRU-3 127 824 34-12-34 B. ADIRS Control Panel ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2FP CDU-ADIRS 20VU 211 831 34-12-12 C. Computers Directly Linked to the CFDS D. Other LRUs of the System ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------3FP1 SENSOR-ANGLE OF ATTACK, 1 127 824 34-11-19 3FP2 SENSOR-ANGLE OF ATTACK, 2 128 824 34-11-19 3FP3 SENSOR-ANGLE OF ATTACK, 3 127 824 34-11-19 11FP1 SENSOR-TAT, 1 121 34-11-18 11FP2 SENSOR-TAT, 2 122 34-11-18 9DA1 PROBE-PITOT, 1 125 812 34-11-15 9DA2 PROBE-PITOT, 2 126 822 34-11-15 9DA3 PROBE-PITOT, 3 125 812 34-11-15 7DA1 PROBE-L STATIC, 1 127 824 34-11-16 7DA2 PROBE-L STATIC, 2 127 824 34-11-16 7DA3 PROBE-L STATIC, 3 121 811 34-11-16 8DA1 PROBE-R STATIC, 1 128 824 34-11-16

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------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------8DA2 PROBE-R STATIC, 2 128 824 34-11-16 8DA3 PROBE-R STATIC, 3 122 811 34-11-16 19FP1 ADM-L TOTAL PRESSURE NONE 125 812 34-11-17 19FP2 ADM-R TOTAL PRESSURE 126 822 34-11-17 19FP3 ADM-STBY TOTAL PRESSURE 125 812 34-11-17 19FP4 ADM-R STATIC PRESSURE 128 824 34-11-17 19FP5 ADM-L STATIC PRESSURE 127 824 34-11-17 19FP6 ADM-R STATIC PRESSURE 128 824 34-11-17 19FP7 ADM-L STATIC PRESSURE 127 824 34-11-17 19FP8 ADM-STBY STATIC PRESSURE 121 811 34-11-17

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3. __________________ System Description A. Reporting Function Each ADIRS BITE message is described in the following pages, with the corresponding fault description and the consequences on the system and in the cockpit. (1) General - IR and ADR faults are classified as follows: . class 1: faults with cockpit effect . class 2: non-critical faults . class 3: minor faults without cockpit effects. - use of indexes in BITE messages: ADIRUi stands for ADIRU 1, ADIRU 2 or ADIRU 3. - ECAM messages: . xxx stands for CAPT or F/O, depending on the ADIRU side (1 or 2) . the letter in parentheses indicates the color used to display the text: (A) Amber, (C) Cyan and (W) White. - IR FAULT: the FAULT legend of the IR pushbutton switch flashes in NAV mode and is steady in ATT mode. (2) Inertial reference faults (Ref. Fig. 002, 003, 004, 005, 006, 007, 008, 009) Some IR faults resulting in warnings (fault annunciation, invalid outputs) are due to an incorrect operational use of the system and not to a system fault. These tests are: - align in air - position-entry (comparison with the last stored position and computed latitude) - Test on motion. (a) Align in air The test fails if, with the OFF/NAV/ATT selector switch on the CDU in the NAV position, the aircraft is detected in flight (TAS greater than 100 kts) at power-up or during the ALIGN phase. The following occurs: - NAV IRi FAULT message is displayed on the upper ECAM display unit. - The FAULT legend of the IR pushbutton switch, on the CDU, comes on. - The IN FLIGHT ALIGNMENT message is sent to the CFDIU. - All BNR output labels are coded Failure Warning (F/W) and all BCD labels are not transmitted. - The SELECT ATT indication is displayed on the CDU (DATA DISPLAY selector switch in STS position).

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The IR portion can be recovered by setting the OFF/NAV/ATT selector switch on the CDU to ATT and by applying the procedure (level flight) to initialize the ATT mode. (b) Position-entry test - Initial position (latitude, longitude) must compare within one degree of the last computed latitude and longitude from the previous flight. If a miscompare exists, then the NOT ALIGN message is displayed on the upper ECAM display unit with a text indicating to enter again the initial position (Ref. 34-14 Para. 3.). The miscompare is removed if the new entered position is identical to the previous one or is within the one-degree threshold. If not, the system waits for other position entry. - At the end of the alignment submode, the IR portion compares the initial latitude to a self-computed latitude. The test fails and the NOT ALIGN message is displayed on the upper ECAM display unit with action to enter again the position, when: . the cosine of the entered latitude differs from the cosine of the computed latitude by more than 0.01234 or . the sine of the entered latitude differs from the sine of the computed latitude by more than 0.01234. The miscompare is removed if a subsequent entry of latitude passes the test. If the sin/cos test fails two times with identical initial latitude entries, the IR system goes in a fault reaction: IR FAULT warning message on the upper ECAM display unit and FAULT legend on the CDU on, invalid outputs. NOTE : No fault message is sent to the CFDIU. ____ (c) Test on motion If taxiing or towing causes a step input which exceeds 0.11 ft/s in the X or Y velocity, the align process is stopped with a message on the upper ECAM display unit indicating IR NOT ALIGN and excessive motion (Ref. 34-14). The status matrix of the attitude data (pitch, roll, heading) is set at NCD which implies a flag on the PFD. NOTE : No fault message is sent to the CFDIU. ____ When the motion is no more detected, the IR reverts to the beginning of the align submode. It is not necessary to re-initialize the position.

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(3) Air data reference faults (Ref. Fig. 010, 011, 012, 013, 014, 015, 016) (a) SDI validity test at power-up A number of data is computed in the ADR portion according to air data correction laws (SSEC, AOA) which are dependent on the ADR side (SDI = 1, 2, 3). The determination of the SDI at power-up is consolidated by the ADR with a logic vote between the SDI discrete inputs and the SDI read on the labels received from the total pressure ADM and the static pressure ADM. Faults are either miscompare between the different sources of SDI or inability to compute the SDI. In this last case, detection of the fault leads to the ADR FAULT annunciation (message on the upper ECAM display unit; FAULT legend on the CDU) associated with invalid outputs. A number of messages can be sent to the CFDIU on label 356 according to the detected miscompare. These messages point the ADIRU or ADM pin program or a mix of them: 341117 341117 341234 341234 341234 (1,5), 341234 (1,5),

ADMi (19FPi) (i = 1, 2 or 3) ADMi (19FPi)/ADMj(19FPj) (i,j) = (1,5), (2,7) or (3,8) WRG: SDI PIN PROG/ADIRUi (1FPi) WRG: SDI PIN PROG/ADMi (19FPi)/ADIRUi (1FPi) WRG: SDI PIN PROG/ADMj (19FPj)/ADIRUi (1FPi) (i,j) = (2,7) or (3,8). WRG: SDI PIN PROG/ADMi/j ADIRUi (1FPi) (19FPi/j) (i,j) = (2,7) or (3,8).

(b) Cross-channel comparison tests A cross-channel comparison of pressures, angle of attack, and temperature parameters is performed to identify drifted air data input sensors. These tests are done for maintenance purpose only and they have no operational effects (no fault warning, output parameters are always valid, class 3 failures). To run these tests, each ADR portion receives one ADR output bus of the other side computers. (Ref. Fig. 001) As the air data sensors are installed per design in different zones and measure different values, the comparison can only be done in an identified flight phase. The tests are performed at takeoff with a CAS between 90 and 200 kts and only if the received ADR data is valid. The thresholds used in the comparison are:

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-----------------------------------------------| Parameter | Threshold | |----------------------------------------------| | Total pressure | 5 hPa | | Averaged static pressure | 5 hPa | | Left static pressure | 2 hPa | | Right static pressure | 2 hPa | | Angle of attack | 4⁰ | | Total air temperature | 3⁰C | -----------------------------------------------Table 1: Comparison Thresholds The messages resulting from a miscompare between parameters point the faulty sensor if it can be identified (one data differs from the two others which are identical) or the sensors which disagree. They are sent to the CFDIU in normal mode through label 356 of the ADR output and can be accessed through the LAST (PREVIOUS) LEG REPORT page on the MCDU menu. The messages have the following format: e.g. for the AOA sensors 341119 AOA SENSORi (3FPi) or 341119 AOA SENSORi (3FPi)/AOA SENSORj (3FPj) or 341119 AOA SNSR1 (3FP1)/SNSR2 (3FP2)/SNSR3 (3FP3) The principle of the messages is the same for other sensors (ADM, TAT). B. Interactive Function (1) General The interactive mode is activated via the SYSTEM REPORT/TEST page related to the ATA 34 chapter (Navigation) including the Air Data and Inertial Reference System (ADIRS). As this system includes two parts (Air Data Reference and Inertial Reference), two interactive functions are available: - IR interactive function (Ref. Fig. 017) - ADR interactive function. (Ref. Fig. 018)

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(2) IR interactive function (Ref. Fig. 019) (a) LAST LEG REPORT This item describes the in-flight class 1 and 2 fault status of the selected IR during the last leg (flight leg 00). (b) PREVIOUS LEGS REPORT This item describes the in-flight class 1 and 2 fault status of the selected IR during the previous legs (flight legs 01-62). (c) LRU IDENTIFICATION (Ref. Fig. 020) This item provides the ADIRU Part Number and Serial Number, as well as the part number of the ADIRU software: P/N-SWAPP for OPS (Operational Software), P/N-SWA/C for OPC 1 (Anemometric correction tables) and P/N-SWMAG for OPC 2 (MAGVAR tables). The Part Number and the Serial Number of the CDU are also displayed. (d) GROUND SCANNING (Ref. Fig. 020) This page layout contains the list of all failures detected while using this function. (e) TROUBLE SHOOTING DATA (Ref. Fig. 021) This item provides, for each fault message stored in the LAST LEG or PREVIOUS LEGS REPORT, additional data required by the maintenance for failure investigation. (f) CLASS 3 FAULTS (Ref. Fig. 021) This item reports all class 3 faults recorded since the last takeoff. (g) SYSTEM TEST (Ref. Fig. 022) This item activates a complete test of the IR system and presents a report to the user.

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(h) INTERFACE TEST (Ref. Fig. 023) This item controls the functional test modes of the selected IR. The test mode is inhibited whenever any of the following conditions exists: - ground speed greater than or equal to 20 kts - IR in the ATT mode. The text displayed describes the various steps of the interface test; when you push the line key adjacent to the START TEST indication, the following test sequence is run: - 0-2 seconds BCD, BNR and Discrete Words are output with SSM set to Functional Test and data set as shown in the following tables. Annunciator discretes are energized: . . . . . . .

ALIGN ON BAT DC FAIL (See note) IR FAULT IR OFF (See note) SPARE IR OUT 1 (See note) SPARE IR OUT 2 (See note)

- after 2 seconds BCD, BNR and Discrete Words are output with SSM set to Functional Test and data set as shown in the following tables. Annunciator discretes are de-energized to the previously indicated status. NOTE : No associated annunciator in the cockpit. ____ ---------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |--------------------------| | | | 0 to 2 s. | After 2 s. | |--------------------------------------------------------------| | 010 | PRESENT POSITION LAT | 188⁰88.8 | N 22⁰30.0 | | 011 | PRESENT POSITION LONG | 188⁰88.8 | E 22⁰30.0 | | 012 | GROUND SPEED | 6888 Kts | 200 Kts | | 013 | TRACK ANGLE-TRUE | 688.8⁰ | 00.0⁰ | | 014 | MAGNETIC HEADING | 688.8⁰ | 15⁰ | | 015 | WIND SPEED | 688 Kts | 100 Kts | | 016 | WIND DIRECTION-TRUE | 688⁰ | 30⁰ | | 041 | SET LATITUDE | 188⁰88.8 | N 22⁰30.0 | | 042 | SET LONGITUDE | 188⁰88.8 | E 22⁰30.0 | | 043 | SET MAGNETIC HEADING | 688⁰ | 15⁰ | | 044 | TRUE HEADING | 688.8⁰ | 10⁰ |

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---------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |--------------------------| | | | 0 to 2 s. | After 2 s. | |--------------------------------------------------------------| ---------------------------------------------------------------Table 2: Output BCD Words ---------------------------------------------------------------| LABEL | PARAMETER | SELF TEST VALUE | |--------------------------------------------------------------| | 052 | PITCH ANGULAR ACCEL | 5.0⁰ /s/s | | 053 | ROLL ANGULAR ACCEL | 5.0⁰ /s/s | | 054 | YAW ANGULAR ACCEL | 5.0⁰ /s/s | | 310 | PRESENT POSITION LAT | N 22.50⁰ | | 311 | PRESENT POSITION LONG | E 22.50⁰ | | 312 | GROUND SPEED | 200 Kts | | 313 | TRACK ANGLE-TRUE | 00.0⁰ | | 314 | TRUE HEADING | 10.0⁰ | | 315 | WIND SPEED | 100 Kts | | 316 | WIND DIRECTION-TRUE | 30⁰ | | 317 | TRACK ANGLE-MAG | 5⁰ | | 320 | MAGNETIC HEADING | 15⁰ | | 321 | DRIFT ANGLE | -10⁰ (Left) | | 322 | FLIGHT PATH ANGLE | -5⁰ | | 323 | FLIGHT PATH ACCEL | 0.02g | | 324 | PITCH ANGLE | 5⁰ | | 325 | ROLL ANGLE | 45⁰ (Right) | | 326 | BODY AXIS PITCH RATE | 10⁰/s | | 327 | BODY AXIS ROLL RATE | 10⁰/s | | 330 | BODY AXIS YAW RATE | 10⁰/s | | 331 | BODY LONGIT ACCEL | 0.02g | | 332 | BODY LATERAL ACCEL | 0.10g | | 333 | BODY NORMAL ACCEL | 0.10g | | 334 | PLATFORM HEADING | 22.50⁰ | | 335 | TRACK ANGLE RATE | 4.0⁰/s | | 336 | PITCH ATT RATE | 10⁰/s | | 337 | ROLL ATT RATE | 10⁰/s | | 340 | TRACK ANGLE GRID | 10⁰ | | 341 | GRID HEADING | 20⁰ | | 360 | POTENTIAL VERT SPEED | -600 ft/mn | | 361 | INERTIAL ALTITUDE | 10,000 ft | | 362 | ALONG TRACK HORIZ ACCEL | 0.02g | | 363 | CROSS TRACK HORIZ ACCEL | 0.02g | | 364 | VERTICAL ACCEL | 0.1g | | 365 | INERTIAL VERT SPEED | -600 ft/mn | | 366 | N-S VELOCITY | 200 Kts (N) |

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---------------------------------------------------------------| LABEL | PARAMETER | SELF TEST VALUE | |--------------------------------------------------------------| | 367 | E-W VELOCITY | 200 Kts (E) | ---------------------------------------------------------------Table 3: Binary Output Labels (i) GROUND REPORT (Ref. Fig. 024) This item reports all internal faults detected since the last landing. (j) INPUT STATUS (Ref. Fig. 025) This item describes the current state/value of the selected IR inputs (discrete and binary inputs).

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ADIRS BITE - IR Main Menu 6/7 Figure 024   EFF : 524-526, 528-599,  34-18-00 Page 35   Config-2 Feb 01/10  CES

 

ADIRS BITE - IR Main Menu 7/7 Figure 025   EFF : 524-526, 528-599,  34-18-00 Page 36   Config-2 Feb 01/10  CES

 

(3) ADR interactive function (a) LAST LEG REPORT (Ref. Fig. 026) This item describes the in-flight class 1 and 2 fault status of the selected ADR and related LRUs during the last leg (flight leg 00). (b) PREVIOUS LEGS REPORT (Ref. Fig. 026) This item describes the in-flight class 1 and 2 fault status of the selected ADR and related LRUs during the previous legs (flight legs 01-62). (c) LRU IDENTIFICATION (Ref. Fig. 027) This item describes the Part Number and Serial Number of the selected ADIRU, as well as the Part Number of the ADMs. (d) GROUND SCANNING (Ref. Fig. 027) This page layout contains the list of all the failures detected while using this function. (e) TROUBLE SHOOTING DATA (Ref. Fig. 028) This item provides, for each fault message stored in the LAST LEG or PREVIOUS LEGS REPORT, additional data required by the maintenance for failure investigation. (f) CLASS 3 FAULTS (Ref. Fig. 028) This item reports all class 3 faults recorded since the last takeoff. (g) SYSTEM TEST (Ref. Fig. 028) This item activates a complete test of the ADR system and presents a report to the user. (h) INTERFACE TEST (OUTPUT TESTS MENU) (Ref. Fig. 029, 030) This item controls the functional test modes of the selected ADR.

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ADIRS BITE - ADR Main Menu 1/8 Figure 026   EFF : 524-526, 528-599,  34-18-00 Page 38   Config-2 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 2/8 Figure 027   EFF : 524-526, 528-599,  34-18-00 Page 39   Config-2 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 3/8 Figure 028   EFF : 524-526, 528-599,  34-18-00 Page 40   Config-2 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 4/8 Figure 029   EFF : 524-526, 528-599,  34-18-00 Page 41   Config-2 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 5/8 Figure 030   EFF : 524-526, 528-599,  34-18-00 Page 42   Config-2 Feb 01/10  CES

 

The displayed text describes the various steps of the interface test; when you push the line key adjacent to the START TEST indication, the following test sequence is run: - 0-5 seconds: Failure Warning Test For 0-5 seconds after initiation of the test mode, the ADR outputs are transmitted as per the following tables. Since this is the failure warning test period, the BCD output parameters are not transmitted and the SSM of the BNR parameters are set to F/W. Timing tolerance is plus or minus 0.5 second. - 5-10 seconds: Altitude Ramp Test For 5-10 seconds after initiation of the test mode, the ADR outputs are transmitted as per the following tables with an SSM coded FT (except for discrete words). Since this is the altitude ramp test period, the altitude outputs are slewed in a positive direction for the entire 5-second period at a rate of 600 ft/min, starting at the ambient computed altitude. Timing tolerance is plus or minus 0.5 second. - 10 seconds until test completion: Fixed Output Test From 10 seconds after initialization of the test mode until the test completion is commanded, the ADR outputs are transmitted as per the following tables, outputting the fixed values specified by these tables with an SSM coded FT (except for discrete words). Timing tolerance is plus or minus 0.5 second.

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ADR Interface test values are shown in the following tables: -----------------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |--------------------------------------| | | | 0 to 5 s | 5 to 10 s | After 10 s | |----------------------------------------------------------------------| | 176 | LEFT STATIC PRESSURE | Last Valid | Last Valid | 696.8 hPa | | 177 | RIGHT STATIC PRESSURE | Last Valid | Last Valid | 696.8 hPa | | 203 | STANDARD ALTITUDE | Last Valid | Slewed | 10,000 ft | | 204 | BARO CORR ALT 1 | Last Valid | Slewed | 10,000 ft | | 205 | MACH | 0 | 0 | 0.66 | | 206 | COMPUTED AIRSPEED | 0 Kts | 0 Kts | 367.7 Kts | | 207 | MAX ALLOWABLE AIRSPEED| Last Valid | Last Valid | Last Valid | | 210 | TRUE AIRSPEED | 0 Kts | 0 Kts | 433 Kts | | 211 | TOTAL AIR TEMP | Last Valid | Last Valid | 35⁰C | | 212 | ALTITUDE RATE | Last Valid | 600 ft/mn | 0 ft/mn | | 213 | STATIC AIR TEMP | Last Valid | Last Valid | 10.3⁰C | | 215 | IMPACT PRESSURE | Last Valid | Last Valid | 236.6 hPa | | 220 | BARO CORR ALT 2 | Last Valid | Slewed | 10,000 ft | | 221 | IND ANGLE OF ATTACK | NOTE 1 | NOTE 1 | 5⁰ | | 241 | CORCTD ANGLE OF ATTACK| NOTE 1 | NOTE 1 | 5⁰ | | 242 | TOTAL PRESSURE | Last Valid | Last Valid | 933.4 hPa | | 245 | UNCRCTD AVG STAT PRESS| Last Valid | Last Valid | 696.8 hPa | | 246 | CORCTD AVG STAT PRESS | Last Valid | Last Valid | 696.8 hPa | | 251 | BARO CORR ALT 3 | Last Valid | Slewed | 10,000 ft | -----------------------------------------------------------------------NOTE : The indicated AOA is a function of the AOA sensor ____ position. The corrected AOA is a function of the AOA alternate discrete inputs, SDI discrete inputs and indicated AOA. The corrected AOA is set to 0⁰ when CAS is less than 60 kts. Output Binary Words

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-------------------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |----------------------------------------| | | | 0 to 5 s | 5 to 10 s | After 10 s | |------------------------------------------------------------------------| | 034 | BARO CORR (hPa) 3 |Not Transmit.| 745.0 hpa | 1013.3 hPa | | 035 | BARO CORR (in.Hg) 3 |Not Transmit.| 22.0 in.Hg | 29.92 in.Hg | | 230 | TRUE AIRSPEED |Not Transmit.| 0 Kts | 433 Kts | | 231 | TOTAL AIR TEMP |Not Transmit.| Last Valid | 35 ⁰C | | 233 | STATIC AIR TEMP |Not Transmit.| Last Valid | 10 ⁰C | | 234 | BARO CORR (hPa) 1 |Not Transmit.| Last Valid | 1013.3 hPa | | 235 | BARO CORR (in.Hg) 1 |Not Transmit.| Last Valid | 29.92 in.Hg | | 236 | BARO CORR (hPa) 2 |Not Transmit.| Last Valid | 1013.3 hPa | | 237 | BARO CORR (in.Hg) 2 |Not Transmit.| Last Valid | 29.92 in.Hg | -------------------------------------------------------------------------Output BCD Words -------------------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | BIT - PARAMETER |----------------------------------------| | | | 0 to 5 s | 5 to 10 s | After 10 s | |------------------------------------------------------------------------| | 270 | 13 - ADR FAULT | 1 | 0 | 0 | | 270 | 19 - OVERSPEED WARNING| 0 | 0 | 1 | | 271 | 13 - LOW SPD WARN 1 | 0 | 0 | 1 | | 271 | 14 - LOW SPD WARN 2 | 0 | 0 | 1 | | 271 | 15 - LOW SPD WARN 3 | 0 | 0 | 0 | | 271 | 16 - LOW SPD WARN 4 | 1 | 1 | 0 | -------------------------------------------------------------------------Output Discrete Words -------------------------------------------------------------------------| | SELF TEST VALUE | | PARAMETER |----------------------------------------| | | 0 to 5 s | 5 to 10 s | After 10 s | |------------------------------------------------------------------------| | LOW SPEED WARNING 1 | OPEN | OPEN | GROUND | | LOW SPEED WARNING 2 | OPEN | OPEN | GROUND | | LOW SPEED WARNING 3 | OPEN | OPEN | OPEN | | LOW SPEED WARNING 4 | GROUND | GROUND | OPEN | | OVERSPEED WARNING | OPEN | OPEN | GROUND | | ADR FAULT | GROUND | OPEN | OPEN | | ADR OFF | GROUND | OPEN | OPEN | -------------------------------------------------------------------------Discrete Outputs

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(i) ALT DYNAMIC SLEW (OUTPUT TESTS menu/SLEW TESTS submenu) (Ref. Fig. 029, 030) The activation of the ALT DYNAMIC SLEW test causes the ADR to output a simulated ramp of altitude (label 203) between low and high altitude limits specified by the operator. These limits, as well as the slew rate, are entered by the operator by means of the MCDU keyboard. The altitude limit values are tested to be within -2000 and +50,000 ft. The altitude lower limit is tested to be less than the altitude upper limit. The altitude slew rate is tested to be within 1 to +20,000 ft/mn. (j) CAS DYNAMIC SLEW (OUTPUT TESTS menu/SLEW TESTS submenu) (Ref. Fig. 029, 031) The activation of the CAS DYNAMIC SLEW test causes the ADR to output a simulated ramp of computed airspeed (label 206) between low and high speed limits specified by the operator. These limits, as well as the slew rate, are entered by the operator by means of the MCDU keyboard. The CAS limit values are tested to be within 0 and +450 kts. The CAS lower limit is tested to be less than the CAS upper limit. The speed slew rate is tested to be within 1 to +100 Kts/mn. (k) AOA SENSOR TEST (OUTPUT TESTS menu) (Ref. Fig. 029, 032) The activation of the AOA SENSOR TEST causes the ADR to output the actual measured values of indicated and corrected AOA with an SSM coded FT, and the AOA special test discrete output to be commanded to the ground state, which causes the AOA sensor to be commanded to a fixed position greater than the stall warning threshold. Thus, the Flight Warning Computer (FWC) activates the aural stall warning. (l) GROUND REPORT (Ref. Fig. 029) This item reports all internal faults detected since the last landing. (m) INPUT STATUS (Ref. Fig. 029, 033) This item describes the current state/value of the selected ADR inputs (discrete, analog and binary inputs).

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ADIRS BITE - ADR Main Menu 6/8 Figure 031   EFF : 524-526, 528-599,  34-18-00 Page 47   Config-2 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 7/8 Figure 032   EFF : 524-526, 528-599,  34-18-00 Page 48   Config-2 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 8/8 Figure 033   EFF : 524-526, 528-599,  34-18-00 Page 49   Config-2 Feb 01/10  CES

 

C. Power-up Test Initialization and Cockpit Repercussions (1) Conditions of power-up test initialization - How long the computer must be de-energized: >20 s. - A/C configuration: - A/C on ground and OFF/NAV/ATT selector switch related to IR 1 (2) (3) (located on the ADIRS panel) set to OFF for 20 s at least then to NAV. (2) Progress of power-up tests (a) Duration: 5 s (b) Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - ADIRS panel: - ON BAT legend annunciator on for 5 s, 2 s after power-up test initialization. (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). (a) Test pass: - ALIGN legend of the IR 1 (2) (3) annunciator on. NOTE : It means that the system is in align mode. ____ (b) Test failed: - ECAM warning - NAV IR 1 (2) (3) FAULT or - NAV ADR 1 (2) (3) FAULT depending on the faulty part. - ADIRS panel: - FAULT legend of the IR 1 (2) (3) annunciator on or FAULT/OFF of the ADR 1 (2) (3) pushbutton switch on depending on the faulty part. NOTE : In case of failure, set the DISPLAY/DATA selector switch ____ to STS then do the troubleshooting procedure on the system according to the error code displayed on the ADIRS panel.

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**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-523, Post SB 34-1240 For A/C 001-049,101-105,151-199,201-203, ADIRS - BITE - DESCRIPTION AND OPERATION ________________________________________

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**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, 1. General _______ **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, The Built-in Test Equipment (BITE) facilitates maintenance on in-service aircraft. It detects and identifies faults related to the Air Data/Inertial Reference System (ADIRS) and reports them to the Centralized Fault Display Interface Unit (CFDIU). The BITE is included in the following LRUs: - Air Data/Inertial Reference Unit (ADIRU) - Air Data Module (ADM) - Control and Display Unit (CDU). It is linked to the CFDIU through the ADIRU (ADR and IR portions) which summarizes the BITE results for its own channel. (Ref. Fig. 001) . The ADM performs various tests to detect its own faults (watchdog timer, RAM addressing, ROM, CPU, RAM, NVM, etc.) and failed input signals (check of programming pins). Faults are annunciated to the ADR by omission or labeling of a faulty output word (pressure label) and through the use of a discrete fault-code word output on the ARINC bus. Fault reports are also stored in a non-volatile memory inside the ADM. The IR BITE monitors: - the performance of both IR NAV and IR I/O processors - external inputs (both digital and discrete) - the functionality of the other internal hardware including the power supply and the inertial sensors (gyro, accelerometers). These BITE tests are performed either at power-up or continuously (Ref. Para. 3.A.(2)). Some tests enable to monitor operation errors: - Align in air - Excessive Motion - Latitude Sin/Cos test. They result in IR warnings but without fault message sent to the CFDIU. Tests and fault reactions are described in Para. 3.B.

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ADIRS - Interface between one ADIRU and the CFDIU Figure 001   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 2 401-499,  Config-3 Feb 01/08  CES

 

The ADR BITE monitors: the performance of the ADR processor the functionality of other ADR internal hardware the status of analog, digital and discrete inputs cross-channel comparisons with the other ADRs. These BITE tests are performed either at power-up or continuously (Ref. Para. 3.A.(3)) with the exception of cross-channel comparisons which are run once at takeoff. The common BITE monitors the computer performances (INTEL 80960 processor and memories) with the following tests: watchdog timer, checksum, RAM pattern monitor. The ADR and IR BITEs send reports to the CFDIU through the ARINC output bus, on label 356. These reports memorize the faults which occurred during the last 63 flight legs with their context. They operate in two modes: - NORMAL mode: fault reporting to the CFDIU during the flight - INTERACTIVE mode: on the ground. Access by the MCDU MENU pages (Ref. Para. 3.B.). -

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, The Built-in Test Equipment (BITE) facilitates maintenance on in-service aircraft. It detects and identifies faults related to the Air Data/Inertial Reference System (ADIRS) and reports them to the Centralized Fault Display Interface Unit (CFDIU). The BITE is included in the following LRUs: - Air Data/Inertial Reference Unit (ADIRU) - Air Data Module (ADM) It is linked to the CFDIU through the ADIRU (ADR and IR portions) which summarizes the BITE results for its own channel. (Ref. Fig. 001A) The ADM performs various tests to detect its own faults (watchdog timer, RAM addressing, ROM, CPU, RAM, NVM etc.) and failed input signals (check of programming pins). Faults are annunciated to the ADR by omission or labeling of a faulty output word (pressure label) and through the use of a discrete fault-code word output on the ARINC bus. Fault reports are also stored in a non-volatile memory inside the ADM. The IR BITE monitors: the performance of both IR NAV and IR I/O processors, external inputs (both digital and discrete), the functionality of the other internal hardware including the power supply and the inertial sensors (gyro, accelerometers). These BITE tests are performed either at power-up or continuously (Ref. Para. 3.A.(2)).

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ADIRS - Interface between one ADIRU and the CFDIU Figure 001A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 4 511-523,  Config-3 Feb 01/10  CES

 

Some tests enable to monitor operation errors. These are: Align in air, Excessive Motion, Latitude Sin/Cos test. They result in IR warnings but without fault message sent to the CFDIU. Tests and fault reactions are described in Para. 3.B. The ADR BITE monitors: the performance of the ADR processor, the functionality of other ADR internal hardware, the status of analog, digital and discrete inputs and cross-channel comparisons with the other ADRs. These BITE tests are performed either at power-up or continuously (Ref. Para. 3.A.(3)) with the exception of cross-channel comparisons which are run once at takeoff. The common BITE monitors the computer performances (INTEL 80960 processor and memories) with the following tests : watchdog timer, checksum, RAM pattern monitor. The ADR and IR BITEs send reports to the CFDIU through the ARINC output bus, on label 356. These reports memorize the faults which occurred during the last 63 flight legs with their context. They operate in two modes: - NORMAL mode: fault reporting to the CFDIU during the flight - INTERACTIVE mode: on the ground. Access by the MCDU MENU pages (Ref. Para. 3.B.). R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, 2. __________________ Component Location A. Computers Directly Linked to the CFDS ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1FP1 ADIRU-1 127 824 34-12-34 1FP2 ADIRU-2 128 824 34-12-34 1FP3 ADIRU-3 127 824 34-12-34 **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, B. ADIRS Control Panel ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2FP CDU-ADIRS 20VU 211 831 34-12-12

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, B. ADIRS Control Panel ------------------------------------------------------------------------------| FIN | FUNCTIONAL DESIGNATION | PANEL | ZONE | ACCESS | ATA | | | | | | DOOR | REF. | |-----------------------------------------------------------------------------| | 41VU | MSU-ADIRS | 41VU | 211 | | | -------------------------------------------------------------------------------

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**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, C. Other LRUs of the System ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------3FP1 SENSOR-ANGLE OF ATTACK, 1 127 824 34-11-19 3FP2 SENSOR-ANGLE OF ATTACK, 2 128 824 34-11-19 3FP3 SENSOR-ANGLE OF ATTACK, 3 127 824 34-11-19 11FP1 SENSOR-TAT, 1 121 34-11-18 11FP2 SENSOR-TAT, 2 122 34-11-18 9DA1 PROBE-PITOT, 1 125 812 34-11-15 9DA2 PROBE-PITOT, 2 126 822 34-11-15 9DA3 PROBE-PITOT, 3 125 812 34-11-15 7DA1 PROBE-L STATIC, 1 127 824 34-11-16 7DA2 PROBE-L STATIC, 2 127 824 34-11-16 7DA3 PROBE-L STATIC, 3 121 811 34-11-16 8DA1 PROBE-R STATIC, 1 128 824 34-11-16 8DA2 PROBE-R STATIC, 2 128 824 34-11-16 8DA3 PROBE-R STATIC, 3 122 811 34-11-16 19FP1 ADM-L TOTAL PRESSURE NONE 125 812 34-11-17 19FP2 ADM-R TOTAL PRESSURE 126 822 34-11-17 19FP3 ADM-STBY TOTAL PRESSURE 125 812 34-11-17 19FP4 ADM-R STATIC PRESSURE 128 824 34-11-17 19FP5 ADM-L STATIC PRESSURE 127 824 34-11-17 19FP6 ADM-R STATIC PRESSURE 128 824 34-11-17 19FP7 ADM-L STATIC PRESSURE 127 824 34-11-17 19FP8 ADM-STBY STATIC PRESSURE 121 811 34-11-17

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3. __________________ System Description A. Reporting Function Each ADIRS BITE message is described in the following pages, with the corresponding fault description and the consequences on the system and in the cockpit. (1) General - IR and ADR faults are classified as follows: . class 1: faults with cockpit effect . class 2: non-critical faults . class 3: minor faults without cockpit effects. - use of indexes in BITE messages: ADIRUi stands for ADIRU 1, ADIRU 2 or ADIRU 3. - ECAM messages: . xxx stands for CAPT or F/O, depending on the ADIRU side (1 or 2) . the letter in parentheses indicates the color used to display the text: (A) Amber, (C) Cyan and (W) White. - IR FAULT: the FAULT legend of the IR pushbutton switch flashes in NAV mode and is steady in ATT mode. (2) Inertial reference faults **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 002) R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (Ref. Fig. 002A) **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 003)

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (Ref. Fig. 003A)

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ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 1/5 Figure 002   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 9 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 1/5 Figure 002A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 10 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 2/5 Figure 003   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 11 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 2/5 Figure 003A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 12 511-523,  Config-3 Feb 01/10  CES

 

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 004) R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (Ref. Fig. 004A) **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 005)

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (Ref. Fig. 005A) **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 006)

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (Ref. Fig. 006A) **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 007)

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**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (Ref. Fig. 007A)

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**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (Ref. Fig. 008)

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ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 3/5 Figure 004   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 14 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 3/5 Figure 004A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 15 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 4/5 Figure 005   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 16 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 4/5 Figure 005A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 17 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 5/5 Figure 006   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 18 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 5/5 Figure 006A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 19 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Inertial Reference System - Class 1 External Faults Figure 007   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 20 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Inertial Reference System - Class 1 External Faults Figure 007A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 21 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Inertial Reference System - Class 3 Faults Figure 008   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 22 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

**ON A/C 052-052, 204-228, 236-238, (Ref. Fig. 008A) **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 009) R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (Ref. Fig. 009A)

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, Some IR faults resulting in warnings (fault annunciation, invalid outputs) are due to an incorrect operational use of the system and not to a system fault. These tests are: - align in air - position-entry (comparison with the last stored position and computed latitude). - Test on motion. **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (a) Align in air The test fails if, with the OFF/NAV/ATT selector switch on the CDU in NAV position, the aircraft is detected in flight (TAS greater than 100 kts) at power-up or during the ALIGN phase. The following occurs: - NAV IRi FAULT message is displayed on the upper ECAM display unit. - the FAULT legend of the IR pushbutton switch, on the CDU, comes on. - the IN FLIGHT ALIGNMENT message is sent to the CFDIU - all BNR output labels are coded Failure Warning (F/W) and all BCD labels are not transmitted. - the SELECT ATT indication is displayed on the CDU (DATA DISPLAY selector switch in STS position). The IR portion can be recovered by setting the OFF/NAV/ATT selector switch on the CDU to ATT and by applying the procedure (level flight) to initialize the ATT mode.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 23 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Inertial Reference System - Class 3 Faults Figure 008A   R EFF : 001-049, 052-052, 101-105, 151-199,  34-18-00 Page 24 201-228, 236-238,  Config-3 Aug 01/09  CES

 

ADIRS BITE - Inertial Reference System - Class 2 Internal Faults Figure 009   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 25 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Inertial Reference System - Class 2 Internal Faults Figure 009A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 26 511-523,  Config-3 Feb 01/10  CES

 

(b) Position-entry test - Initial position (latitude, longitude) must compare within one degree of the last computed latitude and longitude from the previous flight. If a miscompare exists, then the NOT ALIGN message is displayed on the upper ECAM display unit with a text indicating to enter again the initial position (Ref. 34-14 Para. 3.). The miscompare is removed if the new entered position is identical to the previous one or is within the one-degree threshold. If not, the system waits for other position entry. - At the end of the alignment submode, the IR portion compares the initial latitude to a self-computed latitude. The test fails and the NOT ALIGN message is displayed on the upper ECAM display unit with action to enter again the position, when: . the cosine of entered latitude differs from the cosine of computed latitude by more than 0.01234 or . the sine of entered latitude differs from the sine of computed latitude by more than 0.01234. The miscompare is removed if a subsequent entry of latitude passes the test. If the sin/cos test fails two times with identical initial latitude entries, the IR system goes in a fault reaction: IR FAULT warning message on the upper ECAM display unit and FAULT legend on the CDU on, invalid outputs. NOTE : No fault message is sent to the CFDIU. ____ (c) Test on motion If taxiing or towing causes a step input which exceeds 0.11 ft/s in the X or Y velocity, the align process is stopped with a message on the upper ECAM display unit indicating IR NOT ALIGN and excessive motion (Ref. 34-14). The status matrix of the attitude data (pitch, roll, heading) is set at NCD which implies a flag on the PFD. NOTE : No fault message is sent to the CFDIU. ____ When the motion is no more detected, the IR reverts to the beginning of the align submode. It is not necessary to re-initialize the position.

  R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 27 401-499,  Config-3 Feb 01/08  CES

 

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (a) Align in air The test fails if, with the OFF/NAV/ATT selector switch on the MSU in NAV position, the aircraft is detected in flight (TAS greater than 100 kts) at power-up or during the ALIGN phase. The following occurs: - NAV IRi FAULT message is displayed on the upper ECAM display unit. - The FAULT legend of the IR pushbutton switch, on the MSU, comes on. - The IN FLIGHT ALIGNMENT message is sent to the CFDIU. - All BNR output labels are coded Failure Warning (F/W) and all BCD labels are not transmitted. The IR portion can be recovered by setting the OFF/NAV/ATT selector switch on the MSU to ATT and by applying the procedure (level flight) to initialize the ATT mode. (b) Position-entry test - Initial position (latitude, longitude) must compare within one degree of the last computed latitude and longitude from the previous flight. If a miscompare exists, then the NOT ALIGN message is displayed on the upper ECAM display unit with a text indicating to enter again the initial position (Ref. 34-14 Para. 3.). The miscompare is removed if the new entered position is identical to the previous one or is within the one-degree threshold. If not, the system waits for other position entry. - At the end of the alignment submode, the IR portion compares the initial latitude with a self-computed latitude. The test fails and the NOT ALIGN message is displayed on the upper ECAM display unit with action to enter again the position, when: . the cosine of the entered latitude differs from the cosine of the computed latitude by more than 0.01234 or . the sine of the entered latitude differs from the sine of the computed latitude by more than 0.01234. The miscompare is removed if a subsequent entry of latitude passes the test. If the sin/cos test fails two times with identical initial latitude entries, the IR system goes in a fault reaction: IR FAULT warning message on the upper ECAM display unit and FAULT legend on the MSU on, invalid outputs. NOTE : No fault message is sent to the CFDIU. ____

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 28 511-523,  Config-3 Feb 01/10  CES

 

(c) Test on motion If taxiing or towing causes a step input which exceeds 0.11 ft/s in the X or Y velocity, the align process is stopped with a message on the upper ECAM display unit indicating IR NOT ALIGN and excessive motion (Ref. 34-14). The status matrix of the attitude data (pitch, roll, heading) is set at NCD which implies a flag on the PFD. NOTE : No fault message is sent to the CFDIU. ____ When the motion is no more detected, the IR reverts to the beginning of the align submode. It is not necessary to re-initialize the position. **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (3) Air data reference faults **ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, (Ref. Fig. 010) **ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-239, 305-312, 401-499, (Ref. Fig. 010A) **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 011, 012, 013) **ON A/C 051-057, 059-060, 062-099, 106-149, 204-215, 217-217, 219-219, 221-225, 227-233, 236-238, 301-304, (Ref. Fig. 014) **ON A/C 058-058, 061-061, 216-216, 218-218, 220-220, 226-226, 234-235, 239-239, 305-312, 401-499, (Ref. Fig. 014A)

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 29 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 1/4 Figure 010   R EFF : 051-057, 059-060, 062-099, 106-149,  34-18-00 Page 30 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Nov 01/09 236-238, 301-304, CES

 

ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 1/4 Figure 010A   R EFF : 058-058, 061-061, 216-216, 218-218,  34-18-00 Page 31 220-220, 226-226, 234-235, 239-239, 305-312,  Config-3 Nov 01/09 401-499, CES

 

ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 1/4 Figure 010B   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 32 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 2/4 Figure 011   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 33 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 2/4 Figure 011A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 34 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 3/4 Figure 012   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 35 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 3/4 Figure 012A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 36 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 4/4 Figure 013   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 37 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 4/4 Figure 013A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 38 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Air Data Reference System - Class 2 Faults Figure 014   R EFF : 051-057, 059-060, 062-099, 106-149,  34-18-00 Page 39 204-215, 217-217, 219-219, 221-225, 227-233,  Config-3 Nov 01/09 236-238, 301-304, CES

 

ADIRS BITE - Air Data Reference System - Class 2 Faults Figure 014A   R EFF : 058-058, 061-061, 216-216, 218-218,  34-18-00 Page 40 220-220, 226-226, 234-235, 239-239, 305-312,  Config-3 Nov 01/09 401-499, CES

 

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 015, 016) (a) SDI validity test at power-up A number of data are computed in the ADR portion according to air data correction laws (SSEC, AOA) which are dependent on the ADR side (SDI = 1, 2, 3). The determination of the SDI at power-up is consolidated by the ADR with a logic vote between the SDI discrete inputs and the SDI read on the labels received from the total pressure ADM and the static pressure ADM. Faults are either miscompare between the different sources of SDI or unability to compute the SDI. In this last case, detection of the fault leads to the ADR FAULT annunciation (message on the upper ECAM display unit; FAULT legend on the CDU) associated to invalid outputs. A number of messages can be sent to the CFDIU on the label 356 according to the detected miscompare. These messages point the ADIRU or ADM pin program or a mix of them: 341117 341117 341234 341234 341234 (1,5), 341234 (1,5), R

ADMi (19FPi) (i = 1, 2 or 3) ADMi (19FPi)/ADMj(19FPj) (i,j) = (1,5), (2,7) or (3,8) WRG: SDI PIN PROG/ADIRUi (1FPi) WRG: SDI PIN PROG/ADMi (19FPi)/ADIRUi (1FPi) WRG: SDI PIN PROG/ADMj (19FPj)/ADIRUi (1FPi) (i,j) = (2,7) or (3,8). WRG: SDI PIN PROG/ADMi/j ADIRUi (1FPi) (19FPi/j) (i,j) = (2,7) or (3,8).

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (3) Air data reference faults (Ref. Fig. 010B, 011A, 012A, 013A, 014B, 015A, 016) (a) SDI validity test at power-up A number of data is computed in the ADR portion according to air data correction laws (SSEC, AOA) which are dependent on the ADR side (SDI = 1, 2, 3). The determination of the SDI at power-up is consolidated by the ADR with a logic vote between the SDI discrete inputs and the SDI read on the labels received from the total pressure ADM and the static pressure ADM. Faults are either miscompare between the different sources of SDI or inability to compute the SDI.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 41 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Air Data Reference System - Class 2 Faults Figure 014B   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 42 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Air Data Reference System - Class 1 External Faults Figure 015   R EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 43 401-499,  Config-3 Feb 01/08  CES

 

ADIRS BITE - Air Data Reference System - Class 1 External Faults Figure 015A   R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 44 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Air Data Reference System - Class 3 Faults Figure 016   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 45 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

In this last case, detection of the fault leads to the ADR FAULT annunciation (message on the upper ECAM display unit; FAULT legend on the MSU) associated to invalid outputs. A number of messages can be sent to the CFDIU on the label 356 according to the detected miscompare. These messages point the ADIRU or ADM pin program or a mix of them: 341117 341117 341234 341234 341234 (1,5), 341234 (1,5), R R

ADMi (19FPi) (i = 1, 2 or 3) ADMi (19FPi)/ADMj(19FPj) (i,j) = (1,5), (2,7) or (3,8) WRG: SDI PIN PROG/ADIRUi (1FPi) WRG: SDI PIN PROG/ADMi (19FPi)/ADIRUi (1FPi) WRG: SDI PIN PROG/ADMj (19FPj)/ADIRUi (1FPi) (i,j) = (2,7) or (3,8). WRG: SDI PIN PROG/ADMi/j ADIRUi (1FPi) (19FPi/j) (i,j) = (2,7) or (3,8).

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (b) Cross-channel comparison tests A cross-channel comparison of pressures, angle-of-attack, and temperature parameters is performed to identify drifted air data input sensors. These tests are done for maintenance purpose only and they have no operational effects (no fault warning, output parameters are always valid, class 3 failures). To run these tests, each ADR portion receives one ADR output bus of the other side computers **ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (Ref. Fig. 001)

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (Ref. Fig. 001A)

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, As the air data sensors are installed per design in different zones and measure different values, the comparison can only be done in an identified flight phase. The tests are performed at takeoff with a CAS between 90 and 200 kts and only if the received ADR data are valid. The thresholds used in the comparison are:

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 46 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

-----------------------------------------------| Parameter | Threshold | |----------------------------------------------| | Total pressure | 5 hPa | | Averaged static pressure | 5 hPa | | Left static pressure | 2 hPa | | Right static pressure | 2 hPa | | Angle-of-attack | 4⁰ | | Total air temperature | 3⁰C | -----------------------------------------------Table 1 : Comparison Thresholds The messages resulting from a miscompare between parameters point the faulty sensor if it can be identified (one data differs from the two others which are identical) or the sensors which disagree. They are sent to the CFDIU in normal mode through label 356 of the ADR output and can be accessed by the LAST (PREVIOUS) LEG REPORT page on the MCDU menu. The messages have the following format: e.g. for the AOA sensors 341119 AOA SENSORi (3FPi) or 341119 AOA SENSORi (3FPi)/AOA SENSORj (3FPj) or 341119 AOA SNSR1 (3FP1)/SNSR2 (3FP2)/SNSR3 (3FP3) The principle of the messages is the same for other sensors (ADM, TAT). B. Interactive Function (1) General The interactive mode is activated via the SYSTEM REPORT/TEST page related to ATA 34 chapter (Navigation) including the Air Data and Inertial Reference System (ADIRS). As this system includes two parts (Air Data Reference and Inertial Reference), two interactive functions are available: - IR interactive function (Ref. Fig. 017) - ADR interactive function. (Ref. Fig. 018)

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 47 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Activation of IR Interactive Function Figure 017   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 48 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - Activation of ADR Interactive Function Figure 018   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 49 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, (2) IR interactive function (Ref. Fig. 019) (a) LAST LEG REPORT This item describes the in-flight class 1 and 2 fault status of the selected IR during the last leg (flight leg 00). (b) PREVIOUS LEGS REPORT This item describes the in-flight class 1 and 2 fault status of the selected IR during the previous legs (flight legs 01-62). (c) LRU IDENTIFICATION (Ref. Fig. 020) This item provides the ADIRU Part Number and Serial Number. The Part Number and the Serial Number of the CDU are also displayed. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, (2) IR interactive function (Ref. Fig. 019) (a) LAST LEG REPORT This item describes the in-flight class 1 and 2 fault status of the selected IR during the last leg (flight leg 00). (b) PREVIOUS LEGS REPORT This item describes the in-flight class 1 and 2 fault status of the selected IR during the previous legs (flight legs 01-62). (c) LRU IDENTIFICATION (Ref. Fig. 020) This item provides the ADIRU Part Number and Serial Number.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 50 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - IR Main Menu 1/7 Figure 019   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 51 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - IR Main Menu 2/7 Figure 020   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 52 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

R R

**ON A/C 051-099, 106-149, 204-249, 251-299, 301-399, 401-499, 501-509, 511-523, (d) GROUND SCANNING (Ref. Fig. 020) This item describes the current on-the-ground fault status of the selected IR. (e) TROUBLE SHOOTING DATA (Ref. Fig. 021) This item provides, for each fault message stored in the LAST LEG or PREVIOUS LEGS REPORT, additional data required by the maintenance for failure investigation. (f) CLASS 3 FAULTS (Ref. Fig. 021) This item reports all class 3 faults recorded since the last takeoff. (g) SYSTEM TEST (Ref. Fig. 022) This item activates a complete test of the IR system and presents a report to the user. (h) INTERFACE TEST (Ref. Fig. 023) This item controls the functional test modes of the selected IR. The test mode is inhibited whenever any of the following conditions exists: - ground speed greater than or equal to 20 kts - IR in the ATT mode. The text displayed describes the various steps of the interface test; when you push the line key adjacent to the START TEST indication, the following test sequence is run: - 0-2 seconds BCD, BNR and Discrete Words are output with SSM set to Functional Test and data set as shown in the following tables. Annunciator discretes are energized: . . . . .

ALIGN ON BAT DC FAIL (See nota) IR FAULT IR OFF (See nota)

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 53 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - IR Main Menu 3/7 Figure 021   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 54 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - IR Main Menu 4/7 Figure 022   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 55 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - IR Main Menu 5/7 Figure 023   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 56 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

. SPARE IR OUT 1 (See nota) . SPARE IR OUT 2 (See nota) - after 2 seconds BCD, BNR and Discrete Words are output with SSM set to Functional Test and data set as shown in the following tables. Annunciator discretes are de-energized to the previously indicated status. NOTE : No associated annunciator in the cockpit. ____ ---------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |--------------------------| | | | 0 to 2 s. | After 2 s. | |--------------------------------------------------------------| | 010 | PRESENT POSITION LAT | 188⁰88.8 | N 22⁰30.0 | | 011 | PRESENT POSITION LONG | 188⁰88.8 | E 22⁰30.0 | | 012 | GROUND SPEED | 6888 Kts | 200 Kts | | 013 | TRACK ANGLE-TRUE | 688.8⁰ | 00.0⁰ | | 014 | MAGNETIC HEADING | 688.8⁰ | 15⁰ | | 015 | WIND SPEED | 688 Kts | 100 Kts | | 016 | WIND DIRECTION-TRUE | 688⁰ | 30⁰ | | 041 | SET LATITUDE | 188⁰88.8 | N 22⁰30.0 | | 042 | SET LONGITUDE | 188⁰88.8 | E 22⁰30.0 | | 043 | SET MAGNETIC HEADING | 688⁰ | 15⁰ | | 044 | TRUE HEADING | 688.8⁰ | 10⁰ | ---------------------------------------------------------------Table 2 : Output BCD Words

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 57 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

---------------------------------------------------------------| LABEL | PARAMETER | SELF TEST VALUE | |--------------------------------------------------------------| | 052 | PITCH ANGULAR ACCEL | 5.0⁰/s/s | | 053 | ROLL ANGULAR ACCEL | 5.0⁰/s/s | | 054 | YAW ANGULAR ACCEL | 5.0⁰/s/s | | 076 | GPS ALTITUDE | 10,000 ft | | 101 | GPS HDOP | 4.0 | | 102 | GPS VDOP | 3.0 | | 103 | GPS TRACK ANGLE | 0.0⁰ | | 110 | GPS LATITUDE | N 22.50⁰ | | 111 | GPS LONGITUDE | E 22.50⁰ | | 112 | GPS GROUND SPEED | 200 kts | | 120 | GPS LATITUDE FINE | N 00.00⁰ | | 121 | GPS LONGITUDE FINE | E 00.00⁰ | | 125 | UTC TIME | 12:00:00 | | 130 | GPS HORIZ INTEGRITY LIM | 10.0 NM | | 131 | HYBRID HORIZ INTEGRITY | 5.0 NM | | | LIMIT | | | 132 | HYBRID TRUE HEADING | 10⁰ | | 135 | HYBRID VERTICAL FOM | 300 ft | | 136 | GPS VERTICAL FOM | 100 ft | | 137 | HYBRID TRACK ANGLE | 0.0⁰ | | 143 | TERMINAL AREA HIL | 0.8 NM | | 150 | UTC | 12:00:00 | | 162 | DESTINATION ETA | 06:30:00 | | 163 | ALT WAYPOINT ETA | 06:35:00 | | 165 | GPS VERTICAL VELOCITY | -600 ft/mn | | 166 | GPS N/S VELOCITY | 200 kts | | 174 | GPS E/W VELOCITY | 200 kts | | 175 | HYBRID GROUND SPEED | 200 kts | | 247 | GPS HORIZONTAL FOM | 6.0 NM | | 254 | HYBRID LATITUDE | N 22.50⁰ | | 255 | HYBRID LONGITUDE | E 22.50⁰ | | 256 | HYBRID LATITUDE FINE | N 00.00⁰ | | 257 | HYBRID LONGITUDE FINE | E 00.00⁰ | | 260 | DATE | 1/1/99 | | 261 | HYBRID ALTITUDE | 10,000 ft | | 263 | HYBRID FLIGHT PATH ANGLE| -5.0⁰ | | 264 | HYBRID HORIZONTAL FOM | 7.0 NM | | 266 | HYBRID N/S VELOCITY | 200 kts | | 267 | HYBRID E/W VELOCITY | 200 Kts | | 310 | PRESENT POSITION LAT | N 22.50⁰ | | 311 | PRESENT POSITION LONG | E 22.50⁰ | | 312 | GROUND SPEED | 200 Kts | | 313 | TRACK ANGLE-TRUE | 00.0⁰ | | 314 | TRUE HEADING | 10.0⁰ |

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 58 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

---------------------------------------------------------------| LABEL | PARAMETER | SELF TEST VALUE | |--------------------------------------------------------------| | 315 | WIND SPEED | 100 Kts | | 316 | WIND DIRECTION-TRUE | 30⁰ | | 317 | TRACK ANGLE-MAG | 5⁰ | | 320 | MAGNETIC HEADING | 15⁰ | | 321 | DRIFT ANGLE | -10⁰ (Left) | | 322 | FLIGHT PATH ANGLE | -5⁰ | | 323 | FLIGHT PATH ACCEL | 0.02g | | 324 | PITCH ANGLE | 5⁰ | | 325 | ROLL ANGLE | 45⁰ (Right) | | 326 | BODY AXIS PITCH RATE | 10⁰/s | | 327 | BODY AXIS ROLL RATE | 10⁰/s | | 330 | BODY AXIS YAW RATE | 10⁰/s | | 331 | BODY LONGIT ACCEL | 0.02g | | 332 | BODY LATERAL ACCEL | 0.10g | | 333 | BODY NORMAL ACCEL | 0.10g | | 334 | PLATFORM HEADING | 22.50⁰ | | 335 | TRACK ANGLE RATE | 4.0⁰/s | | 336 | PITCH ATT RATE | 10⁰/s | | 337 | ROLL ATT RATE | 10⁰/s | | 340 | TRACK ANGLE GRID | 10⁰ | | 341 | GRID HEADING | 20⁰ | | 343 | DESTINATION HIL | 1.0 NM | | 345 | HYBRID VERTICAL VELOCITY| -600 ft/mn | | 347 | ALT WAYPOINT HIL | 2.0 NM | | 360 | POTENTIAL VERT SPEED | -600 ft/mn | | 361 | INERTIAL ALTITUDE | 10,000 ft | | 362 | ALONG TRACK HORIZ ACCEL | 0.02g | | 363 | CROSS TRACK HORIZ ACCEL | 0.02g | | 364 | VERTICAL ACCEL | 0.1g | | 365 | INERTIAL VERT SPEED | -600 ft/mn | | 366 | N-S VELOCITY | 200 Kts (N) | | 367 | E-W VELOCITY | 200 Kts (E) | ---------------------------------------------------------------Table 3 : Binary Output Labels (i) GROUND REPORT (Ref. Fig. 024) This item reports all internal faults detected since the last landing. (j) INPUT STATUS (Ref. Fig. 025) This item describes the current state/value of the selected IR inputs (discrete and binary inputs).

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ADIRS BITE - IR Main Menu 6/7 Figure 024   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 60 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - IR Main Menu 7/7 Figure 025   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 61 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

(3) ADR interactive function (a) LAST LEG REPORT (Ref. Fig. 026) This item describes the in-flight class 1 and 2 fault status of the selected ADR and related LRUs during the last leg (flight leg 00). (b) PREVIOUS LEGS REPORT (Ref. Fig. 026) This item describes the in-flight class 1 and 2 fault status of the selected ADR and related LRUs during the previous legs (flight legs 01-62). (c) LRU IDENTIFICATION (Ref. Fig. 027) This item describes the Part Number and Serial Number of the selected ADIRU, as well as the Part Number of the ADMs. (d) GROUND SCANNING (Ref. Fig. 027) This item describes the current on-the-ground fault status of the selected ADR. (e) TROUBLE SHOOTING DATA (Ref. Fig. 028) This item provides, for each fault message stored in the LAST LEG or PREVIOUS LEGS REPORT, additional data required by the maintenance for failure investigation. (f) CLASS 3 FAULTS (Ref. Fig. 028) This item reports all class 3 faults recorded since the last takeoff. (g) SYSTEM TEST (Ref. Fig. 028) This item activates a complete test of the ADR system and presents a report to the user. (h) INTERFACE TEST (OUTPUT TESTS MENU) (Ref. Fig. 029, 030) This item controls the functional test modes of the selected ADR.

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ADIRS BITE - ADR Main Menu 1/8 Figure 026   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 63 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 2/8 Figure 027   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 64 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 3/8 Figure 028   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 65 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 4/8 Figure 029   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 66 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 5/8 Figure 030   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 67 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

The text displayed describes the various steps of the interface test; when you push the line key adjacent to the START TEST indication, the following test sequence is run: - 0-5 seconds: Failure Warning Test For 0-5 seconds after initiation of the test mode, the ADR outputs are transmitted per the following tables. Since this is the failure warning test period, the BCD output parameters are not transmitted and the SSM of the BNR parameters are set to F/W. Timing tolerance is plus or minus 0.5 seconds. - 5-10 seconds: Altitude Ramp Test For 5-10 seconds after initiation of the test mode, the ADR outputs are transmitted per the following tables with an SSM coded FT (except for discrete words). Since this is the altitude ramp test period, the altitude outputs are slewed in a positive direction for the entire 5-second period at a rate of 600 ft/mn, starting at the ambient computed altitude. Timing tolerance is plus or minus 0.5 seconds. - 10 second until test completion: Fixed Output Test From 10 seconds after initialization of the test mode until the test completion is commanded, the ADR outputs are transmitted per the following tables, outputting the fixed values specified by these tables with an SSM coded FT (except for discrete words). Timing tolerance is plus or minus 0.5 seconds.

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 68 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADR Interface test values are shown in the following tables: -----------------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |--------------------------------------| | | | 0 to 5 s | 5 to 10 s | After 10 s | |----------------------------------------------------------------------| | 176 | LEFT STATIC PRESSURE | Last Valid | Last Valid | 696.8 hPa | | 177 | RIGHT STATIC PRESSURE | Last Valid | Last Valid | 696.8 hPa | | 203 | STANDARD ALTITUDE | Last Valid | Slewed | 10,000 ft | | 204 | BARO CORR ALT 1 | Last Valid | Slewed | 10,000 ft | | 205 | MACH | 0 | 0 | 0.66 | | 206 | COMPUTED AIRSPEED | 0 Kts | 0 Kts | 367.7 Kts | | 207 | MAX ALLOWABLE AIRSPEED| Last Valid | Last Valid | Last Valid | | 210 | TRUE AIRSPEED | 0 Kts | 0 Kts | 433 Kts | | 211 | TOTAL AIR TEMP | Last Valid | Last Valid | 35⁰C | | 212 | ALTITUDE RATE | Last Valid | 600 ft/mn | 0 ft/mn | | 213 | STATIC AIR TEMP | Last Valid | Last Valid | 10.3⁰C | | 215 | IMPACT PRESSURE | Last Valid | Last Valid | 236.6 hPa | | 220 | BARO CORR ALT 2 | Last Valid | Slewed | 10,000 ft | | 221 | IND ANGLE OF ATTACK | NOTE 1 | NOTE 1 | 5⁰ | | 241 | CORCTD ANGLE OF ATTACK| NOTE 1 | NOTE 1 | 5⁰ | | 242 | TOTAL PRESSURE | Last Valid | Last Valid | 933.4 hPa | | 245 | UNCRCTD AVG STAT PRESS| Last Valid | Last Valid | 696.8 hPa | | 246 | CORCTD AVG STAT PRESS | Last Valid | Last Valid | 696.8 hPa | | 251 | BARO CORR ALT 3 | Last Valid | Slewed | 10,000 ft | -----------------------------------------------------------------------NOTE : Indicated AOA is a function of the AOA sensor position. ____ Corrected AOA is a function of AOA alternate discrete inputs, SDI discrete inputs and indicated AOA. Corrected AOA is set to 0⁰ when CAS is less than 60 kts. Output Binary Words

  R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 69 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

-------------------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |----------------------------------------| | | | 0 to 5 s | 5 to 10 s | After 10 s | |------------------------------------------------------------------------| | 034 | BARO CORR (hPa) 3 |Not Transmit.| 745.0 hpa | 1013.3 hPa | | 035 | BARO CORR (in.Hg) 3 |Not Transmit.| 22.0 in.Hg | 29.92 in.Hg | | 230 | TRUE AIRSPEED |Not Transmit.| 0 Kts | 433 Kts | | 231 | TOTAL AIR TEMP |Not Transmit.| Last Valid | 35 ⁰C | | 233 | STATIC AIR TEMP |Not Transmit.| Last Valid | 10 ⁰C | | 234 | BARO CORR (hPa) 1 |Not Transmit.| Last Valid | 1013.3 hPa | | 235 | BARO CORR (in.Hg) 1 |Not Transmit.| Last Valid | 29.92 in.Hg | | 236 | BARO CORR (hPa) 2 |Not Transmit.| Last Valid | 1013.3 hPa | | 237 | BARO CORR (in.Hg) 2 |Not Transmit.| Last Valid | 29.92 in.Hg | -------------------------------------------------------------------------Output BCD Words -------------------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | BIT - PARAMETER |----------------------------------------| | | | 0 to 5 s | 5 to 10 s | After 10 s | |------------------------------------------------------------------------| | 270 | 13 - ADR FAULT | 1 | 0 | 0 | | 270 | 19 - OVERSPEED WARNING| 0 | 0 | 1 | | 271 | 13 - LOW SPD WARN 1 | 0 | 0 | 1 | | 271 | 14 - LOW SPD WARN 2 | 0 | 0 | 1 | | 271 | 15 - LOW SPD WARN 3 | 0 | 0 | 0 | | 271 | 16 - LOW SPD WARN 4 | 1 | 1 | 0 | -------------------------------------------------------------------------Output Discretes Words -------------------------------------------------------------------------| | SELF TEST VALUE | | PARAMETER |----------------------------------------| | | 0 to 5 s | 5 to 10 s | After 10 s | |------------------------------------------------------------------------| | LOW SPEED WARNING 1 | OPEN | OPEN | GROUND | | LOW SPEED WARNING 2 | OPEN | OPEN | GROUND | | LOW SPEED WARNING 3 | OPEN | OPEN | OPEN | | LOW SPEED WARNING 4 | GROUND | GROUND | OPEN | | OVERSPEED WARNING | OPEN | OPEN | GROUND | | ADR FAULT | GROUND | OPEN | OPEN | | ADR OFF | GROUND | OPEN | OPEN | -------------------------------------------------------------------------Discrete Outputs

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(i) ALT DYNAMIC SLEW (OUTPUT TESTS menu/SLEW TESTS submenu) (Ref. Fig. 029, 030) The activation of the ALT DYNAMIC SLEW test causes the ADR to output a simulated ramp of altitude (label 203) between low and high altitude limits specified by the operator. These limits, as well as the slew rate, are entered by the operator by means of the MCDU keyboard. The altitude limit values are tested to be within -2000 and +50,000 ft. The altitude lower limit is tested to be less than the altitude upper limit. The altitude slew rate is tested to be within 1 to +20,000 ft/mn. (j) CAS DYNAMIC SLEW (OUTPUT TESTS menu/SLEW TESTS submenu) (Ref. Fig. 029, 031) The activation of the CAS DYNAMIC SLEW test causes the ADR to output a simulated ramp of computed airspeed (label 206) between low and high speed limits specified by the operator. These limits, as well as the slew rate, are entered by the operator by means of the MCDU keyboard. The CAS limit values are tested to be within 0 and +450 kts. The CAS lower limit is tested to be less than the CAS upper limit. The speed slew rate is tested to be within 1 to +100 Kts/mn. (k) AOA SENSOR TEST (OUTPUT TESTS menu) (Ref. Fig. 029, 032) The activation of the AOA SENSOR TEST causes the ADR to output the actual measured values of indicated and corrected AOA with an SSM coded FT, and the AOA special test discrete output to be commanded to the ground state, which causes the AOA sensor to be commanded to a fixed position greater than the stall warning threshold. Thus, the Flight Warning Computer (FWC) activates the aural stall warning. (l) GROUND REPORT (Ref. Fig. 029) This item reports all internal faults detected since the last landing. (m) INPUT STATUS (Ref. Fig. 029, 033) This item describes the current state/value of the selected ADR inputs (discrete, analog and binary inputs).

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ADIRS BITE - ADR Main Menu 6/8 Figure 031   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 72 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 7/8 Figure 032   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 73 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

ADIRS BITE - ADR Main Menu 8/8 Figure 033   R EFF : 051-099, 106-149, 204-249, 251-299,  34-18-00 Page 74 301-399, 401-499, 501-509, 511-523,  Config-3 Feb 01/10  CES

 

R

**ON A/C 051-099, 106-149, 204-239, 301-312, 401-499, C. Power-up Test Initialization and Cockpit Repercussions (1) Conditions of power-up test initialization - How long the computer must be de-energized: >20 s. - A/C configuration: - A/C on ground and OFF/NAV/ATT selector switch related to IR 1 (2) (3) (located on the ADIRS panel) set to OFF for 20 s at least then to NAV. (2) Progress of power-up tests (a) Duration: 5 s (b) Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - ADIRS panel: - ON BAT legend annunciator on for 5 s, 2 s after power-up test initialization. (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). (a) Test pass: - ALIGN legend of the IR 1 (2) (3) annunciator on. NOTE : It means that the system is in align mode. ____ (b) Test failed: - ECAM warning - NAV IR 1 (2) (3) FAULT or - NAV ADR 1 (2) (3) FAULT depending on the faulty part. - ADIRS panel: - FAULT legend of the IR 1 (2) (3) annunciator on or FAULT/OFF of the ADR 1 (2) (3) pushbutton switch on. depending on the faulty part. NOTE : In case of failure, set the DISPLAY/DATA selector switch ____ to STS then do the troubleshooting procedure on the system according to the error code displayed on the ADIRS panel.

  EFF : 051-099, 106-149, 204-239, 301-312,  34-18-00 Page 75 401-499,  Config-3 Feb 01/08  CES

 

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-523, C. Power-up Test Initialization and Cockpit Repercussions (1) Conditions of power-up test initialization - How long the computer must be de-energized: >20 s. - A/C configuration: - A/C on ground and OFF/NAV/ATT selector switch related to IR 1 (2) (3) (located on the ADIRS panel) set to OFF for 20 s at least then to NAV. (2) Progress of power-up tests (a) Duration: 5 s (b) Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - ADIRS panel: - ON BAT legend annunciator on for 5 s, 2 s after power-up test initialization. (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). (a) Test pass: - FAULT legend of the IR 1 (2) (3) annunciator off. (b) Test failed: - ECAM warning - NAV IR 1 (2) (3) FAULT or - NAV ADR 1 (2) (3) FAULT depending on the faulty part. - ADIRS MSU: - FAULT legend of the IR 1 (2) (3) annunciator on or FAULT/OFF of the ADR 1 (2) (3) pushbutton switch on. depending on the faulty part.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-18-00 Page 76 511-523,  Config-3 Feb 01/10  CES

 

STANDBY NAVIGATION SYSTEMS - ADJUSTMENT/TEST ____________________________________________ TASK 34-20-00-710-001 ISIS Reset 1. __________________ Reason for the Job Refer to the MPD TASK: 342200-04 2. ______________________ Job Set-up Information Not Applicable 3. __________ Job Set-up Subtask 34-20-00-865-050 A. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/INST 5FN F12 4. Procedure _________ Subtask 34-20-00-710-050 A. Reset of the ISIS Indicator. (1) On the panel 49VU, open the NAV/STBY/INST circuit breaker for more than 5 seconds then close it. (2) After some seconds, on the ISIS Indicator, the INIT page comes into view. 5. Close-up ________

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-20-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 501 Feb 01/10

STANDBY DATA : ALTITUDE AND AIRSPEED - DESCRIPTION AND OPERATION ________________________________________________________________ R 1. General _______ **ON A/C 001-049, 051-099, 101-105, One standby airspeed indicator, one standby altimeter and one metric altimeter are directly connected to the standby pitot and static sources. Each indicator is contained in a 2 ATI case (ARINC 408) and installed on the center instrument panel. The standby circuit can be drained by means of a water drain. **ON A/C 151-199, 201-220, 236-238, R One standby airspeed indicator and one standby altimeter are directly connected to the standby pitot and static sources. Each indicator is contained in a 2 ATI case (ARINC 408) and installed on the center instrument panel. The standby circuit can be drained by means of a water drain. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, R 2. __________________ Component Location **ON A/C 001-049, 051-099, 101-105, (Ref. Fig. 001) **ON A/C 151-199, 201-220, 236-238, R (Ref. Fig. 001A)

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 1 Aug 01/09

Standby Data - Altitude and Airspeed - Component Location Figure 001   R EFF : 001-049, 051-099, 101-105,  34-21-00    CES

 

Page 2 May 01/05

Standby Data - Altitude and Airspeed - Component Location Figure 001A   R EFF : 151-199, 201-220, 236-238,  34-21-00    CES

 

Page 3 Feb 01/08

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, R ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------3FN ALTM-STANDBY 4VU 211 831 34-21-22 9FN IND-STANDBY AIRSPEED 4VU 211 831 34-21-26 15FN ALTIMETER-METRIC 4VU 211 831 34-21-25 3. __________________ System Description **ON A/C 001-049, 051-099, 101-105, (Ref. Fig. 002) **ON A/C 151-199, 201-220, 236-238, R (Ref. Fig. 002A) **ON A/C 001-049, 051-099, 101-105, (Ref. Fig. 003) **ON A/C 151-199, 201-220, 236-238, R (Ref. Fig. 003A) **ON A/C 001-049, 051-099, 101-105, (Ref. Fig. 004) **ON A/C 151-199, 201-220, 236-238, R (Ref. Fig. 004A)

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 4 Aug 01/09

Standby Data - Altitude and Airspeed - Pneumatic Circuit Figure 002   R EFF : 001-049, 051-099, 101-105,  34-21-00    CES

 

Page 5 May 01/05

Standby Data - Altitude and Airspeed - Pneumatic Circuit Figure 002A   R EFF : 151-199, 201-220, 236-238,  34-21-00    CES

 

Page 6 Feb 01/08

Standby Data - Altitude and Airspeed - Electrical Circuit Figure 003   R EFF : 001-049, 051-099, 101-105,  34-21-00    CES

 

Page 7 May 01/05

Standby Data - Altitude and Airspeed - Electrical Circuit Figure 003A   R EFF : 151-199, 201-220, 236-238,  34-21-00    CES

 

Page 8 Feb 01/08

Standby Data - Altitude and Airspeed - Data Indication Figure 004   R EFF : 001-049, 051-099, 101-105,  34-21-00    CES

 

Page 9 May 01/05

Standby Data - Altitude and Airspeed - Data Indication Figure 004A   R EFF : 151-199, 201-220, 236-238,  34-21-00    CES

 

Page 10 Feb 01/08

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, R A. Standby Altimeter The standby altimeter is supplied with static pressure by the standby air data system to indicate the barometric altitude of the aircraft in feet. The barometric altitude is displayed by means of: - a pointer (4) performing one revolution of the dial for 1000 feet - a display counter (5) made up of two drums displaying respectively the tens of thousands and the thousands of feet. When the altitude is below 10,000 feet, the figure zero of the left drum is replaced by black and white stripes. The figure nine is replaced by an orange fire stripped zone. the altitude dial (6) is calibrated from 0 to 1000 feet with 20 feet graduations - the baro correction (2) is displayed on a counter graduated in hecto Pascal - a knob (1) located at the L corner of the indicator enables the display of the reference baro correction in the range of 750 to 1050 hPa. - four manually adjustable white bugs (3) are provided for manual altitude setting. To improve accuracy, 28VDC supplies the internal vibrator of the standby altimeter through a landing gear relay. In straight and level flight, with the internal vibrator operating, the standby altimeter gives the following accuracy: plus or minus 20 ft. at sea level plus or minus 40 ft. at 6000 ft. plus or minus 80 ft. at 10,000 ft. plus or minus 130 ft. at 20,000 ft. plus or minus 205 ft. at 35,000 ft. NOTE : On the ground, with the internal vibrator not supplied, the above ____ figures may be plus or minus 300ft. Integral lighting supplied with external 5VAC is provided to illuminate the presentation. B. Standby Airspeed Indicator The standby airspeed indicator contains a capsule-operated mechanism which measures the pitot/static pressure differential from the standby air data system and provides airspeed indication in terms of knots with the following accuracy: - plus or minus 3 kts for VC < 200 kts - plus or minus 4 kts for 200 kts < VC < 300 kts - plus or minus 5 kts for 300 kts < VC < 450 kts. The airspeed indication is displayed by means of:

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 11 Aug 01/09

- a pointer (9) which moves on a dial (7) graduated between 60 kts and 450 kts. The scale is linear from 60 kts to 250 kts with 5 kts graduations and from 250 kts to 450 kts with 10 kts graduations. - four manually adjustable white bugs (8) provided for manual speed setting. Integral lighting supplied with external 5VAC is provided to illuminate the presentation. **ON A/C 001-049, 051-099, 101-105, C. Metric Altimeter The metric altimeter is supplied with static pressure by the standby air data system to indicate the barometric altitude of the aircraft in meters with the following accuracy: plus or minus 15 m at the sea level plus or minus 20 m at 2000 m plus or minus 35 m at 6000 m plus or minus 40 m at 8000 m plus or minus 45 m at 10,000 m plus or minus 60 m at 15,000 m The barometric altitude is displayed by means of: - a pointer (10) performing one revolution of the dial for 1000 meters. - a display counter (11) made up of two drums displaying respectively the tens of thousands, and the thousands of meters. - the altitude dial (12) is calibrated from 0 to 1000 meters with 50 meters graduations. - the baro correction (14) is displayed on a counter graduated in hecto Pascal. - a knob (13) located at the L corner of the indicator enables the display of the reference baro correction in the range of 870 to 1050 hPa. Integral lighting supplied with external 5VAC is provided to illuminate the presentation. **ON A/C 213-213, R C. Metric Altimeter Not Applicable

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 12 Aug 01/09

STANDBY DATA : ALTITUDE AND AIRSPEED - ADJUSTMENT/TEST ______________________________________________________ TASK 34-21-00-790-001 R

Low-Range Leak Test of the Standby Pneumatic Circuits WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU _______ START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE _______ CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM. AUTOMATIC MOVEMENT OF THE FLIGHT CONTROL SURFACES CAN BE DANGEROUS AND/OR CAUSE DAMAGE. CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO _______ INSTRUMENTS: - THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg) - CHANGES IN STATIC PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE - DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED. CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE _______ STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg). 1. __________________ Reason for the Job Refer to the MPD TASK: 342100-01 - To make sure that there are no leaks in the standby static and pitot circuits.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 501 May 01/08

2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 36122 98D34003500000

circuit breaker(s) safety clip(s) colored adhesive tape 1 GENERATOR - GROUND PRESSURE MINI. 100 MB 1 ADAPTOR-CHARGING,PITOT PROBE 1 ADAPTER COVER-STATIC PORT

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 27-50-00-866-009 31-60-00-860-001 31-60-00-860-002 34-11-15-200-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Retraction of the Flaps on the Ground EIS Start Procedure EIS Stop Procedure Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3)

3. __________ Job Set-up R Subtask 34-21-00-860-056 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). Subtask 34-21-00-865-050 B. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 502 Aug 01/09

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 Subtask 34-21-00-865-052 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/ALTM 16FN F14 **ON A/C 001-049, 051-099, 101-105, 151-199, Subtask 34-21-00-420-050 D. Connection of the Ground Pressure Generator (1) Remove the slip on covers from the static probe and the pitot probe of the standby system. (2) Connect the GENERATOR - GROUND PRESSURE MINI. 100 MB to one standby static probe with the STATIC PORT ADAPTER (98D34003500100) from the ADAPTER COVER-STATIC PORT (98D34003500000). (3) Connect the ground pressure generator to the standby pitot probe with the ADAPTOR-CHARGING,PITOT PROBE. (4) Seal the drain hole of the standby probes: CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT _______ SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE. ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE FIRST AND USE THE COLORED ADHESIVE TAPE TO ATTACH THE PLASTIC. IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE, THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE PROBE. (a) Seal the drain holes of the standby pitot probe with a piece of plastic and colored adhesive tape of very bright color.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,  R  CES

 

Page 503 Aug 01/09

(b) Seal the opposite standby static probe with a piece of plastic (see CAUTION above) and with the STATIC PORT COVER (98D34003500103) from the ADAPTER COVER-STATIC PORT (98D34003500000). (5) Move the vane of the AOA sensor 3 to the upper position. Keep the vane in position with colored adhesive tape. **ON A/C 201-220, 236-238, R Subtask 34-21-00-420-050-A D. Connection of the Ground Pressure Generator (1) Remove the slip on covers from the static probe and the pitot probe of the standby system. (2) Connect the GENERATOR - GROUND PRESSURE MINI. 100 MB to one standby static probe with the STATIC PORT ADAPTER (98D34003500100) from the ADAPTER COVER-STATIC PORT (98D34003500000). (3) Connect the ground pressure generator to the standby pitot probe with the ADAPTOR-CHARGING,PITOT PROBE. NOTE : The ADAPTOR-CHARGING,PITOT PROBE is on the drain hole. Thus it ____ is not necessary to seal the drain hole of the pitot probe. (4) Seal the opposite standby static probe with a piece of plastic and with the STATIC PORT COVER (98D34003500103) from the ADAPTER COVERSTATIC PORT (98D34003500000). (5) Move the vane of the AOA sensor 3 to the upper position. Maintain the vane in position with colored adhesive tape.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 504 Aug 01/09

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, Subtask 34-21-00-860-058 E. Aircraft Maintenance Configuration (1) Do the EIS start procedure (PFD only) (Ref. TASK 31-60-00-860-001). (2) Make sure that the flaps are in the fully retracted position (Ref. TASK 27-50-00-866-009). (3) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to NAV. (4) Start the ground pressure generator. 4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, Subtask 34-21-00-790-050 A. Leak Test NOTE : You can do the test below for a static pressure of 691.4 hPa and ____ an impact pressure of 59 hPa (or a total pressure of 750.4 hPa) but it is less accurate. On the SWITCHING panel 8VU, set the AIR DATA selector switch to CAPT/3 (or F/O/3) position. Make sure that: - the CAPT (or F/O) PFD show 10,237 ft +/- 30 ft and 190 kts +/- 3 kts - the standby altimeters and the standby airspeed indicator show 10,201 ft +/- 83 ft, 3109.26 m +/- 25 m and 189 kts +/- 5 kts. After 5 minutes: - the change of altitude must not be more than 370 ft or 112.8 m. - the change of speed must not be more than 10 Kts. R R R R

NOTE : The input parameters for the ground test (speed and altitude) and ____ the values shown on the cockpit displays are different because of the sum of the tolerances of the air data circuit (ground test unit, ADMs, ADIRUs).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 505 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the standby altimeter and on the metric altimeter, set a barometric pressure of 1013 hPa. 2. On the SWITCHING panel 8VU, set the AIR DATA selector switch to CAPT/3 (or F/O/3) position.

On the CAPT (or F/O) PFD, the indications from ADIRU3 are shown.

3. On the ground pressure generator: - set a static pressure of 455.4 hPa. - set an impact pressure of 186.4 hPa (or a total pressure of 641.8 hPa).

R R R R

4. Close the electrovalves to isolate the static and pitot circuits of the aircraft from the ground pressure generator.

- Make sure that: the CAPT (or F/O) PFD shows 21,369 ft +/- 30 ft and 341 kts +/- 3 kts. the standby altimeters and the standby airspeed indicator show 20,529 ft +/- 135 ft, 6257.23 m +/41 m and 329 kts +/- 5 kts. After 5 minutes : - make sure that the change of altitude is not more than 500 ft or 152.4 m. After 10 minutes : - make sure that the change of speed is not more than 20 Kts.

5. On the ground pressure generator: - slowly balance the pressure in the standby static and pitot circuits and open the electrovalves to get atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn or 1830 m/mn.

6. Stop the ground pressure generator.

  EFF : 001-049, 051-099, 101-105,  34-21-00    CES

 

Page 506 Aug 01/08

**ON A/C 151-199, Subtask 34-21-00-790-050-B A. Leak Test NOTE : You can do the test below for a static pressure of 691 hPa and an ____ impact pressure of 59.3 hPa (or a total pressure of 750.3 hPa) but it is less accurate. On the SWITCHING panel 8VU, set the AIR DATA selector switch to CAPT/3 (or F/O/3) position. Make sure that: - the CAPT (or F/O) PFD shows 10,177 ft +/- 30 ft and 188 kts +/3 kts, - the standby altimeter and the standby airspeed indicator show 10,216 ft +/- 83 ft and 189 kts +/- 5 kts. After 5 minutes: - the change of altitude must not be more than 370 ft. - the change of speed must not be more than 10 Kts. R R R R

NOTE : The input parameters for the ground test (speed and altitude) and ____ the values shown on the cockpit displays are different because of the sum of the tolerances of the air data circuit (ground test unit, ADMs, ADIRUs). ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the standby altimeter, set a barometric pressure of 1013 hPa. 2. On the SWITCHING panel 8VU, set the AIR DATA selector switch to CAPT/3 (or F/O/3) position.

On the CAPT (or F/O) PFD, the indications from ADIRU3 are shown.

3. On the ground pressure generator: - set a static pressure of 462.4 hPa. - set an impact pressure of 179.1 hPa (or a total pressure of 641.5 hPa). 4. Close the electrovalves to isolate the static and pitot circuits of the aircraft from the ground pressure generator.

- Make sure that: the CAPT (or F/O) PFD shows 20,918 ft +/- 30 ft and 335 kts +/- 3 kts, the standby altimeter and the standby airspeed indicator show 20,166 ft +/135 ft and 323 kts +/- 5 kts. After 5 minutes :

  EFF : 151-199,  34-21-00    CES

 

Page 507 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- make sure that the change of altitude is not more than 500 ft. After 10 minutes : - make sure that the change of speed is not more than 20 Kts. 5. On the ground pressure generator: - slowly balance the pressure in the standby static and pitot circuits and open the electrovalves to get atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

6. Stop the ground pressure generator. **ON A/C 201-220, 236-238, Subtask 34-21-00-790-050-A A. Leak Test NOTE : You can do the test below for a static pressure of 691.4 hPa and ____ an impact pressure of 59 hPa (or a total pressure of 750.4 hPa) but it is less accurate. On the SWITCHING panel 8VU, set the AIR DATA selector switch to CAPT/3 (or F/O/3) position. Make sure that: - the CAPT (or F/O) PFD shows 10,237 ft +/- 30 ft and 190 kts +/3 kts. - the standby altimeter and the standby airspeed indicator show 10,201 ft +/- 83 ft and 189 kts +/- 5 kts. After 5 minutes: - the change of altitude must not be more than 370 ft. - the change of speed must not be more than 10 Kts. R R R R

NOTE : The input parameters for the ground test (speed and altitude) and ____ the values shown on the cockpit displays are different because of the sum of the tolerances of the air data circuit (ground test unit, ADMs, ADIRUs).

  EFF : 151-199, 201-220, 236-238,  34-21-00    CES

 

Page 508 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the standby altimeter, set a barometric pressure of 1013 hPa. 2. On the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is in CAPT/3 (or F/O/3) position.

On the CAPT (or F/O) PFD, the indications from ADIRU3 are shown.

3. On the ground pressure generator: - set a static pressure of 455.4 hPa. - set an impact pressure of 186.4 hPa (or a total pressure of 641.8 hPa). R R R R R

4. Close the electrovalves to isolate the static and pitot circuits of the aircraft from the ground pressure generator.

- Make sure that: the CAPT (or F/O) PFD shows 21,369 ft +/- 40 ft and 341 kts +/- 3 kts. the standby altimeter and the standby airspeed indicator show 20,529 ft +/135 ft and 329 kts +/- 5 kts. After 5 minutes : - make sure that the change of altitude is not more than 500 ft. After 10 minutes : - make sure that the change of speed is not more than 20 Kts.

5. On the ground pressure generator: - slowly balance the pressure in the standby static and pitot circuits and open the electrovalves to get atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

6. Stop the ground pressure generator.

  EFF : 201-220, 236-238,  34-21-00    CES

 

Page 509 Aug 01/08

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, 5. Close-up ________ **ON A/C 001-049, 051-099, 101-105, 151-199, Subtask 34-21-00-020-050 A. Remove the ground pressure generator (1) Disconnect the ground pressure generator. (2) Remove the adaptors from the standby static probe and the standby pitot probe. (3) Remove the cover from the opposite standby static probe. (4) Remove the piece of plastic and colored adhesive tape from the drain holes of the standby pitot probe. (5) Remove adhesive tape from the vane of the AOA sensor 3. (6) Install the slip on covers on the standby static probe and the standby pitot probe. **ON A/C 201-220, 236-238, R Subtask 34-21-00-020-050-A A. Remove the ground pressure generator (1) Disconnect the ground pressure generator. (2) Remove the adaptors from the standby static probe and the standby pitot probe. (3) Remove the cover from the opposite standby static probe. (4) Remove the piece of plastic from the opposite standby static probe. (5) Remove adhesive tape from the vane of the AOA sensor 3.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 510 Aug 01/09

(6) Install the slip on covers on the standby static probe and the standby pitot probe. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, R Subtask 34-21-00-865-051 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 Subtask 34-21-00-860-057 C. Put the aircraft back to its initial configuration. (1) On the SWITCHING panel 8VU, set the AIR DATA selector switch to NORM position (2) Do the EIS stop procedure (PFD only) (Ref. TASK 31-60-00-860-002). (3) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF. (4) Do a reset of each ELAC: - on the panel 49VU, open then close the ELAC1 circuit breaker, - on the panel 121VU, open then close the ELAC2 circuit breaker. (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (6) Make sure that the work area is clean and clear of tool(s) and other items. (7) Make sure that the drain holes on the pitot probes are not blocked by unwanted materials (Ref. TASK 34-11-15-200-001).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 511 Aug 01/09

R TASK 34-21-00-720-001 Functional Test of the Standby Airspeed Indicator 1. __________________ Reason for the Job To make sure that the standby instruments operate independently. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 36122 98D34003500000

circuit breaker(s) safety clip(s) colored adhesive tape 1 GENERATOR - GROUND PRESSURE MINI. 100 MB 1 ADAPTOR-CHARGING,PITOT PROBE 1 ADAPTER COVER-STATIC PORT

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-24-34-600-001

Bleeding of the Standby Air Data System

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 512 Aug 01/09

3. __________ Job Set-up **ON A/C 001-049, 051-099, 101-105, 151-199, Subtask 34-21-00-860-050 A. Aircraft Maintenance Configuration (1) Drain the standby air data system (Ref. TASK 12-24-34-600-001). (2) Remove the slip on covers from the standby static probes and the standby pitot probe and connect the GENERATOR - GROUND PRESSURE MINI. 100 MB to : - the L or R standby static probe with the ADAPTER COVER-STATIC PORT (98D34003500100). - the standby pitot probe with the ADAPTOR-CHARGING,PITOT PROBE.

R R

(3) Seal the Standby probes: CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT _______ SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE. ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE FIRST AND USE THE COLORED ADHESIVE TAPE TO ATTACH THE PLASTIC. IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE, THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE PROBE. (a) Seal the drain holes of the pitot probe with the piece of plastic and colored adhesive tape of very bright color. (b) Seal the opposite standby static probe with the piece of plastic (see CAUTION above) and with the STATIC PORT COVER (98D34003500103) from the ADAPTER COVER-STATIC PORT.. (4) Precautions CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT _______ DAMAGE TO INSTRUMENTS: - THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg) - CHANGES IN STATIC PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE - DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 513 Feb 01/09

CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS _______ THAN THE STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg). (5) Start the ground pressure generator. **ON A/C 201-220, 236-238, R Subtask 34-21-00-860-050-A A. Aircraft Maintenance Configuration (1) Drain the standby air data system (Ref. TASK 12-24-34-600-001). (2) Remove the slip on covers from the standby static probes and the standby pitot probe and connect the GENERATOR - GROUND PRESSURE MINI. 100 MB to : - the L or R standby static probe with the ADAPTER COVER-STATIC PORT (98D34003500100). - the standby pitot probe with the ADAPTOR-CHARGING,PITOT PROBE. NOTE : The ADAPTOR-CHARGING,PITOT PROBE is on the drain hole. Thus it ____ is not necessary to seal the drain hole of the pitot probe. (3) Seal the opposite standby static probe with the piece of plastic and with the STATIC PORT COVER (98D34003500103) from the ADAPTER COVERSTATIC PORT.. (4) Precautions CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT _______ DAMAGE TO INSTRUMENTS: - THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg) - CHANGES IN STATIC PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE - DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED. CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS _______ THAN THE STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 514 Aug 01/09

(5) Start the ground pressure generator. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, R Subtask 34-21-00-865-056 B. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 R 4. Procedure _________ R Subtask 34-21-00-720-050 A. Test of the Standby Airspeed Indicator ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the ground pressure generator : - set a static pressure of 314.8 hPa (29,000 ft) - set an impact pressure of 200.1 hPa (340 Kts).

On the standby airspeed indicator: - the pointer shows 340 Kts (+ or - 5 Kts).

- set a static pressure of 571.8 hPa (15,000 ft) - set an impact pressure of 153.5 hPa (300 Kts).

- the pointer shows 300 Kts (+ or - 5 Kts).

- set a static pressure of 843 hPa (5000 ft)

- the pointer shows 180 Kts (+ or - 5 Kts).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 515 Aug 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set an impact pressure of 53.5 hPa (180 Kts). R 5. Close-up ________ **ON A/C 001-049, 051-099, 101-105, 151-199, Subtask 34-21-00-860-051 A. Put the aircraft back to its initial configuration. (1) On the ground pressure generator, slowly decrease the pressure until you get atmospheric pressure. (2) Stop the ground pressure generator. (3) Disconnect the ground pressure generator. (4) Remove the adaptors from the standby static probes and the standby pitot probe. (5) Remove the cover from the opposite standby static probe. (6) Remove the piece of plastic from the opposite standby static probe. (7) Remove the piece of plastic and colored adhesive tape from the drain holes of the standby pitot probe. (8) Install the slip on covers on the standby static probes and the standby pitot probe. (9) Do a reset of each ELAC: - on the panel 49VU, open then close the ELAC1 C/B, - on the panel 121VU, open then close the ELAC2 C/B.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 516 Aug 01/09

**ON A/C 201-220, 236-238, R Subtask 34-21-00-860-051-A A. Put the aircraft back to its initial configuration. (1) On the ground pressure generator, slowly decrease the pressure until you get atmospheric pressure. (2) Stop the ground pressure generator. (3) Disconnect the ground pressure generator. (4) Remove the adaptors from the standby static probes and the standby pitot probe. (5) Remove the cover from the opposite standby static probe. (6) Remove the piece of plastic from the opposite standby static probe. (7) Install the slip on covers on the standby static probes and the standby pitot probe. (8) Do a reset of each ELAC: - on the panel 49VU, open then close the ELAC1 C/B, - on the panel 121VU, open then close the ELAC2 C/B. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, R Subtask 34-21-00-865-057 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 517 Aug 01/09

R TASK 34-21-00-720-002 Functional Test of the Standby Altimeter 1. __________________ Reason for the Job To make sure that the standby altimeter and the metric altimeter operate correctly with information from the ground pressure generator. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 98D10103500001 98D34003500000

circuit breaker(s) safety clip(s) 1 GENERATOR - GROUND PRESSURE MINI. 100 MB 1 COVER-STATIC PROBE 1 ADAPTER COVER-STATIC PORT

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-24-34-600-001 24-41-00-861-002 24-41-00-862-002 32-00-00-860-001 32-00-00-860-002

Bleeding of the Standby Air Data System Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Flight Configuration Precautions with Electrical Power Ground Configuration after Flight Configuration with Electrical Power

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 518 Aug 01/09

3. __________ Job Set-up WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. R Subtask 34-21-00-860-052 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Take the applicable safety precautions before you open the LGCIU circuit breakers (Ref. TASK 32-00-00-860-001). (3) Precautions CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT _______ DAMAGE TO INSTRUMENTS: - THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg) - CHANGES IN STATIC PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE - DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED. CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS _______ THAN THE STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg). (4) Remove the slip on covers from the L and R static probes 7DA3 and 8DA3 of the standby system. (5) Connect the GENERATOR - GROUND PRESSURE MINI. 100 MB to one standby static probe with the ADAPTER COVER-STATIC PORT (98D34003500100). (6) Seal the opposite standby static probe with the COVER-STATIC PROBE (98D34003500103). (7) Start the ground pressure generator and set a static pressure of 1013 mb. (8) Drain the standby air data system (Ref. TASK 12-24-34-600-001).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 519 Aug 01/09

Subtask 34-21-00-865-053 B. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 121VU HYDRAULIC/LGCIU/SYS2 2GA Q35 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34 Subtask 34-21-00-865-054 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/ALTM 16FN F14

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,  R  CES

 

Page 520 Aug 01/09

R 4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, Subtask 34-21-00-720-051 A. Test of the Standby and Metric Altimeters ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the standby altimeter and the metric altimeter, set a barometric pressure of 1013 hPa. 2. On the ground pressure generator: - set a static pressure of 977.1 hPa (1000 ft or 305 m).

Make sure that the standby altimeter indicates 1000 ft (+ or - 20 ft) and the metric altimeter indicates 305 m (+ or - 7 m).

- Set a static pressure of 908.1 hPa (3000 ft or 915 m).

- Make sure that the standby altimeter indicates 3000 ft (+ or - 30 ft) and the metric altimeter indicates 915 m (+ or - 10 m).

- Set a static pressure of 843 hPa (5000 ft or 1525 m)

- make sure that the standby altimeter indicates 5000 ft (+ or - 40 ft) and the metric altimeter indicates 1525 m (+ or - 13 m).

- set a static pressure of 571.8 hPa (15,000 ft or 4570 m).

- make sure that the standby altimeter indicates 15,000 ft (+ or - 110 ft) and the metric altimeter indicates 4570 m (+ or - 34 m).

- set a static pressure of 314.8 hPa (29,000 ft or 8840 m).

- make sure that the standby altimeter indicates 29,000 ft (+ or - 190 ft) and the metric altimeter indicates 8840 m (+ or - 60 m).

- slowly decrease the pressure until you get atmospheric pressure.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 521 Aug 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------3. Stop the ground pressure generator. **ON A/C 151-199, 201-220, 236-238, R Subtask 34-21-00-720-051-A A. Test of the Standby Altimeter ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the standby altimeter, set a barometric pressure of 1013 hPa. 2. On the ground pressure generator: - set a static pressure of 977.1 hPa (1000 ft).

- Make sure that the standby altimeter indicates 1000 ft (+ or - 20 ft).

- Set a static pressure of 908.1 hPa (3000 ft).

- Make sure that the standby altimeter indicates 3000 ft (+ OR - 30 ft).

- Set a static pressure of 843 hPa (5000 ft).

- make sure that the standby altimeter indicates 5000 ft (+ or - 40 ft).

- set a static pressure of 571.8 hPa (15,000 ft).

- make sure that the standby altimeter indicates 15,000 ft (+ or - 110ft).

- set a static pressure of 314.8 hPa (29,000 ft).

- make sure that the standby altimeter indicates 29,000 ft (+ or - 190 ft).

- slowly decrease the pressure until you get atmospheric pressure. 3. Stop the ground pressure generator.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,   CES

 

Page 522 Aug 01/09

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, 5. Close-up ________ Subtask 34-21-00-860-054 A. Put the aircraft back to its initial configuration. (1) Disconnect the ground pressure generator. (2) Remove the adaptor from the standby static probe. (3) Remove the cover from the opposite standby static probe. (4) Install the slip on covers on the static probes. (5) Close the LGCIU circuit breakers and put the aircraft back to its inertial cofiguration (Ref. TASK 32-00-00-860-002). (6) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-21-00-865-055 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 121VU HYDRAULIC/LGCIU/SYS2 2GA Q35 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-00 201-220, 236-238,  R  CES

 

Page 523 Feb 01/10

ALTIMETER - STANDBY (3FN) - REMOVAL/INSTALLATION ________________________________________________ TASK 34-21-22-000-001 Removal of the Standby Altimeter (3FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R

No specific No specific No specific F1402369

blanking caps blanking plugs circuit breaker(s) safety clip(s) 1 EXTRACTING TOOL

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-061, 101-105, 34-21-22-991-001

Fig. 401

**ON A/C 062-099, 151-199, 201-220, 236-238, 34-21-22-991-001-B

Fig. 401A

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-22 201-220, 236-238,   CES

 

Page 401 Feb 01/10

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, 3. __________ Job Set-up Subtask 34-21-22-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/ALTM 16FN F14 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 Subtask 34-21-22-010-050 B. Remove the thermoformed cover from the center instrument panel. 4. Procedure _________ **ON A/C 001-049, 051-061, 101-105, (Ref. Fig. 401/TASK 34-21-22-991-001) **ON A/C 062-099, 151-199, 201-220, 236-238, (Ref. Fig. 401A/TASK 34-21-22-991-001-B) **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, Subtask 34-21-22-020-050 A. Removal of the Standby Altimeter (3FN) (1) Loosen the screws (1). Do not remove them. (2) Push the screws (1) to release the standby altimeter (2) from the clamp. R R

(3) Disengage the standby altimeter (2) from its housing with EXTRACTING TOOL (F1402369). (4) Disconnect the electrical connector (6).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-22 201-220, 236-238,   CES

 

Page 402 Feb 01/10

R

Standby Altimeter Figure 401/TASK 34-21-22-991-001

  EFF : 001-049, 051-061, 101-105,  34-21-22    CES

 

Page 403 Feb 01/07

Standby Altimeter Figure 401A/TASK 34-21-22-991-001-B   R EFF : 062-099, 151-199, 201-220, 236-238,  34-21-22    CES

 

Page 404 Feb 01/08

(5) Disconnect the quick-disconnect coupling (5). (6) Remove the standby altimeter (2). (7) Put blanking caps on the disconnected electrical connectors (4) and (6). (8) Put blanking plugs on the disconnected line ends (3) and (5).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-22 201-220, 236-238,  R  CES

 

Page 405 Feb 01/10

TASK 34-21-22-400-001 Installation of the Standby Altimeter (3FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------25-13-41-000-002 25-13-41-400-002 33-13-00-710-001

Removal of the Sidewall Panels Installation of the Sidewall Panels Operational Test of the Instrument and Panel Integral Lighting

**ON A/C 001-049, 051-061, 101-105, 34-21-22-991-001

Fig. 401

**ON A/C 062-099, 151-199, 201-220, 236-238, 34-21-22-991-001-B

Fig. 401A

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, 34-21-22-991-002

Fig. 402

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-22 201-220, 236-238,  R  CES

 

Page 406 Feb 01/10

R 3. __________ Job Set-up R Subtask 34-21-22-865-051 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/ALTM 16FN F14 R 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED

4LF

Y04

Subtask 34-21-22-010-051 B. Remove the sidewall panel 211LW (Ref. TASK 25-13-41-000-002). R 4. Procedure _________ **ON A/C 001-049, 051-061, 101-105, (Ref. Fig. 401/TASK 34-21-22-991-001) **ON A/C 062-099, 151-199, 201-220, 236-238, R (Ref. Fig. 401A/TASK 34-21-22-991-001-B) **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, R Subtask 34-21-22-420-050 A. Installation of the Standby Altimeter (3FN) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-22 201-220, 236-238,   CES

 

Page 407 Aug 01/09

(3) Remove the blanking plugs from the line ends (3) and (5). (4) Make a loop of the flexible hose and connect the quick-disconnect coupling (5) to the receptacle (3) of the standby altimeter (2). (Ref. Fig. 402/TASK 34-21-22-991-002) (5) Make sure that you can see the blue ring on the quick-disconnect coupling. (6) Pull the quick-disconnect coupling to make sure that it is correctly attached. (7) Remove the blanking caps from the electrical connectors (4) and (6). (8) Connect the electrical connector (6) to the receptacle (4) of the standby altimeter (2). (9) Install the standby altimeter (2) in its housing. (10) Look behind the standby altimeter and make sure that the position of the flexible hoses (static pressure line) is satisfactory (no crushing, kinks, creases or folds). (11) Tighten the screws (1). Subtask 34-21-22-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 16FN, 4LF Subtask 34-21-22-710-050 C. Do the operational test of the instrument and panel integral lighting (Ref. TASK 33-13-00-710-001).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-22 201-220, 236-238,  R  CES

 

Page 408 Aug 01/09

Connection of the Quick-disconnect coupling Figure 402/TASK 34-21-22-991-002   R EFF : 001-049, 051-099, 101-105, 151-199,  34-21-22 201-220, 236-238,   CES

 

Page 409 Feb 01/08

R 5. Close-up ________ R Subtask 34-21-22-410-050 A. Close Access (1) Install the thermoformed cover on the center instrument panel. (2) Install the sidewall 211LW (Ref. TASK 25-13-41-400-002). (3) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-22 201-220, 236-238,   CES

 

Page 410 Aug 01/09

ALTIMETER - STANDBY (3FN) - ADJUSTMENT/TEST ___________________________________________ TASK 34-21-22-820-001 ADJUSTING/ALIGNING/CALIBRATING of the Standby Altimeter 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-21-22-000-001 34-21-22-400-001 34-21-25-000-001 34-21-25-400-001 CMM 341027 CMM 342122

Removal of the Standby Altimeter (3FN) Installation of the Standby Altimeter (3FN) Removal of the Metric Altimeter (15FN) Installation of the Metric Altimeter (15FN)

3. __________ Job Set-up R Subtask 34-21-22-869-050 A. Not Applicable R 4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, Subtask 34-21-22-020-053-A A. Remove the standby altimeter (Ref. TASK 34-21-22-000-001), and the metric altimeter (Ref. TASK 34-21-25-000-001).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-22 201-220, 236-238,   CES

 

Page 501 Aug 01/09

Subtask 34-21-22-820-050-A B. Do a calibration test of the standby altimeter, and the metric altimeter. (Ref. CMM 342122). (Ref. CMM 341027). Subtask 34-21-22-420-053-A C. Install the standby altimeter (Ref. TASK 34-21-22-400-001), and the metric altimeter (Ref. TASK 34-21-25-400-001). **ON A/C 151-199, 201-220, 236-238, R Subtask 34-21-22-020-053 A. Remove the standby altimeter (Ref. TASK 34-21-22-000-001). Subtask 34-21-22-820-050 B. Do a calibration test of the standby altimeter (Ref. CMM 342122). Subtask 34-21-22-420-053 C. Install the standby altimeter (Ref. TASK 34-21-22-400-001).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-22 201-220, 236-238,   CES

 

Page 502 Aug 01/09

ALTIMETER - METRIC (15FN) - REMOVAL/INSTALLATION ________________________________________________ TASK 34-21-25-000-001 Removal of the Metric Altimeter (15FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R

No specific No specific No specific F1402369

blanking caps blanking plugs circuit breaker(s) safety clip(s) 1 EXTRACTING TOOL

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-21-25-991-001

Fig. 401

3. __________ Job Set-up Subtask 34-21-25-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 Subtask 34-21-25-010-050 B. Remove the thermoformed cover from the center instrument panel.

  EFF : 001-049, 051-099, 101-105,  34-21-25    CES

 

Page 401 Feb 01/10

4. Procedure _________ (Ref. Fig. 401/TASK 34-21-25-991-001) Subtask 34-21-25-020-050 A. Removal of the Metric Altimeter (15FN) (1) Loosen the screws (1), do not remove them . (2) Push the screws (1) to release the metric altimeter (2). R R

(3) Remove the metric altimeter (2) from its housing with EXTRACTING TOOL (F1402369). (4) Disconnect the electrical connector (5). (5) Disconnect the quick-disconnect coupling (6). (6) Remove the metric altimeter (2). (7) Put blanking caps on the disconnected electrical connectors (3) and (5). (8) Put blanking plugs on the disconnected pneumatic connectors (4) and (6).

  EFF : 001-049, 051-099, 101-105,  34-21-25    CES

 

Page 402 Feb 01/10

R

Metric Altimeter Figure 401/TASK 34-21-25-991-001

  EFF : 001-049, 051-099, 101-105,  34-21-25    CES

 

Page 403 Feb 01/07

TASK 34-21-25-400-001 Installation of the Metric Altimeter (15FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R R

25-13-41-000-002 25-13-41-400-002 33-13-00-710-001

R

34-21-25-991-001 34-21-25-991-002

Removal of the Sidewall Panels Installation of the Sidewall Panels Operational Test of the Instrument and Panel Integral Lighting Fig. 401 Fig. 402

3. __________ Job Set-up Subtask 34-21-25-865-051 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 R

Subtask 34-21-25-010-051

R

B. Remove the sidewall panel 211LW (Ref. TASK 25-13-41-000-002).

  EFF : 001-049, 051-099, 101-105,  34-21-25    CES

 

Page 404 Feb 01/07

4. Procedure _________ (Ref. Fig. 401/TASK 34-21-25-991-001) Subtask 34-21-25-420-050 A. Installation of the Metric Altimeter (15FN) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. R R

(3) Remove the blanking caps from the electrical connectors (3) and (5).

R R

(4) Make sure that the electrical connectors are clean and in the correct condition.

R

(5) Connect the electrical connector (5) to the receptacle (3) of the metric altimeter (2).

R R

(6) Remove the blanking plugs from the quick-disconnect couplings (4) and (6).

R R R

(7) Connect the quick-disconnect coupling (6) to the receptacle (4) of the metric altimeter (2). (Ref. Fig. 402/TASK 34-21-25-991-002)

R R

(8) Make sure that you can see the blue ring on the quick-disconnect coupling.

R R

(9) Pull the quick-disconnect coupling to be sure that it is correctly attached.

R

(10) Install the metric altimeter (2) in its housing.

R R R

(11) Look behind the metric altimeter and make sure that the position of the flexible hose (static pressure line) is satisfactory (no crushing, kings, crease or folds).

R

(12) Tighten the screws (1). Subtask 34-21-25-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 4LF

  EFF : 001-049, 051-099, 101-105,  34-21-25    CES

 

Page 405 Feb 01/07

R R

Illustration of the Quick-disconnect coupling Figure 402/TASK 34-21-25-991-002

  EFF : 001-049, 051-099, 101-105,  34-21-25    CES

 

Page 406 Feb 01/07

Subtask 34-21-25-710-050 C. Do the operational test of the instrument and panel integral lighting (Ref. TASK 33-13-00-710-001). 5. Close-up ________ Subtask 34-21-25-410-050 A. Put the aircraft back to its initial configuration. (1) Install the thermoformed cover on the center instrument panel. R

(2) Install the sidewall panel 211LW (Ref. TASK 25-13-41-400-002).

R

(3) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : 001-049, 051-099, 101-105,  34-21-25    CES

 

Page 407 Feb 01/07

INDICATOR - STANDBY AIRSPEED (9FN) - REMOVAL/INSTALLATION _________________________________________________________ TASK 34-21-26-000-001 Removal of the Standby Airspeed Indicator (9FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R

No specific No specific No specific F1402369

blanking caps blanking plugs circuit breaker(s) safety clip(s) 1 EXTRACTING TOOL

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-061, 101-105, 34-21-26-991-001

Fig. 401

**ON A/C 062-099, 151-199, 201-220, 236-238, 34-21-26-991-001-A

Fig. 401A

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-26 201-220, 236-238,   CES

 

Page 401 Feb 01/10

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, 3. __________ Job Set-up Subtask 34-21-26-865-053 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 Subtask 34-21-26-010-050 B. Remove the thermoformed cover from the center instrument panel. 4. Procedure _________ **ON A/C 001-049, 051-061, 101-105, (Ref. Fig. 401/TASK 34-21-26-991-001) **ON A/C 062-099, 151-199, 201-220, 236-238, (Ref. Fig. 401A/TASK 34-21-26-991-001-A) **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, Subtask 34-21-26-020-050 A. Removal of the Standby Airspeed Indicator (9FN) (1) Loosen the screws (1). Do not remove them. (2) Push the screws (1) to release the standby airspeed indicator (2). R R

(3) Disengage the standby airspeed indicator (2) from its housing with EXTRACTING TOOL (F1402369)

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-26 201-220, 236-238,   CES

 

Page 402 Feb 01/10

R

Standby Airspeed Indicator Figure 401/TASK 34-21-26-991-001

  EFF : 001-049, 051-061, 101-105,  34-21-26    CES

 

Page 403 Feb 01/07

Standby Airspeed Indicator Figure 401A/TASK 34-21-26-991-001-A   R EFF : 062-099, 151-199, 201-220, 236-238,  34-21-26    CES

 

Page 404 Feb 01/08

(4) Disconnect the electrical connector (6). (5) Disconnect the red and green quick-disconnect couplings (5) from the connectors (4). (6) Remove the standby airspeed indicator (2). (7) Put blanking caps on the disconnected electrical connectors (3) and (6). (8) Put blanking plugs on the disconnected line ends (4) and (5).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-26 201-220, 236-238,  R  CES

 

Page 405 Aug 01/09

R TASK 34-21-26-400-001 Installation of the Standby Airspeed Indicator (9FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------25-13-41-000-002 25-13-41-400-002 33-13-00-710-001

Removal of the Sidewall Panels Installation of the Sidewall Panels Operational Test of the Instrument and Panel Integral Lighting

**ON A/C 001-049, 051-061, 101-105, 34-21-26-991-001

Fig. 401

**ON A/C 062-099, 151-199, 201-220, 236-238, R 34-21-26-991-001-A

Fig. 401A

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, R 34-21-26-991-002

Fig. 402

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-26 201-220, 236-238,   CES

 

Page 406 Aug 01/09

R 3. __________ Job Set-up R Subtask 34-21-26-865-054 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 Subtask 34-21-26-010-051 B. Remove the sidewall panel 211LW (Ref. TASK 25-13-41-000-002) R 4. Procedure _________ **ON A/C 001-049, 051-061, 101-105, (Ref. Fig. 401/TASK 34-21-26-991-001) **ON A/C 062-099, 151-199, 201-220, 236-238, R (Ref. Fig. 401A/TASK 34-21-26-991-001-A) **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, R Subtask 34-21-26-420-050 A. Installation of the Standby Airspeed Indicator (9FN) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking plugs from the line ends (4) and (5).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-26 201-220, 236-238,   CES

 

Page 407 Aug 01/09

(4) Connect the quick-disconnect couplings (5) of the pressure lines (green and red) to the related connectors (4) of the standby airspeed indicator (2). (Ref. Fig. 402/TASK 34-21-26-991-002) (5) Make sure that you can see the blue ring on the quick-disconnect couplings. (6) Pull the quick-disconnect couplings to be sure that they are correctly attached. (7) Remove the blanking caps from the electrical connectors (3) and (6). (8) Make sure that the electrical connectors are clean and in the correct condition. (9) Connect the electrical connector (6) to the receptacle (3) of the standby airspeed indicator (2). (10) Install the standby airspeed indicator (2) in its housing. (11) Look behind the standby airspeed indicator and make sure that the position of the flexible hoses (static and total pressure lines) is satisfactory (no crushing, kinks, creases or folds). (12) Tighten the screws (1). Subtask 34-21-26-865-055 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 4LF Subtask 34-21-26-710-050 C. Do the operational test of the instrument and panel integral lighting (Ref. TASK 33-13-00-710-001).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-26 201-220, 236-238,  R  CES

 

Page 408 Aug 01/09

Illustration of the Quick-disconnect coupling Figure 402/TASK 34-21-26-991-002   R EFF : 001-049, 051-099, 101-105, 151-199,  34-21-26 201-220, 236-238,   CES

 

Page 409 Feb 01/08

R 5. Close-up ________ R Subtask 34-21-26-410-050 A. Put the aircraft back to its initial configuration. (1) Install the thermoformed cover on the center instrument panel. (2) Install the sidewall panel 211LW (Ref. TASK 25-13-41-400-002). (3) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-21-26 201-220, 236-238,   CES

 

Page 410 Aug 01/09

INDICATOR - STANDBY AIRSPEED (9FN) - ADJUSTMENT/TEST ____________________________________________________ TASK 34-21-26-820-001 ADJUSTING/ALIGNING/CALIBRATING of the Standby Airspeed Indicator 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-21-26-000-001 34-21-26-400-001 CMM 341002

Removal of the Standby Airspeed Indicator (9FN) Installation of the Standby Airspeed Indicator (9FN)

3. __________ Job Set-up R Subtask 34-21-26-020-053 A. Remove the standby airspeed indicator (Ref. TASK 34-21-26-000-001). R 4. Procedure _________ R Subtask 34-21-26-820-050 A. Do a calibration test of the standby airspeed indicator (Ref. CMM 341002).

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Page 501 Aug 01/09

R 5. Close-up ________ R Subtask 34-21-26-420-053 A. Install the standby airspeed indicator (Ref. TASK 34-21-26-400-001).

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Page 502 Aug 01/09

STANDBY DATA : ATTITUDE AND HEADING - DESCRIPTION AND OPERATION _______________________________________________________________ 1. General _______ A. Standby Heading The standby heading is performed by a magnetic compass that is an independent instrument which provides the flight crew with the A/C magnetic heading. It is installed on the top of the windshield center post and allows a check of the heading provided by the main sources of the heading system. It acts in standby when these systems are inoperative. B. Standby Attitude The standby attitude is performed by a gyroscopic horizon that is an independent instrument which provides the flight crew, with a constant indication of the aircraft attitude. It is contained in a 3 ATIs case and installed on the center instrument panel. It allows a check of the attitude provided by the main sources of attitude system. It acts in standby when these systems are inoperative. 2. __________________ Component Location **ON A/C 001-049, 051-061, 101-105, 201-203, (Ref. Fig. 001) R

**ON A/C 062-099, 151-199, 204-212, 214-220, 236-238, (Ref. Fig. 001A)

R

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-212, 214-220, 236-238, ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2FN COMPASS-STANDBY 211 831 34-22-23 7FN IND-STANDBY HORIZON 4VU 211 831 34-22-24 3. __________________ System Description

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Standby Data - Attitude and Heading - Component Location Figure 001   R EFF : 001-049, 051-061, 101-105, 201-203,  34-22-00 Page 2   Config-1 May 01/05  CES

 

Standby Data - Attitude and Heading - Component Location Figure 001A   R EFF : 062-099, 151-199, 204-212, 214-220,  34-22-00 Page 3 236-238,  Config-1 Feb 01/08  CES

 

**ON A/C 001-049, 051-061, 101-105, 201-203, (Ref. Fig. 002, 003) A. Standby Compass The standby compass consists of a magnetic element rotating inside a compass bowl, immersed in a damping liquid. The magnetic element (1) is linked to a graduated compass card which moves against a lubber line (2) and gives the magnetic heading. Below the viewing window are two apertures (4) marked N.S and E.W, allowing to achieve compensation by positioning the two small magnetized bars (compensator). Above the viewing window is a non-magnetic lamp (3) assembly which provides illumination of the compass card. R

**ON A/C 062-099, 151-199, 204-212, 214-220, 236-238, (Ref. Fig. 002, 003A) A. Standby Compass The standby compass consists of a magnetic element rotating inside a compass bowl, immersed in a damping liquid. The magnetic element (1) is linked to a graduated compass card which moves against a lubber line (2) and gives the magnetic heading. Above the viewing window are two apertures (4) marked B (E.W) and C (N.S) , allowing to achieve compensation by positioning the two small magnetized bars (compensator). Below the viewing window is a non-magnetic lamp (3) assembly which provides illumination of the compass card.

R

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-212, 214-220, 236-238, B. Standby Horizon Indicator The standby horizon indicator is supplied with 28VDC from essential bus 401PP. A static inverter in the instrument converts this 28VDC into three phase alternate current to supply the gyroscopic motor. The gyro rotor rotates at high speed (> 23,000 RPM) around its vertical axis and provides the vertical reference. The gimbal assy comprises two orthogonal axes (pitch and roll). The internal gimbal which includes the stator controls the rotation of the drum in the pitch axis by means of gear. The pitch gimbal is restricted to approximately plus or minus 85 degrees around the pitch axis (mechanical stop).

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Standby Data - Attitude and Heading - Electrical Circuit Figure 002   R EFF : 001-049, 051-099, 101-105, 151-199,  34-22-00 Page 5 201-212, 214-220, 236-238,  Config-1 Feb 01/08  CES

 

Standby Data - Attitude and Heading - Data Indicating Figure 003   R EFF : 001-049, 051-061, 101-105, 201-203,  34-22-00 Page 6   Config-1 May 01/05  CES

 

Standby Data - Attitude and Heading - Data Indicating Figure 003A   R EFF : 062-099, 151-199, 204-212, 214-220,  34-22-00 Page 7 236-238,  Config-1 Feb 01/08  CES

 

The external gimbal controls the roll rotation. The roll gimbal has unrestricted 360 degrees rotation around the roll axis. The gyro pin axis is maintained in the vertical position by the erection system (unstable pendulum erector) which is removed when the rotor axis deviates more than 9 degrees plus or minus 2 degrees. The accuracy of the vertical position in clean configuration is less than 0.5 degree. The fast resetting of the gyroscopic horizon can be activated by pulling the knob (8) located in the lower R corner of the indicator. The indicator provides the following information : - roll angle, - pitch angle, - instrument failure (RED flag). (1) Pitch information The aircraft symbol (black and yellow) (7) is fixed. The pitch drum (9), in the center of the instrument is divided into two zones separated by the reference horizon (white) : the upper part is blue, the lower part is brown. The pitch indications are displayed by means of a drum which is graduated between -80 and +80 degrees. (2) Roll information The roll information is given by a pointer (10) which moves in front of a dial (5) graduated in 10 degrees increments between -30 and +30 degrees. (3) Failure warning The flag (6) comes into view if a failure is detected in the electrical power supply or if the gyro rotor speed drops below 18,000 RPM.

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__________________________________________________________ STANDBY DATA : INTEGRATED STANDBY INSTRUMENT SYSTEM (ISIS) DESCRIPTION AND OPERATION _________________________ 1. General _______ A. ISIS Indicator The Integrated Standby Instrument System (ISIS) indicator replaces the three conventional standby instruments: - the standby altimeter - the standby horizon indicator - the standby airspeed indicator. It is located on the center instrument panel. B. Standby Compass The standby heading is given by a magnetic compass that is an independent instrument which provides the flight crew with the A/C magnetic heading. It is installed on the top of the windshield center post and allows a check of the heading provided by the main sources of the heading system. It acts in standby when these systems are inoperative. 2. Component __________________ Location (Ref. Fig. 001) ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2FN COMPASS-STANDBY 210 831 34-22-23 22FN IND-ISIS 401VU 211 34-22-25 3. __________________ System Description A. ISIS Indicator (1) Initialization function (Ref. Fig. 002) This function corresponds to the initialization phase of the ISIS indicator. As soon as the ISIS indicator is energized, the display shows these four yellow digital boxes for approximately 90 s: - ATT for the standby horizon function - SPD for the airspeed indicator function, ALT for the altimeter function the standby horizon - INIT 90 S for the initialization function. ISIS performs an excessive motion test during the whole initialization phase.

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ISIS - Component Location Figure 001   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 2 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Initialization Display Figure 002   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 3 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

If aircraft motion is detected, the attitude information is flagged and a yellow ATT:RST flag with a red ATT flag are displayed at the end of the initialization phase (Ref. Fig. 003) Pressing the RST pushbutton switch more than 2 seconds then restarts the initialization phase. The display also shows the baro reference. Baro reference can be set during the initialization phase. (2) Standby airspeed indicator function (Ref. Fig. 004) (a) The standby airspeed indicator function measures the pitot/static pressure differential from the standby air data system and provides airspeed indication in knots. The airspeed indication is displayed by means of a white tape positioned vertically in the left part of the display area. The airspeed scale is linear with five-knot graduations from 5 to 250 kts, ten-knot graduations from 250 to 520 kts and digital values every 20 kts. This tape moves up and down to indicate the A/C actual speed value in front of a fixed yellow reference line. When the airspeed data is not valid, a red SPD flag is displayed in place of the airspeed scale. (b) Mach number (Ref. Fig. 004) The Mach number is always computed. When the Mach number is above .5 (increasing sense) it is displayed in green in the left bottom part of the display area, just below the speed scale in green color. The display range is .50 to .99 (increasing sense) and .99 to .45 (decreasing sense). In case of failure, a red M flag is displayed in place of the Mach number. (3) Standby altimeter function (Ref. Fig. 005) (a) The standby altimeter indication is supplied with static pressure by the standby air data system to indicate the barometric altitude of the aircraft in feet. The barometric altitude indication is displayed by means of a black tape with white indications, positioned vertically in the right part of the display area. The altitude scale is linear from - 2000 to + 50,000 ft with 100 ft graduations, with digital indications every 500 ft.

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ISIS Indicator - Excessive motion during the initialization phase. Figure 003   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 5 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Airspeed Display Figure 004   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 6 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Altitude Display Figure 005   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 7 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

This tape moves up and down with respect to a window surrounded in yellow within which the A/C actual altitude value is displayed in green digits. The window is surrounded in cyan when an altitude bug is hidden by this read-out. In this window, the hundreds of feet are written in a large size whereas the tens and units are displayed by a drum operating as a conventional mechanical altimeter. When the altitude data is not valid, a red ALT flag is displayed in place of the altitude tape, but the selected pressure is always displayed. (b) Negative altitude (Ref. Fig. 006) If the altitude is negative, the NEG indication is displayed in white close to the digital read-out. The range is - 2000 to 0 ft. (c) Optional metric altimeter function (Ref. Fig. 007, 008) The metric altitude can be displayed in the right top part of display in addition to the altitude in feet. The metric altitude indication is displayed in green by means a digital read-out surrounded in yellow. The cyan letter M is written just after the altitude value. The altitude in meters rounded to the closest 10th of meters. In case of negative altitude, the NEG indication is displayed white just before the metric altitude value.

the of is in

(4) Reference barometric pressure indication (Ref. Fig. 009) (a) By pushing the barometric reference (BARO) selector knob located in the right bottom corner of the indicator, the pilot can select the standard barometric pressure 1013.25 hPa (29.9211 in.Hg) or the barometric correction whose value (without units) can be adjusted by turning the knob (first press: STD, second press: baro correction). The barometric correction is displayed in cyan, in the center bottom part of the display, in the range from 745 to 1100 hPa, with a variation of 10 hPa per rotation of the knob. In case of standard barometric pressure selection, a cyan STD flag is displayed in place of the barometric correction value.

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ISIS Indicator - Negative Altitude Display Figure 006   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 9 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Metric Altitude Display Figure 007   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 10 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Negative Altitude Display (in meters) Figure 008   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 11 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Reference Barometric Display Figure 009   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 12 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

(5) Standby horizon function (Ref. Fig. 010) (a) Aircraft symbol The fixed symbol is in yellow color, it comprises three parts: two simplified wing/landing gear parts plus a center part. It provides the pilot with a quick glance attitude information, both in pitch and roll with respect to the attitude sphere. (b) Pitch angle information (Ref. Fig. 010) The A/C present pitch angle is given by the vertical displacements of the pitch attitude scale with respect to the center of the A/C symbol. The scale moves behind the cut-sphere shaped window, limited by the lines of an upper (blue) and a lower (brown) sector. The scale rotates around the center of the A/C symbol in accordance with the A/C present roll angle. The pitch scale comprises white reference lines and associated pitch angle values. The lines are given every 2.5 degrees from 30 to + 30 degrees. Beyond 30 degrees, red large arrow heads (V-shaped) indicate an excessive attitude and the direction to follow in order to reduce it. (c) Roll angle information A yellow triangle which remains on the line going through the center of the A/C symbol and which is perpendicular to the horizon line, moves against the fixed roll scale on the upper contour of the attitude sphere. This fixed roll scale comprises white marks for the 10 degrees, 20 degrees, 30 degrees, 45 degrees and 60 degrees significant values, on either side of the zero position (horizontal wings) which is indicated by a small fixed black triangle surrounded in white. (d) Attitude failure presentation (Ref. Fig. 011) In case of detected failure of the pitch and/or roll angle information, the whole attitude and guidance display is replaced by the ATT red flag.

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ISIS Indicator - Pitch Scale Display Figure 010   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 14 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Attitude Failure Display Figure 011   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 15 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

(e) Lateral acceleration A black surrounded white trapezoidal index below the roll reference triangle represents the A/C lateral acceleration. Lateral acceleration is displayed in the range from -0,2 to +0,2g. If the lateral acceleration exceeds this range, it is not displayed any more. When the lateral acceleration is null, the centre of the symbol is in a neutral zone, the width of which corresponds to the middle of the base of the reference triangle. This can result on ISIS in a shifting up to one millimeter between this triangle and the symbol of lateral acceleration. This behaviour comes from a compromise between the resolution of the sensors, the precision of the display and the mounting of the equipment on the instrument panel. (6) LS function (Ref. Fig. 012, 013) When the LS pushbutton switch located on the right top part of the indicator is pushed, the Glide Slope (G/S) and Localizer (LOC) scales come into view. If the LOC and/or G/S signals are in Failure Warning condition or No Refresh, the relative scale disappears and the relative red flag LOC and/or G/S appears respectively in the left bottom corner and/or in the right top corner of the display area. If the LOC and/or G/S signals are in NCD condition, only the scales without diamond are displayed. (Ref. Fig. 014) B. Standby Compass The standby compass consists of a magnetic element rotating inside a compass bowl, immersed in a damping liquid. The magnetic element (1) is linked to a graduated compass card which moves against a lubber line (2) and gives the magnetic heading. Above the viewing window are two apertures (4) marked B (E.W) and C (N.S), allowing to achieve compensation by positioning the two small magnetized bars (compensator). Below the viewing window is a non-magnetic lamp (3) assembly which provides illumination of the compass card. 4. Power ____________ Supply (Ref. Fig. 015) A. ISIS Indicator The ISIS indicator is supplied with 28VDC from the essential busbar 401PP. In case of loss of this busbar, the supply of the ISIS indicator is automatically switched over to the battery busbar 703PP by means of the relay 7XB. Consumption of the indicator is 20 W maximum in steady state.

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ISIS Indicator - LS Display Figure 012   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 17 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - LS Failure Display Figure 013   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 18 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

Standby Compass - Data Indicating Figure 014   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 19 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Power Supply Figure 015   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 20 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

Transparency time for the ISIS indicator is not less than 50 ms (memorizing of current configuration on power supply transients comprised between 50 and 200 ms). The display is lost during power supply cut off comprised between 50 and 200 ms. The system is supplied through these circuit breakers: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/INST 5FN F12 105VU NAV/STBY/INST/BAT 23FN J01 B. Standby Compass The standby compass is supplied with 28VDC from the sheddable essential bus 801PP. The system is supplied through this circuit breaker: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU LIGHTING/ICE AND STBY/COMP/LIGHT 1LF H04 5. Interface _________ A. Mechanical Interface The ISIS indicator is to 3 ATI size in accordance with ARINC 408A. B. Peripherals (Ref. Fig. 016) (1) Digital data inputs The ISIS indicator receives digital data inputs from the following components: (a) Inertial Reference Two ARINC 429 high-speed buses provide the ISIS indicator with the optional magnetic heading indication (label 320). In normal configuration, the parameters displayed on the ISIS indicator come from the ADIRU 1. When a failure is detected, switching on the ADIRU 3 has to be performed manually through the ATT/HDG selector switch on the SWITCHING panel.

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ISIS - Interfaces Figure 016   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 22 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

(b) ILS 1 (or MMR 1) One ARINC 429 low-speed bus provides the ISIS indicator with the LS function (label 173 for LOC and label 174 for G/S). (c) A fourth ARINC 429 input (low or high speed) is reserved as system provision. (2) Discrete Inputs The ISIS indicator receives the following discrete inputs: (a) Ground/open signal from the ATT/HDG selector switch for selection of active ADIRU 1 or 3. (b) Ref baro pressure in in.Hg and hPa pin-program - this discrete input permits the display of the reference barometric pressure in in.Hg in addition to the reference barometric pressure in hPa. (c) Altitude in meter pin-program - this discrete permits the display of the altitude value in meters in addition to the altitude value in feet. (d) V-bars optional function pin-program - this discrete permits to change the basic A/C symbol by the V-bars symbol. (e) Test discrete input - this discrete input allows the ISIS indicator to manage the BITE failures sent to the CFDIU. (f) Four input discretes are used for indicator face tilting The face of the ISIS indicator can be set at 0 deg. and tilted from 10 to 24 deg. by steps of 1 deg. (g) One discrete input is used as parity. (Ref. Fig. 017) The parity control includes the monitoring of the optional function pin-programs and the ISIS indicator face tilt discretes. The parity discrete is activated only if the sum of the wired discretes is an even result. The parity discrete is monitored during power-up tests and continuous built-in test. If the parity is valid, it is memorized into non volatile memory. If the parity is not valid, the last memorized configuration is used and the white MAINT flag is displayed in the left top part of the display area (when CAS < 50 kts) until the configuration is valid.

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ISIS Indicator - MAINT Flag Display Figure 017   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 24 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

If the ATT 10s message appears when the MAINT flag is shown, the message has priority. The flag is displayed again as soon as the message disappears. (3) Digital data output The ISIS indicator provides the following outputs: (a) Centralised Fault Display Interface Unit (CFDIU) The ISIS indicator is connected to the CFDIU to transmit the following words: - LRU identification, Part Number (P/N) and Serial Number (S/N) (label 354), - Built-In Test (BITE) status (label 356), - Unit code (label 377). (b) ARINC 429 output bus (low speed) for the following air data: - barometric corrected altitude in feet (label 204) and in meters if corresponding option is activated (label 214), - standard altitude in feet (label 203) and in meters if corresponding option is activated (label 216), - altitude rate (label 212), - computed airspeed in knots (label 206), - total pressure in hPa (label 242), - uncorrected average static pressure in hPa (label 245), - Mach number (label 205), - barometric reference setting in hPa (label 234) and in in.Hg if corresponding option is activated (label 235). (c) ARINC 429 output bus (high speed) for the following inertial data: - body roll rate in degrees per second (label 327), - roll angle in degrees (label 325), - body pitch rate in degrees per second (label 326), - pitch angle in degrees (label 324), - body yaw rate in degrees (label 330), - body longitudinal acceleration (label 331), - body lateral acceleration (label 332). (4) Discrete output One discrete output is used for fault/healthy indication. This discrete is grounded when the indicator is out of order and when the OUT OF ORDER message is displayed. (Ref. Fig. 018)

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ISIS Indicator - OUT OF ORDER Display Figure 018   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 26 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

6. _____________________ Component Description A. External Description **ON A/C 106-149, 221-233, 301-312, 401-499, (Ref. Fig. 019) R

**ON A/C 234-235, 239-249, 251-299, 313-399, 501-509, 511-526, 528-599, (Ref. Fig. 019A)

R R

**ON A/C 106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, The face of the ISIS indicator has: - an ATT/RST pushbutton switch to reset the horizon (attitude) function to the true value, - two ( + and - ) brightness adjustment pushbutton switches, - a BUGS pushbutton switch for the display/inhibition of the BUGS function, - a LS pushbutton switch for the engagement/disengagement of the ILS function, - a light sensor, - a BARO rotary knob/pushbutton switch. The pushbutton switch is used to change the barometric pressure (which can be adjusted by the rotary knob) to the standard pressure and back again. The back of the ISIS indicator is equipped with a 41-pin connector, a total pressure pneumatic connector (P) and a static pressure pneumatic connector (S). B. Internal Description (Ref. Fig. 020, 021) The ISIS indicator contains the following subassemblies: - a Filtering Board (FIB) - a Power Supply Unit (PSU) - an Interface Board (INB) - a Pressure Sensor Module (PSM) - an Inertial Measurement Unit (IMU) - a Control Processor and Graphic Display Module (CPGDM) - an Optical Module (OPM).

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ISIS Indicator - Component Description Figure 019   R EFF : 106-149, 221-233, 301-312, 401-499,  34-22-00 Page 28   Config-2 Aug 01/09  CES

 

ISIS Indicator - Component Description Figure 019A   R EFF : 234-235, 239-249, 251-299, 313-399,  34-22-00 Page 29 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Block Diagram Figure 020   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 30 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Location of Internal Components Figure 021   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 31 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

(1) Filtering board This board includes the rear plate with the two pressure unions for the static and the total pressures and the 41-pin external connector. It ensures protection against electromagnetic interference and lightning strikes. (2) Power supply unit From the 28VDC, this unit supplies the voltages necessary for the operation of the indicator. (3) Interface board This board makes the interface between part of the indicator inputs/outputs, the pressure sensors, the inertial sensors, the face, the light box and the CPGDM. It also supplies a clock signal at 20MHz. (4) Pressure sensor module This module contains for each system (static pressure and total pressure): - a pressure sensor with a cell (silicon detector), - a sensor memory with an electronic board that shapes the signals and stores the characterization parameters of the sensor. (5) Inertial measurement unit This unit includes three single-axis rate sensors (with analog outputs) and their temperature probes, two acceleration sensors and their temperature probes, and an electronic board. Its functions are as follows: - angular rate measurement, - temperature measurement, - absolute acceleration measurement, - storing of the IMU parameters (sensors, misalignment, identification), - generation of configuration data (IMU presence, two or three accelerometers), - generation of sensor healthy-operation discretes, - digitization of the sensor data (analog-to-digital converter). (6) Control processor and graphic display module This module performs the computing and graphics generation functions. The Control Processing Unit (CPU) part of the CPGDM processes the data received through the INB and directly from the IMU to calculate the operational parameters (altitude, attitude and airspeed). The graphics part converts the data supplied by the CPU into smoothed symbology and drives the Liquid Crystal Display (LCD).

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 32 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

(7) Optical module This module includes a LCD matrix, backlighting (light box with three tubes) and the control electronics for this lighting. 7. Operation _________ A. System Performance The parameter computation frequency is sufficient to respect the required performances and to avoid important gap between two consecutive displayed values. The elapsed time between the acquisition of air data and the display of the parameters is less than 200 ms. (1) Standby airspeed indicator function The ISIS indicator can operate from 0 to 600 kts without deterioration. (2) Standby altimeter function The ISIS indicator can operate from -2500 to 55,000 ft and at 40,000 ft/mn speed variation without deterioration. (3) Standby horizon function The ISIS indicator can operate from -180 to +180 deg. in pitch and roll without deterioration. - gyrometers (3): the indicator can follow a 100 deg./s pitch or roll variation, a 10,000 deg./square second angular acceleration. The associated monitoring is triggered when angular speeds becomes higher than 100 deg./s. - accelerometers (2): the associated monitoring is triggered when the constant acceleration in x and/or y axis becomes greater than 2.5g. If this monitoring is triggered, the WAIT ATT message is displayed (Ref. Fig. 022) If the conditions become normal againand if the attitude performance remains adequate for 10 seconds, the WAIT ATT message disappears and is replaced by the horizon display. Otherwise, after 10 seconds or if the attitude performance is affected, the attitude function is considered as failed and the ATT:RST message is displayed in place of the WAIT ATT message (Ref. Fig. 023) Pressing the RST pushbutton switch more than 2 seconds in steady flight quickly resets the attitude information.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 33 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS INDICATOR - WAIT ATT Flag Figure 022   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 34 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS INDICATOR - ATT RESET Flag Figure 023   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 35 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

B. Control and Indicating The face of the ISIS indicator includes the following controls: (1) BUGS pushbutton switch (Ref. Fig. 024) When the BUGS pushbutton switch is pushed, the BUGS page is shown. This page is used to program characteristic speeds and altitudes displayed on speed and altitude scales respectively. The BUGS page has two columns positioned vertically: an SPD column made of four boxes and an ALT column made of two boxes. Initially, the first box of the SPD column (left top) is flashing. The corresponding speed value has to be selected using the BARO selector knob (cyan SET/SELECT indication followed by an arrow in the right bottom part of the display). This value cannot be less than 30 kts and can only be selected or changed when OFF function is deselected (true also with altitude bugs). When the correct value is displayed, access to the next box (below) is made by pushing the - pushbutton switch. This box is then active and flashes. After the fourth box of the SPD column, access to the last box of the ALT column (right top) is made by using the BARO selector knob. The altitude values selected cannot be negative. The - pushbutton switch is also used to select the last ALT box and then the first SPD box again. The + pushbutton switch is used to return to the previous box. The operational page is displayed again and the entered values are memorized by pushing the BUGS pushbutton switch or after 15 s without pilot action. These values are memorized until new values are entered, even in case of ISIS indicator power supply cutoff. If one memorized bug has not to be displayed on speed or altitude scale, it is possible to hide it by pushing the BARO selector knob. The OFF indication is shown close to the selected box and the value is still displayed. By pushing the BARO selector knob again, the displayed and memorized bug is active. Initially, speed bugs are set to 30 and altitude bugs are set to 0. All the bugs can be hidden using the OFF function. (2) RST pushbutton switch (Ref. Fig. 025) The RST (reset) pushbutton switch located in the left bottom part of the indicator enables to reset the attitude indication to the true value during stabilized flight (without pitch and roll angles and with stabilized speed). During the reset, a yellow ATT 10s message is shown in the center of the display area, in place of the horizon line. After a 10-second delay, the operational page is automatically displayed.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 36 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Bugs Selection Display Figure 024   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 37 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - Attitude Reset Display Figure 025   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 38 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

(3) LS pushbutton switch This pushbutton switch located in the right top part of the indicator enables the display of the LS bars (LOC and G/S) (if the corresponding pin-program is activated) in place of the magnetic heading indications. (4) BARO selector knob This grey barometric selector knob located in the right bottom corner of the indicator, enables to display the standard barometric pressure or the barometric correction whose value can be adjusted by turning the knob. This knob is used for the selection of the altitude and airspeed bugs. (5) Brightness control The ISIS indicator has a manual and automatic display brightness control device, located on its face. The brightness ensures the readability in all environmental lighting conditions expected in service. After a long power supply interrupt on ground (>200 ms), an average brightness value is selected. In other cases, the last memorized brightness value is selected. The pushbutton switches are lighted for night vision in accordance with the general cockpit selection. 8. Test ____ A. BITE Description (1) General The ISIS indicator is fitted with an internal flight/ground information in order to manage the BITE and to prevent maintenance mode activation in flight. The test is inhibited when the internal computed airspeed is greater than 60 kts. NOTE : The ISIS indicator complies with ABD0018, ABD0048 and ABD0100 ____ Specification. The ISIS indicator is able to display maintenance data when the BUGS and the LS pushbutton switches are pushed simultaneously (at least 2 s). In this case, a menu with two items is shown on the Liquid Crystal Display (LCD).

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(a) OTHER DATA menu When the key adjacent to the OTHER DATA item (-) is pushed, a specific menu made of two items (LRU IDENT and ENGINEERING DATA) is shown. - LRU IDENT item (Ref. Fig. 026) Allows to display the P/N and the S/N of the ISIS indicator, the configuration of the equipment (optional functions activated) and the functional time counter. - ENGINEERING DATA item (Ref. Fig. 027) The engineering data provides correlation parameters and snapshot data concerning the failure displayed. In addition the engineering data enables to display the functional time counter. (b) TESTS menu When the key adjacent to the TESTS item (+) is pushed, a specific menu made of two items (FUNCTIONAL TEST (110s) and DISPLAY TEST) is shown. - DISPLAY TEST item (Ref. Fig. 028) The display test function enables to display white and black screens to check LCD screen state/quality. - FUNCTIONAL TEST (110s) item (Ref. Fig. 029) When the key adjacent to the FUNCTIONAL TEST (110s) item (+) is pushed, the functional test is started and the message IN PROGRESS 110s is shown in the middle of the display area. At the end of the test, the message TEST OK is shown on the display area. In case of fault detection, the BITE displays a message.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 40 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - LRU IDENT Menu Figure 026   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 41 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - ENGINEERING DATA Menu Figure 027   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 42 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - DISPLAY TEST Menu Figure 028   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 43 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

ISIS Indicator - FUNCTIONAL TEST Menu Figure 029   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-00 Page 44 301-399, 401-499, 501-509, 511-526, 528-599,  Config-2 Feb 01/10  CES

 

R R

STANDBY DATA : ATTITUDE AND HEADING - DESCRIPTION AND OPERATION _______________________________________________________________ 1. General _______ A. Standby Heading The standby heading is performed by a magnetic compass that is an independent instrument which provides the flight crew with the A/C magnetic heading. It is installed on the top of the windshield center post and allows a check of the heading provided by the main sources of the heading system. It acts in standby when these systems are inoperative. B. Standby Attitude The standby attitude is performed by a gyroscopic horizon that is an independent instrument which provides the flight crew, with a constant indication of the aircraft attitude. It is contained in a 3 ATIs case and installed on the center instrument panel. It allows a check of the attitude provided by the main sources of attitude system. It acts in standby when these systems are inoperative. 2. __________________ Component Location ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2FN COMPASS-STANDBY 211 831 34-22-23 7FN IND-STANDBY HORIZON 4VU 211 831 34-22-24 3. __________________ System Description A. Standby Compass The standby compass consists of a magnetic element rotating inside a compass bowl, immersed in a damping liquid. The magnetic element (1) is linked to a graduated compass card which moves against a lubber line (2) and gives the magnetic heading. Above the viewing window are two apertures (4) marked B (E.W) and C (N.S) , allowing to achieve compensation by positioning the two small magnetized bars (compensator). Below the viewing window is a non-magnetic lamp (3) assembly which provides illumination of the compass card.

  EFF : 213-213,  34-22-00 Page 1   Config-3 Aug 01/09  CES

 

B. Standby Horizon Indicator The standby horizon indicator is supplied with 28VDC from essential bus 401PP. A static inverter in the instrument converts this 28VDC into three phase alternate current to supply the gyroscopic motor. The gyro rotor rotates at high speed (> 23,000 RPM) around its vertical axis and provides the vertical reference. The gimbal assy comprises two orthogonal axes (pitch and roll). The internal gimbal which includes the stator controls the rotation of the drum in the pitch axis by means of gear. The pitch gimbal is restricted to approximately plus or minus 85 degrees around the pitch axis (mechanical stop). The external gimbal controls the roll rotation. The roll gimbal has unrestricted 360 degrees rotation around the roll axis. The gyro pin axis is maintained in the vertical position by the erection system (unstable pendulum erector) which is removed when the rotor axis deviates more than 9 degrees plus or minus 2 degrees. The accuracy of the vertical position in clean configuration is less than 0.5 degree. The fast resetting of the gyroscopic horizon can be activated by pulling the knob (8) located in the lower R corner of the indicator. The indicator provides the following information : - roll angle, - pitch angle, - instrument failure (RED flag). (1) Pitch information The aircraft symbol (black and yellow) (7) is fixed. The pitch drum (9), in the center of the instrument is divided into two zones separated by the reference horizon (white) : the upper part is blue, the lower part is brown. The pitch indications are displayed by means of a drum which is graduated between -80 and +80 degrees. (2) Roll information The roll information is given by a pointer (10) which moves in front of a dial (5) graduated in 10 degrees increments between -30 and +30 degrees. (3) Failure warning The flag (6) comes into view if a failure is detected in the electrical power supply or if the gyro rotor speed drops below 18,000 RPM.

  EFF : 213-213,  34-22-00 Page 2   Config-3 Nov 01/03  CES

 

Standby Data - Attitude and Heading - Component Location Figure 001   EFF : 213-213,  34-22-00 Page 3   Config-3 Nov 01/03  CES

 

Standby Data - Attitude and Heading - Electrical Circuit Figure 002   EFF : 213-213,  34-22-00 Page 4   Config-3 Nov 01/03  CES

 

Standby Data - Attitude and Heading - Data Indicating Figure 003   EFF : 213-213,  34-22-00 Page 5   Config-3 Nov 01/03  CES

 

STANDBY DATA : ATTITUDE AND HEADING - ADJUSTMENT/TEST _____________________________________________________ TASK 34-22-00-710-001 Operational Check of the standby compass including light test and visual check WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. R R

NOTE : The aircraft must not be near magnetic materials (vehicles, ____ buildings...) when you do this test. 1. __________________ Reason for the Job Refer to the MPD TASK: 342200-01 To make sure that: - the difference between the magnetic heading values on the standby compass and the ND is not more than + or - 8⁰ - the lighting of the standby compass operates correctly - you can read the compass cards . 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 31-60-00-860-002 34-10-00-860-004 34-22-00-730-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure IR Alignment Procedure Compensation Adjustment/Test of the Standby Compass

  EFF : ALL  34-22-00    CES

 

Page 501 Nov 01/06

3. __________ Job Set-up Subtask 34-22-00-860-050 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (CAPT ND only)(Ref. TASK 31-60-00-860001). (3) Do the IR alignement procedure (Ref. TASK 34-10-00-860-004). (4) On the windshield center post, pull the standby compass support that you can retract from its housing. 4. Procedure _________ R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-22-00-710-050 A. Operational Test of the Standby Compass ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the CAPT ND, read the magnetic heading value.

Make sure that: - the difference between the magnetic heading values on the standby compass and the ND is not more than + or 8⁰. NOTE : If the difference between the ____ magnetic heading values on the standby compass and the ND is more than + or - 8⁰ : do the compensation adjustment/test of the standby compass (Ref. TASK 34-22-00-730-001).

2. On the overhead panel, on the ADIRS CDU:

  EFF : ALL  34-22-00    CES

 

Page 502 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set the OFF/NAV/ATT selector switch related to the IR1 to OFF. 3. On the INT LT section of the overhead panel 25VU:

R

On the standby compass:

- set the STBY COMPASS switch to STBY COMPASS

- the lighting is on - you can read the compass cards from the CAPT and F/O seats.

- set the STBY COMPASS switch to OFF

- the lighting goes off.

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-22-00-710-050-A A. Operational Test of the Standby Compass ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the CAPT ND, read the magnetic heading value.

Make sure that: - The difference between the magnetic heading values on the standby compass and the ND is not more than + or 8⁰. NOTE : If the difference between the ____ magnetic heading values on the standby compass and the ND is more than + or - 8⁰ : do the compensation adjustment/test of the standby compass (Ref. TASK 34-22-00-730-001).

2. On the overhead panel, on the ADIRS MSU: - Set the OFF/NAV/ATT selector switch related to the IR1 to OFF.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-22-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 503 Feb 01/10

R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------3. On the INT LT section of the On the standby compass: overhead panel 25VU:

R R R

- Set the STBY COMPASS switch to STBY COMPASS.

- The lighting is on - You can read the compass cards from the CAPT and F/O seats.

R R

- Set the STBY COMPASS switch to OFF.

- The lighting goes off.

R

**ON A/C ALL Subtask 34-22-00-210-050 B. Visual Inspection of the Standby Compass (1) Make sure that: - the support is in good condition - the standby compass is correctly attached to the support - there are no leaks. (2) In the compass bowl, make sure that the liquid: - is clear - does not contain bubbles or sediment. 5. Close-up ________ Subtask 34-22-00-860-051 A. Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure(Ref. TASK 31-60-00-860-002). (2) On the windshield center post, push the standby compass support into its housing. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). (4) Put the aircraft back to the serviceable condition.

  EFF : ALL  34-22-00    CES

 

Page 504 Feb 01/08

TASK 34-22-00-730-001 Compensation Adjustment/Test of the Standby Compass WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. NOTE : To move the aircraft for this procedure, you can use: ____ - a tractor (you must disconnect the tractor and the towbar for each adjustment) or, - the aircraft engines (this is the recommended procedure). 1. __________________ Reason for the Job - to adjust the compensation of the standby compass - to find the deviation curve of the compass values when they are more than + or - 8⁰ from the magnetic heading. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R

No specific No specific CE2-40

2 mm-wide non magnetic screwdriver 2-mm wide non-magnetic screwdriver 2 KEY-CORRECTOR

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 31-60-00-860-002 34-10-00-860-004 34-10-00-860-005 34-22-00-710-001

Energize the Aircraft Electrical Circuits from the APU De-energize the Aircraft Electrical Circuits Supplied from the APU EIS Start Procedure EIS Stop Procedure IR Alignment Procedure ADIRS Stop Procedure Operational Check of the standby compass including light test and visual check

  EFF : ALL  34-22-00    CES

 

Page 505 Feb 01/09

3. __________ Job Set-up **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-22-00-860-052 A. Aircraft Maintenance Configuration

R R

NOTE : For this procedure the aircraft must be on a compensation base ____ that can support the weight of the aircraft. The compensation base must be: - a compensation base certified by the applicable authorities or, - a compensation base with these properties: . a horizontal area in which the horizontal component of the earths magnetic field is constant (+/- 1 degree), .sufficiently large for the aircraft be turn smoothly 360 degrees, .with no metal objects near it ( no vehicles or other aircraft in a radius of 250ft, no buildings with magnetic materials in a radius of 600ft around the aircraft ).

R R

(1) Make sure that there are no ferromagnetic parts installed near the standby compass. Ferromagnetic parts near the standby compass can cause compass heading errors (fasteners, tools, etc...).

R

(2) Energize the aircraft electrical circuits from the APU (Ref. TASK 2441-00-861-002). (3) Make sure that the standby compass operates correctly (Ref. TASK 3422-00-710-001). (4) Do the EIS start procedure (NDs only)(Ref. TASK 31-60-00-860-001). (5) Do the IR alignment procedure(Ref. TASK 34-10-00-860-004). (6) Adjust the position of the aircraft until its lubber line points to the North with a deviation less than 2⁰. (7) On the ADIRS CDU set the DISPLAY DATA selector switch to HDG.

  EFF : ALL  34-22-00    CES

 

Page 506 Feb 01/09

R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-22-00-860-052-A A. Aircraft Maintenance Configuration NOTE : For this procedure the aircraft must be on a compensation base ____ that can support the weight of the aircraft. The compensation base must be: - a compensation base certified by the applicable authorities or, - a compensation base with these properties: . a horizontal area in which the horizontal component of the earths magnetic field is constant (+/- 1 degree), .sufficiently large for the aircraft be turn smoothly 360 degrees, .with no metal objects near it ( no vehicles or other aircraft in a radius of 250ft, no buildings with magnetic materials in a radius of 600ft around the ai rcraft ). (1) Make sure that there are no ferromagnetic parts installed near the standby compass. Ferromagnetic parts near the standby compass can cause compass heading errors(fasteners, tools, etc...). (2) Energize the aircraft electrical circuits from the APU (Ref. TASK 2441-00-861-002). (3) Make sure that the standby compass operates correctly (Ref. TASK 3422-00-710-001). (4) Do the EIS start procedure (NDs only)(Ref. TASK 31-60-00-860-001). (5) Do the IR alignment procedure(Ref. TASK 34-10-00-860-004). (6) Adjust the position of the aircraft until its lubber line points to the North with a deviation less than 2⁰.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-22-00 511-526, 528-599,   CES

 

Page 507 Feb 01/10

**ON A/C ALL Subtask 34-22-00-865-050 B. Make sure that these circuit breakers are closed to get the radio/ magnetic environment that usually occurs in flight : ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-049, 101-105, 151-199, 49VU COM/HF1

1RE1

HA14

2RS1 2RC1 1RP1

G13 G09 H14

**ON A/C ALL 49VU NAV/VOR/1 49VU COM/VHF/1 49VU NAV/ADF/1 R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 49VU COM HF1

R R

1RE1

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/ADF/2

R R

HA14

1RP2

K02

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-210, 234-235, 239-249, 251-299, 301-399, 501-509, 511-526, 528-599, 121VU COM NAV/HF2

1RE2

L13

2RS2 2RC3 2RC2

K08 L05 L04

**ON A/C ALL 121VU COM NAV/VOR/2 121VU COM NAV/VHF/3 121VU COM NAV/VHF/2

  EFF : ALL  34-22-00    CES

 

Page 508 Feb 01/10

4. Procedure _________ R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-22-00-730-050

R R

A. Compensation Adjustment/Test of the Standby Compass (For aircraft fitted with standby compass P/N C5K). NOTE : The reference magnetic heading referred to in this procedure is ____ equal to the true heading indication read on the ADIRS CDU plus the magnetic variation. Magnetic heading = true heading + magnetic variation (a natural phenomenon which varies continuously).

R R

(1) Below the display window on the front face of the standby compass: - remove and safety the protection cover of the compensator.

R

(2) On the standby compass: - put the 2 mm-wide non magnetic screwdriver into the EW hole the display window - use the non magnetic screwdriver to set the EW compensation to zero - put the non magnetic screwdriver into the NS hole below the window - use the non magnetic screwdriver to set the NS compensation to zero.

R

below system display system

(3) Use the system in operation to set the aircraft to north (MHN) (Magnetic Heading North): - calculate and write the magnetic deviation DN between the MHN and the CH (Compass Heading Indication of the Standby Compass): DN = MHN - CH - the Adjustment Value (AV) is equal to DN - correct the CH with the AV to get the compensated compass heading indication (CCH) - put the non magnetic screwdriver into the NS hole of the standby compass - use the non magnetic screwdriver to set the standby compass to CCH. Example: . if MHN = 360⁰ and CH = 356⁰ DN = 360⁰ - 356⁰ = +4⁰ AV (adjustment value) = +4 Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 356⁰ + 4 = 360⁰

  EFF : ALL  34-22-00    CES

 

Page 509 Feb 01/09

. if MHN = 0⁰ and CH = 002⁰ DN = 0⁰ - 2⁰ = -2⁰ AV (Adjustment Value) = -2⁰ Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 2⁰ +(-2⁰) = 0 R

(4) Set the aircraft to East (MHE): - calculate and write the magnetic deviation DE between the MHE and the CH DE = MHE - CH - the Adjustment Value (AV) is equal to DE - correct the CH with the AV to get the CCH - put the non magnetic screwdriver into the EW hole of the standby compass - use the non magnetic screwdriver to set the standby compass to CCH (Ref. Para. (2)).

R

(5) Set the aircraft to South (MHS): - calculate and write the magnetic deviation DS between the MHS and the CH DS = MHS - CH DS the Adjustment Value (AV) is equal to -2 - correct the CH with the AV to get the CCH - put the non magnetic screwdriver into the NS hole of the standby compass - use the non magnetic screwdriver to set the standby compass to CCH. Example: . if MHS = 180⁰ and CH = 174⁰ DS = 180⁰ - 174⁰ = +6⁰ DS 6 AV = -- = + - = +3 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 174⁰ + 3⁰ = 177⁰ . if MHS = 180⁰ and CH = 182⁰ DS = 180⁰ - 182⁰ = -2⁰ DS 2 AV = -- = - - = -1 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 182 + (-1) = 181

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-22-00 201-239, 301-312, 401-499,   CES

 

Page 510 Feb 01/09

(6) Set the aircraft to West (MHW) - calculate and write the magnetic deviation DW between the MHW and the CH DW = MHW - CH DW the Adjustment Valve (AV) is equal to -2 - correct the CH with the AV to get the CCH - put the non magnetic screwdriver into the EW hole of the standby compass - use the non magnetic screwdriver to set the standby compass to CCH. (Ref. Para. (4)). R R

Subtask 34-22-00-730-067

R R

B. Compensation Adjustment/Test of the Standby Compass (For aircraft fitted with standby compass P/N PGA0105W).

R R R R R

NOTE : The reference magnetic heading referred to in this procedure is ____ equal to the true heading indication read on the ADIRS CDU plus the magnetic variation. Magnetic heading = true heading + magnetic variation (a natural phenomenon which varies continuously).

R R R R R R R R R

(1) On the standby compass: - put the KEY-CORRECTOR (CE2-40) into the B hole above the display window - use the non magnetic Compensation Key to set the B compensation system to zero - put the non magnetic Compensation Key into the C hole above the display window - use the non magnetic Compensation Key to set the C compensation system to zero.

R R R R R R R R R R R R

(2) Use the system in operation to set the aircraft to north (MHN) (Magnetic Heading North): - calculate and write the magnetic deviation DN between the MHN and the CH (Compass Heading Indication of the Standby Compass): DN = MHN - CH - the Adjustment Value (AV) is equal to DN - correct the CH with the AV to get the compensated compass heading indication (CCH) - put the non magnetic Compensation Key into the C hole of the standby compass - use the non magnetic Compensation Key to set the standby compass to CCH.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-22-00 201-239, 301-312, 401-499,   CES

 

Page 511 Feb 01/10

R R R R R R R R R R R R R

Example: . if MHN = 360⁰ and CH = 356⁰ DN = 360⁰ - 356⁰ = +4⁰ AV (adjustment value) = +4 Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 356⁰ + 4 = 360⁰ . if MHN = 0⁰ and CH = 002⁰ DN = 0⁰ - 2⁰ = -2⁰ AV (Adjustment Value) = -2⁰ Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 2⁰ +(-2⁰) = 0

R R R R R R R R R R

(3) Set the aircraft to East (MHE): - calculate and write the magnetic deviation DE between the MHE and the CH DE = MHE - CH - the Adjustment Value (AV) is equal to DE - correct the CH with the AV to get the CCH - put the non magnetic Compensation Key into the B hole of the standby compass - use the non magnetic Compensation Key to set the standby compass to CCH (Ref. Para. (2)).

R R R R R R R R R R R R R R R R R R R R R R

(4) Set the aircraft to South (MHS): - calculate and write the magnetic deviation DS between the MHS and the CH DS = MHS - CH DS the Adjustment Value (AV) is equal to -2 - correct the CH with the AV to get the CCH - put the non magnetic Compensation Key into the C hole of the standby compass - use the non magnetic Compensation Key to set the standby compass to CCH. Example: . if MHS = 180⁰ and CH = 174⁰ DS = 180⁰ - 174⁰ = +6⁰ DS 6 AV = -- = + - = +3 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 174⁰ + 3⁰ = 177⁰ . if MHS = 180⁰ and CH = 182⁰

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-22-00 201-239, 301-312, 401-499,   CES

 

Page 512 Feb 01/10

R R R R R R R R R R R R R R R R R R R R

DS = 180⁰ - 182⁰ = -2⁰ DS 2 AV = -- = - - = -1 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 182 + (-1) = 181 (5) Set the aircraft to West (MHW) - calculate and write the magnetic deviation DW between the MHW and the CH DW = MHW - CH DW the Adjustment Valve (AV) is equal to -2 - correct the CH with the AV to get the CCH - put the non magnetic Compensation Key into the B hole of the standby compass - use the non magnetic Compensation Key to set the standby compass to CCH. (Ref. Para. (4)). **ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-22-00-730-050-A A. Compensation Adjustment/Test of the Standby Compass (For aircraft fitted with standby compass P/N C5K). (1) Below the display window on the front face of the standby compass: - remove and safety the protection cover of the compensator. (2) On the standby compass: - put the 2 mm-wide non magnetic screwdriver into the EW hole the display window - use the non magnetic screwdriver to set the EW compensation to zero - put the non magnetic screwdriver into the NS hole below the window - use the non magnetic screwdriver to set the NS compensation to zero.

below system display system

(3) Use the system in operation to set the aircraft to north (MHN) (Magnetic Heading North): - calculate and write the magnetic deviation DN between the MHN and the CH (Compass Heading Indication of the Standby Compass): DN = MHN - CH

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-22-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 513 Feb 01/10

- the Adjustment Value (AV) is equal to DN - correct the CH with the AV to get the compensated compass heading indication (CCH) - put the non magnetic screwdriver into the NS hole of the standby compass - use the non magnetic screwdriver to set the standby compass to CCH. Example: . if MHN = 360⁰ and CH = 356⁰ DN = 360⁰ - 356⁰ = +4⁰ AV (adjustment value) = +4 Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 356⁰ + 4 = 360⁰ . if MHN = 0⁰ and CH = 002⁰ DN = 0⁰ - 2⁰ = -2⁰ AV (Adjustment Value) = -2⁰ Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 2⁰ +(-2⁰) = 0 (4) Set the aircraft to East (MHE): - calculate and write the magnetic deviation DE between the MHE and the CH DE = MHE - CH - the Adjustment Value (AV) is equal to DE - correct the CH with the AV to get the CCH - put the non magnetic screwdriver into the EW hole of the standby compass - use the non magnetic screwdriver to set the standby compass to CCH (Ref. Para. (2)). (5) Set the aircraft to South (MHS): - calculate and write the magnetic deviation DS between the MHS and the CH DS = MHS - CH DS the Adjustment Value (AV) is equal to -2 - correct the CH with the AV to get the CCH - put the non magnetic screwdriver into the NS hole of the standby compass - use the non magnetic screwdriver to set the standby compass to CCH. Example: . if MHS = 180⁰ and CH = 174⁰ DS = 180⁰ - 174⁰ = +6⁰

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-22-00 511-526, 528-599,   CES

 

Page 514 Feb 01/10

DS 6 AV = -- = + - = +3 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 174⁰ + 3⁰ = 177⁰ . if MHS = 180⁰ and CH = 182⁰ DS = 180⁰ - 182⁰ = -2⁰ DS 2 AV = -- = - - = -1 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 182 + (-1) = 181 (6) Set the aircraft to West (MHW) - calculate and write the magnetic deviation DW between the MHW and the CH DW = MHW - CH DW the Adjustment Valve (AV) is equal to -2 - correct the CH with the AV to get the CCH - put the non magnetic screwdriver into the EW hole of the standby compass - use the non magnetic screwdriver to set the standby compass to CCH. (Ref. Para. (4)). R Subtask 34-22-00-730-067-A B. Compensation Adjustment/Test of the Standby Compass (For aircraft fitted with standby compass P/N PGA0105W). (1) On the standby compass: - put the KEY-CORRECTOR (CE2-40) into the B hole above the display window - use the non magnetic Compensation Key to set the B compensation system to zero - put the non magnetic Compensation Key into the C hole above the display window - use the non magnetic Compensation Key to set the C compensation system to zero.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-22-00 511-526, 528-599,   CES

 

Page 515 Feb 01/10

(2) Use the system in operation to set the aircraft to north (MHN) (Magnetic Heading North): - calculate and write the magnetic deviation DN between the MHN and the CH (Compass Heading Indication of the Standby Compass): DN = MHN - CH - the Adjustment Value (AV) is equal to DN - correct the CH with the AV to get the compensated compass heading indication (CCH) - put the non magnetic Compensation Key into the C hole of the standby compass - use the non magnetic Compensation Key to set the standby compass to CCH. Example: . if MHN = 360⁰ and CH = 356⁰ DN = 360⁰ - 356⁰ = +4⁰ AV (adjustment value) = +4 Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 356⁰ + 4 = 360⁰ . if MHN = 0⁰ and CH = 002⁰ DN = 0⁰ - 2⁰ = -2⁰ AV (Adjustment Value) = -2⁰ Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 2⁰ +(-2⁰) = 0 (3) Set the aircraft to East (MHE): - calculate and write the magnetic deviation DE between the MHE and the CH DE = MHE - CH - the Adjustment Value (AV) is equal to DE - correct the CH with the AV to get the CCH - put the non magnetic Compensation Key into the B hole of the standby compass - use the non magnetic Compensation Key to set the standby compass to CCH (Ref. Para. (2)). (4) Set the aircraft to South (MHS): - calculate and write the magnetic deviation DS between the MHS and the CH DS = MHS - CH DS the Adjustment Value (AV) is equal to -2 - correct the CH with the AV to get the CCH - put the non magnetic Compensation Key into the C hole of the standby compass

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-22-00 511-526, 528-599,   CES

 

Page 516 Feb 01/10

- use the non magnetic Compensation Key to set the standby compass to CCH. Example: . if MHS = 180⁰ and CH = 174⁰ DS = 180⁰ - 174⁰ = +6⁰ DS 6 AV = -- = + - = +3 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 174⁰ + 3⁰ = 177⁰ . if MHS = 180⁰ and CH = 182⁰ DS = 180⁰ - 182⁰ = -2⁰ DS 2 AV = -- = - - = -1 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 182 + (-1) = 181 (5) Set the aircraft to West (MHW) - calculate and write the magnetic deviation DW between the MHW and the CH DW = MHW - CH DW the Adjustment Valve (AV) is equal to -2 - correct the CH with the AV to get the CCH - put the non magnetic Compensation Key into the B hole of the standby compass - use the non magnetic Compensation Key to set the standby compass to CCH. (Ref. Para. (4)). Subtask 34-22-00-730-065 C. Compensation Adjustment/Test of the STBY Compass using a 2-mm wide Non Magnetic Screwdriver (1) On the standby compass: - Put the 2-mm wide non-magnetic screwdriver into the EW hole the display window - Use the non magnetic screwdriver to set the EW compensation to zero - Put the non magnetic screwdriver into the NS hole below the window - Use the non magnetic screwdriver to set the NS compensation to zero.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-22-00 511-526, 528-599,   CES

 

below system display system

Page 517 Feb 01/10

(2) Use the system in operation to set the aircraft to North (MHN) (Magnetic Heading North): - Calculate and write the magnetic deviation DN between the MHN and the CH (Compass Heading Indication of the Standby Compass): DN = MHN - CH - The Adjustment Value (AV) is equal to DN. - Correct the CH with the AV to get the compensated compass heading indication (CCH) - Put the non magnetic screwdriver into the NS hole of the standby compass - Use the non magnetic screwdriver to set the standby compass to CCH. Example: . if MHN = 360⁰ and CH = 356⁰ DN = 360⁰ - 356⁰ = +4⁰ AV (Adjustment Value) = +4. Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 356⁰ + 4 = 360⁰. . if MHN = 0⁰ and CH = 002⁰ DN = 0⁰ - 2⁰ = -2⁰ AV (Adjustment Value) = -2⁰. Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 2⁰ +(-2⁰) = 0. (3) Set the aircraft to East (MHE): - Calculate and write the magnetic deviation DE between the MHE and the CH: DE = MHE - CH - The Adjustment Value (AV) is equal to DE. - Correct the CH with the AV to get the CCH - Put the non magnetic screwdriver into the EW hole of the standby compass - Use the non magnetic screwdriver to set the standby compass to CCH (Ref. Para. (2)). (4) Set the aircraft to South (MHS): - Calculate and write the magnetic deviation DS between the MHS and the CH: DS = MHS - CH DS The Adjustment Value (AV) is equal to --. 2 - Correct the CH with the AV to get the CCH - Put the non magnetic screwdriver into the NS hole of the standby compass - Use the non magnetic screwdriver to set the standby compass to CCH.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-22-00 511-526, 528-599,   CES

 

Page 518 Feb 01/10

Example: . if MHS = 180⁰ and CH = 174⁰ DS = 180⁰ - 174⁰ = +6⁰ DS 6 AV = -- = + - = +3. 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 174⁰ + 3⁰ = 177⁰. . if MHS = 180⁰ and CH = 182⁰ DS = 180⁰ - 182⁰ = -2⁰ DS 2 AV = -- = - - = -1. 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 182 + (-1) = 181. (5) Set the aircraft to West (MHW): - Calculate and write the magnetic deviation DW between the MHW and the CH: DW = MHW - CH DW The Adjustment Value (AV) is equal to --. 2 - Correct the CH with the AV to get the CCH - Put the non magnetic screwdriver into the EW hole of the standby compass - Use the non magnetic screwdriver to set the standby compass to CCH (Ref. Para. (4)). Subtask 34-22-00-730-066 D. Compensation Adjustment/Test of the STBY Compass using a Compensation Key (CE 2-40) (1) On the standby compass: - Put the KEY-CORRECTOR (CE2-40) into the B hole above the display window - Use the non magnetic Compensation Key to set the B compensation system to zero - Put the non magnetic Compensation Key into the C hole above the display window - Use the non magnetic Compensation Key to set the C compensation system to zero.

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-22-00 511-526, 528-599,   CES

 

Page 519 Feb 01/10

(2) Use the system in operation to set the aircraft to North (MHN) (Magnetic Heading North): - Calculate and write the magnetic deviation DN between the MHN and the CH (Compass Heading Indication of the Standby Compass): DN = MHN - CH - The Adjustment Value (AV) is equal to DN. - Correct the CH with the AV to get the compensated compass heading indication (CCH) - Put the non magnetic Compensation Key into the C hole of the standby compass - Use the non magnetic Compensation Key to set the standby compass to CCH. Example: . if MHN = 360⁰ and CH = 356⁰ DN = 360⁰ - 356⁰ = +4⁰ AV (Adjustment Value) = +4. Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 356⁰ + 4 = 360⁰. . if MHN = 0⁰ and CH = 002⁰ DN = 0⁰ - 2⁰ = -2⁰ AV (Adjustment Value) = -2⁰ Correct the Compass Heading indication of the standby compass (CH) with the AV to get the CCH 2⁰ +(-2⁰) = 0. (3) Set the aircraft to East (MHE): - Calculate and write the magnetic deviation DE between the MHE and the CH: DE = MHE - CH - The Adjustment Value (AV) is equal to DE. - Correct the CH with the AV to get the CCH - Put the non magnetic Compensation Key into the B hole of the standby compass - Use the non magnetic Compensation Key to set the standby compass to CCH (Ref. Para. (2)). (4) Set the aircraft to South (MHS): - Calculate and write the magnetic deviation DS between the MHS and the CH: DS = MHS - CH DS The Adjustment Value (AV) is equal to --. 2 - Correct the CH with the AV to get the CCH - Put the non magnetic Compensation Key into the C hole of the standby compass

  R EFF : 240-249, 251-299, 313-399, 501-509,  34-22-00 511-526, 528-599,   CES

 

Page 520 Feb 01/10

- Use the non magnetic Compensation Key to set the standby compass to CCH. Example: . if MHS = 180⁰ and CH = 174⁰ DS = 180⁰ - 174⁰ = +6⁰ DS 6 AV = -- = + - = +3. 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 174⁰ + 3⁰ = 177⁰. . if MHS = 180⁰ and CH = 182⁰ DS = 180⁰ - 182⁰ = -2⁰ DS 2 AV = -- = - - = -1. 2 2 Correct the Compass Heading indication of the standby compass (CH) with the Adjustment Value (AV) to get the CCH 182 + (-1) = 181 (5) Set the aircraft to West (MHW): - Calculate and write the magnetic deviation DW between the MHW and the CH: DW = MHW - CH DW The Adjustment Value (AV) is equal to --. 2 - Correct the CH with the AV to get the CCH - Put the non magnetic Compensation Key into the B hole of the standby compass - Use the non magnetic Compensation Key to set the standby compass to CCH (Ref. Para. (4)). **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 401-499, Subtask 34-22-00-730-051 E. Find the deviation curve NOTE : During the adjustment, the standby compass turns 360⁰. Make sure ____ that the letters and graduations on the compass card are not damaged. - set the aircraft to the twelve headings one after the other which are necessary to find the deviation curve: 0⁰, 30⁰, 60⁰, 90⁰, 120⁰, 150⁰, 180⁰, 210⁰, 240⁰, 270⁰, 300⁰, 330⁰

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-22-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 521 Feb 01/10

- write the values of the standby compass and of the NDs (or ADIRS CDU + magnetic variation) for each aircraft position, - calculate the remaining deviation values R(⁰): R(⁰) = MH - indication of standby compass, - make sure that: * the remaining deviation values R(⁰) are not more than + or 8⁰ for each heading, * the maximum range between the positive and negative deviation values R(⁰) is not more than 10⁰, * the difference between each magnetic heading value on the standby compass and the ND is not more than 8⁰. If the difference is more than 8⁰, adjust the compensation, - write the actual compass heading Magnetic Heading (MH) + R(⁰) (Remaining deviation values)⁵ on the two correction cards. Put the cards on each side of the support of the standby compass. R

**ON A/C 240-249, 251-299, 313-399, 501-509, 511-526, 528-599, Subtask 34-22-00-730-051-A E. Find the Deviation Curve NOTE : During the adjustment, the standby compass turns 360⁰. Make sure ____ that the letters and graduations on the compass card are not damaged. - Set the aircraft to the twelve headings one after the other which are necessary to find the deviation curve: 0⁰, 30⁰, 60⁰, 90⁰, 120⁰, 150⁰, 180⁰, 210⁰, 240⁰, 270⁰, 300⁰, 330⁰. - Write the values of the standby compass and of the NDs for each aircraft position. - Calculate the remaining deviation values R(⁰): R(⁰) = MH - indication of standby compass. - Make sure that: * The remaining deviation values R(⁰) are not more than + or 8⁰ for each heading. * The maximum range between the positive and negative deviation values R(⁰) is not more than 10⁰. * The difference between each magnetic heading value on the standby compass and the ND is not more than 8⁰. If the difference is more than 8⁰, adjust the compensation. - Write the actual compass heading Magnetic Heading (MH) + R(⁰) (Remaining deviation values)⁵ on the two correction cards. Put the cards on each side of the support of the standby compass.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-22-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 522 Feb 01/10

**ON A/C ALL 5. Close-up ________ Subtask 34-22-00-860-053 A. Put the aircraft back to its initial configuration. (For aircraft fitted with standby compass P/N C5K). (1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) Install the protection cover on the compensator. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). (5) Put the aircraft back to the serviceable condition. (6) Remove the ground support and maintenance equipment, the special and standard tools and all other items. R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-22-00-860-068 B. Put the aircraft back to its initial configuration. (For aircraft fitted with standby compass P/N PGA0105W). (1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). (4) Put the aircraft back to the serviceable condition. (5) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

  EFF : ALL  34-22-00    CES

 

Page 523 Feb 01/10

**ON A/C ALL TASK 34-22-00-730-003 Compensation Adjustment/Test of the Standby Compass with the Standby Compass Calibrator WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. NOTE : To move the aircraft to the compensation base you can use: ____ - a tractor (you must disconnect the tractor and the towbar before you start the Adjustment/Test) or, - the aircraft engines. 1. __________________ Reason for the Job - To adjust the compensation of the standby compass. - To find the deviation curve of the compass values when they are more than + or - 8 degrees. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific CE2-40 2591553-903

2 mm-wide non-magnetic screwdriver 1 KEY-CORRECTOR 1 STANBY COMPASS CALIB

  R EFF : ALL  34-22-00    CES

 

Page 524 Feb 01/10

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 31-60-00-860-002 34-10-00-860-004 34-10-00-860-005 34-22-00-710-001

Energize the Aircraft Electrical Circuits from the APU De-energize the Aircraft Electrical Circuits Supplied from the APU EIS Start Procedure EIS Stop Procedure IR Alignment Procedure ADIRS Stop Procedure Operational Check of the standby compass including light test and visual check

**ON A/C 001-049, 051-061, 101-105, 201-203, 34-22-00-991-002 R R

Fig. 501

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-22-00-991-002-A

Fig. 501A

**ON A/C 001-049, 051-061, 101-105, 201-203, 34-22-00-991-003 R R

Fig. 502

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-22-00-991-003-A

Fig. 502A

  EFF : ALL  34-22-00    CES

 

Page 525 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-22-00-860-065 A. Aircraft Maintenance Configuration CAUTION : MAKE SURE THAT THE AIRCRAFT IS IN THE SPECIFIED COMPENSATION _______ AREA, AND THAT IT POINTS TO THE NORTH. IF YOU MUST USE THE STANDBY COMPASS CALIBRATOR IN A DIFFERENT LOCATION, YOU MUST CALIBRATE THE STANDBY COMPASS CALIBRATOR AGAIN BEFORE YOU USE IT. NOTE : For this procedure the aircraft must be on a compensation base ____ that can support the weight of the aircraft. The compensation base must have these properties: a horizontal area. be agree with the compensation procedure of the Firstmark Operation and Maintenance Manual (Ref.EB 2992043). There must be a check of the compensation area every three months or each time that you use it. (1) Make sure that there are no ferromagnetic parts installed near the standby compass. Ferromagnetic parts (fasteners, tools, etc.) near the standby compass can cause compass heading errors. (2) Energize the aircraft electrical circuits from the APU (Ref. TASK 2441-00-861-002). (3) Make sure that the standby compass operates correctly (Ref. TASK 3422-00-710-001). (4) Do the EIS start procedure (NDs only)(Ref. TASK 31-60-00-860-001). (5) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (6) Adjust the position of the aircraft: - The lubber line must point to the North with a deviation of less than 2 degrees. - The nose wheel must be on the ground marking defined by the Firstmark area-calibration procedure. (7) On the ADIRS CDU, set the DISPLAY DATA selector switch to HDG.

  EFF : ALL  34-22-00   R  CES

 

Page 526 Feb 01/10

Subtask 34-22-00-865-055 B. Make sure that these circuit breakers are closed to get the radio/ magnetic environment that usually occurs in flight : ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-049, 101-105, 151-199, 49VU COM/HF1

1RE1

HA14

2RS1 2RC1 1RP1

G13 G09 H14

**ON A/C ALL 49VU NAV/VOR/1 49VU COM/VHF/1 49VU NAV/ADF/1 R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 49VU COM HF1

R R

1RE1

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/ADF/2

R R

HA14

1RP2

K02

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-210, 234-235, 239-249, 251-299, 301-399, 501-509, 511-526, 528-599, 121VU COM NAV/HF2

1RE2

L13

2RS2 2RC3 2RC2

K08 L05 L04

**ON A/C ALL 121VU COM NAV/VOR/2 121VU COM NAV/VHF/3 121VU COM NAV/VHF/2

  EFF : ALL  34-22-00    CES

 

Page 527 Feb 01/10

**ON A/C 001-049, 051-061, 101-105, 201-203, Subtask 34-22-00-020-055 C. Below the display window, on the front face of the standby compass: - Remove and safety the protection cover of the compensator. **ON A/C ALL 4. Procedure _________ Subtask 34-22-00-730-062 A. Installation of the standby compass compensator **ON A/C 001-049, 051-061, 101-105, 201-203, (Ref. Fig. 501/TASK 34-22-00-991-002) R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 501A/TASK 34-22-00-991-002-A) **ON A/C 001-049, 051-061, 101-105, 201-203, (Ref. Fig. 502/TASK 34-22-00-991-003)

R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 502A/TASK 34-22-00-991-003-A) **ON A/C ALL (1) Remove the four screws (1) from the plate (2) under the standby compass. (2) Remove the plate (2). (3) Remove the two screws (3) from the standby compass (4).

  EFF : ALL  34-22-00    CES

 

Page 528 Feb 01/10

Standby Compass Figure 501/TASK 34-22-00-991-002   R EFF : 001-049, 051-061, 101-105, 201-203,  34-22-00    CES

 

Page 529 Feb 01/10

Standby Compass Figure 501A/TASK 34-22-00-991-002-A   R EFF : 062-099, 106-149, 151-199, 204-249,  34-22-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 530 Feb 01/10

Standby Compass Calibrating (S.C.C.) Figure 502/TASK 34-22-00-991-003   R EFF : 001-049, 051-061, 101-105, 201-203,  34-22-00    CES

 

Page 531 Feb 01/10

INTENTIONALLY BLANK

  R   34-22-00    CES

 

Page 532 Feb 01/10

Standby Compass Calibrating (S.C.C.) Figure 502A/TASK 34-22-00-991-003-A   R EFF : 062-099, 106-149, 151-199, 204-249,  34-22-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 533 Feb 01/10

(4) Install the standby compass compensator (5) STANBY COMPASS CALIB (2591553-903) with two non-magnetic screws (6) and two adjusting shims (7) on the standby compass (4). **ON A/C 001-049, 051-061, 101-105, 201-203, Subtask 34-22-00-730-063 B. Compensation Adjustment/Test of the standby compass NOTE : The reference magnetic heading referred to in this procedure is ____ the magnetic heading indication read on the knob assembly of the standby compass compensator. Magnetic heading = true heading + magnetic variation (a natural phenomenon which varies continuously). (1) North (N) position compensation (a) On the standby compass compensator, set the two drums of the knob assembly to the N position. (b) On the standby compass, after the compass becomes stable: - Put the 2 mm-wide non-magnetic screwdriver into the NS hole below the display window - Adjust the N indication so that it agrees with the heading indication of the standby compass compensator. (2) East (E) position compensation (a) On the standby compass compensator, set the two drums of the knob assembly to the E position. (b) On the standby compass, after the compass becomes stable: - Put the 2 mm-wide non-magnetic screwdriver into the EW hole below the display window - Adjust the E indication so that it agrees with the heading indication of the standby compass compensator. (3) South (S) position compensation (a) On the standby compass compensator, set the two drums of the knob assembly to the S position.

  EFF : ALL  34-22-00   R  CES

 

Page 534 Nov 01/09

(b) On the standby compass, after the compass becomes stable: - Put the 2 mm-wide non-magnetic screwdriver into the NS hole below the display window - Adjust the S indication by the corrective value, i.e. half the difference between the heading indications of the compass and the compass compensator. Example: .if the standby compass compensator shows 180 degrees (S), and the standby compass 176 degrees (180 - 176 = 4), the corrective value is equal to half the difference = +2 degrees. (4) West (W) position compensation (a) On the standby compass compensator, set the two drums of the knob assembly to the W position. (b) On the standby compass, after the compass becomes stable: - Put the 2 mm-wide non-magnetic screwdriver into the EW hole below the display window - Adjust the W indication by the corrective value, i.e. half the difference between the heading indications of the compass and the compass compensator. Example: .if the standby compass compensator shows 270 degrees (W), and the standby compass 274 degrees (270 - 274 = -4), the corrective value is equal to half the difference = -2 degrees. R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-22-00-730-063-A B. Compensation Adjustment/Test of the Standby Compass NOTE : The reference magnetic heading referred to in this procedure is ____ the magnetic heading indication read on the knob assembly of the standby compass compensator. Magnetic heading = true heading + magnetic variation (a natural phenomenon which varies continuously). (1) North (N) position compensation (a) On the standby compass compensator, set the two drums of the knob assembly to the N position.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-22-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 535 Feb 01/10

(b) On the standby compass, after the compass becomes stable: - Put the KEY-CORRECTOR (CE2-40) (non-magnetic compensation key) into C hole - Adjust the N indication so that it agrees with the heading indication of the standby compass compensator. (2) East (E) position compensation (a) On the standby compass compensator, set the two drums of the knob assembly to the E position. (b) On the standby compass, after the compass becomes stable: - Put the KEY-CORRECTOR (CE2-40) (non-magnetic compensation key) into B hole - Adjust the E indication so that it agrees with the heading indication of the standby compass compensator. (3) South (S) position compensation (a) On the standby compass compensator, set the two drums of the knob assembly to the S position. (b) On the standby compass, after the compass becomes stable: - Put the KEY-CORRECTOR (CE2-40) (non-magnetic compensation key) into C hole - Adjust the S indication by the corrective value, i.e. half the difference between the heading indications of the compass and the compass compensator. Example: . if the standby compass compensator shows 180 degrees (S), and the standby compass 176 degrees (180 - 176 = 4) the corrective value is equal to half the difference = +2 degrees. (4) West (W) position compensation (a) On the standby compass compensator, set the two drums of the knob assembly to the W position. (b) On the standby compass, after the compass becomes stable: - Put the KEY-CORRECTOR (CE2-40) (non-magnetic compensation key) into B hole - Adjust the W indication by the corrective value, i.e. half the difference between the heading indications of the compass and the compass compensator. Example:

  R EFF : 062-099, 106-149, 151-199, 204-249,  34-22-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 536 Feb 01/10

. if the standby compass compensator shows 270 degrees (W), and the standby compass 274 degrees (270 - 274 = -4) the corrective value is equal to half the difference = -2 degrees. **ON A/C ALL Subtask 34-22-00-730-064 C. Calculate the deviation curve NOTE : During this adjustment procedure, the letters and graduations (on ____ the compass card) will be visible because the standby compass turns 360 degrees. Thus it becomes possible to make sure that the letters and graduations are not damaged. - Use the knob assembly to set the compass to these twelve headings (necessary to find the deviation curve) one after the other: 0⁰, 30⁰, 60⁰, 90⁰, 120⁰, 150⁰, 180⁰, 210⁰, 240⁰, 270⁰, 300⁰, 330⁰ - Write the values of the standby compass (CH) and of the standby compass compensator (MH) for each heading - Calculate the remaining deviation values R(⁰) as follows: R(⁰) = MH - CH (indication of standby compass) - Make sure that: * the remaining deviation values R(⁰) are not more than + or - 8 degrees for each heading * the maximum range between the positive and negative deviation values R(⁰) is not more than 10 degrees * the difference between each magnetic heading value on the standby compass and the standby compass compensator is not more than 8 degrees. If the difference is more than 8 degrees, adjust the compensation. - Write the magnetic heading Magnetic Heading (MH) + R(⁰) (Remaining deviation values)⁵ on the two correction cards. Put the cards on each side of the support of the standby compass. 5. Close-up ________ **ON A/C 001-049, 051-061, 101-105, 201-203, Subtask 34-22-00-860-066 A. Below the display window on the front face of the standby compass: - Install the protection cover on the compensator.

  EFF : ALL  34-22-00   R  CES

 

Page 537 Nov 01/09

**ON A/C ALL Subtask 34-22-00-860-067 B. Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) Remove the standby compass compensator. CAUTION : MAKE SURE THAT THE TWO DRUMS OF THE KNOB ASSEMBLY ARE ON _______ THE N (NORTH) POSITION BEFORE YOU PUT THE STANDBY COMPASS COMPENSATOR INTO STORAGE. THIS WILL PREVENT DEMAGNETIZATION. (4) Install the plate (2) with the four screws (1) under the standby compass. (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). (6) Put the aircraft back to the serviceable condition. (7) Remove the ground support and maintenance equipment, the special and standard tools and all other items. Subtask 34-22-00-080-051 C. Tool storage: At the end of the test, refer to the manufacturer recommend.

  EFF : ALL  34-22-00   R  CES

 

Page 538 Nov 01/09

COMPASS - STANDBY (2FN) - REMOVAL/INSTALLATION ______________________________________________ TASK 34-22-23-000-001 Removal of the Standby Compass (2FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

blanking caps circuit breaker(s) safety clip(s)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-061, 101-105, 201-203, 34-22-23-991-001 R R

Fig. 401

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-22-23-991-001-A

Fig. 401A

  EFF : ALL  34-22-23    CES

 

Page 401 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-22-23-865-053 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU LIGHTING/ICE AND STBY/COMP/LIGHT 1LF H04 4. Procedure _________ **ON A/C 001-049, 051-061, 101-105, 201-203, (Ref. Fig. 401/TASK 34-22-23-991-001) R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-22-23-991-001-A) **ON A/C ALL Subtask 34-22-23-020-050 A. Removal of the Standby Compass (2FN) (1) Pull the support (3) that can be retracted from its housing (2). (2) Loosen the four screws (6). (3) Remove the four screws (6). (4) Disengage the standby compass (5) from its support (3). (5) Disconnect the electrical connector (1). (6) Remove the standby compass (5). (7) Put blanking caps on the disconnected electrical connectors (1) and (4).

  EFF : ALL  34-22-23    CES

 

Page 402 Feb 01/10

Standby Compass Figure 401/TASK 34-22-23-991-001   R EFF : 001-049, 051-061, 101-105, 201-203,  34-22-23    CES

 

Page 403 May 01/05

Standby Compass Figure 401A/TASK 34-22-23-991-001-A   R EFF : 062-099, 106-149, 151-199, 204-249,  34-22-23 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 404 Feb 01/10

TASK 34-22-23-400-001 Installation of the Standby Compass (2FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------33-13-00-710-001 34-22-00-730-001

Operational Test of the Instrument and Panel Integral Lighting Compensation Adjustment/Test of the Standby Compass

**ON A/C 001-049, 051-061, 101-105, 201-203, 34-22-23-991-001 R R

Fig. 401

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-22-23-991-001-A

Fig. 401A

**ON A/C ALL 3. __________ Job Set-up Subtask 34-22-23-865-054 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU LIGHTING/ICE AND STBY/COMP/LIGHT 1LF H04

  EFF : ALL  34-22-23    CES

 

Page 405 Feb 01/10

4. Procedure _________ **ON A/C 001-049, 051-061, 101-105, 201-203, (Ref. Fig. 401/TASK 34-22-23-991-001) R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-22-23-991-001-A) **ON A/C ALL Subtask 34-22-23-420-050 A. Installation of the Standby Compass (2FN) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (1) and (4). (4) Make sure that the electrical connectors (1) and (4) are clean and in the correct condition. (5) Connect the electrical connector (1) to the standby compass (5). (6) Install the Standby Compass (5) in its support (3) that can be retracted. (7) Attach the standby compass (5) with the four screws (6). (8) Tighten the four screws (6). Subtask 34-22-23-865-055 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1LF

  EFF : ALL  34-22-23    CES

 

Page 406 Feb 01/10

Subtask 34-22-23-710-050 C. Test R R R

(1) Do the compensation adjustment/test of the standby compass (Ref. TASK 34-22-00-730-001) (2) Do the operational test of the instrument and panel integral lighting (Ref. TASK 33-13-00-710-001) 5. Close-up ________ Subtask 34-22-23-860-050 A. Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the support (3) that can be retracted in its housing (2).

  EFF : ALL  34-22-23    CES

 

Page 407 May 01/00

COMPASS - STANDBY (2FN) - INSPECTION/CHECK __________________________________________ TASK 34-22-23-200-001 Detailed Visual Inspection of the Standby Compass Damping Fluid 1. __________________ Reason for the Job R To make sure that the standby compass operates. 2. ______________________ Job Set-up Information Not Applicable 3. __________ Job Set-up Subtask 34-22-23-860-051 A. Aircraft Maintenance Configuration (1) On the windshield center post, pull the standby compass support that you can retract from its housing. (2) On the INT LT section of the overhead panel 25VU: - set the STBY COMPASS switch 2LF to STBY COMPASS. Make sure that the lighting of the standby compass is on. 4. Procedure _________ Subtask 34-22-23-210-050 A. Visual Inspection of the Standby Compass (1) Make sure that: - the support is in good condition - the standby compass is correctly attached to the support - there are no leaks. (2) In the compass bowl, make sure that the liquid: - is clear - does not contain bubbles or sediment. (3) Make sure that the two correction cards of the compass are on each side of the support.

  EFF : ALL  34-22-23    CES

 

Page 601 May 01/05

5. Close-up ________ Subtask 34-22-23-860-052 A. Put the aircraft back to its initial configuration. (1) On the INT LT section of the overhead panel 25VU: - set the STBY COMPASS switch 2LF to OFF. (2) On the windshield center post, push the standby compass support into its housing. (3) Put the aircraft back to the serviceable condition.

  EFF : ALL  34-22-23    CES

 

Page 602 Feb 01/98

INDICATOR - STANDBY HORIZON (7FN) - REMOVAL/INSTALLATION ________________________________________________________ TASK 34-22-24-000-001 Removal of the Standby Horizon Indicator (7FN) CAUTION : DO NOT REMOVE THE INDICATOR IMMEDIATELY AFTER DE-ENERGIZATION OF THE _______ INDICATOR. THERE MUST BE 10 MINUTES OR MORE BETWEEN ITS DE-ENERGIZATION AND THE START OF THE REMOVAL PROCEDURE. BE CAREFUL WITH INDICATOR DURING THE REMOVAL/INSTALLATION PROCEDURES, THE STANDBY HORIZON INDICATOR IS A FRAGILE INSTRUMENT. NOTE : After long low-rate turns (less than 10 degree bank) the standby horizon ____ indicator does not give accurate bank indications immediately. The specification of the standby horizon indicator accepts this type of operation. Thus, it is not necessary to replace the indicator. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R

No specific No specific No specific F1402369

blanking caps circuit breaker(s) safety clip(s) locking wedge. 1 EXTRACTING TOOL

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-22-24-991-001

Fig. 401

  EFF : 001-049, 051-099, 101-105, 151-199,  34-22-24 201-220, 236-238,   CES

 

Page 401 Feb 01/10

3. __________ Job Set-up Subtask 34-22-24-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-099, 101-105, 151-199, 201-212, 214-220, 236-238, 49VU NAV/STBY/HORIZON

5FN

F12

5FN

F12

4LF

Y04

**ON A/C 213-213, 49VU NAV/STBY/INST **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED Subtask 34-22-24-010-050 B. Remove the thermoformed cover from the center instrument panel. 4. Procedure _________ (Ref. Fig. 401/TASK 34-22-24-991-001) Subtask 34-22-24-020-050 A. Removal of the Standby Horizon Indicator (7FN) CAUTION : IF YOU MOVE THE STANDBY HORIZON INDICATOR WHEN IT IS REMOVED, _______ MAKE SURE THAT YOU FIRST BLOCK THE GYROSCOPE ASSEMBLY WITH THE LOCKING WEDGE (SUPPLIED WITH THE INSTRUMENT). (1) To cage the standby horizon indicator: pull knob (1) and insert the locking wedge. (2) Loosen the two screws (2). Do not remove them.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-22-24 201-220, 236-238,  R  CES

 

Page 402 Feb 01/10

Standby Horizon Indicator Figure 401/TASK 34-22-24-991-001   EFF : 001-049, 051-099, 101-105, 151-199,  34-22-24 201-220, 236-238,  R  CES

 

Page 403 Feb 01/10

(3) Push the screws (2) to release the standby horizon indicator (3) from the clamp. R R

(4) Disengage the standby horizon indicator (3) from its housing with EXTRACTING TOOL (F1402369). (5) Disconnect the electrical connector (5). (6) Remove the standby horizon indicator (3). (7) Put blanking caps on the disconnected electrical connectors (4) and (5).

  EFF : 001-049, 051-099, 101-105, 151-199,  34-22-24 201-220, 236-238,   CES

 

Page 404 Feb 01/10

R TASK 34-22-24-400-001 Installation of the Standby Horizon Indicator (7FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------33-13-00-710-001 R R

44-34-00-040-002

Operational Test of the Instrument and Panel Integral Lighting Deactivation of the On-board Mobile Telephony System

34-22-24-991-001

Fig. 401

  EFF : 001-049, 051-099, 101-105, 151-199,  34-22-24 201-220, 236-238,   CES

 

Page 405 Aug 01/09

R 3. __________ Job Set-up R Subtask 34-22-24-865-054 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-099, 101-105, 151-199, 201-212, 214-220, 236-238, R

49VU NAV/STBY/HORIZON

5FN

F12

5FN

F12

4LF

Y04

**ON A/C 213-213, R

49VU NAV/STBY/INST **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4. Procedure _________

R (Ref. Fig. 401/TASK 34-22-24-991-001) R

**ON A/C 213-213,

R

Subtask 34-22-24-860-050

R

A. Electromagnetic Interference (EMI)

R R R R

CAUTION : THERE IS AN ONBOARD MOBILE-TELEPHONY SYSTEM (OMTS) INSTALLED ON _______ THIS AIRCRAFT. THE OPERATION OF MOBILE PHONES CAN CAUSE ELECTROMAGNETIC INTERFERENCE WITH OTHER AIRCRAFT SYSTEMS IF THE EQUIPMENT INSTALLED DOES NOT HAVE AN APPROVED EMI ASSESSMENT.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-22-24 201-220, 236-238,   CES

 

Page 406 Aug 01/09

(1) Make sure that electromagnetic interference will not have an effect on the operation of the equipment you install. If the part number you will install: - is the same as the part number you removed, continue with the installation procedure. - is not the same as the part number you removed, deactivate the OMTS. (Ref. TASK 44-34-00-040-002).

R R

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 236-238, Subtask 34-22-24-420-050 B. Installation of the Standby Horizon Indicator (7FN) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (4) and (5). (4) Make sure that the electrical connectors are clean and in the correct condition. (5) Connect the electrical connector (5) to the standby horizon indicator (3). (6) Install the standby horizon indicator (3) in its housing. (7) Tighten the two screws (2). Subtask 34-22-24-865-053 C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5FN, 4LF Subtask 34-22-24-710-050 D. Operational Test (1) Do the operational test of the instrument and panel integral lighting (Ref. TASK 33-13-00-710-001). (2) Make sure that the flag is out of view.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-22-24 201-220, 236-238,   CES

 

Page 407 Feb 01/10

(3) One minute and 30 seconds after the energization, pull the resetting knob until the horizon line is stable. Release the knob rapidly. (4) Make sure that the roll index reads zero. (5) Make sure that the horizon line is stable and in line with the aircraft symbol. 5. Close-up ________ Subtask 34-22-24-410-050 A. Put the aircraft back to its initial configuration. (1) Install the thermoformed cover on the center instrument panel. (2) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-22-24 201-220, 236-238,  R  CES

 

Page 408 Feb 01/10

INDICATOR - ISIS (INTEGRATED STANDBY INSTRUMENT SYSTEM) (22FN) - SERVICING __________________________________________________________________________ TASK 34-22-25-170-001 Draining and Flushing of the Standby Static and Standby Total Pressure lines (ISIS) 1. __________________ Reason for the Job Refer to the MPD TASK: 342200-02 - To remove the water from the standby static pressure lines. - To remove dust and particles from the standby static and standby total pressure lines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific 98D34003500000 98D34103002000 98D34103004001

blanking cap dry nitrogen source - 2 bars (29 psi) WIRE-NYLON dia. 0,7 and 0,8mm access platform 1.6 m (5 ft. 3 in.) 2 ADAPTER COVER-STATIC PORT 1 ADAPTERS - AIR DATA SYSTEM FLUSHING 1 CLEANER-PITOT PROBE

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-24-34-600-001 24-41-00-861-002 24-41-00-862-002 34-22-25-000-001 34-22-25-400-001 34-22-25-790-001 34-22-25-991-002 34-22-25-991-004

Bleeding of the Standby Air Data System Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Removal of the ISIS Indicator (22FN) Installation of the ISIS Indicator (22FN) Low range Leak Test of the Standby Pneumatic circuits Fig. 301 Fig. 302

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 301 Feb 01/10

3. __________ Job Set-up (Ref. Fig. 301/TASK 34-22-25-991-002) NOTE : The hose couplings are self-sealing. ____ Subtask 34-22-25-861-051 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 34-22-25-010-051 B. Get Access (1) Put the access platform in position in the zone 110 at the access door 811. (2) Open the access door 811. Subtask 34-22-25-020-052 C. Aircraft Maintenance Configuration (1) Drain the standby air data system (Ref. TASK 12-24-34-600-001). (2) Disconnect the quick-disconnect coupling (4) from the ADM 19FP8 and the quick-disconnect coupling (8) from the ADM 19FP3. (3) Disconnect the cabin-pressure detection pressure-switch 14WN (3) from the static line. Put a blanking cap on the pressure switch. (4) Remove the water drain plug (2) from the water drain (1). (5) In the cockpit, on the center instrument panel: - remove the ISIS indicator 22FN (Ref. TASK 34-22-25-000-001) (6) Disconnect the quick-disconnect coupling (7) from the red 2-pin coupling and disconnect the quick-disconnect coupling (5) from the yellow 3-pin coupling of the ISIS indicator 22FN (6). (7) Connect a ADAPTERS - AIR DATA SYSTEM FLUSHING 3-pin adapter (98D34103002100) ) to the hose (5) and a ADAPTERS - AIR DATA SYSTEM FLUSHING 2-pin adapter (98D34103002102) to the hose (7). Then connect to the dry nitrogen source - 2 bars (29 psi).

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 302 Feb 01/10

Pressure lines Figure 301/TASK 34-22-25-991-002   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 303 Feb 01/10

(8) Attach the hoses to prevent movement. 4. Procedure _________ Subtask 34-22-25-170-050 A. Draining and Flushing of the Standby Static and the Standby Total Pressure Lines (1) Blow the gas into the hoses (5) and into the hose (7), from one to the other, at a pressure of 2 bars (29 psi). Do this for approximately 5 minutes. (2) Clean draining hole of the pitot probe 3 with CLEANER-PITOT PROBE and WIRE-NYLON dia. 0,7 and 0,8mm. (3) Make sure that there is no contamination in the pressurized gas at these outlets: - L static probe 3 and R static probe 3 - Pitot probe 3 - Water drain - Pipe of the cabin-pressure detection pressure-switch. (4) Put an ADAPTER COVER-STATIC PORT on the L static probe 3 then on the R static probe 3. (5) Make sure that the flow of gas is correct at : - the pipe of the pressure switch - the water drain. (6) Stop the flow of gas. Subtask 34-22-25-860-059 B. Put the aircraft back to its initial configuration. (1) Disconnect the dry nitrogen source. (2) Remove the adapters. (3) Install the water drain plug (2) on the water drain (1). (4) Remove the blanking cap from the pressure switch 14WN (3). (5) Connect the static line to the pressure switch 14WN (3).

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 304 Feb 01/10

(6) Connect the quick-disconnect coupling (8) to the ADM 19FP3 and the quick-disconnect coupling (4) to the ADM 19FP8. (Ref. Fig. 302/TASK 34-22-25-991-004) (7) Make sure that you can see the blue ring on the quick-disconnect couplings (4) and (8). (8) Pull the quick-disconnect coupling to be sure that they are correctly attached. (9) Install the ISIS indicator (Ref. TASK 34-22-25-400-001) on the center instrument panel. (10) Release the hoses. (11) Do a visual inspection only, of the quick-disconnect fitting connection, by a second qualified mechanic, with a sign off by both mechanics. Subtask 34-22-25-790-051 C. Leak test (1) Make sure that all the hoses are connected correctly. (2) Do a leak test of the standby air data system (Ref. TASK 34-22-25-790-001). 5. Close-up ________ Subtask 34-22-25-410-051 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (3) Close the access door 811. (4) Remove the access platform(s).

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Page 305 Feb 01/10

Illustration of the Quick-Disconnect coupling Figure 302/TASK 34-22-25-991-004   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 306 Feb 01/10

Subtask 34-22-25-862-050 B. Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 307 Feb 01/10

______________________________________________________________ INDICATOR - ISIS (INTEGRATED STANDBY INSTRUMENT SYSTEM) (22FN) ____________________ REMOVAL/INSTALLATION TASK 34-22-25-000-001 Removal of the ISIS Indicator (22FN) NOTE : After long low-rate turns (less than 6 degree bank) the ISIS ____ indicatorISIS does not give accurate bank indications immediately. The specification of the ISIS indicator accepts this type of operation. Thus, it is not necessary to replace the indicator. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R

No specific No specific No specific F1402369

blanking caps blanking plugs circuit breaker(s) safety clip(s) 1 EXTRACTING TOOL

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 106-149, 221-233, 301-312, 401-499, 34-22-25-991-001 R

Fig. 401

**ON A/C 234-235, 239-249, 251-299, 313-399, 501-509, 511-526, 528-599, 34-22-25-991-001-A

Fig. 401A

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Page 401 Feb 01/10

R R

**ON A/C 106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 3. __________ Job Set-up Subtask 34-22-25-865-058 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/INST 5FN F12 105VU NAV/STBY/INST/BAT 23FN J01 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 Subtask 34-22-25-010-050 B. Remove the thermoformed cover from the center instrument panel. 4. Procedure _________ **ON A/C 106-149, 221-233, 301-312, 401-499, (Ref. Fig. 401/TASK 34-22-25-991-001)

R

**ON A/C 234-235, 239-249, 251-299, 313-399, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-22-25-991-001-A)

R R

**ON A/C 106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-22-25-020-051 A. Removal of the ISIS Indicator (22FN) CAUTION : WHEN YOU REMOVE THE ISIS INDICATOR, DO NOT USE THE BARO BUTTON _______ TO PULL THE INDICATOR OUT OF ITS HOUSING. IF YOU USE THE BARO BUTTON, YOU CAN CAUSE DAMAGE TO THE INDICATOR. (1) Loosen the screws (3). Do not remove them. (2) Push the screws (3) to release the ISIS indicator (1) from the clamp.

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Page 402 Feb 01/10

ISIS Indicator Figure 401/TASK 34-22-25-991-001   R EFF : 106-149, 221-233, 301-312, 401-499,  34-22-25    CES

 

Page 403 Aug 01/09

ISIS Indicator Figure 401A/TASK 34-22-25-991-001-A   R EFF : 234-235, 239-249, 251-299, 313-399,  34-22-25 501-509, 511-526, 528-599,   CES

 

Page 404 Feb 01/10

R R

(3) Disengage the ISIS indicator (1) from its housing EXTRACTING TOOL (F1402369). (4) Disconnect the electrical connector (5). (5) Disconnect the red and green quick-disconnect couplings (4) from the connectors (2). (6) Remove the ISIS indicator (1). (7) Put blanking caps on the disconnected electrical connectors (5) and (6). (8) Put blanking plugs on the disconnected line ends (2) and (4).

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 405 Feb 01/10

TASK 34-22-25-400-001 Installation of the ISIS Indicator (22FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------25-13-41-000-002 25-13-41-400-002 33-13-00-710-001 34-22-25-740-001

Removal of the Sidewall Panels Installation of the Sidewall Panels Operational Test of the Instrument and Panel Integral Lighting BITE Test of the ISIS Indicator with the pushbutton switches on the Face of the Indicator.

R **ON A/C 106-149, 221-233, 301-312, 401-499, 34-22-25-991-001 R

**ON A/C 234-235, 239-249, 251-299, 313-399, 501-509, 511-526, 528-599, 34-22-25-991-001-A

R R

Fig. 401

Fig. 401A

**ON A/C 106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-22-25-991-003 34-22-25-991-005

Fig. 402 Fig. 403

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Page 406 Feb 01/10

3. __________ Job Set-up Subtask 34-22-25-865-059 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/INST 5FN F12 105VU NAV/STBY/INST/BAT 23FN J01 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 Subtask 34-22-25-010-053 B. Remove the sidewall panel 211LW (Ref. TASK 25-13-41-000-002). 4. Procedure _________ **ON A/C 106-149, 221-233, 301-312, 401-499, (Ref. Fig. 401/TASK 34-22-25-991-001) R

**ON A/C 234-235, 239-249, 251-299, 313-399, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-22-25-991-001-A)

R R R

**ON A/C 106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-22-25-420-051

R

A. Installation of the ISIS Indicator (22FN) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking plugs from the line ends (2) and (4).

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 407 Feb 01/10

(4) Connect the quick-disconnect couplings (4) of the pressure lines (green and red) to the related connectors (2) of the ISIS indicator (1). (Ref. Fig. 402/TASK 34-22-25-991-003) (5) Make sure that you can see the blue ring on the quick-disconnect couplings. (6) Pull the quick-disconnect couplings to be sure that they are correctly attached. (7) Remove the blanking caps from the electrical connectors (5) and (6). (8) Make sure that the electrical connectors are clean and in the correct condition. (9) Connect the electrical connector (5) to the receptacle (6) of the ISIS indicator (1). (10) Install the ISIS indicator (1) in its housing. (11) Look behind the ISIS indicator and make sure that the position of the flexible hoses (static and total pressure lines) is satisfactory (no crushing, kinks, creases or folds). (12) Install the screws (3). Do not tighten at this step. Subtask 34-22-25-865-060 R

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 4LF, 5FN, 23FN Subtask 34-22-25-710-050

R

C. Test (1) Make sure that the indications (Roll, Pitch and Lateral Acceleration) on the ISIS indicator are the same as the indications on the CAPT (F/O) PFD. (2) Make sure that the indications of the ISIS indicator are in the tolerances that follow: (Ref. Fig. 403/TASK 34-22-25-991-005) - Roll: less than 2.5 deg. (equivalent to 1/4 of a roll graduation) (item A),

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Page 408 Feb 01/10

Illustration of the Quick-disconnect coupling Figure 402/TASK 34-22-25-991-003   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 409 Feb 01/10

Tolerances limit of the ISIS Indicator (22FN) installation Figure 403/TASK 34-22-25-991-005   R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 410 Feb 01/10

- Pitch: less than 1.25 deg. (equivalent to 1/2 of a pitch graduation) (item B), - Lateral Acceleration: less than 1.3mm (item C). (3) Hold the ISIS indicator in the correct position and tighten the screws (3). (4) Do the operational test of the instrument and panel integral lighting (Ref. TASK 33-13-00-710-001). (5) Do the BITE test of the ISIS indicator (Ref. TASK 34-22-25-740-001). 5. Close-up ________ Subtask 34-22-25-410-050 A. Put the aircraft back to its initial configuration. (1) Install the thermoformed cover on the center instrument panel. (2) Install the sidewall panel 211LW (Ref. TASK 25-13-41-400-002). (3) Make sure that the work area is clean and clear of tool(s) and other items.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 411 Feb 01/10

______________________________________________________________ INDICATOR - ISIS (INTEGRATED STANDBY INSTRUMENT SYSTEM) (22FN) _______________ ADJUSTMENT/TEST TASK 34-22-25-710-001 Operational Check of ISIS DC HOT Bus SUPPLY 1. __________________ Reason for the Job Refer to the MPD TASK: 342000-03 Test of the correct power supply of ISIS DC HOT BUS in emergency configuration when the batteries are the only power supply source. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power

3. __________ Job Set-up Subtask 34-22-25-861-052 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 34-22-25-860-063 B. Aircraft Maintenance Configuration (1) On the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is at NORM.

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Page 501 Feb 01/10

Subtask 34-22-25-865-063 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/INST 5FN F12 105VU NAV/STBY/INST/BAT 23FN J01 Subtask 34-22-25-860-064 D. Aircraft Maintenance Configuration (1) On panel 35VU, make sure that the ELEC/ BAT1 and ELEC/BAT2 pushbutton switches are released. - the OFF legends is on. 4. Procedure _________ Subtask 34-22-25-740-052 A. Operational Test of ISIS DC HOT BUS SUPPLY ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Open circuit breaker 5FN.

On panel 401VU: - make sure that the display of the ISIS indicator (22FN) is off.

2. On overhead panel: - on the panel 21VU, push and hold the EMER GEN TEST pushbutton switch (23XE). - simultaneously, on the panel 35VU, release the ELEC/EXT PWR pushbutton switch (10XG).

- after approximatly 12 seconds, make sure that the display of the ISIS indicator (22FN) is on. The INIT 90s (initialization display) indication comes into view.

3. On the overhead panel: - on the panel 21VU, release the EMER GEN TEST pushbutton switch (23XE). - on the panel 35VU, push the ELEC/EXT PWR pushbutton switch (10XG).

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Page 502 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------4. Close circuit breaker 5FN. - after approximatly 12 seconds, make sure that the display of the ISIS indicator (22FN) is on. The INIT 90s (initialization display) indication comes into view. 5. Close-up ________ Subtask 34-22-25-860-065 A. Put the aircraft back to its initial configuration. Subtask 34-22-25-862-051 B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 503 Feb 01/10

TASK 34-22-25-740-001 BITE Test of the ISIS Indicator with the pushbutton switches on the Face of the Indicator. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

circuit breaker(s) safety clip(s)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-22-25-860-052 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the ADIRS Start procedure (Ref. TASK 34-10-00-860-002)

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 504 Feb 01/10

Subtask 34-22-25-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/INST 5FN F12 Subtask 34-22-25-865-051 C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/INST 5FN F12 Subtask 34-22-25-860-050 D. Aircraft Maintenance Configuration (1) On the center instrument panel 401VU, on the ISIS indicator: - make sure that the INIT 90 s indication comes into view. - make sure that the Functions page comes into view. 4. Procedure _________ Subtask 34-22-25-740-050 A. BITE Test of the ISIS Indicator NOTE : Do not move the aircraft during the alignment period (110s) of ____ this test. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center instrument panel 401VU, on the ISIS indicator: - push the BUGS and the LS pushbutton switches at the same time and hold them pushed for more than 2 seconds.

On the center instrument panel 401VU, on the ISIS indicator: - the maintenance page comes into view with TESTS and OTHER DATA indications.

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Page 505 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the TESTS page comes into view. the TESTS indication. - push the line key adjacent to the FUNCTIONAL TEST (110s) indication.

- the TEST page comes into view. Then the IN PROGRESS 110s indication comes into view. - at the end of the test, the TEST OK indication comes into view.

- push the RST pushbutton switch until the Functions page comes into view. 5. Close-up ________ Subtask 34-22-25-860-051 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS Stop procedure (Ref. TASK 34-10-00-860-005) (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 506 Feb 01/10

TASK 34-22-25-790-001 Low range Leak Test of the Standby Pneumatic circuits WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU _______ START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE _______ CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM. AUTOMATIC MOVEMENT OF THE FLIGHT CONTROL SURFACES CAN BE DANGEROUS AND/OR CAUSE DAMAGE. CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO _______ INSTRUMENTS: - THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg) - CHANGES IN STATIC PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE - DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED. CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE _______ STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg). 1. __________________ Reason for the Job Refer to the MPD TASK: 342200-05 To make sure that there are no leaks in the standby static and standby pitot circuits.

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Page 507 Feb 01/10

2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 36122 98D10103500001 98D34003500000

1 1 1 1

circuit breaker(s) safety clip(s) colored adhesive tape GENERATOR - GROUND PRESSURE MINI. 100 MB ADAPTOR-CHARGING,PITOT PROBE COVER-STATIC PROBE ADAPTER COVER-STATIC PORT

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 27-50-00-866-009 31-60-00-860-001 31-60-00-860-002 34-11-15-200-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Retraction of the Flaps on the Ground EIS Start Procedure EIS Stop Procedure Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3)

3. __________ Job Set-up Subtask 34-22-25-860-053 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 34-22-25-865-052 B. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 508 Feb 01/10

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 Subtask 34-22-25-865-053 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/INST 5FN F12 105VU NAV/STBY/INST/BAT 23FN J01 Subtask 34-22-25-420-050 D. Connection of the Ground Pressure Generator (1) Remove the slip on covers from the static probes 7DA3, 8DA3 and the pitot probe 9DA3 of the standby system. (2) Connect the GENERATOR - GROUND PRESSURE MINI. 100 MB to one standby static probe with the ADAPTER COVER-STATIC PORT (98D34003500100). (3) Connect the ground pressure generator to the standby pitot probe with the ADAPTOR-CHARGING,PITOT PROBE. (4) Seal the opposite standby static probe with a piece of plastic (see CAUTION para.(5) below) and with the COVER-STATIC PROBE (98D34003500103). (5) Seal the drain holes: CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT _______ SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE. ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE FIRST AND USE THE COLORED ADHESIVE TAPE TO ATTACH THE PLASTIC. IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE, THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE PROBE.

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Page 509 Feb 01/10

Seal the drain holes of the pitot probe with a piece of plastic and/or colored adhesive tape of very bright color. (6) Move the vane of the AOA sensor 3 to the upper position. Maintain the vane in position with colored adhesive tape. Subtask 34-22-25-860-067 E. Aircraft Maintenance Configuration (1) Do the EIS start procedure (PFD only) (Ref. TASK 31-60-00-860-001). (2) Make sure that the flaps are in the fully retracted position (Ref. TASK 27-50-00-866-009). (3) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to NAV. (4) Start the ground pressure generator. 4. Procedure _________ **ON A/C 106-149, 221-235, 239-249, 251-299, Subtask 34-22-25-790-050 A. Leak Test NOTE : You can do the test that follows for a static pressure of 691.4 ____ hPa and an impact pressure of 59 hPa (or a total pressure of 750.4 hPa) but it is not as accurate. On the SWITCHING panel 8VU set the AIR DATA selector switch to CAPT ON 3 (or F/O ON 3) position. Make sure that: - the CAPT (or F/O) PFD shows 10,237 ft +/- 30 ft and 190 kts +/3 kts - the ISIS indicator show 10,201 ft +/- 50 ft and airspeed 189 kts +/- 5 kts. After 5 minutes: - the change of altitude must not be more than 370 ft, - the change of speed must not be more than 10 Kts.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 510 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center instrument panel 401VU, on the ISIS indicator: - set a barometric pressure of 1013 hPa. 2. On the SWITCHING panel 8VU set the AIR DATA selector switch to CAPT ON 3 (or F/O ON 3) position.

On the CAPT (or F/O) PFD, the indications from ADIRU3 are shown.

3. On the ground pressure generator: - set a static pressure of 455,4 hPa. - set an impact pressure of 186,4 hPa (or a total pressure of 641,8 hPa). - close the electrovalves to isolate the static and pitot circuits of the aircraft from the ground pressure generator.

- Make sure that: the CAPT (or F/O) PFD shows 21,369 ft +/- 40 ft and 341 kts +/- 3 kts, the ISIS indicator shows 20,529 ft +/- 85 ft and 329 kts +/- 8 kts. After 5 minutes, on the ISIS display and on the CAPT (or F/O) PFD: - make sure that the change of altitude is not more than 500 ft. After 10 minutes: - make sure that the change of speed is not more than 20 Kts.

- slowly balance the pressure in the standby static and pitot circuits and open the electrovalves to get atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25    CES

 

Page 511 Aug 01/09

**ON A/C 301-399, Subtask 34-22-25-790-050-A A. Leak Test R R R

NOTE : You can do the test that follows for a static pressure of 690 hPa ____ and an impact pressure of 60.4 hPa (or a total pressure of 750.4 hPa) but it is not as accurate. On the SWITCHING panel 8VU set the AIR DATA selector switch to CAPT ON 3 (or F/O ON 3) position. Make sure that: - the CAPT (or F/O) PFD shows 10,225 ft +/- 30 ft and 190 kts +/3 kts, - the ISIS indicator show 10,253 ft +/- 50 ft and airspeed 191 kts +/- 5 kts. After 5 minutes: - the change of altitude must not be more than 370 ft, - the change of speed must not be more than 10 Kts.

R R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center instrument panel 401VU, on the ISIS indicator: - set a barometric pressure of 1013 hPa. 2. On the SWITCHING panel 8VU set the AIR DATA selector switch to CAPT ON 3 (or F/O ON 3) position.

On the CAPT (or F/O) PFD, the indications from ADIRU3 are shown.

3. On the ground pressure generator: - set a static pressure of 447.9 hPa. R R R

- set an impact pressure of 193.9 hPa (or a total pressure of 641,8 hPa).

R R

- close the electrovalves to isolate the static and pitot circuits of the aircraft from

- Make sure that: the CAPT (or F/O) PFD shows 21,894 ft +/- 40 ft and 349 kts +/- 3 kts,

  EFF : 301-399,  34-22-25    CES

 

Page 512 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------the ground pressure generator. the ISIS indicator shows 20,923 ft +/- 85 ft and 335 kts +/- 8 kts. After 5 minutes, on the ISIS display and on the CAPT (or F/O) PFD: - make sure that the change of altitude is not more than 500 ft. After 10 minutes: - make sure that the change of speed is not more than 20 Kts. - slowly balance the pressure in the standby static and pitot circuits and open the electrovalves to get atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

**ON A/C 401-499, Subtask 34-22-25-790-050-B A. Leak Test R R R

NOTE : You can do the test that follows for a static pressure of 691 hPa ____ and an impact pressure of 59.3 hPa (or a total pressure of 750.3 hPa) but it is not as accurate. On the SWITCHING panel 8VU set the AIR DATA selector switch to CAPT ON 3 (or F/O ON 3) position. Make sure that: - the CAPT (or F/O) PFD shows 10,177 ft +/- 30 ft and 188 kts +/3 kts, - the ISIS indicator shows 10,216 ft +/- 50 ft and airspeed 189 kts +/- 5 kts. After 5 minutes: - the change of altitude must not be more than 370 ft, - the change of speed must not be more than 10 Kts.

R R R R

  EFF : 301-399, 401-499,  34-22-25    CES

 

Page 513 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center instrument panel 401VU, on the ISIS indicator: - set a barometric pressure of 1013 hPa. 2. On the SWITCHING panel 8VU set the AIR DATA selector switch to CAPT ON 3 (or F/O ON 3) position.

On the CAPT (or F/O) PFD, the indications from ADIRU3 are shown.

3. On the ground pressure generator: R R

- set a static pressure of 462.4 hPa.

R R R

- set an impact pressure of 179,1 hPa (or a total pressure of 641,50 hPa). - close the electrovalves to isolate the static and pitot circuits of the aircraft from the ground pressure generator.

R R R R

- Make sure that: the CAPT (or F/O) PFD shows 20,918 ft +/- 40 ft and 335 kts +/- 3 kts, the ISIS indicator shows 20,166 ft +/- 85 ft and 323 kts +/- 8 kts. After 5 minutes, on the ISIS display and on the CAPT (or F/O) PFD: - make sure that the change of altitude is not more than 500 ft. After 10 minutes: - make sure that the change of speed is not more than 20 Kts.

- slowly balance the pressure in the standby static and pitot circuits and open the electrovalves to get atmospheric pressure.

The rate of descent must not be more than 6000 ft/mn.

  EFF : 401-499,  34-22-25    CES

 

Page 514 Aug 01/08

R

**ON A/C 501-509, 511-526, 528-599, Subtask 34-22-25-790-050-C A. Leak Test NOTE : You can do the test that follows for a static pressure of 691.4 ____ hPa and an impact pressure of 59 hPa (or a total pressure of 750.4 hPa) but it is not as accurate. On the SWITCHING panel 8VU set the AIR DATA selector switch to CAPT ON 3 (or F/O ON 3) position. Make sure that: - the CAPT (or F/O) PFD shows 10,237 ft +/- 30 ft and 190 kts +/3 kts - the ISIS indicator show 10,201 ft +/- 50 ft and airspeed 189 kts +/- 5 kts. After 5 minutes: - the change of altitude must not be more than 370 ft, - the change of speed must not be more than 10 Kts. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center instrument panel 401VU, on the ISIS indicator: - set a barometric pressure of 1013 hPa. 2. On the SWITCHING panel 8VU set the AIR DATA selector switch to CAPT ON 3 (or F/O ON 3) position.

On the CAPT (or F/O) PFD, the indications from ADIRU3 are shown.

3. On the ground pressure generator: - set a static pressure of 456 hPa. - set an impact pressure of 185,8 hPa (or a total pressure of 641,8 hPa). - close the electrovalves to isolate the static and pitot circuits of the aircraft from

- Make sure that: the CAPT (or F/O) PFD shows 21,349 ft +/- 40 ft and 341 kts +/- 3 kts,

  R EFF : 501-509, 511-526, 528-599,  34-22-25    CES

 

Page 515 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------the ground pressure generator. the ISIS indicator shows 20,498 ft +/- 85 ft and 328 kts +/- 8 kts. After 5 minutes, on the ISIS display and on the CAPT (or F/O) PFD: - make sure that the change of altitude is not more than 500 ft. After 10 minutes: - make sure that the change of speed is not more than 20 Kts. - slowly balance the pressure in the standby static and pitot circuits and open the electrovalves to get atmospheric pressure. R R

The rate of descent must not be more than 6000 ft/mn.

**ON A/C 106-149, 221-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 5. Close-up ________ Subtask 34-22-25-020-050 A. Removal of the Ground Pressure Generator (1) Stop the ground pressure generator. (2) Disconnect the ground pressure generator. (3) Remove the adaptors from the standby static probe and the standby pitot probe. (4) Remove the cover from the opposite standby static probe. (5) Remove the piece of plastic and the colored adhesive tape from the drain holes of the standby pitot probe. (6) Remove the colored adhesive tape from the vane of the AOA. (7) Install the slip on covers on the standby static probes and the standby pitot probe.

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Page 516 Feb 01/10

Subtask 34-22-25-865-054 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 3DA3, 5DA3, 7XE Subtask 34-22-25-860-054 C. Put the aircraft back to its initial configuration. (1) On the SWITCHING panel 8VU set the AIR DATA selector switch to NORMAL position. (2) Do the EIS stop procedure (PFD only) (Ref. TASK 31-60-00-860-002). (3) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF. (4) Do a reset of each ELAC: - on the panel 49VU, open then close the ELAC1 C/B, - on the panel 121VU, open then close the ELAC2 C/B. (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (6) Make sure that the work area is clean and clear of tool(s) and other items. (7) Make sure that the drain holes on the pitot probes are not blocked by unwanted materials (Ref. TASK 34-11-15-200-001)

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Page 517 Feb 01/10

TASK 34-22-25-720-001 Functional Test of the ISIS Indicator 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 36122 98D10103500001 98D34003500000

1 1 1 1

circuit breaker(s) safety clip(s) GENERATOR - GROUND PRESSURE MINI. 100 MB ADAPTOR-CHARGING,PITOT PROBE COVER-STATIC PROBE ADAPTER COVER-STATIC PORT

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-24-34-600-001 24-41-00-861-002 24-41-00-862-002 29-00-00-864-001

Bleeding of the Standby Air Data System Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action

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Page 518 Feb 01/10

3. __________ Job Set-up WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. Subtask 34-22-25-860-055 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Make sure that hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001) Subtask 34-22-25-865-055 B. Open, safety and tag this(these) circuit breaker(s): WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU ANTI ICE/PROBES/AOA/1 4DA1 D04 49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 Subtask 34-22-25-865-056 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/INST 5FN F12 105VU NAV/STBY/INST/BAT 23FN J01

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Page 519 Feb 01/10

Subtask 34-22-25-860-056 D. Connection of the Ground Pressure Generator CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE _______ TO INSTRUMENTS: - THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg) - CHANGES IN STATIC PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE - DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED. CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN _______ THE STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg). (1) Remove the slip on covers from the L and R standby static probes 7DA3, 8DA3 and the standby pitot probe 9DA3. (2) Drain the standby air data system (Ref. TASK 12-24-34-600-001). (3) Connect the GENERATOR - GROUND PRESSURE MINI. 100 MB to: - the L or R standby static probe with the ADAPTER COVER-STATIC PORT (98D34003500100). - the standby pitot probe with the ADAPTOR-CHARGING,PITOT PROBE. (4) Seal the opposite standby static probe with the COVER-STATIC PROBE (98D34003500103). (5) Start the ground pressure generator and set a static pressure of 1013 hPa (29,92 in.Hg).

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Page 520 Feb 01/10

4. Procedure _________ Subtask 34-22-25-720-051 A. Test of the Standby Airspeed and Altimeter Functions of the ISIS Indicator ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the ground pressure generator:

On the center instrument panel 401VU:

- set a static pressure of 314.8 hPa (29,000 ft). - set an impact pressure of 200.1 hPa (340 Kts).

- make sure that the ISIS shows 29,000 ft (+ or - make sure that the ISIS shows 340 Kts (+ or - 5

indicator 180 ft). indicator Kts).

- make sure that the ISIS shows 20,000 ft (+ or - make sure that the ISIS shows 340 Kts (+ or - 5

indicator 150 ft). indicator Kts).

- make sure that the ISIS shows 15,000 ft (+ or - make sure that the ISIS shows 300 Kts (+ or - 4

indicator 105 ft). indicator Kts).

- make sure that the ISIS shows 10,000 ft (+ or - make sure that the ISIS shows 250 Kts (+ or - 5

indicator 50 ft). indicator Kts).

- set a static pressure of 465.6 hPa (20,000 ft). - set an impact pressure of 200.1 hPa (340 Kts).

- set a static pressure of 571.8 hPa (15,000 ft). - set an impact pressure of 153.5 hPa (300 Kts).

- set a static pressure of 696.8 hPa (10,000 ft). - set an impact pressure of 105 hPa (250 Kts).

- set a static pressure of 843 hPa (5000 ft).

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Page 521 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set an impact pressure of 53.5 hPa - make sure that the ISIS indicator (180 Kts). shows 5000 ft (+ or - 40 ft). - make sure that the ISIS indicator shows 180 Kts (+ or - 3 Kts). - set a static pressure of 908.1 hPa (3000 ft). - set an impact pressure of 53.5 hPa (180 Kts).

- make sure that the ISIS indicator shows 3000 ft (+ or - 30 ft). - make sure that the ISIS indicator shows 180 Kts (+ or - 5 Kts).

- set a static pressure of 977.1 hPa (1000 ft). - set an impact pressure of 53.5 hPa (180 Kts).

- make sure that the ISIS indicator shows 1000 ft (+ or - 20 ft). - make sure that the ISIS indicator shows 180 Kts (+ or - 5 Kts).

- slowly decrease the pressure until you get atmospheric pressure. 5. Close-up ________ Subtask 34-22-25-860-057 A. Removal of the Ground Pressure Generator (1) Stop the ground pressure generator. (2) Disconnect the ground pressure generator. (3) Remove the adaptors from the standby static probe and the standby pitot probe. (4) Remove the cover from the opposite standby static probe. (5) Install the slip on covers on the standby static probes and the standby pitot probe.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 522 Feb 01/10

Subtask 34-22-25-865-057 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 3DA1, 3DA2, 3DA3, 4DA1, 4DA2, 4DA3, 5DA1, 5DA2, 5DA3, 7XE Subtask 34-22-25-860-058 C. Put the aircraft back to its initial configuration. (1) Do a reset of each ELAC: - on the panel 49VU, open then close the ELAC1 C/B, - on the panel 121VU, open then close the ELAC2 C/B. (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (3) Make sure that the work area is clean and clear of tool(s) and other items.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 523 Feb 01/10

______________________________________________________________ INDICATOR - ISIS (INTEGRATED STANDBY INSTRUMENT SYSTEM) (22FN) ________________ INSPECTION/CHECK TASK 34-22-25-200-001 ISIS Inspection for Legibility 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-21-12-100-001 24-41-00-861-002 24-41-00-862-002 34-22-25-000-001 34-22-25-400-001

Cleaning of the Cockpit Display-Units Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Removal of the ISIS Indicator (22FN) Installation of the ISIS Indicator (22FN)

3. __________ Job Set-up Subtask 34-22-25-860-066 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002) (2) Clean the ISIS screen (Ref. TASK 12-21-12-100-001) Subtask 34-22-25-865-067 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/STBY/INST 5FN F12

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 601 Feb 01/10

4. Procedure _________ Subtask 34-22-25-710-051 A. On the ISIS indicator: - Push the (+) pushbutton switch to maximum brightness. Subtask 34-22-25-740-053 B. On the ISIS indicator: ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ISIS indicator: - Push the BUGS and LS pushbutton switches at the same time and for more than two seconds.

On the ISIS indicator: - The TESTS and OTHER DATA page comes into view.

- Push the (+) pushbutton switch

- The FUNCTIONAL and DISPLAY TESTS page comes into view.

- Push the (-) pushbutton switch

- The screen becomes black.

Subtask 34-22-25-280-050 C. From a distance of 0,40m (15,74inches), do a visual check of the black screen for: - A white line or a line in color, - A white column or a column in color, - Pixels that are failed-on. NOTE : A failed-on pixel is a pixel which is always fully or not fully on ____ (white or in color). The black screen makes it possible to see the failed-on pixels. (1) Count and record the pixels that are defective: - Number of failed-on pixels on the screen - Number of two adjacent failed-on pixels on the screen - Number of sets of two adjacent failed-on pixels on the screen - White line or line in color, white column or column in color. Subtask 34-22-25-740-054 D. On the ISIS indicator, push the (-) pushbutton switch. The screen becomes white.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 602 Feb 01/10

Subtask 34-22-25-280-051 E. From a distance of 0,40m (15,74inches), do a visual check of the white screen for: - A black line or a line in color - A black column or a column in color - Pixels that are failed-off. NOTE : A failed-off pixel is a pixel which is always fully or not fully ____ off (black or in color). The white screen makes it possible to see the failed-off pixels. (1) Count and record the pixels that are defective: - Number of failed-off pixels on the screen - Number of two adjacent failed-off pixels on the screen - Number of sets of two adjacent failed-off pixels on the screen - Black line or line in color, black column or column in color. Subtask 34-22-25-710-052 F. For each screen, if the defective pixels recorded do not obey these conditions: - You must not have more than two adjacent failed-on or failed-off pixels - You must not have more than 5 sets of two adjacent failed-on or failed-off pixels - You must not have a white or black line or column, or a line or column in color - The total of failed-on and failed-off pixels must not be more than 30 pixels, replace the ISIS indicator (Ref. TASK 34-22-25-000-001) and (Ref. TASK 34-22-25-400-001). Then, on the ISIS indicator, push the RST pushbutton switch three times to come back to the operational page. Push the (-) pushbutton switch to come back to a normal brightness. 5. Close-up ________ Subtask 34-22-25-410-053 A. Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002) Make sure that the work area is clean and clear of tool(s) and other items.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 603 Feb 01/10

______________________________________________________________ INDICATOR - ISIS (INTEGRATED STANDBY INSTRUMENT SYSTEM) (22FN) _________________ CLEANING/PAINTING TASK 34-22-25-100-001 Cleaning of the ISIS Indicator 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

absorbent surgical-cotton wadding impregnated screen pad 2000 optical precision pad sterile gauze pad

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 11-010

USA TT-I-735 GRADE A ISOPROPYL ALCOHOL (Ref. 20-31-00)

Material No. 11-020 VISUAL DISPLAY UNIT ANTI-STATIC CLEANER (Ref. 20-31-00) 3. __________ Job Set-up Subtask 34-22-25-869-050 A. There is no special job set-up for this task.

  R EFF : 106-149, 221-235, 239-249, 251-299,  34-22-25 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 701 Feb 01/10

4. Procedure _________ Subtask 34-22-25-100-050 A. Cleaning of the Screen of the ISIS Indicator CAUTION : BE VERY CAREFUL WHEN YOU CLEAN THE FRONT GLASS OF LCDUS. IT IS _______ NOT POSSIBLE TO REPLACE THE GLASS. IF YOU CAUSE DAMAGE TO LCDUS, THE DAMAGE WILL BE PERMANENT. CAUTION : MAKE SURE THAT YOU OBEY THE INSTRUCTIONS IN THE CLEANING _______ PROCEDURE THAT FOLLOWS. INCORRECT CLEANING CAN CAUSE DAMAGE TO THE ANTI-REFLECTIVE COATING. IT IS NOT PERMITTED TO USE TISSUES SUCH AS KLEENEX TISSUES. SUCH TISSUES CAN CAUSE LOCAL REMOVAL OF THE SURFACE TREATMENT, AND THUS HALOS OR SCRATCHES. ALWAYS APPLY THE CLEANING AGENT TO THE PAD AND NOT TO THE SCREEN. CAUTION : USE ONLY THE SPECIFIED MATERIALS AND OBEY THE INSTRUCTIONS FROM _______ THE MANUFACTURERS. OTHER MATERIALS CAN CAUSE DAMAGE TO THE SURFACE PROTECTION OF THE COMPONENTS AND THE RELATED AREA. (1) Make an absorbent surgical-cotton wadding or a sterile gauze pad or an optical precision pad moist with CLEANING AGENTS (Material No. 11020) or CLEANING AGENTS (Material No. 11-010). You can also use an impregnated screen pad 2000. (2) Move the moist wad (or pad) lightly across the surface of the ISIS screen (one time only). (3) If you find again marks or dust on the screen, do steps (1) and (2) again with a new piece of moist wad (or pad). Do these steps again until the screen is fully clean. NOTE : Use a new pad (or wad) each time to prevent scratches that can ____ be caused by a dusty pad. (4) Dry the ISIS screen with a clean wad (or pad). To do this, move the clean wad (or pad) lightly across the surface of the screen (one time only). NOTE : We recommend to frequently clean the screen to remove finger ____ marks or dust.

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Page 702 Feb 01/10

5. Close-up ________ Subtask 34-22-25-942-050 A. Make sure that the work area is clean and clear of tool(s) and other items.

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Page 703 Feb 01/10

ILS - DESCRIPTION AND OPERATION _______________________________ 1. General _______ R

**ON A/C 001-004, The function of the Instrument Landing System (ILS) is to provide the crew and airborne system users with lateral (LOC) and vertical (G/S) deviation signals, with respect to the approach ILS radio beam transmitted by a ground station. The localizer operates in a frequency band which ranges from 108.10 MHz to 111.95 MHz. The glide operates in a frequency band which ranges from 329.15 MHz to 335.00 MHz.

R

**ON A/C 051-060,

R R R R R R R R

The function of the instrument landing system is to measure deviations between aircraft flight path and - glide slope - runway alignment axis (localizer). The localizer operates in a frequency band which ranges from 108 MHz to 111.95 MHz. The glide operates in a frequency band which ranges from 328.6 MHz to 335.4 MHz.

R

**ON A/C 001-004, 051-060,

R

2. Component __________________ Location (Ref. Fig. 001) ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2RT1 RECEIVER-ILS, 1 95VU 121 811 34-36-31 2RT2 RECEIVER-ILS, 2 96VU 122 811 34-36-31 3RT ANTENNA-LOCALIZER 1/2 110 110AL 34-36-11 4RT ANTENNA-GLIDE/SLOPE 1/2 110 110AL 34-36-18

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R R

ILS - Component Location Figure 001

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3. __________________ System Description A. Principle The ILS principle is to receive and demodulate the localizer and glide slope signals transmitted by a ground station. This ILS ground station is composed of: - a localizer transmitter located at the departure end of the runway - a glide slope transmitter located at one side of the front-course of the runway. Each signal is radiated to produce two intersecting lobes, one above the other (glide slope), or side by side (localizer). Each lobe is modulated at predominantly 90 or 150 Hz in each case, so that an aircraft flying down the centerline bisecting the two partially-overlapping lobes would receive an AM-modulated signal with equal levels of each tone. These lines of equal modulation define the localizer course, which bisects the runway centerline, and the G/S course, which provides a glide path at an angle of 2.5 deg. to 3 deg. (Ref. Fig. 002) A station identification is also transmitted on the localizer signal, through a Morse-coded, AM-modulated, 1020 Hz tone. Receive operations are initiated by the selection of a localizer frequency by the frequency control device. Each of the 40 selectable localizer frequencies is paired with one of the 40 glide slope frequencies and the selection of the localizer channel automatically selects the paired glide slope one. In approach mode, the correct ILS frequency being selected, the localizer and glide slope signals are received, filtered, amplified and demodulated by the ILS receiver. With regard to the modulation comparison, it then provides the crew and system users with lateral and vertical deviations.

R

B. System Architecture R

**ON A/C 001-004,

R R

(Ref. Fig. 003) **ON A/C 051-060,

R

(Ref. Fig. 003A)

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ILS Principle Figure 002

R

  R EFF : 001-004, 051-060,  34-36-00 Page 4   Config-1 May 01/05  CES

 

ILS - Block Diagram Figure 003

R

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R R

ILS - Block Diagram Figure 003A

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R

**ON A/C 001-004, 051-060, The ILS comprises two independent ILS receivers 2RT1 and 2RT2 linked to a common localizer antenna 3RT and a glide slope antenna 4RT. The components given after can control the ILS system: (Ref. Fig. 004) - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2) and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection in normal mode of operation, - the Radio Management Panel (RMP) 1RG1 (1RG2) for frequency/course selection in back-up mode, - the MCDU and the Centralized Fault Display Interface Unit (CFDIU) 1TW for test purposes. The Morse-coded audio identification signals are sent to the Audio Management Unit (AMU) 1RN. These signals can be heard in the boomset and on loudspeaker according to the crew selection performed on the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2). The EFIS display units show the ILS data: - the CAPT Primary Flight Display (PFD) and the F/O Navigation Display (ND) show the deviations from the ILS1, - the F/O PFD and the CAPT ND show the deviations from the ILS2. The MCDU(s) shows the maintenance data.

R

C. Utilization Technical Data (1) Data display (Ref. Fig. 005)

R

(a) On the PFDs On the right and below the attitude sphere, the deviation indications come into view in approach. These are : - the vertical deviation scale, - the lateral deviation scale, - the related aircraft deviation symbols. If you select an ILS approach, the scales and symbols give GLIDE/SLOPE and LOCALIZER deviations. The scales come into view when you push the ILS pushbutton switch on the EFIS control section of the Flight Control Unit (FCU). The deviation symbols come into view when the related G/S and LOC signals from the ILS receiver are valid. If the ILS indications are available with the ILS pushbutton switch pushed they have priority over the deviation information of the R NAV approach. In this mode the data given after are shown (item 5): in the left bottom corner: - ILS frequency (plus ILS identification if available),

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- ILS - DME distance. At the top section of the PFD a Flight Mode Annunciator shows the various armed/active longitudinal and lateral modes: (item 1): the G/S longitudinal modes are shown in the 2nd column (cyan for armed or green for active) (item 2): the LOC longitudinal modes are shown in the 3rd column (cyan for armed or green for active) VERTICAL DEVIATION (item 3) The vertical scale shows a classical glide slope deviation. It is linear with 2 dots on each side. Two dots correspond to plus (or minus) 0.175 ddm (150 microA) deviation. The index shows magenta G/S indication. Until the glide beam is captured, the glide index is not shown (Non Computed Data). When the index is against one stop only one half of it is in view (the outer half index). The glide slope index and the scale flash permanently in case of G/S excessive deviation warning. With a glide fault, the G/S index goes out of view and a red G/S failure warning message is shown in the middle of the scale. (Ref. Fig. 006) LATERAL DEVIATION (item 4) The horizontal scale shows a classical LOC deviation with 2 dots on each side. Two dots correspond to plus (or minus) 0.155 ddm (150 micro A) deviation. The index shows magenta LOC indication. Until the LOC is captured, the LOC index is not shown (Non Computed Data). When the index is against one stop, only one half of it is shown. The LOC index and the scale flash permanently in case of LOC excessive deviation warning. With a localizer fault, the LOC index goes out of view and a red LOC failure warning message is shown in the middle of the scale. (Ref. Fig. 006)

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(b) On NDs in the ROSE ILS mode In the ROSE ILS mode, the ND gives a display which is similar to that of a conventional HSI : a heading dial orientated to the magnetic North turns and gives the actual magnetic heading of the aircraft in relation to the stable yellow lubber line. The ND is always heading up : a yellow aircraft model, at the center of the heading dial is stable and pointed up to the yellow lubber line. Small white triangles are put each 45 deg. on the circumference in relation to the lubber line. They are stable and do not turn with the heading dial. A green diamond-shaped symbol moves around the heading dial and gives the actual track of the aircraft.

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ILS - Control and Indicating Figure 004

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ILS - Data Display Figure 005

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ILS - Warning Display Figure 006

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The ND shows the indications given after, when available, in its right top corner (item 8): - the side of the displayed ILS receiver, - the frequency, - the course, - the identification. The ND shows the ILS APP message in its center top section (item 7) when the pilot has selected the ILS approach on the MCDU. LATERAL DEVIATION (item 6) a dagger-shaped pointer points to the selected ILS course. Its center part is the lateral deviation bar, which can move on a scale which is perpendicular to the pointer and has 2 dots on each side. The position of the bar on the scale gives the localizer deviation. The extreme dots correspond to plus or minus 0.155 ddm (plus or minus 150 micro A). With LOC fault a red LOC warning message comes into view in the middle of the LOC scale and the LOC deviation bar goes out of view. VERTICAL DEVIATION (item 9) a magenta lozenge gives the glide slope deviation on a vertical scale at the right of the heading dial if the aircraft is within the condition of reception of the ILS glide slope signal. The extreme dots of the vertical scale correspond to plus or minus 0.175 ddm (plus or minus 150 micro A). With G/S fault, a red G/S warning message comes into view at the top of the scale and the index goes out of view. (c) On ND in ARC and ROSE NAV modes When you push the ILS pushbutton switch in ARC or ROSE NAV mode, the ND shows the symbols given after: - a magenta dagger-shaped pointer which points to the selected QFU, - an arrow which indicates the lateral deviation of the aircraft related to the localizer axis. (2) Audio control The ILS receiver applies its audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loudspeakers. The Audio Management Unit (AMU) controls the audio level through the Audio Control Panel (ACP). On the ACP, the pilot must push the ILS pushbutton switch and adjust the related potentiometer to the correct audio level. With ILS/DME collocated stations, the DME identification Morse code can be listened in sequence with the ILS audio signal when you push the ILS pushbutton switch on the ACP and the ILS pushbutton switch on the FCU.

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D. Warnings (Ref. Fig. 006) The warnings related to the ILS are : - local warning on the instruments that use the ILS information - MASTER CAUT lights on CAPT and F/O glareshield panels - aural warning : single chime (SC) - warning message shown on the upper display unit of the ECAM system.

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4. ____________ Power Supply R

**ON A/C 001-004,

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(Ref. Fig. 003) **ON A/C 051-060,

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(Ref. Fig. 003A) **ON A/C 001-004, 051-060, Energization - 115VAC ESS - 115VAC BUS The system

of each system is through 115VAC 400 Hz buses : BUS 401XP via circuit breaker 1RT1 for system 1 2 204XP via circuit breaker 1RT2 for system 2 is supplied through these circuit breakers:

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/ILS/1 1RT1 G12 121VU COM NAV/ILS/2 1RT2 K09 5. Interface _________ R

**ON A/C 001-004, A. Receiver (1) External description (Ref. Fig. 007) The face of the receiver is fitted with a handle, two attaching parts, two momentary pushbutton switches and a front panel Liquid Crystal Display (LCD).

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ILS Receiver Figure 007

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The LCD is used as a fault display and as an operator interface during certain modes. The front panel display also provides user interfaces for test and troubleshooting. The front panel contains two momentary pushbutton switches for interfacing with the LCD pages. The back is equipped with one ARINC 600 size one connector, which includes three plugs: - Top Plug (TP): connection with the automatic test circuits - Middle Plug (MP): service interconnection - Bottom Plug (BP): connection with the power supply circuit, and the LOC and G/S coaxial interconnections. R

**ON A/C 051-060,

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A. Receiver

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(1) External description (Ref. Fig. 007A) The face of the receiver is fitted with a handle, two attaching parts, a TEST pushbutton switch and two LEDs. The LRU STATUS LED has two colors (red/green). The name, color and function of the two LEDs are as follows: - LRU STATUS (red) indicates that an internal fault is detected during the front panel self-test sequence - LRU STATUS (green) indicates that no internal fault is detected during the front panel self-test sequence - CONTROL FAIL (red) indicates that no control input is available during the test sequence. The back is equipped with one ARINC 600 size one connector, which includes three plugs: - Top Plug (TP): connection with the automatic test circuits - Middle Plug (MP): service interconnection - Bottom Plug (BP): connection with the power supply circuit, and the LOC and G/S coaxial interconnections. **ON A/C 001-004, (2) Internal description (Ref. Fig. 008) The ILS receiver includes: - an RF module, - a main processor board, - a monitor processor board, - a power supply assembly, - a rear interconnect module,

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ILS Receiver Figure 007A

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ILS Receiver - Block Diagram Figure 008

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- a front panel display module, - a memory card module. (a) RF module This module converts the RF signals received by the glide slope and localizer antennas into analog signals for processing by the Digital Signal Processor (DSP). The module consists of two RF sections, one for the UHF glide slope signals and one for the VHF localizer signals. The primary difference between the two sections is in the front end circuitry due to the frequencies involved. BITE circuitry is included to both test and continuously monitor various stages of each receiver. 1 _

Localizer receiver unit The receiver frequency and gain are controlled by the DSP section of the main processor board. The antenna input is coupled to the mixer through the preselector, which is tuned by the Local Oscillator (LO) input supplied by the frequency synthesizer. The frequency synthesizer is tuned by the DSP. The preselector, in conjunction with a balanced mixer, provides rejection of undesired signals and immunity to cross-modulation and inter-modulation effects. The localizer synthesizer controls the localizer VCO frequency ranging from 89.9 to 99.85 MHz. The IF frequency for the localizer is 18.1 MHz. The output of the mixer is filtered by a highly selective 21.4 MHz crystal filter. The amplified signal is then buffered and passed through the detector to provide the composite audio output levels for processing. A carrier-proportional DC voltage is also provided for Automatic Gain Control (AGC). Functional test is accomplished by injecting a test oscillator signal into the receiver and modulating the signal by the BITE. During normal operation, signals from the LOs, the synthesizer and AGC are monitored by the DSP.

2 _

Glide slope receiver unit The glide slope receiver unit receives and detects the modulated glide slope signals, in the frequency range from 329.15 to 335 MHz. Its architecture is similar to the one of the localizer receiver, except that the frequency values are different and that there is no audio identification decoded on the G/S signal.

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(b) Main processor board The main processor board controls the ILS mode of operation, generates the audio and deviation outputs, controls the aircraft interfaces and performs the control and display functions for the front panel. In addition, it also performs the in-line monitoring (BIT) tasks. The board is divided into three major sections: - DSP section, - CPU section, - I/O section. 1 _

DSP section The DSP section processes the analog outputs from the RF module and generates automatic gain control and test signals to the RF module. The localizer and glide slope signals from the RF module are digitized using an A/D converter. The A/D converter is also used to monitor signals from the BITE test points on the RF module and the power supply voltages. The digitized data from the A/D converter is stored in a FIFO which is accessed by the DSP. Within the main DSP, the raw data is formatted and sent to the monitor processor via a serial port prior to the primary processing. The main DSP also sends a time mark to the monitor processor to synchronize the processing of the data sets. 90 Hz and 150 Hz tones are recovered from the digitized localizer and glide slope signals and the deviations are computed based on the depth of modulation of the 90 Hz and 150 Hz tones. Programmable Logic Devices (PLDs) are used by the DSP to generate the control signals for the localizer and glide slope frequency synthesizers. A D/A converter generates the AGC and test control signals for the RF module. A second D/A converter generates the audio outputs. Data is exchanged with the CPU section through a dual-port RAM, providing maximum throughput of both processors.

2 _

CPU section The CPU section processes the data from the DSP section, to provide information to the front panel display and to provide the data and control signals to the I/O section. The data processor (Intel 80486SX) in the CPU section controls all major functions of the ILS receiver. PLDs serve as the microprocessor controller and provide the interfaces to the memory devices (boot routine, program, fault and data), the data recorder/data loader, and the front panel display driver. The data processor also does an independent comparison of the main and monitor DSP deviation computations.

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Data is exchanged with the DSP section through a dual-port RAM. Data is also exchanged with the monitor processor board through a second dual-port RAM. Each processor has a watchdog monitor that monitors expected processor periodic operation. In the absence of such operation, a failure warning is issued. 3 _

I/O section The I/O section consists of ARINC 429 drivers and receivers, discrete I/O logic and an RS-232C test interface. The I/O section provides the interface with other aircraft systems including the Centralized Fault Display Interface Unit (CFDIU), data loader, control panel(s), displays and the Automatic Flight Control System (AFCS). ARINC 429 inputs are processed by a specially designed ARINC 429 Large Scale Integrating (LSI). This LSI also provides the ARINC 429 deviation signals. External buffers are used to satisfy the ARINC 429 characteristics for the transmitters.

(c) Monitor processor board The Monitor processor board provides a redundant dissimilar signal processing path for the localizer and glide slope signals from the main DSP. In order to determine if the main CPU section operates properly, the monitor processor calculates the deviation outputs and compares the results against those being transmitted over the ARINC 429 ILS output ports. If the calculations from the two microprocessors are excessively different, the monitor processor asks the DP processor in the main CPU section to set the deviation words to indicate FAILURE. The monitor processor shuts down the output buses if the SSM of the output words does not indicate failure when required. (d) Power supply Assembly The 115VAC, 400Hz aircraft power is converted by the power supply into the DC operating voltages required by the various modules within the ILS receiver. A self-contained, high efficiency switching power supply is used to minimize power dissipation. Four voltages (+5, +12, -12 and +28V) are supplied and a power-down interrupt provides advanced notice of a power loss, allowing the processors to temporarily retain their status. The power supply provides a transparency time of at least 200 ms to the ILS. (e) Rear interconnect module To prevent High Intensity Radiated Fields (HIRF) from entering via rear connector cables, a HIRF compartment is formed in the rear of the ILS. The signal and power cables are filtered by

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using discrete and distributed filter elements and limiting devices on the rear interconnect module located inside this HIRF compartment. (f) Front panel display module The front panel display contains a low power Liquid Crystal Display (LCD) and display drivers. The LCD is used as a fault display and as an operator interface during certain modes. The display is driven by the CPU section of the main processor module. The front panel display also provides user interfaces for test and troubleshooting, including the push-to-test pushbutton switch and the 9-pin D connector. (g) Memory card module The memory card interface is used to load data into the CPU or record data from the CPU. The memory card module supports either FLASH cards or RAM cards via the front panel Personal Computing Memory Card Interface Adapter (PCMIA) slot. The FLASH card or RAM card is inserted through the front panel. In one mode, data stored on the flash card memory manual is used to update program or data memory in the ILS. In another mode, the flash card functions as a data recorder. (h) Test modes In addition to the approach operating mode, the ILS has two test modes: - the functional test, - the self-test. 1 _

Functional test The ILS can enter the functional test mode only when the FUNCTIONAL TEST INHIBIT signal is inactive, the air/ground discrete is on ground, AND a functional test is initiated via one of the following: - the front panel pushbutton switch, - the CFDIU. Once initiated, the unit immediately starts the functional test. The results of the test are provided on the ILS outputs. Functional testing continues without interruption as long as the ILS remains in functional test mode and above enabling conditions are true. The detection of a malfunction is considered as an ILS failure and annunciated at the end of the test sequence. During functional test, the ARINC 429 output words cycle through the FUNCTIONAL TEST sequence as shown below:

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-------------------------------------------------------------------------| INTERVAL | SSM | DDMs (Ref. NOTE 2) | -------------------------------------------------------------------------| First 3 s. | FAIL | 0 (both LOC and G/S) | |-------------------|--------|-------------------------------------------| | Next 2 s. | NCD | 0 (both LOC and G/S) | |-------------------|--------|-------------------------------------------| | Next 3 s. |Ref. | - 0.0775 (LOC) | | |NOTE 1 | - 0.0875 (G/S) | |-------------------|--------|-------------------------------------------| | Next 2 s. |Ref. | + 0.0048 DDM/60 ms (LOC) | | |NOTE 1 | + 0.0029 DDM/60 ms (G/S) | |-------------------|--------|-------------------------------------------| | Next 6 s. |Ref. | + 0.0775 (LOC) | | |NOTE 1 | + 0.0875 (G/S) | |------------------------------------------------------------------------| | NOTE 1 : The SSM is set to TEST if no faults are detected | | | | NOTE 2 : The deviations shown are loaded directly into the output | | words. These are not the results of the receiver injected | | test signals. | -------------------------------------------------------------------------The following tests are performed when the functional test is requested: a _

Both IF filters (LOC and G/S) are tested for bandpass frequency response.

b _

A modulated RF test signal is generated to produce a Localizer test deviation of 0.1 DDM. This test deviation is checked for accuracy of 1 DDM plus or minus 0.006 DDM. Failure of this test results in a LOC receiver failure annunciation.

c _

A modulated RF test signal is generated to produce a Glide Slope test deviation of 0.2 DDM. This test deviation is checked for accuracy of 2 DDM plus or minus 0.012 DDM. Failure of this test results in a G/S receiver failure annunciation.

d _

The AGC voltages of the LOC and G/S receivers are checked for acceptable range.

e _

Both synthesizers (LOC and G/S) are tested for lock/unlock conditions.

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f _ 2 _

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Both anti-aliasing filters (LOC and G/S) are tested for frequency response.

Self-test The ILS receiver has the capability to perform a signal injection test on both the localizer and glide slope every 30 seconds. The test is executed if any of the following conditions are met: - the ILS tuning frequency indicates Cruise mode but not while performing functional test, - the ILS is in Normal mode but not while performing functional test and both the localizer deviation indicates invalid as determined by the localizer signal analysis, - the self-test is inhibited when the TUNE/FUNC TEST INHIBIT discrete is asserted. The following actions are taken in self-test: - the deviations of both receivers are frozen to their last value for the duration of the test, - a modulated RF test signal is generated to produce a Localizer test deviation of 0.1 DDM. This test deviation is checked for accuracy of .1 DDM plus or minus 0.006 DDM. Failure of this test results in a LOC receiver failure annunciation, - a modulated RF test signal is generated to produce a Glide Slope test deviation of 0.2 DDM. This test deviation is checked for accuracy of .2 DDM plus or minus 0.012 DDM. Failure of this test results in a G/S receiver failure annunciation, - the AGC voltages of the LOC and G/S receivers are checked for acceptacle range, - both synthesizers (LOC and G/S) are tested for lock/unlock conditions, - both anti-aliasing filters (LOC and G/S) are tested for frequency response. Localizer and Glide Slope failures detected during self-test remain latched until the same test passes on a subsequent self-test execution.

(3) Not Applicable

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**ON A/C 051-060,

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(2) Internal description (Ref. Fig. 008A) The ILS receiver consists of five units: - the localizer receiver unit - the glide slope receiver unit - the I/O processor unit - the power supply unit - the BITE processor unit.

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(3) Operating principle

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(a) Localizer receiver unit The localizer receiver unit receives and detects the localizer modulated signals in the frequency range from 108.1 to 111.95 MHz. In approach mode, the RF signal received through the dedicated antenna is the filtered by a low loss broadband filter, and then mixed with the output of the localizer synthesizer. This localizer synthesizer receives tuning information from the I/O processor, and provides an injection signal which is 20.05 MHz below the selected frequency. The 20.05 MHz Intermediate Frequency (IF) tuned signal obtained at the output of the mixer is applied to a 20.05 MHz crystal filter which provides the selectivity for the receiver. It is then amplified and mixed with a second injection frequency 20.505 MHz to produce a 455 kHz signal. After 2 stages of amplification, this second IF signal is applied to an envelope detector. The output of the envelope detector, which only contains the baseband components of the second IF, is fed to: - the Automatic Gain Control (AGC) amplifier/filter, which controls the gain of the different IF amplifiers according to the amplitude of the IF output - the Input/Output (I/O) processor unit for audio identification decoding and localizer deviations computation.

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(b) Glide slope receiver unit The glide slope receiver unit receives and detects the modulated glide slope signals, in the frequency range from 329.15 to 335 MHz. Its architecture is similar to the one of the localizer receiver, except that the frequency values are different, and that there is no audio identification encoded on the G/S signal.

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ILS Receiver - Block Diagram Figure 008A

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Additionally, the glide slope receiver unit includes a localizer and glide slope functional test oscillator/modulator (90 and 150 Hz tones) which generates three functional test conditions: - centered signal condition - down/right signal condition - up/left signal condition. During the down/right and up/left sequence, a 1020 Hz signal is added to the localizer 90 and 150 Hz tones. The functional test oscillators are kept off except during functional tests to prevent possible interference with normal operation.

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(c) I/O processor unit The I/O processor unit comprises three separate processors: - the primary Digital Signal Processor (DSP) - the monitor Digital Signal Processor (DSP) - the system processor.

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1 _

DSPs The DSPs compute the deviation data from the analog outputs of the localizer and the glide slope receiver units. Each DSP, identically but separately: - receives, filters and digitizes data from the glide slope and localizer receiver units - processes these data and elaborates localizer and glide slope deviations (DDM) - determines the DC level of the glide slope and localizer detectors - sets or resets bits in the status byte for low glide slope/localizer signal levels, glide slope/localizer-detector abnormal DC levels or no transmission on the ARINC bus - sets the Sign Status Matrices (SSM), based on the status byte settings - sends deviation and status data to the system processor - individually compares the glide slope and localizer SSMs transmitted by the ARINC Universal Asynchronous Receiver Transmitter (UART) to its own computed SSMs, and sets a bit in the corresponding status byte if the SSM of ARINC transmission is less restrictive than the computed one. If both transmitted and computed SSMs are normal, then the emitted deviation data are compared to the DSP deviations. - stops the transmission of the ARINC bus if the SSM comparison is incorrect or if the control of the SSM is lost, or if the transmitted deviation data are outside a pre-determined limit.

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2 _

System processor The system processor functions as the ILS input/output data handler. The system processor: - receives and processes data from the ARINC UART (it determines the validity of input tuning frequency, and transmits valid commands to the localizer and glide slope synthesizers) - monitors and processes the discrete inputs - compares the localizer and glide slope data received from the primary DSP to the data received from the monitor DSP. If the result of the comparison is outside pre-determined limits, the data are declared failed - transmits data to the primary ARINC UART - monitors the data words sent on the ARINC bus. - determines the system power supply status - provides fault data to the BITE processor - conveys data received from the BITE processor for transmission onto the ARINC 429 output bus.

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(d) BITE processor The BITE processor: - receives and decodes control and data words from the Centralized Fault Display Interface Unit (CFDIU) and transfers interactive or normal mode data to the system processor - processes data received from the system processor, for storage in the non-volatile fault memory. - decodes Morse code station identification and transfers the ident word to the system processor.

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(e) Power supply unit The power supply unit converts the aircraft 115VAC-400 Hz input into the +5VDC, +12VDC, -12VDC and -5VDC necessary to the ILS receiver operation.

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(f) Test modes In addition to the approach operating mode, the ILS has three test modes: - the functional test - the receiver face test - the power-on test.

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Functional test It is initiated on request from the MCDU, under the following conditions: - tune/test inhibit discrete not active - A/C on ground.

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Upon recognition of a valid functional test request, the system processor initiates the following sequence: -------------------------------------------------------------------------| DURATION | PFD and ND | -------------------------------------------------------------------------|Approx. 3 s. | LOC and G/S failure messages. | | | 173 and 174 SSM = FW | | | | |Approx. 2 s. | LOC index/deviation bar: Centered | | | G/S index: Centered | | | 173 and 174 SSM = NCD | | | | |Approx. 3 s. | Transition from centered to Left and | | | centered to upwards | | | 173 and 174 SSM = FT | | | | |Approx. 2 s. | LOC index/deviation bar: 1 dot to the Left| | | G/S index: 1 dot upwards | | | 173 and 174 SSM = FT | | | | |Approx. 2 s. | Transition from Left to right and up to | | | down | | | 173 and 174 SSM = FT | | | | |Approx. 4 s. | LOC index/deviation bar: 1 dot to the | |(total duration: | Right | |16 s) | G/S index: 1 dot downwards | | | 173 and 174 SSM = FT | | | | --------------------------------------------------------------------------

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LOC and G/S deviation data computed by the primary and monitor DSPs are checked by the system processor against stored values for accuracy. If an error is detected, the SSM of the appropriate deviation word is set to NCD or FW, depending on the type of error until another test sequence shows that the deviation data have passed the test. If no error is detected, the deviation words SSMs follow the sequence given in the table above.

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2 _

Receiver face test The receiver face test request is treated as the MCDU request except that the on-ground condition is not taken into account. The sequence is identical to the functional test sequence, with the receiver face LEDs being additionally controlled to reflect the status of the unit.

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3 _

Power-on test The power-on test request is initiated each time the ILS is powered off for longer than the 200 ms play through time and back on again. The power-on test is treated just as the functional test described in para. 1_ above, except that the SSMs of the LOC and G/S remain set to No Computed Data (NCD) for the entire 16-second test sequence. If a fault condition is detected during power-on test, the SSM of the LOC and/or G/S are set to FW until the detected condition is cleared. Additionally, during this power-on functional test, the ability of the DSPs and I/O to identify faulty ARINC output data and shutdown the bus, is tested, and the RAM and ROM tests are performed.

**ON A/C 001-004,

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(4) ILS monitoring The ILS monitoring is based on the on-line monitoring performed during normal unit operation, and on test modes which provide a check of all deviation-affecting circuitry. (a) On-line monitoring 1 _

Redundant computations paths The monitor processor provides a secondary processing path that is dissimilar and independent of the primary path. Every 1ms the monitor processor processes the same sample set of digitized IF data as the main processor DSP (main DSP) but performs an independent validation and deviation computations. Deviation computation implementations in the monitor processor and the main DSP are dissimilar because of: - different programming languages used to code the algorithms in the monitor processor and the main DSP, - different canonical forms of the digital filters used in the implementation of the two algorithms.

2 _

Deviation validation The computed deviations are checked for validity through reasonableness tests performed on the modulating tones. These tests are performed independently on the LOC and G/S signals. The SSM of the respective output word is set to No Computed Data (NCD) based on both the monitor and the main DSP validity determination, within 500 ms, under the following conditions:

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- the Localizer signal depth of modulation of the sum of the 90 Hz and 150 Hz tones is less than 70 per cent of its nominal value, - the Glide Slope signal depth of modulation of the sum of the 90 Hz and 150 Hz tones is less than 70 per cent of its nominal value, the glide slope deviation is flagged, - if either of the two RF signals is not detected on the selected channel while there is no internal failure, - either the 90 Hz component or the 150 Hz component of the modulating signal is absent from the detected output and the modulation depth of the remaining compound retains its nominal value. 3 _

Deviations cross-comparison The computed deviations in each path are cross-checked independently with the deviations from the alternate path every 50 ms. The DP receives the deviations computed by the monitor DSP through a dual-port RAM and compares them to the most recent deviation outputs transmitted on the ARINC 429 bus. A comparison failure is deemed to have occurred if both deviations disagree by more than: - plus or minus 0.0065 DDM for Localizer deviations in the range of -0.310 to +0.310 DDM. plus or minus 0.0325 DDM for Localizer deviations less than -0.310 DDM or greater than +0.310 DDM. - plus or minus 0.009 DDM for Glide Slope deviations in the range of -0.350 to +0.350 DDM. plus or minus 0.045 DDM for Localizer deviations less than -0.350 DDM or greater than +0.350 DDM. On the monitor processor side, Localizer and Glide labels are sampled from output buses 1 and 2 and then compared by the monitor to its own (saved) computed deviations based on the same criteria. The monitor processor and the DP treat the failures specific to the localizer deviation independent of the failures specific to the glide slope deviation. Failure persistence counters are implemented such that intermittent erroneous outputs with a rate of 4 Hz or higher are detected and flagged (i.e. the SSM set to FW) within 500 ms. Each failure persistent counter is implemented such that any combination of errors leading to at least seven miscomparisons out of 10 consecutive samples are flagged as failures within 500 ms. Alternating errors (one good and one bad) are flagged as failures within 1 s.

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4 _

ARINC 429 bus shutdown The monitor processor attempts to shut down buses 1 and 2 after sending a deviation comparison failure indication to the DP for a period of 500 ms, when the SSM of the failing deviation output still indicates Normal and the failure condition is still present. If the unit is in the interrupted mode of operation, the buses are shutdown. Once the output buses are shutdown, the monitor restores both output buses for two output cycles (less than 150 ms but greater than 100 ms) every two seconds to monitor their outputs. The monitor does not restore the activity on the bus until the integrity of the unit is reacquired. The ability of the monitor processor to shutdown the bus is verified upon power up.

5 _

BIT (Built-In Test) In addition to the redundant path computations and deviations cross-comparison, a number of hardware components and software processes are monitored by the BIT manager program resident in the Data Processor (DP). The main DSP collects data from sensors in the RF module. This status data along with power supply data, output status data, program activity status data, and status data collected from the monitor processor (MON) are fed to the BIT manager. The BIT manager filters the data and initiates failure warnings when limits are exceeded. The BIT manager is initiated eight times a second. High-rate faults are monitored eight times a second. Low-rate faults are monitored once a second. Upon activation, faults are reviewed if they have alarmed. Alarms are controlled by the fault invocation rate which is set to either 125 (High-rate) or 1000 (Low-rate) ms. Failures are transmitted on the ARINC 429 buses at an average exposure time of 3 seconds. Failures that have an impact on the integrity of the output are reported faster, nominally within 500 ms, on either or both labels 173 and 174 depending on the nature of the failure.

6 _

ARINC 429 input The selected input ARINC bus is monitored for valid labels, SDI, word rate and odd parity: - words with invalid label or SDI are ignored, - concerning frequency data, if the word rate drops below 3 words per second, or if the data do not contain a valid ILS frequency (which means SSM to Normal Operation (NO) and existing ILS channel), the output frequency word is set to NCD. In fact, unless two consecutive valid input frequency words are received, the ILS holds its last valid frequency, and sends it out at 5 words per second with an NCD coded

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SSM. As described above, the SSM of the input frequency word is monitored for NCD condition. In this particular case, the SSMs of the transmitted deviation output words are forced to NCD. In all cases, if tune/test inhibit is asserted, frequency data on the ARINC input is ignored. (b) Test mode monitoring - the self-test modes provide a check of all deviation-affecting circuitry: as described in Para. (2) internally generated RF carriers with known deviation levels are applied to the receiver inputs. The ILS must then supply an output word with the expected value of deviation. In this way, a satisfactory self-test provides confidence that the ILS is providing correct deviation from modulated RF signals. - additionally, during power-up self test, the ability of the monitor DSP to shut down the buses is tested. - faults detected during test mode set the SSM of the appropriate deviation word according to the test result. Once the fault is cleared and another test is performed and passed, then normal operation is resumed. R

(5) Digital outputs This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives : - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds - CODE : BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system.

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 017 |RUNWAY | FROM 0 TO |Deg.| | 15 |300 |BCD | | | | |HEADING | 359.9 | | | | | | | | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 033 |ILS | FROM 108.10|MHZ | | 15 |200 |BCD | | | | |FREQUENCY | TO 111.95 | | | | | | | | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 105 |RUNWAY | FROM 0 TO |Deg.| | 11 |300 |BNR | | | | |HEADING | 359.9 | | | | | | | | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 173 |LOCALIZER | + or |DDM | 29 | 12 | 50 |BNR | | | | |DEVIATION | - 0.155 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 174 |GLIDE | + or |DDM | 29 | 12 | 50 |BNR | | | | |SLOPE | 0.175 | | | | | | | | | |DEVIATION | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 263 |ILS GROUND| | | | 14 |150 |HYB | | | | |STATION | | | | | | | | | | |IDENT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 264 |ILS GROUND| | | | 14 |150 |HYB | | | | |STATION | | | | | | | | | | |IDENT | | | | | | | | | ------------------------------------------------------------------------------NOTE : Station identification consists of 4 characters max. : label ____ 263 provides the first two characters (bits 11 to 17 for the first character and bits 19 and 25 for the second one) and label 264 gives the last two characters (bits 11 to 17 for the third character and bits 19 to 25 for the fourth one).

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**ON A/C 051-060,

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(4) ILS monitoring The ILS monitoring is based on the on-line monitoring performed during normal unit operation, and on test modes which provide a check of all deviation-affecting circuitry.

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(a) On-line monitoring

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1 _

Localizer and glide slope receivers monitoring Receivers monitoring consists in having the DSPs determine the quality of each receiver envelope-detector output-signal. During on-line operation, an SSM set to NCD is issued by the DSPs in 0.5 s if any of the following conditions on either LOC or G/S detector output is met: - detector dc voltage level out of tolerance - lack of a signal carrier - improper modulation level (a signal carrier being present) - RF signal modulated with standard deflection not producing a deviation of at least 50 per cent of standard deflection.

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2 _

Localizer and glide slope synthesizers monitoring Both the LOC and G/S frequency synthesizers are monitored separately for lock condition. An unlocked condition causes FW to be sent on the deviation output of the affected receiver.

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3 _

Monitoring of deviation calculations - the detector outputs of the LOC and G/S receivers are split into separate but identical channels. The deviation calculations are then performed identically by the two distinct DSPs, each channel being independent and self-supporting with separate clocks and support logic - the I/O processor then compares the deviation calculations from the primary DSP against those from the monitor DSP, and sets the SSM to NCD, FW or NO, depending on the comparison results, before sending them to the output UART.

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4 _

ARINC output monitoring The ARINC 429 output data are monitored by: - the DSPs: If no correct deviation data are fed back, the DSP (as detailed in para. (3)(c)) shuts the output bus off. - the system processor, via a monitor UART: Any input to the UART that does not have proper parity is discarded.

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Thus, any altered word is rejected and not seen by the system processor which checks the output every 10 ms. If no LOC or G/S deviation word is received within 400 ms, the output bus is shut off also by the system processor. Whenever the bus is shut off by the DSPs only, it can be recovered clearing the fault-inducing condition. If the bus is cut off by the system processor, it remains cut off until power is recycled to the ILS. Then the system processor restarts at the beginning of its program, which includes a power-on test. If the fault has not been cleared, the bus is shut off again.

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5 _

ARINC 429 input The selected input ARINC bus is monitored for valid labels, SDI, word rate and odd parity: - words with invalid label or SDI are ignored - concerning frequency data, if the word is received for a period greater than 450 ms or if the data do not contain a valid ILS frequency (which means SSM to Normal Operation (NO) and existing ILS channel), the output frequency word is set to NCD. In fact, unless two consecutive valid input frequency words are received, the ILS holds its last valid frequency, and sends it out at 5 words per second with an SSM coded NCD. As described above, the SSM of the input frequency word is monitored for NCD condition. In this particular case, the SSMs of the transmitted deviation output words are forced to NCD. In all cases, if tune/test inhibit is asserted, frequency data on the ARINC input is ignored, and the output frequency word will contain the last valid tune frequency.

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6 _

Tune/test inhibit discrete input The system processor monitors the two Tune/Test Inhibit (TTI) inputs and if these inputs are not of opposite states, a failure warning flag is issued.

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7 _

Power supply All power supply voltages are monitored continuously by the system processor for operation within predefined windows. If these window limits are exceeded, LOC and G/S deviation outputs are flagged to NCD or FW, depending on the voltages values, and also of the debounce times.

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(b) Test mode monitoring - The functional test modes provide a check of all deviation-affecting circuitry: as described in para. (3), internally generated RF carriers with known deviation levels are applied to the receiver inputs. The ILS must then supply an output word with the expected value of deviation. In this way, a satisfactory functional test provides confidence that the ILS is providing correct deviation from modulated RF signals. - Power-on test (Ref. Para. (3)(f)3_) - Faults detected during test mode set the SSM of the appropriate deviation word according to the test result. Once the fault is cleared, normal operation is resumed. The three types of test modes are defined in para. (3)(f). They perform essentially the same tests but the way they are initiated and their duration are different.

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(c) No Computed Data (NCD) indication for localizer (label 173) and glide slope (label 174) when: - LOC or G/S last value from DSPs was NCD (Ref. Para. (4)(a)1_) - deviation comparison between the two DSPs is more than 0.0065 DDM (LOC) and 0.009 DDM (G/S), with SSM at Normal Operation for more than 450 ms. - the system processor receives only 1 or 2 valid LOC and G/S deviation data messages from DSPs within 50 ms (refresh rate of LOC and G/S parameter = 12 ms) - any of the input voltages to the A/D converter is out of its valid range for two consecutive A/D readings (2 x 280 ms) (power supply and DC level to LOC and G/S detectors) - functional test is performed (Ref. Para. (3)(f)1_) - the output frequency tune word is at NCD (Ref. Para. (4)(a)5_ for the associated input conditions) - LOC and G/S synthesizers are lost while the unit is not performing a functional test (detection of unlock condition).

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(d) Failure Warning (FW) indication for localizer (label 173) and glide slope (label 174) when: - deviation comparison between the two DSPs is more than 0.013 DDM (LOC) and 0.07032 DDM (G/S), with SSM at Normal Operation for more than 450 ms for the LOC and 1s for the G/S. - the system processor receives only one valid LOC and G/S deviation data message from one of the two DSPs within 50 ms (refresh rate of LOC and G/S parameter =12ms). - LOC or G/S synthesizer is lost during a functional test - any of the input voltages to the A/D converter is out of its valid range for four consecutive A/D readings (4 x 280 ms) (continuous monitoring of power supply and check of DC level to LOC and G/S detectors during functional test)

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- unscheduled functional test - functional test is performed (Ref. Para. (3)(f)1_) - the tune/test inhibit input discretes are not of opposite states (350 ms) - cold start initialization test fails (ROM, RAM, UART loop back).

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(5) Digital outputs This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives : - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds - CODE : BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system.

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 033 |ILS | FROM 108.10|MHZ | | 15 |180 |BCD | | | | |FREQUENCY | TO 111.95 | | | | TO | | | | | | | | | | |300 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 105 |RUNWAY | FROM 0 TO |Deg.| | 11 |180 |BNR | | | | |HEADING | 359.9 | | | | TO | | | | | | | | | | |300 | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 173 |LOCALIZER | + or |DDM | 29 | 12 | 50 |BNR | | | | |DEVIATION | - 0.155 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 174 |GLIDE | + or |DDM | 29 | 12 | 50 |BNR | | | | |SLOPE | 0.175 | | | | | | | | | |DEVIATION | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 263 |ILS GROUND| | | | 14 |200 |HYB | | | | |STATION | | | | | | | | | | |IDENT | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 264 |ILS GROUND| | | | 14 |200 |HYB | | | | |STATION | | | | | | | | | | |IDENT | | | | | | | | | -------------------------------------------------------------------------------

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NOTE : Station identification consists of 4 characters max. : label ____ 263 provides the first two characters (bits 11 to 17 for the first character and bits 19 and 25 for the second one) and label 264 gives the last two characters (bits 11 to 17 for the third character and bits 19 to 25 for the fourth one).

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**ON A/C 001-004, 051-060, B. Antennas (Ref. Fig. 009)

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(1) Localizer antenna The localizer antenna is an airborne antenna used to receive LOC signals in the 108-112 MHz range. It is a folded half-loop type driven by capacitive coupling. The antenna has two independent RF connectors used to feed two items of equipment. Connector separation is provided by a hybrid junction in the antenna. (2) Glide/slope antenna The glide/slope antenna is an airborne antenna used to receive GLIDE signals in the 329-335 MHz range. It is a folded half-loop type driven by capacitive coupling. The antenna has two independent RF connectors used to feed two items of equipment. Connector separation is provided by a hybrid junction in the antenna. 6. _____________________ Component Description R

**ON A/C 001-004,

R R

(Ref. Fig. 003) **ON A/C 051-060,

R R

(Ref. Fig. 003A) **ON A/C 001-004, 051-060, A. Control - each ILS receiver is connected to one Radio Management Panel (RMP). The ILS receiver 1 is connected to the RMP1 (the ILS receiver 2 to the RMP2). The ILS receiver 1 receives management bus from the FMGC1 through the RMP1 (the ILS receiver 2 from the FMGC2 through the RMP2) - in normal operation, the FMGC1(2) tunes the ILS 1(2) receiver either automatically or manually by means of the MCDU1(2). In this case the RMP1(2) operates as a relay which sends the frequency information from the FMGC1(2) to the receiver 1(2).

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ILS Antennas Figure 009

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- by a second port, the ILS receiver 1(2) receives a second management bus (ILS1 FREQ + RWY HDG1) directly from the FMGC2(1). The receiver selects one of the two port functions by a discrete signal (RMP1 NAV DISC) which is received from the FMGC1(2) through the RMP1(2). With fault of one FMGC, the second FMGC can control the two ILS receivers, one directly, the other through its RMP. With fault of the RMP1(2) or two RMPs, the concerned RMP is transparent to data and discrete from FMGC. In manual operation (at any time, or with fault of two FMGCs) the RMP1 can control the ILS receiver 1 after ON NAV mode selection. Same possibility for the RMP2 (ILS receiver 2). (Ref. Fig. 010) In this mode the RMP1 can control the ILS2 through the RMP2 after ON NAV mode selection on the RMP2. Same possibility for ILS2 through RMP1. After any frequency selection it is always necessary to select the associated course. - In LAND mode below 700 ft., the FMGC sends a ground signal on the TUNE TEST INHIBIT discrete to the ILS receiver. In this case, whether the frequency is sent by the FMGC or by the RMP, the ILS receiver does not take into account any frequency change.

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B. Reconfiguration Switching In normal utilization, the ILS1 data are shown on the CAPT PFD and the F/O ND ; the ILS2 data on the F/O PFD and the CAPT ND. In addition the DMC 1 supplies data to the CAPT PFD and ND ; the DMC 2 to the F/O PFD and ND. With fault of the DMC 1(2), it is possible to switch over to the DMC 3 with the EIS DMC selector switch. This selector switch is located on panel 8VU on the center pedestal. In this case, the DMC 3 totally replaces the DMC 1(2) through the stage of the output switching relay of the failed DMC. With fault of the PFD, there is an automatic transfer of the PFD image onto the ND. With fault of the ND, you obtain the transfer of the ND image onto the PFD when you push the PFD/ND XFR pushbutton switch on panel 301VU (500VU). When you set the PFD potentiometer to OFF on panel 301VU (500VU), this causes : - deactivation of the PFD - transfer of the PFD image onto the ND. 7. Operation _________

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ILS - Frequency and Course Selection in Emergency Mode Figure 010

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**ON A/C 001-004,

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(Ref. Fig. 011) A. Access to ILS Sub-Menu Functions It is possible to select the maintenance functions of the ILS receiver 1 (2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant ILS on the NAV menu. After these actions, the ILS 1 (2) provides its own menu page and the sub-menu functions can then be chosen by the operator. B. Activation of the Self-Test The self-test can be activated by pushing the TEST pushbutton switch as designed on the front panel LCD, if the test inhibit discrete is not active. A TEST IN PROGRESS message is displayed approximately one second after the TEST pushbutton is pressed. At the end of the self-test, either a TEST COMPLETE, NO FAILURES message screen or a TEST COMPLETE, FAILURES message screen is displayed. The TEST COMPLETE, NO FAILURES screen contains two pushbutton selections (MAINT and RETURN). The TEST COMPLETE, FAILURES screen also contains two pushbutton selections (MAINT and WHY?). For both screens, pressing the left (MAINT) pushbutton initiates the extented maintenance pages of the system for troubleshooting. The right (RETURN) pushbutton associated with the TEST COMPLETE, NO FAILURES screen returns the system to its normal mode screen. The right (WHY?) pushbutton associated with the TEST COMPLETE, FAILURES screen places the system in the display-failures mode where individual system failures (fault memory codes) are displayed, one per page. C. Activation of the Functional Test The functional test can be activated by pushing the line key adjacent to the TEST indication on the ILS maintenance sub-menu, under the following conditions: test inhibit discrete not active and A/C on ground. It is similar to the self-test except that the front panel display screens are not controlled to reflect the status of the unit, which is reported on the MCDU. NOTE : If the test cannot be initiated on ground on the MCDU (which means ____ that a fault affects either the LGCIU, the FMGC or the ILS), a TEST page comes into view on the MCDU. (Ref. Fig. 012, 013)

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ILS - Maintenance Test Procedure Figure 011

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ILS - Maintenance Test Procedure Figure 011A

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ILS Maintenance Test Procedure - Access to Sub-menus 4/5 Figure 012

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ILS Maintenance Test Procedure - Access to Sub-menus 4/5 Figure 012A

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ILS Maintenance Test Procedure - Access to Sub-menus 5/5 Figure 013

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**ON A/C 051-060,

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(Ref. Fig. 011A)

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A. Access to ILS Sub-Menu Functions It is possible to select the maintenance functions of the ILS receiver 1 (2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant ILS on the NAV menu. After these actions, the ILS 1 (2) provides its own menu page and the sub-menu functions can then be chosen by the operator.

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B. Activation of the Receiver Face Test The receiver face test can be activated by pushing the TEST pushbutton switch on the receiver face, if the test inhibit discrete is not active. The sequence below is then generated on the receiver face.

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------------------------------------------------------------------------------| DURATION | Receiver face | |-----------------------------------------------------------------------------| | Approx. 3 s | LRU STATUS LED comes on red | | | CONTROL FAIL LED comes on red | | | | | Approx. 3 s | LRU STATUS LED comes on green | | | CONTROL FAIL LED comes on red | | | | | Approx. 10 s | LRU STATUS LED is off | | | CONTROL FAIL LED is off | -------------------------------------------------------------------------------

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Depending on the outcome of the receiver face test, one of the following results is displayed: ------------------------------------------------------------------------------| DURATION | Receiver face | |-----------------------------------------------------------------------------| | Approx. 30 s | If LRU and Control input pass: | | | LRU STATUS LED comes on green | | | CONTROL FAIL LED is off | |-----------------------|-----------------------------------------------------| | Approx. 30 s | If LRU Fail and Control input pass: | | | LRU STATUS LED comes on red | | | CONTROL FAIL LED is off | |-----------------------|-----------------------------------------------------| | Approx. 30 s | If LRU Pass and Control input Fail: | | | LRU STATUS LED comes on green |

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------------------------------------------------------------------------------| DURATION | Receiver face | |-----------------------------------------------------------------------------| | | CONTROL FAIL LED comes on red | |-----------------------|-----------------------------------------------------| | Approx. 30 s | If LRU Fail and Control input Fail: | | | LRU STATUS LED comes on red | | | CONTROL FAIL LED comes on red | -------------------------------------------------------------------------------

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These LEDs go off automatically after the 30 second duration. Cockpit effects : Ref. Para. 5.A.(3)(f)1_

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C. Activation of the Functional Test The functional test can be activated by pushing the line key adjacent to the TEST indication on the ILS maintenance sub-menu, under the following conditions: test inhibit discrete not active and A/C on ground. It is similar to the receiver face test except that the receiver face LEDs are not controlled to reflect the status of the unit, which is reported on the MCDU.

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NOTE : If the test cannot be initiated on ground on the MCDU (which means ____ that a fault affects either the LGCIU, the FMGC or the ILS), a TEST page comes into view on the MCDU. (Ref. Fig. 012A, 013A) **ON A/C 001-004, 051-060, D. Power-up Tests Initialization and Cockpit Repercussions (1) Conditions of power-up tests initialization - How long the computer must be de-energized: 1 s. - A/C configuration: - whatever the A/C configuration on ground (2) Progress of power-up tests - Duration: 1 s. - Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - MASTER CAUT light on

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ILS Maintenance Test Procedure - Access to Sub-menus 5/5 Figure 013A

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(3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). - Tests pass: - MASTER CAUT light off - ILS information available on ND and PFD if ILS selected on the FCU - Tests failed: - MASTER CAUT light on - ECAM warning NAV ILS 1 or 2 FAULT - ECAM STATUS ILS 1 or 2 INOP * if ILS selected on FCU - CAPT (F/O) PFD ILS 1 (2) and LOC and GLIDE scales in red - CAPT (F/O) ND ILS 1 (2) in red E. CFDIU Interface R

**ON A/C 001-004,

R R

(Ref. Fig. 003) **ON A/C 051-060,

R R

(Ref. Fig. 003A) **ON A/C 001-004, 051-060, (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the ILS. The BITE of the ILS receiver is connected to the CFDIU (Ref. 31-32-00). The BITE: - transmits permanently ILS status and its identification message to the CFDIU - memorizes the failures which occurred during the last 63 flight legs - monitors data inputs from the various peripherals - transmits to the CFDIU the result of the tests performed and selt-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes:

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- the normal mode - the menu mode. (a) Normal mode During the normal mode the BITE monitors cyclically the status of the ILS. It transmits its information to the CFDIU during the concerned flight. In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU by an ARINC 429 message with label 356. (b) Menu mode The menu mode can only be activated on the ground. This mode enables communication between the CFDIU and the ILS BITE by means of the MCDU. R

**ON A/C 001-004,

R R

(Ref. Fig. 011) **ON A/C 051-060,

R R

(Ref. Fig. 011A) **ON A/C 001-004, 051-060, All the information displayed on the MCDU during the BITE Test configuration can be printed by the printer (Ref. 31-35-00). The ILS menu mode is composed of: - LAST LEG REPORT

R

**ON A/C 001-004,

R R

(Ref. Fig. 014) **ON A/C 051-060,

R

(Ref. Fig. 014A)

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ILS Maintenance Test Procedure - Access to Sub-menus 1/5 Figure 014

R

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R R

ILS Maintenance Test Procedure - Access to Sub-menus 1/5 Figure 014A

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R

**ON A/C 001-004, 051-060, This menu contains the fault messages (class 1 and 2, internal and external) detected during the last flight. - PREVIOUS LEGS REPORT

R

**ON A/C 001-004,

R R

(Ref. Fig. 014) **ON A/C 051-060,

R R

(Ref. Fig. 014A) **ON A/C 001-004, 051-060, This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. - LRU IDENTIFICATION

R

**ON A/C 001-004,

R R

(Ref. Fig. 014) **ON A/C 051-060,

R R

(Ref. Fig. 014A) **ON A/C 001-004, 051-060, Allows to display the P/N, the S/N and the SW/N of the equipment. - GND SCANNING

R

**ON A/C 001-004,

R

(Ref. Fig. 015)

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ILS Maintenance Test Procedure - Access to Sub-menus 2/5 Figure 015

R

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R

**ON A/C 051-060,

R R

(Ref. Fig. 015A) **ON A/C 001-004, 051-060, Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. - TROUBLE SHOOTING DATA

R

**ON A/C 001-004,

R R

(Ref. Fig. 015) **ON A/C 051-060,

R R

(Ref. Fig. 015A) **ON A/C 001-004, 051-060, Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. - CLASS 3 FAULTS

R

**ON A/C 001-004,

R R

(Ref. Fig. 016) **ON A/C 051-060,

R R

(Ref. Fig. 016A) **ON A/C 001-004, 051-060, Allows to display the class 3 faults recorded during the last flight leg. - GROUND REPORT.

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R R

ILS Maintenance Test Procedure - Access to Sub-menus 2/5 Figure 015A

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ILS Maintenance Test Procedure - Access to Sub-menus 3/5 Figure 016

R

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R R

ILS Maintenance Test Procedure - Access to Sub-menus 3/5 Figure 016A

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R

**ON A/C 001-004,

R R

(Ref. Fig. 016) **ON A/C 051-060,

R R

(Ref. Fig. 016A) **ON A/C 001-004, 051-060, Allows to present the class 1, 2 or 3 internal failures detected on ground. - TEST.

R

**ON A/C 001-004,

R R

(Ref. Fig. 012) **ON A/C 051-060,

R R

(Ref. Fig. 012A) **ON A/C 001-004,

R R

(Ref. Fig. 013) **ON A/C 051-060,

R R

(Ref. Fig. 013A) **ON A/C 001-004, 051-060, Allows a check of the correct operation of the ILS interrogator. (2) List of components All the components are listed in the Para. 2. Component Location.

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R

**ON A/C 001-004, (3) Reporting function The tables below give the list of internal/external failures: ------------------------------------------------------------------------------| REPORTED INTERNAL FAILURES | |-----------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |----------------------------------------------------------|-------|----------| | ILS i (2RTi) | 1 | 34-36-31 | | ILS LOCALIZER ANTENNA (3RT) | 1 | 34-36-11 | | ILS GLIDE ANTENNA (4RT) | 1 | 34-36-11 | ------------------------------------------------------------------------------------------------------------------------------------------------------------| REPORTED EXTERNAL FAILURES | |-----------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |----------------------------------------------------------|-------|----------| | FMGCi(1CAi)/RMPi(1RGi)/ILSi(2RTi) | 3 | 22-83-34 | | CFDIU(1TW)/ILSi(2RTi) | 3 | 31-32-34 | | DMCi(1WTi)/ILSi(2RTi) | 1 | 31-62-34 | | LGCIUi(5GAi)/FMGCi(1CAi)/ILSi(2RTi) | 3 | 32-31-71 | -------------------------------------------------------------------------------

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R

**ON A/C 051-060,

R R R

(3) Reporting function The tables below give the list of internal/external failures: (i = 1 or 2)

R R R R R R R R R R R R R R R R R

-----------------------------------------------------------------------------| | COCKPIT EFFECT | |CONSEQUENCE| MAINTENANCE | | INTERNAL |------------------|DETECTION| ON THE |------------------------| | FAILURES | LOCAL | ECAM|LVL| | SYSTEM |CLASS|MESSAGE |RECOM- | | | | | | | | |LABEL 356|MENDED | | | | | | | | | |ACTION | -----------------------------------------------------------------------------|ILS |Failure |ILSi | 2 |Permanent|Loss of the| 1 |ILS i |- check | |receiver |warning |fault| |monito- |considered | |(2RTi) | the | |fault: |messages| | |ring |LOC and/or | | | ILSi | | |on the | | | |G/S devia- | | | C/B | | |PFD and | | | |tion infor-| | |- repla-| | |ND | | | |mation. | | | ce the| | |(Ref. | | | | | | | ILS | | |para. | | | | | | | recei-| | |3 C) | | | | | | | ver | ------------------------------------------------------------------------------

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R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R

-----------------------------------------------------------------------------| | COCKPIT EFFECT | |CONSEQUENCE| MAINTENANCE | | EXTERNAL |------------------|DETECTION| ON THE |------------------------| | FAILURES | LOCAL | ECAM|LVL| | SYSTEM |CLASS|MESSAGE |RECOM- | | | | | | | | |LABEL 356|MENDED | | | | | | | | | |ACTION | -----------------------------------------------------------------------------|Incorrect | | | |Permanent|- no conse-| 3 |FMGCi |Check : | |or absent | | | |monito- | quence if| |(1CAi)/ |- FMGC | |input tu- | | | |ring | the tune/| |RMPi |- RMP | |ning data | | | | | test | |(1RGi)/ |- tuning| | | | | | | inhibit | |ILSi | buses | | | | | | | discrete | |(2RTi) | and | | | | | | | is active| | | asso- | | |- no ILS| | | |- if not, | | | ciated| | |informa-| | | | loss of | | | con- | | |tion | | | | the ILS | | | nec- | | |dis| | | | informa- | | | tors | | |played | | | | tion | | | | |----------------------------------------------------------------------------| |CFDIU | | | |Permanent|- no | 3 |CFDIU |Check : | |Fault: | | | |monito- | exchange | |(1TW)/ |- CFDIU | |lack of | | | |ring | with | |ILSi |- Buses | |label 227 | | | | | CFDIU for| |(2RTi) | and | |(mainte- | | | | | ILS BITE | | | asso- | |nance | | | | | informa- | | | ciated| |command | | | | | tion | | | con- | |word) | | | | |- no access| | | nec- | | | | | | | to the | | | tors | | | | | | | Menu mode| | | | | | | | | | of the | | | | | | | | | | ILS re- | | | | | | | | | | ceiver | | | | |----------------------------------------------------------------------------|Functional| | | |During |no conse- | 3 |LGCIUi |Check : | |test acti-| | | |functio- |quence | |(5GAi)/ |- LGCIU | |vation not| | | |nal test | | |FMGCi |- FMGC | |possible | | | |sequence | | |(1CAi)/ | | | | | | |on ground| | |ILSi |- Buses | | | | | | | | |(2RTi) | and | | | | | | | | | | asso- | | | | | | | | | | ciated| | | | | | | | | | con- | | | | | | | | | | nec- | | | | | | | | | | tors | | | | | | | | | | | |-----------------------------------------------------------------------------

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R R R R R R R R R R R

-----------------------------------------------------------------------------| | COCKPIT EFFECT | |CONSEQUENCE| MAINTENANCE | | EXTERNAL |------------------|DETECTION| ON THE |------------------------| | FAILURES | LOCAL | ECAM|LVL| | SYSTEM |CLASS|MESSAGE |RECOM- | | | | | | | | |LABEL 356|MENDED | | | | | | | | | |ACTION | -----------------------------------------------------------------------------|Incorrect |Wrong | | |During |Loss of the| 1 |DMCi |Check : | |test dis- |test | | |test if |ILS display| |(1WTi)/ |- DMC | |play |sequence| | |the ope- |on the con-| |ILSi |- Buses | | |progress| | |rator set|sidered PFD| |(2RTi) | and | | |on the | | |the NO |and ND or | | | asso- | | |displays| | |line key |loss of the| | | ciated| | | | | | |considered | | | con- | | | | | | |ILS RCVR | | | nec- | | | | | | | | | | tors | | | | | | | | | | | |----------------------------------------------------------------------------|

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R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, Post SB

34-1147 For A/C 001-004,051-060, ILS ((MMR)) - DESCRIPTION AND OPERATION _______________________________________

1. _______ General The primary function of the Multi-Mode Receiver (MMR) is to receive and process Instrument Landing System (ILS) and Global Positioning System (GPS) signals. The MMR is a navigation sensor with two internal receivers. A. ILS Receiver The function of the ILS is to provide the crew and airborne system users with lateral (LOC) and vertical (G/S) deviation signals, with respect to the approach ILS radio beam transmitted by a ground station. The localizer operates in a frequency band which ranges from 108.1 MHz to 111.95 MHz and the glide uses the band from 329.15 MHz to 335 MHz as defined by ARINC specification 710. B. GPS Receiver The GPS is a radio aid to worldwide navigation which provides: - the crew with a readout of accurate navigation information, e.g. position, track and speed - the Flight Management and Guidance Computer (FMGC) with position information, after hybridization in the Air Data/Inertial Reference Unit (ADIRU) with inertial parameters, for accurate position fixing. 2. Component __________________ Location (Ref. Fig. 001) The MMR system units are located in the aircraft as follows. ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------40RT1 MMR-1 95VU 120 811 34-36-31 40RT2 MMR-2 96VU 120 811 34-36-31 3RT ANTENNA-LOCALIZER 1/2 110 110AL 34-36-11 4RT ANTENNA-GLIDE/SLOPE 1/2 110 110AL 34-36-18 43RT1 ANTENNA-GPS ACTIVE, 1 210 831 34-36-16 43RT2 ANTENNA-GPS ACTIVE, 2 210 831 34-36-16

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MMR - Component Location Figure 001   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 2 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

3. System __________________ Description (Ref. Fig. 002, 003) The A/C comprises two independent MMRs, 40RT1 and 40RT2, linked to: - a common localizer antenna 3RT - a common glide/slope antenna 4RT - a GPS active antenna 43RT1 (linked to MMR1) - a GPS active antenna 43RT2 (linked to MMR2). A. ILS Operation The equipment given below can control the ILS operation: - the Multipurpose Control and Display Units (MCDU) and the Flight Management and Guidance Computers (FMGC) for frequency/course selection in normal operating mode. - the Radio Management Panels (RMPs) for frequency/course selection in back-up mode. The ILS data are shown on the EFIS displays: - the CAPT Primary Flight Display (PFD) and F/O Navigation Display (ND) show the deviations from the ILS1. - the F/O PFD and CAPT ND show the deviations from the ILS2. The Morse-coded audio identification signals are sent to the Audio Management Unit (AMU). These signals can be heard in the boomset and on the loudspeaker according to the selection by the crew on the Audio Control Panel (ACP). B. GPS Operation (1) Normal operation In normal operation, the GPS 1 data are used by the ADIRUs 1 and 3; the GPS 2 data by the ADIRU 2. NOTE : In order to reduce GPS initialization time, the GPS 1(2) ____ receives data from the ADIRU 1(2). The Inertial Reference (IR) portion of the ADIRU 1(2) provides the FMGC 1(2) with: - pure IR data - pure GPS data (in this case the ADIRU operates as a relay) - hybrid GPIR data. The hybrid GPIR 1(2) data are used by the FMGC 1(2) for position fixing purposes. The pure GPS data are used for display on the MCDU 1 and 2. In case of one GPS only operative GPS In case of ADIRU 1 In case of ADIRU 2

failure, the three ADIRUs automatically select the to compute hybrid GPIR data. failure, the FMGC 1 uses ADIRU 3/GPS 1 data. failure, the FMGC 2 uses ADIRU 3/GPS 2 data.

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MMR - Monitoring and Display Figure 002   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 4 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

MMR - Data Acquisition Figure 003   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 5 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

NOTE : The primary source of the ADIRU 3 being the GPS ____ necessary to select the secondary input port of (GPS 2) by means of the ATT HDG selector switch preserve side 1/side 2 segregation (GPS 1/ADIRU GPS 2/ADIRU 3/FMGC 2 architecture).

1, it is the ADIRU 3 (13FP) to 1/FMGC 1 and

In case of failure of two ADIRUs, the two FMGCs use only the operative ADIRU. This ADIRU receives data from its own side GPS (e.g. ADIRU 1 - GPS 1). C. Maintenance Operation The MMR system provides the Centralized Fault Display Interface Unit (CFDIU) with an interface for onboard testing and fault reporting purposes. The MCDUs show the maintenance data. 4. Power ____________ Supply Each MMR system is energized through 115VAC busbars as follows: - 401XP for system 1 - 204XP for system 2. The system is supplied through these circuit breakers: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/MMR/1 42RT1 G12 R

**ON A/C 062-099, 106-149, 151-199, 204-238, 301-311, 401-499, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, Post SB

34-1147 For A/C 001-004,051-060,

121VU COM NAV/MMR/2

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R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, 5. Interface _________ A. ILS Interface (1) ILS digital outputs The ILS transmits data in compliance with the low speed ARINC 429 standards. The table below contains all the output parameters in the numerical form. ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 173 | LOCALIZER|+ or - 0.155| DDM| 29 | 12 | 50 | BNR| | | | | DEVIATION| | | | | ms | | | | | | | | | | | | | | | | 174 | GLIDE |+ or - 0.175| DDM| 29 | 12 | 50 |BNR | | | | | SLOPE | | | | | ms | | | | | | DEVIATION| | | | | | | | | | | | | | | | | | | | | 033 | ILS |FROM 108.10 |MHz | | 15 |200 |BCD | | | | | FREQUENCY| TO 111.95 | | | | ms | | | | | | | | | | | | | | | | 017 | RUNWAY | FROM 0 TO |Deg.| | 15 |300 |BCD | | | | | HEADING | 359.9 | | | | ms | | | | | | | | | | | | | | | | 105 | RUNWAY | FROM 0 TO |Deg.| | 11 |300 |BNR | | | | | HEADING | 359.9 | | | | ms | | | | | | | | | | | | | | | | 263 |ILS GROUND| | | | 14 |150 |HYB | | | | | STATION | | | | | ms | | | | | | IDENT | | | | | | | | | | | | | | | | | | | | | 264 |ILS GROUND| | | | 14 |150 |HYB | | | | | STATION | | | | | ms | | | | | | IDENT | | | | | | | | | | | | | | | | | | | | | 271 | MMR | | | | 19 |400 |DISC| | | | | DISCRETE | | | | | ms | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | -------------------------------------------------------------------------------------------------------------------------------------------------------------

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B. GPS Interface (1) GPS digital outputs The GPS has three independently buffered high-speed ARINC 429 digital output buses connected to the three ADIRUs. The table below contains all the output parameters in numerical form. ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | 060 | MEASURE- | Pack | N/A| N/A| | 1s | | | | | MENT STS | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | |+/-268435456| | | | | | | | 061 | PSEUDO | 256 | M | 20 | | 1s |BNR | | | | RANGE | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 062 | PSEUDO | 256 | M | 11 | | 1s |BNR | | | | RANGE | 0.125 | | | | | | | | | FINE | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 063 | RANGE | +/-4096 | M/S| 20 | | 1s |BNR | | | | RATE | 0.0039 | | | | | | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 064 | DELTA | +/-4096 | M | 20 | | 1s |BNR | | | | RANGE | 0.0039 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 065 | SV POS X | +/-67108864| M | 20 | | 1s |BNR | | | | | 64 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 066 | SV POS X | 64 | M | 14 | | 1s |BNR | | | | FINE | 0.0039 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | +/-67108864| | | | | | | | 070 | SV POS Y | 64 | M | 20 | | 1s |BNR | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 071 | SV POS Y | 64 | M | 14 | | 1s |BNR | | | | FINE | 0.0039 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 072 | SV POS Z | +/-67108864| M | 20 | | 1s |BNR | | | | | 64 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 073 | SV POS Z | 64 | M | 14 | | 1s |BNR | | | | FINE | 0.0039 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | UTC MEA- | 10.0 | | | | | | | | 074 | SURE TIME| 9.536743 | S | 20 | | 1s |BNR | | | | | micro sec | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS ALT | +/-131072 | | | | | | | | 076 | (MSL) | 0.125 | Ft | 20 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | 1024 | | | | | | | | 101 | HDOP | 0.031 | N/A| 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | 1024 | | | | | | | | 102 | VDOP | 0.031 | N/A| 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS TRACK| +/-180 | | | | | | | | 103 | ANGLE | 0.0055 | Deg| 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | +/-180 | | | | | | | | 110 | LATITUDE | 0.000172 | Deg| 20 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | +/-180 | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 111 | LONGITUDE| 0.000172 | Deg| 20 | | 1s |BNR | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | 4096 | | | | | | | | 112 | GROUND | 0.125 | Kts| 15 | | 1s |BNR | | | | SPEED | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | 0.000172 | | | | | | | | 120 | LATITUDE | 8.38 E-8 | Deg| 11 | | 1s |BNR | | | | FINE | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | 0.000172 | | | | | | | | 121 | LONGITUDE| 8.38 E-8 | Deg| 11 | | 1s |BNR | | | | FINE | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 125 | UTC | 23:59.9 |HR: | 5 | | 1s |BCD | | | | | 0.1 MIN |MIN | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | |HORIZONTAL| 16 | NM | 17 | | 1s |BNR | | | 130 | INTEGRITY| 0.00012 | | | | | | | | | LIMIT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | VERTICAL | 32768 | Ft | 17 | | 1s |BNR | | | 133 | INTEGRITY| 0.25 | | | | | | | | | LIMIT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | VERTICAL | 32768 | | | | | | | | 136 | FIGURE | 0.125 | Ft | 18 | | 1s |BNR | | | | OF MERIT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | 1.0 | | | | | | | | 140 | UTC FINE | 0.9536743 | S | 20 | | 1s |BNR | | | | | micro sec | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | UTC FINE | 0.953674 | S | 10 | | 1s |BNR | | | 141 | FRACTIONS| micron s | | | | | | | | | | 0.9313225ns| | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | APPROACH | 16 | NM | 17 | | 1s |BNR | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 143 | AREA | 0.00012 | | | | | | | | | HIL | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | APPROACH | 32768 | Ft | 17 | | 1s |BNR | | | 144 | AREA | 0.25 | | | | | | | | | HIL | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | |HR: | | | | | | | 150 | UTC | 23:59:59 |MIN:| 17 | | 1s |BNR | | | | | 1.0 s |S | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 162 | DEST | 23:59 |HR: | 11 | |0.5s|BNR | | | | ETA | 1 MIN |MIN | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 163 | ALT | 23:59 |HR: | 11 | |0.5s|BNR | | | | WAYPNT | 1 MIN |MIN | | | | | | | | ETA | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | VERTICAL | +/-32768 | Ft/| | | | | | | 165 | VELOCITY | 1.0 | Mn | 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | N/S | +/-4096 | | | | | | | | 166 | VELOCITY | 0.125 | Kts| 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | E/W | +/-4096 | | | | | | | | 174 | VELOCITY | 0.125 | Kts| 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 226 | DATA | N/A |N/A |N/A | |N/A |ISO | | | | LOADER | | | | | |#5 | | |--------------|----------|------------|----|----|----|----|----|-------------| | |HORIZONTAL| 16 | | | | | | | | 247 | FIGURE | 6.1E-5 | NM | 18 | | 1s |BNR | | | | OF MERIT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | N/A |DAY:| | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 260 | DATE | 1 Day |MON:| 6 | | 1s |BCD | | | | | |YEAR| | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | | | | | | | | | 273 | SENSOR | N/A |N/A |N/A | | 1s |DISC| | | | STATUS | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 343 | DEST | 16 |NM | 11 | |0.5s|BNR | | | | HIL | 0.0078 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | ALT | | | | | | | | | 347 | WAYPNT | 16 |NM | 11 | |0.5s|BNR | | | | HIL | 0.0078 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 354 | GPSSU | N/A |N/A |N/A | | |ISO | | | | IDENT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 356 | MAINT | N/A |N/A |N/A | | |ISO | | | | DATA | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | EQUIP| | | | | | | | | 377 | MENT | N/A |N/A |N/A | | 1s |BCD | | | | ID | | | | | | | | ------------------------------------------------------------------------------6. _____________________ Component Description R

**ON A/C 051-099, A. MMR (1) External description (Ref. Fig. 004) The face of the MMR is fitted with a handle, two attaching parts, a TEST pushbutton switch and three LEDs. The LRU STATUS LED has two colors (red/green). The three LEDs have the following name, color and function:

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MMR - External Description Figure 004   R EFF : 051-099,  34-36-00 Page 14   Config-2 Nov 01/09  CES

 

- LRU STATUS (red) indicates that an internal fault is detected during the front panel self-test sequence - LRU STATUS (green) indicates that no internal fault is detected during the front panel self-test sequence - CONTROL FAIL (red) indicates that no control input is available during the test sequence. - ANT FAIL (red) indicates that a failed antenna is detected during the test sequence. The back of the MMR is equipped with one ARINC 600 size one connector, which includes three plugs: - Top Plug (TP): connection with the GPS antenna - Middle Plug (MP): service interconnection - Bottom Plug (BP): connection with the power supply circuit, and the LOC and G/S coaxial interconnections. (2) Internal description (Ref. Fig. 005) The MMR consists of four parts: - the power supply unit - the ILS receiver - the GPS receiver - the system processor unit. The primary function of the MMR is to receive and process ILS and GPS signals. The ILS receiver and the GPS receiver make up two of the subassemblies. The ILS signals, including both localizer and glideslope, are used to determine flight path deviations during precision approach and landing, and are supplied to the aircraft flight control and instrument systems. These deviations are based on radio frequency signals that the unit receives from a ground-based instrument landing system. The GPS receiver simultaneously tracks signals from up to twelve GPS satellites. The signals are processed to generate a three-dimensional position and a precise time. The receiver generates an estimate of the positional accuracy provided. An integrity alert is activated if an unannounced satellite malfunction is detected. The receiver has the capability of excluding satellites that are malfunctioning. The system processor card has the functions that follow: - output position and deviation data to other aircraft systems, - receive ILS frequency selections, - receive ADIRU & FMGC data for GPS initialization, - dialog with the Centralized Fault Display Interface Unit (CFDIU). - Power supply

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MMR - External Description Figure 004A   R EFF : 001-049, 101-149, 151-199, 201-238,  34-36-00 Page 16 301-311, 401-499,  Config-2 Feb 01/09  CES

 

MMR - Block Diagram Figure 005   R EFF : 051-099,  34-36-00 Page 17   Config-2 Nov 01/09  CES

 

The aircraft supplies the 115 VAC, 400 Hz, single phase power to the MMR. The input power is routed from the rear interconnect to the forward power supply. The forward power supply provides power factor corrections, and outputs +200 VDC for the aft power supply. The aft power supply steps the +200 VDC down to +/- 6.5 and +/13.5 VDC outputs. These unregulated voltages are routed to the other subassemblies where they are post-regulated to +/- 5 VDC and +/- 12 VDC. Post-regulation provides a level of separation between the subassemblies and possible noise on the power lines. It will also allow shut-off of the circuit areas when not needed for a specific phase of flight (not used today). - ILS Receiver The MMR receives VHF localizer and UHF glideslope signals at the antenna jacks in the bottom plug of the rear connector. Coaxial cables route the RF from the rear connector to the ILS receiver. The ILS receiver includes four functional areas: VHF receiver, UHF receiver, primary instrumentation processor, and monitor instrumentation processor. The VHF receiver filters, mixes and amplifies VHF signals. The resulting intermediate frequency signals are converted into serial data and processed by both the primary and the monitor instrumentation circuits. The UHF receiver filters, mixes, amplifies, and detects UHF signals. The detected signals are converted into serial data and processed by the instrumentation processors. The primary instrumentation processor outputs flight path deviations to the system processor. The system processor forwards the flight path deviations to the aircraft instrumentation and auto-pilot computers (FMGC). The monitor instrumentation processor performs a validity check of the primary instrumentation processor deviation output, and disables the outputs if the check fails. The primary and monitor instrumentation processors use ARINC 429 buses for intercommunications and for communications with the system processor. - GPS Receiver The MMR receives RF signals through an active GPS antenna (preamplifier implemented within the antenna). The GPS receiver filters, mixes, and performs analog-to-digital conversions. The resulting data is processed by microprocessors that output position, velocity, time, and integrity data to the system processor. The system processor transmits ARINC 743A-compliant data for use by other aircraft systems. The GPS receiver also outputs a time mark discrete signal that tells users of the ARINC 743A data the instant in time when the position solution is valid.

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- System Processor The system processor controls the flow of data to the ILS and GPS receivers including mode and frequency selections, GPS initialization, and maintenance data requests. The system processor also controls the transmission of output data including ILS deviation, GPS position, velocity, time, integrity, time marks and maintenance data. Circuitry on the system processor converts received data from serial into parallel and also formats parallel data to serial data for transmission on the bus. **ON A/C 001-049, 101-149, 151-199, 201-238, 301-311, 401-499, A. MMR (1) External description (Ref. Fig. 004A) The face of the MMR is fitted with a handle, two attaching parts, a TEST pushbutton switch and four Light Emitting Diodes (LEDs). The four LEDs have the following name, color and function: - TEST OK (green) indicates that no fault is detected during the initiated (by pushbutton switch or by MCDU) self-test or during the power-up test. - MMR FAULT (red) indicates that an internal fault is detected by the MMR itself. - BUS IN FAIL (red) indicates that no control input is available. - TEST ANT (red) indicates that a failed antenna (or coaxial cable) is detected. The back of the MMR is equipped with one ARINC 600 size one connector, which includes three plugs: - Top Plug (TP): connection with the GPS antenna - Middle Plug (MP): service interconnection - Bottom Plug (BP): connection with the power supply circuit, and the LOC and G/S coaxial interconnections. (2) Internal description (Ref. Fig. 005A) The MMR includes: - an ILS RF module (RF) - a main ILS board (CMD) - a monitor ILS board (MON) - a GPS board (GPS) - a power supply module (POWER SUPPLY) - a High Intensity Radiated Field interconnect module (HIRF).

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MMR - Block Diagram Figure 005A   R EFF : 001-049, 101-149, 151-199, 201-238,  34-36-00 Page 20 301-311, 401-499,  Config-2 Feb 01/09  CES

 

The primary function of the MMR is to receive and process ILS and GPS signals. The ILS signals, including both localizer and glide slope, are used to determine flight path deviations during precision approach and landing, and are supplied to the aircraft flight control and instrument systems. These deviations are based on radio frequency signals that the unit receives from a ground-based instrument landing system. The GPS receiver simultaneously tracks signals from up to fifteen GPS satellites. The signals are processed to generate a three-dimensional position and a precise time. The receiver generates an estimate of the positional accuracy provided. An integrity alert is activated if an unannounced satellite malfunction is detected. The receiver has the capability of excluding satellites that are malfunctioning. It is able to incorporate external altimeter data to improve the availability of its integrity monitoring functions. (a) ILS RF module (RF) This module converts (filters, amplifies and demodulates) the RF signals received by the localizer and glide slope antennas into analog signals for processing by the Digital Signal Processor (DSP). The module consists of two RF sections, one for the VHF localizer signals and one for the UHF glide slope signals. (b) Main ILS board (CMD) The main ILS board controls the ILS mode of operation, generates the audio and deviation outputs, controls the aircraft interfaces and performs the maintenance tasks (for CFDIU interface). The board is divided into five sections: - A/D converter (ADC) which digitizes the localizer and glide slope signals from the ILS RF module. - DSP section which formats and sends to the Precision Approach Navigator (PAN) the deviations computed with the depth of modulation of the 90Hz and 150Hz. - PAN section which processes the data from the DSP section to provide the localizer and glide slope deviation information to the Input/Output section (I/O). The PAN compares information from the monitor ILS board with the information it has calculated itself. The PAN sends to the maintenance section the in-line test (BIT) results from all the boards installed in the MMR (RF, CMD, MON, GPS and POWER SUPPLY). - maintenance section which provides the interface with the Centralized Fault Display Interface Unit (CFDIU). - I/O section which consists of ARINC 429 drivers and receivers and discrete I/O logic. The I/O section provides the interface with aircraft systems.

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ARINC 429 inputs/outputs are processed by a specially designed ASIC (GLUCOMA). (c) Monitor ILS board (MON) The monitor ILS board provides a redundant dissimilar signal processing path for the localizer and glide slope signals from the ILS RF module. It also includes an ADC, a DSP, a PAN and an I/O section (as CMD). In order to determine if the main ILS board (CMD) operates properly, the MON PAN calculates the deviation outputs and compares the results against those being transmitted over the ARINC 429 ILS output ports. If the calculations from the two PANs are excessively different, the MON PAN asks the CMD PAN to set the deviation words to indicate failure. The MON PAN shuts down the output buses if the SSM of the output words does not indicate failure when required. (d) GPS Board (GPS) The GPS board receives RF signals through an active GPS antenna, filters, mixes, and performs analog-to-digital conversion and outputs position, velocity, time and integrity data. It also outputs a time mark discrete signal to synchronize users with the raw data sent by this board. The GPS board is divided into four sections: - RF section which filters and mixes the RF signal. - ASIC GNSS which processes the signals from the RF section. - Processor section which performs position, velocity, time (PVT) and integrity calculation with data received from ASIC GNSS. It also provides satellite information to I/O section. - I/O section which consists of ARINC 429 drivers and receivers and discrete I/O logic. It provides PVT, integrity and satellite information with aircraft systems. ARINC 429 inputs/outputs are processed by a specially designed ASIC (GLUCOMA). (e) Power supply module (POWER SUPPLY) The power supply module generates, from 115VAC/400HZ single phase, four regulated power supplies required for operation of the modules and boards (+12VDC, +5VDC, +15VDC, -15VDC). This module protects the secondary power supply voltages against short-circuits and spikes, makes primary power supply micro-interrupts transparent and isolates the equipment from the primary power supply.

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(f) High Intensity Radiated Field interconnect module (HIRF) The HIRF module provides with connection of the different internal modules and connection with the aircraft environment. It protects the MMR against electromagnetic interference, lightning indirect effects and has two filters for the 115VAC/400Hz input power. R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, B. GPS Antenna (Ref. Fig. 006) Two L-Band antennas are mounted on the top of the fuselage, at the centerline, to receive signals from the GPS satellites. The GPS antenna is an active antenna with an integrated preamplifier and filter. It receives GPS signals at 1575.42 MHz and matches to a 50 ohms coaxial cable at the input to the MMR. The antenna has a right-hand circular polarized and omnidirectional radiation pattern. The power supply of the preamplifier is provided by the MMR through the coaxial cable. NOTE : The antenna connectors have a hole to install a lockwire and ____ safety the coaxial cable. C. Localizer Antenna (Ref. Fig. 007) The localizer antenna is an airborne antenna used to receive LOC signals in the 108-112MHz range. It is a folded half-loop type driven by capacitive coupling. The antenna has two independent RF connectors used to feed two independent ILS receivers. Connector separation is provided by a hybrid junction in the antenna. D. Glide Slope Antenna (Ref. Fig. 007) The glide slope antenna is an airborne antenna used to receive GLIDE signals in the 329-335MHz range. It is a folded half-loop type driven by capacitive coupling. The antenna has two independent RF connectors used to feed two independent ILS receivers. Connector separation is provided by a hybrid junction in the antenna.

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GPS Active - Antenna Figure 006   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 24 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

ILS - Antennas Figure 007   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 25 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

7. Operation _________ A. ILS Operation (1) Normal operation (Ref. Fig. 008) Each MMR is connected to one Radio Management Panel (RMP). The MMR 1 is connected to the RMP 1 (the MMR 2 to the RMP 2). The MMR 1 receives management bus from the FMGC 1 through the RMP 1 (the MMR 2 from the FMGC 2 through the RMP 2). In normal operation, the FMGC 1(2) tunes the MMR 1(2) either automatically or manually by means of the MCDU. In this case the RMP 1(2) operates as a relay which sends the frequency information from the FMGC 1(2) to the receiver 1(2). Via a second port, the MMR 1(2) receives a second management bus (ILS FREQ + RWY HDG) directly from the FMGC 2(1). The receiver selects one of the two input ports according to the FREQ/FUNCT DATA SOURCE SEL discrete signal, which is received from the FMGC 1(2) through the RMP 1(2). (2) Operation in case of failure With failure of one FMGC, the second FMGC automatically controls the two MMRs, the off side directly, the on side through its RMP. With failure of the RMP 1(2) or two RMPs, the RMP concerned is transparent to data and discrete from FMGC. (3) Manual operation In manual operation (at any time, or with failure of two FMGCs) the RMP 1 can control the MMR 1 after ON NAV mode selection. Same possibility for the RMP 2 (MMR 2). (Ref. Fig. 009) In this mode the RMP 1 can control the MMR 2 through the RMP 2 after ON NAV mode selection on the RMP 2. Same possibility for RMP 2 through RMP 1. After any frequency selection it is always necessary to select the associated course. (4) Reconfiguration switching In normal utilization, the ILS 1 data are shown on the CAPT PFD and the F/O ND; the ILS 2 data on the F/O PFD and the CAPT ND. The DMC 1 supplies data to the CAPT PFD and ND; the DMC 2 to the F/O PFD and ND. With failure of the DMC 1(2) it is possible to switch over to the DMC 3 with the EIS DMC selector switch located on the panel 8VU on the center pedestal.

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MMR - Control and Indicating Figure 008   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 27 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

MMR - ILS - Course and Frequency Selection in Manual Mode Figure 009   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 28 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

In this case, the DMC 3 totally replaces the DMC 1(2) through the stage of the output switching relay of the failed DMC. With failure of the PFD, there is an automatic transfer of the PFD image onto the ND. With failure of the CAPT (F/O) ND, you obtain the transfer of the ND image onto the CAPT (F/O) PFD when you push the PFD/ND XFR pushbutton switch on panel 301VU (500VU). When you set the PFD potentiometer to OFF on the panel 301VU (500VU) this causes: - deactivation of the CAPT (F/O) PFD - transfer of the PFD image onto the CAPT (F/O) ND. (5) Audio control The MMR applies its audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loudspeakers. The Audio Management Unit (AMU) controls the audio level through the ACP. On the ACP, the pilot must push the ILS pushbutton switch and adjust the related potentiometer to the correct audio level. With ILS/DME collocated stations, the DME identification morse code can be listened in sequence with the ILS audio signal when you push the ILS pushbutton switch on the ACP and the ILS pushbutton switch on the FCU. (6) Data display (Ref. Fig. 010) (a) On the PFDs On the right and below the attitude sphere, the deviation indications come into view in approach. These are: - the vertical deviation scale - the lateral deviation scale - the related aircraft deviation symbols. If you select an ILS approach, the scales and symbols give GLIDE SLOPE and LOCALIZER deviations. The scales come into view when you push the ILS pushbutton switch on the EFIS control section of the Flight Control Unit (FCU). The deviation symbols come into view when the related G/S and LOC signals from the ILS receiver are valid. If the ILS indications are available with the ILS pushbutton switch pushed they have priority over the deviation information of the R NAV approach. In this mode the data given after are shown (item 5): in the left bottom corner: - ILS frequency (plus ILS identification if available) - ILS - DME distance.

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MMR - ILS Data Display Figure 010   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 30 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

At the top section of the PFD a Flight Mode Annunciator shows the various armed/active longitudinal and lateral modes: (item 1): the G/S longitudinal modes are shown in the 2nd column (cyan for armed or green for active) (item 2): the LOC longitudinal modes are shown in the 3rd column (cyan for armed or green for active) VERTICAL DEVIATION (item 3) The vertical scale shows a classical glide slope deviation. It is linear with 2 dots on each side. Two dots correspond to plus (or minus) 0.175 ddm (150 microA) deviation. The index shows magenta G/S indication. Until the glide beam is captured, the glide index is not shown (No Computed Data). When the index is against one stop only one half of it is in view (the outer half index). The glide slope index and the scale flash permanently in case of G/S excessive deviation warning. With a glide fault, the G/S index goes out of view and a red G/S failure warning message is shown in the middle of the scale. (Ref. Fig. 011) LATERAL DEVIATION (item 4) The horizontal scale shows a classical LOC deviation with 2 dots on each side. Two dots correspond to plus (or minus) 0.155 ddm (150 microA) deviation. The index shows magenta LOC indication. Until the LOC is captured, the LOC index is not shown (No Computed Data). When the index is against one stop, only one half of it is shown. The LOC index and the scale flash permanently in case of LOC excessive deviation warning. With a localizer fault, the LOC index goes out of view and a red LOC failure warning message is shown in the middle of the scale. (Ref. Fig. 010, 011) (b) On NDs in the ROSE ILS mode In the ROSE ILS mode, the ND gives a display which is similar to that of a conventional Horizontal Situation Indicator (HSI): a heading dial orientated to the magnetic North turns and gives the actual magnetic heading of the aircraft in relation to the stable yellow lubber line. The ND is always heading up: A yellow aircraft model, at the center of the heading dial is stable and pointed up to the yellow lubber line. Small white triangles are put each 45 deg. on the circumference in relation to the lubber line. They are stable and do not turn with the heading dial. A green diamond-shaped symbol moves around the heading dial and gives the actual track of the aircraft.

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MMR - ILS Warning Display Figure 011   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 32 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

The ND shows the indications given after, when available, in its right top corner (item 8): - the side of the displayed ILS receiver - the frequency - the course - the identification. The ND shows the ILS APP message in its center top section (item 7) when the pilot has selected the ILS approach on the MCDU. LATERAL DEVIATION (item 6) A dagger-shaped pointer points to the selected ILS course. Its center part is the lateral deviation bar, which can move on a scale which is perpendicular to the pointer and has two dots on each side. The position of the bar on the scale gives the localizer deviation. The extreme dots correspond to plus or minus 0.155 ddm (plus or minus 150 microA). With LOC fault a red LOC warning message comes into view in the middle of the LOC scale and the LOC deviation bar goes out of view. VERTICAL DEVIATION (item 9) A magenta lozenge gives the glide slope deviation on a vertical scale at the right of the heading dial if the aircraft is within the condition of reception of the ILS glide slope signal. The extreme dots of the vertical scale correspond to plus or minus 0.175 ddm (plus or minus 150 microA). With G/S fault, a red G/S warning message comes into view at the top of the scale and the index goes out of view. (c) On NDs in ARC and ROSE NAV modes When you push the ILS pushbutton switch in ARC or ROSE NAV mode, the ND shows the symbols given after (item 11): - a magenta dagger-shaped pointer which points to the selected QFU - an arrow which indicates the lateral deviation of the aircraft related to the localizer axis. (7) Warnings (Ref. Fig. 011) The warnings related to the ILS are: - local warning on the instruments that use the ILS information - MASTER CAUT lights on CAPT and F/O glareshield panels - aural warning: single chime (SC) - warning message shown on the upper display unit of the ECAM system.

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B. GPS Function (1) Normal operation (a) General To reduce initialization time, the MMR 1(2) receives position data, LAT/LONG (labels 310/311) from the ADIRU 1(2) and SET LAT, SET LONG (labels 041, 042) UTC/Date from the FMGC 1(2) through the ADIRU 1(2). Each MMR receives the GPS satellite RF signals from the active antenna to compute and provide the three ADIRUs with: - UTC, date - position, altitude - ground speed, track angle - N/S speed, E/W speed, vertical speed - horizontal and vertical dilution of precision, figure of merit - satellite position - satellite measurement (pseudo-range, delta range, range rate, UTC measurement time) - GPS measurement status, sensor status - real time and predictive integrity data. Within each ADIRU an hybridization function performs the following: - monitoring of the MMR using GPS status word and ADIRU BITE - generation of failure message for ECAM display - use of pseudo-range/delta range data to compute GPS position - use of inertial data to smooth GPS position/velocity - use of a Kalman filter to estimate and minimize errors - use of IR data to improve the robustness of the MMR RAIM algorithm. - transmission of GPS and GPIR data to the FMGC for position fixing and display purposes. (b) GPS primary navigation function principle in the FMGC A navigation mode with the least error is chosen based upon the mixed IR position and the best GPIR or radio position available. NOTE : The GPIR position used by the FMGC to determine the ____ aircraft position is computed in the GPIR partition of the ADIRU (hybrid solution). The FMS mode of navigation is selected according to the following hierarchy: - GPIR/Inertial - DME/DME/Inertial - DME/VOR/Inertial

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- Inertial only. The GPIR/INERTIAL mode is selected as long as the following conditions are satisfied: - GPIR position is available and with an estimated accuracy consistent with the intended operation. - GPIR integrity is available and compatible with the applicable phase of flight requirement. As long as the GPS/INERTIAL mode is active, no DME/DME or VOR/DME radio updating is allowed. However, LOC updating can apply to GPS/INERTIAL position. In this navigation mode, N IR/GPS indication is displayed on the POSITION MONITOR page with N being the number of IRs used to compute mixed IR position. The selected hybrid GPIRS position is displayed on the POSITION MONITOR page in place of the radio position. The mixed IR position and the IR deviations displayed on the POSITION MONITOR page do not change and are still computed using pure IR inputs. Aircraft position is generated by a series of filters which use inertial position, GPIR position or radio position, and aircraft velocity as input. A position bias is computed once every second through the position bias filter. This position bias is computed as the difference between the GPIR position (or radio position) and the inertial position. The aircraft position is finally computed every 200 ms based on the corrected inertial position and the aircraft velocity using the aircraft position filter. The GPS/INERTIAL mode can be manually inhibited by pushing the line key adjacent to the DESELECT GPS indication on the SELECTED NAVAIDS page. (Ref. Fig. 012) FMGC computed integrity: When the GPIR position is available in the FMGC but the GPIR integrity is not delivered by the ADIRS, the FMGC is capable of computing an equivalent integrity called AIM (Alternate Integrity Monitoring), using IR data, during a limited period of time. The goal of this FMGC functionality is to improve the availability of the GPS Primary function in the cockpit. (c) Clock synchronization on GPS time 1 _

If a GPS signal is present and valid when the power is on, the clock synchronizes on the GPS time using labels 150 and 260.

2 _

If the signal is not present during synchronization, the clock dispalys dashes on all the digits.

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MMR - GPS SELECTED NAVAIDS Page on MCDU Figure 012   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 36 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

3 _

If the signal is present but not valid during synchronization, the clock indicates 00:00:00.

4 _

If the signal becomes not valid after synchronization, the clock runs on its internal time base.

(d) Display of GPS data on MCDU 1 _

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GPS MONITOR (Ref. Fig. 013) The GPS data are displayed on the GPS MONITOR page of the MCDU. To get the GPS MONITOR page, push the DATA key on the MCDU, then the line key adjacent to the GPS MONITOR indication. The upper part is dedicated to GPS 1 data, the lower part to GPS 2 data. The following data are displayed: - GPS position (lat/long) - true track - GPS altitude - figure of merit (in meters) - ground speed - number of satellites tracked - mode.

**ON A/C 051-099, 106-149, 204-238, 301-311, 401-499, 2 _

PREDICTIVE GPS (Ref. Fig. 014) The integrity prediction results given by the GPS portion of the MMR on Flight Management System (FMS) request are displayed on the PREDICTIVE GPS page of the MCDU (from the progress page which displays required navigation accuracy and estimated position accuracy and GPS PRIMARY indication). The prediction concerns the destination (DEST) and any pilot entered waypoint (WPT) and the integrity availability (HIL < 0.3 Nm) is displayed by Yes (Y) or No (N) for the seven times defined by the five minutes increments for plus or minus 15 minutes around DEST or WPT.

3 _

Progress page The progress page indicates whether the GPS is used by the FMGC for navigation. If it is used, the GPS PRIMARY indication is displayed. If it is not used, the GPS PRIMARY LOST message is shown.

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GPS - GPS MONITOR Page on MCDU Figure 013   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 38 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

GPS - PREDICTIVE GPS Page Figure 014   R EFF : 051-099, 106-149, 204-238, 301-311,  34-36-00 Page 39 401-499,  Config-2 Nov 01/09  CES

 

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4 _

MCDU scratchpad GPS PRIMARY in white or GPS PRIMARY LOST in amber show on the MCDU scratchpad.

5 _

SELECTED NAVAIDS page It is possible to select GPS for navigation computation within the FMS on the SELECTED NAVAIDS page. If you deselected GPS, the message GPS IS DESELECTED appears on the MCDU when a GPS approach starts.

6 _

ARRIVAL page To select a GPS approach, use the ARRIVAL page.

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, (e) Display of GPS messages on ND (Ref. Fig. 015) 1 _

Display of GPS PRIMARY LOST amber message This message is displayed at the bottom of the image in all the ND modes (except engine standby modes) when the GPS primary is lost (this message cannot be cleared from the MCDU). In this case, the GPS is not used for navigation (accuracy and integrity for the intended operation can still be met by the use of alternate navigation means).

2 _

Display of GPS PRIMARY white message This message is displayed at the bottom of the image in all the ND modes (except engine standby modes) when the GPS becomes primary (this message can be cleared from the MCDU).

3 _

Display of GPS APP green message This approach message is displayed at the top of the image in all the ND modes (except engine standby modes) when a GPS approach is selected in the flight plan.

(2) Warning (a) GPS failure The GPSs are monitored by the both FWCs using a status word sent by each GPS. In case of GPS failure, the NAV GPS 1(2) FAULT message is displayed in the lower part of the upper ECAM DU. This message is accompanied by: - activation of the MASTER CAUT lights on the glareshield - aural warning: Single Chime (SC).

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MMR - GPS Data Displayed on the NDs Figure 015   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 41 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

NOTE : The failure is reminded on the INOP SYSTEM page of the ____ lower ECAM DU. The message displayed is GPS 1(2). (b) Loss of the GPS primary navigation When the GPS navigation is lost for any reason, the navigation function is degraded and reverts to the traditional navigation function with IRS positions and radio positions if available (in this case the RNP (Required Navigation Performance) features are still available). Warnings are generated to indicate the loss of GPS PRIMARY navigation: - GPS PRIMARY LOST message on the NDs (cannot be cleared) and MCDU (can be cleared) - in case of GPS non-precision approach, an aural alert is generated (Triple Click) (c) GPS/FMS position disagreement When GPS Primary is active and either FMGC 1 or FMGC 2 latitude (longitude) deviates from either MMR 1 or MMR 2 latitude (longitude) by more than 0.5 Nm, the NAV FMS/GPS POS DISAGREE and A/C POS...........CHECK messages are displayed in amber and cyan respectively on the ECAM DU. These messages are accompanied by: - activation of the MASTER CAUT lights on the glareshield - aural warning: Single Chime (SC).

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8. _____________ BITE Function R

**ON A/C 051-099, A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the MMR. The BITE of the MMR is connected to the CFDIU. The BITE: - transmits permanently MMR status and its identification message to the CFDIU, - memorizes the failures which occurred during the last 63 flight legs, - monitors data inputs from the various peripherals, - transmits to the CFDIU the result of the tests performed and self-tests, - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode, - the menu mode. (a) Normal mode During the normal mode, the BITE cyclically monitors the status of the MMR. It transmits its information to the CFDIU during the concerned flight. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU by an ARINC 429 message with label 356. (b) Menu mode The menu mode can only be activated on ground. This mode enables communication between the CFDIU and the MMR BITE by means of the MCDU. (Ref. Fig. 016) When you get access to the SYSTEM REPORT/TEST/NAV page, the ILS1 and ILS2 indications can be shown instead of the MMR1 and MMR2 indications. In this case, you must do the following steps: - make sure that the the engines are shut down - open CFDIU SUPPLY circuit breaker 2TW - open CFDIU BACK UP circuit breaker 8TW - make sure that MMR1 and MMR2 circuit breakers, 42RT1 and 42RT2, are closed

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MMR - Maintenance Test Procedure Figure 016   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 44 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

- wait for 30 seconds then close the CFDIU circuit breakers 2TW and 8TW - wait for 180 seconds then get access to the SYSTEM REPORT/TEST/NAV page. All the information displayed on the MCDU during the BITE Test configuration can be printed by the printer (Ref. 31-35-00). The MMR menu mode is composed of: - LAST LEG REPORT (Ref. Fig. 017) This menu contains the fault messages (class 1 internal and external) detected during the last flight. - PREVIOUS LEGS REPORT (Ref. Fig. 018) This report contains the fault messages related to the external or internal failures (class 1) recorded during the previous 63 flight legs. - LRU IDENTIFICATION (Ref. Fig. 019) Allows to display the P/N, the serial number and the software number of the equipment. - GND SCANNING (Ref. Fig. 020) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. - TROUBLE SHOOTING DATA (Ref. Fig. 021) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. - CLASS 3 FAULTS (Ref. Fig. 022) Allows to display the class 3 faults recorded during the last flight leg. - GROUND REPORT (Ref. Fig. 023) Allows to present the class 1 or 3 internal failures detected on ground. - SYSTEM TEST (Ref. Fig. 024, 025) Allows a check of the correct operation of the MMR. (2) List of components All the components are listed in Para. 2. Component Location.

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MMR - Last Leg Report Figure 017   R EFF : 051-099,  34-36-00 Page 46   Config-2 Nov 01/09  CES

 

MMR - Last Leg Report and LRU Identification Figure 017A   R EFF : 001-049, 101-149, 151-199, 201-238,  34-36-00 Page 47 301-311, 401-499,  Config-2 Feb 01/09  CES

 

MMR - Previous Legs Report Figure 018   R EFF : 051-099,  34-36-00 Page 48   Config-2 Nov 01/09  CES

 

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MMR - LRU Identification Figure 019   R EFF : 051-099,  34-36-00 Page 50   Config-2 Nov 01/09  CES

 

MMR - Ground Scanning Figure 020   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 51 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

MMR - Trouble Shooting Data Figure 021   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 52 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

MMR - Last Leg Class 3 Faults Figure 022   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 53 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

MMR - Ground Report Figure 023   R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-00 Page 54 201-238, 301-311, 401-499,  Config-2 Nov 01/09  CES

 

MMR - System Test Figure 024   R EFF : 051-099,  34-36-00 Page 55   Config-2 Nov 01/09  CES

 

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MMR - System Test Figure 025   R EFF : 051-099,  34-36-00 Page 57   Config-2 Nov 01/09  CES

 

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**ON A/C 001-049, 101-149, 151-199, 201-238, 301-311, 401-499, A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the MMR. The BITE of the MMR is connected to the CFDIU. The BITE: - transmits permanently MMR status and its identification message to the CFDIU - memorizes the failures which occurred during the last 63 flight legs - monitors data inputs from the various peripherals - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the menu mode. (a) Normal mode During the normal mode, the BITE cyclically monitors the status of the MMR. It transmits its information to the CFDIU during the concerned flight. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU by an ARINC 429 message with label 356. (b) Menu mode The menu mode can only be activated on ground. This mode enables communication between the CFDIU and the MMR BITE by means of the MCDU. (Ref. Fig. 016) When you get access to the SYSTEM REPORT/TEST/NAV page, the ILS1 and ILS2 indications can be shown instead of the MMR1 and MMR2 indications. In this case, you must do the following steps: - make sure that the the engines are shut down - open CFDIU SUPPLY circuit breaker 2TW - open CFDIU BACK UP circuit breaker 8TW - make sure that MMR1 and MMR2 circuit breakers, 42RT1 and 42RT2, are closed - wait for 30 seconds then close the CFDIU circuit breakers 2TW and 8TW

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- wait for 180 seconds then get access to the SYSTEM REPORT/TEST/NAV page. All the information displayed on the MCDU during the BITE Test configuration can be printed by the printer (Ref. 31-35-00). The MMR menu mode is composed of: - LAST LEG REPORT (Ref. Fig. 017A) This menu contains the fault messages (class 1 internal and external) detected during the last flight. - PREVIOUS LEGS REPORT (Ref. Fig. 018A) This report contains the fault messages related to the external or internal failures (class 1) recorded during the previous 63 flight legs. - LRU IDENTIFICATION (Ref. Fig. 017A) Allows to display the P/N and the software numbers of the equipment. - GND SCANNING (Ref. Fig. 020) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. - TROUBLE SHOOTING DATA (Ref. Fig. 021) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. - CLASS 3 FAULTS (Ref. Fig. 022) Allows to display the class 3 faults recorded during the last flight leg. - GROUND REPORT (Ref. Fig. 022) Allows to present the class 1 or 3 internal failures detected on ground. - SYSTEM TEST (Ref. Fig. 024A, 025A) Allows a check of the correct operation of the MMR. (2) List of components All the components are listed in Para. 2. Component Location.

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MMR - System Test Figure 025A   R EFF : 001-049, 101-149, 151-199, 201-238,  34-36-00 Page 60 301-311, 401-499,  Config-2 Feb 01/09  CES

 

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**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, (3) Reporting function The tables below give the list of internal/external failures. (a) Internal failure: ----------------------------------------------------------------------------I ATA I CLASS I MESSAGE I I I (A/C) I I I---------------------------------------------------------------------------I 34-36-31 I 1 I MMRi (40RTi) I I 34-36-11 I 1 I LOCALIZER ANTENNA (3RT)/COAX CABLE/MMRi(40RTi) I I 34-36-18 I 1 I GLIDE ANTENNA (4RT)/COAX CABLE/MMRi (40RTi) I I 34-36-16 I 1 I GPS ANTENNAi (43RTi)/COAX CABLE/MMRi(40RTi) I I I I i = (1,2) I ----------------------------------------------------------------------------(b) External failure: ----------------------------------------------------------------------------I ATA I CLASS I MESSAGE I I I (A/C) I I ----------------------------------------------------------------------------I 31-32-34 I 3 I CFDIU (1TW)/MMRi (40RTi) I I 22-83-34 I 3 I FMGCi (1CAi)/RMPi (1RGi)/MMRi (40RTi) I I 22-83-34 I 3 I FMGCj (1CAj) BUS ILS/MMRi (40RTi) I I 22-83-34 I 3 I FMGC1 (1CA1) BUS GPS/MMRi (40RTi) I I 22-83-34 I 3 I FMGC2 (1CA2) BUS GPS/MMRi (40RTi) I I 34-12-34 I 3 I ADIRUk (1FPk)/MMRi (40RTi) I I 32-31-71 I 3 I LGCIUi (5GAi)/FMGCi (1CAi)/MMRi (40RTi) I I 31-62-34 I 1 I DMCi (1WTi)/MMRi (40RTi) I I I I j,i = (1,2) or (2,1) I I I I k = 1, 2 or 3 I -----------------------------------------------------------------------------

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**ON A/C 051-099, (4) Interactive function To gain access to the BITE, it is necessary to use one MCDU (Ref. 22-82-00). (Ref. Fig. 017, 018, 019, 020, 021, 022, 023, 024, 025) All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00). **ON A/C 001-049, 101-149, 151-199, 201-238, 301-311, 401-499, (4) Interactive function To gain access to the BITE, it is necessary to use one MCDU (Ref. 22-82-00). (Ref. Fig. 017A, 018A, 020, 021, 022, 023, 024A, 025A) All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00).

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**ON A/C 051-099, B. BITE Implementation (1) Activation of the receiver face test The receiver face test can be activated by pushing the TEST pushbutton switch on the receiver face, if the test inhibit discrete is not active. The sequence below is then generated on the receiver face. Depending on the outcome of the receiver face test, one of the following results is displayed: ----------------------------------------------------------------------------I SEQUENCE I LRU STATUS I CONTROL I ANT FAIL I I TIME I I NO. I LED (DS1) I FAIL LED I LED I DEFINITION I DEFINITION I I I I (DS2) I (DS3) I I I I---------------------------------------------------------------------------I I 1 I Red I Red I Red I LED self- I 2 seconds I I I I I I test I I I---------------------------------------------------------------------------I I 2 I Green I Red I Red I LED self- I 2 seconds I I I I I I test I I I---------------------------------------------------------------------------I I 3 I Off I Off I Off I Unit self- I 2 seconds I I I I I I test I minimum I I---------------------------------------------------------------------------I

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----------------------------------------------------------------------------I SEQUENCE I LRU STATUS I CONTROL I ANT FAIL I I TIME I I NO. I LED (DS1) I FAIL LED I LED I DEFINITION I DEFINITION I I I I (DS2) I (DS3) I I I I---------------------------------------------------------------------------I I 4 I Green I Off I Off I Unit passedI 30 seconds I I I-------------------------------------------------I I I I Red I I I Unit I I I I I I I failed I I I I-------------------------------------------------I I I I I Red I I Control I I I I I I Iinput failedI I I I-------------------------------------------------I I I I I I Red I Antenna I I I I I I I failed I I I---------------------------------------------------------------------------I I 5 I Off I Off I Off I Test I Until next I I I I I I complete I requested I I I I I I I self-test I ----------------------------------------------------------------------------(2) Activation of the functional test The functional test can be activated by pushing the line key adjacent to the TEST indication on the MMR maintenance sub-menu. It is similar to the receiver face test except that the receiver face LEDs are not controlled to reflect the status of the unit, which is reported on the MCDU.

  R EFF : 051-099,  34-36-00 Page 63   Config-2 Nov 01/09  CES

 

R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1373 For A/C 001-049,101-149,151-199,201-234,236-238,301-307, 401-499, ILS ((MMR)) - DESCRIPTION AND OPERATION _______________________________________ 1. _______ General The primary function of the Multi-Mode Receiver (MMR) is to receive and process Instrument Landing System (ILS) and Global Positioning System (GPS) signals. The MMR is a navigation sensor with two internal receivers. A. ILS Receiver The function of the ILS is to provide the crew and airborne system users with lateral (LOC) and vertical (G/S) deviation signals, with respect to the approach ILS radio beam transmitted by a ground station. The localizer operates in a frequency band which ranges from 108.1 MHz to 111.95 MHz and the glide uses the band from 329.15 MHz to 335 MHz as defined by ARINC specification 710. B. GPS Receiver The GPS is a radio aid to worldwide navigation which provides: - the crew with a readout of accurate navigation information, e.g. position, track and speed - the Flight Management and Guidance Computer (FMGC) with position information, for accurate position fixing. 2. Component __________________ Location (Ref. Fig. 001) The MMR system units are located in the aircraft as follows. ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------40RT1 MMR-1 95VU 120 811 34-36-31 40RT2 MMR-2 96VU 120 811 34-36-31 3RT ANTENNA-LOCALIZER 1/2 110 110AL 34-36-11 4RT ANTENNA-GLIDE/SLOPE 1/2 110 110AL 34-36-18 43RT1 ANTENNA-GPS ACTIVE, 1 210 831 34-36-16 43RT2 ANTENNA-GPS ACTIVE, 2 210 831 34-36-16

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 1 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - Component Location Figure 001   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 2 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

3. System __________________ Description (Ref. Fig. 002, 003) The A/C comprises two independent MMRs, 40RT1 and 40RT2, linked to: - a common localizer antenna 3RT - a common glide/slope antenna 4RT - a GPS active antenna 43RT1 (linked to MMR1) - a GPS active antenna 43RT2 (linked to MMR2). A. ILS Operation The equipment given below can control the ILS operation: - the Multipurpose Control and Display Units (MCDU) and the Flight Management and Guidance Computers (FMGC) for frequency/course selection in normal operating mode. - the Radio Management Panels (RMP) for frequency/course selection in back-up mode. The ILS data are shown on the EFIS displays: - the CAPT Primary Flight Display (PFD) and F/O Navigation Display (ND) show the deviations from the ILS1. - the F/O PFD and CAPT ND show the deviations from the ILS2. The Morse-coded audio identification signals are sent to the Audio Management Unit (AMU). These signals can be heard in the boomset and on the loudspeaker according to the selection by the crew on the Audio Control Panel (ACP). B. GPS Operation (1) Normal operation In normal operation, the GPS 1 data are used by the ADIRUs 1 and 3; the GPS 2 data by the ADIRU 2. NOTE : In order to reduce GPS initialization time, the GPS 1(2) ____ receives data from the ADIRU 1(2). The Inertial Reference (IR) portion of the ADIRU 1(2) provides the FMGC 1(2) with: - pure IR data - pure GPS data (in this case the ADIRU operates as a relay) - hybrid GPIR data. The hybrid GPIR 1(2) data are used by the FMGC 1(2) for position fixing purposes. The pure GPS data are used for display on the MCDU 1 and 2. In case of one GPS only operative GPS In case of ADIRU 1 In case of ADIRU 2

failure, the three ADIRUs automatically select the to compute hybrid GPIR data. failure, the FMGC 1 uses ADIRU 3/GPS 1 data. failure, the FMGC 2 uses ADIRU 3/GPS 2 data.

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 3 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - Monitoring and Display Figure 002   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 4 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - Data Acquisition Figure 003   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 5 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

NOTE : The primary source of the ADIRU 3 being the GPS ____ necessary to select the secondary input port of (GPS 2) by means of the ATT HDG selector switch preserve side 1/side 2 segregation (GPS 1/ADIRU GPS 2/ADIRU 3/FMGC 2 architecture).

1, it is the ADIRU 3 (13FP) to 1/FMGC 1 and

In case of failure of two ADIRUs, the two FMGCs use only the operative ADIRU. This ADIRU receives data from its own side GPS (e.g. ADIRU 1 - GPS 1). C. Maintenance Operation The MMR system provides the Centralized Fault Display Interface Unit (CFDIU) with an interface for onboard testing and fault reporting purposes. The MCDUs show the maintenance data. 4. Power ____________ Supply Each MMR system is energized through 115VAC busbars as follows: - 401XP for system 1 - 204XP for system 2. The system is supplied through these circuit breakers: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1147 For A/C 001-004, 49VU NAV/MMR/1

R R

42RT1

G12

**ON A/C 106-149, 151-199, 204-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 101-105, 201-203, Post SB

34-1147 For A/C 001-004,

121VU COM NAV/MMR/2

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 6 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, 5. Interface _________ A. ILS Interface (1) ILS digital outputs The ILS transmits data in compliance with the low speed ARINC 429 standards. The table below contains all the output parameters in the numerical form. ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 173 | LOCALIZER|+ or - 0.155| DDM| 29 | 12 | 50 | BNR| | | | | DEVIATION| | | | | ms | | | | | | | | | | | | | | | | 174 | GLIDE |+ or - 0.175| DDM| 29 | 12 | 50 |BNR | | | | | SLOPE | | | | | ms | | | | | | DEVIATION| | | | | | | | | | | | | | | | | | | | | 033 | ILS |FROM 108.10 |MHz | | 15 |200 |BCD | | | | | FREQUENCY| TO 111.95 | | | | ms | | | | | | | | | | | | | | | | 017 | RUNWAY | FROM 0 TO |Deg.| | 15 |300 |BCD | | | | | HEADING | 359.9 | | | | ms | | | | | | | | | | | | | | | | 105 | RUNWAY | FROM 0 TO |Deg.| | 11 |300 |BNR | | | | | HEADING | 359.9 | | | | ms | | | | | | | | | | | | | | | | 263 |ILS GROUND| | | | 14 |150 |HYB | | | | | STATION | | | | | ms | | | | | | IDENT | | | | | | | | | | | | | | | | | | | | | 264 |ILS GROUND| | | | 14 |150 |HYB | | | | | STATION | | | | | ms | | | | | | IDENT | | | | | | | | | | | | | | | | | | | | | 271 | MMR | | | | 19 |400 |DISC| | | | | DISCRETE | | | | | ms | | | |

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 7 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | -------------------------------------------------------------------------------------------------------------------------------------------------------------

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 8 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

B. GPS Interface (1) GPS digital outputs The GPS has three independently buffered high-speed ARINC 429 digital output buses connected to the three ADIRUs. The table below contains all the output parameters in numerical form. ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | 060 | MEASURE- | Pack | N/A| N/A| | 1s | | | | | MENT STS | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | |+/-268435456| | | | | | | | 061 | PSEUDO | 256 | M | 20 | | 1s |BNR | | | | RANGE | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 062 | PSEUDO | 256 | M | 11 | | 1s |BNR | | | | RANGE | 0.125 | | | | | | | | | FINE | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 063 | RANGE | +/-4096 | M/S| 20 | | 1s |BNR | | | | RATE | 0.0039 | | | | | | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 064 | DELTA | +/-4096 | M | 20 | | 1s |BNR | | | | RANGE | 0.0039 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 065 | SV POS X | +/-67108864| M | 20 | | 1s |BNR | | | | | 64 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 066 | SV POS X | 64 | M | 14 | | 1s |BNR | | | | FINE | 0.0039 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | +/-67108864| | | | | | | | 070 | SV POS Y | 64 | M | 20 | | 1s |BNR | | | | | | | | | | | |

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 9 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 071 | SV POS Y | 64 | M | 14 | | 1s |BNR | | | | FINE | 0.0039 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 072 | SV POS Z | +/-67108864| M | 20 | | 1s |BNR | | | | | 64 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | | | | | | | | | 073 | SV POS Z | 64 | M | 14 | | 1s |BNR | | | | FINE | 0.0039 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | UTC MEA- | 10.0 | | | | | | | | 074 | SURE TIME| 9.536743 | S | 20 | | 1s |BNR | | | | | micro sec | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS ALT | +/-131072 | | | | | | | | 076 | (MSL) | 0.125 | Ft | 20 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | 1024 | | | | | | | | 101 | HDOP | 0.031 | N/A| 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | 1024 | | | | | | | | 102 | VDOP | 0.031 | N/A| 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS TRACK| +/-180 | | | | | | | | 103 | ANGLE | 0.0055 | Deg| 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | +/-180 | | | | | | | | 110 | LATITUDE | 0.000172 | Deg| 20 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | +/-180 | | | | | | |

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 10 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 111 | LONGITUDE| 0.000172 | Deg| 20 | | 1s |BNR | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | 4096 | | | | | | | | 112 | GROUND | 0.125 | Kts| 15 | | 1s |BNR | | | | SPEED | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | 0.000172 | | | | | | | | 120 | LATITUDE | 8.38 E-8 | Deg| 11 | | 1s |BNR | | | | FINE | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | 0.000172 | | | | | | | | 121 | LONGITUDE| 8.38 E-8 | Deg| 11 | | 1s |BNR | | | | FINE | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 125 | UTC | 23:59.9 |HR: | 5 | | 1s |BCD | | | | | 0.1 MIN |MIN | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | |HORIZONTAL| 16 | NM | 17 | | 1s |BNR | | | 130 | INTEGRITY| 0.00012 | | | | | | | | | LIMIT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | VERTICAL | 32768 | Ft | 17 | | 1s |BNR | | | 133 | INTEGRITY| 0.25 | | | | | | | | | LIMIT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | VERTICAL | 32768 | | | | | | | | 136 | FIGURE | 0.125 | Ft | 18 | | 1s |BNR | | | | OF MERIT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | 1.0 | | | | | | | | 140 | UTC FINE | 0.9536743 | S | 20 | | 1s |BNR | | | | | micro sec | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | UTC FINE | 0.953674 | S | 10 | | 1s |BNR | | | 141 | FRACTIONS| micron s | | | | | | | | | | 0.9313225ns| | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | APPROACH | 16 | NM | 17 | | 1s |BNR | |

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 11 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 143 | AREA | 0.00012 | | | | | | | | | HIL | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | APPROACH | 32768 | Ft | 17 | | 1s |BNR | | | 144 | AREA | 0.25 | | | | | | | | | HIL | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | |HR: | | | | | | | 150 | UTC | 23:59:59 |MIN:| 17 | | 1s |BNR | | | | | 1.0 s |S | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 162 | DEST | 23:59 |HR: | 11 | |0.5s|BNR | | | | ETA | 1 MIN |MIN | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 163 | ALT | 23:59 |HR: | 11 | |0.5s|BNR | | | | WAYPNT | 1 MIN |MIN | | | | | | | | ETA | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | VERTICAL | +/-32768 | Ft/| | | | | | | 165 | VELOCITY | 1.0 | Mn | 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | N/S | +/-4096 | | | | | | | | 166 | VELOCITY | 0.125 | Kts| 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | E/W | +/-4096 | | | | | | | | 174 | VELOCITY | 0.125 | Kts| 15 | | 1s |BNR | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 226 | DATA | N/A |N/A |N/A | |N/A |ISO | | | | LOADER | | | | | |#5 | | |--------------|----------|------------|----|----|----|----|----|-------------| | |HORIZONTAL| 16 | | | | | | | | 247 | FIGURE | 6.1E-5 | NM | 18 | | 1s |BNR | | | | OF MERIT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | | N/A |DAY:| | | | | |

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 12 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 260 | DATE | 1 Day |MON:| 6 | | 1s |BCD | | | | | |YEAR| | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | GPS | | | | | | | | | 273 | SENSOR | N/A |N/A |N/A | | 1s |DISC| | | | STATUS | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 343 | DEST | 16 |NM | 11 | |0.5s|BNR | | | | HIL | 0.0078 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | ALT | | | | | | | | | 347 | WAYPNT | 16 |NM | 11 | |0.5s|BNR | | | | HIL | 0.0078 | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 354 | GPSSU | N/A |N/A |N/A | | |ISO | | | | IDENT | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | 356 | MAINT | N/A |N/A |N/A | | |ISO | | | | DATA | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-------------| | | EQUIP| | | | | | | | | 377 | MENT | N/A |N/A |N/A | | 1s |BCD | | | | ID | | | | | | | | ------------------------------------------------------------------------------6. _____________________ Component Description A. MMR (1) External description (Ref. Fig. 004) The face of the MMR is fitted with a handle, two attaching parts, a TEST pushbutton switch and four Light Emitting Diodes (LED). The four LEDs have the following name, color and function: - TEST OK (green) indicates that no fault is detected during the initiated (by pushbutton switch or by MCDU) self-test or during the power-up test.

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 13 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - External Description Figure 004   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 14 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

- MMR FAULT (red) indicates that an internal fault is detected by the MMR itself. - BUS IN FAIL (red) indicates that no control input is available. - TEST ANT (red) indicates that a failed antenna (or coaxial cable) is detected. The back of the MMR is equipped with one ARINC 600 size one connector, which includes three plugs: - Top Plug (TP): connection with the GPS antenna - Middle Plug (MP): service interconnection - Bottom Plug (BP): connection with the power supply circuit, and the LOC and G/S coaxial interconnections. (2) Internal description (Ref. Fig. 005) The MMR includes: - an ILS RF module (RF) - a main ILS board (CMD) - a monitor ILS board (MON) - a GPS board (GPS) - a power supply module (POWER SUPPLY) - a High Intensity Radiated Field interconnect module (HIRF). The primary function of the MMR is to receive and process ILS and GPS signals. The ILS signals, including both localizer and glide slope, are used to determine flight path deviations during precision approach and landing, and are supplied to the aircraft flight control and instrument systems. These deviations are based on radio frequency signals that the unit receives from a ground-based instrument landing system. The GPS receiver simultaneously tracks signals from up to fifteen GPS satellites. The signals are processed to generate a three-dimensional position and a precise time. The receiver generates an estimate of the positional accuracy provided. An integrity alert is activated if an unannounced satellite malfunction is detected. The receiver has the capability of excluding satellites that are malfunctioning. It is able to incorporate external altimeter data to improve the availability of its integrity monitoring functions. (a) ILS RF module (RF) This module converts (filters, amplifies and demodulates) the RF signals received by the localizer and glide slope antennas into analog signals for processing by the Digital Signal Processor (DSP). The module consists of two RF sections, one for the VHF localizer signals and one for the UHF glide slope signals.

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MMR - Block Diagram Figure 005   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 16 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

(b) Main ILS board (CMD) The main ILS board controls the ILS mode of operation, generates the audio and deviation outputs, controls the aircraft interfaces and performs the maintenance tasks (for CFDIU interface). The board is divided into five sections: - A/D converter (ADC) which digitizes the localizer and glide slope signals from the ILS RF module. - DSP section which formats and sends to the Precision Approach Navigator (PAN) the deviations computed with the depth of modulation of the 90Hz and 150Hz. - PAN section which processes the data from the DSP section to provide the localizer and glide slope deviation information to the Input/Output section (I/O). The PAN compares information from the monitor ILS board with the information it has calculated itself. The PAN sends to the maintenance section the in-line test (BIT) results from all the boards installed in the MMR (RF, CMD, MON, GPS and POWER SUPPLY). - maintenance section which provides the interface with the Centralized Fault Display Interface Unit (CFDIU). - I/O section which consists of ARINC 429 drivers and receivers and discrete I/O logic. The I/O section provides the interface with aircraft systems. ARINC 429 inputs/outputs are processed by a specially designed ASIC (GLUCOMA). (c) Monitor ILS board (MON) The monitor ILS board provides a redundant dissimilar signal processing path for the localizer and glide slope signals from the ILS RF module. It also includes an ADC, a DSP, a PAN and an I/O section (as CMD). In order to determine if the main ILS board (CMD) operates properly, the MON PAN calculates the deviation outputs and compares the results against those being transmitted over the ARINC 429 ILS output ports. If the calculations from the two PANs are excessively different, the MON PAN asks the CMD PAN to set the deviation words to indicate failure. The MON PAN shuts down the output buses if the SSM of the output words does not indicate failure when required. (d) GPS Board (GPS) The GPS board receives RF signals through an active GPS antenna, filters, mixes, and performs analog-to-digital conversion and outputs position, velocity, time and integrity data. It also outputs a time mark discrete signal to synchronize users with the raw data sent by this board. The GPS board is divided into four sections:

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- RF section which filters and mixes the RF signal. - ASIC GNSS which processes the signals from the RF section. - Processor section which performs position, velocity, time (PVT) and integrity calculation with data received from ASIC GNSS. It also provides satellite information to I/O section. - I/O section which consists of ARINC 429 drivers and receivers and discrete I/O logic. It provides PVT, integrity and satellite information with aircraft systems. ARINC 429 inputs/outputs are processed by a specially designed ASIC (GLUCOMA). (e) Power supply module (POWER SUPPLY) The power supply module generates, from 115VAC/400HZ single phase, four regulated power supplies required for operation of the modules and boards (+12VDC, +5VDC, +15VDC, -15VDC). This module protects the secondary power supply voltages against short-circuits and spikes, makes primary power supply micro-interrupts transparent and isolates the equipment from the primary power supply. (f) High Intensity Radiated Field interconnect module (HIRF) The HIRF module provides with connection of the different internal modules and connection with the aircraft environment. It protects the MMR against electromagnetic interference, lightning indirect effects and has two filters for the 115VAC/400Hz input power. B. GPS Antenna (Ref. Fig. 006) Two L-Band antennas are mounted on the top of the fuselage, at the centerline, to receive signals from the GPS satellites. The GPS antenna is an active antenna with an integrated preamplifier and filter. It receives GPS signals at 1575.42 MHz and matches to a 50 ohms coaxial cable at the input to the MMR. The antenna has a right-hand circular polarized and omnidirectional radiation pattern. The power supply of the preamplifier is provided by the MMR through the coaxial cable. NOTE : The antenna connectors have a hole to install a lockwire and ____ safety the coaxial cable.

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GPS Active - Antenna Figure 006   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 19 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

C. Localizer Antenna (Ref. Fig. 007) The localizer antenna is an airborne antenna used to receive LOC signals in the 108-112MHz range. It is a folded half-loop type driven by capacitive coupling. The antenna has two independent RF connectors used to feed two independent ILS receivers. Connector separation is provided by a hybrid junction in the antenna. D. Glide Slope Antenna (Ref. Fig. 007) The glide slope antenna is an airborne antenna used to receive GLIDE signals in the 329-335MHz range. It is a folded half-loop type driven by capacitive coupling. The antenna has two independent RF connectors used to feed two independent ILS receivers. Connector separation is provided by a hybrid junction in the antenna.

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ILS Antennas Figure 007   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 21 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

7. Operation _________ A. ILS Operation (1) Normal operation (Ref. Fig. 008) Each MMR is connected to one Radio Management Panel (RMP). The MMR 1 is connected to the RMP 1 (the MMR 2 to the RMP 2). The MMR 1 receives management bus from the FMGC 1 through the RMP 1 (the MMR 2 from the FMGC 2 through the RMP 2). In normal operation, the FMGC 1(2) tunes the MMR 1(2) either automatically or manually by means of the MCDU. In this case the RMP 1(2) operates as a relay which sends the frequency information from the FMGC 1(2) to the receiver 1(2). Via a second port, the MMR 1(2) receives a second management bus (ILS FREQ + RWY HDG) directly from the FMGC 2(1). The receiver selects one of the two input ports according to the FREQ/FUNCT DATA SOURCE SEL discrete signal, which is received from the FMGC 1(2) through the RMP 1(2). (2) Operation in case of failure With failure of one FMGC, the second FMGC automatically controls the two MMRs, the off side directly, the on side through its RMP. With failure of the RMP 1(2) or two RMPs, the RMP concerned is transparent to data and discrete from FMGC. (3) Manual operation In manual operation (at any time, or with failure of two FMGCs) the RMP 1 can control the MMR 1 after ON NAV mode selection. Same possibility for the RMP 2 (MMR 2). (Ref. Fig. 009) In this mode the RMP 1 can control the MMR 2 through the RMP 2 after ON NAV mode selection on the RMP 2. Same possibility for RMP 2 through RMP 1. After any frequency selection it is always necessary to select the associated course. (4) Reconfiguration switching In normal utilization, the ILS 1 data are shown on the CAPT PFD and the F/O ND; the ILS 2 data on the F/O PFD and the CAPT ND. The DMC 1 supplies data to the CAPT PFD and ND; the DMC 2 to the F/O PFD and ND. With failure of the DMC 1(2) it is possible to switch over to the DMC 3 with the EIS DMC selector switch located on the panel 8VU on the center pedestal.

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MMR - Control and Indicating Figure 008   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 23 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - ILS - Course and Frequency Selection in Manual Mode Figure 009   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 24 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

In this case, the DMC 3 totally replaces the DMC 1(2) through the stage of the output switching relay of the failed DMC. With failure of the PFD, there is an automatic transfer of the PFD image onto the ND. With failure of the CAPT (F/O) ND, you obtain the transfer of the ND image onto the CAPT (F/O) PFD when you push the PFD/ND XFR pushbutton switch on panel 301VU (500VU). When you set the PFD potentiometer to OFF on the panel 301VU (500VU) this causes: - deactivation of the CAPT (F/O) PFD - transfer of the PFD image onto the CAPT (F/O) ND. (5) Audio control The MMR applies its audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loudspeakers. The Audio Management Unit (AMU) controls the audio level through the ACP. On the ACP, the pilot must push the ILS pushbutton switch and adjust the related potentiometer to the correct audio level. With ILS/DME collocated stations, the DME identification morse code can be listened in sequence with the ILS audio signal when you push the ILS pushbutton switch on the ACP and the ILS pushbutton switch on the Flight Control Unit (FCU). (6) Data display (Ref. Fig. 010) (a) On the PFDs On the right and below the attitude sphere, the deviation indications come into view in approach. These are: - the vertical deviation scale - the lateral deviation scale - the related aircraft deviation symbols. If you select an ILS approach, the scales and symbols give GLIDE SLOPE and LOCALIZER deviations. The scales come into view when you push the ILS pushbutton switch on the EFIS control section of the Flight Control Unit (FCU). The deviation symbols come into view when the related G/S and LOC signals from the ILS receiver are valid. If the ILS indications are available with the ILS pushbutton switch pushed, they have priority over the deviation information of the R NAV approach. In this mode, the data given after are shown (item 5): in the left bottom corner: - ILS frequency (plus ILS identification if available) - ILS - DME distance.

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MMR - ILS Data Display Figure 010   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 26 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

At the top section of the PFD, a Flight Mode Annunciator (FMA) shows the various armed/active longitudinal and lateral modes: (item 1): the G/S longitudinal modes are shown in the 2nd column (cyan for armed or green for active) (item 2): the LOC longitudinal modes are shown in the 3rd column (cyan for armed or green for active) VERTICAL DEVIATION (item 3) The vertical scale shows a classical glide slope deviation. It is linear with 2 dots on each side. Two dots correspond to plus (or minus) 0.175 ddm (150 microA) deviation. The index shows magenta G/S indication. Until the glide beam is captured, the glide index is not shown (No Computed Data). When the index is against one stop, only one half of it is in view (the outer half index). The glide slope index and the scale flash permanently in case of G/S excessive deviation warning. With a glide fault, the G/S index goes out of view and a red G/S failure warning message is shown in the middle of the scale. (Ref. Fig. 011) LATERAL DEVIATION (item 4) The horizontal scale shows a classical LOC deviation with 2 dots on each side. Two dots correspond to plus (or minus) 0.155 ddm (150 microA) deviation. The index shows magenta LOC indication. Until the LOC is captured, the LOC index is not shown (No Computed Data). When the index is against one stop, only one half of it is shown. The LOC index and the scale flash permanently in case of LOC excessive deviation warning. With a localizer fault, the LOC index goes out of view and a red LOC failure warning message is shown in the middle of the scale. (Ref. Fig. 010, 011) (b) On NDs in the ROSE ILS mode In the ROSE ILS mode, the ND gives a display which is similar to that of a conventional Horizontal Situation Indicator (HSI): a heading dial orientated to the magnetic North turns and gives the actual magnetic heading of the aircraft in relation to the stable yellow lubber line. The ND is always heading up: A yellow aircraft model, at the center of the heading dial is stable and pointed up to the yellow lubber line. Small white triangles are put each 45 deg. on the circumference in relation to the lubber line. They are stable and do not turn with the heading dial. A green diamond-shaped symbol moves around the heading dial and gives the actual track of the aircraft.

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MMR - ILS Warning Display Figure 011   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 28 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

The ND shows the indications given after, when available, in its right top corner (item 8): - the side of the displayed ILS receiver - the frequency - the course - the identification. The ND shows the ILS APP message in its center top section (item 7) when the pilot has selected the ILS approach on the MCDU. LATERAL DEVIATION (item 6) A dagger-shaped pointer points to the selected ILS course. Its center part is the lateral deviation bar, which can move on a scale which is perpendicular to the pointer and has two dots on each side. The position of the bar on the scale gives the localizer deviation. The extreme dots correspond to plus or minus 0.155 ddm (plus or minus 150 microA). With LOC fault a red LOC warning message comes into view in the middle of the LOC scale and the LOC deviation bar goes out of view. VERTICAL DEVIATION (item 9) A magenta lozenge gives the glide slope deviation on a vertical scale at the right of the heading dial if the aircraft is within the condition of reception of the ILS glide slope signal. The extreme dots of the vertical scale correspond to plus or minus 0.175 ddm (plus or minus 150 microA). With G/S fault, a red G/S warning message comes into view at the top of the scale and the index goes out of view. (c) On NDs in ARC and ROSE NAV modes When you push the ILS pushbutton switch in ARC or ROSE NAV mode, the ND shows the symbols given after (item 11): - a magenta dagger-shaped pointer which points to the selected QFU - an arrow which indicates the lateral deviation of the aircraft related to the localizer axis. (7) Warnings (Ref. Fig. 011) The warnings related to the ILS are: - local warning on the instruments that use the ILS information - MASTER CAUT lights on CAPT and F/O glareshield panels - aural warning: single chime (SC) - warning message shown on the ECAM upper display unit.

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B. GPS Function (1) Normal operation (a) General To reduce initialization time, the MMR 1(2) receives position data, LAT/LONG (labels 310/311) from the ADIRU 1(2) and SET LAT, SET LONG (labels 041, 042) UTC/Date from the FMGC 1(2) through the ADIRU 1(2). Each MMR receives the GPS satellite RF signals from the active antenna to compute and provide the three ADIRUs with: - UTC, date - position, altitude - ground speed, track angle - N/S speed, E/W speed, vertical speed - horizontal and vertical dilution of precision, figure of merit - satellite position - satellite measurement (pseudo-range, delta range, range rate, UTC measurement time) - GPS measurement status, sensor status - real time and predictive integrity data. Within each ADIRU an hybridization function performs the following: - monitoring of the MMR using GPS status word and ADIRU BITE - generation of failure message for ECAM display - use of pseudo-range/delta range data to compute GPS position - use of inertial data to smooth GPS position/velocity - use of a Kalman filter to estimate and minimize errors - use of IR data to improve the robustness of the MMR RAIM algorithm. - transmission of GPS and GPIR data to the FMGC for position fixing and display purposes. (b) GPS primary navigation function principle in the FMGC A navigation mode with the least error is chosen based upon the mixed IR position and the best GPIR or radio position available. NOTE : The GPIR position used by the FMGC to determine the ____ aircraft position is computed in the GPIR partition of the ADIRU (hybrid solution). The FMS mode of navigation is selected according to the following hierarchy: - GPIR/Inertial - DME/DME/Inertial - DME/VOR/Inertial

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- Inertial only. The GPIR/INERTIAL mode is selected as long as the following conditions are satisfied: - GPIR position is available and with an estimated accuracy consistent with the intended operation. - GPIR integrity is available and compatible with the applicable phase of flight requirement. As long as the GPS/INERTIAL mode is active, no DME/DME or VOR/DME radio updating is allowed. However, LOC updating can apply to GPS/INERTIAL position. In this navigation mode, N IR/GPS indication is displayed on the POSITION MONITOR page with N being the number of IRs used to compute mixed IR position. The selected hybrid GPIRS position is displayed on the POSITION MONITOR page in place of the radio position. The mixed IR position and the IR deviations displayed on the POSITION MONITOR page do not change and are still computed using pure IR inputs. Aircraft position is generated by a series of filters which use inertial position, GPIR position or radio position, and aircraft velocity as input. A position bias is computed once every second through the position bias filter. This position bias is computed as the difference between the GPIR position (or radio position) and the inertial position. The aircraft position is finally computed every 200 ms based on the corrected inertial position and the aircraft velocity using the aircraft position filter. The GPS/INERTIAL mode can be manually inhibited by pushing the line key adjacent to the DESELECT GPS indication on the SELECTED NAVAIDS page. (Ref. Fig. 012) FMGC computed integrity: When the GPIR position is available in the FMGC but the GPIR integrity is not delivered by the ADIRS, the FMGC is capable of computing an equivalent integrity called AIM (Alternate Integrity Monitoring), using IR data, during a limited period of time. The goal of this FMGC functionality is to improve the availability of the GPS Primary function in the cockpit. (c) Clock synchronization on GPS time 1 _

If a GPS signal is present and valid when the power is on, the clock synchronizes on the GPS time using labels 150 and 260.

2 _

If the signal is not present during synchronization, the clock displays dashes on all the digits.

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MMR - GPS SELECTED NAVAIDS Page on MCDU Figure 012   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 32 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

3 _

If the signal is present but not valid during synchronization, the clock indicates 00:00:00.

4 _

If the signal becomes not valid after synchronization, the clock runs on its internal time base.

(d) Display of GPS data on MCDU 1 _

GPS MONITOR (Ref. Fig. 013) The GPS data are displayed on the GPS MONITOR page of the MCDU. To get the GPS MONITOR page, push the DATA key on the MCDU, then the line key adjacent to the GPS MONITOR indication. The upper part is dedicated to GPS 1 data, the lower part to GPS 2 data. The following data are displayed: - GPS position (lat/long) - true track - GPS altitude - figure of merit (in meters) - ground speed - number of satellites tracked - mode.

2 _

PREDICTIVE GPS (Ref. Fig. 014) The integrity prediction results given by the GPS portion of the MMR on Flight Management System (FMS) request are displayed on the PREDICTIVE GPS page of the MCDU (from the progress page which displays required navigation accuracy and estimated position accuracy and GPS PRIMARY indication). The prediction concerns the destination (DEST) and any pilot entered waypoint (WPT) and the integrity availability (HIL < 0.3 Nm) is displayed by Yes (Y) or No (N) for the seven times defined by the five minutes increments for plus or minus 15 minutes around DEST or WPT.

3 _

Progress page The progress page indicates whether the GPS is used by the FMGC for navigation. If it is used, the GPS PRIMARY indication is displayed. If it is not used, the GPS PRIMARY LOST message is shown.

4 _

MCDU scratchpad GPS PRIMARY in white or GPS PRIMARY LOST in amber show on the MCDU scratchpad.

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GPS - GPS MONITOR Page on MCDU Figure 013   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 34 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

GPS - PREDICTIVE GPS Page on MCDU Figure 014   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 35 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

5 _

SELECTED NAVAIDS page It is possible to select GPS for navigation computation within the FMS on the SELECTED NAVAIDS page. If you deselected GPS, the message GPS IS DESELECTED appears on the MCDU when a GPS approach starts.

6 _

ARRIVAL page To select a GPS approach, use the ARRIVAL page.

(e) Display of GPS messages on ND (Ref. Fig. 015) 1 _

Display of GPS PRIMARY LOST amber message This message is displayed at the bottom of the image in all the ND modes (except engine standby modes) when the GPS primary is lost (this message cannot be cleared from the MCDU). In this case, the GPS is not used for navigation (accuracy and integrity for the intended operation can still be met by the use of alternate navigation means).

2 _

Display of GPS PRIMARY white message This message is displayed at the bottom of the image in all the ND modes (except engine standby modes) when the GPS becomes primary (this message can be cleared from the MCDU).

3 _

Display of GPS APP green message This approach message is displayed at the top of the image in all the ND modes (except engine standby modes) when a GPS approach is selected in the flight plan.

(2) Warning (a) GPS failure The GPSs are monitored by the both FWCs using a status word sent by each GPS. In case of GPS failure, the NAV GPS 1(2) FAULT message is displayed in the lower part of the upper ECAM DU. This message is accompanied by: - activation of the MASTER CAUT lights on the glareshield - aural warning: Single Chime (SC). NOTE : The failure is reminded on the INOP SYSTEM page of the ____ lower ECAM DU. The message displayed is GPS 1(2).

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MMR - GPS Data Displayed on the NDs Figure 015   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 37 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

(b) Loss of the GPS primary navigation When the GPS navigation is lost for any reason, the navigation function is degraded and reverts to the traditional navigation function with IRS positions and radio positions if available (in this case the RNP (Required Navigation Performance) features are still available). Warnings are generated to indicate the loss of GPS PRIMARY navigation: - GPS PRIMARY LOST message on the NDs (cannot be cleared) and MCDU (can be cleared) - in case of GPS non-precision approach, an aural alert is generated (Triple Click). (c) GPS/FMS position disagreement When GPS Primary is active and either FMGC 1 or FMGC 2 latitude (longitude) deviates from either MMR 1 or MMR 2 latitude (longitude) by more than 0.5 Nm, the NAV FMS/GPS POS DISAGREE and A/C POS...........CHECK messages are displayed in amber and cyan respectively on the ECAM DU. These messages are accompanied by: - activation of the MASTER CAUT lights on the glareshield - aural warning: Single Chime (SC).

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8. _____________ BITE Function A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the MMR. The BITE of the MMR is connected to the CFDIU. The BITE: - transmits permanently MMR status and its identification message to the CFDIU - memorizes the failures which occurred during the last 63 flight legs - monitors data inputs from the various peripherals - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the menu mode. (a) Normal mode During the normal mode, the BITE cyclically monitors the status of the MMR. It transmits its information to the CFDIU during the concerned flight. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU by an ARINC 429 message with label 356. (b) Menu mode The menu mode can only be activated on ground. This mode enables communication between the CFDIU and the MMR BITE by means of the MCDU. (Ref. Fig. 016) When you get access to the SYSTEM REPORT/TEST/NAV page, the ILS1 and ILS2 indications can be shown instead of the MMR1 and MMR2 indications. In this case, you must do the following steps: - make sure that the the engines are shut down - open CFDIU SUPPLY circuit breaker 2TW - open CFDIU BACK UP circuit breaker 8TW - make sure that MMR1 and MMR2 circuit breakers, 42RT1 and 42RT2, are closed - wait for 30 seconds then close the CFDIU circuit breakers 2TW and 8TW - wait for 180 seconds then get access to the SYSTEM REPORT/TEST/NAV page.

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MMR - Maintenance Test Procedure Figure 016   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 40 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

All the information displayed on the MCDU during the BITE Test configuration can be printed by the printer (Ref. 31-35-00). The MMR menu mode is composed of: - LAST LEG REPORT (Ref. Fig. 017) This menu contains the fault messages (class 1 internal and external) detected during the last flight. - PREVIOUS LEGS REPORT (Ref. Fig. 018) This report contains the fault messages related to the external or internal failures (class 1) recorded during the previous 63 flight legs. - LRU IDENTIFICATION (Ref. Fig. 017) Allows to display the P/N and the software numbers of the equipment. - GND SCANNING (Ref. Fig. 019) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. - TROUBLE SHOOTING DATA (Ref. Fig. 020) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. - CLASS 3 FAULTS (Ref. Fig. 021) Allows to display the class 3 faults recorded during the last flight leg. - GROUND REPORT (Ref. Fig. 021) Allows to present the class 1 or 3 internal failures detected on ground. - SYSTEM TEST (Ref. Fig. 022, 023) Allows a check of the correct operation of the MMR. (2) List of components All the components are listed in Para. 2. Component Location.

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MMR - Last Leg Report and LRU Identification Figure 017   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 42 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - Previous Legs Report Figure 018   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 43 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - Ground Scanning Figure 019   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 44 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - Trouble Shooting Data Figure 020   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 45 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - Last Leg Class 3 Faults Figure 021   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 46 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - System Test Figure 022   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 47 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - System Test Figure 023   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 48 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

(3) Reporting function The tables below give the list of internal/external failures. (a) Internal failure: ----------------------------------------------------------------------------I ATA I CLASS I MESSAGE I I I (A/C) I I I---------------------------------------------------------------------------I 34-36-31 I 1 I MMRi (40RTi) I I 34-36-11 I 1 I LOCALIZER ANTENNA (3RT)/COAX CABLE/MMRi(40RTi) I I 34-36-18 I 1 I GLIDE ANTENNA (4RT)/COAX CABLE/MMRi (40RTi) I I 34-36-16 I 1 I GPS ANTENNAi (43RTi)/COAX CABLE/MMRi(40RTi) I I I I i = (1,2) I ----------------------------------------------------------------------------(b) External failure: ----------------------------------------------------------------------------I ATA I CLASS I MESSAGE I I I (A/C) I I ----------------------------------------------------------------------------I 31-32-34 I 3 I CFDIU (1TW)/MMRi (40RTi) I I 22-83-34 I 3 I FMGCi (1CAi)/RMPi (1RGi)/MMRi (40RTi) I I 22-83-34 I 3 I FMGCj (1CAj) BUS ILS/MMRi (40RTi) I I 22-83-34 I 3 I FMGC1 (1CA1) BUS GPS/MMRi (40RTi) I I 22-83-34 I 3 I FMGC2 (1CA2) BUS GPS/MMRi (40RTi) I I 34-12-34 I 3 I ADIRUk (1FPk)/MMRi (40RTi) I I 32-31-71 I 3 I LGCIUi (5GAi)/FMGCi (1CAi)/MMRi (40RTi) I I 31-62-34 I 1 I DMCi (1WTi)/MMRi (40RTi) I I I I j,i = (1,2) or (2,1) I I I I k = 1, 2 or 3 I -----------------------------------------------------------------------------

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 49 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

(4) Interactive function To gain access to the BITE, it is necessary to use one MCDU (Ref. 22-82-00). (Ref. Fig. 017, 018, 019, 020, 021, 022, 023, 024) All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00).

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 50 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

MMR - Ground Report Figure 024   R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 51 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

ILS - ADJUSTMENT/TEST _____________________ TASK 34-36-00-740-002 BITE Test of the ILS WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. R R

NOTE : If you have a COLLINS ILS-720 receiver, you must do the BITE test of the ____ ILS two times (one immediately after the other). 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-002 34-10-00-860-004 34-36-00-991-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Stop Procedure IR Alignment Procedure Fig. 501

3. __________ Job Set-up Subtask 34-36-00-860-054 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

  EFF : 001-004, 051-060,  34-36-00 Page 501   Config-1 Aug 01/08  CES

 

(3) On the center pedestal, on the RMP1 and RMP2: - set the ON/OFF switch to ON. - push the NAV and then the ILS pushbutton switches (the green LEDs on these pushbutton switches come on). - on the RMP1 or RMP2: set a non local frequency of the ILS1 (ILS2) beacon. (Ref. Fig. 501/TASK 34-36-00-991-001) Subtask 34-36-00-865-057 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/ILS/1 1RT1 G12 121VU COM NAV/ILS/2 1RT2 K09 4. Procedure _________ NOTE : The ILS1 shows indications on the CAPT PFD and the F/O ND. The ILS2 ____ shows indications on the F/O PFD and the CAPT ND. Subtask 34-36-00-740-051 A. BITE Test of the ILS ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the CAPT and F/O EFIS control sections of the FCU: - push the ILS pushbutton switches.

On the CAPT and F/O PFDs: - the LOC and G/S scales come into view.

- set the mode selector switches to ROSE/ILS.

On the CAPT and F/O NDs: - the LOC and G/S scales and the course pointer come into view.

2. On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010).

  R EFF : 001-004, 051-060,  34-36-00 Page 502   Config-1 May 01/05  CES

 

ILS - Frequency and Course Selection Figure 501/TASK 34-36-00-991-001   R EFF : 001-004, 051-060,  34-36-00 Page 503   Config-1 May 01/05  CES

 

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the ILS1 (ILS2) page comes into view. the ILS1 (ILS2) indication. - push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (page 1 to 3).

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 20S indication comes into view. - a fault indication comes into view for approximately 3 seconds. - on the CAPT (F/O) PFD: . the LOC scale goes out of view. . the LOC flag replaces the scale. . the G/S scale goes out of view. . the G/S flag comes into view on the right side of the sphere. . the ILS1 (ILS2) flag comes into view in the left lower corner. - On the F/O (CAPT) ND: . the LOC scale stays in view. . the LOC flag comes into view in the middle of the heading dial. . the G/S scale stays in view. . the G/S flag comes into view in the middle of the scale. . the ILS1 (ILS2) flag comes into view in the right upper corner. - On the glareshield: . the MASTER CAUT lights come on. - On the upper ECAM display unit: * the NAV ILS 1(2) FAULT indication comes into view. - In the loud speakers: . you can hear the single chime. An NCD indication comes into view for approximately 2 seconds: - On the CAPT (F/O) PFD: . the LOC flag goes out of view. . the LOC scale comes into view. . the G/S flag goes out of view. . the G/S scale comes into view. . the ILS1 (ILS2) flag goes out of view.

  R EFF : 001-004, 051-060,  34-36-00 Page 504   Config-1 May 01/05  CES

 

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------. the LOC and G/S indexes are centered. - On the F/O (CAPT) ND: . the LOC flag goes out of view. . the G/S flag goes out of view. . the ILS1 (ILS2) flag goes out of view. . the LOC deviation bar and the G/S index are centered. - On the glareshield: . the MASTER CAUT lights go off. - On the upper ECAM display unit: . the NAV ILS 1(2) FAULT indication goes out of view. A deviation up and to the left side comes into view for approximately 3 seconds: - On the CAPT (F/O) PFD: . the LOC index moves 1 point to the left. . the G/S index moves up 1 point. - On the F/O (CAPT) ND: . the LOC deviation bar moves 1 point to the left. . the G/S index moves up 1 point. A deviation down and to the right side comes into view for approximately 3 seconds: - On the CAPT (F/O) PFD: . the LOC index moves 1 point to the right. . the G/S index moves down 1 point. - On the F/O (CAPT) ND: . the LOC deviation bar moves 1 point to the right. . the G/S index moves down 1 point. At the end of the test: - On the CAPT (F/O) PFD: . the LOC and G/S indexes go out of view. - On the F/O (CAPT) ND: . the LOC deviation bar and the G/S index go out of view. 3. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - the TEST OK indication comes into view.

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5. Close-up ________ Subtask 34-36-00-860-055 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) On the CAPT and F/O EFIS control sections of the FCU, release the ILS pushbutton switches. (3) On the center pedestal, on the RMP1 (RMP2) : - push the NAV and the ILS pushbutton switches (the green LEDs go off). - set the ON/OFF switch to OFF. (4) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (5) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF. (6) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (7) Make sure that the work area is clean and clear of tool(s) and other items.

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TASK 34-36-00-710-001 Operational Test of the ILS WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Reception Test of the ILS beacon. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-36-00-991-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Fig. 501

3. __________ Job Set-up Subtask 34-36-00-860-050 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to ON. Subtask 34-36-00-865-052 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/ILS/1 1RT1 G12 121VU COM NAV/ILS/2 1RT2 K09

  R EFF : 001-004, 051-060,  34-36-00 Page 507   Config-1 May 01/05  CES

 

4. Procedure _________ Subtask 34-36-00-710-055 A. Operational Test of the ILS ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the RMP1 (RMP2):

On the RMP1 (RMP2):

- push the NAV pushbutton switch.

- the green LED on the NAV pushbutton switch comes on.

- set the local frequency of an ILS 1 (ILS 2) beacon with the dual selector knob . (Ref. Fig. 501/TASK 34-36-00991-001)

- the set frequency comes into view in the right display (STBY/CRS).

- push the transfer (double arrow) pushbutton switch.

- the set frequency comes into view in the left display.

2. On the center pedestal, on one ACP: - release the ILS 1 (ILS 2) pushbutton switch. 3. On the RMP1 (RMP2): - push the NAV pushbutton switch.

- in the loud speakers, you can hear the Morse signal of the station. - On the RMP1 (RMP2): - the green LED on the NAV pushbutton switch goes off.

5. Close-up ________ Subtask 34-36-00-860-051 A. Put the aircraft back to its initial configuration. (1) On the center pedestral, on the RMP1 (RMP2), set the ON/OFF switch to OFF. (2) On the center pedestral, on the ACP, push the ILS1 (ILS2) pushbutton switch.

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(3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Make sure that the work area is clean and clear of tool(s) and other items.

  R EFF : 001-004, 051-060,  34-36-00 Page 509   Config-1 May 01/05  CES

 

TASK 34-36-00-720-001 Functional Test of the ILS WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

VOR-ILS ground test unit

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-002 34-10-00-860-004 34-36-00-991-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Stop Procedure IR Alignment Procedure Fig. 501

3. __________ Job Set-up Subtask 34-36-00-860-052 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

  R EFF : 001-004, 051-060,  34-36-00 Page 510   Config-1 May 01/05  CES

 

(3) On the CAPT and F/O EFIS control sections of the FCU, push the ILS pushbutton switches. Set the mode selector switches to ROSE/ILS. (4) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to ON. Subtask 34-36-00-865-054 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/ILS/1 1RT1 G12 121VU COM NAV/ILS/2 1RT2 K09 Subtask 34-36-00-480-050 C. Install the VOR-ILS ground test unit near the radome. To do this, refer to the installation instructions. Set the ON/OFF switch to ON. 4. Procedure _________ NOTE : The ILS1 shows indications on the CAPT PFD and the F/O ND. The ILS2 ____ shows indications on the F/O PFD and the CAPT ND. Subtask 34-36-00-720-050 A. ILS Reception Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the circuit breaker panel 49VU (121VU): - close the circuit breaker 1RT1 (1RT2).

2. On the RMP1 (RMP2):

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the G/S, LOC and ILS flags go out of view. On the RMP1 (RMP2):

  R EFF : 001-004, 051-060,  34-36-00 Page 511   Config-1 May 01/05  CES

 

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the NAV pushbutton switch. - the green LED on the NAV pushbutton switch comes on. - set the frequency related to the signal given by the ground test unit (Ref. Fig. 501/TASK 34-36-00991-001)

- the set frequency comes into view in the left display.

3. On the ground test unit: - set the LOC and G/S selector switches to 0.

On the CAPT (F/O) PFD: - the G/S and LOC indexes come into view in the middle of the scale. On the F/O (CAPT) ND: - the G/S index and the LOC deviation bar come into view in the middle of the scale.

- set the G/S selector switch to up 1 point then up 2 points.

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the G/S index moves up 1 point then up 2 points.

- set the G/S selector switch to down 1 point then down 2 points.

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the G/S index moves down 1 point then down 2 points.

- set the G/S selector switch to 0.

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the G/S index moves to the middle of the scale.

- set the LOC selector switch to left 1 point then left 2 points.

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the LOC index and deviation bar move 1 point then 2 points to the left side.

- set the LOC selector switch to right 1 point then right 2

On the CAPT (F/O) PFD and the F/O (CAPT) ND:

  R EFF : 001-004, 051-060,  34-36-00 Page 512   Config-1 May 01/05  CES

 

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------points. - the LOC index and deviation bar move 1 point then 2 points to the right side. - set the LOC selector switch to 0.

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the LOC index and deviation bar move to the middle of the scale.

4. On one RMP1 (RMP2): - set the CRS related to the aircraft heading +20⁰, then to the aircraft heading -20⁰.

On the F/O (CAPT) ND: - the aircraft heading +20⁰, then the aircraft heading -20⁰ come into view in the right upper corner. - the course pointer moves to the aircraft heading +20⁰, then to the aircraft heading -20⁰.

5. On the circuit breaker panel 121VU (49VU): - close circuit breaker 1RT2 (1RT1). Subtask 34-36-00-720-051 B. ILS Identification Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the circuit breaker panel 49VU (121VU), close the circuit breaker 1RT1 (1RT2). 2. On the ground test unit, set the IDENT selector switch to ON. 3. On the center pedestal, on one ACP : - release the ILS1 (ILS2) pushbutton switch.

- you can hear the identification signal in the loud speakers.

  R EFF : 001-004, 051-060,  34-36-00 Page 513   Config-1 May 01/05  CES

 

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- adjust slowly and continously until the volume is correct. 5. Close-up ________ Subtask 34-36-00-080-050 A. De-energize the VOR/ILS ground test unit and remove it. Subtask 34-36-00-860-053 B. Put the aircraft back to its initial configuration. (1) On the CAPT and F/O EFIS control sections of the FCU, release the ILS pushbutton switches. (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (3) On the center pedestal, on the RMP1 (RMP2): - push the NAV pushbutton switch (the green LED goes off). - set the ON/OFF switch to OFF. (4) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF. (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (6) Make sure that the work area is clean and clear of tool(s) and other items.

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R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, Post SB

34-1147 For A/C 001-004,051-060, ILS ((MMR)) - ADJUSTMENT/TEST _____________________________

TASK 34-36-00-740-003 BITE Test of the MMR 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 31-60-00-860-002 34-10-00-860-004 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure IR Alignment Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-36-00-861-053 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

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Subtask 34-36-00-860-056 B. Aircraft Maintenance Configuration NOTE : Do this test in an open area (not in the hangar). ____ (1) Do the EIS start procedure (PFD DU, ND DU and upper ECAM DU only) (Ref. TASK 31-60-00-860-001). (2) Align the IRs (Ref. TASK 34-10-00-860-004). (3) On the center pedestal, on the RMP1 and RMP2: - set the ON/OFF switch to ON - push the NAV and the ILS pushbutton switches (4) On the RMP1 or RMP2: - set a non local ILS frequency. (5) On the EFIS control panel of the FCU: - push the ILS pushbutton switch (6) Do the procedure to get the SYSTEM REPORT/TEST NAV page (Ref. TASK 31-32-00-860-010). If the SYSTEM REPORT/TEST/NAV page shows the ILS1 and ILS2 indications but not the MMR1 and MMR2 indications, you must do the steps that follow: - make sure that the engines are shut down - open CFDIU SUPPLY circuit breaker 2TW - open CFDIU BACK UP circuit breaker 8TW - make sure that MMR1 and MMR2 circuit breakers, 42RT1 and 42RT2, are closed - after 30 seconds, close CFDIU circuit breakers 2TW and 8TW - after 180 seconds, get access to the SYSTEM REPORT/TEST/NAV page (the MMR indications are shown).

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Subtask 34-36-00-865-058 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FMGC/1 10CA1 B02 49VU COM/RMP/1 2RG1 G10 49VU NAV/MMR/1 42RT1 G12 121VU COM NAV/RMP/2 2RG2 L02 121VU AUTO FLT/FMGC/2 10CA2 M17 R

**ON A/C 062-099, 106-149, 151-199, 204-238, 301-311, 401-499, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2 R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, 4. Procedure _________

R

**ON A/C 051-099, Subtask 34-36-00-740-052-A A. BITE Test of the MMR NOTE : the MMR1 shows indications on the CAPT PFD. ____ The MMR2 shows indications on the F/O PFD. This test is for the MMR1. For the MMR2 use the indications between the parentheses.

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the MMR1 (MMR2) indication.

- the MMR1 (MMR2) page comes into view.

- push the line key adjacent to the SYSTEM TEST indication.

- the MMR1 (MMR2) TEST 1/3 page with instructions comes into view.

- push the NEXT PAGE key.

- the MMR1 (MMR2) TEST 2/3 page with instructions comes into view.

- push the NEXT PAGE key.

- the MMR1 (MMR2) TEST 3/3 page with instructions comes into view.

- push the line key adjacent to the START TEST indication.

- On the MCDU, the TEST IN PROGRESS 16S indication comes into view. - On the CAPT (F/O) PFD: the LOC and G/S scales go out of view, the LOC and G/S red warnings come into view for some seconds, the MASTER CAUT lights come on and the single chime sounds, the LOC and G/S scales come into view, the G/S index comes into view, moves up, moves down, then goes out of view, and simultaneously, the LOC index comes into view, moves to the left then to the right, then goes out of view, the MASTER CAUT lights go off and the single chime stops.

- push the line key adjacent to the YES indication.

- the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication.

- the TEST CLOSE-UP indication comes into view.

- push the line key adjacent to the RETURN indication.

- the test procedure stops.

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R

**ON A/C 001-049, 101-149, 151-199, 201-238, 301-311, 401-499, Subtask 34-36-00-740-052 A. BITE Test of the MMR NOTE : the MMR1 shows indications on the CAPT PFD. ____ The MMR2 shows indications on the F/O PFD. This test is for the MMR1. For the MMR2 use the indications between the parentheses. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the MMR1 (MMR2) indication.

- the MMR1 (MMR2) page comes into view.

- push the line key adjacent to the SYSTEM TEST indication.

- the MMR1 (MMR2) TEST 1/3 page with instructions comes into view.

- push the NEXT PAGE key.

- the MMR1 (MMR2) TEST 2/3 page with instructions comes into view.

- push the NEXT PAGE key.

- the MMR1 (MMR2) TEST 3/3 page with instructions comes into view.

- push the line key adjacent to the START TEST indication.

- On the MCDU, the TEST IN PROGRESS 20S indication comes into view. - On the CAPT (F/O) PFD: the LOC and G/S scales go out of view, the LOC and G/S red warnings come into view for some seconds, the MASTER CAUT lights come on and the single chime sounds, the LOC and G/S scales come into view, the G/S index comes into view, moves up, moves down, then goes out of view, and simultaneously, the LOC index comes into view, moves to the

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------left then to the right, then goes out of view, the MASTER CAUT lights go off and the single chime stops.

R

- push the line key adjacent to the YES indication.

- the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication.

- the TEST CLOSE-UP indication comes into view.

- push the line key adjacent to the RETURN indication.

- the test procedure stops.

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, 5. Close-up ________ Subtask 34-36-00-860-057 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (2) On the RMP1 or on the RMP2, set the ON/OFF switch to OFF. (3) On the EFIS control panel of the FCU, release the ILS pushbutton switch. (4) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (5) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (6) On the MCDU, fully decrease the brightness of the MCDU screen (display off). Subtask 34-36-00-862-053 B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

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TASK 34-36-00-710-002 Operational Test of the GPS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-10-00-860-004

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power IR Alignment Procedure

3. __________ Job Set-up Subtask 34-36-00-860-058 A. Aircraft Maintenance Configuration NOTE : Do this test in an open area (not in the hangar). ____ (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (3) On the center pedestal, on the SWITCHING panel 8VU, make sure that the ATT HDG selector switch is at NORM.

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Subtask 34-36-00-865-059 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/MMR/1 42RT1 G12 R

**ON A/C 062-099, 106-149, 151-199, 204-238, 301-311, 401-499, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2 R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, 4. Procedure _________ Subtask 34-36-00-710-056 A. Operational Test of the GPS NOTE : The actions and the results of this procedure occur on the MCDU ____ used. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------Test of GPS data acquisition with IRS aligned 1. On the MCDU: - push the DATA mode key.

On the MCDU: - the DATA INDEX page comes into view.

2. On the MCDU, on the DATA INDEX page: - push the line key adjacent to the GPS MONITOR indication.

On the MCDU: - the GPS MONITOR page comes into view: NOTE : If you do this test after ____ replacement of the MMR, one minute to twenty minutes are

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------necessary to get the GPS data on the MCDU. - the NAV indication is shown below the MODE indication - the number of satellites tracked is shown below the SAT indication - the related values come into view below the GPS POSITION, GPS ALT, MERIT and GS indications: . the GPS 1 and the GPS 2 POSITION indications give the latitude/longitude of the aircraft - make sure that the values of the two GPS positions are approximately the same. On CAPT and F/O NDs: - the white GPS PRIMARY indication comes into view 3. On the overhead panel, on the ADIRS CDU: - set the DISPLAY DATA selector switch to PPOS.

On the MCDU, on the GPS MONITOR page: - make sure that the GPS position data are approximately the same as the ADIRS position data on the ADIRS CDU.

4. Open the circuit breakers 42RT1 and 42RT2.

On the upper ECAM DU: - the NAV GPS 1 FAULT and NAV GPS 2 FAULT warnings come into view (the NAV ILS 1 FAULT and NAV ILS 2 FAULT are shown too). On the MCDU, on the GPS MONITOR page: . all GPS data below the GPS POSITION, GPS ALT, TTRK, GS and MERIT indications for the two GPS, are cleared. On CAPT and F/O NDs: - the amber GPS PRIMARY LOST indication is shown. NOTE : It is possible that the GPS ____ PRIMARY LOST indication will not come into view immediately after

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------you open the circuit breakers 42RT1 and 42RT2. It can be as much as 60 minutes before the indication comes into view. It is not necessary to wait for the GPS PRIMARY LOST indication to come into view (this indication is not important for the test). 5. Close the circuit breakers 42RT1 and 42RT2.

On the upper ECAM DU: - the NAV GPS 1 FAULT and NAV GPS 2 FAULT warnings go out of view (the NAV ILS 1 FAULT and NAV ILS 2 FAULT warnings go out of view too).

6. On the MCDU, on the GPS MONITOR page: - the INIT indication comes into view below the MODE indication for some seconds - then the ACQ indication comes into view below the MODE indication - the number below the SAT indication increases (number of satellites tracked) - after 75 to 300 seconds, the ACQ indication goes out of view and the NAV indication comes into view below the MODE indication - the related values come into view below the GPS POSITION, GPS ALT, MERIT and GS indications.

On CAPT and F/O NDs: - the amber GPS PRIMARY LOST indication goes out of view - the white GPS PRIMARY indication comes into view.

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Subtask 34-36-00-710-059 B. Operationnal test of the predictive GPS (with Honeywell ADIRU only) NOTE : The actions and the results of this procedure occur on the MCDU ____ used. NOTE : This test concerns system 1. For system 2, use the indications ____ between parentheses. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------Test of the GPS operation through the PREDICTIVE GPS page on the MCDU 1. Open the circuit breaker 42RT2 (42RT1). 2. On the MCDU1 (MCDU2): - push the INIT mode key

On the MCDU1 (MCDU2): - the INIT page comes into view

- enter origin/destination airport data that are in the database.

- the origin/destination airport data come into view on the bottom line of the INIT page

- push the line key adjacent to the FROM/TO indication

- the RTE SELECTION page comes into view

- push the line key adjacent to the RETURN indication

- the INIT page comes into view

3. On MCDU1 (MCDU2): - push the PROG mode key. - push the line key adjacent to the PREDICTIVE GPS indication

On MCDU1 (MCDU2): - the PROGRESS page comes into view - the PREDICTIVE GPS page comes into view - the destination is displayed below the DEST indication

- enter GMT plus 1 hour below the ETA indication (Estimated Time of Arrival).

- after some seconds, the Y or N indication comes into view below the -15, -10, -5, ETA, +5, +10, +15 indications.

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------4. Close the circuit breaker 42RT2 (42RT1). 5. Close-up ________ Subtask 34-36-00-860-059 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the MCDU MENU page. (2) On the ADIRS CDU, set the 3 OFF/NAV/ATT selector switches to OFF. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

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TASK 34-36-00-710-003 Operational Test of the ILS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power

3. __________ Job Set-up Subtask 34-36-00-860-060 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to ON.

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Subtask 34-36-00-865-060 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/MMR/1 42RT1 G12 R

**ON A/C 062-099, 106-149, 151-199, 204-238, 301-311, 401-499, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2 R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, 4. Procedure _________ Subtask 34-36-00-710-057 A. Operational Test of the ILS ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the RMP1 (RMP2):

On the RMP1 (RMP2):

- push the NAV pushbutton switch.

- the green LED on the NAV pushbutton switch comes on.

- set the local frequency of an ILS 1 (ILS 2) beacon with the dual selector knob.

- the set frequency comes into view in the right display (STBY/CRS).

- push the transfer (double arrow) pushbutton switch.

- the set frequency comes into view in the left display.

2. On the center pedestal, on one ACP:

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- release the ILS 1 (ILS 2) - in the loud speakers, you can hear pushbutton switch. the Morse signal of the station. 3. On the RMP1 (RMP2): - push the NAV pushbutton switch.

- On the RMP1 (RMP2): - the green LED on the NAV pushbutton switch goes off.

5. Close-up ________ Subtask 34-36-00-860-061 A. Put the aircraft back to its initial configuration. (1) On the center pedestral, on the RMP1 (RMP2), set the ON/OFF switch to OFF. (2) On the center pedestral, on the ACP, push the ILS1 (ILS2) pushbutton switch. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Make sure that the work area is clean and clear of tool(s) and other items.

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TASK 34-36-00-720-002 Functional Test of the ILS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

VOR-ILS ground test unit

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-002 34-10-00-860-004

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Stop Procedure IR Alignment Procedure

3. __________ Job Set-up Subtask 34-36-00-869-063 A. General (1) Use the VOR/ILS Ramp Test Set NAV401L or equivalent. Subtask 34-36-00-860-062 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

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(3) On the CAPT and F/O EFIS control sections of the FCU, push the ILS pushbutton switches. Set the mode selector switches to ROSE/ILS. (4) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to ON. Subtask 34-36-00-865-061 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/MMR/1 42RT1 G12 R

**ON A/C 062-099, 106-149, 151-199, 204-238, 301-311, 401-499, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2 R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, Subtask 34-36-00-480-051 D. Install the VOR-ILS ground test unit near the radome. To do this, refer to the installation instructions. Set the ON/OFF switch to ON.

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4. Procedure _________ Subtask 34-36-00-720-052 A. ILS Reception Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the circuit breaker panel 49VU (121VU): - close the circuit breaker 42RT1 (42RT2).

2. On the RMP1 (RMP2):

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the G/S, LOC and ILS flags go out of view. On the RMP1 (RMP2):

- push the NAV pushbutton switch.

- the green LED on the NAV pushbutton switch comes on.

- set the frequency related to the signal given by the ground test unit

- the set frequency comes into view in the left display.

3. On the ground test unit: - set the LOC and G/S selector switches to 0.

On the CAPT (F/O) PFD: - the G/S and LOC indexes come into view in the middle of the scale. On the F/O (CAPT) ND: - the G/S index and the LOC deviation bar come into view in the middle of the scale.

- set the G/S selector switch to up 1 point then up 2 points.

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the G/S index moves up 1 point then up 2 points.

- set the G/S selector switch to down 1 point then down 2 points.

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the G/S index moves down 1 point then down 2 points.

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set the G/S selector switch to On the CAPT (F/O) PFD and the F/O 0. (CAPT) ND: - the G/S index moves to the middle of the scale. - set the LOC selector switch to left 1 point then left 2 points.

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the LOC index and deviation bar move 1 point then 2 points to the left side.

- set the LOC selector switch to right 1 point then right 2 points.

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the LOC index and deviation bar move 1 point then 2 points to the right side.

- set the LOC selector switch to 0.

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the LOC index and deviation bar move to the middle of the scale.

4. On one RMP1 (RMP2): - set the CRS related to the aircraft heading +20⁰, then to the aircraft heading -20⁰.

On the F/O (CAPT) ND: - the aircraft heading +20⁰, then the aircraft heading -20⁰ come into view in the right upper corner. - the course pointer moves to the aircraft heading +20⁰, then to the aircraft heading -20⁰.

5. On the circuit breaker panel 121VU (49VU): - close circuit breaker 42RT2 (42RT1).

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Subtask 34-36-00-720-053 B. ILS Identification Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the circuit breaker panel 49VU (121VU), close the circuit breaker 42RT1 (42RT2). 2. On the ground test unit, set the IDENT selector switch to ON. 3. On the center pedestal, on one ACP : - release the ILS1 (ILS2) pushbutton switch.

- you can hear the identification signal in the loud speakers.

- adjust slowly and continously until the volume is correct. 5. Close-up ________ Subtask 34-36-00-080-051 A. De-energize the VOR/ILS ground test unit and remove it. Subtask 34-36-00-860-063 B. Put the aircraft back to its initial configuration. (1) On the CAPT and F/O EFIS control sections of the FCU, release the ILS pushbutton switches. (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (3) On the center pedestal, on the RMP1 (RMP2): - push the NAV pushbutton switch (the green LED goes off). - set the ON/OFF switch to OFF. (4) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF. (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

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(6) Make sure that the work area is clean and clear of tool(s) and other items.

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R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1373 For A/C 001-049,101-149,151-199,201-234,236-238,301-307, 401-499, ILS ((MMR)) - ADJUSTMENT/TEST _____________________________ TASK 34-36-00-740-006 BITE Test of the MMR 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure IR Alignment Procedure ADIRS Stop Procedure

31-32-00-860-010 31-60-00-860-001 31-60-00-860-002 34-10-00-860-004 34-10-00-860-005 3. __________ Job Set-up Subtask 34-36-00-861-055

A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

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Subtask 34-36-00-860-082 B. Aircraft Maintenance Configuration NOTE : Do this test in an open area (not in the hangar). ____ (1) Do the EIS start procedure (PFD DU, ND DU and upper ECAM DU only) (Ref. TASK 31-60-00-860-001). (2) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (3) On the center pedestal, on the RMP1 and RMP2: - set the ON/OFF switch to ON - push the NAV and ILS pushbutton switches. (4) On the RMP1 or RMP2: - set a non local ILS frequency. (5) On the CAPT or F/O EFIS control section of the FCU: - push the ILS pushbutton switch. (6) Do the procedure to get the SYSTEM REPORT/TEST NAV page (Ref. TASK 31-32-00-860-010). If the SYSTEM REPORT/TEST/NAV page shows the ILS1 and ILS2 indications but not the MMR1 and MMR2 indications, you must do the steps that follow: - make sure that the engines are shut down - open CFDIU SUPPLY circuit breaker 2TW - open CFDIU BACK UP circuit breaker 8TW - make sure that MMR1 and MMR2 circuit breakers, 42RT1 and 42RT2, are closed - after 30 seconds, close CFDIU circuit breakers 2TW and 8TW - after 180 seconds, the SYSTEM REPORT/TEST/NAV page shows the MMR1 and MMR2 indications.

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Subtask 34-36-00-865-071 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/FMGC/1 10CA1 B02 49VU COM/RMP/1 2RG1 G10 R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1147 For A/C 001-004, 49VU NAV/MMR/1

R R

42RT1

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/RMP/2 121VU AUTO FLT/FMGC/2

R R

G12

2RG2 10CA2

L02 M17

**ON A/C 106-149, 151-199, 204-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 101-105, 201-203, Post SB

34-1147 For A/C 001-004,

121VU COM NAV/MMR/2 R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, 4. Procedure _________ Subtask 34-36-00-740-055 A. BITE Test of the MMR NOTE : The MMR1 shows indications on the CAPT PFD. ____ The MMR2 shows indications on the F/O PFD. This test is for the MMR1. For the MMR2, use the indications between the parentheses.

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the MMR1 (MMR2) indication.

- the MMR1 (MMR2) page comes into view.

- push the line key adjacent to the SYSTEM TEST indication.

- the MMR1 (MMR2) TEST 1/3 page with instructions comes into view.

- push the NEXT PAGE key.

- the MMR1 (MMR2) TEST 2/3 page with instructions comes into view.

- push the NEXT PAGE key.

- the MMR1 (MMR2) TEST 3/3 page with instructions comes into view.

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 20S indication comes into view. On the CAPT (F/O) PFD: - the LOC and G/S scales go out of view, - the LOC and G/S red warnings come into view for some seconds. The MASTER CAUT lights come on and the single chime sounds. On the CAPT (F/O) PFD: - the LOC and G/S scales come into view, - the G/S index comes into view, moves up, moves down, then goes out of view, and at the same time, the LOC index comes into view, moves to the left then to the right, then goes out of view. The MASTER CAUT lights go off and the single chime stops. On the MCDU:

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the TEST OK indication comes into the YES indication. view. - push the line key adjacent to the RETURN indication.

- the TEST CLOSE-UP indication comes into view.

- push the line key adjacent to the RETURN indication.

- the test procedure stops.

5. Close-up ________ Subtask 34-36-00-860-083 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (2) On the RMP1 or RMP2, set the ON/OFF switch to OFF. (3) On the CAPT or F/O EFIS control section of the FCU, release the ILS pushbutton switch. (4) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (5) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (6) On the MCDU, fully decrease the brightness of the MCDU screen (display off). Subtask 34-36-00-862-055 B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

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TASK 34-36-00-710-008 Operational Test of the GPS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power IR Alignment Procedure

34-10-00-860-004 3. __________ Job Set-up Subtask 34-36-00-860-084

A. Aircraft Maintenance Configuration NOTE : Do this test in an open area (not in the hangar). ____ (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (3) On the center pedestal, on the SWITCHING panel 8VU, make sure that the ATT HDG selector switch is at NORM.

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Subtask 34-36-00-865-072 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1147 For A/C 001-004, 49VU NAV/MMR/1

R R

42RT1

G12

**ON A/C 106-149, 151-199, 204-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 101-105, 201-203, Post SB

34-1147 For A/C 001-004,

121VU COM NAV/MMR/2

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 507 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, 4. Procedure _________ Subtask 34-36-00-710-064 A. Operational Test of the GPS NOTE : The actions and the results of this procedure occur on the MCDU ____ used. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------Test of GPS data acquisition with IRS aligned 1. On the MCDU: - push the DATA mode key.

On the MCDU: - the DATA INDEX page comes into view.

2. On the MCDU, on the DATA INDEX page: - push the line key adjacent to the GPS MONITOR indication.

On the MCDU: - the GPS MONITOR page comes into view: NOTE : If you do this test after ____ replacement of the MMR, one minute to twenty minutes are necessary to get the GPS data on the MCDU. - the NAV indication is shown below the MODE indication - the number of satellites tracked is shown below the SAT indication - the related values come into view below the GPS POSITION, GPS ALT, MERIT and GS indications: . the GPS 1 and the GPS 2 POSITION indications give the latitude/longitude of the aircraft - make sure that the values of the two GPS positions are approximately the same. On CAPT and F/O NDs:

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the white GPS PRIMARY indication comes into view. 3. On the overhead panel, on the ADIRS CDU: - set the DISPLAY DATA selector switch to PPOS.

On the MCDU, on the GPS MONITOR page: - make sure that the GPS position data are approximately the same as the ADIRS position data on the ADIRS CDU.

4. Open the circuit breakers 42RT1 and 42RT2.

On the upper ECAM DU: - the NAV GPS 1 FAULT and NAV GPS 2 FAULT warnings come into view (the NAV ILS 1 FAULT and NAV ILS 2 FAULT are also shown). On the MCDU, on the GPS MONITOR page: - all GPS data below the GPS POSITION, GPS ALT, TTRK, GS and MERIT indications for the two GPS, are cleared. On CAPT and F/O NDs: - the amber GPS PRIMARY LOST indication is shown. NOTE : The GPS PRIMARY LOST indication ____ does not come into view immediately after you open the circuit breakers 42RT1 and 42RT2. It can be as much as 60 minutes before the indication comes into view. It is not necessary to wait for the GPS PRIMARY LOST indication to come into view (this indication is not important for the test).

5. Close the circuit breakers 42RT1 and 42RT2.

On the upper ECAM DU: - the NAV GPS 1 FAULT and NAV GPS 2 FAULT warnings go out of view (the NAV ILS 1 FAULT and NAV ILS 2 FAULT warnings also go out of view).

6. On the MCDU, on the GPS MONITOR

On CAPT and F/O NDs:

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------page: - the amber GPS PRIMARY LOST indication - the INIT indication comes into goes out of view view below the MODE indication - the white GPS PRIMARY indication is for some seconds shown. - then the ACQ indication comes into view below the MODE indication - the number below the SAT indication increases (number of satellites tracked) - after 75 to 300 seconds, the ACQ indication goes out of view and the NAV indication comes into view below the MODE indication - the related values come into view below the GPS POSITION, GPS ALT, MERIT and GS indications. Subtask 34-36-00-710-065 B. Operational Test of the Predictive GPS (with Honeywell ADIRU only) NOTE : The actions and the results of this procedure occur on the MCDU ____ used. NOTE : This test is for system 1. For system 2, use the indications ____ between the parentheses. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------Test of the GPS operation through the PREDICTIVE GPS page on the MCDU 1. Open the circuit breaker 42RT2 (42RT1). 2. On the MCDU1 (MCDU2): - push the INIT mode key

On the MCDU1 (MCDU2): - the INIT page comes into view

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- enter origin/destination - the origin/destination airport data airport data that are in the come into view on the bottom line of database. the INIT page - push the line key adjacent to the FROM/TO indication

- the RTE SELECTION page comes into view

- push the line key adjacent to the RETURN indication

- the INIT page comes into view.

3. On the MCDU1 (MCDU2): - push the PROG mode key. - push the line key adjacent to the PREDICTIVE GPS indication

On the MCDU1 (MCDU2): - the PROGRESS page comes into view - the PREDICTIVE GPS page comes into view - the destination is displayed below the DEST indication

- enter GMT plus 1 hour below the ETA indication (Estimated Time of Arrival).

- after some seconds, the Y or N indication comes into view below the -15, -10, -5, ETA, +5, +10, +15 indications.

4. Close the circuit breaker 42RT2 (42RT1). 5. Close-up ________ Subtask 34-36-00-860-085 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the MCDU MENU page. (2) On the ADIRS CDU, set the three OFF/NAV/ATT selector switches to OFF. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  R EFF : 001-049, 101-149, 151-199, 201-234,  34-36-00 Page 511 236-249, 251-299, 301-307, 312-399, 401-499,  Config-3 Feb 01/10 501-509, 511-526, 528-599, CES

 

TASK 34-36-00-710-009 Operational Test of the MMR 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power

3. __________ Job Set-up Subtask 34-36-00-860-086 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to ON.

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Subtask 34-36-00-865-073 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1147 For A/C 001-004, 49VU NAV/MMR/1

R R

42RT1

G12

**ON A/C 106-149, 151-199, 204-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 101-105, 201-203, Post SB

34-1147 For A/C 001-004,

121VU COM NAV/MMR/2 R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, 4. Procedure _________ Subtask 34-36-00-710-066 A. Operational Test of the ILS ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the RMP1 (RMP2):

On the RMP1 (RMP2):

- push the NAV pushbutton switch.

- the green LED on the NAV pushbutton switch comes on.

- set the local frequency of an ILS1 (ILS2) beacon with the dual selector knob.

- the set frequency comes into view in the right display (STBY/CRS).

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the transfer (double - the set frequency comes into view in arrow) pushbutton switch. the left display. 2. On the center pedestal, on one ACP: - release the ILS1 (ILS2) pushbutton switch. 3. On the RMP1 (RMP2): - push the NAV pushbutton switch.

In the loud speakers, you can hear the Morse signal of the station. On the RMP1 (RMP2): - the green LED on the NAV pushbutton switch goes off.

5. Close-up ________ Subtask 34-36-00-860-087 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to OFF. (2) On the center pedestal, on the ACP, push the ILS1 (ILS2) pushbutton switch. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Make sure that the work area is clean and clear of tool(s) and other items.

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TASK 34-36-00-720-006 Functional Test of the MMR 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

VOR-ILS ground test unit

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Stop Procedure IR Alignment Procedure

31-60-00-860-002 34-10-00-860-004 3. __________ Job Set-up Subtask 34-36-00-869-068 A. General

(1) Use the VOR/ILS Ramp Test Set. Subtask 34-36-00-860-088 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

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(3) On the CAPT and F/O EFIS control sections of the FCU, push the ILS pushbutton switches. Set the mode selector switches to ROSE/ILS. (4) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to ON. Subtask 34-36-00-865-074 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1147 For A/C 001-004, 49VU NAV/MMR/1

R R

42RT1

G12

**ON A/C 106-149, 151-199, 204-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 101-105, 201-203, Post SB

34-1147 For A/C 001-004,

121VU COM NAV/MMR/2 R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-36-00-480-055 D. Install the VOR-ILS ground test unit near the radome. To do this, refer to the installation instructions. Set the ON/OFF switch to ON.

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4. Procedure _________ Subtask 34-36-00-720-060 A. ILS Reception Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the circuit breaker panel 49VU (121VU): - close the circuit breaker 42RT1 (42RT2). 2. On the RMP1 (RMP2):

On the CAPT (F/O) PFD and the F/O (CAPT) ND: - the G/S, LOC and ILS flags go out of view. On the RMP1 (RMP2):

- push the NAV pushbutton switch.

- the green LED on the NAV pushbutton switch comes on.

- set the frequency related to the signal given by the ground test unit

- the set frequency comes into view in the left display.

3. On the ground test unit: - set the LOC and G/S selector switches to 0.

On the CAPT (F/O) PFD: - the G/S and LOC indexes come into view in the middle of the scale. On the F/O (CAPT) ND: - the G/S index and the LOC deviation bar come into view in the middle of the scale.

- set the G/S selector switch to up 1 point then up 2 points.

On the CAPT (F/O) PFD and F/O (CAPT) ND: - the G/S index moves up 1 point then up 2 points.

- set the G/S selector switch to down 1 point then down 2 points.

- the G/S index moves down 1 point then down 2 points.

- set the G/S selector switch to 0.

- the G/S index moves to the middle of the scale.

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set the LOC selector switch to - the LOC index and deviation bar move left 1 point then left 2 1 point then 2 points to the left points. side. - set the LOC selector switch to right 1 point then right 2 points.

- the LOC index and deviation bar move 1 point then 2 points to the right side.

- set the LOC selector switch to 0.

- the LOC index and deviation bar move to the middle of the scale.

4. On the RMP1 (RMP2): - set the CRS related to the aircraft heading +20⁰, then to the aircraft heading -20⁰.

On the F/O (CAPT) ND: - the aircraft heading +20⁰, then the aircraft heading -20⁰ come into view in the right upper corner. - the course pointer moves to the aircraft heading +20⁰, then to the aircraft heading -20⁰.

5. On the circuit breaker panel 121VU (49VU): - close the circuit breaker 42RT2 (42RT1). Subtask 34-36-00-720-061 B. ILS Identification Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the circuit breaker panel 49VU (121VU), close the circuit breaker 42RT1 (42RT2). 2. On the ground test unit, set the IDENT selector switch to ON. 3. On the center pedestal, on one ACP:

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- release the LS pushbutton - you can hear the identification switch. signal in the loud speakers. - turn slowly the LS pushbutton switch until the volume is correct. 5. Close-up ________ Subtask 34-36-00-080-055 A. De-energize the VOR/ILS ground test unit and remove it. Subtask 34-36-00-860-089 B. Put the aircraft back to its initial configuration. (1) On the CAPT and F/O EFIS control sections of the FCU, release the ILS pushbutton switches. (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (3) On the center pedestal, on the RMP1 (RMP2): - push the NAV pushbutton switch (the green LED goes off). - set the ON/OFF switch to OFF. (4) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF. (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (6) Make sure that the work area is clean and clear of tool(s) and other items.

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ANTENNA - LOCALIZER (3RT) - REMOVAL/INSTALLATION ________________________________________________ TASK 34-36-11-000-001 Removal of the Localizer Antenna (3RT) CAUTION : MAKE SURE THAT YOU DO NOT DAMAGE THE FUSELAGE WHEN YOU REMOVE THE _______ SCUFF PLATES. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

blanking caps circuit breaker(s) safety clip(s) warning notice access platform 3.5 m (11 ft. 6 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------53-15-11-010-001 34-36-11-991-001

Opening of the Radome 110AL Fig. 401

  EFF : ALL  34-36-11   R  CES

 

Page 401 Aug 01/98

3. __________ Job Set-up Subtask 34-36-11-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-004, 051-060, 49VU NAV/ILS/1 121VU COM NAV/ILS/2

1RT1 1RT2

G12 K09

5SQ1

K13

**ON A/C ALL 121VU COM NAV/RADAR/1 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL Subtask 34-36-11-010-050 B. Get Access (1) In the cockpit, place a warning notice on the center pedestal to tell persons not to operate the weather radar system. (2) Put the access platform in position below the radome in zone 110. (3) Open the radome 110AL (Ref. TASK 53-15-11-010-001)

  EFF : ALL  34-36-11    CES

 

Page 402 Feb 01/10

4. Procedure _________ (Ref. Fig. 401/TASK 34-36-11-991-001) Subtask 34-36-11-020-050 A. Removal of the Localizer Antenna (1) Remove the screws (5). (2) Isolate the antenna (1) from the bulkhead (2). (3) Disconnect the two coaxial connectors (3). (4) Remove and discard the O-ring (4). (5) Remove the localizer antenna (1). (6) Put blanking caps on the disconnected coaxial connectors (3) and (6).

  EFF : ALL  34-36-11   R  CES

 

Page 403 May 01/05

Localizer Antenna Figure 401/TASK 34-36-11-991-001   EFF : ALL  34-36-11   R  CES

 

Page 404 May 01/05

TASK 34-36-11-400-001 Installation of the Localizer Antenna (3RT) WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN. _______ IF YOU DO: - RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH - WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER. R R R

WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

lint free cloth nonmetallic scraper warning notice access platform 3.5 m (11 ft. 6 in.)

  EFF : ALL  34-36-11    CES

 

Page 405 May 01/05

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 05-013 Material No. 09-016 Material No. 09-019 Material No. 11-003

D TV-53-3507/73 RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) USA AMS 3267/3 NO LONGER AVAILABLE (Ref. 20-31-00) USA ASTM D 740 METHYL-ETHYL-KETONE (Ref. 20-31-00)

C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------4

O-ring

34-36-11 01 -010

D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-720-005

R

34-36-00-720-001 34-36-00-720-002 34-36-00-720-006 51-76-11-300-001 53-15-11-010-001 53-15-11-410-001 34-36-11-991-001

Check of the Electrical Bonding of the Different Components (But not the Fluid Systems and the Components Installed on Composite materials) Functional Test of the ILS Functional Test of the ILS Functional Test of the MMR Repair of the Sealing Opening of the Radome 110AL Closing of the Radome 110AL Fig. 401

  EFF : ALL  34-36-11    CES

 

Page 406 May 01/09

3. __________ Job Set-up Subtask 34-36-11-860-050 A. Aircraft Maintenance Configuration (1) In the cockpit, make sure that the warning notice is in position on the center pedestal to tell persons not to operate the weather radar system. (2) Make sure that the access platform is in position below the radome in zone 110. (3) Make sure that the radome 110AL is open (Ref. TASK 53-15-11-010-001). Subtask 34-36-11-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-004, 051-060, 49VU NAV/ILS/1 121VU COM NAV/ILS/2

1RT1 1RT2

G12 K09

5SQ1

K13

**ON A/C ALL 121VU COM NAV/RADAR/1 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

  EFF : ALL  34-36-11    CES

 

K14

Page 407 Feb 01/10

R

**ON A/C ALL Subtask 34-36-11-160-050 C. Preparation for Installation (1) Precautions : NOTE : If you install the same antenna it is necessary to clean it ____ with CLEANING AGENTS (Material No. 11-003). (2) Remove the used sealant from the bulkhead with CLEANING AGENTS (Material No. 11-003) and a lint free cloth. (3) Clean the component interface and/or the adjacent area. (4) Do an inspection of the component interface and/or the adjacent area. 4. Procedure _________ (Ref. Fig. 401/TASK 34-36-11-991-001) WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE THE SPECIAL _______ MATERIAL. THIS MATERIAL IS DANGEROUS. CAUTION : MAKE SURE THAT YOU DO NOT DAMAGE THE FUSELAGE WHEN YOU REMOVE THE _______ SCUFF PLATES. Subtask 34-36-11-420-050 A. Installation of the Localizer Antenna (1) On the bulkhead (2), apply SPECIAL MATERIALS (Material No. 05-013) with nonmetallic scraper to the attachment of the localizer antenna and to the support of the localizer antenna (1). (2) On the bulkhead (2), apply SEALANTS (Material No. 09-019) with a nonmetallic scraper to the attachment of the localizer antenna and to the support of the localizer antenna (1) (Ref. TASK 51-76-11-300001). NOTE : Make sure that the screw holes do not show any signs of ____ sealing compound. (3) Remove the blanking caps from the coaxial connectors (3) and (6).

  EFF : ALL  34-36-11    CES

 

Page 408 May 01/05

(4) Make sure that the coaxial connectors (3) and (6) are in the correct condition. (5) Put the O-ring (4) in the correct position on the antenna (1). (6) Connect the coaxial connectors (3) and (6) to the localizer antenna (1). (7) Attach the localizer antenna (1) with the screws (5). (8) Remove the unwanted sealing compound from the support of the localizer antenna (1) with a nonmetallic scraper. (9) Make sure that the bonding contact resistance between the antenna (1) and the fuselage structure (2) is not higher than 5 milliohms (Ref. TASK 20-28-00-720-005) . (10) Make a seal around the support of the localizer antenna with SEALANTS (Material No. 09-016) (Ref. TASK 51-76-11-300-001). Subtask 34-36-11-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-004, 051-060, 49VU NAV/ILS/1 121VU COM NAV/ILS/2

1RT1 1RT2

G12 K09

5SQ1

K13

**ON A/C ALL 121VU COM NAV/RADAR/1 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

  EFF : ALL  34-36-11    CES

 

K14

Page 409 Feb 01/10

**ON A/C 001-004, 051-060, Subtask 34-36-11-720-050 C. Do the functional test of the two ILS (para. Identification test with tool) (Ref. TASK 34-36-00-720-001). **ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, Post SB

34-1147 For A/C 001-004,051-060,

Subtask 34-36-11-720-050-A C. Do the functional test of the two MMRs (para. Identification test with tool) (Ref. TASK 34-36-00-720-002). R R

**ON A/C 312-399, Post SB Post SB

001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 401-499, 501-509, 511-526, 528-599, 34-1147 For A/C 001-004, 34-1373 For A/C 001-049,101-149,151-199,201-234,236-238,301-307, 401-499,

Subtask 34-36-11-720-050-B C. Do the functional test of the two MMRs (para. 4.B. ILS Identification Test) (Ref. TASK 34-36-00-720-006). **ON A/C ALL 5. Close-up ________ Subtask 34-36-11-410-050 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the radome 110AL (Ref. TASK 53-15-11-410-001). (3) Remove the access platform(s). (4) Remove the warning notice(s).

  EFF : ALL  34-36-11    CES

 

Page 410 Feb 01/10

**ON A/C ALL Post SB

34-1147 For A/C 001-004,051-060, ANTENNA - GPS ACTIVE (43RT1,43RT2) - REMOVAL/INSTALLATION _________________________________________________________

TASK 34-36-16-000-001 Removal of the GPS Active Antenna (43RT1, 43RT2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

blanking caps circuit breaker(s) safety clip(s) nonmetallic scraper access platform 6.0 m (19 ft. 8 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R

**ON A/C ALL

R

Post SB

34-1373 For A/C 001-004,

34-36-16-991-001

Fig. 401

  EFF : ALL  34-36-16    CES

 

Page 401 Feb 01/09

**ON A/C ALL 3. __________ Job Set-up **ON A/C ALL Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/MMR/1 42RT1 G12 R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2 **ON A/C ALL Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-010-050 B. Get Access (1) Put the access platform in position at zone 220 to get access to the antenna 43RT1 (43RT2).

  EFF : ALL  34-36-16    CES

 

Page 402 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C ALL Post SB

34-1373 For A/C 001-004,

(Ref. Fig. 401/TASK 34-36-16-991-001) **ON A/C 106-149, 213-238, 301-311, 401-499, Subtask 34-36-16-020-050-A A. Removal of the GPS Active Antenna (1) Remove the sealant from the screw heads and around the antenna base with a nonmetallic scraper. (2) Remove the four screws (2) and pull the antenna (1) away from the structure (3). (3) Remove the lockwire and disconnect the coaxial connector (4). (4) Remove the antenna (1) and put blanking caps on the disconnected coaxial connectors. NOTE : The coaxial connector (4) must not go into the fuselage. ____ Attach it to the fuselage with masking tape. (5) Remove and discard the O-ring (5). R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1373 For A/C 001-004,106-149,213-234,236-238,301-307,401-499, Subtask 34-36-16-020-050 A. Removal of the GPS Active Antenna (1) Remove the sealant from the screw heads and around the antenna base with a nonmetallic scraper. (2) Remove the four screws (2) and pull the antenna (1) away from the structure (3).

  EFF : ALL  34-36-16    CES

 

Page 403 Feb 01/10

GPS Active Antenna Figure 401/TASK 34-36-16-991-001   R EFF : ALL  34-36-16    CES

 

Page 404 Feb 01/09

(3) Remove the lockwire and disconnect the coaxial connector (4). (4) Remove the antenna (1) and put blanking caps on the disconnected coaxial connectors. NOTE : The coaxial connector (4) must not go into the fuselage. ____ Attach it to the fuselage with masking tape. (5) If installed, remove the teflon seal (6). NOTE : The teflon seal is optional: you can use sealant as an ____ alternative. You can use the teflon seal again. Do an inspection of the seal and discard it only if necessary. (6) Remove and discard the O-ring (5).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-36-16 201-234, 236-249, 251-299, 301-307, 312-399,  401-499, 501-509, 511-526, 528-599, CES

 

Page 405 Feb 01/10

**ON A/C ALL TASK 34-36-16-400-001 Installation of the GPS Active Antenna (43RT1, 43RT2) with Teflon Seal WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN. _______ IF YOU DO: - RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH - WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER. WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

lint-free cloth nonmetallic scraper access platform 6.0 m (19 ft. 8 in.)

  EFF : ALL  34-36-16   R  CES

 

Page 406 Feb 01/09

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------No specific Material No. 07-001B R Material No. 09-016 Material No. 11-004 Material No. 16-003

lockwire, CRES dia. 0.8 mm (0.030 in.) ELECTRICAL BOND VARNISH (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) USA MIL-T-81533 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM) (Ref. 20-31-00) F ASNB70720 COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------5 5 6 6 6

O-ring O-ring teflon seal teflon seal teflon seal

34-36-16 34-36-16 34-36-01 34-36-01 34-36-01

01 -010 01A-010 02 -030 02A-030 02B-030

D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-720-005 34-10-00-860-004 51-76-11-300-001 R

**ON A/C ALL

R

Post SB

Check of the Electrical Bonding of the Different Components (But not the Fluid Systems and the Components Installed on Composite materials) IR Alignment Procedure Repair of the Sealing

34-1373 For A/C 001-004,

34-36-16-991-001

Fig. 401

  EFF : ALL  34-36-16    CES

 

Page 407 Feb 01/09

**ON A/C ALL 3. __________ Job Set-up **ON A/C ALL Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-865-051 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/MMR/1 42RT1 G12 R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2 **ON A/C ALL Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-010-051 B. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at zone 220 to get access to the antenna.

  EFF : ALL  34-36-16    CES

 

Page 408 Feb 01/10

R

**ON A/C ALL 4. Procedure _________

R

**ON A/C ALL

R

Post SB

34-1373 For A/C 001-004,

(Ref. Fig. 401/TASK 34-36-16-991-001) R

**ON A/C ALL WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE THE SPECIAL _______ MATERIAL. THIS MATERIAL IS DANGEROUS.

R

**ON A/C ALL

R

Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-420-050 A. Installation of the GPS Active Antenna (1) Remove the used sealant from the fuselage structure (3) with a nonmetallic scraper. (2) Clean the mating surfaces with CLEANING AGENTS (Material No. 11-004) and a lint-free cloth. (3) Do an inspection of the component interface and/or the adjacent area. NOTE : The antenna electrical bonding is made through the attachment ____ screws. On the antenna make sure that there is no paint, sealant or corrosion in the recesses of the attachment screw heads. (4) Put a new O-ring (5) in the correct position on the antenna (1). (5) Put the seal that you removed or a new teflon seal (6) on the antenna base. (6) Remove the blanking caps and connect the coaxial connector (4). Install it with the lockwire, CRES dia. 0.8 mm (0.030 in.).

  EFF : ALL  34-36-16    CES

 

Page 409 Feb 01/09

(7) Put the antenna (1) in the correct position on the fuselage. NOTE : Use the small triangle and the F indication which are under ____ the antenna: the triangle must point to the front of the aircraft. (8) Install and tighten the four screws (2). (9) Make sure that the electrical bonding of the antenna is not higher than 5 milliohms (Ref. TASK 20-28-00-720-005). (10) Apply a bead of SEALANTS (Material No. 09-016) around the antenna base and make it smooth (Ref. TASK 51-76-11-300-001) (11) Apply SEALANTS (Material No. 09-016) to the screw heads and make the antenna contour smooth. (12) Let the sealant become dry. (13) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the base of the antenna (1). (14) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001B) to the sealant on the head of the screws (2). NOTE : It is not mandatory to paint the sealant around the base of ____ the antenna and on the head of the screws. Subtask 34-36-16-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/MMR/1 42RT1 G12 R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2

  EFF : ALL  34-36-16    CES

 

Page 410 Feb 01/10

**ON A/C ALL R

Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-710-050 C. Do the operational test of the GPS. (1) Make sure that the IR system is aligned (Ref. TASK 34-10-00-860-004). (2) On one MCDU, push the DATA key to get the DATA INDEX page and then push the line key adjacent to the GPS MONITOR indication. (3) On the GPS MONITOR page, after some minutes, make sure that: - the GPS1(2) POSITION indication is correct. - the TTRK indication shows dashes. - the MERIT indication shows between 0 and 100 m. - the GS indication shows approx. 000. - the MODE indication shows NAV. NOTE : MERIT is an estimate of the 95% position accuracy of the ____ position output by the GPS sensor. (4) On the upper ECAM DU, make sure that there is no GPS fault message. (5) De-energize the aircraft electrical circuits. (6) Put the aircraft back to its initial configuration. R

**ON A/C ALL 5. Close-up ________

R

**ON A/C ALL

R

Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-410-050 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the access platform(s).

  EFF : ALL  34-36-16    CES

 

Page 411 Feb 01/09

R

**ON A/C ALL TASK 34-36-16-400-001- 01 Installation of the GPS Active Antenna (43RT1, 43RT2) without Teflon Seal WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN. _______ IF YOU DO: - RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH - WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER. WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

lint-free cloth masking tape nonmetallic scraper access platform 6.0 m (19 ft. 8 in.)

  EFF : ALL  34-36-16    CES

 

Page 412 Feb 01/09

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------No specific Material No. 05-013

lockwire, CRES dia. 0.8 mm (0.030 in.). D TV-53-3507/73 RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)

Material No. 07-001B R Material No. 09-016 Material No. 09-019 Material No. 11-003 Material No. 16-003

ELECTRICAL BOND VARNISH (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) USA AMS 3267/3 NO LONGER AVAILABLE (Ref. 20-31-00) USA ASTM D 740 METHYL-ETHYL-KETONE (Ref. 20-31-00) F ASNB70720 COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------5 5

O-ring O-ring

34-36-16 01 -010 34-36-16 01A-010

D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-912-004 34-10-00-860-004 51-76-11-300-001 R

**ON A/C ALL

R

Post SB

Electrical Bonding of Components With Conductive Bolts and Screws and Bonding Straps in the Fuselage and in the Wings (this does not include the tanks)IR Alignment Procedure Repair of the Sealing

34-1373 For A/C 001-004,

34-36-16-991-002

Fig. 402

  EFF : ALL  34-36-16    CES

 

Page 413 Feb 01/09

**ON A/C ALL 3. __________ Job Set-up **ON A/C ALL Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-865-053 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/MMR/1 42RT1 G12 R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2 **ON A/C ALL Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-010-052 B. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at zone 220 to get access to the antenna.

  EFF : ALL  34-36-16    CES

 

Page 414 Feb 01/10

R

**ON A/C ALL 4. Procedure _________

R

**ON A/C ALL

R

Post SB

34-1373 For A/C 001-004,

(Ref. Fig. 402/TASK 34-36-16-991-002) R

**ON A/C ALL WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE THE SPECIAL _______ MATERIAL. THIS MATERIAL IS DANGEROUS.

R

**ON A/C ALL

R

Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-420-051 A. Installation of the GPS Active Antenna (1) Remove the used sealant from the fuselage structure (3) with a nonmetallic scraper. (2) Clean the mating surfaces with CLEANING AGENTS (Material No. 11-003) and a lint-free cloth. (3) Do an inspection of the component interface and/or the adjacent area. NOTE : The antenna electrical bonding is made through the attachment ____ screws. On the antenna make sure that there is no paint, sealant or corrosion in the recesses of the attachment screws heads. (4) Apply masking tape to the structure (3), the edge of the antenna (1), the screw holes and the hole for the antenna connector. (5) Apply SPECIAL MATERIALS (Material No. 05-013) to the bottom of the antenna (1).

  EFF : ALL  34-36-16    CES

 

Page 415 Feb 01/09

GPS Active Antenna Figure 402/TASK 34-36-16-991-002   EFF : ALL  34-36-16   R  CES

 

Page 416 Feb 01/09

(6) Apply SEALANTS (Material No. 09-019) to the area of the fuselage (3) that makes an interface with the antenna (1) (Ref. TASK 51-76-11-300001). (7) Remove the masking tape from the screw holes and the hole for the antenna connector. R

(8) Remove the blanking caps from the electrical connector(s). (9) Make sure that the electrical connectors are clean and in the correct condition. (10) Install the new O-ring (5). (11) Connect the coaxial connector (4) to the GPS antenna connector. (12) Safety the coaxial connector (4) with lockwire, CRES dia. 0.8 mm (0.030 in.). (13) Put the antenna (1) in position and install the screws (2). (14) Tighten the screws (2) in a diagonal sequence. (15) Remove the unwanted sealant with a nonmetallic scraper. (16) Remove the remaining masking tape. (17) Make sure that the bonding contact resistance between the antenna (1) and the fuselage structure (3) is not higher than 5 milliohms (Ref. TASK 20-28-00-912-004). (18) Make a sealing bead with SEALANTS (Material No. 09-016) around the antenna (1) (Ref. TASK 51-76-11-300-001). (19) Apply SEALANTS (Material No. 09-016) to the heads of the screws (2). (20) Make the contour of the sealant on the screws (2) and around the antenna (1) smooth. (21) Let the sealant cure. (22) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the base of the antenna (1). (23) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001B) to the sealant on the head of the screws (2).

  EFF : ALL  34-36-16    CES

 

Page 417 Feb 01/10

Subtask 34-36-16-865-054 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/MMR/1 42RT1 G12 R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2 **ON A/C ALL Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-710-051 C. Do the operational test of the GPS. (1) Make sure that the IR system is aligned (Ref. TASK 34-10-00-860-004). (2) On one MCDU, push the DATA key to get the DATA INDEX page and then push the line key adjacent to the GPS MONITOR indication. (3) On the GPS MONITOR page, after some minutes, make sure that: - the GPS1(2) POSITION indication is correct. - the TTRK indication shows dashes. - the MERIT indication shows approx. 100 m. - the GS indication shows approx. 000. - the MODE indication shows NAV. (4) On the upper ECAM DU, make sure that there is no GPS fault message. (5) De-energize the aircraft electrical circuits. (6) Put the aircraft back to its initial configuration.

  EFF : ALL  34-36-16    CES

 

Page 418 Feb 01/10

R

**ON A/C ALL 5. Close-up ________

R

**ON A/C ALL

R

Post SB

34-1373 For A/C 001-004,

Subtask 34-36-16-410-051 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the access platform(s).

  EFF : ALL  34-36-16    CES

 

Page 419 Feb 01/09

ANTENNA - GLIDE/SLOPE (4RT) - REMOVAL/INSTALLATION __________________________________________________ TASK 34-36-18-000-001 Removal of the Glide/Slope Antenna (4RT) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

blanking caps circuit breaker(s) safety clip(s) warning notice access platform 3.5 m (11 ft. 6 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------53-15-11-010-001 34-36-18-991-001

Opening of the Radome 110AL Fig. 401

  EFF : ALL  34-36-18   R  CES

 

Page 401 May 01/05

3. __________ Job Set-up Subtask 34-36-18-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-004, 051-060, 49VU NAV/ILS/1 121VU COM NAV/ILS/2

1RT1 1RT2

G12 K09

5SQ1

K13

**ON A/C ALL 121VU COM NAV/RADAR/1 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL Subtask 34-36-18-010-050 B. Get Access (1) In the cockpit, put a warning notice on the center pedestal to tell persons not to operate or to start the weather radar system. (2) Put the access platform in position in zone 110 below the radome. (3) Open the radome 110AL (Ref. TASK 53-15-11-010-001) .

  EFF : ALL  34-36-18    CES

 

Page 402 Feb 01/10

4. Procedure _________ (Ref. Fig. 401/TASK 34-36-18-991-001) Subtask 34-36-18-020-050 A. Removal of the Glide/Slope Antenna (1) Loosen the screws (6). (2) Disengage the antenna (1) away from the bulkhead (4). (3) Remove and discard the O-rings (2). (4) Disconnect the coaxial connectors (3). (5) Remove the antenna (1). (6) Put blanking caps on the disconnected coaxial connectors (3) and (5).

  EFF : ALL  34-36-18   R  CES

 

Page 403 May 01/05

Glide/Slope Antenna Figure 401/TASK 34-36-18-991-001   EFF : ALL  34-36-18   R  CES

 

Page 404 May 01/05

TASK 34-36-18-400-001 Installation of the Glide/Slope Antenna (4RT) WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN. _______ IF YOU DO: - RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH - WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER. R R R

WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

lint-free cloth warning notice access platform 3.5 m (11 ft. 6 in.)

  EFF : ALL  34-36-18    CES

 

Page 405 May 01/05

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 05-013 Material No. 09-016 Material No. 09-019 Material No. 11-003

D TV-53-3507/73 RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) USA AMS 3267/3 NO LONGER AVAILABLE (Ref. 20-31-00) USA ASTM D 740 METHYL-ETHYL-KETONE (Ref. 20-31-00)

C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------2 2

O-rings O-rings

34-36-18 01 -010 34-36-18 01A-010

D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R

20-28-00-912-005 34-36-00-720-001 34-36-00-720-002 34-36-00-720-006 51-76-11-300-001 53-15-11-010-001 53-15-11-410-001 34-36-18-991-001

Electrical Bonding of Antennas With Conductive Bolts. Functional Test of the ILS Functional Test of the ILS Functional Test of the MMR Repair of the Sealing Opening of the Radome 110AL Closing of the Radome 110AL Fig. 401

  EFF : ALL  34-36-18    CES

 

Page 406 Feb 01/10

3. __________ Job Set-up Subtask 34-36-18-860-050 A. Aircraft Maintenance Configuration (1) In the cockpit, make sure that the warning notice is in position on the center pedestal to tell persons not to operate or to start the weather radar system. (2) Make sure that the access platform is in position below the radome in zone 110. (3) Make sure that the radome 110AL is open (Ref. TASK 53-15-11-010-001). Subtask 34-36-18-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-004, 051-060, 49VU NAV/ILS/1 121VU COM NAV/ILS/2

1RT1 1RT2

G12 K09

5SQ1

K13

**ON A/C ALL 121VU COM NAV/RADAR/1 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

  EFF : ALL  34-36-18    CES

 

K14

Page 407 Feb 01/10

**ON A/C ALL Subtask 34-36-18-160-050 C. Preparation for Installation (1) Precautions NOTE : If you install the same antenna, it is necessary to clean it ____ with CLEANING AGENTS (Material No. 11-003) (2) Remove the used sealant from the fuselage with CLEANING AGENTS (Material No. 11-003) and a lint-free cloth. (3) Clean the component interface and/or the adjacent area. (4) Do an inspection of the component interface and/or the adjacent area. 4. Procedure _________ (Ref. Fig. 401/TASK 34-36-18-991-001) WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE THE SPECIAL _______ MATERIAL. THIS MATERIAL IS DANGEROUS. Subtask 34-36-18-420-050 A. Installation of the Glide/Slope Antenna (1) Apply SPECIAL MATERIALS (Material No. 05-013) to the bulkhead (4) where you install the antenna and to the antenna (1) mount. (2) Apply SEALANTS (Material No. 09-019) to the bulkhead (4) where you install the antenna and to the antenna (1) mount (Ref. TASK 51-76-11300-001). NOTE : Make sure that there is no sealant in the screws holes. ____ (3) Remove the blanking caps from the coaxial connectors (3) and (5). (4) Put the O-rings (2) in the correct position on the antenna (1). (5) Connect the coaxial connectors (3) to the antenna (1). (6) Put the antenna (1) in position on the bulkhead (4).

  EFF : ALL  34-36-18   R  CES

 

Page 408 May 01/09

(7) Attach the antenna (1) with the screws (6). (8) Remove the sealant which is not necessary. (9) Apply a sealing bead with SEALANTS (Material No. 09-016) around the antenna (1). (10) Make the antenna contour smooth. Subtask 34-36-18-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-004, 051-060, 49VU NAV/ILS/1 121VU COM NAV/ILS/2

1RT1 1RT2

G12 K09

5SQ1

K13

**ON A/C ALL 121VU COM NAV/RADAR/1 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

R

**ON A/C ALL

R

Subtask 34-36-18-720-053

R R R

5SQ2

K14

C. Do a check of the maximum bonding value (Ref. TASK 20-28-00-912-005): - Use a MILLIOMMETER MULTIRANGE 0.5 OHMS MAX -10 A MAX. - Make sure that the maximum bonding value is not more than 5 milliohms.

  EFF : ALL  34-36-18    CES

 

Page 409 Feb 01/10

**ON A/C 001-004, 051-060, Subtask 34-36-18-720-050 R

D. Do the functional test of the two ILS (para. Reception test with tool) (Ref. TASK 34-36-00-720-001). **ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499, Post SB

34-1147 For A/C 001-004,051-060,

Subtask 34-36-18-720-050-A R R R

D. Do the functional test of the two MMRs (para. Reception test with tool) (Ref. TASK 34-36-00-720-002). **ON A/C 312-399, Post SB Post SB

001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 401-499, 501-509, 511-526, 528-599, 34-1147 For A/C 001-004, 34-1373 For A/C 001-049,101-149,151-199,201-234,236-238,301-307, 401-499,

Subtask 34-36-18-720-050-B R

D. Do the functional test of the two MMRs (para. 4.B. ILS Identification Test) (Ref. TASK 34-36-00-720-006). **ON A/C ALL 5. Close-up ________ Subtask 34-36-18-410-050 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the radome 110AL (Ref. TASK 53-15-11-410-001). (3) Remove the access platform(s). (4) Remove the warning notice(s).

  EFF : ALL  34-36-18    CES

 

Page 410 Feb 01/10

RECEIVER - ILS (2RT1,2RT2) - REMOVAL/INSTALLATION _________________________________________________ R

**ON A/C 001-004, 051-060, TASK 34-36-31-000-001 Removal of the ILS Receiver (2RT1,2RT2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-36-31-991-001

Fig. 401

3. __________ Job Set-up Subtask 34-36-31-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 2RT1 49VU NAV/ILS/1 1RT1 G12 FOR 2RT2 121VU COM NAV/ILS/2 1RT2 K09

  R EFF : ALL  34-36-31 Page 401   Config-1 Nov 01/09  CES

 

Subtask 34-36-31-010-050 B. Get Access (1) Put the access platform in position at the access door 811 in zone 122. (2) Open the access door 811. 4. Procedure _________ (Ref. Fig. 401/TASK 34-36-31-991-001) Subtask 34-36-31-020-050 A. Removal of the ILS Receiver (2RT1, 2RT2) (1) Loosen the nuts (4). (2) Lower the nuts (4). (3) Pull the ILS receiver (1) on its rack (3) to disconnect the electrical connectors (2). (4) Remove the ILS receiver (1) from its rack. (5) Put blanking caps on the disconnected electrical connectors (2).

  EFF : 001-004, 051-060,  34-36-31 Page 402   Config-1 May 01/09  CES

 

ILS Receiver. Figure 401/TASK 34-36-31-991-001   R EFF : ALL  34-36-31 Page 403   Config-1 Nov 01/09  CES

 

TASK 34-36-31-400-001 Installation of the ILS Receiver (2RT1,2RT2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------22-97-00-710-001 34-36-00-710-001 34-36-00-740-002 34-36-31-991-001

Operational Test of the LAND CAT III Capability Operational Test of the ILS BITE Test of the ILS Fig. 401

3. __________ Job Set-up Subtask 34-36-31-010-051 A. Get Access (1) Make sure that the access platform is in position at the access door 811 in zone 122. (2) Make sure that the access door 811 is open. Subtask 34-36-31-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 2RT1 49VU NAV/ILS/1 1RT1 G12 FOR 2RT2 121VU COM NAV/ILS/2 1RT2 K09

  EFF : 001-004, 051-060,  34-36-31 Page 404   Config-1 May 01/09  CES

 

4. Procedure _________ (Ref. Fig. 401/TASK 34-36-31-991-001) Subtask 34-36-31-420-050 A. Installation of the ILS Receiver (2RT1, 2RT2) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (2). (4) Make sure that the electrical connectors (2) are clean and in the correct condition. (5) Install the ILS receiver (1) on its rack (3). (6) Push the ILS Receiver (1) on its rack (3) to connect the electrical connectors (2). (7) Engage the nuts (4) on the lugs (5) and tighten. Subtask 34-36-31-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 2RT1 49VU NAV/ILS/1 1RT1 G12 FOR 2RT2 121VU COM NAV/ILS/2 1RT2 K09 Subtask 34-36-31-740-050 C. BITE test of the ILS (1) Do the BITE test of the ILS (Ref. TASK 34-36-00-740-002) NOTE : If the airline operates the aircraft in CAT 3 conditions, do ____ the LAND CAT III capability test (Ref. TASK 22-97-00-710-001).

  EFF : 001-004, 051-060,  34-36-31 Page 405   Config-1 May 01/09  CES

 

(2) As an alternative procedure, without the CFDS, you can do the operational test of the ILS (Ref. TASK 34-36-00-710-001). 5. Close-up ________ Subtask 34-36-31-410-050 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the access door 811. (3) Remove the access platform(s).

  EFF : 001-004, 051-060,  34-36-31 Page 406   Config-1 May 01/09  CES

 

R

**ON A/C ALL

R

TASK 34-36-31-400-001-C

R

Installation of the ILS Receiver (2RT1,2RT2)

R

1. __________________ Reason for the Job

R

Self Explanatory

R

2. ______________________ Job Set-up Information

R

A. Referenced Information

R R R

------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------

R R R R

22-97-00-710-001 34-36-00-710-001 34-36-00-740-002 34-36-31-991-001

R

3. __________ Job Set-up

R R R R R

Operational Test of the LAND CAT III Capability Operational Test of the ILS BITE Test of the ILS Fig. 401

NOTE : Removal and installation of the ILS Receiver affects the CAT II/III ____ status of the airplane. A CAT III qualified mechanic is required to return the airplane to a CAT II/III status. The applicable Land CAT III Test (AMM 22-97-00/501) must be performed before the airplane is returned to a CAT II/III status (Ref AMM 22-97-00/201).

  EFF : ALL  34-36-31 Page 407   Config-1 Feb 01/10  CES

 

R

Subtask 34-36-31-865-071

R R

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged

R R R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 2RT1

R

**ON A/C 001-004, 051-060,

R

49VU NAV/ILS/1

R

**ON A/C ALL

R

FOR 2RT2

R

**ON A/C 001-004, 051-060,

R R

**ON A/C ALL

R

4. Procedure _________

R R

G12

1RT2

K09

121VU COM NAV/ILS/2

1RT1

(Ref. Fig. 401/TASK 34-36-31-991-001) Subtask 34-36-31-420-057

R

A. Installation of the ILS Receiver (2RT1, 2RT2)

R

(1) Clean the component interface and/or the adjacent area.

R

(2) Do an inspection of the component interface and/or the adjacent area.

R

(3) Remove the blanking caps from the electrical connectors (2).

R R

(4) Make sure that the electrical connectors (2) are clean and in the correct condition.

R

(5) Install the ILS receiver (1) on its rack (3).

  EFF : ALL  34-36-31 Page 408   Config-1 Feb 01/10  CES

 

R R

(6) Push the ILS Receiver (1) on its rack (3) to connect the electrical connectors (2).

R

(7) Engage the nuts (4) on the lugs (5) and tighten.

R

Subtask 34-36-31-865-072

R R

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

R R R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 2RT1

R

**ON A/C 001-004, 051-060,

R

49VU NAV/ILS/1

R

**ON A/C ALL

R

FOR 2RT2

R

**ON A/C 001-004, 051-060,

R

121VU COM NAV/ILS/2

R

**ON A/C ALL

R

Subtask 34-36-31-740-057

R

1RT1

G12

1RT2

K09

C. BITE test of the ILS

R

(1) Do the BITE test of the ILS (Ref. TASK 34-36-00-740-002).

R R R

NOTE : If the airline operates the aircraft in CAT 3 conditions, do ____ the LAND CAT III capability test (Ref. TASK 22-97-00-710-001).

R R

(2) As an alternative procedure, without the CFDS, you can do the operational test of the ILS (Ref. TASK 34-36-00-710-001).

  EFF : ALL  34-36-31 Page 409   Config-1 Feb 01/10  CES

 

R

5. Close-up ________

R

Subtask 34-36-31-410-057

R

A. Close Access

R R

(1) Make sure that the work area is clean and clear of tool(s) and other items.

R

(2) Close the access door 811.

R

(3) Remove the access platform(s).

  EFF : ALL  34-36-31 Page 410   Config-1 Feb 01/10  CES

 

R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499,

R

Post SB

R

TASK 34-36-31-000-001-A

R

Removal of the Multi Mode Receiver (40RT1, 40RT2)

R

1. __________________ Reason for the Job

R

Self Explanatory

R

34-1147 For A/C 001-004,051-060,

2. ______________________ Job Set-up Information

R

A. Fixtures, Tools, Test and Support Equipment

R R R

------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R R R

No specific No specific No specific

R

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

R R R

------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------

R R R

31-32-00-860-010

R

3. __________ Job Set-up

R

Subtask 34-36-31-810-053

34-36-31-991-005

R R R R R R R R

Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page Fig. 402

A. Trouble Shooting Data If available, you can print the Trouble Shooting Data (TSD) as follows: - get access to the SYSTEM/REPORT TEST NAV page (Ref. TASK 31-32-00-860010). - on this page, push the line key adjacent to the MMR1 (MMR2) indication. - on the MMR1 (MMR2) page, push the line key adjacent to the TROUBLE SHOOTING DATA indication to get the TROUBLE SHOOTING DATA page. - print the TROUBLE SHOOTING DATA (TSD) page(s).

  EFF : 001-049, 051-099, 101-149, 151-199,  34-36-31 Page 411 201-238, 301-311, 401-499,  Config-1 Feb 01/10  CES

 

R

Subtask 34-36-31-865-062

R

B. Open, safety and tag this(these) circuit breaker(s):

R R R R R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 40RT1 49VU NAV/MMR/1 42RT1 G12 FOR 40RT2

R

**ON A/C 062-099, 106-149, 151-199, 204-238, 301-311, 401-499,

R R R

121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2

R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499,

R

Subtask 34-36-31-010-058

R

C. Get Access

R R

(1) Put the access platform in position at the access door 811 in zone 122.

R

(2) Open the access door 811.

R

4. Procedure _________

R R

(Ref. Fig. 402/TASK 34-36-31-991-005) Subtask 34-36-31-020-055

R

A. Removal of the Multi Mode Receiver (40RT1, 40RT2)

R

(1) Loosen the nuts (4).

R

(2) Lower the nuts (4).

R R

(3) Pull the Multi Mode Receiver (1) from its rack (3) to disconnect the electrical connectors (2).

  EFF : 001-049, 051-099, 101-149, 151-199,  34-36-31 Page 412 201-238, 301-311, 401-499,  Config-1 Feb 01/10  CES

 

R R

Multi Mode Receiver Figure 402/TASK 34-36-31-991-005

  EFF : ALL  34-36-31 Page 413   Config-1 Feb 01/10  CES

 

R

(4) Remove the Multi Mode Receiver (1) from its rack.

R

(5) Put blanking caps on the disconnected electrical connectors (2).

  EFF : 001-049, 051-099, 101-149, 151-199,  34-36-31 Page 414 201-238, 301-311, 401-499,  Config-1 Feb 01/10  CES

 

R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499,

R

Post SB

R

TASK 34-36-31-400-001-A

R

Installation of the Multi Mode Receiver (40RT1, 40RT2)

R

1. __________________ Reason for the Job

R

Self Explanatory

R

34-1147 For A/C 001-004,051-060,

2. ______________________ Job Set-up Information

R

A. Referenced Information

R R R

------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------

R R R R

22-97-00-710-001 34-36-00-710-003 34-36-00-740-003 34-36-31-991-005

R

3. __________ Job Set-up

R

Subtask 34-36-31-010-059

R

Operational Test of the LAND CAT III Capability Operational Test of the ILS BITE Test of the MMR Fig. 402

A. Get Access

R R

(1) Make sure that the access platform is in position at the access door 811 in zone 122.

R

(2) Make sure that the access door 811 is open.

  EFF : 001-049, 051-099, 101-149, 151-199,  34-36-31 Page 415 201-238, 301-311, 401-499,  Config-1 Feb 01/10  CES

 

R

Subtask 34-36-31-865-063

R R

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged

R R R R R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 40RT1 49VU NAV/MMR/1 42RT1 G12 FOR 40RT2

R

**ON A/C 062-099, 106-149, 151-199, 204-238, 301-311, 401-499,

R R R

121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2

R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499,

R

4. Procedure _________

R R

(Ref. Fig. 402/TASK 34-36-31-991-005) Subtask 34-36-31-420-054

R

A. Installation of the Multi Mode Receiver (40RT1, 40RT2)

R

(1) Clean the component interface and/or the adjacent area.

R

(2) Do an inspection of the component interface and/or the adjacent area.

R

(3) Remove the blanking caps from the electrical connectors (2).

R R

(4) Make sure that the electrical connectors (2) are clean and in the correct condition.

R

(5) Install the Multi Mode Receiver (1) on its rack (3).

R R

(6) Push the Multi Mode Receiver (1) on its rack (3) to connect the electrical connectors (2).

  EFF : 001-049, 051-099, 101-149, 151-199,  34-36-31 Page 416 201-238, 301-311, 401-499,  Config-1 Feb 01/10  CES

 

R R

(7) Engage the nuts (4) on the lugs (5) and tighten. Subtask 34-36-31-865-064

R R

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

R R R R R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 40RT1 49VU NAV/MMR/1 42RT1 G12 FOR 40RT2

R

**ON A/C 062-099, 106-149, 151-199, 204-238, 301-311, 401-499,

R R R

121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2

R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-238, 301-311, 401-499,

R

Subtask 34-36-31-740-054

R

C. BITE test of the Multi Mode Receiver

R R

(1) Do the BITE test of the Multi Mode Receiver (Ref. TASK 34-36-00-740003)

R R R

NOTE : If the airline operates the aircraft in CAT 3 conditions, do ____ the LAND CAT III capability test (Ref. TASK 22-97-00-710-001).

R R

(2) As an alternative procedure, without the CFDS, you can do the operational test of the ILS (Ref. TASK 34-36-00-710-003).

  EFF : 001-049, 051-099, 101-149, 151-199,  34-36-31 Page 417 201-238, 301-311, 401-499,  Config-1 Feb 01/10  CES

 

R

5. Close-up ________

R

Subtask 34-36-31-410-054

R

A. Close Access

R R

(1) Make sure that the work area is clean and clear of tool(s) and other items.

R

(2) Close the access door 811.

R

(3) Remove the access platform(s).

  EFF : 001-049, 051-099, 101-149, 151-199,  34-36-31 Page 418 201-238, 301-311, 401-499,  Config-1 Feb 01/10  CES

 

R

**ON A/C ALL

R

Post SB

R

TASK 34-36-31-400-001-D

R

Installation of the Multi Mode Receiver (40RT1, 40RT2)

R

1. __________________ Reason for the Job

R

Self Explanatory

R

34-1147 For A/C 001-004,051-060,

2. ______________________ Job Set-up Information

R

A. Referenced Information

R R R

------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------

R R R R

22-97-00-710-001 34-36-00-710-003 34-36-00-740-003 34-36-31-991-005

R

3. __________ Job Set-up

Operational Test of the LAND CAT III Capability Operational Test of the ILS BITE Test of the MMR Fig. 402

R R R R R

NOTE : Removal and installation of the MMR affects the CAT II/III status of ____ the airplane. A CAT III qualified mechanic is required to return the airplane to a CAT II/III status. The applicable Land CAT III Test (AMM 22-97-00/501) must be performed before the airplane is returned to a CAT II/III status (Ref AMM 22-97-00/201).

R R R

NOTE : A functional test of the MMR (Reception test with tool) must be ____ performed to return the airplane to a CAT II/III status after any maintenance action to the MMR (Ref AMM 22-97-00/201).

  EFF : ALL  34-36-31 Page 419   Config-1 Feb 01/10  CES

 

R

Subtask 34-36-31-865-073

R R

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged

R R R R R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 40RT1 49VU NAV/MMR/1 42RT1 G12 FOR 40RT2

R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

R R R

121VU COM NAV/MMR/2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2

R

**ON A/C ALL

R

4. Procedure _________

R R

42RT2

(Ref. Fig. 402/TASK 34-36-31-991-005) Subtask 34-36-31-420-058

R

A. Installation of the Multi Mode Receiver (40RT1, 40RT2)

R

(1) Clean the component interface and/or the adjacent area.

R

(2) Do an inspection of the component interface and/or the adjacent area.

R

(3) Remove the blanking caps from the electrical connectors (2).

R R

(4) Make sure that the electrical connectors (2) are clean and in the correct condition.

R

(5) Install the Multi Mode Receiver (1) on its rack (3).

R R

(6) Push the Multi Mode Receiver (1) on its rack (3) to connect the electrical connectors (2).

  EFF : ALL  34-36-31 Page 420   Config-1 Feb 01/10  CES

 

R R

(7) Engage the nuts (4) on the lugs (5) and tighten. Subtask 34-36-31-865-074

R R

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

R R R R R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 40RT1 49VU NAV/MMR/1 42RT1 G12 FOR 40RT2

R R

**ON A/C 062-099, 106-149, 151-199, 204-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

R R R

121VU COM NAV/MMR/2

42RT2

L07

42RT2

K09

**ON A/C 001-049, 051-061, 101-105, 201-203, 121VU COM NAV/MMR/2

R

**ON A/C ALL

R

Subtask 34-36-31-740-058

R

C. BITE test of the Multi Mode Receiver

R R

(1) Do the BITE test of the Multi Mode Receiver (Ref. TASK 34-36-00-740003)

R R R

NOTE : If the airline operates the aircraft in CAT 3 conditions, do ____ the LAND CAT III capability test (Ref. TASK 22-97-00-710-001).

R R

(2) As an alternative procedure, without the CFDS, you can do the operational test of the ILS (Ref. TASK 34-36-00-710-003).

  EFF : ALL  34-36-31 Page 421   Config-1 Feb 01/10  CES

 

R

5. Close-up ________

R

Subtask 34-36-31-410-058

R

A. Close Access

R R

(1) Make sure that the work area is clean and clear of tool(s) and other items.

R

(2) Close the access door 811.

R

(3) Remove the access platform(s).

  EFF : ALL  34-36-31 Page 422   Config-1 Feb 01/10  CES

 

R R R R

**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1373 For A/C 001-049,101-149,151-199,201-234,236-238,301-307, 401-499,

R

TASK 34-36-31-000-001-B

R

Removal of the Multi Mode Receiver (40RT1, 40RT2)

R

1. __________________ Reason for the Job

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Self Explanatory

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2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment

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------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

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No specific No specific No specific

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blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

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------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------

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31-32-00-860-010

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3. __________ Job Set-up

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Subtask 34-36-31-810-054

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34-36-31-991-006

Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page Fig. 403

A. Trouble Shooting Data If available, you can print the Trouble Shooting Data (TSD) as follows: - get access to the SYSTEM/REPORT TEST NAV page (Ref. TASK 31-32-00-860010). - on this page, push the line key adjacent to the MMR1 (MMR2) indication. - on the MMR1 (MMR2) page, push the line key adjacent to the TROUBLE SHOOTING DATA indication to get the TROUBLE SHOOTING DATA page. - print the TROUBLE SHOOTING DATA (TSD) page(s).

  EFF : 001-049, 101-149, 151-199, 201-234,  34-36-31 Page 423 236-249, 251-299, 301-307, 312-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

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Subtask 34-36-31-865-065 B. Open, safety and tag this(these) circuit breaker(s):

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------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 40RT1

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**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1147 For A/C 001-004,

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49VU NAV/MMR/1

42RT1

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**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599,

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FOR 40RT2

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**ON A/C 106-149, 151-199, 204-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599,

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121VU COM NAV/MMR/2

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**ON A/C 001-049, 101-105, 201-203,

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Post SB

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42RT2

L07

42RT2

K09

34-1147 For A/C 001-004,

121VU COM NAV/MMR/2

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**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599,

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Subtask 34-36-31-010-064

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G12

C. Get Access

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(1) Put the access platform in position at the access door 811 in zone 122.

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(2) Open the access door 811.

  EFF : 001-049, 101-149, 151-199, 201-234,  34-36-31 Page 424 236-249, 251-299, 301-307, 312-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

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4. Procedure _________ (Ref. Fig. 403/TASK 34-36-31-991-006) Subtask 34-36-31-020-056 A. Removal of the Multi Mode Receiver (40RT1, 40RT2)

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(1) Loosen the nuts (4).

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(2) Lower the nuts (4).

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(3) Pull the Multi Mode Receiver (1) from its rack (3) to disconnect the electrical connectors (2).

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(4) Remove the Multi Mode Receiver (1) from its rack.

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(5) Put blanking caps on the disconnected electrical connectors (2).

  EFF : 001-049, 101-149, 151-199, 201-234,  34-36-31 Page 425 236-249, 251-299, 301-307, 312-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

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Multi Mode Receiver Figure 403/TASK 34-36-31-991-006

  EFF : 001-049, 101-149, 151-199, 201-234,  34-36-31 Page 426 236-249, 251-299, 301-307, 312-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

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**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1373 For A/C 001-049,101-149,151-199,201-234,236-238,301-307, 401-499,

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TASK 34-36-31-400-001-B

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Installation of the Multi Mode Receiver (40RT1, 40RT2)

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1. __________________ Reason for the Job

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Self Explanatory

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2. ______________________ Job Set-up Information A. Referenced Information

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------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------

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22-97-00-710-001 34-36-00-710-003 34-36-00-740-006 34-36-31-991-006

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3. __________ Job Set-up

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Subtask 34-36-31-010-061

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Operational Test of the LAND CAT III Capability Operational Test of the ILS BITE Test of the MMR Fig. 403

A. Get Access

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(1) Make sure that the access platform is in position at the access door 811 in zone 122.

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(2) Make sure that the access door 811 is open.

  EFF : 001-049, 101-149, 151-199, 201-234,  34-36-31 Page 427 236-249, 251-299, 301-307, 312-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

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Subtask 34-36-31-865-066 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged

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------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 40RT1

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**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1147 For A/C 001-004,

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49VU NAV/MMR/1

42RT1

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**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599,

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FOR 40RT2

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**ON A/C 106-149, 151-199, 204-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599,

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121VU COM NAV/MMR/2

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**ON A/C 001-049, 101-105, 201-203,

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Post SB

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42RT2

L07

42RT2

K09

34-1147 For A/C 001-004,

121VU COM NAV/MMR/2

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**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599,

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4. Procedure _________

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(Ref. Fig. 403/TASK 34-36-31-991-006) Subtask 34-36-31-420-055 A. Installation of the Multi Mode Receiver (40RT1, 40RT2)

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(1) Clean the component interface and/or the adjacent area.

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(2) Do an inspection of the component interface and/or the adjacent area.

  EFF : 001-049, 101-149, 151-199, 201-234,  34-36-31 Page 428 236-249, 251-299, 301-307, 312-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

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(3) Remove the blanking caps from the electrical connectors (2).

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(4) Make sure that the electrical connectors (2) are clean and in the correct condition.

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(5) Install the Multi Mode Receiver (1) on its rack (3).

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(6) Push the Multi Mode Receiver (1) on its rack (3) to connect the electrical connectors (2).

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(7) Engage the nuts (4) on the lugs (5) and tighten.

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Subtask 34-36-31-865-067

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B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

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------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 40RT1

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**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1147 For A/C 001-004,

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49VU NAV/MMR/1

42RT1

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**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599,

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FOR 40RT2

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**ON A/C 106-149, 151-199, 204-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599,

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121VU COM NAV/MMR/2

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**ON A/C 001-049, 101-105, 201-203,

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Post SB

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G12

42RT2

L07

42RT2

K09

34-1147 For A/C 001-004,

121VU COM NAV/MMR/2

  EFF : 001-049, 101-149, 151-199, 201-234,  34-36-31 Page 429 236-249, 251-299, 301-307, 312-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

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**ON A/C 001-049, 101-149, 151-199, 201-234, 236-249, 251-299, 301-307, 312-399, 401-499, 501-509, 511-526, 528-599,

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Subtask 34-36-31-740-055

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C. BITE test of the Multi Mode Receiver (1) Do the BITE test of the Multi Mode Receiver (Ref. TASK 34-36-00-740006) NOTE : If the airline operates the aircraft in CAT 3 conditions, do ____ the LAND CAT III capability test (Ref. TASK 22-97-00-710-001). (2) As an alternative procedure, without the CFDS, you can do the operational test of the ILS (Ref. TASK 34-36-00-710-003).

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5. Close-up ________

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Subtask 34-36-31-410-055

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A. Close Access

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(1) Make sure that the work area is clean and clear of tool(s) and other items.

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(2) Close the access door 811.

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(3) Remove the access platform(s).

  EFF : 001-049, 101-149, 151-199, 201-234,  34-36-31 Page 430 236-249, 251-299, 301-307, 312-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

WEATHER RADAR SYSTEM - DESCRIPTION AND OPERATION ________________________________________________ 1. General _______ R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, The aircraft is equipped with an X-band weather radar system with Predictive Windshear capability. This system complies with the ARINC Characteristics 708A. The weather radar system enables: - detection and localization of the atmospheric disturbances in the area defined by the antenna scanning: plus or minus 90 deg. of aircraft centerline and up to 320NM in front of the aircraft, - detection of turbulence areas caused by the presence of precipitations up to a distance of 40NM, - presentation of terrain mapping information by the combination of the orientation of the radar beam and of the receiver gain, - detection, if the Predictive Windshear System is operative, of a microburst windshear event in the area defined by the antenna scanning: plus or minus 60 deg. - presentation, if the Predictive Windshear System is operative, of windshear events within an area plus or minus 40 deg. of aircraft centerline and up to 5NM in front of the aircraft. - Autotilt capability (automatic tiltangle), the automatic tilt function is recommended for use in WX and TURB modes. NOTE : A microburst is a cool shaft of air, like a cylinder, between 1000 ____ and 3000 ft. When it encounters the ground (airflow velocity from 40 to 110 kts) the downward moving airflow is translated to a horizontal flow (from 80 to 220 kts), at the base of the air shaft. Two types of microburst exist, wet and dry. Five color displays are used to show precipitations, turbulence and ground mapping to the crew. The location of the windshear events, if the Predictive Windshear System is operative, is indicated by an icon (symbol consisting of alternating red and black arcs).

  EFF : ALL  34-41-00 Page 1   Config-3 Feb 01/10  CES

 

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**ON A/C 051-099, 106-149, 201-233, 236-238,

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The aircraft is equipped with an X-band weather radar system with Predictive Windshear capability. This system complies with the ARINC Characteristics 708A. The weather radar system enables: - detection and localization of the atmospheric disturbances in the area defined by the antenna scanning: plus or minus 90 deg. of aircraft centerline and up to 320NM in front of the aircraft, - detection of turbulence areas caused by the presence of precipitations up to a distance of 40NM, - presentation of terrain mapping information by the combination of the orientation of the radar beam and of the receiver gain, - detection, if the Predictive Windshear System is operative, of a microburst windshear event in the area defined by the antenna scanning: plus or minus 60 deg. - presentation, if the Predictive Windshear System is operative, of windshear events within an area plus or minus 30 deg. of aircraft centerline and up to 5NM in front of the aircraft.

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NOTE : A microburst is a cool shaft of air, like a cylinder, between 1000 ____ and 3000 ft. When it encounters the ground (airflow velocity from 40 to 110 kts) the downward moving airflow is translated to a horizontal flow (from 80 to 220 kts), at the base of the air shaft. Two types of microburst exist, wet and dry.

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Five color displays are used to show precipitations, turbulence and ground mapping to the crew. The location of the windshear events, if the Predictive Windshear System is operative, is indicated by an icon (symbol consisting of alternating red and black arcs).

  R EFF : 051-099, 106-149, 201-233, 236-238,  34-41-00 Page 2   Config-3 May 01/09  CES

 

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**ON A/C 234-235, 239-249, 251-299, 301-399, 401-499,

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The aircraft is equipped with an X-band dual Collins WXR-2100 Multiscan Radar transceiver P/N 822-1710-202 with Predictive Windshear System (PWS). This system is compatible with Electronic Instrument System 1 and 2 (EIS1 and EIS2) and complies with ARINC Characteristics 708A. Multiscan is a radar function that displays all significant weather at all ranges, at all aircraft altitudes, and at all times on a display that is essentially clutter-free, without the need for pilots to input tilt or gain settings. Multiscan reduces pilot workload while enhancing weather detection capability. The Multiscan function optimizes weather detection and minimizes ground clutter. This function determines the optimum tilt angle for the radar through monitoring of: - the aircraft altitude above the terrain (RA and ADR information). - the aircraft position (IR information). - the terrain conditions in the area (information located in an interval Reference table).

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NOTE : A microburst is a cool shaft of air, like a cylinder, between 1000 ____ and 3000 ft. When it encounters the ground (airflow velocity from 40 to 110 kts) the downward moving airflow is translated to a horizontal

Two antenna scans are performed, each scan is optimized for a particular region in front of the aircraft. The upper beam detects medium-range weather and the lower beam detects short and long-range weather by automatically adjusting tilt and gain. The information is then stored in a temporary database. When the captain or the first officer selects a range, the weather radar transceiver retrieves the appropriate portions of the desired information, merges the data and then eliminates ground clutter. The result is an optimized weather display and the flight crew selects the range scale required.

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In the following text, the abbreviation WXR/PWS is used. The WXR/PWS enables: detection and localization of the atmospheric disturbances in the area defined by the antenna scanning: plus or minus 90 deg. of aircraft centerline and up to 320NM in front of the aircraft detection of turbulence areas caused by the presence of precipitations up to a distance of 40NM presentation of terrain mapping information by the combination of the orientation of the radar beam and of the receiver gain detection of a microburst windshear event in the area defined by the antenna scanning: plus or minus 60 deg. presentation of windshear events within an area plus or minus 30 deg. of aircraft centerline and up to 5NM in front of the aircraft.

  EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page 3 401-499,  Config-3 May 01/09  CES

 

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flow (from 80 to 220 kts), at the base of the air shaft. Two types of microburst exist, wet and dry.

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Five color displays are used to show precipitations, turbulence and ground mapping to the crew. The location of the windshear events is indicated by an icon (symbol consisting of alternating red and black arcs).

  R EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page 4 401-499,  Config-3 May 01/09  CES

 

**ON A/C ALL 2. __________________ Component Location R

**ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, **ON A/C 001-049, 101-105, (Ref. Fig. 001)

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**ON A/C 106-149, 151-199, 201-238, 301-310, 401-499, (Ref. Fig. 001B) **ON A/C 001-049, 101-105, (Ref. Fig. 002) **ON A/C 106-149, 201-233, 236-238, (Ref. Fig. 002A) **ON A/C 151-199, (Ref. Fig. 002B)

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**ON A/C 234-235, 301-310, 401-499, (Ref. Fig. 002C)

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**ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, The units of the weather radar system are located in the aircraft as follows:

  EFF : ALL  34-41-00 Page 5   Config-3 Nov 01/09  CES

 

Weather Radar - Component Location Figure 001

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  R EFF : 001-049, 101-105,  34-41-00 Page 6   Config-3 May 01/09  CES

 

Weather Radar - Component Location Figure 001A   R EFF : 051-099, 239-249, 251-299, 311-399,  34-41-00 Page 7 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

Weather Radar - Component Location Figure 001B   R EFF : 106-149, 151-199, 201-238, 301-310,  34-41-00 Page 8 401-499,  Config-3 Nov 01/09  CES

 

Weather Radar - Control and Indicating Figure 002   R EFF : 001-049, 101-105,  34-41-00 Page 9   Config-3 Nov 01/08  CES

 

Weather Radar - Control and Indicating Figure 002A   R EFF : 051-099, 106-149, 201-233, 236-238,  34-41-00 Page 10   Config-3 Feb 01/09  CES

 

Weather Radar - Control and Indicating Figure 002B   R EFF : 151-199,  34-41-00 Page 11   Config-3 Nov 01/08  CES

 

Weather Radar - Control and Indicating Figure 002C   R EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page 12 401-499,  Config-3 May 01/09  CES

 

------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1SQ1 XCVR-WEATHER RADAR, 1 109VU 121 811 34-41-33 3SQ CTL UNIT-WEATHER RADAR 11VU 210 831 34-41-12 7SQ DRIVE-WR ANTENNA 110 110AL 34-41-11 9SQ MTG TRAY-WR XCVR 109VU 121 811 34-41-37 11SQ ANTENNA-WEATHER RADAR 110 110AL 34-41-11

  R EFF : 001-049, 101-149, 151-199, 201-238,  34-41-00 Page 13 301-310, 401-499,  Config-3 Nov 01/09  CES

 

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**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, (Ref. Fig. 001A) **ON A/C 051-099, (Ref. Fig. 002A) **ON A/C 239-249, 251-299, 311-399, (Ref. Fig. 002C)

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**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 002D)

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**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, The components of the weather radar system are located in the aircraft as follows: ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1SQ1 XCVR-WEATHER RADAR, 1 109VU 121 811 34-41-33 1SQ2 XCVR-WEATHER RADAR, 2 109VU 121 811 34-41-33 3SQ CTL UNIT-WEATHER RADAR 11VU 210 831 34-41-12 7SQ DRIVE-WR ANTENNA 110 110AL 34-41-11 9SQ MTG TRAY-WR XCVR 109VU 121 811 34-41-37 11SQ ANTENNA-WEATHER RADAR 110 110AL 34-41-11

  R EFF : 051-099, 239-249, 251-299, 311-399,  34-41-00 Page 14 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

Weather Radar - Control and Indicating Figure 002D   R EFF : 501-509, 511-526, 528-599,  34-41-00 Page 15   Config-3 Feb 01/10  CES

 

**ON A/C ALL 3. __________________ System Description **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 003) **ON A/C 051-099, (Ref. Fig. 003A) **ON A/C 106-149, 201-233, 236-238, (Ref. Fig. 003B) **ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, (Ref. Fig. 003C) R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 003D) **ON A/C 001-049, 101-105, (Ref. Fig. 004)

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**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, (Ref. Fig. 004A) **ON A/C 106-149, 201-238, 301-310, 401-499, (Ref. Fig. 004B)

  EFF : ALL  34-41-00 Page 16   Config-3 Feb 01/10  CES

 

Weather Radar Block Diagram - Data Acquisition Figure 003

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  EFF : 001-049, 101-105, 151-199,  34-41-00 Page 17   Config-3 May 01/09  CES

 

Weather Radar Block Diagram - Data Acquisition Figure 003A   R EFF : 051-099,  34-41-00 Page 18   Config-3 Nov 01/08  CES

 

Weather Radar Block Diagram - Data Acquisition Figure 003B   R EFF : 106-149, 201-233, 236-238,  34-41-00 Page 19   Config-3 Nov 01/08  CES

 

Weather Radar Block Diagram - Data Acquisition Figure 003C   R EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page 20 401-499,  Config-3 May 01/09  CES

 

Weather Radar Block Diagram - Data Acquisition Figure 003D   R EFF : 501-509, 511-526, 528-599,  34-41-00 Page 21   Config-3 Feb 01/10  CES

 

Weather Radar Block Diagram - Control and Display Figure 004

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  R EFF : 001-049, 101-105,  34-41-00 Page 22   Config-3 May 01/09  CES

 

Weather Radar Block Diagram - Control and Display Figure 004A   R EFF : 051-099, 239-249, 251-299, 311-399,  34-41-00 Page 23 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

Weather Radar Block Diagram - Control and Display Figure 004B   R EFF : 106-149, 201-238, 301-310, 401-499,  34-41-00 Page 24   Config-3 Nov 01/09  CES

 

**ON A/C 151-199, (Ref. Fig. 004C) **ON A/C ALL The WR/PWS is composed of items closely associated with its operation, such as peripherals supplying parameters, EFIS display units or maintenance functions. NOTE : The weather radar image is shown on the CAPT and F/O Navigation ____ Displays (ND). The NDs are connected to the three Display Management Computers (DMC) and to the CAPT and F/O EFIS control panels of the FCU. NOTE : The three ADIRUs give data information to the weather radar system. ____ These data ensure the radar antenna stabilization and the computations of the windshear function. R

**ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, A. General The weather radar system, which complies with ARINC Characteristics 708A, consists of: - a transceiver 1SQ1, - a control unit 3SQ, - an antenna drive 7SQ, - an antenna plate 11SQ, - a transceiver single mounting tray 9SQ with a wave guide. (1) Weather Radar Transceiver The receiver-transmitter is the heart of the WR/PWS system, the additional necessary wiring and interfaces enable the weather radar transceiver to operate as a PWS (WR/PWS) and autotilt. The receiver-transmitter ensures the following functions: - generation of the very short intense pulses of microwave energy via an X-band wave guide to the antenna, and the processing of their echoes (radio frequency signals) to obtain the desired information, - the receiver signal is formatted into 1600-bit ARINC 453 words and sent to the Display Management Computers (DMCs), - acquisition of data from Radio Altimeters (RA1 and RA2) and other specific interfaces, - windshear event detection and generation of the appropriate signal, - BITE function of the system.

  EFF : ALL  34-41-00 Page 25   Config-3 Nov 01/09  CES

 

Weather Radar Block Diagram - Control and Display Figure 004C   R EFF : 151-199,  34-41-00 Page 26   Config-3 May 01/09  CES

 

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**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, A. General The weather radar system, which complies with ARINC Characteristics 708A, consists of: - two transceivers 1SQ1, 1SQ2, - a dual control unit 3SQ, - a dual antenna drive 7SQ, - an antenna plate 11SQ, - a transceiver dual mounting tray 9SQ with a wave guide switch. (1) Weather Radar Transceiver The receiver-transmitter is the heart of the WR/PWS system, the additional necessary wiring and interfaces enable the weather radar transceiver to operate as a PWS (WR/PWS). The receiver-transmitter ensures the following functions: - generation of the very short intense pulses of microwave energy via an X-band wave guide to the antenna, and the processing of their echoes (radio frequency signals) to obtain the desired information, - the receiver signal is formatted into 1600-bit ARINC 453 words and sent to the Display Management Computers (DMCs), - acquisition of data from Radio Altimeters (RA1 and RA2) and other specific interfaces, - windshear event detection and generation of the appropriate signal, - BITE function of the system. **ON A/C 001-049, 101-149, 151-199, 201-233, 236-238, (2) Weather Radar Control Unit The control unit generates a 32-bit (label 270) serial control word which describes the selected operating modes (system activation, weather radar modes, activation of the predictive windshear function). The transceiver receives one ARINC 429 bus coming from the control unit. Moreover, the predictive windshear function can be de-activated if the PWS does not operate correctly. (3) WR Antenna Drive The WR antenna drive is the interface of the transceiver to control and monitor the azimuth and elevation of the antenna. (4) Weather Radar Antenna The antenna is used for transmitting and receiving radar radio frequency signals.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-41-00 Page 27 201-233, 236-249, 251-299, 311-399, 501-509,  Config-3 Feb 01/10 511-526, 528-599, CES

 

(5) Transceiver Mounting Tray with a Wave Guide It allows to install the transceiver on the aircraft rack and connects the transceiver to the wave guide. **ON A/C 051-099, (2) Weather Radar Control Unit The control unit generates a 32-bit (label 270) serial control word which describes the selected operating modes (system activation, weather radar modes, activation of the predictive windshear function). The transceiver receives one ARINC 429 bus coming from the control unit. Moreover, the predictive windshear function can be de-activated if the PWS does not operate correctly. (3) WR Antenna Drive The WR antenna drive is the interface of the transceiver to control and monitor the azimuth and elevation of the antenna. (4) Weather Radar Antenna The antenna is used for transmitting and receiving radar radio frequency signals. (5) Transceiver Dual Mounting Tray with a Wave Guide It allows to install each transceiver on the aircraft rack and connects the activated transceiver to the wave guide. The wave guide switch is integral with the mounting tray. It ensures switching of the RF signal from the antenna to each transceiver. Moreover, control circuits recopy the wave guide switch position to avoid transmission on a closed wave guide. R

**ON A/C 234-235, 301-310, 401-499, (2) Weather Radar Control Unit The control unit generates a 32-bit (label 270) serial control word which describes the selected operating modes (1/OFF/2, WX, WX + T, TURB, MAP, PWS, GCS, MULTISCAN, GAIN TILT). The WR/PWS receives one ARINC 429 bus coming from the control unit. Moreover, the predictive windshear function can be de-activated if the PWS does not operate correctly.

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(3) WR Antenna Drive The WXR/PWS has one antenna drive which is the interface of the transceiver to control and monitor the azimuth and elevation of the antenna. (4) Weather Radar Antenna The antenna is used for transmitting and receiving radar radio frequency signals. (5) Transceiver Mounting Tray with a Wave Guide It allows to install the transceiver on the aircraft rack and connects the transceiver to the wave guide. **ON A/C 239-249, 251-299, 311-399, (2) Weather Radar dual Control Unit The control unit generates a 32-bit (label 270) serial control word which describes the selected operating modes (1/OFF/2, WX, WX + T, TURB, MAP, PWS, GCS, MULTISCAN, GAIN TILT). The WR/PWS receives one ARINC 429 bus coming from the control unit. Moreover, the predictive windshear function can be de-activated if the PWS does not operate correctly. (3) WR Antenna Drive The WXR/PWS has one dual antenna drive which is the interface of each transceiver to control and monitor the azimuth and elevation of the antenna. (4) Weather Radar Antenna The antenna is used for transmitting and receiving radar radio frequency signals. (5) Transceiver Dual Mounting Tray with a Wave Guide It allows to install each transceiver on the aircraft rack and connects the activated transceiver to the wave guide. R

**ON A/C 501-509, 511-526, 528-599, (2) Weather Radar dual Control Unit The control unit generates a 32-bit (label 270) serial control word which describes the selected operating modes (1/OFF/2, MAN/TILT/AUTO, WX, WX/TURB, MAP, W/S). The WR/PWS receives one ARINC 429 bus coming from the control unit. Moreover, the predictive windshear function can be de-activated if the PWS does not operate correctly.

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The Autotilt control panel with MAN/TILT/AUTO switch included, it permits the selection of manual tilt or automatic tilt. (3) WR Antenna Drive The WR antenna drive is the interface of the transceiver to control and monitor the azimuth and elevation of the antenna. (4) Weather Radar Antenna Plate The antenna is used for transmitting and receiving radar radio frequency signals. (5) Transceiver Dual Mounting Tray with a Wave Guide It allows to install each transceiver on the aircraft rack and connects the activated transceiver to the wave guide. The wave guide switch is integral with the mounting tray. It ensures switching of the RF signal from the antenna to each transceiver. Moreover, control circuits recopy the wave guide switch position to avoid transmission on a closed wave guide. **ON A/C ALL NOTE : The weather radar and windshear detection image (if the ____ predictive windshear function is activated) is shown on the Captain and First Officer Navigation Displays (ND) and the windshear warning is shown on Captain and First Officer Primary Flight Displays (PFD) and on the upper ECAM DU. The NDs and PFDs are connected to the three Display Management Computers (DMC) and to the Captain and First Officer EFIS control sections of the FCU. NOTE : If the Enhanced GPWS is operative, the WR image is replaced by ____ the terrain image, on the Captain and First Officer NDs, during a terrain alert or a crew action. More explanations are given in 34-48. NOTE : The ADIRUs give to the weather radar system: ____ - the altitude and the true airspeed (TAS) information (Ref. 34-13-00), - the attitude, ground speed, magnetic heading, true heading, E/W velocity, N/S velocity, track angle and drift angle (Ref. 34-14-00). These data ensure the radar antenna stabilization and the corrections of the Doppler mode (turbulence).

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R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 501-509, 511-526, 528-599, B. Peripherals (1) Digital serial data inputs The transceiver receives digital serial data inputs from the following components: (a) Radio Altimeter The Radio Altimeter provides altitude information over two ARINC 429 bus inputs to the WR/PWS (label 164). This data is used for automatic activation of the windshear function. The second bus is for redundancy. (b) Air Data Reference Two ARINC 429 low-speed buses provide: - true airspeed data (label 210) used for velocity calculations - altitude data (label 203) used for sensitivity time control (STC) calculations - corrected altitude data (label 204) used only when label 203 is not available. (c) Inertial Reference Two ARINC 429 high-speed buses provide: - pitch (label 324) and roll (label 325) data for the stabilization and control of the antenna - east/west velocity (label 367) and north/south velocity (label 366) used for velocity calculations - ground speed (label 312) used for velocity calculations - track angle (label 317) used for velocity calculations - true heading (label 314) - Magnetic heading (label 320) - ADIRU align mode (label 270). NOTE : The main air data and heading altitude data are provided ____ by the Air Data/Inertial Reference System (ADIRS). (d) Centralized Fault Display Interface Unit (CFDIU) The WR/PWS communicates with the CFDIU low-speed ARINC 429 buses.

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(e) EFIS Control Section Two ARINC 429 buses provide the CAPT and F/O range selection (label 271). The receiver/transmitter receives one bus from the CAPT EFIS control section and another one from the F/O EFIS control section. (2) Discrete inputs The transceiver receives the following discrete inputs: (a) Ground/flight signal and landing gear extended signal. These signals are provided by the Landing Gear Control and Interface Unit (LGCIU). - Ground/flight signal is used to determine the identifying flight phase for BITE - Landing gear extended signal is used to determine transition from landing mode to takeoff mode to identify a GO AROUND condition. In this case the appropriate aural message is generated. (b) Qualifiers A and B signals (if predictive windshear function is activated) Two types of qualifier inputs are used to control automatic activation of the windshear function. - qualifiers A: two qualifiers A inputs are used. These input signals are provided by the ATC/TCAS control unit. The qualifier A1 signal coming from J1 ATC/TCAS control unit is connected to the WR/PWS transceiver. The qualifier A2 signal coming from J2 ATC/TCAS control unit is connected to the WR/PWS transceiver. The qualifier A2 is for redundancy. This qualifier A is considered valid when one ATC transponder is selected in operative mode on the ATC/TCAS control unit. - qualifiers B: two qualifiers B inputs are also used. These input signals are provided by the engine oil pressure sensors indicating when there is normal operating pressure. The qualifier B1 is connected to engine 1 and the qualifier B2 is connected to engine 2. Qualifiers B1 and B2 are connected to the transceiver. This qualifier B is considered valid when the engine is running (high oil pressure). To automatically activate the windshear function, one of the qualifiers A and one of the qualifiers B have to be valid.

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(c) Windshear function enable signal (if predictive windshear function is activated) This discrete input provided by the weather radar control unit through the windshear AUTO/OFF switch activates the windshear function. This discrete signal is also transmitted to the DMCs which use it for the logic of windshear messages displayed. (d) Windshear BITE enable signal (if predictive windshear function is activated) This discrete input allows the WR/PWS to manage the BITE windshear failures sent to the CFDIU. **ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, B. Peripherals (1) Digital serial data inputs The transceiver receives digital serial data inputs from the following components: (a) Radio Altimeter The Radio Altimeter provides altitude information over two ARINC 429 bus inputs to the WR/PWS (label 164). This data is used for automatic activation of the windshear function. The second bus is for redundancy. (b) Air Data Reference Two ARINC 429 low-speed buses provide: - true airspeed data (label 210) used for velocity calculations - altitude data (label 203) used for sensitivity time control (STC) calculations - corrected altitude data (label 206). (c) Inertial Reference Two ARINC 429 high-speed buses provide: - pitch (label 324) and roll (label 325) data for the stabilization and control of the antenna - east/west velocity (label 367) and north/south velocity (label 366) used for velocity calculations - ground speed (label 312) used for velocity calculations and qualifiers C1, C2 - track angle (label 317) used for velocity calculations - true heading (label 314) - Magnetic heading (label 320)

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- Body longitudinal acceleration (label 331) used for qualifiers D1, D2. NOTE : The main air data and heading altitude data are provided ____ by the Air Data/Inertial Reference System (ADIRS). (d) Centralized Fault Display Interface Unit (CFDIU) The WR/PWS communicates with the CFDIU low-speed ARINC 429 buses. (e) EFIS Control Section Two ARINC 429 buses provide the CAPT and F/O range selection (label 271). The receiver/transmitter receives one bus from the CAPT EFIS control section and another one from the F/O EFIS control panel. (f) One ARINc 429 high-speed bus (Hazard) provides radar data to be recorded on the Flight Data Interface and Management Unit (FDIMU). (g) One ARINC 429 high-speed bus (Hazard) provides radar data to the Enhanced Ground Proximity Warning System (EGPWS). (2) Discrete inputs Each transceiver receives the following discrete inputs: (a) Ground/flight signal and landing gear extended signal. These signals are provided by the Landing Gear Control and Interface Unit (LGCIU). - Ground/flight signal is used to determine the identifying flight phase for BITE - Landing gear extended signal is used to determine transition from landing mode to takeoff mode to identify a GO AROUND condition. In this case the appropriate aural message is generated. (b) Qualifiers B, C, D signals (new qualifier logic/qualifier A: ATC is no more used). Two types of qualifier inputs are used to control automatic activation of the windshear function (B and C or B and D). - qualifiers B: two qualifiers B inputs are used. These input signals are provided by the engine oil pressure sensors indicating when there is normal operating pressure. The qualifier B1 is connected to engine 1 and the qualifier B2 is connected to engine 2. The qualifier B2 is for redundancy. Qualifiers B1 and B2 are connected to transceivers 1 and 2. - Qualifiers C: two qualifiers C inputs are used.

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Qualifier C1: ground speed (label 312 provided by IR bus from IR1) (valid when GS > 30Kts).(Ref. asterisk below) Qualifier C2: ground speed (label 312 provided by IR bus from IR3) (valid when GS > 30Kts). - Qualifiers D: two qualifiers D inputs are used. Qualifier D1: body longitudinal acceleration (label 331 provided by IR bus from IR1) (valid when Nx > 0.07g for at least 0.5 seconds).(Ref. asterisk below) Qualifier D2: body longitudinal acceleration (label 331 provided by IR bus from IR3) (valid when Nx > 0.07g for at least 0.5 seconds). (*) For the second transceiver, C1 and D1 information is provided by IR2. To automatically activate the windshear function, one of the qualifiers B and one of the qualifiers C or D have to be valid. (c) Windshear function enable signal This discrete input provided by the weather radar control unit through switch AUTO/OFF enables the windshear function. This discrete signal is also transmitted to the DMCs which use it for the logic of windshear messages displayed. (d) Windshear BITE enable signal This discrete input allows the WXR/PWS to manage the BITE windshear failures sent to the CFDIU. **ON A/C ALL (3) Outputs The transceiver provides the following outputs: (a) Displays The WR/PWS is connected to the DMCs by an ARINC 453 bus to transmit the weather radar data and windshear data (if predictive windshear function is activated) on the data word of label 055. All the weather and windshear data received by the DMCs are processed to display weather radar image and windshear events by the Electronic Instrument System (EIS). 1 _

The Navigation Display (ND) it provides the following indications: - weather radar image - windshear events location for advisory, caution or warning alert - windshear failures.

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2 _

The Primary Flight Display (PFD) it provides all visual alerts for caution or warning alert. NOTE : The Flight Warning Computers (FWC) and the FDIU receive ____ WR/PWS data through the DMCs. These data are used by the FWCs to display windshear function failure and windshear function de-activation. The FDIU records the windshear alert and failure.

(b) Centralized Fault Display System (CFDS) The WR/PWS is connected to the CFDS to transmit the following words: - label 354: LRU identification P/N and S/N (coded in ISO5) - label 356: fault message (coded in ISO5) - label 377: equipment identification. (c) Audio Mixing Box (if predictive windshear function is activated) An analog audio output allows to transmit the aural alert windshear (synthetic voice message) to an audio mixing box connected to loud speakers. (d) Enhanced Ground Proximity Warning System (Enhanced GPWS) (optional) The Enhanced GPWS receives WR/PWS alerts from WXR1 Hazard bus and WXR2 Hazard bus (when the second transceiver is installed) to determine the alert priorities. Predictive Windshear alerts override a terrain display and revert to the WR display with the corresponding windshear data. The alert priorities between the WR/PWS and the Enhanced GPWS have been defined as follows: 1- WR/PWS Warning, 2- WR/PWS Caution, 3- Terrain Warning, 4- Terrain Caution, 5- WR/PWS advisory (no audio), 6- Terrain background (no audio). (e) Flight Data Interface and Management Unit (FDIMU) One ARINC 429 high speed bus (hazard) provides radar data to be recorded on FDIMU. (f) Windshear function enable signal This discrete input provided by the radar control box through AUTO/OFF switch enables the windshear function. This discrete signal is also transmitted to the DMCs which use it for the logic of windshear messages displayed.

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(4) Audio Inhibit Discrete Signals (if predictive windshear function is activated) These discretes are used to indicate whether the aural alert output has to be active or not: - predictive windshear aural alerts (audio inhibit discrete input) are inhibited by the Reactive Windshear System and stall warning. - predictive windshear audio inhibit discrete output is used to inhibit other aural alerts generated by systems such as: Traffic Alert and Collision Avoidance System (TCAS) or Ground Proximity Warning System (GPWS) or other FWC warnings. This inhibition occurs each time there is a PWS aural alert. (5) Pin Programming (if predictive windshear function is activated) - audio level program pins set the audio output level of the synthetic voice for windshear aural alert. - SDI (Source Destination Identification Encoder) program pins encode the location of the WR/PWS unit on the aircraft when two transceivers are installed. - qualifier polarity program pins: for both qualifiers, this pin program indicates the validity of the signal. - CFDIU interface program pins: when the second WR/PWS is installed on the aircraft, this program pin is activated. The WR/PWS can communicate with the CFDIU. - caution alert audio program: two program pins are provided to select the type of windshear caution aural alert. The MONITOR RADAR DISPLAY synthetic voice is generated instead of the chime. - windshear function enable program pins is used to activate the windshear function. - windshear function bite enable signal allows to send to CFDIU failure related to the predictive windshear function. C. General Technical Characteristics The WR/PWS system is mainly used to detect and localize various types of atmospheric disturbances and windshear events in the area scanned by the antenna. The system shows the disturbance intensity through the use of colors which vary with the atmospheric precipitation rate. The disturbances are shown to the crew members on the NDs with different colors: - black, green, yellow, red to quantify the precipitation rates - magenta to represent the turbulence areas up to 40 NM. The system can show the location of the windshear events via the NDs: alternating black and red arcs depict the windshear event. As the minimum display range is 10 NM, two yellow radials appear at the edges and start beyond the windshear (W/S) event.

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4. ____________ Power Supply **ON A/C 001-049, 101-105, 151-199, Energization of the system is through a 115VAC/400 Hz bus: - 1XP via the busbar 101 XP-C for transceiver 1 Energization of the weather radar control unit and of the WR antenna drive is through the transceiver. Consumption of the transceiver is 125 W nominal. **ON A/C 051-099, 239-249, 251-299, 311-399, Energization of the system is through a 115VAC/400 Hz bus: - 1XP via the sub-busbar 101 XP-C for transceiver 1, - 2XP via the sub-busbar 202 XP-A for transceiver 2. Energization of the weather radar control unit and of the WR antenna drive is through the selected transceiver. Consumption of the transceiver is 145 W maximum. **ON A/C 106-149, 201-238, 301-310, 401-499, Energization of the system is through a 115VAC/400 Hz bus: - 1XP via the sub-busbar 101 XP-C for transceiver 1. Energization of the weather radar control unit and of the WR antenna drive is through the transceiver. Consumption of the transceiver is 145 W maximum. R

**ON A/C 501-509, 511-526, 528-599, Energization of the system is through a 115VAC/400 Hz bus: - 1XP via the sub-busbar 101 XP-C for transceiver 1 - 2XP via the sub-busbar 202 XP-A for transceiver 2. Energization of the weather radar control unit and of the WR antenna drive is through the selected transceiver. Consumption of the transceiver is 165 W maximum.

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**ON A/C ALL The system is supplied through this circuit breaker: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL 5. Interface _________ A. Digital Interface Special for Weather Radar The weather radar data are transmitted via ARINC 429 and 453 buses in compliance with ARINC 708A. The table below contains all the output parameters in the digital form. ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 055 | WXR DATA | | | |1600|7.82| DIS| | | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 270 | CONTROL | | | | 32 |100 | DIS| | | | | WORD 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 271 | CONTROL | | | | 32 |100 | DIS| | | | | WORD 2 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 356 | Mainte- | | | | |100 |ISO5| | | | | nance | | | | | | | | | | | message | | | | | | | | | | | word | | | | | | | | | -------------------------------------------------------------------------------

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(1) Control Words (Labels 270 and 271) The control words are transmitted on the control buses which connect the weather radar control unit to the transceiver. The control word 1 (label 270) provides the following data: - gain, - tilt angle, - selected mode, - stabilization (on/off), - scan angle (normal/reduced), - anticlutter (on/off) (optional) - split function (Capt/Both/F/O) (optional) The control word 2 (label 271) provides the following data: - range, - anticlutter (on/off) (optional), - WR selected on the EFIS control section (master/slave). (2) Data Word (Label 055) The signal transmitted on the data bus line which connects the WR/PWS to the Display Management Computers (DMC) complies with data word format (label 055) as defined by the ARINC Specification 708A (Appendix 15.2). The data bus line transmits 190 data words per second; each word is made up of 1600 bits sent on 1 Megabit/s frequency (ARINC Specification 453) as per MANCHESTER II BI PHASE 2 format. (Ref. Fig. 005) Data word message includes mainly the radar return intensity and windshear data.

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Weather Radar - Manchester II Biphase Format Figure 005   R EFF : ALL  34-41-00 Page 43   Config-3 Nov 01/08  CES

 

----------------------------------------------------------------------------| BITS | FUNCTION | |----------|----------------------------------------------------------------| | 1-8 | Label 00101101 : 055 | | 9-10 | Control Accept | | 11 | Spare | | 12 | Windshear Caution | | 13 | Windshear Warning | | 14-15 | Turbulence and Weather Alert | | 16 | Anticlutter (not used) | | 17 | Sector Scan | | 18 | Stabilization Limits | | 19 | Cooling Transceiver | | 20 | Display Fault (not used) | | 21 | Calibration or Air Data Input | | 22 | Attitude Input | | 23 | Control or Heading Input | | 24 | Antenna | | 25 | R/T or Radio Altimeter | | 26 | Stabilization | | 27-29 | Mode | | 30-36 | Tilt Angle | | 37-42 | Gain | | 43-48 | Range | | 49 | Windshear External Input Fault | | 50-51 | Data Accept | | 52-63 | Scan Angle | | 64 | Windshear Failure | | 65-1600 | Range Bin Data | ----------------------------------------------------------------------------The WR/PWS uses the Space address usage technology defined by the ARINC specification 708A for transmission of information on data bus lines. This is achieved by two different data bus lines, each associated with a control bus line from an EFIS control section of the FCU. Data BUS 1 transmits always data associated to the range selected on EFIS/CAPT (side 1). Data BUS 2 transmits always data associated to the range selected on EFIS/F/O (side 2). The control and data bits of word label 055 are valid at any moment on both DATA BUSES, even if the range selected on sides 1 and 2 of FCU are different.

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6. _____________________ Component Description R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, A. Transceiver **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 006)

R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 006D)

R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, (Ref. Fig. 007) The weather radar transceiver with PWS is a lightweight airborne unit. The transmitter section consists of a crystal-controlled reference oscillator, driver stage and a power amplifier output stage. Pulse widths are either 1.5 microseconds (used to produce the calculated windshear hazard presentation), 6 microseconds or 18 microseconds. Echoes from both the 6 and 18-microsecond pulses are processed to produce targets between 20 and 40 NM. The 6-microsecond pulses are also used for turbulence detection. The master processor is the host control computer for the weather radar system with PWS. It also produces the timing and control signals that control the operations of the modulator/transmitter and receiver, and the weather, turbulence and windshear digital signal processor circuits. The master processor decodes the ARINC 429 mode information from the control unit and selected range. During the transmit period, the radio frequency front end, through its waveguide element, sends the pulse-modulated X-band radar signal to the radar antenna. During the receive period, the radio frequency front end receives signals through the waveguide element and through a filter to the preamplifier. The received signal is mixed to produce the 212 MHz signal which is sent to the receiver. The receiver operates with digital slow AGC and provides high-gain narrow-band amplification. It converts the 212 MHz first i-f signal to a 5 MHz third i-f signal.

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Weather radar - Architecture Figure 006

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Weather radar - Architecture Figure 006A   R EFF : 051-099,  34-41-00 Page 47   Config-3 Nov 01/08  CES

 

Weather radar - Architecture Figure 006B   R EFF : 106-149, 201-233, 236-238,  34-41-00 Page 48   Config-3 Nov 01/08  CES

 

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Weather radar - Architecture Figure 006D   R EFF : 501-509, 511-526, 528-599,  34-41-00 Page 50   Config-3 Feb 01/10  CES

 

Weather Radar Transceiver - Component Description Figure 007   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page 51 511-526, 528-599,  Config-3 Feb 01/10  CES

 

The receiver 5MHz i-f signal output is applied to an analog-to-digital (A/D) converter at the input to the digital signal processor (DSP) subsystem. The analog-to-digital converter digitizes the detected video signal from the receiver. Three separate video processors process the digitized video signal to accommodate three radar displays with independent range selection. The video processor averages the digitized video data within each range bin. A range bin is defined as the range interval over which the radar data are derived. This is determined by the division of the selected range into 512 equal increments. The range averaged data are stored and filtered at each transmission by the video processors. The ARINC 453 interface circuits format the outputs of the video processors and send them to the DMCs and the EFIS. The antenna stabilization circuit is internal to the weather radar transceiver with PWS and is built around a 16-bit microprocessor. It is controlled by a servo loop. Five angles are provided to the microprocessor to solve the stabilization equation (line of sight): - aircraft pitch and roll angles - selected antenna tilt angle - antenna elevation angle - antenna azimuth angle. The aircraft pitch and roll angles are transmitted by the Air Data/Inertial Reference Units (ADIRUs) in the form of ARINC 429 messages. Only the antenna azimuth control is an open loop and the microprocessor generates the antenna feedback signal. The antenna reaches plus or minus 90 deg., on either side of the aircraft centerline. The microprocessor generates the control signals of the elevation and azimuth drive motors of the antenna; the corresponding angular positions are recopied by synchros located in the antenna and processed by the microprocessor. The output data of the linear amplifier is processed for comparison of the detected signals with a threshold said of medium turbulence. Furthermore corrections are made with respect to the selected tilt angle and to the ground speed transmitted by the attitude bus. The control and monitoring circuit is used for the control of the transceiver, the monitoring circuit of the video processors and the ARINC 429 interface circuits. In addition, the control circuit determines the operating mode of the weather radar, the system gain, the tilt angle and the range selection for the video processor. During the program loop, selected inputs are checked or compared to determine the operational status of the weather radar system with PWS. The results of these checks or comparisons are used to display fault warning messages on the display units and to the Liquid Crystal Display of the front panel of the transceiver.

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The display contains a sequence of software controlled pushbutton switches that result in different functions when pressed. Once the TEST pushbutton switch is pressed, the display shows TEST IN PROGRESS. At the end of the test, the display shows RADAR OK, INPUT OK if no faults were detected in either the radar or input connections. The maintenance circuit with processor ensures formatting of signals and the interface with the CFDS. The processor is continuously supplied to answer the interrogations of the CFDS. In addition, it has access to a non volatile fault memory to report all failure conditions. The monitor processor also enables to activate the system complete test from the CFDS. The different flight phases are generated from a flight/ground discrete provided by the Landing Gear Control and Interface Unit (LGCIU). This discrete enables the CFDS flight phases to be consolidated. (1) Not Applicable (2) Not Applicable (3) Not Applicable (4) Not Applicable (5) Not Applicable (6) Not Applicable (7) Not Applicable (8) Not Applicable (9) Not Applicable (10) Not Applicable (11) Not Applicable **ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, A. Transceiver **ON A/C 051-099, (Ref. Fig. 006A)

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**ON A/C 106-149, 201-233, 236-238, (Ref. Fig. 006B) R

**ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, (Ref. Fig. 006C)

R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, (Ref. Fig. 007A) The weather radar transceiver with PWS is a completely solid-state airborne unit. It contains: (1) A power amplifier A single 777.77 MHz multiplier drive signal is developed by the power amplifier. The power amplification of the transmit section is accomplished by splitting the power amplifier drive before recombining the signals into a single multiplier drive signal. (2) A power multiplier The power multiplier produces the 9333.24 MHz transmitter output signal from the single multiplier drive signal (from the power amplifier). The multiplier drive signal is multiplied by 3 to produce a 2333.31 MHz signal. The 2333.31 MHz signal is their quadrupled to produce the 9333.24 MHz transmitter output signal. (3) A duplexer/monitor The transmitter output is coupled through a duplexer/monitor to the waveguide antenna feed through a 4-port circulator. Incorporated in the duplexer operation are monitor circuits to monitor the output power level and develop a frequency loop error signal for the correction of frequency chirp. The monitor circuit also accepts a test signal which causes a portion of the reference signal to be injected into the receiver for test calibration. The 4-port circulator also couples the RF return from the waveguide antenna feed through the preamplifier to the receiver portion of the transceiver.

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Weather Radar Transceiver - Component Description Figure 007A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page 55 301-399, 401-499,  Config-3 May 01/09  CES

 

(4) A preamplifier The preamplifier assembly perform the waveguide limiter functions (protects the mixer diodes from all high power pulses), contains a noise diode circuit and contains a 2-stage RF amplifier which provides +18dB of RF gain. (5) A mixer The mixer circuit processes the detected RF return signal by mixing it with the First local oscillator signal and amplifying the resultant Intermediate Frequency (IF) signal in the First IF amplifier. The first IF amplifier provides 25dB amplification before the First IF signal is applied to the second IF amplifier. (6) A second IF amplifier The second IF amplifier completes the receiver amplification of the RF return signal. The output from the first IF is converted to the 13.8888 MHz second IF signal by mixing it with the 152.77 MHz second local oscillator signal. The second IF signal is double-buffered and applied to a synchronous detector. The third local oscillator signal is phase-split to obtain one signal in phase with the transmitter frequency and one signal phase shifted by 90 deg. (7) A sampler The sampler commands and controls the receive and transmit functions within the receiver-transmitter. A digital signal processor is used to control transmitter timing and receiver normalizer. (8) A digital signal processsor The digital signal processor circuit card performs the weather processing, clutter identification, clutter filtering, velocity extraction and editing, hazard computation and hazard recognition algorithms. Command and control information is passed from the digital signal processor to the sampler through a dual port RAM. (9) A central processing unit Control of internal functions, antenna servo controls, monitoring of system operation and formatting the processed data is accomplished by the central processing unit. It uses a microprocessor and a stored program to execute the following major routines that control the transceiver and system operations: - attitude routine, providing pitch and roll parameters for the stabilization routine - stabilization routine, providing elevation position to the elevation maintenance routine - scan maintenance routine, providing antenna scan drive

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- elevation maintenance routine, providing antenna elevation drive control bus manager routine, determining correct control configuration - problem control monitor routine, programming the internal data collection parameters of the transceiver - data bus formatter routine, processing and assembling the control message of the serial data word sent to the EFIS. (10) An input/output unit All interface functions between the microprocessor of the central processing unit and the rest of the transceiver and units in the system are provided by the input/output unit. Control word buses, digital and analog attitude buses, radio altitude inputs and discrete buses are all connected to the multiplexer and shift register of the input/output unit. In addition, the input/output unit contains speech circuits for windshear hazard annunciation, the synchro-to-digital conversion circuits, discrete warning annunciation outputs, aural warning outputs and remote turn-on circuits. (11) A BITE/monitor The BITE/monitor provides the BITE power supply voltages to BITE functions and circuits, a power monitor for the detected transmitter output and an interconnect for various signals used throughout the transceiver. R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, RF replacement modules: The transmitter, preamplifier and X54 modules of the RF portion of the RTA-4A/4B radar transmitter/receiver have been redesigned. Each of the three RF modules has been designed for complete compatibility and interchangeability with the original modules. As such, functional tests of the radar with the new modules are identical to those used for the original design. - X54 frequency multiplier module: The X54 frequency multiplier module replaces the existing X9, X6 and circulator assemblies in the RDR-4A and RDR-4B transmitter. This module multiplies and amplifies a 173 MHz (nominal) signal input from the frequency source board. The RF outputs a 1557 MHz signal used as the input to the receiver and a 9342 MHz signal for the transmitter. The X54 module includes a VHF amplifier stage, a X9 multiplier stage, an L-band amplifier, a transmit/receive switch, a X6

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multiplier, a modulated X-band amplifier, an isolator and a BITE circuit. Additionally, there is a bias regulation, control, modulation and temperature compensation circuitry to obtain the necessary control signals and bias voltages. - Preamplifier module: The RF preamplifier module includes a solid-state limiter, a low noise amplifier, an image-reject filter, a diode noise generator, a low-power X6 frequency multiplier, and the first mixer stage. The RF preamplifier receives the 9346 MHz (nominal) radar-return signals from the antenna/circulator and produces low-noise, high-gain preamplification and image-rejection filtering. The limiter is an active/passive pin-diode limiter. During transmission, it reduces the level of transmitter RF reaching the preamplifier circuitry. During reception, the limiter protects the preamplifier against the effects of transmissions from other nearby transmitters. - Transmitter module: The new RDR-4A/4B transmitter is based on standard RF amplifier technology using RF Field Effect Transistors (FET) distributed through four power-combined amplifier modules. The transistor amplifier does not produce any microwave signals of its own, but rather amplifies the microwave power provided by the older X6 and X9 multiplier module or the new X54 module. The failure of one of the four amplifier modules will not cause the overall failure of the transmitter, just a small reduction in output power level. The new transmitter has been designed to be a direct replacement for the existing IMPATT transmitter. It mounts using the same mounting points as the older IMPATT transmitter and uses the same power and logic cable connection as the older transmitter. This new transmitter provides roughly the same output power as the older transmitter and exhibits lower levels of electromagnetic interference (EMI) and lower levels of distortion (harmonics and spurious output) than the present transmitter. B. Weather Radar System The system has five modes of operation: - Weather - Weather with Turbulence detection - Ground Mapping - Autotilt - Windshear. The autotilt function is available on P/N:066-50008-0409.

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(1) Weather Radar The weather radar system RDR-4B provides storm detection up to a distance of approximately 320NM under ARINC 708A defined penetration environment. Cloud formations having less moisture content than required to reflect a minimum discernible echo signal do not appear on the ND. The color presentation gives an immediate indication of the location of severe storm areas. These areas might contain air turbulence which should be avoided. A microprocessor processes the weather returns to indentify areas of precipitation with moderate to high turbulence. This capability enhances the rainfall intensity information provided by the basic radar, which to enables pilots to avoid threatening weather. The turbulence detection circuitry uses the Doppler phenomenon, which causes an apparent echo between the radar and the target. The Doppler processor measures the return velocity variance to indicate the turbulence present in the weather. (2) Weather with Turbulence Detection The Doppler processor for the RDR-4B system processes the weather returns to identify areas of precipitation with moderate to high turbulence. This capability enhances the rainfall intensity information provided by the basic radar, which enables pilots to avoid threatening weather. The turbulence detection circuitry uses the Doppler phenomenon, which causes an apparent echo-signal frequency shift due to relative motion between the radar and the target. The Doppler processor measures return velocity variance to indicate the turbulence present in the weather. (3) Ground Mapping Ground mapping with the RDR-4B radar system provides a plan of prominent landmarks and terrain features such as cities, lines, mountains, islands, bay, bridges, etc. These terrain are shown on the ND in slant range and azimuth bearing with to the heading of the aircraft.

picture shore features respect

Of prime importance for the pilot is the extended range of vision and the ability to see this terrain map during darkness and overcast conditions, when visibility is restricted. The display in ground mapping look like a pilotage chart and can be easily interpreted. Cities, open ground, and bodies of water provide progressively less intense reflections. It should be noted that calm water reflects very little signal back to the antenna. However, very rough water provides a signal return of considerable strength.

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The planar antenna array provides only pencil beam. Terrain mapping for short ranges (less than 75NM) requires tilt adjustment to cover the scan area. R R

**ON A/C 001-049, 051-099, 101-105, 151-199, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, (4) Autotilt The weather radar RDR-4B can operate in autotilt mode (automatic tilt angle): the use of the automatic tilt function is recommended in WX and TURB modes. The autotilt function uses the terrain altitude information of the Enhanced GPWS. the Enhanced Ground Proximity Warning System (E-GPWS). Based on the aircraft altitude above the terrain and on terrain conditions in the area, the Enhanced GPWS determines the optimum tilt angle for the radar. This automatic tilt angle setting results in minimum ground clutter on the display while maintaining an optimum weather detection capability. One exception is the autotilt MAP mode, where the radar beam is intentionally aimed at the ground as a function of range. NOTE : Manual tilt should be used when analyzing terrain and storm ____ characteristics. The autotilt function is integrated in the existing windshear submodes. On preparation for takeoff through 2300 feet, the weather scans alternate with the windshear scans. This occurs on approach, as well, below 2300 feet. The autotilt function controls the tilt only during weather scans. The windshear scan algorithm does not change with the autotilt functionality. NOTE : When range settings are different (one display at a range of ____ more than 80NM and the other display at a range of less than or equal to 80NM) the weather radar scans alternately to cover the different range settings. The autotilt functionality is optimized for range settings less than or equal to 80NM (short range) and range settings more than 80NM (long range). If above 2300 feet AGL and if all displays are set to the same setting (either all short range or all long range), the weather display is updated in both directions clockwise (CW) and counterclockwise (CCW). If above 2300 feet AGL and if at least one display is on short range while the others are on long range, then the weather display is updated on alternate scans to account for the different autotilt settings required. Below 2300 feet AGL, the autotilt scans are based on short range tilt setting. There is no

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long range/short range alternate scanning in the windshear active region. R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, (Ref. Fig. 008)

R R

**ON A/C 001-049, 051-099, 101-105, 151-199, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, The antenna scan is divided into five sectors/areas. The tilt angle displayed for each sector is calculated based on aircraft altitude, terrain height and range selection. (5) Antenna Scan Pattern

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**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, (Ref. Fig. 009)

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**ON A/C 001-049, 051-099, 101-105, 151-199, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, Figure 009 shows the benefits of autotilt with manual tilt control: there can be over scan where the weather cells and the terrain are below the antenna beam and the display is blank, or under scan where the antenna scan is basically hitting the ground below the weather cells and the display contains only ground clutter. The integration of Enhanced GPWS and radar functionality (autotilt) provides a layer of protection against these extremes. (6) Autotilt Selection Automatic tilt is selected by setting the TILT (AUTO/MAN) switch to AUTO on the weather radar control unit (CON-4A/4B). Switch to AUTO: Tilt setting for weather scans is automatic. Switch to MAN: Tilt is controlled with the manual tilt control knob. Pitch and roll information from the aircraft vertical gyros, tilt information from the manually set tilt control, azimuth angle information from the azimuth (scan) synchro transmitter, and elevation angle information from the elevation synchro transmitter, are processed by the stabilization microprocessor drive motor. The elevation drive motor repositions the antenna to maintain line-of-sight.

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Weather Radar - Automatic Tilt Antenna Scan Pattern Figure 008   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page 62 511-526, 528-599,  Config-3 Feb 01/10  CES

 

Weather Radar - Manual Tilt/Automatic Tilt Figure 009   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page 63 511-526, 528-599,  Config-3 Feb 01/10  CES

 

Also supplied by the R-T unit is the azimuth motor drive signal which drives the antenna through the oscillating 180 degrees of azimuth (scan). NOTE : Manual TILT should be used when analyzing terain and when ____ analyzing storm characteristics. selection of either manual or autotilt is done with selected control units. The RF signal (transmitted or received) is conveyed by a wave guide between the antenna and the transceiver. Energization of the antenna is 115VAC 400HZ throught the selected transceiver. (7) Dual System Antennas **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 010) R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, (Ref. Fig. 010A)

R R

**ON A/C 001-049, 051-099, 101-105, 151-199, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, To provide for dual system operation, the antenna contains redundant position synchro transmitters. Synchro transmitters B6 and B1 and associated with system 1; synchro transmitters B4 and B3 are associated with system 2. These redundant servo loops are interconnected through redundant antenna connectors (J3001, system 1) and (J3002, system 2) to the RDR-4B system. All circuitry commmon to a dual system is configured in such a way that either a Receiver-Transmitter unit, indicator, or synchro transmitter failure will not render the RDR-4B system inoperative. A system tranfert switch on the CON-4B control panel applies power to the selected system and applies a switching voltage to a waveguide switch mounted on the R-T mounting base. The waveguide switch transfert the antenna rf feed (waveguide) to the selected R-T unit. On the figure, sytem 1 is selected for operation by placing the System Transfert Switch (STS) on the CON-4B in the SYS 1 position. This energizes and initiates the switching necessary for system 1 operation. For either dual or single system operation, motor B5 drives the antenna in azimuth movement and motor B2 drives the antenna in elevation position.

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Weather Radar - Single Motor Antenna Drive Figure 010

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Weather Radar - Dual Redundant Motor Antenna Drive Figure 010A   R EFF : 051-099, 239-249, 251-299, 311-399,  34-41-00 Page 66 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

NOTE : The single system antenna is designed for use with one R-T ____ unit. The function and components of the single system antenna are the same as the dual system antenna except that single synchros are used in lieu of redundant synchros and only on connector (J3001) is wired to electrical components in the antenna. R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, C. Weather Radar Antenna

R

**ON A/C 001-049, 101-105, 501-509, 511-526, 528-599, (Ref. Fig. 011) **ON A/C 151-199, (Ref. Fig. 011B)

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**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, The weather radar antenna is controlled in azimuth and elevation by the transceiver. The antenna movements are ensured by 2 DC motors and the angular positions are recopied by 2 or 4 synchros (2 for a single antenna and 4 for a dual antenna). The RF signal (transmitted or received) is conveyed by a wave guide between the antenna and the transceiver. Energization of the antenna is 115VAC/400 Hz through the transceiver. **ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, C. Weather Radar Antenna (Ref. Fig. 011A) The weather radar antenna is controlled in azimuth and elevation by the transceiver CPU. The binary control data are decoded and activate the antenna scan and elevation steeper motors through corresponding power circuits. The indication of these positions is sent to the CPU for comparison. The RF signal (transmitted or received) is conveyed by a wave guide between the antenna and the transceiver. Energization of the antenna is 115VAC/400 Hz through the transceiver.

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Weather Radar - Dual Antenna Drive Figure 011   R EFF : 001-049, 101-105, 501-509, 511-526,  34-41-00 Page 68 528-599,  Config-3 Feb 01/10  CES

 

Weather Radar - Antenna Figure 011A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page 69 301-399, 401-499,  Config-3 May 01/09  CES

 

Weather Radar - Antenna Figure 011B

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**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 501-509, 511-526, 528-599, D. Weather Radar Control Unit The gain and tilt potentiometric data are digitized by an 8-bit analog-to-digital converter. Moreover the different positions of the mode selector switch and the potentiometric data are formatted according to the ARINC 429 control word. **ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, D. Weather Radar Control Unit Part of weather radar controls is grouped on the control unit (TILT control, system GAIN control, MODE selection control, MULTISCAN MAN/AUTO mode). These data are digitized and monitored by a CPU to generate a control word which is sent to the transceiver through a control bus line. **ON A/C ALL E. Weather Radar Wave Guide and Wave Guide Switch A wave guide assembly ensures the RF connection between the WR antenna drive and the WR transceiver mounting tray (connected to the wave guide switch). The wave guide assembly is made up of rigid and flexible parts which have a standard rectangular section (1 in. x 0.5 in.). The wave guide switch is integral with the mounting tray. It ensures switching of the RF signal from the antenna to the transceiver. Moreover control circuits recopy the wave guide switch position to avoid transmission on a closed wave guide.

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7. Operation _________ R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, A. Operation (1) Weather Radar modes The weather radar system uses the principle of radio echoing. It works at a normal frequency of 9345 MHz. The peak power emitted is 125 W approx. The weather radar transceiver generates microwave energy in the form of electromagnetic pulses via an X-band wave guide to the antenna. When these pulses intercept an appropriate target, part of the energy is reflected back to the weather radar antenna then to the transceiver. For each case, the system uses a different mode of operation which allows to vary the scanning of the antenna, the timing of the pulses and the processing of the weather radar returns and of the predictive windshear events (if the function is activated). The electronics circuits of the transceiver measure the elapsed time between the transmission of the wave and the reception of the echo to determine the target distance (it takes around 12.36 microseconds for the electromagnetic wave to travel out and back for each nautical mile of target range). The angular position of the target is detected by the angular position of the antenna in its scanning in azimuth. As the quantity of energy reflected to the antenna is proportional to the target density, the different levels of atmospheric disturbances (see table 1 below) are shown on the displays by different colors. The detection of the turbulence areas are based on the Doppler phenomenon. -------------------------------------------------------------------------| LEVEL DETECTED | PRECIPITATION RATE | COLOR OF ECHOES | |------------------------|-----------------------|-----------------------| | Z1 < 20 dBz | less than 1 mm/h | black | | 20 less than or equal | from 1 to 4 mm/h | green | | to Z2 < 30 dBz | | | | 30 less than or equal | from 4 to 12 mm/h | yellow | | to Z3 < 40 dBz | | | | 40 less than or equal | 12 mm/h and above | red | | to Z4/Z5 < 50 dBz | | | |------------------------|-----------------------|-----------------------| | Turbulence | 5 m/s | magenta | -------------------------------------------------------------------------| Table 1: Color Correspondence Table

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R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, A. Operation (1) Weather Radar modes The weather radar system uses the principle of radio echoing. It works at a normal frequency of 9333 MHz. The peak power emitted is 120 W approx. The weather radar transceiver generates microwave energy in the form of electromagnetic pulses via an X-band wave guide to the antenna. When these pulses intercept an appropriate target, part of the energy is reflected back to the weather radar antenna then to the transceiver. For each case, the system uses a different mode of operation which allows to vary the scanning of the antenna, the timing of the pulses and the processing of the weather radar returns and of the predictive windshear events (if the function is activated). The electronics circuits of the transceiver measure the elapsed time between the transmission of the wave and the reception of the echo to determine the target distance (it takes around 12.36 microseconds for the electromagnetic wave to travel out and back for each nautical mile of target range). The angular position of the target is detected by the angular position of the antenna in its scanning in azimuth. As the quantity of energy reflected to the antenna is proportional to the target density, the different levels of atmospheric disturbances (see table 1 below) are shown on the displays by different colors. The detection of the turbulence areas are based on the Doppler phenomenon. -------------------------------------------------------------------------| LEVEL DETECTED | PRECIPITATION RATE | COLOR OF ECHOES | |------------------------|-----------------------|-----------------------| | Z1 < 20 dBz | less than 1 mm/h | black | | 20 less than or equal | from 1 to 4 mm/h | green | | to Z2 < 30 dBz | | | | 30 less than or equal | from 4 to 12 mm/h | yellow | | to Z3 < 40 dBz | | | | 40 less than or equal | 12 mm/h and above | red | | to Z4/Z5 < 50 dBz | | | |------------------------|-----------------------|-----------------------| | Turbulence | 5 m/s | magenta | -------------------------------------------------------------------------| Table 1: Color Correspondence Table

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**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, (2) Windshear mode (if the predictive windshear function is activated) The WR/PWS, by a doppler mode, determines the wind field ahead of the aircraft. By a mathematical treatment, the system determines the hazard factor (so-called F factor) related to the danger of a windshear event. An hazard factor exceeding a value of 0.13 and within 5NM ahead of the aircraft is considered as the presence of a dangerous event and a corresponding windshear alert is generated. The display of windshear hazard consits of an icon of red and black bands superimposed on the radar returns. As these events are dangerous during takeoff and landing maneuvers, the PWS mode is automatically activated below 2300 ft radio altimeter and at least one of the qualifier-A and one qualifier-B inputs have to be valid. Windshear detection operates automatically with the above-mentioned reasons, even if the radar function selector switch is set to OFF, but windshear switch has to be set to AUTO. The windshear mode is transparent to the pilot until a windshear event is detected. When a windshear event is detected, the system generates the appropriate annunciations (visual and aural) to the flight crew. The WR/PWS generates a graphic symbol (icon) to the displays indicating where the windshear was detected. The windshear function detection can operate either with weather radar modes activated or independently without these modes. This is accomplished by sharing the antenna scanning: - in clockwise weather scan or windshear scan - in counterclockwise windshear scan. In windshear mode, the TILT and GAIN are controlled automatically on the WR/PWS for the scanning. However, the TILT displayed on the NDs is in accordance with this selected on the radar control panel. When the weather radar transceiver fails, the amber message PRED W/S is displayed on the NDs associated with the amber messages: - NAV: PRED W/S DET FAULT on the upper ECAM DU, - PRED W/S DET in the INOP SYS item of the STATUS page on the SD. NOTE : The system has to reject echoes due to ground clutter or ____ moving surface. NOTE : The pilot has to deselect windshear mode (AUTO/OFF switch to ____ OFF) for the following reasons: - when the aircraft is at a gate area or in maintenance hangars to avoid radiating danger for persons - when nuisance aural alerts are generated.

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NOTE : There is no danger of radiation to persons on the ground if ____ the ATC switch on the ATC/TCAS control unit is set to OFF or STBY after landing, even if the windshear switch on the weather radar control unit is still at AUTO. NOTE : In order to ensure optimum performance for the predictive ____ windshear function, the radome must be at least equal to class B category 1. **ON A/C 051-099, 106-149, 201-233, 236-238, (2) Windshear mode (if the predictive windshear function is activated) The WR/PWS, by a doppler mode, determines the wind field ahead of the aircraft. By a mathematical treatment, the system determines the hazard factor (so-called F factor) related to the danger of a windshear event. An hazard factor exceeding a value of 0.13 and within 5NM ahead of the aircraft is considered as the presence of a dangerous event and a corresponding windshear alert is generated. The display of windshear hazard consits of an icon of red and black bands superimposed on the radar returns. As these events are dangerous during takeoff and landing maneuvers, the PWS mode is automatically activated below 2300 ft radio altimeter and at least one of the qualifier-A and one qualifier-B inputs have to be valid. Windshear detection operates automatically with the above-mentioned reasons, even if the radar function selector switch is set to OFF, but windshear switch has to be set to AUTO. The windshear mode is transparent to the pilot until a windshear event is detected. When a windshear event is detected, the system generates the appropriate annunciations (visual and aural) to the flight crew. The WR/PWS generates a graphic symbol (icon) to the displays indicating where the windshear was detected. The windshear function detection can operate either with weather radar modes activated or independently without these modes. If the radar is already operating in a weather detection mode when a windshear is detected, no pilot intervention will be required. If the radar is OFF when this event is detected, the radar operation will automatically change to WX+T mode (if selected range is less than 60NM) or WX mode (if selected range is more than 60NM), to display weather and windshear icons. The selected range does not change. In windshear mode, the TILT and GAIN are controlled automatically on the WR/PWS for the scanning. However, the TILT displayed on the NDs is in accordance with this selected on the radar control panel.

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When the weather radar transceiver fails, the amber message PRED W/S is displayed on the NDs associated with the amber messages: - NAV: PRED W/S DET FAULT on the upper ECAM DU, - PRED W/S DET in the INOP SYS item of the STATUS page on the SD. The system 2 (if installed), has to be selected on the weather radar control unit to display windshear information. NOTE : The system has to reject echoes due to ground clutter or ____ moving surface. NOTE : In some cases, the pilot has to deselect windshear mode (PWS/ ____ OFF/AUTO switch to OFF) for the following reasons: - when the aircraft is at a gate area or in maintenance hangars to avoid radiating danger for persons, - when nuisance aural alerts are generated. NOTE : There is no danger of radiation to persons on the ground if ____ the ATC switch on the ATC/TCAS control unit is set to OFF or STBY after landing, even if the windshear switch on the weather radar control unit is still at AUTO. NOTE : In order to ensure optimum performance for the predictive ____ windshear function, the radome must be at least equal to class B category 1. R

**ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, (2) Windshear mode (if the predictive windshear function is activated) The WR/PWS, by a doppler mode, determines the wind field ahead of the aircraft. By a mathematical treatment, the system determines the hazard factor (so-called F factor) related to the danger of a windshear event. A hazard factor exceeding a value of 0.13 and within 5NM ahead of the aircraft is considered as the presence of a dangerous event and a corresponding windshear alert is generated. The display of windshear hazard consits of an icon of red and black bands superimposed on the radar returns. As these events are dangerous during takeoff and landing maneuvers, the PWS mode is automatically activated below 2300 ft radio altimeter and at least one of the two qualifier inputs (QB and QC or QB and QD) valid. These conditions enable automatic windshear detection operation even if, on theweather radar control unit, the 1/OFF/2 switch is at OFF; the WINDSHEAR/AUTO/OFFswitch must be set to AUTO. The windshear mode is transparent to the pilot until a windshear event is detected.

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When a windshear event is detected, the system generates the appropriate annunciations (visual and aural) to the flight crew. The WR/PWS generates a graphic symbol (icon) to the displays indicating where the windshear was detected. The windshear function detection can operate either with weather radar modes activated or independently without these modes. If the radar is already operating in a weather detection mode when a windshear is detected, no pilot intervention will be required. If the radar is OFF when this event is detected, the radar operation will automatically change to WX+T mode (if selected range is less than 60NM) or WX mode (if selected range is more than 60NM), to display weather and windshear icons. The selected range does not change. In windshear mode, the TILT and GAIN are controlled automatically on the WR/PWS for the scanning. However, the TILT displayed on the NDs is in accordance with this selected on the radar control panel. When the weather radar transceiver fails, the amber message PRED W/S is displayed on the NDs associated with the amber messages: - NAV: PRED W/S DET FAULT on the upper ECAM DU, - PRED W/S DET in the INOP SYS item of the STATUS page on the SD. The system 2 (if installed), has to be selected on the weather radar control unit to display windshear information. NOTE : The system has to reject echoes due to ground clutter or ____ moving surface. NOTE : In some cases, the pilot has to deselect windshear mode (PWS/ ____ OFF/AUTO switch to OFF) for the following reasons: - when the aircraft is at a gate area or in maintenance hangars to avoid radiating danger for persons, - when nuisance aural alerts are generated. NOTE : There is no danger of radiation to persons on the ground if ____ the ATC switch on the ATC/TCAS control unit is set to OFF or STBY after landing, even if the windshear switch on the weather radar control unit is still at AUTO. NOTE : In order to ensure optimum performance for the predictive ____ windshear function, the radome must be at least equal to class B category 1.

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R R

**ON A/C 001-049, 101-105, 151-199, 234-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (3) Logic of scanning mode

R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, (Ref. Fig. 012) **ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, (Ref. Fig. 012A)

R R

**ON A/C 001-049, 101-105, 151-199, 234-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, The antenna scan pattern varies depending on the mode of operation. (a) Weather radar scan pattern In weather radar mode, the antenna scans a 180 deg. in azimuth and has tilt (pitch) coverage of plus or minus 15 deg. Stabilization limits are plus or minus 25 deg. in the pitch axis and plus or minus 40 deg. in the roll axis. An antenna scanning is performed in 4 seconds, this causes the transmission of 760 data words at each antenna scanning. The weather radar system features a 4-second constant refresh rate of the WX image whatever the ranges selected on the CAPT and F/O EFIS control sections of the FCU. (b) Weather and windshear scan pattern, no detected windshear event When the system is placed into alternate weather/windshear scan pattern and no windshear event is detected, the antenna scan pattern is as follows: - clockwise weather scan with plus or minus 90 deg. of azimuth coverage and processing for weather - counterclockwise windshear scan with full plus or minus 90 deg. of azimuth coverage, but with windshear processing limited to the plus or minus 45 deg. sector. However, the WR/PWS have to update the refresh rate of the WX image to 12 seconds due to sharing of processing between windshear and radar.

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WR/PWS - Logic of scanning mode Figure 012   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page 79 511-526, 528-599,  Config-3 Feb 01/10  CES

 

WR/PWS - Logic of scanning mode Figure 012A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page 80 301-399, 401-499,  Config-3 May 01/09  CES

 

(c) Weather and windshear scan pattern, with windshear event detected When the system is placed into alternate weather/windshear scan pattern and the system detects a windshear event, the antenna scan pattern is as follows: - clockwise weather scan, from minus 90 deg. to plus 90 deg. - counterclockwise windshear scan, from plus 90 deg. to minus 45 deg., with windshear processing between plus 45 deg. and minus 45 deg. - the next clockwise scan is from minus 45 deg. to plus 45 deg. to validate windshear - the next counterclockwise scan is from plus 45 deg. to minus 90 deg. to validate windshear. No processing occurs between plus 45 deg. and minus 90 deg. - clockwise WX scan, from minus 90 deg. to plus 90 deg. The sequence is repeated as long as windshear event is detected. If a windshear event is not detected, the system reverts to the alternating weather/windshear scan pattern described above. The refresh rate of the WX image is minimum 16 sesonds due to sharing processing between radar and windshear event detection. (d) Windshear scan pattern When the system operates in windshear mode only, the scan pattern is plus or minus 45 deg. azimuth coverage on both the clockwise and counterclockwise scans. This mode occurs if the operator has placed the weather radar to OFF mode. Windshear data are processed during both directions of antenna scanning. In this case the windshear mode works transparent to the flight crew until a windshear event is detected. The refresh rate of the display is 8 seconds. **ON A/C 051-099, 106-149, 201-233, 236-238, (3) Logic of scanning mode (Ref. Fig. 012A) The antenna scan pattern varies depending on the mode of operation. (a) Weather radar scan pattern In weather radar mode, the antenna scans a 180 deg. in azimuth and has tilt (pitch) coverage of plus or minus 15 deg. Stabilization limits are plus or minus 25 deg. in the pitch axis and plus or minus 40 deg. in the roll axis. The antenna scans the zone 15 times per minute. Beam opening is 3.6 deg. in elevation and 3.5 deg. in azimuth.

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An antenna scanning is performed in 4 seconds, this causes the transmission of 720 data words to the data bus lines. When the two ranges selected on both EFIS control panels are identical, the radar images displayed on the NDs are refreshed every 4 seconds. On the contrary, when two different ranges are selected on the EFIS control panels, the images are refreshed every 8 seconds. (b) Weather and windshear scan pattern When the system is placed into alternate weather/windshear mode, the weather processing is operating during left-to-right scans and windshear processing is operating during right-to-left scans. In this case, the antenna scans only plus or minus 60 deg. But windshear the targets are displayed only in the area plus or minus 30 deg. from the aircraft centerline. An antenna scanning is performed in 3 seconds three other seconds are used to refresh data inside the CPU. Then, when the two ranges selected on both EFIS control panels are identical, the radar images displayed on the NDs are refreshed every 6 seconds. On the contrary, when two different ranges are selected on the EFIS control panels, the images are refreshed every 12 seconds. (c) Windshear scan pattern The windshear processing is operating during right-to-left scans and left-to-right scans. The antenna scans only plus or minus 60 deg. The detected windshear targets are displayed only in the area plus or minus 30 deg. from the aircraft centerline. When the two ranges selected on both EFIS control panels are identical, the radar images displayed on the NDs are refreshed every 6 seconds. On the contrary, when two different ranges are selected on the EFIS control panels the images are refreshed every 12 seconds. NOTE : For roll angle exceeding 28 deg., the windshear detection ____ is not active. (d) Not Applicable

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**ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, (4) Radar Multiscan mode The Multiscan mode manages the antenna beam tilts automatically. The antenna tilts are controlled for optimum weather detection during each phase of flight. This mode uses a low and high beam to examine short and long range, even while on the ground. Data for display is automatically selected from the upper beam, lower beam or both depending on the flight regime, clutter situation and optimum weather detection requirements. NOTE : At each initial flight of the Multiscan radar transceiver, the ____ transceiver needs to be calibrated (each transceiver must be turned on for approximately four minutes) during a short period in stable flight conditions. Before the initial calibration step, it is possible that the weather image shows an excessive ground clutter. If the initial calibration step is not performed or is uncompleted, the Multiscan radar transceiver will calibrate itself during the next flights. (a) Cycle times Cycle time refers to the total amount of time that the Multiscan radar scans for information during various modes of operation of the radar. Total cycle time can vary between 8 and 15 seconds. The radar updates some portion of the weather, windshear (depending on the mode of operation) on every radar antenna scan. Therefore, a new data set is completed after every radar sweep. If you start from time zero, a completely new data set of information is obtained by the radar at the end of the one cycle. NOTE : The display update rate (Ref. para. E.(4)(a)) is what the ____ flight crew actually sees. Cycle time describes what Multiscan is doing in the background. (b) Weather mode scan pattern (Ref. Fig. 013) When Multiscan operates in the weather mode only two radar scans are utilized. One four-second sweep is utilized for the high beam and one four-second sweep is utilized for the low beam. Therefore, the total cycle time is 8 seconds (Ref.Fig.010).

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Weather Radar - Multisan Scan Pattern Figure 013   R EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page 84 401-499,  Config-3 May 01/09  CES

 

(c) Windshear mode scan patterm The Windshear mode is automatically activated below 2.300 FT AGL. The time required for one radar sweep changes from 4 to 2.8 seconds due to the fact that the radar sweep changes from 180⁰ to 120⁰. In windshear mode, the first antenna scan (left to right) is utilized for the Multiscan high beam. The second scan (right to left) is a windshear scan. The third scan (left to right) is utilized for Multiscan low beam. The fourth scan (right to left) is, again, a windshear scan. Thus, total cycle time during windshear mode is 11.2 seconds (Ref.Fig.010). R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, B. Timing of Transmitted Pulses in WX/MAP Mode and in Doppler Mode (Turbulence) and W/S Mode (Ref. Fig. 014) - in the WX and MAP modes, the basic period of pulse transmission-reception is 5.25 ms. This causes an interrogation frequency (PRF) of 190 Hz. As two pulses are transmitted (6 micros and 18 micros), the specified PRF is 380 Hz. Both 6-micros and 18-micros pulses are used to cover all range scales i.e. from 0 to 320 NM. The 6-micros wide pulse echo is processed for ranges from 0 to 20 NM. The 18-micros wide pulse echo is processed for ranges greater than 40 NM. The 6-micros and 18-micros pulse echoes are processed for ranges between 20 and 40 NM - in the turbulence mode (HIGH PRF), the HIGH PRF and LOW PRF pulses are interlaced. This causes simultaneous WX/MAP and TURBULENCE information. The 6-micros wide pulses 1 to 9 are transmitted at 1600 Hz and are used for turbulence detection. The 18-micros wide pulse 10 is used for the WX/MAP mode. The high frequency of the PRF required for turbulence detection (1600 Hz) limits the range of this detection to 40 NM. - in windshear mode (VERY HIGH PRF) the 1.5-micros wide pulses are transmitted at 6000 Hz. The sequence of transmitted RF pulses consists of two staggered pulse trains, each with the different carrier frequency. Each pulse train has a PRF of 3000 Hz, providing 10 NM (minimum selected range on EFIS control section). (1) Not Applicable (2) Not Applicable (3) Not Applicable (4) Not Applicable

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Weather radar - Pulse Transmission Timing Diagram Figure 014   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page 86 511-526, 528-599,  Config-3 Feb 01/10  CES

 

**ON A/C 051-099, 106-149, 201-233, 236-238, B. Timing of Transmitted Pulses in WX/MAP Mode, in Doppler Mode (Turbulence) and in W/S Mode (Ref. Fig. 014A) - in WX and MAP modes, at short ranges (less than or equal to 60NM) the period of pulse (four) transmission-reception is 5.6 ms. This causes an interrogation frequency (PRF) of 1280 Hz. For medium ranges (greater than 60NM and less than or equal to 165 NM), the period of pulse (two) transmission-reception is 8.4 ms at a PRF of 360 Hz. For ranges greater than 165 NM, the period of pulse (two) transmission-reception is 8.4 ms at a PRF of 240 Hz. - in the turbulence mode (High PRF), the PRF is increased from 240 to 1280 pulses per second. The threshold of turbulent targets is precipitation velocities of 5 m/s. This threshold translates into a Doppler frequency shift of 312,5Hz. It explains the increased PRF. With this high PRF rate, the maximum range for turbulence detection is approximately 56 NM. - in the windshear mode (Very High PRF), 64 pulses are transmitted during a period of 23 ms. The PRF is 3000 Hz. (1) Not Applicable (2) Not Applicable (3) Not Applicable (4) Not Applicable **ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, B. Pulse Duration and Range Timing (Ref. Fig. 014A) This section provides the timing details for the transmitting and the processing of radar data. (1) Epoch timing (non-windshear modes) An epoch is the time interval in which a radial or radar data is processed. The time is equal to the size of the radar processing element in degrees divided by the antenna scan rate. The rate does not include any added dithering delays. Specifications for the range, element size, scan rate, and process epoch period are shown in Table a.

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Weather radar - Pulse Transmission Timing Diagram Figure 014A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page 88 301-399, 401-499,  Config-3 May 01/09  CES

 

----------------------------------| Range | All ranges | |----------------|----------------| | Element size | 0.375 degree | |----------------|----------------| | Scan Rate | 45 deg/sec | |----------------|----------------| | Epoch | 8.333 ms | | Period | +/- 5 microsec| ----------------------------------Table a. Epoch Timing Table (a) Transmitter pulse width values The transmitter pulse widths are 6.0 and 20.0 microseconds . Accuracy of the pulse width is +/- 0.2 microsecond. (b) Transmitter pulse pattern (Ref. Fig. 015) The transmitter pulse pattern is as follows for all selected ranges. One 20 microseconds pulse and four 6 microseconds pulses will be transmitted during each epoch. The Pulse Repetition Frequency (PRF) for the 6 microseconds pulses is 1839Hz (543.83 microseconds). Figure 011 shows the non-windshear pulse pattern. (2) Process epoch timing (windshear mode) An epoch is the time interval in which a radial of radar data is processed. The process epoch timing is maintained by DSP1. The rate does not include any added dithering delays. Specifications for the element size, scan rate and process epoch period are shown in Table b. ----------------------------------| Range | All Ranges | |----------------|----------------| | Element Size | 1.0 degree | |----------------|----------------| | Scan Rate | 45 deg/sec | |----------------|----------------| | Epoch Period | 22.975 ms | ----------------------------------Table b. Process Epoch Timing Table (a) Transmitter pulse width The transmitter pulse width is 2 microseconds for windshear mode. (b) Transmitter pulse pattern The pulse repetition frequency is 3000HZ (333.3333 microseconds) and a total of 64 pulses is transmitted per epoch (Ref.Fig.012).

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Weather Radar - Windshear Transmit Pulse Pattern Figure 015   R EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page 90 401-499,  Config-3 May 01/09  CES

 

(3) Range resolution/timing The requirements for the range resolution and timing for the system are as follows: (a) Windshear mode The unit takes data samples out to a range of 5NM. Sixty-four samples are taken, the sample resolution is 150 meters +/- 6 meters. The receiver starts sampling 4.0 microseconds after the end of the transmit epoch. (b) Non-windshear mode The transceiver splits the radar return into two separate analog channels: in-phase(I) and quadrature(Q) channels. The transceiver simultaneously samples each channel the number of times shown in Table c. per transmit pulse, converting the radar return signal into digital format data. Receiver sampling starts at a time equivalent to a range of 0.5NM after the end of the transmitter pulse. -----------------------------------------------------------------| Pulsewidth | Sampled Range | Number of Sample Taken | |----------------|-------------------|---------------------------| | 6 microsec | 41.424 NM | 247 | |----------------|-------------------|---------------------------| | 20 microsec | 331.392 NM | 504 | -----------------------------------------------------------------Table c. Receiver sample vs. Range The resolution of each individual sample is defined using the following equation: Sample Length = (range)/sample quantity⁵*K Where: range = sampled range sample quantity = 512 K = 12.34 microseconds/NM (electromagnetic propagation constant) The 512 range bins from the 40NM short range data set (6 microseconds tx pulses) and the 512 range bins from the 320NM long range data set (20 microseconds tx pulses) are interpolated/decimated to produce the final 256 data bin set suitable for output at the selected range. The 256 range bins are then linearly expanded to fill the 512 ARINC 708A data bus range bins. The transceiver displays radar returns with a range accuracy of 5% or 1/2NM whichever is larger. (4) Receiver selectivity Selectivity of the receiver filter bandwidth is controlled to match the current transmitter pulse length as shown in Table d. The specified filter bandwidths listed are single sided 3dB bandwidths.

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----------------------------------------| Pulsewidth | Filter | |-------------------|-------------------| | 2.0 microsec | 250 kHz | |-------------------|-------------------| | 6.0 microsec | 100 kHz | |-------------------|-------------------| | 20.0 microsec | 25 kHz | ----------------------------------------Table d. Receiver Selectivity vs. Transmitter Pulsewidth (a) Display Display seconds weather

updates updates occur at a minimum rate of two updates per 26.67 worst case with three problem cases selecting long range and windshear mode operating.

**ON A/C ALL C. Controls and Indicating The various system controls are grouped on the weather radar control unit and on the EFIS control sections of the FCU. Radar image control on the NDs is achieved through the scale selector switches located on the Captain and First Officer EFIS control sections of the FCU. **ON A/C 001-049, 101-105, (1) Weather radar control unit (Ref. Fig. 016) The face of the control unit is provided with integral lighting. The INTEG LT/ MAIN PNL & PED potentiometer enables lighting adjustment. The potentiometer is located on the panel 111VU, at the left aft section of the center pedestal 11VU. The face of the weather radar control unit includes the following controls: (a) A switch, item 1, with two stable positions OFF/ON, which enables the activation of the transceiver. (b) A mode selector switch, item 2, which enables the selection of the WX, WX/TURB or MAP function.

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Weather Radar - Control Unit Figure 016   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page 93 511-526, 528-599,  Config-3 Feb 01/10  CES

 

(c) A TILT selector switch, item 3, which enables the control of the antenna elevation. Antenna position is read in degrees, opposite the notch on the switch: - either from 0 to 15 deg. upwards (UP) - or from 0 to 15 deg. downwards (DN). (d) A GAIN potentiometer, item 5, which enables the manual adjustment of the transceiver gain. (e) A WINDSHEAR switch, item 4, with two stable positions AUTO/OFF, which enables the selection of the windshear function. (f) Not Applicable (g) Not Applicable **ON A/C 051-099, 106-149, 201-233, 236-238, (1) Weather radar control unit (Ref. Fig. 016A) The face of the control unit is provided with integral lighting. The INTEG LT potentiometer enables lighting adjustment. The potentiometer is located on the panel 111VU, at the left aft section of the center pedestal 100VU. The face of the weather radar control unit includes the following controls: (a) A switch, item 6, with three stable positions 1/OFF/2, which enables the activation of the transceiver. (b) A mode selector switch, item 5, which enables the selection of the WX, WX+T, TURB or MAP function. (c) A TILT selector switch, item 3, which enables the control of the antenna elevation. Antenna position is read in degrees, opposite the notch on the switch: - either from 0 to 15 deg. upwards (UP), - or from 0 to 15 deg. downwards (DN).

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Weather Radar - Control Unit Figure 016A   R EFF : 051-099, 106-149, 201-233, 236-238,  34-41-00 Page 95   Config-3 May 01/09  CES

 

(d) A GAIN potentiometer, item 1, which enables the manual adjustment of the transceiver gain. (e) A PWS switch, item 2, with two stable positions AUTO/OFF, which enables the selection of the windshear function. (f) A GND CLTR SPRS switch, item 4, with two stable positions ON/OFF, which enables the selection of the ground clutter suppression. (g) Not Applicable **ON A/C 151-199, (1) Weather radar control unit (Ref. Fig. 016)

R R

The face of the control unit is provided with integral lighting. The INTEG LT/ MAIN PNL & PED potentiometer enables lighting adjustment. The potentiometer is located on the panel 111VU, at the left aft section of the center pedestal 11VU. The face of the weather radar control unit includes the following controls: (a) A switch, item 1, with three stable positions 1/OFF/2, which enables the activation of the transceiver. (b) A mode selector switch, item 2, which enables the selection of the WX, WX/TURB or MAP function. (c) A TILT selector switch, item 3, which enables the control of the antenna elevation. Antenna position is read in degrees, opposite the notch on the switch: - either from 0 to 15 deg. upwards (UP) - or from 0 to 15 deg. downwards (DN). (d) A GAIN potentiometer, item 5, which enables the manual adjustment of the transceiver gain. (e) A WINDSHEAR switch, item 4, with two stable positions AUTO/OFF, which enables the selection of the windshear function. (f) Not Applicable (g) Not Applicable

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**ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, (1) Weather radar control unit The face of the weather radar control unit includes the following controls: (a) A mode selector switch, item 2, which enables the selection of the WX, WX+T, TURB or MAP function. (b) A TILT selector switch, item 3, which enables the control of the antenna elevation. Antenna position is read in degrees, opposite the notch on the switch: - either from 0 to 15 deg. upwards (UP) - or from 0 to -15 deg. downwards (DN). (c) A GAIN potentiometer, item 5, which enables the manual adjustment of the transceiver gain. (d) A switch, item 1, with three stable positions 1/OFF/2, which enables the selection of the transceiver 1 or 2 and the deactivation of the transceivers. (e) A PWS/OFF/AUTO switch, item 4, which enables the selection of the windshear function. The face of the control unit is provided with integral lighting. The INTEG LT potentiometer enables lighting adjustment. The potentiometer is located on the panel 111VU, at the left aft section of the center pedestal 100VU. (f) A GCS switch, item 6, with a Ground Clutter Suppression (GCS) function which is activated in Multiscan AUTOMATIC mode (this is the default position). In manual mode, the GCS is never activated. (g) A Multiscan switch, item 7, which enables the selection between MANUAL mode and Multiscan AUTOMATIC mode. R

**ON A/C 501-509, 511-526, 528-599, (1) Weather radar control unit (Ref. Fig. 016) The face of the weather radar control unit includes the following controls:

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Weather Radar - Control Unit Figure 016B

R

  R EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page 98 401-499,  Config-3 May 01/09  CES

 

(a) A mode selector switch, item 2, which enables the selection of the WX, WX/TURB or MAP function. (b) A TILT selector switch, item 3, which enables the control of the antenna elevation. Antenna position is read in degrees, opposite the notch on the switch: - either from 0 to 15 deg. upwards (UP), - or from 0 to 15 deg. downwards (DN). (c) A GAIN potentiometer, item 5, which enables the manual adjustment of the transceiver gain. (d) A switch, item 1, with three stable positions 1/OFF/2, which enables the activation of the transceiver. (e) A PWS switch, item 4, with two stable positions AUTO/OFF, which enables the selection of the windshear function. This function is inoperative until the windshear function is activated. The face of the control unit is provided with integral lighting. The INTEG LT potentiometer enables lighting adjustment. The potentiometer is located on the panel 111VU, at the left aft section of the center pedestal 100VU. (f) A MAN/TILT/AUTO switch, item 6, which enables the selection of manual tilt or automatic tilt. (g) Not Applicable **ON A/C ALL (2) EFIS control section (on the FCU) In this part, the controls related to the selection of WX and W/S functions are described. (a) A mode selector switch, item 1, made up of a rotary switch enables the selection of the ROSE or ARC function for display of a weather radar image on the CAPT and F/O NDs. Windshear information is available in ARC and ROSE mode. (b) A scale selector switch, item 2, common to EFIS, FMGS and radar systems, enables the selection of 10, 20, 40, 80, 160 or 320 operation range in nautical miles (NM) for display of the weather radar image on the CAPT and F/O NDs.

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Windshear information is presented in the 10 NM minimum range and on other selected ranges. Morever, yellow radial lines are displayed to indicate the W/S included location. NOTE : In the ARC or ROSE mode, if the CAPT or the F/O switches ____ to the OFF mode FM, the offside weather image will also be transferred on the ND. Only one scale selector switch can then control the weather radar image display. (3) Lighting/LOUDSPEAKER control panel CAPT and F/O lighting/LOUDSPEAKER control panels 301VU and 500VU which are connected to CAPT and F/O NDs, include ND concentric potentiometers for adjusting the brightness of the image displayed on the NDs. The outer knob of each potentiometer controls the brightness of the radar image only, item 3. R

**ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, D. Utilization of Controls and Indicating Special precautions to be taken. Before selecting a radar mode on the control unit, make sure that: - no one is within a distance less than 1.50 m from the antenna in movement within an arc of plus or minus 135 deg. on either side of the aircraft centerline - the aircraft is not directed towards any large metallic obstacle, such as a hangar, which is within 5 m in an arc of plus or minus 90 deg. on either side of the aircraft centerline. (1) Operation of the transceiver The transceiver is always supplied in order to achieve maintenance function. On the weather radar control unit, after selection of the radar mode, the system switch has to be set to ON position to set the transceiver in operation. NOTE : No pre-heating time is necessary for the operation of the ____ weather radar transceiver. NOTE : When the aircraft is parked, the TEST mode on the MCDU must be ____ preferably selected as a safety precaution. On either EFIS control section of the FCU, the mode selector switch must be set to the ARC or ROSE position to obtain the image display on the corresponding ND. NOTE : The radar transceiver is de-activated when the system switch ____ on the weather radar control unit is set to the OFF position

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or by placing the mode selector switches on both EFIS control sections in any position other than ROSE or ARC. (2) Utilization of the weather radar control unit **ON A/C 106-149, 201-233, 236-238, (Ref. Fig. 016A) **ON A/C 234-235, 301-310, 401-499, (Ref. Fig. 016B) **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 016) R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, D. Utilization of Controls and Indicating Special precautions to be taken. Before selecting the radar mode on the control unit, make sure that: - no one is within a distance less than 1.50 m from the antenna in movement within an arc of plus or minus 135 deg. on either side of the aircraft centerline - the aircraft is not directed towards any large metallic obstacle, such as a hangar, which is within 5 m in an arc of plus or minus 90 deg. on either side of the aircraft centerline. (1) Operation of the transceiver Only one transceiver works at a time, but both transceivers are always supplied in order to achieve maintenance function. On the weather radar control unit, after selection of the radar mode, the system switch has to be set to 1 or 2 position to set one transceiver in operation. NOTE : No pre-heating time is necessary for the operation of the ____ weather radar transceiver. NOTE : When the aircraft is parked, the TEST mode on the MCDU must be ____ preferably selected as a safety precaution.

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On either EFIS control section of the FCU, the mode selector switch must be set to the ARC or ROSE position to obtain the image display on the corresponding ND. NOTE : The radar transceiver is de-activated when the system switch ____ on the weather radar control unit is set to the OFF position or by placing the mode selector switches on both EFIS control sections in any position other than ROSE or ARC. (2) Utilization of the weather radar control unit R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 016) **ON A/C 051-099, (Ref. Fig. 016A) **ON A/C 239-249, 251-299, 311-399, (Ref. Fig. 016B)

R R

**ON A/C 001-049, 101-105, 151-199, 234-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (a) Mode selection switch (item 2) The modes (WX, WX/TURB, MAP) are selected by placing the notch provided in the mode selector switch in front of the engraving of the function selected. - WX This mode corresponds to the normal operation in weather detection. It provides disturbances up to 320 NM. The radar images are displayed on the NDs in four colors (black, green, yellow, red); their intensity corresponds to the strength of the return signal. - WX/TURB This mode corresponds to the operation in weather and turbulence detections. Turbulence detection is limited to the first 40 NM regardless of the weather radar range selected and displayed. Turbulence areas are displayed on the NDs in magenta.

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All turbulent/non turbulent areas beyond 40 NM are displayed in the conventional black, green, yellow and red as in the weather (WX) mode. NOTE : There is no detection of turbulence in clear sky. ____ - MAP This mode is only used for display of the ground map. A combination of transceiver gain, antenna position (TILT) and range selection enables the display of a larger area and the identification of major changes in the ground map (e.g. a sea cost, a lake, a mountain, an island...). The color display follows the color mentioned in correspondence table (see table 1 - para. 7. A.) If the image is too bright, due to too great reflection intensity, it can be dimmed by the GAIN potentiometer, item 5. **ON A/C 051-099, 106-149, 201-233, 236-238, (a) Mode selection (item 4) The modes (WX, WX+T, TURB, MAP) are selected by placing the notch provided in the mode selector switch in front of the engraving of the function selected. - WX This mode corresponds to the normal operation in weather detection. It provides disturbances up to 320 NM. The radar images are displayed on the NDs in four colors (black, green, yellow, red); their intensity corresponds to the strength of the return signal. - WX+T This mode corresponds to the operation in weather and turbulence detections. All turbulent/non turbulent areas beyond 50 NM are displayed in the conventional black, green, yellow and red as in the weather (WX) mode. - TURB This mode corresponds to the operation in turbulence detection. Turbulence detection is limited to the first 50 NM regardless of the weather radar range selected and displayed. Turbulence areas are displayed on the NDs in magenta. NOTE : There is no detection of turbulence in clear sky. ____ - MAP This mode is only used for display of the ground map. A combination of transceiver gain, antenna position (TILT) and

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range selection enables the display of a larger area and the identification of major changes in the ground map (e.g. a sea cost, a lake, a mountain, an island...). The color display follows the color mentioned in correspondence table (see table 1 - para. 7. A.) If the image is too bright, due to too great reflection intensity, it can be dimmed by the GAIN potentiometer, item 1. **ON A/C 001-049, 101-105, (b) System selection and start up: OFF/ON switch (item 1) This switch enables: - the activation of the transceiver - the suppression of the radar image on the NDs when these NDs are in the ARC or ROSE mode. **ON A/C 051-099, 106-149, 201-233, 236-238, (b) System selection and start up: 1/OFF/2 switch (item 6) This switch enables: - the selection and activation of the transceiver 1 or 2 (if the second transceiver is installed), - the suppression of the radar image on the NDs when these NDs are in the ARC or ROSE mode. R R

**ON A/C 151-199, 234-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (b) System selection and start up: 1/OFF/2 switch (item 1) This switch enables: - the selection and activation of the transceiver 1 or 2 (if the second transceiver is installed) - the suppression of the radar image on the NDs when these NDs are in the ARC or ROSE mode. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-233, 236-238, (c) Gain control (item 5) The GAIN potentiometer enables the manual control of transceiver sensitivity in the WX, WX/TURB and MAP modes. When the potentiometer is rotated fully counterclockwise, the AUTO position provides preset calibrated transceiver gain level (maximum receiver sensitivity). Clockwise rotation of the GAIN potentiometer increases the gain towards the MAX position.

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In the AUTO position, no indication appears in the R lower corner of the NDs. For the other positions, the MAN indication is displayed in white. In the windshear position, the gain control is automatic in the WR/PWS for the scanning. (d) TILT control (item 3) The TILT selector switch enables the variation of the antenna elevation angle in 1/4 deg. steps on a non-linear scale graduated in degrees, within a range of +15 deg. (UP) to -15 deg. (DOWN) in relation to a horizontal plane defined by the stabilization system. This antenna elevation angle is displayed in cyan in the R lower corner of the ND and progresses in steps of 0.25 deg. If the antenna position is different from the TILT selector switch position, a red ANT failure warning message replaces the TILT indication in the R lower corner of the ND. In windshear mode, the tilt is automatic and the tilt displayed on ND is always the selection on the radar control section although different in the antenna. In the windshear position, the tilt control is automatic in the WR/PWS for the scanning. However, the tilt displayed on ND is in accordance with the one selected on the radar control unit. (e) WINDSHEAR/AUTO/OFF switch (item 4) In AUTO position, the windshear detection is automatic if altitude is lower than 2300 ft and qualifiers A and B are valid. This automatic operation can be inhibited when the switch is in the OFF position. **ON A/C 106-149, (c) Gain control (item 1) The GAIN potentiometer enables the manual control of transceiver sensitivity in the WX, WX+T, TURB and MAP modes. Clockwise rotation of the GAIN potentiometer increases the gain towards the MAX position. When the potentiometer is rotated fully clockwise, the CAL position provides preset calibrated transceiver gain level (minimum receiver sensitivity). When the GAIN potentiometer is the CAL position, no indication appears in the R lower corner of the NDs. When the GAIN potentiometer is in a position other than CAL, the MAN GAIN indication is displayed in white. In windshear mode, the gain control is automatic for the WR/PWS scanning.

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(d) TILT control (item 3) The TILT selector switch enables the variation of the antenna elevation angle in 1/4 deg. steps on a non-linear scale graduated in degrees, within a range of +15 deg. (UP) to -15 deg. (DOWN) in relation to a horizontal plane defined by the stabilization system. This antenna elevation angle (TILT), selected on the radar control unit, is displayed in cyan in the R lower corner of the ND in this form: MAN +/-XX.X⁰. If the antenna elevation angle is different from the TILT selector switch position, a red ANT failure warning message replaces the TILT indication in the R lower corner of the ND. In windshear mode, the tilt control is automatic for WR/PWS scanning. (e) PWS/AUTO/OFF switch (item 2) In AUTO position, the windshear detection is automatic if altitude is lower than 2300 ft and qualifiers A and B are valid. This automatic operation can be inhibited when the switch is in the OFF position. (f) Ground clutter suppression (item 4) Activation of the GND CLTR SPRS switch, in weathers modes (WX, WX+T, TURB), reduces the intensity of the ground clutter. These ground returns are replaced by black areas on the radar image when the GND CLTR SPRS switch is placed in ON position. **ON A/C 234-235, 239-249, 251-299, 303-399, 401-499, (c) TILT control value (item 3) The TILT selector switches enable the variation of the antenna elevation angle in 1/4 deg. steps on a non-linear scale graduated in degrees, within a range of +15 deg. (UP) to -15 deg. (DOWN) in relation to a horizontal plane defined by the stabilization system. This antenna elevation angle is displayed in cyan in the R lower corner of the ND and progresses in steps of 0.25 deg. If the antenna position is different from the TILT selector switch position, a red ANT failure warning message replaces the TILT indication in the R lower corner of the ND. In windshear mode, the tilt is automatic and the tilt displayed on ND is always the selection on the radar control section although different in the antenna. In the windshear position, the tilt control is automatic in the WR/PWS for the scanning. However, the tilt displayed on ND is in accordance with the one selected on the radar control unit.

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(d) OFF/AUTO PWS switch (item 4) In AUTO position, the windshear detection is automatic if altitude is lower than 2300 ft and qualifiers A and B are valid. This automatic operation can be inhibited when the switch is in the OFF position. (e) MAN/AUTO TILT switch, item 6, this mode is used to select between manual mode or autotilt mode. In MAN position, all controls operate as described in the manual mode. In AUTO position, the system operates in autotilt mode (automatic tilt and no action of the crew is necessary). **ON A/C 301-302, (c) TILT control value (item 3) The TILT selector switches enable the variation of the antenna elevation angle in 1/4 deg. steps on a non-linear scale graduated in degrees, within a range of +15 deg. (UP) to -15 deg. (DOWN) in relation to a horizontal plane defined by the stabilization system. This antenna elevation angle is displayed in cyan in the R lower corner of the ND and progresses in steps of 0.25 deg. If the antenna position is different from the TILT selector switch position, a red ANT failure warning message replaces the TILT indication in the R lower corner of the ND. In windshear mode, the tilt is automatic and the tilt displayed on ND is always the selection on the radar control section although different in the antenna. In the windshear position, the tilt control is automatic in the WR/PWS for the scanning. However, the tilt displayed on ND is in accordance with the one selected on the radar control unit. (d) OFF/AUTO PWS switch (item 4) In AUTO position, the windshear detection is automatic if altitude is lower than 2300 ft and qualifiers A and B are valid. This automatic operation can be inhibited when the switch is in the OFF position. (e) MAN/AUTO TILT switch, item 6, this mode is used to select between manual mode or autotilt mode. In MAN position, all controls operate as described in the manual mode. In AUTO position, the system operates in autotilt mode (automatic tilt and no action of the crew is necessary).

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R

**ON A/C 501-509, 511-526, 528-599, (c) Gain control (item 1) The GAIN potentiometer enables the manual control of transceiver sensitivity in the WX, WX+T, TURB and MAP modes. Clockwise rotation of the GAIN potentiometer increases the gain towards the MAX position. When the potentiometer is rotated fully clockwise, the CAL position provides preset calibrated transceiver gain level (minimum receiver sensitivity). When the GAIN potentiometer is the CAL position, no indication appears in the R lower corner of the NDs. When the GAIN potentiometer is in a position other than CAL, the MAN GAIN indication is displayed in white. In windshear mode, the gain control is automatic for the WR/PWS scanning. (d) TILT control (item 3) The TILT selector switch enables the variation of the antenna elevation angle in 1/4 deg. steps on a non-linear scale graduated in degrees, within a range of +15 deg. (UP) to -15 deg. (DOWN) in relation to a horizontal plane defined by the stabilization system. This antenna elevation angle (TILT), selected on the radar control unit, is displayed in cyan in the R lower corner of the ND in this form: MAN +/-XX.X⁰. If the antenna elevation angle is different from the TILT selector switch position, a red ANT failure warning message replaces the TILT indication in the R lower corner of the ND. In windshear mode, the tilt control is automatic for WR/PWS scanning. In windshear mode, the tilt indication on the NDs is replaced by the green PWS SCAN indication. (e) PWS/AUTO/OFF switch (item 2) In AUTO position, the windshear detection is automatic if altitude is lower than 2300 ft and qualifiers A and B are valid. This automatic operation can be inhibited when the switch is in the OFF position. (f) Ground clutter suppression (item 4) Activation of the GND CLTR SPRS switch, in weathers modes (WX, WX+T, TURB), reduces the intensity of the ground clutter. These ground returns are replaced by black areas on the radar image when the GND CLTR SPRS switch is placed in ON position.

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**ON A/C ALL (3) Utilization of the EFIS control sections and lighting/LOUDSPEAKER control panels (Ref. Fig. 017) (a) Mode selector switch (item 1) This mode selector switch enables the image display on the corresponding ND whenever the ARC or ROSE mode is selected and the transceiver is supplied. In that case, the radar image is displayed in the background of the navigation image. If neither ROSE or ARC mode is selected, the message W/S CHANGE MODE is shown on both NDs, if there is a windshear alert. The pilot is advised to select ARC or ROSE mode to see the W/S icon. The color depends on the W/S alert level. (b) Scale selector switch (item 2) This selector switch enables the display of the range selected for an optimum use of the radar image on the corresponding ND. For each of the following ranges: 10, 20, 40, 80, 160 and 320, four concentric range arcs are displayed respectively spaced 2.5, 5, 10, 20, 40 and 80 NM, when the mode selector switch is in the ARC position. Only 2 range arcs are displayed in the ROSE mode. Windshear information is presented in the 10 NM range only. If a windshear alert is generated but the selected range is greater than 10 NM, the message W/S: SET RNG 10 NM is shown on the NDs. In this case, the pilot is advised to select the 10 NM range. The color depends on the W/S alert level. (c) Radar image brightness control (item 3) The ND potentiometer enables the adjustment of brightness and contrast of radar echoes in relation to the navigation image, which is superimposed. However, the adjustment range does not allow total extinction of the image. The OFF position of the potentiometer corresponds to the minimum brightness. The BRT position corresponds to the maximum brightness. NOTE : A photoelectric cell associated with each ND also adjusts ____ image brightness as a function of ambient light variations. R

  R EFF : ALL  34-41-00 Page A9   Config-3 May 01/09  CES

 

EFIS Control Sections and EFIS Switching Panels Figure 017   R EFF : ALL  34-41-00 Page A10   Config-3 May 01/09  CES

 

**ON A/C 001-049, 101-105, 151-199, R (4) Weather radar data displayed on the NDs (Ref. Fig. 018) On the figure, the details A) and B) respectively correspond to the ARC and ROSE ND modes for which the display of the radar image is possible. Messages inform the crew of the tilt angle and gain selected on the weather radar control unit. Other messages indicate the failures which affect the operation of the radar system. All these messages are displayed in the R lower corner of each ND whenever a radar image is selected.

R

NOTE : Tilt information and gain selection are displayed on the ND ____ when no failure warning message is generated, or when the TEST mode is not selected. The various failures which can affect the radar image are listed in decreasing order of importance. If several failures occur, only the most important one is displayed (Ref. details C) and D) on the figure).

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Weather radar - Data Displayed on the NDs Figure 018   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page A12 511-526, 528-599,  Config-3 Feb 01/10  CES

 

Two types of failures can affect the radar system: (a) Failures which result in the loss of the radar image The corresponding messages are displayed in red - WXR : indicates an overheating of the Display Unit (DU) DU - WXR : indicates a failure of the weather radar transceiver R/T - WXR : indicates a failure of the weather radar antenna ANT - WXR : indicates a failure of the weather radar control unit CTL - WXR : indicates an error of comparison between the range RNG from the EFIS control section and the copy data received on the DMC via the radar data bus. NOTE : In case of insufficient avionics ventilation, the weather ____ radar image is lost in order to prevent NDs overheat. (b) Failures which do not affect the radar image The corresponding messages are displayed in amber - WXR : indicates the loss of the transceiver calibration WEAK - PRED : indicates a failure of the windshear function W/S - WXR : indicates an attitude failure from the ADIRU ATT - NO : indicates a failure of the autotilt function AUTOTILT - WXR : indicates the loss of the radar antenna stabilization STAB - WXR : indicates the selection of the radar TEST mode. TEST

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R

**ON A/C 051-099, 201-233, 236-238,

R R R R R R R R R R

(4) Weather radar data displayed on the NDs (Ref. Fig. 018A) On the figure, the details A) and B) respectively correspond to the ARC and ROSE ND modes for which the display of the radar image is possible. Messages inform the crew of the tilt angle and gain selected on the weather radar control unit. Other messages indicate the failures which affect the operation of the radar system. All these messages are displayed in the R lower corner of each ND whenever a radar image is selected.

R R R

NOTE : Tilt information and gain selection are displayed on the ND ____ when no failure warning message is generated, or when the TEST mode is not selected.

R R R R

The various failures which can affect the radar image are listed in decreasing order of importance. If several failures occur, only the most important one is displayed (Ref. details C) and D) on the figure).

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Weather radar - Data Displayed on the NDs Figure 018A

R

  R EFF : 051-099, 201-233, 236-238, 301-302,  34-41-00 Page A15   Config-3 May 01/09  CES

 

R

Two types of failures can affect the radar system:

R R R R R R R R R R R

(a) Failures which result in the loss of the radar image The corresponding messages are displayed in red - WR : indicates a failure of the weather radar transceiver R/T - WR : indicates a failure of the weather radar antenna ANT - WR : indicates a failure of the weather radar control unit CTL - WR : indicates an error of comparison between the range RNG from the EFIS control section and the copy data received on the symbol generator via the radar data bus.

R R

NOTE : In case of insufficient avionics ventilation, the weather ____ radar image is lost in order to prevent NDs overheat.

R R R R R R R R R R

(b) Failures which do not affect the radar image The corresponding messages are displayed in amber - WR : indicates the loss of the transceiver calibration WEAK - WR : indicates an attitude failure from the ADIRU ATT - WR : indicates the loss of the radar antenna stabilization STAB - WR : indicates the selection of the radar TEST mode. TEST

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R

**ON A/C 106-149,

R R R R R R R R R R

(4) Weather radar data displayed on the NDs (Ref. Fig. 018B) On the figure, the details A) and B) respectively correspond to the ARC and ROSE ND modes for which the display of the radar image is possible. Messages inform the crew of the tilt angle and gain selected on the weather radar control unit. Other messages indicate the failures which affect the operation of the radar system. All these messages are displayed in the R lower corner of each ND whenever a radar image is selected.

R R R

NOTE : Tilt information and gain selection are displayed on the ND ____ when no failure warning message is generated, or when the TEST mode is not selected.

R R R R

The various failures which can affect the radar image are listed in decreasing order of importance. If several failures occur, only the most important one is displayed (Ref. details C) and D) on the figure).

  R EFF : 106-149,  34-41-00 Page A17   Config-3 May 01/09  CES

 

Weather radar - Data Displayed on the NDs Figure 018B

R

  R EFF : 106-149,  34-41-00 Page A18   Config-3 May 01/09  CES

 

R

Two types of failures can affect the radar system:

R R R R R R R R R R R

(a) Failures which result in the loss of the radar image The corresponding messages are displayed in red - WR : indicates a failure of the weather radar transceiver R/T - WR : indicates a failure of the weather radar antenna ANT - WR : indicates a failure of the weather radar control unit CTL - WR : indicates an error of comparison between the range RNG from the EFIS control section and the copy data received on the symbol generator via the radar data bus.

R R R R R R R R R R

(b) Failures which do not affect the radar image The corresponding messages are displayed in amber - WR : indicates the loss of the transceiver calibration WEAK - WR : indicates an attitude failure from the ADIRU ATT - WR : indicates the loss of the radar antenna stabilization STAB - WR : indicates the selection of the radar TEST mode. TEST

  R EFF : 106-149,  34-41-00 Page A19   Config-3 May 01/09  CES

 

R

**ON A/C 234-235, 239-249, 251-299, 303-399, 401-499,

R R R R R R R R R R

(4) Weather radar data displayed on the NDs (Ref. Fig. 018C) On the figure, the details A) and B) respectively correspond to the ARC and ROSE ND modes for which the display of the radar image is possible. Messages inform the crew of the tilt angle and gain selected on the weather radar control unit. Other messages indicate the failures which affect the operation of the radar system. All these messages are displayed in the R lower corner of each ND whenever a radar image is selected.

R R R

NOTE : Tilt information and gain selection are displayed on the ND ____ when no failure warning message is generated, or when the TEST mode is not selected.

R R R R

The various failures which can affect the radar image are listed in decreasing order of importance. If several failures occur, only the most important one is displayed (Ref. details C) and D) on the figure).

  R EFF : 234-235, 239-249, 251-299, 303-399,  34-41-00 Page A20 401-499,  Config-3 May 01/09  CES

 

Weather radar - Data Displayed on the NDs Figure 018C

R

  R EFF : 234-235, 239-249, 251-299, 303-399,  34-41-00 Page A21 401-499,  Config-3 May 01/09  CES

 

R

Two types of failures can affect the radar system:

R R R R R R R R R R R R R R R

(a) Failures which result in the loss of the radar image The corresponding messages are displayed in red - WXR : indicates the loss of the transceiver calibration WEAK - WXR : indicates an overheating of the Display Unit (DU) DU - WXR : indicates a failure of the weather radar transceiver R/T - WXR : indicates a failure of the weather radar antenna ANT - WXR : indicates a failure of the weather radar control unit CTL - WXR : indicates an error of comparison between the range RNG from the EFIS control section and the copy data received on the DMC via the radar data bus.

R R R R R R R R R R R R

(b) Failures which do not affect the radar image The corresponding messages are displayed in amber - PRED : indicates a failure of the windshear function W/S - WXR : indicates an attitude failure from the ADIRU ATT - NO : indicates a failure of the Multiscan function AUTOTILT - WXR : indicates the loss of the radar antenna stabilization STAB - WXR : indicates the selection of the radar TEST mode. TEST

  R EFF : 234-235, 239-249, 251-299, 303-399,  34-41-00 Page A22 401-499,  Config-3 May 01/09  CES

 

R

**ON A/C 301-302,

R R R R R R R R R R

(4) Weather radar data displayed on the NDs (Ref. Fig. 018A) On the figure, the details A) and B) respectively correspond to the ARC and ROSE ND modes for which the display of the radar image is possible. Messages inform the crew of the tilt angle and gain selected on the weather radar control unit. Other messages indicate the failures which affect the operation of the radar system. All these messages are displayed in the R lower corner of each ND whenever a radar image is selected.

R R R

NOTE : Tilt information and gain selection are displayed on the ND ____ when no failure warning message is generated, or when the TEST mode is not selected.

R R R R

The various failures which can affect the radar image are listed in decreasing order of importance. If several failures occur, only the most important one is displayed (Ref. details C) and D) on the figure).

  R EFF : 301-302,  34-41-00 Page A23   Config-3 May 01/09  CES

 

R

Two types of failures can affect the radar system:

R R R R R R R R R R R R R R R

(a) Failures which result in the loss of the radar image The corresponding messages are displayed in red - WXR : indicates the loss of the transceiver calibration WEAK - WXR : indicates an overheating of the Display Unit (DU) DU - WXR : indicates a failure of the weather radar transceiver R/T - WXR : indicates a failure of the weather radar antenna ANT - WXR : indicates a failure of the weather radar control unit CTL - WXR : indicates an error of comparison between the range RNG from the EFIS control section and the copy data received on the DMC via the radar data bus.

R R

NOTE : In case of insufficient avionics ventilation, the weather ____ radar image is lost in order to prevent NDs overheat.

R R R R R R R R R R R R

(b) Failures which do not affect the radar image The corresponding messages are displayed in amber - PRED : indicates a failure of the windshear function W/S - WXR : indicates an attitude failure from the ADIRU ATT - NO : indicates a failure of the Multiscan function AUTOTILT - WXR : indicates the loss of the radar antenna stabilization STAB - WXR : indicates the selection of the radar TEST mode. TEST

  R EFF : 301-302,  34-41-00 Page A24   Config-3 May 01/09  CES

 

R

**ON A/C 501-509, 511-526, 528-599, (4) Weather radar data displayed on the NDs (Ref. Fig. 018) On the figure, the details A) and B) respectively correspond to the ARC and ROSE ND modes for which the display of the radar image is possible. Messages inform the crew of the tilt angle and gain selected on the weather radar control unit. Other messages indicate the failures which affect the operation of the radar system. All these messages are displayed in the R lower corner of each ND whenever a radar image is selected. NOTE : Tilt information and gain selection are displayed on the ND ____ when no failure warning message is generated, or when the TEST mode is not selected. The various failures which can affect the radar image are listed in decreasing order of importance. If several failures occur, only the most important one is displayed (Ref. details C) and D) on the figure).

  R EFF : 501-509, 511-526, 528-599,  34-41-00 Page A25   Config-3 Feb 01/10  CES

 

Two types of failures can affect the radar system: (a) Failures which result in the loss of the radar image The corresponding messages are displayed in red - WXR : indicates an overheating of the Display Unit (DU) DU - WXR : indicates a failure of the weather radar transceiver R/T - WXR : indicates a failure of the weather radar antenna ANT - WXR : indicates a failure of the weather radar control unit CTL - WXR : indicates an error of comparison between the range RNG from the EFIS control section and the copy data received on the DMC via the radar data bus. (b) Failures which do not affect the radar image The corresponding messages are displayed in amber - WXR : indicates the loss of the transceiver calibration WEAK - PRED : indicates a failure of the windshear function W/S - WXR : indicates an attitude failure from the ADIRU ATT - NO : indicates a failure of the autotilt function AUTOTILT - WXR : indicates the loss of the radar antenna stabilization STAB - WXR : indicates the selection of the radar TEST mode. TEST

  R EFF : 501-509, 511-526, 528-599,  34-41-00 Page A26   Config-3 Feb 01/10  CES

 

R R

**ON A/C 234-235, 239-249, 251-299, 303-399, 401-499, 501-509, 511-526, 528-599, (c) Operational message that does not affect the radar image The following message is displayed in green instead of the TILT value - PWS SCAN : indicates that the weather radar operates in windshear mode only (weather radar system selector switch set to OFF and windshear mode selector switch set to AUTO on weather radar control unit). On ground the qualifier logic has to be satisfied. **ON A/C 001-049, 101-105, 151-199, (5) Windshear data displayed (Ref. table 2 below) (if the predictive windshear function is activated) (Ref. Fig. 019) (a) Windshear indications The location of a windshear phenomenon is indicated to the crew by means of an icon superimposed on the radar image. This icon consists of alternating red and black arcs. For 15 NM range selection and above, yellow radial lines appear at the edges and start beyond the windshear event. These lines, superimposed on the radar image, continue to the edge of the display area to provide directional information for the event. The windshear data are always displayed even if the 1/OFF/2 switch on the radar control unit is set to OFF. The AUTO/OFF/WINDSHEAR switch on the radar control unit has to be set to AUTO. (b) Windshear alert **ON A/C 001-049, 101-105, (Ref. Fig. 020) **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 021)

  R EFF : 001-049, 101-105, 151-199, 234-235,  34-41-00 Page A27 239-249, 251-299, 303-399, 401-499, 501-509,  Config-3 Feb 01/10 511-526, 528-599, CES

 

Windshear - Data Displayed on the NDs Figure 019

R

  R EFF : 001-049, 101-105, 151-199,  34-41-00 Page A28   Config-3 May 01/09  CES

 

Windshear - Data Displayed on the NDs Figure 019A

R

  R EFF : 051-099, 106-149, 201-233, 236-238,  34-41-00 Page A29 301-302,  Config-3 May 01/09  CES

 

Windshear - Data Displayed on the NDs Figure 019B   R EFF : 234-235, 239-249, 251-299, 303-399,  34-41-00 Page A30 401-499, 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

Weather Radar - Windshear Alert Ranges and Altitudes Figure 020

R

  R EFF : 001-049, 101-105,  34-41-00 Page A31   Config-3 May 01/09  CES

 

Windshear - Windshear Alert Ranges and Altitudes Figure 020A   R EFF : 051-099, 106-149, 151-199, 201-249,  34-41-00 Page A32 251-299, 301-399, 401-499, 501-509, 511-526,  Config-3 Feb 01/10 528-599, CES

 

Windshear - Windshear Alert Levels and Locations Figure 021   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page A33 511-526, 528-599,  Config-3 Feb 01/10  CES

 

1 _

Alert levels There are three alert levels defined in function of event seriousness and distance from the aircraft. The weather radar provides the crew with visual and aural warnings which vary in function of the level detected. a _

Windshear warning alert (level 3) This alert corresponds to the most dangerous phenomenons. It is generated for windshear events detected within +/0.25 NM from the longitudinal axis of the aircraft and within +/- 40 deg. scan of the aircraft heading. On the ground, the maximum range is 3 NM. In flight, the maximum range is reduced to 1.5 NM. During takeoff, level 3 covers ranges from 0.5 to 1.5 NM, from 50 to 1200 ft Above Ground Level (AGL). During landing, this coverage is from 1.5 to 0.5 NM, from 375 to 50 ft. Range reduction is a linear function of altitude: at 375 ft, range is equal to 1.5 NM and reaches 0.5 NM at 50 ft. During takeoff, this warning is inhibited from the time the aircraft attains 100 kts and until it reaches 50 ft AGL. Level 3 warning is inhibited below 50 ft (in approach phase) and above 1200 ft. The windshear warning alert is announced by: - an aural warning message: GO AROUND WINDSHEAR AHEAD in approach or WINDSHEAR AHEAD, WINDSHEAR AHEAD at takeoff, generated by the radar synthesized voice. - a visual warning: red W/S AHEAD message on the PFD. Display priority on PFD is given to level 3. The FWC has determine whether the aircraft is taking-off or landing to generate the aural warning: GO AROUND, WINDSHEAR AHEAD or WINDSHEAR AHEAD, WINDSHEAR AHEAD. Transition between the GO AROUND, WINDSHEAR AHEAD and WINDSHEAR AHEAD, WINDS HEAR AHEAD aural warning messages is controlled by the GEAR UP discrete input.

b _

Windshear caution alert (level 2) This level covers the events detected in a region from 0 to 3 NM, within +/- 25 deg. of the aircraft heading but outside the windshear warning alert region (level 3). This caution alert is inhibited: - during takeoff, from the time the aircraft attains 100 kts and until it reaches 50 ft AGL, - during landing, below 50 ft AGL. There should be no windshear caution alert (level 2) above 1200 ft. The windshear caution alert is announced by:

  EFF : 001-049, 101-105, 151-199,  34-41-00 Page A34   Config-3 May 01/09 R  CES

 

- an aural warning: MONITOR RADAR DISPLAY - a visual warning: amber W/S AHEAD message on the PFD. c _

Windshear advisory alert (level 1) This level covers the events located within 5 NM from the aircraft, within +/- 40 deg. of the aircraft heading but outside the windshear warning and caution alert regions (levels 2 and 3). There should be no windshear advisory alert (level 1) above 1500 ft. No aural or visual warnings are provided for this advisory alert: only the windshear icon is superimposed on the radar image. The weather radar transmits the windshear alerts following their detection order. A maximum of 8 events can be transmitted. Therefore, alerts of different levels can be generated simultaneously.

------------------------------------------------------------------------------| ALERTS | PFD | ND | AURAL WARNING | |-------------|-----------------|-------------------|-------------------------| | Advisory | | windshear icon | | |-------------|-----------------|-------------------|-------------------------| | Caution | W/S AHEAD | windshear icon | MONITOR | | | (AMBER) | | RADAR DISPLAY | |-------------|-----------------|-------------------|-------------------------| | Warning | W/S AHEAD | windshear icon | during takeoff: | | | (RED) | | WINDSHEAR AHEAD | | | | | WINDSHEAR AHEAD | | | | | during landing: | | | | | GO AROUND | | | | | WINDSHEAR AHEAD | ------------------------------------------------------------------------------Table 2: PWS OPERATIVE - Windshear Data Displayed NOTE : Between 2300ft and 1500ft, no warning is triggered: ____ the PWS is in standby in this boundary, without any cockpit effect.

  EFF : 001-049, 101-105, 151-199,  34-41-00 Page A35   Config-3 May 01/09 R  CES

 

R

**ON A/C 051-099, 106-149, 201-233, 236-238, 301-302,

R R R

(5) Windshear data displayed (Ref. table 2 below) (if the predictive windshear function is activated) (Ref. Fig. 019A)

R R R R R R R R R R R R

(a) Windshear indications The location of a windshear phenomenon is indicated to the crew by means of an icon superimposed on the radar image. This icon consists of alternating red and black arcs. For 10 NM range selection and above, yellow radial lines appear at the edges and start beyond the windshear event. These lines, superimposed on the radar image, continue to the edge of the display area to provide directional information for the event. The windshear data are always displayed even if the system selector switch on the radar control unit is set to OFF. The windshear switch on the radar control unit has to be set to AUTO.

R R

(b) Windshear alert (Ref. Fig. 020A, 021A)

R R R R R

1 _

R R R R R R R R R R R R R R R R R R

Alert levels There are three alert levels defined in function of event seriousness and distance from the aircraft. The weather radar provides the crew with visual and aural warnings which vary in function of the level detected. a _

Windshear warning alert (level 3) This alert corresponds to the most dangerous phenomenons. It is generated for windshear events detected within +/0.25 NM from the longitudinal axis of the aircraft and within +/- 30 deg. scan of the aircraft heading. On the ground, the maximum range is 3 NM. In flight, the maximum range is reduced to 1.5 NM. During takeoff, level 3 covers ranges from 0 to 1.5 NM, from 50 to 1200 ft Above Ground Level (AGL). During landing, this coverage is from 1.5 to 0.5 NM, from 370 to 50 ft. Range reduction is a linear function of altitude: at 370 ft, range is equal to 1.5 NM and reaches 0.5 NM at 50 ft. During takeoff, this warning is inhibited from the time the aircraft attains 100 kts and until it reaches 50 ft AGL. Level 3 warning is inhibited below 50 ft (in approach phase) and above 1200 ft. The windshear warning alert is announced by:

  R EFF : 051-099, 106-149, 201-233, 236-238,  34-41-00 Page A36 301-302,  Config-3 May 01/09  CES

 

Windshear - Windshear Alert Levels and Locations Figure 021A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A37 301-399, 401-499,  Config-3 May 01/09  CES

 

R R R R R R R R R R R R

- an aural warning message: GO AROUND WINDSHEAR AHEAD in approach or WINDSHEAR AHEAD, WINDSHEAR AHEAD at takeoff, generated by the radar synthesized voice. - a visual warning: red W/S AHEAD message on the PFD. Display priority on PFD is given to level 3. The computer has to determine whether the aircraft is taking-off or landing to generate the aural warning message GO AROUND, WINDSHEAR AHEAD or WINDSHEAR AHEAD, WINDSHEAR AHEAD. Transition between the GO AROUND, WINDSHEAR AHEAD and WINDSHEAR AHEAD, WINDSHEAR AHEAD aural warning messages is controlled by the GEAR UP discrete input.

R R R R R R R R R R R R R

b _

Windshear caution alert (level 2) This level covers the events detected in a region from 0 to 3 NM, within +/- 30 deg. of the aircraft heading but outside the windshear warning alert region (level 3). This caution alert is inhibited: - during takeoff, from the time the aircraft attains 100 kts and until it reaches 50 ft AGL, - during landing, below 50 ft AGL. There should be no windshear caution alert (level 2) above 1200 ft. The windshear caution alert is announced by: - an aural warning: MONITOR RADAR DISPLAY - a visual warning: amber W/S AHEAD message on the PFD.

R R R R R R R R R R R R R R

c _

Windshear advisory alert (level 1) This level covers the events located within 5 NM from the aircraft, within +/- 30 deg. of the aircraft heading but outside the windshear warning and caution alert regions (levels 2 and 3). There should be no windshear advisory alert (level 1) above 1500 ft. No aural or visual warnings are provided for this advisory alert: only the windshear icon is superimposed on the radar image. The weather radar transmits the windshear alerts following their detection order. A maximum of 8 events can be transmitted. Therefore, alerts of different levels can be generated simultaneously.

  R EFF : 051-099, 106-149, 201-233, 236-238,  34-41-00 Page A38 301-302,  Config-3 May 01/09  CES

 

------------------------------------------------------------------------------| ALERTS | PFD | ND | AURAL WARNING | |-------------|-----------------|-------------------|-------------------------| | Advisory | | windshear icon | | |-------------|-----------------|-------------------|-------------------------| | Caution | W/S AHEAD | windshear icon | MONITOR | | | (AMBER) | | RADAR DISPLAY | |-------------|-----------------|-------------------|-------------------------| | Warning | W/S AHEAD | windshear icon | during takeoff: | | | (RED) | | WINDSHEAR AHEAD | | | | | WINDSHEAR AHEAD | | | | | during landing: | | | | | GO AROUND | | | | | WINDSHEAR AHEAD | ------------------------------------------------------------------------------Table 2: Windshear Data Displayed R R

**ON A/C 234-235, 239-249, 251-299, 303-399, 401-499, 501-509, 511-526, 528-599, (5) Windshear data displayed (Ref. table 2 below) (if the predictive windshear function is activated) (Ref. Fig. 019B) (a) Windshear indications The location of a windshear phenomenon is indicated to the crew by means of an icon superimposed on the radar image. This icon consists of alternating red and black arcs. For 10 NM range selection and above, yellow radial lines appear at the edges and start beyond the windshear event. These lines, superimposed on the radar image, continue to the edge of the display area to provide directional information for the event. The windshear data are always displayed even if the system selector switch on the radar control unit is set to OFF. The windshear switch on the radar control unit has to be set to AUTO. When on the radar control unit, the weather radar system selector switch is set to OFF and the windshear mode selector switch is set to AUTO, the green PWS SCAN indication is displayed on the bottom right-hand corner of the NDs instead of the tilt indication to inform the crew that the weather radar operates in windshear mode only.

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A39 301-399, 401-499, 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

(b) Windshear alert (Ref. Fig. 020A) R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 021) **ON A/C 234-235, 239-249, 251-299, 303-399, 401-499, (Ref. Fig. 021A)

R R

**ON A/C 234-235, 239-249, 251-299, 303-399, 401-499, 501-509, 511-526, 528-599, 1 _

Alert levels There are three alert levels defined in function of event seriousness and distance from the aircraft. The weather radar provides the crew with visual and aural warnings which vary in function of the level detected. a _

Windshear warning alert (level 3) This alert corresponds to the most dangerous phenomenons. It is generated for windshear events detected within +/0.25 NM from the longitudinal axis of the aircraft and within +/- 30 deg. scan of the aircraft heading. On the ground, the maximum range is 3 NM. In flight, the maximum range is reduced to 1.5 NM. During takeoff, level 3 covers ranges from 0 to 1.5 NM, from 50 to 1200 ft Above Ground Level (AGL). During landing, this coverage is from 1.5 to 0.5 NM, from 370 to 50 ft. Range reduction is a linear function of altitude: at 370 ft, range is equal to 1.5 NM and reaches 0.5 NM at 50 ft. During takeoff, this warning is inhibited from the time the aircraft attains 100 kts and until it reaches 50 ft AGL. Level 3 warning is inhibited below 50 ft (in approach phase) and above 1200 ft. The windshear warning alert is announced by: - an aural warning message: GO AROUND WINDSHEAR AHEAD in approach or WINDSHEAR AHEAD, WINDSHEAR AHEAD at takeoff, generated by the radar synthesized voice. - a visual warning: red W/S AHEAD message on the PFD. Display priority on PFD is given to level 3. The computer has to determine whether the aircraft is taking-off or landing to generate the aural warning message

  R EFF : 234-235, 239-249, 251-299, 303-399,  34-41-00 Page A40 401-499, 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

GO AROUND, WINDSHEAR AHEAD or WINDSHEAR AHEAD, WINDSHEAR AHEAD. Transition between the GO AROUND, WINDSHEAR AHEAD and WINDSHEAR AHEAD, WINDSHEAR AHEAD aural warning messages is controlled by the GEAR UP discrete input. b _

Windshear caution alert (level 2) This level covers the events detected in a region from 0 to 3 NM, within +/- 30 deg. of the aircraft heading but outside the windshear warning alert region (level 3). This caution alert is inhibited: - during takeoff, from the time the aircraft attains 100 kts and until it reaches 50 ft AGL, - during landing, below 50 ft AGL. There should be no windshear caution alert (level 2) above 1200 ft. The windshear caution alert is announced by: - an aural warning: MONITOR RADAR DISPLAY - a visual warning: amber W/S AHEAD message on the PFD.

c _

Windshear advisory alert (level 1) This level covers the events located within 5 NM from the aircraft, within +/- 30 deg. of the aircraft heading but outside the windshear warning and caution alert regions (levels 2 and 3). There should be no windshear advisory alert (level 1) above 1500 ft. No aural or visual warnings are provided for this advisory alert: only the windshear icon is superimposed on the radar image. The weather radar transmits the windshear alerts following their detection order. A maximum of 8 events can be transmitted. Therefore, alerts of different levels can be generated simultaneously.

------------------------------------------------------------------------------| ALERTS | PFD | ND | AURAL WARNING | |-------------|-----------------|-------------------|-------------------------| | Advisory | | windshear icon | | |-------------|-----------------|-------------------|-------------------------| | Advisory | | PWS SCAN | | | in windshear| | (GREEN) | | | mode only | | | | |-------------|-----------------|-------------------|-------------------------| | Caution | W/S AHEAD | windshear icon | MONITOR | | | (AMBER) | | RADAR DISPLAY | |-------------|-----------------|-------------------|-------------------------|

  R EFF : 234-235, 239-249, 251-299, 303-399,  34-41-00 Page A41 401-499, 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

------------------------------------------------------------------------------| ALERTS | PFD | ND | AURAL WARNING | |-------------|-----------------|-------------------|-------------------------| | Warning | W/S AHEAD | windshear icon | during takeoff: | | | (RED) | | WINDSHEAR AHEAD | | | | | WINDSHEAR AHEAD | | | | | during landing: | | | | | GO AROUND | | | | | WINDSHEAR AHEAD | ------------------------------------------------------------------------------Table 2: Windshear Data Displayed R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, (6) Windshear warning displayed (Ref. table 3 below) (if the predictive windshear function is activated) (Ref. Fig. 022) (a) Windshear flags on NDs When a windshear fault occurs, an amber PRED W/S message comes into view. The radar image remains available if this fault does not affect the radar modes or detection function. A detected fault is displayed when: - the aircraft is on the ground or the flap and slat control lever is in a position different from 0. - the windshear AUTO/OFF switch on the radar control unit is set to AUTO (the fault message is not displayed when the switch is set to OFF). (b) Warning display on EWD A detected windshear fault is indicated by the following amber messages: - NAV: PRED. W/S DET FAULT on EWD. - PRED. W/S DET on SD INOP SYSTEM area. This message is associated to the indications presented on the NDs. When the windshear AUTO/OFF switch is set to OFF on the weather radar control unit, a green or amber PRED W/S OFF memo message is presented to the crew. The color of this message depends on the flight phases.

  R EFF : 001-049, 101-105, 151-199, 234-235,  34-41-00 Page A42 239-249, 251-299, 303-399, 401-499, 501-509,  Config-3 Feb 01/10 511-526, 528-599, CES

 

Messages Displayed on ND and upper ECAM DU Figure 022   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page A43 511-526, 528-599,  Config-3 Feb 01/10  CES

 

------------------------------------------------------------------------------| | EWD | ND | AURAL WARNING | |-------------|-----------------|-------------------|-------------------------| | PWS | NAV: | PRED W/S | Single chime | | SYSTEM | PRED. W/S DET | (AMBER) | | | FAULT | FAULT | | | | | (AMBER) | | | |-------------|-----------------|-------------------|-------------------------| | WINDSHEAR | PRED. W/S OFF | | | | AUTO/OFF | (GREEN or AMBER)| | | | SWITCH ON | | | | | CONTROL | | | | | UNIT IN | | | | | OFF | | | | | POSITION | | | | ------------------------------------------------------------------------------Table 3: PWS INOPERATIVE - Warning Data Displayed (7) Record in the Flight Data Interface Unit (FDIU) The FDIU receives, for recording, the following PWS data through the DMCs: - W/S caution alert (level 2) - W/S warning alert (level 3) - W/S AUTO/OFF - W/S internal fault - W/S external fault - DMCs/FWCs PWS pin program status. This data, except the PWS pin program status, is only transmitted from the DMCs if the DMCs/FWCs PWS pin program is valid (grounded).

  R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page A44 511-526, 528-599,  Config-3 Feb 01/10  CES

 

R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499,

R R R

(6) Windshear warning displayed (Ref. table 3 below) (if the predictive windshear function is activated) (Ref. Fig. 022A)

R R R R R R R R R R

(a) Windshear flags on NDs When a windshear fault occurs, an amber PRED W/S message comes into view. The radar image remains available if this fault does not affect the radar modes or detection function. A detected fault is displayed when: - the aircraft is on the ground or the flap and slat control lever is in a position different from 0. - the windshear AUTO/OFF switch on the radar control unit is set to AUTO (the fault message is not displayed when the switch is set to OFF).

R R R R R R R R R R R

(b) Warning display on Upper ECAM Display Unit A detected windshear fault is indicated by the following amber messages: - NAV: PRED. W/S DET FAULT on EWD. - PRED. W/S DET on SD INOP SYSTEM area. This message is associated to the indications presented on the NDs. When the windshear AUTO/OFF switch is set to OFF on the weather radar control unit, a green or amber PRED W/S OFF memo message is presented to the crew. The color of this message depends on the flight phases.

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A45 301-399, 401-499,  Config-3 May 01/09  CES

 

Messages Displayed on ND and upper ECAM DU Figure 022A

R

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A46 301-399, 401-499,  Config-3 May 01/09  CES

 

R R R R R R R R R R R R R R R R R

------------------------------------------------------------------------------| | UPPER DU ECAM | ND | AURAL WARNING | |-------------|-----------------|-------------------|-------------------------| | PWS | NAV: | PRED W/S | Single chime | | SYSTEM | PRED. W/S DET | (AMBER) | | | FAULT | FAULT | | | | | (AMBER) | | | |-------------|-----------------|-------------------|-------------------------| | WINDSHEAR | PRED. W/S OFF | | | | AUTO/OFF | (GREEN or AMBER)| | | | SWITCH ON | | | | | CONTROL | | | | | UNIT IN | | | | | OFF | | | | | POSITION | | | | ------------------------------------------------------------------------------Table 3: PWS INOPERATIVE - Warning Data Displayed

R R R R R R R R R R R

(7) Record in the Flight Data Interface Unit (FDIU) The FDIU receives, for recording, the following PWS data through the DMCs: - W/S caution alert (level 2) - W/S warning alert (level 3) - W/S AUTO/OFF - W/S internal fault - W/S external fault - DMCs/FWCs PWS pin program status. This data, except the PWS pin program status, is only transmitted from the DMCs if the DMCs/FWCs PWS pin program is valid (grounded).

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A47 301-399, 401-499,  Config-3 May 01/09  CES

 

R

**ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, E. Reconfiguration switching **ON A/C 001-049, 101-105, (Ref. Fig. 002) **ON A/C 106-149, 201-233, 236-238, (Ref. Fig. 002A) **ON A/C 151-199, (Ref. Fig. 002B)

R

**ON A/C 234-235, 301-310, 401-499, (Ref. Fig. 002C)

R

**ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, In normal configuration, the weather radar transceiver receives the altitude information from its corresponding ADIRU. In case of ADIRU1 failure, the pilot can select the altitude information from the ADIRU3. This selection is through the AIR DATA selector switch installed on panel 8VU, on the center pedestal.

  R EFF : 001-049, 101-149, 151-199, 201-238,  34-41-00 Page A48 301-310, 401-499,  Config-3 Nov 01/09  CES

 

R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, E. Reconfiguration switching **ON A/C 051-099, (Ref. Fig. 002A) **ON A/C 239-249, 251-299, 311-399, (Ref. Fig. 002C)

R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 002D)

R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, In normal configuration, each weather radar transceiver receives the altitude information from its corresponding ADIRU. In case of ADIRU1/2 failure, the pilot can select the altitude information from the ADIRU3. This selection is through the AIR DATA selector switch installed on panel 8VU, on the center pedestal.

  R EFF : 051-099, 239-249, 251-299, 311-399,  34-41-00 Page A49 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

**ON A/C ALL 8. Test ____ R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, A. BITE Description (1) General The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the system. The BITE of the WR/PWS is situated in the radar transceiver and through two ARINC 429 low-speed buses (an input bus from the CFDIU and an output bus to the CFDIU). The BITE: - transmits permanently weather radar system status and its identification message to the CFDIU, - memorizes the failures which occurred during the last 63 flight legs, - monitors data inputs from the various peripherals (EFIS control section, ADIRUs, RAs), - transmits to the CFDIU the result of the tests performed and self-tests, - can communicate with the CFDIU through the MCDU menus. - acquires the general maintenance parameters (UTC, date, A/C ident...) and command codes from the CFDIU. The BITE can operate in two operating modes: - in normal mode, to report continuously the failures of all classes, depending on the maintenance flight phase - in interactive mode, to provide an interactive dialog with an operator using an MCDU. NOTE : The WR/PWS complies with Specification ABD0048, issue C. ____ **ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, A. BITE Description (1) General The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the system. The BITE of the WR/PWS is situated in the radar transceiver and through two ARINC 429 low-speed buses (an input bus from the CFDIU and an output bus to the CFDIU).

  EFF : ALL  34-41-00 Page A50   Config-3 Feb 01/10  CES

 

The BITE: - transmits permanently weather radar system status and its identification message to the CFDIU, - memorizes the failures which occurred during the last 63 flight legs, - monitors data inputs from the various peripherals (EFIS control section, ADIRUs, RAs), - transmits to the CFDIU the result of the tests performed and self-tests, - can communicate with the CFDIU through the MCDU menus. - acquires the general maintenance parameters (UTC, date, A/C ident...) and command codes from the CFDIU. The PWS interface with the CFDIU is composed of: - an ARINC 429 low speed bus from the CFDIU. The data sent by the CFDIU are: --------------------------------------------------------| LABEL | PARAMETER | FORMAT | --------------------------------------------------------| 125 | UTC | BCD | | 155 | AIRCRAFT CONFIGURATION 1 | DISC | | 156 | AIRCRAFT CONFIGURATION 2 | DISC | | 227 | COMMAND | DISC | | 260 | DATE | BCD | | 301 | AIRCRAFT IDENT | ISO | | 302 | AIRCRAFT IDENT | ISO | | 303 | AIRCRAFT IDENT | ISO | --------------------------------------------------------- an ARINC 429 low speed output bus to the CFDIU: The data sent to the CFDIU are: --------------------------------------------------------| LABEL | PARAMETER | FORMAT | --------------------------------------------------------| 354 | LRU IDENTIFICATION | ISO | | 356 | FAULT MESSAGES | ISO | | 377 | EQUIPMENT IDENTIFICATION | BCD | --------------------------------------------------------The BITE can operate in two operating modes: * in normal mode, to report continuously the failures of all classes, depending on the maintenance flight phase, * in interactive mode, to provide an interactive dialog with an operator using an MCDU. NOTE : The WR/PWS complies with Specification ABD0048, issue C. ____

  EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A51 301-399, 401-499,  Config-3 Aug 01/09 R  CES

 

**ON A/C 001-049, 101-105, 151-199, (2) Normal mode During the normal mode the BITE monitors cyclically the status of the WR/PWS. It transmits its information to the CFDIU during the concerned flight. In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU by an ARINC 429 message with label 356. (3) Interactive mode The interactive mode can only be activated on the ground and through the line key adjacent to the RADAR 1 indication, presented on the SYSTEM REPORT/TEST/NAV page of any MCDU. This mode enables communication between the CFDIU and the BITE of the weather radar transceiver by means of the MCDU. (Ref. Fig. 023) The interactive mode is composed of: - LAST LEG REPORT (Ref. Fig. 024) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the last flight leg. The following tables give the list of the failure messages which can be reported and indicate the failure class assigned to them as defined by the CFDIU standard.

  R EFF : 001-049, 101-105, 151-199,  34-41-00 Page A52   Config-3 Aug 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Access to the RADAR page Figure 023   R EFF : ALL  34-41-00 Page A53   Config-3 May 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 1) Figure 024   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page A54 511-526, 528-599,  Config-3 Feb 01/10  CES

 

------------------------------------------------------------| Reported Internal Failures | |-----------------------------------------------------------| | MESSAGE | CLASS | ATA | ------------------------------------------------------------| WXR1 (1SQ1) | 1 | 34-41-33 | | WXR ANTENNA (11SQ) | 1 | 34-41-11 | | WXR CTL PNL (3SQ)/WXR1 (1SQ1) | 1 | 34-41-12 | | WXR MOUNTING TRAY (9SQ) | 1 | 34-41-37 | ------------------------------------------------------------------------------------------------------------------------| Reported External Failures | |-----------------------------------------------------------| | MESSAGE | CLASS | ATA | ------------------------------------------------------------| ADIRU1 (1FP1) BUS ADR/WXR1 (1SQ1) | 3 | 34-12-34 | | ADIRU3 (1FP3) BUS ADR/WXR1 (1SQ1) | 3 | 34-12-34 | | ADIRU1 (1FP1) BUS IR/WXR1 (1SQ1) | 1 | 34-12-34 | | ADIRU3 (1FP3) BUS IR/WXR1 (1SQ1) | 1 | 34-12-34 | | FCU (3CA) BUS CP-L/WXR1 (1SQ1) | 1 | 22-81-12 | | FCU (3CA) BUS CP-R/WXR1 (1SQ1) | 1 | 22-81-12 | | CFDIU (1TW)/WXR1 (1SQ1) | 3 | 31-32-34 | | RA1 (2SA1)/WXR1 (1SQ1) | 3 | 34-42-33 | | RA2 (2SA2)/WXR1 (1SQ1) | 3 | 34-42-33 | | RA1 (2SA1)+RA2 (2SA2)/WXR1 (1SQ1) | 1 | 34-42-33 | | GPWC (1WZ)/WXRi (1SQi) | 1 | 34-48-34 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | ------------------------------------------------------------NOTE : Failure of one radio altimeter is a class 3 failure whereas it ____ becomes a class 1 failure when two radio altimeters are faulty. - PREVIOUS LEGS REPORT (Ref. Fig. 024) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. - LRU IDENTIFICATION (Ref. Fig. 024) Allows to display the P/N, the S/N and the SW/N of the equipment. - GND SCANNING (Ref. Fig. 025) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function.

  R EFF : 001-049, 101-105, 151-199,  34-41-00 Page A55   Config-3 May 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 1) Figure 024A   R EFF : 051-099, 106-149, 201-233, 236-238,  34-41-00 Page A56   Config-3 May 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 1) Figure 024B   R EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page A57 401-499,  Config-3 May 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 2) Figure 025   R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page A58 511-526, 528-599,  Config-3 Feb 01/10  CES

 

-

-

-

-

-

The WR/PWS peripheral monitoring and internal cycle tests are used to detect transient failures. By pressing the line key adjacent to the failure message, the operator is allowed to the corresponding Trouble Shooting Data. The peripheral monitoring and WR/PWS internal cyclic tests are used to detect transient failures. TROUBLE SHOOTING DATA (Ref. Fig. 025) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. CLASS 3 FAULTS (Ref. Fig. 026) Allows to display the class 3 faults recorded during the last flight leg. GROUND REPORT (Ref. Fig. 026) Allows to present the class 1, 2 or 3 internal failures detected on ground. These failures differ from those displayed on the LAST LEG REPORT and CLASS 3 FAULTS. By pressing the line key adjacent to the failure message, the operator is allowed to access to the corresponding Trouble Shooting Data. TEST (Ref. Fig. 027, 028, 029) Allows a check of the correct operation of the WR/PWS on ground. This test can be performed by: either selecting the test function on the LCD of the WR transceiver or through the CFDS by selecting on the MCDU the test function on the RADAR 1 main menu page. At the end of the BITE TEST, the test pattern comes into view. (Ref. Fig. 030)

NOTE : If a failure of the windshear system is detected during the ____ BITE TEST, the windshear flags come into view. If the failure does not affect the radar mode, the test pattern stays available. If the failure affects the radar mode, nothing is shown. All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00).

  R EFF : 001-049, 101-105, 151-199,  34-41-00 Page A59   Config-3 May 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 2) Figure 025A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A60 301-399, 401-499,  Config-3 May 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 3) Figure 026   R EFF : ALL  34-41-00 Page A61   Config-3 May 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 4) Figure 027   R EFF : 001-049, 101-105, 151-199,  34-41-00 Page A62   Config-3 May 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 4) Figure 027A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A63 301-399, 401-499, 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 5) Figure 028   R EFF : 001-049, 101-105, 151-199,  34-41-00 Page A64   Config-3 May 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 5) Figure 028A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A65 301-399, 401-499, 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 6) Figure 029   R EFF : 001-049, 101-105, 151-199,  34-41-00 Page A66   Config-3 May 01/09  CES

 

Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 6) Figure 029A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A67 301-399, 401-499, 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

Weather Radar - Test Pattern Figure 030   EFF : 001-049, 101-105, 151-199,  34-41-00 Page A68   Config-3 May 01/09 R  CES

 

R

**ON A/C 051-099,

R R R R R R R

(2) Normal mode During the normal mode the BITE monitors cyclically the status of the WR/PWS. It transmits its information to the CFDIU during the concerned flight. In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU by an ARINC 429 message with label 356.

R R R R R R R R R R R R R R R R

(3) Interactive mode The interactive mode can only be activated on the ground and through the line key adjacent to the RADAR 1 indication, presented on the SYSTEM REPORT/TEST/NAV page of any MCDU. This mode enables communication between the CFDIU and the BITE of the weather radar transceiver by means of the MCDU. (Ref. Fig. 023) The interactive mode is composed of: - LAST LEG REPORT (Ref. Fig. 024A) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the last flight leg. The following tables give the list of the failure messages which can be reported and indicate the failure class assigned to them as defined by the CFDIU standard.

  R EFF : 051-099,  34-41-00 Page A69   Config-3 May 01/09  CES

 

R R R R R R R R R R

------------------------------------------------------------| Reported Internal Failures | |-----------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | ------------------------------------------------------------| WXRi (1SQi) | 1 | 34-41-33 | | WXR ANTENNA (11SQ) | 1 | 34-41-11 | | WXR CNT PNL (3SQ)/WXRi (1SQi) | 1 | 34-41-12 | | WXR MOUNTING TRAY (9SQ) | 1 | 34-41-37 | -------------------------------------------------------------

R R R R R R R R R R R R R R R R R R R

------------------------------------------------------------| Reported External Failures | |-----------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | ------------------------------------------------------------| ADIRU1 (1FP1) ADR BUS/WXR1 (1SQ1) | 3 | 34-12-34 | | ADIRU2 (1FP2) ADR BUS/WXR2 (1SQ2) | 3 | 34-12-34 | | ADIRU3 (1FP3) ADR BUS/WXRi (1SQi) | 3 | 34-12-34 | | ADIRU1 (1FP1) IR BUS/WXR1 (1SQ1) | 1 | 34-12-34 | | ADIRU2 (1FP2) IR BUS/WXR2 (1SQ2) | 1 | 34-12-34 | | ADIRU3 (1FP3) IR BUS/WXRi (1SQi) | 1 | 34-12-34 | | FCU (3CA) CP-L BUS/WXRi (1SQi) | 1 | 22-81-12 | | FCU (3CA) CP-R BUS/WXRi (1SQi) | 1 | 22-81-12 | | CFDIU (1TW)/WXRi (1SQi) | 3 | 31-32-34 | | RA1 (2SA1)/WXRi (1SQi) | 3 | 34-42-33 | | RA2 (2SA2)/WXRi (1SQi) | 3 | 34-42-33 | | RA1 (2SA1)+RA2 (2SA2)/WXRi (1SQi) | 1 | 34-42-33 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | -------------------------------------------------------------

R R R

NOTE : Failure of one radio altimeter is a class 3 failure whereas it ____ becomes a class 1 failure when two radio altimeters are faulty.

R R R R R R R R R R R R

- PREVIOUS LEGS REPORT (Ref. Fig. 024A) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. - LRU IDENTIFICATION (Ref. Fig. 024A) Allows to display the P/N, the S/N and the SW/N of the equipment. - GND SCANNING (Ref. Fig. 025A) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function.

  R EFF : 051-099,  34-41-00 Page A70   Config-3 May 01/09  CES

 

R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R

-

-

-

-

The WR/PWS peripheral monitoring and internal cycle tests are used to detect transient failures. By pressing the line key adjacent to the failure message, the operator is allowed to the corresponding Trouble Shooting Data. The peripheral monitoring and WR/PWS internal cyclic tests are used to detect transient failures. TROUBLE SHOOTING DATA (Ref. Fig. 025A) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. CLASS 3 FAULTS (Ref. Fig. 026) Allows to display the class 3 faults recorded during the last flight leg. GROUND REPORT (Ref. Fig. 026) Allows to present the class 1, 2 or 3 internal failures detected on ground. These failures differ from those displayed on the LAST LEG REPORT and CLASS 3 FAULTS. By pressing the line key adjacent to the failure message, the operator is allowed to access to the corresponding Trouble Shooting Data. TEST (Ref. Fig. 027A, 028A, 029A) Allows a check of the correct operation of the WR/PWS on ground. This test can be performed through the CFDS by selecting on the MCDU the test function on the RADAR 1 (or 2) main menu page. At the end of the BITE TEST, the test pattern comes into view. (Ref. Fig. 030A)

R R R R R

NOTE : If a failure of the windshear system is detected during the ____ BITE TEST, the windshear flags come into view. If the failure does not affect the radar mode, the test pattern stays available. If the failure affects the radar mode, nothing is shown.

R R R R R

All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00). By pressing the line key adjacent to the internal failure message, the operator is allowed to access to the corresponding Trouble Shooting Data.

  R EFF : 051-099,  34-41-00 Page A71   Config-3 May 01/09  CES

 

Weather Radar - Test Pattern Figure 030A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 Page A72 301-399, 401-499, 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

R

**ON A/C 106-149, 201-233, 236-238,

R R R R R R R

(2) Normal mode During the normal mode the BITE monitors cyclically the status of the WR/PWS. It transmits its information to the CFDIU during the concerned flight. In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU by an ARINC 429 message with label 356.

R R R R R R R R R R R R R R R R

(3) Interactive mode The interactive mode can only be activated on the ground and through the line key adjacent to the RADAR 1 indication, presented on the SYSTEM REPORT/TEST/NAV page of any MCDU. This mode enables communication between the CFDIU and the BITE of the weather radar transceiver by means of the MCDU. (Ref. Fig. 023) The interactive mode is composed of: - LAST LEG REPORT (Ref. Fig. 024A) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the last flight leg. The following tables give the list of the failure messages which can be reported and indicate the failure class assigned to them as defined by the CFDIU standard.

  R EFF : 106-149, 201-233, 236-238,  34-41-00 Page A73   Config-3 May 01/09  CES

 

R R R R R R R R R R

------------------------------------------------------------| Reported Internal Failures | |-----------------------------------------------------------| | MESSAGE | CLASS | ATA | ------------------------------------------------------------| WXR1 (1SQ1) | 1 | 34-41-33 | | WXR ANTENNA (11SQ) | 1 | 34-41-11 | | WXR CNT PNL (3SQ)/WXR1 (1SQ1) | 1 | 34-41-12 | | WXR MOUNTING TRAY (9SQ) | 1 | 34-41-37 | -------------------------------------------------------------

R R R R R R R R R R R R R R R R R

------------------------------------------------------------| Reported External Failures | |-----------------------------------------------------------| | MESSAGE | CLASS | ATA | ------------------------------------------------------------| ADIRU1 (1FP1) ADR BUS/WXR1 (1SQ1) | 3 | 34-12-34 | | ADIRU3 (1FP3) ADR BUS/WXR1 (1SQ1) | 3 | 34-12-34 | | ADIRU1 (1FP1) IR BUS/WXR1 (1SQ1) | 1 | 34-12-34 | | ADIRU3 (1FP3) IR BUS/WXR1 (1SQ1) | 1 | 34-12-34 | | FCU (3CA) CP-L BUS/WXR1 (1SQ1) | 1 | 22-81-12 | | FCU (3CA) CP-R BUS/WXR1 (1SQ1) | 1 | 22-81-12 | | CFDIU (1TW)/WXR1 (1SQ1) | 3 | 31-32-34 | | RA1 (2SA1)/WXR1 (1SQ1) | 3 | 34-42-33 | | RA2 (2SA2)/WXR1 (1SQ1) | 3 | 34-42-33 | | RA1 (2SA1)+RA2 (2SA2)/WXR1 (1SQ1) | 1 | 34-42-33 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | -------------------------------------------------------------

R R R

NOTE : Failure of one radio altimeter is a class 3 failure whereas it ____ becomes a class 1 failure when two radio altimeters are faulty.

R R R R R R R R R R R R R R

- PREVIOUS LEGS REPORT (Ref. Fig. 024A) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. - LRU IDENTIFICATION (Ref. Fig. 024A) Allows to display the P/N, the S/N and the SW/N of the equipment. - GND SCANNING (Ref. Fig. 025A) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. The WR/PWS peripheral monitoring and internal cycle tests are used to detect transient failures.

  R EFF : 106-149, 201-233, 236-238,  34-41-00 Page A74   Config-3 May 01/09  CES

 

R R R R R R R R R R R R R R R R R R R R R R R R R R R R

-

-

-

-

By pressing the line key adjacent to the failure message, the operator is allowed to the corresponding Trouble Shooting Data. The peripheral monitoring and WR/PWS internal cyclic tests are used to detect transient failures. TROUBLE SHOOTING DATA (Ref. Fig. 025A) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. CLASS 3 FAULTS (Ref. Fig. 026) Allows to display the class 3 faults recorded during the last flight leg. GROUND REPORT (Ref. Fig. 026) Allows to present the class 1, 2 or 3 internal failures detected on ground. These failures differ from those displayed on the LAST LEG REPORT and CLASS 3 FAULTS. By pressing the line key adjacent to the failure message, the operator is allowed to access to the corresponding Trouble Shooting Data. TEST (Ref. Fig. 027A, 028A, 029A) Allows a check of the correct operation of the WR/PWS on ground. This test can be performed through the CFDS by selecting on the MCDU the test function on the RADAR 1 main menu page. At the end of the BITE TEST, the test pattern comes into view. (Ref. Fig. 030A)

R R R R R

NOTE : If a failure of the windshear system is detected during the ____ BITE TEST, the windshear flags come into view. If the failure does not affect the radar mode, the test pattern stays available. If the failure affects the radar mode, nothing is shown.

R R R R R

All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00). By pressing the line key adjacent to the internal failure message, the operator is allowed to access to the corresponding Trouble Shooting Data.

  R EFF : 106-149, 201-233, 236-238,  34-41-00 Page A75   Config-3 May 01/09  CES

 

R

**ON A/C 234-235, 239-249, 251-299, 301-399, 401-499,

R R R R R R R

(2) Normal mode During the normal mode the BITE monitors cyclically the status of the WR/PWS. It transmits its information to the CFDIU during the concerned flight. In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU by an ARINC 429 message with label 356.

R R R R R R R R R R R R R R R R

(3) Interactive mode The interactive mode can only be activated on the ground and through the line key adjacent to the RADAR 1 (or 2) indication, presented on the SYSTEM REPORT/TEST/NAV page of any MCDU. This mode enables communication between the CFDIU and the BITE of the weather radar transceiver by means of the MCDU. (Ref. Fig. 023) The interactive mode is composed of: - LAST LEG REPORT (Ref. Fig. 024B) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the last flight leg. The following tables give the list of the failure messages which can be reported and indicate the failure class assigned to them as defined by the CFDIU standard.

  R EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page A76 401-499,  Config-3 May 01/09  CES

 

R R R R R R R R R R

------------------------------------------------------------| Reported Internal Failures | |-----------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | ------------------------------------------------------------| WXRi (1SQi) | 1 | 34-41-33 | | WXR ANTENNA (11SQ) | 1 | 34-41-11 | | WXR CTL PNL (3SQ)/WXRi (1SQi) | 1 | 34-41-12 | | WXR MOUNTING TRAY (9SQ) | 1 | 34-41-37 | -------------------------------------------------------------

R R R R R R R R R R R R R R R R R R R R R R R R R

------------------------------------------------------------| Reported External Failures | |-----------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | ------------------------------------------------------------| ADIRU1 (1FP1) BUS ADR/WXR1 (1SQ1) | 3 | 34-12-34 | | ADIRU2 (1FP2) BUS ADR/WXR2 (1SQ2) | 3 | 34-12-34 | | ADIRU3 (1FP3) BUS ADR/WXRi (1SQi) | 3 | 34-12-34 | | ADIRU1 (1FP1) BUS IR/WXR1 (1SQ1) | 1 | 34-12-34 | | ADIRU2 (1FP2) BUS IR/WXR2 (1SQ2) | 1 | 34-12-34 | | ADIRU3 (1FP3) BUS IR/WXRi (1SQi) | 1 | 34-12-34 | | ADIRU1+3 (1FP1+3)/WXR1 (1SQ1) | 1 | 34-12-34 | | ADIRU2+3 (1FP2+3)/WXR2 (1SQ2) | 1 | 34-12-34 | | QUALIFIER B1/2/WXRi (1SQi) | 1 | 79-33-11 | | QUALIFIER C1/2/WXRi (1SQi) | 1 | 34-12-34 | | QUALIFIER D1/2/WXRi (1SQi) | 1 | 34-12-34 | | FCU (3CA) BUS CP-L/WXRi (1SQi) | 1 | 22-81-12 | | FCU (3CA) BUS CP-R/WXRi (1SQi) | 1 | 22-81-12 | | CFDIU (1TW)/WXRi (1SQi) | 3 | 31-32-34 | | RA1 (2SA1)/WXRi (1SQi) | 3 | 34-42-33 | | RA2 (2SA2)/WXRi (1SQi) | 3 | 34-42-33 | | RA1 (2SA1)+RA2 (2SA2)/WXRi (1SQi) | 1 | 34-42-33 | | GPWC (1WZ)/WXRi (1SQi) | 1 | 34-48-34 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | -------------------------------------------------------------

R R R

NOTE : Failure of one radio altimeter is a class 3 failure whereas it ____ becomes a class 1 failure when two radio altimeters are faulty.

R R R R R R

- PREVIOUS LEGS REPORT (Ref. Fig. 024B) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. - LRU IDENTIFICATION

  R EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page A77 401-499,  Config-3 May 01/09  CES

 

R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R

-

-

-

-

-

-

(Ref. Fig. 024B) Allows to display the P/N, the S/N and the SW/N of the equipment. GND SCANNING (Ref. Fig. 025A) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. The WR/PWS peripheral monitoring and internal cycle tests are used to detect transient failures. By pressing the line key adjacent to the failure message, the operator is allowed to the corresponding Trouble Shooting Data. The peripheral monitoring and WR/PWS internal cyclic tests are used to detect transient failures. TROUBLE SHOOTING DATA (Ref. Fig. 025A) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. CLASS 3 FAULTS (Ref. Fig. 026) Allows to display the class 3 faults recorded during the last flight leg. GROUND REPORT (Ref. Fig. 026) Allows to present the class 1, 2 or 3 internal failures detected on ground. These failures differ from those displayed on the LAST LEG REPORT and CLASS 3 FAULTS. By pressing the line key adjacent to the failure message, the operator is allowed to access to the corresponding Trouble Shooting Data. TEST (Ref. Fig. 027A, 028A, 029A) Allows a check of the correct operation of the WR/PWS on ground. This test can be performed by: either selecting the test function on the LCD of the WR transceiver or through the CFDS by selecting on the MCDU the test function on the RADAR 1 (or 2) main menu page. At the end of the BITE TEST, the test pattern comes into view. (Ref. Fig. 030A)

R R R R R

NOTE : If a failure of the windshear system is detected during the ____ BITE TEST, the windshear flags come into view. If the failure does not affect the radar mode, the test pattern stays available. If the failure affects the radar mode, nothing is shown.

R R

All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00).

  R EFF : 234-235, 239-249, 251-299, 301-399,  34-41-00 Page A78 401-499,  Config-3 May 01/09  CES

 

R

**ON A/C 501-509, 511-526, 528-599, (2) Normal mode During the normal mode the BITE monitors cyclically the status of the WR/PWS. It transmits its information to the CFDIU during the concerned flight. In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU by an ARINC 429 message with label 356. (3) Interactive mode The interactive mode can only be activated on the ground and through the line key adjacent to the RADAR 1 (or 2) indication, presented on the SYSTEM REPORT/TEST/NAV page of any MCDU. This mode enables communication between the CFDIU and the BITE of the weather radar transceiver by means of the MCDU. (Ref. Fig. 023) The interactive mode is composed of: - LAST LEG REPORT (Ref. Fig. 024) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the last flight leg. The following tables give the list of the failure messages which can be reported and indicate the failure class assigned to them as defined by the CFDIU standard.

  R EFF : 501-509, 511-526, 528-599,  34-41-00 Page A79   Config-3 Feb 01/10  CES

 

------------------------------------------------------------| Reported Internal Failures | |-----------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | ------------------------------------------------------------| WXRi (1SQi) | 1 | 34-41-33 | | WXR ANTENNA (11SQ) | 1 | 34-41-11 | | WXR CTL PNL (3SQ)/WXRi (1SQi) | 1 | 34-41-12 | | WXR MOUNTING TRAY (9SQ) | 1 | 34-41-37 | ------------------------------------------------------------------------------------------------------------------------| Reported External Failures | |-----------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | ------------------------------------------------------------| ADIRU1 (1FP1) BUS ADR/WXR1 (1SQ1) | 3 | 34-12-34 | | ADIRU2 (1FP2) BUS ADR/WXR2 (1SQ2) | 3 | 34-12-34 | | ADIRU3 (1FP3) BUS ADR/WXRi (1SQi) | 3 | 34-12-34 | | ADIRU1 (1FP1) BUS IR/WXR1 (1SQ1) | 1 | 34-12-34 | | ADIRU2 (1FP2) BUS IR/WXR2 (1SQ2) | 1 | 34-12-34 | | ADIRU3 (1FP3) BUS IR/WXRi (1SQi) | 1 | 34-12-34 | | FCU (3CA) BUS CP-L/WXRi (1SQi) | 1 | 22-81-12 | | FCU (3CA) BUS CP-R/WXRi (1SQi) | 1 | 22-81-12 | | CFDIU (1TW)/WXRi (1SQi) | 3 | 31-32-34 | | RA1 (2SA1)/WXRi (1SQi) | 3 | 34-42-33 | | RA2 (2SA2)/WXRi (1SQi) | 3 | 34-42-33 | | RA1 (2SA1)+RA2 (2SA2)/WXRi (1SQi) | 1 | 34-42-33 | | GPWC (1WZ)/WXRi (1SQi) | 1 | 34-48-34 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | ------------------------------------------------------------NOTE : Failure of one radio altimeter is a class 3 failure whereas it ____ becomes a class 1 failure when two radio altimeters are faulty. - PREVIOUS LEGS REPORT (Ref. Fig. 024) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. - LRU IDENTIFICATION (Ref. Fig. 024) Allows to display the P/N, the S/N and the SW/N of the equipment. - GND SCANNING (Ref. Fig. 025)

  R EFF : 501-509, 511-526, 528-599,  34-41-00 Page A80   Config-3 Feb 01/10  CES

 

-

-

-

-

-

Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. The WR/PWS peripheral monitoring and internal cycle tests are used to detect transient failures. By pressing the line key adjacent to the failure message, the operator is allowed to the corresponding Trouble Shooting Data. The peripheral monitoring and WR/PWS internal cyclic tests are used to detect transient failures. TROUBLE SHOOTING DATA (Ref. Fig. 025) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. CLASS 3 FAULTS (Ref. Fig. 026) Allows to display the class 3 faults recorded during the last flight leg. GROUND REPORT (Ref. Fig. 026) Allows to present the class 1, 2 or 3 internal failures detected on ground. These failures differ from those displayed on the LAST LEG REPORT and CLASS 3 FAULTS. By pressing the line key adjacent to the failure message, the operator is allowed to access to the corresponding Trouble Shooting Data. TEST (Ref. Fig. 027A, 028A, 029A) Allows a check of the correct operation of the WR/PWS on ground. This test can be performed by: either selecting the test function on the LCD of the WR transceiver or through the CFDS by selecting on the MCDU the test function on the RADAR 1 (or 2) main menu page. At the end of the BITE TEST, the test pattern comes into view. (Ref. Fig. 030A)

NOTE : If a failure of the windshear system is detected during the ____ BITE TEST, the windshear flags come into view. If the failure does not affect the radar mode, the test pattern stays available. If the failure affects the radar mode, nothing is shown. All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00).

  R EFF : 501-509, 511-526, 528-599,  34-41-00 Page A81   Config-3 Feb 01/10  CES

 

R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, B. Self-Test **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 030)

R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 030A)

R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, A quick check of the correct operation of the WR/PWS installation can be performed by activating the test function: - either through the CFDS by applying the Radar functional test procedure on the Multipurpose Control and Display Unit (MCDU) - or by pressing the TEST pushbutton switch located on the face of the transceiver. When a fault is detected, it is stored and made available to the front panel Liquid Crystal Display (LCD) when the TEST pushbutton switch is pressed. The LCD is used as a maintenance aid to check the operational status of the WR/PWS. Once this TEST pushbutton switch is pressed, the LCD shows TEST IN PROGRESS. The self-test takes from 5 to 10 seconds to complete. At the end of the test, the LCD shows RADAR OK, INPUT OK if no faults were detected in either the radar or inputs connections. Pressing the return pushbutton switch enables access to the fault main menu. * If radar faults were found during the self-test, the following messages can be displayed: R/T FAULT ANT FAULT CON FAULT WG SWITCH FAULT INDICATOR FAULT COOLING FAULT * If inputs faults were found during the self-test, the following messages can be displayed:

  R EFF : 001-049, 101-105, 151-199, 501-509,  34-41-00 Page A82 511-526, 528-599,  Config-3 Feb 01/10  CES

 

NO RAD ALT NO ALTITUDE IN NO AIR DATA IN NO HEADING INPUT

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WEATHER RADAR SYSTEM - ADJUSTMENT/TEST ______________________________________ TASK 34-41-00-720-002 Functional test of the Tilt Control of the Weather-Radar Antenna Drive-Unit WARNING : MAKE SURE THAT: _______ -ALL PERSONS ARE MORE THAN 5 METERS (16.4FT) FROM THE ANTENNA. -NO PERSON IS IN THE AREA MADE BY AN ARC OF 135⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE. -THERE IS A MINIMUM SAFETY DISTANCE OF 5 METERS (16.4FT) BETWEEN THE AIRCRAFT AND ANY OBSTACLE IN THE AREA MADE BY AN ARC OF 90⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE. THE AIRCRAFT MUST NOT BE IN A HANGAR OR CLOSED AREA. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R

No specific 98F34403500000

access platform 4.6 m (15 ft. 1 in.) 1 DUMMY-LOAD

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 31-60-00-860-002 34-10-00-860-002 34-10-00-860-005 53-15-11-010-001 53-15-11-410-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure ADIRS Stop Procedure Opening of the Radome 110AL Closing of the Radome 110AL

  EFF : ALL  34-41-00    CES

 

Page 501 Nov 01/07

3. __________ Job Set-up Subtask 34-41-00-010-052 A. Get Access WARNING : DO NOT OPEN THE RADOME IF THE WIND SPEED IS MORE THAN 35 KNOTS. _______ NOTE : Two persons are necessary to open the radome. ____ (1) Put the access platform in position below the radome. (2) Open the radome 110AL (Ref. TASK 53-15-11-010-001). (3) Make sure that the retaining arms of the radome lock correctly. Subtask 34-41-00-480-050 B. In the radome, on the weather radar antenna: (1) Release the quick-disconnect fastener to disconnect the waveguide assembly from the antenna drive unit. (2) Remove the O-ring. R

(3) Install the DUMMY-LOAD (98F34403500000) (the cone in the down direction) on the waveguide assembly. (4) Do not install the O-ring between the waveguide assembly and the dummy load. (5) Make sure that there is no space between the waveguide assembly and the dummy load and that their connection is correct. (6) Remove the two screws that prevent operation of the AZ and EL selector switches on the antenna drive unit. (7) Make sure that the AZ and EL selector switches are at ON and that the antenna is free to move in azimuth and in elevation.

  EFF : ALL  34-41-00    CES

 

Page 502 Nov 01/07

Subtask 34-41-00-865-059 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, Subtask 34-41-00-860-062 D. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (EFIS only) (Ref. TASK 31-60-00-860-001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) On the EFIS control panels of the FCU: - set the mode selector switches to ARC. (5) On the EFIS switching panels 417VU and 418VU: - set the outer ND potentiometer to the middle position. (6) On the center pedestal, on the weather radar control unit, set: - the system switch to OFF - the GAIN potentiometer to AUTO (or CAL) - the TILT selector switch to 0⁰ - the mode selector switch to WX - the windshear mode switch to OFF.

  EFF : ALL  34-41-00    CES

 

Page 503 Feb 01/10

R

**ON A/C 501-509, 511-526, 528-599, Subtask 34-41-00-860-062-A D. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (EFIS only) (Ref. TASK 31-60-00-860-001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) On the EFIS control panels of the FCU: - set the mode selector switches to ARC. (5) On the EFIS switching panels 417VU and 418VU: - set the outer ND potentiometer to the middle position. (6) On the center pedestal, on the weather radar control unit, set: - the system switch to OFF - the GAIN potentiometer to AUTO - the TILT selector switch to 0⁰ - the mode selector switch to WX - the PWS mode switch to OFF - the TILT mode switch to MAN. **ON A/C ALL 4. Procedure _________ Subtask 34-41-00-720-050 A. Functional Test of the Tilt Control of the Antenna Drive Unit NOTE : Two persons are necessary to do the test: ____ - one person must be in the cockpit to set the switches on the weather radar control unit - another person must be near the weather radar antenna to do the check of the tilt value on the indicator of the antenna drive unit.

  EFF : ALL  34-41-00    CES

 

Page 504 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the weather radar control unit: - set the system switch to 1 (or ON).

Make sure that the antenna turns in azimuth.

2. On the antenna drive unit: - set the EL and AZ selector switches to OFF

Make sure that the antenna scanning stops after some seconds. On Capt and F/O NDs: - the red WXR ANT indication comes into view.

3. Turn the antenna manually and carefully along the aircraft centerline. 4. On the antenna drive unit: - set the EL selector switch to ON (the AZ selector switch stays at OFF position). 5. On the weather radar control unit: - gradually turn the TILT selector switch to 5 deg. up (5 UP notch)

On the elevation indicator of the antenna drive unit: - make sure that the antenna turns in elevation 5 deg. up.

6. On the weather radar control unit: - gradually turn the TILT selector switch to 10 deg. up (10 UP notch)

On the elevation indicator of the antenna drive unit: - make sure that the antenna turns in elevation 10 deg. up.

7. On the weather radar control unit: - gradually turn the TILT selector switch to 15 deg. up (15 UP notch)

On the elevation indicator of the antenna drive unit: - make sure that the antenna turns in elevation 15 deg. up.

8. On the weather radar control unit:

On the elevation indicator of the antenna drive unit:

  EFF : ALL  34-41-00   R  CES

 

Page 505 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- gradually turn the TILT - make sure that the antenna turns in selector switch to 5 deg. down elevation 5 deg. down. (5 DN notch) 9. On the weather radar control unit: - gradually turn the TILT selector switch to 10 deg. down (10 DN notch)

On the elevation indicator of the antenna drive unit: - make sure that the antenna turns in elevation 10 deg. down.

10. On the weather radar control unit: - gradually turn the TILT selector switch to 15 deg. down (15 DN notch)

On the elevation indicator of the antenna drive unit: - make sure that the antenna turns in elevation 15 deg. down.

11. On the weather radar control unit: - gradually turn the TILT selector switch to 0 deg.

On the elevation indicator of the antenna drive unit: - make sure that the antenna turns in elevation 0 deg.

12. Turn manually and carefully the antenna to 90 deg. right and do again steps 7 through 13. 13. Turn manually and carefully the antenna to 90 deg. left and do again steps 7 through 13. 14. Turn manually and carefully the antenna along the aircraft centerline (0 deg. in azimuth and in elevation). 15. On the weather radar control unit: - set the system switch to OFF. 16. On the antenna drive unit: - set the AZ selector switch to ON.

  EFF : ALL  34-41-00   R  CES

 

Page 506 Feb 01/08

5. Close-up ________ Subtask 34-41-00-860-063 A. Put the aircraft back to its initial configuration. (1) On the CAPT and F/O EFIS switching panels 417VU and 418VU, set the ND potentiometers to OFF. (2) Do the EIS stop procedure (EFIS only) (Ref. TASK 31-60-00-860-002). (3) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-41-00-080-050 B. In the radome, on the weather radar antenna: (1) Remove the dummy load from the waveguide assembly. (2) Install the O-ring on the waveguide connector on the antenna drive unit. (3) Connect the waveguide assembly to the antenna drive unit and lock the quick-disconnect fastener. (4) Make sure that the AZ and EL selector switches are at ON and that the antenna is free to move in azimuth and in elevation. (5) Tighten the two screws that prevent operation of the AZ and EL selector switches on the antenna drive unit. Subtask 34-41-00-410-052 C. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the access door 811 and the radome 110AL (Ref. TASK 53-15-11410-001). (3) Remove the access platform(s).

  EFF : ALL  34-41-00   R  CES

 

Page 507 Feb 01/08

TASK 34-41-00-740-002 BITE Test of the Weather Radar WARNING : MAKE SURE THAT: _______ -ALL PERSONS ARE MORE THAN 5 METERS (16.4FT) FROM THE ANTENNA. -NO PERSON IS IN THE AREA MADE BY AN ARC OF 135⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE. -THERE IS A MINIMUM SAFETY DISTANCE OF 5 METERS (16.4FT) BETWEEN THE AIRCRAFT AND ANY OBSTACLE IN THE AREA MADE BY AN ARC OF 90⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE. THE AIRCRAFT MUST NOT BE IN A HANGAR OR CLOSED AREA. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure ADIRS Start Procedure ADIRS Stop Procedure

**ON A/C 001-049, 101-105, 151-199, 34-41-00-991-001 R

Fig. 501

**ON A/C 051-099, 201-233, 236-238, 34-41-00-991-001-A

Fig. 501A

  EFF : ALL  34-41-00    CES

 

Page 508 Feb 01/09

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R R

**ON A/C 106-149, 234-235, 239-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-41-00-991-001-B

Fig. 501B

**ON A/C ALL 3. __________ Job Set-up **ON A/C 001-049, 101-105, Subtask 34-41-00-860-053 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002) (4) On the center pedestal, on the radar control unit, set : - the ON/OFF switch to OFF - the GAIN potentiometer to AUTO - the TILT selector switch to 0⁰ - the mode selector switch to WX - the WINDSHEAR AUTO/OFF switch to OFF. (5) On the FCU, on the CAPT and F/O EFIS control sections : - set the mode selector switches to ARC - select the scale selector switch to 10 position. (6) On one MCDU : - get the SYSTEM REPORT/TEST NAV menu page (Ref. TASK 31-32-00-860-010) - push the next page function key.

  EFF : ALL  34-41-00    CES

 

Page 509 Feb 01/10

**ON A/C 051-099, 106-149, 201-233, 236-238, Subtask 34-41-00-860-053-B A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) On the center pedestal, on the radar control unit, set : - the SYS 1/OFF/2 selector switch to OFF - the GAIN potentiometer to CAL - the TILT selector switch to 0 deg. - the mode selector switch to WX - the GND CLTR SPRS switch to OFF - the PWS/OFF/AUTO switch to OFF. (5) On the FCU, on the CAPT and F/O EFIS control sections : - set the mode selector switches to ARC. (6) On one MCDU : - get the SYSTEM REPORT/TEST NAV menu page (Ref. TASK 31-32-00-860-010) - push the next page function key. R

**ON A/C 151-199, 501-509, 511-526, 528-599, Subtask 34-41-00-860-053-D A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

  R EFF : 051-099, 106-149, 151-199, 201-233,  34-41-00 236-238, 501-509, 511-526, 528-599,   CES

 

Page 510 Feb 01/10

(4) On the center pedestal, on the radar control unit, set: - the 1/OFF/2 switch to OFF - the GAIN potentiometer to AUTO - the TILT selector switch to 0 deg. - the mode selector switch to WX - the WINDSHEAR AUTO/OFF switch to OFF. (5) On the FCU, on the CAPT and F/O EFIS control sections: - set the mode selector switches to ARC - select the scale selector switch to 10 position. (6) On one MCDU: - get the SYSTEM REPORT/TEST NAV menu page (Ref. TASK 31-32-00-860-010) - push the next page function key. **ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, Subtask 34-41-00-860-053-F A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) On the center pedestal, on the radar control unit, set : - the SYS 1/OFF/2 selector switch to OFF - the GAIN potentiometer to CAL - the TILT selector switch to 0 deg. - the MODE selector switch to WX - the PWS/OFF/AUTO switch to OFF. (5) On the FCU, on the CAPT and F/O EFIS control sections : - set the mode selector switches to ARC. (6) On one MCDU : - get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010) - push the NEXT PAGE function key.

  R EFF : 151-199, 234-235, 239-249, 251-299,  34-41-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 511 Feb 01/10

**ON A/C ALL Subtask 34-41-00-865-055 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 101-105, Subtask 34-41-00-740-050 A. BITE Test of the Weather Radar ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On one MCDU, on the NAV menu page: - push the line key adjacent to the RADAR 1 indication

- the RADAR 1 page comes into view.

2. On the MCDU: - push the line key adjacent to the TEST indication.

- on the MCDU, the TEST page 1/2 comes into view with these initial conditions: INITIAL CONDITIONS: - SET ADIRU 1+2+3 to NAV - SELECT RELEVANT SYSTEM AND SET W/S TO AUTO ON RADAR CONTROL PANEL

  EFF : ALL  34-41-00    CES

 

Page 512 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------MAKE SURE SEQUENCE OCCURS AFTER PUSHING START TEST LINE KEY: - ON PFDS:W/S AHEAD AMBER 3. On the center pedestal, on the radar control unit: - set the SYS ON/OFF selector switch to ON. - set the WINDSHEAR AUTO/OFF switch to AUTO.

On the NDs: - a tilt indication comes into view on the right side - then, the WR TEST indication comes into view immediately below the tilt indication.

4. On the MCDU: - push the next page function key.

On the MCDU: - the TEST page 2/2 comes into view: - AUDIO:MONITOR RADAR DISPLAY - ON NDS AND ECAM: PWS FAILURE MESSAGES - ON PFDS:W/S AHEAD RED - AUDIO: GO AROUND WINDSHEAR AHEAD ONCE + WINDSHEAR AHEAD TWICE

5. On the MCDU: - push the line key adjacent to the START TEST indication.

On the MCDU: - the TEST IN PROGRESS 25S indication comes into view On the CAPT and F/O PFDs: - the amber W/S AHEAD indication comes into view In the loud speakers, you can hear: - the warning MONITOR RADAR DISPLAY - the single chime On the CAPT and F/O NDs: - the amber PRED W/S indication comes into view and the WR TEST indication goes out of view. - after some seconds, the WR TEST indication comes into view again. On the upper ECAM DU: - the amber NAV : PRED W/S DET FAULT warning is shown On the panels 130VU and 131VU:

  EFF : 001-049, 101-105,  34-41-00   R  CES

 

Page 513 Nov 01/06

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the MASTER CAUT lights come on In the loud these aural - GO AROUND - WINDSHEAR

speakers, you can hear warnings: WINDSHEAR AHEAD one time AHEAD two times.

On the CAPT and F/O PFDs: - the red W/S AHEAD indication comes into view - then, it goes out of view when the above aural warnings stop. on the CAPT and F/O NDs: - make sure that the test pattern is shown from one side to the opposite side. (Ref. Fig. 501/TASK 34-41-00-991-001) On the MCDU: - these instructions are shown: MAKE SURE AUDIO ALERTS SEQUENCE OCCURRED: - PWS CAUTION:MONITOR RADAR DISPLAY - PWS WARNING:GO AROUND WINDSHEAR AHEAD ONCE + WINDSHEAR AHEAD TWICE 6. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - these instructions are shown: MAKE SURE SEQUENCE OF MESSAGES WERE DISPLAYED: - ON PFDS:W/S AHEAD AMBER - ON NDS AND ECAM: PWS FAILURE MESSAGES - ON PFDS:W/S AHEAD RED

7. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU - this instruction is shown: MAKE SURE RADAR TEST PATTERN IS DISPLAYED

8. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - the TEST OK indication is shown.

  R EFF : 001-049, 101-105,  34-41-00    CES

 

Page 514 Nov 01/06

Weather Radar Test Figure 501/TASK 34-41-00-991-001   R EFF : 001-049, 101-105, 151-199,  34-41-00    CES

 

Page 515 Nov 01/06

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------9. On the MCDU: On the MCDU: - push the line key adjacent to - the TEST CLOSE-UP page is shown: the RETURN indication. SET ADIRU 1+2+3 TO OFF - SET SYSTEM OFF AND SET W/S TO OFF ON THE RADAR CONTROL PANEL 10. On the center pedestal, on the radar control unit: - set the WINDSHEAR AUTO/OFF switch to OFF. - set the SYS ON/OFF selector switch to OFF. R

On the CAPT and F/O NDs: - the WR TEST and the tilt indications go out of view after some seconds.

**ON A/C 051-099, 234-235, 239-249, 251-299, 305-399, 401-499, Subtask 34-41-00-740-050-C A. BITE Test of the Weather Radar ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On one MCDU, on the NAV menu page: - push the line key adjacent to the RADAR 1 (RADAR 2) indication

- the RADAR 1 (RADAR 2) page comes into view.

2. On the MCDU: - push the line key adjacent to the TEST indication.

On the MCDU: - these instructions come into view: SYSTEM OFF CHANGE CONTROL PANEL SYSTEM SWITCH TO ON AFTER TEST SWITCH SYSTEM TO OFF

3. On the center pedestal, on the radar control unit: - set the SYS 1/OFF/2 selector

On the MCDU: - the PLEASE WAIT indication comes into view for some seconds

  R EFF : 001-049, 051-099, 101-105, 234-235,  34-41-00 239-249, 251-299, 305-399, 401-499,   CES

 

Page 516 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------switch to 1 (2). - then, the TEST page 1/2 comes into - set the PWS AUTO/OFF switch to view with these initial conditions: AUTO. INITIAL CONDITIONS: - SET ADIRU 1+2+3 to NAV - SELECT RELEVANT SYSTEM AND SET PWS TO AUTO ON RADAR CONTROL PANEL MAKE SURE SEQUENCE OCCURS AFTER PUSHING START TEST LINE KEY: - ON PFDS:W/S AHEAD AMBER on the CAPT and F/O NDs: - a tilt indication comes into view on the right side - a WR TEST indication comes into view immediately below the tilt indication. 4. On the MCDU: - push the next page function key.

On the MCDU: - the TEST page 2/2 comes into view: - AUDIO:MONITOR RADAR DISPLAY - ON NDS AND ECAM: PWS FAILURE MESSAGES - ON PFDS:W/S AHEAD RED - AUDIO: GO AROUND WINDSHEAR AHEAD ONCE + WINDSHEAR AHEAD TWICE

5. On the MCDU: - push the line key adjacent to the START TEST indication.

On the MCDU: - the TEST IN PROGRESS 15S indication comes into view On the CAPT and F/O PFDs: - the amber W/S AHEAD indication comes into view In the loud speakers, you can hear: - the warning MONITOR RADAR DISPLAY - the single chime on the CAPT and F/O NDs: - the amber PRED W/S indication comes into view and the WR TEST indication goes out of view. - after some seconds, the WR TEST indication comes into view again.

  R EFF : 051-099, 234-235, 239-249, 251-299,  34-41-00 305-399, 401-499,   CES

 

Page 517 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the upper ECAM DU: - the amber NAV : PRED W/S DET FAULT warning is shown. On the panels 130VU and 131VU: - the MASTER CAUT lights come on In the loud these aural - GO AROUND - WINDSHEAR

speakers, you can hear warnings: WINDSHEAR AHEAD one time AHEAD two times.

On the CAPT and F/O PFDs: - the red W/S AHEAD indication comes into view - then, it goes out of view when the above aural warnings stop. on the CAPT and F/O NDs: - make sure that the test pattern is shown from one side to the opposite side. **ON A/C 051-099, (Ref. Fig. 501A/TASK 34-41-00-991001-A) R

**ON A/C 234-235, 239-249, 251-299, 305-399, 401-499, (Ref. Fig. 501B/TASK 34-41-00-991001-B)

R

**ON A/C 051-099, 234-235, 239-249, 251-299, 305-399, 401-499, On the MCDU: - these instructions are shown: MAKE SURE AUDIO ALERTS SEQUENCE OCCURRED: - PWS CAUTION:MONITOR RADAR DISPLAY

  R EFF : 051-099, 234-235, 239-249, 251-299,  34-41-00 305-399, 401-499,   CES

 

Page 518 May 01/09

Weather Radar Test Figure 501A/TASK 34-41-00-991-001-A   R EFF : 051-099, 201-233, 236-238,  34-41-00    CES

 

Page 519 Feb 01/09

Weather Radar Test Figure 501B/TASK 34-41-00-991-001-B   R EFF : 106-149, 234-235, 239-249, 251-299,  34-41-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 520 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- PWS WARNING:GO AROUND WINDSHEAR AHEAD ONCE + WINDSHEAR AHEAD TWICE 6. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - these instructions are shown: MAKE SURE SEQUENCE OF MESSAGES WERE DISPLAYED: - ON PFDS:W/S AHEAD AMBER - ON NDS AND ECAM: PWS FAILURE MESSAGES - ON PFDS:W/S AHEAD RED

7. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU - this instruction is shown: MAKE SURE RADAR TEST PATTERN IS DISPLAYED

8. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - the TEST OK indication is shown.

9. On the MCDU: - push the line key adjacent to the RETURN indication.

On the MCDU: - the TEST CLOSE-UP page is shown: SET ADIRU 1+2+3 TO OFF - SET SYSTEM OFF AND SET PWS TO OFF ON RADAR CONTROL PANEL

10. On the MCDU: - push the line key adjacent to the RETURN indication.

On the MCDU: - the RADAR 1 (RADAR 2) page comes into view.

11. On the center pedestal, on the radar control unit: - set the PWS AUTO/OFF switch to OFF. - set the SYS 1/OFF/2 selector switch to OFF.

On the CAPT and F/O NDs: - the WR TEST and the tilt indications go out of view after some seconds.

  R EFF : 051-099, 234-235, 239-249, 251-299,  34-41-00 305-399, 401-499,   CES

 

Page 521 May 01/09

R

**ON A/C 106-149, 201-233, 236-238, 301-304, Subtask 34-41-00-740-050-A A. BITE Test of the Weather Radar ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On one MCDU, on the NAV menu page: - push the line key adjacent to the RADAR 1 indication

On the MCDU: - the RADAR 1 page comes into view.

2. On the MCDU: - push the line key adjacent to the TEST indication.

3. On the center pedestal, on the radar control unit: - set the ON/OFF selector switch to ON. - set the PWS AUTO/OFF switch to AUTO.

On the MCDU: - these instructions come into view: SYSTEM OFF CHANGE CONTROL PANEL SYSTEM SWITCH TO ON AFTER TEST SWITCH SYSTEM TO OFF On the MCDU: - the PLEASE WAIT indication comes into view for some seconds - then, the TEST page 1/2 comes into view with these initial conditions: INITIAL CONDITIONS: - SET ADIRU 1+2+3 to NAV - SELECT RELEVANT SYSTEM AND SET PWS TO AUTO ON RADAR CONTROL PANEL MAKE SURE SEQUENCE OCCURS AFTER PUSHING START TEST LINE KEY: - ON PFDS:W/S AHEAD AMBER On the CAPT and F/O NDs: - a tilt indication comes into view on the right side - a WR TEST indication comes into view immediately below the tilt indication.

4. On the MCDU:

On the MCDU:

  R EFF : 106-149, 201-233, 236-238, 301-304,  34-41-00    CES

 

Page 522 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the next page function - the TEST page 2/2 comes into view: key. - AUDIO:MONITOR RADAR DISPLAY - ON NDS AND ECAM: PWS FAILURE MESSAGES - ON PFDS:W/S AHEAD RED - AUDIO: GO AROUND WINDSHEAR AHEAD ONCE + WINDSHEAR AHEAD TWICE 5. On the MCDU: - push the line key adjacent to the START TEST indication.

On the MCDU: - the TEST IN PROGRESS 15S indication comes into view On the CAPT and F/O PFDs: - the amber W/S AHEAD indication comes into view In the loud speakers, you can hear: - the warning MONITOR RADAR DISPLAY - the single chime On the CAPT and F/O NDs: - the amber PRED W/S indication comes into view and the WR TEST indication goes out of view. - after some seconds, the WR TEST indication comes into view again. On the upper ECAM DU: - the amber NAV : PRED W/S DET FAULT warning is shown On the panels 130VU and 131VU: - the MASTER CAUT lights come on In the loud these aural - GO AROUND - WINDSHEAR

speakers, you can hear warnings: WINDSHEAR AHEAD one time AHEAD two times

On the CAPT and F/O PFDs: - the red W/S AHEAD indication comes into view - then, it goes out of view when the above aural warnings stop.

  R EFF : 106-149, 201-233, 236-238, 301-304,  34-41-00    CES

 

Page 523 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------on the CAPT and F/O NDs: - make sure that the test pattern is shown from one side to the opposite side. R

**ON A/C 201-233, 236-238, (Ref. Fig. 501A/TASK 34-41-00-991001-A) **ON A/C 106-149, 301-304,

R (Ref. Fig. 501B/TASK 34-41-00-991001-B) **ON A/C 106-149, 201-233, 236-238, 301-304, On the MCDU: - these instructions are shown: MAKE SURE AUDIO ALERTS SEQUENCE OCCURRED: - PWS CAUTION:MONITOR RADAR DISPLAY - PWS WARNING:GO AROUND WINDSHEAR AHEAD ONCE + WINDSHEAR AHEAD TWICE 6. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - these instructions are shown: MAKE SURE SEQUENCE OF MESSAGES WERE DISPLAYED: - ON PFDS:W/S AHEAD AMBER - ON NDS AND ECAM: PWS FAILURE MESSAGES - ON PFDS:W/S AHEAD RED

7. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU - this instruction is shown: MAKE SURE RADAR TEST PATTERN IS DISPLAYED

8. On the MCDU:

On the MCDU:

  EFF : 106-149, 201-233, 236-238, 301-304,  34-41-00    CES

 

Page 524 Feb 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the TEST OK indication is shown. the YES indication. 9. On the MCDU: - push the line key adjacent to the RETURN indication.

On the MCDU: - the TEST CLOSE-UP page is shown: SET ADIRU 1+2+3 TO OFF - SET SYSTEM OFF AND SET PWS TO OFF ON THE RADAR CONTROL PANEL

10. On the MCDU: - push the line key adjacent to the RETURN indication.

On the MCDU: - the RADAR 1 page comes into view.

11. On the center pedestal, on the radar control unit: - set the PWS AUTO/OFF switch to OFF. - set the ON/OFF selector switch to OFF.

On the CAPT and F/O NDs: - the WR TEST and the tilt indications go out of view after some seconds.

**ON A/C 151-199, Subtask 34-41-00-740-050-B A. BITE Test of the Weather Radar ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On one MCDU, on the NAV menu page: - push the line key adjacent to the RADAR 1 indication.

On the MCDU: - the RADAR 1 page comes into view.

2. On the MCDU: - push the line key adjacent to the TEST indication.

On the MCDU: - the TEST page 1/2 comes into view and these initial conditions are shown: INITIAL CONDITIONS: - SET ADIRU 1+2+3 to NAV - SELECT RELEVANT SYSTEM AND SET W/S TO AUTO ON RADAR CONTROL PANEL

  R EFF : 106-149, 151-199, 201-233, 236-238,  34-41-00 301-304,   CES

 

Page 525 Feb 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------MAKE SURE SEQUENCE OCCURS AFTER PUSHING START TEST LINE KEY: - ON PFDS:W/S AHEAD AMBER 3. On the center pedestal, on the radar control unit: - set the 1/OFF/2 selector switch to 1. - set the WINDSHEAR AUTO/OFF switch to AUTO.

On the CAPT and F/O NDs: - a tilt indication comes into view on the right side - a WR TEST indication comes into view immediately below the tilt indication.

4. On the MCDU: - push the next page function key.

On the MCDU: - the TEST page 2/2 comes into view: - AUDIO:MONITOR RADAR DISPLAY - ON NDS AND ECAM: PWS FAILURE MESSAGES - ON PFDS:W/S AHEAD RED - AUDIO: GO AROUND WINDSHEAR AHEAD ONCE + WINDSHEAR AHEAD TWICE

5. On the MCDU: - push the line key adjacent to the START TEST indication

On the MCDU: - the TEST IN PROGRESS 25S indication comes into view On the CAPT and F/O PFDs: - the amber W/S AHEAD indication comes into view In the loudspeaker, you can hear: - the MONITOR RADAR DISPLAY warning - the single chime On the CAPT and F/O NDs: - the amber PRED W/S indication comes into view and the WR TEST indication goes out of view. - then, the WR TEST indication comes into view again. On the upper ECAM DU: - the amber NAV : PRED W/S DET FAULT warning is shown.

  EFF : 151-199,  34-41-00   R  CES

 

Page 526 Nov 01/06

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On F/O and CAPT glareshield panels 130VU and 131VU: - the MASTER CAUT lights come on In the loudspeaker, you can hear these aural warnings: - GO AROUND WINDSHEAR AHEAD one time - WINDSHEAR AHEAD two times On the CAPT and F/O PFDs: - the red W/S AHEAD indication comes into view - then, it goes out of view when the aural warnings from the loudspeakers stop. On the CAPT and F/O NDs: - make sure that the test pattern is shown from one side to the opposite side. (Ref. Fig. 501/TASK 34-41-00-991-001) On the MCDU: - these instructions are shown: MAKE SURE AUDIO ALERTS SEQUENCE OCCURRED: - PWS CAUTION:MONITOR RADAR DISPLAY - PWS WARNING:GO AROUND WINDSHEAR AHEAD ONCE + WINDSHEAR AHEAD TWICE 6. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - these instructions are shown: MAKE SURE SEQUENCE OF MESSAGE WERE DISPLAYED: - ON PFDS:W/S AHEAD AMBER - ON NDS AND ECAM: PWS FAILURE MESSAGES - ON PFDS:W/S AHEAD RED

7. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - this instruction is shown: MAKE SURE RADAR TEST PATTERN IS DISPLAYED

8. On the MCDU:

On the MCDU:

  EFF : 151-199,  34-41-00   R  CES

 

Page 527 Nov 01/06

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the TEST OK indication is shown. the YES indication. 9. On the MCDU: - push the line key adjacent to the RETURN indication.

On the MCDU: - the TEST CLOSE-UP page is shown: SET ADIRU 1+2+3 TO OFF - SET SYSTEM OFF AND SET W/S TO OFF ON RADAR CONTROL PANEL

10. On the center pedestal, on the radar control unit: - set the WINDSHEAR AUTO/OFF switch to OFF - set the 1/OFF/2 selector switch to OFF. R

On the CAPT and F/O NDs: - the WR TEST and the tilt indications go out of view after some seconds.

**ON A/C 501-509, 511-526, 528-599, Subtask 34-41-00-740-050-D A. BITE Test of the Weather Radar ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On one MCDU, on the NAV menu page: - push the line key adjacent to the RADAR 1 indication.

On the MCDU: - the RADAR 1 page comes into view.

2. On the MCDU: - push the line key adjacent to the TEST indication.

On the MCDU: - the TEST page 1/2 comes into view and these initial conditions are shown: INITIAL CONDITIONS: - SET ADIRU 1+2+3 to NAV - SELECT RELEVANT SYSTEM AND SET W/S TO AUTO ON RADAR CONTROL PANEL MAKE SURE SEQUENCE OCCURS AFTER PUSHING START TEST LINE KEY: - ON PFDS:W/S AHEAD AMBER

  R EFF : 151-199, 501-509, 511-526, 528-599,  34-41-00    CES

 

Page 528 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------3. On the center pedestal, on the On the CAPT and F/O NDs: radar control unit: - a tilt indication comes into view on - set the 1/OFF/2 selector switch the right side to 1 - a WR TEST indication comes into view - set the PWS AUTO/OFF switch to immediately below the tilt AUTO indication. - set the TILT MAN/AUTO switch to MAN. 4. On the MCDU: - push the next page function key.

On the MCDU: - the TEST page 2/2 comes into view: - AUDIO:MONITOR RADAR DISPLAY - ON NDS AND ECAM: PWS FAILURE MESSAGES - ON PFDS:W/S AHEAD RED - AUDIO: GO AROUND WINDSHEAR AHEAD ONCE + WINDSHEAR AHEAD TWICE

5. On the MCDU: - push the line key adjacent to the START TEST indication

On the MCDU: - the TEST IN PROGRESS 25S indication comes into view On the CAPT and F/O PFDs: - the amber W/S AHEAD indication comes into view In the loudspeaker, you can hear: - the MONITOR RADAR DISPLAY warning - the single chime On the CAPT and F/O NDs: - the amber PRED W/S indication comes into view and the WR TEST indication goes out of view. - then, the WR TEST indication comes into view again. On the upper ECAM DU: - the amber NAV : PRED W/S DET FAULT warning is shown. On F/O and CAPT glareshield panels 130VU and 131VU: - the MASTER CAUT lights come on

  R EFF : 501-509, 511-526, 528-599,  34-41-00    CES

 

Page 529 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------In the loudspeaker, you can hear these aural warnings: - GO AROUND WINDSHEAR AHEAD one time - WINDSHEAR AHEAD two times On the CAPT and F/O PFDs: - the red W/S AHEAD indication comes into view - then, it goes out of view when the aural warnings from the loudspeakers stop. On the CAPT and F/O NDs: - make sure that the test pattern is shown from one side to the opposite side. (Ref. Fig. 501B/TASK 34-41-00-991001-B) On the MCDU: - these instructions are shown: MAKE SURE AUDIO ALERTS SEQUENCE OCCURRED: - PWS CAUTION:MONITOR RADAR DISPLAY - PWS WARNING:GO AROUND WINDSHEAR AHEAD ONCE + WINDSHEAR AHEAD TWICE 6. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - these instructions are shown: MAKE SURE SEQUENCE OF MESSAGE WERE DISPLAYED: - ON PFDS:W/S AHEAD AMBER - ON NDS AND ECAM: PWS FAILURE MESSAGES - ON PFDS:W/S AHEAD RED

7. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - this instruction is shown: MAKE SURE RADAR TEST PATTERN IS DISPLAYED

8. On the MCDU: - push the line key adjacent to the YES indication.

On the MCDU: - the TEST OK indication is shown.

  R EFF : 501-509, 511-526, 528-599,  34-41-00    CES

 

Page 530 Feb 01/10

R R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------9. On the MCDU: On the MCDU: - push the line key adjacent to - the TEST CLOSE-UP page is shown: the RETURN indication. SET ADIRU 1+2+3 TO OFF

R R R R R R R R

- SET SYSTEM OFF AND SET W/S TO OFF ON RADAR CONTROL PANEL 10. On the center pedestal, on the radar control unit: - set the PWS AUTO/OFF switch to OFF - set the 1/OFF/2 selector switch to OFF.

On the CAPT and F/O NDs: - the WR TEST and the tilt indications go out of view after some seconds.

**ON A/C ALL 5. Close-up ________ Subtask 34-41-00-860-054 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) On the panels 301VU and 500VU, set the PFD and ND potentiometers to OFF. (3) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005) (4) Make sure that the work area is clean and clear of tool(s) and other items. (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002)

  EFF : ALL  34-41-00    CES

 

Page 531 Feb 01/08

TASK 34-41-00-730-001 System Test of the Weather Radar WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. WARNING : STOP THE FUEL TANKER 60 m (196.85 ft) FROM THE AIRCRAFT NOSE WHILE _______ THE WEATHER RADAR OPERATES. DO NOT OPERATE THE FUEL TANKER/PUMP UNIT UNTIL YOU STOP THE OPERATION OF THE WEATHER RADAR. WARNING : MAKE SURE THAT: _______ -ALL PERSONS ARE MORE THAN 5 METERS (16.4FT) FROM THE ANTENNA. -NO PERSON IS IN THE AREA MADE BY AN ARC OF 135⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE. -THERE IS A MINIMUM SAFETY DISTANCE OF 5 METERS (16.4FT) BETWEEN THE AIRCRAFT AND ANY OBSTACLE IN THE AREA MADE BY AN ARC OF 90⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE. THE AIRCRAFT MUST NOT BE IN A HANGAR OR CLOSED AREA. 1. __________________ Reason for the Job - antenna stabilization test by the ADIRU 3 - antenna control test 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

circuit breaker(s) safety clip(s) warning notice access platform 3.5 m (11 ft. 6 in.)

  EFF : ALL  34-41-00   R  CES

 

Page 532 Feb 01/08

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 53-15-11-010-001 53-15-11-410-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure Opening of the Radome 110AL Closing of the Radome 110AL

3. __________ Job Set-up Subtask 34-41-00-865-053 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL Subtask 34-41-00-010-050 B. Get Access WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER _______ RADAR ARE OPENED, SAFETIED AND TAGGED. (1) In the cockpit, put a warning notice on the center pedestal to tell persons not to operate the weather radar. (2) Put the access platform in position in zone 110 below the radome.

  EFF : ALL  34-41-00    CES

 

Page 533 Feb 01/10

(3) Open the radome 110AL (Ref. TASK 53-15-11-010-001). NOTE : Two persons are necessary to open the radome. ____ (4) Make sure that the retaining arms of the radome lock correctly. **ON A/C 001-049, 101-105, 151-199, Subtask 34-41-00-860-050-C C. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (EFIS only) (Ref. TASK 31-60-00-860-001). (3) On the ADIRS CDU, set the OFF/NAV/ATT selector switch of the ADIRU1 and ADIRU3 to NAV to get the ND display. (4) On the panel 8VU, make sure that the ATT HDG selector switch is at NORM. (5) On the FCU, on the CAPT and F/O EFIS control sections : - set the mode selector switches to ROSE NAV or ARC. (6) On the radar control unit, set : - the ON/OFF switch to OFF - the GAIN potentiometer to AUTO - the TILT selector switch to 0⁰ - the mode selector switch to WX. - the WINDSHEAR AUTO/OFF switch to OFF. R

**ON A/C 051-099, 106-149, 201-233, 236-238, Subtask 34-41-00-860-050-D C. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (EFIS only) (Ref. TASK 31-60-00-860-001).

  EFF : ALL  34-41-00    CES

 

Page 534 Feb 01/09

(3) On the ADIRS CDU, set the OFF/NAV/ATT selector switch of the ADIRU1 and ADIRU3 to NAV to get the ND display. (4) On the panel 8VU, make sure that the ATT HDG selector switch is at NORM. (5) On the FCU, on the CAPT and F/O EFIS control sections : - set the mode selector switches to ROSE NAV or ARC. (6) On the center pedestal, on the radar control unit, set : - the SYS 1/OFF/2 selector switch to OFF - the GAIN potentiometer to CAL - the TILT selector switch to 0⁰ - the mode selector switch to WX - the GNR CLTR SPRS switch to OFF. - the PWS AUTO/OFF switch to OFF. R

**ON A/C 234-235, 239-249, 251-299, 301-399, 401-499, Subtask 34-41-00-860-050-F C. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (EFIS only) (Ref. TASK 31-60-00-860-001). (3) On the ADIRS CDU, set the OFF/NAV/ATT selector switch of the ADIRU1 and ADIRU3 to NAV to get the ND display. (4) On the panel 8VU, make sure that the ATT HDG selector switch is at NORM. (5) On the FCU, on the CAPT and F/O EFIS control sections : - set the mode selector switches to ROSE NAV or ARC. (6) On the radar control unit, set : - the SYS 1/OFF/2 selector switch to OFF - the GAIN potentiometer to CAL - the TILT selector switch to 0⁰ - the PWS AUTO/OFF switch to OFF.

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-00 301-399, 401-499,   CES

 

Page 535 May 01/09

R

**ON A/C 501-509, 511-526, 528-599, Subtask 34-41-00-860-050-G C. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the EIS start procedure (EFIS only) (Ref. TASK 31-60-00-860-001). (3) On the ADIRS CDU, set the OFF/NAV/ATT selector switch of the ADIRU1 and ADIRU3 to NAV to get the ND display. (4) On the panel 8VU, make sure that the ATT HDG selector switch is at NORM. (5) On the FCU, on the CAPT and F/O EFIS control sections : - set the mode selector switches to ROSE NAV or ARC. (6) On the radar control unit, set : - the 1/OFF/2 switch to OFF - the GAIN potentiometer to AUTO - the TILT selector switch to 0⁰ - the mode selector switch to WX - the PWS AUTO/OFF switch to OFF - the TILT MAN/AUTO switch to MAN. **ON A/C ALL Subtask 34-41-00-865-054 D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13

R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

  EFF : ALL  34-41-00    CES

 

K14

Page 536 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 101-105, 151-199, Subtask 34-41-00-730-050 A. Antenna Stabilization Test by the ADIRU 3 ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center pedestal, on the radar control unit : - set the ON/OFF selector switch to ON.

The CAPT and F/O NDs show the radar display.

2. On the panel 8VU : - set the ATT HDG selector switch to CAPT 3.

On the CAPT and F/O NDs, the radar display stays in view.

3. On the ADIRS CDU : - set the OFF/NAV/ATT selector switch of the ADIRU 1 to OFF.

On the CAPT and F/O NDs, the radar display stays in view.

4. On the ADIRS CDU : - set the OFF/NAV/ATT selector switch of the ADIRU 3 to OFF.

On the CAPT and F/O NDs : - after some seconds, the WR ATT warning indication is shown on the right. - the radar display stays in view.

5. On the center pedestal, on the radar control unit : - set the ON/OFF selector switch to OFF.

On the CAPT and F/O NDs : - after some seconds, the radar display and the WR ATT warning indication go out of view.

  R EFF : ALL  34-41-00    CES

 

Page 537 May 01/08

R

**ON A/C 051-099, 239-249, 251-299, 311-399, Subtask 34-41-00-730-050-D A. Antenna Stabilization Test by the ADIRU 3 ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center pedestal, on the radar control unit : - set the SYS 1/OFF/SYS 2 selector switch to 1 (2).

The CAPT and F/O NDs show the radar display.

2. On the panel 8VU : - set the ATT HDG selector switch to CAPT 3.

On the CAPT and F/O NDs, the radar display stays in view.

3. On the ADIRS CDU : - set the OFF/NAV/ATT selector switch of the ADIRU 1 to OFF.

On the CAPT and F/O NDs, the radar display stays in view.

4. On the ADIRS CDU : - set the OFF/NAV/ATT selector switch of the ADIRU 3 to OFF.

On the CAPT and F/O NDs : - after some seconds, the WR ATT warning indication is shown on the right. - the radar display stays in view.

5. On the center pedestal, on the radar control unit : - set the SYS 1/OFF/SYS 2 selector switch to OFF.

On the CAPT and F/O NDs : - after some seconds, the radar display and the WR ATT warning indication go out of view.

  R EFF : 051-099, 239-249, 251-299, 311-399,  34-41-00    CES

 

Page 538 Nov 01/09

R

**ON A/C 106-149, 201-238, 301-310, 401-499, 501-509, 511-526, 528-599, Subtask 34-41-00-730-050-C A. Antenna Stabilization Test by the ADIRU 3 ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center pedestal, on the radar control unit: - set the 1/OFF/2 system selector switch to 1 (2).

The CAPT and F/O NDs show the radar display.

2. On the panel 8VU: - set the ATT HDG selector switch to CAPT 3.

On the CAPT and F/O NDs, the radar display stays in view.

3. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch of the ADIRU 1 to OFF.

On the CAPT and F/O NDs, the radar display stays in view.

4. On the ADIRS CDU: - set the OFF/NAV/ATT selector switch of the ADIRU 3 to OFF.

On the CAPT and F/O NDs: - after some seconds, the WR ATT warning indication is shown on the right. - the radar display stays in view.

5. On the center pedestal, on the radar control unit: - set the 1/OFF/2 system selector switch to OFF.

On the CAPT and F/O NDs: - after some seconds, the radar display and the WR ATT warning indication go out of view.

  R EFF : 106-149, 201-238, 301-310, 401-499,  34-41-00 501-509, 511-526, 528-599,   CES

 

Page 539 Feb 01/10

R

**ON A/C 001-049, 101-149, 201-238, 301-310, 401-499, Subtask 34-41-00-730-051 B. Antenna Control Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On one MCDU : - get the SYSTEM REPORT/TEST NAV menu page (Ref. TASK 31-32-00-860-010) - push the line key adjacent to the RADAR 1 indication. - push the line key adjacent to the TEST indication.

During the test sequence, make sure that the antenna : - turns in elevation (+ 15⁰, - 15⁰) - turns in azimuth from the right side to the left side, then becomes stable at 0⁰, vertical to the aircraft centerline. At the end of the test, on the MCDU, the TEST OK indication comes into view. On the CAPT and F/O NDs, ignore the radar indications.

- push the line key adjacent to the RETURN indication.

On the MCDU : - the MCDU MENU page comes into view.

  R EFF : 001-049, 101-149, 201-238, 301-310,  34-41-00 401-499,   CES

 

Page 540 Nov 01/09

R

**ON A/C 051-099, 239-249, 251-299, 311-399, Subtask 34-41-00-730-051-B B. Antenna Control Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On one MCDU : - get the SYSTEM REPORT/TEST NAV menu page (Ref. TASK 31-32-00-860-010) - push the line key adjacent to the RADAR 1 (RADAR 2) indication. - push the line key adjacent to the TEST indication.

During the test sequence, make sure that the antenna : - turns in elevation (+ 15⁰, - 15⁰) - turns in azimuth from the right side to the left side, then becomes stable at 0⁰, vertical to the aircraft centerline. At the end of the test, on the MCDU, the TEST OK indication comes into view. On the CAPT and F/O NDs, ignore the radar indications

- push the line key adjacent to the RETURN indication.

The antenna stops On the MCDU : - the MCDU MENU page comes into view.

  R EFF : 051-099, 239-249, 251-299, 311-399,  34-41-00    CES

 

Page 541 Nov 01/09

**ON A/C 151-199, Subtask 34-41-00-730-051-A B. Antenna Control Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On one MCDU : - get the SYSTEM REPORT/TEST NAV menu page (Ref. TASK 31-32-00860-010). - push the line key adjacent to the RADAR 1 indication. - push the line key adjacent to the TEST indication.

During the test sequence, make sure that the antenna : - turns in elevation (+10⁰, -10⁰) - turns in azimuth (+15⁰, -15⁰) then scans continuously -90⁰, +90⁰ to the end of the test. At the end of the test, on the MCDU, the TEST OK indication comes into view. On the CAPT and F/O NDs, ignore the radar indications.

- push the line key adjacent to the RETURN indication.

The antenna stops On the MCDU : - the MCDU MENU page comes into view.

  R EFF : 151-199,  34-41-00    CES

 

Page 542 May 01/08

R

**ON A/C 501-509, 511-526, 528-599, Subtask 34-41-00-730-051-C B. Antenna Control Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On one MCDU : - get the SYSTEM REPORT/TEST NAV menu page (Ref. TASK 31-32-00860-010). - push the line key adjacent to the RADAR 1 (RADAR 2) indication. - push the line key adjacent to the TEST indication.

During the test sequence, make sure that the antenna : - turns in elevation (+10⁰, -10⁰) - turns in azimuth (+15⁰, -15⁰) then scans continuously -90⁰, +90⁰ to the end of the test. At the end of the test, on the MCDU, the TEST OK indication comes into view. On the CAPT and F/O NDs, ignore the radar indications.

- push the line key adjacent to the RETURN indication.

The antenna stops. On the MCDU : - the MCDU MENU page comes into view.

**ON A/C ALL 5. Close-up ________ Subtask 34-41-00-860-051 A. Put the aircraft back to its initial configuration. (1) On the panels 301VU and 500VU, set the PFD and ND potentiometers to OFF. (2) On the panel 8VU, set the ATT HDG selector switch to NORM. (3) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-41-00    CES

 

Page 543 Feb 01/10

(4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-41-00-410-050 B. Close Access (1) Close the radome 110AL (Ref. TASK 53-15-11-410-001). NOTE : Make sure that the radome locks correctly. ____ (2) Remove the access platform(s). (3) Remove the warning notice(s).

  EFF : ALL  34-41-00    CES

 

Page 544 May 01/08

ANTENNA ASSEMBLY - WEATHER RADAR (7SQ,11SQ) - REMOVAL/INSTALLATION __________________________________________________________________ TASK 34-41-11-000-004 Removal of the Weather Radar Antenna Assembly (7SQ,11SQ) WARNING : MOVE THE RADAR ANTENNA ASSEMBLY CAREFULLY TO PREVENT INJURY TO _______ PERSONS AND DAMAGE TO EQUIPMENT. THE RADAR ANTENNA ASSEMBLY (ANTENNA/DRIVE) WEIGHS APPROXIMATELY 15kg (33lb). CAUTION : DO NOT USE THE LOCALIZER ANTENNA AT THE BOTTOM OF THE RADOME AS A _______ SUPPORT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

blanking caps circuit breaker(s) safety clip(s) warning notice access platform 3.5 m (11 ft. 6 in.)

  EFF : ALL  34-41-11 Page 401   Config-3 Nov 01/03  CES

 

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------53-15-11-010-001

Opening of the Radome 110AL

**ON A/C 001-049, 101-105, 151-199, 34-41-11-991-001

Fig. 401

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 34-41-11-991-001-A R

Fig. 401A

**ON A/C 501-509, 511-526, 528-599, 34-41-11-991-001-B

Fig. 401B

**ON A/C ALL 3. __________ Job Set-up Subtask 34-41-11-865-059 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

  EFF : ALL  34-41-11 Page 402   Config-3 Feb 01/10  CES

 

**ON A/C ALL Subtask 34-41-11-010-053 B. Get Access (1) In the cockpit, put a warning notice on the center pedestal, to tell persons not to operate the weather radar system. (2) Put the access platform in position in zone 110 below the radome. (3) Open the radome 110AL (Ref. TASK 53-15-11-010-001). 4. Procedure _________ **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 401/TASK 34-41-11-991-001) **ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, (Ref. Fig. 401A/TASK 34-41-11-991-001-A) R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 401B/TASK 34-41-11-991-001-B) **ON A/C ALL NOTE : If you send the antenna drive to the repair shop, also send its ____ plate.

  EFF : ALL  34-41-11 Page 403   Config-3 Feb 01/10  CES

 

Radar Antenna Figure 401/TASK 34-41-11-991-001   R EFF : 001-049, 101-105, 151-199,  34-41-11 Page 404   Config-3 May 01/05  CES

 

Radar Antenna Figure 401A/TASK 34-41-11-991-001-A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-11 Page 405 301-399, 401-499,  Config-3 May 01/09  CES

 

Radar Antenna Figure 401B/TASK 34-41-11-991-001-B   R EFF : 501-509, 511-526, 528-599,  34-41-11 Page 406   Config-3 Feb 01/10  CES

 

**ON A/C 001-049, 101-105, 151-199, Subtask 34-41-11-020-056 R

A. Removal of the Antenna Plate (1) Remove the four screws (20) and the lockwashers (19) which connect the flange of the wave guide (18) to the antenna (1). NOTE : During the removal of the antenna: ____ - one person must hold the antenna - one person must hold the position indicator (14) to prevent damage to the drive caused by fast movement of the counterbalance spring. (2) Remove the eight screws (15) and the lockwashers (16) which connect the ring mount (17) to the antenna (1) and remove the antenna (1). (3) Slowly release the position indicator (14). (4) Put the antenna (1) in a plastic bag and a correct container. Subtask 34-41-11-020-057 B. Removal of the Antenna Assembly (1) Disconnect the electrical connector(s) (11). (2) Loosen the quick disconnect clamp (2) and disconnect the wave guide (3) from the antenna drive (13). (3) Remove and discard the O-ring (4). (4) Put blanking caps on the disconnected connectors (11) and (12) and on the flange of the wave guide (3). (5) Remove the two screws (10) and the washers (9) at the bottom. (6) Loosen the two screws (6) at the top. Do not remove them. (7) Lift the antenna drive (13) until the holes (7) are at the same level as the two screws (6). (8) Remove the antenna drive (13) and put it in a plastic bag and a correct container.

  R EFF : 001-049, 101-105, 151-199,  34-41-11 Page 407   Config-3 Feb 01/08  CES

 

R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-41-11-020-056-A A. Removal of the Antenna Plate NOTE : During the removal of the antenna, one person must hold the ____ antenna. (1) Remove the two bolts (15). (2) Remove the antenna (1) and put the antenna in a plastic bag and a correct container. Subtask 34-41-11-020-057-A B. Removal of the Antenna Assembly (1) Disconnect the electrical connector(s) (12). (2) Disconnect the wave guide (5) from the antenna drive (2) with the quick disconnect clamp (3) and remove the O-ring (4). (3) Put blanking caps on the disconnected connectors (12) and (13) and the flange of the wave guide (5). (4) Remove the two screws (11) and the washers (10) at the bottom. (5) Loosen the two screws (8) and the washers (7) at the top. Do not remove them. (6) Lift the antenna drive (2) until the holes (6) are at the same level as the two top screws (8), then pull carefully. (7) Remove the antenna drive (2) and put it in a plastic bag and a correct container.

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-11 Page 408 301-399, 401-499, 501-509, 511-526, 528-599,  Config-3 Feb 01/10  CES

 

**ON A/C ALL TASK 34-41-11-400-005 Installation of the Weather Radar Antenna Assembly (7SQ,11SQ) WARNING : MOVE THE RADAR ANTENNA ASSEMBLY CAREFULLY TO PREVENT INJURY TO _______ PERSONS AND DAMAGE TO EQUIPMENT. THE RADAR ANTENNA ASSEMBLY (ANTENNA/DRIVE) WEIGHS APPROXIMATELY 15kg (33lb). CAUTION : DO NOT USE THE LOCALIZER ANTENNA AT THE BOTTOM OF THE RADOME AS A _______ SUPPORT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R R R R

No specific No specific No specific No specific

warning notice access platform 3.5 m (11 ft. 6 in.) Torque Wrench : range 0.00 to 1.20 m.daN (0.00 to 9.00 lbf.ft) Torque Wrench : range 0.70 to 10.00 m.daN (5.00 to 75.00 lbf.ft)

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------No specific

lockwire corrosion resistant steel 0.8mm (0.30 in.)

  EFF : ALL  34-41-11 Page 409   Config-3 Feb 01/10  CES

 

C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------4

O-ring

34-41-01 02B-120

D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-41-00-730-001 53-15-11-010-001 53-15-11-410-001

System Test of the Weather Radar Opening of the Radome 110AL Closing of the Radome 110AL

**ON A/C 001-049, 101-105, 151-199, 34-41-11-991-001

Fig. 401

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 34-41-11-991-001-A R

Fig. 401A

**ON A/C 501-509, 511-526, 528-599, 34-41-11-991-001-B

Fig. 401B

**ON A/C ALL 3. __________ Job Set-up Subtask 34-41-11-860-051 A. Aircraft Maintenance Configuration (1) Make sure that the warning notice, which tells persons not to operate the Weather Radar System, is in position in the cockpit on the center pedestal.

  EFF : ALL  34-41-11 Page 410   Config-3 Feb 01/10  CES

 

(2) Make sure that the access platform is in position in zone 110 below the radome. (3) Make sure that the radome 110AL is open (Ref. TASK 53-15-11-010-001). Subtask 34-41-11-865-060 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 401/TASK 34-41-11-991-001) **ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, (Ref. Fig. 401A/TASK 34-41-11-991-001-A) R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 401B/TASK 34-41-11-991-001-B)

  EFF : ALL  34-41-11 Page 411   Config-3 Feb 01/10  CES

 

**ON A/C 001-049, 101-105, 151-199, Subtask 34-41-11-420-056 A. Installation of the Antenna Assembly (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. R R

(3) Install the two top screws (6) and washers (5) and make sure that they are sufficiently loose. (4) Lift the antenna drive (13) up to its support and engage it in the two top screws (6). (5) Install the two bottom screws (10) and washers (9).

R R

(6) TORQUE the screws (6) and (10) to between 3.22 and 3.87 m.daN (23.74 and 28.53 lbf.ft). (7) Remove the blanking caps from the electrical connectors (11) and (12) and the flange of the wave guide (3). (8) Put the O-ring (4) in the correct position on the flange of the wave guide (3). (9) Connect the wave guide (3) to the antenna drive (13) with the quick disconnect clamp (2). (10) Connect the electrical connector(s) (11). Subtask 34-41-11-420-057 B. Installation of the Antenna Plate NOTE : Two persons are necessary to do this work. ____ (1) Attach the antenna (1) to the ring mount (17) with the screws (15) and the lockwashers (16). (2) Connect the flange of the wave guide (18) to the antenna (1). (3) Install the screws (20) and the lockwashers (19).

R

(4) TORQUE the screws (15) and (20) to 0.29 m.daN (25.66 lbf.in).

  EFF : 001-049, 101-105, 151-199,  34-41-11 Page 412   Config-3 Feb 01/10  CES

 

R

(5) Make sure that the antenna assembly turns correctly in azimuth (AZ) and in elevation (EL).

R

(6) Make sure that the locking device is installed on the EL and AZ switches (8) to prevent their operation.

R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-41-11-420-056-A A. Installation of the Antenna Assembly NOTE : Do not remove the transparent plastic windows that are installed: ____ - at the inlet of the antenna drive, and - at the interface between the antenna drive, and the antenna plate.

R

(1) Clean the component interface and/or the adjacent area.

R

(2) Do an inspection of the component interface and/or the adjacent area.

R R

(3) Install the two top screws (8) and washers (7) and make sure that they are sufficiently loose.

R R

(4) Lift the antenna drive (2) up to its support and engage it in the two top screws (8).

R

(5) Install the two bottom screws (11) and washers (10).

R R

(6) TORQUE the screws (8) and (11) to between 3.22 and 3.87 m.daN (23.74 and 28.53 lbf.ft).

R R

(7) Remove the blanking caps from the electrical connectors (12) and (13) and the flange of the wave guide (5).

R R

(8) Put the O-ring (4) in the correct position on the flange of the wave guide (5).

R R

(9) Connect the wave guide (5) to the antenna drive (2) with the quick disconnect clamp (3).

R R

(10) Connect the electrical connector(s) (12).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-41-11 Page 413 201-249, 251-299, 301-399, 401-499, 501-509,  Config-3 Feb 01/10 511-526, 528-599, CES

 

Subtask 34-41-11-420-057-A B. Installation of the Antenna Plate NOTE : Two persons are necessary to do this work. ____ It is possible to install the antenna (1) with the antenna drive (2) installed on the aircraft. R

(1) Put the dowels (16) in the holes (18) of the antenna (1). Then engage the plate (19) between the two slots (17).

R

(2) Install the screws (15) in the dowels (16).

R

(3) TORQUE the screws (15) to 0.23 m.daN (20.35 lbf.in).

R

(4) Safety the two bolts (15) with lockwire corrosion resistant steel 0.8mm (0.30 in.).

R

(5) Make sure that the antenna assembly turns correctly in azimuth (AZ) and in elevation (EL). **ON A/C ALL Subtask 34-41-11-865-061 C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5SQ1, 5SQ2 Subtask 34-41-11-730-053 D. Do the system test of the weather radar system (para. Antenna control) (Ref. TASK 34-41-00-730-001). 5. Close-up ________ Subtask 34-41-11-410-053 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the radome 110AL (Ref. TASK 53-15-11-410-001). (3) Remove the access platform(s).

  EFF : ALL  34-41-11 Page 414   Config-3 Feb 01/10  CES

 

(4) Remove the warning notice(s).

  EFF : ALL  34-41-11 Page 415   Config-3 Feb 01/10  CES

 

CONTROL UNIT - WEATHER RADAR (3SQ) - REMOVAL/INSTALLATION _________________________________________________________ TASK 34-41-12-000-001 Removal of the Weather Radar Control Unit (3SQ) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

blanking caps circuit breaker(s) safety clip(s)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 001-049, 101-105, 151-199, 34-41-12-991-001 R R

Fig. 401

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-41-12-991-001-A

Fig. 401A

  EFF : ALL  34-41-12    CES

 

Page 401 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-41-12-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 401/TASK 34-41-12-991-001) R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-41-12-991-001-A) **ON A/C ALL Subtask 34-41-12-020-051 A. Removal of the Weather Radar Control Unit (1) Loosen the four quarter-turn fasteners (1). (2) Pull the weather radar control unit (2) from its housing (5). (3) Disconnect the electrical connector(s) (4) and hold it them away from the panel.

  EFF : ALL  34-41-12    CES

 

Page 402 Feb 01/10

Weather Radar Control Unit Figure 401/TASK 34-41-12-991-001   R EFF : 001-049, 101-105, 151-199,  34-41-12    CES

 

Page 403 May 01/05

Weather Radar Control Unit Figure 401A/TASK 34-41-12-991-001-A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-12 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 404 Feb 01/10

(4) Remove the weather radar control unit (2). (5) Put blanking caps on the disconnected electrical connectors (3) and (4).

  EFF : ALL  34-41-12   R  CES

 

Page 405 May 01/05

TASK 34-41-12-400-001 Installation of the Weather Radar Control Unit (3SQ) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-41-00-740-002

BITE Test of the Weather Radar

**ON A/C 001-049, 101-105, 151-199, 34-41-12-991-001 R R

Fig. 401

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-41-12-991-001-A

Fig. 401A

**ON A/C ALL 3. __________ Job Set-up Subtask 34-41-12-865-051 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

  EFF : ALL  34-41-12    CES

 

K14

Page 406 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 401/TASK 34-41-12-991-001) R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-41-12-991-001-A)

R

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-228, 236-238, 301-301, Subtask 34-41-12-420-051 A. Installation of the Weather Radar Control Unit (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (3) and (4). (4) Make sure that the electrical connectors are clean and in the correct condition. (5) Connect the electrical connector(s) (4) to the weather radar control unit (2). (6) Install the weather radar control unit (2) in its housing (5). (7) Tighten the four quarter-turn fasteners (1).

  EFF : ALL  34-41-12    CES

 

Page 407 Feb 01/10

R R

**ON A/C 106-149, 229-235, 239-249, 251-299, 302-399, 401-499, 501-509, 511-526, 528-599,

R

Subtask 34-41-12-420-051-B

R

A. Installation of the Weather-Radar Control Unit

R

(1) Clean the component interface and/or the adjacent area.

R

(2) Do an inspection of the component interface and/or the adjacent area.

R

(3) Remove the blanking caps from the electrical connectors (3) and (4).

R R

(4) Make sure that the electrical connectors are clean and in the correct condition.

R R

(5) Connect the electrical connector(s) (4) to the weather-radar control unit (2).

R

(6) Install the weather-radar control unit (2) in its housing (5).

R

(7) Tighten the four quarter-turn fasteners (1).

R R

(8) If applicable, install a DEACT sticker near the position 2 of the activation switch. **ON A/C 151-199, 201-228, 236-238, 301-301, Post SB

34-1310 For A/C 151-199,201-228,236-238,301-301,

Subtask 34-41-12-420-051-A R

A. Installation of the Weather-Radar Control Unit (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (3) and (4). (4) Make sure that the electrical connectors are clean and in the correct condition.

R R

(5) Connect the electrical connector(s) (4) to the weather-radar control unit (2).

R

(6) Install the weather-radar control unit (2) in its housing (5).

  R EFF : 106-149, 151-199, 201-249, 251-299,  34-41-12 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 408 Feb 01/10

(7) Tighten the four quarter-turn fasteners (1). R R R

(8) If applicable, install a DEACT sticker near the position 2 of the activation switch. **ON A/C ALL Subtask 34-41-12-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5SQ1, 5SQ2 Subtask 34-41-12-740-050 C. Do the BITE test of the weather radar system (Ref. TASK 34-41-00-740-002). 5. Close-up ________ Subtask 34-41-12-860-050 A. Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-41-12    CES

 

Page 409 Feb 01/10

TRANSCEIVER - WEATHER RADAR (1SQ1,1SQ2) - REMOVAL/INSTALLATION ______________________________________________________________ TASK 34-41-33-000-004 Removal of the Weather Radar Transceiver (1SQ1, 1SQ2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------31-32-00-860-010

Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page

**ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, 34-41-33-991-003 R

Fig. 401

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 34-41-33-991-003-A

Fig. 401A

  EFF : ALL  34-41-33    CES

 

Page 401 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-41-33-810-050 A. Print the Trouble Shooting Data (1) If required and applicable, print the Trouble Shooting Data (TSD) as follows: (a) Get access to the SYSTEM/REPORT TEST NAV page (Ref. TASK 31-3200-860-010). (b) Get access to the WXR1 (WXR2) page. (c) Get access to the Trouble Shooting Data page. (d) Print the Trouble Shooting Data (TSD). Subtask 34-41-33-865-058 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL Subtask 34-41-33-010-052 C. Get Access (1) Put the access platform in position at the access door 811 in zone 122. (2) Open the access door 811.

  EFF : ALL  34-41-33    CES

 

Page 402 Feb 01/10

4. Procedure _________ **ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, (Ref. Fig. 401/TASK 34-41-33-991-003) R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-41-33-991-003-A) **ON A/C ALL Subtask 34-41-33-020-050 A. Removal of the Weather Radar Transceiver (1) Loosen the nuts (5). (2) Lower the nuts (5). (3) Pull the weather radar transceiver (2) on its rack (1) to disconnect the electrical connectors (4) and (6). (4) Remove the weather radar transceiver (2) from its rack (1). (5) Put blanking caps on the disconnected electrical connectors (4) and (6).

  EFF : ALL  34-41-33    CES

 

Page 403 Feb 01/10

Weather Radar Transceiver Figure 401/TASK 34-41-33-991-003   R EFF : 001-049, 101-149, 151-199, 201-238,  34-41-33 301-310, 401-499,   CES

 

Page 404 Nov 01/09

Weather Radar Transceivers Figure 401A/TASK 34-41-33-991-003-A   R EFF : 051-099, 239-249, 251-299, 311-399,  34-41-33 501-509, 511-526, 528-599,   CES

 

Page 405 Feb 01/10

TASK 34-41-33-400-003 Installation of the Weather Radar Transceiver (1SQ1, 1SQ2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-41-00-740-002

BITE Test of the Weather Radar

**ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, 34-41-33-991-003 R

Fig. 401

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 34-41-33-991-003-A

Fig. 401A

  EFF : ALL  34-41-33    CES

 

Page 406 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-41-33-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at the access door 811 in zone 122. (2) Make sure that the access door 811 is open. Subtask 34-41-33-865-059 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, (Ref. Fig. 401/TASK 34-41-33-991-003) R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-41-33-991-003-A)

  EFF : ALL  34-41-33    CES

 

Page 407 Feb 01/10

R

**ON A/C ALL Subtask 34-41-33-420-050 A. Installation of the Weather Radar Transceiver (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (4) and (6). (4) Make sure that the electrical connectors are clean and in the correct condition. (5) Install the weather radar transceiver (2) on its rack (1). (6) Push the weather radar transceiver (2) on its rack (1) to connect the electrical connectors (4) and (6). (7) Engage the nuts (5) on the lugs (3) and tighten. Subtask 34-41-33-865-060 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5SQ1, 5SQ2

R

Subtask 34-41-33-740-050 C. Do the BITE test of the weather radar (Ref. TASK 34-41-00-740-002). 5. Close-up ________ Subtask 34-41-33-860-051 A. Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-41-33    CES

 

Page 408 May 01/05

Subtask 34-41-33-410-050 B. Close Access (1) Close the access door 811. (2) Remove the access platform(s).

  EFF : ALL  34-41-33    CES

 

Page 409 May 01/05

MOUNTING TRAY - WEATHER RADAR TRANSCEIVER (9SQ) - REMOVAL/INSTALLATION ______________________________________________________________________ TASK 34-41-37-000-001 Removal of the Weather Radar Transceiver Mounting Tray (9SQ) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

blanking caps blanking plugs

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-41-33-000-004

Removal of the Weather Radar Transceiver (1SQ1, 1SQ2)

**ON A/C 001-049, 101-105, 34-41-37-991-001 R R

Fig. 401

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-41-37-991-001-B

Fig. 401A

**ON A/C 151-199, 34-41-37-991-001-C

Fig. 401B

  EFF : ALL  34-41-37    CES

 

Page 401 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up **ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, Subtask 34-41-37-020-050 A. Remove the Weather Radar Transceiver (Ref. TASK 34-41-33-000-004). R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, Subtask 34-41-37-020-050-A A. Remove the Weather Radar Transceivers (Ref. TASK 34-41-33-000-004). **ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 101-105, (Ref. Fig. 401/TASK 34-41-37-991-001)

R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-41-37-991-001-B) **ON A/C 151-199, (Ref. Fig. 401B/TASK 34-41-37-991-001-C)

  EFF : ALL  34-41-37    CES

 

Page 402 Feb 01/10

Weather Radar Transceiver Mounting Tray Figure 401/TASK 34-41-37-991-001   R EFF : 001-049, 101-105,  34-41-37    CES

 

Page 403 May 01/05

Weather Radar Transceiver Mounting Tray Figure 401A/TASK 34-41-37-991-001-B   R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-37 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 404 Feb 01/10

Weather Radar Transceiver Mounting Tray Figure 401B/TASK 34-41-37-991-001-C

R

  R EFF : 151-199,  34-41-37    CES

 

Page 405 May 01/05

**ON A/C 001-049, 101-105, Subtask 34-41-37-020-052 A. Removal of the Mounting tray (1) Disconnect the electrical connector (9). (2) Loosen the four clamps (7). (3) Disconnect the ventilation lines (8). (4) Put blanking plugs on the disconnected line ends (8). (5) Cut and remove the lockwire from the screws (10). (6) Remove the four screws (10) and the washers (11). (7) Remove the wave guide (12) from its support. Remove the window (13) and the O-rings (14). (8) Remove the ten screws (6), the washers (5) and the attachment plates (4). (9) Remove the electrical connectors (3) from their housings. (10) Put blanking caps on the disconnected electrical connectors (1), (3) and (9). (11) Remove the eight screws (22). R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-41-37-020-052-B A. Removal of the Mounting Tray (1) Disconnect the electrical connector (9). (2) Loosen the four clamps (7). (3) Disconnect the ventilation lines (8). (4) Put blanking plugs on the disconnected line ends (8).

  R EFF : 001-049, 051-099, 101-149, 201-249,  34-41-37 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 406 Feb 01/10

(5) Cut and remove the lockwire from the screws (10). (6) Remove the four screws (10) and the washers (11). (7) Remove the wave guide (12) from its support. Remove the window (13) and the O-rings (14). (8) Remove the twenty screws (6), the washers (5) and the attachment plates (4). (9) Remove the electrical connectors (3) from their housings. (10) Put blanking caps on the disconnected electrical connectors (1), (3) and (9). (11) Remove the eight screws (22) and the washers (23). **ON A/C 151-199, Subtask 34-41-37-020-052-C A. Removal of the Mounting tray (1) Disconnect the electrical connector (9). (2) Loosen the four clamps (7). (3) Disconnect the ventilation lines (8). (4) Put blanking plugs on the disconnected line ends (8). (5) Cut and remove the lockwire from the screws (10). (6) Remove the four screws (10) and the washers (11). (7) Remove the wave guide (12) from its support. Remove the window (13) and the O-rings (14). (8) Remove the twenty screws (6), the washers (5) and the attachment plates (4). (9) Remove the electrical connectors (3) from their housings. (10) Put blanking caps on the disconnected electrical connectors (1), (3) and (9).

  R EFF : 051-099, 106-149, 151-199, 201-249,  34-41-37 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 407 Feb 01/10

R

(11) Remove the eight screws (22). **ON A/C ALL Subtask 34-41-37-020-051 B. Removal of the Wave Guide Switch (1) Remove the eight screws (15) and the eight washers (16). (2) Hold the wave guide switch (17) and remove the four screws (18) and the eight washers (19). (3) Disengage the wave guide switch (17) from its support (20). (4) Remove the Mounting tray (21).

  EFF : ALL  34-41-37    CES

 

Page 408 May 01/05

TASK 34-41-37-400-001 Installation of the Weather Radar Transceiver Mounting Tray (9SQ) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------14

O-rings

34-41-01 02B-120

C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-41-33-400-003

Installation of the Weather Radar Transceiver (1SQ1, 1SQ2)

**ON A/C 001-049, 101-105, 34-41-37-991-001 R R

Fig. 401

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-41-37-991-001-B

Fig. 401A

  EFF : ALL  34-41-37    CES

 

Page 409 Feb 01/10

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R

**ON A/C 151-199,

R

34-41-37-991-001-C

Fig. 401B

**ON A/C ALL 3. __________ Job Set-up Subtask 34-41-37-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at the access door 811 in zone 122. (2) Make sure that the access door 811 is open. 4. Procedure _________ Subtask 34-41-37-420-050 A. Installation of the Wave Guide Switch (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Precaution: If you install a new Mounting tray, make sure that you removed the attachment plates (4). (4) Clean and inspect the wave guide switch (17) interface and the adjacent area. (5) Install the wave guide switch (17) on its support (20). (6) Install the four screws (18) and the eight washers (19). Do not tighten. (7) Install the eight screws (15) and the eight washers (16) and tighten.

  EFF : ALL  34-41-37    CES

 

Page 410 May 01/05

(8) Tighten the four screws (18). R

**ON A/C 001-049, 101-105, Subtask 34-41-37-420-052 B. Installation of Mounting Tray (1) Install the Mounting tray (21) in its housing (2). Install the eight screws (22) and tighten. (2) Remove the blanking caps from the disconnected electrical connectors (1), (3) and (9). (3) Make sure that the electrical connectors are clean and in the correct condition. (4) Install the electrical connectors (3) in their housing. (5) Install the attachment plates (4) and attach them with the ten washers (5) and the screws (6). (6) Put the O-rings (14) in their housings. (7) Put the window (13) and the wave guide (12) in position. (8) Install the four washers (11) and the screws (10). (9) Tighten the screws (10) and safety them with the lockwire. (10) Remove the blanking plugs from the disconnected line ends (8). (11) Connect the ventilation lines (8). Tighten the clamps (7). (12) Connect the connector (9) to the receptacle (1). (13) Make sure that the electrical connectors are clean and in the correct condition.

R

  R EFF : ALL  34-41-37    CES

 

Page 411 May 01/05

R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, Subtask 34-41-37-420-052-B B. Installation of Mounting tray (1) Install the Mounting tray (21) in its housing (2) with the eight washers (23) and the screws (22). (2) Remove the blanking caps from the disconnected electrical connectors (1), (3) and (9). (3) Make sure that the electrical connectors are clean and in the correct condition. (4) Install the electrical connectors (3) in their housing. (5) Install the attachment plates (4) and attach them with the twenty washers (5) and the screws (6). (6) Put the O-rings (14) in their housings. (7) Put the window (13) and the wave guide (12) in position. (8) Install the four washers (11) and the screws (10). (9) Tighten the screws (10) and safety them with the lockwire. (10) Remove the blanking plugs from the disconnected line ends (8). (11) Connect the ventilation line (8). Tighten the clamps (7). (12) Connect the connector (9) to the receptacle (1). (13) Make sure that the electrical connectors are clean and in the correct condition.

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-41-37 301-399, 401-499,   CES

 

Page 412 May 01/09

R

**ON A/C 151-199, 501-509, 511-526, 528-599, Subtask 34-41-37-420-052-C B. Installation of Mounting Tray (1) Install the Mounting tray (21) in its housing (2) with the eight screws (22). (2) Remove the blanking caps from the disconnected electrical connectors (1), (3) and (9). (3) Make sure that the electrical connectors are clean and in the correct condition. (4) Install the electrical connectors (3) in their housing. (5) Install the attachment plates (4) and attach them with the twenty washers (5) and the screws (6). (6) Put the O-rings (14) in their housings. (7) Put the window (13) and the wave guide (12) in position. (8) Install the four washers (11) and the screws (10). (9) Tighten the screws (10) and safety them with the lockwire. (10) Remove the blanking plugs from the disconnected line ends (8). (11) Connect the ventilation lines (8). Tighten the clamps (7). (12) Connect the connector (9) to the receptacle (1). (13) Make sure that the electrical connectors are clean and in the correct condition. **ON A/C ALL 5. Close-up ________ **ON A/C 001-049, 101-105, (Ref. Fig. 401/TASK 34-41-37-991-001)

  EFF : ALL  34-41-37    CES

 

Page 413 Feb 01/10

R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401A/TASK 34-41-37-991-001-B) **ON A/C 151-199, (Ref. Fig. 401B/TASK 34-41-37-991-001-C) **ON A/C 001-049, 101-149, 151-199, 201-238, 301-310, 401-499, Subtask 34-41-37-420-051 A. Install the Weather Radar Transceiver (Ref. TASK 34-41-33-400-003).

R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, Subtask 34-41-37-420-051-A A. Install the Weather Radar Transceivers (Ref. TASK 34-41-33-400-003).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-41-37 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 414 Feb 01/10

WAVE GUIDE ASSEMBLY (301FM) - REMOVAL/INSTALLATION __________________________________________________ TASK 34-41-41-000-001 Removal of the Wave Guide Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.) access platform 3.5 m (11 ft. 6 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------53-15-11-010-001 34-41-41-991-001

Opening of the Radome 110AL Fig. 401

3. __________ Job Set-up Subtask 34-41-41-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

  EFF : ALL  34-41-41    CES

 

K14

Page 401 Feb 01/10

R

**ON A/C ALL Subtask 34-41-41-010-050 B. Get Access (1) In the cockpit, put a warning notice on the center pedestal to tell persons not to operate the weather radar. (2) Put the access platform in position. (3) Open the radome 110AL (Ref. TASK 53-15-11-010-001). (4) Put the access platform in position at the access door 811. (5) Open the access door 811. 4. Procedure _________ (Ref. Fig. 401/TASK 34-41-41-991-001) WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR _______ ARE OPENED, SAFETIED AND TAGGED. Subtask 34-41-41-020-050 A. Removal of the Flexible Wave Guide Part (10) Connected to the Mounting Tray of the Weather Radar Transceiver (1) Remove the lockwire and then the four screws (18) and the four washers (17). (2) Disconnect the flange (11). Remove and discard the two O-rings (13) and (16) and the adaptor (12). (3) At the other end, remove the lockwire and then the four screws (5) and washers (6). (4) Disconnect the flange (9) from the flange (7). Remove and discard the O-ring (8). (5) Remove the flexible wave guide part (10). (6) Put blanking caps on the disconnected ends.

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Page 402 May 01/05

Wave Guide Assembly Figure 401/TASK 34-41-41-991-001   EFF : ALL  34-41-41    CES

 

Page 403 Feb 01/98

Subtask 34-41-41-020-051 B. Removal of the Rigid Wave Guide Part (14) Installed in the Avionics Compartment (1) Remove the lockwire and then the four screws (5) and the four washers (6). (2) Disconnect the flange (9). Remove and discard the O-ring (8). (3) At the wave guide feedthrough (25), remove the lockwire and then the four screws (36) and the four washers (35). (4) Hold the wave guide part (14) and remove the screw (21) and the washer (20) which attach the clamp (19) to the structure. (5) Move the rigid wave guide part (14) away from the structure. Remove and discard the O-ring (24). (6) Remove the clamp (19) and the two half bushings (22) from the wave guide. (7) Remove the rigid wave guide part (14). (8) Put blanking caps on the disconnected ends. Subtask 34-41-41-020-052 C. Removal of the Wave Guide Feedthrough (25) NOTE : Two persons are necessary to remove the wave guide feedthrough. ____ (1) If necessary, remove the two rigid wave guide parts (14) and (37) which are connected to the feedthrough. Refer to Para. B. above and Para. D. below. (2) Remove the eight screws (34), the washers (33) and the nuts (32). (3) Move the wave guide feedthrough (25) away from the pressure bulkhead (27). Remove and discard the packing (26). (4) Remove the wave guide feedthrough (25) and put blanking caps on the disconnected ends.

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Page 404 Feb 01/98

Subtask 34-41-41-020-053 D. Removal of the Rigid Wave Guide Part (37) Installed in the Radome (1) Remove the lockwire and then the four screws (38) and the washers (39). (2) Disconnect the flange (2). Remove and discard the O-ring (3). (3) At the wave guide feedthrough (25), remove the lockwire and then the four screws (30) and the four washers (31). (4) Hold the wave guide part (37) and remove the screw (21) and the washer (20) which attach the clamp (19) to the structure. (5) Move the rigid wave guide part (37) away from the structure. Remove and discard the O-ring (28). (6) Remove the clamp (19) and the two half bushings (22) from the wave guide. (7) Remove the rigid wave guide part (37) and put blanking caps on the disconnected ends. Subtask 34-41-41-020-054 E. Removal of the Flexible Wave Guide Part (1) Connected to the Antenna Drive (1) Release the quick-disconnect attach (40). Disconnect the flange (42) from the antenna drive. Remove and discard the O-ring (41). (2) Remove the screw (21) and the washer (20). Then remove the clamp (19) and the two half bushings (22) from the wave guide. (3) At the other end, remove the lockwire and then the four screws (38) and the four washers (39). (4) Disconnect the flange (2) from the flange (4). Remove and discard the O-ring (3). (5) Remove the flexible wave guide part (1) and put blanking caps on the disconnected ends.

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Page 405 Feb 01/98

TASK 34-41-41-400-001 Installation of the Wave Guide Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R R

No specific No specific No specific

access platform 1.6 m (5 ft. 3 in.) access platform 3.5 m (11 ft. 6 in.) Torque Wrench : range 0.00 to 1.20 m.daN (0.00 to 9.00 lbf.ft)

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------No specific Material No. 09-016

corrosion resistant steel lockwire dia. 0.5 mm (0.020 in.) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00)

C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------41

O-ring (7)

34-41-01 02B-120

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Page 406 May 01/05

D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 31-60-00-860-002 53-15-11-410-001 34-41-41-991-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure Closing of the Radome 110AL Fig. 401

3. __________ Job Set-up Subtask 34-41-41-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position and that the radome 110AL is open. (2) Make sure that the access platform is in position at the access door 811 and that the access door 811 is open. (3) In the cockpit make sure that there is a warning notice on the center pedestal to tell persons not to operate the weather radar. NOTE : Remove the blanking caps before you install parts of the wave ____ guide. Make sure that all mating surfaces are clean and in correct condition. NOTE : Each part of the wave guide is identified (ANT, 1, 2, 3, 4 and ____ RT or ANTENNE 1, 2, 3, 4 and EMETTEUR depending on the Vendor marking). When you install the wave guide part, make sure that the number sequence is correct.

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Page 407 Feb 01/98

Subtask 34-41-41-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RADAR/1 5SQ1 K13 R

**ON A/C 051-099, 239-249, 251-299, 311-399, 501-509, 511-526, 528-599, 121VU COM NAV/RADAR/2

5SQ2

K14

**ON A/C ALL 4. Procedure _________ (Ref. Fig. 401/TASK 34-41-41-991-001) Subtask 34-41-41-420-050 A. Installation of the Flexible Wave Guide Part (1) Connected to the Antenna Drive (1) Install a new O-ring (41) and put the flange (ANT reference) in position. (2) Lock the quick-disconnect attach (40). (3) At the other end, install a new O-ring (3) and connect the flanges (2) and (4). (4) Install the four washers (39) and the four screws (38). TORQUE the screws to between 0.19 and 0.21 m.daN (16.81 and 18.58 lbf.in) and install the corrosion resistant steel lockwire dia. 0.5 mm (0.020 in.). (5) Install the two half bushings (22) and the clamp (19) on the wave guide. Put the clamp in position and install the washer (20) and the screw (21).

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Page 408 Feb 01/10

Subtask 34-41-41-420-051 B. Installation of the Rigid Wave Guide Part (37) in the Radome (1) If necessary, install the wave guide feedthrough (25). Refer to Para. C. below. (2) At the two ends, install new O-rings (3) and (28). (3) Hold the rigid wave guide part (37) in position: install the eight washers (31) and (39) and the eight screws (30) and (38). (4) Tighten the screws and install lockwire. (5) Install the two half bushings (22) and the clamp (19) on the wave guide. Put the clamp in position and install the washer (20) and the screw (21). Subtask 34-41-41-420-052 C. Installation of the Wave Guide Feedthrough (25) NOTE : Two persons are necessary to install the wave guide feedthrough. ____ (1) Install a new packing (26) and put the feedthrough (25) into the cutout of the pressure bulkhead (27). (2) Install the eight screws (34), the washers (33) and the nuts (32). TORQUE the nuts to between 0.19 and 0.21 m.daN (16.81 and 18.58 lbf.in). Seal the nuts with SEALANTS (Material No. 09-016). (3) If necessary, install the rigid wave guide parts (14) and (37) which are connected to the feedthrough. Refer to Para. B. above and to Para. D. below. Subtask 34-41-41-420-053 D. Installation of the Rigid Wave Guide Part (14) in the Avionics Compartment (1) If necessary, install the wave guide feedthrough (25). Refer to Para. C. above. (2) At the two ends, install new O-rings (24) and (8). (3) Hold the rigid wave guide part (14) in position and install eight washers (35) and (6) and eight screws (36) and (5). (4) TORQUE the screws to between 0.19 and 0.21 m.daN (16.81 and 18.58 lbf.in) and install the lockwire.

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Page 409 May 01/05

(5) Install the two half bushings (22) and the clamp (19) on the wave guide. Put the clamp in position and install the washer (20) and the screw (21). Subtask 34-41-41-420-054 E. Installation of the Flexible Wave Guide Part (10) Connected to the Mounting Tray of the Weather Radar Transceiver (1) Install a new O-ring (8) and connect the flange (9) to the flange (7). (2) Install the four washers (6) and the four screws (5). TORQUE the screws to between 0.19 and 0.21 m.daN (16.81 and 18.58 lbf.in) and install the lockwire. (3) On the flange of the mounting tray (15), install a new O-ring (13). (4) On the flange (11) (RT reference), install a new O-ring (16). (5) Put the adaptor (12) in position with the arrow which points in the direction of the mounting tray. (6) Install the flange (11) with the four washers (17) and the four screws (18). TORQUE the screws to between 0.19 and 0.21 m.daN (16.81 and 18.58 lbf.in) and install the lockwire. (7) Make sure that the pressurization hole in the wave guide is clean. Subtask 34-41-41-865-052 F. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5SQ1, 5SQ2 Subtask 34-41-41-710-050 G. Test WARNING : MAKE SURE THAT: _______ -ALL PERSONS ARE MORE THAN 5 METERS (16.4FT) FROM THE ANTENNA. -NO PERSON IS IN THE AREA MADE BY AN ARC OF 135⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE. -THERE IS A MINIMUM SAFETY DISTANCE OF 5 METERS (16.4FT) BETWEEN THE AIRCRAFT AND ANY OBSTACLE IN THE AREA MADE BY AN ARC OF 90⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE. THE AIRCRAFT MUST NOT BE IN A HANGAR OR CLOSED AREA.

R

(1) Make sure that all wave guide parts are correctly installed. (2) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002).   EFF : ALL  34-41-41    CES

 

Page 410 May 01/07

(3) Do the EIS start procedure (ND only) (Ref. TASK 31-60-00-860-001). (4) On the ADIRS CDU, on the panel 20VU: - set the three OFF/NAV/ATT selector switches to NAV. (5) On the center pedestal, on the weather radar control unit, set the system to ON. (6) Make sure that the system operates normally: on the ND, the weather radar display is shown. (7) On the weather radar control unit, set the system to OFF. 5. Close-up ________ Subtask 34-41-41-860-052 A. Put the aircraft back to its initial configuration. (1) Do the EIS Stop Procedure (ND only)(Ref. TASK 31-60-00-860-002). (2) On the ADIRS CDU set the OFF/NAV/ATT selector switches to OFF. (3) Make sure that the work area is clean and clear of tool(s) and other items. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). (5) Remove the warning notice(s). Subtask 34-41-41-410-050 B. Close Access (1) Close the access door 811. (2) Close the radome 110AL (Ref. TASK 53-15-11-410-001). (3) Remove the access platform(s).

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Page 411 Feb 01/98

RADIO ALTIMETER - DESCRIPTION AND OPERATION ___________________________________________ 1. _______ General The function of the radio altimeter (RA) is to determine the height of the aircraft above the terrain. One of the main characteristics of the system is that it locks onto the leading edge of the reflected wave. This permits to measure the distance between the aircraft and the nearest obstacle. The radio altimeter can therefore operate over non-flat ground surface. 2. __________________ Component Location R R

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 501-509, 511-526, 528-599, (Ref. Fig. 001) **ON A/C 151-199, 401-499, (Ref. Fig. 001A) **ON A/C 301-399, (Ref. Fig. 001B) **ON A/C ALL ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2SA1 XCVR-RA, 1 152 826 34-42-33 2SA2 XCVR-RA, 2 152 826 34-42-33 3SA1 FAN-RA XCVR 1 152 826 34-42-45 3SA2 FAN-RA XCVR 2 152 826 34-42-45 5SA1 ANTENNA-RA RCPTN, 1 153 34-42-11 5SA2 ANTENNA-RA RCPTN, 2 153 34-42-11 6SA1 ANTENNA-RA XMSN, 1 153 34-42-11 6SA2 ANTENNA-RA XMSN, 2 153 34-42-11

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Page 1 Feb 01/10

Radio Altimeter - Component Location Figure 001   R EFF : 001-049, 051-099, 101-149, 201-249,  34-42-00 251-299, 501-509, 511-526, 528-599,   CES

 

Page 2 Feb 01/10

Radio Altimeter - Component Location Figure 001A   R EFF : 151-199, 401-499,  34-42-00    CES

 

Page 3 Aug 01/05

Radio Altimeter - Component Location Figure 001B

R

  R EFF : 301-399,  34-42-00    CES

 

Page 4 Nov 01/09

3. __________________ System Description A. Principle The principle of the radio altimeter is to : - transmit a frequency modulated signal from the aircraft to the ground - receive the ground reflected signal after a certain delay. The time between the transmitted frequency and the received frequency is proportional to the aircraft height. B. System Architecture (Ref. Fig. 002) The radio altimeter comprises two independent systems. Each system consists of : - one transceiver 2SA1 (2SA2) - one transmission antenna 6SA1 (6SA2) - one reception antenna 5SA1 (5SA2) - one fan 3SA1 (3SA2). In addition, the Centralized Fault-Display Interface-Unit (CFDIU) 1TW controls the system through the Multipurpose Control and Display Unit 1 (2) (MCDU) 3CA1 (3CA2) for test causes. (Ref. Fig. 003) The radio height data is shown on the Primary Flight Display (PFD). In normal operation, system 1 provides information to the CAPT PFD and system 2 to the F/O PFD. C. Utilization Technical Data (Ref. Fig. 004) (1) Height data display (Item 3) The aircraft height data with respect to the ground is shown in the sector 2 of the PFD. This indication is at the bottom of the attitude sphere, for height less than or equal to 2500 ft. The dimension and color of the digits change in relation to the height (H) and decision height (DH) as follows : H more than or equal to 400 ft. : 3 mm green digits 400 ft. > H > DH + 100 ft. : 4 mm green digits H < DH + 100 ft. : 4 mm amber digits. The sensitivity of the digits is also a function of the height : H > 50 ft. : 10 ft. increments 50 ft > or = to H and H > or = to 5 ft : 5 ft. increments H < 5 ft. : 1 ft. increments. With failure of both radio altimeters, a red RA warning message is shown in place of the radio height information (Item 4) in slats extented configuration only. The message flashes during 3 seconds then remains on.

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Page 5 Feb 01/10

Radio Altimeter - Block Diagram Figure 002   R EFF : ALL  34-42-00    CES

 

Page 6 Nov 01/09

Radio Altimeter - Control and Indicating Figure 003   EFF : ALL  34-42-00   R  CES

 

Page 7 Nov 01/09

Radio Altimeter - Data and Warning Displays Figure 004   EFF : ALL  34-42-00   R  CES

 

Page 8 Nov 01/09

When the aircraft is below 500 ft. height above the terrain : a red ribbon comes into view on the bottom of the altitude scale and moves up with this scale as the aircraft is in the descent phase (Item 2). When the aircraft has touched down the ground : the top of this ribbon is at the middle of the altitude window. With failure of both radio altimeters, the ribbon goes out of view. Below 300 ft., the height is shown by the distance between the horizon line and the limit of the sector 2. The limit of the sector 2 moves up as the aircraft is in the descent phase. The distance between these two lines is proportional to the ground height (sensitivity 5 ft./mm). As it moves up, the limit line erases the graduations on the pitch scale. With failure of both radio altimeters, this indication goes out of view. (2) Decision height display (DH) (Item 1) The pilot sets the DH on the MCDU. The DH data are shown on the R top corner of the PFD (3 mm high digits) as soon as the radio altimeter operates. When the height is lower than the DH, a DH amber warning message comes into view at the bottom of the attitude sphere (Item 5). D. Warnings (Ref. Fig. 003, 004) The warnings related to the radio altimeter are : - local warning on the instruments that use the radio altimeter data - MASTER CAUT lights on the CAPT and F/O glareshield panels - aural warning : single chime - warning message shown on the upper ECAM display unit. R 4. Power ____________ Supply (Ref. Fig. 002) Energization of each system is through 115VAC, 400 Hz normal buses : - 115VAC BUS1 101XP via circuit breaker 1SA1 for system 1 - 115VAC BUS2 202XP via circuit breaker 1SA2 for system 2. 5. _____________________ Component Description A. Transceiver

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Page 9 Nov 01/09

R (1) External description (Ref. Fig. 005) The face of the transceiver is fitted with a handle, two attaching parts, a TEST pushbutton switch, a connector (TEST CONN) to connect test set for system test and four LEDs. The name, color and function of the four LEDs are as follows: - SYSTEM OK (green) indicates no fault. - R/T UNIT (red) indicates a fault in the reception-transmission circuit. - ANT (red) indicates a fault in the antenna circuit. - IND (red) indicates a fault in the indicating circuit. The back is equipped with one ARINC 600 electrical receptacle and a slot for the test connector.

R

(2) Internal description (Ref. Fig. 006) The transceiver includes the following boards: - microprocessor - search Track control - Sawtooth generator - UHF source - power supplies - alarm outputs and altitude trips - amplifier - Discriminators. (3) Operation (a) Layout The transmitted wave Tx is mixed with the reflected wave Rx to provide several beat frequencies the weakest of which alone is selected after separation in the amplifier filter. The tracking discriminator generates an error signal Fb (Fb = Fb - Fbo) serving to modify the sawtooth wave so as to obtain a correct Fb ; the sawtooth generator modifies the slope of the sawtooth the amplitude of which is constant. The purpose of the monitoring discriminator is to ensure that the Fb spectrum is definitely centered on the Fbo. In the absence of this spectrum, the monitoring discriminator switches the search track control to search mode. The wave is then transmitted in sawtooth form. The search cycle duration is 0.4 seconds and repeats until Fb is correct. The energy detected by the monitoring discriminator is then sufficient to exceed a preset threshold and the monitoring discriminator performs switching to track mode.

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Page 10 Nov 01/09

Radio Altimeter - Transceiver Figure 005

R

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Page 11 Nov 01/09

Radio Altimeter - Transceiver Figure 005A

R

  R EFF : 001-004,  34-42-00    CES

 

Page 12 Nov 01/09

Radio Altimeter - Simplified Block Diagram Figure 006   R EFF : ALL  34-42-00    CES

 

Page 13 Nov 01/09

(b) Monitoring The radio altimeter is permanently monitored by the monitoring discriminator. In addition, calibration is performed twice per second. During calibration : - the mixer is cut off and the amplifier filter output signal is no longer present. - the monitoring discriminator triggers the search mode. - a second source known as the test source is set into operation and injects an input signal into the amplifier filter. When Fb = Fbo (25 KHz), search is cut off by the monitoring discriminator. The sawtooth generator, which has the same input as the test source, generates a 1 ms sawtooth and the microprocessor calibrates delta F and Fo. The calibration test is then completed. (c) Microprocessor The microprocessor consists of a Motorola 6802 MCU with a 6840 programmable timer module (PTM) and a PROM memory. The microprocessor controls the loop management, inputs, outputs, self calibration and the self monitoring circuits. It measures the duration T of the modulation sawtooth, subtracts the aircraft installation delay value read on the main connector, computes the altitude, filters out the Doppler effect and issues the output information. The microprocessor monitors the monitoring discriminator output and determines whether the loop should be in the track mode or switched to the search mode. In the later case, it energizes the search generator. R **ON A/C 001-004, Post SB

34-1171 For A/C 001-004,

(1) External description (Ref. Fig. 005A) The face of the receiver is fitted with a handle, two attaching parts, two momentary pushbutton switches and a front panel Liquid Crystal Display (LCD). The LCD is used as a fault display and as an operator interface during certain modes. The front panel display also provides user interfaces for test and troubleshooting. The front panel contains two momentary pushbutton switches for interfacing with the LCD pages.

R

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Page 14 Nov 01/09

The back is equipped with one ARINC 600 size one connector, which includes three plugs: - Top Plug (TP): connection with the reception antenna - Middle Plug (MP): service interconnection and connection with the transmission antenna - Bottom Plug (BP): connection with the power supply circuit. (2) Internal description (Ref. Fig. 006A) The transceiver includes the following boards: - an RF module - a main processor module - a monitor processor module - a power supply module - a rear interconnect module - a display data module - a memory card module.

R

(a) RF module The RF module, controlled by the main processor, transmits and receives the altimeter signal. BITE circuitry is included to both test and continuously monitor the RF module functions. The process of generating a transmission begins with the Voltage Controlled Oscillator (VCO) output which is split between the transmitter and receiver Local Oscillator (LO). The received signal is mixed with the VCO signal, producing a difference frequency signal that is amplified and fed to an Analog-to-Digital (A/D) converter on the main processor module. (b) Main processor module The main processor module controls the radio altimeter operation, performs signal processing of the difference frequency and test signals, and controls the aircraft interfaces and the data displayed on the front panel. The main processor module is divided into three major sections: the Digital Signal Processor (DSP) section, the 486 CPU microprocessor section, and the Input/Output (I/O) section. 1 _

DSP section The DSP section is used to process the analog outputs from the RF module and to generate some of the control signals to the RF module for transmit modulation, automatic gain control, and test signals. The DSP processes the difference frequency and calibration frequency into altitude information.

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Page 15 Nov 01/09

Data is exchanged with the CPU section through a dual-port Random Access Memory (RAM), providing maximum throughput of both processors. 2 _

486 CPU microprocessor section The CPU section does frame-to-frame processing of the altitude data from the DSP section providing the resulting altitude to the I/O section. The microprocessor in the CPU section controls all major functions of the radio altimeter. Programmable logic devices serve as the microprocessor controller and provide the interfaces to the memory devices (boot routine, program, fault, and data), the data recorder/data loader flash card, and the front panel display driver.

3 _

I/O section The I/O section provides the two ARINC 429 altitude outputs as well as ARINC 429 interfaces with other aircraft systems including the Centralized Fault Display Interface Unit (CFDIU). All discrete inputs external to the radio altimeter are processed by the I/O section. The I/O section also generates the external discrete outputs which are buffered to prevent damage to the processor circuitry.

(c) Monitor processor module The monitor processor module provides a second signal processing path using a Digital Signal Processor (DSP). The DSP processes the received signal and calibration signal supplied in digital form from the main processor A/D converter. Also present are a clock, an ARINC 429 receiver/selector and static memory. (d) Power supply module The power supply module is a self-contained, high-efficiency, switching power supply that converts the 115VAC, 400 Hz A/C power into the required +5VDC, +12VDC, -12VDC, and +24VDC operating voltages. A power-down interrupt provides advanced notice of a power loss allowing the processors to temporarily retain their status.

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Page 16 Nov 01/09

Radio Altimeter - Simplified Block Diagram Figure 006A

R

 R EFF : 001-004,  34-42-00     CES

 

Page 17/18 Nov 01/09

(e) Rear interconnect module To prevent High Intensity Radiated Fields (HIRF) from entering via rear connector cables, an HIRF compartment is formed in the rear of the RA. The signal and power cables are filtered by using discrete and distributed filter elements and limiting devices on the rear interconnect module located inside this HIRF compartment. The filtered lines are then fed to the appropriate points in the RA. (f) Display date module The display data module is mounted behind the front panel and provides an interface to an operator via a low-power Liquid Crystal Display (LCD) which is visible from the front of the RA. In addition to the LCD, the module contains LED Light Box backlighting, temperature compensation circuitry, and a PC board containing an associated LDC driver, two pushbutton switches, and a 9-pin D connector. (g) Memory card module The memory card interface is used to load data into the CPU or record data from the CPU. The memory card module supports either flash cards or RAM cards via the front panel Personal Computing Memory Card Interface Adapter (PCMCIA) slot. The flash card or RAM card is inserted through the front panel. In one mode, data stored on the flash card memory manual is used to update program or data memory in the RA. In another mode, the flash card functions as a data recorder. (3) Not Applicable R

**ON A/C ALL (4) Digital outputs This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives : - EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label

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Page 19 Nov 01/09

- XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds - CODE : BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 164 |RADIO | 8192 | FT | 29 | 16 | 80 |BNR |RALT | | | |HEIGHT | 0.125 | | | | | | | | | | | | | | | | | | | ------------------------------------------------------------------------------R B. Antennas (Ref. Fig. 007)

R R

The transmission and reception antennas are identical. The small thickness antenna is installed on the skin of the aircraft. Each antenna is supplied through a coaxial connector linked to the transceiver. The operating range of the antenna according to the attitude of the aircraft is limited to + or - 30⁰ for roll and pitch. C. Fans The six-blade fan is integral with a removable base plate attached under the transceiver mount. It is contained in a square aluminum alloy case. It is supplied with 115VAC through a connector and associated wiring connecting it to the transceiver. Interference is suppressed by a capacitor mounted on the fan case.

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Page 20 Nov 01/09

Radio Altimeter - Antennas Figure 007

R

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Page 21 Nov 01/09

6. Operation _________ A. Control In normal operation, system 1 automatically provides the height data for the CAPT PFD and system 2 for the F/O PFD. With failure of one system, the valid system is automatically switched to both CAPT and F/O PFDs. With failure of the two systems, the digits go out of view from the PFD : in place of the digits, a red RA warning message flashes during three seconds then remains on. For information : the pilot sets the DH on the MCDU. The Flight Warning Computer (FWC) generates the DH warning message. With loss of DH information, the DH data are not shown. B. Reconfiguration Switching In normal utilization, the radio altimeter data are shown on the CAPT PFD and F/O PFD through the Display Management Computers 1 and 2 (DMC). With failure of the radio altimeter transceiver 1, the DMC 1 and 2 automatically switch over to the transceiver 2. With failure of the DMC 1 (2), it is possible to switch over to the DMC 3 with the EIS DMC selector switch. This selector switch is located on panel 8VU on the center pedestal. In this case the DMC 3 totally replaces the DMC 1 (2) through the stage of the output switching relay of the failed DMC. With failure of the PFD, there is an automatic transfer of the PFD image onto the Navigation Display (ND). When you set the PFD potentiometer to OFF on panel 301VU (500VU), this causes : - deactivation of the PFD - transfer of the PFD image onto the ND. R

7. ____ Test (Ref. Fig. 008)

R

**ON A/C 001-004,

R

Post SB

R R

34-1171 For A/C 001-004,

(Ref. Fig. 008A) **ON A/C ALL A. Access to Radio Altimeter Sub-menu Functions

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Page 22 Nov 01/09

Radio Altimeter - Maintenance Test Procedure Figure 008

R

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Page 23 Nov 01/09

Radio Altimeter - Maintenance Test Procedure Figure 008A

R

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Page 24 Nov 01/09

R It is possible to select the maintenance functions of the radio altimeter transceiver 1(2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant RA on the NAV menu. After these actions the RA 1(2) provides its own menu page and the sub-menu functions can then be chosen by the operator. NOTE : The test can be performed on the ground only. It is inhibited (the ____ EIU1 (EIU2) sends a ground discrete to the RA1 (RA2)) as soon as N2 rating (high pressure compressor rotational speed) is greater than minimum idle rating. B. Activation of the Test Function (1) ARINC TEST The RA ARINC TEST function can be activated by pressing the line key adjacent to the corresponding indication on the RA maintenance sub-menu or by pressing the pushbutton switch on the face of the transceiver. The following sequence is then generated on the output of the equipment: ------------------------------------------------------------------------------| DURATION | LED STATUS | MESSAGE | |-----------------------|---------------------------|-------------------------| | 0.8 s | ALL ON | FUNCTIONAL TEST | | See NOTE | GREEN ON | ALTITUDE VALUE : | | | | 40 FEET | ------------------------------------------------------------------------------NOTE : The green LED remains on : ____ - until the test sub-menu mode is deactivated. - or until the pushbutton switch on the face of the transceiver is released. (2) RAMP TEST The RAMP TEST function can be activated from the MCDU by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu then selecting the LRRA 1 (LRRA2) on the NAV menu and then selecting the RAMP TEST page. On the RAMP TEST page select : - START ALT : 0 ft. - STOP ALT : 2500 ft. - SLOPE : 25 ft./s. Push the line key adjacent to the TRIGGER indication. On the PFD :

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Page 25 Nov 01/09

* the ramp test starts, it moves up to 2500 ft. it stops after approximately 1 minute 40 seconds. * when the altitude is between 0 and 160 ft. the horizon line moves down. The elevation scale comes into view. * when the altitude is between 0 and 570 ft. the red ribbon adjacent to the altitude scale moves down and then it goes out of view. - on the MCDU, at the altitude 2500 ft. the RAMP TEST STOPPED page comes into view. R **ON A/C 001-004, Post SB

34-1171 For A/C 001-004, It is possible to select the maintenance functions of the radio altimeter transceiver 1(2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant RA on the NAV menu. After these actions the RA 1(2) provides its own menu page and the sub-menu functions can then be chosen by the operator. NOTE : The test can be performed on the ground only. It is inhibited ____ (the EIU1 (EIU2) sends a ground discrete to the RA1 (RA2)) as soon as N2 rating (high pressure compressor rotational speed) is greater than minimum idle rating.

B. Activation of the Test Function (1) Self-Test The self-test can be activated by pushing the TEST pushbutton switch as designed on the front panel LCD, if the test inhibit discrete is not active. A TEST IN PROGRESS message is displayed approximately one second after the TEST pushbutton is pressed. At the end of the self-test, either a TEST COMPLETE, NO FAILURES message screen or a TEST COMPLETE, FAILURES message screen is displayed. The TEST COMPLETE, NO FAILURES screen contains two pushbutton selections (MAINT and RETURN). The TEST COMPLETE, FAILURES screen also contains two pushbutton selections (MAINT and WHY?). For both screens, pressing the left (MAINT) pushbutton initiates the extented maintenance pages of the system for troubleshooting. The right (RETURN) pushbutton associated with the TEST COMPLETE, NO FAILURES screen returns the system to its normal mode screen. The right (WHY?) pushbutton associated with the TEST COMPLETE, FAILURES screen places the system in the display-failures mode where

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Page 26 Nov 01/09

individual system failures (fault memory codes) are displayed, one per page. (2) RAMP TEST The RAMP TEST function can be activated from the MCDU by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu then selecting the RA1 (RA2) on the NAV menu and then selecting the RAMP TEST page. The RA then begins simulating a ramp starting from 500 ft. down to 0 ft. (with a slope of 10 ft/s from 500 ft. to 50 ft. and approximately 3 ft/s from 50 ft. to 0 ft.). (3) SYSTEM TEST The RA SYSTEM TEST function can be activated by pressing the line key adjacent to the corresponding indication on the RA 1(2) maintenance sub-menu. The following sequence occurs : - on the PFD : * the bottom sector line moves down from the horizon line. * the radio altimeter is 40 ft. - on the MCDU, at the end of the test, the TEST OK message comes into view. NOTE : During the test : ____ - You can hear auto call-out announcements 40, 41 or 42 - You must open the RA1 circuit breaker to hear auto call-out announcements during the RA2 SYSTEM TEST. NOTE : If the system test or the ramp test cannot be initiated on ____ ground from the MCDU (which means that a fault affects either the LGCIU, the EIU or the RA) a TEST page comes into view on the MCDU. (Ref. Fig. 009, 010, 011)

R

**ON A/C ALL R

C. Power-up Tests Initialization and Cockpit Repercussions (1) Conditions of power-up tests initialization - How long the computer must be de-energized: 2 s. - A/C configuration: - whatever the A/C configuration on ground

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Page 27 Nov 01/09

RA Maintenance Test Procedure - Access to Sub-menus 4/6 Figure 009

R

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Page 28 Nov 01/09

RA Maintenance Test Procedure - Access to Sub-menus 5/6 Figure 010

R

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Page 29 Nov 01/09

RA Maintenance Test Procedure - Access to Sub-menus 6/6 Figure 011

R

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Page 30 Nov 01/09

(2) Progress of power-up tests - Duration: 3 s. - Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - MASTER CAUT light on (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). - Tests pass: - MASTER CAUT light off - Tests failed: - MASTER CAUT light on - ECAM warning NAV RA 1 or 2 FAULT - ECAM STATUS RA 1 or 2 INOP R **ON A/C 001-004, Post SB R

34-1171 For A/C 001-004,

D. CFDIU Interface (Ref. Fig. 002) (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the RA system. The BITE of the radio altimeter is connected to the CFDIU (Ref. 31-32-00). The BITE: - transmits permanently RA system status and its identification message to the CFDIU - memorizes the failures which occurred during the last 63 flight legs - monitors data inputs from the various peripherals - transmits to the CFDIU the result of the tests performed and selt-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the menu mode. (a) Normal mode During the normal mode the BITE monitors cyclically the status of the RA system. It transmits its information to the CFDIU during the concerned flight.

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Page 31 Nov 01/09

In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU by an ARINC 429 message with label 356. (b) Menu mode The menu mode can only be activated on the ground. This mode enables communication between the CFDIU and the RA BITE by means of the MCDU. (Ref. Fig. 008A) All the information displayed on the MCDU during the BITE Test configuration can be printed by the printer (Ref. 31-35-00). The RA menu mode is composed of: - LAST LEG REPORT (Ref. Fig. 012) This menu contains the fault messages (class 1 and 2, internal and external) detected during the last flight. - PREVIOUS LEGS REPORT (Ref. Fig. 012) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. - LRU IDENTIFICATION (Ref. Fig. 012) Allows to display the P/N, the S/N and the SW/N of the equipment. - GND SCANNING (Ref. Fig. 013) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. - TROUBLE SHOOTING DATA (Ref. Fig. 013) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. - CLASS 3 FAULTS (Ref. Fig. 014) Allows to display the class 3 faults recorded during the last flight leg. - GROUND REPORT. (Ref. Fig. 014) Allows to present the class 1, 2 or 3 internal failures detected on ground. - SYSTEM TEST. (Ref. Fig. 009, 010) Allows a check of the correct operation of the RA transceiver on the ground.

R

R

R

R R

R

R

R

R

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Page 32 Nov 01/09

RA Maintenance Test Procedure - Access to Sub-menus 1/6 Figure 012

R

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Page 33 Nov 01/09

RA Maintenance Test Procedure - Access to Sub-menus 2/6 Figure 013

R

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Page 34 Nov 01/09

RA Maintenance Test Procedure - Access to Sub-menus 3/6 Figure 014

R

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Page 35 Nov 01/09

- RAMP TEST. (Ref. Fig. 011) Allows to verify that auto call out altitudes are correctly announced.

R

(2) List of components All the components are listed in the Para. 2. Component Location.

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Page 36 Nov 01/09

RADIO ALTIMETER - ADJUSTMENT/TEST _________________________________ TASK 34-42-00-740-002 BITE Test of the Radio Altimeter WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 31-60-00-860-002 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-42-00-860-054 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (PFDs only) (Ref. TASK 31-60-00-860-001). (3) Do the ADIRS Start Procedure (Ref. TASK 34-10-00-860-002). (4) On the center pedestral, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010).

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Page 501 Feb 01/98

Subtask 34-42-00-865-056 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RAD ALTM/2 1SA2 K12 121VU COM NAV/RAD ALTM/1 1SA1 K11 4. Procedure _________ R Subtask 34-42-00-740-051 A. BITE Test NOTE : - During the test, you can hear auto call out announcements 40 or ____ 41 or 42. - You must open the RA1 circuit breaker to hear auto call out announcements during the RA2 ARINC TEST. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the MCDU: - get the LRRA1 (LRRA2) page then push the line key adjacent to the ARINC TEST indication.

On the CAPT (F/O PFD): - the bottom sector line moves down from the horizon line. - the radio altitude indication is 40 ft. At the end of the test, on the MCDU, the NO FAILURE DETECTED message comes into view.

- push the line key adjacent to the RETURN indication.

On the CAPT (F/O PFD): - the bottom sector line moves up to the horizon line. - the radio altitude indication is O ft. On the MCDU, the LRRA1 (LRRA2) page comes into view.

R

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Page 502 Nov 01/09

**ON A/C 001-004, Post SB

34-1171 For A/C 001-004,

Subtask 34-42-00-740-051-A A. BITE Test NOTE : - During the test, you can hear auto call out announcements 40 or ____ 41 or 42. - You must open the RA1 circuit breaker to hear auto call out announcements during the RA2 SYSTEM TEST. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- get the RA1 (RA2) page then push the line key adjacent to the SYSTEM TEST indication.

- the INITIAL CONDITIONS are shown (page 1 to 2).

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 5S indication comes into view. On the CAPT (F/O) PFD: - the bottom sector line moves down from the horizon line. - the radio altitude indication is 40 ft. On the MCDU: - at the end of the test, the TEST OK message comes into view.

- push the line key adjacent to the RETURN indication.

- the RA1 (RA2) page comes into view. On the CAPT (F/O) PFD: - the bottom sector line moves up to the horizon line. - the radio altitude indication is O ft.

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Page 503 Nov 01/09

**ON A/C ALL 5. Close-up ________ Subtask 34-42-00-860-055 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (3) On the center pedestal, on the MCDU, push the line key adjacent to the RETURN indication until the MCDU MENU page comes into view. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items.

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Page 504 Nov 01/09

TASK 34-42-00-750-001 Operational Check and Detailed Inspection for Contamination of the Radio Altimeter Fan WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Refer to the MPD TASK: 344200-01 Operational Check and Detailed Inspection for Contamination of Radio Altimeter Fan. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

air blower soft brush access platform 2 m (6 ft. 7 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------22-97-00-710-001 24-41-00-861-002 24-41-00-862-002 34-42-00-740-002 34-42-33-000-001 34-42-33-400-001 34-42-45-000-001 34-42-45-400-001

Operational Test of the LAND CAT III Capability Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power BITE Test of the Radio Altimeter Removal of the Radio Altimeter Transceiver 2SA1 and 2SA2 Installation of the Radio Altimeter Transceiver 2SA1 and 2SA2 Removal of the Radio Altimeter-Transceiver Fan 3SA1 (3SA2) Installation of the Radio Altimeter-Transceiver Fan 3SA1 (3SA2)

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Page 505 Nov 01/09

INTENTIONALLY BLANK

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Page 506 Nov 01/09

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------52-30-00-860-001 52-30-00-860-002

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

3. __________ Job Set-up Subtask 34-42-00-860-056 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 34-42-00-010-050 B. Get Access (1) Put an access platform in position at the aft cargo door 826. (2) Open the aft cargo door 826 (Ref. TASK 52-30-00-860-001). (3) Remove the sidewall panel 152GW. Subtask 34-42-00-865-055 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RAD ALTM/2 1SA2 K12 121VU COM NAV/RAD ALTM/1 1SA1 K11 4. Procedure _________ Subtask 34-42-00-020-050 A. Remove the two Radio Altimeter Transceivers (Ref. TASK 34-42-33-000-001).

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Page 507 May 01/09

Subtask 34-42-00-210-051 B. Detailed Inspection of the two RA transceiver Fans (1) Do a detailed visual inspection of the two RA transceiver fans and of the fan housing. (2) Remove the RA transceiver fans (Ref. TASK 34-42-45-000-001). (3) Lock the RA transceiver fans and their housings to prevent movement. NOTE : When you clean the fan with the air blower, the fan can turn ____ too quickly and thus a fault can occur. (4) Clean the RA transceiver fans and their housings with a soft brush and/or an air blower. (5) Install the RA transceiver fans (Ref. TASK 34-42-45-400-001). Subtask 34-42-00-420-050 C. Install the two Radio Altimeter Transceivers (Ref. TASK 34-42-33-400001). (1) Close the circuit breakers 1SA1 and 1SA2 on the panel 121VU. Subtask 34-42-00-720-053 D. Functional Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the rear circuit breaker panel 121VU:

In the aft cargo compartment (zone 152, door 826), below the transceiver mount:

- open the circuit breaker 1SA1 (1SA2).

- make sure that the RA transceiver fan 3SA1 (3SA2) does not blow.

- close the circuit breaker 1SA1 (1SA2).

- make sure that the RA transceiver fan 3SA1 (3SA2) blows air up.

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Page 508 May 01/09

Subtask 34-42-00-740-052 E. Do the BITE test of the radio altimeter (Ref. TASK 34-42-00-740-002). NOTE : If the airline operates the aircraft in CAT III conditions, you ____ must also do the LAND CAT III capability test (Ref. TASK 22-97-00710-001). 5. Close-up ________ Subtask 34-42-00-410-050 A. Close Access (1) Install the sidewall panel 152GW. (2) Close the aft cargo door 826 (Ref. TASK 52-30-00-860-002). (3) Remove the access platform(s). Subtask 34-42-00-865-059 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RAD ALTM/2 1SA2 K12 121VU COM NAV/RAD ALTM/1 1SA1 K11 Subtask 34-42-00-860-057 C. Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (2) Make sure that the work area is clean and clear of tool(s) and other items.

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Page 509 May 01/09

TASK 34-42-00-730-002 Ramp Test of the Radio Altimeter WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Test of the automatic simulation of a change in altitude. 2. ______________________ Job Set-up Information R R

A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-50-00-710-006 31-60-00-860-001 31-60-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page Operational Test of the Automatic Call-Out EIS Start Procedure EIS Stop Procedure

3. __________ Job Set-up R Subtask 34-42-00-860-052 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). (3) Do the EIS start procedure (PFDs only) (Ref. TASK 31-60-00-860-001).

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Page 510 Nov 01/09

(4) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector switches to NAV. R Subtask 34-42-00-865-057 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RAD ALTM/2 1SA2 K12 121VU COM NAV/RAD ALTM/1 1SA1 K11 Subtask 34-42-00-865-058 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------R 121VU EIS/GPWS/115VAC

3WZ

P07

R 4. Procedure _________ R Subtask 34-42-00-730-050 A. System Test NOTE : This note is for RA1 test, for RA2 test you must open the circuit ____ breaker 1SA1. If you do this test in descent, you can make sure that the auto call out announcements are correct. To do this, set a small SLOPE. To decrease the total test time, increase the speed of the altitude change. To do this, adjust SLOPE to a larger value or set a lower STOP ALT. NOTE : This test is the radio altimeter ramp test. For auto call-out ____ announcement, do the operational test of the automatic call-out (Ref. TASK 31-50-00-710-006).

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Page 511 Nov 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU: - push the line the RA1 (RA2) push the line the RAMP TEST

key adjacent to indication. Then key adjacent to indication.

On the MCDU: - the LRRA1 (LRRA2) RAMP TEST page comes into view.

- for each value, enter the number in the scratchpad and push the related line key:

On the MCDU, these values come into view:

* START ALT : 0 ft. * STOP ALT : 2500 ft. * SLOPE : 25 ft/s. (Ref. NOTE).

* + 0 ft. * + 2500 ft. * 25 ft/s.

- push the line key adjacent to the TRIGGER indication.

On the CAPT and F/O PFDs, the ramp test starts. The speed scale moves up to 2500 ft. and stops after approximately 1 minute 40 seconds. On the MCDU, the RAMP TEST PROCESSING message comes into view. When the altitude increases: - on the CAPT and F/O PFDs: . when the altitude is between 0 and 160 ft., the horizon line moves down. The elevation scale comes into view. . when the altitude is between 0 and 570 ft., the red ribbon adjacent to the altitude scale moves down and then it goes out of view.

- push the line key adjacent to the RETURN indication.

On the MCDU: - the LRRA1 (LRRA2) page comes into view.

R

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Page 512 Nov 01/09

**ON A/C 001-004, Post SB

34-1171 For A/C 001-004,

Subtask 34-42-00-730-050-A A. System Test NOTE : This note is for RA1 test, for RA2 test you must open the circuit ____ breaker 1SA1. If you do this test in descent, you can make sure that the auto call out announcements are correct. To do this, set a small SLOPE. To decrease the total test time, increase the speed of the altitude change. To do this, adjust SLOPE to a larger value or set a lower STOP ALT. NOTE : This test is the radio altimeter ramp test. For auto call-out ____ announcement, do the operational test of the automatic call-out (Ref. TASK 31-50-00-710-006). ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU: - push the line the RA1 (RA2) push the line the RAMP TEST

key adjacent to indication. Then key adjacent to indication.

On the MCDU: - the RA1 (RA2) RAMP TEST page comes into view with these indications: TWO SUCCESSIVES RAMPS: RAMP1: 500-50FT (10FT/S) RAMP2: 50-0FT (3FT/S) MAKE SURE THAT AUTO CALL OUT ALTITUDES ARE CORRECTLY ANNOUNCED On the CAPT (F/O) PFD: - the ramp test starts. The speed scale moves down from 500 to 0 ft. and stops after approximately 1 minute. - when the altitude is between 500 and 0 ft., the red ribbon adjacent to the altitude scale moves up. On the MCDU: - at the end of the test, the TEST OK page comes into view.

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Page 513 Nov 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the RA1 (RA2) page comes into view. the RETURN indication. **ON A/C ALL 5. Close-up ________ R Subtask 34-42-00-860-053 A. Put the aircraft back to its initial configuration. (1) On the center pedestral, on the MCDU, push the line key adjacent to the RETURN indication until the CFDS page comes into view. (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (3) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items. R

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Page 514 Nov 01/09

TASK 34-42-00-710-001 Warning Test of the Radio Altimeter WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Test of the operation of the RA warning. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 27-80-00-866-004 27-80-00-866-005 31-60-00-860-001 31-60-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Extending the Slats on the Ground Retracting the Slats on the Ground EIS Start Procedure EIS Stop Procedure

3. __________ Job Set-up Subtask 34-42-00-860-050 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

  R EFF : ALL  34-42-00    CES

 

Page 515 Nov 01/09

Subtask 34-42-00-865-051 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RAD ALTM/2 1SA2 K12 121VU COM NAV/RAD ALTM/1 1SA1 K11 4. Procedure _________ Subtask 34-42-00-710-051 A. Test of the Operation of the RA Warning ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center pedestal: - move the slat/flap control lever to the position 1 (Ref. TASK 27-80-00-866-004).

The slats extend to the full position.

2. On the rear circuit breaker panel 121VU: - open the circuit breaker 1SA1.

On the CAPT and F/O PFDs: - the altitude 0 ft. stays in view. On the upper ECAM display unit: - the NAV RA1 FAULT indication comes into view. On the CAPT and F/O glareshield panels: - the MASTER CAUT lights come on. In the loud speakers: - you can hear the single chime.

- open the circuit breaker 1SA2.

On the CAPT and F/O PFDs: - the altitude 0 ft. goes out of view. - the RA warning comes into view. On the upper ECAM display unit: - the NAV RA1 FAULT indication stays in view. - the NAV RA2 FAULT indication comes into view.

  EFF : ALL  34-42-00   R  CES

 

Page 516 Nov 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT and F/O glareshield panels: - the MASTER CAUT lights stay on. In the loud speakers: - you can hear the single chime. 3. On the rear circuit breaker panel 121VU: - close the circuit breakers 1SA1 and 1SA2.

On the CAPT and F/O PFDs: - the RA warning goes out of view after 15 seconds. - the altitude 0 ft. comes into view. On the upper ECAM display unit: - the NAV RA1 FAULT and NAV RA2 FAULT indications go out of view.

5. Close-up ________ Subtask 34-42-00-860-051 A. Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2) Put the aircraft in clean configuration (Ref. TASK 27-80-00-866-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-42-00   R  CES

 

Page 517 Nov 01/09

ANTENNA - RADIO ALTIMETER (5SA1,5SA2,6SA1,6SA2) - REMOVAL/INSTALLATION ______________________________________________________________________ TASK 34-42-11-000-001 Removal of the Radio Altimeter Antennas 5SA1, 5SA2, 6SA1, 6SA2 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) 3 SCRAPER - NON METALLIC

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-42-00-861-001 R

Energize the Ground Service Network from the External Power

**ON A/C 061-099, 102-105, 151-199, 201-220, 34-42-11-991-001-A

R

Fig. 401

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-524, 34-42-11-991-001-B

R

**ON A/C 525-526, 528-599,

R

34-42-11-991-001

Fig. 401A

Fig. 401B

  EFF : ALL  34-42-11    CES

 

Page 401 Feb 01/10

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, 34-42-11-991-003

Fig. 402

**ON A/C 301-399, 34-42-11-991-003-A

Fig. 402A

**ON A/C ALL 3. __________ Job Set-up Subtask 34-42-11-861-050 A. Energize the ground service network (Ref. TASK 24-42-00-861-001). Subtask 34-42-11-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 5SA1(6SA1) 121VU COM NAV/RAD ALTM/1 1SA1 K11 FOR 5SA2(6SA2) 121VU COM NAV/RAD ALTM/2 1SA2 K12 4. Procedure _________ R

**ON A/C 061-099, 102-105, 151-199, 201-220, (Ref. Fig. 401/TASK 34-42-11-991-001-A)

R

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-524, (Ref. Fig. 401A/TASK 34-42-11-991-001-B)

  EFF : ALL  34-42-11    CES

 

Page 402 Feb 01/10

Radio Altimeter Antennas Figure 401/TASK 34-42-11-991-001-A   R EFF : 061-099, 102-105, 151-199, 201-220,  34-42-11    CES

 

Page 403 Feb 01/10

Radio Altimeter Antennas Figure 401A/TASK 34-42-11-991-001-B   R EFF : 106-149, 221-249, 251-299, 301-399,  34-42-11 401-499, 501-509, 511-524,   CES

 

Page 404 Feb 01/10

R R R R

**ON A/C 525-526, 528-599, (Ref. Fig. 401B/TASK 34-42-11-991-001) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 402/TASK 34-42-11-991-003) **ON A/C 301-399, (Ref. Fig. 402A/TASK 34-42-11-991-003-A)

R **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, Subtask 34-42-11-020-055 R R

A. Removal of the Radio Altimeter Antenna with Teflon Seal and Water Ingress Protection **ON A/C 061-099, 102-105, 151-199, 201-220, (Ref. Fig. 401/TASK 34-42-11-991-001-A)

R

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, NOTE : This new procedure is the same for the radio altimeter antennas ____ 5SA1, 5SA2, 6SA1, 6SA2. (1) Remove the sealant from the heads of the screws (5) with a SCRAPER NON METALLIC. (2) Remove the attachment screws (5) from the antenna (4). (3) Pull the antenna (4) carefully away until you can see the shrink sleeve(11). (4) Remove the sealant from the shrink sleeve (11) with a SCRAPER - NON METALLIC.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-42-11 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 405 Feb 01/10

R R

Radio Altimeter Antennas Figure 401B/TASK 34-42-11-991-001

  R EFF : 525-526, 528-599,  34-42-11    CES

 

Page 406 Feb 01/10

Radio Altimeter Antennas (Alternative) Figure 402/TASK 34-42-11-991-003   R EFF : 001-049, 051-099, 101-149, 151-199,  34-42-11 201-249, 251-299, 401-499, 501-509, 511-526,  528-599, CES

 

Page 407 Feb 01/10

Radio Altimeter Antennas Figure 402A/TASK 34-42-11-991-003-A   R EFF : 301-399,  34-42-11    CES

 

Page 408 Feb 01/10

(5) Carefully remove the shrink sleeves (11),(10) and (12) from the connectors (2) and (3). (6) Temporarily attach the coaxial connector (2) on the external side of the fuselage. NOTE : The connector (2) could move inside the hole, if is not ____ blocked. (7) Disconnect the coaxial connector (2) from the antenna connector (3). (8) Remove the antenna (4). (9) Do an inspection of the component interface and/or the adjacent area. (10) Make sure that: - there is no rust on the antenna connector (3), - there is no erosion, corrosion or scratches at the bottom of the antenna (4), - there are no paint or paint flaking at the bottom antenna (4) area, - the alignment marks are fuly visible. Discard all parts with damages or stains of paint and use new ones. R

(11) Put blanking caps on the disconnected electrical connector(s). (12) Remove the O-ring (6). NOTE : If the O-ring is in a good condition you can keep it for the ____ subsequent installation. (13) Remove the teflon gasket (8).

R R

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-42-11-020-055-A

R R

A. Removal of the Radio Altimeter Antenna with Teflon Seal and Water Ingress Protection **ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-524, (Ref. Fig. 401A/TASK 34-42-11-991-001-B)

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-42-11 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 409 Feb 01/10

R

**ON A/C 525-526, 528-599,

R R R

(Ref. Fig. 401B/TASK 34-42-11-991-001) **ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, NOTE : This new procedure is the same for the radio altimeter antennas ____ 5SA1, 5SA2, 6SA1, 6SA2. (1) Remove the sealant from the heads of the screws (5) with a SCRAPER NON METALLIC. (2) Remove the attachment screws (5) from the antenna (4). (3) Pull the antenna (4) carefully away until you can see the shrink sleeve(11). (4) Remove the sealant from the shrink sleeve (11) with a SCRAPER - NON METALLIC. (5) Carefully remove the shrink sleeves (11), and (10) from the connectors (2) and (3). (6) Temporarily attach the coaxial connector (2) on the external side of the fuselage. NOTE : The connector (2) could move inside the hole, if is not ____ blocked. (7) Disconnect the coaxial connector (2) from the antenna connector (3). (8) Remove the antenna (4). (9) Do an inspection of the component interface and/or the adjacent area. (10) Make sure that: - there is no rust on the antenna connector (3), - there is no erosion, corrosion or scratches at the bottom of the antenna (4), - there are no paint or paint flaking at the bottom antenna (4) area, - the alignment marks are fuly visible. Discard all parts with damages or stains of paint and use new ones.

R

(11) Put blanking caps on the disconnected electrical connector(s).

  R EFF : 106-149, 221-249, 251-299, 301-399,  34-42-11 401-499, 501-509, 511-526, 528-599,   CES

 

Page 410 Feb 01/10

(12) Remove the O-ring (6). NOTE : If the O-ring is in a good condition you can keep it for the ____ subsequent installation. (13) Remove the teflon gasket (8). R R

**ON A/C 061-099, 102-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

R

Subtask 34-42-11-020-051

R R R R R R R R R

B. Removal of the Radio Altimeter Antenna with Teflon Seal **ON A/C 061-099, 102-105, 151-199, 201-220, (Ref. Fig. 401/TASK 34-42-11-991-001-A) **ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-524, (Ref. Fig. 401A/TASK 34-42-11-991-001-B) **ON A/C 525-526, 528-599, (Ref. Fig. 401B/TASK 34-42-11-991-001) **ON A/C 061-099, 102-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

R R

WARNING : CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE _______ LOCKWIRE CAN CUT OR BLIND YOU.

R R

NOTE : The procedure is the same for the radio altimeter antennas 5SA1, ____ 5SA2, 6SA1, 6SA2.

R

(1) Remove the sealant from the heads of the screws (5) with a SCRAPER NON METALLIC.

R

(2) Remove the attachment screws (5) from the antenna (4).

R R

(3) Pull the antenna (4) carefully away until you can see the coaxial connector (2).

  R EFF : 061-099, 102-149, 151-199, 201-249,  34-42-11 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 411 Feb 01/10

R R

(4) Remove and discard the lockwire from the coaxial connector (2), if installed.

R

(5) Disconnect the coaxial connector (2) from the antenna connector (3).

R

(6) Remove the antenna (4).

R

(7) Put blanking caps on the disconnected electrical connector(s).

R

(8) Remove the O-ring (6).

R R R R R

NOTE : If the O-ring is in a good condition you can keep it for the ____ subsequent installation. (9) Remove the teflon gasket (8). **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, Subtask 34-42-11-020-054 C. Removal of the Radio Altimeter Antenna without Teflon Seal (Ref. Fig. 402/TASK 34-42-11-991-003) WARNING : CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE _______ LOCKWIRE CAN CUT OR BLIND YOU. NOTE : The procedure is the same for the radio altimeter antennas 5SA1, ____ 5SA2, 6SA1, 6SA2. (1) Remove the sealant from the heads of the screws (5) with a SCRAPER NON METALLIC. (2) Remove the attachment screws (5) from the antenna (4). (3) Pull the antenna (4) carefully away until you can see the coaxial connector (2). (4) Remove and discard the lockwire from the coaxial connector (2), if installed. (5) Disconnect the coaxial connector (2) from the antenna connector (3). (6) Remove the antenna (4).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-42-11 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 412 Feb 01/10

(7) Remove the O-ring (6). NOTE : If the O-ring is in a good condition you can keep it for the ____ subsequent installation. R

(8) Put blanking caps on the disconnected electrical connector(s). **ON A/C 301-399, Subtask 34-42-11-020-054-A C. Removal of the Radio Altimeter Antenna without Teflon Seal (Ref. Fig. 402A/TASK 34-42-11-991-003-A) WARNING : CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE _______ LOCKWIRE CAN CUT OR BLIND YOU. NOTE : The procedure is the same for the radio altimeter antennas 5SA1, ____ 5SA2, 6SA1, 6SA2. (1) Remove the sealant from the heads of the screws (5) with a SCRAPER NON METALLIC. (2) Remove the attachment screws (5) from the antenna (4). (3) Pull the antenna (4) carefully away until you can see the coaxial connector (2). (4) Remove and discard the lockwire from the coaxial connector (2), if installed. (5) Disconnect the coaxial connector (2) from the antenna connector (3). (6) Remove the antenna (4). (7) Remove the O-ring (6). NOTE : If the O-ring is in a good condition you can keep it for the ____ subsequent installation.

R

(8) Put blanking caps on the disconnected electrical connector(s).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-42-11 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 413 Feb 01/10

**ON A/C ALL TASK 34-42-11-400-001 Installation of the Radio Altimeter Antennas 5SA1, 5SA2, 6SA1, 6SA2 WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN. _______ IF YOU DO: - RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH - WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER. WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R

No specific No specific

2 SCRAPER - NON METALLIC Torque Wrench : range 0.00 to 1.20 m.daN (0.00 to 9.00 lbf.ft)

  EFF : ALL  34-42-11    CES

 

Page 414 Feb 01/10

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------No specific

O-ring P/N 2611-080-07275

R Material No. 07-001 NO LONGER AVAILABLE RPLD BY 07001B/D/F (Ref. 20-31-00) R Material No. 08-092 Material No. 09-001B Material No. 09-001D Material No. 09-008E Material No. 09-016

C Z-15.243 ADHESIVE/SEALANT (Ref. 20-31-00) USA AMS-S-8802 TYPE 1 CLASS A FUEL TANK SEALANT (Ref. 20-31-00) F ASNA 4157 FUEL TANK SEALANTPOLYSULFIDE (Ref. 20-31-00) USA AMS 3277 QUICK REPAIR FUEL TA NK SEALANT TEMPORARY (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00)

R Material No. 11-010 Material No. 16-003 R R

Material No. 19-003

USA TT-I-735 GRADE A ISOPROPYL ALCOHOL (Ref. 20-31-00) F ASNB70720 COATING (OBSOLETE USE 16-021) (Ref. 20-31-00) USA AMS 3819 LINT-FREE COTTON CLOTH (Ref. 20-31-00)

C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------8 8 8 8 8 8 8

teflon-gasket teflon-gasket teflon-gasket teflon-gasket teflon-gasket teflon-gasket teflon-gasket

34-42-04 34-42-04 34-42-04 34-42-04 34-42-04 34-42-04 34-42-04

  EFF : ALL  34-42-11    CES

 

05A-035 05B-035 05B-035A 05C-035 06B-025 06C-025 06C-025A

Page 415 Feb 01/10

D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-912-005 24-42-00-861-001 24-42-00-862-001

Electrical Bonding of Antennas With Conductive Bolts. Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power BITE Test of the Radio Altimeter

34-42-00-740-002 R

**ON A/C 061-099, 102-105, 151-199, 201-220, 34-42-11-991-001-A

R

Fig. 401

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-524, 34-42-11-991-001-B

Fig. 401A

R

**ON A/C 525-526, 528-599,

R

34-42-11-991-001

R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, 34-42-11-991-003

Fig. 401B

Fig. 402

**ON A/C 301-399, 34-42-11-991-003-A R

**ON A/C ALL

R

34-42-11-991-004

Fig. 402A

Fig. 403

  EFF : ALL  34-42-11    CES

 

Page 416 Feb 01/10

R 3. __________ Job Set-up Subtask 34-42-11-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001). (2) Make sure that the aircraft is in the same configuration as for the removal task. (3) Make sure that the parts retained from the removed component are clean and in the correct condition. Subtask 34-42-11-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 5SA1(6SA1) 121VU COM NAV/RAD ALTM/1 1SA1 K11 FOR 5SA2(6SA2) 121VU COM NAV/RAD ALTM/2 1SA2 K12 4. Procedure _________ R

**ON A/C 061-099, 102-105, 151-199, 201-220, (Ref. Fig. 401/TASK 34-42-11-991-001-A)

R

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-524, (Ref. Fig. 401A/TASK 34-42-11-991-001-B)

R

**ON A/C 525-526, 528-599,

R

(Ref. Fig. 401B/TASK 34-42-11-991-001)

  EFF : ALL  34-42-11    CES

 

Page 417 Feb 01/10

R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 402/TASK 34-42-11-991-003) **ON A/C 301-399, (Ref. Fig. 402A/TASK 34-42-11-991-003-A) **ON A/C ALL WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE THE SPECIAL _______ MATERIAL. THIS MATERIAL IS DANGEROUS.

R R

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 301-399, 501-509, 511-526, 528-599,

R

Subtask 34-42-11-140-052

R R

A. Preparation for Installation of Radio Altimeter Antenna with Teflon Seal and Water Ingress Protection

R R

(1) Remove the used sealant from the fuselage structure (1) with a SCRAPER - NON METALLIC.

R R R

(2) Clean the component interface and/or the adjacent area with CLEANING AGENTS (Material No. 11-010) and the MISCELLANEOUS (Material No. 19003).

R

(3) Do an inspection of the component interface and/or the adjacent area.

R R R

NOTE : Make sure that the antenna-attachment screw-head recesses have ____ no signs of paint, corrosion or sealant because the antenna electrical bonding is made through the attachment screws.

R

(4) Make sure that the O-ring (6) is in good condition.

R

NOTE : If necessary install a new O-ring. ____

R

(5) Install the O-ring P/N 2611-080-07275 (6).

R

NOTE : If necessary install a new teflon-gasket. ____

R

(6) Install the teflon-gasket (8) to the antenna (4).

  R EFF : ALL  34-42-11    CES

 

Page 418 Feb 01/10

R

**ON A/C 151-199, 401-499,

R

Subtask 34-42-11-140-052-A

R R

A. Preparation for Installation of Radio Altimeter Antenna with Teflon Seal and Water Ingress Protection

R R

(1) Remove the used sealant from the fuselage structure (1) with a SCRAPER - NON METALLIC.

R R R

(2) Clean the component interface and/or the adjacent area with CLEANING AGENTS (Material No. 11-010) and the MISCELLANEOUS (Material No. 19003).

R

(3) Do an inspection of the component interface and/or the adjacent area.

R R R

NOTE : Make sure that the antenna-attachment screw-head recesses have ____ no signs of paint, corrosion or sealant because the antenna electrical bonding is made through the attachment screws.

R

(4) Make sure that the O-ring (6) is in good condition.

R

NOTE : If necessary install a new O-ring. ____

R

(5) Install the O-ring P/N 2611-080-07275 (6).

R

NOTE : If necessary install a new teflon-gasket. ____

R R R

(6) Install the teflon-gasket (8) to the antenna (4). **ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-42-11-420-055-B

R R

B. Installation of the Radio Altimeter Antenna with Teflon Seal and Water Ingress Protection **ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-524, (Ref. Fig. 401A/TASK 34-42-11-991-001-B)

  R EFF : 106-149, 151-199, 221-249, 251-299,  34-42-11 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 419 Feb 01/10

R

**ON A/C 525-526, 528-599,

R R R

(Ref. Fig. 401B/TASK 34-42-11-991-001) **ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, WARNING : MAKE SURE THAT THERE IS A GOOD FLOW OF AIR THROUGH THE WORK _______ AREA WHEN YOU USE SPECIAL MATERIALS. IF YOU GET ONE OF THESE MATERIALS ON YOUR SKIN, IN YOUR MOUTH OR IN YOUR EYES : -FLUSH IT AWAY WITH A FLOW OF CLEAN WATER FOR BETWEEN 10 AND 15 MINUTES. -GET IMMEDIATE MEDICAL AID IF IRRITATION OCCURS. DO NOT BREATHE THE FUMES FROM THE MATERIAL. DO NOT SMOKE WHEN YOU USE THE MATERIAL. DO NOT USE THE MATERIAL NEAR A FLAME, SPARKS OR SOURCES OF HEAT. THESE MATERIALS ARE DANGEROUS : THEY ARE POISONOUS, FLAMMABLE AND SKIN IRRITANTS. (1) Push the shrink sleeve (11) ABS0916B08 in position below the thread (12) of the antenna connector (3) and shrink it.

R

(2) Remove the blanking caps from the electrical connector(s). (3) Make sure that the electrical connectors are clean and in the correct condition. (4) Connect the coaxial connector (2) to the antenna connector (3). (5) TORQUE the coaxial connector (2) to 0.265 m.daN (23.45 lbf.in). (6) Apply BONDING AND ADHESIVE COMPOUNDS (Material No. 08-092) (10) around the cable. (7) Apply sealant: WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE _______ THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Apply some sealant SEALANTS (Material No. 09-001B) or SEALANTS (Material No. 09-001D) over the ends of the shrink sleeve (11) and also on the antenna body (inner part up to the O-ring).

  R EFF : 106-149, 221-249, 251-299, 301-399,  34-42-11 401-499, 501-509, 511-526, 528-599,   CES

 

Page 420 Feb 01/10

(b) Apply sealant SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008E) on the periphery of the antenna flange an approximately 3 mm (0.1181 in.) wide interface. (8) Put the antenna (4) in position. (9) Make sure that the FWD sign or the datum mark on the antenna points are in the direction of flight. (10) Install the screws (5). (11) Prepare for electrical bonding (Ref. TASK 20-28-00-912-005). NOTE : The antenna mounting screws give the electrical bonding ____ between the antenna and the fuselage structure. (12) TORQUE the screws (5) to between 0.3 and 0.35 m.daN (26.54 and 30.97 lbf.in) in a diagonally opposite sequence. (13) Remove sealant: WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE _______ THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Remove the unwanted sealant with a SCRAPER - NON METALLIC. (14) Make sure that the bonding contact resistance between the antenna (4) and the fuselage structure (1) is not higher than 5 milliohms (Ref. TASK 20-28-00-912-005). (15) Apply the sealant: WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE _______ THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Apply a sealant bead with SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008E) around the antenna (4). (16) Apply SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09008E) to the heads of the screws (5).

  R EFF : 106-149, 221-249, 251-299, 301-399,  34-42-11 401-499, 501-509, 511-526, 528-599,   CES

 

Page 421 Feb 01/10

(17) Make the contour of the sealant: WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE _______ THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Make the contour of the sealant on the screws (5) and around the antenna (4) smooth. (18) Let the sealant cure. NOTE : If the cure time of the sealant will cause a flight delay, the ____ aircraft can operate without the sealant for a maximum period of 24 hours from installation of the antenna. Before application of the sealant, it is necessary to make sure that the surfaces are clean and in the correct condition (no moisture, dust, etc.). (19) Apply to the sealant: WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE _______ THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the base of the antenna (4). (20) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001) to the sealant on the head of the screws (5). NOTE : It is not mandatory to paint the sealant around the base of ____ the antenna and on the head of the screws.

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Page 422 Feb 01/10

R

**ON A/C ALL

R

Subtask 34-42-11-420-056

R R R

C. Installation of the Radio Altimeter Antenna with Teflon Seal and Water Ingress Protection (Ref. Fig. 403/TASK 34-42-11-991-004)

R R R R R R R R R R R R R

WARNING : MAKE SURE THAT THERE IS A GOOD FLOW OF AIR THROUGH THE WORK _______ AREA WHEN YOU USE SPECIAL MATERIALS. IF YOU GET ONE OF THESE MATERIALS ON YOUR SKIN, IN YOUR MOUTH OR IN YOUR EYES : -FLUSH IT AWAY WITH A FLOW OF CLEAN WATER FOR BETWEEN 10 AND 15 MINUTES. -GET IMMEDIATE MEDICAL AID IF IRRITATION OCCURS. DO NOT BREATHE THE FUMES FROM THE MATERIAL. DO NOT SMOKE WHEN YOU USE THE MATERIAL. DO NOT USE THE MATERIAL NEAR A FLAME, SPARKS OR SOURCES OF HEAT. THESE MATERIALS ARE DANGEROUS : THEY ARE POISONOUS, FLAMMABLE AND SKIN IRRITANTS.

R R

(1) Push the shrink sleeve (12) ABS0916B07 in position below the thread (14) of the antenna connector (3) and shrink it.

R

(2) Push the shrink sleeve (11) ABS0916B08 over the coaxial cable.

R

(3) Remove the blanking caps from the electrical connector(s).

R R

(4) Make sure that the electrical connectors are clean and in the correct condition.

R

(5) Connect the coaxial connector (2) to the antenna connector (3).

R

(6) TORQUE the coaxial connector (2) to 0.265 m.daN (23.45 lbf.in).

R R

(7) Apply BONDING AND ADHESIVE COMPOUNDS (Material No. 08-092) (10) around the cable.

R R

(8) Push the shrink sleeve (12) ABS0916B08 in position over both connectors (2) and (3) and shrink it.

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Page 423 Feb 01/10

R R

Radio Altimeter Antennas with Teflon Seal and Water Ingress Protection Figure 403/TASK 34-42-11-991-004

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Page 424 Feb 01/10

R

(9) Apply sealant:

R R R

WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE _______ THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK.

R R R

(a) Apply some sealant SEALANTS (Material No. 09-001B) or SEALANTS (Material No. 09-001D) over the ends of the shrink sleeve (11) and also on the antenna body (inner part up to the O-ring).

R R R

(b) Apply sealant SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008E) on the periphery of the antenna flange an approximately 3 mm (0.1181 in.) wide interface.

R

(10) Put the antenna (4) in position.

R R

(11) Make sure that the FWD sign or the datum mark on the antenna points are in the direction of flight.

R

(12) Install the screws (5).

R

(13) Prepare for electrical bonding (Ref. TASK 20-28-00-912-005).

R R

NOTE : The antenna mounting screws give the electrical bonding ____ between the antenna and the fuselage structure.

R R

(14) TORQUE the screws (5) to between 0.3 and 0.35 m.daN (26.54 and 30.97 lbf.in) in a diagonally opposite sequence.

R

(15) Remove the unwanted sealant from the antenna:

R R R

WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE _______ THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK.

R

(a) Remove the unwanted sealant with a SCRAPER - NON METALLIC.

R R R

(16) Make sure that the bonding contact resistance between the antenna (4) and the fuselage structure (1) is not higher than 5 milliohms (Ref. TASK 20-28-00-912-005).

R

(17) Apply a new sealant on the antenna:

R R R

WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE _______ THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK.

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Page 425 Feb 01/10

R R

(a) Aplly a sealant bead with SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008E) around the antenna (4).

R R

(18) Apply SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09008E) to the heads of the screws (5).

R

(19) Make the contour of the sealant:

R R R

WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE _______ THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK.

R R

(a) Make the contour of the sealant on the screws (5) and around the antenna (4) smooth.

R

(20) Let the sealant cure.

R R R R R R

NOTE : If the cure time of the sealant will cause a flight delay, the ____ aircraft can operate without the sealant for a maximum period of 24 hours from installation of the antenna. Before application of the sealant, it is necessary to make sure that the surfaces are clean and in the correct condition (no moisture, dust, etc.).

R

(21) Apply paint to the sealant:

R R R

WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE _______ THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK.

R R

(a) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the base of the antenna (4).

R R

(b) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07-001) to the sealant on the head of the screws (5).

R R

NOTE : It is not mandatory to paint the sealant around the base ____ of the antenna and on the head of the screws.

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Page 426 Feb 01/10

R Subtask 34-42-11-865-052 R

D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 5SA1(6SA1) 1SA1 FOR 5SA2(6SA2) 1SA2 Subtask 34-42-11-740-050

R

E. Do the BITE test of the radio altimeter system (Ref. TASK 34-42-00-740002). 5. Close-up ________ Subtask 34-42-11-862-050 A. De-energize the ground service network (Ref. TASK 24-42-00-862-001).

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Page 427 Feb 01/10

TRANSCEIVER - RADIO ALTIMETER (2SA1,2SA2) - REMOVAL/INSTALLATION ________________________________________________________________ TASK 34-42-33-000-001 Removal of the Radio Altimeter Transceiver 2SA1 and 2SA2 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 2 m (6 ft. 7 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-42-00-861-001 52-30-00-860-001 34-42-33-991-001

Energize the Ground Service Network from the External Power Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Fig. 401

3. __________ Job Set-up Subtask 34-42-33-861-050 A. Energize the ground service network (Ref. TASK 24-42-00-861-001)

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Page 401 Feb 01/98

Subtask 34-42-33-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 2SA1 121VU COM NAV/RAD ALTM/1 1SA1 K11 FOR 2SA2 121VU COM NAV/RAD ALTM/2 1SA2 K12 Subtask 34-42-33-010-050 C. Get Access (1) Open the AFT Cargo Door 826. (Ref. TASK 52-30-00-860-001) (2) Put the access platform at the aft cargo door 826. R

(3) Remove the access panel 152GW. 4. Procedure _________ (Ref. Fig. 401/TASK 34-42-33-991-001) Subtask 34-42-33-020-051 A. Removal of Radio Altimeter Transceiver NOTE : The removal procedure is the same for the radio altimeter ____ transceiver 2SA1 and 2SA2. (1) Loosen the knurled nuts (3) and lower the fasteners.

R

(2) Carefully remove the transceiver (1) from the rack (2).

R R

NOTE : Make sure that you do not damage the electrical connector ____ pins.

R (3) Put blanking caps on the disconnected electrical connectors.

  EFF : ALL  34-42-33    CES

 

Page 402 Aug 01/98

R

Radio Altimeter Transceiver Figure 401/TASK 34-42-33-991-001

  EFF : ALL  34-42-33    CES

 

Page 403 Aug 01/98

TASK 34-42-33-400-001 Installation of the Radio Altimeter Transceiver 2SA1 and 2SA2 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 2 m (6 ft. 7 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------22-97-00-710-001 24-42-00-861-001 24-42-00-862-001 34-42-00-740-002 52-30-00-860-001 52-30-00-860-002 34-42-33-991-001

Operational Test of the LAND CAT III Capability Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power BITE Test of the Radio Altimeter Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Fig. 401

3. __________ Job Set-up Subtask 34-42-33-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001) (2) Make sure that the AFT cargo-compartment door (Ref. TASK 52-30-00860-001) is open.

  EFF : ALL  34-42-33    CES

 

Page 404 Feb 01/98

R

(3) Make sure that the access panel 152GW is removed. (4) Make sure that the access platform is in position at the Aft cargo door 826. Subtask 34-42-33-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 2SA1 121VU COM NAV/RAD ALTM/1 1SA1 K11 FOR 2SA2 121VU COM NAV/RAD ALTM/2 1SA2 K12 4. Procedure _________ (Ref. Fig. 401/TASK 34-42-33-991-001) Subtask 34-42-33-420-050 A. Installation of the Radio Altimeter Transceiver NOTE : The installation procedure is the same for the radio altimeter ____ transceiver 2SA1 and 2SA2. (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors. (4) Make sure that the electrical connectors are clean and in the correct condition. (5) Carefully install the transceiver (1) into the rack (2). NOTE : Make sure that the transceiver is correctly aligned to prevent ____ damage to the electrical connectors (4). (6) Lift the fasteners and tighten the knurled nuts (3) until the transceiver (1) is correctly attached.

  EFF : ALL  34-42-33    CES

 

Page 405 Aug 01/98

Subtask 34-42-33-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 2SA1 1SA1 FOR 2SA2 1SA2 Subtask 34-42-33-740-050 C. Do the BITE test of the radio altimeter (Ref. TASK 34-42-00-740-002). NOTE : If the aircraft is operated in actual CAT 3 conditions, you must ____ also do the LAND CAT III capability test: (Ref. TASK 22-97-00-710001). 5. Close-up ________ Subtask 34-42-33-860-051 A. Aircraft Maintenance Configuration R R

(1) On the FTL CTL panel 23VU, push the FAC1 pushbutton switch (the OFF legend goes off.

R R

(2) On the FTL CTL panel 24VU, push the ELAC2 pushbutton switch (the OFF legend goes off. Subtask 34-42-33-410-052 B. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the access panel 152GW. (3) Remove the access platform(s). (4) Close the AFT Cargo Door 826 (Ref. TASK 52-30-00-860-002).

  EFF : ALL  34-42-33    CES

 

Page 406 Feb 01/02

Subtask 34-42-33-862-050 C. De-energize the ground service network (Ref. TASK 24-42-00-862-001)

  EFF : ALL  34-42-33    CES

 

Page 407 Feb 01/98

FAN - RADIO ALTIMETER TRANSCEIVER (3SA1,3SA2) - REMOVAL/INSTALLATION ____________________________________________________________________ TASK 34-42-45-000-001 Removal of the Radio Altimeter-Transceiver Fan 3SA1 (3SA2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 2 m (6 ft. 7 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-42-00-861-001 52-30-00-860-001 34-42-45-991-001

Energize the Ground Service Network from the External Power Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Fig. 401

3. __________ Job Set-up Subtask 34-42-45-861-050 A. Energize the ground service network (Ref. TASK 24-42-00-861-001)

  EFF : ALL  34-42-45    CES

 

Page 401 Feb 01/98

Subtask 34-42-45-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3SA1 121VU COM NAV/RAD ALTM/1 1SA1 K11 FOR 3SA2 121VU COM NAV/RAD ALTM/2 1SA2 K12 Subtask 34-42-45-010-050 C. Get Access (1) Open the AFT Cargo Door 826 (Ref. TASK 52-30-00-860-001). (2) Put the access platform at the aft cargo door 826. (3) Remove the access panel 152HW. 4. Procedure _________ (Ref. Fig. 401/TASK 34-42-45-991-001) Subtask 34-42-45-020-052 A. Removal of the Radio Altimeter Transceiver Fan NOTE : The procedure is the same for the radio altimeter-transceiver fans ____ 3SA1 and 3SA2. (1) Disconnect the electrical connector (8). (2) Remove the screws (2), the washers (3) and remove the fan assembly (1). (3) Remove the nuts (6), the washers (5), the bolts (4), and remove the cover (7). (4) Disconnect the electrical connections (13). (5) Put blanking caps on the disconnected electrical connectors. (6) Remove the nuts (11), the washers (10) and the bolts (9).

  EFF : ALL  34-42-45    CES

 

Page 402 Feb 01/98

Radio Altimeter-Transceiver Fan. Figure 401/TASK 34-42-45-991-001   EFF : ALL  34-42-45    CES

 

Page 403 Feb 01/98

(7) Remove the blower (12).

  EFF : ALL  34-42-45    CES

 

Page 404 Feb 01/98

TASK 34-42-45-400-001 Installation of the Radio Altimeter-Transceiver Fan 3SA1 (3SA2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 2 m (6 ft. 7 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-42-00-861-001 24-42-00-862-001 R R

34-42-00-750-001 52-30-00-860-001 52-30-00-860-002

Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Detailed Inspection and Operational Check of the Radio Altimeter Fan Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

3. __________ Job Set-up Subtask 34-42-45-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001) (2) Make sure that the Aft cargo-compartment door (Ref. TASK 52-30-00860-001) is open.

  EFF : ALL  34-42-45    CES

 

Page 405 Aug 01/02

(3) Make sure that the access panel 152HW is removed. (4) Make sure that the access platform is in position at the Aft cargo door 826. Subtask 34-42-45-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3SA1 121VU COM NAV/RAD ALTM/1 1SA1 K11 FOR 3SA2 121VU COM NAV/RAD ALTM/2 1SA2 K12 4. Procedure _________ Subtask 34-42-45-420-050 A. Installation of the Radio Altimeter Transceiver Fan (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors. (4) Make sure that the electrical connectors are clean and in the correct condition. (5) Install the blower (12) with the bolts (9), the washers (10) and the nuts (11). (6) Connect the electrical connections (13). (7) Install the cover (7) with the bolts (4), the washers (5) and the nuts (6). (8) Install the fan assembly (1) with the screws (2) and the washers (3). (9) Connect the electrical connector (8).

  EFF : ALL  34-42-45   R  CES

 

Page 406 Aug 01/02

Subtask 34-42-45-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 3SA1 1SA1 FOR 3SA2 1SA2 Subtask 34-42-45-750-050 C. Do the fan test of the radio altimeter system (Ref. TASK 34-42-00-750001). 5. Close-up ________ Subtask 34-42-45-410-050 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the access panel 152HW. (3) Remove the access platform(s). (4) Close the AFT Cargo Door 826 (Ref. TASK 52-30-00-860-002). Subtask 34-42-45-862-050 B. De-energize the ground service network (Ref. TASK 24-42-00-862-001)

  EFF : ALL  34-42-45    CES

 

Page 407 Feb 01/98

FAN - RADIO ALTIMETER TRANSCEIVER (3SA1,3SA2) - CLEANING/PAINTING _________________________________________________________________ TASK 34-42-45-100-001 Cleaning of the Radio Altimeter Transceiver Fan 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

air blower circuit breaker(s) safety clip(s) soft brush access platform 2 m (6 ft. 7 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------22-97-00-710-001 24-42-00-861-001 24-42-00-862-001 34-42-00-740-002 34-42-00-750-001 34-42-33-000-001 34-42-33-400-001 34-42-45-000-001 34-42-45-400-001 52-30-00-860-001

Operational Test of the LAND CAT III Capability Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power BITE Test of the Radio Altimeter Detailed Inspection and Operational Check of the Radio Altimeter Fan Removal of the Radio Altimeter Transceiver 2SA1 and 2SA2 Installation of the Radio Altimeter Transceiver 2SA1 and 2SA2 Removal of the Radio Altimeter-Transceiver Fan 3SA1 (3SA2) Installation of the Radio Altimeter-Transceiver Fan 3SA1 (3SA2) Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

  EFF : ALL  34-42-45    CES

 

Page 701 Aug 01/02

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------52-30-00-860-002

Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

3. __________ Job Set-up Subtask 34-42-45-861-051 A. Energize the ground service network (Ref. TASK 24-42-00-861-001) Subtask 34-42-45-865-053 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3SA1 121VU COM NAV/RAD ALTM/1 1SA1 K11 FOR 3SA2 121VU COM NAV/RAD ALTM/2 1SA2 K12 Subtask 34-42-45-010-051 C. Get Access (1) Open the AFT Cargo Door 826 (Ref. TASK 52-30-00-860-001). (2) Put the access platform at the aft cargo door 826. (3) Remove the access panel 152HW. 4. Procedure _________ Subtask 34-42-45-020-053 A. Remove the radio altimeter units (1) Remove the radio altimeter transceiver (Ref. TASK 34-42-33-000-001). (2) Remove the radio altimeter transceiver fan (Ref. TASK 34-42-45-000001).

  EFF : ALL  34-42-45    CES

 

Page 702 Aug 01/02

Subtask 34-42-45-100-052 B. Cleaning (1) Use a soft brush and/or an air blower to clean the fan or the fan housing. NOTE : Make sure that the fan and the fan housing are blocked when ____ you use an air blower. Cleaning with an air blower can cause exessive fan rotation speed and thus fan failure. Subtask 34-42-45-420-051 C. Install the radio altimeter units (1) Install the radio altimeter transceiver fan (Ref. TASK 34-42-45-400001). (2) Install the radio altimeter transceiver (Ref. TASK 34-42-33-400-001). Subtask 34-42-45-865-054 D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 3SA1 1SA1 FOR 3SA2 1SA2 Subtask 34-42-45-710-051 E. Do the test (1) Do the fan test of the radio altimeter system (Ref. TASK 34-42-00750-001). (2) Do the Bite test of the radio altimeter (Ref. TASK 34-42-00-740-002). NOTE : If the aircraft is operated in actual CAT 3 conditions, you ____ must also do the LAND CAT III capabillity test (Ref. TASK 2297-00-710-001).

  EFF : ALL  34-42-45    CES

 

Page 703 Aug 01/02

5. Close-up ________ Subtask 34-42-45-410-052 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the access panel 152HW. (3) Remove the access platform(s). (4) Close the AFT Cargo Door 826 (Ref. TASK 52-30-00-860-002). Subtask 34-42-45-862-051 B. De-energize the ground service network (Ref. TASK 24-42-00-862-001)

  EFF : ALL  34-42-45    CES

 

Page 704 Aug 01/02

TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS) - DESCRIPTION AND OPERATION _____________________________________________________________________ 1. General _______ **ON A/C 001-049, 101-105, 151-199, 208-209, A. Presentation The TCAS II (Traffic Collision Avoidance System) is an optional system whose function is to detect and display aircraft in the immediate vicinity and to provide the flight crew with indications to avoid these intruders by changing the flight path in the vertical plane only. The TCAS periodically interrogates their transponders, computes their trajectories and constantly determines their potential threat. The acquisition of their signals is achieved by means of two transmit/receive antennas, one located on the underside of the fuselage and the other on the top. The system can establish individualized communications with each aircraft through ATC/Mode S transponders, thus permitting operation in dense traffic areas while avoiding an overload of radio-electric transmissions that would result from a general all-intruder response. The TCAS II system is designed to provide the air traffic control system with an additional possibility. It usually operates independently but may be controlled from ground stations. The TCAS has the capability to communicate with ATCRBS (Air Traffic Control Radar Beacon System) ground stations equipped with the Mode S system to indicate to them the vertical maneuver orders presented to the aircraft pilot. This information can facilitate the task of the ground station controller who, in turn, can modify the TCAS operating mode and cancel the avoidance orders if he deems it necessary for safety. The system maintains surveillance within a sphere determined by the transmit power and receiver sensitivity of the TCAS computer. The area in which a threat is imminent depends on the speed and path of the own A/C and the threat A/C. There is an area defined as TAU within the surveillance arc which represents the minimum time the flight crew needs to discern a collision threat and take evasive action. The TCAS detection capability covers an area of 30 NM in range and plus or minus 9900 ft in altitude but display range is authorized up to plus or minus 2700 ft in altitude. (Ref. Fig. 001)

  R EFF : ALL  34-43-00 Page 1   Config-1 Nov 01/09  CES

 

TCAS - Surveillance and Display Figure 001   R EFF : 001-049, 051-099, 101-105, 151-199,  34-43-00 Page 2 208-209, 251-299,  Config-1 Nov 01/09  CES

 

R

**ON A/C 051-099, 251-299, A. Presentation The TCAS II (Traffic Collision Avoidance System) is a system whose function is to detect and display aircraft in the immediate vicinity and to provide the flight crew with indications to avoid these intruders by changing the flight path in the vertical plane only. TCAS change 7 has been mandatory in Europe since year 2000. The TCAS periodically interrogates their transponders, computes their trajectories and constantly determines their potential threat. Their acquisition is achieved by means of two transmit/receive antennas, one located on the underside of the fuselage and the other on the top. The system can establish individualized communications with each aircraft through ATC/Mode S transponders, thus permitting operation in dense traffic areas while avoiding an overload of radio-electric transmissions that would result from a general all-intruder response. The TCAS II system is designed to provide the air traffic control system with an additional possibility: it usually operates independently but may be also controlled from ground stations. The TCAS has the capability to communicate with ATCRBS (Air Traffic Control Radar Beacon System) ground stations equipped with the Mode S system to indicate to them the vertical maneuver orders presented to the aircraft pilot. This information can facilitate the task of the ground station controller who, in turn, can modify the TCAS operating mode and cancel the avoidance orders if he deems it necessary for safety. The system maintains surveillance within a sphere determined by the transmit power and receiver sensitivity of the TCAS computer. The area in which a threat is imminent depends on the speed and path of the own A/C and the threat A/C. There is an area defined as TAU (Ref. para. 6.D.(2)) within the surveillance arc which represents the minimum time the flight crew needs to discern a collision threat and take evasive action. The TCAS can track up to 40 intruders at the same time. Its detection capability covers: - in range: an area of 30 NM around the aircraft - in altitude: plus or minus 9900 ft. Display is authorized in three possible ranges: - Above: -2700 ft to 9900 ft - Below: -9900 ft to 2700 ft - Normal: -2700 ft to 2700 ft (Ref. Fig. 001) The description of the system is conform to the RTCA DO 185A change 7.

  R EFF : 051-099, 251-299,  34-43-00 Page 3   Config-1 Nov 01/09  CES

 

R

**ON A/C 201-207,

R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R

A. Presentation The TCAS II (Traffic Collision Avoidance System) is an optional system whose function is to detect and display aircraft in the immediate vicinity and to provide the flight crew with indications to avoid these intruders by changing the flight path in the vertical plane only. The TCAS periodically interrogates their transponders, computes their trajectories and constantly determines their potential threat. The acquisition of their signals is achieved by means of two transmit/receive antennas, one located on the underside of the fuselage and the other on the top. The system can establish individualized communications with each aircraft through ATC/Mode S transponders, thus permitting operation in dense traffic areas while avoiding an overload of radio-electric transmissions that would result from a general all-intruder response. The TCAS II system is designed to provide the air traffic control system with an additional possibility. It usually operates independently but may be controlled from ground stations. The TCAS has the capability to communicate with ATCRBS (Air Traffic Control Radar Beacon System) ground stations equipped with the Mode S system to indicate to them the vertical maneuver orders presented to the aircraft pilot. This information can facilitate the task of the ground station controller who, in turn, can modify the TCAS operating mode and cancel the avoidance orders if he deems it necessary for safety. The current surveillance envelope covers an area of plus or minus 2700 ft in altitude and 14 NM minimum in range, but display range is authorized up to 30 NM in range and plus or minus 1200 ft in altitude. The system maintains surveillance within a sphere determined by the transmit power and receiver sensitivity of the TCAS computer. The area in which a threat is imminent depends on the speed and path of the own A/C and the threat A/C. There is an area defined as TAU within the surveillance arc which represents the minimum time the flight crew needs to discern a collision threat and take evasive action. The TCAS detection capability covers an area of 30 NM in range and plus or minus 9900 ft in altitude but display range is authorized up to plus or minus 1200 ft in altitude. (Ref. Fig. 001A)

  EFF : 201-207,  34-43-00 Page 4   Config-1 May 01/09  CES

 

TCAS - Surveillance and Display Figure 001A   EFF : 051-061, 201-207,  34-43-00 Page 5   Config-1 May 01/09  CES

 

R

**ON A/C 501-509, 511-526, 528-599, A. Presentation The TCAS II (Traffic Collision Avoidance System) is a system whose function is to detect and display aircraft in the immediate vicinity and to provide the flight crew with indications to avoid these intruders by changing the flight path in the vertical plane only. TCAS Change 7 has been mandatory in Europe since year 2000. The TCAS periodically interrogates their transponders, computes their trajectories and constantly determines their potential threat. The acquisition of their signals is achieved by means of two transmit/receive antennas, one located on the underside of the fuselage and the other on the top. The system can establish individualized communications with each aircraft through ATC/Mode S transponders, thus permitting operation in dense traffic areas while avoiding an overload of radio-electric transmissions that would result from a general all-intruder response. The TCAS II system is designed to provide the air traffic control system with an additional possibility. It usually operates independently but may be controlled from ground stations. The TCAS has the capability to communicate with ATCRBS (Air Traffic Control Radar Beacon System) ground stations equipped with the Mode S system to indicate to them the vertical maneuver orders presented to the aircraft pilot. This information can facilitate the task of the ground station controller who, in turn, can modify the TCAS operating mode and cancel the avoidance orders if he deems it necessary for safety. The system maintains surveillance within a sphere determined by the transmit power and receiver sensitivity of the TCAS computer. The area in which a threat is imminent depends on the speed and path of the own A/C and the threat A/C. There is an area defined as TAU within the surveillance arc which represents the minimum time the flight crew needs to discern a collision threat and take evasive action. The TCAS can track up to 40 intruders at the same time. Its detection capability covers: - in range: an area of 60 NM in forward direction, 30 NM in the side quadrants and 20 NM in aft direction. However (in forward direction and on condition that the aircraft is at FL 180 or above, and in an area of low traffic density) the detection capability can cover up to 100 NM - in altitude: plus or minus 9900 ft. Display is authorized in three possible ranges: - Above: -2700 ft to 9900 ft - Below: -9900 ft to 2700 ft - All traffic: -2700 ft to 2700 ft. (Ref. Fig. 001B)

  R EFF : 501-509, 511-526, 528-599,  34-43-00 Page 6   Config-1 Feb 01/10  CES

 

TCAS - Surveillance and Display Figure 001B   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page 7   Config-1 Feb 01/10  CES

 

The TCAS computer can store the ten most recent Resolution Advisory (RA) and the sixty most recent Traffic Advisory (TA) events in its memory with information related to the aircraft involved (range, altitude, bearing, Mode S adress,etc.). These events can be downloaded through a PCMCIA card inserted in the front face of the TCAS computer. The TCAS can also receive and compute passive surveillance Automatic Dependent Surveillance-Broadcast (ADS-B or extended squitters) from the Enhanced Surveillance (EHS) transponders. This function is activated through pin programming. NOTE : The description of this system is based on the information ____ provided by RTCA D0185A change 7.0. **ON A/C 106-149, 201-207, 210-249, 301-399, 401-499, Post SB Post SB

34-1179 For A/C 201-207, 34-1238 For A/C 201-207,

A. Presentation The TCAS II (Traffic Collision Avoidance System) is a system whose function is to detect and display aircraft in the immediate vicinity and to provide the flight crew with indications to avoid these intruders by changing the flight path in the vertical plane only. The TCAS periodically interrogates their transponders, computes their trajectories and constantly determines their potential threat. The acquisition of their signals is achieved by means of two transmit/receive antennas, one located on the underside of the fuselage and the other on the top. The system can establish individualized communications with each aircraft through ATC/Mode S transponders, thus permitting operation in dense traffic areas while avoiding an overload of radio-electric transmissions that would result from a general all-intruder response. The TCAS II system is designed to provide the air traffic control system with an additional possibility. It usually operates independently but may be controlled from ground stations. The TCAS has the capability to communicate with ATCRBS (Air Traffic Control Radar Beacon System) ground stations equipped with the Mode S system to indicate to them the vertical maneuver orders presented to the aircraft pilot. This information can facilitate the task of the ground station controller who, in turn, can modify the TCAS operating mode and cancel the avoidance orders if he deems it necessary for safety. The system maintains surveillance within a sphere determined by the transmit power and receiver sensitivity of the TCAS computer. The area in which a threat is imminent depends on the speed and path of the own A/C and the threat A/C.

  R EFF : 106-149, 201-207, 210-249, 301-399,  34-43-00 Page 8 401-499, 501-509, 511-526, 528-599,  Config-1 Feb 01/10  CES

 

There is an area defined as TAU within the surveillance arc which represents the minimum time the flight crew needs to discern a collision threat and take evasive action. The TCAS detection capability covers an area of 35-40 NM in range and plus or minus 9900 ft in altitude but display range is authorized up to plus or minus 2700 ft in altitude. NOTE : The ABOVE/BELOW function on the ATC/TCAS control unit is used to ____ increase the display range above 1200 ft and below -1200 ft. NOTE : The description of the system conforms to RTCA/DO-185A Change 7.0. ____ (Ref. Fig. 001C) R

**ON A/C ALL B. Principle When an aircraft is airborne, its TCAS periodically transmits interrogation signals for all ATCRBS and Mode S transponder-equipped aircraft in the vicinity. These interrogations are received by the ATCRBS ground stations and by the transponders of the other aircraft. In response to these interrogations, the transponders of nearby aircraft return signals containing their altitude value. The TCAS computes the range between the two aircraft by measuring the elapsed time between transmission of the interrogation and reception of the reply. The altitude, altitude rate, range and range rate are determined by a periodic tracking of these exchanges and the data are used for intruder threat assessment. Each threat is treated individually but the TCAS determines the best collision avoidance possibility with respect to all aircraft in its vicinity, while establishing maneuver coordination with the other TCAS-equipped aircraft. The optimum maneuver is the one that ensures an adequate separation of trajectories with a minimum vertical trend variation. C. Advisories Visual and aural advisories are supplied by the TCAS computer whenever assessment of the relative position of two aircraft reveals a potential collision hazard. The Traffic Advisories (TA) indicate the position of nearby aircraft which are or may become a threat. Their display alerts the flight crew to the presence of intruders and facilitates their visual acquisition. The Resolution Advisories (RA) may be divided into two categories: - Corrective Advisories that instruct the pilot to deviate from current vertical rate

  R EFF : ALL  34-43-00 Page 9   Config-1 Nov 01/09  CES

 

TCAS - Surveillance and Display Figure 001C   EFF : 106-149, 201-207, 210-249, 301-399,  34-43-00 Page 10 401-499,  Config-1 May 01/09  CES

 

- Preventive Advisories that instruct the pilot to avoid certain maneuvers. D. Display Visual indications are presented on the Electronic Flight Instrument System (EFIS). The Navigation Display (ND) is used to indicate the situation in the nearby traffic area: a symbol is displayed for each intruder on the image in the ARC or ROSE mode. The avoidance maneuver indications, if any, are displayed on the vertical speed scale of the Primary Flight Display (PFD) by means of a band of colored sectors showing the vertical speed value to be adopted in order to avoid any risk of collision. E. Coordination The avoidance maneuvers initiated by the TCAS could create a conflict situation if directed at another TCAS-equipped aircraft as this aircraft may also take similar evasive action, resulting in an unchanged situation. To avoid this situation, a communication link between the two aircraft is established via the transponders, exchanging coordination messages. The first aircraft to detect the other one initiates the communication procedure, indicates the maneuvers it intends to perform and communicates orders to the other aircraft requesting it to maintain its trajectory. This necessarily involves the use of Mode S transponders, the only equipment of this type possessing the LINK function required for data exchange. The Mode S transponders provide the capability to transmit a unique address (24 bits) assigned to each aircraft, permitting them to reply individually to other TCAS-equipped aircraft. It can respond to ground station interrogations in Mode A and Mode C and also in Mode S if the stations are suitably equipped. The ground stations can modify the TCAS operating mode via the transponder link so as to inhibit resolution advisories in certain conditions. 2. __________________ Component Location R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, (Ref. Fig. 002) **ON A/C 051-099, 251-299, (Ref. Fig. 002A)

  EFF : ALL  34-43-00 Page 11   Config-1 Feb 01/10  CES

 

TCAS - Component Location Figure 002   R EFF : 001-049, 101-105, 151-199, 501-509,  34-43-00 Page 12 511-526, 528-599,  Config-1 Feb 01/10  CES

 

TCAS - Component Location Figure 002A   R EFF : 051-099, 251-299,  34-43-00 Page 13   Config-1 Nov 01/09  CES

 

**ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 002B) **ON A/C ALL ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------3SH CTL UNIT-ATC/TCAS 11VU 211 831 34-52-12 1SG CMPTR-TCAS 82VU 128 824 34-43-34 7SG1 ANTENNA-TCAS, TOP 230 34-43-11 7SG2 ANTENNA-TCAS, BOTTOM 130 34-43-11 3. System __________________ Description (Ref. Fig. 003) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-239, 301-312, 315-399, 401-499, 501-501, 503-503, (Ref. Fig. 004) R

**ON A/C 240-249, 251-299, 313-314, 502-502, 504-509, 511-526, 528-599, (Ref. Fig. 004A) **ON A/C ALL The TCAS environment is composed of items closely associated with its operation, such as the transponders and the EFIS display units and peripherals supplying parameters or with maintenance functions. A. TCAS Computer The TCAS computer is the heart of the TCAS II system. It complies with the dimensional standard in ARINC 600 for 6 MCU form factor. It is compatible with ARINC 600 forced air cooling. It ensures two main functions: - a radio-electric transmission reception function in the L-band frequency for intruder acquisition

  EFF : ALL  34-43-00 Page 14   Config-1 Feb 01/10  CES

 

TCAS - Component Location Figure 002B   EFF : 106-149, 201-249, 301-399, 401-499,  34-43-00 Page 15   Config-1 May 01/09  CES

 

TCAS Block Diagram - Data Acquisition Figure 003   R EFF : ALL  34-43-00 Page 16   Config-1 Nov 01/09  CES

 

TCAS Block Diagram - Maintenance and Display Figure 004   EFF : 001-049, 051-099, 101-149, 151-199,  34-43-00 Page 17 201-239, 301-312, 315-399, 401-499, 501-501,  Config-1 May 01/09 503-503, CES

 

TCAS Block Diagram - Maintenance and Display Figure 004A   R EFF : 240-249, 251-299, 313-314, 502-502,  34-43-00 Page 18 504-509, 511-526, 528-599,  Config-1 Feb 01/10  CES

 

- a processing function ensuring total operation control: digital, discrete and analog-type interfaces, intruder trajectory computation and tracking, visual and aural alert commands. B. Directional Antennas The TCAS has two antennas, one located on the top of the aircraft and the other on the underside of the fuselage. These antennas, of the transmit/receive type, provide azimuth information on aircraft located within the TCAS surveillance range. They consist of four independent elements. In reception, the amplitude of the signals received by each element depends on the direction of the signal source, which permits the relative bearing of the transmitting aircraft to be determined. C. ATC/TCAS Control Unit The ATC/TCAS control unit common to the ATC transponders and the TCAS, enables the operating modes of these two items of equipment to be selected. Information intended for the TCAS is transmitted via an ARINC 429 bus to the transponders which in turn transmit it to the TCAS computer. **ON A/C 001-049, 101-149, 151-199, 201-249, 301-399, 401-499, D. Associated Items (1) ATC/Mode S transponders Two ATC/Mode S transponders, one active and the other on standby, are used with their antennas. Each transponder is linked to the TCAS by one high-speed ARINC 429 bus for transmission and another one for reception. Apart from the specific transponder functions (response to ATC ground station interrogations) they permit communication between the TCAS and a TCAS-equipped detected aircraft. (2) Displays Advisories are displayed by the Electronic Instrument System (EIS) by high speed transmission of ARINC 429 messages on the buses linking the TCAS to the DMCs 1 on one hand and to the DMC2 on the other hand. Depending on the EFIS DMC selection, the DMC 3 receives either the TA/RA display bus 1 (CAPT3/NORM positions) or the TA/RA display bus 2 (FO3 position). The FWCs connected in parallel on these buses monitor the validity of the information. The NDs provide indications on the location of intruders in the traffic area. The PFDs provide the flight crew with vertical speed correction information to avoid them. The ECAM system also presents warning messages.

  R EFF : ALL  34-43-00 Page 19   Config-1 Nov 01/09  CES

 

E. Peripherals The TCAS receives information from the following equipment: (1) Radio altimeter The radio altitude is an essential parameter for the TCAS. In the 0 to 2500 ft range it permits modulation of system sensitivity and triggering of inhibit orders. For this reason, two radio altimeters, one active and the other in standby, are linked to the TCAS via the low speed ARINC 429 bus. (2) Air data system Barometric altitude information fulfils the same functions as radio altitude information but for the range over 2500 ft. The ADIRU, which is not directly linked to the TCAS computer, transmits this information to the computer across the transponders via the ARINC 429 buses. (3) Inertial reference system The TCAS is linked by a high speed ARINC 429 bus to the aircraft ADIRU1 which supplies it with magnetic heading and pitch and roll attitude information. (4) Landing Gear Control and Interface Unit (LGCIU) The LGCIU provides the TCAS with the following discrete signals: - ground/flight signal - landing gear extended signal. (5) Centralized Fault Display Interface Unit (CFDIU) The TCAS computer communicates with the Centralized Fault Display System (CFDS) via two low speed ARINC 429 buses. (6) Data loader It is possible to load software data into the TCAS computer by means of a mobile data loader with remote loading capability linked by two low speed ARINC 429 buses to a dedicated connector in the aircraft. (7) Flight Data Interface Unit (FDIU) The FDIU receives TCAS data from the DMC. The following parameters are recorded by the FDIU: - RA related information (label 270): * advisory rate to maintain * combined control * vertical control * up advisory * down advisory - manual sensitivity level (SL 0, 1, 2) - TA issued or not.

  EFF : 001-049, 101-149, 151-199, 201-249,  34-43-00 Page 20 301-399, 401-499,  Config-1 May 01/09  CES

 

(8) Various discrete signals Discretes are used for the inhibition of certain advisories by equipment with higher priority than the TCAS: - advisory inhibit by the windshear signal - advisory inhibit by the stall warning - advisory inhibits by the ground proximity warning. (9) Pin programming Discrete pin program inputs are used: - audio level to set the audio level of the synthetic voice output - all traffic/threat traffic display at Threat Traffic indicates that intruders are only displayed if a TA or RA is presented - ground display mode: specifies that the display mode, when the aircraft is on the ground, is the TA mode only - display intruder limit: indicates the maximum number of intruders that can be displayed (8) - aircraft altitude limit, configured at 48,000 ft informs the TCAS computer that it must inhibit climb orders above this altitude. R

**ON A/C 051-099, 251-299, D. Associated Items (1) ATC/Mode S transponders Two ATC/Mode S transponders, one active and the other on standby, are used with their antennas. Each transponder is linked to the TCAS by one high-speed ARINC 429 bus for transmission and another one for reception. Apart from the specific transponder functions (response to ATC ground station interrogations) they permit communication between the TCAS and a TCAS-equipped detected aircraft. (2) Displays Advisories are displayed by the Electronic Instrument System (EIS) by high speed transmission of ARINC 429 messages on the buses linking the TCAS to the DMCs 1 on one hand and to the DMC2 on the other hand. Depending on the EFIS DMC selection, the DMC 3 receives either the TA/RA display bus 1 (CAPT3/NORM positions) or the TA/RA display bus 2 (FO3 position). The FWCs connected in parallel on these buses monitor the validity of the information. The NDs provide indications on the location of intruders in the traffic area. The PFDs provide the flight crew with vertical speed correction information to avoid them. The ECAM system also presents warning messages.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-43-00 Page 21 201-249, 251-299, 301-399, 401-499,  Config-1 Nov 01/09  CES

 

E. Peripherals The TCAS receives information from the following equipment: (1) Radio altimeter The radio altitude is an essential parameter for the TCAS. In the 0 to 2500 ft range it permits modulation of system sensitivity and triggering of inhibit orders. For this reason, two radio altimeters, are linked to the TCAS via the low speed ARINC 429 bus. Radio Altimeter 1 is used first, and if not available (or if it is NCD), then Radio Altimeter 2 is used to calculate altitude, and compute inhibitions. (2) Air data system Barometric altitude information fulfils the same functions as radio altitude information but for the range over 2500 ft. The ADIRU, which is not directly linked to the TCAS computer, transmits this information to the computer across the transponders via the ARINC 429 buses. (3) Inertial reference system The TCAS is linked by a high speed ARINC 429 bus to the aircraft ADIRU1 which supplies it with magnetic heading and pitch and roll attitude information. (4) Landing Gear Control and Interface Unit (LGCIU) The LGCIU provides the TCAS with the following discrete signals: - ground/flight signal (RH main landing gear compressed) - landing gear extended signal (LH main landing gear downlocked). (5) Centralized Fault Display Interface Unit (CFDIU) The TCAS computer communicates with the Centralized Fault Display System (CFDS) via two low speed ARINC 429 buses. (6) Multipurpose Disk Drive Unit (MDDU) It is possible to load software data (operating algorithms and the reconfiguration of the inputs/outputs) into the TCAS computer by means of the MDDU via two low speed ARINC 429 buses. These data are stored on a 3.5 inch disk. It is then used by the data loader to transfer its contents into the Non-Volatile Memories (NVM) of the TCAS computer (more details in chapter 31-38-00). NOTE : Data loading is allowed only through application of Airbus ____ Service Bulletin or Vendor Service Bulletin.

  R EFF : 051-099, 251-299,  34-43-00 Page 22   Config-1 Nov 01/09  CES

 

(7) Flight Data Interface Unit (FDIU) The FDIU receives TCAS data from the DMC. The following parameters are recorded by the FDIU: - RA related information (label 270): * advisory rate to maintain * combined control * vertical control * up advisory * down advisory - manual sensitivity level (SL 0, 1, 2) - TA issued or not. (8) Various discrete signals Discretes are used for the inhibition of certain advisories by equipment with higher priority than the TCAS: - advisory inhibit by the windshear signal - advisory inhibit by the stall warning - advisory inhibits by the ground proximity warning. The TCAS has higher priority than the auto call outs supplied by the FWC. Three TCAS discretes (aural advisory discrete outputs) inhibit these auto call outs. (9) Pin programming Discrete pin program inputs are used: - audio level to set the audio level of the synthetic voice output - all traffic/threat traffic display at Threat Traffic indicates that intruders are only displayed if a TA or RA is presented - ground display mode: specifies that the display mode, when the aircraft is on the ground, is the TA mode only - display intruder limit: indicates the maximum number of intruders that can be displayed (8 intruders) - aircraft altitude limit, configured at 48,000 ft informs the TCAS computer that it must inhibit climb orders above this altitude. R

**ON A/C 501-509, 511-526, 528-599, D. Associated Items (1) ATC/Mode S transponders Two ATC/Mode S transponders, one active and the other on standby, are used with their antennas. Each transponder is linked to the TCAS by one high-speed ARINC 429 bus for transmission and another one for reception. Apart from the specific transponder functions (response to ATC ground station interrogations) they permit communication between the TCAS and a TCAS-equipped detected aircraft.

  R EFF : 051-099, 251-299, 501-509, 511-526,  34-43-00 Page 23 528-599,  Config-1 Feb 01/10  CES

 

(2) Displays Advisories are displayed by the Electronic Instrument System (EIS) by high speed transmission of ARINC 429 messages on the buses linking the TCAS to the DMCs 1 on one hand and to the DMC2 on the other hand. Depending on the EFIS DMC selection, the DMC 3 receives either the TA/RA display bus 1 (CAPT3/NORM positions) or the TA/RA display bus 2 (FO3 position). The FWCs connected in parallel on these buses monitor the validity of the information. The NDs provide indications on the location of intruders in the traffic area. The PFDs provide the flight crew with vertical speed correction information to avoid them. The ECAM system also presents warning messages. E. Peripherals The TCAS receives information from the following equipment: (1) Radio altimeter The radio altitude is an essential parameter for the TCAS. In the 0 to 2500 ft range it permits modulation of system sensitivity and triggering of inhibit orders. For this reason, two radio altimeters, are linked to the TCAS via the low speed ARINC 429 bus. Radio Altimeter 1 is used first, and if not available (or if it is NCD), then Radio Altimeter 2 is used to calculate altitude, and compute inhibitions. (2) Air data system Barometric altitude information fulfils the same functions as radio altitude information but for the range over 2500 ft. The ADIRU, which is not directly linked to the TCAS computer, transmits this information to the computer across the transponders via the ARINC 429 buses. (3) Inertial reference system The TCAS is linked by a high speed ARINC 429 bus to the aircraft ADIRU1 which supplies it with magnetic heading and pitch and roll attitude information. (4) Landing Gear Control and Interface Unit (LGCIU) The LGCIU provides the TCAS with the following discrete signals: - ground/flight signal (RH main landing gear compressed) - landing gear extended signal (LH main landing gear downlocked). (5) Centralized Fault Display Interface Unit (CFDIU) The TCAS computer communicates with the Centralized Fault Display System (CFDS) via two low speed ARINC 429 buses.

  R EFF : 501-509, 511-526, 528-599,  34-43-00 Page 24   Config-1 Feb 01/10  CES

 

(6) Data loader It is possible to load software data into the TCAS computer by means of a mobile data loader with remote loading capability linked by two low speed ARINC 429 buses to a dedicated connector in the aircraft. NOTE : Data loading is allowed only through application of Airbus ____ Service Bulletin or Vendor Service Bulletin. (7) Flight Data Interface Unit (FDIU) The FDIU receives TCAS data from the DMC. The following parameters are recorded by the FDIU: - RA related information (label 270): * advisory rate to maintain * combined control * vertical control * up advisory * down advisory - manual sensitivity level (SL 0, 1, 2) - TA issued or not. (8) Various discrete signals Discretes are used for the inhibition of certain advisories by equipment with higher priority than the TCAS: - advisory inhibit by the windshear signal - advisory inhibit by the stall warning - advisory inhibits by the ground proximity warning. (9) Pin programming Discrete pin program inputs are used: - audio level to set the audio level of the synthetic voice output - all traffic/threat traffic display at Threat Traffic indicates that intruders are only displayed if a TA or RA is presented - ground display mode: specifies that the display mode, when the aircraft is on the ground, is the TA mode only - display intruder limit: indicates the maximum number of intruders that can be displayed (8) - aircraft altitude limit, configured at 48,000 ft informs the TCAS computer that it must inhibit climb orders above this altitude. R

  R EFF : 501-509, 511-526, 528-599,  34-43-00 Page 25   Config-1 Feb 01/10  CES

 

**ON A/C ALL 4. Power ____________ Supply The TCAS is supplied with 115VAC, 100 watt power rating. The ATC/TCAS control unit, common to the transponders and the TCAS, is also supplied with 115VAC: - the 115VAC BUS1 101XP supplies the TCAS via circuit breaker 4SG - the 115VAC SHED ESS BUS 801XP supplies the ATC1 system via circuit breaker 5SH1 - the 115VAC BUS2 204XP supplies the ATC2 system via circuit breaker 5SH2. The ATC/TCAS control unit is energized through the two circuit breakers 5SH1 and 5SH2. The system is supplied through these circuit breakers: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/TCAS 4SG K10 121VU COM NAV/ATC/2 5SH2 K07 5. _____________________ Component Description R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, A. TCAS Computer **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 005)

R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 005C)

R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, (Ref. Fig. 006)

  EFF : ALL  34-43-00 Page 26   Config-1 Feb 01/10  CES

 

TCAS Computer Figure 005   EFF : 001-049, 101-105, 151-199,  34-43-00 Page 27   Config-1 May 01/09  CES

 

TCAS Computer Figure 005A   R EFF : 051-099, 251-299,  34-43-00 Page 28   Config-1 Nov 01/09  CES

 

TCAS Computer Figure 005B   EFF : 201-209,  34-43-00 Page 29   Config-1 May 01/09  CES

 

TCAS Computer Figure 005C   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page 30   Config-1 Feb 01/10  CES

 

TCAS Computer Figure 005D   EFF : 106-149, 201-207, 210-249, 301-399,  34-43-00 Page 31 401-499,  Config-1 May 01/09  CES

 

TCAS Computer - Block Diagram Figure 006   R EFF : 001-049, 101-105, 151-199, 501-509,  34-43-00 Page 32 511-526, 528-599,  Config-1 Feb 01/10  CES

 

(1) Introduction The TCAS computer is divided into four major sections: - Radio Frequency section (RF) - Video Processor (VP) - Data Processor (DP) - Input/Output Processor (IOP) (2) Radio frequency section (a) General The RF section consists of receiver, transmitter and RF switch portions. The receiver processes the raw ATCRBS or Mode S intruder reply data received from either the top or bottom antenna. The transmitter portion of the RF section interrogates intruders once per second, also using either antenna. The RF switch portion selects the antenna (top or bottom) for the transmission and reception of the TCAS signals. For ATCRBS intruders, interrrogations are accomplished by controlling a whisper shout attenuation system which provides successive responses, starting with the nearest aircraft and continuing progressively to those farther away so as to avoid saturating the radio-electric space and resulting interference. (b) RF switch The RF switch is dual-purpose: - it switches the transmission/reception circuits between the top and bottom antennas - it directs antenna links either to the transmit circuits or to the receive circuits as the antenna links and elements are used indifferently for transmission and reception. The four elements of each antenna are connected to hyperfrequency multiplexers controlled by the video controller. (c) Transmitter The transmitter generates the 1030 MHz carrier frequency required for TCAS transmission. For a Mode S interrogation, this frequency is modulated in DPSK (Data Phase Shift Keyed) format by the video controller module. For Mode C interrogations the frequency is applied to the whisper shout attenuator which attenuates the signal from 0 to 32 dB in 1 dB increments. The modulated frequency is then split into four parts by a programmable circuit controlled by the video controller so as to divide transmitter output into four separate antenna-element drive channels.

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(d) Receiver The receive circuitry consists of three RF channels. The signals are received through the antenna elements and processed as pairs. The paths of the signals between antenna element pairs and receiver pairs are exchanged by swap switches to eliminate the phase error in the different circuits. In each receiver, the RF signal is mixed with the local oscillator signal to produce a 60 MHz intermediate frequency signal. The processed signals are applied to phase detectors that determine the sine and cosine relationship between antenna element pairs. After amplification, these signals are transmitted to the video processor where relative bearing is determined. Logarithmic outputs from the three receivers are also applied to a log summer which passes the log sum signal to the video processor where it is decoded to determine range and altitude. (3) Not Applicable **ON A/C 051-099, 251-299, A. TCAS Computer (1) Introduction The TCAS computer is divided into five major sections: - a receiver (A5) - a transmitter (A6) - an Input/Output (I/O) module (A4) - two Central Processing Units (CPU) (A2, A3) - a power supply unit (A1) (Ref. Fig. 005A, 006A) (2) Radio frequency section (a) General The RF section consists of a receiver, a transmitter and an I/O module. The receiver processes the raw ATCRBS or Mode S intruder reply data received from either the top or the bottom antenna. The transmitter portion of the RF section controls all interrogation, it interrogates intruders once per second, also using either antenna.

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TCAS Computer - Block Diagram Figure 006A   R EFF : 051-099, 251-299,  34-43-00 Page 35   Config-1 Nov 01/09  CES

 

The I/O module is used to route signals to and from the antennas. For ATCRBS intruders, interrogations are accomplished by controlling a whisper-shout attenuation system which provides successive responses, starting with the nearest aircraft and continuing progressively to those farther away so as to avoid saturating the radio-electric space and resulting interference. (b) I/O module The I/O module controls the transmit and receive RF path selection, generates self-test signals and waveforms. All RF switching is done electronically by pin-diodes. The antenna steering is an electronic switch consisting of electronic components which send receive and transmit signals into different paths according to the antenna direction (0, 90, 180 and 270 degrees). The selected path is routed to the appropriate switch which drives the signal to either a top or bottom antenna. There are 8 ports on the switch: 4 for each direction of the top antenna and 4 for each direction of the bottom antenna. The received signals (all 4 received channels are on at one time) are channeled to the antenna steering where they are electronically connected to the receiver. The I/O module incorporates self-test circuitry for the receiver and the transmitter. There is also the antenna self-test function. The receiver self-test circuitry simulates ATCRBS/mode S replies which are injected at an appropriate level into each receiver RF path. The transmitter self-test verifies proper power/path integrity and the I/O module continuously monitors antenna integrity as well. (c) Transmitter The transmitter controls all interrogations waveforms and power levels. It consists of both pulse and DPSK modulators, all power amplification stages, high-power precision step attenuator (whisper-shout), as well as harmonic filter and spectrum filter, and BITE power detection circuitry. The L-band transmitter has a peak power output of 1.2 kW at 1030 MHz. The transmitter signal is amplified and a DPSK modulator is also provided for Mode S interrogations. This signal is divided into 4 in the proper phase relationship. The modulator/driver provides power and control signals, it sends discrete signals to the CPU which provides the correct pulse width for modulation.

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The final signal is increased up to 1500 W and it is fed into the whisper-shout module. This module is a precision 27 step attenuator (1 dB by step) which controls the power level. The output is fed through the filters before it is driven to the I/O module which applies the power to the appropriate antenna. (d) Receiver The receiver consists of 4 matched channels which provide very accurate bearing information. Each receiver channel consists of a single conversion receiver, high-quality logarithmic amplifier and high-resolution A/D converter. The receiver consists of 4 virtually identical receive channels coupled to 2 separate digital video sections. Each receiver uses a single conversion heterodyne circuit. The preselector, included in each receiver, contains an L-band, band pass filter which selects the 1090 MHz frequency band. It provides selection of unwanted signals in excess of 60 dB outside the 30 MHz bandwidth. This signal is converted from 1090 MHz to 60 MHz. The processed signal is applied to the logarithmic amplifier. The logarithmic amplifier video output is fed to a video amplifier where the actual magnitude of the slope and offset level is controlled precisely. This video signal is fed to the digital video circuit. This one samples the analog video signal at an 8 MHz rate for mode S and 8.276 MHz for ATCRBS. Each of the 2 digital video A/D converters selects the 2 strongest signals from the 4 receive channels. (3) Not Applicable **ON A/C 201-209, A. TCAS Computer (Ref. Fig. 005B, 006B) (1) Introduction The TCAS computer is divided into four major sections: - Radio Frequency section (RF Assembly A6) - Signal Processor (A4) - Central Processing Unit (CPU A3) - Input/Output Processor (I/O A2)

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TCAS Computer - Block Diagram Figure 006B   EFF : 201-209,  34-43-00 Page 38   Config-1 May 01/09  CES

 

(2) Radio frequency section (a) General The RF section consists of receiver, transmitter and RF switch portions. The receiver processes the raw ATCRBS or Mode S intruder reply data received from either the top or bottom antenna. The transmitter portion of the RF section interrogates intruders once per second, also using either antenna. The RF switch portion selects the antenna (top or bottom) for the transmission and reception of the TCAS signals. For ATCRBS intruders, interrrogations are accomplished by controlling a whisper shout attenuation system which provides successive responses, starting with the nearest aircraft and continuing progressively to those farther away so as to avoid saturating the radio-electric space and resulting interference. (b) Description 1 _

Transmitter The transmitter is a solid-state circuit that develops 1030 MHz outputs. The TCAS transmitter/receiver has a transmit/listen cycle of approximately 1 s intervals. A series of increasing power mode C interrogations is first transmitted. This is the whisper-shout sequence (4-pulse group repeated with increasing power to 20 dB at 1 ms intervals). Immediately following is a mode S interrogation modulated in DPSK (Data Phase Shift Keyed) format. The remainder of the 1s-cycle is spent in listen mode. After the whisper shout attenuator, the signal is fed through diplexers, beam-steering networks and top/bottom antenna switch. The beam-steering network generates and controls the phase relationships of the four RF outputs from the transmitter. These outputs are connected to the four elements of the TCAS antenna.

2 _

Receiver The receiver has four individual RF and IF sections, one for each directional antenna segment. The receive frequency is 1090 MHz. The signal received from each antenna element is passed through one of the four parallel top/bottom antenna switches, beam-steering networks, transmit/receive switches, then to four identical receiver RF circuits. These four signals are further applied to mixer circuits to develop IF signals (the local oscillator frequency used by the mixers is 1030 MHz from the transmitter sub-assembly). These IF signals

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are amplified, filtered and applied to splitters for output to the video processor. 3 _

Video processor One output from each of the four signal splitters is recombined and output as a video signal. This signal is used to detect mode C and mode S data pulses. These items of information are checked and invalid pulses eliminated so the outputs of the video processor are mode C and mode S data. The output from each signal splitter is applied to the bearing detector.

4 _

Bearing detector One of the IF signals is applied to one limiter as a reference signal. Outputs of two other limiters are mixed with the reference signal for phase detection. The resulting phase detector outputs are dc signals whose levels are directly proportional to the angle of arrival of the RF signal at the antenna.

(3) Not Applicable **ON A/C 106-149, 201-207, 210-249, 301-399, 401-499, Post SB Post SB

34-1179 For A/C 201-207, 34-1238 For A/C 201-207,

A. TCAS Computer (Ref. Fig. 005D, 006C) (1) Introduction The TCAS computer is divided into four major sections: - Beam Steering/Receiver Module (A2) - Transmitter Module Assembly (A3) - Digital Signal Processor (DSP) Assembly (A4) - Input/Output (I/O) CPU Assembly (A5) (2) Beam Steering/Receiver Module (A2) (a) Beam steering The purpose of beam steering is to vary phasing of the transmit signal to the four directional elements in each (top and bottom) antenna.

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TCAS Computer - Block Diagram Figure 006C   EFF : 106-149, 201-207, 210-249, 301-399,  34-43-00 Page 41 401-499,  Config-1 May 01/09  CES

 

The antenna elements are numbered 1 through 4 with number 1 element of the top antenna pointing to the nose of the aircraft, number 2 to the right, number 3 to the rear, and number 4 to the left. (b) Receiver The TCAS 1090 MHz receiver sensitivity level is such that it has the ability to receive broadcast messages (squitters) from an intruder Mode S transponder. Data contained in these squitters allow passive tracking of aircraft beyond 100 NM with the introduction of a software upgrade option. This requires that the intruder aircraft be equipped with an ADS-B capable transponder and a GNSS receiver. (3) Transmitter module assembly (A3) The transmitter is a solid-state circuit that develops 1030 MHz outputs. The TCAS transmitter/receiver has a transmit/listen cycle of approximately 1s intervals. A series of increasing power mode C interrogations is first transmitted. This is the whisper-shout sequence (4-pulse group repeated with increasing power to 20 dB at 1 ms intervals). Immediately following is a Mode S interrogation modulated in DPSK ( Differential Phase-Shift Keying) format. The remainder of the 1 s-cycle is spent in listen mode. **ON A/C 001-049, 101-105, 151-199, (4) Video processor The video processor contains circuitry needed to perform the following functions: - analog-to-digital conversion of the sine, cosine and log sum inputs - quantization of the log video inputs by comparing the log video against a threshold level to reduce the effect of multi-path replies - decoding of ATCRBS Mode A and Mode C replies and elimination of phantom replies - Mode S and address decoding and error detection/correction - storing of real time bearing information versus range during ATCRBS or Mode S interrogations. The video processor uses the video memory module to temporarily store the following information: - squitter bearing and data - interrogation bearing and data - range - reply edge data for range measurement.

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The video controller generates outputs as required for control of the transmitter, antenna switches and receiver. (5) Data processor The data processor module processes the data input from the video processor and input/output circuits. It also operates the links between the associated transponders and supplies the connector, reserved for the data recorder, mounted on the computers front panel, via the interface circuits. The data processor module provides the computational capabilities required for processing the TCAS functions. It is based on an Intel 80386 microprocessor operated at 32 MHz. It is optimized for numeric processing and associated with an 80387 numeric data coprocessor. Program memory, which contains the preprogrammed system operating instructions is contained in EPROMs (programmable read only memory erasable by ultra-violet rays ) on memory module I. Random access memory (RAM) on memory modules I and II provides temporary storage for data that is acquired or used during system operation. Input/output circuitry permits direct communication with the transponders via an ARINC 429 high speed bus interface. It also includes a discrete I/O interface for a data recorder, a port for connection to Automatic Test Equipment (ATE) and an RS-232 interface for use with a simulator. (6) Inputs/Outputs (I/O) Managed by an Intel 80C186 microprocessor whose program is contained in a Read Only Memory (ROM), the I/O module provides the main interface between the data processor and external hardware. It acquires most of the aircraft data used by the TCAS and transmits control and information signals to the other equipment. This modules activity is under control of the data processor who exchanges with it specific messages via a storage serving as a mailbox in both directions. The data is composed of discrete inputs/outputs, program pins and ARINC 429 data except those of the transponder, acquired directly by the data processor. This module also contains the synthesized voice message generation and possess the capability to process analog signals for non-digital aircraft. A validity check is performed on ARINC 429 input data. The synthesized voice generator transmits messages from a ROM containing all the information required to generate advisories. Two audio output channels (low and high level) are available. The low level audio outputs are connected to the cockpit loud speakers through the AMU.

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(7) Data loader A plug is installed next to the computer for the loading of the operational program and I/O configuration data into the TCAS computer via 2 ARINC 429 low speed buses, by means of a data loader. Presently, this operation can only be done by Vendor Service Bulletin. R

**ON A/C 051-099, 251-299, (4) CAS CPU The Collision Avoidance System (CAS) function is performed at the beginning of each processing cycle (nominally 1 second). The CAS processes own altitude and data from the intruder surveillance buffer to track intruders, detects threats and generates proximity traffic and resolution advisories. The CAS function also performs coordination with TCAS-equipped intruders. It contains CAS CPU, supporting logic, memory devices and interface circuits. The CAS CPU controls the following functions which are executed by the hardware on the surveillance card: - speech synthesis - ARINC 429 interfaces - access to shared RAM. This CPU utilizes a 16-bit SDP 185 as the processing element. This processor uses a 36 MHz clock to control internal operation. External extension registers are incorporated to expand the addressable memory to 128 kwords. The SDP 185 companion ASIC contains memory cycle timing, system reset, general purpose timers and a digital heartbeat monitor. . Onboard memory is provided for program, variable and maintenance fault storage. . The remainder of the CCA is utilized to accommodate the aircraft interfaces specified in ARINC 735. The input, output and discrete interfaces are buffered, level shifted and sent to specific internal and/or external interface. (5) Surveillance CPU The surveillance function uses information from squitters, Mode S fruit, Mode S replies, and ATCRBS replies to generate the surveillance track file. This surveillance CPU supports logic circuits, memory devices and interface circuits. - The CPU uses the same SDP 185 processor and SDP 185 companion ASIC as the CAS CPU. Processor memory consists of 72 K words of EEPROM to provide 64 K words of usable program memory and 8 K words of configuration memory. The remainder of this CCA is utilized by the

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CPU shared SRAM, ARINC 735 I/O, RF interface circuitry and speech processor. - Aural annunciation is provided through a speech synthesis processor which contains speech data in ROM. Two outputs are provided with program pin volume control selection. - The interface to the RF modules is contained in 3 ASICs. The pulse decoder ASIC accepts receiver data and performs basic pulse detection of incoming replies. A reply decoder ASIC sends processed replies to FIFO for processor retrieval. The CPU initiates and controls the generation of ATCRBS and mode S interrogations through the transmitter control ASIC. This ASIC also provides CPU interface for the RF self-test capability. Suppression pulse interface is provided by the transmitter control ASIC. The pulse decoder ASIC checks the suppression bus for proper transmit receive sequencing. (6) Inputs/Outputs (I/O) Managed by an Intel 80C186 microprocessor whose program is contained in a Read Only Memory (ROM), the I/O module provides the main interface between the data processor and external hardware. It acquires most of the aircraft data used by the TCAS and transmits control and information signals to the other equipment. This modules activity is under control of the data processor who exchanges with it specific messages via a storage serving as a mailbox in both directions. The data is composed of discrete inputs/outputs, program pins and ARINC 429 data except those of the transponder, acquired directly by the data processor. This module also contains the synthesized voice message generation and possess the capability to process analog signals for non-digital aircraft. A validity check is performed on ARINC 429 input data. The synthesized voice generator transmits messages from a ROM containing all the information required to generate advisories. Two audio output channels (low and high level) are available. The low level audio outputs are connected to the cockpit loud speakers through the AMU. (7) Data loader A plug is installed operational program via 2 ARINC 429 low be possible to load (MDDU) (data loader Loader.

next to the computer for the loading of the and I/O configuration data into the TCAS computer speed buses, by means of a data loader. It will data by means of the Multipurpose Disk Drive Unit installed on the aircraft), or the Portable Data

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**ON A/C 201-209, (4) Signal processor (A4) The signal processor serves as an interface between the RF assembly and the system software. It receives the three signal outputs from the RF assembly: bearing information, mode S and mode C data. The bearing data are converted into digital signals and applied to the RAM. The mode S and C video signals are formatted, checked for errors and applied to the RAM. Data from range counters are also stored in the RAM. So in linking mode S and C data with bearing data, the CPU is able to estimate the target aircraft range and bearing. Additional tasks of the signal processor are: management of system interface, buffer configuration, test, monitoring and fault isolation, mode S and C interrogation/reply management. (5) CPU card (A3) The CPU is the computational center of the TCAS. The CPU is made up of three microprocessors and associated circuits. It contains the programs for analyzing data developed as a result of signals from other transponders, and generates the traffic and resolution advisories for the cockpit display. Intruder range, altitude and bearing are calculated from received data. For TCAS equipped intruders, a data link is established to coordinate resolution of the threat condition. (6) Input/output card (A2) The input/output interface circuits handle the A/D, D/A, ARINC, discrete and analog signal conversions required for communication with external TCAS equipment. (7) Data loader A plug is installed next to the computer for the loading of the operational program and I/O configuration data into the TCAS computer via 2 ARINC 429 low speed buses, by means of a data loader. R

**ON A/C 501-509, 511-526, 528-599, (4) Video processor The video processor contains circuitry needed to perform the following functions: - analog-to-digital conversion of the sine, cosine and log sum inputs - quantization of the log video inputs by comparing the log video against a threshold level to reduce the effect of multi-path replies

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- decoding of ATCRBS Mode A and Mode C replies and elimination of phantom replies - Mode S and address decoding and error detection/correction - storing of real time bearing information versus range during ATCRBS or Mode S interrogations. The video processor uses the video memory module to temporarily store the following information: - squitter bearing and data - interrogation bearing and data - range - reply edge data for range measurement. The video controller generates outputs as required for control of the transmitter, antenna switches and receiver. (5) Data processor The data processor module processes the data input from the video processor and input/output circuits. It also operates the links between the associated transponders and supplies the connector, reserved for the data recorder, mounted on the computers front panel, via the interface circuits. The data processor module provides the computational capabilities required for processing the TCAS functions. It is based on an Intel 80386 microprocessor operated at 32 MHz. It is optimized for numeric processing and associated with an 80387 numeric data coprocessor. Program memory, which contains the preprogrammed system operating instructions is contained in EPROMs (programmable read only memory erasable by ultra-violet rays ) on memory module I. Random access memory (RAM) on memory modules I and II provides temporary storage for data that is acquired or used during system operation. Input/output circuitry permits direct communication with the transponders via an ARINC 429 high speed bus interface. It also includes a discrete I/O interface for a data recorder (via PCMCIA card or a Portable Data Loader). It uses a new Simsoft protocol by means of the PCMCIA card inserted in the front face of the computer TPA 100A. A converter from PCMCIA to RS-232 protocol is necessary to link the TCAS to the simulator. (6) Inputs/Outputs (I/O) Managed by an Intel 80C186 microprocessor whose program is contained in a Read Only Memory (ROM), the I/O module provides the main interface between the data processor and external hardware. It acquires most of the aircraft data used by the TCAS and transmits control and information signals to the other equipment. This modules activity is under control of the data processor who exchanges with it specific messages via a storage serving as a mailbox in both directions.

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The data is composed of discrete inputs/outputs, program pins and ARINC 429 data except those of the transponder, acquired directly by the data processor. This module also contains the synthesized voice message generation and possess the capability to process analog signals for non-digital aircraft. A validity check is performed on ARINC 429 input data. The synthesized voice generator transmits messages from a ROM containing all the information required to generate advisories. Two audio output channels (low and high level) are available. The low level audio outputs are connected to the cockpit loud speakers through the AMU. (7) Data loader A plug is installed next to the computer for the loading of the operational program and I/O configuration data into the TCAS computer via 2 ARINC 429 low speed buses, by means of a data loader. It will be possible to load data by means of the Multipurpose Disk Drive Unit (MDDU) (data loader installed on the aircraft), or the Portable Data Loader or throught the PCMCIA card incerted in the front face of the TCAS computer. **ON A/C 106-149, 201-207, 210-249, 301-399, 401-499, Post SB Post SB

34-1179 For A/C 201-207, 34-1238 For A/C 201-207,

(4) DSP assembly (A4) A signal processor and CPU (Central Processing Unit) provide the control and data analysis necessary for the TCAS computer operation. The signal processor circuits serve as a preprocessor between the system software and the RF circuits. The CPU is made of two microprocessors and their associated memories. This is the portion of the TCAS computer that contains the algorithms for analyzing data developed as a result of signals from transponders of other aircraft. The CPU generates the traffic and resolution advisories for output to the cockpit displays. It is software-controlled and communicates with the signal processor and input/output interface through the system bus. The input/output interface circuits are the A/D, D/A, ARINC, discrete and analog circuits required to communicate with external TCAS equipment. The interface has a CPU to control its operation.

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(5) I/O CPU assembly (A5) Three ARIES ARINC 429 unloader Application Specific Integrated Circuits (ASIC) are used to load/unload ARINC 429 data directly from/to the global memory space. Access to the global memory space is arbitrated between CPU A (AMP2) and CPU I (AMP5V) and the ARIES devices. CPU A is without peripherals in its local memory space. CPU A communicates with CPU I and the signal processor through the global memory space. CPU A local memory space contains only RAM, program memory (FLASH), memory mapped access to the global space, and an interrupt controller. CPU I memory space also contains RAM, program memory (FLASH), memory mapped access to the global space and an interrupt controller, plus several local peripherals, an analog-to-digital converter, a dual serial port, a speech device, and discrete I/O. The global memory space contains a 2-channel timer, RAM, the signal processor dual port, EEPROM (for fault logging), cross interrupts, discrete I/O, ARINC 429, display port, a memory card interface and discrete I/O. Data is passed directly to the memory card. (6) Input/output card (A2) The input/output interface circuits handle the A/D, D/A, ARINC, discrete and analog signal conversions required for communication with external TCAS equipment. (7) Data loader A plug is installed next to the computer for the loading of the operational program and I/O configuration data into the TCAS computer via 2 ARINC 429 low speed buses, by means of a data loader. R

**ON A/C ALL B. ATC/TCAS Control Unit For detailed description, Ref. 34-52-00, Para. 5.B.

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R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, C. TCAS Antennas (Ref. Fig. 007) The directional antenna is composed of four passive vertically-polarized elements. This high-strength composite antenna is provided with a curved base (110 in), eight fuselage mounting screws and four color-coded connectors used to coaxially connect the four antenna elements to the TCAS computer. A teflon gasket is located between the fuselage and the base of the antenna, in order to facilitate the removal of the antenna. An O-ring is provided to seal the antenna to the fuselage. The antenna is used to receive and provide directional information for 1090 MHz Mode S squitters, Mode S and Air Traffic Control Radar Beacon System (ATCRBS) replies. Proper phasing of the four antenna elements enables omni or directional transmission of 1030 MHz broadcast or coordination messages and ATCRBS or Mode S interrogations. **ON A/C 051-099, 251-299, C. TCAS Antennas (Ref. Fig. 007A) The TCAS directional antenna is a four-element, vertically polarized, monopole array which is capable of transmitting in four selected directions at 1030 MHz and receiving omnidirectionally with bearing at 1090 MHz using amplitude monopulse techniques. Both directional antennas are curved base plates (77 in. Radius). A teflon gasket is located between the fuselage and the base of the antenna. One O-ring is used at the center connectors in order to withstand the max pressure differential. **ON A/C 106-149, 201-249, 301-399, 401-499, C. TCAS Antennas (Ref. Fig. 007B) The directional antenna is composed of four passive vertically-polarized elements. This high-strength composite antenna is provided with a curved base (110 in), eight fuselage mounting screws and four color-coded connectors used to coaxially connect the four antenna elements to the TCAS computer.

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TCAS Antenna Figure 007   R EFF : 001-049, 101-105, 151-199, 501-509,  34-43-00 Page 51 511-526, 528-599,  Config-1 Feb 01/10  CES

 

TCAS Antenna Figure 007A   R EFF : 051-099, 251-299,  34-43-00 Page 52   Config-1 Nov 01/09  CES

 

TCAS Antenna Figure 007B   EFF : 106-149, 201-249, 301-399, 401-499,  34-43-00 Page 53   Config-1 May 01/09  CES

 

A teflon gasket is located between the fuselage and the base of the antenna, in order to facilitate the removal of the antenna. An O-ring is provided to seal the antenna to the fuselage. The antenna is used to receive and provide directional information for 1090 MHz Mode S squitters, Mode S and Air Traffic Control Radar Beacon System (ATCRBS) replies. Proper phasing of the four antenna elements enables omni or directional transmission of 1030 MHz broadcast or coordination messages and ATCRBS or Mode S interrogations. R

**ON A/C ALL 6. Operation _________ **ON A/C 001-049, 101-149, 151-199, 201-249, 301-399, 401-499, (Ref. Fig. 008) A. Intruder Detection The TCAS detects A/C equipped with Mode S transponders by listening for squitter transmissions. Mode S transponders announce their presence by transmitting squitter messages once every second. The TCAS also detects A/C equipped with transponders that do not reply to Mode S interrogations but do reply to Mode C interrogations. The TCAS must actively search for Mode C equipped intruder aircraft because Mode C transponders do not transmit squitter messages. Once the presence of a Mode C intruder is confirmed, it is tracked by the TCAS. The TCAS is capable of tracking up to a combined total of 30 Mode S and Mode C intruders. Tracking is performed by repetitive TCAS interrogations in Mode S and Mode C format. (1) Interrogation of aircraft equipped with Mode A or Mode C transponders With respect to aircraft equipped with Mode A or Mode C transponders, the TCAS is active and transmits Mode C only all-call interrogations (P1, P3 and P4 pulses). The code is similar to the one used by the Mode A and Mode C ground stations. The P4 pulse informs those Mode S transponders that this interrogation is not addressed to them (Ref. Fig. 009) The nominal time interval between two interrogations is one second. But, to limit radio-electric interference in dense traffic areas, each interrogation consists of a series of interrogations of increasing strength to reach more remote aircraft (whisper-shout) with 1 ms time periods inside the series. (Ref. Fig. 010) The first transmission consists of relatively low power P1, P3 and P4 pulses only.

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TCAS - Operation / Control and Indicating Figure 008   R EFF : ALL  34-43-00 Page 55   Config-1 Nov 01/09  CES

 

TCAS - Mode C Only All-Call Interrogation Figure 009   R EFF : ALL  34-43-00 Page 56   Config-1 Nov 01/09  CES

 

TCAS - Whisper-Shout Transmitter Sequence Figure 010   R EFF : ALL  34-43-00 Page 57   Config-1 Nov 01/09  CES

 

Therefore, only the nearest aircraft will receive and reply to these interrogations. Then an S1 pulse is also transmitted. This pulse is at a lower amplitude, causing the close-in aircraft to interpret this as a side lobe from the transmitting station, requiring no reply. The purpose of the whisper-shout sequence is to reduce the number of aircraft replying to any one interrogation, thus limiting interference. (2) Replies of aircraft equipped with Mode A or Mode C transponders Aircraft equipped with Mode C transponders reply by transmitting their altitude, octal encoded in four digits ABCD, with a value of 100 ft for the LSB in the ATCRBS format. For aircraft of which the Mode A and C transponders do not have the altitude report, the intruder presentation on the ND is limited to a display of its position in range and bearing. (Ref. Fig. 011) Aircraft equipped with Mode A transponders only cannot be detected by the TCAS. R

**ON A/C 051-099, 251-299, 501-509, 511-526, 528-599, (Ref. Fig. 008) A. Intruder Detection The TCAS detects A/C equipped with Mode S transponders by listening for squitter transmissions. Mode S transponders announce their presence by transmitting squitter messages once every second. The TCAS also detects A/C equipped with transponders that do not reply to Mode S interrogations but do reply to Mode C interrogations. The TCAS must actively search for Mode C equipped intruder aircraft because Mode C transponders do not transmit squitter messages. Once the presence of a Mode C intruder is confirmed, it is tracked by the TCAS. The TCAS is capable of tracking up to a combined total of 45 Mode S and Mode C intruders. Tracking is performed by repetitive TCAS interrogations in Mode S and Mode C format. (1) Interrogation of aircraft equipped with Mode A or Mode C transponders With respect to aircraft equipped with Mode A or Mode C transponders, the TCAS is active and transmits Mode C only all-call interrogations (P1, P3 and P4 pulses). The code is similar to the one used by the Mode A and Mode C ground stations. The P4 pulse informs those Mode S transponders that this interrogation is not addressed to them (Ref. Fig. 009)

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TCAS - Mode C Reply Figure 011   R EFF : ALL  34-43-00 Page 59   Config-1 Nov 01/09  CES

 

The nominal time interval between two interrogations is one second. But, to limit radio-electric interference in dense traffic areas, each interrogation consists of a series of interrogations of increasing strength to reach more remote aircraft (whisper-shout) with 1 ms time periods inside the series. (Ref. Fig. 010) The first transmission consists of relatively low power P1, P3 and P4 pulses only. Therefore, only the nearest aircraft will receive and reply to these interrogations. Then an S1 pulse is also transmitted. This pulse is at a lower amplitude, causing the close-in aircraft to interpret this as a side lobe from the transmitting station, requiring no reply. The purpose of the whisper-shout sequence is to reduce the number of aircraft replying to any one interrogation, thus limiting interference. (2) Replies of aircraft equipped with Mode A or Mode C transponders Aircraft equipped with Mode C transponders reply by transmitting their altitude, octal encoded in four digits ABCD, with a value of 100 ft for the LSB in the ATCRBS format. For aircraft of which the Mode A and C transponders do not have the altitude report, the intruder presentation on the ND is limited to a display of its position in range and bearing. (Ref. Fig. 011) Aircraft equipped with Mode A transponders only cannot be detected by the TCAS. R

**ON A/C ALL (3) Interrogation of aircraft equipped with Mode S transponders (a) Transmission coding The TCAS uses the Mode S function for certain identification of intruders as a 24-bit address is definitively assigned to each aircraft by air traffic control. The interrogation comprises three pulses: P1, P2 and P6. P2 level is equal to or greater than the P1 level, which is the no-reply condition for the aircraft equipped with Mode A or C transponders. Therefore, only Mode S transponders reply to the interrogation. The useful information is contained in P6 divided into 56 or 112 chips. A chip is an unmodulated interval of 0.25 microseconds, preceded by possible phase reversals. The message formats contain a number of bits permitting a more complete and diversified information exchange than in Mode C.

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There are two distinct message formats: - all Mode S interrogations (UPLINK format) are binary differential phase shift keying (DPSK) signals - Mode S replies (DOWNLINK format) are formed by pulse position modulation (PPM) encoding the reply data. (Ref. Fig. 012) The Mode S reply is preceded by a preamble containing four pulses of specific duration and intervals intended to guarantee received message validity. Any messages whose preamble is not in complete conformity with the model are rejected by the TCAS. This information is encoded in PPM mode with, for each bit, a logic level one if the first half of the interval is at 1 and a logic level zero if it is at zero. (b) Squitters The Mode S transponder participates actively in its own detection by transmitting signals, at one second intervals, intended to inform nearby aircraft of its presence. This transmission, called squitter transmission, consists of a Format DF = 11 message, containing the Mode S 24-bit address assigned to the aircraft, whereas all the bits of the message PI field at zero indicates a squitter. **ON A/C 001-049, 101-149, 151-199, 201-249, 301-399, 401-499, (c) Mode S communication messages The Mode S ATC communications system supporting personalized exchanges between ATC ground stations and Mode S transponder-equipped aircraft comprises: - a set of 25 standard messages for station-aircraft uplinks (Uplink format) identified UFxx - another set of 25 standard messages for downlinks (Downlink format) identified DFxx. The message may be long or short and contain either 56 or 112 bits. Each message consists of specific fields with bit combinations that have specific meanings. Two fields, however, have an identical definition for all messages: - the message-type field consisting of bits 1 to 5 whose coding translates the format decimal value into binary - the address field containing the last 24 bits of the message (bits 33 to 56 or bits 89 to 112 depending on whether the message is short or long). These 24 bits contain the Mode S address of the transmitter.

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TCAS - Mode S - Interrogation and Reply Figure 012   R EFF : ALL  34-43-00 Page 62   Config-1 Nov 01/09  CES

 

The TCAS uses this bidirectional link capability to communicate with other TCAS equipped aircraft to coordinate avoidance maneuvers. It may also dialog with ground stations: these stations have the possibility of monitoring and modifying its action. In the Mode S message set, the TCAS uses only six UF-type messages and seven DF-type messages. These messages are: - UF0, UF4, UF5, UF16, UF20, UF21 - DF0, DF4, DF5, DF11, DF16, DF20, DF21. The following two figures give the list of messages used by the TCAS for communications with other aircraft and with ground stations. They are followed by the definition of the fields used in the messages. NOTE : The TCAS only uses short messages (56 bits). ____ (Ref. Fig. 013, 014)

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TCAS - Message Uplink Format Figure 013   R EFF : ALL  34-43-00 Page 64   Config-1 Nov 01/09  CES

 

TCAS - Message Downlink Format Figure 014   EFF : 001-049, 101-149, 151-199, 201-249,  34-43-00 Page 65 301-399, 401-499,  Config-1 May 01/09  CES

 

DEFINITION OF UPLINK FORMAT MESSAGE FIELDS ------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | |-------------|----------------|----------------------------------------------| | AP | ADDRESS PARITY | Coded address with parity check | | AQ | ACQUISITION | Indicates if it is an interrogation message; | | | | 1 = interrogation | | DI | DESIGNATOR | Specifies type of information contained in SD| | | IDENT | field | | MA | MESSAGE | Used by ground station to transmit a TCAS SL | | | Comm-A | command to a TCAS-equipped aircraft | | MU | MESSAGE | Used by TCAS to transmit to other aircraft RA| | | Comm-U | coordination information (under fields UDS, | | | | MTB, CVC, VRC, CHC, HRC, HSB, VSB) | | PC | PROTOCOL | Operating commands to the transponder | | RL | REPLY LENGTH | Indicates if message is short (0) or long (1)| | RR | REPLY REQUEST | Length and content of reply information | | | | requested by the interrogator | | SD | SPECIAL | Contains control codes affecting the | | | DESIGNATOR | transponder protocol | ------------------------------------------------------------------------------DEFINITION OF DOWNLINK FORMAT MESSAGE FIELDS ------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | |-------------|----------------|----------------------------------------------| | AA | ADDRESS | Mode S address in the clear in 24 bits | | | ANNOUNCED | | | AC | ALTITUDE CODE | Information indicating aircraft altitude | | AP | ADDRESS PARITY | Coded address with parity check | | CA | CAPABILITY | Transponder capability | | DR | DOWNLINK | Requests extraction of downlink message by | | | REQUEST | the interrogator (existing RA) | | FS | FLIGHT STATUS | Flight status of the aircraft: ground, | | | | flight, alert, SPI | | ID | IDENTIFICATION | Contains the Mode A identification code | | | CODE | | | MB | MESSAGE | Indicates Advisory content to the ground | | | Comm-B | station | | MV | MESSAGE | Contains ARA, RAC, VDS subfields used for | | | Comm-V | coordination | | RI | REPLY | Type of reply and airspeed capability | | | INFORMATION | | | SL | SENSITIVITY | TCAS current sensitivity level | | | LEVEL | |

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------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | |-------------|----------------|----------------------------------------------| | UM | UTILITY MESSAGE| Transponder status readouts | | VS | VERTICAL STATUS| Aircraft status: 0 = airborne, 1 = ground | ------------------------------------------------------------------------------R

**ON A/C 051-099, 251-299, 501-509, 511-526, 528-599, (c) Mode S communication messages The Mode S ATC communications system supporting personalized exchanges between ATC ground stations and Mode S transponder-equipped aircraft comprises: - a set of 25 standard messages for station-aircraft uplinks (Uplink format) identified UFxx - another set of 25 standard messages for downlinks (Downlink format) identified DFxx. The message may be long or short and contain either 56 or 112 bits. Each message consists of specific fields with bit combinations that have specific meanings. Two fields, however, have an identical definition for all messages: - the message-type field consisting of bits 1 to 5 whose coding translates the format decimal value into binary - the address field containing the last 24 bits of the message (bits 33 to 56 or bits 89 to 112 depending on whether the message is short or long). These 24 bits contain the Mode S address of the transmitter. The TCAS uses this bidirectional link capability to communicate with other TCAS equipped aircraft to coordinate avoidance maneuvers. It may also dialog with ground stations: these stations have the possibility of monitoring and modifying its action. In the Mode S message set, the TCAS uses only six UF-type messages and eight DF-type messages. These messages are: - UF0, UF4, UF5, UF16, UF20, UF21 - DF0, DF4, DF5, DF11, DF16, DF17, DF20, DF21. The following two figures give the list of messages used by the TCAS for communications with other aircraft and with ground stations. They are followed by the definition of the fields used in the messages. (Ref. Fig. 013, 014A)

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TCAS - Message Downlink Format Figure 014A   R EFF : 051-099, 251-299, 501-509, 511-526,  34-43-00 Page 68 528-599,  Config-1 Feb 01/10  CES

 

DEFINITION OF UPLINK FORMAT MESSAGE FIELDS ------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | |-------------|----------------|----------------------------------------------| | AP | ADDRESS PARITY | Coded address with parity check | | AQ | ACQUISITION | Indicates if it is an interrogation message; | | | | 1 = interrogation | | DI | DESIGNATOR | Specifies type of information contained in SD| | | IDENT | field | | MA | MESSAGE | Used by ground station to transmit a TCAS SL | | | Comm-A | command to a TCAS-equipped aircraft | | MU | MESSAGE | Used by TCAS to transmit to other aircraft RA| | | Comm-U | coordination information (under fields UDS, | | | | MTB, CVC, VRC, CHC, HRC, HSB, VSB) | | PC | PROTOCOL | Operating commands to the transponder | | RL | REPLY LENGTH | Indicates if message is short (0) or long (1)| | RR | REPLY REQUEST | Length and content of reply information | | | | requested by the interrogator | | SD | SPECIAL | Contains control codes affecting the | | | DESIGNATOR | transponder protocol | ------------------------------------------------------------------------------DEFINITION OF DOWNLINK FORMAT MESSAGE FIELDS ------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | |-------------|----------------|----------------------------------------------| | AA | ADDRESS | Mode S address in the clear in 24 bits | | | ANNOUNCED | | | AC | ALTITUDE CODE | Information indicating aircraft altitude | | AP | ADDRESS PARITY | Coded address with parity check | | CA | CAPABILITY | Transponder capability | | DR | DOWNLINK | Requests extraction of downlink message by | | | REQUEST | the interrogator (existing RA) | | FS | FLIGHT STATUS | Flight status of the aircraft: ground, | | | | flight, alert, SPI | | ID | IDENTIFICATION | Contains the Mode A identification code | | | CODE | | | MB | MESSAGE | Indicates Advisory content to the ground | | | Comm-B | station | | MV | MESSAGE | Contains ARA, RAC, VDS subfields used for | | | Comm-V | coordination | | RI | REPLY | Type of reply and airspeed capability | | | INFORMATION | | | SL | SENSITIVITY | TCAS current sensitivity level | | | LEVEL | |

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------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | |-------------|----------------|----------------------------------------------| | UM | UTILITY MESSAGE| Transponder status readouts | | VS | VERTICAL STATUS| Aircraft status: 0 = airborne, 1 = ground | ------------------------------------------------------------------------------R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, B. Measurement of Intruder Parameters (1) Principle (a) Determination of relative altitude Upon confirmed transponder reception, the TCAS starts to interrogate the intruder. Its altitude is transmitted directly in the reply (standard barometric altitude) and this information is used to determine the relative altitude of the two aircraft, by calculating the barometric altitude difference. This computation is, however, only possible with respect to Mode C or Mode S transponder-equipped aircraft. (Ref. Fig. 015) (b) Range measurement The range is calculated by measuring the elapsed time between transmission of the interrogation signal and return of the reply transmitted by the intruder. Aircraft are detected from a minimum range of 14 NM. (c) Determination of Azimuth There are several methods for calculating the angle of reception of a radio-electric signal with respect to a reference direction such as the aircraft centerline. The technique used in the TCAS II computer is the interferometer system. The interferometry principle is based on a comparison of signal phases received by four independent elements of the directional antenna, taken in pairs. With two poles, E2 and E4, the phase difference of signals received on the two elements depends on the angle of reception of these signals since the difference in distance to the source of the two reception poles varies with this angle. (Ref. Fig. 016) If the distance separating the two poles, and the source signal wavelength are known, the following ratio is obtained:

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TCAS - Relative Altitude Calculation Principle Figure 015   R EFF : ALL  34-43-00 Page 71   Config-1 Nov 01/09  CES

 

TCAS - Determination of Azimuth Figure 016   R EFF : 001-049, 101-105, 151-199, 501-509,  34-43-00 Page 72 511-526, 528-599,  Config-1 Feb 01/10  CES

 

d S2-S4 = -------- x 360 x sin B Lambda where B S2-S4 d Lambda

: : : : f

source signal reception angle phase difference of signal received on poles E2 and E4 distance between the two poles signal wavelength, i.e. for = 1090 MHz, 3.10expnt8/1.09 x 10expnt9 = 0.2752 m.

To calculate angle B, the TCAS uses 4 elements installed perpendicularly two by two which gives: d S2-S4 = -------- x 360 x sin B Lambda d S1-S3 = -------- x 360 x cos B Lambda and therefore: S2 - S4 B = Arc tan --------S1 - S3 If the antenna is aligned on the aircraft centerline, angle B represents the source azimuth and may be used to indicate the intruders bearing on the ND. **ON A/C 051-099, 251-299, B. Measurement of Intruder Parameters (1) Principle (a) Determination of relative altitude Upon confirmed transponder reception, the TCAS starts to interrogate the intruder. Its altitude is transmitted directly in the reply (standard barometric altitude) and this information is used to determine the relative altitude of the two aircraft, by calculating the barometric altitude difference. This computation is, however, only possible with respect to Mode C or Mode S transponder-equipped aircraft. (Ref. Fig. 015)

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(b) Range measurement The range is calculated by measuring the elapsed time between transmission of the interrogation signal and return of the reply transmitted by the intruder. Aircraft are detected from a minimum range of 14 NM. (c) Determination of bearing Two basic means exist for performing the direction finding function required by the TCAS: one based on phase and the other one based on amplitude. The amplitude monopulse technique is used. This system is a four element, vertically polarized, monopole array which is capable of transmitting in 4 selectable directions at 1030 MHz and receiving omnidirectionally with bearing at 1090 MHz. The amplitude monopulse system generates four separate cardioid antenna patterns, each with its own receiver channel to view all four 90 degree sectors simultaneously (forward, aft, left and right sectors). The bearing angle of a target is determined by the amplitude ratio of adjacent patterns. The TCAS takes a ratio of the amplitude of the two strongest signals from two 90-degree antenna beams to determine a bearing angle. This technique also prevents a bearing measurement from being reflected into a wrong quadrant. Because an amplitude ratio is used, distortions in the antenna patterns tend to be cancelled out. When transmitting, the TCAS computer interrogates one sector at a time using a whisper-shout sequence of stepped power level interrogations. **ON A/C 106-149, 201-249, 301-399, 401-499, B. Measurement of Intruder Parameters (1) Principle (a) Determination of relative altitude Upon confirmed transponder reception, the TCAS starts to interrogate the intruder. Its altitude is transmitted directly in the reply (standard barometric altitude) and this information is used to determine the relative altitude of the two aircraft, by calculating the barometric altitude difference. This computation is, however, only possible with respect to Mode C or Mode S transponder-equipped aircraft. (Ref. Fig. 015)

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(b) Range measurement The range is calculated by measuring the elapsed time between transmission of the interrogation signal and return of the reply transmitted by the intruder. Aircraft are detected from a minimum range of 14 NM. (c) Determination of Azimuth There are several methods for calculating the angle of reception of a radio-electric signal with respect to a reference direction such as the aircraft centerline. The TCAS utilizes a four-element antenna and a form of phase interferometry to derive bearing from the received signal. The interferometry principle is based on a comparison of signal phases received by four independent elements of the directional antenna. For any given direction of reception, three antenna elements and their corresponding receiver channels are used. The elements which are used are the one physically positioned in the center of the quadrant being interrogated and the elements adjacent to it. Two phase measurements are performed: one corresponding to the difference in phase between the center element and the element on its right, and one corresponding to the phase difference between the center element and the element on its left. These two signals are converted from analog to digital information and stored. The bearing is calculated by reading the phase detector outputs, taking the ratio of the phase detector outputs with respect to each other, and performing a table lookup which relates the ratio to the phase difference from beam center. R

**ON A/C ALL (d) Tracking Once identified, the intruders are tracked by a series of interrogation-replies in Mode C only all-call for Mode C transponder-equipped aircraft, and in Mode S for Mode S transponder-equipped aircraft. These exchanges permit the TCAS to periodically update the altitude, range and bearing data for each intruder and to compute the range rate and altitude rate variations. These data are then used to determine the time separating the two aircraft from their closest point of approach.

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(e) Broadcast messages Every ten seconds, the TCAS transmits a broadcast message intended to inform nearby aircraft, themselves equipped with a TCAS, of the presence of a TCAS-equipped aircraft in their traffic area. These messages, received by the Mode S transponders, are communicated to the TCAS computer to enable it to know the number of TCAS-equipped aircraft in its detection envelope. This information is then used in the interference limitation formulas whose results modulate the Mode S interrogation output power level in inverse proportion to the number of aircraft. This reduces the number of non-elicited replies received by ground ATC stations. The messages transmitted are of the uplink format type UF = 16 with the Mode S 24 bit address of the interrogating TCAS included in the MID field (bits 65 to 88) with the UDS field (bits 33 to 40) containing the code F50. No response is expected for this type of message. (f) Communications frequencies Communications between two aircraft are always crossed between transponder and TCAS. The TCAS transmits at a frequency of 1030 MHz to the transponder of the other aircraft, whose reply signals are at a frequency of 1090 MHz to the TCAS receiver. This choice allows system compatibility with ground station-transponder links as the ground stations use the same frequencies as the TCAS. (Ref. Fig. 017) C. Coordination Two TCAS-equipped aircraft must coordinate their maneuvers to avoid the flight path corrections ordered by each TCAS resulting in a hazardous situation. (1) Coordination principle In most cases of encounters between two TCAS-equipped aircraft, mutual identification is almost but not quite simultaneous, with sufficient time lag to establish the priority necessary for the coordination process. The first aircraft to detect a potentially dangerous configuration computes a deviation maneuver sense and communicates it to the other aircraft. This aircraft takes the information into account and in turn computes a correction.

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TCAS - Communication Principle Figure 017   R EFF : ALL  34-43-00 Page 77   Config-1 Nov 01/09  CES

 

If two aircraft detect each other at exactly the same time and simultaneously transmit coordination messages containing incompatible deviation senses it is, by convention, the aircraft that has the highest Mode S address that cancels its trajectory correction. A time delay in the display of orders on the display units avoids opposing orders. (2) Communications protocol Communications between two aircraft comprises three phases: (a) Detection phase The TCAS receives squitter messages transmitted by the transponder of the intruder aircraft. These are DF11-type messages transmitted periodically at one second intervals and intended to enable its detection and identification. This message essentially uses two fields: - an AA (Address Announced) field containing the Mode S address which must be acknowledged - A PI (parity interrogator Identity) field which is the result of a parity encoding using a method of polynominal multiplication. On reception, the Address Announced field is multiplied by the same polynominal and the result is compared with the received value. (b) Surveillance phase After detection, a surveillance phase starts. This phase is composed of an acquisition part and a tracking part. 1 _

Acquisition interrogation When the TCAS receives a squitter and acquires the Mode S address of the intruder it enters into contact by transmitting a UFO-type message (Short special surveillance interrogation) with the following specific fields: - bit 9, RL = 0: reply message length requested short (56 bits) - bit 14, AQ = 1: acquisition-type message indication.

2 _

Acquisition reply The intruders transponder replies to this request by a DFO message containing the following information: - bit 6, VS: Vertical Status, = 1 if the aircraft is on the ground, = 0 if the aircraft is airborne - bits 9 to 11, SL: Sensitivity level indicates in which sensitivity level its TCAS is operating - bits 14 to 17, RI: combinations of bits, from values 8 to 15, specify the maximum speed the aircraft can reach. The other combinations are not used

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- bits 20 to 32, AC: aircraft altitude code indicating the barometric altitude. 3 _

Tracking interrogation After its acquisition, the intruder is tracked by UFO-type interrogations with the following field values: - RL = 0: reply message length requested short - AQ = 0: not an acquisition message.

4 _

Tracking reply The intruders transponder replies with a DFO message indicating altitude and TCAS sensitivity level by a combination of fields SL and RI: - SL: bits 9 to 11 - RI: bits 14 to 17, combination values 0 to 7. Values 8 to 15 are not used - AC: bits 20 to 32, aircraft altitude code.

(c) Coordination phase If the intruder becomes a threat, the TCAS programs a deviation maneuver to avoid a risk of collision. A coordination procedure is initiated between the two aircraft with an exchange of the following messages: 1 _

Coordination interrogation The TCAS transmits a UF16 Long Special Surveillance message whose fields contain the following indications:

--------------------------------------------------------------------| BITS | FIELD | INDICATION | |-------|--------|--------------------------------------------------| | 9 | RL | = 1: reply message length requested long | | 14 | AQ | = 0: non-acquisition type interrogation | | 33-40 | UDS | U Definition Subfield - defines the other data | | | | in the MU field (Comm-U), composed of bits 42 | | | | to 88 | | 42 | MTB | Indicates multiple threat processing | | 43-44 | CVC | Cancel Vertical resolution advisory Complement - | | | | used to cancel an RA complement sent earlier to | | | | an intruder | | 45-46 | VRC | Vertical Resolution advisory Complement - used to| | | | transmit an RA vertical complement to the intru- | | | | der requesting it not to modify its trajectory | | | | (dont climb, dont descend) | | 47-49 | CHC | Cancel Horizontal resolution advisory Complement-| | | | not used in TCAS II | | 50-52 | HRC | Horizontal Resolution advisory Complement - not |

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--------------------------------------------------------------------| BITS | FIELD | INDICATION | |-------|--------|--------------------------------------------------| | | | used in TCAS II | | 53-55 | | not used | | 56-60 | HSB | Encoded Sense bits for Horizontal resolution | | | | advisory complement - not used in TCAS II | | 61-64 | VSB | Encoded Sense Bits for Vertical resolution advi- | | | | sory complement - parity code to protect the 4 | | | | vertical command bits (43-46) | | 65-88 | MID | Interrogator TCAS-equipped aircraft Mode S | | | | address. | --------------------------------------------------------------------2 _

Coordination reply After acquisition of this message, the intruders transponder replies with a Long Special Surveillance DF 16 type message, containing the information previously transmitted to it by its own TCAS:

--------------------------------------------------------------------| BITS | FIELD | INDICATION | |------ |-------|---------------------------------------------------| | 6 | VS | Vertical Status - indicates whether aircraft is | | | | on ground or airborne | | 9-11 | SL | With RI, SL indicates the sensitivity level at | | | | which the interrogated aircrafts TCAS is | | | | operating | | 14-17 | RI | Reply Information | | 20-32 | AC | Altitude Code - contains aircraft altitude | | | | encoded in 100 ft increments if bit 28 equals 0, | | | | and in 25 ft increments if bit 28 equals 1 | | 33-40 | VDS | V Definition Subfield defines the contents of the| | | | data and coding in the field MV (Comm V) composed| | | | of bits 41 to 88 | | 41-54 | ARA | Active Resolution Advisory - indicates the RA | | | | type currently generated by the TCAS | | 55-58 | RAC | Resolution Advisory Complement - Indicates the RA| | | | complement type currently received from other | | | | TCAS-equipped aircraft | | 59-88 | | Not used | ---------------------------------------------------------------------

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(d) Correspondence of radio messages with ARINC 429 words The coordination information exchanged between two aircraft transits via ARINC 429 buses linking the transponder to the TCAS. The following table gives the correspondence between the two types of link: --------------------------------------------------| 1 - TRANSPONDER TO TCAS | |-------------------------------------------------| | | RADIO MESSAGE | ARINC MESSAGE | |---------|-------------------|-------------------| | FIELD | MESSAGE | BITS | LABEL | BITS | |---------|---------|---------|---------|---------| | MTB | UF16 | 42 | 271 | 09 | | CVC | | 43-44 | | 10-11 | | VRC | | 45-46 | | 12-13 | | CHC | | 47-49 | | 14-16 | | HRC | | 50-52 | | 17-19 | | HSB | | 56-60 | | 20-24 | | VSB | | 61-64 | | 25-28 | ----------------------------------------------------------------------------------------------------| 2 - TCAS TO TRANSPONDER | |-------------------------------------------------| | | RADIO MESSAGE | ARINC MESSAGE | |---------|-------------------|-------------------| | FIELD | MESSAGE | BITS | LABEL | BITS | |---------|---------|---------|---------|---------| | SL | DF16 | 09-11 | 274 | 23-25 | | RI | | 14-17 | | 26-29 | | ARA | | 41-54 | 273 | 12-25 | | RAC | | 55-58 | | 26-29 | --------------------------------------------------D. Principles of Computation In the TCAS, target aircraft are categorized depending on specific criteria varying in function of altitude. The TCAS essentially uses two types of information to perform this classification: - the relative altitude between two aircraft, known by the difference of their barometric altitudes - the distance or range separating them. (Ref. Fig. 018) Acquisition of these two parameters at regular intervals (tracking) enables their variations to be calculated: - altitude rate

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TCAS - Definition of Main Parameters Figure 018   R EFF : ALL  34-43-00 Page 82   Config-1 Nov 01/09  CES

 

- range rate. Assessment of the potential threat represented by an intruder depends on two criteria determined with respect to a point in the traffic area called Closest Point of Approach (CPA). This is the point of minimum distance between the two aircraft, assuming that their trajectories do not deviate. The two criteria are: - vertical separation at CPA - time left before reaching CPA. (1) Projected vertical separation The threat is evaluated by calculating the vertical separation between the two aircraft at the closest point of approach. (Ref. Fig. 019) The TCAS computer processes the current altitude and altitude rate of the intruder to predict whether it will be within limits considered dangerous at the closest point of approach. Intruder 1 penetrates the altitude zone delimited by the upper and lower thresholds but when it reaches CPA, it will be outside this zone. Therefore no advisory will be issued. However, when intruder 2 reaches CPA it is still inside this zone and therefore an advisory will be issued. R R

**ON A/C 001-049, 051-099, 101-105, 151-199, 251-299, 501-509, 511-526, 528-599, (2) Time to intercept (TAU) The TCAS does not need to locate the CPA in space, but rather it needs to know the time to intercept for two aircraft. For example, if two aircraft are approaching on the same axis on a collision course, this time is the ratio of distance between them to the sum of their speeds. D T = --------V1 + V2 More generally, the TCAS uses range and range rate measurement to compute this time: RANGE R(NM) TAU = ------------ i.e. TAU(s) = 3600 -------RANGE RATE RR (Kts) With the risk of collision being in inverse proportion to this time, trajectory correction orders are initiated by crossing predetermined time thresholds whose values depend on the altitude layer in which the aircraft is located.

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TCAS - Threat Evaluation Figure 019   R EFF : ALL  34-43-00 Page 84   Config-1 Nov 01/09  CES

 

This method of calculation avoids the initiation of corrections if, from a certain distance, the TAU trend is inverted even though the distance separating the two aircraft decreases. For example, in the case of two aircraft moving on parallel axes but in the opposite direction. (Ref. Fig. 020) The curve represents the TAU variation before the closest point of approach. (Ref. Fig. 021) This time decreases as the range decreases, reaches a minimum when the intruders relative bearing is 45 deg. and then increases rapidly. If the time corresponding to a predetermined threshold has not been reached before the minimum TAU value, a trajectory correction is not initiated. Certain conditions exist, however, in which this formula may prove insufficient. This may arise for example when two aircraft fly in the same direction with a very low closure rate. In this case, the range/range rate ratio gives a high TAU value whereas in fact, the two aircraft could be very near. The TCAS uses a slightly different formula to preclude this situation: range - X (DMOD) to the power two TAU = ---------with X = --------range rate range This formula represents an estimate of the time the aircraft would take to penetrate a sphere around the intruder with a radius equal to (DMOD)expnt2/range. The DMOD coefficients are in function of altitude, ranging from 0.20 NM for 1000-2350 ft, to 1.1 NM above 30,000 ft as shown below (for the RA DMOD): Altitude DMOD TA DMOD RA (ft) (NM) (NM) 0-1000 0.30 1000-2350 0.33 0.20 2350-5000 0.48 0.35 5000-10000 0.75 0.55 10,000-20,000 1.0 0.80 >20,000 1.3 1.1 **ON A/C 201-209, (2) Time to intercept (TAU) The TCAS does not need to locate the CPA in space, but rather it needs to know the time to intercept for two aircraft. For example, if two aircraft are approaching on the same axis on a collision course, this time is the ratio of distance between them to the sum of their speeds.

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TCAS - TAU Minimum Configuration Figure 020   R EFF : ALL  34-43-00 Page 86   Config-1 Nov 01/09  CES

 

TCAS - TAU Curve Figure 021   R EFF : ALL  34-43-00 Page 87   Config-1 Nov 01/09  CES

 

R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R

D T = --------V1 + V2 More generally, the TCAS uses range and range rate measurement to compute this time: RANGE R(NM) TAU = ------------ i.e. TAU(s) = 3600 -------RANGE RATE RR (Kts) With the risk of collision being in inverse proportion to this time, trajectory correction orders are initiated by crossing predetermined time thresholds whose values depend on the altitude layer in which the aircraft is located. This method of calculation avoids the initiation of corrections if, from a certain distance, the TAU trend is inverted even though the distance separating the two aircraft decreases. For example, in the case of two aircraft moving on parallel axes but in the opposite direction. (Ref. Fig. 020, 021) The curve represents the TAU variation before the closest point of approach. (Ref. Fig. 021) This time decreases as the range decreases, reaches a minimum when the intruders relative bearing is 45 deg. and then increases rapidly. If the time corresponding to a predetermined threshold has not been reached before the minimum TAU value, a trajectory correction will not be initiated. Certain conditions exist, however, in which this formula may prove insufficient. This may arise for example when two aircraft fly in the same direction with a very low closure rate. In this case, the range/range rate ratio gives a high TAU value whereas in fact, the two aircraft could be very near. The TCAS uses a slightly different formula to preclude this situation: range - X (DMOD) to the power two TAU = ---------with X = --------range rate range This formula represents an estimate of the time the aircraft would take to penetrate a sphere around the intruder with a radius equal to (DMOD)expnt2/range. The DMOD coefficients are in function of altitude, ranging from 0.20 NM for 1000-2350ft, to 1.1 NM above 20,000 ft as shown below:

  EFF : 201-209,  34-43-00 Page 88   Config-1 May 01/09  CES

 

R R R R R R R R

Altitude (ft) 0-1000 1000-2350 2350-5000 5000-10000 10000-20000 more than 20000

DMOD (NM) 0.20 0.35 0.55 0.80 1.10

**ON A/C 106-149, 201-207, 210-249, 301-399, 401-499, Post SB Post SB

34-1179 For A/C 201-207, 34-1238 For A/C 201-207,

(2) Time to intercept (TAU) The TCAS does not need to locate the CPA in space, but rather it needs to know the time to intercept for two aircraft. For example, if two aircraft are approaching on the same axis on a collision course, this time is the ratio of distance between them to the sum of their speeds. D T = --------V1 + V2 More generally, the TCAS uses range and range rate measurement to compute this time: RANGE R(NM) TAU = ------------ i.e. TAU(s) = 3600 -------RANGE RATE RR (Kts) With the risk of collision being in inverse proportion to this time, trajectory correction orders are initiated by crossing predetermined time thresholds whose values depend on the altitude layer in which the aircraft is located. This method of calculation avoids the initiation of corrections if, from a certain distance, the TAU trend is inverted even though the distance separating the two aircraft decreases. For example, in the case of two aircraft moving on parallel axes but in the opposite direction. (Ref. Fig. 020, 021) The curve represents the TAU variation before the closest point of approach. (Ref. Fig. 021) This time decreases as the range decreases, reaches a minimum when the intruders relative bearing is 45 deg. and then increases rapidly. If the time corresponding to a predetermined threshold has not been reached before the minimum TAU value, a trajectory correction will not be initiated.

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Certain conditions exist, however, in which this formula may prove insufficient. This may arise for example when two aircraft fly in the same direction with a very low closure rate. In this case, the range/range rate ratio gives a high TAU value whereas in fact, the two aircraft could be very near. The TCAS uses a slightly different formula to preclude this situation: range - X (DMOD) to the power two TAU = ---------with X = --------range rate range This formula represents an estimate of the time the aircraft would take to penetrate a sphere around the intruder with a radius equal to (DMOD)expnt2/range. The DMOD coefficients are in function of altitude, ranging from 0.20 NM for 1000-2350ft, to 1.1 NM above 20,000 ft as shown below: Altitude DMOD (ft) (NM) 0-1000 1000-2350 0.20 2350-5000 0.35 5000-10000 0.55 10000-20000 0.80 20000-42000 1.10 above 42000 1.10 **ON A/C 001-049, 051-061, 101-149, 201-249, 301-399, 401-499, E. Definition of Target Aircraft Target aircraft are divided into four categories: OTHER - PROXIMATE TRAFFIC ADVISORY (TA) RESOLUTION ADVISORY (RA). NOTE : Since the Display Management Computers (DMC) do not sort the OTHER ____ intruders, the latter are not presented on the NDs. Their presentation is optional. It is activated by pin programming and replacement of ATC/TCAS control unit (ALL TRAFFIC configuration). (1) Other traffic (optional) Aircraft detected by the TCAS are defined as OTHER traffic if: - they are within + or - 2700 ft vertically of own aircraft - and if they do not enter in the PROXIMATE, TA or RA categories. These targets are represented by a white diamond, outline only, on the ND.

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(2) Proximate aircraft Targets are defined as proximate traffic if the difference between their altitude and that of the TCAS aircraft is less than 1200 ft and if their range is within 6 NM. Their presentation on the ND is conditioned by the presence of another TA or RA intruder. Generally aircraft not in the immediate vicinity enter into this category. Depending on their trajectory, they may: - conserve this status and move away without an advisory being declared. In this case the pilot is informed of their presence on the ND by a white filled diamond symbol and can monitor their progress, or - have a trajectory liable to lead to a conflict situation and in this case they require a traffic advisory and their symbol changes.

R R

(3) Traffic advisory aircraft (Ref. Fig. 022) When an intruder is relatively near but does not represent an immediate threat the TCAS issues a traffic advisory. Its presence is displayed on the ND by an amber filled circle. Its display is accompanied by an aural alert: Traffic Traffic. The pilot is therefore aware of its presence and knows its range and relative bearing. Its display is linked to vertical separation and time TAU before CPA values. Depending on its trajectory, an intruder may conserve this status and move away, or it may become a collision threat. In this case avoidance maneuvers are suggested to the pilot via a resolution advisory. (4) Resolution advisory aircraft (Ref. Fig. 022) In resolution displays, the intruder is represented on the ND by a red filled square and corrective orders are issued on the vertical speed scale of the PFD. Crossing into resolution advisory occurs for a TAU time threshold 10 to 15 seconds lower than a traffic advisory threshold. Vertical separation between the two aircraft is also taken into account for this category. There are two types of resolution advisory, in function of the vertical separation value: - Preventive Advisories - Corrective Advisories.

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TCAS - Threat Threshold Scale Figure 022   R EFF : ALL  34-43-00 Page 92   Config-1 Nov 01/09  CES

 

(a) Preventive Advisory In this case the vertical separation is less than a threshold S1 and greater than a threshold S2. The advisory instructs the pilot to avoid certain deviations from current vertical rate, this measure being sufficient to avoid a risk of collision. On the PFD speed scale, the forbidden values are indicated by red sectors. (b) Corrective advisory In this case, the vertical separation is lower than the threshold S2. On the vertical speed scale of the PFD, colored sectors depict avoidance maneuvers to be performed: - red sector = forbidden vertical speeds - green fly to sector = a vertical speed range to be respected. (Ref. Fig. 022) **ON A/C 062-099, E. Definition of Target Aircraft Target aircraft are divided into four categories: OTHER - PROXIMATE TRAFFIC ADVISORY (TA) - RESOLUTION ADVISORY (RA). (1) Other aircraft Depending on the Above/Below selection, targets are defined as other intruders if their: - altitude is between 2700 ft and 9900 ft above or below the TCAS equipped aircraft - distance is more than 14 NM. Their presentation on the ND is permanent (TFC function selected = full time display function activated) or conditioned by the presence of a TA/RA intruder (TA or TA/RA function selected). Depending on their trajectory, they may: - conserve this status and move away without an advisory being declared. In this case the pilot is informed of their presence on the ND by a white outlined diamond symbol and can monitor their progress, or - have a trajectory liable to lead to a conflict situation and in this case they require a new category and a symbol change.

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(2) Proximate aircraft Targets are defined as proximate traffic if the difference between their altitude and that of the TCAS aircraft is less than 1200 ft and if their range is within 6 NM. Their presentation on the ND is permanent (TFC function selected = full time display function activated) or conditioned by the presence of a TA/RA intruder (TA or TA/RA function selected). Generally aircraft not in the immediate vicinity enter into this category. Depending on their trajectory, they may: - conserve this status and move away without an advisory being declared. In this case the pilot is informed of their presence on the ND by a white filled diamond symbol and can monitor their progress, or - have a trajectory liable to lead to a conflict situation and in this case they require a traffic advisory and their symbol changes. (3) Traffic advisory aircraft (Ref. Fig. 022) When an intruder is relatively near but does not represent an immediate threat the TCAS issues a traffic advisory. Its presence is displayed on the ND by an amber filled circle. Its display is accompanied by an aural alert: Traffic Traffic. The pilot is therefore aware of its presence and knows its range and relative bearing. Its display is linked to vertical separation and time TAU before CPA values. Depending on its trajectory, an intruder may conserve this status and move away, or it may become a collision threat. In this case avoidance maneuvers are suggested to the pilot via a resolution advisory. (4) Resolution advisory aircraft (Ref. Fig. 022) In resolution displays, the intruder is represented on the ND by a red filled square and corrective orders are issued on the vertical speed scale of the PFD. Crossing into resolution advisory occurs for a TAU time threshold 10 to 15 seconds lower than a traffic advisory threshold. Vertical separation between the two aircraft is also taken into account for this category. There are two types of resolution advisory, in function of the vertical separation value: - Preventive Advisories - Corrective Advisories.

  EFF : 062-099,  34-43-00 Page 94   Config-1 May 01/09  CES

 

(a) Preventive Advisory In this case the vertical separation is less than a threshold S1 and greater than a threshold S2. The advisory instructs the pilot to avoid certain deviations from current vertical rate, this measure being sufficient to avoid a risk of collision. On the PFD speed scale, the forbidden values are indicated by red sectors. (b) Corrective advisory In this case, the vertical separation is lower than the threshold S2. On the vertical speed scale of the PFD, colored sectors depict avoidance maneuvers to be performed: - red sector = forbidden vertical speeds - green fly to sector = a vertical speed range to be respected. (Ref. Fig. 022) R R

**ON A/C 001-049, 051-061, 101-105, 151-199, 251-299, 501-509, 511-526, 528-599, Post SB 34-1177 For A/C 001-049,101-105, E. Definition of Target Aircraft Target aircraft are divided into four categories: OTHER - PROXIMATE TRAFFIC ADVISORY (TA) RESOLUTION ADVISORY (RA). NOTE : Since the Display Management Computers (DMC) do not sort the OTHER ____ intruders, the latter are not presented on the NDs. Their presentation is optional. It is activated by pin programming and replacement of ATC/TCAS control unit (ALL TRAFFIC configuration). (1) Other traffic (optional) Aircraft detected by the TCAS are defined as OTHER traffic if: - they are in the area from +/- 1200 ft to +/- 9900ft, - and if they do not enter in the PROXIMATE, TA or RA categories. These targets are represented by a white diamond, outline only, on the ND. (2) Proximate aircraft Targets are defined as proximate traffic if the difference between their altitude and that of the TCAS aircraft is less than 1200 ft and if their range is within 6 NM. Their presentation on the ND is conditioned by the presence of another TA or RA intruder. Generally aircraft not in the immediate vicinity enter into this category. Depending on their trajectory, they may:

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- conserve this status and move away without an advisory being declared. In this case the pilot is informed of their presence on the ND by a white filled diamond symbol and can monitor their progress, or - have a trajectory liable to lead to a conflict situation and in this case they require a traffic advisory and their symbol changes. (3) Traffic advisory aircraft (Ref. Fig. 022) When an intruder is relatively near but does not represent an immediate threat the TCAS issues a traffic advisory. Its presence is displayed on the ND by an amber filled circle. Its display is accompanied by an aural alert: Traffic Traffic. The pilot is therefore aware of its presence and knows its range and relative bearing. Its display is linked to vertical separation and time TAU before CPA values. Depending on its trajectory, an intruder may conserve this status and move away, or it may become a collision threat. In this case avoidance maneuvers are suggested to the pilot via a resolution advisory. (4) Resolution advisory aircraft (Ref. Fig. 022) In resolution displays, the intruder is represented on the ND by a red filled square and corrective orders are issued on the vertical speed scale of the PFD. Crossing into resolution advisory occurs for a TAU time threshold 10 to 15 seconds lower than a traffic advisory threshold. Vertical separation between the two aircraft is also taken into account for this category. There are two types of resolution advisory, in function of the vertical separation value: - Preventive Advisories - Corrective Advisories. (a) Preventive Advisory In this case the vertical separation is less than a threshold S1 and greater than a threshold S2. The advisory instructs the pilot to avoid certain deviations from current vertical rate, this measure being sufficient to avoid a risk of collision. On the PFD speed scale, the forbidden values are indicated by red sectors.

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(b) Corrective advisory In this case, the vertical separation is lower than the threshold S2. On the vertical speed scale of the PFD, colored sectors depict avoidance maneuvers to be performed: - red sector = forbidden vertical speeds - green fly to sector = a vertical speed range to be respected. (Ref. Fig. 022) **ON A/C 001-049, 051-061, 101-105, 201-207, (c) Aural alerts Trajectory correction or holding visual orders are accompanied by synthesized voice announcements whose level cannot be adjusted by the pilot. These announcements are generated by the TCAS computer and broadcast via the cockpit loud speakers. These messages and their meanings are described below: - CLIMB, CLIMB, CLIMB. Climb at the rate shown by the green sector on the PFD (1500 ft/mn), - CLIMB, CROSSING CLIMB, CLIMB, CROSSING CLIMB. As above except that it further indicates that own flight path will cross through that of the intruder, - REDUCE CLIMB, REDUCE CLIMB. Reduce vertical speed to that shown by the green sector on the PFD, - INCREASE CLIMB, INCREASE CLIMB Follows a climb advisory. The vertical speed of the aircraft should be increased (2500 ft/mn), - CLIMB, CLIMB NOW, CLIMB, CLIMB NOW. Follows a descend advisory when a reversal in sense is required to achieve safe vertical separation from a maneuvering intruder, - DESCEND, DESCEND, DESCEND Descend at the rate indicated by the green sector on the PFD (-1500 ft/mn), - DESCEND, CROSSING DESCEND, DESCEND, CROSSING DESCEND As above except that it further indicates that own flight path will cross through that of the intruder, - REDUCE DESCENT, REDUCE DESCENT Reduce vertical speed to that shown by the green sector on the PFD, - INCREASE DESCENT, INCREASE DESCENT Follows a descend advisory. The vertical speed of the descent should be increased (-2500 ft/mn),

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- DESCEND, DESCEND NOW, DESCEND, DESCEND NOW Follows a climb advisory when a reversal in sense is required to achieve safe vertical separation from a maneuvering intruder. Two other aural advisories are also generated: - MONITOR VERTICAL SPEED, MONITOR VERTICAL SPEED Indicates that a forbidden vertical speed range exists (red sector) and that pilot must monitor vertical speed so as not to enter this range (Preventive Advisory). This message is spoken only once if softening from a previous corrective advisory, - CLEAR OF CONFLICT Indicates that separation has been achieved and range has started to increase. R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, Post SB

34-1177 For A/C 001-049,101-105, (c) Aural alerts Trajectory correction or holding visual orders are accompanied by synthesized voice announcements whose level cannot be adjusted by the pilot. These announcements are generated by the TCAS computer and broadcast via the cockpit loud speakers. These messages and their meanings are described below: - CLIMB, CLIMB Climb at the rate shown by the green sector on the PFD (1500 ft/mn), - CLIMB, CROSSING CLIMB, CLIMB, CROSSING CLIMB As above except that it further indicates that own flight path will cross through that of the intruder, - INCREASE CLIMB, INCREASE CLIMB Follows a climb advisory. The vertical speed of the aircraft should be increased (2500 ft/mn), - CLIMB, CLIMB NOW, CLIMB, CLIMB NOW Follows a descend advisory when a reversal in sense is required to achieve safe vertical separation from a maneuvering intruder, - DESCEND, DESCEND Descend at the rate indicated by the green sector on the PFD (-1500 ft/mn), - DESCEND, CROSSING DESCEND, DESCEND, CROSSING DESCEND As above except that it further indicates that own flight path will cross through that of the intruder, - ADJUST VERTICAL SPEED, ADJUST Reduce vertical speed to that shown by the green sector on the PFD,

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- INCREASE DESCENT, INCREASE DESCENT Follows a descend advisory. The vertical speed of the descent should be increased (-2500 ft/mn), - DESCEND, DESCEND NOW, DESCEND, DESCEND NOW Follows a climb advisory when a reversal in sense is required to achieve safe vertical separation from a maneuvering intruder. Three other aural advisories are also generated: - MONITOR VERTICAL SPEED Indicates that a forbidden vertical speed range exists (red sector) and that pilot must monitor vertical speed so as not to enter this range (Preventive Advisory), - MAINTAIN VERTICAL SPEED, MAINTAIN Indicates a non-crossing advisory type, maintains rate RAs (corrective), - MAINTAIN VERTICAL SPEED, CROSSING MAINTAIN Indicates an altitude crossing advisory type, maintains rate RAs (corrective). This message is spoken only once if softening from a previous corrective advisory, - CLEAR OF CONFLICT. Indicates that separation has been achieved and range has started to increase. **ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, Post SB Post SB

34-1179 For A/C 201-207, 34-1238 For A/C 201-207, (c) Aural alerts Trajectory correction or holding visual orders are accompanied by synthesized voice announcements whose level cannot be adjusted by the pilot. These announcements are generated by the TCAS computer and broadcast via the cockpit loud speakers. These messages and their meanings are described below: - CLIMB, CLIMB: Climb at the rate shown by the green sector on the PFD (1500 ft/min), - CLIMB, CROSSING CLIMB, CLIMB, CROSSING CLIMB: As above except that it further indicates that own flight path will cross through that of the intruder, - INCREASE CLIMB, INCREASE CLIMB: Follows a climb advisory. The vertical speed of the aircraft should be increased (2500 ft/min),

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- CLIMB, CLIMB NOW, CLIMB, CLIMB NOW: Follows a descend advisory when a reversal in sense is required to achieve safe vertical separation from a maneuvering intruder, - DESCEND, DESCEND: Descend at the rate indicated by the green sector on the PFD (-1500 ft/min), - DESCEND, CROSSING DESCEND, DESCEND, CROSSING DESCEND: As above except that it further indicates that own flight path will cross through that of the intruder, - INCREASE DESCENT, INCREASE DESCENT: Follows a descend advisory. The vertical speed of the descent should be increased (-2500 ft/min), - DESCEND, DESCEND NOW, DESCEND, DESCEND NOW: Follows a climb advisory when a reversal in sense is required to achieve safe vertical separation from a maneuvering intruder, - ADJUST VERTICAL SPEED, ADJUST: Reduce vertical speed to that shown by the green sector on the PFD. It can correspond to a corrective reduce climb or reduce descent. It can also represent a weakening of corrective RA. Four other aural advisories are also generated: - MONITOR VERTICAL SPEED: Indicates that a forbidden vertical speed range exists (red sector) and that pilot must monitor vertical speed so as not to enter this range (Preventive Advisory). - MAINTAIN VERTICAL SPEED, MAINTAIN: Indicates a non-crossing advisory type, maintains rate RAs (corrective). - MAINTAIN VERTICAL SPEED, CROSSING MAINTAIN: Indicates an altitude crossing advisory type, maintains rate RAs (corrective). These messages are spoken only once if softening from a previous corrective advisory, - CLEAR OF CONFLICT:

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Indicates that separation has been achieved and range has started to increase. **ON A/C 001-049, 101-105, (5) Advisory inhibit conditions In certain particular conditions, certain advisories are not generated as they could lead to the pilot adopting flight conditions that are hazardous or outside the aircrafts performance capability. (a) Low altitude inhibitions Ground proximity leads to the inhibition of those advisories liable to cause a hazardous situation at this level. In decreasing altitude, these are: - below 1450 ft above ground level (AGL) inhibition of Increase Descend resolution advisories (RA) - below 1200 ft AGL at take-off and 1000 ft AGL in approach, inhibition of Descend resolution advisories (RA) - inhibition of all resolution advisories (RA) and inhibition of aural traffic advisories (TA) below 1000 ft +/- 100 ft (1100 ft in climb, 900 ft in descent). (b) High altitude inhibition Above 48,000 ft, further climb orders are inapplicable as the aircraft performance capability does not permit them to be taken into account. As the certified envelope of the A320 is 39,000 ft, it means that there is no altitude limitation for the TCAS on the A320. Climb advisories are therefore inhibited above this altitude. (c) Advisory inhibit discretes Three discretes are used to manage priority between: - windshear/stall - GPWS - G/S - and the TCAS computer. The environmental alert priorities are: windshear/stall, GPWS G/S and then TCAS II. When TCAS II is inhibited, the TA ONLY mode is selected and the voice announcements are cancelled.

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(d) Rejection of signals from aircraft on ground (Ref. Fig. 023) Aircraft on the ground may reply to TCAS interrogations, producing an unnecessary overload in the processing and display of information. For this reason, the TCAS systematically eliminates responses from aircraft at an altitude below 180 ft when its own altitude is itself below 1700 ft AGL. But, as the altitude transmitted by the intruder is a barometric altitude with respect to sea level, the TCAS shall process this value to convert it into height above ground level in order to compare it with the 180 ft threshold. In the figure below, the intruders height above ground level can be deduced: Z i/s = Z t/s -(Z t/m - Z i/m) where: Z i/s = height of intruder above ground level Z i/m = altitude of intruder above sea level Z t/s = height of TCAS above ground level measured by radio altimeter Z t/m = altitude of TCAS above sea level measured by ADIRU. (e) Not Applicable R

**ON A/C 051-099, 251-299, (5) Advisory inhibit conditions In certain particular conditions, certain advisories are not generated as they could lead to the pilot adopting flight conditions that are hazardous or outside the aircrafts performance capability. (a) Low altitude inhibitions Ground proximity leads to the inhibition of those advisories liable to cause a hazardous situation at this level. In decreasing altitude, these are: - below 1550 +/- 100 ft above ground level (AGL) inhibition of Increase Descend resolution advisories (RA), - below 1100 +/- 100 ft AGL, inhibition of Descend resolution advisories (RA), - below 1000 ft +/- 100 ft AGL, TCAS automatic switching to TA Only mode (inhibition of all resolution advisories), - below 500 +/- 100 ft AGL (600 ft in climb, 400 ft in descent), inhibition of all resolution advisories (RA) and of aural traffic advisories (TA).

  R EFF : 001-049, 051-099, 101-105, 251-299,  34-43-00 Page A2   Config-1 Nov 01/09  CES

 

TCAS - Inhibition Condition Figure 023   R EFF : ALL  34-43-00 Page A3   Config-1 Nov 01/09  CES

 

(b) High altitude inhibition Above 48,000 ft, given by pin program (ref para. 3. E. (9)), further climb orders are inapplicable as the aircraft performance capability does not permit them to be taken into account. Climb advisories are therefore inhibited above this altitude. (c) Advisory inhibit discretes Three discretes are used to manage priority between: - windshear/stall, - Enhanced GPWS - G/S, - and the TCAS computer. The environmental alert priorities are: windshear/stall, Enhanced GPWS - G/S and then TCAS II. When TCAS II is inhibited, the TA ONLY mode is selected and the voice announcements are cancelled. (d) Rejection of signals from aircraft on ground (Ref. Fig. 023) Aircraft on the ground may reply to TCAS interrogations, producing an unnecessary overload in the processing and display of information. The ground logic aircraft declared on the ground is enabled when the own aircraft descends below 1650 ft AGL and when it climbs up to 1750 ft AGL (1700 +/- 50 ft.). Intruders are declared to be on-ground if they are within 360 ft from the ground when descending, and if they are within 400 ft from the ground when climbing (380 +/- 20 ft.). All on-ground intruders are displayed as non-threat traffic (white unfilled diamond). Intruders declared to be on-ground can never cause proximate, traffic or resolution advisory (TA, RA). But, as the altitude transmitted by the intruder is a barometric altitude with respect to sea level, the TCAS shall process this value to convert it into height above ground level in order to compare it with the 380 ft (plus or minus 20 ft) threshold. In the figure, the intruders height above ground level can be deduced: Z i/s = Z t/s -(Z t/m - Z i/m) where: Z i/s = height of intruder above ground level Z i/m = altitude of intruder above sea level Z t/s = height of TCAS above ground level measured by radio altimeter Z t/m = altitude of TCAS above sea level measured by ADIRU. NOTE : If the intruder is equipped with a Mode S transponder, the ____ ground/flight information is sent in the DF message. The TCAS directly knows if this intruder is on the ground.

  R EFF : 051-099, 251-299,  34-43-00 Page A4   Config-1 Nov 01/09  CES

 

(e) Rejection of non altitude reporting aircraft by the own aircraft The TCAS does not display non altitude reporting aircraft above 15,500 ft MSL. **ON A/C 201-207, (5) Advisory inhibit conditions In certain particular conditions, certain advisories are not generated as they could lead to the pilot adopting flight conditions that are hazardous or outside the aircrafts performance capability. (a) Low altitude inhibitions Ground proximity leads to the inhibition of those advisories liable to cause a hazardous situation at this level. In decreasing altitude, these are: - below 1450 ft above ground level (AGL) inhibition of Increase Descend resolution advisories (RA) - below 1200 ft AGL at take-off and 1000 ft AGL in approach, inhibition of Descend resolution advisories (RA) - below 1100 ft AGL at take-off and 900 ft AGL in approach, inhibition of all aural traffic advisories (TA) and all resolution advisories (RA). (b) High altitude inhibition Above 48,000 ft, further climb orders are inapplicable as the aircraft performance capability does not permit them to be taken into account. Climb advisories are therefore inhibited above this altitude. (c) Advisory inhibit discretes Three discretes are used to manage priority between: - windshear/stall - GPWS - G/S - and the TCAS computer. The environmental alert priorities are: windshear/stall, GPWS G/S and then TCAS II. When TCAS II is inhibited, the TA ONLY mode is selected and the voice announcements are cancelled. (d) Rejection of signals from aircraft on ground (Ref. Fig. 023) Aircraft on the ground may reply to TCAS interrogations, producing an unnecessary overload in the processing and display of information. The ground logic aircraft declared on the ground is enabled when the own aircraft descends below 1650 ft AGL and when it climbs up to 1750 ft AGL.

  R EFF : 051-099, 201-207, 251-299,  34-43-00 Page A5   Config-1 Nov 01/09  CES

 

All on-ground intruders are displayed as non-threat traffic white unfilled diamond. Intruders are declared to be on-ground if they are within 380 ft from the ground when descending, and if they are within 400 ft from the ground when climbing. Intruders declared to be on-ground can never cause proximate, traffic or resolution advisory. But, as the altitude transmitted by the intruder is a barometric altitude with respect to sea level, the TCAS shall process this value to convert it into height above ground level in order to compare it with the 380 ft (+ or - 20 ft) threshold. (e) Rejection of non altitude reporting aircraft by the own aircraft The TCAS does not display non altitude reporting aircraft above 15,500 ft MSL. R

**ON A/C 501-509, 511-526, 528-599, (5) Advisory inhibit conditions In certain particular conditions, certain advisories are not generated as they could lead to the pilot adopting flight conditions that are hazardous or outside the aircrafts performance capability. (a) Low altitude inhibitions Ground proximity leads to the inhibition of those advisories liable to cause a hazardous situation at this level. In decreasing altitude, these are: - below 1550 +/- 100 ft above ground level (AGL) inhibition of Increase Descend resolution advisories (RA), - below 1100 +/- 100 ft AGL, inhibition of Descend resolution advisories (RA), - below 1000 ft +/- 100 ft AGL, TCAS automatic switching to TA Only mode (inhibition of all resolution advisories), - below 500 +/- 100 ft AGL (600 ft in climb, 400 ft in descent), inhibition of all resolution advisories (RA) and of aural traffic advisories (TA). (b) High altitude inhibition Above 48,000 ft, further climb orders are inapplicable as the aircraft performance capability does not permit them to be taken into account. Climb advisories are therefore inhibited above this altitude.

  R EFF : 201-207, 501-509, 511-526, 528-599,  34-43-00 Page A6   Config-1 Feb 01/10  CES

 

(c) Advisory inhibit discretes Three discretes are used to manage priority between: - windshear/stall, - GPWS - G/S, - and the TCAS computer. The environmental alert priorities are: windshear/stall, GPWS G/S and then TCAS II. When TCAS II is inhibited, the TA ONLY mode is selected and the voice announcements are cancelled. (d) Rejection of signals from aircraft on ground (Ref. Fig. 023) Aircraft on the ground may reply to TCAS interrogations, producing an unnecessary overload in the processing and display of information. The ground logic aircraft declared on the ground is enabled when the own aircraft descends below 1650 ft AGL and when it climbs up to 1750 ft AGL. All on-ground intruders are displayed as non-threat traffic white unfilled diamond. Intruders are declared to be on-ground if they are within 380 ft from the ground when descending, and if they are within 400 ft from the ground when climbing. Intruders declared to be on-ground can never cause proximate, traffic or resolution advisory. But, as the altitude transmitted by the intruder is a barometric altitude with respect to sea level, the TCAS shall process this value to convert it into height above ground level in order to compare it with the 380 ft (plus or minus 20 ft) threshold. (e) Rejection of non altitude reporting aircraft by the own aircraft The TCAS does not display non altitude reporting aircraft above 15,500 ft MSL. **ON A/C 001-049, 101-149, 151-199, 201-249, 301-399, 401-499, Post SB Post SB

34-1177 For A/C 001-049,101-105, 34-1179 For A/C 201-207,

(5) Advisory inhibit conditions In certain particular conditions, certain advisories are not generated as they could lead to the pilot adopting flight conditions that are hazardous or outside the aircrafts performance capability. (a) Low altitude inhibitions Ground proximity leads to the inhibition of those advisories liable to cause a hazardous situation at this level. In decreasing altitude, these are:

  R EFF : 001-049, 101-149, 151-199, 201-249,  34-43-00 Page A7 301-399, 401-499, 501-509, 511-526, 528-599,  Config-1 Feb 01/10  CES

 

R R R R R R R R R

- below 1550 +/- 100 ft above ground level (AGL) inhibition of Increase Descend resolution advisories (RA), - below 1100 +/- 100 ft AGL, inhibition of Descend resolution advisories (RA), - below 1000 ft +/- 100 ft AGL, TCAS automatic switching to TA Only mode (inhibition of all resolution advisories), - below 500 +/- 100 ft AGL (600 ft in climb, 400 ft in descent), inhibition of all resolution advisories (RA) and of aural traffic advisories (TA).

R R R R R

(b) High altitude inhibition Above 48,000 ft, further climb orders are inapplicable as the aircraft performance capability does not permit them to be taken into account. Climb advisories are therefore inhibited above this altitude.

R R R R R R R R R

(c) Advisory inhibit discretes Three discretes are used to manage priority between: - windshear/stall, - GPWS - G/S, - and the TCAS computer. The environmental alert priorities are: windshear/stall, GPWS G/S and then TCAS II. When TCAS II is inhibited, the TA ONLY mode is selected and the voice announcements are cancelled.

R R R R R R R R R R R R R R R R R R

(d) Rejection of signals from aircraft on ground (Ref. Fig. 023) Aircraft on the ground may reply to TCAS interrogations, producing an unnecessary overload in the processing and display of information. The ground logic aircraft declared on the ground is enabled when the own aircraft descends below 1650 ft AGL and when it climbs up to 1750 ft AGL. All on-ground intruders are displayed as non-threat traffic white unfilled diamond. Intruders are declared to be on-ground if they are within 380 ft from the ground when descending, and if they are within 400 ft from the ground when climbing. Intruders declared to be on-ground can never cause proximate, traffic or resolution advisory. But, as the altitude transmitted by the intruder is a barometric altitude with respect to sea level, the TCAS shall process this value to convert it into height above ground level in order to compare it with the 380 ft (plus or minus 20 ft) threshold.

  EFF : 001-049, 101-149, 151-199, 201-249,  34-43-00 Page A8 301-399, 401-499,  Config-1 May 01/09  CES

 

R R R

(e) Rejection of non altitude reporting aircraft by the own aircraft The TCAS does not display non altitude reporting aircraft above 15,500 ft MSL. **ON A/C 001-049, 101-105, F. Sensitivity Level The notion of sensitivity level is very important in the TCAS as many of the operating modes depend on it. The TCAS separates the surrounding airspace into altitude layers. A different Sensitivity Level (SL) threshold for issuing advisories is applied to each altitude layer. The sensitivity level is decreased at low altitude to prevent unnecessary advisories in higher traffic densities such as terminal areas. Generally, the level is determined automatically by the TCAS in function of: - altitude values from the radio altimeter up to 2500 ft AGL - barometric altitude values in the 2500 ft to 48,000 ft range. TAU values corresponding to each sensitivity level indicate the TA and RA thresholds. The vertical separation thresholds at CPA also vary in function of the sensitivity level for the different types of advisory. The following table summarizes these data: ---------------------------------------------------------------------| | TAU thresholds | Vertical separation | | | | thresholds | |----------------------------|-----------------|---------------------| | Source | Altitude | SL TA RA | S0 S1 S2 | | Altitude | | | TA RA RA | | | | | prev cor | | | | (sec) (sec) | (ft) (ft) (ft) | |------------|---------------|-----------------|---------------------| | Radio Alt |less than 1000 | 2 20 | 850 | | Radio Alt | 1000-2350 | 3 25 15 | 850 600 300 | | Baro | 2350-5000 | 4 30 20 | 850 600 300 | | Baro | 5000-10000 | 5 40 25 | 850 600 350 | | Baro | 10000-20000 | 6 45 30 | 850 600 400 | | Baro | 20000-30000 | 7 48 35 | 850 700 600 | | Baro |more than 30000| 7 48 35 | 1200 800 700 | ---------------------------------------------------------------------NOTE : Level 1 corresponds to Standby Mode in which no advisory is ____ generated. NOTE : This table indicates the threshold based on own aircraft altitude. ____ Each aircraft altitude depends on an hysteresis:

  EFF : 001-049, 101-149, 151-199, 201-249,  34-43-00 Page A9 301-399, 401-499,  Config-1 May 01/09  CES

 

-

1000 + or - 100 ft 2350 + or - 200 ft 5000 + or - 500 ft 10000 + or - 500 ft 20000 + or - 500 ft 30000 + or - 500 ft For example, to switch from sensitivity level 3 to sensitivity level 2, the altitude must fall below 900 ft. However, to switch from sensitivity level 2 to sensitivity level 3, the altitude value must go above 1100 ft. (Ref. Fig. 024) There are two other means of modifying the sensitivity level: - selecting TA only mode on the ATC/TCAS control unit forces level 2. In this case, intruders of all types are displayed but will not be transformed into RA symbols and no vertical speed modification indications will be issued. - the ATC/Mode S equipped ground stations may modify the sensitivity level of the aircraft TCAS via the uplink without, however, having the capability to force the Standby Mode. If several ground stations command sensitivity levels, the TCAS logic selects the lowest level. Definition of priority logic: First a sensitivity level based on altitude is selected. Level 2 is selected if the radio altimeter altitude is less than 1000 ft. Level 2 is also selected if own aircraft is configured such that both CLIMB and DESCEND RAs are inhibited. Level 3 is selected if the aircraft is above 1000 ft and below 2350 ft AGL. If the aircraft is above 2350 ft AGL, barometric altitude is used to select either level 4 (below 5000 ft), 5 (from 5000 to 10,000 ft), 6 (from 10,000 to 20,000 ft), and 7 (above 20,000 ft). ATC/TCAS control unit input is read by the TCAS computer. If the pilot has selected Automatic Mode (TA/RA), then the altitude-based sensivity level will be used in comparisons to determine the final level. From all sensitivity level commands, if any, received from ground stations, the lowest is selected. If the TA ONLY mode is selected, either manually via the control unit or by a ground station, the altitude-based sensitivity level is used for TA thresholds and the RAs are inhibited. Otherwise, the lowest of all inputs is chosen.

  EFF : 001-049, 101-105,  34-43-00 Page A10   Config-1 May 01/09  CES

 

TCAS - Separation into Altitude Layers Figure 024   EFF : 001-049, 051-061, 101-105,  34-43-00 Page A11   Config-1 May 01/09  CES

 

R

**ON A/C 051-099, 251-299, F. Sensitivity Level The notion of Sensitivity Level (SL) is very important in the TCAS as many of the operating modes depend on it. The TCAS separates the surrounding airspace into altitude layers. A different sensitivity level threshold for issuing advisories is applied to each altitude layer. The sensitivity level is decreased at low altitude to prevent unnecessary advisories in higher traffic densities such as terminal areas. Generally, the level is determined automatically by the TCAS in function of: - altitude values from the radio altimeter up to 2500 ft AGL - barometric altitude values in the 2500 ft to 48,000 ft range. TAU values corresponding to each sensitivity level indicate the TA and RA thresholds. The vertical separation thresholds at CPA also vary in function of the sensitivity level for the different types of advisory. The following table summarizes these data: ---------------------------------------------------------------------| | TAU thresholds | Vertical separation | | | | thresholds | |-----------------------------|----------------|---------------------| | Source | Altitude | SL TA RA | S0 S1 S2 | | Altitude | | | TA RA RA | | | | | prev cor | | | | (sec) (sec) | (ft) (ft) (ft) | |------------|----------------|----------------|---------------------| | Radio Alt |less than 1000 | 2 20 | 850 | | Radio Alt | 1000-2350 | 3 25 15 | 850 600 300 | | Baro | 2350-5000 | 4 30 20 | 850 600 300 | | Baro | 5000-10,000 | 5 40 25 | 850 600 350 | | Baro | 10,000-20,000 | 6 45 30 | 850 600 400 | | Baro | 20,000-42,000 | 7 48 35 | 850 700 600 | | Baro |more than 42,000| 7 48 35 | 1200 800 700 | ---------------------------------------------------------------------NOTE : This table shows the sensitivity levels based on the TCAS ____ altitude. There is an hysteresis when switching from a sensitivity level to another one: - 1000 plus or minus 100 ft; - 2350 plus or minus 200 ft; - 5000 plus or minus 500 ft; - 10,000 plus or minus 500 ft; - 20,000 plus or minus 500 ft; - 42,000 plus or minus 500 ft.

  R EFF : 051-099, 251-299,  34-43-00 Page A12   Config-1 Nov 01/09  CES

 

for example: switching from SL3 to SL2 is performed at 900 ft and switching from SL2 to SL3 at 1100 ft. Level 1 corresponds to Standby Mode in which no advisory is generated. (Ref. Fig. 024B) There are two other means of modifying the sensitivity level: - selecting TA only mode on the ATC/TCAS control unit forces level 2. In this case, intruders of all types are displayed but are not transformed into RA symbols and no vertical speed modification indications are issued. - the ATC/Mode S-equipped ground stations may modify the sensitivity level of the aircraft TCAS via the uplink without, however, having the capability to force the Standby Mode. If several ground stations command sensitivity levels, the TCAS logic selects the lowest level. Definition of priority logic: First a sensitivity level based on altitude is selected. Level 2 is selected if the radio altimeter altitude is less than 1000 ft. Level 2 is also selected if own aircraft is configured such that both CLIMB and DESCEND RAs are inhibited (e.g., below 1000 ft AGL with insufficient climb performance). Level 3 is selected if the aircraft is above 1000 ft and below 2350 ft AGL. Level 4 is selected if the aircraft is above 2350 ft and below 5000 ft AGL. Level 3 is the least sensitive of the levels selected automatically by the TCAS; in fact in this altitude layer, the numerous inhibitions reduce the appearance of RA. If the aircraft is above 2500 ft AGL, barometric altitude is used to select either level 4 (from 2350 to 5000 ft), 5 (from 5000 to 10,000 ft), 6 (from 10,000 to 20,000 ft) and 7 (above 20,000 ft). NOTE : Intruders which do not report their altitude are not displayed ____ above 15,500 ft. ATC/TCAS control unit input is read by the TCAS computer. If the pilot has selected Automatic Mode (TA/RA), then the altitude-based sensivity level is used in comparisons to determine the final level. From all sensitivity level commands, if any, received from ground stations, the lowest is selected. If the TA ONLY mode is selected, either manually via the control unit or by a ground station, the altitude-based sensitivity level is used for TA thresholds and the RAs are inhibited. Otherwise, the lowest of all inputs is chosen.

  R EFF : 051-099, 251-299,  34-43-00 Page A13   Config-1 Nov 01/09  CES

 

TCAS - Separation into Altitude Layers Figure 024A   EFF : 106-149, 201-207, 211-249, 301-399,  34-43-00 Page A14 401-499,  Config-1 May 01/09  CES

 

TCAS - Separation into Altitude Layers Figure 024B   R EFF : 001-049, 051-099, 101-105, 151-199,  34-43-00 Page A15 201-210, 251-299, 501-509, 511-526, 528-599,  Config-1 Feb 01/10  CES

 

**ON A/C 201-207, F. Sensitivity Level The notion of sensitivity level is very important in the TCAS as many of the operating modes depend on it. The TCAS separates the surrounding airspace into altitude layers. A different Sensitivity Level (SL) threshold for issuing advisories is applied to each altitude layer. The sensitivity level is decreased at low altitude to prevent unnecessary advisories in higher traffic densities such as terminal areas. Generally, the level is determined automatically by the TCAS in function of: - altitude values from the radio altimeter up to 2500 ft AGL - barometric altitude values in the 2500 ft to 48,000 ft range. TAU values corresponding to each sensitivity level indicate the TA and RA thresholds. The vertical separation thresholds at CPA also vary in function of the sensitivity level for the different types of advisory. The following table summarizes these data: ---------------------------------------------------------------------| | TAU thresholds | Vertical separation | | | | thresholds | |----------------------------|-----------------|---------------------| | Source | Altitude | SL TA RA | S0 S1 S2 | | Altitude | | | TA RA RA | | | | | prev cor | | | | (sec) (sec) | (ft) (ft) (ft) | |------------|---------------|-----------------|---------------------| | Radio Alt |less than 1000 | 2 20 | 850 | | Radio Alt | 1000-2350 | 3 25 15 | 850 600 300 | | Baro | 2350-5000 | 4 30 20 | 850 600 300 | | Baro | 5000-10000 | 5 40 25 | 850 600 350 | | Baro | 10000-20000 | 6 45 30 | 850 600 400 | | Baro | 20000-30000 | 7 48 35 | 850 700 600 | | Baro |more than 30000| 7 48 35 | 1200 800 700 | ---------------------------------------------------------------------NOTE : Level 1 corresponds to Standby Mode in which no advisory is ____ generated. NOTE : This table indicates the threshold based on own aircraft altitude. ____ Each aircraft altitude depends on an hysteresis: - 1000 + or - 100 ft - 2350 + or - 200 ft - 5000 + or - 500 ft - 10000 + or - 500 ft

  EFF : 201-207,  34-43-00 Page A16   Config-1 May 01/09  CES

 

- 20000 + or - 500 ft - 30000 + or - 500 ft For example, to switch from sensitivity level 3 to sensitivity level 2, the altitude must fall below 900 ft. However, to switch from sensitivity level 2 to sensitivity level 3, the altitude value must go above 1100 ft. (Ref. Fig. 024A) There are two other means of modifying the sensitivity level: - selecting TA only mode on the ATC/TCAS control unit forces level 2. In this case, intruders of all types are displayed but are not transformed into RA symbols and no vertical speed modification indications are issued. - the ATC/Mode S-equipped ground stations may modify the sensitivity level of the aircraft TCAS via the uplink without, however, having the capability to force the Standby Mode. If several ground stations command sensitivity levels, the TCAS logic selects the lowest level. Definition of priority logic: First a sensitivity level based on altitude is selected. Level 2 is selected if the radio altimeter altitude is less than 1000 ft. Level 2 is also selected if own aircraft is configured such that both CLIMB and DESCEND RAs are inhibited. Level 3 is selected if the aircraft is above 1000 ft and below 2350 ft AGL. If the aircraft is above 2350 ft AGL, barometric altitude is used to select either level 4 (below 5000 ft), 5 (from 5000 to 10,000 ft), 6 (from 10,000 to 20,000 ft), and 7 (above 20,000 ft). ATC/TCAS control unit input is read by the TCAS computer. If the pilot has selected Automatic Mode (TA/RA), then the altitude-based sensivity level is used in comparisons to determine the final level. From all sensitivity level commands, if any, received from ground stations, the lowest is selected. If the TA ONLY mode is selected, either manually via the control unit or by a ground station, the altitude-based sensitivity level is used for TA thresholds and the RAs are inhibited. Otherwise, the lowest of all inputs is chosen.

  EFF : 201-207,  34-43-00 Page A17   Config-1 May 01/09  CES

 

R R

**ON A/C 511-526, Post SB Post SB Post SB

001-049, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 528-599, 34-1177 For A/C 001-049,101-105, 34-1179 For A/C 201-207, 34-1238 For A/C 201-207,

F. Sensitivity Level The notion of sensitivity level is very important in the TCAS as many of the operating modes depend on it. The TCAS separates the surrounding airspace into altitude layers. A different Sensitivity Level (SL) threshold for issuing advisories is applied to each altitude layer. The sensitivity level is decreased at low altitude to prevent unnecessary advisories in higher traffic densities such as terminal areas. Generally, the level is determined automatically by the TCAS in function of: - altitude values from the radio altimeter up to 2500 ft AGL, - barometric altitude values in the 2500 ft to 48,000 ft range. TAU values corresponding to each sensitivity level indicate the TA and RA thresholds. The vertical separation thresholds at CPA also vary in function of the sensitivity level for the different types of advisory. The following table summarizes these data: ---------------------------------------------------------------------| | TAU thresholds | Vertical separation | | | | thresholds | |----------------------------|-----------------|---------------------| | Source | Altitude | SL TA RA | S0 S1 S2 | | Altitude | | | TA RA RA | | | | | prev cor | | | | (sec) (sec) | (ft) (ft) (ft) | |------------|---------------|-----------------|---------------------| | Radio Alt |less than 1000 | 2 20 | 850 | | Radio Alt | 1000-2350 | 3 25 15 | 850 600 300 | | Baro | 2350-5000 | 4 30 20 | 850 600 300 | | Baro | 5000-10000 | 5 40 25 | 850 600 350 | | Baro | 10000-20000 | 6 45 30 | 850 600 400 | | Baro | 20000-42000 | 7 48 35 | 850 700 600 | | Baro |more than 42000| 7 48 35 | 1200 800 700 | ---------------------------------------------------------------------NOTE : Level 1 corresponds to Standby Mode in which no advisory is ____ generated. NOTE : This table indicates the threshold based on own aircraft altitude. ____ Each aircraft altitude depends on an hysteresis: - 1000 plus or minus 100 ft,

  R EFF : 001-049, 101-149, 151-199, 201-249,  34-43-00 Page A18 301-399, 401-499, 501-509, 511-526, 528-599,  Config-1 Feb 01/10  CES

 

-

2350 plus or minus 200 ft, 5000 plus or minus 500 ft, 10,000 plus or minus 500 ft, 20,000 plus or minus 500 ft, 42,000 plus or minus 500 ft. For example, to switch from sensitivity level 3 to sensitivity level 2, the altitude must fall below 900 ft. However, to switch from sensitivity level 2 to sensitivity level 3, the altitude value must go above 1100 ft.

**ON A/C 106-149, 211-249, 301-399, 401-499, (Ref. Fig. 024A) R

**ON A/C 001-049, 101-105, 151-199, 201-210, 501-509, 511-526, 528-599, Post SB Post SB Post SB

34-1177 For A/C 001-049,101-105, 34-1179 For A/C 201-207, 34-1238 For A/C 201-207, (Ref. Fig. 024B)

R R

**ON A/C 511-526, Post SB Post SB Post SB

001-049, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 528-599, 34-1177 For A/C 001-049,101-105, 34-1179 For A/C 201-207, 34-1238 For A/C 201-207, There are two other means of modifying the sensitivity level: - selecting TA only mode on the ATC/TCAS control unit forces level 2. In this case, intruders of all types are displayed but will not be transformed into RA symbols and no vertical speed modification indications will be issued. - the ATC/Mode S equipped ground stations may modify the sensitivity level of the aircraft TCAS via the uplink without, however, having the capability to force the Standby Mode. If several ground stations command sensitivity levels, the TCAS logic selects the lowest level. Definition of priority logic: First a sensitivity level based on altitude is selected. Level 2 is selected if the radio altimeter altitude is less than 1000 ft. Level 2 is also selected if own aircraft is configured such that both CLIMB and DESCEND RAs are inhibited. Level 3 is selected if the aircraft is above 1000 ft and below 2350 ft AGL. If the aircraft is above 2350 ft AGL, barometric altitude is used to select either level 4 (below 5000 ft), 5 (from 5000 to

  R EFF : 001-049, 101-149, 151-199, 201-249,  34-43-00 Page A19 301-399, 401-499, 501-509, 511-526, 528-599,  Config-1 Feb 01/10  CES

 

10,000 ft), 6 (from 10,000 to 20,000 ft), and 7 (above 20,000 ft). ATC/TCAS control unit input is read by the TCAS computer. If the pilot has selected Automatic Mode (TA/RA), then the altitude-based sensivity level will be used in comparisons to determine the final level. From all sensitivity level commands, if any, received from ground stations, the lowest is selected. If the TA ONLY mode is selected, either manually via the control unit or by a ground station, the altitude-based sensitivity level is used for TA thresholds and the RAs are inhibited. Otherwise, the lowest of all inputs is chosen. R

**ON A/C ALL G. Information Display The TCAS information is presented on the CAPT and F/O NDs of the EFIS system. Additional messages can also be presented on the display units of the ECAM system. (1) Traffic information on the ND Target aircraft are presented on the ND in ROSE or ARC mode but not in PLAN mode. These traffic indications show the situation in the surveillance zone. The aircraft present in this zone are represented by symbols whose shape and color correspond to the type of intruders defined in the TCAS. The symbols are positioned on the ND so as to depict their relative bearing and range. Data tags are associated with intruders. These tags consist of: - two digits indicating their relative altitude in hundreds of feet - a symbol indicating whether the intruder is above (+) or below (-) the aircraft. An arrow to the right of the symbol indicates the vertical trend of the aircraft. Targets are symbolized according to their type: - OTHER TRAFFIC: white outlined diamond, height 7 mm - PROXIMATE TRAFFIC: white filled diamond, height 7 mm - TRAFFIC ADVISORY: amber filled circle, diameter 5 mm - RESOLUTION ADVISORY: red filled square, side 5 mm. The display only presents the eight most threatening intruders (number determined through program pins on the TCAS computer). The own aircraft is represented by the aircraft symbol at the center of the dial in ROSE mode and at the lower quarter and at the center of the image in ARC mode.

  R EFF : ALL  34-43-00 Page A20   Config-1 Nov 01/09  CES

 

A white range ring with markings at each of the twelve clock positions is placed around the own aircraft symbol at a radius of 2.5 NM. The following figure shows an example of the display on the ND: (Ref. Fig. 025) These indications are only presented for the 10, 20 and 40 NM range selections. If a TA or RA type intruder is detected and the display range is at a higher scale, the following message comes into view at the center of the display, in red for RA and in amber for TA: REDUCE RANGE If a TA or RA type intruder is detected and the ND mode is inadequate for display, the following message comes into view at the center of the display in the same colors as above: CHANGE MODE The TCAS can detect an intruder without acquiring its bearing (for instance, multipath problem). In this case its range, relative altitude and an arrow are displayed in the TCAS area (at the bottom of the ND). The color of the display is the same as the color of the intruder symbol. (Ref. Fig. 026) OFF SCALE intruder: if only a half of a symbol is displayed, the target is defined as an off scale intruder. This calls for increasing the range selection on the ND. (2) Aircraft control information on the PFD Resolution advisories are represented on the vertical speed scale of the PFD by indications given in the form of a band made up of colored sectors: - a red sector represents a forbidden vertical speed range - a green sector indicates the vertical speed range the aircraft should fly in to avoid a collision threat represented by one or more intruders. (3) Corrective advisory display Corrective resolution advisories are displayed to advise the crew to perform an avoidance maneuver in the vertical sense. This maneuver may take different forms: - climb or descent if the aircraft is in level flight - reducing or increasing rate of climb or reversing to descent if the aircraft is in climb - reducing or increasing rate of descent or reversing to climb if the aircraft is in descent. When resolution advisories are displayed, the vertical speed scale surface changes from trapezoidal to rectangular.

  R EFF : ALL  34-43-00 Page A21   Config-1 Nov 01/09  CES

 

TCAS - ND Data Display Figure 025   R EFF : ALL  34-43-00 Page A22   Config-1 Nov 01/09  CES

 

TCAS - Display of Intruders on ND Figure 026   R EFF : ALL  34-43-00 Page A23   Config-1 Nov 01/09  CES

 

The grey background is replaced by green and red sectors defining the optimum vertical speed values. The pilots task is to maneuver the aircraft to keep the needle out of the red sectors and place it in the adjacent green Fly-to sector. The vertical speed information needle and digits are colored in red when the vertical speed is in the forbidden area. It becomes green when the vertical speed is in the authorized area. (Ref. Fig. 027) (4) Preventive advisory display Preventive resolution advisories advise the pilot to avoid vertical speeds that could lead to a hazardous situation. They are represented by one or two red sectors on the vertical speed scale. The pilot must keep the vertical speed of his aircraft outside these zones. For example, if own and intruders flight paths are horizontal and cross through each other, the intruder being at a higher flight level, if the vertical separation is sufficient, it is not necessary to modify the aircraft flight path. The positive vertical speed sector is in red to indicate that the aircraft may remain at its present level or may descend but must not climb. (Ref. Fig. 027) If intruders are detected above and below, two red sectors are displayed leaving an uncolored zone around the zero value on the vertical speed scale advising the pilot to maintain the aircraft at its current level. The following figure shows several examples of corrective and preventive advisories. (Ref. Fig. 028) (5) Messages annunciated on the ND As well as intruder information, the ND also displays operating mode messages or fault data. This information is presented in the lower section of the ND (message zone): - TA ONLY - white - for the TA mode (automatic or manual switching) - TCAS - red - to indicate a TCAS computer failure. (Ref. Fig. 029) (6) Display on A red TCAS the PFD if (Ref. Fig.

the PFD flag appears to the left of the vertical speed scale on the TCAS cannot deliver RA data. 030)

  R EFF : ALL  34-43-00 Page A24   Config-1 Nov 01/09  CES

 

TCAS - PFD Data Display Figure 027   R EFF : ALL  34-43-00 Page A25   Config-1 Nov 01/09  CES

 

TCAS - Sector Displays on Vertical Speed Scale Figure 028   R EFF : ALL  34-43-00 Page A26   Config-1 Nov 01/09  CES

 

TCAS - Messages Displayed on ND Figure 029   R EFF : ALL  34-43-00 Page A27   Config-1 Nov 01/09  CES

 

TCAS - Messages Displayed on PFD and ECAM Figure 030   R EFF : ALL  34-43-00 Page A28   Config-1 Nov 01/09  CES

 

(7) Display on the upper ECAM DU - If a TCAS fault is detected, the amber warning message NAV TCAS FAULT is displayed on the upper ECAM DU. - Selection of the TCAS STBY mode on the ATC/TCAS control unit results in the display of the TCAS STBY message (green) in the memo section of the upper ECAM DU. (Ref. Fig. 030) H. ATC/TCAS Control Unit Operational Use The TCAS is a cooperative system whose operating mode is very close to the ATC Mode S transponder associated to it. The main controls are thus grouped on the ATC/TCAS control unit and the traffic and conflict resolution information is presented on the EFIS displays. NOTE : - Operation of the ATC Mode S transponder is described in 34-52. ____ - The EFIS components are also described in 31-64 for the PFD and 31-65 for the ND. The manual operating modes of the TCAS are selected via the ATC/TCAS control unit (Ref. Fig. 031) (1) TCAS modes of operation The TCAS mode of operation is selected by means of two selectors switches. - STBY, TA and TA/RA - THRT, ALL, ABV and BLW (a) STBY mode In the Standby Mode, the advisory generation and surveillance functions are inhibited. No TCAS information can be displayed on the PFDs and NDs. The aircraft symbol and the range ring remain on the ND and vertical speed information is not displayed on the PFD. The green TCAS STBY message is displayed in the memo section of the upper ECAM DU. If the mode selector is set to XPDR, the TCAS also operates in standby mode. (b) TA mode In this mode, intruders are displayed on the ND according to their position in the airspace. The RA type intruder symbols are converted into TA type symbols. The TCAS performs surveillance functions but does not generate any resolution advisories.

  R EFF : ALL  34-43-00 Page A29   Config-1 Nov 01/09  CES

 

TCAS - ATC/TCAS Control Unit Figure 031   R EFF : ALL  34-43-00 Page A30   Config-1 Nov 01/09  CES

 

The TA ONLY message is displayed in white on the NDs in the left corner of the TCAS message area. (c) TA/RA mode The TCAS performs all TA mode functions and also issues preventive or corrective resolution advisories, represented in the form of colored sectors along the vertical speed scale on the PFD. The sensitivity level is determined automatically in function of altitude. NOTE : The final mode of operation is a combination taking into ____ account the aircraft altitude and any instructions received from ATC Mode S ground stations. For further information refer to the priority logic definition (Ref. Para. 6.F.). (d) THRT mode In this mode, TCAS intruders (proximate or/and other) are displayed if a TA or a RA is already displayed. (e) ALL mode This selection enables display of all intruders without any conditions (TCAS intruders are displayed when detected). (f) ABV and BLW modes This selection controls the above and below vertical altitude for traffic advisory: - ABV: altitude range is set to 9900 ft above the aircraft and 2700 ft below - BLW: altitude range is set to 9900 ft below the aircraft and 2700 ft above. (2) ATC mode of operation The mode of operation of the transponder is selected by a switch with three positions STBY, AUTO, ON. (a) STBY mode When the transponder is in standby it does not transmit either squitters or replies to ground station or other aircraft interrogations.

  R EFF : ALL  34-43-00 Page A31   Config-1 Nov 01/09  CES

 

(b) AUTO mode In flight, the aircraft operates as in the ON mode: all its functions are active. When the aircraft touches down, the landing gear ground/flight relay disables the Mode A and C replies of the selected transponder from ground station interrogations. However the Mode S replies and squitter are not inhibited when the A/C is on the ground. (c) ON mode The Mode S transponder operates permanently, both in flight and on the ground. It periodically transmits squitters (at 1 second intervals) to be detected by other aircraft and replies to their interrogations and those from ground stations. This function permits, on ground, to override the inhibition of replies from interrogations in Mode A or C. It is used by the air traffic controller to check the correct operation of the aircraft Mode A or C transponder prior to takeoff. (3) Altitude reporting (a) OFF position Selection of the ALT RPTG switch OFF position has the following results: - the Mode S transponder continues to transmit squitters and replies to Mode A, C and S interrogations but does not report altitude. - the TCAS switches to STBY (TCAS STBY message in green on the upper ECAM DU), - the PFD and ND display corresponds to the standby mode. (b) ON position The active transponder replies to interrogations and reports its altitude. The TCAS operates in the mode selected by its logic in function of information input from the control unit, ATCRBS/MODE S ground stations and in function of aircraft altitude. (4) Selection of system 1/2 active transponder The 1/2 switch permits selection of the active transponder. The non-selected transponder is placed in standby. (5) Identification code in Mode A The Mode S transponder also replies to Mode A interrogations from ground stations. A keyboard permits the pilot to set the Mode A octal code assigned to the aircraft by the ATC ground station controller and included in the transmitted replies. A window on the control unit

  R EFF : ALL  34-43-00 Page A32   Config-1 Nov 01/09  CES

 

displays this code permanently as long as the content of the digital output message complies with the displayed data. (6) IDENT pushbutton switch On ground station request, an addition pulse must be included in the Mode A and Mode C replies transmitted by the transponder to enable a more precise location. This operation is performed by pressing the IDENT pushbutton switch on the control unit. 7. Test ____ **ON A/C 001-049, 101-105, 151-199, A. Self-Test A quick check of the correct operation of the TCAS installation can be performed by activating the TEST function: - either by pressing the pushbutton switch on the front of the TCAS computer - or through the CFDIU by applying the procedure TCAS functional test on the MCDU. The self-test sequence checks the main functions of the computer and transmits to the displays: - resolution advisory characteristics (0 ft/mn advisory, up corrective advisory, dont descend, dont climb > 2000 ft/mn, rate to maintain) on label 270 - label frames 130, 131, 132 containing the data for each of the four intruders according to the following table: -------------------------------------------------------------------------| INTRUDER | TYPE | RANGE | REL ALT | BEARING | VERTICAL RATE | | | | (NM) | (FEET) | (DEG) | | |------------|--------|---------|-----------|-----------|----------------| | 1 | RA | 2.00 | -1000 | +90 |no vertical rate| | 2 | TA | 2.00 | -200 | -90 |climbing | | 3 | PROX | 3.625 | +200 | +33.75 |descending | | 4 | OTHER | 3.625 | +1000 | -33.75 |no vertical rate| -------------------------------------------------------------------------(1) ND image The ND must display the images corresponding to the four types of intruders: Other, Proximate, TA and RA. The shapes and colors of the traffic symbols are: - white outlined diamond for Other traffic - white diamond for Proximate traffic - yellow circle for TA traffic - red square for RA traffic

  R EFF : ALL  34-43-00 Page A33   Config-1 Nov 01/09  CES

 

(Ref. Fig. 032) (2) PFD image At the beginning of the test sequence, the vertical speed scale on the PFD is divided in three sectors: one green and two red ones. Then a resolution advisory display is shown. (Ref. Fig. 032) (3) Fault indication At the end of the test sequence, the system generates a synthesized voice message: TCAS SYSTEM TEST OK if the system operates correctly or: TCAS SYSTEM TEST FAIL if an anomaly has been detected. In this case the NDs, the PFDs and the ECAM show the fault messages described in Para. 6.G.(5), (6) and (7). In addition, two windows on the front of the TCAS computer display a code identifying the failed component according to the table below: ---------------------------------------| CODE | COMPONENT | |----------|---------------------------| | TP | TCAS PROCESSOR | | T1 | TOP ANTENNA ELEMENT E1 | | T2 | TOP ANTENNA ELEMENT E2 | | T3 | TOP ANTENNA ELEMENT E3 | | T4 | TOP ANTENNA ELEMENT E4 | | B1 | BOTTOM ANTENNA ELEMENT E1| | B2 | BOTTOM ANTENNA ELEMENT E2| | B3 | BOTTOM ANTENNA ELEMENT E3| | B4 | BOTTOM ANTENNA ELEMENT E4| | X1 | MODE S TRANSPONDER 1 | | X2 | MODE S TRANSPONDER 2 | | RA | RADIO ALTIMETER 1 AND 2 | | | OR 1 FOR SINGLE | | | INSTALLATION | | PT | PITCH ATTITUDE DATA | | RL | ROLL ATTITUDE DATA | | HD | HEADING DATA | | RD | RA DISPLAY 1 AND 2 | | PP | PROGRAM PINS | | SP | SUPPRESSION LINE | | AG | AIR/GROUND DISCRETE | ---------------------------------------R

  EFF : 001-049, 101-105, 151-199,  34-43-00 Page A34   Config-1 May 01/09  CES

 

TCAS - Test Display Figure 032   R EFF : 001-049, 101-105, 151-199, 501-509,  34-43-00 Page A35 511-526, 528-599,  Config-1 Feb 01/10  CES

 

R

**ON A/C 051-099, 251-299, A. Self-Test A quick check of the correct operation of the TCAS installation can be performed by activating the FUNCTIONAL TEST function: - either by pressing the pushbutton switch on the front of the TCAS computer - or through the CFDIU by applying the procedure TCAS functional test on the MCDU. The self-test sequence checks the main functions of the computer and transmits to the displays: - resolution advisory characteristics (0 ft/mn advisory, up corrective advisory, dont descend, dont climb > 2000 ft/mn, rate to maintain) on label 270 - label frames 130, 131, 132 containing the data for each of the four intruders according to the following table: -------------------------------------------------------------------------| INTRUDER | TYPE | RANGE | REL ALT | BEARING | VERTICAL RATE | | | | (NM) | (FEET) | (DEG) | | |------------|--------|---------|-----------|-----------|----------------| | 1 | RA | 2.00 | +200 | +90 |no vertical rate| | 2 | TA | 2.00 | -200 | -90 |climbing | | 3 | PROX | 3.625 | -1000 | +33.75 |descending | | 4 | OTHER | 3.625 | +1000 | -33.75 |no vertical rate| -------------------------------------------------------------------------(1) ND image The ND must display the images corresponding to the four types of intruders: Other, Proximate, TA and RA. The shapes and colors of the traffic symbols are: - white outlined diamond for Other traffic - white diamond for Proximate traffic - yellow circle for TA traffic - red square for RA traffic (Ref. Fig. 032A) NOTE : Presentation of the TCAS test on the NDs does not agree with ____ ARINC 735 specification. (2) PFD image At the beginning of the test sequence, green and red sectors must appear sequentially on the vertical speed scale of the PFD. Then a resolution advisory display is shown (Ref. Fig. 032A)

  R EFF : 051-099, 251-299,  34-43-00 Page A36   Config-1 Nov 01/09  CES

 

TCAS - Test Display Figure 032A   R EFF : 051-099, 251-299,  34-43-00 Page A37   Config-1 Nov 01/09  CES

 

(3) Fault indication At the end of the test sequence, the system generates a synthesized voice message: TCAS SYSTEM TEST PASS if the system operates correctly or: TCAS SYSTEM TEST FAIL if an anomaly has been detected. In this case the NDs, the PFDs and the ECAM show the fault messages described in Para. 6.G.(5), (6) and (7). There are several fail lamps on the face of the TCAS computer to identify the failed component according to the table below: -------------------------------------------------| LIGHTS | ASSOCIATED FAULTS | |-------------|----------------------------------| | TCAS PASS | No fault detected | | TCAS FAIL | Any detected faults | | TOP ANT | Top antenna | | BOT ANT | Bottom antenna | | XPDR BUS | Update rate, data format, | | | signal range | | RAD ALT | Radio Altimeter | | RA DISP | Resolution advisory display | | TA DISP | Traffic advisory display | -------------------------------------------------**ON A/C 106-149, 201-249, 301-399, 401-499, A. Self-Test A quick check of the correct operation of the TCAS installation can be performed by activating the TEST function: - either by pressing the pushbutton switch on the front of the TCAS computer - or through the CFDIU by applying the procedure TCAS functional test on the MCDU. The self-test sequence checks the main functions of the computer and transmits to the displays: - resolution advisory characteristics (0 ft/mn advisory, up corrective advisory, dont descend, dont climb > 2000 ft/mn, rate to maintain) on label 270 - label frames 130, 131, 132 containing the data for each of the four intruders according to the following table:

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-43-00 Page A38 301-399, 401-499,  Config-1 Nov 01/09  CES

 

R R R R R R R R R

-------------------------------------------------------------------------| INTRUDER | TYPE | RANGE | REL ALT | BEARING | VERTICAL RATE | | | | (NM) | (FEET) | (DEG) | | |------------|--------|---------|-----------|-----------|----------------| | 1 | RA | 2.00 | +200 | +90 |no vertical rate| | 2 | TA | 2.00 | -200 | -90 |climbing | | 3 | PROX | 3.625 | -1000 | +33.75 |descending | | 4 | OTHER | 3.625 | +1000 | -33.75 |no vertical rate| --------------------------------------------------------------------------

R R R R R R R R R R

(1) ND image The ND must display the images corresponding to the four types of intruders: Other, Proximate, TA and RA. The shapes and colors of the traffic symbols are: - white outlined diamond for Other traffic - white diamond for Proximate traffic - yellow circle for TA traffic - red square for RA traffic (Ref. Fig. 032B)

R R R R R

(2) PFD image At the beginning of the test sequence, green and red sectors must appear sequentially on the vertical speed scale of the PFD. Then a resolution advisory display is shown. (Ref. Fig. 032B)

R R R R R R R R R R R

(3) Fault indication At the end of the test sequence, the system generates a synthesized voice message: TCAS SYSTEM TEST OK if the system operates correctly or: TCAS SYSTEM TEST FAIL if an anomaly has been detected. In this case the NDs, the PFDs and the ECAM show the fault messages described in Para. 6.G.(5), (6) and (7). In addition, two windows on the front of the TCAS computer display a code identifying the failed component according to the table below:

  EFF : 106-149, 201-249, 301-399, 401-499,  34-43-00 Page A39   Config-1 May 01/09  CES

 

TCAS - Test Display Figure 032B   EFF : 106-149, 201-249, 301-399, 401-499,  34-43-00 Page A40   Config-1 May 01/09  CES

 

------------------------------------------------------------------------------| CONTROL/ | LOCATION | FUNCTION | | INDICATING | | | |------------------|-------------|--------------------------------------------| | TTR PASS | Front panel | Comes on to indicate TTR has passed self- | |(indicator light) | | test | | TTR FAIL | Front panel | Comes on to indicate TTR has failed self- | |(indicator light) | | test | | XPNDR | Front panel | Comes on to indicate transponder or data | |(indicator light) | | link interface failure | | UPPER ANT | Front panel | Comes on to indicate upper TCAS antenna | |(indicator light) | | failure | | LOWER ANT | Front panel | Comes on to indicate lower TCAS antenna | |(indicator light) | | failure | | RAD ALT | Front panel | Comes on to indicate lack of radio | |(indicator light) | | altimeter data | | HDNG | Front panel | Comes on to indicate lack of heading data | |(indicator light) | | | | R/A | Front panel | Comes on to indicate RA indicator failure | |(indicator light) | | | | T/A | Front panel | Comes on to indicate TA indicator failure | |(indicator light) | | | | TEST (pushbutton | Front panel | Initiates self-test when pressed | | switch) | | | ------------------------------------------------------------------------------R

**ON A/C 501-509, 511-526, 528-599, A. Self-Test A quick check of the correct operation of the TCAS installation can be performed by activating the TEST function: - either by pressing the pushbutton switch on the front of the TCAS computer - or through the CFDIU by applying the procedure TCAS functional test on the MCDU. The self-test sequence checks the main functions of the computer and transmits to the displays: - resolution advisory characteristics (0 ft/mn advisory, up corrective advisory, dont descend, dont climb > 2000 ft/mn, rate to maintain) on label 270 - label frames 130, 131, 132 containing the data for each of the four intruders according to the following table:

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-43-00 Page A41 501-509, 511-526, 528-599,  Config-1 Feb 01/10  CES

 

-------------------------------------------------------------------------| INTRUDER | TYPE | RANGE | REL ALT | BEARING | VERTICAL RATE | | | | (NM) | (FEET) | (DEG) | | |------------|--------|---------|-----------|-----------|----------------| | 1 | RA | 2.00 | -1000 | +90 |no vertical rate| | 2 | TA | 2.00 | -200 | -90 |climbing | | 3 | PROX | 3.61 | +200 | +33.69 |descending | | 4 | OTHER | 3.61 | +1000 | -33.69 |no vertical rate| -------------------------------------------------------------------------(1) ND image The ND must display the images corresponding to the four types of intruders: Other, Proximate, TA and RA. The shapes and colors of the traffic symbols are: - white outlined diamond for Other traffic - white diamond for Proximate traffic - yellow circle for TA traffic - red square for RA traffic (Ref. Fig. 032) (2) PFD image At the beginning of the test sequence, the vertical speed scale on the PFD is divided in three sectors: one green and two red ones. Then a resolution advisory display is shown. (Ref. Fig. 032) (3) Fault indication At the end of the test sequence, the system generates a synthesized voice message: TCAS SYSTEM TEST OK if the system operates correctly or: TCAS SYSTEM TEST FAIL if an anomaly has been detected. In this case the NDs, the PFDs and the ECAM show the fault messages described in Para. 6.G.(5), (6) and (7). In addition, two windows on the front of the TCAS computer display a code identifying the failed component according to the table below:

  R EFF : 501-509, 511-526, 528-599,  34-43-00 Page A42   Config-1 Feb 01/10  CES

 

-----------------------------------------------------------------| CODE | COMPONENT | |--------------------------|-------------------------------------| | System OK | NO FAILURE | | Top Ant Fail | TCAS TOP ANTENNA | | Top Ant E1 | TOP ANTENNA ELEMENT 1 | | Top Ant E2 | TOP ANTENNA ELEMENT 2 | | Top Ant E3 | TOP ANTENNA ELEMENT 3 | | Top Ant E4 | TOP ANTENNA ELEMENT 4 | | Bott Ant Fail | TCAS BOTTOM ANTENNA | | Bot Ant E1 | BOTTOM ANTENNA ELEMENT 1 | | Bot Ant E2 | BOTTOM ANTENNA ELEMENT 2 | | Bot Ant E3 | BOTTOM ANTENNA ELEMENT 3 | | Bot Ant E4 | BOTTOM ANTENNA ELEMENT 4 | | Transponder 1 | MODE S TRANSPONDER 1 | | Transponder 2 | MODE S TRANSPONDER 2 | | Radio Alt 1 | RADIO ALTIMETER 1 | | Radio Alt 2 | RADIO ALTIMETER 2 | | Pitch Att Data | PITCH ATTITUDE DATA | | Roll Att Data | ROLL ATTITUDE DATA | | Heading Data | HEADING DATA | | CMC Bus | CENTRALIZED MAINTENANCE COMPUTER | | ATC Ctl Panel | ATC CONTROL PANEL | | FMC | FLIGHT MANAGEMENT COMPUTER | | PP (+ PIN ALLOCATION) | PROGRAM PINS | | Suppression Line | SUPPRESSION LINE | | Power Supply | POWER SUPPLY | | TCAS Unit Failed | TCAS UNIT | -----------------------------------------------------------------R

**ON A/C ALL B. CFDS (1) Introduction The CFDS permits to present the TCAS computer faults on the Multipurpose Control and Display Units (MCDU) and on the printer. The TCAS computer which is classified Type 1 system in the CFDS also delivers data related to fault diagnoses required for its maintenance. It communicates with the CFDS through two ARINC 429 low speed buses. The CFDS is characterized by two operating modes: - MENU mode - NORMAL mode.

  R EFF : ALL  34-43-00 Page A43   Config-1 Nov 01/09  CES

 

**ON A/C 001-049, 101-105, 151-199, (2) Menu Mode (a) SYSTEM REPORT/TEST function This function enables access to all the electronic systems and to the TCAS computer. The display of the SYSTEM REPORT/TEST page for the NAV components on which the TCAS is accessible is shown on the following figure. When the line key adjacent to the TCAS indication is pressed, the CFDIU establishes the dialog and provides access to one of the seven following items: - LAST LEG REPORT - PREVIOUS LEGS REPORT - LRU IDENTIFICATION - GROUND SCANNING - CLASS 3 FAULTS - GROUND REPORT - TEST. The procedure used to get the page for selection of an item is shown in the figure (Ref. Fig. 033) (b) LAST LEG REPORT This report contains the computer internal and external faults recorded during the last flight. The following tables give the lists of the fault messages which can be reported and indicate the fault class assigned to them as defined by the CFDS standard. **ON A/C 051-099, 201-209, (2) Menu Mode (a) SYSTEM REPORT/TEST function This function enables access to all the electronic systems and to the TCAS computer. The display of the SYSTEM REPORT/TEST page for the NAV components on which the TCAS is accessible is shown on the following figure. When the line key adjacent to the TCAS indication is pressed, the CFDIU establishes the dialog and provides access to one of the eight following items: - LAST LEG REPORT - PREVIOUS LEGS REPORT - LRU IDENTIFICATION

  EFF : 001-049, 051-099, 101-105, 151-199,  34-43-00 Page A44 201-209,  Config-1 May 01/09  CES

 

TCAS - Maintenance Test Procedure Figure 033   EFF : 001-049, 101-105, 151-199,  34-43-00 Page A45   Config-1 May 01/09  CES

 

- GROUND SCANNING - TROUBLE SHOOTING DATA - CLASS 3 FAULTS - GROUND REPORT - TEST. The procedure used to get the page for selection of an item is shown in the figure (Ref. Fig. 033A) (b) LAST LEG REPORT This report contains the computer class 1 internal and external faults recorded during the last flight. The following tables give the lists of the fault messages which can be reported and indicate the fault class assigned to them as defined by the CFDS standard. R R

**ON A/C 051-099, 106-149, 201-207, 210-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1238 For A/C 201-207, (2) Menu Mode (a) SYSTEM REPORT/TEST function This function enables access to all the electronic systems and to the TCAS computer. The display of the SYSTEM REPORT/TEST page for the NAV components on which the TCAS is accessible is shown on the following figure. When the line key adjacent to the TCAS indication is pressed, the CFDIU establishes the dialog and provides access to one of the eight following items: - LAST LEG REPORT - PREVIOUS LEGS REPORT - LRU IDENTIFICATION - GROUND SCANNING - TROUBLE SHOOTING DATA - CLASS 3 FAULTS - GROUND REPORT - DISCRETE CONFIGURATION - TEST. The procedure used to get the page for selection of an item is shown in the figure (Ref. Fig. 033B)

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TCAS - Maintenance Test Procedure Figure 033A   EFF : 051-099, 201-209,  34-43-00 Page A47   Config-1 May 01/09  CES

 

TCAS - Maintenance Test Procedure Figure 033B   R EFF : 051-099, 106-149, 201-207, 210-249,  34-43-00 Page A48 251-299, 301-399, 401-499, 501-509, 511-526,  Config-1 Feb 01/10 528-599, CES

 

(b) LAST LEG REPORT This report contains the computer internal and external faults recorded during the last flight. The following tables give the lists of the fault messages which can be reported and indicate the fault class assigned to them as defined by the CFDS standard. R R

**ON A/C 001-049, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, 1 _

Internal faults

------------------------------------------------------------------------------| LIST OF INTERNAL FAULT MESSAGES | |-----------------------------------------------------------------------------| | ATA | CLASS | MESSAGE | |-----------------------------------------------------------------------------| | 344334 | 1 | TCAS (1SG) | | 344311 | 1 | TCAS TOP ANTENNA (7SG1) | | 344311 | 1 | TCAS TOP ANTENNA (7SG1) | | | | COAXIAL J1 | | 344311 | 1 | TCAS TOP ANTENNA (7SG1) | | | | COAXIAL J2 | | 344311 | 1 | TCAS TOP ANTENNA (7SG1) | | | | COAXIAL J3 | | 344311 | 1 | TCAS TOP ANTENNA (7SG1) | | | | COAXIAL J4 | | 344311 | 1 | TCAS BOT ANTENNA (7SG2) | | 344311 | 1 | TCAS BOT ANTENNA (7SG2) | | | | COAXIAL J1 | | 344311 | 1 | TCAS BOT ANTENNA (7SG2) | | | | COAXIAL J2 | | 344311 | 1 | TCAS BOT ANTENNA (7SG2) | | | | COAXIAL J3 | | 344311 | 1 | TCAS BOT ANTENNA (7SG2) | | | | COAXIAL J4 | ------------------------------------------------------------------------------The following figure shows the sequence of menus to display these messages. **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 034)

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-43-00 Page A49 201-249, 251-299, 301-399, 401-499, 501-509,  Config-1 Feb 01/10 511-526, 528-599, CES

 

TCAS - Internal Fault Messages Figure 034   EFF : 001-049, 101-105, 151-199,  34-43-00 Page A50   Config-1 May 01/09  CES

 

**ON A/C 201-209, (Ref. Fig. 034A) R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 034C) **ON A/C 106-149, 201-207, 210-249, 301-399, 401-499, Post SB

34-1238 For A/C 201-207, (Ref. Fig. 034D)

**ON A/C 051-099, 251-299, 1 _

Internal faults

------------------------------------------------------------------------------| LIST OF INTERNAL FAULT MESSAGES | |-----------------------------------------------------------------------------| | ATA | CLASS | MESSAGE | |-----------------------------------------------------------------------------| | 344334 | 1 | TCAS (1SG) | | 344311 | 1 | TCAS TOP ANTENNA (7SG1) | | 344311 | 1 | TCAS BOT ANTENNA (7SG2) | ------------------------------------------------------------------------------The following figure shows the sequence of menus to display these messages. **ON A/C 051-099, (Ref. Fig. 034A) **ON A/C 051-099, 251-299, (Ref. Fig. 034B)

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-43-00 Page A51 301-399, 401-499, 501-509, 511-526, 528-599,  Config-1 Feb 01/10  CES

 

TCAS - Internal Fault Messages Figure 034A   EFF : 051-099, 201-209,  34-43-00 Page A52   Config-1 May 01/09  CES

 

TCAS - Last Leg Report - Internal Fault Messages Figure 034B   R EFF : 051-099, 251-299,  34-43-00 Page A53   Config-1 Nov 01/09  CES

 

TCAS - Internal Fault Messages Figure 034C   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page A54   Config-1 Feb 01/10  CES

 

TCAS - Internal Fault Messages Figure 034D   EFF : 106-149, 201-207, 210-249, 301-399,  34-43-00 Page A55 401-499,  Config-1 May 01/09  CES

 

R

**ON A/C 001-049, 051-099, 101-105, 151-199, 251-299, 2 _

External faults External faults and associated messages are listed in the table below:

------------------------------------------------------------------------------| LIST OF EXTERNAL FAULT MESSAGES | |-----------------------------------------------------------------------------| | ATA | CLASS | MESSAGE | |-----------------------------------------------------------------------------| | 344233 | 3 | RA1 (2SA1)/TCAS (1SG) | | 344233 | 3 | RA2 (2SA2)/TCAS (1SG) | | 344233 | 1 | RA1 (2SA1)/TCAS (1SG) | | 344233 | 1 | RA2 (2SA2)/TCAS (1SG) | | 345233 |1 or 3 | ATC 1(1SH1)/TCAS (1SG) | | 345233 |1 or 3 | ATC 2(1SH2)/TCAS (1SG) | | 345233 | 1 | ATC 1(1SH1)/TCAS (1SG) | | 345233 | 1 | ATC 2(1SH2)/TCAS (1SG) | | 341234 | 1 | ADIRU1 (1FP1)/TCAS (1SG) | | 240000 | 1 | POWER SUPPLY INTERRUPT | | 355212 | 1 | ATC - TCAS CTL PNL (3SH)/TCAS (1SG) | | 313234 | 3 | CFDIU (1TW)/TCAS (1SG) | ------------------------------------------------------------------------------NOTE : Fault of the selected ATC is a class 1 failure. ____ Fault of the ATC in standby is a class 3 failure. NOTE : Fault of one radio altimeter is a class 3 fault whereas ____ it becomes a class 1 fault when two radio altimeters are faulty. The class 3 recorded external faults are displayed through the menu sequence as shown in the following figure. **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 035) **ON A/C 051-099, (Ref. Fig. 035A)

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-43-00 Page A56 251-299,  Config-1 Nov 01/09  CES

 

TCAS - External Fault Messages Figure 035   EFF : 001-049, 101-105, 151-199,  34-43-00 Page A57   Config-1 May 01/09  CES

 

TCAS - External Fault Messages Figure 035A   EFF : 051-099, 201-209,  34-43-00 Page A58   Config-1 May 01/09  CES

 

R

**ON A/C 051-099, 251-299, (Ref. Fig. 035B)

  R EFF : 051-099, 251-299,  34-43-00 Page A59   Config-1 Nov 01/09  CES

 

TCAS - Last Leg Report - External Fault Messages/Class 3 fault Figure 035B   R EFF : 051-099, 251-299,  34-43-00 Page A60   Config-1 Nov 01/09  CES

 

**ON A/C 106-149, 201-249, 301-399, 401-499, 2 _

External faults External faults and associated messages are listed in the table below:

------------------------------------------------------------------------------| LIST OF EXTERNAL FAULT MESSAGES | |-----------------------------------------------------------------------------| | ATA | CLASS | MESSAGE | |-----------------------------------------------------------------------------| | 344233 | 3 | RA1 (2SA1)/TCAS (1SG) | | 344233 | 3 | RA2 (2SA2)/TCAS (1SG) | | 344233 | 1 | RA1 (2SA1)+RA2 (2SA2)/TCAS (1SG) | | 345233 | 3 | ATC 1(1SH1)/TCAS (1SG) | | 345233 | 3 | ATC 2(1SH2)/TCAS (1SG) | | 345233 | 1 | ATC1 (1SH1)+ATC2 (1SH2)/TCAS (1SG) | | 341234 | 3 | ADIRU1 (1FP1)/TCAS (1SG) | | 240000 | 1 | POWER SUPPLY INTERRUPT | | 355212 | 1 | ATC - TCAS CTL PNL (3SH)/TCAS (1SG) | | 313234 | 3 | CFDIU (1TW)/TCAS (1SG) | ------------------------------------------------------------------------------NOTE : Fault of one ATC is a class 3 fault. ____ Fault of both ATCs is a class 1 fault. NOTE : Fault of one radio altimeter is a class 3 fault whereas ____ it becomes a class 1 fault when two radio altimeters are faulty. The class 3 recorded external faults are displayed through the CLASS 3 FAULTS menu sequence as shown in the following figure. **ON A/C 201-209, (Ref. Fig. 035A) **ON A/C 106-149, 201-207, 210-249, 301-399, 401-499, Post SB

34-1238 For A/C 201-207, (Ref. Fig. 035D)

  EFF : 106-149, 201-249, 301-399, 401-499,  34-43-00 Page A61   Config-1 May 01/09  CES

 

TCAS - External Fault Messages Figure 035C   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page A62   Config-1 Feb 01/10  CES

 

TCAS - External Fault Messages Figure 035D   EFF : 106-149, 201-207, 210-249, 301-399,  34-43-00 Page A63 401-499,  Config-1 May 01/09  CES

 

R

**ON A/C 501-509, 511-526, 528-599, 2 _

External faults External faults and associated messages are listed in the table below:

------------------------------------------------------------------------------| LIST OF EXTERNAL FAULT MESSAGES | |-----------------------------------------------------------------------------| | ATA | CLASS | MESSAGE | |-----------------------------------------------------------------------------| | 344233 | 3 | RA1 (2SA1)/TCAS (1SG) | | 344233 | 3 | RA2 (2SA2)/TCAS (1SG) | | 344233 | 1 | RA1 (2SA1)/TCAS (1SG) | | 344233 | 1 | RA2 (2SA2)/TCAS (1SG) | | 345233 |1 or 3 | ATC 1(1SH1)/TCAS (1SG) | | 345233 |1 or 3 | ATC 2(1SH2)/TCAS (1SG) | | 345233 | 1 | ATC 1(1SH1)/TCAS (1SG) | | 345233 | 1 | ATC 2(1SH2)/TCAS (1SG) | | 341234 | 1 | ADIRU1 (1FP1)/TCAS (1SG) | | 240000 | 1 | POWER SUPPLY INTERRUPT | | 355212 | 1 | ATC - TCAS CTL PNL (3SH)/TCAS (1SG) | | 313234 | 3 | CFDIU (1TW)/TCAS (1SG) | | 344300 | 1 | SUPPRESSION LINE | | 344300 | 1 | PIN PROG/TCAS (1SG) | ------------------------------------------------------------------------------NOTE : Fault of the selected ATC is a class 1 failure. ____ Fault of the ATC in standby is a class 3 failure. NOTE : Fault of one radio altimeter is a class 3 fault whereas ____ it becomes a class 1 fault when two radio altimeters are faulty. The class 3 recorded external faults are displayed through the menu sequence as shown in the following figure. (Ref. Fig. 035C) **ON A/C 001-049, 101-105, 151-199, (3) PREVIOUS LEGS REPORT The messages are identical to those shown in the Para. above but concern the last 63 flights if faults have occurred during these flights. (Ref. Fig. 036)

  R EFF : 001-049, 101-105, 151-199, 501-509,  34-43-00 Page A64 511-526, 528-599,  Config-1 Feb 01/10  CES

 

TCAS - PREVIOUS LEGS REPORT Figure 036   EFF : 001-049, 101-105, 151-199,  34-43-00 Page A65   Config-1 May 01/09  CES

 

(4) LRU IDENTIFICATION (Ref. Fig. 037) (5) GROUND SCANNING This function enables consultation of the TCAS computer fault recordings as defined by the Component Manufacturer. The TCAS peripheral monitoring and internal cyclic tests are used in order to detect transient faults. (Ref. Fig. 038) (6) GROUND REPORT This function is used to present class 1, 2 or 3 internal faults when they are detected on ground. These faults differ from those displayed on the LAST LEG REPORT page. The following figure shows examples of internal faults recorded on ground by the TCAS system. The relevant trouble shooting data are displayed by pressing the line key adjacent to the fault indication. (Ref. Fig. 039) (7) Not Applicable (8) Not Applicable **ON A/C 051-099, 201-209, (3) PREVIOUS LEGS REPORT The messages are identical to those shown in the Para. above but concern the last 63 flights if faults have occurred during these flights. (Ref. Fig. 036A) (4) LRU IDENTIFICATION R **ON A/C 201-207, (Ref. Fig. 037B) **ON A/C 208-209, (Ref. Fig. 037C)

  EFF : 001-049, 051-099, 101-105, 151-199,  34-43-00 Page A66 201-209,  Config-1 May 01/09  CES

 

TCAS - PREVIOUS LEGS REPORT Figure 036A   EFF : 051-099, 201-209,  34-43-00 Page A67   Config-1 May 01/09  CES

 

TCAS - Previous Leg Report Figure 036B   R EFF : 051-099, 251-299,  34-43-00 Page A68   Config-1 Nov 01/09  CES

 

TCAS - PREVIOUS LEGS REPORT Figure 036C   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page A69   Config-1 Feb 01/10  CES

 

TCAS - PREVIOUS LEGS REPORT Figure 036D   EFF : 106-149, 201-207, 210-249, 301-399,  34-43-00 Page A70 401-499,  Config-1 May 01/09  CES

 

TCAS - LRU IDENTIFICATION Figure 037   EFF : 001-049, 101-105, 151-199,  34-43-00 Page A71   Config-1 May 01/09  CES

 

TCAS - LRU Identification Figure 037A   R EFF : 051-099, 251-299,  34-43-00 Page A72   Config-1 Nov 01/09  CES

 

TCAS - LRU IDENTIFICATION Figure 037B   EFF : 201-207,  34-43-00 Page A73   Config-1 May 01/09  CES

 

TCAS - LRU IDENTIFICATION Figure 037C   EFF : 208-209,  34-43-00 Page A74   Config-1 May 01/09  CES

 

TCAS - LRU IDENTIFICATION Figure 037D   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page A75   Config-1 Feb 01/10  CES

 

TCAS - LRU IDENTIFICATION Figure 037E

R

  EFF : 106-149, 201-207, 210-249, 301-399,  34-43-00 Page A76 401-499,  Config-1 May 01/09  CES

 

TCAS - GROUND SCANNING Figure 038   EFF : 001-049, 101-105, 151-199,  34-43-00 Page A77   Config-1 May 01/09  CES

 

TCAS - GROUND SCANNING Figure 038A   EFF : 051-099, 201-209,  34-43-00 Page A78   Config-1 May 01/09  CES

 

TCAS - GROUND SCANNING Figure 038B   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page A79   Config-1 Feb 01/10  CES

 

TCAS - GROUND SCANNING Figure 038C   R EFF : 051-099, 106-149, 201-207, 210-249,  34-43-00 Page A80 251-299, 301-399, 401-499,  Config-1 Nov 01/09  CES

 

TCAS - GROUND REPORT Figure 039   EFF : 001-049, 101-105, 151-199,  34-43-00 Page A81   Config-1 May 01/09  CES

 

**ON A/C 051-099, 201-209, (5) GROUND SCANNING This function enables consultation of the TCAS computer fault recordings as defined by the Component Manufacturer. The TCAS peripheral monitoring and internal cyclic tests are used in order to detect transient faults. (Ref. Fig. 038A) (6) TROUBLE SHOOTING DATA This function allows to analyze the snapshot of the recorded fault to detect any software bug. Two types of data are displayed: - some correlation parameters which are the date and the UTC hour displayed in clear english, - some snapshot data delivered in hexadecimal code or in clear message. (Ref. Fig. 040) (7) GROUND REPORT This function is used to present class 1, 2 or 3 internal faults when they are detected on ground. These faults differ from those displayed on the LAST LEG REPORT page. The following figure shows examples of internal faults recorded on ground by the TCAS system. The relevant trouble shooting data are displayed by pressing the line key adjacent to the fault indication. (Ref. Fig. 039A) (8) Not Applicable R

**ON A/C 051-099, 251-299, 501-509, 511-526, 528-599, (3) PREVIOUS LEGS REPORT The messages are identical to those shown in the Para. above but concern the last 63 flights if faults have occurred during these flights. **ON A/C 051-099, 251-299, (Ref. Fig. 036B)

  R EFF : 051-099, 201-209, 251-299, 501-509,  34-43-00 Page A82 511-526, 528-599,  Config-1 Feb 01/10  CES

 

TCAS - GROUND REPORT Figure 039A   EFF : 051-099, 201-209,  34-43-00 Page A83   Config-1 May 01/09  CES

 

TCAS - GROUND REPORT Figure 039B   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page A84   Config-1 Feb 01/10  CES

 

TCAS - GROUND REPORT Figure 039C   R EFF : 051-099, 106-149, 201-207, 210-249,  34-43-00 Page A85 251-299, 301-399, 401-499,  Config-1 Nov 01/09  CES

 

TCAS - TROUBLE SHOOTING DATA Figure 040   EFF : 051-099, 201-209,  34-43-00 Page A86   Config-1 May 01/09  CES

 

R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 036C)

R

**ON A/C 051-099, 251-299, 501-509, 511-526, 528-599, (4) LRU IDENTIFICATION **ON A/C 051-099, 251-299, (Ref. Fig. 037A)

R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 037D)

R

**ON A/C 051-099, 251-299, 501-509, 511-526, 528-599, (5) GROUND SCANNING This function enables consultation of the TCAS computer fault recordings as defined by the Component Manufacturer. The TCAS peripheral monitoring and internal cyclic tests are used in order to detect transient faults.

R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 038B) **ON A/C 051-099, 251-299, (Ref. Fig. 038C)

  R EFF : 051-099, 251-299, 501-509, 511-526,  34-43-00 Page A87 528-599,  Config-1 Feb 01/10  CES

 

R

**ON A/C 051-099, 251-299, 501-509, 511-526, 528-599, (6) TROUBLE SHOOTING DATA This function allows to analyze the snapshot of the recorded fault to detect any software bug. Two types of data are displayed: - some correlation parameters which are the date and the UTC hour displayed in clear english, - some snapshot data delivered in hexadecimal code or in clear message.

R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 040A) **ON A/C 051-099, 251-299, (Ref. Fig. 040B)

R

**ON A/C 051-099, 251-299, 501-509, 511-526, 528-599, (7) GROUND REPORT This function is used to present class 1, 2 or 3 internal faults when they are detected on ground. These faults differ from those displayed on the LAST LEG REPORT page. The following figure shows examples of internal faults recorded on ground by the TCAS system. The relevant trouble shooting data are displayed by pressing the line key adjacent to the fault indication.

R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 039B) **ON A/C 051-099, 251-299, (Ref. Fig. 039C)

  R EFF : 051-099, 251-299, 501-509, 511-526,  34-43-00 Page A88 528-599,  Config-1 Feb 01/10  CES

 

TCAS - TROUBLE SHOOTING DATA Figure 040A   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page A89   Config-1 Feb 01/10  CES

 

TCAS - TROUBLE SHOOTING DATA Figure 040B   R EFF : 051-099, 106-149, 201-207, 210-249,  34-43-00 Page A90 251-299, 301-399, 401-499,  Config-1 Nov 01/09  CES

 

R

**ON A/C 051-099, 251-299, 501-509, 511-526, 528-599, (8) DISCRETE CONFIGURATION This function is used to present the value or the status of several discretes. A report screen for each data shows the status of the discrete at the time this menu is selected. (Ref. Fig. 041, 042, 043) **ON A/C 106-149, 201-207, 210-249, 301-399, 401-499, Post SB

34-1238 For A/C 201-207,

(3) PREVIOUS LEGS REPORT The messages are identical to those shown in the Para. above but concern the last 63 flights if faults have occurred during these flights. (Ref. Fig. 036D) (4) LRU IDENTIFICATION **ON A/C 106-149, 201-207, 210-249, 301-399, 401-499, Post SB Post SB

34-1179 For A/C 201-207, 34-1238 For A/C 201-207, (Ref. Fig. 037E)

**ON A/C 106-149, 201-207, 210-249, 301-399, 401-499, Post SB

34-1238 For A/C 201-207,

(5) GROUND SCANNING This function enables consultation of the TCAS computer fault recordings as defined by the Component Manufacturer. The TCAS peripheral monitoring and internal cyclic tests are used in order to detect transient faults. (Ref. Fig. 038C) (6) TROUBLE SHOOTING DATA This function allows to analyze the snapshot of the recorded fault to detect any software bug. Two types of data are displayed: - some correlation parameters which are the date and the UTC hour displayed in clear english,

  R EFF : 051-099, 106-149, 201-207, 210-249,  34-43-00 Page A91 251-299, 301-399, 401-499, 501-509, 511-526,  Config-1 Feb 01/10 528-599, CES

 

TCAS - DISCRETE CONFIGURATION 1/3 Figure 041   R EFF : 051-099, 251-299, 501-509, 511-526,  34-43-00 Page A92 528-599,  Config-1 Feb 01/10  CES

 

TCAS - DISCRETE CONFIGURATION Figure 041A   EFF : 106-149, 201-207, 210-249, 301-399,  34-43-00 Page A93 401-499,  Config-1 May 01/09  CES

 

TCAS - DISCRETE CONFIGURATION 2/3 Figure 042   R EFF : 051-099, 251-299, 501-509, 511-526,  34-43-00 Page A94 528-599,  Config-1 Feb 01/10  CES

 

TCAS - DISCRETE CONFIGURATION 3/3 Figure 043   R EFF : 051-099, 251-299, 501-509, 511-526,  34-43-00 Page A95 528-599,  Config-1 Feb 01/10  CES

 

- some snapshot data delivered in hexadecimal code or in clear message. (Ref. Fig. 040B) (7) GROUND REPORT This function is used to present class 1, 2 or 3 internal faults when they are detected on ground. These faults differ from those displayed on the LAST LEG REPORT page. The following figure shows examples of internal faults recorded on ground by the TCAS system. The relevant trouble shooting data are displayed by pressing the line key adjacent to the fault indication. (Ref. Fig. 039C) (8) DISCRETE CONFIGURATION This function is used to present the value or the status of several discretes. A report screen for each data shows the status of the discrete at the time this menu is selected. (Ref. Fig. 041A) **ON A/C 001-049, 101-105, (9) TCAS functional test A TCAS built-in functional test can be initiated by pressing the line key adjacent to the TEST indication on the TCAS maintenance sub-menu. The following sequence is then generated. (Ref. Fig. 044, 045) - the test ends with the display of the following message on the MCDU: TEST OK or TEST FAIL When all the tests are completed and no fault has been detected, the synthesized voice message TCAS SYSTEM TEST OK is announced. If one of the test criteria has not been met, the synthesized voice message TCAS SYSTEM TEST FAIL is announced. Remarks: - this short test permits to check rapidly, on ground, the functionality of the TCAS and particularly that of the PFD/NDs via the DMC. In addition it enables to check correct operation of the synthesized voice message system. NOTE : To date, the DMCs cannot present four intruders as specified ____ on the instruction page. Only three intruders (RA, TA, PROXIMATE) are shown on the test display. The future Full Time Display will call for their presentation.

  EFF : 001-049, 101-149, 201-207, 210-249,  34-43-00 Page A96 301-399, 401-499,  Config-1 May 01/09  CES

 

TCAS - Functional Test (Sheet 1/2) Figure 044   EFF : 001-049, 101-105, 151-199,  34-43-00 Page A97   Config-1 May 01/09  CES

 

TCAS - Functional Test (Sheet 1/2) Figure 044A   R EFF : 051-099, 251-299,  34-43-00 Page A98   Config-1 Nov 01/09  CES

 

TCAS - Functional Test (Sheet 1/2) Figure 044B   EFF : 201-209,  34-43-00 Page A99   Config-1 May 01/09  CES

 

TCAS - Functional Test 1/2 Figure 044C   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page B0   Config-1 Feb 01/10  CES

 

TCAS - Functional Test (Sheet 1/2) Figure 044D

R

  EFF : 106-149, 201-207, 210-249, 301-399,  34-43-00 Page B1 401-499,  Config-1 May 01/09  CES

 

TCAS - Functional Test (Sheet 2/2) Figure 045   EFF : 001-049, 101-105, 151-199,  34-43-00 Page B2   Config-1 May 01/09  CES

 

(10) Software configuration follow-up The TCAS has the DATA BASE loading capacity from a portable data loader or an airborne data loader (MDDU) in compliance with ARINC 615 characteristics. Consequently it must be possible to check correct downloading by using the CFDS/MCDU interface. The LRU IDENTIFICATION item displays the downloaded software version reference. NOTE : The TCAS is not data loadable. ____ R

**ON A/C 051-099, 251-299, (9) TCAS functional test A TCAS built-in functional test can be initiated by pressing the line key adjacent to the TEST indication on the TCAS maintenance sub-menu. The following sequence is then generated. (Ref. Fig. 044A, 045A) - the test ends with the display of the following message on the MCDU: TEST OK or TEST FAIL - at the end of the functional test the TCAS computer generates a complete sequence of synthesized voice messages. When all the tests are completed and no fault has been detected the computer reports: TCAS SYSTEM TEST PASS. If one of the test criteria has not been met, the synthesized voice message is announced: TCAS SYSTEM TEST FAIL Remarks: - this short test permits to check rapidly, on ground, the functionality of the TCAS and particularly that of the PFD/NDs via the DMC. In addition it enables to check correct operation of the synthesized voice message system. (10) Software configuration follow-up The software of the TCAS can be loaded from an airborne data loader (MDDU) in compliance with ARINC 615-3 characteristics. Consequently it must be possible to check correct downloading by using the CFDS/MCDU interface. The LRU IDENTIFICATION item displays the downloaded software version reference (line SW/N). The software can also be loaded throught the connector RS-232 in the front face of the TCAS computer.

  R EFF : 001-049, 051-099, 101-105, 251-299,  34-43-00 Page B3   Config-1 Nov 01/09  CES

 

TCAS - Functional Test 2/2 Figure 045A   R EFF : 051-099, 251-299,  34-43-00 Page B4   Config-1 Nov 01/09  CES

 

NOTE : Data loading is allowed only through application of Airbus ____ Service Bulletin or Vendor Service Bulletin. **ON A/C 106-149, 201-249, 301-399, 401-499, (9) TCAS functional test A TCAS built-in functional test can be initiated by pressing the line key adjacent to the TEST indication on the TCAS maintenance sub-menu. The following sequence is then generated. **ON A/C 201-209, (Ref. Fig. 044B) **ON A/C 106-149, 201-207, 210-249, 301-399, 401-499, Post SB

34-1238 For A/C 201-207, (Ref. Fig. 044D)

**ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 045B) - the test ends with the display of the following message on the MCDU: TEST OK or TEST FAIL - at the end of the functional test the TCAS computer generates a complete sequence of synthesized voice messages. When all the tests are completed and no fault has been detected the computer reports TCAS SYSTEM TEST OK. If one of the test criteria has not been met, the synthesized voice message TCAS SYSTEM TEST FAIL is announced. Remarks: - this short test permits to check rapidly, on ground, the functionality of the TCAS and particularly that of the PFD/NDs via the DMC. In addition it enables to check correct operation of the synthesized voice message system - to date the DMCs cannot present the OTHER type intruders. The future Full Time Display installation will call for their presentation.

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-43-00 Page B5 301-399, 401-499,  Config-1 Nov 01/09  CES

 

TCAS - Functional Test (Sheet 2/2) Figure 045B   EFF : 106-149, 201-249, 301-399, 401-499,  34-43-00 Page B6   Config-1 May 01/09  CES

 

(10) Software configuration follow-up The TCAS has the DATA BASE loading capacity from a portable data loader or an airborne data loader (MDDU) in compliance with ARINC 615 characteristics. Consequently it must be possible to check correct downloading by using the CFDS/MCDU interface. The LRU IDENTIFICATION item displays the downloaded software version reference (line SW/N). R

**ON A/C 501-509, 511-526, 528-599, (9) TCAS functional test A TCAS built-in functional test can be initiated by pressing the line key adjacent to the TEST indication on the TCAS maintenance sub-menu. The following sequence is then generated. (Ref. Fig. 044C, 045C) - the test ends with the display of the following message on the MCDU: TEST OK or TEST FAIL - at the end of the functional test the TCAS computer generates a complete sequence of synthesized voice messages. When all the tests are completed and no fault has been detected the computer reports TCAS SYSTEM TEST OK. If one of the test criteria has not been met, the synthesized voice message TCAS SYSTEM TEST FAIL is announced. Remarks: - this short test permits to check rapidly, on ground, the functionality of the TCAS and particularly that of the PFD/NDs via the DMC. In addition it enables to check correct operation of the synthesized voice message system. (10) Software configuration follow-up The software of the TCAS can be loaded from an airborne data loader (MDDU) in compliance with ARINC 615-3 characteristics. Consequently it must be possible to check correct downloading by using the CFDS/MCDU interface. The LRU IDENTIFICATION item displays the downloaded software version reference (line SW/N). The software can also be loaded throught the PDL or the PCMCIA card inserted in the front face of the TCAS computer. NOTE : Data loading is allowed only through application of Airbus ____ Service Bulletin or Vendor Service Bulletin.

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-43-00 Page B7 501-509, 511-526, 528-599,  Config-1 Feb 01/10  CES

 

TCAS - Functional Test 2/2 Figure 045C   R EFF : 501-509, 511-526, 528-599,  34-43-00 Page B8   Config-1 Feb 01/10  CES

 

R

**ON A/C 001-049, 101-105, 151-199,

R

Post SB

34-1177 For A/C 001-049,101-105,

R R R R R R R R R R R R R R R R R R

(9) TCAS functional test A TCAS built-in functional test can be initiated by pressing the line key adjacent to the TEST indication on the TCAS maintenance sub-menu. The following sequence is then generated. (Ref. Fig. 044, 045) - the test ends with the display of the following message on the MCDU: TEST OK or TEST FAIL When all the tests are completed and no fault has been detected, the synthesized voice message TCAS SYSTEM TEST OK is announced. If one of the test criteria has not been met, the synthesized voice message TCAS SYSTEM TEST FAIL is announced. Remarks: - this short test permits to check rapidly, on ground, the functionality of the TCAS and particularly that of the PFD/NDs via the DMC. In addition it enables to check correct operation of the synthesized voice message system.

R R R R

NOTE : To date, the DMCs cannot present four intruders as specified ____ on the instruction page. Only three intruders (RA, TA, PROXIMATE) are shown on the test display. The future Full Time Display will call for their presentation.

R R R R R R R R

(10) Software configuration follow-up The TCAS has the DATA BASE loading capacity from a portable data loader or an airborne data loader (MDDU) in compliance with ARINC 615 characteristics. Consequently it must be possible to check correct downloading by using the CFDS/MCDU interface. The LRU IDENTIFICATION item displays the downloaded software version reference.

  EFF : 001-049, 101-105, 151-199,  34-43-00 Page B9   Config-1 May 01/09  CES

 

TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS) - SERVICING _____________________________________________________ **ON A/C 001-049, 051-061, 101-105, TASK 34-43-00-610-001 Uploading Procedure with Portable Data Loader (SFIM or equivalent) to Load the Operational Software of the TCAS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific YV68A110

circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.) 1 PORTABLE DATA LOADER

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 52-41-00-410-002 34-43-00-991-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page Close the Avionics Compartment Doors after Access Fig. 301

3. __________ Job Set-up Subtask 34-43-00-861-051 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

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Subtask 34-43-00-860-071 B. On the PORTABLE DATA LOADER (YV68A110), make sure that the ON/OFF switch is at OFF. Subtask 34-43-00-010-052 C. Get Access (1) Put the access platform in position at the access door 824 in zone 128. (2) Open the access door 824. Subtask 34-43-00-865-067 D. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/TCAS 4SG K10 Subtask 34-43-00-860-072 E. Aircraft Maintenance Configuration (1) On the panel 188VU (Ref. Fig. 301/TASK 34-43-00-991-001) (a) Remove the blanking cap from the DATA LOADER connector 194VC. (b) Connect the cable of the portable data loader to the DATA LOADER connector 194VC. (2) Make sure that the aircraft is in ground configuration.

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Data Loader Connector Figure 301/TASK 34-43-00-991-001   EFF : 001-049, 051-099, 101-105,  34-43-00 Page 303   Config-1 May 01/09  CES

 

Subtask 34-43-00-865-068 F. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/MCDU/1 11CA1 B01 49VU L/G/LGCIU/SYS1/NORM 1GA C09 121VU CFDS/CFDIU/SPLY 2TW J18 121VU CFDS/CFDIU/BACK/UP 8TW J17 121VU AUTO FLT/MCDU/2 11CA2 N20 121VU HYDRAULIC/LGCIU/SYS2 2GA Q35 Subtask 34-43-00-865-069 G. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 4SG. 4. Procedure _________ Subtask 34-43-00-970-052 A. Loading of the Operational Software NOTE : After the uploading operations, you must do a check on the MCDU, ____ of the reference of the data loaded in the computer. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the portable data loader:

On the portable data loader:

- set the ON/OFF switch to ON.

- the < < MDDU READY > > indication comes into view.

- put the disk into the disk drive, the label in the forward direction.

- the READY indication comes into view - then, the WAIT RESPONSE indication comes into view - then, the TRANSF IN PROG indication comes into view.

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------NOTE : If more than one disk is ____ necessary, the EJECT DISK and INSERT NEXT DISK indications come into view one after the other. They tell you to put a new disk in the portable data loader. - when all the data are in the computer, the TRANSF COMPLETE indication comes into view. - eject the disk from the disk drive.

- the < < MDDU READY > > indication comes into view.

Subtask 34-43-00-280-055 B. On the MCDU Check of the Reference of the Data Loaded in the TCAS (1) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). (2) Do a check of the identification of the loaded disk. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the TCAS indication.

- the TCAS page comes into view.

- push the line key adjacent to the LRU IDENT indication.

- the LRU IDENTIFICATION page comes into view. NOTE : Make sure that the SW/N ____ indication shown is the same as the SW/N indication read on the disk.

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5. Close-up ________ Subtask 34-43-00-860-073 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) On the portable data loader, set the ON/OFF switch to OFF. Subtask 34-43-00-865-070 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/TCAS 4SG K10 Subtask 34-43-00-860-074 C. Aircraft Maintenance Configuration (1) On the panel 188VU, disconnect the cable of the portable data loader from the DATA LOADER connector (2) install the blanking cap on the DATA LOADER connector. Subtask 34-43-00-865-071 D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 4SG. Subtask 34-43-00-862-051 E. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). Subtask 34-43-00-410-052 F. Close Access (1) Close the access door 824 (Ref. TASK 52-41-00-410-002). (2) Remove the access platform(s).

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R R

**ON A/C 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, TASK 34-43-00-610-001-B Uploading Procedure to Load the Operational Software of the TCAS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page

3. __________ Job Set-up Subtask 34-43-00-861-053 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 34-43-00-860-077 B. Make sure that the aircraft is in the ground configuration.

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Subtask 34-43-00-865-075 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/MCDU/1 11CA1 B01 49VU L/G/LGCIU/SYS1/NORM 1GA C09 121VU CFDS/CFDIU/SPLY 2TW J18 121VU AUTO FLT/MCDU/2 11CA2 N20 121VU HYDRAULIC/LGCIU/SYS2 2GA Q35 R R

**ON A/C 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 31-1163 For A/C 155-156,208-209, 121VU CFDS/CFDIU/BACK/UP

R R

8TW

J17

**ON A/C 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 4. Procedure _________ Subtask 34-43-00-970-054 A. Loading Procedure of the Operational Software ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU: - turn the BRT knob.

The MCDU is on.

2. On the overhead panel, on the Data Loading Selector: - set the ON/OFF switch to ON.

On the display of the Data Loading Selector: - DB/N: PUSH NEXT/PREV indication is shown On the multipurpose disk drive unit: - the < < MDDU READY > > indication is shown.

3. On the overhead panel, on the Data Loading Selector:

On the display of the Data Loading Selector:

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the PREV or NEXT key until - TCAS you get the indication of the NOT SELECTED TCAS indication is shown 4. Put the software standard application (5RB) disk into the disk drive of the data loader, the label in the forward direction

On the multipurpose disk drive unit: - the READY indication is shown - then, the WAIT RESPONSE indication is shown

5. On the overhead panel, on the Data Loading Selector: - push the SEL CTL key

On the display of the Data Loading Selector: - TCAS SELECTED indication is shown On the multipurpose disk drive unit: - the TRANS IN PROG indication is shown - when all the data are put into the computer, the TRANSF COMPLETE indication is shown

6. On the overhead panel, on the Data Loading Selector: - push the SEL CTL key

On the display of the Data Loading Selector: - TCAS NOT SELECTED indication is shown

7. Eject the disk from the disk drive of the data loader

On the multipurpose disk drive unit: - the < < MDDU READY > > indication is shown

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Subtask 34-43-00-280-057 B. On the MCDU Check of the Reference of the Data Loaded in the TCAS (1) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). (2) Do a check of the identification of the loaded disk. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the TCAS indication.

- the TCAS page comes into view.

- push the line key adjacent to the LRU IDENT indication.

- the LRU IDENTIFICATION page comes into view. NOTE : Make sure that the SW/N ____ indication shown is the same as the SW/N indication read on the disk.

5. Close-up ________ Subtask 34-43-00-860-078 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) On the MCDU, set the BRT knob to OFF. (3) Put the disk in the storage box. Subtask 34-43-00-080-051 B. Deactivation of the Data Loading System (1) On the Data Loading Selector, set the ON/OFF switch to OFF. (2) Make sure that MDDU door is closed

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Subtask 34-43-00-862-053 C. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).

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**ON A/C 062-099, TASK 34-43-00-610-001-C Uploading Procedure with Portable Data Loader (SFIM or equivalent) to Load the Operational Software of the TCAS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific YV68A110

circuit breaker(s) safety clip(s) 1 ACCESS PLATFORM 1M(3 FT) 1 PORTABLE DATA LOADER

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 52-41-00-410-002 34-43-00-991-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page Close the Avionics Compartment Doors after Access Fig. 301

3. __________ Job Set-up Subtask 34-43-00-861-060 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

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Subtask 34-43-00-860-109 B. On the PORTABLE DATA LOADER (YV68A110), make sure that the ON/OFF switch is at OFF. Subtask 34-43-00-010-057 C. Get Access (1) Put the ACCESS PLATFORM 1M(3 FT) in position at the access door 824 in zone 128. (2) Open the access door 824. Subtask 34-43-00-865-105 D. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/TCAS 4SG K10 Subtask 34-43-00-860-110 E. Aircraft Maintenance Configuration (1) On the panel 188VU (Ref. Fig. 301/TASK 34-43-00-991-001) (a) Remove the blanking cap from the DATA LOADER connector 194VC. (b) Connect the cable of the portable data loader to the DATA LOADER connector 194VC. (2) Make sure that the aircraft is in ground configuration.

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Subtask 34-43-00-865-106 F. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU AUTO FLT/MCDU/1 11CA1 B01 49VU L/G/LGCIU/SYS1/NORM 1GA C09 121VU CFDS/CFDIU/SPLY 2TW J18 121VU CFDS/CFDIU/BACK/UP 8TW J17 121VU AUTO FLT/MCDU/2 11CA2 N20 121VU HYDRAULIC/LGCIU/SYS2 2GA Q35 Subtask 34-43-00-865-107 G. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 4SG. 4. Procedure _________ Subtask 34-43-00-970-060 A. Loading of the Operational Software NOTE : After the uploading operations, you must do a check on the MCDU, ____ of the reference of the data loaded in the computer. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the portable data loader:

On the portable data loader:

- set the ON/OFF switch to ON.

- the < < MDDU READY > > indication comes into view.

- put the disk into the disk drive, the label in the forward direction.

- the READY indication comes into view - then, the WAIT RESPONSE indication comes into view - then, the TRANSF IN PROG indication comes into view.

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------NOTE : If more than one disk is ____ necessary, the EJECT DISK and INSERT NEXT DISK indications come into view one after the other. They tell you to put a new disk in the portable data loader. - when all the data are in the computer, the TRANSF COMPLETE indication comes into view. - eject the disk from the disk drive.

- the < < MDDU READY > > indication comes into view.

Subtask 34-43-00-280-062 B. On the MCDU Check of the Reference of the Data Loaded in the TCAS (1) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). (2) Do a check of the identification of the loaded disk. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the TCAS indication.

- the TCAS page comes into view.

- push the line key adjacent to the LRU IDENT indication.

- the LRU IDENTIFICATION page comes into view. NOTE : Make sure that the SW/N ____ indication shown is the same as the SW/N indication read on the disk.

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5. Close-up ________ Subtask 34-43-00-860-111 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) On the portable data loader, set the ON/OFF switch to OFF. Subtask 34-43-00-865-108 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/TCAS 4SG K10 Subtask 34-43-00-860-112 C. Aircraft Maintenance Configuration (1) On the panel 188VU, disconnect the cable of the portable data loader from the DATA LOADER connector (2) install the blanking cap on the DATA LOADER connector. Subtask 34-43-00-865-109 D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 4SG. Subtask 34-43-00-862-060 E. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). Subtask 34-43-00-410-059 F. Close Access (1) Close the access door 824 (Ref. TASK 52-41-00-410-002). (2) Remove the access platform(s).

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TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS) - DEACTIVATION/REACTIVATION _____________________________________________________________________ TASK 34-43-00-040-001 Deactivation of the TCAS 1. __________________ Reason for the Job Refer to the MMEL TASK: 34-43-01 NAVIGATION TCAS (FAA Only) 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-60-00-860-001 31-60-00-860-002 34-10-00-860-004

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure IR Alignment Procedure

3. __________ Job Set-up Subtask 34-43-00-860-067 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (PFDs and NDs only) (Ref. TASK 31-60-00860-001). (3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (4) On the EFIS control sections of the FCU: - set the mode selector switches to ROSE. - set the scale selector switches to 10.

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Subtask 34-43-00-865-063 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/TCAS 4SG K10 121VU COM NAV/ATC/2 5SH2 K07 4. Procedure _________ Subtask 34-43-00-040-050 A. Deactivation of the TCAS (1) Open, safety and tag the circuit breaker 4SG of the TCAS (ignore the related warnings). 5. Close-up ________ Subtask 34-43-00-860-068 A. Put the aircraft back to its initial configuration. (1) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF. (2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (3) Make an entry in the log book. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items.

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TASK 34-43-00-440-001 Reactivation of the TCAS 1. __________________ Reason for the Job Refer to the MMEL TASK: 34-43-01 NAVIGATION TCAS (FAA Only) 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power

3. __________ Job Set-up Subtask 34-43-00-860-069 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). 4. Procedure _________ Subtask 34-43-00-440-050 A. Do the Trouble Shooting of the TCAS - Do the trouble shooting procedure related to the maintenance message.

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5. Close-up ________ Subtask 34-43-00-860-070 A. Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (2) Make sure that the work area is clean and clear of tool(s) and other items.

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TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS) - ADJUSTMENT/TEST ___________________________________________________________ TASK 34-43-00-740-001 BITE Test of the TCAS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 31-60-00-860-001 31-60-00-860-002 34-10-00-860-004

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page EIS Start Procedure EIS Stop Procedure IR Alignment Procedure

3. __________ Job Set-up Subtask 34-43-00-860-050 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the EIS start procedure (PFDs and NDs only) (Ref. TASK 31-60-00860-001). (3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (4) On the EFIS control sections of the FCU: - set the mode selector switches to ROSE - set the scale selector switches to 10.

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(5) On the center pedestal, if the ATC/TCAS control unit has the ALTITUDE REPORTING function , set the ALT RPTG (or ALT RPT) switch to ON. (6) Do the procedure to get access to the SYSTEM REPORT/TEST NAV page on one MCDU (Ref. TASK 31-32-00-860-010): - push the NEXT PAGE function key (two times) until the TCAS menu page comes into view. Subtask 34-43-00-865-118 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/TCAS 4SG K10 121VU COM NAV/ATC/2 5SH2 K07 121VU AUDIO MIXING 14WW K03 4. Procedure _________ R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, Subtask 34-43-00-740-050-F A. BITE Test of the TCAS NOTE : During the test, obey the instructions shown on the MCDU used. ____ ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the MCDU: - push the line key adjacent to the TEST indication.

- on the MCDU, the subsequent TEST page with instructions comes into view. - on the CAPT and F/O NDs, these symbols come into view: * a white unfilled diamond with a + 10 indication. * a white solid diamond with a down arrow and a + 02 indication. * an amber solid circle with an up arrow and a - 02 indication.

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------* a red solid square with a - 10 indication. - on the CAPT and F/O PFDs: * the V/S scale is divided in three sectors: one grey and two red ones. * on the CAPT and F/O NDs, the symbols go out of view. * then the V/S scale goes back to the normal configuration. - in the loudspeakers: * you can hear the TCAS TEST OK voice. - on the MCDU, the TEST OK indication comes into view. **ON A/C 051-099, 251-299, Subtask 34-43-00-740-050-E A. BITE Test of the TCAS NOTE : During the test, obey the instructions shown on the MCDU used. ____ ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the MCDU:

On the MCDU:

- push the line key adjacent to the TEST indication.

- the subsequent TCAS TEST page with instructions comes into view.

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 8 S indication comes into view. - this sequence starts: - in the loudspeakers: * you can hear the TCAS TEST message. - on the CAPT and F/O NDs, these symbols come into view: * a white unfilled diamond with a +10 indication. * a white solid diamond with a down arrow and a - 10 indication.

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------* an amber solid circle with an up arrow and a - 02 indication. * a red solid square with a + 02 indication. - on the CAPT and F/O PFDs: * the V/S scale is divided into three sectors: one grey and two red. * the symbols go out of view. * the V/S scale goes back to the normal configuration. - in the loudspeakers: * you can hear the TCAS TEST PASSED message. On the MCDU: - push the line key adjacent to the YES indication.

- THE SYNTHETIC VOICE WAS GENERATED: indication comes into view.

- push the line key adjacent to the PASS indication.

- the TEST OK page comes into view after a short period.

- push the line key adjacent to the RETURN indication.

- the TCAS menu page comes into view.

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**ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-43-00-740-050-G A. BITE Test of the TCAS NOTE : During the test, obey the instructions shown on the MCDU used. ____ ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the MCDU:

On the MCDU:

- push the line key adjacent to the TEST indication.

- the subsequent TCAS TEST page with instructions comes into view.

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 12 S indication comes into view. - this sequence starts: - on the CAPT and F/O NDs, these symbols come into view: * a white unfilled diamond with a + 10 indication. * a white solid diamond with a down arrow and a - 10 indication. * an amber solid circle with an up arrow and a - 02 indication. * a red solid square with a + 02 indication. - on the CAPT and F/O PFDs: * a sequence of RA advisories (grey and red sectors) comes into view on the V/S scale. * at the end of this sequence, the V/S scale goes back to the normal configuration. - in the loudspeakers: * you can hear the TCAS SYSTEM TEST OK message.

- push the line key adjacent to the TCAS SYSTEM TEST OK indication.

- on the MCDU, the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication.

- on the MCDU, the TCAS menu page comes into view.

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**ON A/C ALL 5. Close-up ________ R R

**ON A/C 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-43-00-860-136 A. Do a reset of the EIS. (1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001). **ON A/C ALL Subtask 34-43-00-860-051 B. Put the aircraft back to its initial configuration. (1) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF. (2) On the center pedestal, on the MCDU, push the line key adjacent to the RETURN indication until the MCDU MENU page comes into view. (3) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items.

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TASK 34-43-00-720-001 Functional Test of the TCAS Antennas 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

access platform aluminum adhesive tape circuit breaker(s) safety clip(s) ATC/TCAS test set

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 32-69-00-860-001 34-10-00-860-004

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Simulation of Flight, with the Aircraft on the Ground IR Alignment Procedure

3. __________ Job Set-up Subtask 34-43-00-480-050 A. Put an aluminum adhesive tape on the RA reception antenna 2 (5SA2).

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Subtask 34-43-00-860-079 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the ADIRS alignment procedure (Ref. TASK 34-10-00-860-004). (3) On the panel 13VU, on the CAPT and F/O EFIS control sections of the FCU: - set the mode selector switch to ROSE/NAV - set the scale selector switch to 10. Subtask 34-43-00-865-079 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/RAD ALTM/2 1SA2 K12 121VU COM NAV/TCAS 4SG K10 121VU COM NAV/ATC/2 5SH2 K07 Subtask 34-43-00-865-082 D. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/RAD ALTM/1 1SA1 K11 Subtask 34-43-00-860-080 E. Aircraft Maintenance Configuration NOTE : Ignore all the warnings. ____ (1) For the test of the TCAS bottom antenna: - On the center pedestal, on one MCDU, get the LGCIU 1 page and simulate a flight condition (Ref. TASK 32-69-00-860-001) - Push the line key adjacent to the NOSE+LH+RH FLIGHT indication.

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(2) On the center pedestal, on the ATC/TCAS control unit: - Start the ATC 1 system - Enter the ATC code 7776, or a different code given by your local authorities, to keep the traffic interference to a minimum - Set the STBY/AUTO/ON switch to ON - Set the STBY/TA/TA/RA switch to TA/RA - Set the THRT/ALL/ABV/BLW switch to ALL - Set the ALT RPTG/OFF/ON switch to ON. Subtask 34-43-00-480-051 F. Put the ATC/TCAS test set in position. NOTE : For the test of the TCAS top antenna, put the ATC/TCAS test set on ____ an access platform. (1) Put the ATC/TCAS test set in position on the right side of the aircraft at 40 ft. (12.19 m) from the bottom (top) antenna and at the same level as the antenna. (2) Connect the test antenna to the ATC/TCAS test set. (3) Make sure that the test antenna is in the line of sight of the TCAS bottom (top) antenna. (4) Energize the ATC/TCAS test set. 4. Procedure _________ Subtask 34-43-00-720-050 A. Functional Test of the TCAS Antennas ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ATC/TCAS test set: - set the ATCRBS/MODE S/TCAS/XPDR TEST selector switch to TCAS - set the TCAS-intruder scenario selector-switch so that the intruder has the same altitude as the aircraft - range: 14 NM - closing speed: +300 kts or more

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------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- start the test On the ATC/TCAS test set, the scenario starts. After some minutes, a minimum of two symbols come into view one after the other, in the right part of the ND: - a yellow circle (Traffic Advisory) in the 5NM range - then the yellow circle becomes a red square (Resolution Advisory). 2. Put the ATC/TCAS test set in position on the left side of the aircraft. 3. On the ATC/TCAS test set, start the test

On the ATC/TCAS test set, the scenario starts. After some minutes, a minimum of two symbols come into view one after the other, in the left part of the ND: - a yellow circle (Traffic Advisory) in the 5NM range - then the yellow circle becomes a red square (Resolution Advisory).

5. Close-up ________ Subtask 34-43-00-865-083 A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1SA1 Subtask 34-43-00-860-081 B. Put the aircraft back to its initial configuration. (1) On the center pedestal, put the ATC/TCAS control unit back to its initial configuration (standby/off mode). (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).

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Subtask 34-43-00-080-052 C. Remove the ground support and maintenance equipment, the special and standard tools and all other items. (1) Remove the aluminum adhesive tape from the RA reception antenna 2. (2) Remove the ATC/TCAS test set and the test antenna. Subtask 34-43-00-410-053 D. Close Access (1) Remove the access platform(s).

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R

**ON A/C 501-509, 511-526, 528-599, TASK 34-43-00-740-007 Read the TCAS CONFIGURATION Data of the TCAS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page

3. __________ Job Set-up Subtask 34-43-00-860-139 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the procedure to get access to the SYSTEM REPORT/TEST NAV page on one MCDU (Ref. TASK 31-32-00-860-010): - Push the NEXT PAGE function key until the TCAS menu page comes into view.

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Subtask 34-43-00-865-144 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/TCAS 4SG K10 4. Procedure _________ Subtask 34-43-00-740-058 A. Read the TCAS CONFIGURATION Data of the TCAS. NOTE : The actions and the results of this procedure occur on the MCDU ____ used. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Push the line key adjacent to the TCAS indication.

- The TCAS page comes into view.

2. Push the line key adjacent to the DISCRETE CONFIGURATION indication.

- The TCAS CONFIGURATION 1/2 page comes into view.

3. Push the down arrow key until the TCAS CONFIGURATION 2/2 page comes into view.

- The TCAS CONFIGURATION 2/2 page comes into view.

5. Close-up ________ Subtask 34-43-00-860-140 A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the MAINTENANCE MENU 1/2 page comes into view. (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

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ANTENNA - TCAS (7SG1,7SG2) - REMOVAL/INSTALLATION _________________________________________________ TASK 34-43-11-000-001 Removal of the TCAS Antenna (7SG1, 7SG2) WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific FOR FIN 7SG1 No specific

blanking caps circuit breaker(s) safety clip(s) nonmetallic scraper access platform 6.0 m (19 ft. 8 in.) blanking caps

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 11-003

USA ASTM D 740 METHYL-ETHYL-KETONE (Ref. 20-31-00)

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C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, 34-43-11-991-001

Fig. 401

**ON A/C 051-099, 251-299, 34-43-11-991-001-B

Fig. 401A

**ON A/C 106-149, 201-249, 301-399, 401-499, 34-43-11-991-001-A

Fig. 401B

**ON A/C ALL 3. __________ Job Set-up Subtask 34-43-11-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/TCAS 4SG K10 Subtask 34-43-11-010-050 B. Get Access (1) Put the access platform in position at zone 230 to get access to the TCAS top antenna 7SG1

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4. Procedure _________ R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, Subtask 34-43-11-020-050 A. Removal of the TCAS Antenna (Ref. Fig. 401/TASK 34-43-11-991-001) (1) Remove the sealant and the cord from the head of the screws (7). (2) Remove the screws (7) and the washers (8). (3) Pull the antenna (6) away from the fuselage structure (2). (4) Disconnect the coaxial connectors (1). NOTE : For the antenna 7SG1, the coaxial connectors (1) must not go ____ into the fuselage. (5) FOR 7SG1 Remove the foam washer (5). (6) Remove and discard the O-ring (4). (7) Remove the gasket (3). (8) Remove the antenna (6). (9) Put blanking caps on the disconnected coaxial connectors (1) and (9). (10) FOR 7SG1 Put masking tape around the coaxial cables (1) and attach them to the fuselage. (11) Remove the sealant with a nonmetallic scraper and clean the fuselage structure with CLEANING AGENTS (Material No. 11-003).

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TCAS Antenna Figure 401/TASK 34-43-11-991-001   R EFF : 001-049, 101-105, 151-199, 501-509,  34-43-11 Page 404 511-526, 528-599,  Config-1 Feb 01/10  CES

 

R

**ON A/C 051-099, 251-299, Subtask 34-43-11-020-050-B A. Removal of the TCAS Antenna (Ref. Fig. 401A/TASK 34-43-11-991-001-B) (1) Remove the sealant from the screw heads and around the antenna base. (2) Remove the screws (8) and the washers (7). (3) Pull the antenna (6) away from the fuselage structure (1). (4) Disconnect the four coaxial connectors (2). NOTE : For the antenna 7SG1, the coaxial connectors (2) must not go ____ into the fuselage. (5) FOR 7SG1 Remove the foam washer (5). (6) Remove and discard the O-ring (4) and the gasket (3). (7) Remove the antenna (6). (8) Put blanking caps on the disconnected coaxial connectors (2) and (9). (9) FOR 7SG1 Put masking tape around the coaxial cables (2) and attach them to the fuselage. (10) Remove the sealant with a nonmetallic scraper and clean the fuselage structure with CLEANING AGENTS (Material No. 11-003). **ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-43-11-020-050-A A. Removal of the TCAS Antenna (Ref. Fig. 401B/TASK 34-43-11-991-001-A) (1) Remove the sealant from the screw heads and around the antenna base. (2) Remove the screws (9) and the washers (8).

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TCAS Antenna Figure 401A/TASK 34-43-11-991-001-B   R EFF : 051-099, 251-299,  34-43-11 Page 406   Config-1 Nov 01/09  CES

 

TCAS Antenna Figure 401B/TASK 34-43-11-991-001-A   EFF : 106-149, 201-249, 301-399, 401-499,  34-43-11 Page 407   Config-1 May 01/09  CES

 

(3) Pull the antenna (6) away from the fuselage structure (1). (4) Disconnect the four coaxial connectors (2). NOTE : For the antenna 7SG1, the coaxial connectors (2) must not go ____ into the fuselage. (5) FOR 7SG1 Remove the foam washer (5). (6) Remove and discard the O-ring (4) and the gasket (3). (7) Remove the antenna (6). (8) Put blanking caps on the disconnected coaxial connectors (2) and (7). (9) FOR 7SG1 Put masking tape around the coaxial cables (2) and attach them to the fuselage. (10) Remove the sealant with a nonmetallic scraper and clean the fuselage structure with CLEANING AGENTS (Material No. 11-003).

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R

**ON A/C ALL TASK 34-43-11-400-001 Installation of the TCAS Antenna (7SG1, 7SG2) WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

FOR FIN 7SG1 No specific

lint-free cloth nonmetallic scraper access platform 6.0 m (19 ft. 8 in.) Torque Wrench : range 0.00 to 1.20 m.daN (0.00 to 9.00 lbf.ft) Torque Wrench : range 0.00 to 1.20 m.daN (0.00 to 9.00 lbf.ft)

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B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------No specific

corrosion-resistant-steel lockwire 0.4 mm (0.016 in.) dia.

Material No. 07-001B Material No. 09-008D Material No. 09-016 Material No. 11-003 Material No. 11-004 Material No. 16-003 Material No. 19-002 FOR FIN 7SG1 No specific

ELECTRICAL BOND VARNISH (Ref. 20-31-00) USA AMS-S-83318 CLASS B QUICK REPAIR FUEL TA NK SEALANT TEMPORARY (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) USA ASTM D 740 METHYL-ETHYL-KETONE (Ref. 20-31-00) USA MIL-T-81533 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM) (Ref. 20-31-00) F ASNB70720 COATING (OBSOLETE USE 16-021) (Ref. 20-31-00) USA MIL-T-713 SYNTHETIC FIBRE CORD (NYLON) 2.5MM DIA. (Ref. 20-31-00) corrosion-resistant steel lockwire 0.4 mm (0.016 in.) dia.

Material No. 07-001B Material No. 09-008D Material No. 09-016 Material No. 16-003 Material No. 19-002

ELECTRICAL BOND VARNISH (Ref. 20-31-00) USA AMS-S-83318 CLASS B QUICK REPAIR FUEL TA NK SEALANT TEMPORARY (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) F ASNB70720 COATING (OBSOLETE USE 16-021) (Ref. 20-31-00) USA MIL-T-713 SYNTHETIC FIBRE CORD (NYLON) 2.5MM DIA. (Ref. 20-31-00)

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C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-912-005 34-43-00-740-001 R

Electrical Bonding of Antennas With Conductive Bolts. BITE Test of the TCAS

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, 34-43-11-991-001

Fig. 401

**ON A/C 051-099, 251-299, 34-43-11-991-001-B

Fig. 401A

**ON A/C 106-149, 201-249, 301-399, 401-499, 34-43-11-991-001-A FOR FIN 7SG1 20-28-00-912-005

Fig. 401B Electrical Bonding of Antennas With Conductive Bolts.

**ON A/C ALL 3. __________ Job Set-up Subtask 34-43-11-860-050 A. Get Access (1) Make sure that the access platform is in position at zone 230 to get access to the TCAS top antenna 7SG1. Subtask 34-43-11-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/TCAS 4SG K10

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4. Procedure _________ WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN. _______ IF YOU DO: - RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH - WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER. WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. R

**ON A/C 001-049, 101-105, 151-199, 501-509, 511-526, 528-599, Subtask 34-43-11-420-050 A. Installation of the TCAS Antenna (Ref. Fig. 401/TASK 34-43-11-991-001) WARNING : OBEY THE COLOR CODES WHEN YOU CONNECT THE ELECTRICAL CONNECTORS _______ (THIS WILL PREVENT CROSS-CONNECTIONS). MAKE SURE THAT YOU INSTALL THE ANTENNA IN THE CORRECT DIRECTION. IF THE ANTENNA DOES NOT POINT IN THE CORRECT DIRECTION, THE TCAS WILL ONLY SENSE TRAFFIC BEHIND THE AIRCRAFT. (1) Remove the used sealant from the fuselage structure (2) with a nonmetallic scraper. (2) Clean the component interface and/or the adjacent area with CLEANING AGENTS (Material No. 11-004) and a lint-free cloth. NOTE : If you install the same antenna it is necessary to clean it ____ with CLEANING AGENTS (Material No. 11-003). (3) Do an inspection of the component interface and/or the adjacent area. (4) Put the new O-ring (4) in the correct position on the antenna (6). (5) FOR 7SG1 Install the foam washer (5). (6) Align the new gasket (3) on the fuselage with the screw holes. (7) Remove the blanking caps from the coaxial connectors (1) and (9).

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(8) Make sure that the electrical connectors are clean end in the correct condition. (9) Remove the masking tape from the coaxial cables and connect each connector (1) to the related connector (9) (see color code). NOTE : You must connect the connector J1 (YELLOW) to the front. ____ (10) Safety the coaxial connectors (1) and (9) with corrosion-resistant steel lockwire 0.4 mm (0.016 in.) dia.. (11) Install the antenna (6) on the fuselage structure (2) with the screws (7) and the washers (8) and then tighten: - TORQUE the screws to between 0.27 and 0.37 m.daN (23.89 and 32.74 lbf.in) (12) Make sure that the bonding contact resistance between the antenna (6) and the fuselage structure (2) is not higher than 5 milliohms (Ref. TASK 20-28-00-912-005). (13) Install the MISCELLANEOUS (Material No. 19-002) (10) on the screw heads with the SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008D). This is necessary for the subsequent removal of the antenna. (see detail on section B-B). (14) Put a bead of SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008D) around the antenna (6). (15) Let the sealant become dry. (16) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the antenna and the screw heads. (17) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001B) to the sealant of the head of the screws (7). NOTE : It is not mandatory to paint the sealant around the base of ____ the antenna and on the head of the screws.

  R EFF : 001-049, 101-105, 151-199, 501-509,  34-43-11 Page 413 511-526, 528-599,  Config-1 Feb 01/10  CES

 

R

**ON A/C 051-099, 251-299, Subtask 34-43-11-420-050-B A. Installation of the TCAS Antenna (Ref. Fig. 401A/TASK 34-43-11-991-001-B) WARNING : OBEY THE COLOR CODES WHEN YOU CONNECT THE ELECTRICAL CONNECTORS _______ (THIS WILL PREVENT CROSS-CONNECTIONS). MAKE SURE THAT YOU INSTALL THE ANTENNA IN THE CORRECT DIRECTION. IF THE ANTENNA DOES NOT POINT IN THE CORRECT DIRECTION, THE TCAS WILL ONLY SENSE TRAFFIC BEHIND THE AIRCRAFT. (1) Remove the used sealant from the fuselage structure (1) with a nonmetallic scraper. (2) Clean the component interface and/or the adjacent area with CLEANING AGENTS (Material No. 11-004) and a lint-free cloth. NOTE : If you install the same antenna it is necessary to clean it ____ with CLEANING AGENTS (Material No. 11-003). (3) Do an inspection of the component interface and/or the adjacent area. (4) Put the new O-ring (4) in the correct position on the antenna (6). (5) FOR 7SG1 Install the foam washer (5). (6) Align the new gasket (3) with the screw holes. (7) Remove the blanking caps from the coaxial connectors (2) and (9). (8) Make sure that the electrical connectors are clean and in the correct condition. (9) Remove the masking tape from the coaxial cables and connect each connector (2) to the related connector (9) (see color code). NOTE : You must connect the connector J3 (BLUE) forward. ____ (10) Safety the coaxial connectors (2) and (9) with corrosion-resistantsteel lockwire 0.4 mm (0.016 in.) dia..

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(11) Install the antenna (6) on the fuselage structure (1) with the screws (8) and the washers (7) and then tighten: - TORQUE the screws to between 0.22 and 0.28 m.daN (19.46 and 24.77 lbf.in) (12) Make sure that the bonding contact resistance between the antenna (6) and the fuselage structure (1) is not higher than 5 milliohms (Ref. TASK 20-28-00-912-005). (13) Install the MISCELLANEOUS (Material No. 19-002) on the screw heads with the SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09008D). This is necessary for the subsequent removal of the antenna. (14) Put a bead of SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008D) around the antenna (6). (15) Let the sealant become dry. (16) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the antenna and the screw heads. (17) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001B) to the sealant of the head of the screws (8). NOTE : It is not mandatory to paint the sealant around the base of ____ the antenna and on the head of the screws. **ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-43-11-420-050-A A. Installation of the TCAS Antenna (Ref. Fig. 401B/TASK 34-43-11-991-001-A) WARNING : OBEY THE COLOR CODES WHEN YOU CONNECT THE ELECTRICAL CONNECTORS _______ (THIS WILL PREVENT CROSS-CONNECTIONS). MAKE SURE THAT YOU INSTALL THE ANTENNA IN THE CORRECT DIRECTION. IF THE ANTENNA DOES NOT POINT IN THE CORRECT DIRECTION, THE TCAS WILL ONLY SENSE TRAFFIC BEHIND THE AIRCRAFT. (1) Remove the used sealant from the fuselage structure (1) with a nonmetallic scraper.

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(2) Clean the component interface and/or the adjacent area with CLEANING AGENTS (Material No. 11-004) and a lint-free cloth. NOTE : If you install the same antenna it is necessary to clean it ____ with CLEANING AGENTS (Material No. 11-003). (3) Do an inspection of the component interface and/or the adjacent area. (4) Put the new O-ring (4) in the correct position on the antenna (6). NOTE : If the O-ring has a flat face, make sure that this face is ____ against the antenna and not against the a/c surface. (5) FOR 7SG1 Install the foam washer (5). (6) Align the new gasket (3) with the screw holes. (7) Remove the blanking caps from the coaxial connectors (2) and (7). (8) Make sure that the electrical connectors are clean and in the correct condition. (9) Remove the masking tape from the coaxial cables and connect each connector (2) to the related connector (7) (see color code). (10) Safety the coaxial connectors (2) and (7) with corrosion-resistantsteel lockwire 0.4 mm (0.016 in.) dia.. (11) Install the antenna (6) (9) and the washers (8) - TORQUE the four outer and 29.20 lbf.in) - TORQUE the four inner and 14.15 lbf.in)

on the fuselage structure (1) with the screws and then tighten: screws to between 0.23 and 0.33 m.daN (20.35 screws to between 0.12 and 0.16 m.daN (10.61

(12) Make sure that the bonding contact resistance between the antenna (6) and the fuselage structure (1) is not higher than 5 milliohms (Ref. TASK 20-28-00-912-005). (13) Install the MISCELLANEOUS (Material No. 19-002) (10) on the screw heads with the SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008D). This is necessary for the subsequent removal of the antenna. (see detail on section B-B). (14) Put a bead of SEALANTS (Material No. 09-016) or SEALANTS (Material No. 09-008D) around the antenna (6).

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(15) Let the sealant become dry. (16) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the antenna and the screw heads. (17) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001B) to the sealant of the head of the screws (9). NOTE : It is not mandatory to paint the sealant around the base of ____ the antenna and on the head of the screws. R

**ON A/C ALL Subtask 34-43-11-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 4SG Subtask 34-43-11-740-050 C. Do the BITE test of the TCAS (Ref. TASK 34-43-00-740-001) 5. Close-up ________ Subtask 34-43-11-410-050 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) For 7SG1 only. Remove the access platform(s).

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COMPUTER - TCAS (1SG) - REMOVAL/INSTALLATION ____________________________________________ TASK 34-43-34-000-001 Removal of the TCAS Computer (1SG) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-43-34-991-001

Fig. 401

3. __________ Job Set-up Subtask 34-43-34-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/TCAS 4SG K10

  R EFF : ALL  34-43-34 Page 401   Config-1 Nov 01/09  CES

 

Subtask 34-43-34-010-050 B. Get Access (1) Put the access platform in position at the access door 824 in zone 128 (2) Open the access door 824. 4. Procedure _________ Subtask 34-43-34-020-050 A. Removal of the TCAS Computer (Ref. Fig. 401/TASK 34-43-34-991-001) (1) Loosen the nuts (4). (2) Lower the nuts (4). (3) Pull the TCAS computer (1) on its rack (3) to disconnect the electrical connectors (2). (4) Remove the TCAS computer (1) from its rack (3). (5) Put blanking caps on the disconnected electrical connectors (2).

  R EFF : ALL  34-43-34 Page 402   Config-1 Nov 01/09  CES

 

TCAS Computer Figure 401/TASK 34-43-34-991-001   R EFF : ALL  34-43-34 Page 403   Config-1 Nov 01/09  CES

 

TASK 34-43-34-400-001 Installation of the TCAS Computer (1SG) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-43-00-740-001 52-41-00-410-002 34-43-34-991-001

BITE Test of the TCAS Close the Avionics Compartment Doors after Access Fig. 401

3. __________ Job Set-up Subtask 34-43-34-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at the access door 824 in zone 128. (2) Make sure that the access door 824 is open.

  R EFF : ALL  34-43-34 Page 404   Config-1 Nov 01/09  CES

 

Subtask 34-43-34-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU COM NAV/TCAS 4SG K10 4. Procedure _________ Subtask 34-43-34-420-050 A. Installation of the TCAS Computer (Ref. Fig. 401/TASK 34-43-34-991-001) (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (2). (4) Make sure that the electrical connectors are clean and in the correct condition. (5) Install the TCAS computer (1) on its rack (3) to connect the electrical connectors (2). (6) Engage the nuts (4) on the lugs (5) and tighten. Subtask 34-43-34-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 4SG Subtask 34-43-34-740-050 C. Do the BITE test of the TCAS (Ref. TASK 34-43-00-740-001).

  R EFF : ALL  34-43-34 Page 405   Config-1 Nov 01/09  CES

 

5. Close-up ________ Subtask 34-43-34-860-051 A. Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tool(s) and other items. Subtask 34-43-34-410-050 B. Close Access (1) Close the access door 824 (Ref. TASK 52-41-00-410-002). (2) Remove the access platform(s).

  R EFF : ALL  34-43-34 Page 406   Config-1 Nov 01/09  CES

 

R

**ON A/C ALL Post SB

34-1278 For A/C 001-049,051-060,101-104,

ENHANCED GROUND PROXIMITY WARNING SYSTEM (GPWS) - DESCRIPTION AND OPERATION ___________________________________________________________________________ 1. General _______ **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, (Ref. Fig. 001) The purpose of the Enhanced Ground Proximity Warning System (Enhanced GPWS) is to alert the flight crew of potentially hazardous conditions with respect to the terrain. The system achieves this objective by accepting a variety of aircraft parameters as inputs, applying alerting algorithms, and providing the flight crew with aural alert messages and visual annunciations and displays in the event that the boundaries of any alerting envelope are exceeded. Enhanced features have been added to existing basic Ground Proximity Warning Modes 1 to 5 which are the backbone of the system. R

**ON A/C ALL Post SB Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

The purpose of the Enhanced Ground Proximity Warning System (Enhanced GPWS) is to alert the flight crew of potentially hazardous conditions with respect to the terrain. The system achieves this objective by accepting a variety of aircraft parameters as inputs, applying alerting algorithms, and providing the flight crew with aural alert messages and visual annunciations and displays in the event that the boundaries of any alerting envelope are exceeded. The Enhanced GPWC, will be able to use preferably GPS position when available on board and to activate peaks and/or obstacle functions with EFIS/EIS1/EIS2 display. Two architectures will be available to receive GPS data. The first one using the ADIRS connection as GPS data are transmitted via the IRS bus, and the second one will be a direct connection between Enhanced GPWS and GPS sensor (MMR or GPSSU) if ADIRS is not able to transmit GPS data. NOTE : Enhanced GPWS will then use preferably GPS and corrected IRS latitude ____ and longitude data as valid position source, if these position are downgraded, then FMS position will be used.

  R EFF : ALL  34-48-00 Page 1   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Enhanced Ground Proximity Warning System Figure 001   R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page 2 201-233, 236-238, 301-304, 401-403,  Config-1 Feb 01/08  CES

 

Enhanced features have been added to existing basic Ground Proximity Warning Modes 1 to 5 which are the backbone of the system. The primary design objective has been to maintain the integrity of these modes independent of the other functions. For example, loss of the Terrain Awareness Display (TAD) function does not affect the operation of the basic GPWS modes. Also, loss of basic GPWS modes does not affect TAD function. The following illustration provides an overall system block diagram. (Ref. Fig. 001A) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, Several main alerting functional areas are integrated into the Enhanced GPWC, which is a single Line Replaceable Unit (LRU). Except for basic GPWS, each function is pin selectable. The functional areas are: - basic Ground Proximity Warning System (GPWS) (Modes 1 to 5), - Terrain Clearance Floor function (TCF), - Terrain Awareness and Display (TAD) function. R

**ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

Several main alerting functional areas are integrated into the Enhanced GPWC, which is a single Line Replaceable Unit (LRU). Except for basic GPWS, each function is pin selectable. The functional areas are: - basic Ground Proximity Warning System (GPWS) (Modes 1 to 5), - Terrain Clearance Floor function (TCF), - Terrain Awareness and Display (TAD) function. - peaks function, - obstacle function. R

**ON A/C ALL A. Basic GPWS Modes The basic GPWS modes generate aural and visual warnings if the aircraft adopts a potentially hazardous condition with respect to: Mode 1 - Excessive rate of descent. Mode 2 - Excessive closure rate with terrain. Mode 3 - Descent after takeoff and minimum terrain clearance. Mode 4 - Unsafe terrain clearance. Mode 5 - Descent below glide slope.

  R EFF : ALL  34-48-00 Page 3   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Enhanced Ground Proximity Warning System Figure 001A   R EFF : ALL  34-48-00 Page 4   Config-1 Nov 01/09  CES

 

B. Enhanced Features The Enhanced GPWC includes enhanced features which complete the basic GPWS modes. (1) Terrain Clearance Floor (TCF) function The Terrain Clearance Floor (TCF) function adds an additional element of protection to the basic GPWS modes. It creates an increasing terrain clearance envelope around the intended airport runway directly related to the distance from the runway. TCF alerts are based on current aircraft location, nearest runway center point position and radio altitude. TCF is active during takeoff, cruise and final approach. This alert mode complements existing Mode 4 protection by providing an alert based on insufficient terrain clearance even when in landing configuration. TCF function generates aural and visual alert. (2) Terrain Awareness alerting and Display (TAD) function A major new feature of the Enhanced GPWS is the incorporation of the terrain awareness alerting and display functions. These functions use aircraft geographic position, aircraft altitude and a terrain data base to predict potential conflicts between the aircraft flight path and the terrain, and to provide graphic displays of the conflicting terrain, as illustrated by the block diagram. (Ref. Fig. 002) The terrain awareness alerting algorithms continuously compute terrain clearance envelopes ahead of the aircraft. If the boundaries of these envelopes conflict with terrain elevation data in the terrain database, then alerts are issued. R

**ON A/C ALL Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

(3) Geometric altitude The geometric altitude is a computed aircraft altitude designed to help ensure optimal operation of the EGPWS TAD function through all phases of flight and atmospheric conditions. Geometric altitude uses an improved pressure altitude calculation, GPS altitude, radio altitude, and terrain and runway elevation data to reduce or eliminate errors potentially induced in corrected barometric altitude by temperature extremes, non standard altitude conditions and, altimeters miss-sets.

  R EFF : ALL  34-48-00 Page 5   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Terrain Awareness Functions Figure 002   R EFF : ALL  34-48-00 Page 6   Config-1 Nov 01/09  CES

 

(4) GPS position When available on board, EGPWS will use preferably GPS, then IRS latitude and longitude data as valid position source and, if these positions are downgraded, then FMS position will be used. When EGPWS is pin programmed to use GPS position, then geometric altitude is also activated. **ON A/C 106-149, 220-233, 301-304, 401-403, Post SB

34-1287 For A/C 220-228,301-302,

(3) Geometric altitude The geometric altitude is a computed aircraft altitude designed to help ensure optimal operation of the EGPWS TAD function through all phases of flight and atmospheric conditions. Geometric altitude uses an improved pressure altitude calculation, GPS altitude, radio altitude, and terrain and runway elevation data to reduce or eliminate errors potentially induced in corrected barometric altitude by temperature extremes, non standard altitude conditions and, altimeters miss-sets. R

**ON A/C ALL 2. __________________ Component Location **ON A/C 105-105, (Ref. Fig. 003, 004) ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1WZ GPWC 88VU 128 824 34-48-34 4WZ P/BSW-GPWS/G/S 500VU 212 831 34-48-00 5WZ P/BSW-GPWS/G/S 301VU 211 831 34-48-00 7WZ P/BSW-GPWS/FLAP MODE 21VU 211 831 34-48-00 9WZ P/BSW-GPWS/SYS 21VU 211 831 34-48-00 11WZ P/BSW-GPWS/G/S MODE 21VU 211 831 34-48-00 13WZ P/BSW-GPWS/LDG FLAP 3 21VU 211 831 34-48-00 30WZ1 P/BSW-TERR ON ND,CAPT 403VU 211 831 34-48-00 30WZ2 P/BSW-TERR ON ND,F/O 402VU 212 831 34-48-00 31WZ P/BSW-GPWS/TERR 21VU 211 831 34-48-00 32WZ RELAY-TERRAIN/WEATHER RADAR 1 DATA 187VU 127 824 34-48-00 SWITCHING, F/O

  R EFF : ALL  34-48-00 Page 7   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Component Location 1/2 Figure 003   EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page 8 201-214,  Config-1 May 01/09 R  CES

 

Enhanced GPWS - Component Location 1/2 Figure 003A   R EFF : ALL  34-48-00 Page 9   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Component Location 2/2 Figure 004   R EFF : 105-105,  34-48-00 Page 10   Config-1 May 01/09  CES

 

------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------33WZ RELAY-TERRAIN/WEATHER RADAR 1 DATA 187VU 127 824 34-48-00 SWITCHING, CAPT **ON A/C 001-049, 051-099, 101-104, 151-199, 201-214, (Ref. Fig. 003) **ON A/C 001-049, 051-060, 101-104, (Ref. Fig. 003A) **ON A/C 001-049, 051-099, 101-104, 151-199, 201-214, (Ref. Fig. 004A) ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1WZ GPWC 88VU 128 824 34-48-34 4WZ P/BSW-GPWS/G/S 500VU 212 831 34-48-00 5WZ P/BSW-GPWS/G/S 301VU 211 831 34-48-00 7WZ P/BSW-GPWS/FLAP MODE 21VU 211 831 34-48-00 9WZ P/BSW-GPWS/SYS 21VU 211 831 34-48-00 11WZ P/BSW-GPWS/G/S MODE 21VU 211 831 34-48-00 13WZ P/BSW-GPWS/LDG FLAP 3 21VU 211 831 34-48-00 30WZ1 P/BSW-TERR ON ND,CAPT 403VU 211 831 34-48-00 30WZ2 P/BSW-TERR ON ND,F/O 402VU 212 831 34-48-00 31WZ P/BSW-GPWS/TERR 21VU 211 831 34-48-00 32WZ RELAY-TERRAIN/WEATHER RADAR 1 DATA 187VU 127 824 34-48-00 SWITCHING, F/O 33WZ RELAY-TERRAIN/WEATHER RADAR 1 DATA 187VU 127 824 34-48-00 SWITCHING, CAPT 34WZ RELAY-WEATHER RADAR 2 DATA CUTOFF, 188VU 128 824 34-48-00 F/O 35WZ RELAY-WEATHER RADAR 2 DATA CUTOFF, 188VU 128 824 34-48-00 CAPT

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page 11 201-214,  Config-1 May 01/09  CES

 

Enhanced GPWS - Component Location 2/2 Figure 004A   R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page 12 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

R R

**ON A/C 001-049, 051-099, 101-104, 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, **ON A/C 001-049, 051-060, 101-104, (Ref. Fig. 003)

R R

**ON A/C 001-049, 051-099, 101-104, 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 003A)

R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 004A)

R R

**ON A/C 001-049, 051-099, 101-104, 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1WZ GPWC 88VU 128 824 34-48-34 4WZ P/BSW-PULL UP/GPWS 500VU 212 831 34-48-00 5WZ P/BSW-PULL UP/GPWS 301VU 211 831 34-48-00 7WZ P/BSW-GPWS/FLAP MODE 21VU 211 831 34-48-00 9WZ P/BSW-GPWS/SYS 21VU 211 831 34-48-00 11WZ P/BSW-GPWS/G/S MODE 21VU 211 831 34-48-00 13WZ P/BSW-GPWS/LDG FLAP 3 21VU 211 831 34-48-00 30WZ1 P/BSW-TERR ON ND,CAPT 403VU 211 831 34-48-00 30WZ2 P/BSW-TERR ON ND,F/O 402VU 212 831 34-48-00 31WZ P/BSW-GPWS/TERR 21VU 211 831 34-48-00 32WZ RELAY-TERRAIN/WEATHER RADAR 1 DATA 187VU 127 824 34-48-00 SWITCHING, F/O 33WZ RELAY-TERRAIN/WEATHER RADAR 1 DATA 187VU 127 824 34-48-00 SWITCHING, CAPT 34WZ RELAY-WEATHER RADAR 2 DATA CUTOFF, 188VU 128 824 34-48-00 F/O 35WZ RELAY-WEATHER RADAR 2 DATA CUTOFF, 188VU 128 824 34-48-00 CAPT

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page 13 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

**ON A/C 105-105, (Ref. Fig. 003A) ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1WZ GPWC 88VU 128 824 34-48-34 4WZ P/BSW-PULL UP/GPWS 500VU 212 831 34-48-00 5WZ P/BSW-PULL UP/GPWS 301VU 211 831 34-48-00 7WZ P/BSW-GPWS/FLAP MODE 21VU 211 831 34-48-00 9WZ P/BSW-GPWS/SYS 21VU 211 831 34-48-00 11WZ P/BSW-GPWS/G/S MODE 21VU 211 831 34-48-00 13WZ P/BSW-GPWS/LDG FLAP 3 21VU 211 831 34-48-00 30WZ1 P/BSW-TERR ON ND,CAPT 403VU 211 831 34-48-00 30WZ2 P/BSW-TERR ON ND,F/O 402VU 212 831 34-48-00 31WZ P/BSW-GPWS/TERR 21VU 211 831 34-48-00 32WZ RELAY-TERRAIN/WEATHER RADAR 1 DATA 187VU 127 824 34-48-00 SWITCHING, F/O 33WZ RELAY-TERRAIN/WEATHER RADAR 1 DATA 187VU 127 824 34-48-00 SWITCHING, CAPT R

**ON A/C ALL 3. __________________ System Description A. General The Enhanced GPWS monitors data inputs from the navigation sensors. This information is used to provide suitable aural and visual warnings to alert the crew of a hazardous situation with respect to the terrain. B. Warnings Warnings are generated by the Enhanced GPWC which is installed on the shelf 88VU, in the aft electronics rack 80VU. Aural warnings are broadcast from the cockpit loud speakers. **ON A/C 105-105, C. Digital Data Inputs (Ref. Fig. 005) The Enhanced GPWC receives serial digital data inputs from: - radio altimeter transceiver 1 (radio altitude), - Air Data/Inertial Reference Unit 1 (ADIRU),

  R EFF : ALL  34-48-00 Page 14   Config-1 Nov 01/09  CES

 

Enhanced GPWC - Inputs and Outputs (Buses) Figure 005   R EFF : 105-105,  34-48-00 Page 15   Config-1 May 01/09  CES

 

- ADR portion (barometric altitude, barometric altitude rate, computed airspeed), - IR portion (latitude, longitude, magnetic heading), - Multi-Mode Receiver 1 (MMR) (glide slope deviation, localizer deviation, selected runway heading), - Flight Management and Guidance Computer (FMGC) (latitude, longitude, track, navigation modes), - Centralized Fault Display Interface Unit (CFDIU) (command word, date, flight number, UTC), - Flight Control Unit (FCU) 1 and 2 (CAPT and F/O ranges), - Weather Radar 1 (hazard bus). **ON A/C 001-049, 051-099, 101-104, 151-199, 201-228, 236-238, 301-302, Post SB

34-1147 For A/C 001-004,051-060,

C. Digital Data Inputs (Ref. Fig. 005B) The Enhanced GPWC receives serial digital data inputs from: - radio altimeter transceiver 1 (radio altitude), - Air Data/Inertial Reference Unit 1 (ADIRU), * ADR portion (barometric altitude, barometric altitude rate, computed airspeed), * IR portion (latitude, longitude, magnetic heading), - Multi-Mode Receiver 1 (MMR) (glide slope deviation, localizer deviation, selected runway heading), - Flight Management and Guidance Computer (FMGC) (latitude, longitude, track, navigation modes), - Centralized Fault Display Interface Unit (CFDIU) (command word, date, flight number, UTC), - Flight Control Unit (FCU) 1 and 2 (CAPT and F/O ranges), - Weather Radar 1 and 2 (hazard busses).

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page 16 201-228, 236-238, 301-302,  Config-1 May 01/09  CES

 

Enhanced GPWC - Inputs and Outputs (Buses) Figure 005A   R EFF : 501-509, 511-526, 528-599,  34-48-00 Page 17   Config-1 Feb 01/10  CES

 

Enhanced GPWC - Inputs and Outputs (Buses) Figure 005B   R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page 18 151-199, 201-233, 236-238, 301-304, 401-403,  Config-1 May 01/09  CES

 

R R

**ON A/C 301-399, Post SB Post SB Post SB Post SB

001-049, 051-099, 101-104, 106-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, 34-1147 For A/C 001-004,051-060, 34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-104,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-104,106-149,151-199,201-233, 236-238,301-304,401-403,

C. Digital Data Inputs R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 005A) **ON A/C 239-249, Post SB Post SB Post SB

001-049, 061-099, 101-104, 106-149, 151-199, 201-219, 229-235, 251-299, 303-399, 401-499, 34-1147 For A/C 001-004, 34-1351 For A/C 001-049,061-099,101-104,151-199,201-219, 34-1352 For A/C 001-049,061-099,101-104,106-149,151-199,201-219, 229-233,303-304,401-403,

(Ref. Fig. 005C) **ON A/C 051-060, 220-228, 236-238, 301-302, Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 051-060,220-228,236-238,301-302, 34-1352 For A/C 051-060,220-228,236-238,301-302,

(Ref. Fig. 005D) R R

**ON A/C 301-399, Post SB Post SB Post SB Post SB

001-049, 051-099, 101-104, 106-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, 34-1147 For A/C 001-004,051-060, 34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-104,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-104,106-149,151-199,201-233, 236-238,301-304,401-403,

The Enhanced GPWC receives serial digital data inputs from: - radio altimeter transceiver 1 (radio altitude), - Air Data/Inertial Reference Unit 1 (ADIRU), * ADR portion (SAT, barometric altitude, barometric altitude rate, computed airspeed),

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page 19 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

Enhanced GPWC - Inputs and Outputs (Buses) Figure 005C   R EFF : 001-049, 061-099, 101-104, 106-149,  34-48-00 Page 20 151-199, 201-219, 229-235, 239-249, 251-299,  Config-1 Nov 01/09 303-399, 401-499, CES

 

Enhanced GPWC - Inputs and Outputs (Buses) Figure 005D   R EFF : 051-060, 220-228, 236-238, 301-302,  34-48-00 Page 21   Config-1 May 01/09  CES

 

-

* IR portion (latitude, longitude, magnetic heading, GPS parameters if ADIRU is in hybrid configuration), Multi-Mode Receiver 1 (MMR) (glide slope deviation, localizer deviation, selected runway heading and GPS parameters if ADIRU is in autonomous configuration), Flight Management and Guidance Computer (FMGC) (latitude, longitude, track, navigation modes), Centralized Fault Display Interface Unit (CFDIU) (command word, date, flight number, UTC), Flight Control Unit (FCU) 1 and 2 (CAPT and F/O ranges), Weather Radar 1 and 2 (hazard busses).

**ON A/C 105-105, Post SB Post SB

34-1351 For A/C 105-105, 34-1352 For A/C 105-105,

C. Digital Data Inputs (Ref. Fig. 005E) The Enhanced GPWC receives serial digital data inputs from: - radio altimeter transceiver 1 (radio altitude), - Air Data/Inertial Reference Unit 1 (ADIRU), * ADR portion (SAT, barometric altitude, barometric altitude rate, computed airspeed), * IR portion (latitude, longitude, magnetic heading, GPS parameters if ADIRU is in hybrid configuration), - Multi-Mode Receiver 1 (MMR) (glide slope deviation, localizer deviation, selected runway heading and GPS parameters if ADIRU is in autonomous configuration), - Flight Management and Guidance Computer (FMGC) (latitude, longitude, track, navigation modes), - Centralized Fault Display Interface Unit (CFDIU) (command word, date, flight number, UTC), - Flight Control Unit (FCU) 1 and 2 (CAPT and F/O ranges), - Weather Radar 1 (hazard bus). **ON A/C 106-149, 220-233, 301-304, 401-403, Post SB

34-1287 For A/C 220-228,301-302,

C. Digital Data Inputs **ON A/C 106-149, 229-233, 303-304, 401-403, (Ref. Fig. 005B)

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page 22 201-249, 251-299, 301-399, 401-499, 501-509,  Config-1 Feb 01/10 511-526, 528-599, CES

 

Enhanced GPWC - Inputs and Outputs (Buses) Figure 005E

R

  R EFF : 105-105,  34-48-00 Page 23   Config-1 Feb 01/08  CES

 

**ON A/C 106-149, 220-233, 301-304, 401-403, Post SB

34-1287 For A/C 220-228,301-302,

The Enhanced GPWC receives serial digital data inputs from: - radio altimeter transceiver 1 (radio altitude), - Air Data/Inertial Reference Unit 1 (ADIRU), * ADR portion (SAT, barometric altitude, barometric altitude rate, computed airspeed), * IR portion (latitude, longitude, magnetic heading, GPS parameters), - Multi-Mode Receiver 1 (MMR) (glide slope deviation, localizer deviation, selected runway heading), - Flight Management and Guidance Computer (FMGC) (latitude, longitude, track, navigation modes), - Centralized Fault Display Interface Unit (CFDIU) (command word, date, flight number, UTC), - Flight Control Unit (FCU) 1 and 2 (CAPT and F/O ranges), - Weather Radar 1 and 2 (hazard busses). **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, D. Discrete Data Inputs (Ref. Fig. 006A) **ON A/C 001-049, 051-060, 101-104, Post SB

34-1352 For A/C 001-049,051-060,101-104,

(Ref. Fig. 006B) **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, Discrete data inputs are received from the following: - Slat Flap Control Computer 1 (SFCC) (3 and FULL flap position), - Flight Warning Computer 1 and 2 (FWC) (all audio inhibition), - Landing Gear Control and Interface Unit (LGCIU) (main landing gear retracted or extended), - ECAM control panel (audio suppression), - GPWS/FLAP MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides a flap abnormal condition input, - GPWS/SYS pushbutton switch which, when pressed (in) (white OFF legend on), inhibits Modes 1 to 5 warnings, - GPWS/G/S MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides the glide slope mode,

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page 24 201-214, 220-233, 301-304, 401-403,  Config-1 May 01/09  CES

 

Enhanced GPWC - Inputs (Discretes) Figure 006   R EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00 Page 25 401-403,  Config-1 May 01/09  CES

 

Enhanced GPWC - Inputs (Discretes) Figure 006A   R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page 26 201-214,  Config-1 May 01/09  CES

 

Enhanced GPWC - Inputs (Discretes) Figure 006B   R EFF : ALL  34-48-00 Page 27   Config-1 Nov 01/09  CES

 

- GPWS/G/S pushbutton switch which, when pressed (in), enables the Enhanced GPWC to perform test, - GPWS/TERR pusbutton switch which, when pressed (in) (white OFF legend on), inhibits TAD and TCF functions, - TERR ON ND (CAPT or F/O) pushbutton switches allow the crew to select or deselect terrain display on NDs, - Weather Radar control unit, - Weather Radar with Predictive Windshear System (WR/PWS), inhibition of Enhanced GPWS aural and/or visual alerts each time there are PWS aural and/or visual alerts. **ON A/C 001-049, 101-105, D. Discrete Data Inputs **ON A/C 001-049, 101-104, (Ref. Fig. 006A) **ON A/C 001-049, 101-105, Post SB

34-1352 For A/C 001-049,101-105,

(Ref. Fig. 006B) **ON A/C 001-049, 101-105, Discrete data inputs are received from the following: - Slat Flap Control Computer 1 (SFCC) (3 and FULL flap position), - Flight Warning Computer 1 and 2 (FWC) (all audio inhibition), - Landing Gear Control and Interface Unit (LGCIU) (main landing gear retracted or extended), - ECAM control panel (audio suppression), - GPWS/FLAP MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides a flap abnormal condition input, - GPWS/SYS pushbutton switch which, when pressed (in) (white OFF legend on), inhibits Modes 1 to 5 warnings, - GPWS/G/S MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides the glide slope mode, - PULL UP/GPWS pushbutton switch which, when pressed (in), enables the Enhanced GPWC to perform test, - GPWS/TERR pusbutton switch which, when pressed (in) (white OFF legend on), inhibits TAD and TCF functions,

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page 28 201-214,  Config-1 May 01/09  CES

 

- TERR ON ND (CAPT or F/O) pushbutton switches allow the crew to select or deselect terrain display on NDs, - Weather Radar control unit, - Weather Radar with Predictive Windshear System (WR/PWS), inhibition of Enhanced GPWS aural and/or visual alerts each time there are PWS aural and/or visual alerts. R R

**ON A/C 051-099, 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, D. Discrete Data Inputs **ON A/C 106-149, 215-233, 236-238, 301-304, 401-403, (Ref. Fig. 006) **ON A/C 051-060, (Ref. Fig. 006A)

R R

**ON A/C 051-099, 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1352 For A/C 051-099,106-149,151-199,201-233,236-238,301-304, 401-403, (Ref. Fig. 006B)

R R

**ON A/C 051-099, 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Discrete data inputs are received from the following: - Slat Flap Control Computer 1 (SFCC) (3 and FULL flap position), - Flight Warning Computer 1 and 2 (FWC) (all audio inhibition), - Landing Gear Control and Interface Unit (LGCIU) (main landing gear retracted or extended), - ECAM control panel (audio suppression), - GPWS/FLAP MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides a flap abnormal condition input, - GPWS/SYS pushbutton switch which, when pressed (in) (white OFF legend on), inhibits Modes 1 to 5 warnings, - GPWS/G/S MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides the glide slope mode, - PULL UP/GPWS pushbutton switch which, when pressed (in), enables the Enhanced GPWC to perform test,

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page 29 201-249, 251-299, 301-399, 401-499, 501-509,  Config-1 Feb 01/10 511-526, 528-599, CES

 

- GPWS/TERR pusbutton switch which, when pressed (in) (white OFF legend on), inhibits TAD and TCF functions, - TERR ON ND (CAPT or F/O) pushbutton switches allow the crew to select or deselect terrain display on NDs, - Weather Radar control unit, - Weather Radar with Predictive Windshear System (WR/PWS), inhibition of Enhanced GPWS aural and/or visual alerts each time there are PWS aural and/or visual alerts. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, E. Warning Outputs **ON A/C 001-049, 051-099, 101-102, 201-202, 211-214, (Ref. Fig. 007) **ON A/C 001-049, 101-102, Post SB

34-1345 For A/C 001-049,101-102,

(Ref. Fig. 007A) **ON A/C 051-060, Post SB

34-1345 For A/C 051-060,

(Ref. Fig. 007B) **ON A/C 103-104, Post SB

34-1345 For A/C 103-104,

(Ref. Fig. 007C) **ON A/C 103-105, 151-199, 203-210, (Ref. Fig. 007D)

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page 30 201-249, 251-299, 301-399, 401-499, 501-509,  Config-1 Feb 01/10 511-526, 528-599, CES

 

Enhanced GPWC - Outputs Figure 007

R

  EFF : 001-049, 051-099, 101-102, 201-202,  34-48-00 Page 31 211-214,  Config-1 Feb 01/08  CES

 

Enhanced GPWC - Outputs Figure 007A   R EFF : 001-049, 101-102, 105-149, 151-199,  34-48-00 Page 32 201-202, 211-249, 251-299, 301-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

Enhanced GPWC - Outputs Figure 007B   R EFF : 051-099, 106-149, 215-233, 236-238,  34-48-00 Page 33 301-304, 401-403,  Config-1 May 01/09  CES

 

Enhanced GPWC - Outputs Figure 007C   R EFF : 103-104, 203-210,  34-48-00 Page 34   Config-1 May 01/09  CES

 

Enhanced GPWC - Outputs Figure 007D   R EFF : 103-105, 151-199, 203-210,  34-48-00 Page 35   Config-1 May 01/09  CES

 

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, - two discrete outputs from the Enhanced GPWC control the GPWS/G/S pushbutton switches located on Captain and First Officer main instrument panels. Each pushbutton switch is a momentary-action pushbutton switch with an illuminated split legend cap. The upper legend identified GPWS, controlled by the first output, comes on red when a ground proximity warning is generated by the Enhanced GPWC for Modes 1 to 4 or TAD and TCF warnings. The lower legend identified G/S, controlled by the second output, comes on amber when a glide slope (Mode 5) caution alert is generated by the Enhanced GPWC. The pushbutton switch provides a facility to cancel a glide slope warning, if in progress, or to initiate an Enhanced GPWS self-test. - both discrete outputs are also used to inhibit TCAS and automatic call out when the GPWS or G/S warnings are in progress. - both discrete outputs are also used for the Digital Flight Data Recorder (DFDR). ------------------------------------------------------------------------------NAME ELECTRICAL LEVEL TO SIGNAL STATUS ------------------------------------------------------------------------------FAULT LEGEND GND/OC SYS P/BSW/SDACs GND = VALID G/S VISUAL ALERT GND/OC FWCs GND = VALID GPWS LEGEND GND/OC FWCs GND = VALID ------------------------------------------------------------------------------R

**ON A/C 001-049, 061-099, 101-105, 151-199, 201-214, 251-299, E. Warning Outputs **ON A/C 001-049, 101-102, (Ref. Fig. 007)

R

**ON A/C 001-049, 101-102, 105-105, 151-199, 201-202, 211-214, 251-299, Post SB

34-1345 For A/C 001-049,101-102,105-105,151-199,201-202,211-214,

(Ref. Fig. 007A)

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page 36 201-214, 251-299,  Config-1 Nov 01/09  CES

 

**ON A/C 061-099, Post SB

34-1345 For A/C 061-099,

(Ref. Fig. 007B) **ON A/C 103-104, 203-210, Post SB

34-1345 For A/C 103-104,203-210,

(Ref. Fig. 007C) **ON A/C 103-104, (Ref. Fig. 007D) R

**ON A/C 001-049, 061-099, 101-105, 151-199, 201-214, 251-299, - Two discrete outputs from the Enhanced GPWC control the PULL UP/GPWS pushbutton switches located on Captain and First Officer main instrument panels. Each pushbutton switch is a momentary-action pushbutton switch with an illuminated split legend cap. The upper legend identified PULL UP, controlled by the first output, comes on red when a ground proximity warning message including PULL UP is generated by the Enhanced GPWC. The lower legend identified GPWS, controlled by the second output, comes on amber for all the other alerts. The pushbutton switch provides a facility to cancel a glide slope warning. - Both discrete outputs are also used to inhibit TCAS and automatic call out when the PULL UP or GPWS warnings are in progress. - Both discrete outputs are also used for the Digital Flight Data Recorder (DFDR). ------------------------------------------------------------------------------NAME ELECTRICAL LEVEL TO SIGNAL STATUS ------------------------------------------------------------------------------FAULT LEGEND GND/OC SYS P/BSW/SDACs GND = VALID GPWS ALERT GND/OC FWCs GND = VALID GPWS LEGEND GND/OC FWCs GND = VALID -------------------------------------------------------------------------------

  R EFF : 001-049, 061-099, 101-105, 151-199,  34-48-00 Page 37 201-214, 251-299,  Config-1 Nov 01/09  CES

 

R R

**ON A/C 051-060, 106-149, 215-249, 301-399, 401-499, 501-509, 511-526, 528-599, E. Warning Outputs **ON A/C 051-060, (Ref. Fig. 007)

R

**ON A/C 106-149, 215-249, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB

34-1345 For A/C 106-149,215-233,236-238,301-304,401-403,

(Ref. Fig. 007A) **ON A/C 051-060, 106-149, 215-233, 236-238, 301-304, 401-403, Post SB

34-1345 For A/C 051-060,

(Ref. Fig. 007B) R R

**ON A/C 051-060, 106-149, 215-249, 301-399, 401-499, 501-509, 511-526, 528-599, - two discrete outputs from the Enhanced GPWC control the PULL UP/GPWS pushbutton switches located on Captain and First Officer main instrument panels. Each pushbutton switch is a momentary-action pushbutton switch with an illuminated split legend cap. The upper legend identified PULL UP, controlled by the first output, comes on red when a ground proximity warning message including PULL UP is generated by the Enhanced GPWC. The lower legend identified GPWS, controlled by the second output, comes on amber when a glide slope (Mode 5) caution alert is generated by the Enhanced GPWC. The pushbutton switch provides a facility to cancel a glide slope warning, if in progress, or to initiate an Enhanced GPWS self-test. - both discrete outputs are also used to inhibit TCAS and automatic call out when the PULL UP or GPWS warnings are in progress. - both discrete outputs are also used for the Digital Flight Data Recorder (DFDR).

  R EFF : 051-060, 106-149, 215-249, 301-399,  34-48-00 Page 38 401-499, 501-509, 511-526, 528-599,  Config-1 Feb 01/10  CES

 

------------------------------------------------------------------------------NAME ELECTRICAL LEVEL TO SIGNAL STATUS ------------------------------------------------------------------------------FAULT LEGEND GND/OC SYS P/BSW/SDACs GND = VALID GPWS ALERT GND/OC FWCs GND = VALID PULL UP LEGEND GND/OC FWCs GND = VALID ------------------------------------------------------------------------------**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, F. Monitor Outputs There are two monitor outputs: - GPWS monitor output controls the FAULT legend of the SYS pushbutton switch and indicates a failure of Modes 1 to 5, - TERR monitor output controls the FAULT legend of the TERR pushbutton switch and indicates a failure of TAD and TCF functions. ------------------------------------------------------------------------------NAME ELECTRICAL LEVEL TO SIGNAL STATUS ------------------------------------------------------------------------------GPWS MONITOR OUTPUT GND/OC BOARD-ANN LT GND=FAULT TEST and INTFC SDAC1 SDAC2 TERR MONITOR OUTPUT GND/OC BOARD-ANN LT GND=FAULT TEST and INTFC SDAC1 SDAC2 ------------------------------------------------------------------------------R

**ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

F. Monitor Outputs There are three monitor outputs: - GPWS monitor output controls the FAULT legend of the SYS pushbutton switch and indicates a failure of Modes 1 to 5, - TERR monitor output controls the FAULT legend of the TERR pushbutton switch and indicates a failure of TAD and TCF functions. - TERR NOT AVAIL output allows FWC to generate a TERR STBY ECAM memo. This output is triggered when EGPWS is valid but the TAD/TCF function cannot be temporarily computed.

  R EFF : ALL  34-48-00 Page 39   Config-1 Nov 01/09  CES

 

------------------------------------------------------------------------------NAME ELECTRICAL LEVEL TO SIGNAL STATUS ------------------------------------------------------------------------------GPWS MONITOR OUTPUT GND/OC BOARD-ANN LT GND=FAULT TEST and INTFC SDAC1 SDAC2 TERR MONITOR OUTPUT GND/OC BOARD-ANN LT GND=FAULT TEST and INTFC SDAC1 SDAC2 TERR NOT AVAIL MONITOR OUTPUT GND/OC SDAC1 GND=FAULT SDAC2 ------------------------------------------------------------------------------R

**ON A/C 501-509, 511-526, 528-599, G. Bus Output The bus output is used by the Aircraft Integrated Data System (AIDS), Data Management Unit (DMU), Weather Radar Auto-Tilt function and by the Centralized Fault Display Interface Unit (CFDIU) for test causes. **ON A/C 001-049, 051-099, 101-102, 106-149, 201-202, 211-249, 251-299, 301-399, 401-499, G. Bus Output The bus output is used by the Aircraft Integrated Data System (AIDS), Data Management Unit (DMU) and by the Centralized Fault Display Interface Unit (CFDIU) for test causes. **ON A/C 103-105, 151-199, 203-210, G. Bus Output The bus output is used by the Aircraft Integrated Data System (AIDS) and by the Centralized Fault Display Interface Unit (CFDIU) for test causes. **ON A/C ALL H. Audio Output The audio output is used by the cockpit loud speakers for aural warning messages. 4. ____________ Power Supply

  EFF : ALL  34-48-00 Page 40   Config-1 Feb 01/10  CES

 

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, **ON A/C 001-049, 051-099, 101-102, 201-202, 211-214, (Ref. Fig. 007) **ON A/C 106-149, 215-233, 236-238, 301-304, 401-403, (Ref. Fig. 007B) **ON A/C 103-105, 151-199, 203-210, (Ref. Fig. 007D) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, The Enhanced GPWC power supply circuits receive 115VAC, 400 Hz, single phase (22 W max.) supply from the aircraft AC power.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page 41 201-233, 236-238, 301-304, 401-403,  Config-1 May 01/09  CES

 

**ON A/C ALL Post SB R R

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

**ON A/C 001-049, 101-102, 106-149, 215-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,101-102,106-149,215-233,236-238,301-304, 401-403, (Ref. Fig. 007A) **ON A/C 051-060, Post SB

34-1345 For A/C 051-060,

(Ref. Fig. 007B) **ON A/C 103-104, Post SB

34-1345 For A/C 103-104,

(Ref. Fig. 007C) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

The Enhanced GPWC power supply circuits receive 115VAC, 400 Hz, single phase (22 W max.) and 28VDC supply from the aircraft AC power. |----------------------------------------------------------------------------| | Voltage | C/B FIN | Designation | |------------------|---------------------|-----------------------------------| | 28VDC | 2WZ | 101PP BUS 1 | | | | | | 115VAC | 3WZ | 103XP BUS1 | |----------------------------------------------------------------------------|

  EFF : ALL  34-48-00 Page 42   Config-1 Feb 01/10  CES

 

R

**ON A/C ALL 5. Interface _________ **ON A/C 105-105, A. Digital Outputs This table contains all the output parameters in digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI: output label for which the parameter is available, - PARAMETER DEFINITION: parameter name, - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy, - UNIT: unit in which the digital value is transmitted, - SIG BIT: indicates whether a sign bit is available, - BITS: number of bits used by the parameter in the label, - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds, - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code, - SOURCE ORIGIN: parameter source computer or system.

  R EFF : ALL  34-48-00 Page 43   Config-1 Nov 01/09  CES

 

INTENTIONALLY BLANK

  R   34-48-00 Page 44   Config-1 May 01/09  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 1.270.00 |ENH. GPWS |(1=voice on)| | | | 50 |DIS | | | | |ALER DSCRT| | | | | to | | | | | |WORD 1 | | | | |100 | | | | | | | | | | | | | | | | |SINKRATE- |bit status 1| | | 11 | | | | | | |PAUSE| | | | | | | | | | |SINKRATE | | | | | | | | | | | | | | | | | | | | | |PULL UP |bit status 1| | | 12 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 13 | | | | | | | | | | | | | | | | | |DONT SINK|bit status 1| | | 14 | | | | | | |-PAUSE| | | | | | | | | | |DONT SINK| | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | | 15 | | | | | | |GEAR | | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | | 16 | | | | | | |FLAPS | | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | | 17 | | | | | | |TERRAIN | | | | | | | | | | | | | | | | | | | | | |GLIDESLOPE|bit status 1| | | 18 | | | | | | | | | | | | | | | | | |NOT USED | | | | 19 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 20 | | | | | | |PULL UP | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 21 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 22 | | | | | | |AHEAD PULL| | | | | | | | | | |UP | | | | | | | | | | | | | | | | | | | |

  EFF : 105-105,  34-48-00 Page 45   Config-1 Nov 01/07 R  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |NOT USED | | | | 23 | | | | | | | | | | | | | | | | | |NOT USED | | | | 24 | | | | | | | | | | | | | | | | | |NOT USED | | | | 25 | | | | | | | | | | | | | | | | | |NOT USED | | | | 26 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 27 | | | | | | |AHEAD | | | | | | | | | | | | | | | | | | | | | |SPARE | | | | 28 | | | | | | | | | | | | | | | | | |Reserved | | | | 29 | | | | | | |for obsta.| | | | | | | | | | |voice | | | | | | | | | | 1.274.00 |ENH. GPWS |(1= on) | | | | 50 |DIS | | | | |ALER DSCRT| | | | | to | | | | | |WORD 2 | | | | |100 | | | | | | | | | | | | | | | | |G/S CANCEL|bit status 1| | | 11 | | | | | | | | | | | | | | | | | |GPWS ALERT|bit status 1| | | 12 | | | | | | | | | | | | | | | | | |GPWS |bit status 1| | | 13 | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |GPWS INOP |bit status 1| | | 14 | | | | | | | | | | | | | | | | | |WINDSHEAR |bit status 1| | | 15 | | | | | | |WARNING | | | | | | | | | | |(IF WR/PWS| | | | | | | | | | |INSTALLED)| | | | | | | | | | | | | | | | | | | | | |AUDIO ON |bit status 1| | | 16 | | | | | | | | | | | | | | | | | |NOT USED | | | | 17 | | | | | | | | | | | | | | | |

  EFF : 105-105,  34-48-00 Page 46   Config-1 Nov 01/07 R  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |NOT USED | | | | 18 | | | | | | | | | | | | | | | | | |NOT USED | | | | 19 | | | | | | | | | | | | | | | | | |NOT USED | | | | 20 | | | | | | | | | | | | | | | | | |NOT USED | | | | 21 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 22 | | | | | | |AWARENESS | | | | | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 23 | | | | | | |AWARENESS | | | | | | | | | | |CAUTION | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 24 | | | | | | |AWARENESS | | | | | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |EXTERNAL |bit status 1| | | 25 | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |COMPUTER |bit status 1| | | 26 | | | | | | |FAIL | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 27 | | | | | | |AWARENESS | | | | | | | | | | |NOT AVAIL.| | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 28 | | | | | | |DISPLAY | | | | | | | | | | |DSCRT 1 | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 29 | | | | | | |DISPLAY | | | | | | | | | | |DSCRT 2 | | | | | | | | | | | | | | | | | | | |

  EFF : 105-105,  34-48-00 Page 47   Config-1 Nov 01/07 R  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 1.271.00 |ENH. GPWS |(1= warn. | | | |100 |DIS | | | | |LOGIC DSCR|in progress)| | | | to | | | | | | | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | | 11 | | | | | | | | | | | | | | | | | |NOT USED | | | | 12 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 13 | | | | | | |CLEARANCE | | | | | | | | | | |FLOOR ALER| | | | | | | | | | | | | | | | | | | | | |ENV.MOD IN|bit status 1| | | 14 | | | | | | |PROGRESS | | | | | | | | | | | | | | | | | | | | | |ENV.MOD |bit status 1| | | 15 | | | | | | |SNAPSHOT | | | | | | | | | | |LATCH SET | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 16 | | | | | | | | | | | | | | | | | |NOT USED | | | | 17 | | | | | | | | | | | | | | | | | |TAKE OFF |bit status 1| | | 18 | | | | | | |MODE | | | | | | | | | | | | | | | | | | | | | |MODE 1 |bit status 1| | | 19 | | | | | | |SINKRATE | | | | | | | | | | | | | | | | | | | | | |MODE 1 |bit status 1| | | 20 | | | | | | |PULL UP | | | | | | | | | | | | | | | | | | | | | |MODE 2 |bit status 1| | | 21 | | | | | | |TERRAIN | | | | | | | | | | | | | | | | | | | | | |MODE 2 |bit status 1| | | 22 | | | | | | |PULL UP | | | | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |MODE 3 |bit status 1| | | 23 | | | | | | |VISUAL | | | | | | | | | | | | | | | | | | | | | |MODE 4 |bit status 1| | | 24 | | | | | | |VISUAL | | | | | | | | | | | | | | | | | | | | | |MODE 5 |bit status 1| | | 25 | | | | | | |VISUAL | | | | | | | | | | | | | | | | | | | | | |MODE 7 |bit status 1| | | 26 | | | | | | |VISUAL | | | | | | | | | | |ALERT | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 27 | | | | | | |AWARENESS | | | | | | | | | | |CAUTION | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 28 | | | | | | |AWARENESS | | | | | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 29 | | | | | | | | | | | | | | | | | 1.300.00 |ENH. GPWC | | | | | 50 |DIS | | | | |ALERT DSCR| | | | | to | | | | | |WORD3 | | | | |100 | | | | | | | | | | | | | | | | |MODES 1 TO| | | | 11 | | | | | | |4 INOP | | | | | | | | | | | | | | | | | | | | | |MODE 5 | | | | 12 | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 13 | | | | | | | | | | | | | | | | | |NOT USED | | | | 14 | | | | | | | | | | | | | | | | | |NOT USED | | | | 15 | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |TERR CLEA.| | | | 16 | | | | | | |FLOOR INOP| | | | | | | | | | | | | | | | | | | | | |TERR AWAR.| | | | 17 | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |ENV. MODU.| | | | 18 | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |SPARE | | | | 19 | | | | | | | | | | | | | | | | | |SPARE | | | | 20 | | | | | | | | | | | | | | | | | |SPARE | | | | 21 | | | | | | | | | | | | | | | | | |SPARE | | | | 22 | | | | | | | | | | | | | | | | | |SPARE | | | | 23 | | | | | | | | | | | | | | | | | |SPARE | | | | 24 | | | | | | | | | | | | | | | | | |SPARE | | | | 25 | | | | | | | | | | | | | | | | | |SPARE | | | | 26 | | | | | | | | | | | | | | | | | |SPARE | | | | 27 | | | | | | | | | | | | | | | | | |SPARE | | | | 28 | | | | | | | | | | | | | | | | | |SPARE | | | | 29 | | | | | | | | | | | | | | | | | 1.275.00 |PROGRAM |(1=Open | | | |100 |DIS | | | | |PIN STATUS|0=Ground) | | | | to | | | | | |WORD 1 | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | | 11 | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |CFDS |bit status 1| | | 12 | | | | | | |ENABLE | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 13 | | | | | | |SELECT 6 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 14 | | | | | | |SELECT 1 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 15 | | | | | | |SELECT 2 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 16 | | | | | | |SELECT 3 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 17 | | | | | | | | | | | | | | | | | |NOT USED | | | | 18 | | | | | | | | | | | | | | | | | |AUDIO |bit status 0| | | 19 | | | | | | |DECLUTTER | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 20 | | | | | | | | | | | | | | | | | |NOT USED | | | | 21 | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 22 | | | | | | |SELECT 7 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 23 | | | | | | | | | | | | | | | | | |NOT USED | | | | 24 | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 25 | | | | | | |SELECT 5 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 26 | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |AIRCRAFT | | | | 27 | | | | | | |SELECT 4 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 28 | | | | | | | | | | | | | | | | | |NOT USED | | | | 29 | | | | | | | | | | | | | | | | | 1.276.00 |PROGRAM |(1=Open | | | |100 |DIS | | | | |PIN STATUS|0=Ground) | | | | to | | | | | |WORD 2 | | | | |200 | | | | | | | | | | | | | | | | |VOICE | | | | 11 | | | | | | |SELECT 1 | | | | | | | | | | | | | | | | | | | | | |VOICE | | | | 12 | | | | | | |SELECT 2 | | | | | | | | | | | | | | | | | | | | | |VOICE | | | | 13 | | | | | | |SELECT 3 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 14 | | | | | | | | | | | | | | | | | |AUDIO |bit status 1| | | 15 | | | | | | |SUPPRESS | | | | | | | | | | | | | | | | | | | | | |ATERNATE |bit status 1| | | 16 | | | | | | |MODE 4 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 17 | | | | | | | | | | | | | | | | | |FMGC |bit status 1| | | 18 | | | | | | |SELECT | | | | | | | | | | | | | | | | | | | | | |ALTERN. |bit status 1| | | 19 | | | | | | |G/S CANCEL| | | | | | | | | | | | | | | | | | | | | |LAMP |bit status 1| | | 20 | | | | | | |FORMAT | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |QFE/QNH |bit status 1| | | 21 | | | | | | |SELECT |=QFE SELECT | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 22 | | | | | | | | | | | | | | | | | |NOT USED | | | | 23 | | | | | | | | | | | | | | | | | |G/S |bit status 1| | | 24 | | | | | | |INHIBIT | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 25 | | | | | | | | | | | | | | | | | |NOT USED | | | | 26 | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 27 | | | | | | |SELECT 8 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 28 | | | | | | |SELECT 9 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 29 | | | | | | | | | | | | | | | | | 1.277.00 |PROGRAM |(1=Open | | | |100 |DIS | | | | |PIN STATUS|0=Ground) | | | | to | | | | | |WORD 3 | | | | |200 | | | | | | | | | | | | | | | | |ALTER.VOL.|bit status 1| | | 11 | | | | | | |SELECTED | | | | | | | | | | | | | | | | | | | | | |SPARE | | | | 12 | | | | | | | | | | | | | | | | | |SPARE | | | | 13 | | | | | | | | | | | | | | | | | |NOT USED | | | | 14 | | | | | | | | | | | | | | | | | |NOT USED | | | | 15 | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |NOT USED | | | | 16 | | | | | | | | | | | | | | | | | |TCF |bit status 1| | | 17 | | | | | | |DISABLE | | | | | | | | | | | | | | | | | | | | | |TAD |bit status 1| | | 18 | | | | | | |DISABLE | | | | | | | | | | | | | | | | | | | | | |SPARE | | | | 19 | | | | | | | | | | | | | | | | | |SPARE | | | | 20 | | | | | | | | | | | | | | | | | |NOT USED | | | | 21 | | | | | | | | | | | | | | | | | |NOT USED | | | | 22 | | | | | | | | | | | | | | | | | |NOT USED | | | | 23 | | | | | | | | | | | | | | | | | |SPARE | | | | 24 | | | | | | | | | | | | | | | | | |SPARE | | | | 25 | | | | | | | | | | | | | | | | | |SPARE | | | | 26 | | | | | | | | | | | | | | | | | |NOT USED | | | | 27 | | | | | | | | | | | | | | | | | |NOT USED | | | | 28 | | | | | | | | | | | | | | | | | |NOT USED | | | | 29 | | | | | | | | | | | | | | | | | 1.350.00 |FAULT |(1=Failed)| | | |100 |DIS | | | | |DIAGNOSTIC| | | | | to | | | | | |WORD 1 | | | | |200 | | | | | | | | | | | | | | | | |ARINC 429 | | | | 11 | | | | | | |IR1 INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |ARINC 429 | | | | 12 | | | | | | |FMGC1 | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 13 | | | | | | |ADR1 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 14 | | | | | | |FCU BUS 1 | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 15 | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 16 | | | | | | |ILS1 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 17 | | | | | | |FMGC1(Nav | | | | | | | | | | |Modes) IN.| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 18 | | | | | | |RA1 INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 19 | | | | | | |FCU BUS 2 | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 20 | | | | | | |CFDIU | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |ARINC 429 | | | | 21 | | | | | | |WXR HZD | | | | | | | | | | |BUS1 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 22 | | | | | | | | | | | | | | | | | |NOT USED | | | | 23 | | | | | | | | | | | | | | | | | |NOT USED | | | | 24 | | | | | | | | | | | | | | | | | |NOT USED | | | | 25 | | | | | | | | | | | | | | | | | |NOT USED | | | | 26 | | | | | | | | | | | | | | | | | |PROGRAM | | | | 27 | | | | | | |PIN FAULT | | | | | | | | | | | | | | | | | | | | | |FLAP | | | | 28 | | | | | | |INPUT FAI.| | | | | | | | | | | | | | | | | | | | | |GEAR | | | | 29 | | | | | | |INPUT FAI.| | | | | | | | | | | | | | | | | | | | | 1.351.00 |FAULT |(1=Failed)| | | |100 |DIS | | | | |DIAGNOSTIC| | | | | to | | | | | |WORD 2 | | | | |200 | | | | | | | | | | | | | | | | |G/S CANCEL| | | | 11 | | | | | | |DSCR. FAI.| | | | | | | | | | | | | | | | | | | | | |MOMENTARY | | | | 12 | | | | | | |AUDIO SUPP| | | | | | | | | | |DSCR. FAI.| | | | | | | | | | | | | | | | | | | | | |AUDIO | | | | 13 | | | | | | |INHIBIT | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |DSCR. FAI.| | | | | | | | | | | | | | | | | | | | | |SELF-TEST | | | | 14 | | | | | | |DSCR INPUT| | | | | | | | | | |FAILED | | | | | | | | | | | | | | | | | | | | | |SUPPORT | | | | 15 | | | | | | |TASK FAULT| | | | | | | | | | | | | | | | | | | | | |NVM FAULT | | | | 16 | | | | | | | | | | | | | | | | | |WATCHDOG | | | | 17 | | | | | | |TIMER FAUL| | | | | | | | | | | | | | | | | | | | | |A/D FAIL | | | | 18 | | | | | | | | | | | | | | | | | |VOICE FAIL| | | | 19 | | | | | | | | | | | | | | | | | |DITS | | | | 20 | | | | | | |OUTPUT FAI| | | | | | | | | | | | | | | | | | | | | |TERRAIN | | | | 21 | | | | | | |DATABASE | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |FLASH FILE| | | | 22 | | | | | | |SYSTEM | | | | | | | | | | |WRITE | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |DITS INPUT| | | | 23 | | | | | | |FAIL | | | | | | | | | | | | | | | | | | | | | |VOICE | | | | 24 | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |SYSTEM OR | | | | 25 | | | | | | |MODE TASK | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |FAULT | | | | | | | | | | | | | | | | | | | | | |ENV. MOD. | | | | 26 | | | | | | |DATABASE | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |WATCHDOG | | | | 27 | | | | | | |FAIL COUNT| | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 28 | | | | | | |DATABASE | | | | | | | | | | |FAULT OR| | | | | | | | | | |CRC FAULT | | | | | | | | | | | | | | | | | | | | | |IMAGE DSP | | | | 29 | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | 1.355.00 |FAULT |(1=Failed)| | | |100 |DIS | | | | |DIAGNOSTIC| | | | | to | | | | | |WORD 3 | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | | 11 | | | | | | | | | | | | | | | | | |NOT USED | | | | 12 | | | | | | | | | | | | | | | | | |NOT USED | | | | 13 | | | | | | | | | | | | | | | | | |NOT USED | | | | 14 | | | | | | | | | | | | | | | | | |NOT USED | | | | 15 | | | | | | | | | | | | | | | | | |NOT USED | | | | 17 | | | | | | | | | | | | | | | | | |NOT USED | | | | 18 | | | | | | | | | | | | | | | | | |SPARE | | | | 19 | | | | | | | | | | | | | | | | | |SPARE | | | | 20 | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |SPARE | | | | 21 | | | | | | | | | | | | | | | | | |SPARE | | | | 22 | | | | | | | | | | | | | | | | | |SPARE | | | | 23 | | | | | | | | | | | | | | | | | |SPARE | | | | 24 | | | | | | | | | | | | | | | | | |SPARE | | | | 25 | | | | | | | | | | | | | | | | | |SPARE | | | | 26 | | | | | | | | | | | | | | | | | |SPARE | | | | 27 | | | | | | | | | | | | | | | | | |SPARE | | | | 28 | | | | | | | | | | | | | | | | | |SPARE | | | | 29 | | | | | | | | | | | | | | | | | 1.357.00 |INPUT | | | | |100 |DIS | | | | |DSCRT STAT| | | | | to | | | | | |WORD 1 | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | | 11 | | | | | | | | | | | | | | | | | |G/S |(1= | | | 12 | | | | | | |INHIBIT |inhibit) | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 13 | | | | | | | | | | | | | | | | | |NOT USED | | | | 14 | | | | | | | | | | | | | | | | | |GPWS MODES|(1= | | | 15 | | | | | | |1 TO 5 |inhibit) | | | | | | | | | |INHIBIT | | | | | | | | | | |(AUDIO AND| | | | | | | | | | |VISUAL) | | | | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |NOT USED | | | | 16 | | | | | | | | | | | | | | | | | |MOMENTARY |(1= | | | 17 | | | | | | |AUDIO SUPP|suppress) | | | | | | | | | | | | | | | | | | | | |SELF-TEST | | | | 18 | | | | | | | | | | | | | | | | | |LANDING |(1= down) | | | 19 | | | | | | |GEAR | | | | | | | | | | | | | | | | | | | | | |LANDING |(1= | | | 20 | | | | | | |FLAPS |extended) | | | | | | | | | | | | | | | | | | | | |G/S CANCEL|(1= | | | 21 | | | | | | | |cancelled) | | | | | | | | | | | | | | | | | | | | |WXR 1 |(1= ON) | | | 22 | | | | | | |ON/OFF | | | | | | | | | | | | | | | | | | | | | |TAD AND |(1= | | | 23 | | | | | | |TCF |inhibit) | | | | | | | | | |INHIBIT | | | | | | | | | | | | | | | | | | | | | |TERR ON ND| | | | 25 | | | | | | |CAPT INPUT| | | | | | | | | | | | | | | | | | | | | |TERR ON ND| | | | 26 | | | | | | |F/O INPUT | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 27 | | | | | | | | | | | | | | | | | |NOT USED | | | | 28 | | | | | | | | | | | | | | | | | |ALL AUDIO |(1= | | | 29 | | | | | | |INHIBIT |inhibit) | | | | | | | | -------------------------------------------------------------------------------

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R R

**ON A/C 001-049, 051-099, 101-104, 106-149, 151-199, 201-233, 236-238, 301-304, 401-403, A. Digital Outputs This table contains all the output parameters in digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI: output label for which the parameter is available, - PARAMETER DEFINITION: parameter name, - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy, - UNIT: unit in which the digital value is transmitted, - SIG BIT: indicates whether a sign bit is available, - BITS: number of bits used by the parameter in the label, - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds, - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code, - SOURCE ORIGIN: parameter source computer or system. ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 1.270.00 |ENH. GPWS |(1=voice on)| | | | 50 |DIS | | | | |ALER DSCRT| | | | | to | | | | | |WORD 1 | | | | |100 | | | | | | | | | | | | | | | | |SINKRATE- |bit status 1| | | 11 | | | | | | |PAUSE| | | | | | | | | | |SINKRATE | | | | | | | | | | | | | | | | | | | | | |PULL UP |bit status 1| | | 12 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 13 | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |DONT SINK|bit status 1| | | 14 | | | | | | |-PAUSE| | | | | | | | | | |DONT SINK| | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | | 15 | | | | | | |GEAR | | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | | 16 | | | | | | |FLAPS | | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | | 17 | | | | | | |TERRAIN | | | | | | | | | | | | | | | | | | | | | |GLIDESLOPE|bit status 1| | | 18 | | | | | | | | | | | | | | | | | |NOT USED | | | | 19 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 20 | | | | | | |PULL UP | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 21 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 22 | | | | | | |AHEAD PULL| | | | | | | | | | |UP | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 23 | | | | | | | | | | | | | | | | | |NOT USED | | | | 24 | | | | | | | | | | | | | | | | | |NOT USED | | | | 25 | | | | | | | | | | | | | | | | | |NOT USED | | | | 26 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 27 | | | | | | |AHEAD | | | | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |SPARE | | | | 28 | | | | | | | | | | | | | | | | | |Reserved | | | | 29 | | | | | | |for obsta.| | | | | | | | | | |voice | | | | | | | | | | 1.274.00 |ENH. GPWS |(1= on) | | | | 50 |DIS | | | | |ALER DSCRT| | | | | to | | | | | |WORD 2 | | | | |100 | | | | | | | | | | | | | | | | |G/S CANCEL|bit status 1| | | 11 | | | | | | | | | | | | | | | | | |GPWS ALERT|bit status 1| | | 12 | | | | | | | | | | | | | | | | | |GPWS |bit status 1| | | 13 | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |GPWS INOP |bit status 1| | | 14 | | | | | | | | | | | | | | | | | |WINDSHEAR |bit status 1| | | 15 | | | | | | |WARNING | | | | | | | | | | |(IF WR/PWS| | | | | | | | | | |INSTALLED)| | | | | | | | | | | | | | | | | | | | | |AUDIO ON |bit status 1| | | 16 | | | | | | | | | | | | | | | | | |NOT USED | | | | 17 | | | | | | | | | | | | | | | | | |NOT USED | | | | 18 | | | | | | | | | | | | | | | | | |NOT USED | | | | 19 | | | | | | | | | | | | | | | | | |NOT USED | | | | 20 | | | | | | | | | | | | | | | | | |NOT USED | | | | 21 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 22 | | | | | | |AWARENESS | | | | | | | | | | |WARNING | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |TERRAIN |bit status 1| | | 23 | | | | | | |AWARENESS | | | | | | | | | | |CAUTION | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 24 | | | | | | |AWARENESS | | | | | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |EXTERNAL |bit status 1| | | 25 | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |COMPUTER |bit status 1| | | 26 | | | | | | |FAIL | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 27 | | | | | | |AWARENESS | | | | | | | | | | |NOT AVAIL.| | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 28 | | | | | | |DISPLAY | | | | | | | | | | |DSCRT 1 | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 29 | | | | | | |DISPLAY | | | | | | | | | | |DSCRT 2 | | | | | | | | | | | | | | | | | | | | | 1.271.00 |ENH. GPWS |(1= warn. | | | |100 |DIS | | | | |LOGIC DSCR|in progress)| | | | to | | | | | | | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | | 11 | | | | | | | | | | | | | | | | | |NOT USED | | | | 12 | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 13 | | | | | | |CLEARANCE | | | | | | | | | | |FLOOR ALER| | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |ENV.MOD IN|bit status 1| | | 14 | | | | | | |PROGRESS | | | | | | | | | | | | | | | | | | | | | |ENV.MOD |bit status 1| | | 15 | | | | | | |SNAPSHOT | | | | | | | | | | |LATCH SET | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 16 | | | | | | | | | | | | | | | | | |NOT USED | | | | 17 | | | | | | | | | | | | | | | | | |TAKE OFF |bit status 1| | | 18 | | | | | | |MODE | | | | | | | | | | | | | | | | | | | | | |MODE 1 |bit status 1| | | 19 | | | | | | |SINKRATE | | | | | | | | | | | | | | | | | | | | | |MODE 1 |bit status 1| | | 20 | | | | | | |PULL UP | | | | | | | | | | | | | | | | | | | | | |MODE 2 |bit status 1| | | 21 | | | | | | |TERRAIN | | | | | | | | | | | | | | | | | | | | | |MODE 2 |bit status 1| | | 22 | | | | | | |PULL UP | | | | | | | | | | | | | | | | | | | | | |MODE 3 |bit status 1| | | 23 | | | | | | |VISUAL | | | | | | | | | | | | | | | | | | | | | |MODE 4 |bit status 1| | | 24 | | | | | | |VISUAL | | | | | | | | | | | | | | | | | | | | | |MODE 5 |bit status 1| | | 25 | | | | | | |VISUAL | | | | | | | | | | | | | | | | | | | | | |MODE 7 |bit status 1| | | 26 | | | | | | |VISUAL | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |ALERT | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 27 | | | | | | |AWARENESS | | | | | | | | | | |CAUTION | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 28 | | | | | | |AWARENESS | | | | | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 29 | | | | | | | | | | | | | | | | | 1.300.00 |ENH. GPWC | | | | | 50 |DIS | | | | |ALERT DSCR| | | | | to | | | | | |WORD3 | | | | |100 | | | | | | | | | | | | | | | | |MODES 1 TO| | | | 11 | | | | | | |4 INOP | | | | | | | | | | | | | | | | | | | | | |MODE 5 | | | | 12 | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 13 | | | | | | | | | | | | | | | | | |NOT USED | | | | 14 | | | | | | | | | | | | | | | | | |NOT USED | | | | 15 | | | | | | | | | | | | | | | | | |TERR CLEA.| | | | 16 | | | | | | |FLOOR INOP| | | | | | | | | | | | | | | | | | | | | |TERR AWAR.| | | | 17 | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |ENV. MODU.| | | | 18 | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |SPARE | | | | 19 | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |SPARE | | | | 20 | | | | | | | | | | | | | | | | | |SPARE | | | | 21 | | | | | | | | | | | | | | | | | |SPARE | | | | 22 | | | | | | | | | | | | | | | | | |SPARE | | | | 23 | | | | | | | | | | | | | | | | | |SPARE | | | | 24 | | | | | | | | | | | | | | | | | |SPARE | | | | 25 | | | | | | | | | | | | | | | | | |SPARE | | | | 26 | | | | | | | | | | | | | | | | | |SPARE | | | | 27 | | | | | | | | | | | | | | | | | |SPARE | | | | 28 | | | | | | | | | | | | | | | | | |SPARE | | | | 29 | | | | | | | | | | | | | | | | | 1.275.00 |PROGRAM |(1=Open | | | |100 |DIS | | | | |PIN STATUS|0=Ground) | | | | to | | | | | |WORD 1 | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | | 11 | | | | | | | | | | | | | | | | | |CFDS |bit status 1| | | 12 | | | | | | |ENABLE | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 13 | | | | | | |SELECT 6 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 14 | | | | | | |SELECT 1 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 15 | | | | | | |SELECT 2 | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |AIRCRAFT | | | | 16 | | | | | | |SELECT 3 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 17 | | | | | | | | | | | | | | | | | |NOT USED | | | | 18 | | | | | | | | | | | | | | | | | |AUDIO |bit status 0| | | 19 | | | | | | |DECLUTTER | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 20 | | | | | | | | | | | | | | | | | |NOT USED | | | | 21 | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 22 | | | | | | |SELECT 7 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 23 | | | | | | | | | | | | | | | | | |NOT USED | | | | 24 | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 25 | | | | | | |SELECT 5 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 26 | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 27 | | | | | | |SELECT 4 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 28 | | | | | | | | | | | | | | | | | |NOT USED | | | | 29 | | | | | | | | | | | | | | | | | 1.276.00 |PROGRAM |(1=Open | | | |100 |DIS | | | | |PIN STATUS|0=Ground) | | | | to | | | | | |WORD 2 | | | | |200 | | | | | | | | | | | | | | |

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page 68 151-199, 201-233, 236-238, 301-304, 401-403,  Config-1 Feb 01/08  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |VOICE | | | | 11 | | | | | | |SELECT 1 | | | | | | | | | | | | | | | | | | | | | |VOICE | | | | 12 | | | | | | |SELECT 2 | | | | | | | | | | | | | | | | | | | | | |VOICE | | | | 13 | | | | | | |SELECT 3 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 14 | | | | | | | | | | | | | | | | | |AUDIO |bit status 1| | | 15 | | | | | | |SUPPRESS | | | | | | | | | | | | | | | | | | | | | |ATERNATE |bit status 1| | | 16 | | | | | | |MODE 4 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 17 | | | | | | | | | | | | | | | | | |FMGC |bit status 1| | | 18 | | | | | | |SELECT | | | | | | | | | | | | | | | | | | | | | |ALTERN. |bit status 1| | | 19 | | | | | | |G/S CANCEL| | | | | | | | | | | | | | | | | | | | | |LAMP |bit status 1| | | 20 | | | | | | |FORMAT | | | | | | | | | | | | | | | | | | | | | |QFE/QNH |bit status 1| | | 21 | | | | | | |SELECT |=QFE SELECT | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 22 | | | | | | | | | | | | | | | | | |NOT USED | | | | 23 | | | | | | | | | | | | | | | | | |G/S |bit status 1| | | 24 | | | | | | |INHIBIT | | | | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |NOT USED | | | | 25 | | | | | | | | | | | | | | | | | |NOT USED | | | | 26 | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 27 | | | | | | |SELECT 8 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 28 | | | | | | |SELECT 9 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 29 | | | | | | | | | | | | | | | | | 1.277.00 |PROGRAM |(1=Open | | | |100 |DIS | | | | |PIN STATUS|0=Ground) | | | | to | | | | | |WORD 3 | | | | |200 | | | | | | | | | | | | | | | | |ALTER.VOL.|bit status 1| | | 11 | | | | | | |SELECTED | | | | | | | | | | | | | | | | | | | | | |SPARE | | | | 12 | | | | | | | | | | | | | | | | | |SPARE | | | | 13 | | | | | | | | | | | | | | | | | |NOT USED | | | | 14 | | | | | | | | | | | | | | | | | |NOT USED | | | | 15 | | | | | | | | | | | | | | | | | |NOT USED | | | | 16 | | | | | | | | | | | | | | | | | |TCF |bit status 1| | | 17 | | | | | | |DISABLE | | | | | | | | | | | | | | | | | | | | | |TAD |bit status 1| | | 18 | | | | | | |DISABLE | | | | | | | | | | | | | | | | | | | | | |SPARE | | | | 19 | | | | | | | | | | | | | | | | | |SPARE | | | | 20 | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |NOT USED | | | | 21 | | | | | | | | | | | | | | | | | |NOT USED | | | | 22 | | | | | | | | | | | | | | | | | |NOT USED | | | | 23 | | | | | | | | | | | | | | | | | |SPARE | | | | 24 | | | | | | | | | | | | | | | | | |SPARE | | | | 25 | | | | | | | | | | | | | | | | | |SPARE | | | | 26 | | | | | | | | | | | | | | | | | |NOT USED | | | | 27 | | | | | | | | | | | | | | | | | |NOT USED | | | | 28 | | | | | | | | | | | | | | | | | |NOT USED | | | | 29 | | | | | | | | | | | | | | | | | 1.350.00 |FAULT |(1=Failed)| | | |100 |DIS | | | | |DIAGNOSTIC| | | | | to | | | | | |WORD 1 | | | | |200 | | | | | | | | | | | | | | | | |ARINC 429 | | | | 11 | | | | | | |IR1 INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 12 | | | | | | |FMGC1 | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 13 | | | | | | |ADR1 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 14 | | | | | | |FCU BUS 1 | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 15 | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 16 | | | | | | |ILS1 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 17 | | | | | | |FMGC1(Nav | | | | | | | | | | |Modes) IN.| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 18 | | | | | | |RA1 INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 19 | | | | | | |FCU BUS 2 | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 20 | | | | | | |CFDIU | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 21 | | | | | | |WXR HZD | | | | | | | | | | |BUS1 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 22 | | | | | | | | | | | | | | | | | |NOT USED | | | | 23 | | | | | | | | | | | | | | | | | |NOT USED | | | | 24 | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |NOT USED | | | | 25 | | | | | | | | | | | | | | | | | |NOT USED | | | | 26 | | | | | | | | | | | | | | | | | |PROGRAM | | | | 27 | | | | | | |PIN FAULT | | | | | | | | | | | | | | | | | | | | | |FLAP | | | | 28 | | | | | | |INPUT FAI.| | | | | | | | | | | | | | | | | | | | | |GEAR | | | | 29 | | | | | | |INPUT FAI.| | | | | | | | | | | | | | | | | | | | | 1.351.00 |FAULT |(1=Failed)| | | |100 |DIS | | | | |DIAGNOSTIC| | | | | to | | | | | |WORD 2 | | | | |200 | | | | | | | | | | | | | | | | |G/S CANCEL| | | | 11 | | | | | | |DSCR. FAI.| | | | | | | | | | | | | | | | | | | | | |MOMENTARY | | | | 12 | | | | | | |AUDIO SUPP| | | | | | | | | | |DSCR. FAI.| | | | | | | | | | | | | | | | | | | | | |AUDIO | | | | 13 | | | | | | |INHIBIT | | | | | | | | | | |DSCR. FAI.| | | | | | | | | | | | | | | | | | | | | |SELF-TEST | | | | 14 | | | | | | |DSCR INPUT| | | | | | | | | | |FAILED | | | | | | | | | | | | | | | | | | | | | |SUPPORT | | | | 15 | | | | | | |TASK FAULT| | | | | | | | | | | | | | | | | | | | | |NVM FAULT | | | | 16 | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |WATCHDOG | | | | 17 | | | | | | |TIMER FAUL| | | | | | | | | | | | | | | | | | | | | |A/D FAIL | | | | 18 | | | | | | | | | | | | | | | | | |VOICE FAIL| | | | 19 | | | | | | | | | | | | | | | | | |DITS | | | | 20 | | | | | | |OUTPUT FAI| | | | | | | | | | | | | | | | | | | | | |TERRAIN | | | | 21 | | | | | | |DATABASE | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |FLASH FILE| | | | 22 | | | | | | |SYSTEM | | | | | | | | | | |WRITE | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |DITS INPUT| | | | 23 | | | | | | |FAIL | | | | | | | | | | | | | | | | | | | | | |VOICE | | | | 24 | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |SYSTEM OR | | | | 25 | | | | | | |MODE TASK | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |ENV. MOD. | | | | 26 | | | | | | |DATABASE | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |WATCHDOG | | | | 27 | | | | | | |FAIL COUNT| | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | | 28 | | | | | | |DATABASE | | | | | | | | |

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page 74 151-199, 201-233, 236-238, 301-304, 401-403,  Config-1 Feb 01/08  CES

 

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |FAULT OR| | | | | | | | | | |CRC FAULT | | | | | | | | | | | | | | | | | | | | | |IMAGE DSP | | | | 29 | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | 1.355.00 |FAULT |(1=Failed)| | | |100 |DIS | | | | |DIAGNOSTIC| | | | | to | | | | | |WORD 3 | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | | 11 | | | | | | | | | | | | | | | | | |NOT USED | | | | 12 | | | | | | | | | | | | | | | | | |NOT USED | | | | 13 | | | | | | | | | | | | | | | | | |NOT USED | | | | 14 | | | | | | | | | | | | | | | | | |NOT USED | | | | 15 | | | | | | | | | | | | | | | | | |ARINC 429 | | | | 16 | | | | | | |WRX HZD | | | | | | | | | | |BUS2 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 17 | | | | | | | | | | | | | | | | | |NOT USED | | | | 18 | | | | | | | | | | | | | | | | | |SPARE | | | | 19 | | | | | | | | | | | | | | | | | |SPARE | | | | 20 | | | | | | | | | | | | | | | | | |SPARE | | | | 21 | | | | | | | | | | | | | | | | | |SPARE | | | | 22 | | | | | | | | | | | | | | | | | |SPARE | | | | 23 | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |SPARE | | | | 24 | | | | | | | | | | | | | | | | | |SPARE | | | | 25 | | | | | | | | | | | | | | | | | |SPARE | | | | 26 | | | | | | | | | | | | | | | | | |SPARE | | | | 27 | | | | | | | | | | | | | | | | | |SPARE | | | | 28 | | | | | | | | | | | | | | | | | |SPARE | | | | 29 | | | | | | | | | | | | | | | | | 1.357.00 |INPUT | | | | |100 |DIS | | | | |DSCRT STAT| | | | | to | | | | | |WORD 1 | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | | 11 | | | | | | | | | | | | | | | | | |G/S |(1= | | | 12 | | | | | | |INHIBIT |inhibit) | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 13 | | | | | | | | | | | | | | | | | |NOT USED | | | | 14 | | | | | | | | | | | | | | | | | |GPWS MODES|(1= | | | 15 | | | | | | |1 TO 5 |inhibit) | | | | | | | | | |INHIBIT | | | | | | | | | | |(AUDIO AND| | | | | | | | | | |VISUAL) | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 16 | | | | | | | | | | | | | | | | | |MOMENTARY |(1= | | | 17 | | | | | | |AUDIO SUPP|suppress) | | | | | | | | | | | | | | | | | | | | |SELF-TEST | | | | 18 | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |LANDING |(1= down) | | | 19 | | | | | | |GEAR | | | | | | | | | | | | | | | | | | | | | |LANDING |(1= | | | 20 | | | | | | |FLAPS |extended) | | | | | | | | | | | | | | | | | | | | |G/S CANCEL|(1= | | | 21 | | | | | | | |cancelled) | | | | | | | | | | | | | | | | | | | | |WXR 1 |(1= ON) | | | 22 | | | | | | |ON/OFF | | | | | | | | | | | | | | | | | | | | | |TAD AND |(1= | | | 23 | | | | | | |TCF |inhibit) | | | | | | | | | |INHIBIT | | | | | | | | | | | | | | | | | | | | | |WXR 2 |(1= ON) | | | 24 | | | | | | |ON/OFF | | | | | | | | | | | | | | | | | | | | | |TERR ON ND| | | | 25 | | | | | | |CAPT INPUT| | | | | | | | | | | | | | | | | | | | | |TERR ON ND| | | | 26 | | | | | | |F/O INPUT | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | | 27 | | | | | | | | | | | | | | | | | |NOT USED | | | | 28 | | | | | | | | | | | | | | | | | |ALL AUDIO |(1= | | | 29 | | | | | | |INHIBIT |inhibit) | | | | | | | | -------------------------------------------------------------------------------

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page 77 151-199, 201-233, 236-238, 301-304, 401-403,  Config-1 Feb 01/08  CES

 

R

**ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

A. Digital Outputs This table contains all the output parameters in digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI: output label for which the parameter is available, - PARAMETER DEFINITION: parameter name, - WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy, - UNIT: unit in which the digital value is transmitted, - SIG BIT: indicates whether a sign bit is available, - BITS: number of bits used by the parameter in the label, - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds, - CODE: BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code, - SOURCE ORIGIN: parameter source computer or system. ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 1.270.00 |ENH. GPWS |(1=voice on)| | | | 50 |DIS | | | | |ALER DSCRT| | | | | to | | | | | |WORD 1 | | | | |100 | | | | | | | | | | | | | | | | |SINKRATE- |bit status 1| | 11 | | | | | | | |PAUSE| | | | | | | | | | |SINKRATE | | | | | | | | | | | | | | | | | | | | | |PULL UP |bit status 1| | 12 | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |TERRAIN |bit status 1| | 13 | | | | | | | | | | | | | | | | | | |DONT SINK|bit status 1| | 14 | | | | | | | |-PAUSE| | | | | | | | | | |DONT SINK| | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | 15 | | | | | | | |GEAR | | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | 16 | | | | | | | |FLAPS | | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | 17 | | | | | | | |TERRAIN | | | | | | | | | | | | | | | | | | | | | |GLIDESLOPE|bit status 1| | 18 | | | | | | | | | | | | | | | | | | |NOT USED | | | 19 | | | | | | | | | | | | | | | | | | |NOT USED |bit status 1| | 20 | | | | | | | | | | | | | | | | | | |NOT USED | | | 21 | | | | | | | | | | | | | | | | | | |TERRAIN or|bit status 1| | 22 | | | | | | | |OBSTACLE | | | | | | | | | | |AHEAD PULL| | | | | | | | | | |UP | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 23 | | | | | | | | | | | | | | | | | | |NOT USED | | | 24 | | | | | | | | | | | | | | | | | | |NOT USED | | | 25 | | | | | | | | | | | | | | | | | | |NOT USED | | | 26 | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | 27 | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |AHEAD | | | | | | | | | | | | | | | | | | | | | |OBSTACLE |bit status 1| | 28 | | | | | | | |AHEAD | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 29 | | | | | | | | | | | | | | | | | | 1.274.00 |ENH. GPWS |(1= on) | | | | 50 |DIS | | | | |ALER DSCRT| | | | | to | | | | | |WORD 2 | | | | |100 | | | | | | | | | | | | | | | | |DOUTL 1 |bit status 1| | 11 | | | | | | | |G/S CANCEL| | | | | | | | | | | | | | | | | | | | | |DOUTL 2 |bit status 1| | 12 | | | | | | | |GPWS ALERT| | | | | | | | | | | | | | | | | | | | | |DOUTL 3 |bit status 1| | 13 | | | | | | | |GPWS | | | | | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |GPWS INOP |bit status 1| | 14 | | | | | | | | | | | | | | | | | | |NOT USED | | | 15 | | | | | | | | | | | | | | | | | | |DOUTL 6 |bit status 1| | 16 | | | | | | | |AUDIO ON | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 17 | | | | | | | | | | | | | | | | | | |NOT USED | | | 18 | | | | | | | | | | | | | | | | | | |NOT USED | | | 19 | | | | | | | | | | | | | | | | | | |NOT USED | | | 20 | | | | | | | | | | | | | | | | | | |NOT USED | | | 21 | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |TERRAIN or|bit status 1| | 22 | | | | | | | |OBSTACLE | | | | | | | | | | |AWARENESS | | | | | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |TERRAIN or|bit status 1| | 23 | | | | | | | |OBSTACLE | | | | | | | | | | |AWARENESS | | | | | | | | | | |CAUTION | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | 24 | | | | | | | |AWARENESS | | | | | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |EXTERNAL |bit status 1| | 25 | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |COMPUTER |bit status 1| | 26 | | | | | | | |FAIL | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | 27 | | | | | | | |AWARENESS | | | | | | | | | | |NOT AVAIL.| | | | | | | | | | | | | | | | | | | | | |DOUTL 8 |bit status 1| | 28 | | | | | | | |TERRAIN | | | | | | | | | | |DISPLAY | | | | | | | | | | |DSCRT 1 | | | | | | | | | | | | | | | | | | | | | |DOUTL 9 |bit status 1| | 29 | | | | | | | |TERRAIN | | | | | | | | | | |DISPLAY | | | | | | | | | | |DSCRT 2 | | | | | | | | | | | | | | | | | | | | | 1.271.00 |ENH. GPWS |(1= warn. | | | |100 |DIS | | | | |LOGIC DSCR|in progress)| | | | to | | | | | | | | | | |200 | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |NOT USED | | | 11 | | | | | | | | | | | | | | | | | | |NOT USED | | | 12 | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | 13 | | | | | | | |CLEARANCE | | | | | | | | | | |FLOOR ALER| | | | | | | | | | | | | | | | | | | | | |ENV.MOD IN|bit status 1| | 14 | | | | | | | |PROGRESS | | | | | | | | | | | | | | | | | | | | | |ENV.MOD |bit status 1| | 15 | | | | | | | |SNAPSHOT | | | | | | | | | | |LATCH SET | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 16 | | | | | | | | | | | | | | | | | | |NOT USED | | | 17 | | | | | | | | | | | | | | | | | | |TAKE OFF |bit status 1| | 18 | | | | | | | |MODE | | | | | | | | | | | | | | | | | | | | | |MODE 1 |bit status 1| | 19 | | | | | | | |SINKRATE | | | | | | | | | | | | | | | | | | | | | |MODE 1 |bit status 1| | 20 | | | | | | | |PULL UP | | | | | | | | | | | | | | | | | | | | | |MODE 2 |bit status 1| | 21 | | | | | | | |TERRAIN | | | | | | | | | | | | | | | | | | | | | |MODE 2 |bit status 1| | 22 | | | | | | | |PULL UP | | | | | | | | | | | | | | | | | | | | | |MODE 3 |bit status 1| | 23 | | | | | | | |VISUAL | | | | | | | | | | | | | | | | | | | | | |MODE 4 |bit status 1| | 24 | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |VISUAL | | | | | | | | | | | | | | | | | | | | | |MODE 5 |bit status 1| | 25 | | | | | | | |VISUAL | | | | | | | | | | | | | | | | | | | | | |NOT USED |bit status 1| | 26 | | | | | | | | | | | | | | | | | | |NOTE USED | | | 27 | | | | | | | | | | | | | | | | | | |NOTE USED | | | 28 | | | | | | | | | | | | | | | | | | |NOT USED | | | 29 | | | | | | | | | | | | | | | | | | 1.300.00 |ENH. GPWC | | | | | 50 |DIS | | | | |ALERT DSCR| | | | | to | | | | | |WORD3 | | | | |100 | | | | | | | | | | | | | | | | |MODES 1 TO| | | 11 | | | | | | | |4 INOP | | | | | | | | | | | | | | | | | | | | | |MODE 5 | | | 12 | | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 13 | | | | | | | | | | | | | | | | | | |NOT USED | | | 14 | | | | | | | | | | | | | | | | | | |NOT USED | | | 15 | | | | | | | | | | | | | | | | | | |TERR CLEA.| | | 16 | | | | | | | |FLOOR INOP| | | | | | | | | | | | | | | | | | | | | |TERR AWAR.| | | 17 | | | | | | | |INOP | | | | | | | | | | | | | | | | | | | | | |ENV. MODU.| | | 18 | | | | | | | |INOP | | | | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |NOT USED | | | 19 | | | | | | | | | | | | | | | | | | |NOT USED | | | 20 | | | | | | | | | | | | | | | | | | |TCAS | | | 21 | | | | | | | |INHIBIT | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 22 | | | | | | | | | | | | | | | | | | |NOT USED | | | 23 | | | | | | | | | | | | | | | | | | |NOT USED | | | 24 | | | | | | | | | | | | | | | | | | |SPARE | | | 25 | | | | | | | | | | | | | | | | | | |NOT USED | | | 26 | | | | | | | | | | | | | | | | | | |FLAP OVRD | | | 27 | | | | | | | |LATCH | | | | | | | | | | | | | | | | | | | | | |OBST | | | 28 | | | | | | | |AWARENESS | | | | | | | | | | |CAUTION | | | | | | | | | | | | | | | | | | | | | |OBST | | | 29 | | | | | | | |AWARENESS | | | | | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | 1.275.00 |PROGRAM |(1=Open | | | |100 |DIS | | | | |PIN STATUS|0=Ground) | | | | to | | | | | |WORD 1 | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | 11 | | | | | | | | | | | | | | | | | | |CFDS |bit status 1| | 12 | | | | | | | |ENABLE | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | 13 | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |SELECT 6 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | 14 | | | | | | | |SELECT 1 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | 15 | | | | | | | |SELECT 2 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | 16 | | | | | | | |SELECT 3 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 17 | | | | | | | | | | | | | | | | | | |NOT USED | | | 18 | | | | | | | | | | | | | | | | | | |AUDIO |bit status 0| | 19 | | | | | | | |DECLUTTER | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 20 | | | | | | | | | | | | | | | | | | |NOT USED | | | 21 | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | 22 | | | | | | | |SELECT 7 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 23 | | | | | | | | | | | | | | | | | | |NOT USED | | | 24 | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | 25 | | | | | | | |SELECT 5 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 26 | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | 27 | | | | | | | |SELECT 4 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 28 | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |NOT USED | | | 29 | | | | | | | | | | | | | | | | | | 1.276.00 |PROGRAM |(1=Open | | | | 50 |DIS | | | | |PIN STATUS|0=Ground) | | | | to | | | | | |WORD 2 | | | | |100 | | | | | | | | | | | | | | | | |VOICE | | | 11 | | | | | | | |SELECT 1 | | | | | | | | | | | | | | | | | | | | | |VOICE | | | 12 | | | | | | | |SELECT 2 | | | | | | | | | | | | | | | | | | | | | |VOICE | | | 13 | | | | | | | |SELECT 3 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 14 | | | | | | | | | | | | | | | | | | |AUDIO |bit status 1| | 15 | | | | | | | |SUPPRESS | | | | | | | | | | | | | | | | | | | | | |ATERNATE |bit status 1| | 16 | | | | | | | |MODE 4 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 17 | | | | | | | | | | | | | | | | | | |OPTIONAL |bit status 1| | 18 | | | | | | | |INPUT | | | | | | | | | | |SELECT | | | | | | | | | | | | | | | | | | | | | |ALTERN. |bit status 1| | 19 | | | | | | | |G/S CANCEL| | | | | | | | | | | | | | | | | | | | | |LAMP |bit status 1| | 20 | | | | | | | |FORMAT |= Lamp | | | | | | | | | | | Format 2 | | | | | | | | | | | | | | | | | | | | |QFE/QNH |bit status 1| | 21 | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |SELECT |=QFE SELECT | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 22 | | | | | | | | | | | | | | | | | | |NOT USED | | | 23 | | | | | | | | | | | | | | | | | | |G/S | | | 24 | | | | | | | |INHIBIT | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 25 | | | | | | | | | | | | | | | | | | |NOT USED | | | 26 | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | 27 | | | | | | | |SELECT 8 | | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | 28 | | | | | | | |SELECT 9 | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 29 | | | | | | | | | | | | | | | | | | 1.277.00 |PROGRAM |(1=Open | | | |100 |DIS | | | | |PIN STATUS|0=Ground) | | | | to | | | | | |WORD 3 | | | | |200 | | | | | | | | | | | | | | | | |ALTER.VOL.|bit status 1| | 11 | | | | | | | |SELECTED | | | | | | | | | | | | | | | | | | | | | |CONF |bit status 1| | 12 | | | | | | | |OPTION 1= | | | | | | | | | | |GPS SELECT| | | | | | | | | | | | | | | | | | | | | |CONF |bit status 1| | 13 | | | | | | | |OPTION 2= | | | | | | | | | | |MAN DESEL | | | | | | | | | | | | | | | | | | | | | |SINGLE GPS|bit status 1| | 14 | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |NOT USED | | | 15 | | | | | | | | | | | | | | | | | | |NOT USED | | | 16 | | | | | | | | | | | | | | | | | | |TCF |bit status 1| | 17 | | | | | | | |DISABLE | | | | | | | | | | | | | | | | | | | | | |TAD |bit status 1| | 18 | | | | | | | |DISABLE | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 19 | | | | | | | | | | | | | | | | | | |PWS OPTION|bit status 1| | 20 | | | | | | | | | | | | | | | | | | |NOT USED | | | 21 | | | | | | | | | | | | | | | | | | |NOT USED | | | 22 | | | | | | | | | | | | | | | | | | |NOT USED | | | 23 | | | | | | | | | | | | | | | | | | |ALTERNATE |bit status 1| | 24 | | | | | | | |GPS SPEED | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 25 | | | | | | | | | | | | | | | | | | |OBSTACLE | | | 26 | | | | | | | |CONTROL | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 27 | | | | | | | | | | | | | | | | | | |NOT USED | | | 28 | | | | | | | | | | | | | | | | | | |NOT USED | | | 29 | | | | | | | | | | | | | | | | | | 1.350.00 |FAULT |(1=Failed)| | | |100 |DIS | | | | |DIAGNOSTIC| | | | | to | | | | | |WORD 1 | | | | |200 | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |ARINC 429 | | | 11 | | | | | | | |IR1 INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | 12 | | | | | | | |FMGC1 | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | 13 | | | | | | | |ADR1 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | 14 | | | | | | | |FCU BUS 1 | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 15 | | | | | | | | | | | | | | | | | | |ARINC 429 | | | 16 | | | | | | | |ILS1 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | 17 | | | | | | | |FMGC1(Nav | | | | | | | | | | |Modes) IN.| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | 18 | | | | | | | |RA1 INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | 19 | | | | | | | |FCU BUS 2 | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |ARINC 429 | | | 20 | | | | | | | |CFDIU | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |ARINC 429 | | | 21 | | | | | | | |WXR HZD | | | | | | | | | | |BUS1 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 22 | | | | | | | | | | | | | | | | | | |NOT USED | | | 23 | | | | | | | | | | | | | | | | | | |NOT USED | | | 24 | | | | | | | | | | | | | | | | | | |NOT USED | | | 25 | | | | | | | | | | | | | | | | | | |NOT USED | | | 26 | | | | | | | | | | | | | | | | | | |PROGRAM | | | 27 | | | | | | | |PIN FAULT | | | | | | | | | | | | | | | | | | | | | |FLAP | | | 28 | | | | | | | |INPUT FAI.| | | | | | | | | | | | | | | | | | | | | |GEAR | | | 29 | | | | | | | |INPUT FAI.| | | | | | | | | | | | | | | | | | | | | 1.351.00 |FAULT |(1=Failed)| | | |100 |DIS | | | | |DIAGNOSTIC| | | | | to | | | | | |WORD 2 | | | | |200 | | | | | | | | | | | | | | | | |G/S CANCEL| | | 11 | | | | | | | |DSCR. FAI.| | | | | | | | | | | | | | | | | | | | | |MOMENTARY | | | 12 | | | | | | | |AUDIO SUPP| | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |DSCR. FAI.| | | | | | | | | | | | | | | | | | | | | |AUDIO | | | 13 | | | | | | | |INHIBIT | | | | | | | | | | |DSCR. FAI.| | | | | | | | | | | | | | | | | | | | | |SELF-TEST | | | 14 | | | | | | | |DSCR INPUT| | | | | | | | | | |FAILED | | | | | | | | | | | | | | | | | | | | | |SUPPORT | | | 15 | | | | | | | |TASK FAULT| | | | | | | | | | | | | | | | | | | | | |NVM FAULT | | | 16 | | | | | | | | | | | | | | | | | | |WATCHDOG | | | 17 | | | | | | | |TIMER FAUL| | | | | | | | | | | | | | | | | | | | | |A/D FAIL | | | 18 | | | | | | | | | | | | | | | | | | |VOICE FAIL| | | 19 | | | | | | | | | | | | | | | | | | |DITS | | | 20 | | | | | | | |OUTPUT FAI| | | | | | | | | | | | | | | | | | | | | |TERRAIN | | | 21 | | | | | | | |DATABASE | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |FLASH FILE| | | 22 | | | | | | | |SYSTEM | | | | | | | | | | |WRITE | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |DITS INPUT| | | 23 | | | | | | | |FAIL | | | | | | | | | | | | | | | | | | | | | |VOICE | | | 24 | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |FAULT | | | | | | | | | | | | | | | | | | | | | |SYSTEM OR | | | 25 | | | | | | | |MODE TASK | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |ENV. MOD. | | | 26 | | | | | | | |DATABASE | | | | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | |WATCHDOG | | | 27 | | | | | | | |FAIL COUNT| | | | | | | | | | | | | | | | | | | | | |AIRCRAFT | | | 28 | | | | | | | |DATABASE | | | | | | | | | | |FAULT OR| | | | | | | | | | |CRC FAULT | | | | | | | | | | | | | | | | | | | | | |IMAGE DSP | | | 29 | | | | | | | |FAULT | | | | | | | | | | | | | | | | | | | | | 1.355.00 |FAULT |(1=Failed)| | | |100 |DIS | | | | |DIAGNOSTIC| | | | | to | | | | | |WORD 3 | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | 11 | | | | | | | | | | | | | | | | | | |NOT USED | | | 12 | | | | | | | | | | | | | | | | | | |NOT USED | | | 13 | | | | | | | | | | | | | | | | | | |NOT USED | | | 14 | | | | | | | | | | | | | | | | | | |ARINC 429 | | | 15 | | | | | | | |GPS BUS | | | | | | | | | | |INPUT | | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |ARINC 429 | | | 16 | | | | | | | |WXR HZD | | | | | | | | | | |BUS2 INPUT| | | | | | | | | | |INACTIVE | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 17 | | | | | | | | | | | | | | | | | | |NOT USED | | | 18 | | | | | | | | | | | | | | | | | | |SPARE | | | 19 | | | | | | | | | | | | | | | | | | |SPARE | | | 20 | | | | | | | | | | | | | | | | | | |SPARE | | | 21 | | | | | | | | | | | | | | | | | | |SPARE | | | 22 | | | | | | | | | | | | | | | | | | |SPARE | | | 23 | | | | | | | | | | | | | | | | | | |SPARE | | | 24 | | | | | | | | | | | | | | | | | | |SPARE | | | 25 | | | | | | | | | | | | | | | | | | |SPARE | | | 26 | | | | | | | | | | | | | | | | | | |SPARE | | | 27 | | | | | | | | | | | | | | | | | | |SPARE | | | 28 | | | | | | | | | | | | | | | | | | |SPARE | | | 29 | | | | | | | | | | | | | | | | | | 1.357.00 |INPUT | | | | |100 |DIS | | | | |DSCRT STAT| | | | | to | | | | | |WORD 1 | | | | |200 | | | | | | | | | | | | | | | | |NOT USED | | | 11 | | | | | | | | | | | | | | | | | | |G/S |(1= | | 12 | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |INHIBIT |inhibit) | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 13 | | | | | | | | | | | | | | | | | | |NOT USED | | | 14 | | | | | | | | | | | | | | | | | | |GPWS MODES|(1= | | 15 | | | | | | | |1 TO 5 |inhibit) | | | | | | | | | |INHIBIT | | | | | | | | | | |(AUDIO AND| | | | | | | | | | |VISUAL) | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 16 | | | | | | | | | | | | | | | | | | |MOMENTARY |(1= | | 17 | | | | | | | |AUDIO SUPP|suppress) | | | | | | | | | | | | | | | | | | | | |SELF-TEST | | | 18 | | | | | | | | | | | | | | | | | | |LANDING |(1= down) | | 19 | | | | | | | |GEAR | | | | | | | | | | | | | | | | | | | | | |LANDING |(1= | | 20 | | | | | | | |FLAPS |extended) | | | | | | | | | | | | | | | | | | | | |G/S CANCEL|(1= | | 21 | | | | | | | | |cancelled) | | | | | | | | | | | | | | | | | | | | |WXR 1 |(1= ON) | | 22 | | | | | | | |ON/OFF | | | | | | | | | | | | | | | | | | | | | |TAD AND |(1= | | 23 | | | | | | | |TCF |inhibit) | | | | | | | | | |INHIBIT | | | | | | | | | | | | | | | | | | | | | |WXR 2 |(1= ON) | | 24 | | | | | | | |ON/OFF | | | | | | | | | | | | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |TERR ON ND| | | 25 | | | | | | | |CAPT INPUT| | | | | | | | | | | | | | | | | | | | | |TERR ON ND| | | 26 | | | | | | | |F/O INPUT | | | | | | | | | | | | | | | | | | | | | |NOT USED | | | 27 | | | | | | | | | | | | | | | | | | |NOT USED |(1= | | 28 | | | | | | | |(RAAS) |activated) | | | | | | | | | | | | | | | | | | | | |ALL AUDIO |(1= | | 29 | | | | | | | |INHIBIT |inhibit) | | | | | | | | ------------------------------------------------------------------------------R

**ON A/C ALL 6. _____________________ Component Description **ON A/C 105-105, A. Enhanced GPWC (1) External descrition (Ref. Fig. 008) The Enhanced GPWC is packaged in a 2 MCU ARINC 600-6 form factor enclosure. The enclosure of the unit is painted with a blue semi-gloss coating, except for the bottom, which is unpainted. The computer is composed of the following subassemblies: - rear panel assembly, - front panel assembly, - chassis, - PCMCIA interface, - front connector.

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Enhanced GPWC Figure 008   R EFF : ALL  34-48-00 Page 96   Config-1 Nov 01/09  CES

 

(a) Rear panel assembly The rear panel assembly contains a 2 MCU ARINC 600-6 form aircraft interface connector. The top and middle shells contain all interface signals. Power interface is in the bottom shell, isolated from interface signals. Connector index pin coding is orientation 08 or 10 in accordance with ARINC 723-1 recommendations for GPWS. The rear panel assembly also contains the interconnection between the aircraft interface connector and the internal interface Circuit Card Assembly (CCA), A5, and the Backplane CCA, A4, which provide all internal electrical interconnects between CCAs and other circuitry. The Enhanced GPWC pins are listed in the table below (N/U means Not Used): --------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 6A| 429 INPUT 1(A) ADIRU1 BUS IR (A) | | MIDDLE | 6B| 429 INPUT 1(B) ADIRU1 BUS IR (B) | | TOP | 9A| 429 INPUT 10(A) CFDIU (A) | | TOP | 9B| 429 INPUT 10(B) CFDIU (B) | | TOP | 8A| 429 INPUT 11(A) WXR1 HZD BUS (A) | | TOP | 8B| 429 INPUT 11(B) WXR1 HZD BUS (B) | | TOP | 8C| 429 INPUT 12(A) N/U | | TOP | 8D| 429 INPUT 12(B) N/U | | TOP | 5A| 429 INPUT 13(A) N/U | | TOP | 6A| 429 INPUT 13(B) N/U | | TOP | 1C| 429 INPUT 14(A) N/U | | TOP | 1D| 429 INPUT 14(B) N/U | | TOP | 4A| 429 INPUT 15(A) N/U | | TOP | 4B| 429 INPUT 15(B) N/U | | MIDDLE |10C| 429 INPUT 2(A) FMGC1 (A) | | MIDDLE |10D| 429 INPUT 2(B) FMGC1 (B) | | MIDDLE |11A| 429 INPUT 3(A) ADIRU 1 BUS ADR (A) | | MIDDLE |11B| 429 INPUT 3(B) ADIRU 1 BUS ADR (B) | | MIDDLE |12A| 429 INPUT 4(A) FCU 1 (A) | | MIDDLE |12B| 429 INPUT 4(B) FCU 1 (B) | | MIDDLE |10A| 429 INPUT 5(A) N/U | | MIDDLE |10B| 429 INPUT 5(B) N/U | | MIDDLE |11C| 429 INPUT 6(A) ILS 1 (A) | | MIDDLE |11D| 429 INPUT 6(B) ILS 1 (B) | | MIDDLE |12C| 429 INPUT 7(A) FMGC 1 DISCWORD (A) | | MIDDLE |12D| 429 INPUT 7(B) FMGC 1 DISCWORD (B) | | MIDDLE |13A| 429 INPUT 8(A) RA 1 (A) | | MIDDLE |13B| 429 INPUT 8(B) RA 1 (B) | | TOP | 9C| 429 INPUT 9(A) FCU 2 (A) |

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--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| TOP | 9D| 429 INPUT 9(B) FCU 2 (B) | | MIDDLE | 1C| 429 OUTPUT 1(A) CFDIU (A) | | MIDDLE | 1D| 429 OUTPUT 1(B) CFDIU (B) | | TOP | 2A| 429 OUTPUT 2(A) N/U | | TOP | 2B| 429 OUTPUT 2(B) N/U | | TOP | 5C| 429 INPUT 16(A) N/U | | TOP | 5D| 429 INPUT 16(B) N/U | | TOP |11C| 429 INPUT 17(A) N/U | | TOP |11D| 429 INPUT 17(B) N/U | | TOP | 3A| 453 OUTPUT 1(A) TERR DATA R1 (A) | | TOP | 3B| 453 OUTPUT 1(B) TERR DATA R1 (B) | | TOP | 3C| 453 OUTPUT 2(A) TERR DATA R2 (A) | | TOP | 3D| 453 OUTPUT 2(B) TERR DATA R2 (B) | | TOP |13A| DC ANALOG INPUT 1 (+) N/U | | TOP |13B| DC ANALOG INPUT 1 (-) N/U | | TOP |14A| DC ANALOG INPUT 2 (+) N/U | | TOP |14B| DC ANALOG INPUT 2 (-) N/U | | TOP |13C| DC ANALOG INPUT 3 (+) N/U | | TOP |13D| DC ANALOG INPUT 3 (-) N/U | | TOP |14C| DC ANALOG INPUT 4 (+) N/U | | TOP |14D| DC ANALOG INPUT 4 (-) N/U | | MIDDLE |13D| 600 OHM AUDIO OUTPUT (C) | | MIDDLE |13C| 600 OHM AUDIO OUTPUT (H) | | MIDDLE | 3C| HIGH LEVEL 8 OHM AUDIO OUTPUT (C) N/U | | MIDDLE | 3B| HIGH LEVEL 8 OHM AUDIO OUTPUT (H) N/U | | BOTTOM | 1| Optional GPS COAX CONNECTION | | MIDDLE | 3A| PROGRAM PIN COMMON | | TOP |15A| 28 VDC DISCRETE INPUT 1 N/U | | TOP |15B| 28 VDC DISCRETE INPUT 2 N/U | | TOP |15C| 28 VDC DISCRETE INPUT 3 N/U | | TOP |15D| 28 VDC DISCRETE INPUT 4 N/U | | TOP | 7A| 28 VDC DISCRETE INPUT 5 N/U | | TOP | 7B| 28 VDC DISCRETE INPUT 6 N/U | | TOP | 7C| 28 VDC DISCRETE INPUT 7 N/U | | TOP | 7D| 28 VDC DISCRETE INPUT 8 N/U | | MIDDLE |1A | GND DISCRETE INPUT 1 N/U | | MIDDLE |9C | GND DISCRETE INPUT 10 LDG FLAP | | MIDDLE |9D | GND DISCRETE INPUT 11 G/S MANUAL | | MIDDLE |14A| GND DISCRETE INPUT 12 WXR1 ON/OFF | | MIDDLE |14B| GND DISCRETE INPUT 13 TAD and TCF INHIBIT| | TOP | 1A| GND DISCRETE INPUT 15 CAPT TERR SELECTION| | TOP | 1B| GND DISCRETE INPUT 16 F/O TERR SELECTION | | MIDDLE | 2B| GND DISCRETE INPUT 17 N/U | | TOP | 4C| GND DISCRETE INPUT 18 N/U |

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--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 5D| GND DISCRETE INPUT 19 ALL AUDIO INHIBIT | | MIDDLE | 1B| GND DISCRETE INPUT 2 G/S INHIBIT | | MIDDLE | 7A| GND DISCRETE INPUT 20 N/U | | MIDDLE | 2A| GND DISCRETE INPUT 3 N/U | | MIDDLE | 5C| GND DISCRETE INPUT 4 N/U | | MIDDLE | 7D| GND DISCRETE INPUT 5 INHIBIT MODES 1 TO 5| | | | (AUDIO AND VISUAL) | | MIDDLE | 8C| GND DISCRETE INPUT 6 N/U | | MIDDLE | 8D| GND DISCRETE INPUT 7 AUDIO SUPPRESS | | | | (MOMENTARY) | | MIDDLE | 9A| GND DISCRETE INPUT 8 SELF TEST | | MIDDLE | 9B| GND DISCRETE INPUT 9 LDG GEAR | | MIDDLE |15D| GND DISCRETE OUTPUT 1 | | MIDDLE | 3D| GND DISCRETE OUTPUT 2 G/S ALERT OUTPUT | | MIDDLE | 7B| GND DISCRETE OUTPUT 3 WARNING OUTPUT | | TOP |12C| GND DISCRETE OUTPUT 4 | | TOP |12A| GND DISCRETE OUTPUT 5 | | TOP |12B| GND DISCRETE OUTPUT 6 | | TOP | 4D| GND DISCRETE OUTPUT 7 | | TOP |10D| GND DISCRETE OUTPUT 8 CAPT POP-UP OUTPUT | | MIDDLE |14C| GND DISCRETE OUTPUT 9 F/O POP-UP OUTPUT | | TOP |11A| GND DISCRETE OUTPUT 10 | | MIDDLE | 7C| DISCRETE MONITOR OUTPUT 1 GPWS MONITOR | | | | OUTPUT | | TOP |12D| DISCRETE MONITOR OUTPUT 2 TERR NOT AVAIL | | | | OUTPUT | | TOP |11B| DISCRETE MONITOR OUTPUT 3 TERRAIN MONITOR| | | | OUTPUT | | BOTTOM | 4 | CHASSIS GND | | BOTTOM | 2 | PRIMARY PWR (H) | | BOTTOM | 3 | PRIMARY PWR (L) | | TOP |10A| PROGRAM PIN 1 | | MIDDLE | 4A| PROGRAM PIN 10 | | MIDDLE | 4C| PROGRAM PIN 11 | | TOP | 5B| PROGRAM PIN 12 | | MIDDLE | 5B| PROGRAM PIN 13 | | TOP | 2C| PROGRAM PIN 14 | | MIDDLE |15C| PROGRAM PIN 15 | | MIDDLE | 8B| PROGRAM PIN 16 | | TOP | 6D| PROGRAM PIN 17 | | TOP |10B| PROGRAM PIN 2 | | TOP |10C| PROGRAM PIN 3 | | MIDDLE | 4D| PROGRAM PIN 4 | | MIDDLE | 4B| PROGRAM PIN 5 |

  R EFF : 105-105,  34-48-00 Page 99   Config-1 Nov 01/07  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 8A| PROGRAM PIN 6 | | MIDDLE |14D| PROGRAM PIN 7 | | MIDDLE | 5A| PROGRAM PIN 8 | | MIDDLE | 2C| PROGRAM PIN 9 | | TOP | 2D| OUTPUT REF 10.00 VDC | | TOP | 6C| RS232 RECEIVE | | TOP | 6B| RS232 TRANSMIT | | BOTTOM | 5 | Spare | | MIDDLE |15A| Spare | | MIDDLE |15B| Spare | --------------------------------------------------------(b) Front panel assembly The front panel assembly contains identification and modification status labels, status LEDs, a latched door for access to a SELF-TEST pushbutton switch, a HEADPHONE jack, a RS232 test connector (P1), and a Personal Computing Memory Card Interface Adapter (PCMCIA) interface and status LEDs. There is also a handle for ease of carrying and installation/removal, and a hold-down hook for securing at installation. (c) Chassis The chassis is welded aluminum, composed of a top and bottom and two sides. It provides slots for CCA and space for the front and rear panel assemblies. (d) PCMCIA interface The standard Type II PCMCIA interface provided at the front panel allows for both the uploading and downloading of internal Enhanced GPWC information. Control of the upload/download process is accomplished by insertion of the PCMCIA card into the front panel access. Four LEDs are provided for PCMCIA interface operation. The PCMCIA card does not remain installed during normal Enhanced GPWC operation, and is not intended as an on-line/inflight storage medium. (e) Front connector A 15-pin (double density, D-Sub) test connector is located on the front panel, which provides for connection to either a CRT terminal or a PC. This connector provides the following interfaces:

  R EFF : 105-105,  34-48-00 Page A0   Config-1 Nov 01/07  CES

 

1 _

Three-wire serial interface, compatible with RS232 This port can be used to access internal data from the Enhanced GPWC for both bench simulation and aircraft testing. Unit configuration and flight history can also be accessed. This port can also be used to upload software and data bases.

2 _

ARINC 429/422/423 data loader interface This port can be used to upload software and data bases. System power is provided on two of the pins for data loader use. The Enhanced GPWC front connector pins are listed in the table below (N/U means Not Used): --------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| FRONT | 8 | 429 INPUT 20(A)/422 INPUT 2(A) | | FRONT |13 | 429 INPUT 20(B)/422 INPUT 2(B) | | FRONT | 9 | 429 OUTPUT 5(A)/422 OUTPUT 2(A) | | FRONT |14 | 429 OUTPUT 5(B)/422 OUTPUT 2(B) | | FRONT | 2 | RESERVED FOR BOOT CODE LOAD N/U | | FRONT | 6 | PCMCIA BOOT ENABLE N/U | | FRONT | 11| RS422 SELECT N/U | | FRONT | 1| Ground | | FRONT | 10| POWER PIN ISOLATOR | | FRONT | 15| 115 VAC-C (OR 28 VDC-) | | FRONT | 5| 115 VAC-H (OR 28 VDC+) | | FRONT | 3| RS232 RECEIVE | | FRONT | 4| RS232 TRANSMIT | | FRONT | 7| Spare | | FRONT | 12| Spare | |FRT JACK| 1 | 600 OHM AUDIO OUTPUT (C) | |FRT JACK| 2 | 600 OHM AUDIO OUTPUT (H) | ---------------------------------------------------------

R

**ON A/C 501-509, 511-526, 528-599, A. Enhanced GPWC (1) External descrition (Ref. Fig. 008) The Enhanced GPWC is packaged in a 2 MCU ARINC 600-6 form factor enclosure. The enclosure of the unit is painted with a blue semi-gloss coating, except for the bottom, which is unpainted. The computer is composed of the following subassemblies:

  R EFF : 105-105, 501-509, 511-526, 528-599,  34-48-00 Page A1   Config-1 Feb 01/10  CES

 

-

rear panel assembly, front panel assembly, chassis, PCMCIA interface, front connector.

(a) Rear panel assembly The rear panel assembly contains a 2 MCU ARINC 600-6 form aircraft interface connector. The top and middle shells contain all interface signals. Power interface is in the bottom shell, isolated from interface signals. Connector index pin coding is orientation 08 or 10 in accordance with ARINC 723-1 recommendations for GPWS. The rear panel assembly also contains the interconnection between the aircraft interface connector and the internal interface Circuit Card Assembly (CCA), A5, and the Backplane CCA, A4, which provide all internal electrical interconnects between CCAs and other circuitry. The Enhanced GPWC pins are listed in the table below (N/U means Not Used): --------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 6A| 429 INPUT 1(A) ADIRU1 BUS IR (A) | | MIDDLE | 6B| 429 INPUT 1(B) ADIRU1 BUS IR (B) | | TOP | 9A| 429 INPUT 10(A) CFDIU (A) | | TOP | 9B| 429 INPUT 10(B) CFDIU (B) | | TOP | 8A| 429 INPUT 11(A) WXR1 HZD BUS (A) | | TOP | 8B| 429 INPUT 11(B) WXR1 HZD BUS (B) | | TOP | 8C| 429 INPUT 12(A) N/U | | TOP | 8D| 429 INPUT 12(B) N/U | | TOP | 5A| 429 INPUT 13(A) N/U | | TOP | 6A| 429 INPUT 13(B) N/U | | TOP | 1C| 429 INPUT 14(A) N/U | | TOP | 1D| 429 INPUT 14(B) N/U | | TOP | 4A| 429 INPUT 15(A) N/U | | TOP | 4B| 429 INPUT 15(B) N/U | | MIDDLE | 6C| 429 INPUT 18(A) WXR2 HZD BUS | | MIDDLE | 6D| 429 INPUT 18(B) WXR2 HZD BUS | | MIDDLE |10C| 429 INPUT 2(A) FMGC1 (A) | | MIDDLE |10D| 429 INPUT 2(B) FMGC1 (B) | | MIDDLE |11A| 429 INPUT 3(A) ADIRU 1 BUS ADR (A) | | MIDDLE |11B| 429 INPUT 3(B) ADIRU 1 BUS ADR (B) | | MIDDLE |12A| 429 INPUT 4(A) FCU 1 (A) | | MIDDLE |12B| 429 INPUT 4(B) FCU 1 (B) | | MIDDLE |10A| 429 INPUT 5(A) N/U |

  R EFF : 501-509, 511-526, 528-599,  34-48-00 Page A2   Config-1 Feb 01/10  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE |10B| 429 INPUT 5(B) N/U | | MIDDLE |11C| 429 INPUT 6(A) ILS 1 (A) | | MIDDLE |11D| 429 INPUT 6(B) ILS 1 (B) | | MIDDLE |12C| 429 INPUT 7(A) FMGC 1 DISCWORD (A) | | MIDDLE |12D| 429 INPUT 7(B) FMGC 1 DISCWORD (B) | | MIDDLE |13A| 429 INPUT 8(A) RA 1 (A) | | MIDDLE |13B| 429 INPUT 8(B) RA 1 (B) | | TOP | 9C| 429 INPUT 9(A) FCU 2 (A) | | TOP | 9D| 429 INPUT 9(B) FCU 2 (B) | | MIDDLE | 1C| 429 OUTPUT 1(A) CFDIU (A) | | MIDDLE | 1D| 429 OUTPUT 1(B) CFDIU (B) | | TOP | 2A| 429 OUTPUT 2(A) WXR1 & WXR2 AUTOTILT | | TOP | 2B| 429 OUTPUT 2(B) WXR1 & WXR2 AUTOTILT | | TOP | 5C| 429 INPUT 16(A) N/U | | TOP | 5D| 429 INPUT 16(B) N/U | | TOP |11C| 429 INPUT 17(A) GPS1 BUS | | TOP |11D| 429 INPUT 17(B) GPS1 BUS | | TOP | 3A| 453 OUTPUT 1(A) TERR DATA R1 (A) | | TOP | 3B| 453 OUTPUT 1(B) TERR DATA R1 (B) | | TOP | 3C| 453 OUTPUT 2(A) TERR DATA R2 (A) | | TOP | 3D| 453 OUTPUT 2(B) TERR DATA R2 (B) | | TOP |13A| DC ANALOG INPUT 1 (+) N/U | | TOP |13B| DC ANALOG INPUT 1 (-) N/U | | TOP |14A| DC ANALOG INPUT 2 (+) N/U | | TOP |14B| DC ANALOG INPUT 2 (-) N/U | | TOP |13C| DC ANALOG INPUT 3 (+) N/U | | TOP |13D| DC ANALOG INPUT 3 (-) N/U | | TOP |14C| DC ANALOG INPUT 4 (+) N/U | | TOP |14D| DC ANALOG INPUT 4 (-) N/U | | MIDDLE |13D| 600 OHM AUDIO OUTPUT (C) | | MIDDLE |13C| 600 OHM AUDIO OUTPUT (H) | | MIDDLE | 3C| HIGH LEVEL 8 OHM AUDIO OUTPUT (C) N/U | | MIDDLE | 3B| HIGH LEVEL 8 OHM AUDIO OUTPUT (H) N/U | | BOTTOM | 1| Optional GPS COAX CONNECTION | | MIDDLE | 3A| PROGRAM PIN COMMON | | TOP |15A| 28 VDC DISCRETE INPUT 1 N/U | | TOP |15B| 28 VDC DISCRETE INPUT 2 N/U | | TOP |15C| 28 VDC DISCRETE INPUT 3 N/U | | TOP |15D| 28 VDC DISCRETE INPUT 4 N/U | | TOP | 7A| 28 VDC DISCRETE INPUT 5 N/U | | TOP | 7B| 28 VDC DISCRETE INPUT 6 N/U | | TOP | 7C| 28 VDC DISCRETE INPUT 7 N/U | | TOP | 7D| 28 VDC DISCRETE INPUT 8 N/U | | MIDDLE |1A | GND DISCRETE INPUT 1 N/U |

  R EFF : 501-509, 511-526, 528-599,  34-48-00 Page A3   Config-1 Feb 01/10  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE |9C | GND DISCRETE INPUT 10 LDG FLAP | | MIDDLE |9D | GND DISCRETE INPUT 11 G/S MANUAL | | MIDDLE |14A| GND DISCRETE INPUT 12 WXR1 ON/OFF | | MIDDLE |14B| GND DISCRETE INPUT 13 TAD and TCF INHIBIT| | MIDDLE | 2D| GND DISCRETE INPUT 14 WXR2 ON/OFF | | TOP | 1A| GND DISCRETE INPUT 15 CAPT TERR SELECTION| | TOP | 1B| GND DISCRETE INPUT 16 F/O TERR SELECTION | | MIDDLE | 2B| GND DISCRETE INPUT 17 N/U | | TOP | 4C| GND DISCRETE INPUT 18 N/U | | MIDDLE | 5D| GND DISCRETE INPUT 19 ALL AUDIO INHIBIT | | MIDDLE | 1B| GND DISCRETE INPUT 2 G/S INHIBIT | | MIDDLE | 7A| GND DISCRETE INPUT 20 N/U | | MIDDLE | 2A| GND DISCRETE INPUT 3 N/U | | MIDDLE | 5C| GND DISCRETE INPUT 4 N/U | | MIDDLE | 7D| GND DISCRETE INPUT 5 INHIBIT MODES 1 TO 5| | | | (AUDIO AND VISUAL) | | MIDDLE | 8C| GND DISCRETE INPUT 6 N/U | | MIDDLE | 8D| GND DISCRETE INPUT 7 AUDIO SUPPRESS | | | | (MOMENTARY) | | MIDDLE | 9A| GND DISCRETE INPUT 8 SELF TEST | | MIDDLE | 9B| GND DISCRETE INPUT 9 LDG GEAR | | MIDDLE |15D| GND DISCRETE OUTPUT 1 | | MIDDLE | 3D| GND DISCRETE OUTPUT 2 G/S ALERT OUTPUT | | MIDDLE | 7B| GND DISCRETE OUTPUT 3 WARNING OUTPUT | | TOP |12C| GND DISCRETE OUTPUT 4 | | TOP |12A| GND DISCRETE OUTPUT 5 | | TOP |12B| GND DISCRETE OUTPUT 6 | | TOP | 4D| GND DISCRETE OUTPUT 7 | | TOP |10D| GND DISCRETE OUTPUT 8 CAPT POP-UP OUTPUT | | MIDDLE |14C| GND DISCRETE OUTPUT 9 F/O POP-UP OUTPUT | | TOP |11A| GND DISCRETE OUTPUT 10 | | MIDDLE | 7C| DISCRETE MONITOR OUTPUT 1 GPWS MONITOR | | | | OUTPUT | | TOP |12D| DISCRETE MONITOR OUTPUT 2 TERR NOT AVAIL | | | | OUTPUT | | TOP |11B| DISCRETE MONITOR OUTPUT 3 TERRAIN MONITOR| | | | OUTPUT | | BOTTOM | 4 | CHASSIS GND | | BOTTOM | 2 | PRIMARY PWR (H) | | BOTTOM | 3 | PRIMARY PWR (L) | | TOP |10A| PROGRAM PIN 1 | | MIDDLE | 4A| PROGRAM PIN 10 | | MIDDLE | 4C| PROGRAM PIN 11 | | TOP | 5B| PROGRAM PIN 12 |

  R EFF : 501-509, 511-526, 528-599,  34-48-00 Page A4   Config-1 Feb 01/10  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 5B| PROGRAM PIN 13 | | TOP | 2C| PROGRAM PIN 14 | | MIDDLE |15C| PROGRAM PIN 15 | | MIDDLE | 8B| PROGRAM PIN 16 | | TOP | 6D| PROGRAM PIN 17 | | TOP |10B| PROGRAM PIN 2 | | TOP |10C| PROGRAM PIN 3 | | MIDDLE | 4D| PROGRAM PIN 4 | | MIDDLE | 4B| PROGRAM PIN 5 | | MIDDLE | 8A| PROGRAM PIN 6 | | MIDDLE |14D| PROGRAM PIN 7 | | MIDDLE | 5A| PROGRAM PIN 8 | | MIDDLE | 2C| PROGRAM PIN 9 | | TOP | 2D| OUTPUT REF 10.00 VDC | | TOP | 6C| RS232 RECEIVE | | TOP | 6B| RS232 TRANSMIT | | BOTTOM | 5 | Spare | | MIDDLE |15A| Spare | | MIDDLE |15B| Spare | --------------------------------------------------------(b) Front panel assembly The front panel assembly contains identification and modification status labels, status LEDs, a latched door for access to a SELF-TEST pushbutton switch, a HEADPHONE jack, a RS232 test connector (P1), and a Personal Computing Memory Card Interface Adapter (PCMCIA) interface and status LEDs. There is also a handle for ease of carrying and installation/removal, and a hold-down hook for securing at installation. (c) Chassis The chassis is welded aluminum, composed of a top and bottom and two sides. It provides slots for CCA and space for the front and rear panel assemblies. (d) PCMCIA interface The standard Type II PCMCIA interface provided at the front panel allows for both the uploading and downloading of internal Enhanced GPWC information. Control of the upload/download process is accomplished by insertion of the PCMCIA card into the front panel access. Four LEDs are provided for PCMCIA interface operation.

  R EFF : 501-509, 511-526, 528-599,  34-48-00 Page A5   Config-1 Feb 01/10  CES

 

The PCMCIA card does not remain installed during normal Enhanced GPWC operation, and is not intended as an on-line/inflight storage medium. (e) Front connector A 15-pin (double density, D-Sub) test connector is located on the front panel, which provides for connection to either a CRT terminal or a PC. This connector provides the following interfaces: 1 _

Three-wire serial interface, compatible with RS232 This port can be used to access internal data from the Enhanced GPWC for both bench simulation and aircraft testing. Unit configuration and flight history can also be accessed. This port can also be used to upload software and data bases.

2 _

ARINC 429/422/423 data loader interface This port can be used to upload software and data bases. System power is provided on two of the pins for data loader use. The Enhanced GPWC front connector pins are listed in the table below (N/U means Not Used): --------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| FRONT | 8 | 429 INPUT 20(A)/422 INPUT 2(A) | | FRONT |13 | 429 INPUT 20(B)/422 INPUT 2(B) | | FRONT | 9 | 429 OUTPUT 5(A)/422 OUTPUT 2(A) | | FRONT |14 | 429 OUTPUT 5(B)/422 OUTPUT 2(B) | | FRONT | 2 | RESERVED FOR BOOT CODE LOAD N/U | | FRONT | 6 | PCMCIA BOOT ENABLE N/U | | FRONT | 11| RS422 SELECT N/U | | FRONT | 1| Ground | | FRONT | 10| POWER PIN ISOLATOR | | FRONT | 15| 115 VAC-C (OR 28 VDC-) | | FRONT | 5| 115 VAC-H (OR 28 VDC+) | | FRONT | 3| RS232 RECEIVE | | FRONT | 4| RS232 TRANSMIT | | FRONT | 7| Spare | | FRONT | 12| Spare | |FRT JACK| 1 | 600 OHM AUDIO OUTPUT (C) | |FRT JACK| 2 | 600 OHM AUDIO OUTPUT (H) | ---------------------------------------------------------

  R EFF : 501-509, 511-526, 528-599,  34-48-00 Page A6   Config-1 Feb 01/10  CES

 

R R

**ON A/C 001-049, 051-099, 101-104, 106-149, 151-199, 201-233, 236-238, 301-304, 401-403, A. Enhanced GPWC (1) External descrition (Ref. Fig. 008) The Enhanced GPWC is packaged in a 2 MCU ARINC 600-6 form factor enclosure. The enclosure of the unit is painted with a blue semi-gloss coating, except for the bottom, which is unpainted. The computer is composed of the following subassemblies: - rear panel assembly, - front panel assembly, - chassis, - PCMCIA interface, - front connector. (a) Rear panel assembly The rear panel assembly contains a 2 MCU ARINC 600-6 form aircraft interface connector. The top and middle shells contain all interface signals. Power interface is in the bottom shell, isolated from interface signals. Connector index pin coding is orientation 08 or 10 in accordance with ARINC 723-1 recommendations for GPWS. The rear panel assembly also contains the interconnection between the aircraft interface connector and the internal interface Circuit Card Assembly (CCA), A5, and the Backplane CCA, A4, which provide all internal electrical interconnects between CCAs and other circuitry. The Enhanced GPWC pins are listed in the table below (N/U means Not Used): --------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 6A| 429 INPUT 1(A) ADIRU1 BUS IR (A) | | MIDDLE | 6B| 429 INPUT 1(B) ADIRU1 BUS IR (B) | | TOP | 9A| 429 INPUT 10(A) CFDIU (A) | | TOP | 9B| 429 INPUT 10(B) CFDIU (B) | | TOP | 8A| 429 INPUT 11(A) WXR1 HZD BUS (A) | | TOP | 8B| 429 INPUT 11(B) WXR1 HZD BUS (B) | | TOP | 8C| 429 INPUT 12(A) N/U | | TOP | 8D| 429 INPUT 12(B) N/U | | TOP | 5A| 429 INPUT 13(A) N/U | | TOP | 6A| 429 INPUT 13(B) N/U | | TOP | 1C| 429 INPUT 14(A) N/U |

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A7 151-199, 201-233, 236-238, 301-304, 401-403,  Config-1 Feb 01/08  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| TOP | 1D| 429 INPUT 14(B) N/U | | TOP | 4A| 429 INPUT 15(A) N/U | | TOP | 4B| 429 INPUT 15(B) N/U | | MIDDLE | 6C| 429 INPUT 18(A) WXR2 HZD BUS | | MIDDLE | 6D| 429 INPUT 18(B) WXR2 HZD BUS | | MIDDLE |10C| 429 INPUT 2(A) FMGC1 (A) | | MIDDLE |10D| 429 INPUT 2(B) FMGC1 (B) | | MIDDLE |11A| 429 INPUT 3(A) ADIRU 1 BUS ADR (A) | | MIDDLE |11B| 429 INPUT 3(B) ADIRU 1 BUS ADR (B) | | MIDDLE |12A| 429 INPUT 4(A) FCU 1 (A) | | MIDDLE |12B| 429 INPUT 4(B) FCU 1 (B) | | MIDDLE |10A| 429 INPUT 5(A) N/U | | MIDDLE |10B| 429 INPUT 5(B) N/U | | MIDDLE |11C| 429 INPUT 6(A) ILS 1 (A) | | MIDDLE |11D| 429 INPUT 6(B) ILS 1 (B) | | MIDDLE |12C| 429 INPUT 7(A) FMGC 1 DISCWORD (A) | | MIDDLE |12D| 429 INPUT 7(B) FMGC 1 DISCWORD (B) | | MIDDLE |13A| 429 INPUT 8(A) RA 1 (A) | | MIDDLE |13B| 429 INPUT 8(B) RA 1 (B) | | TOP | 9C| 429 INPUT 9(A) FCU 2 (A) | | TOP | 9D| 429 INPUT 9(B) FCU 2 (B) | | MIDDLE | 1C| 429 OUTPUT 1(A) CFDIU (A) | | MIDDLE | 1D| 429 OUTPUT 1(B) CFDIU (B) | | TOP | 2A| 429 OUTPUT 2(A) N/U | | TOP | 2B| 429 OUTPUT 2(B) N/U | | TOP | 5C| 429 INPUT 16(A) N/U | | TOP | 5D| 429 INPUT 16(B) N/U | | TOP |11C| 429 INPUT 17(A) N/U | | TOP |11D| 429 INPUT 17(B) N/U | | TOP | 3A| 453 OUTPUT 1(A) TERR DATA R1 (A) | | TOP | 3B| 453 OUTPUT 1(B) TERR DATA R1 (B) | | TOP | 3C| 453 OUTPUT 2(A) TERR DATA R2 (A) | | TOP | 3D| 453 OUTPUT 2(B) TERR DATA R2 (B) | | TOP |13A| DC ANALOG INPUT 1 (+) N/U | | TOP |13B| DC ANALOG INPUT 1 (-) N/U | | TOP |14A| DC ANALOG INPUT 2 (+) N/U | | TOP |14B| DC ANALOG INPUT 2 (-) N/U | | TOP |13C| DC ANALOG INPUT 3 (+) N/U | | TOP |13D| DC ANALOG INPUT 3 (-) N/U | | TOP |14C| DC ANALOG INPUT 4 (+) N/U | | TOP |14D| DC ANALOG INPUT 4 (-) N/U | | MIDDLE |13D| 600 OHM AUDIO OUTPUT (C) | | MIDDLE |13C| 600 OHM AUDIO OUTPUT (H) | | MIDDLE | 3C| HIGH LEVEL 8 OHM AUDIO OUTPUT (C) N/U |

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A8 151-199, 201-233, 236-238, 301-304, 401-403,  Config-1 Feb 01/08  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 3B| HIGH LEVEL 8 OHM AUDIO OUTPUT (H) N/U | | BOTTOM | 1| Optional GPS COAX CONNECTION | | MIDDLE | 3A| PROGRAM PIN COMMON | | TOP |15A| 28 VDC DISCRETE INPUT 1 N/U | | TOP |15B| 28 VDC DISCRETE INPUT 2 N/U | | TOP |15C| 28 VDC DISCRETE INPUT 3 N/U | | TOP |15D| 28 VDC DISCRETE INPUT 4 N/U | | TOP | 7A| 28 VDC DISCRETE INPUT 5 N/U | | TOP | 7B| 28 VDC DISCRETE INPUT 6 N/U | | TOP | 7C| 28 VDC DISCRETE INPUT 7 N/U | | TOP | 7D| 28 VDC DISCRETE INPUT 8 N/U | | MIDDLE |1A | GND DISCRETE INPUT 1 N/U | | MIDDLE |9C | GND DISCRETE INPUT 10 LDG FLAP | | MIDDLE |9D | GND DISCRETE INPUT 11 G/S MANUAL | | MIDDLE |14A| GND DISCRETE INPUT 12 WXR1 ON/OFF | | MIDDLE |14B| GND DISCRETE INPUT 13 TAD and TCF INHIBIT| | MIDDLE | 2D| GND DISCRETE INPUT 14 WXR2 ON/OFF | | TOP | 1A| GND DISCRETE INPUT 15 CAPT TERR SELECTION| | TOP | 1B| GND DISCRETE INPUT 16 F/O TERR SELECTION | | MIDDLE | 2B| GND DISCRETE INPUT 17 N/U | | TOP | 4C| GND DISCRETE INPUT 18 N/U | | MIDDLE | 5D| GND DISCRETE INPUT 19 ALL AUDIO INHIBIT | | MIDDLE | 1B| GND DISCRETE INPUT 2 G/S INHIBIT | | MIDDLE | 7A| GND DISCRETE INPUT 20 N/U | | MIDDLE | 2A| GND DISCRETE INPUT 3 N/U | | MIDDLE | 5C| GND DISCRETE INPUT 4 N/U | | MIDDLE | 7D| GND DISCRETE INPUT 5 INHIBIT MODES 1 TO 5| | | | (AUDIO AND VISUAL) | | MIDDLE | 8C| GND DISCRETE INPUT 6 N/U | | MIDDLE | 8D| GND DISCRETE INPUT 7 AUDIO SUPPRESS | | | | (MOMENTARY) | | MIDDLE | 9A| GND DISCRETE INPUT 8 SELF TEST | | MIDDLE | 9B| GND DISCRETE INPUT 9 LDG GEAR | | MIDDLE |15D| GND DISCRETE OUTPUT 1 | | MIDDLE | 3D| GND DISCRETE OUTPUT 2 G/S ALERT OUTPUT | | MIDDLE | 7B| GND DISCRETE OUTPUT 3 WARNING OUTPUT | | TOP |12C| GND DISCRETE OUTPUT 4 | | TOP |12A| GND DISCRETE OUTPUT 5 | | TOP |12B| GND DISCRETE OUTPUT 6 | | TOP | 4D| GND DISCRETE OUTPUT 7 | | TOP |10D| GND DISCRETE OUTPUT 8 CAPT POP-UP OUTPUT | | MIDDLE |14C| GND DISCRETE OUTPUT 9 F/O POP-UP OUTPUT | | TOP |11A| GND DISCRETE OUTPUT 10 | | MIDDLE | 7C| DISCRETE MONITOR OUTPUT 1 GPWS MONITOR |

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A9 151-199, 201-233, 236-238, 301-304, 401-403,  Config-1 Feb 01/08  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| | | OUTPUT | | TOP |12D| DISCRETE MONITOR OUTPUT 2 TERR NOT AVAIL | | | | OUTPUT | | TOP |11B| DISCRETE MONITOR OUTPUT 3 TERRAIN MONITOR| | | | OUTPUT | | BOTTOM | 4 | CHASSIS GND | | BOTTOM | 2 | PRIMARY PWR (H) | | BOTTOM | 3 | PRIMARY PWR (L) | | TOP |10A| PROGRAM PIN 1 | | MIDDLE | 4A| PROGRAM PIN 10 | | MIDDLE | 4C| PROGRAM PIN 11 | | TOP | 5B| PROGRAM PIN 12 | | MIDDLE | 5B| PROGRAM PIN 13 | | TOP | 2C| PROGRAM PIN 14 | | MIDDLE |15C| PROGRAM PIN 15 | | MIDDLE | 8B| PROGRAM PIN 16 | | TOP | 6D| PROGRAM PIN 17 | | TOP |10B| PROGRAM PIN 2 | | TOP |10C| PROGRAM PIN 3 | | MIDDLE | 4D| PROGRAM PIN 4 | | MIDDLE | 4B| PROGRAM PIN 5 | | MIDDLE | 8A| PROGRAM PIN 6 | | MIDDLE |14D| PROGRAM PIN 7 | | MIDDLE | 5A| PROGRAM PIN 8 | | MIDDLE | 2C| PROGRAM PIN 9 | | TOP | 2D| OUTPUT REF 10.00 VDC | | TOP | 6C| RS232 RECEIVE | | TOP | 6B| RS232 TRANSMIT | | BOTTOM | 5 | Spare | | MIDDLE |15A| Spare | | MIDDLE |15B| Spare | --------------------------------------------------------(b) Front panel assembly The front panel assembly contains identification and modification status labels, status LEDs, a latched door for access to a SELF-TEST pushbutton switch, a HEADPHONE jack, a RS232 test connector (P1), and a Personal Computing Memory Card Interface Adapter (PCMCIA) interface and status LEDs. There is also a handle for ease of carrying and installation/removal, and a hold-down hook for securing at installation.

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A10 151-199, 201-233, 236-238, 301-304, 401-403,  Config-1 Feb 01/08  CES

 

(c) Chassis The chassis is welded aluminum, composed of a top and bottom and two sides. It provides slots for CCA and space for the front and rear panel assemblies. (d) PCMCIA interface The standard Type II PCMCIA interface provided at the front panel allows for both the uploading and downloading of internal Enhanced GPWC information. Control of the upload/download process is accomplished by insertion of the PCMCIA card into the front panel access. Four LEDs are provided for PCMCIA interface operation. The PCMCIA card does not remain installed during normal Enhanced GPWC operation, and is not intended as an on-line/inflight storage medium. (e) Front connector A 15-pin (double density, D-Sub) test connector is located on the front panel, which provides for connection to either a CRT terminal or a PC. This connector provides the following interfaces: 1 _

Three-wire serial interface, compatible with RS232 This port can be used to access internal data from the Enhanced GPWC for both bench simulation and aircraft testing. Unit configuration and flight history can also be accessed. This port can also be used to upload software and data bases.

2 _

ARINC 429/422/423 data loader interface This port can be used to upload software and data bases. System power is provided on two of the pins for data loader use. The Enhanced GPWC front connector pins are listed in the table below (N/U means Not Used): --------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| FRONT | 8 | 429 INPUT 20(A)/422 INPUT 2(A) | | FRONT |13 | 429 INPUT 20(B)/422 INPUT 2(B) | | FRONT | 9 | 429 OUTPUT 5(A)/422 OUTPUT 2(A) | | FRONT |14 | 429 OUTPUT 5(B)/422 OUTPUT 2(B) | | FRONT | 2 | RESERVED FOR BOOT CODE LOAD N/U | | FRONT | 6 | PCMCIA BOOT ENABLE N/U | | FRONT | 11| RS422 SELECT N/U | | FRONT | 1| Ground | | FRONT | 10| POWER PIN ISOLATOR |

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A11 151-199, 201-233, 236-238, 301-304, 401-403,  Config-1 Feb 01/08  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| FRONT | 15| 115 VAC-C (OR 28 VDC-) | | FRONT | 5| 115 VAC-H (OR 28 VDC+) | | FRONT | 3| RS232 RECEIVE | | FRONT | 4| RS232 TRANSMIT | | FRONT | 7| Spare | | FRONT | 12| Spare | |FRT JACK| 1 | 600 OHM AUDIO OUTPUT (C) | |FRT JACK| 2 | 600 OHM AUDIO OUTPUT (H) | --------------------------------------------------------R R

**ON A/C 001-049, 051-099, 101-104, 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, Post SB 34-1352 For A/C 001-049,051-099,101-104,106-149,151-199,201-233, 236-238,301-304,401-403, A. Enhanced GPWC (1) External descrition (Ref. Fig. 008) The Enhanced GPWC is packaged in a 2 MCU ARINC 600-6 form factor enclosure. The enclosure of the unit is painted with a blue semi-gloss coating, except for the bottom, which is unpainted. The computer is composed of the following subassemblies: - rear panel assembly, - front panel assembly, - chassis, - PCMCIA interface, - front connector. (a) Rear panel assembly The rear panel assembly contains a 2 MCU ARINC 600-6 form aircraft interface connector. The top and middle shells contain all interface signals. Power interface is in the bottom shell, isolated from interface signals. Connector index pin coding is orientation 08 or 10 in accordance with ARINC 723-1 recommendations for GPWS. The rear panel assembly also contains the interconnection between the aircraft interface connector and the internal interface Circuit Card Assembly (CCA), A5, and the Backplane CCA, A4, which provide all internal electrical interconnects between CCAs and other circuitry. The Enhanced GPWC pins are listed in the table below (N/U means Not Used):

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A12 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Nov 01/09  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 6A| 429 INPUT 1(A) ADIRU1 BUS IR (A) | | MIDDLE | 6B| 429 INPUT 1(B) ADIRU1 BUS IR (B) | | TOP | 9A| 429 INPUT 10(A) CFDIU (A) | | TOP | 9B| 429 INPUT 10(B) CFDIU (B) | | TOP | 8A| 429 INPUT 11(A) WXR1 HZD BUS (A) | | TOP | 8B| 429 INPUT 11(B) WXR1 HZD BUS (B) | | TOP | 8C| 429 INPUT 12(A) N/U | | TOP | 8D| 429 INPUT 12(B) N/U | | TOP | 5A| 429 INPUT 13(A) N/U | | TOP | 6A| 429 INPUT 13(B) N/U | | TOP | 1C| 429 INPUT 14(A) N/U | | TOP | 1D| 429 INPUT 14(B) N/U | | TOP | 4A| 429 INPUT 15(A) N/U | | TOP | 4B| 429 INPUT 15(B) N/U | | MIDDLE | 6C| 429 INPUT 18(A) WXR2 HZD BUS | | MIDDLE | 6D| 429 INPUT 18(B) WXR2 HZD BUS | | MIDDLE |10C| 429 INPUT 2(A) FMGC1 (A) | | MIDDLE |10D| 429 INPUT 2(B) FMGC1 (B) | | MIDDLE |11A| 429 INPUT 3(A) ADIRU 1 BUS ADR (A) | | MIDDLE |11B| 429 INPUT 3(B) ADIRU 1 BUS ADR (B) | | MIDDLE |12A| 429 INPUT 4(A) FCU 1 (A) | | MIDDLE |12B| 429 INPUT 4(B) FCU 1 (B) | | MIDDLE |10A| 429 INPUT 5(A) N/U | | MIDDLE |10B| 429 INPUT 5(B) N/U | | MIDDLE |11C| 429 INPUT 6(A) ILS 1 (A) | | MIDDLE |11D| 429 INPUT 6(B) ILS 1 (B) | | MIDDLE |12C| 429 INPUT 7(A) FMGC 1 DISCWORD (A) | | MIDDLE |12D| 429 INPUT 7(B) FMGC 1 DISCWORD (B) | | MIDDLE |13A| 429 INPUT 8(A) RA 1 (A) | | MIDDLE |13B| 429 INPUT 8(B) RA 1 (B) | | TOP | 9C| 429 INPUT 9(A) FCU 2 (A) | | TOP | 9D| 429 INPUT 9(B) FCU 2 (B) | | MIDDLE | 1C| 429 OUTPUT 1(A) CFDIU (A) | | MIDDLE | 1D| 429 OUTPUT 1(B) CFDIU (B) | | TOP | 2A| 429 OUTPUT 2(A) N/U | | TOP | 2B| 429 OUTPUT 2(B) N/U | | TOP | 5C| 429 INPUT 16(A) N/U | | TOP | 5D| 429 INPUT 16(B) N/U | | TOP |11C| 429 INPUT 17(A) GPS1 BUS | | TOP |11D| 429 INPUT 17(B) GPS1 BUS | | TOP | 3A| 453 OUTPUT 1(A) TERR DATA R1 (A) | | TOP | 3B| 453 OUTPUT 1(B) TERR DATA R1 (B) | | TOP | 3C| 453 OUTPUT 2(A) TERR DATA R2 (A) | | TOP | 3D| 453 OUTPUT 2(B) TERR DATA R2 (B) |

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A13 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Nov 01/09  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| TOP |13A| DC ANALOG INPUT 1 (+) N/U | | TOP |13B| DC ANALOG INPUT 1 (-) N/U | | TOP |14A| DC ANALOG INPUT 2 (+) N/U | | TOP |14B| DC ANALOG INPUT 2 (-) N/U | | TOP |13C| DC ANALOG INPUT 3 (+) N/U | | TOP |13D| DC ANALOG INPUT 3 (-) N/U | | TOP |14C| DC ANALOG INPUT 4 (+) N/U | | TOP |14D| DC ANALOG INPUT 4 (-) N/U | | MIDDLE |13D| 600 OHM AUDIO OUTPUT (C) | | MIDDLE |13C| 600 OHM AUDIO OUTPUT (H) | | MIDDLE | 3C| HIGH LEVEL 8 OHM AUDIO OUTPUT (C) N/U | | MIDDLE | 3B| HIGH LEVEL 8 OHM AUDIO OUTPUT (H) N/U | | BOTTOM | 1| Optional GPS COAX CONNECTION | | MIDDLE | 3A| PROGRAM PIN COMMON | | TOP |15A| 28 VDC DISCRETE INPUT 1 N/U | | TOP |15B| 28 VDC DISCRETE INPUT 2 N/U | | TOP |15C| 28 VDC DISCRETE INPUT 3 N/U | | TOP |15D| 28 VDC DISCRETE INPUT 4 N/U | | TOP | 7A| 28 VDC DISCRETE INPUT 5 N/U | | TOP | 7B| 28 VDC DISCRETE INPUT 6 N/U | | TOP | 7C| 28 VDC DISCRETE INPUT 7 N/U | | TOP | 7D| 28 VDC DISCRETE INPUT 8 N/U | | MIDDLE |1A | GND DISCRETE INPUT 1 N/U | | MIDDLE |9C | GND DISCRETE INPUT 10 LDG FLAP | | MIDDLE |9D | GND DISCRETE INPUT 11 G/S MANUAL | | MIDDLE |14A| GND DISCRETE INPUT 12 WXR1 ON/OFF | | MIDDLE |14B| GND DISCRETE INPUT 13 TAD and TCF INHIBIT| | MIDDLE | 2D| GND DISCRETE INPUT 14 WXR2 ON/OFF | | TOP | 1A| GND DISCRETE INPUT 15 CAPT TERR SELECTION| | TOP | 1B| GND DISCRETE INPUT 16 F/O TERR SELECTION | | MIDDLE | 2B| GND DISCRETE INPUT 17 N/U | | TOP | 4C| GND DISCRETE INPUT 18 N/U | | MIDDLE | 5D| GND DISCRETE INPUT 19 ALL AUDIO INHIBIT | | MIDDLE | 1B| GND DISCRETE INPUT 2 G/S INHIBIT | | MIDDLE | 7A| GND DISCRETE INPUT 20 N/U | | MIDDLE | 2A| GND DISCRETE INPUT 3 N/U | | MIDDLE | 5C| GND DISCRETE INPUT 4 N/U | | MIDDLE | 7D| GND DISCRETE INPUT 5 INHIBIT MODES 1 TO 5| | | | (AUDIO AND VISUAL) | | MIDDLE | 8C| GND DISCRETE INPUT 6 N/U | | MIDDLE | 8D| GND DISCRETE INPUT 7 AUDIO SUPPRESS | | | | (MOMENTARY) | | MIDDLE | 9A| GND DISCRETE INPUT 8 SELF TEST | | MIDDLE | 9B| GND DISCRETE INPUT 9 LDG GEAR |

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A14 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Nov 01/09  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE |15D| GND DISCRETE OUTPUT 1 | | MIDDLE | 3D| GND DISCRETE OUTPUT 2 G/S ALERT OUTPUT | | MIDDLE | 7B| GND DISCRETE OUTPUT 3 WARNING OUTPUT | | TOP |12C| GND DISCRETE OUTPUT 4 | | TOP |12A| GND DISCRETE OUTPUT 5 | | TOP |12B| GND DISCRETE OUTPUT 6 | | TOP | 4D| GND DISCRETE OUTPUT 7 | | TOP |10D| GND DISCRETE OUTPUT 8 CAPT POP-UP OUTPUT | | MIDDLE |14C| GND DISCRETE OUTPUT 9 F/O POP-UP OUTPUT | | TOP |11A| GND DISCRETE OUTPUT 10 | | MIDDLE | 7C| DISCRETE MONITOR OUTPUT 1 GPWS MONITOR | | | | OUTPUT | | TOP |12D| DISCRETE MONITOR OUTPUT 2 TERR NOT AVAIL | | | | OUTPUT | | TOP |11B| DISCRETE MONITOR OUTPUT 3 TERRAIN MONITOR| | | | OUTPUT | | BOTTOM | 4 | CHASSIS GND | | BOTTOM | 2 | PRIMARY PWR (H) | | BOTTOM | 3 | PRIMARY PWR (L) | | TOP |10A| PROGRAM PIN 1 | | MIDDLE | 4A| PROGRAM PIN 10 | | MIDDLE | 4C| PROGRAM PIN 11 | | TOP | 5B| PROGRAM PIN 12 | | MIDDLE | 5B| PROGRAM PIN 13 | | TOP | 2C| PROGRAM PIN 14 | | MIDDLE |15C| PROGRAM PIN 15 | | MIDDLE | 8B| PROGRAM PIN 16 | | TOP | 6D| PROGRAM PIN 17 | | TOP |10B| PROGRAM PIN 2 | | TOP |10C| PROGRAM PIN 3 | | MIDDLE | 4D| PROGRAM PIN 4 | | MIDDLE | 4B| PROGRAM PIN 5 | | MIDDLE | 8A| PROGRAM PIN 6 | | MIDDLE |14D| PROGRAM PIN 7 | | MIDDLE | 5A| PROGRAM PIN 8 | | MIDDLE | 2C| PROGRAM PIN 9 | | TOP | 2D| OUTPUT REF 10.00 VDC | | TOP | 6C| RS232 RECEIVE | | TOP | 6B| RS232 TRANSMIT | | BOTTOM | 5 | Spare | | MIDDLE |15A| Spare | | MIDDLE |15B| Spare | ---------------------------------------------------------

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A15 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Nov 01/09  CES

 

(b) Front panel assembly The front panel assembly contains identification and modification status labels, status LEDs, a latched door for access to a SELF-TEST pushbutton switch, a HEADPHONE jack, a RS232 test connector (P1), and a Personal Computing Memory Card Interface Adapter (PCMCIA) interface and status LEDs. There is also a handle for ease of carrying and installation/removal, and a hold-down hook for securing at installation. (c) Chassis The chassis is welded aluminum, composed of a top and bottom and two sides. It provides slots for CCA and space for the front and rear panel assemblies. (d) PCMCIA interface The standard Type II PCMCIA interface provided at the front panel allows for both the uploading and downloading of internal Enhanced GPWC information. Control of the upload/download process is accomplished by insertion of the PCMCIA card into the front panel access. Four LEDs are provided for PCMCIA interface operation. The PCMCIA card does not remain installed during normal Enhanced GPWC operation, and is not intended as an on-line/inflight storage medium. (e) Front connector A 15-pin (double density, D-Sub) test connector is located on the front panel, which provides for connection to either a CRT terminal or a PC. This connector provides the following interfaces: 1 _

Three-wire serial interface, compatible with RS232 This port can be used to access internal data from the Enhanced GPWC for both bench simulation and aircraft testing. Unit configuration and flight history can also be accessed. This port can also be used to upload software and data bases.

2 _

ARINC 429/422/423 data loader interface This port can be used to upload software and data bases. System power is provided on two of the pins for data loader use. The Enhanced GPWC front connector pins are listed in the table below (N/U means Not Used):

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A16 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Nov 01/09  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| FRONT | 8 | 429 INPUT 20(A)/422 INPUT 2(A) | | FRONT |13 | 429 INPUT 20(B)/422 INPUT 2(B) | | FRONT | 9 | 429 OUTPUT 5(A)/422 OUTPUT 2(A) | | FRONT |14 | 429 OUTPUT 5(B)/422 OUTPUT 2(B) | | FRONT | 2 | RESERVED FOR BOOT CODE LOAD N/U | | FRONT | 6 | PCMCIA BOOT ENABLE N/U | | FRONT | 11| RS422 SELECT N/U | | FRONT | 1| Ground | | FRONT | 10| POWER PIN ISOLATOR | | FRONT | 15| 115 VAC-C (OR 28 VDC-) | | FRONT | 5| 115 VAC-H (OR 28 VDC+) | | FRONT | 3| RS232 RECEIVE | | FRONT | 4| RS232 TRANSMIT | | FRONT | 7| Spare | | FRONT | 12| Spare | |FRT JACK| 1 | 600 OHM AUDIO OUTPUT (C) | |FRT JACK| 2 | 600 OHM AUDIO OUTPUT (H) | --------------------------------------------------------**ON A/C 105-105, Post SB

34-1352 For A/C 105-105,

A. Enhanced GPWC (1) External descrition (Ref. Fig. 008) The Enhanced GPWC is packaged in a 2 MCU ARINC 600-6 form factor enclosure. The enclosure of the unit is painted with a blue semi-gloss coating, except for the bottom, which is unpainted. The computer is composed of the following subassemblies: - rear panel assembly, - front panel assembly, - chassis, - PCMCIA interface, - front connector. (a) Rear panel assembly The rear panel assembly contains a 2 MCU ARINC 600-6 form aircraft interface connector. The top and middle shells contain all interface signals. Power interface is in the bottom shell, isolated from interface signals. Connector index pin coding is

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page A17 201-249, 251-299, 301-399, 401-499,  Config-1 Nov 01/09  CES

 

orientation 08 or 10 in accordance with ARINC 723-1 recommendations for GPWS. The rear panel assembly also contains the interconnection between the aircraft interface connector and the internal interface Circuit Card Assembly (CCA), A5, and the Backplane CCA, A4, which provide all internal electrical interconnects between CCAs and other circuitry. The Enhanced GPWC pins are listed in the table below (N/U means Not Used): --------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 6A| 429 INPUT 1(A) ADIRU1 BUS IR (A) | | MIDDLE | 6B| 429 INPUT 1(B) ADIRU1 BUS IR (B) | | TOP | 9A| 429 INPUT 10(A) CFDIU (A) | | TOP | 9B| 429 INPUT 10(B) CFDIU (B) | | TOP | 8A| 429 INPUT 11(A) WXR1 HZD BUS (A) | | TOP | 8B| 429 INPUT 11(B) WXR1 HZD BUS (B) | | TOP | 8C| 429 INPUT 12(A) N/U | | TOP | 8D| 429 INPUT 12(B) N/U | | TOP | 5A| 429 INPUT 13(A) N/U | | TOP | 6A| 429 INPUT 13(B) N/U | | TOP | 1C| 429 INPUT 14(A) N/U | | TOP | 1D| 429 INPUT 14(B) N/U | | TOP | 4A| 429 INPUT 15(A) N/U | | TOP | 4B| 429 INPUT 15(B) N/U | | MIDDLE | 6C| 429 INPUT 18(A) WXR2 HZD BUS | | MIDDLE | 6D| 429 INPUT 18(B) WXR2 HZD BUS | | MIDDLE |10C| 429 INPUT 2(A) FMGC1 (A) | | MIDDLE |10D| 429 INPUT 2(B) FMGC1 (B) | | MIDDLE |11A| 429 INPUT 3(A) ADIRU 1 BUS ADR (A) | | MIDDLE |11B| 429 INPUT 3(B) ADIRU 1 BUS ADR (B) | | MIDDLE |12A| 429 INPUT 4(A) FCU 1 (A) | | MIDDLE |12B| 429 INPUT 4(B) FCU 1 (B) | | MIDDLE |10A| 429 INPUT 5(A) N/U | | MIDDLE |10B| 429 INPUT 5(B) N/U | | MIDDLE |11C| 429 INPUT 6(A) ILS 1 (A) | | MIDDLE |11D| 429 INPUT 6(B) ILS 1 (B) | | MIDDLE |12C| 429 INPUT 7(A) FMGC 1 (A) | | MIDDLE |12D| 429 INPUT 7(B) FMGC 1 (B) | | MIDDLE |13A| 429 INPUT 8(A) RA 1 (A) | | MIDDLE |13B| 429 INPUT 8(B) RA 1 (B) | | TOP | 9C| 429 INPUT 9(A) FCU 2 (A) | | TOP | 9D| 429 INPUT 9(B) FCU 2 (B) | | MIDDLE | 1C| 429 OUTPUT 1(A) CFDIU (A) | | MIDDLE | 1D| 429 OUTPUT 1(B) CFDIU (B) |

  R EFF : 105-105,  34-48-00 Page A18   Config-1 Feb 01/08  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| TOP | 2A| 429 OUTPUT 2(A) N/U | | TOP | 2B| 429 OUTPUT 2(B) N/U | | TOP | 5C| 429 INPUT 16(A) N/U | | TOP | 5D| 429 INPUT 16(B) N/U | | TOP |11C| 429 INPUT 17(A) GPS1 BUS | | TOP |11D| 429 INPUT 17(B) GPS1 BUS | | TOP | 3A| 453 OUTPUT 1(A) TERR DATA R1 (A) | | TOP | 3B| 453 OUTPUT 1(B) TERR DATA R1 (B) | | TOP | 3C| 453 OUTPUT 2(A) TERR DATA R2 (A) | | TOP | 3D| 453 OUTPUT 2(B) TERR DATA R2 (B) | | TOP |13A| DC ANALOG INPUT 1 (+) N/U | | TOP |13B| DC ANALOG INPUT 1 (-) N/U | | TOP |14A| DC ANALOG INPUT 2 (+) N/U | | TOP |14B| DC ANALOG INPUT 2 (-) N/U | | TOP |13C| DC ANALOG INPUT 3 (+) N/U | | TOP |13D| DC ANALOG INPUT 3 (-) N/U | | TOP |14C| DC ANALOG INPUT 4 (+) N/U | | TOP |14D| DC ANALOG INPUT 4 (-) N/U | | MIDDLE |13D| 600 OHM AUDIO OUTPUT (C) | | MIDDLE |13C| 600 OHM AUDIO OUTPUT (H) | | MIDDLE | 3C| HIGH LEVEL 8 OHM AUDIO OUTPUT (C) N/U | | MIDDLE | 3B| HIGH LEVEL 8 OHM AUDIO OUTPUT (H) N/U | | BOTTOM | 1| Optional GPS COAX CONNECTION | | MIDDLE | 3A| PROGRAM PIN COMMON | | TOP |15A| 28 VDC DISCRETE INPUT 1 N/U | | TOP |15B| 28 VDC DISCRETE INPUT 2 N/U | | TOP |15C| 28 VDC DISCRETE INPUT 3 N/U | | TOP |15D| 28 VDC DISCRETE INPUT 4 N/U | | TOP | 7A| 28 VDC DISCRETE INPUT 5 N/U | | TOP | 7B| 28 VDC DISCRETE INPUT 6 N/U | | TOP | 7C| 28 VDC DISCRETE INPUT 7 N/U | | TOP | 7D| 28 VDC DISCRETE INPUT 8 N/U | | MIDDLE |1A | GND DISCRETE INPUT 1 N/U | | MIDDLE |9C | GND DISCRETE INPUT 10 LDG FLAP | | MIDDLE |9D | GND DISCRETE INPUT 11 G/S MANUAL | | MIDDLE |14A| GND DISCRETE INPUT 12 WXR1 ON/OFF | | MIDDLE |14B| GND DISCRETE INPUT 13 TAD and TCF INHIBIT| | MIDDLE | 2D| GND DISCRETE INPUT 14 WXR2 ON/OFF | | TOP | 1A| GND DISCRETE INPUT 15 F/O TERR SELECTION | | TOP | 1B| GND DISCRETE INPUT 16 CAPT TERR SELECTION| | MIDDLE | 2B| GND DISCRETE INPUT 17 N/U | | TOP | 4C| GND DISCRETE INPUT 18 RAAS ENABLE | | MIDDLE | 5D| GND DISCRETE INPUT 19 ALL AUDIO INHIBIT | | MIDDLE | 1B| GND DISCRETE INPUT 2 G/S INHIBIT |

  R EFF : 105-105,  34-48-00 Page A19   Config-1 Feb 01/08  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 7A| GND DISCRETE INPUT 20 N/U | | MIDDLE | 2A| GND DISCRETE INPUT 3 N/U | | MIDDLE | 5C| GND DISCRETE INPUT 4 N/U | | MIDDLE | 7D| GND DISCRETE INPUT 5 INHIBIT MODES 1 TO 5| | | | (AUDIO AND VISUAL) | | MIDDLE | 8C| GND DISCRETE INPUT 6 N/U | | MIDDLE | 8D| GND DISCRETE INPUT 7 AUDIO SUPPRESS | | | | (MOMENTARY) | | MIDDLE | 9A| GND DISCRETE INPUT 8 SELF TEST | | MIDDLE | 9B| GND DISCRETE INPUT 9 LDG GEAR | | MIDDLE |15D| GND DISCRETE OUTPUT 1 G/S OFF LAMP | | MIDDLE | 3D| GND DISCRETE OUTPUT 2 GPWS ALERT OUTPUT | | MIDDLE | 7B| GND DISCRETE OUTPUT 3 PULL UP WARNG OUTPT| | TOP |12C| GND DISCRETE OUTPUT 4 | | TOP |12A| GND DISCRETE OUTPUT 5 | | TOP |12B| GND DISCRETE OUTPUT 6 | | TOP | 4D| GND DISCRETE OUTPUT 7 | | TOP |10D| GND DISCRETE OUTPUT 8 CAPT POP-UP OUTPUT | | MIDDLE |14C| GND DISCRETE OUTPUT 9 F/O POP-UP OUTPUT | | TOP |11A| GND DISCRETE OUTPUT 10 | | MIDDLE | 7C| DISCRETE MONITOR OUTPUT 1 GPWS MONITOR | | | | OUTPUT | | TOP |12D| DISCRETE MONITOR OUTPUT 2 TERR NOT AVAIL | | | | OUTPUT | | TOP |11B| DISCRETE MONITOR OUTPUT 3 TERRAIN MONITOR| | | | OUTPUT | | BOTTOM | 4 | CHASSIS GND | | BOTTOM | 2 | PRIMARY PWR (H) | | BOTTOM | 3 | PRIMARY PWR (L) | | TOP |10A| PROGRAM PIN 1 | | MIDDLE | 4A| PROGRAM PIN 10 | | MIDDLE | 4C| PROGRAM PIN 11 | | TOP | 5B| PROGRAM PIN 12 | | MIDDLE | 5B| PROGRAM PIN 13 | | TOP | 2C| PROGRAM PIN 14 | | MIDDLE |15C| PROGRAM PIN 15 | | MIDDLE | 8B| PROGRAM PIN 16 | | TOP | 6D| PROGRAM PIN 17 | | TOP |10B| PROGRAM PIN 2 | | TOP |10C| PROGRAM PIN 3 | | MIDDLE | 4D| PROGRAM PIN 4 | | MIDDLE | 4B| PROGRAM PIN 5 | | MIDDLE | 8A| PROGRAM PIN 6 | | MIDDLE |14D| PROGRAM PIN 7 |

  R EFF : 105-105,  34-48-00 Page A20   Config-1 Feb 01/08  CES

 

--------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| MIDDLE | 5A| PROGRAM PIN 8 | | MIDDLE | 2C| PROGRAM PIN 9 | | TOP | 2D| OUTPUT REF 10.00 VDC | | TOP | 6C| RS232 RECEIVE | | TOP | 6B| RS232 TRANSMIT | | BOTTOM | 5 | Spare | | MIDDLE |15A| PROGRAM PIN 18 | | MIDDLE |15B| PROGRAM PIN 1 | --------------------------------------------------------(b) Front panel assembly The front panel assembly contains identification and modification status labels, status LEDs, a latched door for access to a SELF-TEST pushbutton switch, a HEADPHONE jack, a RS232 test connector (P1), and a Personal Computing Memory Card Interface Adapter (PCMCIA) interface and status LEDs. There is also a handle for ease of carrying and installation/removal, and a hold-down hook for securing at installation. (c) Chassis The chassis is welded aluminum, composed of a top and bottom and two sides. It provides slots for CCA and space for the front and rear panel assemblies. (d) PCMCIA interface The standard Type II PCMCIA interface provided at the front panel allows for both the uploading and downloading of internal Enhanced GPWC information. Control of the upload/download process is accomplished by insertion of the PCMCIA card into the front panel access. Four LEDs are provided for PCMCIA interface operation. The PCMCIA card does not remain installed during normal Enhanced GPWC operation, and is not intended as an on-line/inflight storage medium. (e) Front connector A 15-pin (double density, D-Sub) test connector is located on the front panel, which provides for connection to either a CRT terminal or a PC. This connector provides the following interfaces: 1 _

Three-wire serial interface, compatible with RS232 This port can be used to access internal data from the Enhanced GPWC for both bench simulation and aircraft testing.

  R EFF : 105-105,  34-48-00 Page A21   Config-1 Feb 01/08  CES

 

Unit configuration and flight history can also be accessed. This port can also be used to upload software and data bases. 2 _

ARINC 429/422/423 data loader interface This port can be used to upload software and data bases. System power is provided on two of the pins for data loader use. The Enhanced GPWC front connector pins are listed in the table below (N/U means Not Used): --------------------------------------------------------|LRU Con |Pin| Description | --------------------------------------------------------| FRONT | 8 | 429 INPUT 20(A)/422 INPUT 2(A) | | FRONT |13 | 429 INPUT 20(B)/422 INPUT 2(B) | | FRONT | 9 | 429 OUTPUT 5(A)/422 OUTPUT 2(A) | | FRONT |14 | 429 OUTPUT 5(B)/422 OUTPUT 2(B) | | FRONT | 2 | RESERVED FOR BOOT CODE LOAD N/U | | FRONT | 6 | PCMCIA BOOT ENABLE N/U | | FRONT | 11| Spare | | FRONT | 1| Ground | | FRONT | 10| Spare | | FRONT | 15| Spare | | FRONT | 5| Spare | | FRONT | 3| RS232 RECEIVE | | FRONT | 4| RS232 TRANSMIT | | FRONT | 7| Spare | | FRONT | 12| Spare | |FRT JACK| 1 | 600 OHM AUDIO OUTPUT (C) | |FRT JACK| 2 | 600 OHM AUDIO OUTPUT (H) | ---------------------------------------------------------

R

**ON A/C ALL (2) Internal Description (Ref. Fig. 009) (a) The hardware consists of three main circuit card assemblies: - the controller card, - the accessory card, - the analog acquisition card. 1 _

The controller card contains the main processor (microprocessor 486DX4), the Digital Information Transfer System (DITS) handler microcontroller and the image generator DSP.

  R EFF : ALL  34-48-00 Page A22   Config-1 Nov 01/09  CES

 

Enhanced GPWC - Block Diagram Figure 009   R EFF : ALL  34-48-00 Page A23   Config-1 Nov 01/09  CES

 

2 _

The accessory card contains the power supply and the voice generator DSP.

3 _

The analog acquisition card contains the analog acquisition microcontroller.

(b) The Enhanced GPWC contains the following five processors: - main processor (486DX4) that runs the Enhanced GPWC Application software and the Boot Loader Software, - DITS handler microcontroller that runs the DITS Handler software, - image generator DPS that runs the image generator software, which is a part of the Application software, - voice generator DSP that runs the voice generator software, which is part of the Application software, - analog acquisition microcontroller that runs the Analog Acquisition software. **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-310, 401-499, B. Pushbutton Switches **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, (Ref. Fig. 003) **ON A/C 001-049, 051-060, 101-104, 106-149, 215-233, 236-238, 301-310, 401-499, (Ref. Fig. 003A) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-310, 401-499, (1) GPWS/LDG FLAP 3 pushbutton switch 13WZ To avoid nuisance warnings during approach, the Enhanced GPWC needs to know at which flap position the crew intends to land. This pushbutton switch (item 5), when pressed (in) (white ON legend on), indicates to the Enhanced GPWC that the pilot intends to land in flap 3 position. When released (out), the pushbutton switch indicates to the Enhanced GPWC that the pilot intends to land in flap FULL position. The GPWS FLAP message is permanently displayed in green on the MEMO of the ECAM display unit if no warning is in progress.

  R EFF : ALL  34-48-00 Page A24   Config-1 Nov 01/09  CES

 

(2) GPWS/FLAP MODE pushbutton switch 7WZ This pushbutton switch (item 4), when pressed (in) (white OFF legend on), overrides flap abnormal condition input and generates the GPWS FLAP MODE OFF message (green) in the memo area of the upper ECAM display unit. (3) GPWS/G/S MODE pushbutton switch 11WZ This pushbutton switch (item 3), when pressed (in) (white OFF legend on), inhibits the glide slope mode. (4) GPWS/SYS pushbutton switch 9WZ When this pushbutton switch (item 2) is pressed (white OFF legend on), all ground proximity alerts (Mode 1 to 5) are inhibited (visual and audio) and no Enhanced GPWC self-test is possible. - This pushbutton switch provides a FAULT warning indicating that a failure in Modes 1 to 5 has been detected by the Enhanced GPWC. When the FAULT legend comes on, the following messages are displayed: . on the upper ECAM display unit if they are not inhibited by the FWC: NAV - GPWS FAULT (amber) GPWS ........OFF (cyan) (associated with action requested) . in the INOP SYS item, on the STATUS page of the lower ECAM display unit: GPWS (amber) A fault message is sent to the CFDIU. (Ref. Fig. 010) (5) GPWS/TERR pushbutton switch 31WZ - When this pushbutton switch (item 1) is pressed (white OFF legend on), the TAD and TCF functions are inhibited (visual display and audio inhibition). - The pushbutton switch provides a FAULT warning indicating that a failure of TAD and/or TCF functions has been detected by the Enhanced GPWC. When the FAULT legend comes on, the following messages are displayed: . on the upper ECAM display unit if they are not inhibited by the FWC: NAV - GPWS TERR DET FAULT (amber) GPWS TERR.............OFF (cyan) . in the INOP SYS item, on the STATUS page of the lower ECAM display unit: GPWS TERR (amber) A fault message is sent to the CFDIU.

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Enhanced GPWS - Messages Displayed on Upper and Lower ECAM DU Figure 010   R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page A26 201-233, 236-238, 301-310, 401-499,  Config-1 May 01/08  CES

 

**ON A/C ALL Post SB Post SB

31-1267 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-310,401-499, 31-1300 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-310,401-499,

B. Pushbutton Switches **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, Post SB Post SB

31-1267 For A/C 001-049,051-099,101-105,151-199,201-214, 31-1300 For A/C 001-049,051-099,101-105,151-199,201-214,

(Ref. Fig. 003) R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 31-1267 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-310,401-499, Post SB 31-1300 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-310,401-499, (Ref. Fig. 003A) **ON A/C ALL Post SB Post SB

31-1267 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-310,401-499, 31-1300 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-310,401-499,

(1) GPWS/LDG FLAP 3 pushbutton switch 13WZ To avoid nuisance warnings during approach, the Enhanced GPWC needs to know at which flap position the crew intends to land. This pushbutton switch (item 5), when pressed (in) (white ON legend on), indicates to the Enhanced GPWC that the pilot intends to land in flap 3 position. When released (out), the pushbutton switch indicates to the Enhanced GPWC that the pilot intends to land in flap FULL position. The GPWS FLAP message is permanently displayed in green on the MEMO of the ECAM display unit if no warning is in progress.

  EFF : ALL  34-48-00 Page A27   Config-1 Feb 01/10  CES

 

(2) GPWS/FLAP MODE pushbutton switch 7WZ This pushbutton switch (item 4), when pressed (in) (white OFF legend on), overrides flap abnormal condition input and generates the GPWS FLAP MODE OFF message (green) in the memo area of the upper ECAM display unit. (3) GPWS/G/S MODE pushbutton switch 11WZ This pushbutton switch (item 3), when pressed (in) (white OFF legend on), inhibits the glide slope mode. (4) GPWS/SYS pushbutton switch 9WZ When this pushbutton switch (item 2) is pressed (white OFF legend on), all ground proximity alerts (Mode 1 to 5) are inhibited (visual and audio) and no Enhanced GPWC self-test is possible. - This pushbutton switch provides a FAULT warning indicating that a failure in Modes 1 to 5 has been detected by the Enhanced GPWC. When the FAULT legend comes on, the following messages are displayed: . on the upper ECAM display unit if they are not inhibited by the FWC: NAV - GPWS FAULT (amber) GPWS ........OFF (cyan) (associated with action requested) . in the INOP SYS item, on the STATUS page of the lower ECAM display unit: GPWS (amber) A fault message is sent to the CFDIU. (Ref. Fig. 010A) (5) GPWS/TERR pushbutton switch 31WZ - When this pushbutton switch (item 1) is pressed (white OFF legend on), the TAD and TCF functions are inhibited (visual display and audio inhibition). - The pushbutton switch provides a FAULT warning indicating that a failure of TAD and/or TCF functions has been detected by the Enhanced GPWC. When the FAULT legend comes on, the following messages are displayed: . on the upper ECAM display unit if they are not inhibited by the FWC: TERR OFF (green or amber) GPWS TERR.............OFF (cyan) . in the INOP SYS item, on the STATUS page of the lower ECAM display unit: GPWS TERR (amber) A fault message is sent to the CFDIU.

  R EFF : ALL  34-48-00 Page A28   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Messages Displayed on Upper and Lower ECAM DU Figure 010A   R EFF : ALL  34-48-00 Page A29   Config-1 Nov 01/09  CES

 

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, (6) CAPT and F/O GPWS/G/S pushbutton switches 5WZ and 4WZ These pushbutton switches, located on panels 301VU and 500VU, have two functions when pressed (in): - they cancel the glide slope alert, or - they initiate the self-test sequence if the aircraft is on ground. (7) CAPT and F/O TERR ON ND pushbutton switches 30WZ1 and 30WZ2 These pushbutton switches (items 6 and 7) allow the crew to select or deselect terrain display on ND. The ON legends indicate that terrain data is displayed on ND (following manual or automatic pop up selection). R

**ON A/C ALL (6) CAPT and F/O PULL UP/GPWS pushbutton switches 5WZ and 4WZ These pushbutton switches, located on panels 301VU and 500VU, have two functions when pressed (in): - they cancel the glide slope alert, or - they initiate the self-test sequence if the aircraft is on ground. (7) CAPT and F/O TERR ON ND pushbutton switches 30WZ1 and 30WZ2 These pushbutton switches (items 6 and 7) allow the crew to select or deselect terrain display on ND. The ON legends indicate that terrain data is displayed on ND (following manual or automatic pop up selection).

R

**ON A/C ALL Post SB

34-1345 For A/C 001-049,051-060,101-104,

7. Operation _________ R

**ON A/C ALL A. General (1) Warning modes The serial digital data and discrete data inputs are interfaced and used in different combinations to monitor aircraft situation awareness with respect to the terrain. The following functions are implemented within the Enhanced GPWS: Mode 1 - Excessive rate of descent

  R EFF : ALL  34-48-00 Page A30   Config-1 Nov 01/09  CES

 

Mode 2 - Excessive closure rate with terrain Mode 3 - Descent after takeoff and minimum terrain clearance Mode 4 - Unsafe terrain clearance Mode 5 - Descent below glide slope Terrain Awareness and Display (TAD) Terrain Clearance Floor (TCF) **ON A/C 106-149, 215-233, 236-238, 301-304, (2) Aural alert messages Each mode computes and compares aircraft behaviour with a corresponding alert envelope. If the alert envelope is penetrated, visual and aural alerts are generated. The aural message is broadcast through the cockpit loud speakers. The messages are as follows: MODE AURAL ALERTS VISUAL ALERTS 1 SINK RATE GPWS 1 PULL UP PULL UP 2 TERRAIN GPWS 2 TERRAIN TERRAIN PULL UP 2 PULL UP PULL UP 3 DONT SINK DONT SINK GPWS 4 TOO LOW TERRAIN GPWS 4 TOO LOW GEAR GPWS 4 TOO LOW FLAPS GPWS 5 GLIDE SLOPE GPWS TAD TERRAIN AHEAD GPWS TAD TERRAIN AHEAD PULL UP PULL UP TCF TOO LOW TERRAIN GPWS Each of these alerts inhibits the automatic call out. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, (2) Aural alert messages Each mode computes and compares aircraft behaviour with a corresponding alert envelope. If the alert envelope is penetrated, visual and aural alerts are generated. The aural message is broadcast through the cockpit loud speakers. The messages are as follows:

  R EFF : ALL  34-48-00 Page A31   Config-1 Nov 01/09  CES

 

MODE AURAL ALERTS VISUAL ALERTS 1 SINK RATE GPWS 1 PULL UP GPWS 2 TERRAIN GPWS 2 TERRAIN TERRAIN GPWS 2 PULL UP GPWS 3 DONT SINK DONT SINK GPWS 4 TOO LOW TERRAIN GPWS 4 TOO LOW GEAR GPWS 4 TOO LOW FLAPS GPWS 5 GLIDE SLOPE G/S TAD TERRAIN AHEAD GPWS TAD TERRAIN AHEAD PULL UP GPWS TCF TOO LOW TERRAIN GPWS Each of these alerts inhibits the automatic call out. R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-214, 220-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-099,101-149,151-199,201-214,220-233, 236-238,301-304,401-403, (2) Aural alert messages Each mode computes and compares aircraft behaviour with a corresponding alert envelope. If the alert envelope is penetrated, visual and aural alerts are generated. The aural message is broadcast through the cockpit loud speakers. The messages are as follows: MODE AURAL ALERTS VISUAL ALERTS 1 SINK RATE GPWS 1 PULL UP PULL UP 2 TERRAIN GPWS 2 TERRAIN TERRAIN PULL UP PULL UP 3 DONT SINK GPWS 4 TOO LOW TERRAIN GPWS 4 TOO LOW GEAR GPWS 4 TOO LOW FLAPS GPWS 5 GLIDE SLOPE GPWS TAD TERRAIN AHEAD TERRAIN AHEAD GPWS TAD TERRAIN AHEAD PULL UP TERRAIN AHEAD PULL UP PULL UP OBSTACLE OBSTACLE AHEAD OBSTACLE AHEAD GPWS OBSTACLE OBSTACLE AHEAD PULL UP OBSTACLE AHEAD PULL UP PULL UP TCF TOO LOW TERRAIN GPWS Each of these alerts inhibits the automatic call out.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page A32 201-214, 220-249, 251-299, 301-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

R

**ON A/C 215-219, Post SB

34-1345 For A/C 215-219,

(2) Aural alert messages Each mode computes and compares aircraft behaviour with a corresponding alert envelope. If the alert envelope is penetrated, visual and aural alerts are generated. The aural message is broadcast through the cockpit loud speakers. The messages are as follows: MODE AURAL ALERTS VISUAL ALERTS 1 SINK RATE GPWS 1 PULL UP PULL UP 2 TERRAIN GPWS 2 TERRAIN TERRAIN PULL UP 2 PULL UP PULL UP 3 DONT SINK DONT SINK GPWS 4 TOO LOW TERRAIN GPWS 4 TOO LOW GEAR GPWS 4 TOO LOW FLAPS GPWS 4 TOO LOW TERRAIN GPWS 5 GLIDE SLOPE GPWS 5 TOO LOW TERRAIN GPWS TAD OBSTACLE AHEAD GPWS TAD OBSTACLE AHEAD GPWS TAD OBSTACLE AHEAD PULL UP PULL UP TCF TOO LOW TERRAIN GPWS Each of these alerts inhibits the automatic call out. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, (3) Inhibitions (Ref. Fig. 010) **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, Post SB Post SB

31-1267 For A/C 001-049,051-099,101-105,151-199,201-214, 31-1300 For A/C 001-049,051-099,101-105,151-199,201-214, (Ref. Fig. 010A)

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, Alerts may be cancelled by:

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page A33 201-219,  Config-1 Nov 01/08  CES

 

(a) Pressing the EMER CANC key on the ECAM control panel (aural alert only). (b) Pressing the GPWS/G/S pushbutton switch on the main instrument panel for Mode 5 (glide slope) visual and aural alert. This inhibition is temporary and the mode is automatically reactivated for a new envelope penetration. (c) Pressing the G/S MODE pushbutton switch on the overhead panel for Mode 5 (glide slope) visual and aural alert (permanent inhibition). (d) Pressing the SYS pushbutton switch on the overhead panel for inhibition of GPWS Modes 1 to 5 (visual and aural alerts). (e) Pressing the TERR pushbutton switch on the overhead panel for inhibition of TAD and TCF functions (visual and aural alerts). (f) All aural messages are inhibited if a stall or a windshear (if WR/PWS is installed) is in progress. (4) Faults which prevent normal Enhanced GPWC operation are stored in the BITE memory. They can be read on the MCDU. **ON A/C ALL (3) Inhibitions **ON A/C 001-049, 051-060, 101-104, 106-149, 215-233, 236-238, 301-310, 401-499, (Ref. Fig. 010) R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 31-1267 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-310,401-499, Post SB 31-1300 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-310,401-499, (Ref. Fig. 010A) **ON A/C ALL Alerts may be cancelled by:

  EFF : ALL  34-48-00 Page A34   Config-1 Feb 01/10  CES

 

(a) Pressing the EMER CANC key on the ECAM control panel (aural alert only). (b) Pressing the PULL UP/GPWS pushbutton switch on the main instrument panel for Mode 5 (glide slope) visual and aural alert. This inhibition is temporary and the mode is automatically reactivated for a new envelope penetration. (c) Pressing the G/S MODE pushbutton switch on the overhead panel for Mode 5 (glide slope) visual and aural alert (permanent inhibition). (d) Pressing the SYS pushbutton switch on the overhead panel for inhibition of GPWS Modes 1 to 5 (visual and aural alerts). (e) Pressing the TERR pushbutton switch on the overhead panel for inhibition of TAD and TCF functions (visual and aural alerts). (f) All aural messages are inhibited if a stall or a windshear (if WR/PWS is installed) is in progress. (4) Faults which prevent normal Enhanced GPWC operation are stored in the BITE memory. They can be read on the MCDU. B. Detailed Operation - Modes 1 through 5 This section describes the five warning modes of the Enhanced GPWC and describes the operation of each of the modes. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, (1) Mode 1 - Excessive rate of descent (Ref. Fig. 011) (a) Mode 1 provides the pilot with an alert/warning for high descent rates into terrain. The pilot also receives a timely alert for rapidly building sink rates near the runway when landing. The figure shows the outer and inner boundaries whose penetration triggers the alert/warnings. (b) The outer boundary is a straight line which has an equation of: H warn (ft.) = - 572 ft. - 0.6035 X Altitude rate. NOTE : The descent rate is considered negative during the ____ descent. The formulas provide theoretical target values only.

  R EFF : ALL  34-48-00 Page A35   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Excessive Rate of Descent Figure 011   R EFF : ALL  34-48-00 Page A36   Config-1 Nov 01/09  CES

 

(c) The outer warning boundary is biased to the right as a function of glide slope deviation above (Fly Down) the beam in order to prevent unwanted warnings while re-positioning from above the beam. (d) The penetration of this outer boundary activates the GPWS legends and produces the voice warning SINK RATE repeated twice, then remains silent unless the excessive descent rate condition degrades by approximately 20 per cent. (e) Further penetration of the first boundary reaches the inner boundary where the voice warning changes from SINK RATE to PULL UP. This inner boundary is composed of two straight lines. The equation which describes the lower line is: H warn (ft.) = - 1620 ft. - 1.1133 X Altitude rate. The equation which describes the upper line is: H warn (ft.) = - 400 ft. - 0.400 X Altitude rate. (f) Both boundaries are cut off at the top by 2450 ft. The lower is cut off at 10 ft. A seconds is included in the upper function warnings caused by the momentary boundary

a radio altitude of delay equivalent to 0.8 to minimize the penetration.

(g) Both boundaries can be biased to the right at certain airports through envelope modulation to minimize nuisance warnings. **ON A/C ALL (1) Mode 1 - Excessive rate of descent R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 011) **ON A/C ALL (a) Mode 1 provides the pilot with an alert/warning for high descent rates into terrain. The pilot also receives a timely alert for rapidly building sink rates near the runway when landing. The figure shows the outer and inner boundaries whose penetration triggers the alert/warnings.

  EFF : ALL  34-48-00 Page A37   Config-1 Feb 01/10  CES

 

(b) The outer boundary is a straight line which has an equation of: H warn (ft.) = - 572 ft. - 0.6035 X Altitude rate. NOTE : The descent rate is considered negative during the ____ descent. The formulas provide theoretical target values only. (c) The outer warning boundary is biased to the right as a function of glide slope deviation above (Fly Down) the beam in order to prevent unwanted warnings while re-positioning from above the beam. (d) The penetration of this outer boundary activates the PULL UP legends and produces the voice warning SINK RATE repeated twice, then it remains silent unless the excessive descent rate condition degrades by approximately 20 per cent. (e) Further penetration of the first boundary reaches the inner boundary where the voice warning changes from SINK RATE to PULL UP. This inner boundary is composed of two straight lines. The equation which describes the lower line is: H warn (ft.) = - 1620 ft. - 1.1133 X Altitude rate. The equation which describes the upper line is: H warn (ft.) = - 400 ft. - 0.400 X Altitude rate. (f) Both boundaries are cut off at the top by 2450 ft. The lower is cut off at 10 ft. A seconds is included in the upper function warnings caused by the momentary boundary

a radio altitude of delay equivalent to 0.8 to minimize the penetration.

(g) Both boundaries can be biased to the right at certain airports through envelope modulation to minimize nuisance warnings. (2) Mode 2 - Excessive closure rate with terrain (Ref. Fig. 012) (a) Mode 2 provides a warning based on the radio altitude between the aircraft and the ground and on how rapidly the radio altitude decreases. The barometric altitude of the aircraft is not important for the initiation of this warning.

  R EFF : ALL  34-48-00 Page A38   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Terrain Closure Rate - Mode Figure 012   R EFF : ALL  34-48-00 Page A39   Config-1 Nov 01/09  CES

 

(b) The altitude rate is complemented in the filter to provide lead information. The increase of the altitude descent rate tends to speed up the warning occurrence. The reduction of the altitude descent rate or the initiation of a climb tends to delay the warning occurrence or reduce the time the warning is on. (c) This mode has two areas of application that are generally referred to as Mode 2A and Mode 2B. Mode 2A is applied when the landing flaps are not down and the aircraft is not in the glide slope beam. Mode 2B requires that the landing flaps be down or that the aircraft be in the glide slope beam within +/- 2 dots of deviation during an ILS approach. The figure shows the warning boundary for Mode 2A (landing flaps up). The closure rate is the computed change in the radio altitude between the aircraft and the ground. It is considered positive when the altitude decreases. The lower sloped line has an equation of: H warn (ft.) = - 1579 ft. + 0.7895 X closure rate (FPM). The upper sloped line has an equation of: H warn (ft.) = 522 ft. + 0.1968 X closure rate (FPM). (d) The normal upper limit of the boundary is horizontal at 1650 ft. radio altitude due to a computed maximum closure rate limit of 5733 FPM. As the airspeed increases from 220 Kts up to 310 Kts, the maximum rate limit is linearly increased to 9800 FPM. This allows the upper boundary to also linearly increase up to 2450 ft. The upper boundary is limited at certain airports to reduce the warning sensitivity and minimize the nuisance warnings. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, (e) Upon penetration of the boundary, either on the slope or from the top, the GPWS legends come on and the voice message is TERRAIN TERRAIN. If the boundary penetration lasts beyond these two TERRAIN messages, approximately 1 second, then the warning switches to PULL UP repeated continuously until the boundary is departed. When the Mode 2A envelope is exited, after having been violated for more than 3 seconds, an altitude gain feature is automatically activated. First the altitude at this instant is sampled and stored. The GPWS legends remain on and the voice message is TERRAIN. After three hundred feet of altitude are

  R EFF : ALL  34-48-00 Page A40   Config-1 Nov 01/09  CES

 

gained from the stored value, or 45 seconds have elapsed from the point where the PULL UP envelope was exited, the GPWS legends and voice stop. If another boundary penetration occurs during this altitude gain time, and it lasts long enough to restart the PULL UP warning plus 3 seconds, then the whole process begins again with a new reference altitude for the 300 ft. after boundary separation. In this manner the aircraft is directed up and over the terrain to a safer altitude. (f) Lowering the flaps to the landing position automatically switches the GPWS to Mode 2B. The static boundary for Mode 2B is the same as the Mode 2A boundary except the upper limit has been lowered to 789 ft. at a maximum closure rate of 3000 FPM. The lower part of the Mode 2B boundary is controlled as a function of radio altitude and altitude rate when flaps are in full landing configuration. (g) Mode 2B is also selected when the aircraft is performing an ILS approach and the glide slope and localizer deviations are less than +/- 2 dots. However, the warning envelope is slightly different from the flaps down case in that the lower boundary is controlled only as a function of radio altitude, having a constant lower cutoff of 30 ft. above ground level. When the flaps are selected to landing configuration in the ILS beams, the lower boundary is activated, (Mode 2B inhibit). (h) When the envelope boundary conditions for Mode 2B are violated, the GPWS legends come on, and the voice message is repeated until the boundary is exited. If the gear or the flaps are up, then the message is TERRAIN TERRAIN followed by PULL UP if the condition persists. If both gear and flaps are in the landing configuration, the message is TERRAIN. R

**ON A/C ALL Post SB

34-1351 For A/C 001-049,051-099,101-105,151-199,201-214, (e) Upon penetration of the boundary, either on the slope or from the top, the PULL UP legends come on and the voice message is TERRAIN TERRAIN. If the boundary penetration lasts beyond these two TERRAIN messages, approximately 1 second, then the warning switches to PULL UP repeated continuously until the boundary is departed. When the Mode 2A envelope is exited, after having been violated for more than 3 seconds, an altitude gain feature is automatically activated. First the altitude at this instant is

  R EFF : ALL  34-48-00 Page A41   Config-1 Nov 01/09  CES

 

sampled and stored. The PULL UP legends remain on and the voice message is TERRAIN. After three hundred feet of altitude are gained from the stored value, or 45 seconds have elapsed from the point where the PULL UP envelope was exited, the PULL UP legends and voice stop. If another boundary penetration occurs during this altitude gain time, and it lasts long enough to restart the PULL UP warning plus 3 seconds, then the whole process begins again with a new reference altitude for the 300 ft. after boundary separation. In this manner the aircraft is directed up and over the terrain to a safer altitude. (f) Lowering the flaps to the landing position automatically switches the GPWS to Mode 2B. The static boundary for Mode 2B is the same as the Mode 2A boundary except the upper limit has been lowered to 789 ft. at a maximum closure rate of 3000 FPM. The lower part of the Mode 2B boundary is controlled as a function of radio altitude and altitude rate when flaps are in full landing configuration. (g) Mode 2B is also selected when the aircraft is performing an ILS approach and the glide slope and localizer deviations are less than +/- 2 dots. However, the warning envelope is slightly different from the flaps down case in that the lower boundary is controlled only as a function of radio altitude, having a constant lower cutoff of 30 ft. above ground level. When the flaps are selected to landing configuration in the ILS beams, the lower boundary is activated, (Mode 2B inhibit). (h) When the envelope boundary conditions for Mode 2B are violated, the PULL UP legends come on, and the voice message is repeated until the boundary is exited. If the gear or the flaps are up, then the message is TERRAIN TERRAIN followed by PULL UP if the condition persists. If both gear and flaps are in the landing configuration, the message is TERRAIN.

  R EFF : ALL  34-48-00 Page A42   Config-1 Nov 01/09  CES

 

R

**ON A/C ALL Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, (i) When the following conditions are available: - Enhanced functions valid, - Terrain database quality good, - Geometric Altitude valid, - Terrain awareness functions in high integrity, Current Mode 2 alert envelopes are modified in order to limit spurious alert. The new envelope limits the top of the Mode 2 curve to 950 ft. RA. The Mode 2 envelope is also reduced to the existing Mode 2 B limit of 789 ft. whenever the aircraft is within 10NM and 3500 ft. of the runway. (Ref. Fig. 013)

**ON A/C 106-149, 220-233, 301-304, 401-403, Post SB

34-1287 For A/C 220-228,301-302, (i) When the following conditions are available: - Enhanced functions valid, - Terrain database quality good, - Geometric Altitude valid, - Terrain awareness functions in high integrity, Current Mode 2 alert envelopes are modified in order to limit spurious alert. The new envelope limits the top of the Mode 2 curve to 1250 ft. RA. The Mode 2 envelope is also reduced to the existing Mode 2 B limit of 789 ft.whenever the aircraft is within 5NM of the runway. (Ref. Fig. 013A)

  R EFF : ALL  34-48-00 Page A43   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Mode 2 with Geometric altitude Figure 013   R EFF : ALL  34-48-00 Page A44   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Mode 2 with Geometric altitude Figure 013A   R EFF : 106-149, 220-233, 301-304, 401-403,  34-48-00 Page A45   Config-1 Feb 01/08  CES

 

R

**ON A/C ALL (3) Mode 3 - Insufficient climb performance after takeoff (Ref. Fig. 014) (a) Mode 3 provides a warning for excessive altitude loss after takeoff. Mode 3 is based primarily on radio altitude, altitude (IR inertial altitude, internally computed inertial altitude, or barometric altitude), and altitude rate (IVS, internally computed inertial altitude rate, or barometric altitude rate). (b) Penetration of the Mode 3 alert/boundary results in the message DONT SINK and is based on altitude loss and radio altitude. This alert/warning is only provided during takeoff when the aircraft looses a predetermined amount of altitude. (Ref. Fig. 014) The sloped portion of the static warning envelope depicted is defined by the following equation: ALTITUDE LOSS (FT.) = 5.4 + 0.092 (RADIO ALTITUDE (FT.)) (c) Inertially compensated air data signals are used when possible. IVS is used when valid data is available and barometric altitude rate is used only when valid IVS is not available and the internal computed inertial data is not valid. The Mode 3 warning envelopes are inhibited close to the ground. (d) The descent required for a warning varies as a function of flight profile and time. Once a descent begins during the takeoff phase of flight, as determined by the polarity of the altitude rate signal and takeoff/approach mode logic, the Enhanced GPWC stores the existing value of altitude. Subsequent samples of altitude, altitude rate, and radio altitude are examined for warning conditions. The original stored value of altitude indicating where the descent began is retained until the aircraft ascends above the stored altitude value. When the polarity of the altitude rate signal indicates ascent rather than descent, the warning is cut off to indicate recovery is being initiated. A subsequent return to descent prior to regaining the altitude lost enables the warning. The altitude loss required to resume the message and legend activation is based on the initially stored altitude value. In this manner, the possibility of stair stepping down without Mode 3 warning indication is eliminated.

  R EFF : ALL  34-48-00 Page A46   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Descent After Takeoff Figure 014   R EFF : ALL  34-48-00 Page A47   Config-1 Nov 01/09  CES

 

(e) Mode 3 is biased or desensitized under certain conditions. This is accomplished by sampling radio altitude and altitude at takeoff or go-around, and combining these signals to establish the field elevation (or ground elevation) at takeoff or at the point of go-around. Subsequent altitude information is then compared to this value to determine the altitude gained since takeoff or go-around. (f) A delay equivalent to 0.8 second is added to the warning output to prevent the possibility of nuisance warnings caused by static pressure disturbances during gear retraction. **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, (4) Mode 4 - Unsafe terrain clearance (a) Mode 4 generates three types of voice warnings based on the radio altitude, computed airspeed, and aircraft configuration, commonly referred to as Modes 4A, 4B and 4C. Mode 4A is active during cruise and approach with gear and flaps not in landing configuration (conf 3 or full), the voice message is TOO LOW GEAR. Mode 4B is active in cruise and approach, with either gear or flaps in landing configuration. The upper boundary of the mode 4A and 4B envelope depends on the enhanced mo des. When TCF is enabled and TAD in high integrity, mode 4A upper boundary is maintained at 500ft for all airspeed and mode 4B upper boundary is maintained at 245ft for all airspeed. All mode 4A/4B alerts are disabled when the aircraft is in full landing configuration. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, (Ref. Fig. 015) **ON A/C 106-149, 220-233, 236-238, 301-304, 401-403, (Ref. Fig. 015A) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, The equation for the sloped portion of the warning curve is:

  R EFF : ALL  34-48-00 Page A48   Config-1 Nov 01/09  CES

 

H warn (ft) = -1083ft + 8.333 x Computed Airspeed (Kts) Mode 4C is active diring takeoff phase with either gear or flaps not in landing configuration. It provides a warning based on minimum radio altitude clearance during takeoff. This warning is similar to the Mode 4A warning that is active during the cruise and approach phases of flight, only in this case, the minimum terrain clearance is a function of the radio altitude of the aircraft. The slopped portion of the envelope boundary is described by the equation: MIN TERRAIN CLEARANCE (ft) = 0.75 (RADIO ALTITUDE (ft) Mode 4C is based on a minimum terrain clearance, or floor, that increases with radio altitude during takeoff. A value equal to 75 per cent of the current rad io altitude is accumulated in a long term filter that is only allowed to increase in value. If the radio altitude later decreases, the filter stores its maximum attained value. Further decrease of radio altitude below the stored filter value with gear or flaps up results in the warning TOO LOW TERRAIN (or equivalent). A simplified example illustrates this operation. First assume the radio altitude increase rapidly from 0ft to 400ft. The filter begins charging to 75 per cent of 400ft or 300ft. In 20 seconds, the filter has charged up to approximately 220ft. Now if the radio altitude decreases so that 75 per cent of this value results in something less than 220ft (i.e., approximately 295ft or less), the filter remains at a value of 220ft . Further reductions in radio altitude below 220ft result in the TOO LOW TERRAIN warning. This warning is provided to prevent inadvertent controlled flight into the ground during takeoff climb into terrain that produces insufficient closure rate for a Mode 2 warning. After takeoff, and mode change over from Takeoff to Cruise or Approach, then Mode 4A and 4B provide this protection. The basic audio de-clutter feature applies a ratched function to the Mode 4C voice warning which is equivalent to the ratcheting voice message described above. Once the message is given, the envelope is biased down by 20 per cent and further warnings are held off until this additional 20 per cent radio altitude is lost. The lamp is not affected and remains on until the terrain clearance problem is rectified. (b) The Mode 4A/4B maximum altitude is lowered from 1000 to 800 ft. of radio altitude when an overflight is detected. An overflight can be detected by sensing the sudden change in radio altitude (-2200ft/s). The 800 ft limit is maintained for 60 seconds after an overflight to ensure that a nuisance warning is not issued.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page A49 201-233, 236-238, 301-304, 401-403,  Config-1 Feb 01/08  CES

 

Enhanced GPWS - Unsafe Terrain Clearance - Mode Figure 015 (SHEET 1)   R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page A50 201-219,  Config-1 Feb 01/08  CES

 

Enhanced GPWS - Unsafe Terrain Clearance - Mode Figure 015 (SHEET 2)   R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page A51 201-219,  Config-1 Feb 01/08  CES

 

Enhanced GPWS - Unsafe Terrain Clearance - Mode Figure 015A (SHEET 1)   R EFF : ALL  34-48-00 Page A52   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Unsafe Terrain Clearance - Mode Figure 015A (SHEET 2)   R EFF : ALL  34-48-00 Page A53   Config-1 Nov 01/09  CES

 

(c) When the landing gear or flaps are lowered, the upper boundary decreases to 245 ft. To maintain the same airspeed expansion function up to 1000 ft. nominal at 250 Kts, the lower level corner is at 159 Kts. Penetration below 159 Kts results in TOO LOW GEAR messages with gear up or TOO LOW FLAPS message with gear down and flaps not in landing configuration, while above 159 Kts the message is TOO LOW TERRAIN. (d) The basic audio de-clutter feature applies a ratched function to the Mode 4 voice warning which is similar to the Mode 3 ratcheting voice message. Once the message is given, the envelope is biased down by 20 per cent and further warnings are held off until this additional 20 per cent radio altitude is lost. The lamp is not affected and remains on until the radio altitude becomes greater than indicated on the curves. A simplified example illustrates this operation. First assume the radio altitude increases rapidly from 0 ft. to 400 ft. The filter begins charging to 75 per cent of 400 ft., or 300 ft. In 20 seconds, the filter has charged up to approximately 220 ft. (e) The gear-down logic requirement for Mode 5is deleted at certains airports. **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

(4) Mode 4 - Unsafe terrain clearance R R

**ON A/C 001-049, 051-060, 101-104, 234-235, 239-249, 251-299, 305-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104, (Ref. Fig. 015A) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (a) Mode 4 generates three types of voice warning messages based on the radio altitude, computed airspeed, and aircraft configuration. Mode 4 is composed of three sub-modes referred to as Modes 4A, 4B and 4C.

  EFF : ALL  34-48-00 Page A54   Config-1 Feb 01/10  CES

 

Mode 4A is active during cruise and approach, with gear not in landing configuration and flaps not in landing configuration (full or conf 3 + LDG FLAP 3 selected on the overhead GPWS control panel). Mode 4B is active during cruise and approach, with: - gear in landing configuration OR - flaps in landing configuration and gear not in landing configuration. All Mode 4 alerts are inhibited if flaps and gear are in landing configuration. A push action on the GPWS/FLAP MODE pushbutton switch (OFF legend on) inhibits all Mode 4 alerts if gear is in landing configuration. (b) The standard upper boundary for Mode 4A is at 500 ft. radio altitude. Below 190 kts, if the aircraft penetrates this boundary with the gear still up and flap not in landing configuration, the voice message is TOO LOW GEAR. Above 190 kts : - if flaps are not in landing configuration and TCF enabled or TAD in high integrity (A/C position and geometric altitude have a high accuracy), the upper boundary stays constant to a value of 500 ft. radio altitude. Penetrating this airspeed expanded boundary produces a TOO LOW TERRAIN voice message. R R

**ON A/C 001-049, 051-060, 101-104, 234-235, 239-249, 251-299, 305-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104, (Ref. Fig. 015A) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (See top fig. (SHEET1)) - if flaps are not in landing configuration and TCF disabled and TAD not in high integrity, the upper boundary increases linearly with airspeed to a maximum of 1000 ft. radio altitude at 250 kts or more. Penetrating this airspeed expanded boundary produces a TOO LOW TERRAIN voice message.

  EFF : ALL  34-48-00 Page A55   Config-1 Feb 01/10  CES

 

Lowering the flaps or the gear in landing configuration results in transition to Mode 4B. R R

**ON A/C 001-049, 051-060, 101-104, 234-235, 239-249, 251-299, 305-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104, (Ref. Fig. 015A) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (See bottom fig. (SHEET1)) (c) The standard upper boundary for Mode 4B is at 245 ft. radio altiude. Penetration below 159 kts results in TOO LOW GEAR voice message with gear up, or TOO LOW FLAPS message with gear down and flaps not in Landing configuration Above 159 kts : - if landing gear is up and flaps are down, the voice message is TOO LOW GEAR. The upper boundary stays constant to a value of 245 ft.

R R

**ON A/C 001-049, 051-060, 101-104, 234-235, 239-249, 251-299, 305-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104, (Ref. Fig. 015A) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (See top fig. (SHEET2)) - if landing gear is down and flaps are not in landing configuration, the voice message is TOO LOW TERRAIN. The upper boundary stays constant to a value of 245 ft. if TAD is in high integrity or TCF enabled.

R R

**ON A/C 001-049, 051-060, 101-104, 234-235, 239-249, 251-299, 305-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104, (Ref. Fig. 015A)

  EFF : ALL  34-48-00 Page A56   Config-1 Feb 01/10  CES

 

**ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (See middle fig. (SHEET2)) Otherwise, the upper boundary increases linearly with airspeed to a maximum value of 1000 ft. radio altitude at 250 kts or more.

R R

**ON A/C 001-049, 051-060, 101-104, 234-235, 239-249, 251-299, 305-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104, (Ref. Fig. 015A) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (See bottom fig. (SHEET2)) (d) The Mode 4A and 4B maximum altitudes are reduced under different circumstances to help reduce nuisance alerts. First, through Envelope Modulation, lower maximums are used at certain airports where operational procedures and terrain characteristics may result in potential nuisance warnings. Secondly, the Mode 4 maximum altitude is reduced from 1000 ft. to 800 ft. radio altitude if an overflight is detected. An overflight is detected by sensing sudden changes in radio altitude. Current holding patterns can allow a 1000 ft. separation between aircraft. Due to barometric altimetry errors, the actual separation can be somewhat less than 1000 ft. If the radio altitude rate of change is greater than or equal to -2200 ft. per second, then the Mode 4 maximum altitude is reduced to 800 ft. for 60 seconds following the excessive rate detection. (e) Mode 4 also provides an alert based on a minimum radio altitude clearance during takeoff. This alert is similar to the Mode 4A alert that is active during the cruise and approach phases of flight, only in this case, the minimum terrain clearance is a function of the radio altitude of the aircraft. A value equal to 75 percent of the current radio altitude is accumulated in a long-term filter that is only allowed to increase in value. If the radio altitude later decreases, the

  EFF : ALL  34-48-00 Page A57   Config-1 Feb 01/10  CES

 

filter stores its maximum attained value. Further decrease of radio altitude below the stored filter value with gear or flap results in the TOO LOW TERRAIN voice message (or equivalent). A simplified example illustrates this operation. First assume the radio altitude increases rapidly from zero foot to 400 ft. The filter begins charging to 75 percent of 400 ft., or 300 ft. In 20 seconds, the filter will have charged up to approximately 220 ft. If the radio altitude decreases so that 75 percent of this value results in something less than 220 ft. (i.e., approximately 295 ft. or less), the filter remains at a value of 220 ft. Further reductions in radio altitude below 220 ft. will result in the TOO LOW TERRAIN voice message. This warning is provided to prevent inadvertent controlled flight into the ground during takeoff climb into terrain that produces insufficient closure rate for a Mode 2 warning. After change from takeoff to cruise and approach, then Modes 4A and 4B provide this protection. The basic audio declutter feature applies a ratchet function to the Mode 4 aural alerts which are similar to the Mode 3 ratcheting alert/warning. Once the alert/warning is provided, the envelope is biased down by 20 percent and further alerts are held off until this additional 20 percent radio altitude is lost. The lamp is not affected and remains on until the radio altitude becomes greater than the indication on the curves. R

**ON A/C ALL (5) Mode 5 - Descent below glide slope (Ref. Fig. 016) (a) Mode 5 provides two levels of warning when the aircraft flight path descends below the glide slope beam on front course ILS approaches. The upper limit of 1000 ft. nominal allows the capture of the beam before enabling this mode. Higher upper limits are used at certain airports to increase the warning envelope. The deviation boundaries are shown in dots below the beam where one dot equals 0.0875 DDM = 0,36 degree. The first warning occurs whenever the aircraft is more than 1.3 dots below the beam. It is called a soft glide slope warning because the volume level of the GLIDE SLOPE warning is approximately one half (- 6 db) that of the other warnings. A second warning boundary occurs below 300 ft. radio altitude and more than 2 dots below the beam. It is called loud glide slope because the volume level is increased to that of the other warnings.

  R EFF : ALL  34-48-00 Page A58   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Descent Below Glide Slope Figure 016   R EFF : ALL  34-48-00 Page A59   Config-1 Nov 01/09  CES

 

(b) Both boundaries allow additional deviation below 150 ft. of radio altitude to allow for normal beam variations near the threshold. (c) The basic audio de-clutter feature provides GLIDE SLOPE message logic which suppresses the aural alert after one message has been given. Follow-on alerts are only allowed when the aircraft descends lower on the glide slope beam by approximately 20 per cent. The alert lamp remains on until the excessive FLY UP condition has been corrected. The aural alerts are provided continuously once the aircraft exceeds 2 dots FLY UP. Below 300 ft. AGL the messages speed up as altitude is lowered or deviation is increased. Actual time between GLIDE SLOPE messages for these conditions is controlled by the equation: RADIO ALTITUDE (FT.) PAUSE(SEC) = --------------------------------- X 0.0067 GLIDE SLOPE DEVIATION (DOTS FLY UP) Additionally, the audio de-clutter feature allows for Mode 5 GLIDE SLOPE alerts to occur during penetration of the Mode 1 outer envelope while the Mode 1 SINKRATE audio is suppressed. (d) The GLIDE SLOPE warning can be manually cancelled by the crew. This can be done any time below 2000 ft. nominal radio altitude. Cancel can be reset by ascending above 2000 ft. nominal, or descending below 30 ft. (e) The change from constant deviation to a slope below 150 ft. radio altitude is shown along with the constant separation 0.7 dot between the two boundaries. A delay of approximately 0.8 second is inserted between the warning output and the enabling logic during a warning condition. The delay also turns off the warning output when two successive samples show a loss of the enabling logic. The repetition rate of the GLIDE SLOPE message is controlled by the radio altitude and the glide slope deviation as shown in the equation above. (f) The gear-down logic requirement for Mode 5 is deleted at certain airports. R

**ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (g) Mode 5 is inhibited when aircraft performed a FLS approach.

  R EFF : ALL  34-48-00 Page A60   Config-1 Nov 01/09  CES

 

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, Post SB 34-1147 For A/C 001-004,051-060, C. Envelope Modulation (1) Background During the past 20 years, experience with GPWS has shown that normal approaches to certain airports can be incompatible with the normal warning envelopes and signal filtering. The envelope modulation feature provides improved alert/warning protection at some key locations throughout the world, while improving nuisance margins at others. This is made possible with the use of navigational signals from modern inertially based navigation equipment. This feature utilizes updated flight management system navigational signals. R

**ON A/C ALL Post SB Post SB

34-1147 For A/C 001-004,051-060, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

C. Envelope Modulation (1) Background During the past 20 years, experience with GPWS has shown that normal approaches to certain airports can be incompatible with the normal warning envelopes and signal filtering. The envelope modulation feature provides improved alert/warning protection at some key locations throughout the world, while improving nuisance margins at others. This is made possible with the use of navigational signals from GPS/IRS/FMS navigation equipement. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, A number of enhancements to the envelopes and filters have been developed during this time in an attempt to accommodate these few airports, without compromising the overall GPWS effectiveness for all the other airport normal approaches. However, there remains a limited number of cases which are still not satisfactory persist despite these efforts. All of the noticeable cases have been due to nuisance warnings for approaches and departures at particular airports. The majority of nuisance warnings involves Mode 2 closure rate due to terrain under the approach path or rising terrain just before the runway threshold.

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Others involve Mode 4 terrain clearance warnings during initial approach. A few Mode 1 warnings are the results of steeper than normal approaches over terrain which slopes down to the runway at some airports. A different type of case is the inadequate warning protection during ILS approaches because Mode 5 is limited to less than 1000 ft. radio altitude. There are airports located at a significantly higher altitude than the surrounding terrain. In some instances this difference is over 1000 ft., thus requiring the aircraft to be below the runway elevation before a Mode 5 warning is possible during most of the approach. Until recently there has been no reasonable way to accomodate these few special cases without compromising the Enhanced GPWC at all other airports. What is needed is the ability to recognize when the aircraft is approaching one of these airports and then adjust the warning criteria to suit the particular approach. The availability of accurate, low drift, latitude and longitude information from the latest generation inertial navigation equipment now makes individual airport recognition possible. After recognizing the approach to or departure from one of these airports, it is also important to verify the aircraft is at a reasonable altitude before desensitizing any warning criteria. If the aircraft is already low, further warning reduction is not desirable. This requires the use of corrected altitude signals. (2) Functional description Furthermore, in order to prevent inadvertent activation of envelope modulation, cross checks must be made which validate the navigational and altitude information. This requires a cross check to other ground based navigational aids. Corrected altitude information from the ADIRU is used. This data can be either QNH or QFE corrected (selectable via program pin). This altitude information is verified in one of two ways: - For ILS approaches, the glide slope deviation is used to establish that adequate terrain clearance exists (i.e. a normal approach). Consequently, errors in altitude data do not enable envelope modulation during an unsafe condition, - When ILS information is not available, stored terrain elevation data is matched against computed elevation data (i.e. corrected altitude - radio altitude) to verify altitude. This is done for a snapshot location immediately prior to the envelope modulation area.

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R

**ON A/C ALL A number of enhancements to the envelopes and filters have been developed during this time in an attempt to accommodate these few airports, without compromising the overall GPWS effectiveness for all the other airport normal approaches. However, there remains a limited number of cases which are still not satisfactory persist despite these efforts. All of the noticeable cases have been due to nuisance warnings for approaches and departures at particular airports. The majority of nuisance warnings involves Mode 2 closure rate due to terrain under the approach path or rising terrain just before the runway threshold. Others involve Mode 4 terrain clearance warnings during initial approach. A few Mode 1 warnings are the results of steeper than normal approaches over terrain which slopes down to the runway at some airports. A different type of case is the inadequate warning protection during ILS approaches because Mode 5 is limited to less than 1000 ft. radio altitude. There are airports located at a significantly higher altitude than the surrounding terrain. In some instances this difference is over 1000 ft., thus requiring the aircraft to be below the runway elevation before a Mode 5 warning is possible during most of the approach. Until recently there has been no reasonable way to accomodate these few special cases without compromising the Enhanced GPWC at all other airports. What is needed is the ability to recognize when the aircraft is approaching one of these airports and then adjust the warning criteria to suit the particular approach. The availability of accurate, low drift, latitude and longitude information from the latest generation inertial navigation equipment now makes individual airport recognition possible. After recognizing the approach to or departure from one of these airports, it is also important to verify the aircraft is at a reasonable altitude before desensitizing any warning criteria. If the aircraft is already low, further warning reduction is not desirable. This requires the use of corrected altitude signals. (2) Functional description Furthermore, in order to prevent inadvertent activation of envelope modulation, cross checks must be made which validate the navigational and altitude information. This requires a cross check to other ground based navigational aids. Corrected altitude information from the ADIRU is used. This data can be either QNH or QFE corrected. This altitude information is verified in one of two ways:

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- For ILS approaches, the glide slope deviation is used to establish that adequate terrain clearance exists (i.e. a normal approach). Consequently, errors in altitude data do not enable envelope modulation during an unsafe condition, - When ILS information is not available, stored terrain elevation data is matched against computed elevation data (i.e. corrected altitude - radio altitude) to verify altitude. This is done for a snapshot location immediately prior to the envelope modulation area. **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, Post SB 34-1147 For A/C 001-004,051-060, The following input data are used for airport recognition: - latitude position from the FMGC or the ADIRU, - longitude position from the FMGC or the ADIRU, - glide slope deviation from the ILS portion of the MMR, - localizer deviation from the ILS portion of the MMR, - aircraft magnetic track angle from the FMGC or the ADIRU, - runway course from the ILS portion of the MMR, - corrected barometric altitude from the ADIRU, - QNH or QFE mode of baro altitude correction via program pin. QNH mode is the baro altitude correction to sea level. QFE mode is selected with a program pin for baro altitude correction to the airport field elevation, - radio altitude. Latitude and longitude data are continuously monitored for the airport locations. Additional data processing for envelope modulation is not required until the aircraft approaches one of the envelope modulation areas. Then the other data inputs are checked for a normal approach before any warning envelopes are modulated. The FMGC is the preferred source for latitude and longitude data because these data were corrected for the normal drift of the ADIRU basic latitude and longitude data. R

**ON A/C ALL Post SB Post SB

34-1147 For A/C 001-004,051-060, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, The following input data are used for airport recognition: - latitude position from GPS or FMGC or the ADIRU, - longitude position from GPS or FMGC or the ADIRU, - glide slope deviation from the ILS, - localizer deviation from the ILS,

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-

aircraft magnetic track angle from the FMGC or the ADIRU, runway course from the ILS, corrected barometric altitude from the ADIRU, QNH or QFE mode of baro altitude correction. QNH mode is baro altitude correction to sea level. QFE mode is selected for baro altitude correction to the airport field elevation, - radio altitude. Latitude and longitude data are continuously monitored for the airport locations. Additional data processing for envelope modulation is not required until the aircraft approaches one of the envelope modulation areas. Then the other data inputs are checked for a normal approach before any warning envelopes are modulated. The GPS is the preferred source for latitude and longitude. The Enhanced-GPWS will then us preferably GPS and corrected IRS latitude and longitude data as valid position source, if these position are downgraded, then FMS position will be used. **ON A/C ALL (3) Types of envelope modulation - There are currently four types of envelope modulation required for particular airport approaches. - bias the Mode 1 warning boundaries for SINK RATE and PULL UP to the right to allow greater altitude descent rates before a warning is generated. (Ref. Fig. 011) - lower the maximum upper limit for Mode 2A and Mode 2B. This limits the maximum radio altitude, or the minimum terrain clearance required to generate a warning. (Ref. Fig. 012) - lower the maximum upper limit for Mode 4 to allow less minimum terrain clearance before a warning is generated. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, (Ref. Fig. 015) R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 220-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104, (Ref. Fig. 015A)

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R

**ON A/C ALL - expand the maximum Mode 5 radio altitude level where a warning can begin. This allows GLIDE SLOPE warnings for higher radio altitudes. The gear down requirement is also removed during warning expansion, to allow gear up warnings. The actual data for each of the established areas is in tables stored in the Enhanced GPWC non-volatile memory. This data can be for either a snapshot area or an envelope modulation area. In fact, these areas can actually overlap since the envelope modulation is not performed until the snapshot conditions have been verified. Every snapshot has an associated envelope modulation area, but not every envelope modulation area has an associated snapshot area. This is because some locations use glide slope instead of the snapshot feature as a cross check on corrected altitude data. All of the data extracted for each location is used to form a unique key which establishes the aircraft position, orientation and altitude. Stored data for latitude, longitude, terrain elevation, expected elevation tolerance, minimum expected radio altitude, heading (track) and maximum allowable time to reach the envelope modulation area are compared to real time computed values for these parameters in order to set snapshot latch. This latch is intentionally stored in volatile RAM memory and cleared during power loss recovery. The associated signal validities are used to establish signal integrity prior to setting the snapshot latch. The maximum time term is used to clear the snapshot latch once this time has expired unless the envelope modulation conditions are satisfied first. Logic is required to satisfy one or more of the envelope modulation keys. In each case, if the key is required, the associated conditions are monitored. The following is a summary of the envelope modulation, and snapshot keys: ENVELOPE MODULATION KEYS ----------------------------------------------------------------------------| SELECTED KEY | DESCRIPTION | |------------------|--------------------------------------------------------| | ENVELOPE | REQUIRES VALID LATITUDE AND LONGITUDE TO BE WITHIN | | MODULATION AREA | DEFINED AREA | |------------------|--------------------------------------------------------| | G/S SELECTED | REQUIRES VALID GLIDE SLOPE WITHIN +/- 2 DOTS | |------------------|--------------------------------------------------------| | LOC SELECTED | REQUIRES VALID LOCALIZER WITHIN +/- 2 DOTS | |------------------|--------------------------------------------------------| | HDG SELECTED | REQUIRES VALID HEADING WITHIN +/- 30 DEG OF SELECTED | | | VALUE |

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----------------------------------------------------------------------------| SELECTED KEY | DESCRIPTION | |------------------|--------------------------------------------------------| |------------------|--------------------------------------------------------| | CRS SELECTED | REQUIRES VALID RUNWAY COURSE WITHIN +/- 10 DEG OF | | | SELECTED VALUE | | | If the aircraft installation does not provide runway | | | course (or selected heading) then this key is not | | | required. | |------------------|--------------------------------------------------------| | MIN ALTITUDE | REQUIRES VALID CORRECTED ALTITUDE (QFE OR QNH) TO BE | | SELECTED | GREATER THAN SELECTED VALUE | |------------------|--------------------------------------------------------| | SNAPSHOT SELECTED| REQUIRES SNAPSHOT DETECTED | ----------------------------------------------------------------------------SNAPSHOT KEYS ----------------------------------------------------------------------------| SELECTED KEY | DESCRIPTION | |------------------|--------------------------------------------------------| | SNAPSHOT AREA | REQUIRES VALID LATITUDE AND LONGITUDE TO BE WITHIN | | | DEFINED AREA | |------------------|--------------------------------------------------------| | HDG SELECTED | REQUIRES VALID HEADING WITHIN +/- 30 DEG OF SELECTED | | | VALUE | |------------------|--------------------------------------------------------| | MINIMUM RADIO | REQUIRES VALID RADIO ALTITUDE TO BE GREATER THAN | | ALTITUDE | SELECTED VALUE | |------------------|--------------------------------------------------------| | TERRAIN ELEVATION| REQUIRES TERRAIN ELEVATION (QFE OR QNH) TO BE WITHIN | | | A SPECIFIC TOLERANCE OF THE SELECTED VALUE | |------------------|--------------------------------------------------------| | MAXIMUM TIME | MAXIMUM TIME PERMITTED TO SATISFY ALL ENVELOPE | | | MODULATION KEYS AFTER LEAVING THE SNAPSHOT | |__________________|________________________________________________________| All of the keys, either by virtue of not being selected, or by being selected and satisfied, are required to enable envelope modulation. Envelope modulation parameters are either within the selected values if the keys fit, or defaulted to normal values if the keys do not fit. These parameters are used as inputs to the warning modes and thereby provide the mechanism for envelope modulation.

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D. Enhanced Features (1) Terrain Awareness alerting and Display (TAD) functions The terrain awareness component of the Enhanced GPWS is divided into functional blocks with an interface to Navigation Display. **ON A/C 105-105, (Ref. Fig. 017) R R

**ON A/C 001-049, 051-099, 101-104, 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 017A) **ON A/C ALL The highlighted blocks monitor aircraft position with respect to local terrain data base and provide rapid audio and visual alerts when a terrain threat is detected. Terrain threats are recognized and annunciated when terrain violates specific computed envelope boundaries forward of the aircraft path. The terrain awareness alert lamps and audio outputs behave in the same manner as the standard GPWS mode alerts. A terrain caution alert or terrain warning alert initiates a specific audio alert phrase (Ref. para.D.(1)(d)2_ and D.(1)(d)3_). Complementing the terrain threat alerts, the Enhanced GPWS also maintains a synthetic image of local terrain forward of the aircraft for display on EFIS Navigation Displays (ND). The Enhanced GPWS is configured to automatically de-select the weather display and pop-up a display of the terrain threats when they occur. The logic used provides an external input for predictive windshear alerts that can override a terrain display and revert to the weather display with the corresponding windshear data (if WR/PWS installed). The Enhanced GPWS provides two external display outputs, each with independent range-scaling control in the same fashion as a weather radar on both NDs. Changes of range scaling to one ND do not affect the other display. Each of these two independent outputs may be used to drive more than one display.

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Enhanced GPWS - Terrain Awareness Functions Figure 017   R EFF : 105-105,  34-48-00 Page A69   Config-1 Feb 01/08  CES

 

Enhanced GPWS - Terrain Awareness Functions Figure 017A   R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page A70 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

(a) Enhanced GPWS Input processing and signal selection function. **ON A/C 105-105, (Ref. Fig. 017) R R

**ON A/C 001-049, 051-099, 101-104, 106-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 017A) **ON A/C ALL The input processing and signal selection function conditions and formats aircraft data into proper form for use by the Enhanced GPWS while insulating the Enhanced GPWS from variations in aircraft type and configuration. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-228, 236-238, 301-302, 1 _

Aircraft data inputs Aircraft position latitude and longitude are required for terrain awareness operation and are received from the Global Positioning System (GPS). The Enhanced GPWS will use GPS and corrected IRS as valid position sources, if the figures of merit (FOM) of these sources exceed 0,5NM then FMS data will be used. The terrain peration and a threat detection and display processing are automatically disabled in some particular conditions. This is indicated to the flight crew by an ECAM memo (TERR STBY). (Ref. Fig. 010)

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-228, 236-238, 301-302, Post SB Post SB

31-1267 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, 31-1300 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, (Ref. Fig. 010A)

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**ON A/C 001-049, 051-099, 101-105, 151-199, 201-228, 236-238, 301-302, Additionally, aircraft ground track and ground speed data are received from the IR portion of the ADIRU 1 (IRS). The aircraft altitude MSL is received from the air data portion of the ADIRU 1. When QNH baro setting is selected on FCU, baro correction altitude (label 204) from ADIRU 1 is used. When STD baro setting is selected on FCU, standard altitude (label 203) from ADIRU 1 is used. When QFE baro setting is selected on FCU (assuming QFE option activated), the altitude is computed: - during take off, using standard altitude (label 203) from ADIRU 1 and landing elevation, - during approach, using standard altitude (label 203) from ADIRU 1 and QNH baro correction entered by the crew via the MCDU. On the MCDU, a prompt comes into view adjacent to the line key related to QNH information for input when < 180 NM from destination. Other aircraft inputs include aircraft heading (from the IR), roll attitude (from IR) and flight path angle (Gamma, derived by the Enhanced GPWC). R

**ON A/C ALL Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, 1 _

Aircraft data inputs The Enhanced GPWS will use GPS, corrected IRS and FMS as valid position sources and will inhibit itself automatically if all the figures of merit (FOM) for these sources exceed the current Enhanced GPWS required accuracy. The terrain threat detection and display processing are automatically disabled. This is indicated to the flight crew by an ECAM memo (TERR STBY).

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**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-310, 401-499, Post SB 34-1287 For A/C 220-228,236-238,301-302, Post SB 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, Post SB 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (Ref. Fig. 010) R

**ON A/C ALL Post SB Post SB Post SB Post SB Post SB

31-1267 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-310,401-499, 31-1300 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-310,401-499, 34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (Ref. Fig. 010A)

R

**ON A/C ALL Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, Additionally, aircraft ground track and ground speed data are received from the IR portion of the ADIRU 1 (IRS). The aircraft altitude MSL is received from the air data portion of the ADIRU 1. When QNH baro setting is selected on FCU, baro correction altitude (label 204) from ADIRU 1 is used. When STD baro setting is selected on FCU, standard altitude (label 203) from ADIRU 1 is used. When QFE baro setting is selected on FCU (assuming QFE option activated), the altitude is computed: - during take off, using standard altitude (label 203) from ADIRU 1 and landing elevation, - during approach, using standard altitude (label 203) from ADIRU 1 and QNH baro correction entered by the crew via the MCDU. On the MCDU, a prompt comes into view adjacent to the

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line key related to QNH information for input when < 180 NM from destination. Other aircraft inputs include aircraft heading (from the IR), roll attitude (from IR) and flight path angle (Gamma, derived by the Enhanced GPWC). Aircraft altitude for the Terrain Awareness functions is also computed from pressure altitude and SAT received from the air data portion of the ADIRU, altitude from the Global Positioning System (if available), and height above ground provided by the Radio Altimeter (RA). When GPS parameters are available via a specific Pin-Program, and from GPIRS, the Enhanced GPWS computes a Geometric Altitude. **ON A/C 106-149, 220-233, 301-304, 401-403, Post SB

34-1287 For A/C 220-228,301-302, 1 _

Aircraft data inputs Aircraft position latitude and longitude are required for terrain awareness operation and are received from the Global Positioning System (GPS). The Enhanced GPWS will use GPS and corrected IRS as valid position sources, if the figures of merit (FOM) of these sources exceed 0,5NM then FMS data will be used. The terrain peration and a threat detection and display processing are automatically disabled in some particular conditions. This is indicated to the flight crew by an ECAM memo (TERR STBY). (Ref. Fig. 010)

**ON A/C 106-149, 220-233, 301-304, 401-403, Post SB Post SB Post SB

31-1267 For A/C 106-149,220-233,301-304,401-403, 31-1300 For A/C 106-149,220-233,301-304,401-403, 34-1287 For A/C 220-228,301-302, (Ref. Fig. 010A)

**ON A/C 106-149, 220-233, 301-304, 401-403, Post SB

34-1287 For A/C 220-228,301-302, Additionally, aircraft ground track and ground speed data are received from the IR portion of the ADIRU 1 (IRS). The aircraft altitude MSL is received from the air data portion of the ADIRU 1.

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When QNH baro setting is selected on FCU, baro correction altitude (label 204) from ADIRU 1 is used. When STD baro setting is selected on FCU, standard altitude (label 203) from ADIRU 1 is used. When QFE baro setting is selected on FCU (assuming QFE option activated), the altitude is computed: - during take off, using standard altitude (label 203) from ADIRU 1 and landing elevation, - during approach, using standard altitude (label 203) from ADIRU 1 and QNH baro correction entered by the crew via the MCDU. On the MCDU, a prompt comes into view adjacent to the line key related to QNH information for input when < 180 NM from destination. Other aircraft inputs include aircraft heading (from the IR), roll attitude (from IR) and flight path angle (Gamma, derived by the Enhanced GPWC). Aircraft altitude for the Terrain Awareness functions is also computed from pressure altitude and SAT received from the air data portion of the ADIRU, altitude from the Global Positioning System (if available), and height above ground provided by the Radio Altimeter (RA). When GPS parameters are available via a specific Pin-Program, and from GPIRS, the Enhanced GPWS computes a Geometric Altitude. R

**ON A/C ALL 2 _

Control Inputs Installations provide discrete terrain display select pushbutton switches (TERR ON ND) in the cockpit for each display. These are momentary-action pushbutton switches that are processed by the Enhanced GPWS input processing and signal selection block as input to display control logic. Additionally, for aircraft with predictive windshear radar capability (if WR/PWS installed), a windshear override boolean is computed using alert level bits from label 077 on WXR hazard bus for the display control logic.

**ON A/C 105-105, (Ref. Fig. 005)

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R

**ON A/C 501-509, 511-526, 528-599, (Ref. Fig. 005A) **ON A/C 001-049, 051-099, 101-104, 106-149, 151-199, 201-233, 236-238, 301-304, 401-403, Post SB 34-1147 For A/C 001-004,051-060, (Ref. Fig. 005B) **ON A/C 239-249, Post SB Post SB Post SB

001-049, 061-099, 101-104, 106-149, 151-199, 201-219, 229-235, 251-299, 303-399, 401-499, 34-1147 For A/C 001-004, 34-1351 For A/C 001-049,061-099,101-104,151-199,201-219, 34-1352 For A/C 001-049,061-099,101-104,106-149,151-199,201-219, 229-233,303-304,401-403, (Ref. Fig. 005C)

**ON A/C 051-060, 220-228, 236-238, 301-302, Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 051-060,220-228,236-238,301-302, 34-1352 For A/C 051-060,220-228,236-238,301-302, (Ref. Fig. 005D)

**ON A/C 105-105, Post SB Post SB

34-1351 For A/C 105-105, 34-1352 For A/C 105-105, (Ref. Fig. 005E)

**ON A/C ALL This boolean allows the Enhanced GPWC to manage priority between Enhanced GPWC alerts and PWS alerts. The installation requires input of cockpit-selected range scales provided by the FCU for each ND.

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R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, (b) Local Terrain Processing The local terrain processing block extracts and formats local topographic data and terrain features from the related data bases creating a set of digital elevation matrix overlays for use by the terrain threat detection and display processing functions. Additionally, data for the nearest runway are also extracted for use by the terrain threat detection and display processing functions. Processing for each topographic data base and the runway data base are described in the following sub-sections. 1 _

Terrain Surface Data Local terrain processing of topographic surface data updates a set of digital elevation matrix overlays that are positioned with respect to aircraft position. Each matrix element contains the highest terrain altitude with respect to mean sea level in that element area. Elements where terrain data are not available are marked invalid. These unknown data are displayed in magenta low density on ND whatever the altitude.

2 _

Obstacle Data In addition to terrain surface data, provisions are made for future use of an obstacle data base providing obstacle data in the vicinity of major airports. Local terrain processing will update a dedicated overlay within the digital elevation matrix overlays with local obstacle altitude data.

3 _

Nearest Runway Data Data for the nearest runway are extracted and processed for use by the terrain threat detection and display processing functions. Data are extracted from the same airport data base used by the Terrain Clearance Floor functions (Ref. para. D.(2)). This data base contains data on all hard-surface runways 3500 ft. or more in length with published coordinates. The contents of the data base are processed by the local terrain processing into nearest runway center position, nearest runway threshold position, and nearest runway altitude for use by the Enhanced GPWS. These data are updated when the terrain threat detection and display processing functions are performed.

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R

**ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, (b) Local Terrain Processing The local terrain processing block extracts and formats local topographic data and terrain features from the related data bases creating a set of digital elevation matrix overlays for use by the terrain threat detection and display processing functions. Additionally, data for the nearest runway are also extracted for use by the terrain threat detection and display processing functions. Processing for each topographic data base and the runway data base are described in the following sub-sections. 1 _

Terrain Surface Data Local terrain processing of topographic surface data updates a set of digital elevation matrix overlays that are positioned with respect to aircraft position. Each matrix element contains the highest terrain altitude with respect to mean sea level in that element area. Elements where terrain data are not available are marked invalid. These unknown data are displayed in magenta low density on ND whatever the altitude.

2 _

Obstacle Data In addition to terrain surface data, the terrain database contains obstacle data. The obstacle data are displayed as terrain data (same coloring scheme) and cause visual indications of warning and caution alerts as terrain. The current obstacle database is obtained from N.O.A.A. (National Oceanic and Atmospheric Administration). It includes obtacles in the United States and part of Canada, Mexico, the Bahamas and Europe. Obstacle alerting and display is activated via a specific programming pin.

3 _

Nearest Runway Data Data for the nearest runway are extracted and processed for use by the terrain threat detection and display processing functions. Data are extracted from the same airport data base used by the Terrain Clearance Floor functions (Ref. para. D.(2)). This data base contains data on all hard-surface runways 3500 ft. or more in length with published coordinates. The contents of the data base are processed by the local terrain processing into nearest runway center position, nearest runway threshold position, and nearest runway altitude for use by the Enhanced GPWS. These data are updated when the

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terrain threat detection and display processing functions are performed. R

**ON A/C ALL (c) Terrain Threat Detection The terrain threat detection and display processing block performs the threat analysis on the terrain data within computed caution and warning envelope boundaries below and forward of the aircraft path. Results of these threat assessments are combined with background terrain data and data for the nearest runway and formatted into a terrain display image which can be displayed on Navigation Display in place of the weather image. In the event of terrain caution or warning conditions, a specific audio alert is triggered and the terrain display image is enhanced to highlight each of the types of terrain threats. 1 _

Terrain Caution and Warning Envelopes (Ref. Fig. 018) a _

Caution Altitude Floor The caution altitude floor (or terrain floor) is computed as a function of aircraft altitude with respect to nearest runway altitude and range to the nearest runway threshold position. This parameter represents a distance below the aircraft. The relationship to the nearest runway threshold location prevents undesired alerts when the aircraft is taking off or landing at an airport. The system is compatible with terrain clearances allowed for by regulatory approach and departure design criteria.

b _

Caution Look Ahead Distance The caution look ahead distance is computed from aircraft ground speed and turn rate to provide an advanced caution with adequate time for the crew to react safely. Depending on the situation this distance roughly corresponds to between 40 and 60 seconds for advance alerting.

c _

Warning Altitude Floor The warning altitude floor is set to a fraction of the caution altitude floor, as illustrated in the upper part of this illustration. (Ref. Fig. 018)

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Enhanced GPWS - Terrain Detection Envelope Figure 018   R EFF : ALL  34-48-00 Page A80   Config-1 Nov 01/09  CES

 

The warning altitude floor is computed as a function of aircraft altitude with respect to nearest runway altitude and range to the nearest runway threshold position. This parameter represents a distance below the aircraft. The relationship to the nearest runway threshold location prevents undesired alerts when the aircraft is taking off or landing at an airport. d _

R

Warning Look Ahead Distance The warning look ahead distance is a fraction of the caution look ahead distance (computed from aircraft ground speed and turn rate) to provide an advanced warning with adequate time for the crew to react safely.

**ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, e _

Cut off altitude around airport The Enhanced GPWS look ahead algorithms as well as the terrain display ignores all terrain and obstacles below a calculated altitude define as the Absolute Cut Off Altitude (ACOA). ACOA de-clutters terrain around airport, especially during final approach when the aircraft normally approaches the ground. It also has the effect to clearly showing the runway approach and departure routes on the terrain display because the valley floors will typically be black. Cut off altitude value depends on the destination runway and is comprised between 200ft and 400ft.

**ON A/C 106-149, 215-233, 236-238, 301-304, (d) Terrain Displays and Alerts (Ref. Fig. 019, 020) The terrain awareness alerting and display function maintains a background display of local terrain forward of the aircraft for cockpit display. In the event of terrain caution or warning conditions, an aural alert and lamp outputs are triggered. The background image is then enhanced to highlight related terrain threats forward of the aircraft. The background terrain is depicted as variable density dot patterns in green, yellow or red. The density and color being a function of how close the terrain is relative to aircraft altitude. Terrain alerts are depicted by painting the threatening terrain as solid yellow or red.

  R EFF : ALL  34-48-00 Page A81   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Terrain Background Display Legend Figure 019   R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page A82 201-233, 236-238, 301-304,  Config-1 Feb 01/08  CES

 

Enhanced GPWS - Terrain Background Display on ND Figure 020   R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page A83 201-233, 236-238, 301-304,  Config-1 Feb 01/08  CES

 

The set of digital elevation matrix overlays is processed by the terrain display algorithms into a matching set of display matrix overlays and passed to the radar display output processor. The display matrix overlays hold display attributes rather than altitude for each matrix element. These attributes are computed for the background and terrain threat areas and kept small (one byte) to reduce memory requirements and transfer time to the radar display output processor. The aircraft position and aircraft heading are used at the radar display output processor to extract a specific sweeping image ahead of the aircraft from the display overlays. Each element of the output display matrix overlays holds a single display attribute byte with fields for the colors, patterns, and symbols shown in the following table: ------------------------------------------------------------------------------| Color | Threat | ------------------------------------------------------------------------------| Solid Red | Warning terrain (approximately 30 seconds from | | | impact) | |---------------------|-------------------------------------------------------| | Solid Yellow | Caution terrain (approximately 60 seconds from | | | impact) | |---------------------|-------------------------------------------------------| | High Density Red | Terrain that is more than 2000 ft. above aircraft | | | altitude | |---------------------|-------------------------------------------------------| | High Density | Terrain that is between 1000 and 2000 ft. above | | Yellow | aircraft altitude | |---------------------|-------------------------------------------------------| | Medium Density | Terrain that is 500 (250 with gear down) ft. below | | Yellow | to 1000 ft. above aircraft altitude | |---------------------|-------------------------------------------------------| | Medium Density | Terrain that is 500 (250 with gear down) ft. below | | Green | to 1000 ft. below aircraft altitude | |---------------------|-------------------------------------------------------| | Light Density Green | Terrain that is 1000 to 2000 ft. below aircraft | | | altitude | |---------------------|-------------------------------------------------------| | Black | No close terrain (Ref. NOTE in para. D.(1)(d)1_) | |---------------------|-------------------------------------------------------| | Light Density | Unknown terrain | | Magenta | | -------------------------------------------------------------------------------

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1 _

Background Display (Ref. Fig. 020) The background display is computed from the aircraft altitude with respect to the terrain data in the digital elevation matrix overlays. Where terrain data are available and sufficiently close to the aircraft altitude, they are presented in background color dot patterns reflecting the projected separations shown in this illustration. (Ref. Fig. 019) Different dot density patterns and colors are used to represent terrain altitude bands with respect to the aircraft. Areas with no terrain data available are painted with the low density magenta. Known terrain sufficiently below the aircraft altitude is black. NOTE : Terrain is not shown if more than 2000 ft. below ____ reference altitude AND/OR Terrain is not shown if terrain elevation is within 400 ft. of runway elevation nearest the aircraft.

2 _

Terrain Caution Alert (Ref. Fig. 021) When the conditions have been met to generate a terrain caution alert, a specific audio alert and light output is triggered and the background image is enhanced to highlight the terrain caution threats. At the start of a terrain caution alert, the terrain awareness function triggers the caution audio alert phrase TERRAIN AHEAD. The phrase is repeated after seven seconds if still within the terrain caution envelope. During a terrain caution alert the PULL UP legend of pushbutton switches 4WZ and 5WZ is on. During a terrain caution alert, areas where terrain violates the terrain caution envelope along the aircraft track, and within plus or minus 90 deg. of the aircraft track, are painted with the caution color 100 per cent yellow.

3 _

Terrain Warning Alert (Ref. Fig. 021) When the conditions have been met to generate a terrain warning alert, a specific audio alert and light output is triggered and the background image is enhanced to highlight the terrain caution and warning threats.

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Enhanced GPWS - Warning and Caution Display on ND Figure 021   R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page A86 201-233, 236-238, 301-304,  Config-1 Feb 01/08  CES

 

At the start of a terrain warning alert, the terrain awareness function triggers the warning audio alert phrase TERRAIN AHEAD, PULL UP. The phrase is repeated continuously while within the terrain warning envelope. During a terrain warning alert the PULL UP legend of pushbutton switches 4WZ and 5WZ is on. During a terrain warning alert, areas where terrain violates the terrain warning envelope along the aircraft track, and within plus or minus 90 deg. of the aircraft track, are painted with the warning color 100 per cent red. NOTE : -Terrain may only be displayed on NDs when FCU mode ____ ARC or ROSE is selected. -When an alert occurs (caution or warning) and the FCU mode is not in a correct mode (ARC or ROSE), the message TERR. CHANGE MODE is displayed on NDs. -When an alert occurs (caution or warning) and the FCU range selected is 160 or 320Nm the message TERR. REDUCE RANGE is displayed on NDs. (e) Terrain Data Base Local terrain processing extracts and formats local topographic terrain data from the Enhanced GPWS terrain data base for use by the terrain threat detection and display processing functions. This terrain data base divides the earth surface into grid sets referenced horizontally on the geographic (latitude/longitude) coordinate system of the WGS-84. Elements of the grid sets record the highest terrain altitude (above MSL) in that element respective area. Grid sets vary in resolution depending on geographic location. Higher resolution grids are used around airports. Lower resolution grids are used outside of airport areas where aircraft altitude enroute makes hazardous conditions unlikely and for which detailed terrain features are not important to the flight crew. Digital Elevation Models (DEM) are available for most of the airports around the world today. In cases where the data are not currently available, DEMs are generated in-house from available topographic maps, sectional charts, and airline approach plates. The process of acquiring, generating, assembling, and updating the data base is governed by strict configuration controls to ensure the highest level of data integrity. DEMs from external sources are inputs to this process and are checked and formatted for generation of the Enhanced GPWS terrain data base. The global Enhanced GPWS terrain data base is organized in a flexible manner. Using digital compression techniques, the complete data base is stored in non-volatile memory within the LRU. Updates and additions are easily accomplished by inserting a

  R EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00 Page A87   Config-1 Feb 01/08  CES

 

single PCMCIA card in the card slot on the LRU front panel. Status LEDs on the LRU front panel allow the operator to monitor the data base load progress and completion. (f) Obstacle Data Base Provisions are also made for future use of an obstacle data base providing obstacle data in the vicinity of major airports. This data base will provide altitude for man-made obstacles or groups of obstacles that protrude above the Enhanced GPWS terrain protection floors. R **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, (d) Terrain Displays and Alerts (Ref. Fig. 019, 020) The terrain awareness alerting and display function maintains a background display of local terrain forward of the aircraft for cockpit display. In the event of terrain caution or warning conditions, an aural alert and lamp outputs are triggered. The background image is then enhanced to highlight related terrain threats forward of the aircraft. The background terrain is depicted as variable density dot patterns in green, yellow or red. The density and color being a function of how close the terrain is relative to aircraft altitude. Terrain alerts are depicted by painting the threatening terrain as solid yellow or red. The set of digital elevation matrix overlays is processed by the terrain display algorithms into a matching set of display matrix overlays and passed to the radar display output processor. The display matrix overlays hold display attributes rather than altitude for each matrix element. These attributes are computed for the background and terrain threat areas and kept small (one byte) to reduce memory requirements and transfer time to the radar display output processor. The aircraft position and aircraft heading are used at the radar display output processor to extract a specific sweeping image ahead of the aircraft from the display overlays. Each element of the output display matrix overlays holds a single display attribute byte with fields for the colors, patterns, and symbols shown in the following table:

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page A88 201-233, 236-238, 301-304,  Config-1 Nov 01/08  CES

 

------------------------------------------------------------------------------| Color | Threat | ------------------------------------------------------------------------------| Solid Red | Warning terrain (approximately 30 seconds from | | | impact) | |---------------------|-------------------------------------------------------| | Solid Yellow | Caution terrain (approximately 60 seconds from | | | impact) | |---------------------|-------------------------------------------------------| | High Density Red | Terrain that is more than 2000 ft. above aircraft | | | altitude | |---------------------|-------------------------------------------------------| | High Density | Terrain that is between 1000 and 2000 ft. above | | Yellow | aircraft altitude | |---------------------|-------------------------------------------------------| | Medium Density | Terrain that is 500 (250 with gear down) ft. below | | Yellow | to 1000 ft. above aircraft altitude | |---------------------|-------------------------------------------------------| | Medium Density | Terrain that is 500 (250 with gear down) ft. below | | Green | to 1000 ft. below aircraft altitude | |---------------------|-------------------------------------------------------| | Light Density Green | Terrain that is 1000 to 2000 ft. below aircraft | | | altitude | |---------------------|-------------------------------------------------------| | Black | No close terrain (Ref. NOTE in para. D.(1)(d)1_) | |---------------------|-------------------------------------------------------| | Light Density | Unknown terrain | | Magenta | | ------------------------------------------------------------------------------1 _

Background Display (Ref. Fig. 020) The background display is computed from the aircraft altitude with respect to the terrain data in the digital elevation matrix overlays. Where terrain data are available and sufficiently close to the aircraft altitude, they are presented in background color dot patterns reflecting the projected separations shown in this illustration. (Ref. Fig. 019) Different dot density patterns and colors are used to represent terrain altitude bands with respect to the aircraft. Areas with no terrain data available are painted with the low density magenta. Known terrain sufficiently below the aircraft altitude is black. NOTE : Terrain is not shown if more than 2000 ft. below ____ reference altitude

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AND/OR Terrain is not shown if terrain elevation is within 400 ft. of runway elevation nearest the aircraft. 2 _

Terrain Caution Alert (Ref. Fig. 021) When the conditions have been met to generate a terrain caution alert, a specific audio alert and light output is triggered and the background image is enhanced to highlight the terrain caution threats. At the start of a terrain caution alert, the terrain awareness function triggers the caution audio alert phrase TERRAIN AHEAD. The phrase is repeated after seven seconds if still within the terrain caution envelope. During a terrain caution alert, the GPWS legend of pushbutton switches 4WZ and 5WZ is on. During a terrain caution alert, areas where terrain violates the terrain caution envelope along the aircraft track, and within plus or minus 90 deg. of the aircraft track, are painted with the caution color 100 per cent yellow.

3 _

Terrain Warning Alert (Ref. Fig. 021) When the conditions have been met to generate a terrain warning alert, a specific audio alert and light output is triggered and the background image is enhanced to highlight the terrain caution and warning threats. At the start of a terrain warning alert, the terrain awareness function triggers the warning audio alert phrase TERRAIN AHEAD, PULL UP. The phrase is repeated continuously while within the terrain warning envelope. During a terrain warning alert, the GPWS legend of pushbutton switches 4WZ and 5WZ is on. During a terrain warning alert, areas where terrain violates the terrain warning envelope along the aircraft track, and within plus or minus 90 deg. of the aircraft track, are painted with the warning color 100 per cent red. NOTE : -Terrain may only be displayed on NDs when FCU mode ____ ARC or ROSE is selected. -When an alert occurs (caution or warning) and the FCU mode is not in a correct mode (ARC or ROSE), the message TERR. CHANGE MODE is displayed on NDs. -When an alert occurs (caution or warning) and the FCU range selected is 160 or 320Nm the message TERR. REDUCE RANGE is displayed on NDs.

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page A90 201-214,  Config-1 Nov 01/08  CES

 

(e) Terrain Data Base Local terrain processing extracts and formats local topographic terrain data from the Enhanced GPWS terrain data base for use by the terrain threat detection and display processing functions. This terrain data base divides the earth surface into grid sets referenced horizontally on the geographic (latitude/longitude) coordinate system of the WGS-84. Elements of the grid sets record the highest terrain altitude (above MSL) in that element respective area. Grid sets vary in resolution depending on geographic location. Higher resolution grids are used around airports. Lower resolution grids are used outside of airport areas where aircraft altitude enroute makes hazardous conditions unlikely and for which detailed terrain features are not important to the flight crew. Digital Elevation Models (DEM) are available for most of the airports around the world today. In cases where the data are not currently available, DEMs are generated in-house from available topographic maps, sectional charts, and airline approach plates. The process of acquiring, generating, assembling, and updating the data base is governed by strict configuration controls to ensure the highest level of data integrity. DEMs from external sources are inputs to this process and are checked and formatted for generation of the Enhanced GPWS terrain data base. The global Enhanced GPWS terrain data base is organized in a flexible manner. Using digital compression techniques, the complete data base is stored in non-volatile memory within the LRU. Updates and additions are easily accomplished by inserting a single PCMCIA card in the card slot on the LRU front panel. Status LEDs on the LRU front panel allow the operator to monitor the data base load progress and completion. (f) Obstacle Data Base Provisions are also made for future use of an obstacle data base providing obstacle data in the vicinity of major airports. This data base will provide altitude for man-made obstacles or groups of obstacles that protrude above the Enhanced GPWS terrain protection floors.

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**ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (d) Terrain / obstacle displays and Alerts

R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304, (Ref. Fig. 022)

R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304,401-403, (Ref. Fig. 023) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, The terrain awareness alerting and display function maintains a background display of local terrain forward of the aircraft for cockpit display. In the event of terrain or obstacle caution or warning conditions, an aural alert and lamp outputs are triggered. The background image is then enhanced to highlight terrain or obstacle threats forward of the aircraft. Obstacle threats forward of the aircraft are also enhanced if the adjacent terrain altitude is within a lowerterrain layer, or if the adjacent cells are not illuminated. Obstacle enhancement is only applicable to the 15, 30 and 60 arc second tiers. The background terrain is depicted as variable density dot patterns in green, yellow or red. The density and color vary according to how close the terrain or obstacle in relation to aircraft altitude. Additionally, the display of terrain based on absolute terrain elevation is provided if the optional Peaks mode is enabled. Terrain and obstacle alerts are depicted by displaying the threatening terrain as solid yellow and/or red.

  EFF : ALL  34-48-00 Page A92   Config-1 Feb 01/10  CES

 

Enhanced GPWS - Warning and Caution Display on ND (with EIS2) Figure 021A   R EFF : ALL  34-48-00 Page A93   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Peaks Terrain background display legend Figure 022   R EFF : ALL  34-48-00 Page A94   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Terrain background display on ND Figure 023   R EFF : ALL  34-48-00 Page A95   Config-1 Nov 01/09  CES

 

The terrain display algorithms process the set of digital elevation matrix overlays into a matching set of display matrix overlays and passed to the radar display output processor. The display matrix overlays hold display attributes rather than altitude for each matrix element. These attributes are computed for the background and terrain threat areas and kept small to reduce memory requirements and transfer time to the radar display output processor. The aircraft position and aircraft heading are used at the radar display output processor to extract the radar-like sweeping image ahead of the aircraft from the display overlays. Each element of the output display matrix overlays holds a single display attribute byte with fields for the colors, patterns, and symbols shown in the following table: ------------------------------------------------------------------------------| Color | Threat | ------------------------------------------------------------------------------| Solid Red | Warning terrain (approximately 30 seconds from | | | impact) | |---------------------|-------------------------------------------------------| | Solid Yellow | Caution terrain (approximately 60 seconds from | | | impact) | |---------------------|-------------------------------------------------------| | High Density Red | Terrain that is more than 2000 ft. above aircraft | | | altitude | |---------------------|-------------------------------------------------------| | High Density | Terrain that is between 1000 ft. and 2000 ft. above | | Yellow | aircraft altitude | |---------------------|-------------------------------------------------------| | Medium Density | Terrain that is 500 ft. (250 ft. with gear down) | | Yellow | below to 1000 ft. above aircraft altitude | |---------------------|-------------------------------------------------------| | Solid Green | (Peaks only) Highest terrain not within 500 ft. | | | (250 ft. with gear down) of aircraft altitude. | | | Mainly appears with dotted yellow terrain when the | | | aircraft altitude is within 500 ft. (250 ft. with | | | gear down) of terrain. | |---------------------|-------------------------------------------------------| | Hight Density | Terrain that is 500 ft. (250 ft. with gear down) below| | Green Dots (1) | to 1000 ft. below aircraft altitude. | | |-------------------------------------------------------| | | (Peaks only) Terrain that is the middle elevation band| | | when there are no red or yellow terrain areas within | | | range on the display. | |---------------------|-------------------------------------------------------| | Low Density | Terrain that is 1000 ft. to 2000 ft. below aircraft |

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------------------------------------------------------------------------------| Color | Threat | ------------------------------------------------------------------------------| Green Dots | altitude. | | |-------------------------------------------------------| | | (Peaks only) Terrain that is the middle elevation band| | | when there are no red or yellow terrain areas within | | | range on the display | |---------------------|-------------------------------------------------------| | Black | No close terrain (Ref. NOTE in para. D.(1)(d)1_) | |---------------------|-------------------------------------------------------| | Low Density | (Peaks only) Terrain elevation equal to 0 ft. MSL. | | Cyan Dots | | |---------------------|-------------------------------------------------------| | Light Density | Unknown terrain | | Magenta | | ------------------------------------------------------------------------------1 _ R R

Background display (Option)

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304, (Ref. Fig. 022) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, There are two different background Terrain Awareness display mode: standard and Peaks. For both modes the background display is computed from the aircraft altitude with respect to the terrain data in the digital elevation matrix overlays. - Standard mode Terrain is displayed using colors and shading patterns corresponding to the vertical displacement between the terrain elevation and the current aircraft altitude. Red and yellow dot patterns indicate terrain near or above the current altitude of the aircraft. Solid yellow and red colors indicate caution and warning areas with respect to the flight path of the aircraft. High and low density green display patterns indicate terrain that is below the aircraft and within 2000 ft. of the aircraft altitude. Terrain more than 2000 ft. below the

  EFF : ALL  34-48-00 Page A97   Config-1 Feb 01/10  CES

 

aircraft is not displayed and the terrain display is typically blank during the enroute portion of the flight. - Peaks mode The Peaks terrain display adds additional density patterns and level thresholds to the standard mode display levels and patterns. These additionallevels are based on absolute terrain elevations in relation to the range and distribution of terrain in the display area. The Peaks display is thus a merged display applicable to all phases of flight. At altitude safely above all terrain for the display range chosen, the terrain is displayed independent of aircraft altitude emphasizing the highest and lowest elevations to provide increased situational awareness. This increased awareness can be particularly valuable to the flight crew in the event of an unplanned descent or off-route deviation and for the purpose of previewing terrain prior to descent. The Peaks display includes a high green level to indicate the highest non-threatening terrain. The standard lower density green display patterns indicate mid and upper terrain in the display area as well as terrain that is within 2000 ft.of the aircraft. The red and yellow dot patterns are unchanged and continue to indicate terrain that is near or above the current altitude of the aircraft. Solid yellow and red colors are also unchanged and continue to indicate caution and warning areas in relation to the flight path of the aircraft. Terrain identified as water (0 ft. MSL) is displayed as cyan dots. The Peaks display is prioritized such that higher level colors and densities override lower color and densities for maximum situational awareness of the most significant terrain in relation to the altitude and flight path of the aircraft. R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304, (Ref. Fig. 022) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, With the Peaks display, on EIS 2, two elevation numbers indicating the highest and lowest terrain currently being displayed are shown on the display. The elevation numbers

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indicate terrain in hundred of feet above sea level (MSL). The terrain elevation numbers are displayed with the highest terrain number on top, and the lowest terrain number beneath it. The highest terrain number is shown in the same color as the highest terrain color pattern on the display, and the lowest terrain number is shown in the color of the lowest terrain color pattern shown on the display. A single elevation number is displayed when the screen is all black or blue as a result of flying over water or relatively flat terrain where there is no appreciable difference in terrain elevations. On EIS 1, only the highest elevation number is displayed within the terrain frame. The elevation numbers on the display are an additional indication that the terrain display is selected. R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304,401-403, (Ref. Fig. 023) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, 2 _

R R

Terrain and Obstacle caution alert (option)

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304, (Ref. Fig. 021A) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, When the conditions have been met to generate a terrain or obstacle caution alert, a specific audio alert and light output is triggered and the background image is enhanced to highlight the terrain caution threats.

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At the start of a terrain caution alert, the Terrain Awareness function triggers the caution audio alert phrase TERRAIN AHEAD, TERRAIN AHEAD. The phrase is repeated after seven seconds if still within the terrain caution envelope. The Terrain Awareness function respond to an obstacle caution alert by triggering the obstacle caution audio alert phrase OBSTACLE AHEAD, OBSTACLE AHEAD. The phrase is repeated after seven seconds if still within the terrain caution envelope. During a terrain caution alert or obstacle caution alert, the GPWS legend of the PULL UP/GPWS pushbutton switches 4WZ and 5WZ is on. During a terrain caution alert, areas where terrain violates the terrain caution envelope along the aircraft track, and within plus or minus 90 deg. of the aircraft track, are painted with the caution color 100 per cent yellow. During an obstacle caution alert areas where an obstacle violates the terraincaution envelope along the aircraft track, and within plus or minus 90 deg. of the aircraft track, are displayed with the caution color yellow. 3 _ R R

Terrain and obstacle warning alert (option)

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304, (Ref. Fig. 021A) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, When the conditions have been met to generate a terrain or obstacle warning alert, a specific audio alert and light output is triggered and the background image is enhanced to highlight the terrain or obstacle caution and warning threats. At the start of a terrain warning alert, the Terrain Awareness function triggers the warning audio alert phrase TERRAIN AHEAD, PULL UP. The phrase is repeated continuously while within the terrain warning envelope. The Terrain Awareness function responds to an obstacle warning alert by triggering the obstacle warning audio alert OBSTACLE AHEAD, PULL UP. The phrase is repeated continuously while within the terrain warning envelope.

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During a terrain or obstacle warning alert, the PULL UP legend of the PULL UP/GPWS pushbutton switches 4WZ and 5WZ is on. During a terrain warning alert, areas where terrain violates the terrain warning envelope along the aircraft track, and within plus or minus 90 deg. of the aircraft track, are displayed with the warning color 100 per cent red. NOTE : - Terrain is displayed on NDs if the ARC or ROSE mode ____ is selected on the FCU. - When an alert (caution or warning) occurs and the FCU mode is not a correct mode (ARC or ROSE), the message TERR. CHANGE MODE is displayed on NDs. - When an alert (caution or warning) occurs and the range selected on the FCU is 160 or 320 NM the message TERR. REDUCE RANGE is displayed on NDs. (e) Terrain Data Base Local terrain processing extracts and formats local topographic terrain data from the Enhanced GPWS terrain data base for use by the terrain threat detection and display processing functions. This terrain data base divides the earth surface into grid sets referenced horizontally on the geographic (latitude/longitude) coordinate system of the WGS-84. Elements of the grid sets record the highest terrain altitude (above MSL) in that element respective area. Grid sets vary in resolution depending on geographic location. Higher resolution grids are used around airports. Lower resolution grids are used outside airport areas where aircraft enroute altitude makes hazardous conditions unlikely and for which detailed terrain features are not important to the flight crew. Digital Elevation Models (DEM) are available for most of the airports around the world today. In cases where the data are not currently available, DEMs are generated in-house from available topographic maps, sectional charts, and airline approach plates. The process of acquiring, generating, assembling, and updating the data base is governed by strict configuration controls to ensure the highest level of data integrity. DEMs from external sources are input to this process, and are checked and formatted for generation of the Enhanced GPWS terrain data base. The global Enhanced GPWS terrain data base is organized in a flexible manner. Using digital compression techniques, the complete data base is stored in non-volatile memory within the Enhanced GPWC. Updates and additions are easily accomplished by inserting a single PCMCIA card in the card slot on the face of the Enhanced GPWC. Status LEDs on the face of the Enhanced GPWC allow the operator to monitor the data base load progress and completion.

  R EFF : ALL  34-48-00 Page B1   Config-1 Nov 01/09  CES

 

(f) Obstacle database (option) The obstacle database is included with the terrain database in the terrain database PCMCIA card. Both files are loaded in the Enhanced GPWC with the obstacle database being accessed by the Enhanced GPWS application only if obstacle alerting is basic to the aircraft type, or if not basic, if enabled via program pin. The obstacle data is processed by the display processing function in the same fashion as terrain is presented on the display as terrain (coloring scheme), and causes visual indications of warning and caution alerts like terrain. **ON A/C 215-228, 236-238, 301-302, (2) Terrain Clearance Floor (TCF) The Terrain Clearance Floor (TCF) alert function adds an additional element of protection to the standard Ground Proximity Warning System. It creates an increasing terrain clearance envelope around the airport runway to provide protection against Controlled Flight Into Terrain (CFIT) situations beyond that which is currently provided. TCF alerts are based on current aircraft location, nearest runway center point position and radio altitude. TCF is active during takeoff, cruise and final approach. This alert mode complements the existing Mode 4 protection by providing an alert based on insufficient terrain clearance even when in landing configuration. Alerts for TCF illuminate GPWS cockpit lamps and produce aural messages. (a) System inputs The following table lists the inputs required to allow implementation of the TCF function: ------------------------------------------------------------------------------| Input | Source | ------------------------------------------------------------------------------| Radio Altitude | External: Radio Altimeter | |----------------------------------|------------------------------------------| | Latitude | External: FMS | |----------------------------------|------------------------------------------| | Longitude | External: FMS | |----------------------------------|------------------------------------------| | Runway Center Latitude | Internal: data base | |----------------------------------|------------------------------------------| | Runway Center Longitude | Internal: data base | |----------------------------------|------------------------------------------| | Navigation mode | FMS | |----------------------------------|------------------------------------------|

  R EFF : ALL  34-48-00 Page B2   Config-1 Nov 01/09  CES

 

------------------------------------------------------------------------------| Input | Source | ------------------------------------------------------------------------------| Alert Envelope Parameters | Internal: data base | |----------------------------------|------------------------------------------| | 1/2 Runway Length | Internal: data base | |----------------------------------|------------------------------------------| | System Error Factor | Internal: data base | ------------------------------------------------------------------------------(b) Runway Data Base The TCF runway data base consists of data records containing the position of airport runway center points along with 1/2 the runway length. The data base includes all hard surface runways in the world greater than or equal to 3500 ft. in length. The process of generating this data base is certified and includes an end check that validates that the data was not corrupted in the translation process. This data base can be updated without affecting the customer certified system part number. The design of the data base and related software is such that additional runway records can be added in the future without altering the code. The data base provides a means of accessing the runway record of the runway closest to the current aircaft position. (c) Alert Envelope The TCF alert envelope is a circular band centered over the nearest runway. (Ref. Fig. 024) The distance from the runway center to the inner envelope edge is equal to 1/2 the runway length plus the envelope bias factor. Thus the inner and outer radius of the envelope are modulated based on the runway length and envelope bias factor. Runway length varies from one runway to the next, and the envelope bias factor is typically 1/2 NM to 2 NM and varies with position accuracy. The outer alert envelope boundary extends to infinity, or until it meets the outer alert envelope boundary of another runway. The alert is inhibited below radio altitude of 30 ft. This cutoff value was chosen to match the current Mode 4 lower cutoff value.

  R EFF : 215-228, 236-238, 301-302,  34-48-00 Page B3   Config-1 Nov 01/08  CES

 

Enhanced GPWS - TCF Alert Envelope Figure 024   R EFF : ALL  34-48-00 Page B4   Config-1 Nov 01/09  CES

 

(d) System Outputs When an aircraft penetrates the TCF alert envelope the following aural message occurs: TOO LOW TERRAIN. This aural message occurs once when initial envelope penetration occurs, and one time thereafter for each 20 per cent degradation in radio altitude. At the same time the PULL UP legend of pushbutton switches 4WZ and 5WZ comes on. The legends remain on until the alert envelope is exited. (3) Not Applicable (4) Not Applicable **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, (2) Terrain Clearance Floor (TCF) The Terrain Clearance Floor (TCF) alert function adds an additional element of protection to the standard GPWS. It creates an increasing terrain clearance envelope around the airport runway to provide protection against Controlled Flight Into Terrain (CFIT) situations beyond that which is currently provided. TCF alerts are based on current aircraft location, nearest runway center point position and radio altitude. TCF is active during takeoff, cruise and final approach. This alert mode complements the existing Mode 4 protection by providing an alert based on insufficient terrain clearance even when in landing configuration. Alerts for TCF illuminate GPWS cockpit lamps and produce aural messages. (a) System inputs The following table lists the inputs required to allow implementation of the TCF function: ------------------------------------------------------------------------------| Input | Source | ------------------------------------------------------------------------------| Radio Altitude | External: Radio Altimeter | |----------------------------------|------------------------------------------| | Latitude | External: FMS | |----------------------------------|------------------------------------------| | Longitude | External: FMS | |----------------------------------|------------------------------------------| | Runway Center Latitude | Internal: data base | |----------------------------------|------------------------------------------| | Runway Center Longitude | Internal: data base | |----------------------------------|------------------------------------------| | Navigation mode | FMS |

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page B5 201-228, 236-238, 301-302,  Config-1 Nov 01/08  CES

 

------------------------------------------------------------------------------| Input | Source | ------------------------------------------------------------------------------|----------------------------------|------------------------------------------| | Alert Envelope Parameters | Internal: data base | |----------------------------------|------------------------------------------| | 1/2 Runway Length | Internal: data base | |----------------------------------|------------------------------------------| | System Error Factor | Internal: data base | ------------------------------------------------------------------------------(b) Runway Data Base The TCF runway data base consists of data records containing the position of airport runway center points along with 1/2 the runway length. The data base includes all hard surface runways in the world greater than or equal to 3500 ft. in length. The process of generating this data base is certified and includes an end check that validates that the data was not corrupted in the translation process. This data base can be updated without affecting the customer certified system part number. The design of the data base and related software is such that additional runway records can be added in the future without altering the code. The data base provides a means of accessing the runway record of the runway closest to the current aircraft position. (c) Alert Envelope The TCF alert envelope is a circular band centered over the nearest runway. (Ref. Fig. 024) The distance from the runway center to the inner envelope edge is equal to 1/2 the runway length plus the envelope bias factor. Thus the inner and outer radius of the envelope are modulated based on the runway length and envelope bias factor. Runway length varies from one runway to the next, and the envelope bias factor is typically 1/2 NM to 2 NM and varies with position accuracy. The outer alert envelope boundary extends to infinity, or until it meets the outer alert envelope boundary of another runway. The alert is inhibited below radio altitude of 30 ft. This cutoff value was chosen to match the current Mode 4 lower cutoff value. (d) System Outputs When an aircraft penetrates the TCF alert envelope the following aural message occurs: TOO LOW TERRAIN. This aural message occurs once when initial envelope penetration occurs, and one time thereafter for each 20 per cent degradation

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page B6 201-214,  Config-1 Nov 01/08  CES

 

in radio altitude. At the same time the GPWS legend of pushbutton switches 4WZ and 5WZ comes on. The legends remain on until the alert envelope is exited. (3) Not Applicable (4) Not Applicable R

**ON A/C ALL Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

(2) Airbus Corrected Barometric Altitude Airbus Corrected Barometric Altitude is available on A318/A319/A320/A321 series aircraft. It provides accurate corrected barometric altitude data regardless of the altimeter reference setting (QNH or QFE). Airbus corrected baro altitude allows the Terrain Awareness and Display function to remain enabled during QFE approaches conducted by aircraft not equipped with GPS, and provides a more accurate corrected baro altitude input to the Geometric Altitude algorithm for GPS-equipped aircraft. The Enhanced GPWS examines the selected baro reference (QNH, STD or QFE) from the Flight Control Unit (FCU). If the selected baro reference is QFE, then the Enhanced GPWS computes corrected barometric altitude using destination QNH data from the Flight Management System (FMS) and standard (uncorrected) altitude. For aircraft not equipped with GPS, Airbus corrected barometric altitude is used as the altitude source for the Terrain Awareness and Display functions and the Envelope Modulation function. (3) Geometric Altitude Geometric Altitude is a computed aircraft altitude designed to help to ensure optimal operation of the Enhanced GPWS Terrain Awareness and Display functions through all phases of flight and atmospheric conditions. Geometric Altitude uses an improved pressure altitude calculation, GPS altitude, radio altitude, and terrain and runway elevation data to reduce or eliminate errors potentially induced in corrected barometric altitude by temperature extremes, non-standard altitude conditions, and altimeter miss-sets. Geometric Altitude also allows continuous Enhanced GPWS operations in QFE environments without custom inputs or special operational procedures. With the Geometric Altitude function, Enhanced GPWS can operate reliably throughout extreme local pressure or temperature variations from

  R EFF : ALL  34-48-00 Page B7   Config-1 Nov 01/09  CES

 

standard, is not susceptible to altimeter miss-sets by the flight crew, and will not require any custom inputs or special procedures by the flight crew when operating in a QFE environment. (a) Required inputs. The Geometric Altitude algorithm requires GPS altitude with Vertical Figure of Merit (VFOM) and RAIM failure indication along with standard (uncorrected) altitude and radio altitude. Ground speed, roll angle, and position (latitude and longitude) are used indirectly and are also required. Additionally, corrected barometric altitude, static air temperature (SAT), GPS operational mode and the number of satellites tracked are used if available. The required GPS signals are provided via ADIRU on the GPIRS bus or directly from the GPSSU or MMR. Standard altitude, corrected barometric altitude, and SAT are provided directly from the ADR. If SAT is not available, geometric altitude is computed using standard altitude with a corresponding reduction in accuracy. (b) Altitude calculation The Geometric Altitude consists of three main functions: - computation of non-standard altitude - computation of the component altitudes and VFOMs - final altitude-signal blending. Additional logic exists to handle reversionary modes and signal reasonable checking for each component altitude. R R

**ON A/C 401-499, Post SB Post SB Post SB

001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 501-509, 511-526, 528-599, 34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-060,101-104,215-228,236-238,301-302, 34-1352 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304,401-403, (Ref. Fig. 025)

  EFF : ALL  34-48-00 Page B8   Config-1 Feb 01/10  CES

 

Enhanced GPWS - Additional logic Figure 025   R EFF : ALL  34-48-00 Page B9   Config-1 Nov 01/09  CES

 

R

**ON A/C ALL Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, 1 _

Non-Standart Altitude To support the Geometric Altitude function, the Enhanced GPWS computes a non-standard altitude using the hydrostatic equation relating changes in height to changes in pressure and temperature. Non-standard altitude uses static pressure derived from standard altitude, along with static air temperature, to continuously accumulate changes in Geometric Altitude. Since the non-standard altitude algorithm incorporates actual atmospheric temperature, it does not suffer from errors due to non-standard temperatures. Non-standard altitude is highly accurate for measuring relative vertical changes over short periods of time and distance, such as during take off and approach. Non-standard altitude does not provide an absolute altitude and is prone to significant errors over extended periods of time and distance due to the effects of pressure gradients and long-term integration errors. Due to these limitations, non-standard altitude is not used directly, but is calibrated using additional signals and data to produce a set of component altitudes for use in the final altitude solution.

2 _

Computed component altitudes The Enhanced GPWS generates three component altitudes that are combined, along with corrected altitude if available, to produce Geometric Altitude. These component altitudes are runway calibrated altitude, GPS calibrated altitude, and radio altitude calibrated altitude. - Runway calibrated altitude is a one-time calibration of non-standard altitude during take off run. A correction factor for non-standard is computed using the runway elevation from the Enhanced GPWS runway database while the aircraft is on the ground. Runway calibrated altitude is used during the take off and climb-out portions of flight. VFOM of runway calibrated altitude is estimated based on changes in altitude since calibration, time since calibration, and distance from the runway. - GPS calibrated altitude is produced by combining GPS altitude and non-standard altitude through a complementary filter. The complementary filter is dynamically optimized to

  R EFF : ALL  34-48-00 Page B10   Config-1 Nov 01/09  CES

 

reduce errors in GPS altitude while minimizing pressure gradient and drift errors of non-standard altitude. GPS calibrated altitude is accurate through all phases of flight and is the primary altitude source during the cruise portion of flight. GPS calibrated altitude VFOM is estimate using GPS VFOM and estimated non-standard altitude drift errors. - Radio altitude calibrated altitude is a calibration of non-standard altitude during approach using an altitude derived from radio altitude (height above terrain) and the terrain elevation data stored in the Enhanced GPWS terrain database. This calibration is performed during the approach phase of flight when the aircraft is within a minimum distance and elevation of any runway. Once a correction factor is determined, it is applied to non-standard altitude until the aircraft lands. VFOM of radio altitude calibrated altitude is based on the accuracy of the calibration as estimated from the resolution of the terrain data and flatness of the terrain. The altitude is re-calibrated if a correction with a higher estimated accuracy is computed. An estimated VFOM for corrected barometric altitude is computed in order to determine its weight in the final altitude. VFOM of corrected barometric altitude is based on aircraft altitude above and distance from the nearest runway, with the accuracy assumed to be the highest close to runway. 3 _

Blending and reasonableness checking The final Geometric Altitude is computed by combining the three computed component altitudes with optional corrected barometric altitude. The weighting of each altitude in the final solution is based on the corresponding estimated VFOM. The blending algorithm gives the most weight to altitudes with a higher estimated accuracy, reducing the effect of less accurate altitudes on the final computed altitude. Each component altitude is also checked for reasonableness using a window monitor computed from GPS altitude and GPS VFOM. Altitudes that are invalid, not available, or fall outside the reasonableness window are not included in the final blended altitude.

(4) The Terrain Clearance Floor (TCF) The Terrain Clearance Floor (TCF) alert function adds an additional element of protection to the standard Ground Proximity Warning System. It creates an increasing terrain clearance envelope around the airport runway to provide protection against Controlled Flight Into Terrain (CFIT) situations beyond that which is currently provided. TCF alerts are based on current aircraft location, nearest runway center point position and radio altitude. TCF is active during

  R EFF : ALL  34-48-00 Page B11   Config-1 Nov 01/09  CES

 

takeoff, cruise and final approach. This alert mode complements the existing Mode 4 protection by providing an alert based on insufficient terrain clearance even when in landing configuration. Alerts for TCF illuminate GPWS cockpit lamps and produce aural messages. (a) System inputs The following table lists the inputs required to allow implementation of the TCF function: ------------------------------------------------------------------------------| Input | Source | ------------------------------------------------------------------------------| Radio Altitude | External: Radio Altimeter | |----------------------------------|------------------------------------------| | Latitude | External: GPS/IRS/FMS | |----------------------------------|------------------------------------------| | Longitude | External: GPS/IRS/FMS | |----------------------------------|------------------------------------------| | Runway Center Latitude | Internal: data base | |----------------------------------|------------------------------------------| | Runway Center Longitude | Internal: data base | |----------------------------------|------------------------------------------| | Navigation mode | FMS | |----------------------------------|------------------------------------------| | Alert Envelope Parameters | Internal: data base | |----------------------------------|------------------------------------------| | 1/2 Runway Length | Internal: data base | |----------------------------------|------------------------------------------| | System Error Factor | Internal: data base | ------------------------------------------------------------------------------(b) Runway Data Base The TCF runway data base consists of data records containing the position of airport runway center points along with 1/2 the runway length. The data base includes all hard surface runways in the world greater than or equal to 3500 ft. in length. The process of generating this data base is certified and includes an end check that validates that the data was not corrupted in the translation process. This data base can be updated without affecting the customer certified system part number. The design of the data base and related software is such that additional runway records can be added in the future without altering the code. The data base provides a means of accessing the runway record of the runway closest to the current aircaft position.

  R EFF : ALL  34-48-00 Page B12   Config-1 Nov 01/09  CES

 

(c) Alert Envelope The TCF alert envelope is a circular band centered over the nearest runway. R R

**ON A/C 401-499, Post SB Post SB Post SB

001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 501-509, 511-526, 528-599, 34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-060,101-104,215-228,236-238,301-302, 34-1352 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304,401-403, (Ref. Fig. 024)

**ON A/C ALL Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, The distance from the runway center to the inner envelope edge is equal to 1/2 the runway length plus the envelope bias factor. Thus the inner and outer radii of the envelope are modulated based on the runway length and envelope bias factor. Runway length varies from one runway to the next, and the envelope bias factor is typically 0.25 NM to 1 NM and varies with position accuracy. The outer alert envelope boundary extends to infinity, or until it meets the outer alert envelope boundary of another runway. The alert is inhibited below radio altitude of 30 ft. This cutoff value was chosen to match the current Mode 4 lower cutoff value. The TCF curve is limited to a minimum value of 245 ft. when it is determined that the aircraft is to the side of the runway.

R R

**ON A/C 401-499, Post SB Post SB Post SB Post SB

001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 501-509, 511-526, 528-599, 34-1287 For A/C 220-228,236-238,301-302, 34-1345 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304,401-403, 34-1351 For A/C 001-049,051-060,101-104,215-228,236-238,301-302, 34-1352 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304,401-403, (Ref. Fig. 026)

  EFF : ALL  34-48-00 Page B13   Config-1 Feb 01/10  CES

 

Enhanced GPWS - TCF Curve Limit Figure 026   R EFF : ALL  34-48-00 Page B14   Config-1 Nov 01/09  CES

 

**ON A/C 106-149, 229-233, 303-304, 401-403, Post SB

34-1352 For A/C 106-149,229-233,303-304,401-403, (Ref. Fig. 026A)

**ON A/C ALL Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, This feature provides improved alerting when landing to the side of the runway. (d) Runway Field Clearance Floor (RFCF) The Runway Field Clearance Floor (RFCF) alert envelope is a circular band centered over the selected runway. But unlike the radio altitude based TCF envelope, the RFCF envelope only extends 5 NM past the end of the runway. The bias factor (where the protection starts) is equal to the TCF Bias factor (k) plus an additional offset proportional to the Geometric Altitude Figure Of Merit (FOM).

R R

**ON A/C 401-499, Post SB Post SB Post SB

001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 501-509, 511-526, 528-599, 34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-060,101-104,215-228,236-238,301-302, 34-1352 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304,401-403, (Ref. Fig. 027)

  EFF : ALL  34-48-00 Page B15   Config-1 Feb 01/10  CES

 

Enhances GPWS - TCF Curve Limit Figure 026A   R EFF : 106-149, 220-233, 301-304, 401-403,  34-48-00 Page B16   Config-1 Nov 01/08  CES

 

Enhanced GPWS - Shape of the Alert Envelope Figure 027   R EFF : ALL  34-48-00 Page B17   Config-1 Nov 01/09  CES

 

R

**ON A/C ALL Post SB Post SB Post SB

34-1287 For A/C 220-228,236-238,301-302, 34-1351 For A/C 001-049,051-099,101-105,151-199,201-228,236-238, 301-302, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, This feature provides improved alerting for cases where the runway is at a high elevation compared to the terrain below the approach path. In these cases the radio altitude may be large enough to inhibit normal TCF operation, but the aircraft could actually be below the runway elevation. Field clearance (height above runway) is determined by subtracting the elevation of the selected destination runway from the current altitude (MSL). (e) System Outputs When an aircraft penetrates the TCF alert envelope, the following aural message occurs: TOO LOW TERRAIN. This aural message occurs once when initial envelope penetration occurs, and one time thereafter for each 20 per cent degradation in radio altitude. At the same time the GPWS legend of pushbutton switches 4WZ and 5WZ comes on. The legends remain on until the alert envelope is exited.

**ON A/C 106-149, 220-233, 301-304, 401-403, Post SB

34-1287 For A/C 220-228,301-302,

(2) Airbus Corrected Barometric Altitude Airbus Corrected Barometric Altitude is available on A318/A319/A320/A321 series aircraft. It provides accurate corrected barometric altitude data regardless of the altimeter reference setting (QNH or QFE). Airbus corrected baro altitude allows the Terrain Awareness and Display function to remain enabled during QFE approaches conducted by aircraft not equipped with GPS, and provides a more accurate corrected baro altitude input to the Geometric Altitude algorithm for GPS-equipped aircraft. The Enhanced GPWS examines the selected baro reference (QNH, STD or QFE) from the Flight Control Unit (FCU). If the selected baro reference is QFE, then the Enhanced GPWS computes corrected barometric altitude using destination QNH data from the Flight Management System (FMS) and standard (uncorrected) altitude. For aircraft not equipped with GPS, Airbus corrected barometric altitude is used as the altitude source for the Terrain Awareness and Display functions and the Envelope Modulation function.

  R EFF : ALL  34-48-00 Page B18   Config-1 Nov 01/09  CES

 

(3) Geometric Altitude Geometric Altitude is a computed aircraft altitude designed to help to ensure optimal operation of the Enhanced GPWS Terrain Awareness and Display functions through all phases of flight and atmospheric conditions. Geometric Altitude uses an improved pressure altitude calculation, GPS altitude, radio altitude, and terrain and runway elevation data to reduce or eliminate errors potentially induced in corrected barometric altitude by temperature extremes, non-standard altitude conditions, and altimeter miss-sets. Geometric Altitude also allows continuous Enhanced GPWS operations in QFE environments without custom inputs or special operational procedures. With the Geometric Altitude function, Enhanced GPWS can operate reliably throughout extreme local pressure or temperature variations from standard, is not susceptible to altimeter miss-sets by the flight crew, and will not require any custom inputs or special procedures by the flight crew when operating in a QFE environment. (a) Required inputs. The Geometric Altitude algorithm requires GPS altitude with Vertical Figure of Merit (VFOM) and RAIM failure indication along with standard (uncorrected) altitude and radio altitude. Ground speed, roll angle, and position (latitude and longitude) are used indirectly and are also required. Additionally, corrected barometric altitude, static air temperature (SAT), GPS operational mode and the number of satellites tracked are used if available. The required GPS signals are provided via ADIRU on the GPIRS bus or directly from the GPSSU or MMR. Standard altitude, corrected barometric altitude, and SAT are provided directly from the ADR. If SAT is not available, geometric altitude is computed using standard altitude with a corresponding reduction in accuracy. (b) Altitude calculation The Geometric Altitude consists of three main functions: - computation of non-standard altitude - computation of the component altitudes and VFOMs - final altitude-signal blending. Additional logic exists to handle reversionary modes and signal reasonable checking for each component altitude. **ON A/C 106-149, 229-233, 303-304, 401-403, (Ref. Fig. 025)

  R EFF : 106-149, 220-233, 301-304, 401-403,  34-48-00 Page B19   Config-1 Nov 01/08  CES

 

**ON A/C 106-149, 220-233, 301-304, 401-403, Post SB

34-1287 For A/C 220-228,301-302, 1 _

Non-Standart Altitude To support the Geometric Altitude function, the Enhanced GPWS computes a non-standard altitude using the hydrostatic equation relating changes in height to changes in pressure and temperature. Non-standard altitude uses static pressure derived from standard altitude, along with static air temperature, to continuously accumulate changes in Geometric Altitude. Since the non-standard altitude algorithm incorporates actual atmospheric temperature, it does not suffer from errors due to non-standard temperatures. Non-standard altitude is highly accurate for measuring relative vertical changes over short periods of time and distance, such as during take off and approach. Non-standard altitude does not provide an absolute altitude and is prone to significant errors over extended periods of time and distance due to the effects of pressure gradients and long-term integration errors. Due to these limitations, non-standard altitude is not used directly, but is calibrated using additional signals and data to produce a set of component altitudes for use in the final altitude solution.

2 _

Computed component altitudes The Enhanced GPWS generates three component altitudes that are combined, along with corrected altitude if available, to produce Geometric Altitude. These component altitudes are runway calibrated altitude, GPS calibrated altitude, and radio altitude calibrated altitude. - Runway calibrated altitude is a one-time calibration of non-standard altitude during take off run. A correction factor for non-standard is computed using the runway elevation from the Enhanced GPWS runway database while the aircraft is on the ground. Runway calibrated altitude is used during the take off and climb-out portions of flight. VFOM of runway calibrated altitude is estimated based on changes in altitude since calibration, time since calibration, and distance from the runway. - GPS calibrated altitude is produced by combining GPS altitude and non-standard altitude through a complementary filter. The complementary filter is dynamically optimized to reduce errors in GPS altitude while minimizing pressure gradient and drift errors of non-standard altitude. GPS calibrated altitude is accurate through all phases of flight and is the primary altitude source during the cruise portion

  R EFF : 106-149, 220-233, 301-304, 401-403,  34-48-00 Page B20   Config-1 Nov 01/08  CES

 

of flight. GPS calibrated altitude VFOM is estimate using GPS VFOM and estimated non-standard altitude drift errors. - Radio altitude calibrated altitude is a calibration of non-standard altitude during approach using an altitude derived from radio altitude (height above terrain) and the terrain elevation data stored in the Enhanced GPWS terrain database. This calibration is performed during the approach phase of flight when the aircraft is within a minimum distance and elevation of any runway. Once a correction factor is determined, it is applied to non-standard altitude until the aircraft lands. VFOM of radio altitude calibrated altitude is based on the accuracy of the calibration as estimated from the resolution of the terrain data and flatness of the terrain. The altitude is re-calibrated if a correction with a higher estimated accuracy is computed. An estimated VFOM for corrected barometric altitude is computed in order to determine its weight in the final altitude. VFOM of corrected barometric altitude is based on aircraft altitude above and distance from the nearest runway, with the accuracy assumed to be the highest close to runway. 3 _

Blending and reasonableness checking The final Geometric Altitude is computed by combining the three computed component altitudes with optional corrected barometric altitude. The weighting of each altitude in the final solution is based on the corresponding estimated VFOM. The blending algorithm gives the most weight to altitudes with a higher estimated accuracy, reducing the effect of less accurate altitudes on the final computed altitude. Each component altitude is also checked for reasonableness using a window monitor computed from GPS altitude and GPS VFOM. Altitudes that are invalid, not available, or fall outside the reasonableness window are not included in the final blended altitude.

(4) The Terrain Clearance Floor (TCF) The Terrain Clearance Floor (TCF) alert function adds an additional element of protection to the standard Ground Proximity Warning System. It creates an increasing terrain clearance envelope around the airport runway to provide protection against Controlled Flight Into Terrain (CFIT) situations beyond that which is currently provided. TCF alerts are based on current aircraft location, nearest runway center point position and radio altitude. TCF is active during takeoff, cruise and final approach. This alert mode complements the existing Mode 4 protection by providing an alert based on insufficient terrain clearance even when in landing configuration.

  R EFF : 106-149, 220-233, 301-304, 401-403,  34-48-00 Page B21   Config-1 Nov 01/08  CES

 

Alerts for TCF illuminate GPWS cockpit lamps and produce aural messages. (a) System inputs The following table lists the inputs required to allow implementation of the TCF function: ------------------------------------------------------------------------------| Input | Source | ------------------------------------------------------------------------------| Radio Altitude | External: Radio Altimeter | |----------------------------------|------------------------------------------| | Latitude | External: FMS | |----------------------------------|------------------------------------------| | Longitude | External: FMS | |----------------------------------|------------------------------------------| | Runway Center Latitude | Internal: data base | |----------------------------------|------------------------------------------| | Runway Center Longitude | Internal: data base | |----------------------------------|------------------------------------------| | Navigation mode | FMS | |----------------------------------|------------------------------------------| | Alert Envelope Parameters | Internal: data base | |----------------------------------|------------------------------------------| | 1/2 Runway Length | Internal: data base | |----------------------------------|------------------------------------------| | System Error Factor | Internal: data base | ------------------------------------------------------------------------------(b) Runway Data Base The TCF runway data base consists of data records containing the position of airport runway center points along with 1/2 the runway length. The data base includes all hard surface runways in the world greater than or equal to 3500 ft. in length. The process of generating this data base is certified and includes an end check that validates that the data was not corrupted in the translation process. This data base can be updated without affecting the customer certified system part number. The design of the data base and related software is such that additional runway records can be added in the future without altering the code. The data base provides a means of accessing the runway record of the runway closest to the current aircaft position.

  EFF : 106-149, 220-233, 301-304, 401-403,  34-48-00 Page B22   Config-1 Nov 01/08 R  CES

 

(c) Alert Envelope The TCF alert envelope is a circular band centered over the nearest runway. (Ref. Fig. 024) The distance from the runway center to the inner envelope edge is equal to 1/2 the runway length plus the envelope bias factor. Thus the inner and outer radii of the envelope are modulated based on the runway length and envelope bias factor. Runway length varies from one runway to the next, and the envelope bias factor is typically 1/2 NM to 2 NM and varies with position accuracy. The outer alert envelope boundary extends to infinity, or until it meets the outer alert envelope boundary of another runway. The alert is inhibited below radio altitude of 30 ft. This cutoff value was chosen to match the current Mode 4 lower cutoff value. The TCF curve is limited to a minimum value of 245 ft. when it is determined that the aircraft is to the side of the runway. **ON A/C 106-149, 229-233, 303-304, 401-403, R (Ref. Fig. 026) **ON A/C 106-149, 220-233, 301-304, 401-403, Post SB

34-1287 For A/C 220-228,301-302, (Ref. Fig. 026A) This feature provides improved alerting when landing to the side of the runway. (d) Runway Field Clearance Floor (RFCF) The Runway Field Clearance Floor (RFCF) alert envelope is a circular band centered over the selected runway. But unlike the radio altitude based TCF envelope, the RFCF envelope only extends 5 NM past the end of the runway. The bias factor (where the protection starts) is equal to the TCF Bias factor (k) plus an additional offset proportional to the Geometric Altitude Figure Of Merit (FOM).

**ON A/C 106-149, 229-233, 303-304, 401-403, (Ref. Fig. 027)

  R EFF : 106-149, 220-233, 301-304, 401-403,  34-48-00 Page B23   Config-1 Nov 01/08  CES

 

**ON A/C 106-149, 220-233, 301-304, 401-403, Post SB

34-1287 For A/C 220-228,301-302, This feature provides improved alerting for cases where the runway is at a high elevation compared to the terrain below the approach path. In these cases the radio altitude may be large enough to inhibit normal TCF operation, but the aircraft could actually be below the runway elevation. Field clearance (height above runway) is determined by subtracting the elevation of the selected destination runway from the current altitude (MSL). (e) System Outputs When an aircraft penetrates the TCF alert envelope, the following aural message occurs: TOO LOW TERRAIN. This aural message occurs once when initial envelope penetration occurs, and one time thereafter for each 20 per cent degradation in radio altitude. At the same time the PULL UP legend of pushbutton switches 4WZ and 5WZ comes on. The legends remain on until the alert envelope is exited.

  R EFF : 106-149, 220-233, 301-304, 401-403,  34-48-00 Page B24   Config-1 Nov 01/08  CES

 

**ON A/C 106-149, 215-233, 236-238, 301-304, E. Warning Generation and Inhibition (1) Audio Output Alert outputs result in an audio voice warning unless inputs are invalid or one of the audio suppression discretes is active. The actual output message, or intended message during audio suppression, is sent to the warning lamp logic for proper output activation. The audio outputs consist of a transformer isolated 600 Ohm output. Aural warnings and their priority rate are as follows: -----------------------------------------------------------------------| RELATIVE | WARNING | POSSIBLE | LEGEND | | PRIORITY | CONDITION | MESSAGES | | |----------------------------------------------------------------------| | HIGHEST | Mode 1 Pull Up | PULL UP | PULL UP | |----------|--------------------------|-------------------|------------| | | Mode 2 Pull Up Preface | TERRAIN TERRAIN | PULL UP | |----------|--------------------------|-------------------|------------| | | Mode 2 Pull Up | PULL UP | PULL UP | |----------|--------------------------|-------------------|------------| | | Terrain Awareness Preface| TERRAIN AHEAD | PULL UP | | | | PULL UP | | |----------|--------------------------|-------------------|------------| | | Terrain Awareness Warning| TERRAIN AHEAD | PULL UP | | | | PULL UP | | |----------|--------------------------|-------------------|------------| | | Mode 2 Terrain | TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | * | Terrain Awareness Caution| TERRAIN AHEAD | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Terrain | TOO LOW TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | | TCF Too Low Terrain | TOO LOW TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Gear | TOO LOW GEAR | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Flaps | TOO LOW FLAPS | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 1 Sinkrate | SINKRATE | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 3 Dont Sink | DONT SINK | GPWS | |----------|--------------------------|-------------------|------------| | LOWEST * | Mode 5 Glide slope | GLIDE SLOPE | GPWS | ------------------------------------------------------------------------

  R EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00 Page B25   Config-1 Nov 01/08  CES

 

* Allows interleaving of multiple alerts. The voice warning circuits also contain logic elements which ensure that: - only one message at a time is output, - higher priority messages interrupt lower priority messages except if interleaving is allowed (Ref. table above), - a triggered message is completed even when warning condition ceases, - a 0.75 second pause exists between warning messages. (2) Alert discrete outputs Mode 5 GLIDE SLOPE message activates the alert lamp output (which illuminates GPWS amber legend). All other messages activate the warning lamp output (which illuminates PULL UP red legend). (Ref. Fig. 003A) (3) Control and Indicating (Ref. Fig. 028) (4) Inhibitions (Ref. Fig. 006) (a) All audio inhibition: - The INHIBIT ALL AUDIO discrete input controls the audio outputs as follows. When grounded, all voices are inhibited (not interrupted, all aural messages once started are finished). Visual and display indications are not affected. This input is used to manage the audio priority with other systems (FWS, PWS, TCAS). (b) Modes 1 to 5 inhibitions: - The INHIBIT MODES 1 TO 5 discrete input controls the audio and visual outputs as follows. When grounded,this input always inhibits all GPWS aural and visual indications with the exception of Terrain Clearance Floor Alerts and Terrain Awareness caution and warnings. This input is wired to SYS pushbutton switch to manually inhibit GPWS Modes 1 to 5. (c) TAD and TCF inhibitions: - The TERRAIN AWARENESS INHIBIT discrete input controls the audio, visual and display outputs as follows. When grounded, this input always inhibits TAD and TCF aural, visual and display indications. This input is wired to the TERR push-button switch to manually inhibit the TAD and TCF functions.

  R EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00 Page B26   Config-1 Nov 01/08  CES

 

- When automatic deselection is activated TAD and TCF functions may also be inhibit automatically when the FMS aircraft position accuracy is not accurate enough. This is indicated to the crew by the automatic deselection of terrain display and the illumation of the TERR STBY memo on the ECAM display unit.

  R EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00 Page B27   Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028 (SHEET 1)   R EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00 Page B28 401-403,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028 (SHEET 2)   R EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00 Page B29 401-403,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028 (SHEET 3)   R EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00 Page B30 401-403,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028 (SHEET 4)   R EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00 Page B31 401-403,  Config-1 Nov 01/08  CES

 

**ON A/C 401-403, E. Warning Generation and Inhibition (1) Audio Output Alert outputs result in an audio voice warning unless inputs are invalid or one of the audio suppression discretes is active. The actual output message, or intended message during audio suppression, is sent to the warning lamp logic for proper output activation. The audio outputs consist of a transformer isolated 600 Ohm output. Aural warnings and their priority rate are as follows: -----------------------------------------------------------------------| RELATIVE | WARNING | POSSIBLE | LEGEND | | PRIORITY | CONDITION | MESSAGES | | |----------------------------------------------------------------------| | HIGHEST | Mode 1 Pull Up | PULL UP | PULL UP | |----------|--------------------------|-------------------|------------| | | Mode 2 Pull Up Preface | TERRAIN TERRAIN | PULL UP | |----------|--------------------------|-------------------|------------| | | Mode 2 Pull Up | PULL UP | PULL UP | |----------|--------------------------|-------------------|------------| | | Terrain Awareness Preface| TERRAIN AHEAD | PULL UP | | | | PULL UP | | |----------|--------------------------|-------------------|------------| | | Terrain Awareness Warning| TERRAIN AHEAD | PULL UP | | | | PULL UP | | |----------------------------------------------------------------------| | | Obstacle awareness | OBSTACLE AHEAD | PULL UP | | | Preface | PULL UP | | |----------|--------------------------|-------------------|------------| | | Obstacle Awareness | OBSTACLE AHEAD | PULL UP | | | Warning | PULL UP | | |----------|--------------------------|-------------------|------------| | | Mode 2 Terrain | TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | * | Terrain Awareness Caution| TERRAIN AHEAD | GPWS | |----------|--------------------------|-------------------|------------| | | Obstacle Awareness | OBSTACLE AHEAD | GPWS | | | Caution | | | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Terrain | TOO LOW TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | | TCF Too Low Terrain | TOO LOW TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Gear | TOO LOW GEAR | GPWS |

  R EFF : 401-403,  34-48-00 Page B32   Config-1 Nov 01/08  CES

 

-----------------------------------------------------------------------| RELATIVE | WARNING | POSSIBLE | LEGEND | | PRIORITY | CONDITION | MESSAGES | | |----------------------------------------------------------------------| |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Flaps | TOO LOW FLAPS | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 1 Sinkrate | SINKRATE | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 3 Dont Sink | DONT SINK | GPWS | |----------|--------------------------|-------------------|------------| | LOWEST * | Mode 5 Glide slope | GLIDE SLOPE | GPWS | -----------------------------------------------------------------------* Allows interleaving of multiple alerts. The voice warning circuits also contain logic elements which ensure that: - only one message at a time is output, - higher priority messages interrupt lower priority messages except if interleaving is allowed (Ref. table above), - a triggered message is completed even when warning condition ceases, - a 0.75 second pause exists between warning messages. (2) Alert discrete outputs PULL UPaudio message activate the warning lamp output (which illuminates PULL UP red legend). All other messages activate the alert lamp output (which illuminates GPWS amber legend). (Ref. Fig. 003A) (3) Control and Indicating (Ref. Fig. 028) (4) Inhibitions (Ref. Fig. 006) (a) All audio inhibition: - The INHIBIT ALL AUDIO discrete input controls the audio outputs as follows. When grounded, all voices are inhibited (not interrupted, all aural messages once started are finished). Visual and display indications are not affected. This input is used to manage the audio priority with other systems (FWS, PWS, TCAS).

  R EFF : 401-403,  34-48-00 Page B33   Config-1 Nov 01/08  CES

 

(b) Modes 1 to 5 inhibitions: - The INHIBIT MODES 1 TO 5 discrete input controls the audio and visual outputs as follows. When grounded,this input always inhibits all GPWS aural and visual indications with the exception of Terrain Clearance Floor Alerts and Terrain Awareness caution and warnings. This input is wired to SYS pushbutton switch to manually inhibit GPWS Modes 1 to 5. (c) TAD and TCF inhibitions: - The TERRAIN AWARENESS INHIBIT discrete input controls the audio, visual and display outputs as follows. When grounded, this input always inhibits TAD and TCF aural, visual and display indications. This input is wired to the TERR pushbutton switch to manually inhibit the TAD and TCF functions. - When the automatic deselection option actived TAD and TCF functions may also be inhibit automatically when the FMS aircraft position accuracy is not accurate enough. This is indicated to the crew by the automatic deselection of terrain display and the illumation of the TERR STBY memo on the ECAM display unit.

  R EFF : 401-403,  34-48-00 Page B34   Config-1 Nov 01/08  CES

 

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, E. Warning Generation and Inhibition (1) Audio Output Alert outputs result in an audio voice warning unless inputs are invalid or one of the audio suppression discretes is active. The actual output message, or intended message during audio suppression, is sent to the warning lamp logic for proper output activation. The audio outputs consist of a transformer isolated 600 Ohm output. Aural warnings and their priority rate are as follows: -----------------------------------------------------------------------| RELATIVE | WARNING | POSSIBLE | LEGEND | | PRIORITY | CONDITION | MESSAGES | | |----------------------------------------------------------------------| | HIGHEST | Mode 1 Pull Up | PULL UP | GPWS | |----------|--------------------------|-------------------|------------| | | Mode 2 Pull Up Preface | TERRAIN TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | | Mode 2 Pull Up | PULL UP | GPWS | |----------|--------------------------|-------------------|------------| | | Terrain Awareness Preface| TERRAIN AHEAD | GPWS | | | | PULL UP | | |----------|--------------------------|-------------------|------------| | | Terrain Awareness Warning| TERRAIN AHEAD | GPWS | | | | PULL UP | | |----------|--------------------------|-------------------|------------| | | Mode 2 Terrain | TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | * | Terrain Awareness Caution| TERRAIN AHEAD | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Terrain | TOO LOW TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | | TCF Too Low Terrain | TOO LOW TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Gear | TOO LOW GEAR | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Flaps | TOO LOW FLAPS | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 1 Sinkrate | SINKRATE | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 3 Dont Sink | DONT SINK | GPWS | |----------|--------------------------|-------------------|------------| | LOWEST * | Mode 5 Glide slope | GLIDE SLOPE | G/S | ------------------------------------------------------------------------

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page B35 201-214,  Config-1 Nov 01/08  CES

 

* Allows interleaving of multiple alerts. The voice warning circuits also contain logic elements which ensure that: - only one message at a time is output, - higher priority messages interrupt lower priority messages except if interleaving is allowed (Ref. table above), - a triggered message is completed even when warning condition ceases, - a 0.75 second pause exists between warning messages. (2) Alert Discrete Outputs Mode 5 GLIDE SLOPE message activates the alert lamp output (which illuminates G/S amber legend). All other messages activate the warning lamp output (which illuminates GPWS red legend). (Ref. Fig. 003) **ON A/C 001-049, 051-060, 101-104, (Ref. Fig. 003A) **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, (3) Control and Indicating (Ref. Fig. 028A) (4) Inhibitions (Ref. Fig. 006A) (a) All audio inhibition: - The INHIBIT ALL AUDIO discrete input controls the audio outputs as follows. When grounded, all voices are inhibited (not interrupted, all aural messages once started are finished). Visual and display indications are not affected. This input is used to manage the audio priority with other systems (FWS, PWS, TCAS). (b) Modes 1 to 5 inhibitions: - The INHIBIT MODES 1 TO 5 discrete input controls the audio and visual outputs as follows. When grounded,this input always inhibits all GPWS aural and visual indications with the exception of Terrain Clearance Floor Alerts and Terrain Awareness caution and warnings. This input is wired to SYS pushbutton switch to manually inhibit GPWS Modes 1 to 5.

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page B36 201-214,  Config-1 Nov 01/08  CES

 

(c) TAD and TCF inhibitions: - The TERRAIN AWARENESS INHIBIT discrete input controls the audio, visual and display outputs as follows. When grounded, this input always inhibits TAD and TCF aural, visual and display indications. This input is wired to the TERR pushbutton switch to manually inhibit the TAD and TCF functions. - When the automatic deselection option actived TAD and TCF functions may also be inhibit automatically when the FMS aircraft position accuracy is not accurate enough. This is indicated to the crew by the automatic deselection of terrain display and the illumation of the TERR STBY memo on the ECAM display unit.

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page B37 201-214,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028A (SHEET 1)   R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page B38 201-214,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028A (SHEET 2)   R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page B39 201-214,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028A (SHEET 3)   R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page B40 201-214,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028A (SHEET 4)   EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page B41 201-214,  Config-1 Nov 01/08 R  CES

 

R

**ON A/C ALL Post SB Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

E. Warning Generation and Inhibition (1) Audio Output Alert outputs result in an audio voice warning unless inputs are invalid or one of the audio suppression discretes is active. The actual output message, or intended message during audio suppression, is sent to the warning lamp logic for proper output activation. The audio outputs consist of a transformer isolated 600 Ohm output. Aural warnings and their priority rate are as follows: -----------------------------------------------------------------------| RELATIVE | WARNING | POSSIBLE | LEGEND | | PRIORITY | CONDITION | MESSAGES | | |----------------------------------------------------------------------| | HIGHEST | Mode 1 Pull Up | PULL UP | PULL UP | |----------|--------------------------|-------------------|------------| | | Mode 2 Pull Up Preface | TERRAIN TERRAIN | PULL UP | |----------|--------------------------|-------------------|------------| | | Mode 2 Pull Up | PULL UP | PULL UP | |----------|--------------------------|-------------------|------------| | | Terrain Awareness Preface| TERRAIN AHEAD | PULL UP | | | | PULL UP | | |----------|--------------------------|-------------------|------------| | | Terrain Awareness Warning| TERRAIN AHEAD | PULL UP | | | | PULL UP | | |----------------------------------------------------------------------| | | Obstacle awareness | OBSTACLE AHEAD | PULL UP | | | Preface | PULL UP | | |----------|--------------------------|-------------------|------------| | | Obstacle Awareness | OBSTACLE AHEAD | PULL UP | | | Warning | PULL UP | | |----------|--------------------------|-------------------|------------| | | Mode 2 Terrain | TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | * | Terrain Awareness Caution| TERRAIN AHEAD | GPWS | |----------|--------------------------|-------------------|------------| | | Obstacle Awareness | OBSTACLE AHEAD | GPWS | | | Caution | | | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Terrain | TOO LOW TERRAIN | GPWS |

  R EFF : ALL  34-48-00 Page B42   Config-1 Nov 01/09  CES

 

-----------------------------------------------------------------------| RELATIVE | WARNING | POSSIBLE | LEGEND | | PRIORITY | CONDITION | MESSAGES | | |----------------------------------------------------------------------| |----------|--------------------------|-------------------|------------| | | TCF Too Low Terrain | TOO LOW TERRAIN | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Gear | TOO LOW GEAR | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 4 Too Low Flaps | TOO LOW FLAPS | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 1 Sinkrate | SINKRATE | GPWS | |----------|--------------------------|-------------------|------------| | * | Mode 3 Dont Sink | DONT SINK | GPWS | |----------|--------------------------|-------------------|------------| | LOWEST * | Mode 5 Glide slope | GLIDE SLOPE | GPWS | -----------------------------------------------------------------------* Allows interleaving of multiple alerts. The voice warning circuits also contain logic elements which ensure that: - only one message at a time is output, - higher priority messages interrupt lower priority messages except if interleaving is allowed (Ref. table above), - a triggered message is completed even when warning condition ceases, - a 0.75 second pause exists between warning messages. (2) Alert discrete outputs PULL UPaudio message activate the warning lamp output (which illuminates PULL UP red legend). All other messages activate the alert lamp output (which illuminates GPWS amber legend). **ON A/C 001-049, 051-060, 101-104, Post SB Post SB

34-1345 For A/C 001-049,051-060,101-104, 34-1352 For A/C 001-049,051-060,101-104, (Ref. Fig. 003)

  R EFF : ALL  34-48-00 Page B43   Config-1 Nov 01/09  CES

 

**ON A/C ALL Post SB Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, (Ref. Fig. 003A)

(3) Control and Indicating NOTE : Indications on ECAM might be inhibited depending on phase of ____ flights computed by FWC. **ON A/C 401-403, Post SB

34-1352 For A/C 401-403, (Ref. Fig. 028)

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-310, 404-499, Post SB 34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, Post SB 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, (Ref. Fig. 028B) R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 404-499, 501-509, 511-526, 528-599, Post SB 31-1267 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-310,404-499, Post SB 31-1300 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-310,404-499, Post SB 34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, Post SB 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, (Ref. Fig. 028C)

  EFF : ALL  34-48-00 Page B44   Config-1 Feb 01/10  CES

 

R

**ON A/C ALL Post SB Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, 34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

(4) Inhibitions (Ref. Fig. 006B) (a) All audio inhibition: - The INHIBIT ALL AUDIO discrete input controls the audio outputs as follows. When grounded, all voices are inhibited (not interrupted, all aural messages once started are finished). Visual and display indications are not affected. This input is used to manage the audio priority with other systems (FWS, PWS, TCAS). (b) Modes 1 to 5 inhibitions: - The INHIBIT MODES 1 TO 5 discrete input controls the audio and visual outputs as follows. When grounded,this input always inhibits all GPWS aural and visual indications with the exception of Terrain Clearance Floor Alerts and Terrain Awareness caution and warnings. This input is wired to SYS pushbutton switch to manually inhibit GPWS Modes 1 to 5. (c) TAD and TCF inhibitions: - The TERRAIN AWARENESS INHIBIT discrete input controls the audio, visual and display outputs as follows. When grounded, this input always inhibits TAD and TCF aural, visual and display indications. This input is wired to the TERR pushbutton switch to manually inhibit the TAD and TCF functions. - When the automatic deselection is activated, the TAD and TCF functions can also be automatically inhibited when the aircraft position is not accurate enough. This is indicated to the crew by the automatic deselection of the terrain display and the illumination of the TERR STBY memo on the EWD.

  R EFF : ALL  34-48-00 Page B45   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Control and Indicating Figure 028B (SHEET 1)   R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page B46 201-233, 236-238, 301-310, 401-499,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028B (SHEET 2)   R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page B47 201-233, 236-238, 301-310, 401-499,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028B (SHEET 3)   R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page B48 201-233, 236-238, 301-310, 401-499,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028B (SHEET 4)   R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page B49 201-233, 236-238, 301-310, 401-499,  Config-1 Nov 01/08  CES

 

Enhanced GPWS - Control and Indicating Figure 028C (SHEET 1)   R EFF : ALL  34-48-00 Page B50   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Control and Indicating Figure 028C (SHEET 2)   R EFF : ALL  34-48-00 Page B51   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Control and Indicating Figure 028C (SHEET 3)   R EFF : ALL  34-48-00 Page B52   Config-1 Nov 01/09  CES

 

Enhanced GPWS - Control and Indicating Figure 028C (SHEET 4)   R EFF : ALL  34-48-00 Page B53   Config-1 Nov 01/09  CES

 

**ON A/C ALL (5) Autotilt capability The automatic tilt angle capability uses aircraft altitude above the terrain and terrain elevations in the area to generate a tilt angle for the weather radar system. This automatic tilt angle setting causes minimum ground clutter to be displayed while maintaining the optimum weather detection capability. With manual tilt control, there is a possibility of: - overscan where the weather cells and the terrain are below the antenna beam scan and in this case, the display is blank, or - underscan where the antenna scan basically hits the ground below the weather cells and in this case, the display only shows the ground clutter. The calculated tilt angle is transmitted to the weather radar system via an ARINC 429 output bus on labels 061, 062, 063, 064 and 065. The Enhanced GPWS computes a tilt angle for each sector based on underlying terrain elevations. There are two tilt angles: a Short Range Tilt (SRT) angle and a Long Range Tilt (LRT) angle. The SRT angle covers 95 per cent of the ground below the aircraft within 80 NM from the aircraft. The LRT angle covers 90 per cent of the ground below the aircraft within 160 NM from the aircraft. The terrain database is divided into five short-range sectors and five long- range sectors in a semi-circle in front of the aircraft. (Ref. Fig. 029) R R

**ON A/C 001-049, 051-099, 101-102, 106-149, 201-202, 211-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, F. Enhanced GPWC Maintenance Output A maintenance output signal (label 270 octal) is provided by the ARINC 429 transmitter. The transmitter converts the microprocessor parallel data to standard serial data for the DMU of the AIDS. **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-060,101-104,

8. Test ____

  EFF : ALL  34-48-00 Page B54   Config-1 Feb 01/10  CES

 

Enhanced GPWS - Autotilt Capability Figure 029   R EFF : ALL  34-48-00 Page B55   Config-1 Nov 01/09  CES

 

**ON A/C 106-149, 215-233, 236-238, 301-304, A. Self-Tests (1) On the ground only, the Enhanced GPWC provides self-test capability, providing an indication of the ability of the Enhanced GPWC to perform its intended function. (2) The Enhanced GPWC self-test is initiated by momentarily pressing PULL UP/GPWS pushbutton switches or activated via the MCDU on the ground. When activated by pressing the PULL UP/GPWS pushbutton switches, the self-test is enunciated, via the same audio system as the Enhanced GPWS alerts. This self-test can also be accessed via the headphone jack on the front panel of the Enhanced GPWC and it has been divided into six different levels to help with Enhanced GPWC testing and troubleshooting. (a) Level 1 Level 1, functional testing, provides an overview of the current operational functions selected and provides an indication of their operational status. Level 1 self-test sequence: - the FAULT legend of the GPWS/SYS pushbutton switch is on, - the FAULT legend of the GPWS/TERR pushbutton switch is on, - GPWS legends of both PULL UP/GPWS pushbutton switches are on, - GLIDE SLOPE audio phase is broadcast, - GPWS legends of both PULL UP/GPWS pushbutton switches go off, - PULL UP legends of both PULL UP/GPWS pushbutton switches are on, - PULL UP audio phase is broadcast, - TERRAIN AHEAD PULL UP audio phase is broadcast, - PULL UP legends of both PULL UP/GPWS pushbutton switches go off, - ON legends of both TERR ON ND pushbutton switches are on, - terrain self-test pattern is displayed on both NDs, (Ref. Fig. 030) A long level 1 self-test sequence is initiated when the PULL UP/GPWS pushbutton switch is not released while self-test voices start. - Additional sequence when long self-test initiated:

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Enhanced GPWS - Test Pattern Figure 030

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SINK RATE PULL UP TERRAIN PULL UP DONT SINK DONT SINK TOO LOW TERRAIN TOO LOW GEAR TOO LOW FLAPS TOO LOW TERRAIN GLIDE SLOPE TOO LOW TERRAIN TERRAIN AHEAD TERRAIN AHEAD TERRAIN AHEAD PULL UP - terrain self-test pattern turns off, - ON legends of both TERR ON ND pushbutton switches and the images displayed on both NDs revert to the configuration selected before the test, - the FAULT legend of the GPWS/SYS pushbutton switch goes off, - the FAULT legend of the GPWS/TERR pushbutton switch goes off. (b) Level 2 Level 2, current faults, provides a listing of the internal and external faults currently detected by the Enhanced GPWC. Level 2 self-test is initiated by pressing the PULL UP/GPWS pushbutton switch within 3 seconds after the end of level 1 self-test. (c) Level 3 Level 3, Enhanced GPWS configuration, indicates the current configuration by listing the current hardware, software, data bases and program pin inputs detected by the Enhanced GPWC. This level is initiated by pressing the PULL UP/GPWS pushbutton switch when PRESS TO CONTINUE message is enunciated. (d) Level 4 Level 4, fault history, provides a historical record of both internal and external faults detected by the Enhanced GPWC. This level is initiated by pressing the PULL UP/GPWS pushbutton switch when PRESS TO CONTINUE message is enunciated.

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(e) Level 5 Level 5, warning history, provides a historical record of the warnings and cautions given by the Enhanced GPWC. This level is initiated by pressing the PULL UP/GPWS pushbutton switch when PRESS TO CONTINUE message is enunciated. (f) Level 6 Level 6, discrete test, provides annunciation of discrete input transitions to be used for maintenance support. This level is initiated by pressing the PULL UP/GPWS pushbutton switch when PRESS TO CONTINUE message is enunciated. (3) To speed up the navigation of self-test levels and information two types of cancel sequences are supported. Pressing and holding the PULL UP/GPWS pushbutton switch for less than 2 seconds is considered to be a short cancel. Pressing and holding the cockpit PULL UP/GPWS pushbutton switch for more than 2 seconds is considered to be a long cancel. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, A. Self-Tests (1) On the ground only, the Enhanced GPWC provides self-test capability, providing an indication of the ability of the Enhanced GPWC to perform its intended function. (2) The Enhanced GPWC self-test is initiated by momentarily pressing GPWS/G/S pushbutton switches or activated via the MCDU on the ground. When activated by pressing the GPWS/G/S pushbutton switches, the self-test is enunciated, via the same audio system as the Enhanced GPWS alerts. This self-test can also be accessed via the headphone jack on the front panel of the Enhanced GPWC and it has been divided into six different levels to help with Enhanced GPWC testing and troubleshooting. (a) Level 1 Level 1, functional testing, provides an overview of the current operational functions selected and provides an indication of their operational status. Level 1 self-test sequence: - the FAULT legend of the GPWS/SYS pushbutton switch is on, - the FAULT legend of the GPWS/TERR pushbutton switch is on, - G/S legends of both GPWS/G/S pushbutton switches are on, - GLIDE SLOPE audio phase is broadcast, - G/S legends of both GPWS/G/S pushbutton switches go off,

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-

GPWS legends of both GPWS/G/S pushbutton switches are on, PULL UP audio phase is broadcast, TERRAIN AHEAD PULL UP audio phase is broadcast, GPWS legends of both GPWS/G/S pushbutton switches go off, ON legends of both TERR ON ND pushbutton switches are on, terrain self-test pattern is displayed on both NDs, (Ref. Fig. 030) A long level 1 self-test sequence is initiated when the GPWS/G/S pushbutton switch is not released while self-test voices start. - Additional vocabulary sequence when long self-test initiated:

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SINK RATE PULL UP TERRAIN PULL UP DONT SINK DONT SINK TOO LOW TERRAIN TOO LOW GEAR TOO LOW FLAPS TOO LOW TERRAIN GLIDE SLOPE TOO LOW TERRAIN TERRAIN AHEAD TERRAIN AHEAD TERRAIN AHEAD PULL UP - terrain self-test pattern turns off, - ON legends of both TERR ON ND pushbutton switches and the images displayed on both NDs revert to the configuration selected before the test, - the FAULT legend of the GPWS/SYS pushbutton switch goes off, - the FAULT legend of the GPWS/TERR pushbutton switch goes off. (b) Level 2 Level 2, current faults, provides a listing of the internal and external faults currently detected by the Enhanced GPWC. Level 2 self-test is initiated by pressing the GPWS/G/S pushbutton switch within 3 seconds after the end of level 1 self-test. (c) Level 3 Level 3, Enhanced GPWS configuration, indicates the current configuration by listing the current hardware, software, data bases and program pin inputs detected by the Enhanced GPWC.

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This level is initiated by pressing the GPWS/G/S pushbutton switch when PRESS TO CONTINUE message is enunciated. (d) Level 4 Level 4, fault history, provides a historical record of both internal and external faults detected by the Enhanced GPWC. This level is initiated by pressing the GPWS/G/S pushbutton switch when PRESS TO CONTINUE message is enunciated. (e) Level 5 Level 5, warning history, provides a historical record of the warnings and cautions given by the Enhanced GPWC. This level is initiated by pressing the GPWS/G/S pushbutton switch when PRESS TO CONTINUE message is enunciated. (f) Level 6 Level 6, discrete test, provides annunciation of discrete input transitions to be used for maintenance support. This level is initiated by pressing the GPWS/G/S pushbutton switch when PRESS TO CONTINUE message is enunciated. (3) To speed up the navigation of self-test levels and information two types of cancel sequences are supported. Pressing and holding the GPWS/G/S pushbutton switch for less than 2 seconds is considered to be a short cancel. Pressing and holding the cockpit GPWS/G/S pushbutton switch for more than 2 seconds is considered to be a long cancel. R

**ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,

A. Self-Tests (1) On the ground only, the Enhanced GPWC provides self-test capability, both in flight and on ground, providing an indication of the ability of the Enhanced GPWC to perform its intended function. (2) The Enhanced GPWC self-test is initiated by momentarily pressing PULL UP/GPWS pushbutton switches or via the MCDU on the ground. When activated by pressing the PULL UP/GPWS pushbutton switches, the self-test is enunciated, via the same audio system as the Enhanced GPWS alerts. This self-test can also be accessed via the headphone jack on the front panel of the Enhanced GPWC. The self-test is divided into six different levels to help with Enhanced GPWC testing and troubleshooting.

  R EFF : ALL  34-48-00 Page B61   Config-1 Nov 01/09  CES

 

(a) Level 1 Level 1 (functional testing) provides an overview of the current operational functions selected and provides an indication of their operational status. Level 1 self-test sequence: - the FAULT legend of the GPWS/SYS pushbutton switch comes on, - the FAULT legend of the GPWS/TERR pushbutton switch comes on, - the GPWS legends of both PULL UP/GPWS pushbutton switches come on, - the GLIDE SLOPE audio phase is broadcast, - the GPWS legends of both PULL UP/GPWS pushbutton switches go off, - the PULL UP legends of both PULL UP/GPWS pushbutton switches come on, - the PULL UP audio phase is broadcast, - the TERRAIN AHEAD PULL UP audio phase is broadcast, - the PULL UP legends of both PULL UP/GPWS pushbutton switches go off, - the ON legends of both TERR ON ND pushbutton switches come on, - the terrain self-test pattern is displayed on both NDs. * The uppers area is colored in cyan if peaks option is activated, black otherwise. **ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 404-499, 501-509, 511-515, Post SB 34-1345 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304, Post SB 34-1412 For A/C 001-049,051-060,101-104,106-149,215-249,251-299, 301-399,404-499,501-509,511-515, (Ref. Fig. 030A) R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 215-249, 251-299, 301-399, 404-499, 501-509, 511-526, 528-599, Post SB 34-1345 For A/C 001-049,051-060,101-104,106-149,215-233,236-238, 301-304, (Ref. Fig. 030B) **ON A/C ALL Post SB

34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, A long level 1 self-test sequence is initiated when the PULL UP/GPWS pushbutton switch is not released while self-test voices start.

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Enhanced GPWS - Test Pattern Figure 030A

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Enhanced GPWS - Test Pattern Figure 030B

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- Additional sequence when long self-test initiated: SINK RATE PULL UP TERRAIN PULL UP DONT SINK DONT SINK TOO LOW TERRAIN TOO LOW GEAR TOO LOW FLAPS TOO LOW TERRAIN GLIDE SLOPE TOO LOW TERRAIN TERRAIN AHEAD TERRAIN AHEAD TERRAIN AHEAD PULL UP OBSTACLE AHEAD OBSTACLE AHEAD OBSTACLE AHEAD PULL UP - the terrain self-test pattern disappears. - the ON legends of both TERR ON ND pushbutton switches and the images displayed on both NDs revert to the configuration selected before the test, - the FAULT legend of the GPWS/SYS pushbutton switch goes off, - the FAULT legend of the GPWS/TERR pushbutton switch goes off. If the aircraft is fitted with EIS2 and if the Peaks display option is selected, then the Peaks elevations are provided to the displays as follows: XXX (amber) XXX (amber) for 5 seconds and then: 290 (Red) High altitude -13 (Green) Low altitude (b) Level 2 Level 2 (current faults) provides a listing of the internal and external fault currently detected by the Enhanced GPWC. Level 2 self-test is initiated by pressing the PULL UP/GPWS pushbutton switch within 3 seconds after the end of level 1 self-test. (c) Level 3 Level 3 ( Enhanced GPWS configuration) indicates the current configuration by listing the current hardware, software, databases and program pin inputs detected by the Enhanced GPWC.

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This level is initiated by pressing the PULL UP/GPWS pushbutton switch when the PRESS TO CONTINUE message is enunciated. (d) Level 4 Level 4 (fault history) provides a historical record of both internal and external faults detected by the Enhanced GPWC. This level is initiated by pressing the PULL UP/GPWS pushbutton switch when the PRESS TO CONTINUE message is enunciated. (e) Level 5 Level 5 (warning history) provides a historical record of the warnings and cautions given by the Enhanced GPWC. This level is initiated by pressing the PULL UP/GPWS pushbutton switch when the PRESS TO CONTINUE message is enunciated. (f) Level 6 Level 6 (discrete test) provides annunciation of discrete input transitions to be used for maintenance support. This level is initiated by pressing the PULL UP/GPWS pushbutton switch when the PRESS TO CONTINUE message is enunciated. (3) To speed up the navigation of self-test levels and information, two types of cancel sequences are supported. Pressing and holding the PULL UP/GPWS pushbutton switch for less than 2 seconds is considered to be a short cancel. Pressing and holding the PULL UP/GPWS pushbutton switch for more than 2 seconds is considered to be a long cancel. **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, B. CFDS Interface (1) Interactive function To gain access to the BITE, it is necessary to use one MCDU (Ref. 22-82-00). All information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00). (2) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies faults related to the Enhanced GPWS. The BITE of the Enhanced GPWC is connected to the CFDIU. The BITE: - continuously transmits Enhanced GPWS status and its identification message to the CFDIU,

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- memorizes the faults which occurred during the last 63 flight segments, - monitors data inputs from the various peripherals (FMGC, RA transceiver, ILS receiver, ADIRU, SFCC, LGCIU, ECAM control panel and CFDIU), - transmits to the CFDIU the result of the tests performed, - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - Nnormal mode - Interactive mode. (a) Normal mode During normal mode, the BITE monitors cyclically the status of the Enhanced GPWS. It transmits its information to the CFDIU during the given flight. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 100 ms by an ARINC 429 message with label 356. (b) Interactive mode The interactive mode can only be activated on the ground. This mode enables communication between the CFDIU and the Enhanced GPWC BITE by means of the MCDU. The Enhanced GPWS menu mode is composed of: - LAST LEG REPORT **ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, (Ref. Fig. 031) **ON A/C 001-049, 051-060, 101-104, 106-149, 220-233, 236-238, 301-304, 401-403, (Ref. Fig. 031A) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, - PREVIOUS LEGS REPORT **ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, (Ref. Fig. 031)

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Maintenance Test Procedure - Sub-Menu Function Figure 031   R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 Page B68 201-219,  Config-1 Nov 01/08  CES

 

Maintenance Test Procedure - Sub-Menu Function Figure 031A   R EFF : ALL  34-48-00 Page B69   Config-1 Nov 01/09  CES

 

**ON A/C 001-049, 051-060, 101-104, 106-149, 220-233, 236-238, 301-304, 401-403, (Ref. Fig. 031A) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, - LRU IDENTIFICATION **ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, (Ref. Fig. 031) **ON A/C 001-049, 051-060, 101-104, 106-149, 220-233, 236-238, 301-304, 401-403, (Ref. Fig. 031A) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, - GROUND SCANNING (Ref. Fig. 032) - TROUBLE SHOOTING DATA (Ref. Fig. 033) - CLASS 3 FAULTS **ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, (Ref. Fig. 031) **ON A/C 001-049, 051-060, 101-104, 106-149, 220-233, 236-238, 301-304, 401-403, (Ref. Fig. 031A) **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 401-403, - GROUND REPORT (Ref. Fig. 032) - CURRENT STATUS (Ref. Fig. 033) - TEST

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Maintenance Test Procedure - Sub-Menu Function Figure 032   R EFF : ALL  34-48-00 Page B71   Config-1 Nov 01/09  CES

 

Maintenance Test Procedure - Sub-Menu Function Figure 033   R EFF : ALL  34-48-00 Page B72   Config-1 Nov 01/09  CES

 

(Ref. Fig. 034)

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Maintenance Test Procedure - Sub-Menu Function Figure 034   R EFF : ALL  34-48-00 Page B74   Config-1 Nov 01/09  CES

 

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**ON A/C ALL Post SB

34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403,

B. CFDS Interface (1) Interactive function To gain access to the BITE, it is necessary to use one MCDU (Ref. 22-82-00). All information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00). (2) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies faults related to the Enhanced GPWS. The BITE of the Enhanced GPWC is connected to the CFDIU. The BITE: - continuously transmits Enhanced GPWS status and its identification message to the CFDIU, - memorizes the faults which occurred during the last 63 flight segments, - monitors data inputs from the various peripherals (FMGC, RA transceiver, ILS receiver, ADIRU, SFCC, LGCIU, ECAM control panel, GPS and CFDIU), - transmits to the CFDIU the result of the tests performed, - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - Nnormal mode - Interactive mode. (a) Normal mode During normal mode, the BITE monitors cyclically the status of the Enhanced GPWS. It transmits its information to the CFDIU during the given flight. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 100 ms by an ARINC 429 message with label 356. (b) Interactive mode The interactive mode can only be activated on the ground. This mode enables communication between the CFDIU and the Enhanced GPWC BITE by means of the MCDU. The Enhanced GPWS menu mode is composed of: - LAST LEG REPORT

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**ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, Post SB

34-1352 For A/C 001-049,051-099,101-105,151-199,201-219, (Ref. Fig. 031)

R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 220-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1352 For A/C 001-049,051-060,101-104,106-149,220-233,236-238, 301-304,401-403, (Ref. Fig. 031A) **ON A/C ALL Post SB

34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, - PREVIOUS LEGS REPORT

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, Post SB

34-1352 For A/C 001-049,051-099,101-105,151-199,201-219, (Ref. Fig. 031)

R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 220-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1352 For A/C 001-049,051-060,101-104,106-149,220-233,236-238, 301-304,401-403, (Ref. Fig. 031A) **ON A/C ALL Post SB

34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, - LRU IDENTIFICATION

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, Post SB

34-1352 For A/C 001-049,051-099,101-105,151-199,201-219, (Ref. Fig. 031)

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**ON A/C 001-049, 051-060, 101-104, 106-149, 220-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1352 For A/C 001-049,051-060,101-104,106-149,220-233,236-238, 301-304,401-403, (Ref. Fig. 031A) **ON A/C ALL Post SB

34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, - GROUND SCANNING (Ref. Fig. 032) - TROUBLE SHOOTING DATA (Ref. Fig. 033) - CLASS 3 FAULTS

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-219, Post SB

34-1352 For A/C 001-049,051-099,101-105,151-199,201-219, (Ref. Fig. 031)

R R

**ON A/C 001-049, 051-060, 101-104, 106-149, 220-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Post SB 34-1352 For A/C 001-049,051-060,101-104,106-149,220-233,236-238, 301-304,401-403, (Ref. Fig. 031A) **ON A/C ALL Post SB

34-1352 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,401-403, - GROUND REPORT (Ref. Fig. 032) - CURRENT STATUS (Ref. Fig. 033) - TEST (Ref. Fig. 034)

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**ON A/C ALL (3) Failure condition ------------------------------------------------------------------------------| FAULT | EXAMPLE | REASON | |-----------------------------------------------------------------------------| | ARINC 429 | IRS BUS INACTIVE | No expected input labels received | | Bus Fault | | for more than 4 s. | |-----------------------------------------------------------------------------| | ARINC 429 | FMGC LATITUDE | The SSM of the input data indicates| | Signal Fault | FAILURE | Failure/Warning or the input label | | | | is not meeting the required update | | | | rate. | |-----------------------------------------------------------------------------| | Discrete | Flaps stuck down | For at least 60 s: | | Input Faults | | - FLAPS are in landing configura- | | | | tion through SFFC1 (GROUND | | | | signal at GPWC FLAPS discrete | | | | input) or FLAP MODE pushbutton | | | | switch is selected OFF and | | | | - AIRSPEED > 250 Kts and | | | | - IN AIR and | | | | - RADIO ALT VALID and | | | | - AIRSPEED VALID. | | |--------------------------------------------------------------| | | Flaps stuck up | For at least 2 s: | | | | - FLAPS are not in landing configu-| | | | ration and FLAP MODE pushbutton | | | | switch is in normal position | | | | (not OFF) and | | | | - RADIO ALT < = 100 ft. and | | | | - MODE 4 TOO LOW FLAPS alert is | | | | on. | | |--------------------------------------------------------------| | | Gear stuck down | For at least 60 s: | | | | - GEAR is down through LGCIU1 and | | | | - AIRSPEED > 290 Kts and | | | | - IN AIR and | | | | - RADIO ALT VALID and | | | | - AIRSPEED VALID. | | |--------------------------------------------------------------| | | Gear stuck up | For at least 2 s: | | | | - GEAR not down and | | | | - RADIO ALT < = 100 ft. and | | | | - MODE 4 TOO LOW GEAR alert is |

  R EFF : ALL  34-48-00 Page B78   Config-1 Nov 01/09  CES

 

------------------------------------------------------------------------------| FAULT | EXAMPLE | REASON | |-----------------------------------------------------------------------------| | | | on. | ------------------------------------------------------------------------------**ON A/C 061-099, 151-199, 201-214, (4) Reporting function (a) Internal failures --------------------------------------------------------------------------| Reported Internal Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWC (1WZ) | 1 | 34-48-34 | | GPWC (1WZ) | 3 | 34-48-34 | | WRG:PIN PROG/GPWC (1WZ) | 1 | 34-48-34 | | CAPT/FO GPWS GS PB SW (4WZ/5WZ)/GPWC(1WZ) | 1 | 34-48-34 | | FO GPWS GS PB SW (5WZ)/GPWC(1WZ) | 1 | 34-48-08 | | ECP(6WT)/GPWC(1WZ) | 1 | 31-61-12 | | GPWS SYS PB SW (9WZ)/GPWC (1WZ) | 1 | 34-48-08 | | GPWS TERR PB SW (31WZ)/GPWC(1WZ) | 1 | 34-48-08 | | GPWC(1WZ)/FWC1/2(1WW1/2)/WXR1/2(1SQ1/2) | 1 | 34-48-34 | | CAPT TERR ON ND PB SW (30WZ1)/GPWC (1WZ) | 1 | 34-48-08 | | FO TERR ON ND PB SW (30WZ2)/GPWC (1WZ) | 1 | 34-48-08 | ---------------------------------------------------------------------------

  R EFF : ALL  34-48-00 Page B79   Config-1 Nov 01/09  CES

 

(b) External failures --------------------------------------------------------------------------| Reported External Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWS FLP MODE PB SW (7WZ)/SFCC1(21CV)/GPWC(1WZ) | 1 | 34-48-08 | | LGCIU1 (5GA1)/GPWC (1WZ) | 1 | 32-31-71 | | CFDIU (1TW)/GPWC (1WZ) | 3 | 31-32-34 | | RA1 (2SA1)/GPWC (1WZ) | 1 | 34-42-33 | | ADIRU1 (1FP1)/GPWC (1WZ) | 1 | 34-12-34 | | ADIRU1 (1FP1)/GPWC (1WZ) | 3 | 34-12-34 | | MMR1 (40RT1)/GPWC (1WZ) | 1 | 34-36-31 | | MMR1 (40RT1)/GPWC (1WZ) | 3 | 34-36-31 | | FMGC1 (1CA1)/GPWC (1WZ) | 1 | 22-83-34 | | FMGC1 (1CA1)/GPWC (1WZ) | 3 | 22-83-34 | | FCU (3CA) BUS CP-L/GPWC (1WZ) | 1 | 22-81-12 | | FCU (3CA) BUS CP-R/GPWC (1WZ) | 1 | 22-81-12 | | WXR1 (1SQ1) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR1 (1SQ1)/GPWC (1WZ) | 1 | 34-41-33 | | WXR2 (1SQ2) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR2 (1SQ2)/GPWC (1WZ) | 1 | 34-41-33 | --------------------------------------------------------------------------**ON A/C 105-105, (4) Reporting function (a) Internal failures --------------------------------------------------------------------------| Reported Internal Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWC (1WZ) | 1 | 34-48-34 | | GPWC (1WZ) | 3 | 34-48-34 | | WRG:PIN PROG/GPWC (1WZ) | 1 | 34-48-34 | | CAPT/FO GPWS GS PB SW (4WZ/5WZ)/GPWC(1WZ) | 1 | 34-48-34 | | FO GPWS GS PB SW (5WZ)/GPWC(1WZ) | 1 | 34-48-08 | | ECP(6WT)/GPWC(1WZ) | 1 | 31-61-12 | | GPWS SYS PB SW (9WZ)/GPWC (1WZ) | 1 | 34-48-08 | | GPWS TERR PB SW (31WZ)/GPWC(1WZ) | 1 | 34-48-08 | | GPWC(1WZ)/FWC1/2(1WW1/2)/WXR1/2(1SQ1/2) | 1 | 34-48-34 | | CAPT TERR ON ND PB SW (30WZ1)/GPWC (1WZ) | 1 | 34-48-08 |

  R EFF : 061-099, 105-105, 151-199, 201-214,  34-48-00 Page B80   Config-1 Nov 01/08  CES

 

--------------------------------------------------------------------------| Reported Internal Failures | |-------------------------------------------------------------------------| | FO TERR ON ND PB SW (30WZ2)/GPWC (1WZ) | 1 | 34-48-08 | ---------------------------------------------------------------------------

  R EFF : 105-105,  34-48-00 Page B81   Config-1 Nov 01/08  CES

 

(b) External failures --------------------------------------------------------------------------| Reported External Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWS FLP MODE PB SW (7WZ)/SFCC1(21CV)/GPWC(1WZ) | 1 | 34-48-08 | | LGCIU1 (5GA1)/GPWC (1WZ) | 1 | 32-31-71 | | CFDIU (1TW)/GPWC (1WZ) | 3 | 31-32-34 | | RA1 (2SA1)/GPWC (1WZ) | 1 | 34-42-33 | | ADIRU1 (1FP1)/GPWC (1WZ) | 1 | 34-12-34 | | ADIRU1 (1FP1)/GPWC (1WZ) | 3 | 34-12-34 | | MMR1 (40RT1)/GPWC (1WZ) | 1 | 34-36-31 | | MMR1 (40RT1)/GPWC (1WZ) | 3 | 34-36-31 | | FMGC1 (1CA1)/GPWC (1WZ) | 1 | 22-83-34 | | FMGC1 (1CA1)/GPWC (1WZ) | 3 | 22-83-34 | | FCU (3CA) BUS CP-L/GPWC (1WZ) | 1 | 22-81-12 | | FCU (3CA) BUS CP-R/GPWC (1WZ) | 1 | 22-81-12 | | WXR1 (1SQ1) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR1 (1SQ1)/GPWC (1WZ) | 1 | 34-41-33 | --------------------------------------------------------------------------**ON A/C 001-004, 051-060, (4) Reporting function (a) Internal failures --------------------------------------------------------------------------| Reported Internal Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWC (1WZ) | 1 | 34-48-34 | | GPWC (1WZ) | 3 | 34-48-34 | | WRG:PIN PROG/GPWC (1WZ) | 1 | 34-48-34 | | CAPT/FO GPWS GS PB SW (4WZ/5WZ)/GPWC(1WZ) | 1 | 34-48-34 | | FO GPWS GS PB SW (5WZ)/GPWC(1WZ) | 1 | 34-48-08 | | ECP(6WT)/GPWC(1WZ) | 1 | 31-61-12 | | GPWS SYS PB SW (9WZ)/GPWC (1WZ) | 1 | 34-48-08 | | GPWS TERR PB SW (31WZ)/GPWC(1WZ) | 1 | 34-48-08 | | GPWC(1WZ)/FWC1/2(1WW1/2)/WXR1/2(1SQ1/2) | 1 | 34-48-34 | | CAPT TERR ON ND PB SW (30WZ1)/GPWC (1WZ) | 1 | 34-48-08 | | FO TERR ON ND PB SW (30WZ2)/GPWC (1WZ) | 1 | 34-48-08 | ---------------------------------------------------------------------------

  R EFF : 001-004, 051-060, 105-105,  34-48-00 Page B82   Config-1 Nov 01/08  CES

 

(b) External failures --------------------------------------------------------------------------| Reported External Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWS FLP MODE PB SW (7WZ)/SFCC1(21CV)/GPWC(1WZ) | 1 | 34-48-08 | | LGCIU1 (5GA1)/GPWC (1WZ) | 1 | 32-31-71 | | CFDIU (1TW)/GPWC (1WZ) | 3 | 31-32-34 | | RA1 (2SA1)/GPWC (1WZ) | 1 | 34-42-33 | | ADIRU1 (1FP1)/GPWC (1WZ) | 1 | 34-12-34 | | ADIRU1 (1FP1)/GPWC (1WZ) | 3 | 34-12-34 | | ILS1 (2RT1)/GPWC (1WZ) | 1 | 34-36-31 | | ILS1 (2RT1)/GPWC (1WZ) | 3 | 34-36-31 | | FMGC1 (1CA1)/GPWC (1WZ) | 1 | 22-83-34 | | FMGC1 (1CA1)/GPWC (1WZ) | 3 | 22-83-34 | | FCU (3CA) BUS CP-L/GPWC (1WZ) | 1 | 22-81-12 | | FCU (3CA) BUS CP-R/GPWC (1WZ) | 1 | 22-81-12 | | WXR1 (1SQ1) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR1 (1SQ1)/GPWC (1WZ) | 1 | 34-41-33 | | WXR2 (1SQ2) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR2 (1SQ2)/GPWC (1WZ) | 1 | 34-41-33 | --------------------------------------------------------------------------(4) Reporting function (a) Internal failures --------------------------------------------------------------------------| Reported Internal Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWC (1WZ) | 1 | 34-48-34 | | GPWC (1WZ) | 3 | 34-48-34 | | WRG:PIN PROG/GPWC (1WZ) | 1 | 34-48-34 | | CAPT/FO PULL UP/GPWS PB SW (4WZ/5WZ)/GPWC(1WZ) | 1 | 34-48-34 | | F/O PULL UP/GPWS PB SW (5WZ)/GPWC(1WZ) | 1 | 34-48-08 | | ECP(6WT)/GPWC(1WZ) | 1 | 31-61-12 | | GPWS SYS PB SW (9WZ)/GPWC (1WZ) | 1 | 34-48-08 | | GPWS TERR PB SW (31WZ)/GPWC(1WZ) | 1 | 34-48-08 | | GPWC(1WZ)/FWC1/2(1WW1/2)/WXR1/2(1SQ1/2) | 1 | 34-48-34 | | CAPT TERR ON ND PB SW (30WZ1)/GPWC (1WZ) | 1 | 34-48-08 | | FO TERR ON ND PB SW (30WZ2)/GPWC (1WZ) | 1 | 34-48-08 | ---------------------------------------------------------------------------

  R EFF : 001-004, 051-060,  34-48-00 Page B83   Config-1 Nov 01/08  CES

 

(b) External failures --------------------------------------------------------------------------| Reported External Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWS FLP MODE PB SW (7WZ)/SFCC1(21CV)/GPWC(1WZ) | 1 | 34-48-08 | | LGCIU1 (5GA1)/GPWC (1WZ) | 1 | 32-31-71 | | CFDIU (1TW)/GPWC (1WZ) | 3 | 31-32-34 | | RA1 (2SA1)/GPWC (1WZ) | 1 | 34-42-33 | | ADIRU1 (1FP1)/GPWC (1WZ) | 1 | 34-12-34 | | ADIRU1 (1FP1)/GPWC (1WZ) | 3 | 34-12-34 | | ILS1 (2RT1)/GPWC (1WZ) | 1 | 34-36-31 | | ILS1 (2RT1)/GPWC (1WZ) | 3 | 34-36-31 | | FMGC1 (1CA1)/GPWC (1WZ) | 1 | 22-83-34 | | FMGC1 (1CA1)/GPWC (1WZ) | 3 | 22-83-34 | | FCU (3CA) BUS CP-L/GPWC (1WZ) | 1 | 22-81-12 | | FCU (3CA) BUS CP-R/GPWC (1WZ) | 1 | 22-81-12 | | WXR1 (1SQ1) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR1 (1SQ1)/GPWC (1WZ) | 1 | 34-41-33 | | WXR2 (1SQ2) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR2 (1SQ2)/GPWC (1WZ) | 1 | 34-41-33 | --------------------------------------------------------------------------R R

**ON A/C 301-399, Post SB Post SB

001-049, 051-099, 101-104, 106-149, 151-199, 201-249, 251-299, 401-499, 501-509, 511-526, 528-599, 34-1147 For A/C 001-004,051-060, 34-1351 For A/C 001-049,051-099,101-104,151-199,201-214,

(4) Reporting function (a) Internal failures --------------------------------------------------------------------------| Reported Internal Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWC (1WZ) | 1 | 34-48-34 | | GPWC (1WZ) | 3 | 34-48-34 | | WRG:PIN PROG/GPWC (1WZ) | 1 | 34-48-34 | | CAPT/FO PULL UP/GPWS PB SW (4WZ/5WZ)/GPWC(1WZ) | 1 | 34-48-34 | | F/O PULL UP/GPWS PB SW (5WZ)/GPWC(1WZ) | 1 | 34-48-08 | | ECP(6WT)/GPWC(1WZ) | 1 | 31-61-12 | | GPWS SYS PB SW (9WZ)/GPWC (1WZ) | 1 | 34-48-08 | | GPWS TERR PB SW (31WZ)/GPWC(1WZ) | 1 | 34-48-08 |

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page B84 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

--------------------------------------------------------------------------| Reported Internal Failures | |-------------------------------------------------------------------------| | GPWC(1WZ)/FWC1/2(1WW1/2)/WXR1/2(1SQ1/2) | 1 | 34-48-34 | | CAPT TERR ON ND PB SW (30WZ1)/GPWC (1WZ) | 1 | 34-48-08 | | FO TERR ON ND PB SW (30WZ2)/GPWC (1WZ) | 1 | 34-48-08 | ---------------------------------------------------------------------------

  R EFF : 001-049, 051-099, 101-104, 106-149,  34-48-00 Page B85 151-199, 201-249, 251-299, 301-399, 401-499,  Config-1 Feb 01/10 501-509, 511-526, 528-599, CES

 

(b) External failures --------------------------------------------------------------------------| Reported External Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWS FLP MODE PB SW (7WZ)/SFCC1(21CV)/GPWC(1WZ) | 1 | 34-48-08 | | LGCIU1 (5GA1)/GPWC (1WZ) | 1 | 32-31-71 | | CFDIU (1TW)/GPWC (1WZ) | 3 | 31-32-34 | | RA1 (2SA1)/GPWC (1WZ) | 1 | 34-42-33 | | ADIRU1 (1FP1)/GPWC (1WZ) | 1 | 34-12-34 | | ADIRU1 (1FP1)/GPWC (1WZ) | 3 | 34-12-34 | | MMR1 (40RT1)/GPWC (1WZ) | 1 | 34-36-31 | | MMR1 (40RT1)/GPWC (1WZ) | 3 | 34-36-31 | | FMGC1 (1CA1)/GPWC (1WZ) | 1 | 22-83-34 | | FMGC1 (1CA1)/GPWC (1WZ) | 3 | 22-83-34 | | FCU (3CA) BUS CP-L/GPWC (1WZ) | 1 | 22-81-12 | | FCU (3CA) BUS CP-R/GPWC (1WZ) | 1 | 22-81-12 | | WXR1 (1SQ1) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR1 (1SQ1)/GPWC (1WZ) | 1 | 34-41-33 | | WXR2 (1SQ2) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR2 (1SQ2)/GPWC (1WZ) | 1 | 34-41-33 | --------------------------------------------------------------------------**ON A/C 105-105, Post SB

34-1351 For A/C 105-105,

(4) Reporting function (a) Internal failures --------------------------------------------------------------------------| Reported Internal Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWC (1WZ) | 1 | 34-48-34 | | GPWC (1WZ) | 3 | 34-48-34 | | WRG:PIN PROG/GPWC (1WZ) | 1 | 34-48-34 | | CAPT/FO PULL UP/GPWS PB SW (4WZ/5WZ)/GPWC(1WZ) | 1 | 34-48-34 | | F/O PULL UP/GPWS PB SW (5WZ)/GPWC(1WZ) | 1 | 34-48-08 | | ECP(6WT)/GPWC(1WZ) | 1 | 31-61-12 | | GPWS SYS PB SW (9WZ)/GPWC (1WZ) | 1 | 34-48-08 | | GPWS TERR PB SW (31WZ)/GPWC(1WZ) | 1 | 34-48-08 | | GPWC(1WZ)/FWC1/2(1WW1/2)/WXR1/2(1SQ1/2) | 1 | 34-48-34 |

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 Page B86 201-249, 251-299, 301-399, 401-499, 501-509,  Config-1 Feb 01/10 511-526, 528-599, CES

 

--------------------------------------------------------------------------| Reported Internal Failures | |-------------------------------------------------------------------------| | CAPT TERR ON ND PB SW (30WZ1)/GPWC (1WZ) | 1 | 34-48-08 | | FO TERR ON ND PB SW (30WZ2)/GPWC (1WZ) | 1 | 34-48-08 | ---------------------------------------------------------------------------

  R EFF : 105-105,  34-48-00 Page B87   Config-1 Nov 01/08  CES

 

(b) External failures --------------------------------------------------------------------------| Reported External Failures | |-------------------------------------------------------------------------| | MESSAGE | CLASS | ATA | |-------------------------------------------------------------------------| | GPWS FLP MODE PB SW (7WZ)/SFCC1(21CV)/GPWC(1WZ) | 1 | 34-48-08 | | LGCIU1 (5GA1)/GPWC (1WZ) | 1 | 32-31-71 | | CFDIU (1TW)/GPWC (1WZ) | 3 | 31-32-34 | | RA1 (2SA1)/GPWC (1WZ) | 1 | 34-42-33 | | ADIRU1 (1FP1)/GPWC (1WZ) | 1 | 34-12-34 | | ADIRU1 (1FP1)/GPWC (1WZ) | 3 | 34-12-34 | | MMR1 (40RT1)/GPWC (1WZ) | 1 | 34-36-31 | | MMR1 (40RT1)/GPWC (1WZ) | 3 | 34-36-31 | | FMGC1 (1CA1)/GPWC (1WZ) | 1 | 22-83-34 | | FMGC1 (1CA1)/GPWC (1WZ) | 3 | 22-83-34 | | FCU (3CA) BUS CP-L/GPWC (1WZ) | 1 | 22-81-12 | | FCU (3CA) BUS CP-R/GPWC (1WZ) | 1 | 22-81-12 | | WXR1 (1SQ1) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 | | WXR1 (1SQ1)/GPWC (1WZ) | 1 | 34-41-33 | --------------------------------------------------------------------------R

**ON A/C ALL C. BITE Implementation The BITE capability is implemented primarily in software. Most of the tests run continuously, while the remainder run only as the result of certain events (e.g. power-up). Failures are indicated by monitor output discretes, the ARINC 429 outputs, the Enhanced GPWC audio output, and on the MCDU (interactive mode). These failures are saved in the flight history memory if they occurred during flight. Some BITE failures inhibit alerts and warnings. In these cases, the self-test is inhibited. Internal test processing:

  R EFF : ALL  34-48-00 Page B88   Config-1 Nov 01/09  CES

 

-----------------------------------------------------------------------------| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION | | DESIGNATION | | | CONDITIONS | |----------------------------------------------------------------------------| | MCDU system | - CPU | 30 s | Relevant MCDU | | test | - RAM | | menu line key | | | - EPROM | | selection | | | - Wait state | | | | | - Non Envelope modulation NVM | | | | | - Watchdog timer | | | | | - A/D converter | | | | | - Voice generator | | | | | - ARINC 429 transmitter | | | | | - Software configuration data | | | | | base monitor | | | | | - ARINC 429 parity | | | | | - Software operating system | | | | | monitor | | | | | - Software watchdog monitor | | | | | - Envelope modulation NVM | | | | | - ARINC 429 receiver | | | |----------------------------------------------------------------------------| | Cockpit | Ref. para. 8. A. | | Ref. para. 8. A.| | Self-test | | | | -----------------------------------------------------------------------------R R

**ON A/C 061-099, 105-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, D. Power-up Test Initialization and Cockpit Repercussions (1) Conditions of power-up test initialization - How long the computer must be de-energized: 1 s. - A/C configuration: - whatever the A/C configuration on ground (2) Progress of power-up tests - Duration: 20 s. - Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - none

  EFF : ALL  34-48-00 Page B89   Config-1 Feb 01/10  CES

 

(3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). - Tests pass: - none - Tests failed: - GPWS panel: FAULT legend of SYS pushbutton switch on and/or FAULT legend of pushbutton switch on (depending on the faulty part) - MASTER CAUT light on and single chime - ECAM warning: NAV GPWS FAULT and/or NAV GPWS TERR FAULT (depending on the faulty part) - ECAM STATUS: GPWS INOP and/or GPWS TERR INOP (depending on the faulty part)

  R EFF : 061-099, 105-149, 151-199, 201-249,  34-48-00 Page B90 251-299, 301-399, 401-499, 501-509, 511-526,  Config-1 Feb 01/10 528-599, CES

 

GROUND PROXIMITY WARNING SYSTEM (GPWS) - DESCRIPTION AND OPERATION __________________________________________________________________ 1. _______ General (Ref. Fig. 001) The Ground Proximity Warning System (GPWS) generates aural and visual warnings if the aircraft adopts a potentially hazardous condition with respect to: Mode 1 - Excessive rate of descent Mode 2 - Excessive closure rate with terrain Mode 3 - Descent after takeoff and minimum terrain clearance Mode 4 - Unsafe terrain clearance Mode 5 - Descent below glide slope. The system is operative between 30 ft. and 2450 ft. radio altitude. Four pushbutton switches on the overhead panel enable the flight crew to inhibit an abnormal flap condition signal, all GPWS warning signals and a glide slope warning signal. A GPWS/G/S pushbutton switch located on the main instrument panel (Captain and F/O) is also used to initiate the GPWC self-test when the aircraft is above 1000 ft. or below 30 ft. radio altitude. The Ground Proximity Warning Computer (GPWC) is installed in the avionics compartment. Aural warnings are broadcast from the cockpit loud speakers. The FAULT legend of the SYS pushbutton switch, located on the overhead panel 21VU, comes on to indicate system fault. (Ref. Fig. 001) R

**ON A/C 001-049, 051-060, 101-104,

R

Post SB

R R R R R R R R R R R R R R R R

34-1278 For A/C 001-049,051-060,101-104,

(Ref. Fig. 001A) The Ground Proximity Warning System (GPWS) generates aural and visual warnings if the aircraft adopts a potentially hazardous condition with respect to: Mode 1 - Excessive rate of descent Mode 2 - Excessive closure rate with terrain Mode 3 - Descent after takeoff and minimum terrain clearance Mode 4 - Unsafe terrain clearance Mode 5 - Descent below glide slope. The system is operative between 30 ft. and 2450 ft. radio altitude. Four pushbutton switches on the overhead panel enable the flight crew to inhibit an abnormal flap condition signal, all GPWS warning signals and a glide slope warning signal. A PULL UP/GPWS pushbutton switch located on the main instrument panel (Captain and F/O) is also used to initiate the GPWC self-test when the aircraft is above 1000 ft. or below 30 ft. radio altitude.

  EFF : 001-049, 051-060, 101-104,  34-48-00 Page 1   Config-2 Feb 01/07  CES

 

R

GPWS - Component Location Figure 001

  EFF : 001-049, 051-060, 101-104,  34-48-00 Page 2   Config-2 May 01/06  CES

 

R R

GPWS - Component Location Figure 001A

  EFF : 001-049, 051-060, 101-104,  34-48-00 Page 3   Config-2 Feb 01/07  CES

 

R R R R R R

The Ground Proximity Warning Computer (GPWC) is installed in the avionics compartment. Aural warnings are broadcast from the cockpit loud speakers. The FAULT legend of the SYS pushbutton switch, located on the overhead panel 21VU, comes on to indicate system fault. **ON A/C 001-049, 051-060, 101-104, 2. Component __________________ Location (Ref. Fig. 001) ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1WZ GPWC 88VU 128 824 34-48-34 4WZ P/BSW-GPWS/G/S 500VU 212 34-48-00 5WZ P/BSW-GPWS/G/S 301VU 211 34-48-00 7WZ P/BSW-GPWS/FLAP MODE 21VU 211 34-48-00 9WZ P/BSW-GPWS/SYS 21VU 211 34-48-00 11WZ P/BSW-GPWS/G/S MODE 21VU 211 34-48-00 13WZ P/BSW-GPWS/LDG FLAP 3 21VU 211 34-48-00

R

**ON A/C 001-049, 051-060, 101-104,

R

Post SB

R R R R R R R R R R R R

34-1278 For A/C 001-049,051-060,101-104,

(Ref. Fig. 001A) ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1WZ GPWC 88VU 128 824 34-48-34 4WZ P/BSW-PULL UP/GPWS 500VU 212 34-48-00 5WZ P/BSW-PULL UP/GPWS 301VU 211 34-48-00 7WZ P/BSW-GPWS/FLAP MODE 21VU 211 34-48-00 9WZ P/BSW-GPWS/SYS 21VU 211 34-48-00 11WZ P/BSW-GPWS/G/S MODE 21VU 211 34-48-00 13WZ P/BSW-GPWS/LDG FLAP 3 21VU 211 34-48-00

  R EFF : 001-049, 051-060, 101-104,  34-48-00 Page 4   Config-2 Feb 01/07  CES

 

R

**ON A/C 001-049, 051-060, 101-104, 3. __________________ System Description A. General The GPWS monitors data inputs from the navigation sensors. This information is used to provide suitable aural warnings to alert the crew of insufficient terrain clearance or excessive descent rate. B. Warnings Warnings are generated by the Ground Proximity Warning Computer (GPWC) which is installed on the shelf 88VU, in the aft electronics rack 80VU. Aural warnings are broadcast from the cockpit loud speakers. **ON A/C 001-004, 051-060, C. Digital Data Inputs (Ref. Fig. 002) The GPWC receives serial digital data inputs from the following: - radio altimeter transceiver 1 (radio altitude) - Air Data/Inertial Reference Unit 1 (ADIRU) - ADR portion (barometric altitude, barometric altitude rate, computed airspeed) - IR portion (latitude, longitude, magnetic heading) - ILS receiver 1 (glide slope deviation, localizer deviation, selected runway heading) - Flight Management and Guidance Computer (FMGC) (latitude, longitude, track). **ON A/C 001-049, 051-060, 101-104, Post SB

34-1147 For A/C 001-004,051-060,

C. Digital Data Inputs (Ref. Fig. 002A) The GPWC receives serial digital data inputs from the following: - radio altimeter transceiver 1 (radio altitude), - Air Data/Inertial Reference Unit 1 (ADIRU), - ADR portion (barometric altitude, barometric altitude rate, computed airspeed), - IR portion (latitude, longitude, magnetic heading), - Multi-Mode Receiver 1 (MMR) (glide slope deviation, localizer deviation, selected runway heading), - Flight Management and Guidance Computer (FMGC) (latitude, longitude, track).

  EFF : 001-049, 051-060, 101-104,  34-48-00 Page 5   Config-2 Feb 01/07  CES

 

GPWS - Inputs (Buses) Figure 002   R EFF : 001-004, 051-060,  34-48-00 Page 6   Config-2 Feb 01/07  CES

 

GPWC - Inputs (Buses) Figure 002A   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 7   Config-2 Feb 01/07 R  CES

 

**ON A/C 001-049, 051-060, 101-104, D. Discrete Data Inputs **ON A/C 001-049, 101-104, (Ref. Fig. 003) **ON A/C 051-060, (Ref. Fig. 003A) **ON A/C 001-049, 051-060, 101-104, Discrete data inputs are received from the following: - Slat Flap Control Computer 1 (SFCC) (3 and FULL flap position) - Flight Warning Computer 1 and 2 (FWC) (stall warning inhibition) - main landing gear - ECAM control panel (audio suppression) - FLAP MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides a flap abnormal condition input - SYS pushbutton switch which, when pressed (in) (white OFF legend on), overrides all the GPWS warnings - G/S MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides the glide slope mode - GPWS/G/S pushbutton switch which, when pressed (in), enables the GPWC to perform test - Weather Radar with Predictive Windshear System (WR/PWS), inhibition of GPWS aural alert each time there is a PWS aural alert. R

**ON A/C 001-049, 051-060, 101-104,

R

Post SB

34-1278 For A/C 001-049,051-060,101-104,

R

D. Discrete Data Inputs

R

**ON A/C 001-049, 101-104,

R

Post SB

R

34-1278 For A/C 001-049,101-104,

(Ref. Fig. 003)

  R EFF : 001-049, 051-060, 101-104,  34-48-00 Page 8   Config-2 Feb 01/07  CES

 

GPWS - Inputs (Discretes) Figure 003   R EFF : 001-049, 101-104,  34-48-00 Page 9   Config-2 Feb 01/07  CES

 

GPWS - Inputs (Discretes) Figure 003A   R EFF : 051-060,  34-48-00 Page 10   Config-2 Feb 01/07  CES

 

R

**ON A/C 051-060,

R

Post SB

R

34-1278 For A/C 051-060,

(Ref. Fig. 003A)

R

**ON A/C 001-049, 051-060, 101-104,

R

Post SB

R R R R R R R R R R R R R R R R

34-1278 For A/C 001-049,051-060,101-104,

Discrete data inputs are received from the following: - Slat Flap Control Computer 1 (SFCC) (3 and FULL flap position) - Flight Warning Computer 1 and 2 (FWC) (stall warning inhibition) - main landing gear - ECAM control panel (audio suppression) - FLAP MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides a flap abnormal condition input - SYS pushbutton switch which, when pressed (in) (white OFF legend on), overrides all the GPWS warnings - G/S MODE pushbutton switch which, when pressed (in) (white OFF legend on), overrides the glide slope mode - PULL UP/GPWS pushbutton switch which, when pressed (in), enables the GPWC to perform test. - Weather Radar with Predictive Windshear (WR/PWS), inhibition of GPWS aural alert each time there is a PWS aural alert. **ON A/C 001-049, 051-060, 101-104, E. Warning Outputs (Ref. Fig. 004) - two discrete outputs from the GPWC control the GPWS/G/S pushbutton switches located on Captain and First Officer main instrument panels. Each pushbutton switch is a momentary contact pushbutton switch with an illuminated split legend cap. The upper legend identified GPWS, controlled by the first output, comes on red when a ground proximity warning is generated by the GPWC for modes 1 to 4. The lower legend identified G/S, controlled by the second output, comes on amber when a glide slope (Mode 5) advisory alert is generated by the GPWC. The pushbutton switch provides a facility to cancel a glide slope warning, if in progress, or to initiate a GPWS self-test. - both discrete outputs are also used to inhibit automatic call out when the GPWS or G/S warnings are in progress. - both discrete outputs are also used for the Digital Flight Data Recorder (DFDR).

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GPWS - Outputs Figure 004   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 12   Config-2 Feb 01/07 R  CES

 

------------------------------------------------------------------------------NAME ELECTRICAL LEVEL TO SIGNAL STATUS ------------------------------------------------------------------------------FAULT LEGEND GND/OC SYS P/BSW/SDACs GND = VALID G/S VISUAL ALERT GND/OCFWCsGND = VALID GPWS LEGEND GND/OCFWCsGND = VALID ------------------------------------------------------------------------------R

**ON A/C 001-049, 051-060, 101-104,

R

Post SB

34-1278 For A/C 001-049,051-060,101-104,

R R R R R R R R R R R R R R R R R

E. Warning Outputs (Ref. Fig. 004A) - two discrete outputs from the GPWC control the PULL UP/GPWS pushbutton switches located on Captain and First Officer main instrument panels. Each pushbutton switch is a momentary contact pushbutton switch with an illuminated split legend cap. The upper legend identified PULL UP, controlled by the first output, comes on red when a ground proximity warning is generated by the GPWC for modes 1 to 4. The lower legend identified GPWS, controlled by the second output, comes on amber when a glide slope (Mode 5) advisory alert is generated by the GPWC. The pushbutton switch provides a facility to cancel a glide slope warning, if in progress, or to initiate a GPWS self-test. - both discrete outputs are also used to inhibit automatic call out when the GPWS or GPWS warnings are in progress. - both discrete outputs are also used for the Digital Flight Data Recorder (DFDR).

R R R R R R R

------------------------------------------------------------------------------NAME ELECTRICAL LEVEL TO SIGNAL STATUS ------------------------------------------------------------------------------FAULT LEGEND GND/OC SYS P/BSW/SDACs GND = VALID G/S VISUAL ALERT GND/OC FWCs GND = VALID GPWS LEGEND GND/OC FWCs GND = VALID -------------------------------------------------------------------------------

R

**ON A/C 001-049, 051-060, 101-104, F. Monitor Output The monitor output from the GPWC controls the FAULT legend of the SYS pushbutton switch .

  EFF : 001-049, 051-060, 101-104,  34-48-00 Page 13   Config-2 Feb 01/07  CES

 

R R

GPWS - Outputs Figure 004A

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G. Bus Output The bus output could be used by the aircraft integrated data system (AIDS) (data management unit (DMU) and by the Centralized Fault-Display Interface - Unit (CFDIU) for test causes. H. Audio Output The audio output is used by the cockpit loud speakers for aural warning messages. 4. Power ____________ Supply (Ref. Fig. 004) R

**ON A/C 001-049, 051-060, 101-104,

R

Post SB

R R

34-1278 For A/C 001-049,051-060,101-104,

(Ref. Fig. 004A) **ON A/C 001-049, 051-060, 101-104, The GPWC power supply circuits receive 115VAC, 400 Hz, single phase (20 W max.) supply from the aircraft AC power and converts this supply to the following DC levels: plus or minus 15VDC from linear regulators with current limiting + 5VDC from a compensated switching regulator with current limiting - 30VDC from a voltage doubler, fed by the 15VDC regulated supply. 5. _____________________ Component Description A. GPWC (1WZ) (1) Description (Ref. Fig. 005) (a) The GPWC comprises an ARINC 600-2MCU case, housing interfacing, computing and warning output circuits. (b) The face of the GPWC contains a STATUS/HISTORY test switch and associated 8-character, alpha-numeric BITE display. If the STATUS/HISTORY switch is momentarily set to PRESENT STATUS, the BITE display provides a sequential readout of system operational status. If the STATUS/HISTORY switch is momentarily set to FLIGHT HISTORY, the BITE display provides a sequential readout of system faults stored from the previous 10 flights.

  EFF : 001-049, 051-060, 101-104,  34-48-00 Page 15   Config-2 Feb 01/07  CES

 

GPWC Figure 005   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 16   Config-2 Feb 01/07 R  CES

 

(c) The back of the GPWC contains an ARINC 600, shell size connector to provide electrical connections to the aircraft wiring via mount. Contact grouping is as follows: - Top contact set - ATE interface + system interconnections - Center contact set - System interconnections - Bottom contact set - Power supply and bonding.

  EFF : 001-049, 051-060, 101-104,  34-48-00 Page 17   Config-2 Feb 01/07 R  CES

 

(2) Operation (Ref. Fig. 006) (a) Input/output circuits The input/output circuits contain six ARINC 429 receivers. Each receiver converts specified ARINC 429 format serial digital data to 32-bit parallel words for storage in a Random Access Memory (RAM). Data is accessed from RAM and checked for updating by the processor/voice/memory circuit. Discrete inputs to the GPWC are detected by ground sensing buffers and converted to a digital word. An ARINC 429 transmitter provides the GPWS output data words in ARINC 429 format (label 270 octal) for the Data Management Unit (DMU) and the maintenance labels for the CFDIU. Discrete outputs for the FAULT legend of the SYS pushbutton switch are provided by over-voltage and reverse-voltage protected lamp drivers. (b) Processor/voice/memory The processor/voice/memory consists of a 16-bit microprocessor (with associated timing and buffer circuits), program and voice memories, delta modulator, serial data stream generator, serial communication port, interrupt controllers and various associated logic. The 16-bit microprocessor is driven by a 4 MHz clock and is monitored by a watchdog timer. The watchdog timer resets the processor in the event of an incomplete program iteration. The aural warning messages reside in two 64 Kbytes X 8 Erasable Programmable Read Only Memories (EPROMs). The vocabulary for the messages can be defined by an alternate audio alert select discrete input. When a message is required for broadcast, the associated bits are converted from parallel to serial format and shifted into the delta modulator. The audio output is filtered, amplified and isolated to provide a suitable signal for the cockpit loud speakers. Data storage in the scratchpad memory is achieved using two 8 Kbytes RAMs. Fault history data is stored in an Electrically Erasable Programmable ROM (EEPROM) which is also used to store present flight characteristics data for use after momentary power losses. The program memory resides in 64 Kbytes EPROMs. The EPROMs are ultra-violet light erasable.

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GPWC - Block Diagram Figure 006   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 19   Config-2 Feb 01/07 R  CES

 

(3) Digital outputs This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI: (SDAC,FWC,DRC___) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds - CODE : BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 1.270.00 |GPWS DSCRT| | | | | 50 |DIS | | | | |WORD 1 | | | | | | | | | | | | | | | | | | | | | |SINK RATE |bit status 1| | | 11 | | | | | | | | | | | | | | | | | |WHOOP |bit status 1| | | 12 | | | | | | |WHOOP | | | | | | | | | | |PULL UP | | | | | | | | | | | | | | | | | | | | | |TERRAIN |bit status 1| | | 13 | | | | | | | | | | | | | | | | | |DONT |bit status 1| | | 14 | | | | | | |SINK | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| | | | | | | | | | | | |TOO LOW |bit status 1| | | 15 | | | | | | |GEAR | | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | | 16 | | | | | | |FLAP | | | | | | | | | | | | | | | | | | | | | |TOO LOW |bit status 1| | | 17 | | | | | | |TERRAIN | | | | | | | | | | |(mode 4) | | | | | | | | | | | | | | | | | | | | | |GLIDESLOPE|bit status 1| | | 18 | | | | | | | | | | | | | | | | | |NOT USED | | | | 19 | | | | | | | | | | | | | | | | | |TERRAIN - |bit status 1| | | 20 | | | | | | |PULL UP | | | | | | | | | | | | | | | | | | | | | |SPARE | | | | 21 | | | | | | | | | | | | | | | | | |SPARE | | | | 22 | | | | | | | | | | | | | | | | | |SPARE | | | | 23 | | | | | | | | | | | | | | | | | |SPARE | | | | 24 | | | | | | | | | | | | | | | | | |SPARE | | | | 25 | | | | | | | | | | | | | | | | | |SPARE | | | | 26 | | | | | | | | | | | | | | | | | |SPARE | | | | 27 | | | | | | | | | | | | | | | | | |SPARE | | | | 28 | | | | | | | | | | | | | | | | | |SPARE | | | | 29 | | | | | | | | | | | | | | | | | 125 |UNIVERSAL | | | | | |BCD | | | | |TIME | | | | | | | | |

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------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| |CORRELA- | | | | | | | | | | |TION | | | | | | | | | | | | | | | | | | | | | 227 |BITE | | | | | |BNR | | | | |COMMAND | | | | | | | | | | |WORD | | | | | | | | | | | | | | | | | | | | | 260 |DATE | | | | | |BCD | | | | | | | | | | | | | | | 356 |CFDIU | | | | | |BNR | | | | |MAINT WORD| | | | | | | | | ------------------------------------------------------------------------------B. Pushbutton Switches (Ref. Fig. 001) R

**ON A/C 001-049, 051-060, 101-104,

R

Post SB

R R

34-1278 For A/C 001-049,051-060,101-104,

(Ref. Fig. 001A) **ON A/C 001-049, 051-060, 101-104, The pushbutton switches are located on the overhead panel 21VU. (1) LDG FLAP 3 pushbutton switch 13WZ To avoid nuisance warnings during approach, the GPWC needs to know at which flap position the crew intends to land. The LDG FLAP 3 pushbutton switch (item 4), when pressed (in) (white ON legend on), indicates to the GPWC that the pilot intends to land in flap 3 position, inhibits the GPWC warnings TOO LOW FLAPS. When released (out), the pushbutton switch indicates to the GPWS that the pilot intends to land in flap FULL position. The GPWS FLAP message is permamently displayed in green on the MEMO of the ECAM display unit if no warning is in progress.

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(2) FLAP MODE pushbutton switch 7WZ The pushbutton switch (item 3), when pressed (in) (white OFF legend on), overrides flap abnormal condition input. (3) SYS pushbutton switch 9WZ The pushbutton switch (item 1), when pressed (in) (white OFF legend on), inhibits all the GPWS warnings. (4) G/S MODE pushbutton switch 11WZ The pushbutton switch (item 2), when pressed (in) (white OFF legend on), inhibits the glide slope mode. C. SYS Pushbutton Switch 9WZ (Ref. Fig. 001) R

**ON A/C 001-049, 051-060, 101-104,

R

Post SB

R R

34-1278 For A/C 001-049,051-060,101-104,

(Ref. Fig. 001A) **ON A/C 001-049, 051-060, 101-104, (1) The SYS pushbutton switch, located on the overhead panel 24VU, provides a FAULT warning indicating that a system fault has been detected by the GPWC. (2) When the FAULT legend comes on, all the ground proximity warnings are inhibited and no GPWC self-test is possible. (3) When the FAULT legend comes on, messages are displayed on the upper ECAM display unit (if they are not inhibited by the FWC): NAV: - GPWS FAULT (amber) associated with action requested - GPWS OFF (cyan). A fault message is sent to the CFDIU. A GPWS message (amber) is also displayed on the STATUS page on the lower ECAM display unit.

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6. Operation _________ A. General (1) Warning modes The serial digital data and discrete data inputs are interfaced and used in different combinations to monitor aircraft vertical performance. The following functions are monitored: Mode 1 - Excessive rate of descent (Ref. Fig. 007) Mode 2 - Excessive closure rate with terrain (Ref. Fig. 008) Mode 3 - Descent after takeoff and minimum terrain clearance (Ref. Fig. 009) Mode 4 - Unsafe terrain clearance (Ref. Fig. 010) Mode 5 - Descent below glide slope (Ref. Fig. 011) (2) Warning messages (Ref. Fig. 008, 009, 010, 011) Each mode computes and compares aircraft behaviour with a corresponding warning envelope. If the warning envelope is penetrated, visual and aural warnings are generated. The aural message is broadcast through the cockpit loud speakers. The messages are as follows: MODE AURAL WARNING VISUAL WARNING 1 SINK RATE GPWS 1 WHOOP WHOOP PULL UP GPWS 2 TERRAIN GPWS 2 WHOOP WHOOP PULL UP GPWS 3 DONT SINK GPWS 3 TERRAIN GPWS 4 TOO LOW TERRAIN GPWS 4 TOO LOW GEAR GPWS 4 TOO LOW FLAPS GPWS 5 GLIDE SLOPE G/S Each of these warnings inhibits the automatic call out. NOTE : During mode 2, the TERRAIN warning is broadcast for 1.4 ____ seconds and then, unless the warning envelope is departed, changes to WHOOP WHOOP PULL UP. This latter warning will be continuously broadcast until the aircraft departs from the original warning envelope, then the TERRAIN warning is broadcast again until the aircraft has climbed through a further 300 ft. of radio altitude.

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Excessive Rate of Descent Figure 007   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 25   Config-2 Feb 01/07 R  CES

 

Terrain Cloture Rate - Mode Figure 008   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 26   Config-2 Feb 01/07 R  CES

 

Descent After Takeoff Figure 009   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 27   Config-2 Feb 01/07 R  CES

 

Unsafe Terrain Clearance Figure 010   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 28   Config-2 Feb 01/07 R  CES

 

Descent Below Glide Slope Figure 011   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 29   Config-2 Feb 01/07 R  CES

 

(3) Inhibitions Warnings may be cancelled by: (a) Pressing the EMER CANC key on the ECAM control panel (aural warning only). (b) Pressing the GPWS/G/S pushbutton switch on the main instrument panel for mode 5 (glide slope) visual and aural warning. This inhibition is temporary and the mode will be automatically reactivated for a new envelope penetration. (c) Pressing the G/S MODE pushbutton switch on the overhead panel for mode 5 (glide slope) visual and aural warning (permanent inhibition). (d) Pressing the SYS pushbutton switch on the overhead panel for inhibition of all the modes (visual and aural warnings). (e) The GPWC is automatically inhibited if a stall warning is in progress. (4) Faults which prevent normal GPWC operation are stored in the BITE memory and may be read on the BITE display by operating the STATUS/ HISTORY switch located on the GPWC face below the BITE display. R

**ON A/C 001-049, 051-060, 101-104,

R

Post SB

R R

34-1278 For A/C 001-049,051-060,101-104,

(3) Inhibitions Warnings may be cancelled by:

R R

(a) Pressing the EMER CANC key on the ECAM control panel (aural warning only).

R R R R

(b) Pressing the PULL UP/GPWS pushbutton switch on the main instrument panel for mode 5 (glide slope) visual and aural warning. This inhibition is temporary and the mode will be automatically reactivated for a new envelope penetration.

R R R

(c) Pressing the G/S MODE pushbutton switch on the overhead panel for mode 5 (glide slope) visual and aural warning (permanent inhibition).

R R

(d) Pressing the SYS pushbutton switch on the overhead panel for inhibition of all the modes (visual and aural warnings).

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R R

(e) The GPWC is automatically inhibited if a stall warning is in progress.

R R R R R

(4) Faults which prevent normal GPWC operation are stored in the BITE memory and may be read on the BITE display by operating the STATUS/ HISTORY switch located on the GPWC face below the BITE display. When the fault is stored, the FAULT legend of the SYS pushbutton switch comes on.

R

**ON A/C 001-049, 051-060, 101-104, B. Detailed Operation - Modes 1 through 5 This section describes the five warning modes of the GPWC and describes the operation of each of the modes. The voice messages are illustrated for the basic vocabulary, i.e., no audio select program pins connected. (1) Mode 1 - Excessive rate of descent (Ref. Fig. 007) (a) The mode 1 provides the pilot with an alert/warning for the high descent rates into terrain. The pilot also receives a timely alert for rapidly building sink rates near the runway when landing. The figure shows the outer and inner boundaries whose penetrations trigger the alert/warnings. (b) The outer boundary is a straight line which has an equation of: H warn (ft.) = - 572 ft. - 0.6035 X Altitude rate. NOTE : The descent rate is considered negative during the ____ descent. The formulas provide design goals only. (c) The penetration of this outer boundary will activate the GPWS legends and produce the voice warning SINK RATE. This will continue until the boundary penetration is corrected. (d) Further penetration of the first boundary will reach the inner boundary where the voice warning will change from SINK RATE to WHOOP WHOOP PULL UP. This inner boundary is composed of two straight lines. The equation which describes the lower line is: H warn (ft) = - 1620 ft. - 1.1133 X Altitude rate. The equation which describes the upper line is: H warn (ft) = - 400 ft. - 0.400 X Altitude rate.

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(e) Both boundaries are cut off at the top by 2450 ft. The lower is cut off at 10 ft. A seconds is included in the upper function warnings caused by the momentary boundary

a radio altitude of delay equivalent to 0.8 to minimize the penetration.

(2) Mode 2 - Excessive closure rate with terrain (Ref. Fig. 008) (a) The mode 2 provides a warning based on the radio altitude between the aircraft and the ground and on how rapidly the radio altitude decreases. The barometric altitude of the aircraft is not important for the initiation of this warning. (b) The altitude rate is complemented in the filter to provide lead information. The increase of the altitude descent rate will tend to speed up the warning occurrence. The reduction of the altitude descent rate or the initiation of a climb will tend to delay the warning occurrence or reduce the time the warning is on. (c) This mode has two areas of application that are generally referred to as mode 2A and mode 2B. The mode 2A is applied when the landing flaps are not down and the aircraft is not in the glide slope beam. The mode 2B requires that the landing flaps be down or that the aircraft be in the glide slope beam within +/- 2 dots of deviation during an ILS approach. The figure shows the warning boundary for the mode 2A (landing flaps up). The closure rate is the computed change in the radio altitude between the aircraft and the ground. It is considered positive when the altitude decreases. The lower sloped line has an equation of : H warn (ft.) = - 1579 ft. + 0.7895 X Closure Rate (FPM). The upper sloped line has an equation of: H warn (ft) = 522 ft + 0.1968 X closure rate (FPM). (d) The normal upper limit of the boundary is horizontal at 1650 ft. radio altitude due to a computed maximum closure rate limit of 5733 FPM. As the airspeed increases from 220 Kts up to 310 Kts, the maximum rate limit is linearly increased to 9800 FPM. This allows the upper boundary to also linearly increase up to 2450 ft. The upper boundary is limited at certain airports to reduce the warning sensitivity and minimize the nuisance warnings.

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(e) Upon penetration of the boundary, either on the slope or from the top, the GPWS legends come on and the voice message is TERRAIN. If the boundary penetration lasts beyond two TERRAIN messages, approximately 1.4 seconds, then the warning switches to WHOOP WHOOP/ PULL UP repeated continuously until the boundary is departed. The altitude gain feature is automatically activated. First the altitude at this instant is sampled and stored. The GPWS legends remain on and the voice message is TERRAIN. After three hundred feet of altitude are gained from the stored value, the GPWS legends and voice stop. If another boundary penetration occurs during this altitude gain time, and it lasts long enough to restart the PULL UP warning, 1.4 seconds, then the whole process begins again with a new reference altitude for the 300 ft. after boundary separation. In this manner the aircraft is directed up and over the terrain to a safer altitude. (f) Lowering the flaps to the landing position automatically switches the GPWS to Mode 2B. The static boundary for Mode 2B is the same as the Mode 2A boundary except the upper limit has been lowered to 789 ft. at a maximum closure rate of 3000 FPM. The lower part of the Mode 2B boundary is controlled as a function of radio altitude and altitude rate when flaps are in full landing configuration. (g) Mode 2B is also selected when the aircraft is performing an ILS approach and the glide slope deviation is less than +/- 2 dots. However, the warning envelope is slightly different from the flaps down case in that the lower boundary is controlled only as a function of radio altitude, having a constant lower cutoff of 30 ft. above ground level. When the flaps are selected to landing configuration in the ILS glide slope beam, the lower boundary is activated. (h) When the envelope boundary conditions for Mode 2B are violated, the GPWS legends come on, and the voice message is repeated until the boundary is exited. If the gear or the flaps are up, then the message will be TERRAIN TERRAIN followed by WHOOP WHOOP PULL UP if the condition persists. If both gear and flaps are in the landing configuration, the message will be TERRAIN.

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(3) Mode 3 - Insufficient climb performance after takeoff (Ref. Fig. 009, 010) (a) Mode 3 provides a warning for excessive altitude loss after takeoff. Mode 3 is based primarily on radio altitude, altitude (IR inertial altitude, internally computed inertial altitude, or barometric altitude), and altitude rate (IVS, internally computed inertial altitude rate, or barometric altitude rate). (b) Inertially compensated air data signals are used when possible. IVS is used when valid data is available and barometric altitude rate is used only when valid IVS is not available and the internal computed inertial data is not valid. The Mode 3 warning envelopes are inhibited close to the ground. (c) The descent required for a warning varies as a function of flight profile and time. Once a descent begins during the takeoff phase of flight, as determined by the polarity of the altitude rate signal and takeoff/approach mode logic, the GPWC will store the existing value of altitude. Subsequent samples of altitude, altitude rate, and radio altitude are examined for warning conditions. The original stored value of altitude indicating where the descent began is retained until the aircraft ascends above the stored altitude value. When the polarity of the altitude rate signal indicates ascent rather than descent, the warning is cut off to indicate recovery is being initiated. A subsequent return to descent prior to regaining the altitude lost enables the warning. The altitude loss required to resume the message and legend activation is based on the initially stored altitude value. In this manner, the possibility of stair stepping down without Mode 3 warning indication is eliminated. (d) Mode 3 is biased or desensitized under certain conditions. In the Mode 3 operation, as more radio altitude and time are accumulated after departure, the warning envelope is effectively moved to the right, allowing more altitude loss. This is accomplished using an integrated function of radio altitude to control the Mode 3 bias or washout. Greater radio altitude and increasing time will gradually desensitize the warning criteria. For example, at 400 ft. radio altitude, the altitude loss required for a warning increases at the rate of 0.4 feet per second. (e) A delay equivalent to 0.8 second is added to the warning output to prevent the possibility of nuisance warnings caused by static pressure disturbances during gear retraction.

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(4) Mode 4 - Unsafe terrain clearance (Ref. Fig. 010) (a) The mode 4 generates three types of voice warnings based on the radio altitude, computed airspeed, and aircraft configuration. The standard upper boundary is at 500 ft. radio altitude. If the aircraft penetrates this boundary with the landing gear still up, the voice message will be TOO LOW GEAR. Above 190 Kts airspeed, the upper boundary increases linearly with airspeed to a maximum of 1000 ft. radio altitude at 250 Kts or more. Penetrating this boundary produces a repetitive TOO LOW TERRAIN message. Other maximums are used at certain airports to minimize the nuisance warnings. The mode 4 maximum altitude is lowered from 1000 to 800 ft. of radio altitude when an overflight is detected. An overflight can be detected by sensing the sudden change in radio altitude. The 800 ft. limit is maintained for 60 seconds after an overflight to insure that a nuisance warning is not issued. (b) When the landing gear or flaps are lowered, the upper boundary decreases to 245 ft. To maintain the same airspeed expansion function up to 1000 ft. nominal at 250 Kts, the lower level corner is at 159 Kts. Penetration below 159 Kts results in TOO LOW GEAR messages with gear up or TOO LOW FLAPS message with gear down and flaps not in landing configuration, while above 159 Kts the message is TOO LOW TERRAIN. (c) The equation for the sloped portion of the warning curve is: H warn (ft.) = - 1083 ft. + 8.333 X Computed Airspeed (Kts) (5) Mode 5 - Descent below glide slope (Ref. Fig. 011) (a) The mode 5 provides two levels of warning when the aircraft flight path descends below the glide slope beam on front course ILS approaches. The upper limit of 1000 ft. nominal allows the capture of the beam before enabling this mode. Other upper limits are used at certain airports to increase the warning envelope. The deviation boundaries are shown in dots below the beam where one dot equals 0.0875 DDM. The first warning occurs whenever the aircraft is more than 1.3 dots below the beam. It is called a soft glide slope warning because the volume level of the GLIDE SLOPE warning is approximately one half (- 6 db) that of the other warnings.

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A second warning boundary occurs below 300 ft. radio altitude and below 2 dots deviation. It is called loud glide slope because the volume level is increased to that of the other warnings. (b) Both boundaries allow additional deviation below 150 ft. of radio altitude to allow for normal beam variations near the threshold. (c) The repetition rate of the GLIDE SLOPE messages also varies as a function of radio altitude and glide slope deviation. It is slow at 1000 ft. and 1.3 dots and speeds up as altitude is lowered or deviation is increased. Actual time between glide slope messages is controlled by the equation: Radio Alt (ft.) Time = ---------------------G/S Deviation (Dots)

X 0.0067

(d) The GLIDE SLOPE warning can be manually cancelled by the crew. This can be done any time below 1000 ft. nominal radio altitude. Cancel can be reset by ascending above 1000 ft. nominal, or descending below 30 ft. Cancel can also be reset by reselecting the ILS frequency in certain installations. (e) The change from constant deviation to a slope below 150 ft. radio altitude is shown along with the constant separation 0.7 dots between the two boundaries. A delay of approximately 0.8 seconds is inserted between the warning output and the enabling logic during a warning condition. The delay shall also turn off the warning output when two successive samples show a loss of the enabling logic. The repetition rate of the glide slope message is controlled by the radio altitude and the glide slope deviation as shown in the equation above. (f) The gear-down logic requirement for mode 5 is deleted at certain airports. (g) The glide-slope cancel latch will be set by a momentary cancel command that lasts for at least two successive processor cycles. Reset of the latch is accomplished by: 1 _

Climb above 1000 ft. radio altitude.

2 _

Descent below 30 ft. radio altitude.

3 _

Change of valid ILS select data.

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(h) The reset condition must last for at least two successive processor cycles. A reset condition will inhibit the set command. (i) The state of the cancel latch must be retained during loss of computer power. **ON A/C 001-004, 051-060, C. Envelope Modulation (1) Background During the past 20 years, experience with GPWS have shown that normal approaches to certain airports can be incompatible with the normal warning envelopes and signal filtering. A number of enhancements to the envelopes and filters have been developed during this time in an attempt to accommodate these few airports, without compromising the overall GPWS effectiveness for all the other normal airport approaches. However, there remain a limited number of cases which are still not satisfactory despite these efforts. All of the noticeable cases have been due to nuisance warnings for approaches and departures at particular airports. The majority of nuisance warnings involves mode 2 closure rate due to terrain under the approach path or rising terrain just before the runway threshold. Others involve mode 4 terrain clearance warnings during initial approach. A few mode 1 warnings are the results of steeper than normal approaches over terrain which slopes down to the runway at some airports. A different type of case is the inadequate warning protection during ILS approaches when the upper limit of mode 5 is 1000 ft. radio altitude. There are airports located at a significantly higher altitude than the surrounding terrain. In some instances this difference is over 1000 ft., thus requiring the aircraft to be below the runway elevation before a mode 5 warning is possible during most of the approach. Until recently there has been no reasonable way to accomodate these few special cases without compromising the GPWC at all other airports. What is needed is the ability to recognize when the aircraft is approaching one of these airports and then adjust the warning criteria to suit the particular approach. The availability of accurate, low drift, latitude and longitude information from the latest generation inertial navigation equipment now makes individual airport recognition possible. After recognizing the approach to or departure from one of these airports, it is also important to verify the aircraft is at a reasonable altitude before

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desensitizing any warning criteria. If the aircraft is already low, further warning reduction is not desirable. (2) Functional description - A reasonable altitude is verified in one of two ways. - for the ILS approaches, the glide slope deviation is used to verify a normal approach, - when the ILS information is not available, terrain and altitude matching is used to verify a normal approach. The following input data are used for airport recognition: - latitude position from the FMGC or the ADIRU - longitude position from the FMGC or the ADIRU - glide slope deviation from the ILS - localizer deviation from the ILS - aircraft magnetic track angle from the FMGC or the ADIRU - runway course from the ILS - corrected barometric altitude from the ADIRU - QNH or QFE mode of baro altitude correction via program pin. QNH mode is baro altitude correction to sea level. QFE mode is selected with a program pin for baro altitude correction to the airport field elevation. - radio altitude. Latitude and longitude data are continuously monitored for the airport locations. Additional data processing for envelope modulation is not required until the aircraft approaches one of the airports. Then the other data inputs are checked for a normal approach before any warning envelopes are modulated. The FMGC is the preferred source for latitude and longitude data because these data were corrected for the normal drift of the ADIRU basic latitude and longitude data. If the FMGC data are invalid, or missing, then the GPWC will automatically switch back to the ADIRU data. (3) Types of envelope modulation - There are currently four types of envelope modulation required for the airport approaches causing problems for the GPWC. - bias the mode 1 warning boundaries for SINK RATE and PULL UP to the right to allow greater altitude descent rate before a warning is generated. (Ref. Fig. 007) - lower the maximum upper limit for mode 2A and mode 2B. This limits the maximum radio altitude, or the minimum terrain clearance required to generate a warning. (Ref. Fig. 008) - lower the maximum upper limit for mode 4 to allow less minimum terrain clearance before a warning is generated. (Ref. Fig. 010)

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- expand the maximum mode 5 radio altitude level where a warning can begin. This will allow GLIDE SLOPE warnings for higher radio altitudes. The gear down requirement is also removed during warning expansion, to allow gear up warnings. (4) List of envelope modulation airports The following list represents the status of airports with Envelope Modulations. The majority of the identified areas require Mode 2A envelope modulations. (a) EUROPE ALICANTE SPAIN ILS RWY 11 GENEVA SWITZERLAND ILS RWY 05 NURNBERG GERMANY R.V. TO ILS OR NDB RWY 28 TENERIFE CANARY IS. ILS RWY 30 (b) NORTH AMERICA NORTH BAY ONTARIO I.A. TO VOR DME YYB ONTARIO CA VOR RWY 26R RENO NV LOC DME B/C-B SAN DIEGO CA LOC DME B/C RWY 27 (c) SOUTH AMERICA CUENCA EQUADOR ILS/DME RWY 23 QUITO EQUADOR DEP RWY 17/ILS RWY 35 (d) FAR EAST HONG KONG (A) B.C.C. IGS/NDB RWY 13 KAGOSHIMA JAPAN ILS RWY 34 SEOUL S. KOREA I.A. VOR DME RWY 32 (e) PACIFIC AGANA NAS (A) GUAM IS. ILS RWY 6L AGANA NAS (B+C) GUAM IS. ILS RWY 6L HIROSHIMA JAPAN I.A. NDB LOC RWY 4 TAIPEI TAIWAN ILS-1 RWY 10

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**ON A/C 001-049, 051-060, 101-104, Post SB

34-1147 For A/C 001-004,051-060,

C. Envelope Modulation (1) Background During the past 20 years, experience with GPWS have shown that normal approaches to certain airports can be incompatible with the normal warning envelopes and signal filtering. A number of enhancements to the envelopes and filters have been developed during this time in an attempt to accommodate these few airports, without compromising the overall GPWS effectiveness for all the other normal airport approaches. However, there remain a limited number of cases which are still not satisfactory despite these efforts. All of the noticeable cases have been due to nuisance warnings for approaches and departures at particular airports. The majority of nuisance warnings involves Mode 2 closure rate due to terrain under the approach path or rising terrain just before the runway threshold. Others involve Mode 4 terrain clearance warnings during initial approach. A few Mode 1 warnings are the results of steeper than normal approaches over terrain which slopes down to the runway at some airports. A different type of case is the inadequate warning protection during ILS approaches when the upper limit of Mode 5 is 1000 ft. radio altitude. There are airports located at a significantly higher altitude than the surrounding terrain. In some instances this difference is over 1000 ft., thus requiring the aircraft to be below the runway elevation before a Mode 5 warning is possible during most of the approach. Until recently there has been no reasonable way to accomodate these few special cases without compromising the GPWC at all other airports. What is needed is the ability to recognize when the aircraft is approaching one of these airports and then adjust the warning criteria to suit the particular approach. The availability of accurate, low drift, latitude and longitude information from the latest generation inertial navigation equipment now makes individual airport recognition possible. After recognizing the approach to or departure from one of these airports, it is also important to verify that the aircraft is at a reasonable altitude before desensitizing any warning criteria. If the aircraft is already low, further warning reduction is not desirable.

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(2) Functional description - A reasonable altitude is verified in one of two ways: - for the ILS approaches, the glide slope deviation is used to verify a normal approach, - when the ILS information is not available, terrain and altitude matching is used to verify a normal approach. The following input data are used for airport recognition: - latitude position from the FMGC or the ADIRU, - longitude position from the FMGC or the ADIRU, - glide slope deviation from the ILS portion of the MMR, - localizer deviation from the ILS portion of the MMR, - aircraft magnetic track angle from the FMGC or the ADIRU, - runway course from the ILS portion of the MMR, - corrected barometric altitude from the ADIRU, - QNH or QFE mode of baro altitude correction via program pin. QNH mode is the baro altitude correction to sea level. QFE mode is selected with a program pin for baro altitude correction to the airport field elevation. - radio altitude. Latitude and longitude data are continuously monitored for the airport locations. Additional data processing for envelope modulation is not required until the aircraft approaches one of the airports. Then the other data inputs are checked for a normal approach before any warning envelopes are modulated. The FMGC is the preferred source for latitude and longitude data because these data were corrected for the normal drift of the ADIRU basic latitude and longitude data. If the FMGC data are invalid, or missing, then the GPWC will automatically switch back to the ADIRU data. (3) Types of envelope modulation - There are currently four types of envelope modulation required for the airport approaches causing problems for the GPWC. - bias the Mode 1 warning boundaries for SINK RATE and PULL UP to the right to allow greater altitude descent rate before a warning is generated. (Ref. Fig. 007) - lower the maximum upper limit for Mode 2A and Mode 2B. This limits the maximum radio altitude, or the minimum terrain clearance required to generate a warning. (Ref. Fig. 008) - lower the maximum upper limit for Mode 4 to allow less minimum terrain clearance before a warning is generated. (Ref. Fig. 010) - expand the maximum Mode 5 radio altitude level where a warning can begin. This will allow GLIDE SLOPE warnings for higher radio

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altitudes. The gear down requirement is also removed during warning expansion, to allow gear up warnings. (4) List of envelope modulation airports The following list represents the status of airports with Envelope Modulations. The majority of the identified areas require Mode 2A envelope modulations. (a) EUROPE ALICANTE SPAIN ILS RWY 11 GENEVA SWITZERLAND ILS RWY 05 NURNBERG GERMANY R.V. TO ILS OR NDB RWY 28 TENERIFE CANARY IS. ILS RWY 30 (b) NORTH AMERICA NORTH BAY ONTARIO I.A. TO VOR DME YYB ONTARIO CA VOR RWY 26R RENO NV LOC DME B/C-B SAN DIEGO CA LOC DME B/C RWY 27 (c) SOUTH AMERICA CUENCA EQUADOR ILS/DME RWY 23 QUITO EQUADOR DEP RWY 17/ILS RWY 35 (d) FAR EAST HONG KONG (A) B.C.C. IGS/NDB RWY 13 KAGOSHIMA JAPAN ILS RWY 34 SEOUL S. KOREA I.A. VOR DME RWY 32 (e) PACIFIC AGANA NAS (A) GUAM IS. ILS RWY 6L AGANA NAS (B+C) GUAM IS. ILS RWY 6L HIROSHIMA JAPAN I.A. NDB LOC RWY 4 TAIPEI TAIWAN ILS-1 RWY 10 **ON A/C 001-049, 051-060, 101-104, D. Warning Generation and Inhibition (Ref. Fig. 012) Warning triggers from modes 1 thru 5 computations are applied to the voice warning circuits. The outputs from these are processed by an isolation transformer and audio amplifier to provide an 8-ohm impedance output at Captain and First Officer loud speakers. Should triggers from two or more modes be present, the highest priority trigger is accepted and the associated aural warning is produced as defined by the audio program discrete. Aural warnings and their priority rate are as follows :

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GPWC - Generation and Inhibition Figure 012   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 43   Config-2 Feb 01/07 R  CES

 

PRIORITY TRIGGER WARNING MODE 1 No warn 2 Pull-up WHOOP WHOOP, PULL UP 1, 2 3 Terrain TERRAIN 2 4 Too low TOO LOW 3 5 Too low terrain TOO LOW TERRAIN 4 6 Too low gear TOO LOW GEAR 4 7 Too low flaps TOO LOW FLAPS 4 8 N/A N/A N/A 9 Sink rate SINK RATE 1 10 Dont sink gear DONT SINK GEAR 3 11 Dont sink DONT SINK 3 12 Glide slope GLIDE SLOPE 5 The voice warning circuits also contain logic elements which ensure that: - only one message at a time is output. - higher priority messages interrupt lower priority messages. - a triggered message is completed even when warning condition ceases. - a 0.75 s pause exists between warning messages. The voice warning circuits are inhibited by the priority 1 input (no warn). The priority 1 input is present if the internally generated master valid signal is lost or the momentary audio suppress discrete is present. Should the master valid signal be recovered or the momentary audio suppress discrete be removed, the priority 1 input is cancelled and the previous warning will return (providing the associated warning envelope is still penetrated). Mode 5 GLIDE SLOPE warnings can only be cancelled by pressing the G/S MODE pushbutton switch on the overhead panel 21VU. E. GPWC Maintenance Output (Ref. Fig. 013) A maintenance output signal (label 270 octal) is provided by the ARINC 429 transmitter. The transmitter converts the microprocessor parallel data to standard serial data for the DMU of the AIDS. 7. ____ Test The GPWC interruptive self-test facility provides the following test modes: - airborne self-test - ground self-test - ground vocabulary test - status/history test.

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GPWC - Warning Mode and Maintenance Word Format Figure 013   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 45   Config-2 Feb 01/07 R  CES

 

A. Airborne Self-test (1) The airborne self-test is enabled when the following conditions are met: - radio altitude input is greater than 1000 ft. and valid and airspeed is greater than 90 Kts - the GPWS/G/S pushbutton switch has been pressed. (2) With no system faults present, the GPWC generates the following warning sequence: (a) A single soft GLIDE SLOPE aural warning is broadcast. (b) A single WHOOP WHOOP PULL UP aural warning is broadcast. B. Ground Self-Test (1) The ground self-test presents the same test sequence as the airborne test but also includes an internal check. The internal test is enabled by a radio altitude input indicating an altitude below 5 ft., and computed airspeed below 60 Kts. The test is initiated by pressing and holding the GPWS/G/S pushbutton switch for 0.5 seconds. NOTE : Holding the switch pressed either continuously or during the ____ PULL UP sequence of the ground test will initiate the vocabulary test. (2) Upon initiation of the test, providing there are no faults present, the sequence will start. Between the first and second sequence steps (soft GLIDE SLOPE and WHOOP WHOOP PULL UP broadcasts) an internal check is made of the following: - processor instruction set - program memory contents - voice memory contents. The internal clock must not exceed four seconds. R

**ON A/C 001-049, 051-060, 101-104,

R

Post SB

R R R R R R

34-1278 For A/C 001-049,051-060,101-104, The GPWC interruptive self-test facility provides the following test modes: - airborne self-test - ground self-test - ground vocabulary test - status/history test.

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R

A. Airborne Self-test

R R R R R

(1) The airborne self-test is enabled when the following conditions are met: - radio altitude input is greater than 1000 ft. and valid and airspeed is greater than 90 Kts - the PULL UP/GPWS pushbutton switch has been pressed.

R R

(2) With no system faults present, the GPWC generates the following warning sequence:

R

(a) A single soft GLIDE SLOPE aural warning is broadcast.

R

(b) A single WHOOP WHOOP PULL UP aural warning is broadcast.

R

B. Ground Self-Test

R R R R R

(1) The ground self-test presents the same test sequence as the airborne test but also includes an internal check. The internal test is enabled by a radio altitude input indicating an altitude below 5 ft., and computed airspeed below 60 Kts. The test is initiated by pressing and holding the PULL UP/GPWS pushbutton switch for 0.5 seconds.

R R R

NOTE : Holding the switch pressed either continuously or during the ____ PULL UP sequence of the ground test will initiate the vocabulary test.

R R R R R R R R R

(2) Upon initiation of the test, providing there are no faults present, the sequence will start. Between the first and second sequence steps (soft GLIDE SLOPE and WHOOP WHOOP PULL UP broadcasts) an internal check is made of the following: - processor instruction set - program memory contents - voice memory contents. The internal clock must not exceed four seconds. **ON A/C 001-049, 051-060, 101-104, C. Ground Vocabulary Test The ground vocabulary test is initiated if you press the GPWS/G/S pushbutton switch continuously or during the PULL UP portion of the ground test. NOTE : Fault to observe the above procedure will initiate the ground self ____ test.

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The test sequence is as follows: (1) Verify that the system status is correct for the ground test (radio altitude < 5 ft., computed airspeed below 60 kts). (2) Carry out the internal tests as detailed in the ground self-test. (3) Carry out the output sequence of the ground self-test of the GPWC. (4) Generate all aural warnings in this sequence: ORDER 1 2 3 4 5 6 7 8 9 10 11

TRIGGER Sink rate Pull up Terrain Pull up Dont sink Too low terrain Too low gear Too low flaps Too low terrain Glide slope Minimums

WARNING SINK RATE WHOOP WHOOP PULL UP TERRAIN WHOOP WHOOP PULL UP DONT SINK TOO LOW TERRAIN TOO LOW GEAR TOO LOW FLAPS TOO LOW TERRAIN GLIDE SLOPE MINIMUMS MINIMUMS

D. Status History Test (Ref. Fig. 014) (1) The test is controlled by the STATUS/HISTORY switch on the GPWC. The results are depicted on an 8-character BITE display also located on the face of the GPWC. The STATUS test is initiated if you momentarily select PRESENT STATUS with the STATUS/HISTORY switch. The HISTORY test is initiated if you momentarily select FLIGHT HISTORY with the STATUS/HISTORY switch. The STATUS test will depict the status of the latest flight information. The HISTORY test will depict the information related to the last ten flights. Both tests commence with ALL SEGMENTS TEST and terminate with END TEST messages. The computer faults are indicated by the message GPWC FAILED or FLT HIST INVALID. All other fault messages indicate an incorrect input condition. (2) The desired information is read from memory and converted to alphanumeric data for presentation on the BITE display. Messages are presented by means of this vocabulary:

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Status/History Test Readouts Figure 014   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 49   Config-2 Feb 01/07  CES

 

IN TEST END TEST GPWS OK GPWC RADIO ALTIMETR BARORATE AIRSPEED ALTITUDE GLIDE SLOPE CANCEL COURSE GEAR RUNWAY HEADING FLAPS

INVALID INACTIVE INHIBIT PREVIOUS TEN FLIGHTS OK FAILED AIR DATA ILS DATA IRS DATA EXTERNAL FLT HIST INPUT PROCESSR OUTPUT ASSEMBLY

LAMPTEST AUDIO SELECT FLIGHT-0 FLIGHT-1 FLIGHT-2 FLIGHT-3 FLIGHT-4 FLIGHT-5 FLIGHT-6 FLIGHT-7 FLIGHT-8 FLIGHT-9 CORRECTD LOCALIZR LATITUDE LONGITUD

(3) Examples of the STATUS test vocabulary are: GPWS OF

GEAR INVALID GPWC FAILED

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(4) Examples of the HISTORY test vocabulary are: RADIO ALTIMETR INACTIVE FLIGHT-1 FLAPS INVALID FLIGHT-8 -

BARORATE INVALID FLIGHT-2

ILS DATA INACTIVE FLIGHT-3 FLIGHT-4 PREVIOUS TEN FLIGHTS OK

(5) No aural warnings are broadcast during either test. (6) If the history test message you read is too long, you can stop the test. To do this, you must set the STATUS/HISTORY switch to PRESENT STATUS until the BITE display is blank. The display will then show CANCEL followed by END TEST. This operation will have no adverse effect on the data held in the flight history memory. (7) The sequences of the flight history test and those of the present status test will not activate the cockpit voice outputs. E. CFDS Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies faults related to the GPWS. The BITE of the GPWC is connected to the CFDIU. The BITE: - transmits permanently GPWS status and its identification message to the CFDIU - memorizes the faults which occurred during the last 63 flight segments - monitors data inputs from the various peripherals (FMGC, RA transceiver, ILS receiver, ADIRU, SFCC, LGCIU, ECAM control panel and CFDIU) - transmits to the CFDIU the result of the tests performed - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the menu mode. (a) Normal mode During the normal mode, the BITE monitors cyclically the status of the GPWS. It transmits its information to the CFDIU during the concerned flight.

  EFF : 001-049, 051-060, 101-104,  34-48-00 Page 51   Config-2 Feb 01/07  CES

 

In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 100 ms by an ARINC 429 message with label 356. (b) Menu mode The menu mode can only be activated on the ground. This mode enables communication between the CFDIU and the GPWC BITE by means of the MCDU. The GPWS menu mode is composed of: - LAST LEG REPORT - PREVIOUS LEGS REPORT - LRU IDENTIFICATION - GROUND SCANNING - TROUBLE SHOOTING DATA - CLASS 3 FAULTS - TEST - GROUND REPORT. (Ref. Fig. 015, 016, 017) F. Power-up Tests Initialization and Cockpit Repercussions (1) Conditions of power-up tests initialization - How long the computer must be de-energized: 1 s. - A/C configuration: - whatever the A/C configuration on ground (2) Progress of power-up tests - Duration: 20 s. - Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - none (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). - Tests pass: - none - Tests failed: - GPWS panel: FAULT legend of SYS P/BSW on - MASTER CAUT light on and single chime - ECAM warning: NAV GPWS FAULT - ECAM STATUS: GPWS INOP

  EFF : 001-049, 051-060, 101-104,  34-48-00 Page 52   Config-2 Feb 01/07  CES

 

Maintenance Test Procedure - Sub-Menu Function 1/3 Figure 015   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 53   Config-2 Feb 01/07  CES

 

Maintenance Test Procedure - Sub-Menu Function 2/3 Figure 016   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 54   Config-2 Feb 01/07  CES

 

Maintenance Test Procedure - Sub-Menu Function 3/3 Figure 017   EFF : 001-049, 051-060, 101-104,  34-48-00 Page 55   Config-2 Feb 01/07  CES

 

GROUND PROXIMITY WARNING SYSTEM (GPWS) - SERVICING __________________________________________________ TASK 34-48-00-610-001 Uploading of the Enhanced GPWC Database 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-48-00-740-002 52-41-00-410-002 34-48-00-991-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power BITE Test of the Enhanced GPWS Close the Avionics Compartment Doors after Access Fig. 301

3. __________ Job Set-up NOTE : Refer to the equipment manufacturer Service Bulletin related to the ____ version of the database that you upload. Subtask 34-48-00-861-055 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

  R EFF : ALL  34-48-00    CES

 

Page 301 Nov 01/09

Subtask 34-48-00-010-053 B. Get Access (1) Put the access platform in position at the access door 824 in zone 128. (2) Open the access door 824. Subtask 34-48-00-865-066 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU EIS/GPWS/115VAC 3WZ P07 4. Procedure _________ (Ref. Fig. 301/TASK 34-48-00-991-002) Subtask 34-48-00-970-050 A. Loading of the PCMCIA Card Software NOTE : Before you load the software make sure that the version of the ____ terrain data base is correct. (1) Make sure that the COMPUTER OK LED on the face of the Enhanced GPWC, is on. (2) Open the door on the face of the Enhanced GPWC. (3) Put the PCMCIA card into the PCMCIA card slot. (4) During software loading, the IN PROG LED stays on and the COMPUTER OK LED is off. (5) When the loading is completed, the XFER COMP LED comes on. (6) Remove the PCMCIA card from the Enhanced GPWC. (7) After approximately 15 seconds, the COMPUTER OK LED comes on to tell the operator that the loading of the PCMCIA card contents is completed.

  R EFF : ALL  34-48-00    CES

 

Page 302 Nov 01/09

Enhanced GPWC Face Figure 301/TASK 34-48-00-991-002   R EFF : ALL  34-48-00    CES

 

Page 303 Nov 01/09

(8) On the label on the front panel door of the Enhanced GPWC, write the number of the database that you loaded. (9) Close the door on the face of the Enhanced GPWC. Subtask 34-48-00-740-053 B. Do the BITE Test of the Enhanced GPWC (Ref. TASK 34-48-00-740-002). 5. Close-up ________ Subtask 34-48-00-410-053 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the access door 824 (Ref. TASK 52-41-00-410-002). (3) Remove the access platform(s). Subtask 34-48-00-862-054 B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

  R EFF : ALL  34-48-00    CES

 

Page 304 Nov 01/09

GROUND PROXIMITY WARNING SYSTEM (GPWS) - ADJUSTMENT/TEST ________________________________________________________ TASK 34-48-00-710-001-B Operational Test of the Enhanced GPWS Ground Self-Test Function WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Refer to the MPD TASK: 344800-01 Operational test of GPWS ground self-test function 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, 34-48-00-991-001 R R

**ON A/C 401-499, Post SB Post SB

R R

Post SB

R

34-48-00-991-001-D

Fig. 501

001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 501-509, 511-515, 34-1278 For A/C 001-049,051-099,101-105,151-199,201-219, 34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, 34-1412 For A/C 001-049,051-099,101-149,151-199,201-249,251-299, 301-399,401-499,501-509,511-515, Fig. 501A

  R EFF : ALL  34-48-00    CES

 

Page 501 Nov 01/09

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R R

**ON A/C 401-499, Post SB Post SB

001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 501-509, 511-526, 528-599, 34-1278 For A/C 001-049,051-099,101-105,151-199,201-219, 34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,

34-48-00-991-001-C

Fig. 501B

**ON A/C ALL 3. __________ Job Set-up Subtask 34-48-00-860-059 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector switch related to the ADIRU1 to NAV (Ref. TASK 34-10-00-860-002). (3) On the overhead control and indicating panel 21VU, on the GPWS section, make sure that the five GPWS pushbutton switches are released (legends off). (4) On the CAPT and F/O LIGHTING/LOUD SPEAKER control panels 301VU and 500VU, set the ND potentiometer to BRT. (5) On the FCU, on the CAPT and F/O EFIS control panels, set the mode selector switch to ARC. (6) On the FCU, on the CAPT and F/O EFIS control panels, set the scale selector switch to 160.

  EFF : ALL  34-48-00    CES

 

Page 502 Feb 01/10

Subtask 34-48-00-865-057 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU EIS/GPWS/115VAC 3WZ P07 121VU EIS/GPWS/28VDC 2WZ P06 4. Procedure _________ Subtask 34-48-00-860-080 A. Status (1) On the center pedestral, on one MCDU, get access to the SYSTEM REPORT/TEST NAV page (Ref. TASK 31-32-00-860-010). (a) Push the line key adjacent to the GPWC indication. (b) Push the line key adjacent to the CURRENT STATUS indication. 1 _

If the CPWC/CURRENT STATUS page shows: - AUDIO MENU: 0, do the para. related to the operational test of the enhanced GPWS ground self-test function with AUDIO MENU: 0 - AUDIO MENU: 1, do the para. related to the operational test of the enhanced GPWS ground self-test function with AUDIO MENU: 1

2 _

Record the AIRCRAFT TYPE (the AIRCRAFT TYPE can be 113 or 132).

  R EFF : ALL  34-48-00    CES

 

Page 503 Nov 01/09

**ON A/C 001-049, 051-099, 101-105, 151-199, 201-214, Subtask 34-48-00-710-066 B. Operational Test of Enhanced GPWS Ground Self-test Function with AUDIO MENU: O ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT (F/O) LIGHTING/LOUD SPEAKER control panel 301VU (500VU): - push the GPWS/G/S pushbutton switch and hold it for five seconds after the first aural warning.

On the panel 21VU: - the FAULT legend of the pushbutton switch comes - the FAULT legend of the pushbutton switch comes

GPWS/SYS on. GPWS/TERR on.

On the panels 301VU and 500VU: - the G/S legends come on. In the loudspeakers: - the GLIDESLOPE aural warning operates then stops. On the panels 301VU and 500VU: - the G/S legends go off. - the GPWS legends come on. In the loudspeakers: - the PULL UP aural warning operates then stops. - the TERRAIN TERRAIN PULL UP aural warning operates then stops. On the panels 301VU and 500VU: - the GPWS legends go off. On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches come on.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 201-214,  R  CES

 

Page 504 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT (F/O) NDs: - the TEST PATTERN is shown and the amber TERR TST indication comes into view. (Ref. Fig. 501/TASK 34-48-00-991-001) The above warnings operate, then all these warnings, one after the other: - SINK RATE - PULL UP - TERRAIN - PULL UP - DONT SINK - DONT SINK - TOO LOW TERRAIN - TOO LOW GEAR - TOO LOW FLAPS - TOO LOW TERRAIN - GLIDE SLOPE - MINIMUMS MINIMUMS (with P/N 102-102 only) - TOO LOW TERRAIN - CAUTION TERRAIN - CAUTION TERRAIN - TERRAIN TERRAIN PULL UP On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches go off. On the CAPT (F/O) NDs: - the amber TERR TST indication goes out of view. On the panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch goes off. - the FAULT legend of the GPWS/TERR pushbutton switch goes off. On the CAPT (F/O) NDs: - the TEST PATTERN goes out of view.

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 201-214,   CES

 

Page 505 May 01/09

Enhanced GPWS - Test Pattern Figure 501/TASK 34-48-00-991-001   R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 201-233, 236-238, 301-304,   CES

 

Page 506 May 01/09

Subtask 34-48-00-710-067 C. Operational Test of Enhanced GPWS Ground Self-test Function with Audio Menu: 1 ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT (F/O) LIGHTING/LOUD SPEAKER control panel 301VU (500VU): - push the GPWS/G/S pushbutton switch and hold it for five seconds after the first aural warning.

On the panel 21VU: - the FAULT legend of the pushbutton switch comes - the FAULT legend of the pushbutton switch comes

GPWS/SYS on. GPWS/TERR on.

On the panels 301VU and 500VU: - the G/S legends come on. In the loudspeakers: - the GLIDESLOPE aural warning operates then stops. On the panels 301VU and 500VU: - the G/S legends go off. - the GPWS legends come on. In the loudspeakers: - the PULL UP aural warning operates then stops. - the TERRAIN AHEAD PULL UP aural warning operates then stops. On the panels 301VU and 500VU: - the GPWS legends go off. On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches come on. On the CAPT (F/O) NDs:

  EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 201-214,  R  CES

 

Page 507 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the TEST PATTERN is shown and the amber TERR TST indication comes into view. (Ref. Fig. 501/TASK 34-48-00-991-001) The above warnings operate, then all these warnings, one after the other: - SINK RATE - PULL UP - TERRAIN - PULL UP - DONT SINK - DONT SINK - TOO LOW TERRAIN - TOO LOW GEAR - TOO LOW FLAPS - TOO LOW TERRAIN - GLIDE SLOPE - MINIMUMS MINIMUMS (with P/N 102-102 only) - TOO LOW TERRAIN - TERRAIN AHEAD - TERRAIN AHEAD - TERRAIN AHEAD PULL UP On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches go off. On the CAPT (F/O) NDs: - the amber TERR TST indication goes our of view. On the panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch goes off. - the FAULT legend of the GPWS/TERR pushbutton switch goes off. On the CAPT (F/O) NDs: - the TEST PATTERN goes out of view.

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-48-00 201-214,   CES

 

Page 508 May 01/09

**ON A/C 106-149, 215-233, 236-238, 301-304, Subtask 34-48-00-710-066-A B. Operational Test of Enhanced GPWS Ground Self-test Function with AUDIO MENU: O ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT (F/O) LIGHTING/LOUD SPEAKER control panel 301VU (500VU): - push the PULL UP/GPWS pushbutton switch and hold it for five seconds after the first aural warning.

On the panel 21VU: - the FAULT legend of the pushbutton switch comes - the FAULT legend of the pushbutton switch comes

GPWS/SYS on. GPWS/TERR on.

On the panels 301VU and 500VU: - the GPWS legends come on. In the loudspeakers: - the GLIDESLOPE aural warning operates then stops. On the panels 301VU and 500VU: - the GPWS legends go off. - the PULL UP legends come on. In the loudspeakers: - the PULL UP aural warning operates then stops. - the TERRAIN TERRAIN PULL UP aural warning operates then stops. On the panels 301VU and 500VU: - the PULL UP legends go off - the GPWS legends come on then go off (if the AIRCRAFT TYPE is 132).

R R R

On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU:

  EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00    CES

 

Page 509 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the ON legends of the TERR ON ND pushbutton switches come on. On the CAPT (F/O) NDs: - the TEST PATTERN is shown and the amberTERR TST indication comes into view. (Ref. Fig. 501/TASK 34-48-00-991-001) The above warnings operate, then all these warnings, one after the other: - SINK RATE - PULL UP - TERRAIN - PULL UP - DONT SINK - DONT SINK - TOO LOW TERRAIN - TOO LOW GEAR - TOO LOW FLAPS - TOO LOW TERRAIN - GLIDE SLOPE - TOO LOW TERRAIN - CAUTION TERRAIN - CAUTION TERRAIN - TERRAIN TERRAIN PULL UP On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches go off. On the CAPT (F/O) NDs: - the amber TERR TST indication goes out of view. On the panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch goes off. - the FAULT legend of the GPWS/TERR pushbutton switch goes off. On the CAPT (F/O) NDs:

  EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00   R  CES

 

Page 510 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the TEST PATTERN goes out of view. Subtask 34-48-00-710-067-A C. Operational Test of Enhanced GPWS Ground Self-test Function with AUDIO MENU: 1 ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT (F/O) LIGHTING/LOUD SPEAKER control panel 301VU (500VU): - push the PULL UP/GPWS pushbutton switch and hold it for five seconds after the first aural warning.

On the panel 21VU: - the FAULT legend of the pushbutton switch comes - the FAULT legend of the pushbutton switch comes

GPWS/SYS on. GPWS/TERR on.

On the panels 301VU and 500VU: - the GPWS legends come on. In the loudspeakers: - the GLIDESLOPE aural warning operates then stops. On the panels 301VU and 500VU: - the GPWS legends go off. - the PULL UP legends come on. In the loudspeakers: - the PULL UP aural warning operates then stops. - the TERRAIN AHEAD PULL UP aural warning operates then stops. On the panels 301VU and 500VU: - the PULL UP legends go off - the GPWS legends come on then go off (if the AIRCRAFT TYPE is 132).

R R R

  EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00    CES

 

Page 511 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches come on. On the CAPT (F/O) NDs: - the TEST PATTERN is shown and the amber TERR TST indication comes into view. (Ref. Fig. 501/TASK 34-48-00-991-001) The above warnings operate, then all these warnings, one after the other: - SINK RATE - PULL UP - TERRAIN - PULL UP - DONT SINK - DONT SINK - TOO LOW TERRAIN - TOO LOW GEAR - TOO LOW FLAPS - TOO LOW TERRAIN - GLIDE SLOPE - TOO LOW TERRAIN - TERRAIN AHEAD - TERRAIN AHEAD - TERRAIN AHEAD PULL UP On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches go off. On the CAPT (F/O) NDs: - the amber TERR TST indication goes out of view. On the panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch goes off.

  EFF : 106-149, 215-233, 236-238, 301-304,  34-48-00   R  CES

 

Page 512 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the FAULT legend of the GPWS/TERR pushbutton switch goes off. On the CAPT (F/O) NDs: - the TEST PATTERN goes out of view. R R

**ON A/C 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-48-00-710-066-D B. Operational Test of the Enhanced GPWS Ground Self-Test Function with AUDIO MENU: O ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT (F/O) LIGHTING/LOUD SPEAKER control panel 301VU (500VU): - push the PULL UP/GPWS pushbutton switch and hold it for five seconds after the first aural warning.

On the panel 21VU: - the FAULT legend of the pushbutton switch comes - the FAULT legend of the pushbutton switch comes

GPWS/SYS on. GPWS/TERR on.

On the panels 301VU and 500VU: - the GPWS legends come on. In the loudspeakers: - the GLIDESLOPE aural warning operates then stops. On the panels 301VU and 500VU: - the GPWS legends go off. - the PULL UP legends come on. In the loudspeakers: - the PULL UP aural warning operates then stops. - the TERRAIN TERRAIN PULL UP aural warning operates then stops.

  R EFF : 106-149, 215-249, 251-299, 301-399,  34-48-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 513 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the panels 301VU and 500VU: - the PULL UP legends go off - the GPWS legends come on then go off (if the AIRCRAFT TYPE is 132). On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches come on. On the CAPT (F/O) ND: - the test pattern is shown. On the test pattern - the amber TERR TST indication comes into view - the Peaks Elevation numbers come into view for five seconds as follows: * XXX (amber) * XXX (amber) and then * 290 (red) high altitude * -13 (green) low altitude - the Terrain Database (TDB) number comes into view. **ON A/C 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-515, Post SB

34-1412 For A/C 234-235,239-249,251-299,305-399,401-499,501-509, 511-515, (Ref. Fig. 501A/TASK 34-48-00-991001-D)

R R

**ON A/C 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 501B/TASK 34-48-00-991001-C) Then all these warnings operate, one after the other: - SINK RATE

  R EFF : 234-235, 239-249, 251-299, 305-399,  34-48-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 514 Feb 01/10

Enhanced GPWS - Test Pattern Figure 501A/TASK 34-48-00-991-001-D

R

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-515, CES

 

Page 515 Nov 01/09

Enhanced GPWS - Test Pattern Figure 501B/TASK 34-48-00-991-001-C

R

  R EFF : ALL  34-48-00    CES

 

Page 516 Nov 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- PULL UP - TERRAIN - PULL UP - DONT SINK - DONT SINK - TOO LOW TERRAIN - TOO LOW GEAR - TOO LOW FLAPS - TOO LOW TERRAIN - GLIDE SLOPE - TOO LOW TERRAIN - CAUTION TERRAIN - CAUTION TERRAIN - TERRAIN TERRAIN PULL UP - CAUTION OBSTACLE - CAUTION OBSTACLE - OBSTACLE OBSTACLE PULL UP On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches go off. On the panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch goes off. - the FAULT legend of the GPWS/TERR pushbutton switch goes off. On the CAPT (F/O) NDs: - the test pattern goes out of view.

  R EFF : 234-235, 239-249, 251-299, 305-399,  34-48-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 517 Feb 01/10

Subtask 34-48-00-710-067-D C. Operational Test of the Enhanced GPWS Ground Self-Test Function with AUDIO MENU: 1 ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT (F/O) LIGHTING/LOUD SPEAKER control panel 301VU (500VU): - push the PULL UP/GPWS pushbutton switch and hold it for five seconds after the first aural warning.

On the panel 21VU: - the FAULT legend of the pushbutton switch comes - the FAULT legend of the pushbutton switch comes

GPWS/SYS on. GPWS/TERR on.

On the panels 301VU and 500VU: - the GPWS legends come on. In the loudspeakers: - the GLIDESLOPE aural warning operates then stops. On the panels 301VU and 500VU: - the GPWS legends go off. - the PULL UP legends come on. In the loudspeakers: - the PULL UP aural warning operates then stops. - the TERRAIN AHEAD PULL UP aural warning operates then stops. On the panels 301VU and 500VU: - the PULL UP legends go off - the GPWS legends come on then go off (if the AIRCRAFT TYPE is 132). On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches come on. On the CAPT (F/O) ND:

  R EFF : 234-235, 239-249, 251-299, 305-399,  34-48-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 518 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the test pattern is shown. On the test pattern - the amber TERR TST indication comes into view - the Peaks Elevation numbers come into view for five seconds as follows: * XXX (amber) * XXX (amber) and then * 290 (red) high altitude * -13 (green) low altitude - the Terrain Database (TDB) number comes into view. **ON A/C 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-515, Post SB

34-1412 For A/C 234-235,239-249,251-299,305-399,401-499,501-509, 511-515, (Ref. Fig. 501A/TASK 34-48-00-991001-D)

R R

**ON A/C 234-235, 239-249, 251-299, 305-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 501B/TASK 34-48-00-991001-C) Then all these warnings operate, one after the other: - SINK RATE - PULL UP - TERRAIN - PULL UP - DONT SINK - DONT SINK - TOO LOW TERRAIN - TOO LOW GEAR - TOO LOW FLAPS - TOO LOW TERRAIN - GLIDE SLOPE - TOO LOW TERRAIN - TERRAIN AHEAD

  R EFF : 234-235, 239-249, 251-299, 305-399,  34-48-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 519 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- TERRAIN AHEAD - TERRAIN AHEAD PULL UP - OBSTACLE AHEAD - OBSTACLE AHEAD - OBSTACLE AHEAD PULL UP On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches go off. On the panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch goes off. - the FAULT legend of the GPWS/TERR pushbutton switch goes off. On the CAPT (F/O) NDs: - the test pattern goes out of view. **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, Post SB Post SB

34-1278 For A/C 001-049,051-099,101-105,151-199,201-219, 34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304,

Subtask 34-48-00-710-066-E B. Operational Test of the Enhanced GPWS Ground Self-Test Function with AUDIO MENU: O ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT (F/O) LIGHTING/LOUD SPEAKER control panel 301VU (500VU): - push the PULL UP/GPWS pushbutton switch and hold it for five seconds after the first aural warning.

On the panel 21VU: - the FAULT legend of the pushbutton switch comes - the FAULT legend of the pushbutton switch comes

GPWS/SYS on. GPWS/TERR on.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 520 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the panels 301VU and 500VU: - the GPWS legends come on. In the loudspeakers: - the GLIDESLOPE aural warning operates then stops. On the panels 301VU and 500VU: - the GPWS legends go off. - the PULL UP legends come on. In the loudspeakers: - the PULL UP aural warning operates then stops. - the TERRAIN TERRAIN PULL UP aural warning operates then stops. On the panels 301VU and 500VU: - the PULL UP legends go off - the GPWS legends come on then go off (if the AIRCRAFT TYPE is 132). On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches come on. On the CAPT (F/O) ND: - the test pattern is shown. On the test pattern - the amber TERR TST indication comes into view - the Terrain Database (TDB) number comes into view.

  EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 201-233, 236-238, 301-304,  R  CES

 

Page 521 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, Post SB Post SB Post SB

34-1278 For A/C 001-049,051-099,101-105,151-199,201-219, 34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, 34-1412 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, (Ref. Fig. 501A/TASK 34-48-00-991001-D)

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, Post SB Post SB

34-1278 For A/C 001-049,051-099,101-105,151-199,201-219, 34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, (Ref. Fig. 501B/TASK 34-48-00-991001-C) Then all these warnings operate, one after the other: - SINK RATE - PULL UP - TERRAIN - PULL UP - DONT SINK - DONT SINK - TOO LOW TERRAIN - TOO LOW GEAR - TOO LOW FLAPS - TOO LOW TERRAIN - GLIDE SLOPE - TOO LOW TERRAIN - CAUTION TERRAIN - CAUTION TERRAIN - TERRAIN TERRAIN PULL UP - CAUTION OBSTACLE - CAUTION OBSTACLE - OBSTACLE OBSTACLE PULL UP On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU:

  EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 201-233, 236-238, 301-304,  R  CES

 

Page 522 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the ON legends of the TERR ON ND pushbutton switches go off. On the panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch goes off. - the FAULT legend of the GPWS/TERR pushbutton switch goes off. On the CAPT (F/O) NDs: - the test pattern goes out of view. Subtask 34-48-00-710-067-E C. Operational Test of the Enhanced GPWS Ground Self-Test Function with AUDIO MENU: 1 ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the CAPT (F/O) LIGHTING/LOUD SPEAKER control panel 301VU (500VU): - push the PULL UP/GPWS pushbutton switch and hold it for five seconds after the first aural warning.

On the panel 21VU: - the FAULT legend of the pushbutton switch comes - the FAULT legend of the pushbutton switch comes

GPWS/SYS on. GPWS/TERR on.

On the panels 301VU and 500VU: - the GPWS legends come on. In the loudspeakers: - the GLIDESLOPE aural warning operates then stops. On the panels 301VU and 500VU: - the GPWS legends go off. - the PULL UP legends come on. In the loudspeakers: - the PULL UP aural warning operates then stops.

  EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 201-233, 236-238, 301-304,  R  CES

 

Page 523 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the TERRAIN AHEAD PULL UP aural warning operates then stops. On the panels 301VU and 500VU: - the PULL UP legends go off - the GPWS legends come on then go off (if the AIRCRAFT TYPE is 132). On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches come on. On the CAPT (F/O) ND: - the test pattern is shown. On the test pattern - the amber TERR TST indication comes into view - the Terrain Database (TDB) number comes into view. **ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, Post SB Post SB Post SB

34-1278 For A/C 001-049,051-099,101-105,151-199,201-219, 34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, 34-1412 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, (Ref. Fig. 501A/TASK 34-48-00-991001-D)

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-233, 236-238, 301-304, Post SB Post SB

34-1278 For A/C 001-049,051-099,101-105,151-199,201-219, 34-1345 For A/C 001-049,051-099,101-149,151-199,201-233,236-238, 301-304, (Ref. Fig. 501B/TASK 34-48-00-991001-C)

  EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 201-233, 236-238, 301-304,  R  CES

 

Page 524 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------Then all these warnings operate, one after the other: - SINK RATE - PULL UP - TERRAIN - PULL UP - DONT SINK - DONT SINK - TOO LOW TERRAIN - TOO LOW GEAR - TOO LOW FLAPS - TOO LOW TERRAIN - GLIDE SLOPE - TOO LOW TERRAIN - TERRAIN AHEAD - TERRAIN AHEAD - TERRAIN AHEAD PULL UP - OBSTACLE AHEAD - OBSTACLE AHEAD - OBSTACLE AHEAD PULL UP On the LANDING GEAR control and indicating panel 402VU and on the TERR ON ND panel 403VU: - the ON legends of the TERR ON ND pushbutton switches go off. On the panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch goes off. - the FAULT legend of the GPWS/TERR pushbutton switch goes off. On the CAPT (F/O) NDs: - the test pattern goes out of view.

  EFF : 001-049, 051-099, 101-149, 151-199,  34-48-00 201-233, 236-238, 301-304,  R  CES

 

Page 525 Feb 01/10

**ON A/C ALL 5. Close-up ________ Subtask 34-48-00-860-060 A. Put the aircraft back to its initial configuration. (1) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector switch related to the ADIRU1 to OFF. (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (3) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-48-00   R  CES

 

Page 526 Feb 01/10

TASK 34-48-00-710-002-B Operational Test of the Enhanced GPWS with Stall Warning Test and Activation of the GPWS/SYS Pushbutton Switch and EMER CANC Key WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure

3. __________ Job Set-up Subtask 34-48-00-860-061 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) On the overhead control and indicating panel 21VU, on the GPWS section, make sure that the five GPWS pushbutton switches are released (legends off). (3) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010).

  R EFF : ALL  34-48-00    CES

 

Page 527 Nov 01/09

(4) On the overhead panel, on the the ADIRS CDU, set the OFF/NAV/ATT selector switch related to the ADIRU1 to NAV (Ref. TASK 34-10-00-860002). **ON A/C ALL Post SB

34-1249 For A/C 001-049,052-052,058-058,101-104,

Subtask 34-48-00-865-058 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU FWS/FWC1/SPLY 3WW F01 121VU EIS/GPWS/115VAC 3WZ P07 121VU EIS/GPWS/28VDC 2WZ P06 121VU EIS/FWC2/SPLY 2WW Q07 **ON A/C ALL 4. Procedure _________ R R

**ON A/C 001-049, 051-061, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-48-00-710-057 A. Operational Test of the Enhanced GPWS with Stall Warning Test and Activation of the GPWS/SYS Pushbutton Switch and EMER CANC Key ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU, on the NAV page: - push the line key adjacent to the ADR1 indication.

On the MCDU: - the ADIRS ADR1 menu page comes into view.

- push the line key adjacent to the OUTPUT TESTS indication.

- the OUTPUT TESTS page comes into view.

- push the line key adjacent to

- these indications come into view:

  EFF : ALL  34-48-00    CES

 

Page 528 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------the AOA SENSOR TEST indication. AOA SENSOR COMMANDED TO FIXED POSITION CHECK STALL WARNING. On the panel 21VU: - the FAULT legend of the GPWS/SYS and GPWS/TERR pushbutton switches comes on after a time between 4 and 60 seconds. On the CAPT and F/O glareshield panels 130VU and 131VU: - the MASTER WARN lights flash. In the loudspeakers: - you can hear the cricket aural warning and the stall voice. - push the line key adjacent to the YES indication.

On the MCDU: - the TEST OK indication comes into view. On the panel 21VU: - the FAULT legend of the GPWS/SYS and GPWS/TERR pusbutton switches goes off. On the CAPT and F/O glareshield panels 130VU and 131VU: - the MASTER WARN lights go off. In the loudspeakers: - the aural warnings stop.

On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. 2. On the center pedestal, on the ECAM control panel: - push and hold the EMER CANC

On the panel 21VU:

  R EFF : 001-049, 051-061, 101-149, 151-199,  34-48-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 529 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------key. - the FAULT legend of the GPWS/SYS pushbutton switch comes on after approximately 35 seconds. 3. On the panel 21VU: - push the GPWS/SYS pushbutton switch - release the GPWS/SYS pushbutton switch.

- the FAULT legend goes off. - the OFF legend comes on. - the FAULT legend comes on. - the OFF legend goes off.

4. On the center pedestal, on the ECAM control panel: - release the EMER CANC key.

On the overhead panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch goes off.

5. On the overhead circuit breaker panel 49VU: - open the circuit breaker 3WW. On the rear circuit breaker panel 121VU: - open the circuit breaker 2WW. 6. Close the circuit breakers 2WW and 3WW.

  R EFF : 001-049, 051-061, 101-149, 151-199,  34-48-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 530 Feb 01/10

R

**ON A/C 001-049, 062-099, 101-105, 151-199, 201-203, Post SB

34-1249 For A/C 001-049,101-105,151-199,201-203,

Subtask 34-48-00-710-057-A A. Operational Test of the Enhanced GPWS with Stall Warning Test and Activation of the GPWS/SYS Pushbutton Switch and EMER CANC Key ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU, on the NAV page: - push the line key adjacent to the ADR1 indication.

On the MCDU: - the ADIRS ADR1 1/2 menu page comes into view.

- push the NEXT PAGE function key.

- the ADIRS ADR1 2/2 menu page comes into view.

- push the line key adjacent to the AOA SENSOR TEST indication.

- these indications come into view: AOA SENSOR COMMANDED TO FIXED POSITION CHECK STALL WARNING.

- push the line key adjacent to the TEST START indication.

On the panel 21VU: - the FAULT legend of the GPWS/SYS and GPWS/TERR pushbutton switches comes on after a time between 4 and 60 seconds. On the CAPT and F/O glareshield panels 130VU and 131VU: - the MASTER WARN lights flash. In the loudspeakers: - you can hear the cricket aural warning and the stall voice.

- push the line key adjacent to the RETURN indication.

On the panel 21VU: - the FAULT legend of the GPWS/SYS and GPWS/TERR pusbutton switches goes off. On the CAPT and F/O glareshield panels 130VU and 131VU:

  R EFF : 001-049, 062-099, 101-105, 151-199,  34-48-00 201-203,   CES

 

Page 531 Nov 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the MASTER WARN lights go off. In the loudspeakers: - the aural warnings stop. 2. On the center pedestal, on the ECAM control panel: - push and hold the EMER CANC key.

3. On the panel 21VU: - push the GPWS/SYS pushbutton switch - release the GPWS/SYS pushbutton switch.

On the panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch comes on after approximately 35 seconds. - the FAULT legend goes off. - the OFF legend comes on. - the FAULT legend comes on. - the OFF legend goes off.

4. On the center pedestal, on the ECAM control panel: - release the EMER CANC key.

On the overhead panel 21VU: - the FAULT legend of the GPWS/SYS pushbutton switch goes off.

5. On the overhead circuit breaker panel 49VU: - open the circuit breaker 3WW. On the rear circuit breaker panel 121VU: - open the circuit breaker 2WW. 6. Close the circuit breakers 2WW and 3WW.

  R EFF : 001-049, 062-099, 101-105, 151-199,  34-48-00 201-203,   CES

 

Page 532 Nov 01/09

R

**ON A/C ALL 5. Close-up ________ Subtask 34-48-00-860-062 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the MCDU, push the line key adjacent to the RETURN indication until the MCDU MENU page comes into view. (2) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector switch related to the ADIRU1 to OFF. (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Make sure that the work area is clean and clear of tool(s) and other items.

  R EFF : ALL  34-48-00    CES

 

Page 533 Nov 01/09

TASK 34-48-00-740-002-B BITE Test of the Enhanced GPWS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-48-00-860-063 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) On the overhead control and indicating panel 21VU, on the GPWS section, make sure that the five GPWS pushbutton switches are released (legends off). (3) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page then push the NEXT PAGE function key until the GPWC indication comes into view. (Ref. TASK 31-32-00-860-010). (4) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector switch related to the ADIRU1 to NAV (Ref. TASK 34-10-00-860-002).

  R EFF : ALL  34-48-00    CES

 

Page 534 Nov 01/09

R R

(5) On the FCU, on the CAPT and F/O EFIS control panels, set the mode selector switch to ARC.

R R

(6) On the FCU, on the CAPT and F/O EFIS control panels, set the scale selector switch to 160. Subtask 34-48-00-865-059 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU EIS/GPWS/115VAC 3WZ P07 121VU EIS/GPWS/28VDC 2WZ P06 4. Procedure _________ Subtask 34-48-00-740-051-A A. BITE Test of the Enhanced GPWC NOTE : The actions and the results of this procedure occur on the MCDU ____ used. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the MCDU, on the NAV page:

On the MCDU:

- push the line key adjacent to the GPWC indication.

- the GPWC page comes into view.

- push the line key adjacent to the TEST indication.

- the subsequent GPWC TEST pages with instructions come into view.

- push the line key adjacent to the START TEST indication,

- the TEST IN PROGRESS 20S indication comes into VIEW. - after 20s obey the instructions that are shown on the subsequent pages until the TEST OK indication comes into view.

  R EFF : ALL  34-48-00    CES

 

Page 535 Nov 01/09

5. Close-up ________ Subtask 34-48-00-860-064 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the MCDU, push the line key adjacent to the RETURN indication until the MCDU MENU page comes into view. (2) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector switch related to the ADIRU1 to OFF (Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Make sure that the work area is clean and clear of tool(s) and other items.

  R EFF : ALL  34-48-00    CES

 

Page 536 Nov 01/09

COMPUTER - GROUND PROXIMITY WARNING (GPWC) (1WZ) - REMOVAL/INSTALLATION _______________________________________________________________________ TASK 34-48-34-000-001 Removal of the GPWC (1WZ) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-48-34-991-001

Fig. 401

3. __________ Job Set-up Subtask 34-48-34-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU EIS/GPWS/115VAC 3WZ P07 121VU EIS/GPWS/28VDC 2WZ P06

  R EFF : ALL  34-48-34    CES

 

Page 401 Nov 01/09

Subtask 34-48-34-010-050 B. Get Access (1) Put the access platform in position at the access door 824 in zone 128. (2) Open the access door 824. 4. Procedure _________ (Ref. Fig. 401/TASK 34-48-34-991-001) Subtask 34-48-34-020-050 A. Removal of the GPWC (1) Loosen the nut (4). (2) Lower the nut (4). (3) Pull the GPWC (1) on its rack (3) to disconnect the electrical connectors (2). (4) Remove the GPWC (1) from its rack (3). (5) Put blanking caps on the disconnected electrical connectors (2).

  R EFF : ALL  34-48-34    CES

 

Page 402 Nov 01/09

GPWC Figure 401/TASK 34-48-34-991-001   R EFF : ALL  34-48-34    CES

 

Page 403 Nov 01/09

TASK 34-48-34-400-001 Installation of the GPWC (1WZ) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------31-32-00-860-001 34-48-00-610-001 34-48-00-710-001 52-41-00-410-002 34-48-34-991-001

Procedure to Get Access to the SYSTEM REPORT/TEST Menu Page Uploading of the Enhanced GPWC Database Operational Test of the Enhanced GPWS Ground Self-Test Function Close the Avionics Compartment Doors after Access Fig. 401

3. __________ Job Set-up Subtask 34-48-34-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at the access door 824 in zone 128. (2) Make sure that the access door 824 is open.

  R EFF : ALL  34-48-34    CES

 

Page 404 Nov 01/09

Subtask 34-48-34-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------121VU EIS/GPWS/115VAC 3WZ P07 121VU EIS/GPWS/28VDC 2WZ P06 4. Procedure _________ (Ref. Fig. 401/TASK 34-48-34-991-001) Subtask 34-48-34-420-050 A. Installation of the GPWC (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (2). (4) Make sure that the electrical connectors (2) are clean and in the correct condition. (5) Install the GPWC (1) on its rack (3). (6) Push the GPWC (1) on its rack (3) to connect the electrical connectors (2). (7) Engage the nut (4) on the lug (5) and tighten. Subtask 34-48-34-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 3WZ, 2WZ

  R EFF : ALL  34-48-34    CES

 

Page 405 Nov 01/09

Subtask 34-48-34-710-050-A C. Do a check of the version of the terrain database loaded in the Enhanced GPWC, on the MCDU, on the LRU IDENTIFICATION page (access from the SYSTEM REPORT/TEST NAV: RADIO NAV page 3/3 (Ref. TASK 31-32-00-860-001)). (1) Make sure that the version of the terrain database loaded in the Enhanced GPWC is the latest available (Refer to SIL 34-080). (2) Do the operational test of the Enhanced GPWS (Ref. TASK 34-48-00-710001). Subtask 34-48-34-610-050 D. If the Enhanced GPWS has not the last updated database, do the loading of the Enhanced GPWC Data Base (Ref. TASK 34-48-00-610-001) at the next maintenance opportunity. 5. Close-up ________ Subtask 34-48-34-860-051 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 34-48-34-410-050 B. Close Access (1) Close the access door 824 (Ref. TASK 52-41-00-410-002). (2) Remove the access platform(s).

  R EFF : ALL  34-48-34    CES

 

Page 406 Nov 01/09

DME - DESCRIPTION AND OPERATION _______________________________

R

1. _______ General The Distance Measuring Equipment (DME) is a radio aid to medium range navigation which provides the crew with : - a digital readout of the slant range distance of the aircraft from a selected ground station - audio signals which identify the selected ground station. The DME uses the frequency band from 962 MHz to 1213 MHz for reception and transmission. 2. Component __________________ Location (Ref. Fig. 001) ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2SD1 INTRG-DME, 1 81VU 127 824 34-51-33 2SD2 INTRG-DME, 2 82VU 128 824 34-51-33 3SD1 ANTENNA-DME, 1 121 NONE 34-51-11 3SD2 ANTENNA-DME, 2 NONE 127 NONE 34-51-11 3. __________________ System Description **ON A/C 001-049, 101-105, 151-199, A. Principle - The principle of the DME navigation is based on the measurement of the transmission time. Paired interrogation pulses go from an onboard interrogator to a selected ground station. After 50 microseconds, the station transmits the reply pulses to the aircraft. - The measurement of time between transmitting the interrogation pulses and receiving the reply pulses is a function of the slant range distance of the aircraft to the ground station. The measurement value is converted into nautical miles and shown to the crew. - The interrogation frequencies vary from 1025 to 1150 MHz. The reply frequencies vary from 962 to 1213 MHz. - Furthermore, the ground station provides a Morse identification.

  EFF : ALL  34-51-00    CES

 

Page 1 Aug 01/07

DME - Component Location Figure 001   EFF : ALL  34-51-00    CES

 

Page 2 Feb 01/98

B. System Architecture (Ref. Fig. 002) The DME comprises two independent systems. Each system consists of: - one DME interrogator 2SD1 (2SD2), - one DME antenna 3SD1 (3SD2), - one dual VOR/DME Radio Magnetic Indicator (VOR/DME RMI) 11FN. The components given after can control the DME system: (Ref. Fig. 003) - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio Management Unit (AMU) 1RN for audio controls, - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2), and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection, - The MCDU and the Centralized Fault Display Interface Unit (CFDIU) 1TW for test causes. The DME data are shown on: - the CAPT and F/O Primary Flight Displays (PFD), - the CAPT and F/O Navigation Displays (ND), - the VOR/DME RMI, - the MCDU(s) (maintenance data). C. Utilization Technical Data (1) Data display (Ref. Fig. 004) (a) On the PFDs With ILS/DME collocated stations, the ILS/DME distance is shown in magenta in the L lower corner of the PFD (Item 1). These data come into view when you push the ILS pushbutton switch located on the EFIS control section of the Flight Control Unit (FCU). (b) On the NDs The VOR/DME distance is shown in green in the L lower corner of the ND for DME system 1 (Item 2), and in the R lower corner of the ND for DME system 2 (Item 3) when: - you set the mode selector switch on the EFIS control section of the FCU to ROSE (ILS, VOR, NAV) or ARC, - you set the ADF/VOR/OFF switch to VOR. In addition, when you push the VOR-D pushbutton switch on the EFIS control section of the FCU, this causes: display of the VOR/DME and DME ground stations which are not already included in the flight plan, with the mode selector switch in ROSE NAV and ARC positions: - a circle for the DME station, - circle plus cross symbol for the VOR/DME station.

  R EFF : 001-049, 101-105, 151-199,  34-51-00    CES

 

Page 3 May 01/05

DME - Block Diagram Figure 002   R EFF : 001-049, 051-099, 101-105, 151-199,  34-51-00    CES

 

Page 4 May 01/05

DME - Block Diagram Figure 002A   R EFF : 106-149, 201-249, 301-399, 401-499,  34-51-00    CES

 

Page 5 Nov 01/08

DME - Block Diagram Figure 002B   R EFF : 251-299, 501-509, 511-526, 528-599,  34-51-00    CES

 

Page 6 Feb 01/10

DME - Control and Indicating Figure 003  R EFF : 001-049, 051-099, 101-105, 151-199,  34-51-00     CES

 

Page 7/8 May 01/05

DME - Control and Indicating Figure 003A  R EFF : 106-149, 201-249, 301-399, 401-499,  34-51-00     CES

 

Page 9/10 Nov 01/08

DME - Control and Indicating Figure 003B   R EFF : 251-299, 501-509, 511-526, 528-599,  34-51-00    CES

 

Page 11 Feb 01/10

DME - Data and Fault Displays Figure 004   EFF : 001-049, 051-099, 101-105, 151-199,  34-51-00   R  CES

 

Page 12 Nov 01/07

(c) On the VOR/DME RMI Two windows are available for indication of both distances from the DME 1 and DME 2 (Item 4) when the VOR/DME stations are collocated. When the DME or RMI monitoring circuits detect a fault, the corresponding display window (Item 5) is blanked. In case of No Computed Data (NCD) (out-of-range station) the windows show white horizontal dashed lines (Item 6). In addition, the LEDs on the face of the DME interrogator indicate the status of the DME system. (2) Audio control The DME interrogator applies its audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loudspeakers. The pilot can control the DME audio signals by pressing the VOR pushbutton switch on the ACP and adjusting the related potentiometer to the correct audio level. In case of collocated ILS/DME ground stations and when the ILS pushbutton switch is pressed on the EFIS control section of the FCU, the pilot can control the DME audio signal through the VOR pushbutton switch on the ACP. **ON A/C 051-099, A. Principle - The principle of the DME navigation is based on the measurement of the transmission time. Paired interrogation pulses go from an onboard interrogator to a selected ground station. After 50 microseconds, the station transmits the reply pulses to the aircraft. - The measurement of time between transmitting the interrogation pulses and receiving the reply pulses is a function of the slant range distance of the aircraft to the ground station. The measurement value is converted into nautical miles and shown to the crew. - The interrogation frequencies vary from 1041 to 1150 MHz. The reply frequencies vary from 962 to 1213 MHz. - Furthermore, the ground station provides a Morse identification. B. System Architecture (Ref. Fig. 002) The DME comprises two independent systems. Each system consists of : - one DME interrogator 2SD1 (2SD2) - one DME antenna 3SD1 (3SD2) - one dual VOR/DME Radio Magnetic Indicator (VOR/DME RMI) 11FN. The components given after can control the DME system: (Ref. Fig. 003)

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-51-00    CES

 

Page 13 Nov 01/07

- the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio Management Unit (AMU) 1RN for audio controls - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2), and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection - The MCDU and the Centralized Fault-Display Interface-Unit (CFDIU) 1TW for test causes. The DME data are shown on : - the CAPT and F/O Primary Flight Displays (PFD) - the CAPT and F/O Navigation Displays (ND) - the VOR/DME RMI - the MCDU(s) (maintenance data). C. Utilization Technical Data (1) Data display (Ref. Fig. 004) (a) On the PFDs With ILS/DME collocated stations, the ILS/DME distance is shown in magenta in the L lower corner of the PFD (Item 1). These data come into view when you push the ILS pushbutton switch located on the EFIS control section of the Flight Control Unit (FCU). (b) On the NDs The VOR/DME distance is shown in green in the L lower corner of the ND for DME system 1 (Item 2), and in the R lower corner of the ND for DME system 2 (Item 3) when : - you set the mode selector switch on the EFIS control section of the FCU to ROSE (ILS, VOR, NAV) or ARC - you set the ADF/VOR/OFF switch to VOR. In addition, when you push the VOR-D pushbutton switch on the EFIS control section of the FCU, this causes : Display of the VOR/DME and DME ground stations which are not already included in the flight plan, with the mode selector switch in ROSE NAV and ARC positions : - a circle for the DME station - circle plus cross symbol for the VOR/DME station. (c) On the VOR/DME RMI Two windows are available for indication of both distances from the DME 1 and DME 2 (Item 4) when the VOR/DME stations are collocated. When the DME or RMI monitoring circuits detect a fault, the corresponding display window (Item 5) is blanked.

  R EFF : 051-099,  34-51-00    CES

 

Page 14 Nov 01/07

In case of No Computed Data (NCD) (out-of-range station) the windows show white horizontal dashed lines (Item 6). In addition, the LEDs on the face of the DME interrogator indicate the status of the DME system. (2) Audio control The DME interrogator applies its audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The pilot can control the DME audio signals by pressing the VOR pushbutton switch on the ACP and adjusting the related potentiometer to the correct audio level. In case of collocated ILS/DME ground stations and when the ILS pushbutton switch is pressed on the EFIS control section of the FCU, the pilot can control the DME audio signal through the VOR pushbutton switch on the ACP. R

**ON A/C 106-149, 201-233, 236-238, 301-304, A. Principle - The principle of the DME navigation is based on the measurement of the transmission time. Paired interrogation pulses go from an onboard interrogator to a selected ground station. After 50 microseconds, the station transmits the reply pulses to the aircraft. - The measurement of time between transmitting the interrogation pulses and receiving the reply pulses is a function of the slant range distance of the aircraft to the ground station. The measurement value is converted into nautical miles and shown to the crew. - The interrogation frequencies vary from 1041 to 1150 MHz. The reply frequencies vary from 962 to 1213 MHz. - Furthermore, the ground station provides a Morse identification. B. System Architecture (Ref. Fig. 002A) The DME comprises two independent systems. Each system consists of : - one DME interrogator 2SD1 (2SD2) - one DME antenna 3SD1 (3SD2) - one dual VOR/ADF/DME Radio Magnetic Indicator (VOR/ADF/DME RMI) 21FN. The components given after can control the DME system : (Ref. Fig. 003A) - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio Management Unit (AMU) 1RN for audio controls - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2), and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection

  R EFF : 051-099, 106-149, 201-233, 236-238,  34-51-00 301-304,   CES

 

Page 15 Feb 01/08

- the MCDU and the Centralized Fault-Display Interface-Unit (CFDIU) 1TW for test causes. The DME data are shown on : - the CAPT and F/O Primary Flight Displays (PFD) - the CAPT and F/O Navigation Displays (ND) - the VOR/ADF/DME RMI - the MCDU(s) (maintenance data). C. Utilization Technical Data (1) Data display (Ref. Fig. 004A) (a) On the PFDs With ILS/DME collocated stations, the ILS/DME distance is shown in magenta in the L lower corner of the PFD (Item 1). These data come into view when you push the ILS pushbutton switch located on the EFIS control section of the Flight Control Unit (FCU). (b) On the NDs The VOR/DME distance is shown in green in the L lower corner of the ND for DME system 1 (Item 2), and in the R lower corner of the ND for DME system 2 (Item 3) when : - you set the mode selector switch on the EFIS control section of the FCU to ROSE (ILS, VOR, NAV) or ARC - you set the ADF/VOR/OFF switch to VOR. In addition, when you push the VOR-D pushbutton switch on the EFIS control section of the FCU, this causes: Display of the VOR/DME and DME ground stations which are not already included in the flight plan, with the mode selector switch in ROSE NAV and ARC positions: - a circle for the DME station - circle plus cross symbol for the VOR/DME station. (c) On the VOR/ADF/DME RMI Two windows are available for indication of both distances from the DME 1 and DME 2 (Item 4) when the VOR/DME stations are collocated. When the DME or RMI monitoring circuits detect a fault, the corresponding display window (Item 5) is blanked. In case of Non Computed Data (NCD) (out-of-range station) the windows show white horizontal dashed lines (Item 6). In addition, the LEDs on the face of the DME interrogator indicate the status of the DME system.

  R EFF : 106-149, 201-233, 236-238, 301-304,  34-51-00    CES

 

Page 16 Feb 01/08

DME - Data and Fault Displays Figure 004A   R EFF : 106-149, 201-249, 301-399, 401-499,  34-51-00    CES

 

Page 17 Nov 01/08

(2) Audio control The DME interrogator applies its audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The pilot can control the DME audio signals by pressing the VOR pushbutton switch on the ACP and adjusting the related potentiometer to the correct audio level. In case of collocated ILS/DME ground stations and when the ILS pushbutton switch is pressed on the EFIS control section of the FCU, the pilot can control the DME audio signal through the VOR pushbutton switch on the ACP. R

**ON A/C 234-235, 239-249, 305-399, 401-499, A. Principle - The principle of the DME navigation is based on the measurement of the transmission time. Paired interrogation pulses go from an onboard interrogator to a selected ground station. After 50 microseconds, the station transmits the reply pulses to the aircraft. - The measurement of time between transmitting the interrogation pulses and receiving the reply pulses is a function of the slant range distance of the aircraft to the ground station. The measurement value is converted into nautical miles and shown to the crew. - The interrogation frequencies vary from 1041 to 1150 MHz. The reply frequencies vary from 962 to 1213 MHz. - Furthermore, the ground station provides a Morse identification. B. System Architecture (Ref. Fig. 002A) The DME comprises two independent systems. Each system consists of : - one DME interrogator 2SD1 (2SD2) - one DME antenna 3SD1 (3SD2) - one dual VOR/ADF/DME Radio Magnetic Indicator (VOR/ADF/DME RMI) 21FN. The components given after can control the DME system : (Ref. Fig. 003A) - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio Management Unit (AMU) 1RN for audio controls - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2), and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection - the MCDU and the Centralized Fault-Display Interface-Unit (CFDIU) 1TW for test causes. The DME data are shown on : - the CAPT and F/O Primary Flight Displays (PFD) - the CAPT and F/O Navigation Displays (ND)

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-51-00    CES

 

Page 18 Nov 01/08

- the VOR/ADF/DME RMI - the MCDU(s) (maintenance data). C. Utilization Technical Data (1) Data display (Ref. Fig. 004A) (a) On the PFDs With ILS/DME collocated stations, the ILS/DME distance is shown in magenta in the L lower corner of the PFD (Item 1). These data come into view when you push the ILS pushbutton switch located on the EFIS control section of the Flight Control Unit (FCU). (b) On the NDs The VOR/DME distance is shown in green in the L lower corner of the ND for DME system 1 (Item 2), and in the R lower corner of the ND for DME system 2 (Item 3) when : - you set the mode selector switch on the EFIS control section of the FCU to ROSE (ILS, VOR, NAV) or ARC - you set the ADF/VOR/OFF switch to VOR. In addition, when you push the VOR-D pushbutton switch on the EFIS control section of the FCU, this causes: Display of the VOR/DME and DME ground stations which are not already included in the flight plan, with the mode selector switch in ROSE NAV and ARC positions: - a circle for the DME station - circle plus cross symbol for the VOR/DME station. (c) On the VOR/ADF/DME RMI Two windows are available for indication of both distances from the DME 1 and DME 2 (Item 4) when the VOR/DME stations are collocated. When the DME or RMI monitoring circuits detect a fault, the corresponding display window (Item 5) is blanked. In case of Non Computed Data (NCD) (out-of-range station) the windows show white horizontal dashed lines (Item 6). In addition, the LEDs on the face of the DME interrogator indicate the status of the DME system. (2) Audio control The DME interrogator applies its audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The pilot can control the DME audio signals by pressing the VOR pushbutton switch on the ACP and adjusting the related potentiometer to the correct audio level.

  R EFF : 234-235, 239-249, 305-399, 401-499,  34-51-00    CES

 

Page 19 Nov 01/08

In case of collocated ILS/DME ground stations and when the ILS pushbutton switch is pressed on the EFIS control section of the FCU, the pilot can control the DME audio signal through the ILS pushbutton switch on the ACP. R

**ON A/C 251-299, 501-509, 511-526, 528-599, A. Principle - The principle of the DME navigation is based on the measurement of the transmission time. Paired interrogation pulses go from an onboard interrogator to a selected ground station. After 50 microseconds, the station transmits the reply pulses to the aircraft. - The measurement of time between transmitting the interrogation pulses and receiving the reply pulses is a function of the slant range distance of the aircraft to the ground station. The measurement value is converted into nautical miles and shown to the crew. - The interrogation frequencies vary from 1041 to 1150 MHz. The reply frequencies vary from 962 to 1213 MHz. - Furthermore, the ground station provides a Morse identification. B. System Architecture (Ref. Fig. 002B) The DME comprises two independent systems. Each system consists of : - one DME interrogator 2SD1 (2SD2) - one DME antenna 3SD1 (3SD2) The components given after can control the DME system: (Ref. Fig. 003B) - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio Management Unit (AMU) 1RN for audio controls - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2), and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection - The MCDU and the Centralized Fault-Display Interface-Unit (CFDIU) 1TW for test causes. The DME data are shown on : - the CAPT and F/O Primary Flight Displays (PFD) - the CAPT and F/O Navigation Displays (ND) - the MCDU(s) (maintenance data).

  R EFF : 234-235, 239-249, 251-299, 305-399,  34-51-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 20 Feb 01/10

C. Utilization Technical Data (1) Data display (Ref. Fig. 004B) (a) On the PFDs With ILS/DME collocated stations, the ILS/DME distance is shown in magenta in the L lower corner of the PFD (Item 1). These data come into view when you push the ILS pushbutton switch located on the EFIS control section of the Flight Control Unit (FCU). (b) On the NDs The VOR/DME distance is shown in green in the L lower corner of the ND for DME system 1 (Item 2), and in the R lower corner of the ND for DME system 2 (Item 3) when : - you set the mode selector switch on the EFIS control section of the FCU to ROSE (ILS, VOR, NAV) or ARC - you set the ADF/VOR/OFF switch to VOR. In addition, when you push the VOR-D pushbutton switch on the EFIS control section of the FCU, this causes : Display of the VOR/DME and DME ground stations which are not already included in the flight plan, with the mode selector switch in ROSE NAV and ARC positions : - a circle for the DME station - circle plus cross symbol for the VOR/DME station. (c) In addition, the LEDs on the face of the DME interrogator indicate the status of the DME system. (2) Audio control The DME interrogator applies its audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The pilot can control the DME audio signals by pressing the VOR pushbutton switch on the ACP and adjusting the related potentiometer to the correct audio level. In case of collocated ILS/DME ground stations and when the ILS pushbutton switch is pressed on the EFIS control section of the FCU, the pilot can control the DME audio signal through the ILS pushbutton switch on the ACP. **ON A/C ALL 4. ____________ Power Supply

  EFF : ALL  34-51-00   R  CES

 

Page 21 Feb 01/10

DME - Data and Fault Displays Figure 004B   R EFF : 251-299, 501-509, 511-526, 528-599,  34-51-00    CES

 

Page 22 Feb 01/10

**ON A/C 001-049, 051-099, 101-105, 151-199, (Ref. Fig. 002) Energization of each system is through 115VAC 400 Hz buses : - 115VAC SHED ESS BUS 801XP via circuit breaker 1SD1 for system 1 - 115VAC BUS2 BUS 204XP via circuit breaker 1SD2 for system 2. The 115VAC ESS BUS 401XP energizes the VOR/DME RMI via circuit breaker 12FN. **ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 002A) Energization of each system is through 115VAC 400 Hz buses : - 115VAC SHED ESS BUS 801XP via circuit breaker 1SD1 for system 1 - 115VAC BUS2 BUS 204XP via circuit breaker 1SD2 for system 2. The 115VAC ESS BUS 401XP energizes the VOR/ADF/DME RMI via circuit breaker 12FN. R

**ON A/C 251-299, 501-509, 511-526, 528-599, (Ref. Fig. 002B) Energization of each system is through 115VAC 400 Hz buses : - 115VAC SHED ESS BUS 801XP via circuit breaker 1SD1 for system 1 - 115VAC BUS2 BUS 204XP via circuit breaker 1SD2 for system 2. **ON A/C ALL 5. _____________________ Component Description **ON A/C 001-049, 101-105, 151-199, A. DME Interrogator (1) External description (Ref. Fig. 005) The face of the interrogator is fitted with a handle, two attaching parts, two momentary pushbutton switches and a front panel Liquid Crystal Display (LCD). The LCD is used as a fault display and as an operator interface during certain modes. The front panel display also provides user interfaces for test and troubleshooting. The front panel contains two momentary pushbutton switches for interfacing with the LCD pages.

  EFF : ALL  34-51-00    CES

 

Page 23 Feb 01/10

DME - Interrogator Figure 005   R EFF : 001-049, 101-105, 151-199,  34-51-00    CES

 

Page 24 Nov 01/09

An RS-232 maintenace access port is provided on the front panel. This port is compatible with RS-232 serial ports on Personal Computers (PC). The back is equipped with one ARINC 600 size one connector, which includes three plugs: - Top Plug (TP): is not installed - Middle Plug (MP): aircraft interconnection, and the coaxial antenna - Bottom Plug (BP): connection with the power supply circuit. R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, A. DME Interrogator (1) Description (Ref. Fig. 005A) The face of the interrogator is fitted with a handle, two lugs, a TEST pushbutton switch and two LEDs. The name, color and function of the two LEDs are as follows: - CONTROL FAIL (red) indicates invalid frequency input tuning words - LRU STATUS (green) indicates that no faults are detected during the test sequence - LRU STATUS (red) indicates that a fault is detected during the test sequence. The back is equipped with two ARINC 600 size one connectors which include three plugs: - Top Plug (TP): connection with the automatic test circuit - Middle Plug (MP): connection with the antenna and peripheral circuits - Bottom Plug (BP): connection with the power supply circuit and suppressor. **ON A/C 001-049, 101-105, 151-199, (2) Internal description (Ref. Fig. 006) The DME interrogator includes: - an RF module, - a synthesizer/modulator assembly, - a main processor (CPU and I/O) assembly, - a video processor, - a power supply assembly, - a rear interconnect module, - a front panel display module, - a memory card interface module.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-51-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 25 Feb 01/10

DME - Interrogator Figure 005A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-51-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 26 Feb 01/10

DME Interrogator - Simplified Block Diagram Figure 006   R EFF : 001-049, 101-105, 151-199,  34-51-00    CES

 

Page 27 Nov 01/09

(a) RF module This module consists of a single Personal Computer (PC) board that is mounted in a closed aluminum chassis. It contains: - a transmitter, - a receiver, - a circulator, - a low-pass filter. 1 _

Transmitter The solid-state transmitter contains a six-stage amplifier followed by a 700W (typical) final amplifier. The pulse modulation is applied to the first six stages of amplification. It is tuned to frequencies in the 1025-1150 MHz range.

2 _

Receiver The single-conversion superheterodyne receiver consists of a varactor tuned preselector, 1 GHz preamplifier, mixer, band-pass filters, and a 63 MHz logarithmic IF amplifier. The preselector is tuned to frequencies in the 962-1213 MHz range.

3 _

Circulator The circulator routes the transmitter output to the antenna and the antenna received signal to the receiver. It provides isolation to protect the transmitter output amplifier devices from reflected signals.

4 _

Low-pass filter The low-pass filter prevents internal transmitter harmonics from being passed to the antenna.

(b) Synthetizer/Modulator Assembly This module contains the digital frequency synthesizer and transmitter modulator circuits. The digital frequency synthesizer supplies a signal used both as the local oscillator input to the receiver mixer and as the low-level CW signal the transmitter. This circuit consists of a phase-locked loop and Voltage Control Oscillator (VCO) which is tuned to the desired channel frequency by a serial tuning word supplied by the video processor module. The modulator supplies the on/off signal that corresponds to the X or Y pulse pairs associated with the channel frequency. An interrogation is transmitted by triggering the series of on/off modulation to control the transmitter amplifier stages that drive the final amplifier.

  R EFF : 001-049, 101-105, 151-199,  34-51-00    CES

 

Page 28 Nov 01/09

(c) Main Processor (CPU and I/O) Assembly This module contains the CPU that executes the signal processing using a microprocessor. It also contains the I/O section consisting of ARINC 429 transmitters and receivers, and discrete I/O logic to provide the interfaces with other aircraft systems including the Centralized Fault Display System (CFDS) and displays. ARINC 429 inputs and outputs are processed by a specially designed ARINC 429 LSI transceiver device. External level converters are used to satisfy the ARINC 429 characteristics for the transmitters and convert input ARINC 429 signals to logic levels. All discrete inputs and outputs external to the DME are processed by discrete components to provide level shifting and latching. The following types of devices are employed: - digital-to-analog converter devices to generate control and test signals, - Field Programmable Logic Array (FPLA) devices to accept, decode and generate discrete signals, - memory devices (bootstrap, program, nonvolatile, and data), - data recorder interface, - front panel display driver, - RS-232 interface, - clock generators. (d) Video Processor This module contains a Field Programmable Gate Array (FPGA) which is the control center for the video processor. The video processor provides the following operations: - converts tuning commands from CPU to serial data to tune the transmit/receive frequency synthesizer, - generates the corresponding receiver preselector tuning voltage, - generates the corresponding X or Y pulse modulation for the interrogation, - generates the output mutual suppression pulse for an interrogation, - detects the input mutual suppression pulse and inhibits reception and video processing, - determines the logarithmic IF noise threshold setting, - starts the range (distance) counter when an interrogation is transmitted, - digitizes the video signals from the receiver logarithmic IF amplifier, - validates the amplitude, spacing, and width of the digitized video pulse pairs,

  R EFF : 001-049, 101-105, 151-199,  34-51-00    CES

 

Page 29 Nov 01/09

- stores the range counter value in a FIFO when each valid pulse pair is decoded, - analog-to-digital converter devices to process the received signals and BITE test point voltages, - generates the audio tone for the Morse code station identity aural output, - provides for integrity testing. (e) Power Supply Assembly This module is a self contained, high efficiency power supply that converts the 115 VAC, 400 Hz AC power into the required DC operating voltages (+70V, +24V, +12V, -12V and +5V). It includes an EMI filter to reduce electromagnetic interference from being radiated from the power lines. (f) Rear Interconnect Module The rear connector assembly provides the interwiring from the aircraft interface to the internal modules. A combination of series resistors, series of transient voltage suppressors, and ferrite pin filters provide High Intensity Radiation Fields (HIRF) and lightning protection. To prevent HIRF or lightning from affecting operation by entering via rear connector cables, a HIRF compartment is formed in the rear of the DME Interrogator. The signal and power cables are filtered by using discrete and distributed filter elements and limiting devices on the rear interconnect module located inside HIRF compartment. The filtered lines are then fed to the appropriate points in the DME Interrogator. The DME Interrogator is packaged in an aluminum casting. This seamless main frame ensures HIRF cannot enter the unit through structural seams. The slots formed by the removable side covers are sealed against HIRF with protective gaskets and metal covers. (g) Front Panel Display Module The front panel display module is mounted behind the front panel and provides an interface to an operator via a low-power Liquid Crystal Display (LCD) that is visible from the front of the DME Interrogator. In addition to the LCD, the module contains Light Pipe back lightning, temperature compensation circuitry, and a PC board containing an associated LCD driver, two pushbutton switches used to enter functional test and to control the display menus, and a nine-pin, RS-232 serial type connector. (h) Memory Card Interface Module The memory card interface module is used to load data into the CPU or record data from the CPU. The memory card interface module supports either flash cards or RAM cards via the front panel

  R EFF : 001-049, 101-105, 151-199,  34-51-00    CES

 

Page 30 Nov 01/09

Personal Computing Memory Card Interface (PCMCIA) slot. The flash card or RAM card is inserted through the front panel. In one mode, data stored on the flash card memory module is used to update program or data memory in the DME Interrogator. In another mode, the flash card memory module functions as a data recorder. (3) Not Applicable **ON A/C 051-099, 106-149, 201-249, 301-399, 401-499, (2) Operation (Ref. Fig. 006A) (a) Interrogation When the frequency for a DME ground station is selected on the RMP or by the FMGC, a serial digital tuning word is transmitted along an ARINC 429 data bus to the range processor in the interrogator. The range processor uses the frequency data to provide a tuning word for the synthesizer. In the synthesizer the Voltage Controlled Oscillator (VCO), which operates in the L-band range of 1025 to 1150 MHz, generates the transmitter signal which after amplification is applied to the driver. The transmitter part of the interrogator consists of a VCO with a quartz-stabilized, phase-locked-loop frequency synthesizer and a power amplifier. The synthesizer is controlled by the 8OC/86 CPU. The power amplifier is energized only during the pulse transmission and the transmitted energy goes to the antenna through a circulator. The receiver part consists of a preselecting filter, an RF amplifier, a mixer and an IF amplifier centered on 63 MHz. The IF amplifier output pulses are then detected. (b) Reply signal processing Reply pulses from a DME ground station are received by the antenna and applied through the circulator to the receiver. In the receiver the reply pulses are filtered, amplified and mixed with the local oscillation from the driver to produce a 63 MHz IF signal. After further amplification and filtering, a second mixer combines the 63 MHz signal with a local 52.3 MHz oscillation to produce a 10.7 MHz IF signal which is applied to the video processor through a video detector.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-51-00 201-249, 301-399, 401-499,   CES

 

Page 31 Nov 01/09

DME Interrogator - Simplifed Block Diagram Figure 006A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-51-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 32 Feb 01/10

In the video processor the signal is applied to a threshold detector and a pulse pair decoder. The threshold detector determines the range measurement timing. The video processor verifies that a valid pulse is received and applies the valid video pulse to the range processor module. An audio identification algorithm executed by the processor board decodes and synthesizes a 1350 Hz audio signal which reproduces the source identification signal transmitted by the DME ground station and provides an output to the audio integrating system in the aircraft. (c) Distance measurement A range counter in the range processor module, which generates the driver and power amplifier trigger pulses, measures the time interval between the first interrogation pulse and the reception of the first valid video pulse. The time delay of the reply pulse is converted to a distance value and stored in memory. During an interrogation cycle, additional reply pulse delay measurements are made and processed to produce an accurate range distance. The range distance data is transmitted through ARINC 429 data ports to the DMC, the RMI and the FMGC. (d) Suppression A suppression coaxial connects all these units: the DME interrogators and ATC/ TCAS system. This prevents transmission from one system while the other is in reception mode. This is necessary because all these systems operate on the same frequency range. (e) Modes The DME system has three basic modes : standby, directed and free scan. - Standby mode: in this mode no distance data is computed, the NCD indication appears in the RMI, and the NCD signal is also transmitted to the FMGC. The DME reverts to the standby mode when it is not communicating with a ground station. - Directed mode: in this mode up to five foreground stations are designated by the FMGC to the DME interrogator. - Free scanning mode: in this mode any or all of five stations can be designated by the FMGC. If less than five stations are designated, the DME fills the empty slots with the closest stations. The DME scans the background loop, consisting of the other 247 stations, searching for station pulses.

  EFF : 051-099, 106-149, 201-249, 301-399,  34-51-00 401-499,  R  CES

 

Page 33 Nov 01/09

(3) Manual self-test and automatic monitoring (a) Purpose The fault monitor of the DME interrogator periodically checks the circuits and operation of the interrogator while the unit is installed in the aircraft. The fault monitor uses Built-In Test Equipment (BITE) to gather operating parameters relating to the fault and stores historical fault data relating to the failure in the maintenance fault memory. If a failure is detected, the crew and/or the FMCS is alerted that the unit does not operate correctly. The stored fault data can be used by the shop technician as an aid in trouble shooting the faulty LRU. (b) Operation The fault monitor self-test periodically interrupts normal DME operation and uses BITE to monitor a number of parameters selected to determine the status of functionally replaceable modules. Under normal conditions, the self-test is performed every 60 s. If a failure is detected, the self-test is performed every 5 s. Safety related failures detected while the aircraft is in the air cause DME service to be denied to the crew and/or the FMCS. A detected failure causes the DME to output ARINC data words containing failure and No Computed Data indications. Safety related failures include wrong distance, wrong channel, etc. If the failure is not safety related (low RF power, poor receiver sensitivity, etc.), the DME continues to attempt to operate normally until the aircraft is on the ground. If any failure is detected while the aircraft is on the ground, DME service is denied to the crew and/or the FMCS. The DME outputs ARINC data words containing failure and No Computed Data indications. Data relating to any failure detected when the aircraft is in the air is stored in Non-Volatile Memory on processor card A7. The Non-Volatile Memory can be accessed by the shop technician as an aid to fault isolation. The DME self-test procedure can be manually initiated by either the ARINC 429 input control word or the DME functional test rear connector discrete. When the self-test procedure is initiated in one of these ways, the ARINC output data words indicate a failure for 2 seconds, No Computed Data for 2 seconds, and then a continuous self-test indication. The DME stays in self-test until released. While the self-test procedure is being performed, the DME continues to calculate distance, except when the fault monitor test is initiated.

  R EFF : 051-099, 106-149, 201-249, 301-399,  34-51-00 401-499,   CES

 

Page 34 Nov 01/09

R

**ON A/C 251-299, 501-509, 511-526, 528-599, (2) Operation (Ref. Fig. 006A) (a) Interrogation When the frequency for a DME ground station is selected on the RMP or by the FMGC, a serial digital tuning word is transmitted along an ARINC 429 data bus to the range processor in the interrogator. The range processor uses the frequency data to provide a tuning word for the synthesizer. In the synthesizer the Voltage Controlled Oscillator (VCO), which operates in the L-band range of 1025 to 1150 MHz, generates the transmitter signal which after amplification is applied to the driver. The transmitter part of the interrogator consists of a VCO with a quartz-stabilized, phase-locked-loop frequency synthesizer and a power amplifier. The synthesizer is controlled by the 8OC/86 CPU. The power amplifier is energized only during the pulse transmission and the transmitted energy goes to the antenna through a circulator. The receiver part consists of a preselecting filter, an RF amplifier, a mixer and an IF amplifier centered on 63 MHz. The IF amplifier output pulses are then detected. (b) Reply signal processing Reply pulses from a DME ground station are received by the antenna and applied through the circulator to the receiver. In the receiver the reply pulses are filtered, amplified and mixed with the local oscillation from the driver to produce a 63 MHz IF signal. After further amplification and filtering, a second mixer combines the 63 MHz signal with a local 52.3 MHz oscillation to produce a 10.7 MHz IF signal which is applied to the video processor through a video detector. In the video processor the signal is applied to a threshold detector and a pulse pair decoder. The threshold detector determines the range measurement timing. The video processor verifies that a valid pulse is received and applies the valid video pulse to the range processor module. An audio identification algorithm executed by the processor board decodes and synthesizes a 1350 Hz audio signal which reproduces the source identification signal transmitted by the DME ground station and provides an output to the audio integrating system in the aircraft.

  R EFF : 251-299, 501-509, 511-526, 528-599,  34-51-00    CES

 

Page 35 Feb 01/10

(c) Distance measurement A range counter in the range processor module, which generates the driver and power amplifier trigger pulses, measures the time interval between the first interrogation pulse and the reception of the first valid video pulse. The time delay of the reply pulse is converted to a distance value and stored in memory. During an interrogation cycle, additional reply pulse delay measurements are made and processed to produce an accurate range distance. The range distance data is transmitted through ARINC 429 data ports to the DMC and the FMGC. (d) Suppression A suppression coaxial connects all these units: the DME interrogators and ATC/ TCAS system. This prevents transmission from one system while the other is in reception mode. This is necessary because all these systems operate on the same frequency range. (e) Modes The DME system has three basic modes : standby, directed and free scan. - Standby mode: in this mode no distance data is computed, and the NCD signal is also transmitted to the FMGC. The DME reverts to the standby mode when it is not communicating with a ground station. - Directed mode: in this mode up to five foreground stations are designated by the FMGC to the DME interrogator. - Free scanning mode: in this mode any or all of five stations can be designated by the FMGC. If less than five stations are designated, the DME fills the empty slots with the closest stations. The DME scans the background loop, consisting of the other 247 stations, searching for station pulses. (3) Manual self-test and automatic monitoring (a) Purpose The fault monitor of the DME interrogator periodically checks the circuits and operation of the interrogator while the unit is installed in the aircraft. The fault monitor uses Built-In Test Equipment (BITE) to gather operating parameters relating to the fault and stores historical fault data relating to the failure in the maintenance fault memory. If a failure is detected, the crew and/or the FMCS is alerted that the unit does not operate correctly. The stored fault data can be used by the shop technician as an aid in trouble shooting the faulty LRU.

  R EFF : 251-299, 501-509, 511-526, 528-599,  34-51-00    CES

 

Page 36 Feb 01/10

(b) Operation The fault monitor self-test periodically interrupts normal DME operation and uses BITE to monitor a number of parameters selected to determine the status of functionally replaceable modules. Under normal conditions, the self-test is performed every 60 s. If a failure is detected, the self-test is performed every 5 s. Safety related failures detected while the aircraft is in the air cause DME service to be denied to the crew and/or the FMCS. A detected failure causes the DME to output ARINC data words containing failure and No Computed Data indications. Safety related failures include wrong distance, wrong channel, etc. If the failure is not safety related (low RF power, poor receiver sensitivity, etc.), the DME continues to attempt to operate normally until the aircraft is on the ground. If any failure is detected while the aircraft is on the ground, DME service is denied to the crew and/or the FMCS. The DME outputs ARINC data words containing failure and No Computed Data indications. Data relating to any failure detected when the aircraft is in the air is stored in Non-Volatile Memory on processor card A7. The Non-Volatile Memory can be accessed by the shop technician as an aid to fault isolation. The DME self-test procedure can be manually initiated by either the ARINC 429 input control word or the DME functional test rear connector discrete. When the self-test procedure is initiated in one of these ways, the ARINC output data words indicate a failure for 2 seconds, No Computed Data for 2 seconds, and then a continuous self-test indication. The DME stays in self-test until released. While the self-test procedure is being performed, the DME continues to calculate distance, except when the fault monitor test is initiated. **ON A/C ALL B. DME Antenna (Ref. Fig. 007) The L-band antenna is an airborne antenna for the DME interrogator. It is a blade type with a radiating cavity driven by capacitive coupling. This antenna is designed for installation on fast aircraft and operation within the L-band from 960 to 1250 MHz.

  R EFF : ALL  34-51-00    CES

 

Page 37 Nov 01/09

DME - Antenna Figure 007   R EFF : ALL  34-51-00    CES

 

Page 38 Nov 01/09

6. Operation _________ **ON A/C 001-049, 051-099, 101-105, 151-199, (Ref. Fig. 002) **ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 002A) R

**ON A/C 251-299, 501-509, 511-526, 528-599, (Ref. Fig. 002B) **ON A/C ALL A. Control - Each DME interrogator is connected to one RMP. The DME interrogator 1 is connected to the RMP 1 (DME interrogator 2 to RMP 2). The RMP 1 also receives the management bus from the FMGC 1 (RMP 2 from FMGC 2). - In normal operation the FMGC 1(2) tunes the DME interrogator 1(2) either automatically or manually by means of the MCDU 1(2). In this case the RMP 1(2) operates as a relay which sends the frequency information from the FMGC 1(2) to the DME interrogator 1(2). - By a second port, the DME interrogator 1(2) receives a second management bus directly from the FMGC 2(1). The interrogator selects one of the two port functions by a discrete signal coming from the FMGC 1(2) through the RMP 1(2). - In case of one FMGC fault, the other FMGC can control the two DME interrogators, one directly, the other through its RMP. - In case of the RMP 1(2)fault, the concerned RMP is transparent to data and discrete coming from the FMGC. - In manual operation (at any time or with failure of the two FMGCs), the RMP 1 can control the DME interrogator 1 after ON NAV mode selection. Same possibility for the RMP 2 (DME interrogator 2). (Ref. Fig. 008) - In addition, a suppressor coaxial connects the ATC transponders to the DME interrogators. This prevents transmission from one system while the other is in reception mode. This is necessary because the DME and the ATC systems operate on the same frequency range.

  EFF : ALL  34-51-00    CES

 

Page 39 Feb 01/10

DME - Frequency Selection in Emergency Mode Figure 008   EFF : ALL  34-51-00   R  CES

 

Page 40 Nov 01/09

B. Reconfiguration Switching In normal utilization, the DME 1 and 2 data are shown on both CAPT and F/O NDs through the Display Management Computer (DMC 1(2)). ILS/DME data are shown on both CAPT and F/O PFDs. In caes of DMC 1(2) fault, it is possible to switch over to the DMC 3 with the EIS DMC selector switch. This selector switch is located on panel 8VU on the center pedestal. In this case, the DMC 3 totally replaces the DMC 1(2) through the stage of the output switching relay of the failed DMC. In case of PFD fault, there is an automatic transfer of the PFD image onto the ND. In case of ND fault: you obtain the transfer of the ND image onto the PFD when you push the PFD/ND XFR pushbutton switch on panel 301VU (501VU). When you set the PFD potentiometer to OFF on panel 301VU (501VU), this causes : - deactivation of the PFD - transfer of the PFD image onto the ND. 7. _____________ BITE Function R

**ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 009) A. Access to DME Sub-menu Functions It is possible to select the maintenance functions of the DME interrogator 1(2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant DME on the NAV menu. After these actions the DME 1(2) provides its own menu page and the sub-menu functions can then be chosen by the operator. B. Activation of the Test Function The DME 1(2) test function can be activated in ground conditions only by pressing the line key adjacent to the TEST indication on the DME 1(2) maintenance sub-menu or by pressing the TEST pushbutton switch as designed on the front panel LCD (For more details see para. 7.D.).

  EFF : ALL  34-51-00    CES

 

Page 41 Nov 01/09

DME - Maintenance Test Procedure Figure 009   EFF : ALL  34-51-00   R  CES

 

Page 42 Nov 01/09

R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 009) A. Access to DME Sub-menu Functions It is possible to select the maintenance functions of the DME interrogator 1(2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant DME on the NAV menu. After these actions the DME 1(2) provides its own menu page and the sub-menu functions can then be chosen by the operator. B. Activation of the Test Function The DME 1(2) test function can be activated in ground conditions only by pressing the line key adjacent to the TEST indication on the DME 1(2) maintenance sub-menu or by pressing the pushbutton switch on the face of the interrogator. **ON A/C ALL C. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the DME system. The BITE of the DME interrogator is connected to the CFDIU (Ref. 31-32-00). The BITE: - transmits permanently DME system status and its identification message to the CFDIU - memorizes the failures which occurred during the last 63 flight segments - monitors data inputs from the various peripherals (FMGC, RMP and CFDIU) - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the menu mode (a) Normal mode During the normal mode the BITE monitors cyclically the status of the DME system. It transmits its information to the CFDIU during the concerned flight.

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Page 43 Feb 01/10

In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 167 ms by an ARINC 429 message with label 356. (b) Menu mode The menu mode can only be activated on the ground. This mode enables communication between the CFDIU and the DME interrogator BITE by means of the MCDU. The DME menu mode is composed of: - LAST LEG REPORT - PREVIOUS LEGS REPORT - LRU IDENTIFICATION - GND SCANNING - TROUBLE SHOOTING DATA - CLASS 3 FAULTS - GROUND REPORT - TEST. (2) Interactive function The interactive mode can be activated on the ground only, using the line key adjacent to the DME 1 (or 2) indication on the SYSTEM REPORT/TEST page of any MCDU (Ref. 22-82-00). This mode enables communication between the CFDIU and the BITE of the DME interrogator by means of the MCDU. (Ref. Fig. 009) The interactive mode is composed of: - LAST LEG REPORT **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 010) R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 010A) **ON A/C ALL This menu contains the fault messages (class 1 and 2, internal and external) detected during the last flight. - PREVIOUS LEGS REPORT

  EFF : ALL  34-51-00    CES

 

Page 44 Feb 01/10

DME - Maintenance Test Procedure - DME Menu (sheet 1/5) Figure 010   R EFF : 001-049, 101-105, 151-199,  34-51-00    CES

 

Page 45 Nov 01/09

DME - Maintenance Test Procedure - DME Menu (sheet 1/5) Figure 010A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-51-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 46 Feb 01/10

**ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 010) R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 010A) **ON A/C ALL This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. - LRU IDENTIFICATION **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 010)

R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 010A) **ON A/C ALL Allows to display the P/N and the S/N of the equipment. - GND SCANNING (Ref. Fig. 011) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. - TROUBLE SHOOTING DATA (Ref. Fig. 011) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. - CLASS 3 FAULTS (Ref. Fig. 012) Allows to display the class 3 faults recorded during the last flight leg. - GROUND REPORT (Ref. Fig. 012)

  EFF : ALL  34-51-00    CES

 

Page 47 Feb 01/10

DME - Maintenance Test Procedure - DME Menu (sheet 2/5) Figure 011   R EFF : ALL  34-51-00    CES

 

Page 48 Nov 01/09

DME - Maintenance Test Procedure - DME Menu (sheet 3/5) Figure 012   EFF : ALL  34-51-00   R  CES

 

Page 49 Nov 01/09

Allows to present the class 1, 2 or 3 internal failures detected on ground. - TEST. **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 013) R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 013A) **ON A/C ALL (Ref. Fig. 014) allows a check of the correct operation of the DME interrogator. (3) List of components All the components are listed in the Para. 2. Component Location.

  EFF : ALL  34-51-00    CES

 

Page 50 Feb 01/10

DME - Maintenance Test Procedure - DME Menu (sheet 4/5) Figure 013   R EFF : 001-049, 101-105, 151-199,  34-51-00    CES

 

Page 51 Nov 01/09

DME - Maintenance Test Procedure - DME Menu (sheet 4/5) Figure 013A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-51-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 52 Feb 01/10

DME - Maintenance Test Procedure - DME Menu (sheet 5/5) Figure 014   R EFF : ALL  34-51-00    CES

 

Page 53 Nov 01/09

(4) Reporting function The tables below give the list of internal/external failures: ------------------------------------------------------------------------------| REPORTED INTERNAL FAILURES | |-----------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |----------------------------------------------------------|-------|----------| | DME i (2SDi) | 1 | 34-51-33 | | DME i ANTENNA (3SDi) | 1 | 34-51-11 | ------------------------------------------------------------------------------------------------------------------------------------------------------------| REPORTED EXTERNAL FAILURES | |-----------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |----------------------------------------------------------|-------|----------| | FMGCi(1CA1)/RMPi(1RGi)/DMEi(2SDi) | 3 | 22-83-34 | | CFDIU(1TW)/DMEi(2SDi) | 3 | 31-32-34 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | | DMC1/2(1WT1/2)/DDRMI(1FN)/DME1(2SD1) | 1 | 31-62-34 | | DMC2/1(1WT2/1)/DDRMI(1FN)/DME2(2SD2) | 1 | 31-62-34 | | LGCIU(5GAi)/DMEi(2SDi) | 3 | 32-31-71 | ------------------------------------------------------------------------------R

**ON A/C 001-049, 101-105, 151-199, D. BITE Implementation (1) Activation of the Self-Test A functional self-test of the DME Interrogator may be initiated from the normal mode screen by pressing the TEST pushbutton switch as designated on the front panel LCD. A self-test mode is initiated and a TEST IN PROGRESS message is displayed approximately one second after the TEST pushbutton is pressed. This message is displayed for four seconds with a moving thermometer along the bottom of the LCD indicating the progress of the test from one to five seconds. At the end of the self-test, either a TEST COMPLETE, NO FAILURES message screen or a TEST COMPLETE, FAILURES message screen is displayed. The TEST COMPLETE, NO FAILURES screen contains two pushbutton selections (MAINT and RETURN). The TEST COMPLETE, FAILURES screen also contains two pushbutton selections (MAINT and WHY?).

  EFF : ALL  34-51-00    CES

 

Page 54 Nov 01/09

For both screens, pressing the left (MAINT) pushbutton initiates the extended maintenance pages of the system for troubleshooting. The right (RETURN) pushbutton associated with the TEST COMPLETE, NO FAILURES screen returns the system to its normal mode screen. The right (WHY?) pushbutton associated with the TEST COMPLETE, FAILURES screen places the system in the display-failures mode where individual system failures (fault memory codes) are displayed, one per page. **ON A/C 051-099, 106-149, 201-249, 301-399, 401-499, D. BITE Implementation (1) Internal test processing --------------------------------------------------------------------------| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION | | DESIGNATION | | | CONDITIONS | |----------------|----------------------------|----------|----------------| | Power-up | Power supply module | | Power interrupt| | test | | | > 200ms | |----------------|----------------------------|----------|----------------| | MCDU system | - processor board | | Relevant MCDU | | test | - receiver | | menu line key | | | - synthesizer | | selection | | | - power amplifier | | | | | - driver | | | | | - AGC circuitry | | | |----------------|----------------------------|----------|----------------| | FACE TEST | ditto | | Relevant P/BSW | | | | | activated on | | | | | the receiver | | | | | face | --------------------------------------------------------------------------(2) Activation of the test on the indicators The DME 1(2) test function can be activated only by pressing the pushbutton switch on the face of the interrogator. The following sequence is then generated on the output of the equipment:

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-51-00 201-249, 301-399, 401-499,   CES

 

Page 55 Nov 01/09

--------------------------------------------------------------------------| DURATION | MESSAGE | RMI DISPLAY | |---------------------|-------------------------|-------------------------| | 2 s approx. | FAILURE | Blanked window | | 2 s approx. | NCD | Dashed lines | | Duration of test | TEST | 0.0 | --------------------------------------------------------------------------During the first 2 s, the green LRU STATUS and the red CONTROL FAIL LEDs on the face of the interrogator are on. During the next 2 s, the red LRU STATUS and the red CONTROL FAIL LEDs are on. During the next 2 s, all LEDs go off. The green LRU STATUS remains on for 30 s or until the pushbutton switch on the face of the interrogator is pressed and the sequence starts again. R

**ON A/C 251-299, 501-509, 511-526, 528-599, D. BITE Implementation (1) Internal test processing --------------------------------------------------------------------------| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION | | DESIGNATION | | | CONDITIONS | |----------------|----------------------------|----------|----------------| | Power-up | Power supply module | | Power interrupt| | test | | | > 200ms | |----------------|----------------------------|----------|----------------| | MCDU system | - processor board | | Relevant MCDU | | test | - receiver | | menu line key | | | - synthesizer | | selection | | | - power amplifier | | | | | - driver | | | | | - AGC circuitry | | | |----------------|----------------------------|----------|----------------| | FACE TEST | ditto | | Relevant P/BSW | | | | | activated on | | | | | the receiver | | | | | face | ---------------------------------------------------------------------------

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-51-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 56 Feb 01/10

(2) Activation of the test The DME 1(2) test function can be activated only by pressing the pushbutton switch on the face of the interrogator. The following sequence is then generated on the output of the equipment: During the first 2 s, the green LRU STATUS and the red CONTROL FAIL LEDs on the face of the interrogator are on. During the next 2 s, the red LRU STATUS and the red CONTROL FAIL LEDs are on. During the next 2 s, all LEDs go off. The green LRU STATUS remains on for 30 s or until the pushbutton switch on the face of the interrogator is pressed and the sequence starts again. **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, E. Power-up Tests Initialization and Cockpit Repercussions (1) Conditions of power-up tests initialization - How long the computer must be de-energized: 2 s. - A/C configuration: - whatever the A/C configuration on ground (2) Progress of power-up tests - Duration: 2 s. - Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - DME RMI display dashes during 1 s distance diplayed (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). - Tests pass: - DME RMI display distance displayed - ND distance displayed - Tests failed: - DME RMI display black - ND DME in red

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-51-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 57 Feb 01/10

R

**ON A/C 251-299, 501-509, 511-526, 528-599, E. Power-up Tests Initialization and Cockpit Repercussions (1) Conditions of power-up tests initialization - How long the computer must be de-energized: 2 s. - A/C configuration: - whatever the A/C configuration on ground (2) Progress of power-up tests - Duration: 2 s. - Cockpit repercussions directly linked to power-up test accomplishment (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). - Tests pass: - ND distance displayed - Tests failed: - ND DME in red

  R EFF : 251-299, 501-509, 511-526, 528-599,  34-51-00    CES

 

Page 58 Feb 01/10

DME - ADJUSTMENT/TEST _____________________ TASK 34-51-00-740-002 BITE Test of the DME WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-004 34-10-00-860-005 34-51-00-991-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure IR Alignment Procedure ADIRS Stop Procedure Fig. 501

3. __________ Job Set-up Subtask 34-51-00-860-054 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits(Ref. TASK 24-41-00-861002). (2) On the EFIS control sections of the FCU: - set the mode selector switches to ROSE or ARC - set the ADF/VOR selector switches to VOR - push the ILS pushbutton switches.

  EFF : ALL  34-51-00    CES

 

Page 501 Feb 01/98

(3) On the center pedestal, on the RMP1 and RMP2: - set the ON/OFF switches to ON - set a non local frequency of a VOR/DME1 and VOR/DME2. (Ref. Fig. 501/TASK 34-51-00-991-001) (4) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). (5) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (6) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). Subtask 34-51-00-865-056 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 49VU NAV/VOR/DME/RMI

12FN

F13

**ON A/C ALL 49VU NAV/DME/1 121VU COM NAV/DME/2

1SD1 1SD2

G14 K06

4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, 151-199, Subtask 34-51-00-740-051 A. BITE Test of the DME NOTE : The DME and the VOR/DME data come into view on the ND. The ILS/DME ____ data come into view on the PFD. NOTE : During the BITE TEST (DME1 or 2) by the MCDU, the indications ____ related to the two receivers (CAPT and F/O) are shown at the same time. This has no effect on the test or component operation.

  EFF : ALL  34-51-00    CES

 

Page 502 Nov 01/08

VOR/DME - Frequency Selection Figure 501/TASK 34-51-00-991-001   EFF : ALL  34-51-00    CES

 

Page 503 Feb 01/98

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the DME1 (DME2) indication.

- the DME1 (DME2) page comes into view.

- push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (page 1 to 2).

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 10s indication comes into view. From 0 to 4s: - on the CAPT and F/O NDs and PFDs: . the DME1(DME2) red warning flag comes into view at the bottom and on the left (right) side then it goes out of view. - on the VOR/DME RMI: . the left (right) window is blanked. From 4 to 7s: - on the VOR/DME RMI: . the left (right) window shows white horizontal dashes. From 7 to 10s: - on the VOR/DME RMI: . the distance of 0.0 comes into view.

- push the line key adjacent to the YES indication.

On the MCDU: - the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication.

The test procedure stops.

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Page 504 May 01/05

R

**ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-51-00-740-051-A A. BITE Test of the DME NOTE : The DME and the VOR/DME data come into view on the ND. The ILS/DME ____ data come into view on the PFD. NOTE : During the BITE TEST (DME1 or 2) by the MCDU, the indications ____ related to the two receivers (CAPT and F/O) are shown at the same time. This has no effect on the test or component operation. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the DME1 (DME2) indication.

- the DME1 (DME2) page comes into view.

- push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (page 1 to 2).

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 10s indication comes into view. From 0 to 4s: - on the CAPT and F/O NDs and PFDs: . the DME1(DME2) red warning flag comes into view at the bottom and on the left (right) side then it goes out of view. - on the VOR/ADF/DME RMI: . the left (right) window is blanked. From 4 to 7s: - on the VOR/ADF/DME RMI: . the left (right) window shows white horizontal dashes. From 7 to 10s: - on the VOR/ADF/DME RMI: . the distance of 0.0 comes into view.

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-51-00    CES

 

Page 505 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to On the MCDU: the YES indication. - the TEST OK indication comes into view. - push the line key adjacent to the RETURN indication. R

The test procedure stops.

**ON A/C 251-299, 501-509, 511-526, 528-599, Subtask 34-51-00-740-051-C A. BITE Test of the DME NOTE : The DME and the VOR/DME data come into view on the ND. The ILS/DME ____ data come into view on the PFD. NOTE : During the BITE TEST (DME1 or 2) by the MCDU, the indications ____ related to the two receivers (CAPT and F/O) are shown at the same time. This has no effect on the test or component operation. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the DME1 (DME2) indication.

- the DME1 (DME2) page comes into view.

- push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (page 1 to 2). NOTE : Ignore all the checks to be done ____ on the DDRMI.

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 10s indication comes into view. From 0 to 4s: - on the CAPT and F/O NDs and PFDs:

  R EFF : 106-149, 201-249, 251-299, 301-399,  34-51-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 506 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------. the DME1(DME2) red warning flag comes into view at the bottom and on the left (right) side then it goes out of view. - push the line key adjacent to the YES indication.

On the MCDU: - the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication.

The test procedure stops.

**ON A/C ALL 5. Close-up ________ Subtask 34-51-00-860-055 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (2) On the center pedestal, on the MCDU, push the line key adjacent to the RETURN indication until the MCDU MENU page comes into view. (3) On the RMP, set the ON/OFF switch to OFF. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-51-00   R  CES

 

Page 507 Aug 01/08

TASK 34-51-00-710-001 Operational Test of the DME WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Reception Test of the DME beacon. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-10-00-860-002 34-10-00-860-004 34-10-00-860-005 R R

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power ADIRS Start Procedure IR Alignment Procedure ADIRS Stop Procedure

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-51-00-991-001

Fig. 501

**ON A/C ALL 3. __________ Job Set-up Subtask 34-51-00-860-050 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits. (Ref. TASK 24-41-00-861002) (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

  EFF : ALL  34-51-00    CES

 

Page 508 Feb 01/10

(3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (4) On the EFIS control sections of the FCU: - set the mode selector switches to ROSE or ARC - set the ADF/VOR selector switches to VOR. (5) On the center pedestal, on the RMP1 and RMP2, set the ON/OFF switches to ON. Subtask 34-51-00-865-051 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/DME/1 1SD1 G14 121VU COM NAV/DME/2 1SD2 K06 4. Procedure _________ R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, Subtask 34-51-00-710-055 A. Operational Test of the DME NOTE : The DME and the VOR/DME data come into view on the ND. The ILS/DME ____ data come into view on the PFD. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the RMP1 (RMP2): - set the local frequency of a VOR/DME1 (DME2) or ILS/DME1 (DME2) station (Ref. Fig. 501/TASK 34-51-00991-001)

On the CAPT (F/O) ND for VOR/DME or on the CAPT (F/O) PFD for ILS/DME, the range between the aircraft and the station comes into view at the bottom. On the RMI, the range between the aircraft and the station is also in view.

  EFF : ALL  34-51-00    CES

 

Page 509 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------NOTE : If you set the frequency of an ____ ILS/DME station, DME data are not shown on the RMI. 2. On the center pedestal, on the ACP: - push the VOR1 (VOR2) or ILS pushbutton switch. R

In the loudspeakers, you can hear the Morse code signal from the station set.

**ON A/C 251-299, 501-509, 511-526, 528-599, Subtask 34-51-00-710-055-A A. Operational Test of the DME NOTE : The DME and the VOR/DME data come into view on the ND. The ILS/DME ____ data come into view on the PFD. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the RMP1 (RMP2): - set the local frequency of a VOR/DME1 (DME2) or ILS/DME1 (DME2) station (Ref. Fig. 501/TASK 34-51-00991-001)

On the CAPT (F/O) ND for VOR/DME or on the CAPT (F/O) PFD for ILS/DME, the range between the aircraft and the station comes into view at the bottom.

2. On the center pedestal, on the ACP: - push the VOR1 (VOR2) or ILS pushbutton switch.

In the loudspeakers, you can hear the Morse code signal from the station set.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-51-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 510 Feb 01/10

**ON A/C ALL 5. Close-up ________ Subtask 34-51-00-860-051 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (2) On the RMP, set the ON/OFF switch to OFF. (3) On the ACP, release the VOR1 (VOR2) or ILS pushbutton switch. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-51-00   R  CES

 

Page 511 Aug 01/08

TASK 34-51-00-720-001 Functional Test of the DME WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Make sure that the system operates correctly. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

DME ground test unit

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-10-00-860-002 34-10-00-860-004 34-10-00-860-005 R R

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power ADIRS Start Procedure IR Alignment Procedure ADIRS Stop Procedure

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-51-00-991-001

Fig. 501

  EFF : ALL  34-51-00    CES

 

Page 512 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-51-00-860-052 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Install the DME ground test unit near the DME1 (DME2) antenna. To do this, obey the operating instructions. Set the VOR/DME ground test unit to ON. (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (5) On the EFIS control sections of the FCU, set the mode selector switches to ROSE or ARC. (6) On the FCU, set the ADF/VOR selector switches to VOR. (7) On the center pedestal, on the RMP1 and RMP2, set the ON/OFF selector switches to ON. Subtask 34-51-00-865-054 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 49VU NAV/VOR/DME/RMI

12FN

  EFF : ALL  34-51-00    CES

 

F13

Page 513 Nov 01/08

**ON A/C ALL Subtask 34-51-00-865-055 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/DME/1 1SD1 G14 121VU COM NAV/DME/2 1SD2 K06 4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, 151-199, Subtask 34-51-00-720-050 A. DME Reception and Identification Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the RMP1 (RMP2): - set the VOR/DME1 (VOR/DME2) test frequency of the ground test unit. (Ref. Fig. 501/TASK 34-51-00991-001) 2. On the panel 49VU (121VU) : - close the circuit breaker 1SD1 (1SD2).

On the CAPT and F/O NDs, on the left (right) side: - the DME1 (DME2) flag goes out of view - the horizontal dashs come into view. On the VOR/DME RMI, in the left (right) window: - the horizontal dashs come into view.

3. On the ground test unit, set the IDENT signal on

  EFF : ALL  34-51-00   R  CES

 

Page 514 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------4. On the center pedestal, on one ACP: - push the VOR1 (VOR2) pushbutton switch

You can hear the identification signal in the loudspeaker.

- adjust the volume to the volume you need.

Do the adjustment slowly and continuously .There is no unwanted noise.

- push the ON VOICE pushbutton switch.

The audio signal in the loudspeaker stops.

5. On the ground test unit: - set the IDENT signal off. - set a DME1 (DME2) range of 5 NM.

On the left (right) side of the CAPT and F/O NDs: - the range 5.0 comes into view. On the VOR/DME RMI, in the left (right) window: - the range 5.0 comes into view.

- set a range of 270 NM.

On the ND and the VOR/DME RMI : - the range 270.0 comes into view.

6. On the ground test unit, set the IDENT signal on 7. On the center pedestal, on the ACP: - release the ON VOICE pushbutton switch.

You can hear the audio signal in the loudspeaker.

8. On the center pedestal, on the ATC control unit: - set the ATC master switch to the ON or XPNDR position.

On the CAPT and F/O NDs and the VOR/DME RMI: - the DME1 (DME2) indication does not change.

  EFF : 001-049, 051-099, 101-105, 151-199,  34-51-00   R  CES

 

Page 515 Aug 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------In the loudspeaker : - the audio signal does not change. - set the ATC master switch to the standby position. 9. On the ground test unit, set the IDENT signal off. R

**ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-51-00-720-050-A A. DME Reception and Identification Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the RMP1 (RMP2): - set the VOR/DME1 (VOR/DME2) test frequency of the ground test unit (Ref. Fig. 501/TASK 34-51-00991-001) 2. On the panel 49VU (121VU): - close the circuit breaker 1SD1 (1SD2).

On the CAPT and F/O NDs, on the left (right) side: - the DME1 (DME2) flag goes out of view. - the horizontal dashs come into view. On the VOR/ADF/DME RMI, in the left (right) window: - the horizontal dashs come into view.

3. On the ground test unit, set the IDENT signal on. 4. On the center pedestal, on one ACP:

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-51-00 201-249, 301-399, 401-499,   CES

 

Page 516 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the VOR1 (VOR2) pushbutton You can hear the identification signal switch in the loudspeaker. - adjust the volume to the volume you need.

Do the adjustment slowly and continuously. There is no unwanted noise.

- push the ON VOICE pushbutton switch.

The audio signal in the loudspeaker stops.

5. On the ground test unit, set the IDENT signal off. 6. On the ground test unit: - set a DME1 (DME2) range of 5 NM.

On the left (right) side of the CAPT and F/O NDs: - the range 5.0 comes into view . On the VOR/ADF/DME RMI, in the left (right) window: - the range 5.0 comes into view.

- set a range of 270 NM.

On the ND and the VOR/ADF/DME RMI: - the range 270.0 comes into view.

7. On the ground test unit, set the IDENT signal on. 8. On the center pedestal, on the ACP: - release the ON VOICE pushbutton switch.

You can hear the audio signal in the loudspeaker.

9. On the center pedestal, on the ATC control unit: - set the ATC master switch to the ON or XPNDR position.

On the CAPT and F/O NDs and the VOR/ADF/DME RMI: - the DME1 (DME2) indication does not change. In the loudspeaker :

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-51-00    CES

 

Page 517 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the audio signal does not change. - set the ATC master switch to the standby position. 10. On the ground test unit, set the IDENT signal off. R

**ON A/C 251-299, 501-509, 511-526, 528-599, Subtask 34-51-00-720-050-B A. DME Reception and Identification Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the RMP1 (RMP2): - set the VOR/DME1 (VOR/DME2) test frequency of the ground test unit. (Ref. Fig. 501/TASK 34-51-00991-001) 2. On the panel 49VU (121VU) : - close the circuit breaker 1SD1 (1SD2).

On the CAPT and F/O NDs, on the left (right) side: - the DME1 (DME2) flag goes out of view - the horizontal dashs come into view.

3. On the ground test unit, set the IDENT signal on 4. On the center pedestal, on one ACP: - push the VOR1 (VOR2) pushbutton switch

You can hear the identification signal in the loudspeaker.

  R EFF : 106-149, 201-249, 251-299, 301-399,  34-51-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 518 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- adjust the volume to the volume Do the adjustment slowly and you need. continuously .There is no unwanted noise. - push the ON VOICE pushbutton switch.

The audio signal in the loudspeaker stops.

5. On the ground test unit: - set the IDENT signal off. - set a DME1 (DME2) range of 5 NM.

On the left (right) side of the CAPT and F/O NDs: - the range 5.0 comes into view.

- set a range of 270 NM.

On the ND: - the range 270.0 comes into view.

6. On the ground test unit, set the IDENT signal on 7. On the center pedestal, on the ACP: - release the ON VOICE pushbutton switch.

You can hear the audio signal in the loudspeaker.

8. On the center pedestal, on the ATC control unit: - set the ATC master switch to the ON or XPNDR position.

On the CAPT and F/O NDs: - the DME1 (DME2) indication does not change. In the loudspeaker : - the audio signal does not change.

- set the ATC master switch to the standby position. 9. On the ground test unit, set the IDENT signal off.

  R EFF : 251-299, 501-509, 511-526, 528-599,  34-51-00    CES

 

Page 519 Feb 01/10

**ON A/C ALL 5. Close-up ________ Subtask 34-51-00-860-053 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (2) On the center pedestal, on the RMP, set the ON/OFF switch to OFF. (3) De-energize the DME ground test unit. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-51-00   R  CES

 

Page 520 Aug 01/08

ANTENNA - DME (3SD1,3SD2) - REMOVAL/INSTALLATION ________________________________________________ TASK 34-51-11-000-002 Removal of the DME Antenna (3SD1, 3SD2) WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) nonmetallic scraper

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-51-11-991-002

Fig. 401

  EFF : ALL  34-51-11    CES

 

Page 401 Feb 01/98

3. __________ Job Set-up Subtask 34-51-11-865-052 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3SD1 49VU NAV/DME/1 1SD1 G14 FOR 3SD2 121VU COM NAV/DME/2 1SD2 K06 4. Procedure _________ (Ref. Fig. 401/TASK 34-51-11-991-002) Subtask 34-51-11-020-050 A. Removal of the DME Antenna (1) Remove the sealant from the heads of the screws (5) with a nonmetallic scraper. (2) Remove the screws (5). (3) Put the antenna (4) away from the fuselage (1). (4) Disconnect the coaxial connector (2). (5) Remove the antenna (4). (6) Put blanking caps on the disconnected coaxial connectors (2) and (3). (7) Remove and discard the O-ring seal (6).

  EFF : ALL  34-51-11    CES

 

Page 402 Feb 01/98

DME Antenna Figure 401/TASK 34-51-11-991-002   EFF : ALL  34-51-11    CES

 

Page 403 Feb 01/98

TASK 34-51-11-400-002 Installation of the DME Antenna (3SD1, 3SD2) WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN. _______ IF YOU DO: - RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH - WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

lint-free cloth masking tape nonmetallic scraper

  EFF : ALL  34-51-11    CES

 

Page 404 Feb 01/98

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 05-013

D TV-53-3507/73 RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)

Material No. 07-001B R Material No. 09-008 Material No. 09-016 Material No. 09-019 Material No. 11-003 Material No. 16-003

ELECTRICAL BOND VARNISH (Ref. 20-31-00) USA MIL-S-8802 CLASS A NO LONGER AVAILABLE (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) USA AMS 3267/3 NO LONGER AVAILABLE (Ref. 20-31-00) USA ASTM D 740 METHYL-ETHYL-KETONE (Ref. 20-31-00) F ASNB70720 COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------6

O-ring seal

34-51-11 01 -010

D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-912-005 34-51-00-710-001 34-51-00-720-001 51-76-11-300-001 34-51-11-991-002

Electrical Bonding of Antennas With Conductive Bolts. Operational Test of the DME Functional Test of the DME Repair of the Sealing Fig. 401

  EFF : ALL  34-51-11    CES

 

Page 405 Feb 01/09

3. __________ Job Set-up Subtask 34-51-11-865-053 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3SD1 49VU NAV/DME/1 1SD1 G14 FOR 3SD2 121VU COM NAV/DME/2 1SD2 K06 4. Procedure _________ (Ref. Fig. 401/TASK 34-51-11-991-002) WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE THE SPECIAL _______ MATERIAL. THIS MATERIAL IS DANGEROUS. Subtask 34-51-11-420-050 R

A. Installation of the DME Antenna (1) Remove the used sealant from the fuselage with CLEANING AGENTS (Material No. 11-003) and a nonmetallic scraper. NOTE : If you install the same antenna it is necessary to clean it ____ with a lint-free cloth. (2) Do an inspection of the component interface and/or the adjacent area. NOTE : Make sure that the antenna attachment screw-head recesses have ____ no signs of paint, corrosion or sealant because the antenna electrical bonding is made through the attachment screws. (3) Apply masking tape to the structure (1), the edge of the antenna (4), the screw holes and the hole for the antenna connector.

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Page 406 Aug 01/08

(4) Apply SPECIAL MATERIALS (Material No. 05-013) on the antenna (4) mount and on the fuselage (1). (5) Apply SEALANTS (Material No. 09-019) on the antenna (4) mount and on the fuselage (1) (Ref. TASK 51-76-11-300-001). NOTE : Make sure that there is no sealant in the screw holes. ____ (6) Remove the blanking caps from the coaxial connectors (2) and (3). (7) Install the new O-ring seal (6). (8) Connect the coaxial connector (2) to the antenna (4). (9) Put the antenna (4) in position on the fuselage (1). (10) Attach the antenna (4) with the screws (5). (11) Remove the sealant which is not necessary with a nonmetallic scraper. (12) Make sure that the bonding contact resistance between the antenna (4) and the fuselage structure (1) is not higher than 5 milliohms (Ref. TASK 20-28-00-912-005). R R R

(13) Apply a sealing bead with SEALANTS (Material No. 09-016) or use as an alternative SEALANTS (Material No. 09-008) around the antenna (4) (Ref. TASK 51-76-11-300-001).

R R

(14) Apply SEALANTS (Material No. 09-016) or use as an alternative SEALANTS (Material No. 09-008) on the heads of the screws (5). (15) Make the contour of the screws (5) and the antenna (4) smooth. (16) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the base of the antenna (4). (17) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001B) to the sealant on the head of the screws (5). NOTE : It is not mandatory to paint the sealant around the base of ____ the antenna and on the head of the screws.

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Page 407 Aug 01/08

Subtask 34-51-11-865-054 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 3SD1 1SD1 FOR 3SD2 1SD2 Subtask 34-51-11-720-050 C. Do the functional test of the DME with tool (Ref. TASK 34-51-00-720-001) or the operational test of the DME without tool (Ref. TASK 34-51-00-710001). 5. Close-up ________ Subtask 34-51-11-410-050 A. Make sure that the work area is clean and clear of tool(s) and other items.

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Page 408 Aug 01/07

INTERROGATOR - DME (2SD1,2SD2) - REMOVAL/INSTALLATION _____________________________________________________ TASK 34-51-33-000-001 Removal of the DME Interrogator (2SD1,2SD2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-51-33-991-001

Fig. 401

3. __________ Job Set-up Subtask 34-51-33-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 2SD1 49VU NAV/DME/1 1SD1 G14 FOR 2SD2 121VU COM NAV/DME/2 1SD2 K06

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Page 401 Feb 01/98

Subtask 34-51-33-010-050 B. Get Access (1) Put the access platform in position at the access door 824 in zone 128. (2) Open the access door 824. 4. Procedure _________ (Ref. Fig. 401/TASK 34-51-33-991-001) Subtask 34-51-33-020-050 A. Removal of the DME Interrogator (1) Loosen the nuts (4). (2) Lower the nuts (4). (3) Pull the DME interrogator (1) on its rack (3) to disconnect the electrical connectors (2). (4) Remove the DME interrogator (1) from its rack (3). (5) Put blanking caps on the disconnected electrical connectors (2).

  EFF : ALL  34-51-33    CES

 

Page 402 Feb 01/98

DME Interrogator Figure 401/TASK 34-51-33-991-001   EFF : ALL  34-51-33    CES

 

Page 403 Feb 01/98

TASK 34-51-33-400-001 Installation of the DME Interrogator (2SD1,2SD2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R

34-51-00-710-001 52-41-00-410-002 34-51-33-991-001

Operational Test of the DME Close the Avionics Compartment Doors after Access Fig. 401

3. __________ Job Set-up Subtask 34-51-33-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at the access door 824 in zone 128. (2) Make sure that the access door 824 is open.

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Page 404 Feb 01/02

Subtask 34-51-33-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 2SD1 49VU NAV/DME/1 1SD1 G14 FOR 2SD2 121VU COM NAV/DME/2 1SD2 K06 4. Procedure _________ (Ref. Fig. 401/TASK 34-51-33-991-001) Subtask 34-51-33-420-050 A. Installation of the DME Interrogator (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (2). (4) Make sure that the electrical connectors (2) are clean and in the correct condition. (5) Install the DME interrogator (1) on its rack (3). (6) Push the DME interrogator (1) on its rack (3) to connect the electrical connectors (2). (7) Engage the nuts (4) on the lugs (5) and tighten. Subtask 34-51-33-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 2SD1 1SD1 FOR 2SD2 1SD2

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Page 405 Feb 01/98

Subtask 34-51-33-710-050 C. Do the operational test of the DME (Ref. TASK 34-51-00-710-001). 5. Close-up ________ Subtask 34-51-33-860-051 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 34-51-33-410-050 B. Close Access R

(1) Close the access door 824 (Ref. TASK 52-41-00-410-002). (2) Remove the access platform(s).

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Page 406 Feb 01/02

ATC/MODE S (SELECT) - DESCRIPTION AND OPERATION _______________________________________________ R

1. General _______ **ON A/C 001-049, 101-105, 151-199, 201-220, The Air Traffic Control (ATC) system is based on the replies provided by the airborne transponders in response to interrogations from the ATC secondary radar. The ground ATC secondary radar uses technics which provide the air traffic control with information that cannot be acquired by the primary radar. This system enables to distinguish between aircraft and to maintain effective ground surveillance of the air traffic. The system provides the air traffic controllers with : - Mode A : transmission of aircraft identification or, - Mode C : transmission of aircraft barometric altitude or, - Mode S : aircraft selection and transmission of flight data for the ground surveillance. The mode S is fully compatible with the other modes, A and C. The mode S bas been designed as an evolutionary addition to the ATC system to provide the enhanced surveillance and communication capability required for air traffic control automation. NOTE : The ATC/mode S will be able to provide the Traffic Collision ____ Avoidance System (TCAS) with the aircraft address. **ON A/C 051-099, The Air Traffic Control (ATC) system is based on the replies provided by the airborne transponders in response to interrogations from the ATC Secondary Surveillance Radar (SSR). The ground ATC secondary radar uses technics which provide the air traffic control with information that cannot be acquired by the primary radar. This system serves to distinguish between aircraft and to maintain effective ground surveillance of the air traffic. The system provides the air traffic controllers with: - Mode A: transmission of aircraft identification (code number) - Mode C: transmission of aircraft barometric altitude - Mode S: selective calling. The ATC/Mode S transponder receives interrogations from: . Mode S and SSR ground stations . TCAS-equipped aircraft (the Mode S transponder transmits TCAS data from another TCAS-equipped aircraft to its own TCAS computer if installed).

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Page 1 Aug 01/05

Additional to earlier Air Traffic Control Radar Beacon System (ATCRBS) transponders, the Mode S transponder is capable of providing enhanced surveillance (capability to send and receive data link messages). The minimum data link transponder supports all surveillance functions, in addition to bidirectional air-to-air data exchange, ground-to-air data uplink (COMM A), air-to-ground data dowlink (COMM B), and multisite message protocol. In addition, the transponder is capable of receiving Extended Length Messages (ELMs) from the ground. ELMs are received in the COMM C format. ELM transmittals to the ground use the COMM D format. NOTE : The ATC is a level 4 transponder. ____ The transponder is capable of processing COMM A/B/C/D data link messages and can be interfaced to an external Mode S Airborne Data Link Processor (ADLP). The transponder has the ability to be upgraded to a level 5 transponder with an internal ADLP function. Each (ATC Mode S-equipped) aircraft has its own Mode S address. This address (24-bit) is included in all Mode S transmissions, so that every interrogation can be directed to a specific aircraft, preventing multiple replies. Also, answers are unequivocal from only one specific aircraft. If the discrete address is included in an interrogation, the discrete address is also a part of the reply. This is especially important for use in conjunction with TCAS. For SSR interrogations, the transponder transmits the selectable code number (Mode A) or the barometric altitude (Mode C) if required. For SSR/Mode S all call interrogations, the transponder transmits the same information. NOTE : The transponder contains data link capabilities, in addition to Mode ____ S specific services, to function as part of the aircraft telecommunications network. The transponder has the capability of interfacing to a Global Positioning System (GPS) to provide differential GPS operation. The transponder is designed with upgrade-ability to meet future requirements which result from Future Air Navigation System (FANS) and aircraft telecommunication network definitions and enhancements. R

**ON A/C 106-149, 221-249, 301-399, 401-499, The Air Traffic Control (ATC) system is based on the replies provided by the airborne transponders in response to interrogations from the ATC Secondary Surveillance Radar (SSR). The ground ATC secondary radar uses technics which provide the air traffic control with information that cannot be acquired by the primary radar.

  R EFF : 051-099, 106-149, 221-249, 301-399,  34-52-00 401-499,   CES

 

Page 2 Nov 01/08

This system serves to distinguish between aircraft and to maintain effective ground surveillance of the air traffic. The system provides the air traffic controllers with : - Mode A: transmission of aircraft identification (code number) - Mode C: transmission of aircraft barometric altitude - Mode S: aircraft selective calling and transmission of flight data for the ground surveillance. The mode S is fully compatible with the other modes, A and C. The mode S has been designed as an evolutionary addition to the ATC system to provide the enhanced surveillance and communication capability required for air traffic control automation. Each (ATC Mode S-equipped) aircraft has its own Mode S address. This address (24-bit) is included in all Mode S transmissions, so that every interrogation can be directed to a specific aircraft, preventing multiple replies. Also, answers are unequivocal from only one specific aircraft. If the discrete address is included in an interrogation, the discrete address is also a part of the reply. This is especially important for use in conjunction with TCAS. NOTE : The ATC/mode S will be able to provide the Traffic Collision ____ Avoidance System (TCAS) with the aircraft address. For SSR interrogations, the transponder transmits the selectable code number (Mode A) or the barometric altitude (Mode C) if required. For SSR/Mode S all call interrogations, the transponder transmits the same information. In addition, new functionalities are required for ATC/Mode S transponders: - elementary surveillance (mandatory in Europe after March 31, 2003), - enhanced surveillance (mandatory in Europe after March 31, 2005). The transponder meets the requirements for elementary surveillance and has the capability for enhanced surveillance (ref. para. 6.A.(3).). It can also transmit extended squitters. Enhanced surveillance parameters and extended squitters are transmitted if the wiring provisions for enhanced surveillance are installed. Moreover, the following functionalities are available: - com A/B: capability to receive ground to air data uplink (com A) and to transmit air to ground data downlink (com B) in addition to bidirectional data exchange - com C: capability to receive Extended Length Messages (ELM) It also incorporates the following improvements: - it has interface characteristics in compliance with ARINC 718A. - as a Mark IV transponder, this transponder needs additional wiring to perform enhanced surveillance and extented squitters functions. If this wiring is not installed, the transponder will operate as a Mark III transponder. In this case, nor enhanced surveillance parameters neither extented squitters are available. - its software is fully loadable.

  R EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00    CES

 

Page 3 Nov 01/08

The transponder is a level 3 transponder since it is capable of processing com A/B/C/ data link messages. R

**ON A/C 251-299,

R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R

The Air Traffic Control (ATC) system is based on the replies provided by the airborne transponders in response to interrogations from the ATC Secondary Surveillance Radar (SSR). The ground ATC secondary radar uses technics which provide the air traffic control with information that cannot be acquired by the primary radar. This system serves to distinguish between aircraft and to maintain effective ground surveillance of the air traffic. The system provides the air traffic controllers with : - Mode A: transmission of aircraft identification (code number) - Mode C: transmission of aircraft barometric altitude - Mode S: selective calling. The ATC/Mode S transponder receives interrogations from: . Mode S and SSR ground stations . TCAS-equipped aircraft (the Mode S transponder transmits TCAS data from another TCAS-equipped aircraft to its own TCAS computer). Each (ATC Mode S-equipped) aircraft has its own Mode S address. This address (24-bit) is included in all Mode S transmissions, so that every interrogation can be directed to a specific aircraft, preventing multiple replies. Also, answers are unequivocal from only one specific aircraft. If the discrete address is included in an interrogation, the discrete address is also a part of the reply. This is especially important for use in conjunction with TCAS. For SSR interrogations, the transponder transmits the selectable code number (Mode A) or the barometric altitude (Mode C) if required. For SSR/Mode S all call interrogations, the transponder transmits the same information. In addition, new functionalities are required for ATC/Mode S transponders: - elementary surveillance (mandatory after 31 March 2003), - enhanced surveillance (mandatory after 31 March 2005). The transponder meets the requirements for elementary surveillance and has the capability for enhanced surveillance (Ref. para. 6.A.(3).). It can also transmit extended squitters. Enhanced surveillance parameters and extended squitters are transmitted if the modification related to enhanced surveillance/extended squitters is embodied. This modification consists in connecting avionics peripherals (IR, FCU, ATSU) to the transponder. Moreover, the following functionalities are available: - com A/B: capability to receive ground to air data uplink (com A) and to transmit air to ground data downlink (com B) in addition to bidirectional data exchange

  R EFF : 106-149, 221-249, 251-299, 301-399,  34-52-00 401-499,   CES

 

Page 4 May 01/09

- com C: capability to receive Extended Length Messages (ELM) if an external Data Link Processor (DLP) is installed - com D: capability to transmit ELMs if an external DLP is installed. It also incorporates the following improvements: - it has interface characteristics in compliance with ARINC 718A - it is backward compatible with Mark III transponders (Arinc 718-4) installations - its software is fully loadable. The transponder is a level 4 transponder since it is capable of processing com A/B/C/D data link messages. In addition, it has the capability to be upgraded to a level 5 transponder with an internal Airborne Data Link Processor (ADLP) (software change only) (level 4 plus enhanced protocol for parallel processing of com A/B, up and downlink ELMs). R

**ON A/C 501-509, 511-526, 528-599, The Air Traffic Control (ATC) system is based on the replies provided by the airborne transponders in response to interrogations from the ATC Secondary Surveillance Radar (SSR). The ground ATC secondary radar uses technics which provide the air traffic control with information that cannot be acquired by the primary radar. This system serves to distinguish between aircraft and to maintain effective ground surveillance of the air traffic. The system provides the air traffic controllers with : - Mode A: transmission of aircraft identification (code number) - Mode C: transmission of aircraft barometric altitude - Mode S: selective calling. The ATC/Mode S transponder receives interrogations from: . Mode S and SSR ground stations . TCAS-equipped aircraft (the Mode S transponder transmits TCAS data from another TCAS-equipped aircraft to its own TCAS computer). Each (ATC Mode S-equipped) aircraft has its own Mode S address. This address (24-bit) is included in all Mode S transmissions, so that every interrogation can be directed to a specific aircraft, preventing multiple replies. Also, answers are unequivocal from only one specific aircraft. If the discrete address is included in an interrogation, the discrete address is also a part of the reply. This is especially important for use in conjunction with TCAS. For SSR interrogations, the transponder transmits the selectable code number (Mode A) or the barometric altitude (Mode C) if required. For SSR/Mode S all call interrogations, the transponder transmits the same information. In addition, new functionalities are required for ATC/Mode S transponders: - elementary surveillance (mandatory in Europe after 31 March , 2003), - enhanced surveillance (mandatory in Europe after 31 March , 2005).

  R EFF : 251-299, 501-509, 511-526, 528-599,  34-52-00    CES

 

Page 5 Feb 01/10

The transponder meets the requirements for elementary surveillance and has the capability for enhanced surveillance (Ref. para. 6.A.(3).). It can also transmit extended squitters. Enhanced surveillance parameters and extended squitters are transmitted if the modification related to enhanced surveillance/extended squitters is embodied. This modification consists in connecting avionics peripherals (IR, FCU, ATSU) to the transponder. Moreover, the following functionalities are available: - com A/B: capability to receive ground to air data uplink (com A) and to transmit air to ground data downlink (com B) in addition to bidirectional data exchange It also incorporates the following improvements: - it has interface characteristics in compliance with ARINC 718A - it is backward compatible with Mark III transponders (Arinc 718-4) installations - its software is not loadable. The transponder is a level 2 transponder since it is capable of processing com A/B data link messages. **ON A/C ALL 2. Component __________________ Location (Ref. Fig. 001) ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1SH1 XPDR-ATC/MODE S, 1 81VU 127 824 34-52-33 1SH2 XPDR-ATC/MODE S, 2 82VU 128 824 34-52-33 7SH1 ANTENNA-ATC BOTTOM, 1 127 34-52-11 7SH2 ANTENNA-ATC BOTTOM, 2 128 34-52-11 7SH3 ANTENNA-ATC TOP, 1 224 34-52-11 7SH4 ANTENNA-ATC TOP, 2 223 34-52-11 3SH CTL UNIT-ATC/TCAS 11VU 211 831 34-52-12 3. __________________ System Description R

**ON A/C 001-049, 101-105, 151-199, 201-220, 501-509, 511-526, 528-599, A. Principle (Ref. Fig. 002) An airborne transponder provides coded reply signals in response to interrogation signals from the ground secondary radar and from aircraft which will be eventually equipped with the TCAS.

  EFF : ALL  34-52-00    CES

 

Page 6 Feb 01/10

ATC - Component Location Figure 001   EFF : ALL  34-52-00   R  CES

 

Page 7 May 01/09

ATC - Principle Figure 002   R EFF : ALL  34-52-00    CES

 

Page 8 May 01/09

This ground interrogation is transmitted in the form of pair of pulses P1 and P3 for the mode A or C and in the form of pulses P1, P3 and P4 for the mode S. The decoding of the time between the interrogation pulses determines the operating mode of the transponder : - mode A (identification) - mode C (altitude range) - mode S (flight data) The interrogation frequency is 1030 MHz. The reply frequency is 1090 MHz. The system is provided with four antennas : - two antennas are located at the upper part of the fuselage - two antennas are located at the lower part of the fuselage. According to the aircraft configuration, the transponder selects the antennas (lower or upper) which receive the best transmission signal from the ground ATC secondary radar. **ON A/C 051-099, 251-299, A. Principle (Ref. Fig. 002) An airborne transponder provides coded reply signals in response to interrogation signals from the ground secondary radar and from aircraft which is equipped with the TCAS. The ATC/Mode S system has the capability for Modes A, C and S. Mode A: identification Mode C: altitude range Mode S: In a Mode S environment, the transponder responds to ATCRBS-formatted interrogations with ATCRBS-formatted replies, but, in addition, it can be discretely addressed directly by Mode S interrogators. Discrete addressing means that only the specifically addressed Mode S transponder replies. Top and bottom antennas and associated antenna switching and signal processing features provide the Diversity Antenna features that allow compatibility with TCAS II. The diversity antenna allows selection of signal receptions from either the top or the bottom antenna based on the characteristics of the received interrogation signals. This improves air-to-air surveillance and communication. The ATC/Mode S transponder, is also used in collision avoidance (if TCAS installed). In this role, the transponder performs as an ATCRBS and Mode S transponder for ATC requirements, while simultaneously serving as an integral part of TCAS. The Mode S transponder has two basic functions related to TCAS: (1) Approximately every second, a Mode S transponder makes a transmission known as squitter. These transmissions alternate between the top and bottom Mode S antennas. Squitter is coded with the aircraft Mode S address and equipment capabilities. A ground station and airborne TCAS

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-52-00 201-220, 251-299, 501-509, 511-526, 528-599,   CES

 

Page 9 Feb 01/10

listen for squitter as the initial indication that a Mode S-equipped aircraft has entered the surveillance area. (2) The communication between two TCAS-equipped aircraft occurs from the TCAS antenna of one aircraft to the Mode S transponder antenna of the other aircraft. Aboard the TCAS-equipped aircraft, data received by the Mode S transponder is passed to a TCAS computer, and the TCAS computer determines the content of reply messages. The Mode S reply includes the flight number transmitted by the Flight Management and Guidance Computer (FMGC). The ATC system operates with two frequencies: - interrogation: 1030 MHz - reply: 1090 MHz Modes A, C and All call interrogations are transmitted in the form of coded pulses PPM (Pulse Position Modulation). An All call interrogation is an interrogation which generates Mode A or C and Mode S replies. The transponder contains data link capability, which allows it to receive uplink messages and uplink extended length messages. The transponder can transmit Downlink Messages and Downlink Extended Length Messages (DELM). The transmitter has the capability of transmitting sets of 16 segment DELMs at a rate of 8 per second. **ON A/C 106-149, 221-249, 301-399, 401-499, A. Principle (Ref. Fig. 002) An airborne transponder provides coded reply signals in response to interrogation signals from the ground secondary radar and from aircraft which is equipped with the TCAS. The ATC/Mode S system has the capability for Modes A, C and S. Mode A: identification Mode C: altitude range Mode S: In a Mode S environment, the transponder responds to ATCRBS-formatted interrogations with ATCRBS-formatted replies, but, in addition, it can be discretely addressed directly by Mode S interrogators. Discrete addressing means that only the specifically addressed Mode S transponder replies. Top and bottom antennas and associated antenna switching and signal processing features provide the Diversity Antenna features that allow compatibility with TCAS II. The diversity antenna allows selection of signal receptions from either the top or the bottom antenna based on the characteristics of the received interrogation signals. The transponder selects the antennas (lower or upper) which receive the best transmission signal from the ground ATC secondary radar . This improves air-to-air surveillance and communication. The ATC/Mode S transponder, is also used in collision avoidance. In this role, the transponder performs as an ATCRBS and Mode S

  R EFF : 051-099, 106-149, 221-249, 251-299,  34-52-00 301-399, 401-499,   CES

 

Page 10 May 01/09

transponder for ATC requirements, while simultaneously serving as an integral part of TCAS. The Mode S transponder has two basic functions related to TCAS: (1) Approximately every second, a Mode S transponder makes a transmission known as squitter. These transmissions alternate between the top and bottom Mode S antennas. Squitter is coded with the aircraft Mode S address and equipment capabilities. A ground station and airborne TCAS listen for squitter as the initial indication that a Mode S-equipped aircraft has entered the surveillance area. (2) The communication between two TCAS-equipped aircraft occurs from the TCAS antenna of one aircraft to the Mode S transponder antenna of the other aircraft. Aboard the TCAS-equipped aircraft, data received by the Mode S transponder is passed to a TCAS computer, and the TCAS computer determines the content of reply messages. The Mode S reply includes the flight number transmitted by the Flight Management and Guidance Computer (FMGC). The ATC system operates with two frequencies: - interrogation: 1030 MHz - reply: 1090 MHz Modes A, C and All call interrogations are transmitted in the form of coded pulses PPM (Pulse Position Modulation). An All call interrogation is an interrogation which generates Mode A or C and Mode S replies. The transponder contains data link capability, which allows it to receive uplink messages and uplink extended length messages. The transponder can transmit downlink messages. **ON A/C ALL B. System Architecture **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, (Ref. Fig. 003) R R

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 003A) **ON A/C ALL The ATC comprises two independent systems. Each system consists of: - one transponder 1SH1 (1SH2),

  EFF : ALL  34-52-00    CES

 

Page 11 Feb 01/10

ATC - Block Diagram Figure 003   R EFF : 001-049, 051-099, 101-105, 151-199,  34-52-00 201-220,   CES

 

Page 12 May 01/09

ATC - Block Diagram Figure 003A   R EFF : 106-149, 221-249, 251-299, 301-399,  34-52-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 13 Feb 01/10

- two antennas 7SH1,7SH3 (7SH2,7SH4), - one ATC/TCAS control unit 3SH common to the two systems. In addition, the Centralized Fault-Display Interface-Unit (CFDIU) 1TW enables access to the maintenance part of the ATC system through one Multipurpose Control and Display Unit (MCDU) 3CA1 (3CA2). (Ref. Fig. 004) C. Warning The warning related to the ATC is only the FAULT or FAIL indicator light of the ATC control unit : when the system is faulty, the amber FAULT or FAIL indicator light comes on. 4. Power ____________ Supply Energization of each system is through : - 115VAC ESS BUS SHEDDABLE 801XP via circuit breaker 5SH1 for system 1. - 115VAC BUS 2 204XP via circuit breaker 5SH2 for system 2. Energization of the ATC control unit is through the two circuit breakers 5SH1 and 5SH2. ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07 R R

**ON A/C 051-099, 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 5. Interface _________ **ON A/C 051-099, (Ref. Fig. 003) Two types of ARINC signals, ARINC 429 and ARINC 575, provide a two-way interface between the transponder and other aircraft systems. The ARINC 429 signals consist of 32-bit data words. The first 8 bits of the word make up a label which specifies the type of information contained in that word. The ARINC 429 buses provide the following information: - control data input - air data input 1 and 2 - maintenance data. The low-speed 429 buses are repetitive buses that provide the transponder interfaces between: - control panel - altitude information from the ADIRUs

  EFF : ALL  34-52-00    CES

 

Page 14 Feb 01/10

ATC - Control & Indicating Figure 004   R EFF : ALL  34-52-00    CES

 

Page 15 May 01/09

- CFDIU. The high-speed 429 buses permit the transfer of data between the transponder and the TCAS (if installed). A. Control Panel Buses Control panel labels which are received from the tuning transmitted to the TCAS as periodic labels. Only labels received from the control panel are transmitted without the TCAS, however the transponder must receive at least operational.

source are which are modification to label 016 to be

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 013 |CTL WORD 1| | | | | | | | | 015 |CTL WORD 2| | | | | | | | | 016 |CTL WORD 3| | | | | | | | | 031 |CTL WORD 4| | | | | | | | ------------------------------------------------------------------------------NOTE : CTL WORD 1: TCAS display mode and range control information ____ CTL WORD 2: TCAS altitude limit control information CTL WORD 3: transponder and TCAS control information CTL WORD 4: transponder control information, and is designed for interface with older ATCRBS control panels.

  EFF : 051-099,  34-52-00   R  CES

 

Page 16 May 01/09

B. Transponder Buses (1) TCAS interface Data between the transponder and the TCAS are transferred on two unidirectional buses. These buses are high-speed ARINC 429 buses. (2) ADIRU interface The transponder receives inputs from two ADIRUs. Air data 1 and Air data 2 supply the transponder with barometric altitude data. (3) CFDIU interface The Centralized Fault Display Interface Unit (CFDIU) bus consists of two low-speed ARINC 429 buses, one in each direction. (4) FMGC interface The transponder receives flight identification on an ARINC 429 low-speed bus in four labels. The Flight identification may be transmitted to the ground.

  EFF : 051-099,  34-52-00   R  CES

 

Page 17 May 01/09

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| 125 |TIME | | | | | |BCD | | | | 126 |FLIGHT | | | | | |BNR | | | | |PHASE | | | | | | | | | | 155 |AIRCRAFT | | | | | |DISC| | | | |CONFIGURA | | | | | | | | | | |TION | | | | | | | | | | 271 |WORD 1 | | | | | |DISC| | | | 272 |WORD 2 | | | | | |DISC| | | | 273 |WORD 3 | | | | | |DISC| | | | 203 |WORD 4 | | | | | |BCD | | | | 275 |WORD 5 | | | | | |DISC| | | | 276 |WORD 6 | | | | | |DISC| | | | 277 |WORD 7 | | | | | |DISC| | | | 274 |WORD 8 | | | | | |DISC| | | | 350 |MAINTENAN | | | | | |DISC| | | | |CE | | | | | | | | | | 356 |BITE | | | | | |N/A | | | | |STATUS | | | | | | | | | | | | | | | | | | | | | 233-236 |FLIGHT | | | | | |BNR | | | | |NUMBER | | | | | | | | | | |STATUS | | | | | | | | | ------------------------------------------------------------------------------NOTE : WORD ____ WORD WORD WORD WORD WORD WORD WORD

1: 2: 3: 4: 5: 6: 7: 8:

TCAS broadcast coordination data 1 TCAS broadcast coordination data 2 Mode S ground uplink sensitivity level command Baro corrected altitude Mode S address part 1 Mode S address part 2 Acknowledgement of non periodic message TCAS broadcast coordination data

  R EFF : 051-099,  34-52-00    CES

 

Page 18 May 01/09

R R

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, The ARINC 429 signals provide a two-way interface between the transponder and other aircraft systems. The ARINC 429 signals consist of 32-bit data words. The first 8 bits of the word make up a label which specifies the type of information contained in that word. The ARINC 429 buses provide the interfaces with: - The Traffic Collision Avoidance System (TCAS) computer - The Air Data and Inertial Reference Units (ADIRUs, ADC and IRS) - The Centralized Fault Display Interface Unit (CFDIU) - The Flight Management and Guidance Computer (FMGC) - The Flight Control Unit (FCU) - The ATC/TCAS Control Panel NOTE : MMR/ATC link, ATSU/ATC link, FCU/ATC link and ADIRU (IR ____ part)/ATC link are installed if the optional wiring provisions for enhanced surveillance/extended squitters are validated. No data are currentlty transmitted on ATSU/ATC link; MMR /ATC link are provisions only. A. Transponder Input Data ---------------------------------------------------------------------------| SOURCE | LABEL | PARAMETER | ---------------------------------------------------------------------------| ATC/TCAS | 013 | TCAS display control | | control panel | 015 | Display altitude | | | 016 | TCAS/ATC control | | | 031 | ATCRBS control | | | disc | STBY/ON | | | disc | Air/Ground | -----------------|---------------------------------------------------------| TCAS | 273 | Tx word 1 | | | 274 | Tx word 2 | | | 275 | Tx word 3 | ---------------------------------------------------------------------------| FCU | 102 | Selected Altitude | ---------------------------------------------------------------------------| CFDIU | 227 | Command to systems | | | 125 | GMT | | | 260 | Date | | |233 to 236| Flight number | | |040 to 042| City pair | | |301 to 304| A/C ident | | | 126 | Flight phase |

  R EFF : 106-149, 221-249, 251-299, 301-399,  34-52-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 19 Feb 01/10

---------------------------------------------------------------------------| SOURCE | LABEL | PARAMETER | ---------------------------------------------------------------------------| |155 to 157| A/C configuration | ---------------------------------------------------------------------------| ADIRU | 310 | Latitude present position | | (IR part) | 311 | Longitude present position | | | 312 | Ground speed | | | 313 | True track angle | | | 320 | Magnetic heading | | | 325 | Roll angle | | | 335 | Track angle rate | | | 365 | Inertial vertical velocity | | | 366 | N/S velocity | | | 367 | E/W velocity | | | 076 | GNSS alt | | | 103 | GNSS track angle | | | 110 | GNSS latitude coarse | | | 111 | GNSS longitude coarse | | | 112 | GNSS ground speed | | | 120 | GNSS latitude fine | | | 121 | GNSS longitude fine | | | 130 | Autonomous Hill | | | 150 | Time | | | 165 | GNSS vertical velocity | | | 166 | GNSS N/S velocity | | | 174 | GNSS E/W velocity | | | 247 | Horizontal figure of merite | ---------------------------------------------------------------------------| ADIRU | 203 | Altitude barometric | | (ADR part) | 205 | Mach | | | 206 | Computed airspeed | | | 210 | True airspeed | | | 212 | Altitude rate barometric | | | 234 | Baro correction | ---------------------------------------------------------------------------| FMS | 233 | Flight number word 1 | | | 234 | Flight number word 2 | | | 235 | Flight number word 3 | | | 236 | Flight number word 4 | | | 310 | Latitude present position | | | 311 | Longitude present position | ----------------------------------------------------------------------------

  R EFF : 106-149, 221-249, 251-299, 301-399,  34-52-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 20 Feb 01/10

B. Transponder output buses ---------------------------------------------------------------------------| DESTINATION | LABEL | PARAMETER | ---------------------------------------------------------------------------| TCAS | 271 | TCAS coordination data 1 | | | 272 | TCAS coordination data 2 | | | 273 | Mode S ground uplink | | | 203 | Barometric altitude | | | 275 | Mode S adress part 1 | | | 276 | Mode S adress part 2 | | | 277 | Acknowledgement | | | 274 | Lock confirmation | | | 204 | Baro corrected altitude | | | 013 | TCAS display control | | | 015 | Display altitude limit | | | 016 | TCAS/ATC control | | | 210 | Airspeed | | | 212 | Altitude rate | | | 350 | Maintenance word | ---------------------------------------------------------------------------| CFDIU | 356 | Normal mode | ---------------------------------------------------------------------------**ON A/C ALL 6. _____________________ Component Description **ON A/C 001-049, 101-105, 151-199, A. ATC Transponder (1) External description (Ref. Fig. 005) The face of the transponder is fitted with a handle, two attaching parts, a TEST pushbutton switch and ten LEDs. The name, color and function of the ten LEDs are as follows: - TPR (green) indicates that no faults are detected during the reply - TPR (red) indicates fault of ATC function - ANT TOP (red) indicates that the top antennas are incorrectly connected or are failed - ANT BOT (red) indicates that the bottom antennas are incorrectly connected or are failed - ALT (red) indicates that the altitude is not in correct format

  R EFF : ALL  34-52-00    CES

 

Page 21 May 01/09

ATC - Transponder Figure 005   R EFF : 001-049, 101-105, 151-199, 501-509,  34-52-00 511-526, 528-599,   CES

 

Page 22 Feb 01/10

- DATA IN (red) indicates that the data input is not in correct format - TCAS (red) indicates that the data input from the TCAS is abnormal - MAINTENANCE (red) indicates that the maintenance data are abnormal - RESERVED (red) are reserved for future use. The back of the transponder contains an ARINC 600, shell size connector to provide electrical connections to the aircraft wiring via mount. Contact grouping is as follows: - Top contact set - ATE interface - Center contact set - System interconnections - Bottom contact set - Power supply and bonding. (2) Not Applicable R

**ON A/C 051-099, 251-299, A. ATC Transponder (1) External description (Ref. Fig. 005A) The face of the transponder is fitted with a handle, two attaching parts, a PUSH TO TEST pushbutton switch, six LEDs and a DATA LOADER plug. The PUSH TO TEST pushbutton switch is used to initiate the LED test and transponder self-test. All LEDs are on for approximately three seconds following self-test initiation. After three seconds, the front panel LEDs indicate the current condition of the unit. If the PUSH TO TEST pushbutton switch is not pushed again, the LEDs go off. If the PUSH TO TEST pushbutton switch is pushed while the LEDs are still on, the next previous flight leg is displayed. The transponder has the capability to store 10 flight legs. To display all stored flight legs, the PUSH TO TEST pushbutton switch must be pushed when the previous flight leg is being displayed. When all flight legs are displayed, all LEDs flash to indicate the end of the routine. All LEDs go off within 10 s after self-test is completed. The functions of the LEDs are indicated on the table below:

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-52-00 251-299,   CES

 

Page 23 May 01/09

ATC - Transponder Figure 005A   R EFF : 051-099, 251-299,  34-52-00    CES

 

Page 24 May 01/09

------------------------------------------------------------------------| LEDs | FUNCTION | ------------------------------------------------------------------------| XPDR PASS (green) | On after test indicates normal operation. | |----------------------|------------------------------------------------| | XPDR FAIL (red) | On after test indicates malfunction. | |----------------------|------------------------------------------------| | CNTL PNL (red) | On after test indicates abnormal input of 429 | | | word data from control unit, or associated | | | circuitry. | |----------------------|------------------------------------------------| | TOP ANT (red) | Indicates that the upper antennas are | | | incorrectly connected or are failed (comes on | | | during BITE self-test). | |----------------------|------------------------------------------------| | BOT ANT (red) | Indicates that the lower antennas are | | | incorrectly connected or are failed (comes on | | | during BITE self-test). | |----------------------|------------------------------------------------| | ALT SIG (red) | On after test indicates abnormal input from | | | ALT data system bus, or associated circuitry. | |----------------------|------------------------------------------------| The back of the transponder contains an ARINC 600, shell-size connector to provide electrical connections to the aircraft wiring via mount. Contact grouping is as follows: - Top contact set - ATE interface - Center contact set - System interconnections - Bottom contact set - Power supply and bonding. (2) Not Applicable **ON A/C 106-149, 221-249, 301-399, 401-499, A. ATC Transponder (1) External description (Ref. Fig. 005B) The face of the transponder is fitted with a handle, two attaching parts, a TEST pushbutton switch and five LEDs. The TEST pushbutton switch is used to initiate the BITE self-test. During the self-test, the transponder performs the following functions: With TEST pushbutton switch pressed for less than 5 seconds: - stops normal processing - performs test of full-time ROM checksum status

  R EFF : 051-099, 106-149, 221-249, 251-299,  34-52-00 301-399, 401-499,   CES

 

Page 25 May 01/09

ATC - Transponder Figure 005B   R EFF : 106-149, 211-249, 301-399, 401-499,  34-52-00    CES

 

Page 26 May 01/09

-

performs RAM tests stimulates receiver noise sources and monitors results checks antenna integrity injects simulated ATCRBS/Mode S all-call into top and bottom receivers samples transmitter monitor, following transmission , and verifies reply is correct samples power supply monitor performs test on non-active serial buses (TCAS, COM A/B and C/D) updates maintenance portion of nonvolatile memory returns unit to normal operation performs receiver test: All LEDs come on red for 2 seconds. Then the LRU status LED becomes green and the other LEDs remain red for 2 seconds. Then all LEDs go off for 2 seconds, then the test results are displayed for 30 seconds: LRU status - green for LRU with no fault, red for LRU fault; all other LEDs are off for no fault, red for fault.

  EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00   R  CES

 

Page 27 May 01/09

With TEST pushbutton switch pressed for more than 5 seconds: - Instead of self-test, the unit reads nonvolatile memory fault data for the last four flight legs and the applicable LEDs come on. The functions of the LEDs are indicated on the table below: ------------------------------------------------------------------------| LEDs | FUNCTION | ------------------------------------------------------------------------| LRU STATUS (green) | On after test indicates normal operation. | |----------------------|------------------------------------------------| | LRU STATUS (red) | On after test indicates malfunction. | |----------------------|------------------------------------------------| | ANTENNA TOP (red) | Indicates that the upper antennas are | | FAIL | incorrectly connected or are failed (comes on | | | during BITE self-test). | |----------------------|------------------------------------------------| | ANTENNA BOT (red) | Indicates that the lower antennas are | | FAIL | incorrectly connected or are failed (comes on | | | during BITE self-test). | |----------------------|------------------------------------------------| | ALTITUDE FAIL(red) | Indicates abnormal input from ALT data system | | | bus, or associated circuitry (comes on during | | | BITE self-test). | |----------------------|------------------------------------------------| | CONTROL FAIL (red) | Indicates abnormal input of 429 word data from | | | control unit, or associated circuitry (comes | | | on during BITE self-test). | ------------------------------------------------------------------------The back of the transponder contains an ARINC 600, shell-size connector to provide electrical connections to the aircraft wiring via mount. Contact grouping is as follows : - Top contact set and Center contact set - System interconnections - Bottom contact set - Power supply and bonding.

  EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00   R  CES

 

Page 28 May 01/09

(2) Internal description (Ref. Fig. 006B) Input signals (1030 MHz interrogations/uplinks) are received at one or both of the antennas. Each received antenna signal is pulse demodulated and sent to the processing circuits where the diversity selection is made. The diversity selection determines which receiver provides the stronger (or first) signal. The selected received signal is then applied through a demodulator circuit to the processing circuits. The processing circuits determine if the interrogation is an ATCRBS interrogation, a mode S interrogation addressed to the particular aircraft or a mode S addressed to another aircraft. Depending upon the type of the interrogation, the processing circuits determine the proper reply ( if one is required) and send the appropriate reply through a message processing circuit to the diversity switching circuits. The diversity switching circuits select the antenna through which the reply will be transmitted. The reply message is transmitted through the same antenna from which the selected received signal originated. The I/O circuit is an interface circuit to receive serial ARINC 429 data, the 24 bit address input, the code altitude input and various discretes. The CPU provides the link between the I/O and the signal processing circuits. The signal processing circuits consist of a video processor, a PAM decoder and a message processor. The video processor analyzes the received signals (pulses and pulse amplitude). If the received signal is valid, the PAM decoder determines the type of interrogation. Then the decoder output is sent to the message processor where appropriate reply format is generated. The message processor output is amplified and the resultant 1090 MHz transmit signal is applied to the antennas through a diplexer/diversity switch. The received signals from the antennas are sent to the receiver stage. The 60 MHz IF output is used to drive the video processor and the message processor (DSPK function). The input of the receiver stage is filtered to reduce the susceptibility to HIRF signals. The power supply is a pulse-width modulated switching regulator. It supplies all the necessary DC voltages required by the internal circuitry. An integrated monitoring function gives protection to the power supply circuits and reset signals to the CPUs each time primary power is applied. (a) Not Applicable (b) Not Applicable (c) Not Applicable

  R EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00    CES

 

Page 29 May 01/09

ATC - Transponder Figure 005C   R EFF : 201-210,  34-52-00    CES

 

Page 30 May 01/09

ATC Transponder - Simplified Block Diagram Figure 006   R EFF : 001-049, 101-105, 151-199,  34-52-00    CES

 

Page 31 May 01/09

ATC Transponder - Simplified Block Diagram Figure 006A   R EFF : 051-099, 251-299,  34-52-00    CES

 

Page 32 May 01/09

ATC Transponder - Simplified Block Diagram Figure 006B   R EFF : 106-149, 211-249, 301-399, 401-499,  34-52-00    CES

 

Page 33 May 01/09

(d) Not Applicable (e) Not Applicable (f) Not Applicable **ON A/C 201-210, A. ATC Transponder (1) External description (Ref. Fig. 005C) The face of the transponder is fitted with a handle, two attaching parts, a TEST pushbutton switch and five LEDs. The name, color and function of the five LEDs are as follows: - LRU STATUS (green) indicates that no faults are detected during the BITE self-test - LRU STATUS (red) indicates that a fault(s) is detected during the BITE self-test - ANTENNA TOP FAIL (red) indicates that the upper antennas are incorrectly connected or are failed (comes on during BITE self-test) - ANTENNA BOT FAIL (red) indicates that the lower antennas are incorrectly connected or are failed (comes on during BITE self-test) - ALTITUDE FAIL (red) indicates that the altitude data is not in correct format or that the internal data receiver circuit is faulty (comes on during BITE self-test) - CONTROL FAIL (red) indicates that the control input is not in correct format or that the internal data receiver circuit is faulty (comes on during BITE self-test). The back of the transponder contains an ARINC 600, shell size connector to provide electrical connections to the aircraft wiring via mount. Contact grouping is as follows : - Top contact set - ATE interface - Center contact set - System interconnections - Bottom contact set - Power supply and bonding. (2) Not Applicable

  R EFF : 106-149, 201-210, 221-249, 301-399,  34-52-00 401-499,   CES

 

Page 34 May 01/09

**ON A/C 211-220, A. ATC Transponder (1) External description (Ref. Fig. 005B) The face of the transponder is fitted with a handle, two attaching parts, a TEST pushbutton switch and five indicator lights. These indicator lights are active for thirty-six seconds following a commanded self-test. During the active period, they operate in the following sequence: - all indicator lights are on red for 2 seconds, - the LRU STATUS indicator light is on green and all other indicator lights remain on red for 2 seconds. - all indicator lights are off for 2 seconds, - for the remainder of the active period, the LRU STATUS indicator light is on green if no LRU failure has been detected. If a LRU failure is found, the LRU STATUS indicator light comes on red. One of the other ANTENNA TOP FAIL, ANTENNA BOT FAIL, ALTITUDE FAIL, or CONTROL FAIL indicator lights can come on red when the associated fault condition is detected. (2) Not Applicable R

**ON A/C 501-509, 511-526, 528-599, A. ATC Transponder (1) External description (Ref. Fig. 005) The face of the transponder is fitted with a handle, two attaching parts, a TEST pushbutton switch and ten LEDs. The TEST pushbutton switch initiates the LED test and transponder self-test. When pressed and held, it initiates the LED test: - three seconds on and three seconds off. After the LED test, the LEDs indicate unit operational status and any current major malfunctions. The functions of the LEDs are indicated on the table below:

  R EFF : 211-220, 501-509, 511-526, 528-599,  34-52-00    CES

 

Page 35 Feb 01/10

------------------------------------------------------------------------| LEDs | FUNCTION | ------------------------------------------------------------------------| TPR (green) | On after test indicates normal operation. | |----------------------|------------------------------------------------| | TPR (red) | On after test indicates malfunction. | |----------------------|------------------------------------------------| | ALT (red) | On after test indicates abnormal input from | | | ALT data system bus, or associated circuitry. | |----------------------|------------------------------------------------| | DATA IN (red) | On after test indicates abnormal input of 429 | | | word data from control unit, or associated | | | circuitry. | |----------------------|------------------------------------------------| | TOP (red) | On after test indicates malfunctioning top | | | transponder antenna (if installed), | | | or associated circuitry. | |----------------------|------------------------------------------------| | BOT (red) | On after test indicates malfunctioning bottom | | | transponder antenna, or associated circuitry. | |----------------------|------------------------------------------------| | TCAS (red) | On after test indicates abnormal input of 429 | | | word data from the TCAS unit (if installed), | | | or associated circuitry. | |----------------------|------------------------------------------------| | MAINTENANCE (red) | On after test indicates abnormal input from | | | Maintenance data system bus, or associated | | | circuitry. | ------------------------------------------------------------------------The back is equipped with one ARINC 600 electrical receptacle and a slot for the test connector. (2) Internal description (Ref. Fig. 006D) (a) Antenna switch and low pass filter board: The antenna switch and low pass filter board routes and filters the received or transmitted RF signal. (b) Pin diode driver board: The pin diode driver board selects the antenna and receives a transmit mode according to its inputs. The pin diode contains BITE which monitors the antenna, modulator and pin diode driver.

  R EFF : 501-509, 511-526, 528-599,  34-52-00    CES

 

Page 36 Feb 01/10

ATC Transponder - Simplified Block Diagram Figure 006C   R EFF : 201-210,  34-52-00    CES

 

Page 37 May 01/09

ATC Transponder - Simplified Block Diagram Figure 006D   R EFF : 501-509, 511-526, 528-599,  34-52-00    CES

 

Page 38 Feb 01/10

(c) Receive function: The receive function consists of the RF/IF board and the video/DPSK board. The RF/IF board filters, amplifies and converts the antenna signals into IF frequency. Two outputs are generated: - the top/bottom video signal which is processed by the video processing circuit in order to determine whether it is correct or a parasite signal. - a top/bottom IF signal which is sent to the DPSK demodulator circuit which converts it into TTL logic level and transmits it to the I/O processor board. (d) The transmit function consists of: - the modulator board - the transmitter board - the band pass filter - the RF interconnect board The I/O processor board transmits an information signal which is converted into a pulsed output. The pulsed output is applied to the pulsed oscillator of the transmitter board then amplifed, filtered and fed to the antenna through the RF interconnect board. (e) Test function: The test function consists of: - the test oscillator modulator board - the test oscillator board. It allows generation of test signals applied to the antenna. (f) I/O processor board The heart of the I/O processor board is an 80186 microprocessor (16 bits). This microprocessor is connected with interface circuits to various A/C systems. The microprocessor controls: - the input/output requirement of the transponder - the receive/transmit function - the BITE of the transponder. **ON A/C 001-049, 101-105, 151-199, (3) Principle of operation (Ref. Fig. 003) Each ground interrogator transmits its interrogations at the frequency of 1030 MHz in the form of a series of two pulses. Depending on the pulse intervals and numbers, they define three different interrogation modes. After receiving these pulses, the TRA-67A transponder identifies and decodes the interrogations.

  R EFF : 001-049, 101-105, 151-199, 501-509,  34-52-00 511-526, 528-599,   CES

 

Page 39 Feb 01/10

Depending on the detected interrogation mode, the TRA-67A transponder transmits either the identification of the aircraft or its barometric altitude or flight data. To perform these functions, the transponder is associated with a control unit defining the aircraft identification code, the Air Data/Inertial Reference Units (ADIRUs) the Flight Management and Guidance Computers (FMGCs) and the Traffic Collision Avoidance System (TCAS). The transmission of the replies to the ground takes place on a carrier frequency of 1090 MHz. If the interrogation is sent by the side lobe of the radar a characteristic signal is sent allowing the transponder to disregard the interrogation. In addition to its specific transponder functions, it enables communication between the TCAS and a detected aircraft if equipped with the TCAS. (a) Interrogations (Ref. Fig. 002) Three classes of interrogations are transmitted by the ground interrogator, they are: - Mode A or C interrogations - Mode S all call interrogations - Mode S interrogations. 1 _

Mode A or C interrogation A mode A or C interrogation consists of two pulses labelled P1 and P3. A control pulse P2 is transmitted following the first interrogation pulse. P1 and P3 are radiated by a narrow rotating beam antenna. P2, also called the Side Lobe Suppression (SLS) pulse, is radiated by an omnidirectional antenna with an amplitude of 6 dB below P1 and P2 within the main lobe. P1 amplitude is greater than or equal to P2 amplitude from the greatest side lobe transmission of the antenna radiating P1.

2 _

Mode S all call interrogation (Ref. Fig. 007) A mode S all call interrogation consists of three transmitted pulses labelled P1, P3 and P4. A control pulse P2 (Side Lobe Suppression Pulse) is transmitted following P1. P1 amplitude is greater than or equal to P2 amplitude from the greatest side lobe transmission of the antenna radiating P1. P2 amplitude is at a level lower than 6 dB below P1 amplitude within the main lobe. P4 duration is 0.8 or 1.6 microseconds depending on the interrogation mode.

  R EFF : 001-049, 101-105, 151-199,  34-52-00    CES

 

Page 40 May 01/09

ATC - Mode S All Call Pulse Characteristics Figure 007   R EFF : ALL  34-52-00    CES

 

Page 41 May 01/09

If P4 is equal to 0.8 microseconds, this means that the interrogation only concerns conventional ATC mode A or C transponder, and consequently the Mode S transponder should not reply. If P4 is equal to 1.6 microseconds, this means that the mode S transponder should reply with mode S information. 3 _

Mode S interrogation (Ref. Fig. 008) A mode S interrogation consists of a two-bit preamble followed by a data block. The preamble consists of two transmitted pulses labelled P1 and P2. The characteristics of P1 and P2 are the same as for the mode S all call interrogation, except that P2 amplitude is equal to P1. The data block consists of a single pulse P6 with a Differential Phase Shift Keying (DPSK) modulation. Pulse duration : short 15.5 microseconds, long 29.5 microseconds, Data block : 56 or 112 bits.

(b) Encoded reply 1 _

Mode A or C reply A mode A or C reply consists of two framing pulses F1 and F2, separated by a 20.3 microseconds time interval. The encoding of the reply is done by means of the presence (1) or absence (0) of 13 reply pulses (12 pulses plus X pulse).

2 _

Mode S reply A mode S reply occurs after a mode S interrogation or a mode S all call interrogation (P4 duration 1.6 microseconds). A mode S reply consists of a four-bit preamble followed by a data block. The data block contains 56 or 112 position modulated pulses.

  R EFF : 001-049, 101-105, 151-199,  34-52-00    CES

 

Page 42 May 01/09

ATC - Mode S Pulse Characteristics Figure 008   R EFF : ALL  34-52-00    CES

 

Page 43 May 01/09

3 _

Mode S message content The minimum data link transponder supports all surveillance functions, in addition to bidirectional air-to-air data exchange, ground-to-air data uplink (Comm A), air-to-ground data downlink (Comm B), and multisite message protocol. In addition, the transponder is capable of receiving Extended Length Messages (ELMs) from the ground. ELMS are received in the Comm C format. ELM transmittals to the ground use the Comm D format. (Note: Comm C and Comm D are future applications). All discrete Mode S interrogations and replies (except the all-call reply) contain the 24-bit discrete address of the Mode S transponder upon which 24 error detection parity check bits are overlaid. In the all-call reply, the 24 parity check bits are overlaid on the Mode S interrogation address and the transponders discrete address is included in the text of the reply. The main function of Mode S is surveillance. To accomplish this function, the Mode S transponder uses the 56-bit transmissions (in each direction). In the 56-bit transmissions, the aircraft reports its altitude or ATCRBS 4096 code, and the flight status (airborne, on-ground, alert, Special Position Identification (SPI), etc. The discrete addressing and digital encoding of Mode S transmissions permit their use as a digital data link. The interrogation and reply formats of the Mode S system contain sufficient coding space to permit the transmission of data. These data transmissions may be used for air traffic control purposes, air-to-air data interchange for collision avoidance, or to provide flight advisory services such as weather reports, or Automated Terminal Information System (ATIS). Most Mode S data link transmissions will be handled as one 56-bit message included as part of a long 112-bit interrogation or reply. These transmission include the message in addition to the surveillance data. Longer messages are transmitted using the Extended Length Message (ELM) capability. The ELM is capable of transmitting up to sixteen 80-bit message segments, either ground-to-air or air-to-ground. The ELM can be acknowledged with a single reply or interrogation. ELMs uplinked need not be replied to individually, but can be acknowledged in a reply containing a summary of the received interrogations. ELMs do not contain surveillance data. The following table gives the definition of uplink format message fields:

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------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AP | address parity | 24-bit address and parity overlaid | | | | | | AQ | acquisition | differentiates acquisition from non-acquisi- | | | | tion interrogations | | | | | | DI | designator | identifies the coding contained in the SD | | | identification | field | | | | | | II | interrogator | identifies the interrogator | | | identification | | | | | | | MA | message | 56-bit MA field contains messages directed | | | Comm A | to the A/C | | | | | | MC | message | 80-bit MC field contains one segment of a | | | Comm C | sequence of segments transmitted in ELM mode. | | | | | | MU | message | 56-bit MU messages contains information used | | | Comm U | in air-to-air exchanges | | | | | | NC | number of C | number of segments transmitted in ELM mode | | | segments | | | | | | | PC | protocol | operating commands of the transponder | | | | | | PR | probability | contains commands to the transponder to | | | of reply | specify the reply probability to the mode S | | | | only all-call interrogations (Allows | | | | operators to acquire closely spaced A/C). | | | | | | RC | reply | designates the transmitted segment as initial,| | | control | intermediate or final | | | | | | RL | reply | indicates if message is short or long | | | length | | | | | | | RR | reply | length and content of the reply information | | | request | requested by the interrogator | | | | | | SD | special | contains control codes affecting the link | | | designator | protocol | -------------------------------------------------------------------------------

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The table below gives the definition of downlink format message fields: ------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AA | address | contains the A/C mode S address | | | announced | | | | | | | AC | altitude | information containing the A/C altitude | | | code | | | | | | | AP | address | 24-bit address and parity overlaid | | | parity | | | | | | | CA | transponder | reports transponder capability | | | capability | | | | | | | DR | downlink | requests extraction of downlink messages from | | | request | the transponder by the interrogator | | | | | | FS | flight | flight status | | | status | | | | | | | ID | identification | contains the Mode A identification code | | | | | | MB | message | 56-bit MB field contains the message | | | Comm B | transmitted to the interrogator | | | | | | MD | message | 80-bit MD field contains one segment of a | | | Comm D | sequence of segments in the ELM Mode | ------------------------------------------------------------------------------(4) Operation (Ref. Fig. 006) The transponder operation is under the control of a processor which drives all the transponder functions and performs the self monitoring. Each function or module has dedicated tasks, exchanges data with the processor and receives commands. The transponder consists of nine main sections. (a) Antenna switching circuit This circuit ensures the connection with the antennas. It transmits and filters the Radio Frequency (RF) signals from the antennas to the receiver circuit. This circuit switches to the top or bottom antenna according to the signal received from the

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antenna selection circuit. The interrogation or reply signals are routed to the antennas via coaxial cables. (b) Antenna selection and BITE circuit The antenna selection circuit receives a control signal from the Input/Output (I/O) processor circuit. This circuit selects the transmit or receive mode, the top or bottom antenna and then transmits the signal to the antenna switching circuit. It also contains the self-test circuit (BITE). (c) Receiver circuit The signal from the top or bottom antenna is demodulated at the input of the receiver circuit. The video processing circuit determines whether the received signal is in a main or a side lobe by comparing amplitude of pulses P1 and P2 in modes A and C and amplitude of pulses P3 and P4 in mode S. The video processing circuit identifies the received signal and validates the interrogations. It then demodulates and transmits the signal to the I/O processor circuit. (d) Modulator circuit This circuit receives triggering signals (MOD TRIG) from the I/O processor circuit and produces modulated pulses. These pulses are transmitted to the emitter on the radio transmitter circuit. The modulator contains a self-test circuit (BITE) which receives a sample of RF pulses (TX SENSE) from the radio transmitter circuit. It checks the signal validity and sends it to the I/O processor and self-test circuits (BITE). (e) Radio transmitter circuit This circuit comprises a transmitter board, a filter and an RF interconnect board. The output oscillator transmits a 1090 MHz frequency. (f) Test oscillator modulator This modulator generates the proper amplitude and phase-modulated signals used by the test oscillator. Two inputs TEST OSC MODE 1 and TEST OSC MODE 2 select the type of desired interrogation. A third input TEST OSCILLATOR START initializes the interrogation. (g) Test oscillator circuit This circuit generates the signals required during the transponder self-test as well as mode S or all call type interrogation signals.

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(h) Power supply module The power supply module converts the aircraft 115VAC into +5, +12, -12, +65 and -200VDC for the various internal circuits. It receives a suppression signal from each DME interrogator, the other ATC transponder and the TCAS computer. This signal prevents simultaneous transmissions and inhibits receptions from other systems. (i) I/O processor circuit This circuit ensures the interface between the transponder and the aircraft. It receives and transmits information via ARINC 429 data bases. It also connects the various internal circuits of the transponder. It is built around a 16-bit 80186 microprocessor. The transponder is connected to the TCAS through two high-speed 429 buses, one for transmission, the other for reception. The discrete output from transponder is : ------------------------------------------------------------------------------NAME ELECTRICAL LEVEL TO SIGNAL STATUS ------------------------------------------------------------------------------LAMP B FAULT OC/5VDC CTL UNIT - ATC 5VDC = FAULT ------------------------------------------------------------------------------(5) Not Applicable **ON A/C 051-099, (3) Principle of operation (Ref. Fig. 003) Each ground interrogator transmits its interrogations at the frequency of 1030 MHz in the form of a series of two pulses. Depending on the pulse intervals and numbers, they define three different interrogation modes. After receiving these pulses, the transponder identifies and decodes the interrogations. Depending on the detected interrogation mode, the transponder transmits either the identification of the aircraft or its barometric altitude or flight data. To perform these functions, the transponder is associated with a control unit defining the aircraft identification code, the Air Data/Inertial Reference Units (ADIRUs) the Flight Management and Guidance Computers (FMGCs) and the Traffic Collision Avoidance System (TCAS)(if installed). The transmission of the replies to the ground takes place on a carrier frequency of 1090 MHz. If the interrogation is sent by the side lobe of the radar a characteristic signal is sent allowing the transponder to disregard the interrogation.

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In addition to its specific transponder functions, it enables communication between the TCAS and a detected aircraft if equipped with the TCAS. (a) Interrogations (Ref. Fig. 002) Three classes of interrogations are transmitted by the ground interrogator, they are: - Mode A or C interrogations - Mode S all call interrogations - Mode S interrogations. 1 _

Mode A or C interrogation A mode A or C interrogation consists of two pulses labelled P1 and P3. A control pulse P2 is transmitted following the first interrogation pulse. P1 and P3 are radiated by a narrow rotating beam antenna. P2, also called the Side Lobe Suppression (SLS) pulse, is radiated by an omnidirectional antenna with an amplitude of 6 dB below P1 and P2 within the main lobe. P1 amplitude is greater than or equal to P2 amplitude from the greatest side lobe transmission of the antenna radiating P1.

2 _

Mode S all call interrogation (Ref. Fig. 007) A mode S all call interrogation consists of three transmitted pulses labelled P1, P3 and P4. A control pulse P2 (Side Lobe Suppression Pulse) is transmitted following P1. P1 amplitude is greater than or equal to P2 amplitude from the greatest side lobe transmission of the antenna radiating P1. P2 amplitude is at a level lower than 6 dB below P1 amplitude within the main lobe. P4 duration is 0.8 or 1.6 microseconds depending on the interrogation mode. If P4 is equal to 0.8 microseconds, this means that the interrogation only concerns conventional ATC mode A or C transponder, and consequently the Mode S transponder must not reply. If P4 is equal to 1.6 microseconds, this means that the mode S transponder must reply with mode S information.

3 _

Mode S interrogation (Ref. Fig. 008) A mode S interrogation consists of a two-bit preamble followed by a data block. The preamble consists of two transmitted pulses labelled P1 and P2. The characteristics of P1 and P2 are the same as for

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the mode S all call interrogation, except that P2 amplitude is equal to P1. The data block consists of a single pulse P6 with a Differential Phase Shift Keying (DPSK) modulation. Pulse duration : short 15.5 microseconds, long 29.5 microseconds, Data block : 56 or 112 bits. (b) Encoded reply 1 _

Mode A or C reply A mode A or C reply consists of two framing pulses F1 and F2, separated by a 20.3 microseconds time interval. The encoding of the reply is done by means of the presence (1) or absence (0) of 13 reply pulses (12 pulses plus X pulse).

2 _

Mode S all-call reply A mode S all-call reply consists of a four-bit preamble followed by a data block. The data block contains 56 position modulated pulses.

3 _

Mode S reply A mode S reply occurs after a mode S interrogation or a mode S all call interrogation (P4 duration 1.6 microseconds). A mode S reply consists of a four-bit preamble followed by a data block. The data block contains 56 or 112 position modulated pulses. The replies are PPM coded.

4 _

Mode S message contents The transponder must have the following Mode S message capabilities: - surveillance functions of both ATCRBS and Mode S ground sensors (UF=4.5 / DF=4.5) - surveillance functions of airborne interrogators (UF=0 /DF=0) - bi-directional air-to-air information exchange, COMM-U/V (UF=16 / DF=16) - ground-to-air data uplink, COMM-A (UF=20.21) - air-to-ground data downlink, COMM-B (DF=20.21) - ground-to-air Uplink Extended length message (UELM), COMM-C (UF=24) (if external ADLP is installed) - air-to-ground Downlink Extended length message (DELM), COMM-D (DF=24). (if external ADLP is installed) All discrete Mode S interrogations and replies (except the all-call reply) contain the 24-bit discrete address of the Mode S transponder upon which 24 error detection parity check

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bits are overlaid. In the all-call reply, the 24 parity check bits are overlaid on the Mode S interrogation address and the transponders discrete address is included in the text of the reply. The main function of Mode S is surveillance. To accomplish this function, the Mode S transponder uses the 56-bit transmissions (in each direction). In the 56-bit transmissions, the aircraft reports its altitude or ATCRBS 4096 code, and the flight status (airborne, on-ground, alert, Special Position Identification (SPI), etc. The discrete addressing and digital encoding of Mode S transmissions permit their use as a digital data link. The interrogation and reply formats of the Mode S system contain sufficient coding space to permit the transmission of data. These data transmissions may be used for air traffic control purposes, air-to-air data interchange for collision avoidance, or to provide flight advisory services such as weather reports, or Automated Terminal Information System (ATIS). Most Mode S data link transmissions will be handled as one 56-bit message included as part of a long 112-bit interrogation or reply. These transmission include the message in addition to the surveillance data. Longer messages are transmitted using the Extended Length Message (ELM) capability (if external ADLP is installed). The ELM is capable of transmitting up to sixteen 80-bit message segments at a rate of 8 per second, either ground-to-air or air-to-ground. The ELM can be acknowledged with a single reply or interrogation. ELMs uplinked need not be replied to individually, but can be acknowledged in a reply containing a summary of the received interrogations. ELMs do not contain surveillance data. a _

Mode S interrogation message formats All valid Mode S interrogation are listed here. The first 5 bits of the message indicate a UF message format. Items in brackets, e.g (AP:24) represent the AP field code, and the number of bits in the field 24. Underscored numbers represent unused fields and must not be processed. - TCAS Surveillance: UF=0 (0 0000) 3_ (RL:1) 4_ (AQ:1) 18_ (AP:24) - Surveillance, Altitude Request: UF=4 (0 0100) (PC:3) (RR:5) (DI:3) (SD:16) (AP:24) - Surveillance, Identity Request:

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UF=5 (0 0101) (PC:3) (RR:5) (DI:3) (SD:16) (AP:24) - Mode S All-Call Interrogation: UF=11 (0 1011) (PR:4) (II:4) 19_ (AP:24) - Long TCAS Interrogation (COMM-U): UF=16 (1 0000) 3_ (RL:1) 4_ (AQ:1) 18_ (MU:56) (AP:24) - COMM-A Interrogation, Altitude: UF=20 (1 0100) (PC:3) (RR:5) (DI:3) (SD:16) (MA:56) (AP:24) - COMM-A Interrogation, Identity: UF=21 (1 0101) (PC:3) (RR:5) (DI:3) (SD:16) (MA:56) (AP:24) - Uplink Extended Length Message (UELM)/COMM-C Interrogation: UF=24 (1 1) (RC:2) (NC:4) (MC:80) (AP:24) NOTE : PC, RR, DI and SD subfields are undefined for ____ UF=20/21 broadcast interrogations. b _

Mode S reply message formats All valid Mode S replies are listed here. The first 5 bits of the message indicate a UF message format. Items in brackets, e.g (AP:24) represent the AP field code, and the number of bits in the field 24. Underscored numbers representing unused fields must be set to zero. - TCAS Surveillance: DF=0 (0 0000) (VS:1) 2_ (SL:3) 2_ (RI:4) 2_ (AC:13) (AP:24) - Surveillance, Altitude: DF=4 (0 0100) (FS:3) (DR:5) (UM:6) (AC:13) (AP:24) - Surveillance, Identity: DF=5 (0 0101) (FS:3) (DR:5) (UM:6) (ID:13) (AP:24) - Mode S All-Call Reply, ATCRBS/Mode S All-Call Reply, Mode S Squitter: DF=11 (0 1011) (CA:3) (AA:24) (PI:24) - Long TCAS Reply (COMM-V):

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DF=16 (1 0000) (VS:1) 2_ (SL:3) 2_ (RI:4) (AC:13) (MV:56) (AP:24) - COMM-B Reply, Altitude: DF=20 (1 0100) (FS:3) (DR:5) (UM:6) (AC:13) (MB:56) (AP:24) - COMM-B Reply, Identity: DF=21 (1 0101) (FS:3) (DR:5) (UM:6) (ID:13) (MB:56) (AP:24) - Downlink Extended Length Message (DELM)/COMM-D: DF=24 (1 1) 1_ (KE:1) (ND:4) (MD:80) (AP:24) c _

Mode S interrogation data field definition The following table gives the definition of uplink format message fields:

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------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AP | address parity | 24-bit address and parity overlaid | | | | | | AQ | acquisition | differentiates acquisition from non-acquisi- | | | | tion interrogations | | | | | | DI | designator | identifies the coding contained in the SD | | | identification | field | | | | | | II | interrogator | identifies the interrogator | | | identification | | | | | | | MA | message | 56-bit MA field contains messages directed | | | Comm A | to the A/C | | | | | | MC | message | 80-bit MC field contains one segment of a | | | Comm C | sequence of segments transmitted in ELM mode. | | | | | | MU | message | 56-bit MU messages contains information used | | | Comm U | in air-to-air exchanges | | | | | | NC | number of C | number of segments transmitted in ELM mode | | | segments | | | | | | | PC | protocol | operating commands of the transponder | | | | | | PR | probability | contains commands to the transponder to | | | of reply | specify the reply probability to the mode S | | | | only all-call interrogations (Allows | | | | operators to acquire closely spaced A/C). | | | | | | RC | reply | designates the transmitted segment as initial,| | | control | intermediate or final | | | | | | RL | reply | indicates if message is short or long | | | length | | | | | | | RR | reply | length and content of the reply information | | | request | requested by the interrogator | | | | | | SD | special | contains control codes affecting the link | | | designator | protocol | -------------------------------------------------------------------------------

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The table below gives the definition of downlink format message fields: ------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AA | address | contains the A/C mode S address | | | announced | | | | | | | AC | altitude | information containing the A/C altitude | | | code | | | | | | | AP | address | 24-bit address and parity overlaid | | | parity | | | | | | | CA | transponder | reports transponder capability | | | capability | | | | | | | DR | downlink | requests extraction of downlink messages from | | | request | the transponder by the interrogator | | | | | | FS | flight | flight status | | | status | | | | | | | ID | identification | contains the Mode A identification code | | | | | | MB | message | 56-bit MB field contains the message | | | Comm B | transmitted to the interrogator | | | | | | MD | message | 80-bit MD field contains one segment of a | | | Comm D | sequence of segments in the ELM Mode | ------------------------------------------------------------------------------(c) Data transmitted for elementary surveillance The specific data related to the elementary surveillance are the following: - 24 bits A/C adress (coded in AA field of DF11) - flight number (MB field of DF20 or DF21 filled in with Binary Data Stores (BDS) 2.0 - transponder capability report (coded in CA field of DF11) - altitude/ground reporting (coded in AC field of DF4 or DF20) - flight status (coded in FS field of DF4) - RA report (MB field of DF20 or DF21 filled in with BDS 3.0) - Surveillance Identifier (SI) (coded in PI field of DF11)

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(d) Data transmitted for enhanced surveillance (if modification 32467 is validated) The specific data related to the enhanced surveillance are the following: - selected altitude - barometric pressure setting - roll angle - track angle rate - true track angle - ground speed - true air speed - magnetic heading - indicated airspeed - mach - barometric altitude rate - inertial vertical velocity These data are transmitted in MB field of BDS 4.0, 5.0 or 6.0 in DF20 or DF21. (e) Data transmitted in extended squitters (if modification 32467 is validated) The specific data related to the extended squitters are the following: - altitude - longitude - latitude - movement - ground track - flight number - E/W velocity - N/S velocity - vertical rate These data are transmitted in ME field of BDS 0.5, 0.6, 0.8 or 0.9 in DF17. (4) Operation (Ref. Fig. 006A) The transponder consists of a receiver, a transmitter, an interface/Central Processing Unit (CPU) assembly and a power supply/modulator assembly. (a) Receiver The receiver (top and bottom receiver channels), which consists of a ceramic pre-selector filter, self-test coupler, low noise amplifier, mixer, Intermediate Frequency (IF) amplifier and band-pass filter, logarithmic amplifier (log amp) detectors and a Differential Phase Shift Keying (DPSK) demodulator, has the

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circuitry required to accept the Radio Frequency (RF) signal and convert it into a voltage signal to be used by the signal processing elements. (b) Transmitter The transmitter, which consists of a 1090 MHz local oscillator, RF transmitter gain stages, transmit/receive pin diode switches, forward power and antenna monitors and a low-pass harmonic filter, is unique in that it is an all solid-state unit with the capability for the Mode S message requirements, which impose increased operating requirements on the transmitter. (c) Interface/CPU assembly The interface/CPU assembly contains a microprocessor and supporting memory and logic circuitry. The support circuitry includes Flash EPROM memory devices for the operational program, boot program and system data, system RAM memory for program execution, and an EEPROM memory for calibration and self-test error logging. The assembly contains Application Specific Integrated Circuits (ASICs) for the RF processing functions (interrogations and replies), and communication over ARINC 429 data buses. In addition to the RF ASIC the assembly contains circuitry for processing receiver video signals. The assembly supports all external interface functions, including processing discrete inputs/outputs and analog synchro interfaces. (d) Power supply/modulator assembly The transponder has its own internal self-contained power supply. The 115V, 400 Hz power supply input is applied through the rear connector of the unit. The power supply modulator assembly has an EMI filter, 115VAC to DC converter, power interrupt monitor, +60VDC switching supply for transmitter energy storage, a fly-back supply for generating internal unit voltages, and a +35VDC and +28VDC regulator for supplying transmitter voltages. The assembly contains PIN diode driver circuitry for driving the RF transmit/receive switches, pulse and envelope modulator circuitry for modualting the RF transistors. The assembly also contains a self-test modulator and power supply monitors. (5) Theory of operation Interrogations which are received by the transponder are filtered and amplified by the 1030MHz receiver, converted to a 60MHz IF by the mixer and IF filter on the receiver. The interrogations (pulses) are then converted to a base-band analog video signals by the log amps. The DPSK portion of a Mode S interrogation is turned into a digital video signal by the DPSK demodulator. The analog video signal is then

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processed by the video processor circuit on the interface/CPU assembly, where it is converted to a digital video signal. The digital video signals and DPSK video signals are then processed by the RF ASIC, which determines the validity and type of interrogation. If a valid interrogation is received, the RF ASIC in conjunction with the microprocessor and software generates a reply. The RF ASIC generates digital pulses which are used to modulate the transmitter. The digital signals are converted to analog modulator signals by the pulse and envelope modulator circuitry on the power supply/modulator. The analog modulator signals are then used to turn the transmitter stages on or off as is appropriate to generate the pulsed replies. **ON A/C 106-149, 221-249, 301-399, 401-499, (3) Principle of operation (Ref. Fig. 003A) Each ground interrogator transmits its interrogations at the frequency of 1030 MHz in the form of a series of two pulses. Depending on the pulse intervals and numbers, they define three different interrogation modes. After receiving these pulses, the transponder identifies and decodes the interrogations. Depending on the detected interrogation mode, the transponder transmits either the identification of the aircraft or its barometric altitude or flight data. The transmission of the replies takes place on a carrier frequency of 1090 Mhz. If the interrogation is sent by the side lobe of the radar, a characteristic signal is sent allowing the transponder to disregard the interrogation. (a) Interrogations Three classes of interrogations are transmitted by the ground interrogator; they are: - Mode A or C interrogations - Mode S all-call interrogations - Mode S interrogations. 1 _

Mode A or C interrogation A mode A or C interrogation consists of two pulses labelled P1 and P3. A control pulse P2 is transmitted following the first interrogation pulse. P1 and P3 are radiated by a narrow rotating beam antenna. P2, also called the Side Lobe Suppression (SLS) pulse, is radiated by an omnidirectional antenna with an amplitude of 9 dB below P1 and P2 within the main lobe. P1 amplitude is greater than or equal to P2 amplitude from the greatest side lobe transmission of the antenna radiating P1.

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2 _

Mode S all-call interrogation (Ref. Fig. 007) A Mode S all-call interrogation consists of three transmitted pulses labelled P3 and P4. A control pulse P2 (Side Lobe Suppression Pulse) is transmitted following P1. P1 amplitude is greater than or equal to P2 amplitude from the greatest side lobe transmission of the antenna radiating P1. P2 amplitude is at a level lower than 9 dB below P1 amplitude within the main lobe. P4 duration is 0.8 or 1.6 microseconds depending on the interrogation mode. If P4 is equal to 0.8 microseconds, this means that the interrogation only concerns conventional ATC mode A or C transponders, and consequently the Mode S transponder should not reply. If P4 is equal to 1.6 microseconds, this means that the mode S transponder should reply with mode S information.

3 _

Mode S interrogation (Ref. Fig. 008) A Mode S interrogation consists of a two-bit preamble followed by a data block. The preamble consists of two transmitted pulses labelled P1 and P2. The characteristics of P1 and P2 are the same as for the mode S all call interrogation, except that P2 amplitude is equal to P1. The data block consists of a single pulse P6 with a Differential Phase Shift Keying (DPSK) modulation. . Pulse duration: short 15.5 microseconds / long 29.5 microseconds . Data block: 56 or 112 bits.

(b) Encoded reply 1 _

Mode A or C reply A Mode A or C reply consists of two framing pulses F1 and F2, separated by a 20.3 microsecond time interval. The encoding of the reply is done by means of the presence (1) or absence (0) of 13 reply pulses (12 pulses plus X pulse).

2 _

Mode S all-call reply A Mode S all-call reply consists of a four-bit preamble followed by a data block. The data block contains 56 position modulated pulses.

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3 _

Mode S reply A Mode S reply occurs after a mode S interrogation or a mode S all-call interrogation (P4 duration 1.6 microseconds). A mode S reply consists of a four-bit preamble (duration 8 microseconds) followed by a data block. The data block contains 56 or 112 position modulated pulses. The replies are PPM coded.

(c) Mode S message content The minimum data link transponder supports all surveillance functions, in addition to bidirectional air-to-air data exchange, ground-to-air data uplink (Comm A), air-to-ground data downlink (Comm B), and multisite message protocol. In addition, the transponder is capable of receiving Extended Length Messages (ELMs) from the ground. ELMS are received in the Comm C format. ELM transmittals to the ground use the Comm D format. (Note: The ATC Collins is capable of comm A(B) C data-link operation). All discrete Mode S interrogations and replies (except the all-call reply) contain the 24-bit discrete address of the Mode S transponder upon which 24 error detection parity check bits are overlaid. In the all-call reply, the 24 parity check bits are overlaid on the Mode S interrogation address and the transponders7 discrete address is included in the text of the reply. The main function of Mode S is surveillance. To accomplish this function, the Mode S transponder uses the 56-bit transmissions ( each direction). In the 56-bit transmissions, the aircraft repor its altitude or ATCRBS 4096 code, and the flight status (airborn on-ground, alert, Special Position Identification (SPI), etc. The discrete addressing and digital encoding of Mode S transmiss permit their use as a digital data link. The interrogation and r formats of the Mode S system contain sufficient coding space to permit the transmission of data. These data transmissions may be for air traffic control purposes, air-to-air data interchange fo collision avoidance, or to provide flight advisory services such weather reports, or Automated Terminal Information System (ATIS) Most Mode S data link transmissions will be handled as one 56-bi message included as part of a long 112-bit interrogation or repl These transmission include the message in addition to the surveillance data. Longer messages are transmitted using the Extended Length Message (ELM) capability. The ELM is capable of transmitting up to sixteen 80-bit message segments, either ground-to-air or air-to-ground. The ELM can be acknowledged with a single reply or interrogation. ELMs uplinked need not be replied to individually, but can be acknowledged in a reply containing a summary of the received interrogations. ELMs do not contain surveillance data.

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1 _

Mode S interrogation message formats All valid Mode S interrogation are listed here. The first 5 bits of the message indicate a UF message format. Items in brackets, e.g (AP:24) represent the NAPN field code, and the number of bits in the field N24N. Undescrored numbers represent unused fields and should not be processed. - TCAS Surveillance: UF=0 (0 0000) 3_ (RL:1) 4_ (AQ:1) 18_ (AP:24) - Surveillance, Altitude Request: UF=4 (0 0100) (PC:3) (RR:5) (DI:3) (SD:16) (AP:24) - Surveillance, Identity Request: UF=5 (0 0101) (PC:3) (RR:5) (DI:3) (SD:16) (AP:24) - Mode S All-Call Interrogation: UF=11 (0 1011) (PR:4) (II:4) 19_ (AP:24) - Long TCAS Interrogation (COMM-U): UF=16 (1 0000) 3_ (RL:1) 4_ (AQ:1) 18_ (MU:56) (AP:24) - COMM-A Interrogation, Altitude: UF=20 (1 0100) (PC:3) (RR:5) (DI:3) (SD:16) (MA:56) (AP:24) - COMM-A Interrogation, Identity: UF=21 (1 0101) (PC:3) (RR:5) (DI:3) (SD:16) (MA:56) (AP:24) - Uplink Extended Length Message (UELM)/COMM-C Interrogation: UF=24 (1 1) (RC:2) (NC:4) (MC:80) (AP:24) NOTE : PC, RR, DI and SD subfields are undefined for UF=20/21 ____ broadcast interrogations.

2 _

Mode S messages downlink formats All valid Mode S replies are listed here. The first 5 bits of the message indicate a UF message format. Items in brackets, e.g (AP:24) represent the NAPN field code, and the number of bits in the field N24N. Underscrored numbers represent unused fields are shall be set to zero. - TCAS Surveillance: DF=0 (0 0000) (VS:1) 2_ (SL:3) 2_ (RI:4) 2_ (AC:13) (AP:24) - Surveillance, Altitude:

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DF=4 (0 0100) (FS:3) (DR:5) (UM:6) (AC:13) (AP:24) - Surveillance, Identity: DF=5 (0 0101) (FS:3) (DR:5) (UM:6) (ID:13) (AP:24) - Mode S All-Call Reply, ATCRBS/Mode S All-Call Reply, Mode S Squitter: DF=11 (0 1011) (CA:3) (AA:24) (PI:24) - Long TCAS Reply (COMM-V): DF=16 (1 0000) (VS:1) 2_ (SL:3) 2_ (RI:4) (AC:13) (MV:56) (AP:24) - Extended Squitters: DF=17 (1 0001) (CA:3) (AA:24) (ME:56) (PI:24) - COMM-B Reply, Altitude: DF=20 (1 0100) (FS:3) (DR:5) (UM:6) (AC:13) (MB:56) (AP:24) - COMM-B Reply, Identity: DF=21 (1 0101) (FS:3) (DR:5) (UM:6) (ID:13) (MB:56) (AP:24) - Downlink Extended Length Message (DELM)/COMM-D: DF=24 (1 1) 1_ (KE:1) (ND:4) (MD:80) (AP:24) 3 _

Mode S interrogation data field definition The following table gives the definition of uplink format message fields:

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------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AP | address parity | 24-bit address and parity overlaid | | | | | | AQ | acquisition | differentiates acquisition from non-acquisi- | | | | tion interrogations | | | | | | DI | designator | identifies the coding contained in the SD | | | identification | field | | | | | | II | interrogator | identifies the interrogator | | | identification | | | | | | | MA | message | 56-bit MA field contains messages directed | | | Comm A | to the A/C | | | | | | MC | message | 80-bit MC field contains one segment of a | | | Comm C | sequence of segments transmitted in ELM mode. | | | | | | MU | message | 56-bit MU messages contains information used | | | Comm U | in air-to-air exchanges | | | | | | NC | number of C | number of segments transmitted in ELM mode | | | segments | | | | | | | PC | protocol | operating commands of the transponder | | | | | | PR | probability | contains commands to the transponder to | | | of reply | specify the reply probability to the mode S | | | | only all-call interrogations (Allows | | | | operators to acquire closely spaced A/C). | | | | | | RC | reply | designates the transmitted segment as initial,| | | control | intermediate or final | | | | | | RL | reply | indicates if message is short or long | | | length | | | | | | | RR | reply | length and content of the reply information | | | request | requested by the interrogator | | | | | | SD | special | contains control codes affecting the link | | | designator | protocol | -------------------------------------------------------------------------------

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The table below gives the definition of downlink format message fields: ------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AA | address | contains the A/C mode S address | | | announced | | | | | | | AC | altitude | information containing the A/C altitude | | | code | | | | | | | AP | address | 24-bit address and parity overlaid | | | parity | | | | | | | CA | transponder | reports transponder capability | | | capability | | | | | | | DR | downlink | requests extraction of downlink messages from | | | request | the transponder by the interrogator | | | | | | FS | flight | flight status | | | status | | | | | | | ID | identification | contains the Mode A identification code | | | | | | MB | message | 56-bit MB field contains the message | | | Comm B | transmitted to the interrogator | | | | | | MD | message | 80-bit MD field contains one segment of a | | | Comm D | sequence of segments in the ELM Mode | ------------------------------------------------------------------------------4 _

Data transmitted for elementary surveillance The specific data related to the elementary surveillance are the following: - 24 bits A/C adress (coded in AA field of DF11) - flight number (MB field of DF20 or DF21 filled in with Binary Data Stores (BDS) 2.0 - transponder capability report (coded in CA field of DF11) - altitude/ground reporting (coded in AC field of DF4 or DF20) - flight status (coded in FS field of DF4) - RA report (MB field of DF20 or DF21 filled in with BDS 3.0) - Surveillance Identifier (SI) (coded in PI field of DF11)

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5 _

Data transmitted for enhanced surveillance (if the optional wiring provisions for enhanced surveillance/extended squitters are valitated) The specific parameters related to the enhanced surveillance are: - selected altitude - barometric pressure setting - roll angle - track angle rate - true track angle - ground speed - true air speed - magnetic heading - indicated airspeed - mach - barometric altitude rate - inertial vertical velocity Data is transmitted in MB field of BDS 4.0, 5.0 or 6.0 in DF20 or DF21, upon request from ground station.

6 _

Data transmitted in extended squitters (if the optional wiring provisions for enhanced surveillance/extended squitters are validated) The specific parameters related to the extended squitters are: - altitude - longitude - latitude - movement - ground track - flight number - E/W velocity - N/S velocity - vertical rate These data are transmitted in ME field of BDS 0.5, 0.6, 0.7, 0.8 or 0.9 in DF17. Extended squitters are automatically broadcast at different rates as shown in the following table. (Ref. Fig. 009)

(4) Not Applicable (5) Not Applicable

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ATC - Extended Squitters (Automatic Dependent Surveillance Broadcast (ADS-B)) DF17 Format Figure 009  R EFF : 106-149, 221-249, 251-299, 301-399,  Page 66 401-499, 501-509, 511-526, 528-599,  Feb 01/10   CES 



34-52-00

**ON A/C 201-220, (3) Principle of operation (Ref. Fig. 003) Each ground interrogator transmits its interrogations at the frequency of 1030 MHz in the form of a series of two pulses. Depending on the pulse intervals and numbers, they define four different interrogation modes: - Mode A interrogations - Mode C interrogations - Mode S all call interrogations - Mode S interrogations. After receiving these pulses, the transponder identifies and decodes the interrogations. Depending on the detected interrogation mode, the transponder transmits the identification of the aircraft or its barometric altitude. The transponder is provided with the Mode S Data Link capability. The transmission of the replies to the ground takes place on a carrier frequency of 1090 MHz. (a) Interrogations (Ref. Fig. 002) Four classes of interrogations are transmitted by the ground interrogator, they are: 1 _

Mode A or C interrogations A mode A or C interrogation consists of two pulses labelled P1 and P3. These pulses are transmitted by the directional antenna of the Secondary Surveillance Radar (SSR) and spaced according to the SSR mode of operation. A control pulse P2 is radiated by the omnidirectional antenna of the SSR two microseconds after the pulse P1 is transmitted from the directional antenna of the SSR. Amplitude of pulses P1 and P3 varies according to the position of the directional antenna. P1 and P3 are at higher amplitude than P2 when the aircraft flies in the antenna main beam. Amplitude of the pulse P2, also called side lobe suppression pulse, is constant whichever the position of the omnidirectional antenna. The aircraft receives the P1 pulse at a higher amplitude than P2. The aircraft transponder detects this amplitude difference and determines the interrogation to be a valid interrogation. When the transponder detects that P2 is within 6 dB of P1, in amplitude, it determines that the interrogation is not valid.

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2 _

Mode S all call interrogation (Ref. Fig. 007) A mode S all call interrogation consists of three pulses labelled P1, P3 and P4. They are transmitted by a directional antenna. A control pulse P2 (Side Lobe Suppression Pulse) is transmitted following P1 by an omnidirectional antenna. The detection of pulse P1, P2 and P3 is the same as for mode A or C interrogation. The transponder initiates a reply until the presence of the pulse P4 is detected. Upon detection of the pulse P4, the reply is terminated. If the width of the pulse P4 is 0.8 microseconds (mode A or mode C only all-call), no reply is transmitted. If the width of the pulse is 1.6 microseconds (mode S all-call), a mode S reply is generated 128 microseconds after the leading edge of the pulse P4.

3 _

Mode S interrogation (Ref. Fig. 008) A mode S interrogation consists of a preamble followed by a data block. The preamble consists of two equal transmitted pulses labelled P1 and P2 and spaced by two microseconds. The data block consists of a single pulse P6 with a synchro phase reversal modulation. Pulse P6 duration : short 15.5 microseconds, long 29.5 microseconds, Data block : 56 or 112 bits. The pulse P5, which is radiated by the omnidirectional antenna may be overlaid on P6 by the ground interrogator as a Side Lobe Suppression (SLS) signal in any mode S interrogation. The pulse P5 is spaced 0.4 microsecond from the synchro phase reversal.

(b) Encoded reply 1 _

Mode A or C reply A mode A or C reply consists of two framing pulses F1 and F2, separated by a 20.3 microseconds time interval. The encoding of the reply is done by means of the presence (1) or absence (0) of 13 reply pulses (12 pulses plus X pulse).

2 _

Mode S all call reply A mode S all call reply consists of a four-bit preamble followed by a data block. The data block contains 56 position modulated pulses.

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3 _

Mode S reply A mode S reply occurs after a mode S interrogation or a mode S all call interrogation (P4 duration 1.6 microseconds). A mode S reply consists of a four-bit preamble followed by a data block. The data block contains 56 (short) or 112 (long) position modulated pulses.

4 _

Mode S message content The minimum data link transponder supports all surveillance functions, in addition to bidirectional air-to-air data exchange, ground-to-air data uplink (Comm A), air-to-ground data downlink (Comm B), and multisite message protocol. In addition, the transponder is capable of receiving Extended Length Messages (ELMs) from the ground. ELMS are received in the Comm C format. ELM transmittals to the ground use the Comm D format (Note: Comm C and Comm D are future applications; Comm D is not available with this transponder). All discrete Mode S interrogations and replies (except the all-call reply) contain the 24-bit discrete address of the Mode S transponder upon which 24 error detection parity check bits are overlaid. In the all-call reply, the 24 parity check bits are overlaid on the Mode S interrogation address and the transponders discrete address is included in the text of the reply. The main function of Mode S is surveillance. To accomplish this function, the Mode S transponder uses the 56-bit transmissions (in each direction). In the 56-bit transmissions, the aircraft reports its altitude or ATCRBS 4096 code, and the flight status (airborne, on-ground, alert, Special Position Identification (SPI), etc. The discrete addressing and digital encoding of Mode S transmissions permit their use as a digital data link. The interrogation and reply formats of the Mode S system contain sufficient coding space to permit the transmission of data. These data transmissions may be used for air traffic control purposes, air-to-air data interchange for collision avoidance, or to provide flight advisory services such as weather reports, or Automated Terminal Information System (ATIS). Most Mode S data link transmissions will be handled as one 56-bit message included as part of a long 112-bit interrogation or reply. These transmissions include the message in addition to the surveillance data. Longer messages are transmitted using the Extended Length Message (ELM) capability. The ELM is capable of transmitting up to sixteen 80-bit message segments, either ground-to-air or air-to-ground. The ELM can be acknowledged with a single reply or interrogation. ELMs uplinked need not be replied to individually, but can be acknowledged in a reply containing a summary of the received interrogations. ELMs do not contain surveillance data. The following table gives the definition of uplink format message fields:

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------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AP | address parity | 24-bit address and parity overlaid | | | | | | AQ | acquisition | differentiates acquisition from non-acquisi- | | | | tion interrogations | | | | | | DI | designator | identifies the coding contained in the SD | | | identification | field | | | | | | II | interrogator | identifies the interrogator | | | identification | | | | | | | MA | message | 56-bit MA field contains messages directed | | | Comm A | to the A/C | | | | | | MC | message | 80-bit MC field contains one segment of a | | | Comm C | sequence of segments transmitted in ELM mode. | | | | | | MU | message | 56-bit MU messages contain information used | | | Comm U | in air-to-air exchanges | | | | | | NC | number of C | number of segments transmitted in ELM mode | | | segments | | | | | | | PC | protocol | operating commands of the transponder | | | | | | PR | probability | contains commands to the transponder to | | | of reply | specify the reply probability to the mode S | | | | only all-call interrogations (Allows | | | | operators to acquire closely spaced A/C). | | | | | | RC | reply | designates the transmitted segment as initial,| | | control | intermediate or final | | | | | | RL | reply | indicates if message is short or long | | | length | | | | | | | RR | reply | length and content of the reply information | | | request | requested by the interrogator | | | | | | SD | special | contains control codes affecting the link | | | designator | protocol | -------------------------------------------------------------------------------

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The table below gives the definition of downlink format message fields: ------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AA | address | contains the A/C mode S address | | | announced | | | | | | | AC | altitude | information containing the A/C altitude | | | code | | | | | | | AP | address | 24-bit address and parity overlaid | | | parity | | | | | | | CA | transponder | reports transponder capability | | | capability | | | | | | | DR | downlink | requests extraction of downlink messages from | | | request | the transponder by the interrogator | | | | | | FS | flight | flight status | | | status | | | | | | | ID | identification | contains the Mode A identification code | | | | | | MB | message | 56-bit MB field contains the message | | | Comm B | transmitted to the interrogator | | | | | | MD | message | 80-bit MD field contains one segment of a | | | Comm D | sequence of segments in the ELM Mode | ------------------------------------------------------------------------------(4) Operation **ON A/C 211-220, (Ref. Fig. 006B) **ON A/C 201-210, (Ref. Fig. 006C)

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**ON A/C 201-220, (a) Introduction The transponder is capable of operating with ATC Radar Beacon System interrogators, as well as mode S interrogators and is also designed to accept two antenna inputs for diversity operation. Diversity operation in a Mode S transponder is an added feature to improve air to air surveillance as part of a collision avoidance system. An additional feature of a Mode S transponder is the ability to send and receive data link messages via the reply and interrogation mode S message formats. (b) Simplified theory The transponder consists of four principal assemblies: the transmitter, the receiver, the I/O and processor circuit card and the power supply. Input signals (1030 MHz interrogations/uplinks) are received at one or both of the antennas. Each received antenna signal is pulse demodulated and sent to the processing circuits, where the diversity selection is made. The diversity selection determines which receiver provides the stronger (or first) signal. The selected received signal is then applied through a demodulator circuit to the processing circuits. The processing circuits determine if the interrogation is an ATC Radar Beacon System interrogation, a mode S interrogation addressed to the particular aircraft, or a mode S interrogation addressed to another aircraft. Depending upon the type of the interrogation, the processing circuits determine the proper reply (if one is required) and send the appropriate reply through a message processing circuit to the diversity switching circuits. The diversity switching circuits select the antenna that the reply will be transmitted through. The reply message is transmitted through the same antenna from which the selected received signal originated. - The I/O circuit is an interface circuit to receive serial ARINC 429 data, the 24 bit address input, the code altitude input and various discretes. The CPU provides the link between the I/O and the signal processing circuits. - The signal processing cicuits consist of a video processor, a PAM decoder and a message processor. The video processor analyzes the received signals ( pulses and pulse amplitude). If the received signal is valid, the PAM decoder determines the type of interrogation. Then the decoder ouput is sent to the message processor where appropriate reply format is generated.

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Page 72 Nov 01/07

- The message processor output is amplified and the resultant 1090 MHz transmit signal is applied to the antennas through a diplexer/diversity switch. - The received signals from the antennas are sent to the receiver stage. The 60 MHz IF output is used to drive the video processor and the message processor (DSPK function). The input of the receiver stage is filtered to reduce the susceptibility to HIRF signals. - The power supply is a pulse-width modulated switching regulator. It supplies all the necessary DC voltages required by the internal circuitry. An integrated monitoring function gives protection to the power supply circuits and reset signals to the CPUs each time primary power is applied. (c) Outputs The discrete output from transponder is : ------------------------------------------------------------------------------NAME ELECTRICAL LEVEL TO SIGNAL STATUS ------------------------------------------------------------------------------XPNDR FAIL OC/5VDC CTL UNIT - ATC 5VDC = FAULT ------------------------------------------------------------------------------(5) Not Applicable R

**ON A/C 251-299,

R R R R R R R R R R R R R R R R R R R

(3) Principle of operation (Ref. Fig. 003A) Each ground interrogator transmits its interrogations at the frequency of 1030 MHz in the form of a series of two pulses. Depending on the pulse intervals and numbers, they define three different interrogation modes. After receiving these pulses, the transponder identifies and decodes the interrogations. Depending on the detected interrogation mode, the transponder transmits either the identification of the aircraft or its barometric altitude or flight data. To perform these functions, the transponder is associated with a control unit defining the aircraft identification code, the Air Data/Inertial Reference Units (ADIRUs) the Flight Management and Guidance Computers (FMGCs) and the Traffic Collision Avoidance System (TCAS)(if installed). The transmission of the replies to the ground takes place on a carrier frequency of 1090 MHz. If the interrogation is sent by the side lobe of the radar a characteristic signal is sent allowing the transponder to disregard the interrogation.

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R R R

In addition to its specific transponder functions, it enables communication between the TCAS and a detected aircraft if equipped with the TCAS.

R R R R R R R

(a) Interrogations (Ref. Fig. 002) Three classes of interrogations are transmitted by the ground interrogator, they are: - Mode A or C interrogations - Mode S all call interrogations - Mode S interrogations.

R R R R R R R R R R

1 _

Mode A or C interrogation A mode A or C interrogation consists of two pulses labelled P1 and P3. A control pulse P2 is transmitted following the first interrogation pulse. P1 and P3 are radiated by a narrow rotating beam antenna. P2, also called the Side Lobe Suppression (SLS) pulse, is radiated by an omnidirectional antenna with an amplitude of 6 dB below P1 and P2 within the main lobe. P1 amplitude is greater than or equal to P2 amplitude from the greatest side lobe transmission of the antenna radiating P1.

R R R R R R R R R R R R R R R R R

2 _

Mode S all call interrogation (Ref. Fig. 007) A mode S all call interrogation consists of three transmitted pulses labelled P1, P3 and P4. A control pulse P2 (Side Lobe Suppression Pulse) is transmitted following P1. P1 amplitude is greater than or equal to P2 amplitude from the greatest side lobe transmission of the antenna radiating P1. P2 amplitude is at a level lower than 6 dB below P1 amplitude within the main lobe. P4 duration is 0.8 or 1.6 microseconds depending on the interrogation mode. If P4 is equal to 0.8 microseconds, this means that the interrogation only concerns conventional ATC mode A or C transponder, and consequently the Mode S transponder must not reply. If P4 is equal to 1.6 microseconds, this means that the mode S transponder must reply with mode S information.

R R R R R R

3 _

Mode S interrogation (Ref. Fig. 008) A mode S interrogation consists of a two-bit preamble followed by a data block. The preamble consists of two transmitted pulses labelled P1 and P2. The characteristics of P1 and P2 are the same as for

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R R R R R R R

the mode S all call interrogation, except that P2 amplitude is equal to P1. The data block consists of a single pulse P6 with a Differential Phase Shift Keying (DPSK) modulation. Pulse duration : short 15.5 microseconds, long 29.5 microseconds, Data block : 56 or 112 bits.

R

(b) Encoded reply

R R R R R

1 _

Mode A or C reply A mode A or C reply consists of two framing pulses F1 and F2, separated by a 20.3 microseconds time interval. The encoding of the reply is done by means of the presence (1) or absence (0) of 13 reply pulses (12 pulses plus X pulse).

R R R R

2 _

Mode S all-call reply A mode S all-call reply consists of a four-bit preamble followed by a data block. The data block contains 56 position modulated pulses.

R R R R R R R

3 _

Mode S reply A mode S reply occurs after a mode S interrogation or a mode S all call interrogation (P4 duration 1.6 microseconds). A mode S reply consists of a four-bit preamble followed by a data block. The data block contains 56 or 112 position modulated pulses. The replies are PPM coded.

R R R R R R R R R R R R R R R R R R

4 _

Mode S message contents The transponder must have the following Mode S message capabilities: - surveillance functions of both ATCRBS and Mode S ground sensors (UF=4.5 / DF=4.5) - surveillance functions of airborne interrogators (UF=0 /DF=0) - bi-directional air-to-air information exchange, COMM-U/V (UF=16 / DF=16) - ground-to-air data uplink, COMM-A (UF=20.21) - air-to-ground data downlink, COMM-B (DF=20.21) - ground-to-air Uplink Extended length message (UELM), COMM-C (UF=24) (if external ADLP is installed) - air-to-ground Downlink Extended length message (DELM), COMM-D (DF=24). (if external ADLP is installed) All discrete Mode S interrogations and replies (except the all-call reply) contain the 24-bit discrete address of the Mode S transponder upon which 24 error detection parity check

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R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R

bits are overlaid. In the all-call reply, the 24 parity check bits are overlaid on the Mode S interrogation address and the transponders discrete address is included in the text of the reply. The main function of Mode S is surveillance. To accomplish this function, the Mode S transponder uses the 56-bit transmissions (in each direction). In the 56-bit transmissions, the aircraft reports its altitude or ATCRBS 4096 code, and the flight status (airborne, on-ground, alert, Special Position Identification (SPI), etc. The discrete addressing and digital encoding of Mode S transmissions permit their use as a digital data link. The interrogation and reply formats of the Mode S system contain sufficient coding space to permit the transmission of data. These data transmissions may be used for air traffic control purposes, air-to-air data interchange for collision avoidance, or to provide flight advisory services such as weather reports, or Automated Terminal Information System (ATIS). Most Mode S data link transmissions will be handled as one 56-bit message included as part of a long 112-bit interrogation or reply. These transmission include the message in addition to the surveillance data. Longer messages are transmitted using the Extended Length Message (ELM) capability (if external ADLP is installed). The ELM is capable of transmitting up to sixteen 80-bit message segments at a rate of 8 per second, either ground-to-air or air-to-ground. The ELM can be acknowledged with a single reply or interrogation. ELMs uplinked need not be replied to individually, but can be acknowledged in a reply containing a summary of the received interrogations. ELMs do not contain surveillance data.

R R R R R R R R R R R R R R R R

a _

Mode S interrogation message formats All valid Mode S interrogation are listed here. The first 5 bits of the message indicate a UF message format. Items in brackets, e.g (AP:24) represent the AP field code, and the number of bits in the field 24. Underscored numbers represent unused fields and must not be processed. - TCAS Surveillance: UF=0 (0 0000) 3_ (RL:1) 4_ (AQ:1) 18_ (AP:24) - Surveillance, Altitude Request: UF=4 (0 0100) (PC:3) (RR:5) (DI:3) (SD:16) (AP:24) - Surveillance, Identity Request:

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R R R R R R R R R R R R R R R R R R R R

UF=5 (0 0101) (PC:3) (RR:5) (DI:3) (SD:16) (AP:24) - Mode S All-Call Interrogation: UF=11 (0 1011) (PR:4) (II:4) 19_ (AP:24) - Long TCAS Interrogation (COMM-U): UF=16 (1 0000) 3_ (RL:1) 4_ (AQ:1) 18_ (MU:56) (AP:24) - COMM-A Interrogation, Altitude: UF=20 (1 0100) (PC:3) (RR:5) (DI:3) (SD:16) (MA:56) (AP:24) - COMM-A Interrogation, Identity: UF=21 (1 0101) (PC:3) (RR:5) (DI:3) (SD:16) (MA:56) (AP:24) - Uplink Extended Length Message (UELM)/COMM-C Interrogation: UF=24 (1 1) (RC:2) (NC:4) (MC:80) (AP:24)

R R

NOTE : PC, RR, DI and SD subfields are undefined for ____ UF=20/21 broadcast interrogations.

R R R R R R R R R R R R R R R R R R R R R R

b _

Mode S messages downlink formats All valid Mode S replies are listed here. The first 5 bits of the message indicate a UF message format. Items in brackets, e.g (AP:24) represent the AP field code, and the number of bits in the field 24. Underscored numbers representing unused fields must be set to zero. - TCAS Surveillance: DF=0 (0 0000) (VS:1) 2_ (SL:3) 2_ (RI:4) 2_ (AC:13) (AP:24) - Surveillance, Altitude: DF=4 (0 0100) (FS:3) (DR:5) (UM:6) (AC:13) (AP:24) - Surveillance, Identity: DF=5 (0 0101) (FS:3) (DR:5) (UM:6) (ID:13) (AP:24) - Mode S All-Call Reply, ATCRBS/Mode S All-Call Reply, Mode S Squitter:

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R R R R R R R R R R R R R R R R R R R R

DF=11 (0 1011) (CA:3) (AA:24) (PI:24) - Long TCAS Reply (COMM-V): DF=16 (1 0000) (VS:1) 2_ (SL:3) 2_ (RI:4) (AC:13) (MV:56) (AP:24) - Extended Squitters: DF=17 (1 0001) (CA:3) (AA:24) (ME:56) (PI:24) - COMM-B Reply, Altitude: DF=20 (1 0100) (FS:3) (DR:5) (UM:6) (AC:13) (MB:56) (AP:24) - COMM-B Reply, Identity: DF=21 (1 0101) (FS:3) (DR:5) (UM:6) (ID:13) (MB:56) (AP:24) - Downlink Extended Length Message (DELM)/COMM-D: DF=24 (1 1) 1_ (KE:1) (ND:4) (MD:80) (AP:24)

R R R

c _

Mode S interrogation data field definition The following table gives the definition of uplink format message fields:

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R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R

------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AP | address parity | 24-bit address and parity overlaid | | | | | | AQ | acquisition | differentiates acquisition from non-acquisi- | | | | tion interrogations | | | | | | DI | designator | identifies the coding contained in the SD | | | identification | field | | | | | | II | interrogator | identifies the interrogator | | | identification | | | | | | | MA | message | 56-bit MA field contains messages directed | | | Comm A | to the A/C | | | | | | MC | message | 80-bit MC field contains one segment of a | | | Comm C | sequence of segments transmitted in ELM mode. | | | | | | MU | message | 56-bit MU messages contains information used | | | Comm U | in air-to-air exchanges | | | | | | NC | number of C | number of segments transmitted in ELM mode | | | segments | | | | | | | PC | protocol | operating commands of the transponder | | | | | | PR | probability | contains commands to the transponder to | | | of reply | specify the reply probability to the mode S | | | | only all-call interrogations (Allows | | | | operators to acquire closely spaced A/C). | | | | | | RC | reply | designates the transmitted segment as initial,| | | control | intermediate or final | | | | | | RL | reply | indicates if message is short or long | | | length | | | | | | | RR | reply | length and content of the reply information | | | request | requested by the interrogator | | | | | | SD | special | contains control codes affecting the link | | | designator | protocol | -------------------------------------------------------------------------------

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R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R

The table below gives the definition of downlink format message fields: ------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AA | address | contains the A/C mode S address | | | announced | | | | | | | AC | altitude | information containing the A/C altitude | | | code | | | | | | | AP | address | 24-bit address and parity overlaid | | | parity | | | | | | | CA | transponder | reports transponder capability | | | capability | | | | | | | DR | downlink | requests extraction of downlink messages from | | | request | the transponder by the interrogator | | | | | | FS | flight | flight status | | | status | | | | | | | ID | identification | contains the Mode A identification code | | | | | | MB | message | 56-bit MB field contains the message | | | Comm B | transmitted to the interrogator | | | | | | MD | message | 80-bit MD field contains one segment of a | | | Comm D | sequence of segments in the ELM Mode | -------------------------------------------------------------------------------

R R R R R R R R R R R

(c) Data transmitted for elementary surveillance The specific data related to the elementary surveillance are the following: - 24 bits A/C adress (coded in AA field of DF11) - flight number (MB field of DF20 or DF21 filled in with Binary Data Stores (BDS) 2.0 - transponder capability report (coded in CA field of DF11) - altitude/ground reporting (coded in AC field of DF4 or DF20) - flight status (coded in FS field of DF4) - RA report (MB field of DF20 or DF21 filled in with BDS 3.0) - Surveillance Identifier (SI) (coded in PI field of DF11)

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R R R R R R R R R R R R R R R R R R

(d) Data transmitted for enhanced surveillance (if the optional wiring provisions for enhanced surveillance/extended squitters are validated). The specific parameters related to the enhanced surveillance are: - selected altitude - barometric pressure setting - roll angle - track angle rate - true track angle - ground speed - true air speed - magnetic heading - indicated airspeed - mach - barometric altitude rate - inertial vertical velocity Data is transmitted in MB field of BDS 4.0, 5.0 or 6.0 in DF20 or DF21, upon request from ground station.

R R R R R R R R R R R R R R R R R R

(e) Data transmitted in extended squitters (if the optional wiring provisions for enhanced surveillance/extended squitters are validated). The specific parameters related to the extended squitters are: - altitude - longitude - latitude - movement - ground track - flight number - E/W velocity - N/S velocity - vertical rate Data is transmitted in ME field of BDS 0.5, 0.6, 0.7, 0.8 or 0.9 in DF17. Extended squitters are automatically broadcast at different rates as shown in the following table. (Ref. Fig. 009)

R R R R R

(4) Operation (Ref. Fig. 006A) The transponder consists of a receiver, a transmitter, an interface/Central Processing Unit (CPU) assembly and a power supply/modulator assembly.

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R R R R R R R R R

(a) Receiver The receiver (top and bottom receiver channels), which consists of a ceramic pre-selector filter, self-test coupler, low noise amplifier, mixer, Intermediate Frequency (IF) amplifier and band-pass filter, logarithmic amplifier (log amp) detectors and a Differential Phase Shift Keying (DPSK) demodulator, has the circuitry required to accept the Radio Frequency (RF) signal and convert it into a voltage signal to be used by the signal processing elements.

R R R R R R R

(b) Transmitter The transmitter, which consists of a 1090 MHz local oscillator, RF transmitter gain stages, transmit/receive pin diode switches, forward power and antenna monitors and a low-pass harmonic filter, is unique in that it is an all solid-state unit with the capability for the Mode S message requirements, which impose increased operating requirements on the transmitter.

R R R R R R R R R R R R R

(c) Interface/CPU assembly The interface/CPU assembly contains a microprocessor and supporting memory and logic circuitry. The support circuitry includes Flash EPROM memory devices for the operational program, boot program and system data, system RAM memory for program execution, and an EEPROM memory for calibration and self-test error logging. The assembly contains Application Specific Integrated Circuits (ASICs) for the RF processing functions (interrogations and replies), and communication over ARINC 429 data buses. In addition to the RF ASIC the assembly contains circuitry for processing receiver video signals. The assembly supports all external interface functions, including processing discrete inputs/outputs and analog synchro interfaces.

R R R R R R R R R R R R R

(d) Power supply/modulator assembly The transponder has its own internal self-contained power supply. The 115V, 400 Hz power supply input is applied through the rear connector of the unit. The power supply modulator assembly has an EMI filter, 115VAC to DC converter, power interrupt monitor, +60VDC switching supply for transmitter energy storage, a fly-back supply for generating internal unit voltages, and a +35VDC and +28VDC regulator for supplying transmitter voltages. The assembly contains PIN diode driver circuitry for driving the RF transmit/receive switches, pulse and envelope modulator circuitry for modualting the RF transistors. The assembly also contains a self-test modulator and power supply monitors.

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(5) Theory of operation Interrogations which are received by the transponder are filtered and amplified by the 1030MHz receiver, converted to a 60MHz IF by the mixer and IF filter on the receiver. The interrogations (pulses) are then converted to a base-band analog video signals by the log amps. The DPSK portion of a Mode S interrogation is turned into a digital video signal by the DPSK demodulator. The analog video signal is then processed by the video processor circuit on the interface/CPU assembly, where it is converted to a digital video signal. The digital video signals and DPSK video signals are then processed by the RF ASIC, which determines the validity and type of interrogation. If a valid interrogation is received, the RF ASIC in conjunction with the microprocessor and software generates a reply. The RF ASIC generates digital pulses which are used to modulate the transmitter. The digital signals are converted to analog modulator signals by the pulse and envelope modulator circuitry on the power supply/modulator. The analog modulator signals are then used to turn the transmitter stages on or off as is appropriate to generate the pulsed replies. R

**ON A/C 501-509, 511-526, 528-599, (3) Principle of operation (Ref. Fig. 003A) Each ground interrogator transmits its interrogations at the frequency of 1030 MHz in the form of a series of two pulses. Depending on the pulse intervals and numbers, they define three different interrogation modes. After receiving these pulses, the transponder identifies and decodes the interrogations. Depending on the detected interrogation mode, the transponder transmits either the identification of the aircraft or its barometric altitude or flight data. To perform these functions, the transponder is associated with a control unit defining the aircraft identification code, the Air Data/Inertial Reference Units (ADIRUs) the Flight Management and Guidance Computers (FMGCs) and the Traffic Collision Avoidance System (TCAS)(if installed). The transmission of the replies to the ground takes place on a carrier frequency of 1090 MHz. If the interrogation is sent by the side lobe of the radar a characteristic signal is sent allowing the transponder to disregard the interrogation. In addition to its specific transponder functions, it enables communication between the TCAS and a detected aircraft if equipped with the TCAS.

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(a) Interrogations (Ref. Fig. 002) Three classes of interrogations are transmitted by the ground interrogator, they are: - Mode A or C interrogations - Mode S all call interrogations - Mode S interrogations. 1 _

Mode A or C interrogation A mode A or C interrogation consists of two pulses labelled P1 and P3. A control pulse P2 is transmitted following the first interrogation pulse. P1 and P3 are radiated by a narrow rotating beam antenna. P2, also called the Side Lobe Suppression (SLS) pulse, is radiated by an omnidirectional antenna with an amplitude of 6 dB below P1 and P2 within the main lobe. P1 amplitude is greater than or equal to P2 amplitude from the greatest side lobe transmission of the antenna radiating P1.

2 _

Mode S all call interrogation (Ref. Fig. 007) A mode S all call interrogation consists of three transmitted pulses labelled P1, P3 and P4. A control pulse P2 (Side Lobe Suppression Pulse) is transmitted following P1. P1 amplitude is greater than or equal to P2 amplitude from the greatest side lobe transmission of the antenna radiating P1. P2 amplitude is at a level lower than 6 dB below P1 amplitude within the main lobe. P4 duration is 0.8 or 1.6 microseconds depending on the interrogation mode. If P4 is equal to 0.8 microseconds, this means that the interrogation only concerns conventional ATC mode A or C transponder, and consequently the Mode S transponder must not reply. If P4 is equal to 1.6 microseconds, this means that the mode S transponder must reply with mode S information.

3 _

Mode S interrogation (Ref. Fig. 008) A mode S interrogation consists of a two-bit preamble followed by a data block. The preamble consists of two transmitted pulses labelled P1 and P2. The characteristics of P1 and P2 are the same as for the mode S all call interrogation, except that P2 amplitude is equal to P1. The data block consists of a single pulse P6 with a Differential Phase Shift Keying (DPSK) modulation.

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Pulse duration : short 15.5 microseconds, long 29.5 microseconds, Data block : 56 or 112 bits. (b) Encoded reply 1 _

Mode A or C reply A mode A or C reply consists of two framing pulses F1 and F2, separated by a 20.3 microseconds time interval. The encoding of the reply is done by means of the presence (1) or absence (0) of 13 reply pulses (12 pulses plus X pulse).

2 _

Mode S all-call reply A mode S all-call reply consists of a four-bit preamble followed by a data block. The data block contains 56 position modulated pulses.

3 _

Mode S reply A mode S reply occurs after a mode S interrogation or a mode S all call interrogation (P4 duration 1.6 microseconds). A mode S reply consists of a four-bit preamble followed by a data block. The data block contains 56 or 112 position modulated pulses. The replies are PPM coded.

4 _

Mode S message contents The transponder must have the following Mode S message capabilities: - surveillance functions of both ATCRBS and Mode S ground sensors (UF=4.5 / DF=4.5) - surveillance functions of airborne interrogators (UF=0 /DF=0) - bi-directional air-to-air information exchange, COMM-U/V (UF=16 / DF=16) - ground-to-air data uplink, COMM-A (UF=20.21) - air-to-ground data downlink, COMM-B (DF=20.21) All discrete Mode S interrogations and replies (except the all-call reply) contain the 24-bit discrete address of the Mode S transponder upon which 24 error detection parity check bits are overlaid. In the all-call reply, the 24 parity check bits are overlaid on the Mode S interrogation address and the transponders discrete address is included in the text of the reply. The main function of Mode S is surveillance. To accomplish this function, the Mode S transponder uses the 56-bit transmissions (in each direction). In the 56-bit transmissions, the aircraft reports its altitude or ATCRBS

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4096 code, and the flight status (airborne, on-ground, alert, Special Position Identification (SPI), etc. The discrete addressing and digital encoding of Mode S transmissions permit their use as a digital data link. The interrogation and reply formats of the Mode S system contain sufficient coding space to permit the transmission of data. These data transmissions may be used for air traffic control purposes, air-to-air data interchange for collision avoidance, or to provide flight advisory services such as weather reports, or Automated Terminal Information System (ATIS). Most Mode S data link transmissions will be handled as one 56-bit message included as part of a long 112-bit interrogation or reply. These transmission include the message in addition to the surveillance data. a _

Mode S interrogation message formats All valid Mode S interrogation are listed here. The first 5 bits of the message indicate a UF message format. Items in brackets, e.g (AP:24) represent the AP field code, and the number of bits in the field 24. Underscored numbers represent unused fields and must not be processed. - TCAS Surveillance: UF=0 (0 0000) 3_ (RL:1) 4_ (AQ:1) 18_ (AP:24) - Surveillance, Altitude Request: UF=4 (0 0100) (PC:3) (RR:5) (DI:3) (SD:16) (AP:24) - Surveillance, Identity Request: UF=5 (0 0101) (PC:3) (RR:5) (DI:3) (SD:16) (AP:24) - Mode S All-Call Interrogation: UF=11 (0 1011) (PR:4) (II:4) 19_ (AP:24) - Long TCAS Interrogation (COMM-U): UF=16 (1 0000) 3_ (RL:1) 4_ (AQ:1) 18_ (MU:56) (AP:24) - COMM-A Interrogation, Altitude: UF=20 (1 0100) (PC:3) (RR:5) (DI:3) (SD:16) (MA:56) (AP:24) - COMM-A Interrogation, Identity: UF=21 (1 0101) (PC:3) (RR:5) (DI:3) (SD:16) (MA:56) (AP:24)

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NOTE : PC, RR, DI and SD subfields are undefined for ____ UF=20/21 broadcast interrogations. b _

Mode S messages downlink formats All valid Mode S replies are listed here. The first 5 bits of the message indicate a UF message format. Items in brackets, e.g (AP:24) represent the AP field code, and the number of bits in the field 24. Underscored numbers representing unused fields must be set to zero. - TCAS Surveillance: DF=0 (0 0000) (VS:1) 2_ (SL:3) 2_ (RI:4) 2_ (AC:13) (AP:24) - Surveillance, Altitude: DF=4 (0 0100) (FS:3) (DR:5) (UM:6) (AC:13) (AP:24) - Surveillance, Identity: DF=5 (0 0101) (FS:3) (DR:5) (UM:6) (ID:13) (AP:24) - Mode S All-Call Reply, ATCRBS/Mode S All-Call Reply, Mode S Squitter: DF=11 (0 1011) (CA:3) (AA:24) (PI:24) - Long TCAS Reply (COMM-V): DF=16 (1 0000) (VS:1) 2_ (SL:3) 2_ (RI:4) (AC:13) (MV:56) (AP:24) - Extended Squitters: DF=17 (1 0001) (CA:3) (AA:24) (ME:56) (PI:24) - COMM-B Reply, Altitude: DF=20 (1 0100) (FS:3) (DR:5) (UM:6) (AC:13) (MB:56) (AP:24) - COMM-B Reply, Identity: DF=21 (1 0101) (FS:3) (DR:5) (UM:6) (ID:13) (MB:56) (AP:24)

c _

Mode S interrogation data field definition The following table gives the definition of uplink format message fields:

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------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AP | address parity | 24-bit address and parity overlaid | | | | | | AQ | acquisition | differentiates acquisition from non-acquisi- | | | | tion interrogations | | | | | | DI | designator | identifies the coding contained in the SD | | | identification | field | | | | | | II | interrogator | identifies the interrogator | | | identification | | | | | | | MA | message | 56-bit MA field contains messages directed | | | Comm A | to the A/C | | | | | | MU | message | 56-bit MU messages contains information used | | | Comm U | in air-to-air exchanges | | | | | | NC | number of C | number of segments transmitted in ELM mode | | | segments | | | | | | | PC | protocol | operating commands of the transponder | | | | | | PR | probability | contains commands to the transponder to | | | of reply | specify the reply probability to the mode S | | | | only all-call interrogations (Allows | | | | operators to acquire closely spaced A/C). | | | | | | RC | reply | designates the transmitted segment as initial,| | | control | intermediate or final | | | | | | RL | reply | indicates if message is short or long | | | length | | | | | | | RR | reply | length and content of the reply information | | | request | requested by the interrogator | | | | | | SD | special | contains control codes affecting the link | | | designator | protocol | -------------------------------------------------------------------------------

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The table below gives the definition of downlink format message fields: ------------------------------------------------------------------------------| DESIGNATOR | FIELD | INDICATION | ------------------------------------------------------------------------------| AA | address | contains the A/C mode S address | | | announced | | | | | | | AC | altitude | information containing the A/C altitude | | | code | | | | | | | AP | address | 24-bit address and parity overlaid | | | parity | | | | | | | CA | transponder | reports transponder capability | | | capability | | | | | | | DR | downlink | requests extraction of downlink messages from | | | request | the transponder by the interrogator | | | | | | FS | flight | flight status | | | status | | | | | | | ID | identification | contains the Mode A identification code | | | | | | MB | message | 56-bit MB field contains the message | | | Comm B | transmitted to the interrogator | | | | | ------------------------------------------------------------------------------(c) Data transmitted for elementary surveillance The specific data related to the elementary surveillance are the following: - 24 bits A/C adress (coded in AA field of DF11) - flight number (MB field of DF20 or DF21 filled in with Binary Data Stores (BDS) 2.0 - transponder capability report (coded in CA field of DF11) - altitude/ground reporting (coded in AC field of DF4 or DF20) - flight status (coded in FS field of DF4) - RA report (MB field of DF20 or DF21 filled in with BDS 3.0) - Surveillance Identifier (SI) (coded in PI field of DF11) (d) Data transmitted for enhanced surveillance (if the optional wiring provisions for enhanced surveillance/extended squitters are validated) The specific parameters related to the enhanced surveillance are:

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- selected altitude - barometric pressure setting - roll angle - track angle rate - true track angle - ground speed - true air speed - magnetic heading - indicated airspeed - mach - barometric altitude rate - inertial vertical velocity Data is transmitted in MB field of BDS 4.0, 5.0 or 6.0 in DF20 or DF21, upon request from ground station. (e) Data transmitted in extended squitters (if the optional wiring provisions for enhanced surveillance/extended squitters are validated) The specific parameters related to the extended squitters are: - altitude - longitude - latitude - movement - ground track - flight number - E/W velocity - N/S velocity - vertical rate Data is transmitted in ME field of BDS 0.5, 0.6, 0.7, 0.8 or 0.9 in DF17. Extended squitters are automatically broadcast at different rates as shown in the following table. (Ref. Fig. 009) (4) Operation (Ref. Fig. 006D) The transponder consists of a receiver, a transmitter, an interface/Central Processing Unit (CPU) assembly and a power supply/modulator assembly. (a) Receiver The receiver (top and bottom receiver channels), which consists of a ceramic pre-selector filter, self-test coupler, low noise amplifier, mixer, Intermediate Frequency (IF) amplifier and band-pass filter, logarithmic amplifier (log amp) detectors and a Differential Phase Shift Keying (DPSK) demodulator, has the circuitry required to accept the Radio Frequency (RF) signal and

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convert it into a voltage signal to be used by the signal processing elements. (b) Transmitter The transmitter, which consists of a 1090 MHz local oscillator, RF transmitter gain stages, transmit/receive pin diode switches, forward power and antenna monitors and a low-pass harmonic filter, is unique in that it is an all solid-state unit with the capability for the Mode S message requirements, which impose increased operating requirements on the transmitter. (c) Interface/CPU assembly The interface/CPU assembly contains a microprocessor and supporting memory and logic circuitry. The support circuitry includes Flash EPROM memory devices for the operational program, boot program and system data, system RAM memory for program execution, and an EEPROM memory for calibration and self-test error logging. The assembly contains Application Specific Integrated Circuits (ASICs) for the RF processing functions (interrogations and replies), and communication over ARINC 429 data buses. In addition to the RF ASIC the assembly contains circuitry for processing receiver video signals. The assembly supports all external interface functions, including processing discrete inputs/outputs and analog synchro interfaces. (d) Power supply/modulator assembly The transponder has its own internal self-contained power supply. The 115V, 400 Hz power supply input is applied through the rear connector of the unit. The power supply modulator assembly has an EMI filter, 115VAC to DC converter, power interrupt monitor, +60VDC switching supply for transmitter energy storage, a fly-back supply for generating internal unit voltages, and a +35VDC and +28VDC regulator for supplying transmitter voltages. The assembly contains PIN diode driver circuitry for driving the RF transmit/receive switches, pulse and envelope modulator circuitry for modualting the RF transistors. The assembly also contains a self-test modulator and power supply monitors. (5) Theory of operation Interrogations which are received by the transponder are filtered and amplified by the 1030MHz receiver, converted to a 60MHz IF by the mixer and IF filter on the receiver. The interrogations (pulses) are then converted to a base-band analog video signals by the log amps. The DPSK portion of a Mode S interrogation is turned into a digital video signal by the DPSK demodulator. The analog video signal is then processed by the video processor circuit on the interface/CPU

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assembly, where it is converted to a digital video signal. The digital video signals and DPSK video signals are then processed by the RF ASIC, which determines the validity and type of interrogation. If a valid interrogation is received, the RF ASIC in conjunction with the microprocessor and software generates a reply. The RF ASIC generates digital pulses which are used to modulate the transmitter. The digital signals are converted to analog modulator signals by the pulse and envelope modulator circuitry on the power supply/modulator. The analog modulator signals are then used to turn the transmitter stages on or off as is appropriate to generate the pulsed replies. **ON A/C ALL B. ATC/TCAS Control Unit (Ref. Fig. 010) The processor-based unit conforms to the ARINC 718 specification. The front panel is integrally lit by clear 5V lamps and features : - a liquid crystal display window in which the identification code is displayed - an ATC FAIL indicator light which indicates a transponder failure - a IDENT pushbutton switch - an ALT RPTG/ON/OFF switch which controls the transmission of altitude data from the transponder to the ATC ground control stations - a keyboard to select the four-digit transmit code (from 0000 to 7777) - a 1/2 selector switch which enables the operation of the ATC system 1 or 2 - a STBY/AUTO/ON selector switch which enables the ATC operating modes - a TCAS mode selector switch (STBY/TA/TA-RA) which enables the ATC/TCAS operating modes (Ref. 34-43-00 for more details). - a THRT/ALL/ABV/BLW selector switch which controls the type of traffic to be displayed as well as the above and below vertical altitude for traffic advisory. According to the 1/2 selection, the processor 1 or 2 controls the functions of the unit. Each processor can compensate for the other in case of failure. The selected processor reads the switch selections and : - drives the LCD display - formats the ARINC control word. In case of transponder failure, two independent circuits control : - the failure indicator light - the failure mode of the processor.

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ATC/TCAS - Control Unit Figure 010   R EFF : ALL  34-52-00    CES

 

Page 93 May 01/09

C. Antenna (Ref. Fig. 011) The L-band antenna is a short stub, all aluminum blade type which is completely sealed to prevent failure from moisture incursion. It is vertically polarized, has an impedance of 50 ohms, a Voltage Standing Wave Ratio (VSWR) of 1,5 : 1 and operates in the 960 MHz to 1220 MHz frequency band. Lightning protection is provided to prevent damage to the antenna and the transponder. Four antennas must be provided on the aircraft. The desire for improved upper hemisphere coverage usually leads to a choice of upper and lower mounting locations for the transponder antennas on the aircraft. 7. Operation _________ A. Control (Ref. Fig. 004) (1) In normal operation, you select the ATC 1(2) through the 1/2 switch on the control unit in either position 1 or 2. A STBY/AUTO/ON selector switch enables the functions given below: - in STBY position: the two transponders are electrically supplied but do not operate - in AUTO position: the selected transponder operates in flight but operates only in mode S on ground - in ON position: the selected transponder operates when the aircraft is in flight or on ground. R R

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

R R

(Ref. Fig. 012) **ON A/C ALL (2) Upon energization of the aircraft or modification of system selection, the last ATC code selected is displayed before the new code selection. This code comes into view on the display window of the control unit. When you set the ALT RPTG/ON/OFF switch to ON, the altitude information transmission of the selected transponder is enabled. (3) When you push the IDENT pushbutton switch (ON configuration), this generates an additional identification pulse in the reply signal.

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Page 95 May 01/09

R R

ATC - Transponder - Modes of Operation Figure 012

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(4) With failure of the ATC/TCAS control unit, the transponder continues to transmit the last displayed code. No new code selection is possible. (5) In addition, a suppressor coaxial connects the ATC tranponders to the Distance Measuring Equipment (DME) interrogators. This prevents transmission from one system while the other is in reception mode. This is necessary because the ATC and the DME systems operate on the same frequency range. B. Reconfiguration Switching (Ref. Fig. 004) In normal configuration, each ATC receives the altitude information from its corresponding Air Data/Inertial Reference Unit (ATC1 from ADIRU1, ATC2 from ADIRU2). With failure of the ADIRU corresponding to the serviceable transponder, the pilot can select the altitude information from the ADIRU 3. This selection is through the AIR DATA selector switch installed on panel 8VU on the center pedestal. 8. Test ____ **ON A/C 001-049, 101-105, 151-199, A. Maintenance Test (Ref. Fig. 013) It is possible to do the maintenance tests with the centralized fault-display system (CFDS). The primary components of the CFDS are : - the Multipurpose Control and Display Unit (MCDU) - the Centralized Fault Display Interface Unit (CFDIU) - the Built-In Test Equipment (BITE) internal to the ATC transponder. It is possible to perform these tests on the ground only. To get the ATC 1(2) page on the MCDU: - select of the SYSTEM REPORT/TEST item on the CFDS menu - then, push the line key adjacent to the ATC 1(2) indication on the NAV menu. The test sequence starts when you push the line key adjacent to the TEST indication on the ATC 1(2) page. After the INTERFACE TEST selection, the message : PLEASE CHECK IF THE CONTROL PANEL SWITCH IS ON SYSTEM (1 OR 2) AND PRESS TEST KEY is displayed on the MCDU.

R

(1) Not Applicable (2) Not Applicable

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ATC - Maintenance Test Procedure - ATC Menu Figure 013

R

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**ON A/C 051-099, A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the ATC system. The BITE of the ATC transponder is connected to the CFDIU. The unit tested is the ATC transponder. The BITE: - transmits permanently ATC system status and its identification message to the CFDIU - memorizes the faults which occurred during the last 63 flight legs - monitors data inputs from the various peripherals (FMGC, ADIRU, ATC CTL UNIT and CFDIU) - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the interactive mode. (a) Normal mode During the normal mode the BITE monitors cyclically the status of the ATC system. It transmits its information to the CFDIU during the flight concerned. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 100 ms by an ARINC 429 message with label 350. (b) Interactive mode: The interactive mode can only be activated on the ground. This mode enables communication between the CFDIU and the ATC transponder BITE by means of the MCDU. (Ref. Fig. 013A, 014, 015, 016, 017, 018) All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer. The ATC interactive mode is composed of: - LAST LEG REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the last flight. - PREVIOUS LEGS REPORT

R

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ATC Maintenance Test Procedure - ATC Menu Figure 013A

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ATC Maintenance Test Procedure - ATC Menu Figure 013B

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ATC Maintenance Test Procedure - ATC Menu Figure 013C

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ATC Maintenance Test Procedure - ATC Menu Figure 013D

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ATC Maintenance Test Procedure - ATC Menu Figure 013E

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ATC Maintenance Test Procedure - Last Leg Report - Previous Legs Report - LRU Ident R Figure 014  R EFF : 051-099,  Page A5   Feb 01/10   CES 



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ATC Maintenance Test Procedure - Last Leg Report - Previous Legs Report - LRU Ident R Figure 014A  R EFF : 106-149, 221-249, 301-399, 401-499,  Page A6   Feb 01/10   CES 



34-52-00

ATC Maintenance Test Procedure - Last Leg Report - Previous Legs Report - LRU Ident R Figure 014B  R EFF : 201-210,  Page A7   Feb 01/10   CES 



34-52-00

ATC Maintenance Test Procedure - Last Leg Report - Previous Legs Report - LRU Ident R Figure 014C  R EFF : 211-220,  Page A8   Feb 01/10   CES 



34-52-00

ATC Maintenance Test Procedure - Last Leg Report - Previous Legs Report - LRU Ident R Figure 014D  R EFF : 251-299,  Page A9   Feb 01/10   CES 



34-52-00

ATC Maintenance Test Procedure - ATC Menu Figure 014E

R

  R EFF : 501-509, 511-526, 528-599,  34-52-00    CES

 

Page A10 Feb 01/10

ATC Maintenance Test Procedure - Trouble Shooting Data - Class 3 Faults Figure 015

R

  R EFF : 051-099,  34-52-00    CES

 

Page A11 Feb 01/10

ATC Maintenance Test Procedure - Trouble Shooting Data Figure 015A

R

  R EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00    CES

 

Page A12 Feb 01/10

ATC Maintenance Test Procedure - Trouble Shooting Data - Ground Scanning Figure 015B

R

  R EFF : 201-210,  34-52-00    CES

 

Page A13 Feb 01/10

ATC Maintenance Test Procedure - Trouble Shooting Data - Ground Scanning Figure 015C

R

  R EFF : 211-220,  34-52-00    CES

 

Page A14 Feb 01/10

ATC Maintenance Test Procedure - Trouble Shooting Data - Class 3 Faults Figure 015D

R

  R EFF : 251-299,  34-52-00    CES

 

Page A15 Feb 01/10

ATC Maintenance Test Procedure - Ground Report Figure 016

R

  R EFF : 051-099,  34-52-00    CES

 

Page A16 Feb 01/10

ATC Maintenance Test Procedure - Ground Report Figure 016A

R

  R EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00    CES

 

Page A17 Feb 01/10

ATC Maintenance Test Procedure - Ground Report - Class 3 Faults Figure 016B

R

  R EFF : 201-210,  34-52-00    CES

 

Page A18 Feb 01/10

ATC Maintenance Test Procedure - Ground Report - Class 3 Faults Figure 016C

R

  R EFF : 211-220,  34-52-00    CES

 

Page A19 Feb 01/10

ATC Maintenance Test Procedure - Ground Report Figure 016D

R

  R EFF : 251-299,  34-52-00    CES

 

Page A20 Feb 01/10

ATC Maintenance Test Procedure - Configuration Data Figure 017

R

  R EFF : 051-099,  34-52-00    CES

 

Page A21 Feb 01/10

ATC Maintenance Test Procedure - Discrete Configuration 1/4 Figure 017A

R

  R EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00    CES

 

Page A22 Feb 01/10

ATC Maintenance Test Procedure - Discrete Status - Test Figure 017B

R

  R EFF : 201-210,  34-52-00    CES

 

Page A23 Feb 01/10

ATC Maintenance Test Procedure - Discrete Data - Test Figure 017C

R

  R EFF : 211-220,  34-52-00    CES

 

Page A24 Feb 01/10

ATC Maintenance Test Procedure - Discrete Configuration 1/4 Figure 017D

R

  R EFF : 251-299,  34-52-00    CES

 

Page A25 Feb 01/10

ATC Maintenance Test Procedure - Test Figure 018

R

  EFF : 051-099,  34-52-00    CES

 

Page A26 Feb 01/10

-

-

-

-

The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the previous flights. When no fault has been detected during the last 63 flights, the NO FAULT DETECTED message is displayed. LRU IDENTIFICATION The purpose of this item is to present the Part Number (PN), the Serial Number (SN) and the Software Number (SW/N) of the component. TROUBLE SHOOTING DATA This item allows to analyze the snapshot of the recorded failure to detect the software bugs. CLASS 3 FAULTS The purpose of this item is to present the class 3 fault messages that appeared during the last flight. There is no date and no failure classification. GROUND REPORT The purpose of this item is to present the class 1, 2 or 3 internal failures when they are detected on ground. CONFIGURATION DATA The purpose of this item is to present in three pages, each formatted differently, the current configuration and discrete data and format the data for display on the MCDU. TEST The activation of this manual test shall only be allowed on the ground. The results of the test are transmitted to the CFDIU but are not memorized.

(2) Reporting functions -------------------------------------------------------------------------| REPORTED INTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATCi (1SHi) | 1 | 34-52-33 | | ATC1 TOP ANTENNA (7SH3) | 1 | 34-52-11 | | ATC1 BOT ANTENNA (7SH1) | 1 | 34-52-11 | | ATC2 TOP ANTENNA (7SH4) | 1 | 34-52-11 | | ATC2 BOT ANTENNA (7SH2) | 1 | 34-52-11 | | WRG : MODE S ADRESS/ATCi (1SHi) | 1 | 34-52-33 | --------------------------------------------------------------------------

  R EFF : 051-099,  34-52-00    CES

 

Page A27 Feb 01/10

-------------------------------------------------------------------------| REPORTED EXTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATC CTL PNL (3SH)/ATCi (1SHi) | 1 | 34-52-12 | | ADIRU i/3(1FPi/3)/ATCi (1SHi) | 1 | 34-12-34 | | TCAS(1SG)/ATCi(1SHi) | 3 | 34-43-34 | | CFDIU(1TW)/ATCi(1SHi) | 3 | 31-32-34 | | FMGCi(1CAi)/ATCi(1SHi) | 3 | 22-83-34 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | | LGCIUi(5GAi)/ATCi(1SHi) | 3 | 32-31-71 | -------------------------------------------------------------------------**ON A/C 106-149, 221-249, 301-399, 401-499, A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the ATC system. The BITE of the ATC transponder is connected to the CFDIU. The unit tested is the ATC transponder. The BITE: - transmits permanently ATC system status and its identification message to the CFDIU - memorizes the faults which occurred during the last 63 flight legs - monitors data inputs from the various peripherals (FMGC, ADIRU, ATC CTL UNIT and CFDIU) - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the interactive mode. (a) Normal mode During the normal mode the BITE monitors cyclically the status of the ATC system. It transmits its information to the CFDIU during the flight concerned. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 100 ms by an ARINC 429 message with label 350.

  R EFF : 051-099, 106-149, 221-249, 301-399,  34-52-00 401-499,   CES

 

Page A28 Feb 01/10

(b) Interactive mode: The interactive mode can only be activated on the ground. This mode enables communication between the CFDIU and the ATC transponder BITE by means of the MCDU. (Ref. Fig. 013B, 014A, 015A, 016A, 017A, 018A, 019, 020, 021, 022) All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer. The ATC interactive mode is composed of: - LAST LEG REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the last flight. - PREVIOUS LEGS REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the previous flights. When no fault has been detected during the last 63 flights, the NO FAULT DETECTED message is displayed. - LRU IDENTIFICATION The purpose of this item is to present the Part Number (PN), the Serial Number (SN) and the Software Number (SW/N) of the component. - GROUND SCANNING This item is based on the monitoring and fault analysis used during the flight. The system peripherals monitoring and system internal cyclic tests are used to detect transient anomalies. - TROUBLE SHOOTING DATA This item allows to analyze the snapshot of the recorded failure to detect the software bugs. - CLASS 3 FAULTS The purpose of this item is to present the class 3 fault messages that appeared during the last flight. There is no date and no failure classification. - GROUND REPORT The purpose of this item is to present the class 1, 2 or 3 internal failures when they are detected on ground. - DISCRETE CONFIGURATION The purpose of this item is to present many information of program pins dedicated to the ATC system installation. - TEST The activation of this manual test shall only be allowed on the ground. The results of the test are transmitted to the CFDIU but are not memorized.

R

  EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00    CES

 

Page A29 Feb 01/10

ATC Maintenance Test Procedure - Test Figure 018A

R

  R EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00    CES

 

Page A30 Feb 01/10

ATC Maintenance Test Procedure - Test Figure 018B

R

  R EFF : 251-299,  34-52-00    CES

 

Page A31 Feb 01/10

ATC Maintenance Test Procedure - Ground Scanning Figure 019

R

  R EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00    CES

 

Page A32 Feb 01/10

ATC Maintenance Test Procedure - Discrete Configuration 2/4 Figure 020

R

  EFF : 106-149, 221-249, 251-299, 301-399,  34-52-00 401-499,   CES

 

Page A33 Feb 01/10

ATC Maintenance Test Procedure - Discrete Configuration 3/4 Figure 021

R

  EFF : 106-149, 221-249, 251-299, 301-399,  34-52-00 401-499,   CES

 

Page A34 Feb 01/10

ATC Maintenance Test Procedure - Discrete Configuration 4/4 Figure 022

R

  R EFF : 106-149, 221-249, 251-299, 301-399,  34-52-00 401-499,   CES

 

Page A35 Feb 01/10

(2) Reporting functions -------------------------------------------------------------------------| REPORTED INTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATCi (1SHi) | 1 | 34-52-33 | | ATC1 TOP ANTENNA (7SH3) | 1 | 34-52-11 | | ATC1 BOT ANTENNA (7SH1) | 1 | 34-52-11 | | ATC2 TOP ANTENNA (7SH4) | 1 | 34-52-11 | | ATC2 BOT ANTENNA (7SH2) | 1 | 34-52-11 | | WRG : MODE S ADRESS/ATCi (1SHi) | 1 | 34-52-33 | --------------------------------------------------------------------------------------------------------------------------------------------------| REPORTED EXTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATC CTL PNL (3SH)/ATCi (1SHi) | 1 | 34-52-12 | | ADIRU i/3(1FPi/3)/ATCi (1SHi) | 1 | 34-12-34 | | TCAS(1SG)/ATCi(1SHi) | 3 | 34-43-34 | | CFDIU(1TW)/ATCi(1SHi) | 3 | 31-32-34 | | FMGCi(1CAi)/ATCi(1SHi) | 3 | 22-83-34 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | | LGCIUi(5GAi)/ATCi(1SHi) | 3 | 32-31-71 | --------------------------------------------------------------------------

  R EFF : 106-149, 221-249, 301-399, 401-499,  34-52-00    CES

 

Page A36 Feb 01/10

**ON A/C 201-210, A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the ATC system. The BITE of the ATC transponder is connected to the CFDIU. The unit tested is the ATC transponder. The BITE: - transmits permanently ATC system status and its identification message to the CFDIU - memorizes the faults which occurred during the last 63 flight legs - monitors data inputs from the various peripherals (FMGC, ADIRU, ATC CTL UNIT and CFDIU) - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the interactive mode. (a) Normal mode During the normal mode the BITE monitors cyclically the status of the ATC system. It transmits its information to the CFDIU during the flight concerned. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 100 ms by an ARINC 429 message with label 350. (b) Interactive mode: The interactive mode can only be activated on the ground. This mode enables communication between the CFDIU and the ATC transponder BITE by means of the MCDU. (Ref. Fig. 013C) The ATC interactive mode is composed of: (Ref. Fig. 014B, 015B, 016B, 017B) - LAST LEG REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the last flight. - PREVIOUS LEGS REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the previous flights.

R R

  EFF : 201-210,  34-52-00    CES

 

Page A37 Feb 01/10

-

-

-

-

When no fault has been detected during the last 63 flights, the NO FAULT DETECTED message is displayed. LRU IDENTIFICATION The purpose of this item is to present the part number (P/N) and the software number (SW/N) of the component. GROUND SCANNING This item is based on the monitoring and fault analysis used during the flight. The system peripherals monitoring and system internal cyclic tests are used to detect transient anomalies. TROUBLE SHOOTING DATA This item allows to analyze the snapshot of the recorded failure to detect the software bugs. CLASS 3 FAULTS The purpose of this item is to present the class 3 fault messages that appeared during the last flight. There is no date and no failure classification. GROUND REPORT The purpose of this item is to present the class 1, 2 or 3 internal failures when they are detected on ground. DISCRETE STATUS This item includes display of all input discretes, display of instrumentation port data blocks or any other information that may be helpful in system trouble-shooting or any other application. TEST The activation of this manual test shall only be allowed on the ground. The results of the test are transmitted to the CFDS but are not memorized.

(2) Reporting functions -------------------------------------------------------------------------| REPORTED INTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATCi (1SHi) | 1 | 34-52-33 | | ATC1 TOP ANTENNA (7SH3) | 1 | 34-52-11 | | ATC1 BOT ANTENNA (7SH1) | 1 | 34-52-11 | | ATC2 TOP ANTENNA (7SH4) | 1 | 34-52-11 | | ATC2 BOT ANTENNA (7SH2) | 1 | 34-52-11 | | WRG : MODE S ADRESS/ATCi (1SHi) | 1 | 34-52-33 | --------------------------------------------------------------------------

  R EFF : 201-210,  34-52-00    CES

 

Page A38 Feb 01/10

-------------------------------------------------------------------------| REPORTED EXTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATC CTL PNL (3SH)/ATCi (1SHi) | 1 | 34-52-12 | | ADIRU i/3(1FPi/3)/ATCi (1SHi) | 1 | 34-12-34 | | TCAS(1SG)/ATCi(1SHi) | 3 | 34-43-34 | | CFDIU(1TW)/ATCi(1SHi) | 3 | 31-32-34 | | FMGCi(1CAi)/ATCi(1SHi) | 3 | 22-83-34 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | | LGCIUi(5GAi)/ATCi(1SHi) | 3 | 32-31-71 | -------------------------------------------------------------------------**ON A/C 211-220, A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the ATC system. The BITE of the ATC transponder is connected to the CFDIU. The unit tested is the ATC transponder. The BITE: - transmits permanently ATC system status and its identification message to the CFDIU - memorizes the faults which occurred during the last 63 flight legs - monitors data inputs from the various peripherals (FMGC, ADIRU, ATC CTL UNIT and CFDIU) - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the interactive mode. (a) Normal mode During the normal mode the BITE monitors cyclically the status of the ATC system. It transmits its information to the CFDIU during the flight concerned. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 100 ms by an ARINC 429 message with label 350.

  R EFF : 201-220,  34-52-00    CES

 

Page A39 Feb 01/10

(b) Interactive mode: The interactive mode can only be activated on the ground. This mode enables communication between the CFDIU and the ATC transponder BITE by means of the MCDU. (Ref. Fig. 013D) The ATC interactive mode is composed of: (Ref. Fig. 014C, 015C, 016C, 017C) - LAST LEG REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the last flight. - PREVIOUS LEGS REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the previous flights. When no fault has been detected during the last 63 flights, the NO FAULT DETECTED message is displayed. - LRU IDENTIFICATION The purpose of this item is to present the part number (P/N) and the software number (SW/N) of the component. - GROUND SCANNING This item is based on the monitoring and fault analysis used during the flight. The system peripherals monitoring and system internal cyclic tests are used to detect transient anomalies. - TROUBLE SHOOTING DATA This item allows to analyze the snapshot of the recorded failure to detect the software bugs. - CLASS 3 FAULTS The purpose of this item is to present the class 3 fault messages that appeared during the last flight. There is no date and no failure classification. - GROUND REPORT The purpose of this item is to present the class 1, 2 or 3 internal failures when they are detected on ground. - DISCRETE DATA This item includes display of all input discretes, display of instrumentation port data blocks or any other information that may be helpful in system trouble-shooting or any other application. - TEST The activation of this manual test shall only be allowed on the ground. The results of the test are transmitted to the CFDS but are not memorized.

R R

  R EFF : 211-220,  34-52-00    CES

 

Page A40 Feb 01/10

(2) Reporting functions -------------------------------------------------------------------------| REPORTED INTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATCi (1SHi) | 1 | 34-52-33 | | ATC1 TOP ANTENNA (7SH3) | 1 | 34-52-11 | | ATC1 BOT ANTENNA (7SH1) | 1 | 34-52-11 | | ATC2 TOP ANTENNA (7SH4) | 1 | 34-52-11 | | ATC2 BOT ANTENNA (7SH2) | 1 | 34-52-11 | | WRG : MODE S ADRESS/ATCi (1SHi) | 1 | 34-52-33 | --------------------------------------------------------------------------------------------------------------------------------------------------| REPORTED EXTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATC CTL PNL (3SH)/ATCi (1SHi) | 1 | 34-52-12 | | ADIRU i/3(1FPi/3)/ATCi (1SHi) | 1 | 34-12-34 | | TCAS(1SG)/ATCi(1SHi) | 3 | 34-43-34 | | CFDIU(1TW)/ATCi(1SHi) | 3 | 31-32-34 | | FMGCi(1CAi)/ATCi(1SHi) | 3 | 22-83-34 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | | LGCIUi(5GAi)/ATCi(1SHi) | 3 | 32-31-71 | -------------------------------------------------------------------------**ON A/C 251-299, A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the ATC system. The BITE of the ATC transponder is connected to the CFDIU. The unit tested is the ATC transponder. The BITE: - transmits permanently ATC system status and its identification message to the CFDIU - memorizes the faults which occurred during the last 63 flight legs - monitors data inputs from the various peripherals (FMGC, ADIRU, ATC CTL UNIT and CFDIU) - transmits to the CFDIU the result of the tests performed and self-tests

  R EFF : 211-220, 251-299,  34-52-00    CES

 

Page A41 Feb 01/10

- can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the interactive mode. (a) Normal mode During the normal mode the BITE monitors cyclically the status of the ATC system. It transmits its information to the CFDIU during the flight concerned. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 100 ms by an ARINC 429 message with label 350. (b) Interactive mode: The interactive mode can only be activated on the ground. This mode enables communication between the CFDIU and the ATC transponder BITE by means of the MCDU. (Ref. Fig. 013E, 014D, 015D, 016D, 017D, 018B, 020, 021, 022) All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer. The ATC interactive mode is composed of: - LAST LEG REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the last flight. - PREVIOUS LEGS REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the previous flights. When no fault has been detected during the last 63 flights, the NO FAULT DETECTED message is displayed. - LRU IDENTIFICATION The purpose of this item is to present the Part Number (PN), the Serial Number (SN) and the Software Number (SW/N) of the component. - TROUBLE SHOOTING DATA This item allows to analyze the snapshot of the recorded failure to detect the software bugs. - CLASS 3 FAULTS The purpose of this item is to present the class 3 fault messages that appeared during the last flight. There is no date and no failure classification. - GROUND REPORT The purpose of this item is to present the class 1, 2 or 3 internal failures when they are detected on ground. - DISCRETE CONFIGURATION

R

  R EFF : 251-299,  34-52-00    CES

 

Page A42 Feb 01/10

The purpose of this item is to present many information of program pins dedicated to the ATC system installation. - TEST The activation of this manual test shall only be allowed on the ground. The results of the test are transmitted to the CFDIU but are not memorized. (2) Reporting functions -------------------------------------------------------------------------| REPORTED INTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATCi (1SHi) | 1 | 34-52-33 | | ATC1 TOP ANTENNA (7SH3) | 1 | 34-52-11 | | ATC1 BOT ANTENNA (7SH1) | 1 | 34-52-11 | | ATC2 TOP ANTENNA (7SH4) | 1 | 34-52-11 | | ATC2 BOT ANTENNA (7SH2) | 1 | 34-52-11 | | WRG : MODE S ADRESS/ATCi (1SHi) | 1 | 34-52-33 | --------------------------------------------------------------------------------------------------------------------------------------------------| REPORTED EXTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATC CTL PNL (3SH)/ATCi (1SHi) | 1 | 34-52-12 | | ADIRU i/3(1FPi/3)/ATCi (1SHi) | 1 | 34-12-34 | | TCAS(1SG)/ATCi(1SHi) | 3 | 34-43-34 | | CFDIU(1TW)/ATCi(1SHi) | 3 | 31-32-34 | | FMGCi(1CAi)/ATCi(1SHi) | 3 | 22-83-34 | | POWER SUPPLY INTERRUPT | 1 | 24-00-00 | | LGCIUi(5GAi)/ATCi(1SHi) | 3 | 32-31-71 | -------------------------------------------------------------------------R

**ON A/C 501-509, 511-526, 528-599, A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the ATC system. The BITE of the ATC transponder is connected to the CFDIU. The unit tested is the ATC transponder. The BITE:

  R EFF : 251-299, 501-509, 511-526, 528-599,  34-52-00    CES

 

Page A43 Feb 01/10

- transmits permanently ATC system status and its identification message to the CFDIU - memorizes the faults which occurred during the last 63 flight legs - monitors data inputs from the various peripherals (FMGC, ADIRU, ATC CTL UNIT and CFDIU) - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the interactive mode. (a) Normal mode During the normal mode the BITE monitors cyclically the status of the ATC system. It transmits its information to the CFDIU during the flight concerned. In case of fault detection, the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 100 ms by an ARINC 429 message with label 350. (b) Interactive mode: The interactive mode can only be activated on the ground. This mode enables communication between the CFDIU and the ATC transponder BITE by means of the MCDU. (Ref. Fig. 013, 014E) All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer. The ATC interactive mode is composed of: - LAST LEG REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the last flight. - PREVIOUS LEGS REPORT The purpose of this item is to present the fault messages (class 1 and 2, internal and external) that appeared during the previous flights. When no fault has been detected during the last 63 flights, the NO FAULT DETECTED message is displayed. - LRU IDENTIFICATION The purpose of this item is to present the Part Number (PN), the Serial Number (SN) and the Software Number (SW/N) of the component. - TEST The activation of this manual test shall only be allowed on the ground. The results of the test are transmitted to the CFDIU but are not memorized.

R

  R EFF : 501-509, 511-526, 528-599,  34-52-00    CES

 

Page A44 Feb 01/10

(2) Reporting functions -------------------------------------------------------------------------| REPORTED INTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATCi TRANSPONDER | 1 | 34-52-33 | | ATC1 ANTENNA T | 1 | 34-52-11 | | ATC1 ANTENNA B | 1 | 34-52-11 | | ATC2 ANTENNA T | 1 | 34-52-11 | | ATC2 ANTENNA B | 1 | 34-52-11 | --------------------------------------------------------------------------

  R EFF : 501-509, 511-526, 528-599,  34-52-00    CES

 

Page A45 Feb 01/10

-------------------------------------------------------------------------| REPORTED EXTERNAL FAILURES | |------------------------------------------------------------------------| | MESSAGE (i = 1 or 2) | CLASS | ATA | |---------------------------------------------|---------|----------------| | ATCi NO DATA FROM CONTROL SOURCE | 1 | 34-52-12 | | ATCi NO DATA FROM ADIRU | 1 | 34-12-34 | | ATCi NO DATA FROM TCAS | 3 | 34-43-34 | | ATCi NO DATA FROM CFDIU | 3 | 31-32-34 | | ATCi NO DATA FROM DAPS/ADS-B SRC | 3 | 34-XX-XX | -------------------------------------------------------------------------R

**ON A/C 051-099, 251-299, 501-509, 511-526, 528-599, B. BITE Implementation (1) Internal test processing ---------------------------------------------------------------------------| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION | | DESIGNATION | | | CONDITIONS | ---------------------------------------------------------------------------| Power-up test | Power supply module | 3 s | Power interrupt| | | ROM - RAM | | > 200 ms | |---------------|------------------------------|----------|----------------| | MCDU system | - NAV receiver | | Relevant MCDU | | test | - BITE circuitry | | menu and line | | | - SYS failure LED indication | | key selection | | | on the ATC control unit | | | |---------------|------------------------------|----------|----------------| | Face test | - ROM, RAM check | | Relevant P/BSW | | | - Antenna integrity | | activated on | | | - Receiver (top/bottom) | | XPDR face. | | | - Transmitter | | | | | - Reply format | | | | | - Power supply monitor | | | | | - I/O bus check | | | | | - Non-Volatile Memory | | | ---------------------------------------------------------------------------(2) Activation of the test on the indicators The ATC 1(2) test function can be activated in ground conditions only by pressing the TEST key on the ATC 1(2) maintenance sub-menu or by pressing the pushbutton switch on the face of the transponder. The following sequence is then generated on the output of the equipment:

  R EFF : 051-099, 251-299, 501-509, 511-526,  34-52-00 528-599,   CES

 

Page A46 Feb 01/10

------------------------------------------------------------------------| DURATION | MESSAGE | ATC CONTROL UNIT AND FACE OF ATC TRANSPONDER | ------------------------------------------------------------------------| FOR 3 s | Failure | - Failure light comes on on control unit | | | | - all LEDs come on on transponder face | | AFTER 3 s | | - ATC Transponder LEDs indicate the current | | | | condition of the unit | | FOR 10 s | | - The LEDs associated with the self-test results| | | | come on. Afterwards, all LEDs go off. | ------------------------------------------------------------------------When the selected system on the ATC control unit is different from the system under test, this causes illumination of a message on the MCDU after the TEST selection. This message is: PLEASE CHECK IF THE CONTROL PANEL SWITCH IS ON SYSTEM (1 OR 2) AND PRESS TEST KEY. Reminder: The TEST pushbutton switch is used to initiate the LED test and transponder self-test. When this pushbutton switch is pressed while the LEDs are still on, the next previous flight leg is displayed. The transponder has the capability to store 10 flight legs. To display all stored flight legs, the pushbutton switch must be pushed when the previous flight leg is being displayed. When all flight legs are displayed, all LEDS flash to indicate the end of the routine. **ON A/C 106-149, 201-210, 221-249, 301-399, 401-499, B. BITE Implementation (1) Internal test processing ---------------------------------------------------------------------------| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION | | DESIGNATION | | | CONDITIONS | ---------------------------------------------------------------------------| Power-up test | Power supply module | 3 s | Power interrupt| | | ROM - RAM | | > 200 ms | |---------------|------------------------------|----------|----------------| | MCDU system | - NAV receiver | | Relevant MCDU | | test | - BITE circuitry | | menu and line | | | - SYS failure LED indication | | key selection | | | on the ATC control unit | | | |---------------|------------------------------|----------|----------------| | Face test | - ROM, RAM check | | Relevant P/BSW | | | - Antenna integrity | | activated on | | | - Receiver (top/bottom) | | XPDR face. | | | - Transmitter | | |

  R EFF : 051-099, 106-149, 201-210, 221-249,  34-52-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page A47 Feb 01/10

---------------------------------------------------------------------------| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION | | DESIGNATION | | | CONDITIONS | ---------------------------------------------------------------------------| | - Reply format | | | | | - Power supply monitor | | | | | - I/O bus check | | | | | - Non-Volatile Memory | | | ---------------------------------------------------------------------------(2) Activation of the test on the indicators The ATC 1(2) test function can be activated in ground conditions only by pressing the TEST key on the ATC 1(2) maintenance sub-menu or by pressing the pushbutton switch on the face of the transponder. The following sequence is then generated on the output of the equipment: ------------------------------------------------------------------------| DURATION | MESSAGE | ATC CONTROL UNIT AND FACE OF ATC TRANSPONDER | ------------------------------------------------------------------------| FOR 1 s | Failure | - Failure light comes on on control unit | | | | - all LEDs come on on transponder face | | AFTER 1 s | | - All indicator lights go off | | FOR 10 s | | - The indicator lights associated with the | | | | self-test results come on. Afterwards, all | | | | indicator lights go off. | ------------------------------------------------------------------------When the selected system on the ATC control unit is different from the system under test, this causes illumination of a message on the MCDU after the TEST selection. This message is: PLEASE CHECK IF THE CONTROL PANEL SWITCH IS ON SYSTEM (1 OR 2) AND PRESS TEST KEY. Reminder: The TEST pushbutton switch is used to initiate the LED test and transponder self-test. When this pushbutton switch is pressed for more than five seconds, the transponder reads the Non-Volatile Memory fault data for last four legs and the applicable fault indicator lights come on. **ON A/C ALL C. Power-up Tests Initialization and Cockpit Repercussions (1) Conditions of power-up tests initialization - How long the computer must be de-energized: 1 s. - A/C configuration: whatever the A/C configuration on ground

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Page A48 Feb 01/10

(2) Duration of power-up tests: 3 s approx. (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). - Tests pass: none - Tests failed: on the ATC control unit, FAULT or FAIL indicator light comes on or F indication appears on the display (depending on the type of the control unit).

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Page A49 Feb 01/10

ATC/MODE S (SELECT) - MAINTENANCE PRACTICES ___________________________________________ TASK 34-52-00-860-001 R

Change of ICAO Address (after a Change of Aircraft Registration Number) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

circuit breaker(s) safety clip(s)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R R R R R R R

24-41-00-861-002 24-41-00-862-002 34-10-00-860-002 34-10-00-860-005 34-52-00-720-005 AWM 345205 AWM 345206

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power ADIRS Start Procedure ADIRS Stop Procedure Functional Test of the ATC/Mode S Transponder

3. __________ Job Set-up R

Subtask 34-52-00-860-098

R

A. Aircraft Maintenance Configuration

R R

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

R

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

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Page 201 Aug 01/07

Subtask 34-52-00-865-068 R

B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07 4. Procedure _________ Subtask 34-52-00-860-093 A. Change of ICAO Address

R

(1) Change the ICAO address to binary format (a) Find the correct plug (Ref. AWM 345205) and (Ref. AWM 345206). (b) Do the pin-programming in relation to the binary format of the ICAO address. For a pin to be at 1 on the plug, you must connect this pin to common pin b of the same plug.

R R

NOTE : Pin A of the plug is Most Significant Bit (MSB). ____ R R R R R R R

NOTE : For example, for ICAO address C0099D ____ (hexadecimal)/60004635 (octal): - you change it to binary format: 1100 0000 0000 1001 1001 1101. - you connect pins A, B, N, S, T, W, X, Y and a of the plug to pin b (Ref. AWM 345205) and (Ref. AWM 345206). Subtask 34-52-00-865-069

R

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5SH1, 5SH2.

R R

Subtask 34-52-00-720-068

R

C. Test of the MODE S aircraft code.

R R

(1) Do the AMM task 34-52-00-720-005-02 (Ref. TASK 34-52-00-720-005) up to Para 4. A. step 3.

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Page 202 Aug 01/07

R

5. Close-up ________

R

Subtask 34-52-00-860-099

R

A. Put the aircraft back to its initial configuration.

R R

(1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

R

(2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

R R

(3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

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Page 203 Aug 01/07

ATC - ADJUSTMENT/TEST _____________________ TASK 34-52-00-740-004 BITE Test of the ATC WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R R

22-70-00-710-002 24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002

Operational Test of the Initialization of the Flight Plan Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure

3. __________ Job Set-up Subtask 34-52-00-860-089 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector switches to NAV (Ref. TASK 34-10-00-860-002). (3) On the center pedestal, on the ATC control unit, set: - the ATC system 1(2) on. - the ALT RPTG/OFF/ON switch to OFF. - the STBY/AUTO/ON switch to AUTO.

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Page 501 May 01/08

(4) Enter a flight plan to get a flight number (Ref. TASK 22-70-00-710002). NOTE : Use a company route stored in the NAV DATA BASE or enter the ____ flight number TEST manually in the MCDU if it is not displayed. Subtask 34-52-00-860-086 B. On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page then push the NEXT PAGE function key. (Ref. TASK 31-32-00-860-010) Subtask 34-52-00-865-055 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07 4. Procedure _________ R

**ON A/C 001-049, 101-105, 151-199, 201-220, 501-509, 511-526, 528-599, Subtask 34-52-00-740-054 A. BITE Test of the ATC ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the MCDU:

On the MCDU:

- on the NAV page, push the line key adjacent to the ATC1 (ATC2) indication.

- the ATC page comes into view.

- push the line key adjacent to the TEST indication.

On the ATC/TCAS control unit: - the ATC FAULT or FAIL indicator light comes on during 2 seconds approx.

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Page 502 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------At the end of the test, on the MCDU, the TEST OK indication comes into view. **ON A/C 051-099, 106-149, 221-249, 251-299, 301-399, 401-499, Subtask 34-52-00-740-054-A A. BITE Test of the ATC ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the MCDU:

On the MCDU:

1. On the NAV page, push the line key adjacent to the ATC1 (ATC2) indication.

- the ATC1 (ATC2) page comes into view.

2. Push the line key adjacent to the TEST indication.

- the ATC1 (ATC2) TEST page with INITIAL CONDITIONS indication comes into view.

3. Push the line key adjacent to the START TEST indication.

On the ATC/TCAS control unit: - the ATC FAULT or FAIL indicator light comes on during 2 s approx. On the MCDU: - the ATC1 (ATC2) TEST page with TEST IN PROGRESS indication comes into view - after some seconds, the TEST OK indication comes into view.

4. Push the line key adjacent to the RETURN indication.

- the ATC1 (ATC2) TEST CLOSE-UP page comes into view.

5. Push the line key adjacent to the RETURN indication.

- the test procedure stops.

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Page 503 Feb 01/10

R

**ON A/C ALL 5. Close-up ________ Subtask 34-52-00-860-090 A. Put the aircraft back to its initial configuration. (1) On the ATC/TCAS control unit, set the master switch to the standby position. (2) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF. (3) On the center pedestal, on the MCDU, push the line key adjacent to the RETURN indication until the MCDU MENU page comes into view. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items.

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Page 504 Feb 01/04

TASK 34-52-00-710-003 Operational Test of the ATC WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-10-00-860-002 34-10-00-860-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power ADIRS Start Procedure ADIRS Stop Procedure

3. __________ Job Set-up Subtask 34-52-00-860-080 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) On the center pedestal, on the ATC/TCAS control unit, set: - the ATC system 1(2) on. - the ALT RPTG ON/OFF switch to ON. - the AUTO/ON/STBY switch to AUTO.

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Page 505 Feb 01/04

Subtask 34-52-00-865-054 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07 4. Procedure _________ Subtask 34-52-00-710-055 A. Transmission Test ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the ATC/TCAS control unit: - set the AUTO ON/STBY switch to ON.

On the ATC/TCAS control unit: - the ATC FAULT or FAIL indicator light stays off.

- set the AUTO ON/STBY switch to STBY.

On the ATC/TCAS control unit: - the display stays on.

R 5. Close-up ________ Subtask 34-52-00-860-062 A. Put the aircraft back to its initial configuration. (1) Do the ADIRS Stop Procedure (Ref. TASK 34-10-00-860-005). (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (3) Make sure that the work area is clean and clear of tool(s) and other items.

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Page 506 May 01/04

TASK 34-52-00-720-004 Functional Test of the Altitude Reporting Function NOTE : You must do this test very quickly to prevent interference with air ____ traffic, specially if the aircraft is in the open air. If the test is long you must tell the nearest airport of this test. 1. __________________ Reason for the Job Refer to the MPD TASK: 345200-01 Functional Test of the Altitude Reporting Function. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

circuit breaker(s) safety clip(s) ATC ground test unit

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-10-00-860-002 34-10-00-860-005 34-13-00-710-004

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power ADIRS Start Procedure ADIRS Stop Procedure Operational Test of the ALT DYNAMIC SLEW TEST

3. __________ Job Set-up Subtask 34-52-00-865-074 A. Open, safety and tag this(these) circuit breaker(s): R R R

WARNING : OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE _______ DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED.

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Page 507 Nov 01/07

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 Subtask 34-52-00-860-088 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) Install the ATC ground test unit in the cockpit. Put the antenna of the ATC ground test unit at 50 cm (approx. 2 ft) from the ATC antennas. Connect the antenna to the ATC ground test unit. (4) On the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is at NORM. (5) On the center pedestal, on the ATC/TCAS control unit: - set the ATC system 1(2) on. - set the ALT RPTG/OFF/ON switch to OFF. - set the AUTO/ON/STBY switch to ON. - make sure that the display does not show an emergency code: 7500, 7600 or 7700. (6) On the panel 13VU, on the CAPT and F/O EFIS control sections of the FCU, make sure that the baro displays show STD. (7) Do the operational test of ALT DYNAMIC SLEW TEST (Ref. TASK 34-13-00710-004) to simulate an altitude of 23,458 ft. On the MCDU, enter 0/23 458 as SLEW LIMITS and push the line key adjacent to the UP (START SLEW) indication to start the test. Subtask 34-52-00-865-056 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07

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Page 508 Nov 01/07

4. Procedure _________ Subtask 34-52-00-720-061 A. Functional Test of the Altitude Reporting Function ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ATC/TCAS control unit:

- set the ALT RPTG ON/OFF switch to ON.

On the ATC/TCAS control unit: - the ATC FAULT or FAIL indicator light is off. On the ATC ground test unit a display shows the standard altitude of approx. 23,458 ft or equivalent and the last code set. The difference between the altitude shown on CAPT and F/O PFDs and that shown on the ATC ground test unit must not be more than 125 ft.

- set the AUTO/ON/STBY switch to STBY.

On the ATC/TCAS control unit: - the display stays on.

5. Close-up ________ Subtask 34-52-00-860-059 A. Put the aircraft back to its initial configuration. (1) Disconnect the ATC ground test unit. (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (4) Make sure that the work area is clean and clear of tool(s) and other items.

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Page 509 Nov 01/07

Subtask 34-52-00-865-075 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 7XE.

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Page 510 Nov 01/07

TASK 34-52-00-720-005 Functional Test of the ATC/Mode S Transponder NOTE : You must do this test very quickly to prevent interference with air ____ traffic, specially if the aircraft is in the open air. If the test is long, you must tell the nearest airport of this test. NOTE : For best test results, buildings, vehicles and other aircraft must not ____ be in the area of the main antenna lobe (approx 30 ft.). 1. __________________ Reason for the Job Refer to the MPD TASK: 345200-03 NOTE : There are alternative methods for this procedure. This task gives one ____ of the methods. For the other method with a different Ground Test Unit, refer to the other task in this page block. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No

specific specific specific specific

access platform circuit breaker(s) safety clip(s) telescopic pole T49 - ATC GROUND TEST UNIT (or equivalent)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------22-70-00-710-002 24-41-00-861-002 24-41-00-862-002 32-00-00-860-001

Operational Test of the Initialization of the Flight Plan Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Flight Configuration Precautions with Electrical Power

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Page 511 May 01/07

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------32-00-00-860-002 34-10-00-860-002 34-10-00-860-005 34-52-00-720-005

Ground Configuration after Flight Configuration with Electrical Power ADIRS Start Procedure ADIRS Stop Procedure Functional Test of the ATC/Mode S Transponder

3. __________ Job Set-up R R

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-52-00-800-051 A. Aircraft Configuration NOTE : When the aircraft transponders can operate in Elementary ____ Surveillance or Enhanced Surveillance mode, do the functional test of the ATC/Mode S transponder. Refer to TASK 34-52-00-720-005-02 (Ref. TASK 34-52-00-720-005). **ON A/C ALL Subtask 34-52-00-860-083 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) Enter a flight entry to get a flight number (Ref. TASK 22-70-00-710002). NOTE : Use a company route stored in the NAV DATA BASE. Enter the ____ flight number manually in the MCDU if it is not displayed.

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Page 512 Feb 01/10

(4) On the center pedestal: (a) On the ATC/TCAS control unit: - Start the ATC system 1(2) - Enter the ATC code 7776, or a different code given by your local authorities, to keep the traffic interference to a minimum - Set the ALT RPTG ON/OFF switch to ON - Set the ON/AUTO/STBY switch to ON. (b) On the SWITCHING panel 8VU: - Make sure that the AIR DATA selector switch is at NORM. Subtask 34-52-00-865-057 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07 Subtask 34-52-00-480-050 D. Install the T49 - ATC GROUND TEST UNIT (or equivalent) in the cockpit. (1) Connect the test antenna to the test unit. (2) Put the test antenna near the ATC antenna for which you do the test (approx. 2 ft.). NOTE : Use an access platform or a telescopic pole to put the test ____ antenna near the ATC bottom antenna. Subtask 34-52-00-860-073 E. Obey the applicable safety precautions before you open the LGCIU circuit breakers (Ref. TASK 32-00-00-860-001).

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Page 513 May 01/07

Subtask 34-52-00-865-061 F. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU L/G/LGCIU/SYS1/NORM 1GA C09 121VU HYDRAULIC/LGCIU/SYS2 2GA Q35 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34 4. Procedure _________ Subtask 34-52-00-720-051-A A. Functional Test of the ATC/Mode S Transponder NOTE : Do the test of the ATC bottom antenna 1(2) first. ____ Then, do the test of the ATC top antenna 1(2). ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the ATC ground test unit:

On the ATC ground test unit:

- set the ATCRBS/MODE S/TCAS/XPDR TEST switch to XPDR TEST. - push the TEST pushbutton switch to start the operation of the test set.

- the data display shows: MODE S XPDR COM A/B INTERROGATE TO TEST.

NOTE : You can also start the ____ same test procedure if you push the INTERROGATE pushbutton switch. At the end of this test procedure, a test message shows the system status but all the results given below are not shown. - push the TEST pushbutton switch.

- the data display shows: ATCRBS/A TESTING and then,

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Page 514 May 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------ATCRBS/A 7776, or the code given by the local authorities (see para. 3) XX% REPLY (XX is a number which indicates the local conditions of reception). NOTE : You must do the steps that ____ follow in a fast sequence to keep incorrect traffic alarms to a minimum. 2. On the ATC/TCAS control unit: - set the ALT RPTG selector switch to ON. 3. On the test unit: - push the TEST pushbutton switch.

On the test unit: - the data display shows: ATCRBS/C TESTING and then, ATCRBS/C Z,ZZZ ft XX% REPLY (Z,ZZZ is a number which shows, approximately, the local field elevation).

- push the TEST pushbutton switch.

- the data display shows: ATCRBS/A MODE S ALL TESTING and then, ATCRBS/A MODE S ALL AIRCRAFT CODE XX% REPLY (the aircraft code is on 6 digits).

- push the TEST pushbutton switch.

- the data display shows: ATCRBS/C MODE S ALL TESTING and then, ATCRBS/C MODE S ALL AIRCRAFT CODE XX% REPLY.

- push the TEST pushbutton switch.

- the data display shows: ATCRBS/A ONLY TESTING

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Page 515 May 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------and then, ATCRBS/A ONLY NO REPLY FROM XPDR. - push the TEST pushbutton switch.

- the data display shows: ATCRBS/C ONLY TESTING and then, ATCRBS/C ONLY NO REPLY FROM XPDR.

- push the TEST pushbutton switch.

- the data display shows: MODE S SURV IDENTITY TESTING MODE S SURV ALTITUDE TESTING MODE S SURV SHORT TESTING and then: MODE S SURV XX% REPLY AIRCRAFT CODE (Make sure that the code display agrees with the code S given to that aircraft - 6 digits) APPROXIMATE LOCAL FIELD-ELEVATION.

- push the TEST pushbutton switch.

- the data display shows: UNDESIRED REPLIES TESTING and after a short time during which the display flashes: UNDESIRED REPLIES NO REPLIES.

- push the TEST pushbutton switch.

- the data display shows: SQUITTER TESTING and then, SQUITTER PASS.

- push the TEST pushbutton switch.

- the data display shows: DIVERSITY PASS

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Page 516 May 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the TEST pushbutton - the data display shows: switch. MAX TRUE AIRSPEED GT 300 LE 600KTS - push the TEST pushbutton switch. (optional step, not mandatory)

- the data display shows: FLIGHT NO. TESTING and then, FLIGHT NO. 12345678

- push the TEST pushbutton switch.

- the data display shows: PWR. RCVR. FREQ TESTING and then, 1090 MHZ plus or minus 1 MHz POWER: is more than or equal to 125 W and less than or equal to 500 W SENSITIVITY: 74 dBm plus or minus 3 dBm

- At the end of the test, set the LIGHTS/OFF switch to OFF.

- the display goes off.

5. Close-up ________ Subtask 34-52-00-860-051 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the ATC/TCAS control unit, set: - the ALT RPTG ON/OFF switch to OFF. - the AUTO/ON/STBY switch to STBY. (2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005). (3) On the test unit, set the OFF/LIGHTS switch to OFF. (4) Remove the test antenna and the test unit. (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).

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Page 517 May 01/07

Subtask 34-52-00-865-062 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1GA, 2GA, 52GA Subtask 34-52-00-860-074 C. Do the ground configuration after the flight configuration (Ref. TASK 3200-00-860-002).

  EFF : ALL  34-52-00   R  CES

 

Page 518 May 01/07

TASK 34-52-00-720-005- 01 Functional Test of the ATC/Mode S Transponder NOTE : You must do this test very quickly to prevent interference with air ____ traffic. If the test is long, you must tell the nearest airport of this test. NOTE : For best test results, buildings, vehicles and other aircraft must not ____ be in the area of the main antenna lobe (approx. 30 ft.). 1. __________________ Reason for the Job Refer to the MPD TASK: 345200-03 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

antenna shield ATC-601 test set (version 2.22) or equivalent

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-10-00-860-002 34-10-00-860-005 34-52-00-720-005

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power ADIRS Start Procedure ADIRS Stop Procedure Functional Test of the ATC/Mode S Transponder

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Page 519 May 01/07

3. __________ Job Set-up R R

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-52-00-800-052 A. Aircraft Configuration NOTE : When the aircraft transponders can operate in Elementary ____ Surveillance or Enhanced Surveillance mode, do the functional test of the ATC/Mode S transponder. Refer to TASK 34-52-00-720-005-02 (Ref. TASK 34-52-00-720-005). **ON A/C ALL Subtask 34-52-00-860-084 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) On the center pedestal: (a) On the ATC/TCAS control unit: - Start the ATC system 1(2) - Enter the ATC code 7776, or a different code given by your local authorities, to keep the traffic interference to a minimum - Set the ALT RPTG ON/OFF switch to ON - Set the AUTO/ON/STBY switch to ON. (b) On the SWITCHING panel 8VU: - Make sure that the AIR DATA selector switch is at NORM.

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Page 520 Feb 01/10

Subtask 34-52-00-865-058 C. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07 Subtask 34-52-00-480-051-A D. Install the ATC-601 test set (version 2.22) or equivalent (1) Make sure that the test set and the test antenna are in the correct position: - for the test of the bottom antenna: 10 ft. (3 m) approximately from this antenna, - for the test of the top antenna: in the line of sight of this antenna, at less than 200 ft. (60.95 m). (2) Connect the test antenna to the test set with the coaxial cable. (3) Put an antenna shield on the bottom antenna during the test of the top antenna. (4) On the test set: - push the POWER key, - push the SELF TEST key, - push the RUN/STOP key and make sure that the test is satisfactory, - push the SETUP key to record the antenna setup data in the SETUP MENU: . RANGE, HEIGHT, SELECTED antenna and GAIN read on the test antenna. 4. Procedure _________ Subtask 34-52-00-720-052 A. Functional Test of the ATC/Mode S Transponder. NOTE : Do the test of the ATC top antenna 1(2) first with the antenna ____ shield on the bottom antenna. Then, do the test of the ATC bottom antenna 1(2) without the antenna shield.

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Page 521 May 01/07

Ignore the indications VS, RI, FS, DR, UM, CA, PI, MV, MB, because they are not related to this test. NOTE : For the AIRCRAFT CODE, make sure that the code display agree with ____ the code S given to that aircraft - 6 digits. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the test set: - push the AUTO TEST key. - push the RUN/STOP key to start the operation of the test set.

The data display shows the TEST RUNNING indication and asterisks on the bottom line. At the end of the test, the AUTO TEST PASSED, comes into view with these indications: MODE TESTED - A, C, S FREQ: 1090 (+/1) MHZ MODE PASSED - A, C, S ERP: 54 (+/- 4) dBm MODE FAILED - . . . . MTL: -74 (+/3)dBm DIVERSITY ISOLATION: more than or equal to 20 dBm Press RUN to start

2. To know the 19 available, push the SELECT keys and push the RUN/STOP key to start the test. - push the right SELECT key until the REPLY DELAY TEST menu page comes into view.

On the REPLY DELAY TEST - PASSED page, the results of the test come into view: MODE S: 128.00 (+/- 0.25) microseconds ITM A: 128.00 (+/- 0.25) microseconds C: 128.00 (+/- 0.25) microseconds ATC A: 3.00 (+/- 0.5) microseconds C: 3.00 (+/- 0.5) microseconds Press run to start.

- push the right SELECT key.

On the REPLY JITTER TEST - PASSED page, the results of the test come into view: MODE S: XXX (less than or equal to 0.08) microseconds

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Page 522 May 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------ITM A: XXX (less than or equal to 0.1) microseconds C: XXX (less than or equal to 0.1) microseconds ATC A: XXX (less than or equal to 0.1) microseconds C: XXX (less than or equal to 0.1) microseconds Press run to start. - push the right SELECT key.

On the ATCRBS REPLY TEST - PASSED page, the results of the test come into view: F1 TO F2 SPACING A: 20.3 (+/- 0.10) microseconds C: 20.3 (+/- 0.10) microseconds F1 PULSE WIDTH A: 0.45 (+/- 0.10) microseconds C: 0.45 (+/- 0.10) microseconds F2 PULSE WIDTH A: 0.45 (+/- 0.10) microseconds C: 0.45 (+/- 0.10) microseconds CODE= 7776, or the code given by the local authorities (see para. 3) ALT= XX,XXX FT. Press run to start.

- push the right SELECT key.

On the SLS LEVEL TEST - PASSED page, the results of the test come into view: -9dB: REPLY 0dB: NO REPLY Press run to start.

- push the right SELECT key.

On the ATC ONLY ALL-CALL TEST - PASSED page, the indication PASSED TEST comes into view Press run to start.

- push the right SELECT key.

On the MODE S ALL-CALL TEST - PASSED page, the indication ALL-CALL ADDRESS = XXXXXX comes into view Press run to start.

- push the right SELECT key.

On the INVALID ADDRESS TEST - PASSED page, the indication PASSED TEST comes into view Press run to start.

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Page 523 May 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the right SELECT key. On the SPR ON/OFF TEST - PASSED page, the results of the test come into view: SPR ON : REPLY SPR OFF : NO REPLY Press run to start. - push the right SELECT key.

On the MODE S UF0 TEST - PASSED page, these indications come into view: DF 0 VS=X RI=X AC=XXXXX FT ADDRESS=XXXXXX Press run to start.

- push the right SELECT key.

On the MODE S UF4 TEST - PASSED page, these indications come into view: DF 4 FS=X DR=XX UM=XX AC=XXXXX FT ADDRESS=XXXXXX Press run to start.

- push the right SELECT key.

On the MODE S UF5 TEST - PASSED page, these indications come into view: DF 5 FS=X DR=XX UM=XX ID=7776, or the code given by the local authorities (see para. 3) ADDRESS=XXXXXX Press run to start.

- push the right SELECT key.

On the MODE S UF11 TEST - PASSED page, these indications come into view: DF 11 CA=X AA=XXXXXX PI=XXXXXX Press run to start.

- push the right SELECT key.

On the MODE S UF16 TEST - PASSED page, these indications come into view: DF 16 VS=X RI=X AC=XX XXX FT MV=XXXXXXXXXXXXXX ADDRESS=XXXXXX (If TCAS is not installed or is in standby mode, the only NO REPLY indication comes into view). Press run to start.

- push the right SELECT key.

On the MODE S UF20 TEST - PASSED page, ignore the results.

- push the right SELECT key.

On the MODE S UF21 TEST - PASSED page, ignore the results.

R R R

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Page 524 Aug 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the right SELECT key. On the SQUITTER TEST - PASSED page, these indications come into view: PERIOD = X.XX SECONDS (PERIOD is 0.8 s to 2.4 s) TAIL NUMBER = XXXXXX SQUITTER ADDRESS=XXXXXX Press run to start. - push the right SELECT key.

On the FREQUENCY TEST - PASSED page, the indication FREQUENCY = 1090 (plus or minus 3) MHz comes into view Press run to start.

- push the right SELECT key.

On the DIVERSITY TEST - PASSED page, the indication DIVERSITY ISOLATION: XX (more than or equal to 20) dB comes into view Press run to start. You must do this test at a distance of less than 50 ft. (15.24 m) of the antenna).

- push the right SELECT key.

On the MTL DIFFERENCE TEST - PASSED page, the indication MODE A MTL - MODE C MTL = X.X (less than or equal to 1) dB comes into view with the indication Press run to start.

3. On the test set: - push the POWER TEST key

The results of the last power test are displayed: ** POWER TEST ** .................ERP..MTL .TOP AVG (dBm) = XX.X -XX.X .BOT AVG (dBm) = XX.X -XX.X INSTANTANEOUS = Press RUN to start

- push the left or right SELECT key to select the top (bottom) antenna.

The dot in front of TOP or BOT indicates which set of antennas has been selected.

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Page 525 May 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------Hold the directional flat test set antenna at arms length over your head, aim it and on its handle: - push the pushbutton switch to start the test. - move the antenna downward from the top position within approximately 2 seconds to near the level of your ankles.

After a short while the display shows: - for the top antenna: ** POWER TEST ** .................ERP..MTL .TOP AVG (dBm) = .BOT AVG (dBm) = NOT RUN INSTANTANEOUS = XX.X -XX.X Press RUN to start - for the bottom antenna: ** POWER TEST ** .................ERP..MTL .TOP AVG (dBm) = NOT RUN .BOT AVG (dBm) = INSTANTANEOUS = XX.X -XX.X Press RUN to start NOTE : The indicated values in the ____ places of XX.X represent the specific data measured presently.

On the handle of the directional flat test set antenna: - push the pushbutton switch to stop the power test.

The display shows: - for the top antenna: ** POWER TEST ** .................ERP..MTL .TOP AVG (dBm) = XX.X -XX.X .BOT AVG (dBm) = NOT RUN INSTANTANEOUS = Press RUN to start

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Page 526 May 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- for the bottom antenna: ** POWER TEST ** .................ERP..MTL .TOP AVG (dBm) = NOT RUN .BOT AVG (dBm) = XX.X -XX.X INSTANTANEOUS = Press RUN to start NOTE : The indicated values should be: ____ - ERP: less than 57.0 dBm and more than 48.5 dBm - MTL: -73.0 (plus/minus 4.0) dBm. 4. At the end of the test, push the POWER key.

The display goes off.

5. Close-up ________ Subtask 34-52-00-860-053 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the ATC/TCAS control unit, set: - the ALT RPTG ON/OFF switch to OFF. - the ON/AUTO/STBY switch to STBY. (2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005). (3) Remove the test antenna and the test set. Subtask 34-52-00-862-054 B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).

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Page 527 May 01/07

TASK 34-52-00-720-005- 02 Functional Test of the ATC/Mode S Transponder NOTE : You must do this test very quickly to prevent interference with air ____ traffic. If the test is long, you must tell the nearest airport of this test. NOTE : For best test results, buildings, vehicles and other aircraft must not ____ be in the area of the main antenna lobe (approx. 30 ft.). 1. __________________ Reason for the Job Refer to the MPD TASK: 345200-03 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

Mode S/ATCRB system test set (with the ELS/EHS functions) and user manual Mode S/ATCRB system test set and user manual

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------22-70-00-710-002 24-41-00-861-002 24-41-00-862-002 32-00-00-860-002 32-69-00-860-001 34-10-00-860-002 34-10-00-860-005

Operational Test of the Initialization of the Flight Plan Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Ground Configuration after Flight Configuration with Electrical Power Simulation of Flight, with the Aircraft on the Ground ADIRS Start Procedure ADIRS Stop Procedure

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Page 528 May 01/07

3. __________ Job Set-up Subtask 34-52-00-860-094 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). R

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) Enter a flight plan to get a flight number (Ref. TASK 22-70-00-710002). NOTE : Use a company route stored in the NAV DATA BASE or enter the ____ flight number TEST manually in the MCDU if it is not displayed. (4) On the SWITCHING panel 8VU: - Make sure that the AIR DATA selector switch is set to NORM. **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, Subtask 34-52-00-480-054 B. If possible, put the Mode S/ATCRB system test set and user manual in the cockpit. NOTE : You can do this test ____ - You use a test set - You make sure that all the parameters

automatically if: that has the automatic test function. the automatic test procedure does a test of given in this procedure.

(1) Make sure that the test set is in correct condition. (2) Connect the test antenna to the test set. (3) Put the test antenna in position in the line of sight of the ATC1 (2) bottom antenna only.

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Page 529 Aug 01/09

R R

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-52-00-480-054-A B. If possible, put the Mode S/ATCRB system test set (with the ELS/EHS functions) and user manual in the cockpit. NOTE : You can do this test ____ - You use a test set - You make sure that all the parameters

automatically if: that has the automatic test function. the automatic test procedure does a test of given in this procedure.

(1) Make sure that the test set is in correct condition. (2) Connect the test antenna to the test set. (3) Put the test antenna in position in the line of sight of the ATC1 (2) bottom antenna only. **ON A/C ALL Subtask 34-52-00-860-095 C. Aircraft Maintenance Configuration (1) On the center pedestal, on one MCDU, get the LGCIU 1 (2) page and simulate a flight condition (Ref. TASK 32-69-00-860-001) - Push the line key adjacent to the NOSE+LH+RH FLIGHT indication. NOTE : Simulation of flight automatically stops after a period of ____ time (approx. 5min.). When the aircraft goes back to ground configuration, the bottom antennas no longer transmit squitters. (2) On the center pedestal, on the ATC/TCAS control unit: - Start the ATC system 1(2) - Enter the ATC code 7776, or a different code given by your local authorities, to keep the traffic interference to a minimum - Set the ALT RPTG/ON/OFF switch to ON - Set the AUTO/ON/STBY switch to AUTO. Subtask 34-52-00-865-076 D. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07   EFF : ALL  34-52-00    CES

 

Page 530 Feb 01/10

4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, Subtask 34-52-00-720-064 A. Functional Test of the ATC MODE S NOTE : Do the test for the system 1. ____ Then, do the test for the system 2. NOTE : There are many different types of test benches. This procedure ____ gives a typical test sequence. The test sequence can change with the test bench used. NOTE : For Elementary Surveillance (ELS) and Enhanced Surveillance (EHS) ____ capable transponders, use an Extended Squitters (ES) capable test set. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Set the test set (or bench) for:

The test set must show:

- Interrogation MODE A

- MODE A: 7776 or the code given by the local authorities (see para. 3)

- Interrogation MODE A ONLY (ATCRBS - Mode A Only).

- No reply or PASS or OK.

2. Set the Test set (or bench) for:

The test set must show:

- Interrogation MODE C

- MODE C code: Z,ZZZ ft (Z,ZZZ is a number that gives approximately the local field elevation).

- Interrogation MODE C ONLY (ATCRBS - Mode C Only).

- No reply or PASS or OK.

3. Set the test set (or bench) for: - Interrogation MODE S

The test set must show: - MODE S aircraft with the - Mode A

aircraft code: XXXXXX (the code has 6 digits and agrees 24-bit Mode S address). in DF 5 format

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Page 531 May 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- MODE C in DF 4 format - Flight number/Flight ID - Acquisition Squitters (PERIOD is between 0.8 second and 2.4 seconds in DF 11 format) - Aircraft status: Flight or Air. 4. Set the test set (or bench) for: - Side Lobe Suppression (SLS) test

The test set must show:

- SLS: -9 dB

- MODE A: 7776 or the code given by the local authorities (see para. 3) or PASS - MODE C: Z,ZZZ or PASS

- SLS: 0 dB.

- MODE A: no reply or PASS - MODE C: no reply or PASS.

5. Set the test set (or bench) for: - INVALID ADDRESS/UNDESIRED REPLY MODE S test. 6. On the center pedestal, on the ATC control unit: - Set the ALT RPTG/ON/OFF switch to OFF.

The test set must show: - MODE S ADDRESS: no reply or PASS. The test set must show:

Set the test set (or bench) for: - Interrogation in MODE C. 7. On the center pedestal, on the ATC control unit: - Set the ALT RPTG/ON/OFF switch to ON.

- MODE C: no Altitude Value. On the test set: The results must show:

- Push the IDENT pushbutton switch. Set the test set for: - Interrogation in MODE A.

- The ident pulse is transmitted for a minimum of 20 seconds.

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Page 532 May 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------8. Set the test set (or bench) for: On the test set: - Antenna diversity test

- The antenna diversity or isolation must be more than or equal to 20 dB.

NOTE : Refer to the diversity testing procedure given in the test-bench user ____ manual. 9. Set the test set (or bench) for:

On the test set: - The POWER must be more than or equal to 125 W and less than or equal to 500 W.

- FREQUENCY test

- The FREQUENCY must be 1090 MHZ plus or minus 1 MHZ.

- SENSITIVITY test

- The SENSITIVITY or MTL must be -74 dBm plus or minus 3 dBm.

- SENSITIVITY difference MODE A/MODE C test.

- The SENSITIVITY difference must be less than or equal to 1 dB.

R R

- POWER test

NOTE : To measure the ATC 1(2) power and the ATC 1(2) sensitivity, the test ____ antenna must be: - In the line of sight of the ATC 1(2) bottom antenna - Then in the line of sight of the ATC 1(2) top antenna. You must enter the distance between the ATC antennas and the test antenna in the set up menu of the test set. This distance is different for the bottom antenna and the top antenna of the ATC transponder on which you do the test. You must measure the distance with precision. If not, the results of the power test and the sensitivity test will be unsatisfactory. For more information, refer to the User Manual of your test set. 10. Put the aircraft back to ground configuration (Ref. TASK 32-0000-860-002)

The test sets must show:

Set the test set (or bench) for: - Interrogation in MODE A

- MODE A: no reply

- Interrogation in MODE C

- MODE C: no reply

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Page 533 Aug 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Interrogation in MODE S. - MODE S aircraft code: XXXXXX - Flight number/Flight ID - Acquisition Squitters (PERIOD is between 0.8 second and 2.4 seconds in DF 11 format) - Aircraft status: Ground. R R

**ON A/C 106-149, 221-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-52-00-720-064-A A. Functional Test of the ATC MODE S NOTE : Do the test for the system 1. ____ Then, do the test for the system 2. NOTE : There are many different types of test benches. This procedure ____ gives a typical test sequence. The test sequence can change with the test bench used. NOTE : For Elementary Surveillance (ELS) and Enhanced Surveillance (EHS) ____ capable transponders, use an Extended Squitters (ES) capable test set. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Set the test set (or bench) for:

The test set must show:

- Interrogation MODE A

- MODE A: 7776 or the code given by the local authorities (see para. 3)

- Interrogation MODE A ONLY (ATCRBS - Mode A Only).

- No reply or PASS or OK.

2. Set the Test set (or bench) for:

The test set must show:

- Interrogation MODE C

- MODE C code: Z,ZZZ ft (Z,ZZZ is a number that gives approximately the local field elevation).

- Interrogation MODE C ONLY

- No reply or PASS or OK.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-52-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 534 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------(ATCRBS - Mode C Only). 3. Set the test set (or bench) for: - Interrogation MODE S.

4. Set the test set (or bench) for: - Side Lobe Suppression (SLS) test

The test set must show: - MODE S aircraft code: XXXXXX (the aircraft code has 6 digits and agrees with the 24-bit Mode S address). - Mode A in DF 5 format - MODE C in DF 4 format - Flight number/Flight ID - Acquisition Squitters (PERIOD is between 0.8 second and 2.4 seconds in DF 11 format). - Aircraft status: Flight or Air. The test set must show:

- SLS: -9 dB

- MODE A: 7776 or the code given by the local authorities (see para. 3) or PASS - MODE C: Z,ZZZ or PASS

- SLS: 0 dB.

- MODE A: no reply or PASS - MODE C: no reply or PASS.

5. Set the test set (or bench) for: - INVALID ADDRESS/UNDESIRED REPLY MODE S test. 6. On the center pedestal, on the ATC control unit: - Set the ALT RPTG/ON/OFF switch to OFF.

The test set must show: - MODE S ADDRESS: no reply or PASS. The test set must show:

Set the test set (or bench) for: - Interrogation in MODE C. 7. On the center pedestal, on the ATC control unit: - Set the ALT RPTG/ON/OFF switch to ON

- MODE C: no Altitude Value. On the test set:

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Page 535 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Push the IDENT pushbutton switch. Set the test set for: - Interrogation in MODE A. 8. Set the test set (or bench) for: - Antenna diversity test.

- The ident pulse is transmitted for a minimum of 20 seconds. On the test set: - The antenna diversity or isolation must be more than or equal to 20 dB.

NOTE : Refer to the diversity testing procedure given in the test-bench user ____ manual. 9. Set the test set (or bench) for:

On the test set:

- POWER test

- The POWER must be more than or equal to 125 W and less than or equal to 500 W.

- FREQUENCY test

- The FREQUENCY must be 1090 MHZ plus or minus 1 MHZ.

- SENSITIVITY test

- The SENSITIVITY or MTL must be -74 dBm plus or minus 3 dBm.

- SENSITIVITY difference MODE A/MODE C test.

- The SENSITIVITY difference must be less than or equal to 1 dB.

NOTE : To measure the ATC 1(2) power and the ATC 1(2) sensitivity, the test ____ antenna must be: - In the line of sight of the ATC 1(2) bottom antenna - Then in the line of sight of the ATC 1(2) top antenna. You must enter the distance between the ATC antennas and the test antenna in the set up menu of the test set. This distance is different for the bottom antenna and the top antenna of the ATC transponder on which you do the test. You must measure the distance with precision. If not, the results of the power test and the sensitivity test will be unsatisfactory. For more information, refer to the User Manual of your test set.

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Page 536 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------10. Put the aircraft back to ground The test set must show: configuration (Ref. TASK 32-0000-860-002) Set the test set (or bench) for: - Interrogation in MODE A

- MODE A: no reply

- Interrogation in MODE C

- MODE C: no reply

- Interrogation in MODE S.

- MODE S aircraft code: XXXXXX - Flight number/Flight ID - Aircraft status: Ground.

Subtask 34-52-00-720-065 B. Functional Test of the ATC MODE S for Elementary Surveillance. (1) On the center pedestal, on one MCDU, get the LGCIU 1 (2) page and simulate a flight condition (Ref. TASK 32-69-00-860-001) - Push the line key adjacent to the NOSE+LH+RH FLIGHT indication. (2) Put the test antenna in position in the line of sight of the ATC1 (2) bottom antenna. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Set the test set (or bench) for the capability Report Comm B Data 7 (BDS 1.0) test:

The test set must show:

- Surveillance Identifier (SI code test)

- PASS or OK or YES

- A/C Ident capability.

- OK or PASS or YES.

2. Set the test set (or bench) for the capability Report Comm B Data (BDS 1.7) test:

The test set must show: - No null coding or PASS.

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Page 537 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------3. Set the test set (or bench) for The test set must show: the capability report Comm B Data (BDS 3.0) test: - Resolution Advisory (RA) test.

- No RA or Pass or OK.

(3) Put the aircraft back to ground configuration (Ref. TASK 32-00-00860-002). R R

**ON A/C 106-149, 234-249, 251-299, 303-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-52-00-720-066 C. Functional Test of the ATC MODE S for Enhanced Surveillance. NOTE : The verification of Enhanced Surveillance functionality is focused ____ on one parameter per BDS, and one parameter from each source (FCU, ADC, IRS). (1) On the center pedestal, on one MCDU, get the LGCIU 1 (2) page and simulate a flight condition (Ref. TASK 32-69-00-860-001) - Push the line key adjacent to the NOSE+LH+RH FLIGHT indication. (2) Put the test antenna in position in the line of sight of the ATC1 (2) bottom antenna. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. Set the test set (or bench) for the heading and speed report BDS 6.0 test: - Magnetic heading.

The test set must show:

- Magnetic heading of the aircraft.

NOTE : It is not necessary to do a check of the other parameters (barometric ____ altitude rate, inertial vertical velocity, indicated airspeed, Mach number) from BDS 6.0 as sources are already validated. 2. Set the test set (or bench) for The track and turn report BDS 5.0 test:

The test set must show:

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Page 538 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- Roll angle - X degrees (X is a number that gives approximately the roll of the aircraft) NOTE : It is not necessary to do a check of the other parameters (True ____ Airspeed, Ground speed, True track angle, Track angle rate) from BDS 5.0 as sources are already validated. 3. In the center of the FCU: - Turn the altitude selector knob to set an altitude of 10,000 ft in the ALT field of the display window - Pull the altitude selector knob. 4. On the CAPT and F/O sides of the FCU: - Turn the baro reference selector knob until a pressure of 1013 hPa shows on the CAPT and F/O baro display - Do not pull the baro reference selector knob. 5. Set the test set (or bench) for The selected vertical intention BDS 4.0 test: - Barometric pressure setting - FCU selected altitude.

The test set must show:

- 1013 hPa - 10,000 ft.

(3) Put the aircraft back to ground configuration (Ref. TASK 32-00-00860-002).

  R EFF : 106-149, 234-249, 251-299, 303-399,  34-52-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 539 Feb 01/10

**ON A/C ALL 5. Close-up ________ Subtask 34-52-00-860-096 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the ATC/TCAS control unit, set: - the ALT RPTG ON/OFF switch to OFF - the ON/AUTO/STBY switch to STBY. (2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005). (3) Remove the test antenna and the test set. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). Subtask 34-52-00-080-051 B. Remove the ground support and maintenance equipment, the special and standard tools and all other items.

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Page 540 May 01/07

TASK 34-52-00-720-006 Functional Test of the ATC Antennas 1. __________________ Reason for the Job Refer to the MPD TASK: 345200-02 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

access platform telescopic pole ATC grount test unit

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power

3. __________ Job Set-up Subtask 34-52-00-861-055 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 34-52-00-865-059 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07

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Page 541 May 01/07

Subtask 34-52-00-480-052 C. Install the ATC grount test unit in the cockpit. (1) Put the antenna of the ATC ground test unit at 50cm (approx 2 ft.) from the ATC antennas. NOTE : Use an access platform or a telescopic pole to put the test ____ antenna near the ATC bottom antenna. (2) Connect the antenna to the ATC ground test unit. (3) Set the ATC ground test unit to ON. Subtask 34-52-00-860-085 D. On the center pedestal, on the ATC/TCAS control unit, set: - the ATC system 1(2) on. - the ATC code 7776, or a different code given by your local authorities, to keep the traffic interference to a minimum. - the ALT RPTG OFF/ON switch to OFF. - the STBY/AUTO/ON selector switch to STBY. 4. Procedure _________ Subtask 34-52-00-720-059 A. Functional Test of the ATC Antennas NOTE : Do the test of the ATC bottom antenna 1(2) first. ____ Then, do the test of the ATC top antenna 1(2). ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------On the ATC/TCAS control unit: - set the STBY/AUTO/ON switch to ON.

On the ATC ground test unit, the data display shows the code 7776, or the code given by the local authorities (see para. 3).

On the ATC/TCAS control unit: - set the STBY/AUTO/ON switch to STBY.

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Page 542 May 01/07

5. Close-up ________ Subtask 34-52-00-860-087 A. Put the aircraft back to its initial configuration. (1) Set the ATC ground test unit to OFF. (2) Remove the test antenna and the ground test unit. Subtask 34-52-00-862-055 B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).

  EFF : ALL  34-52-00    CES

 

Page 543 May 01/07

ANTENNA - ATC (7SH1,7SH2,7SH3,7SH4) - REMOVAL/INSTALLATION __________________________________________________________ TASK 34-52-11-000-001 Removal of the ATC Antenna (7SH1,7SH2,7SH3,7SH4) WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific FOR FIN 7SH3, 7SH4 No specific

blanking caps circuit breaker(s) safety clip(s) nonmetallic scraper access platform 6.0 m (19 ft. 8 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-52-11-991-001

Fig. 401

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Page 401 Feb 01/98

3. __________ Job Set-up Subtask 34-52-11-865-050 A. Open, safety and tag this(these) circuit breaker(s):

R R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 7SH1, 7SH3 49VU COM NAV/ATC/1 5SH1 G11 FOR 7SH2, 7SH4 121VU COM NAV/ATC/2 5SH2 K07 Subtask 34-52-11-010-050 B. Get Access (1) FOR 7SH1, 7SH2 Find the ATC bottom antenna 1 7SH1 at zone 127 or ATC bottom antenna 2 7SH2 at zone 128. (2) FOR 7SH3, 7SH4 Put the access platform in position at zone 224 (ATC top antenna 1 7SH3) or at zone 223 (ATC top antenna 2 7SH4) 4. Procedure _________ (Ref. Fig. 401/TASK 34-52-11-991-001) Subtask 34-52-11-020-050 A. Removal of the ATC Antenna NOTE : The procedure is the same for the ATC antennas 7SH1, 7SH2, 7SH3 ____ and 7SH4. (1) Remove the sealant from the heads of the screws (5) with anonmetallic scraper. (2) Remove the screws (5). (3) Pull the antenna (4) away from the fuselage (1). (4) Disconnect the coaxial connector (2) from the ATC antenna connector (3).

  EFF : ALL  34-52-11    CES

 

Page 402 Feb 01/03

ATC Antenna Figure 401/TASK 34-52-11-991-001   EFF : ALL  34-52-11    CES

 

Page 403 Feb 01/98

(5) Remove the antenna (4). (6) Put blanking caps on the disconnected coaxial connectors (2) and (3). (7) Remove and discard the O-ring seal (6).

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Page 404 Feb 01/98

TASK 34-52-11-400-001 Installation of the ATC Antenna (7SH1,7SH2,7SH3,7SH4) WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific FOR FIN 7SH3, 7SH4 No specific

lint-free cloth masking tape nonmetallic scraper access platform 6.0 m (19 ft. 8 in.)

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 05-013

D TV-53-3507/73 RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)

Material No. 07-001B R Material No. 09-008 Material No. 09-016

ELECTRICAL BOND VARNISH (Ref. 20-31-00) USA MIL-S-8802 CLASS A NO LONGER AVAILABLE (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00)

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Page 405 Feb 01/09

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 09-019 Material No. 11-003 Material No. 16-003

USA AMS 3267/3 NO LONGER AVAILABLE (Ref. 20-31-00) USA ASTM D 740 METHYL-ETHYL-KETONE (Ref. 20-31-00) F ASNB70720 COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------6

O-ring seal

34-52-11 01 -010

D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-912-005 34-52-00-710-003 51-76-11-300-001 34-52-11-991-001

Electrical Bonding of Antennas With Conductive Bolts. Operational Test of the ATC Repair of the Sealing Fig. 401

3. __________ Job Set-up Subtask 34-52-11-860-050 A. Aircraft Maintenance Configuration (1) FOR 7SH1, 7SH2 Find the ATC bottom antenna 1 7SH1 at zone 127 or ATC bottom antenna 2 7SH2 at zone 128. (2) FOR 7SH3, 7SH4 Make sure that the access platform is in position at zone 224 (ATC top antenna 1 7SH3) or at zone 223 (ATC top antenna 2 7SH4).

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Page 406 Feb 01/09

Subtask 34-52-11-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 7SH1, 7SH3 49VU COM NAV/ATC/1 5SH1 G11 FOR 7SH2, 7SH4 121VU COM NAV/ATC/2 5SH2 K07 4. Procedure _________ (Ref. Fig. 401/TASK 34-52-11-991-001) WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN. _______ IF YOU DO: - RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH - WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER. WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE THE SPECIAL _______ MATERIAL. THIS MATERIAL IS DANGEROUS. Subtask 34-52-11-420-050 A. Installation of the ATC Antenna NOTE : The procedure is the same for the ATC antennas 7SH1, 7SH2, 7SH3 ____ and 7SH4. (1) Remove the sealant from the fuselage with CLEANING AGENTS (Material No. 11-003) and a nonmetallic scraper NOTE : If you install the same antenna it is necessary to clean it ____ with a lint-free cloth.

  EFF : ALL  34-52-11   R  CES

 

Page 407 Feb 01/09

(2) Do an inspection of the component interface and/or the adjacent area. NOTE : Make sure that the antenna-attachment screw-head recesses have ____ no signs of paint, corrosion or sealant because the antenna electrical bonding is made through the attachment screws. (3) Apply masking tape to the structure (1), the edge of the antenna (4), the screw holes and the hole for the antenna connector. (4) Apply SPECIAL MATERIALS (Material No. 05-013) on the mount of the antenna (4) and on the fuselage (1). (5) Apply SEALANTS (Material No. 09-019) on the mount of the antenna (4) and on the fuselage (1) (Ref. TASK 51-76-11-300-001). NOTE : Make sure that there is no sealant in the screw holes. ____ (6) Remove the blanking caps from the coaxial connectors (2) and (3). (7) Install the new O-ring seal (6). (8) Connect the coaxial connector (2) to the antenna connector (3). (9) Put the antenna (4) in position on the fuselage (1) and install the screws (5). (10) Tighten the screws (5). (11) Remove the sealant which is not necessary. (12) Make sure that the bonding contact resistance between the antenna (4) and the fuselage structure (1) is not higher than 5 milliohms (Ref. TASK 20-28-00-912-005). (13) Apply a sealing bead with SEALANTS (Material No. 09-016) or use as an alternative SEALANTS (Material No. 09-008) around the antenna (4) (Ref. TASK 51-76-11-300-001). (14) Apply SEALANTS (Material No. 09-016) or use as an alternative SEALANTS (Material No. 09-008) on the heads of the screws (5). (15) Make the contour of the screws (5) and the antenna (4) smooth. (16) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the base of the antenna (4).

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Page 408 Feb 01/09

(17) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001B) to the sealant on the heads of the screws (5). NOTE : It is not mandatory to paint the sealant around the base of ____ the antenna and on the head of the screws. Subtask 34-52-11-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 7SH1, 7SH3 5SH1 FOR 7SH2, 7SH4 5SH2 Subtask 34-52-11-710-050 C. Do the operational test of the ATC (Ref. TASK 34-52-00-710-003). 5. Close-up ________ Subtask 34-52-11-410-050 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the access platform(s).

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Page 409 Feb 01/09

CONTROL UNIT - ATC/TCAS (3SH) - REMOVAL/INSTALLATION ____________________________________________________ TASK 34-52-12-000-001 Removal of the ATC/TCAS Control Unit (3SH) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

blanking caps circuit breaker(s) safety clip(s)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-52-12-991-001

Fig. 401

3. __________ Job Set-up Subtask 34-52-12-865-050 A. Open, safety and tag this(these) circuit breaker(s):

R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07

  EFF : ALL  34-52-12    CES

 

Page 401 Feb 01/03

4. Procedure _________ (Ref. Fig. 401/TASK 34-52-12-991-001) Subtask 34-52-12-020-050 A. Removal of the ATC/TCAS Control Unit (3SH) R R R R R

NOTE : If your ATC/TCAS control unit has an INOP label(s) on its face and ____ if you must use this (these) label(s) for the new ATC/TCAS control unit: - remove this (these) label(s) carefully - keep them for installation on the new ATC/TCAS control unit. (1) Loosen the four quarter-turn fasteners (1). (2) Disengage the ATC/TCAS control unit (2) from its housing (5). (3) Disconnect the electrical connectors (4) and hold them away from the panel. (4) Remove the ATC/TCAS control unit (2). (5) Put blanking caps on the disconnected electrical connectors (3) and (4).

  EFF : ALL  34-52-12    CES

 

Page 402 Nov 01/01

ATC/TCAS Control Unit Figure 401/TASK 34-52-12-991-001   EFF : ALL  34-52-12    CES

 

Page 403 Feb 01/98

TASK 34-52-12-400-001 Installation of the ATC/TCAS Control Unit (3SH) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-52-00-740-004 34-52-12-991-001

BITE Test of the ATC Fig. 401

3. __________ Job Set-up Subtask 34-52-12-865-051 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged

R

------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU COM NAV/ATC/1 5SH1 G11 121VU COM NAV/ATC/2 5SH2 K07 4. Procedure _________ (Ref. Fig. 401/TASK 34-52-12-991-001) Subtask 34-52-12-420-050 A. Installation of the ATC/TCAS Control Unit (3SH) NOTE : If the new ATC/TCAS control unit has some inoperative ____ functions/modes, install the INOP labels that were on the removed ATC/TCAS control unit. (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (3) and (4).

  EFF : ALL  34-52-12    CES

 

Page 404 Feb 01/03

(4) Make sure that the electrical connectors are clean and in the correct condition. (5) Connect the electrical connectors (4) to the ATC/TCAS Control Unit (2). (6) Install the ATC/TCAS Control Unit (2) in its housing (5). (7) Tighten the four quarter-turn fasteners (1). Subtask 34-52-12-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5SH1, 5SH2 Subtask 34-52-12-740-050 C. Do the BITE test of the ATC (Ref. TASK 34-52-00-740-004). 5. Close-up ________ Subtask 34-52-12-860-050 A. Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-52-12    CES

 

Page 405 Feb 01/98

TRANSPONDER - ATC/MODE S (1SH1,1SH2) - REMOVAL/INSTALLATION ___________________________________________________________ TASK 34-52-33-000-001 Removal of the ATC/Mode S Transponder (1SH1, 1SH2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 211-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-52-33-991-001

Fig. 401

**ON A/C 201-210, 34-52-33-991-001-A

Fig. 401A

  EFF : ALL  34-52-33    CES

 

Page 401 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-52-33-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 1SH1 49VU COM NAV/ATC/1 5SH1 G11 FOR 1SH2 121VU COM NAV/ATC/2 5SH2 K07 Subtask 34-52-33-010-050 B. Get Access (1) Put the access platform in position at the access door 824 in zone 128. (2) Open the access door 824. 4. Procedure _________ R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 211-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401/TASK 34-52-33-991-001) **ON A/C 201-210, (Ref. Fig. 401A/TASK 34-52-33-991-001-A)

  EFF : ALL  34-52-33    CES

 

Page 402 Feb 01/10

ATC/Mode S Transponder Figure 401/TASK 34-52-33-991-001   R EFF : 001-049, 051-099, 101-149, 151-199,  34-52-33 211-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 403 Feb 01/10

ATC/Mode S Transponder Figure 401A/TASK 34-52-33-991-001-A   R EFF : 201-210,  34-52-33    CES

 

Page 404 Aug 01/02

R

**ON A/C ALL Subtask 34-52-33-020-050 A. Removal of the ATC/Mode S Transponder (1) Loosen the nuts (4). (2) Lower the nuts (4). (3) Pull the ATC/Mode S transponder, on its rack (3) to disconnect the electrical connectors (2). (4) Remove the ATC/Mode S transponder (1) from its rack (3). (5) Put blanking caps on the disconnected electrical connectors (2).

  EFF : ALL  34-52-33    CES

 

Page 405 Feb 01/99

TASK 34-52-33-400-001 Installation of the ATC/Mode S Transponder (1SH1,1SH2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-52-00-740-004 52-41-00-410-002 R R

BITE Test of the ATC Close the Avionics Compartment Doors after Access

**ON A/C 001-049, 051-099, 101-149, 151-199, 211-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-52-33-991-001

Fig. 401

**ON A/C 201-210, 34-52-33-991-001-A

Fig. 401A

  EFF : ALL  34-52-33    CES

 

Page 406 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-52-33-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at the access door 824 in zone 128. (2) Make sure that the access door 824 is open. Subtask 34-52-33-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 1SH1 49VU COM NAV/ATC/1 5SH1 G11 FOR 1SH2 121VU COM NAV/ATC/2 5SH2 K07 4. Procedure _________ R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 211-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401/TASK 34-52-33-991-001) **ON A/C 201-210, (Ref. Fig. 401A/TASK 34-52-33-991-001-A)

  EFF : ALL  34-52-33    CES

 

Page 407 Feb 01/10

R

**ON A/C ALL Subtask 34-52-33-420-050 A. Installation of the ATC/Mode S Transponder. (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (2). (4) Make sure that the electrical connectors (2) are clean and in the correct condition. (5) Install the ATC/Mode S transponder (1) on its rack (3). (6) Push the ATC/Mode S transponder (1) on its rack (3) to connect the electrical connectors (2). (7) Engage the nuts (4) on the lugs (5) and tighten. Subtask 34-52-33-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 1SH1 5SH1 FOR 1SH2 5SH2 Subtask 34-52-33-740-050 C. Do the BITE test of the ATC (Ref. TASK 34-52-00-740-004). 5. Close-up ________ Subtask 34-52-33-860-051 A. Make sure that the work area is clean and clear of tool(s) and other items.

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Page 408 Feb 01/99

Subtask 34-52-33-410-050 B. Close Access R

(1) Close the access door 824 (Ref. TASK 52-41-00-410-002). (2) Remove the access platform(s).

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Page 409 Feb 01/02

ADF - DESCRIPTION AND OPERATION _______________________________ 1. General _______ R R

**ON A/C 001-049, 051-051, 053-099, 101-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, The Automatic Direction Finder (ADF) is a radio navigation aid which provides : - an indication of the relative bearing of the aircraft to a selected ground station (150 to 1799 KHz) - aural identification of the ground station. The frequency range includes : - the standard commercial broadcast AM stations (550 to 1610 KHz) located at known co-ordinates around the world - the Non-Directional Beacons (NDB) (190 to 550 KHz). **ON A/C 052-052, 151-199, The Automatic Direction Finder (ADF) is a radio navigation aid which provides : - an indication of the relative bearing of the aircraft to a selected ground station : this station operates in a frequency range of 190 to 1750 KHz - aural identification of the ground station. The frequency range includes : - the standard commercial broadcast AM stations (550 to 1610 KHz) located at known co-ordinates around the world - the Non-Directional Beacons (NDB) (190 to 550 KHz). **ON A/C ALL 2. __________________ Component Location

R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599,

R

**ON A/C 001-049, 051-099, 101-149, 201-249, 501-509, 511-526, 528-599, (Ref. Fig. 001) **ON A/C 151-199, 401-499, (Ref. Fig. 001A)

  EFF : ALL  34-53-00    CES

 

Page 1 Feb 01/10

ADF - Component Location Figure 001   R EFF : 001-049, 051-099, 101-149, 201-249,  34-53-00 501-509, 511-526, 528-599,   CES

 

Page 2 Feb 01/10

ADF - Component Location Figure 001A   R EFF : 151-199, 401-499,  34-53-00    CES

 

Page 3 Aug 01/05

**ON A/C 301-399, (Ref. Fig. 001C) R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2RP1 RECEIVER-ADF, 1 81VU 127 824 34-53-31 2RP2 RECEIVER-ADF, 2 82VU 128 824 34-53-31 3RP1 ANTENNA-ADF LOOP AND SENSE, 1 244 34-53-11 3RP2 ANTENNA-ADF LOOP AND SENSE, 2 253 34-53-11 **ON A/C 251-299, (Ref. Fig. 001B) ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------2RP1 RECEIVER-ADF, 1 81VU 127 824 34-53-31 3RP1 ANTENNA-ADF LOOP AND SENSE, 1 244 34-53-11 3RP2 ANTENNA-ADF LOOP AND SENSE, 2 253 34-53-11 **ON A/C ALL 3. __________________ System Description A. Principle The principle of the ADF navigation is to determine the relative bearing of a selected ground station. This is obtained by the combination of : - the signals from two loop and sense antennas positioned 90 deg. apart with - the signal from an omni-directional sense antenna. This signal is not affected by the relative bearing. An external 96Hz signal modulates the composite signal which is processed in order to deliver the relative bearing. An additional Morse signal is provided to identify the selected ground station.

  EFF : ALL  34-53-00    CES

 

Page 4 Feb 01/10

R R

ADF - Component Location Figure 001B

  R EFF : 251-299,  34-53-00    CES

 

Page 5 May 01/09

ADF - Component Location Figure 001C

R

  R EFF : 301-399,  34-53-00    CES

 

Page 6 May 01/09

B. System Architecture R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, **ON A/C 001-004, 051-060, (Ref. Fig. 002)

R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, Post SB

34-1147 For A/C 001-004,051-060,

(Ref. Fig. 002C) R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, The ADF comprises two independent systems. Each system consists of : - one receiver 2RP1 (2RP2) - one loop and sense antenna 3RP1 (3RP2). In addition, the components given after control the system : (Ref. Fig. 003) - the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2) - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2) - the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) - the Centralized Fault-Display Interface-Unit (CFDIU) 1TW - the Audio Management Unit (AMU) 1RN. The Navigation Displays (ND) show the ADF1 and ADF2 data. **ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 002A) The ADF comprises two independent systems. Each system consists of : - one receiver 2RP1 (2RP2) - one loop and sense antenna 3RP1 (3RP2) - one VOR/ADF/DME Radio Magnetic Indicator (VOR/ADF/DME RMI) 21FN. In addition, the components given after control the system : (Ref. Fig. 003A) - the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2) - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2) - the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) - the Centralized Fault-Display Interface-Unit (CFDIU) 1TW

  EFF : ALL  34-53-00    CES

 

Page 7 Feb 01/10

ADF - Block Diagram Figure 002   R EFF : 001-004, 051-060,  34-53-00    CES

 

Page 8 May 01/09

ADF - Block Diagram Figure 002A   R EFF : 106-149, 201-249, 301-399, 401-499,  34-53-00    CES

 

Page 9 May 01/09

R R

ADF - Block Diagram Figure 002B

  R EFF : 251-299,  34-53-00    CES

 

Page 10 May 01/09

ADF - Block Diagram Figure 002C   R EFF : 001-049, 051-099, 101-105, 151-199,  34-53-00 501-509, 511-526, 528-599,   CES

 

Page 11 Feb 01/10

ADF - Control and Indicating Figure 003   R EFF : 001-049, 051-099, 101-105, 151-199,  34-53-00 251-299, 501-509, 511-526, 528-599,   CES

 

Page 12 Feb 01/10

ADF - Control and Indicating Figure 003A   R EFF : 106-149, 201-249, 301-399, 401-499,  34-53-00    CES

 

Page 13 May 01/09

- the Audio Management Unit (AMU) 1RN. The Navigation Displays (ND) show the ADF1 and ADF2 data. **ON A/C 251-299, (Ref. Fig. 002B) The ADF comprises one system which consists of: - one receiver 2RP1 - one loop and sense antenna 3RP1. The second system is in space provision and consists of : - one loop and sense antenna 3RP2. In addition, the components given after control the system: (Ref. Fig. 003) - the Radio Management Panel 1 (RMP) 1RG1 - the CAPT (F/0) Audio Control Panel (ACP) 2RN1 (2RN2) - the Multipurpose Control and Display Unit 1 (2) (MCDU) 3CA1 (3CA2) - the Flight Management and Guidance Computer 1 (2) (FMGC) 1CA1 (1CA2) - the Centralized Fault-Display Interface-Unit (CFDIU) 1TW - the Audio Management Unit (AMU) 1RN. The Navigation Displays (ND) show the ADF data. R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, C. Utilisation Technical Data (1) Data Display

R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, (Ref. Fig. 004) **ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 004A)

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-53-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 14 Feb 01/10

ADF - Data and Warning Displays Figure 004   R EFF : 001-049, 051-099, 101-105, 151-199,  34-53-00 501-509, 511-526, 528-599,   CES

 

Page 15 Feb 01/10

ADF - Data and Warning Displays Figure 004A   R EFF : 106-149, 201-249, 301-399, 401-499,  34-53-00    CES

 

Page 16 May 01/09

R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, (a) In ROSE and ARC modes If you set the ADF/VOR/OFF switches on the EFIS control section of the FCU to ADF, this causes : display of the characteristics of the ADF 1 and/or 2 stations in the L and/or R lower corner of the ND (item 3) : - type of station - shape of the associated bearing display - station identification or frequency - tuning mode (nothing : automatically tuned, M : manually tuned and R : if tuned by the RMP). A single pointer on the heading dial shows the bearing of the ADF 1, a double pointer that of the ADF 2 (item 2). All these data are shown in green except the tuning mode which is shown in white. (b) In ROSE NAV and ARC modes If you push the NDB pushbutton switch on the EFIS control section of the FCU, triangle symbols show the ADF stations (item 1). (c) In case of NCD, the station characteristics and associated pointer(s) go out of view. (d) In case of ADF 1 (2) fault, a red ADF warning message is shown in place of the station characteristics. **ON A/C 251-299, C. Utilisation Technical Data (1) Data display (Ref. Fig. 004B) (a) In ROSE and ARC modes If you set the ADF/VOR/OFF switch on the EFIS control section of the Flight Control Unit (FCU) to ADF, this causes : display of the characteristics of the ADF 1 station in the L lower corner of the ND (item 3) : - type of station - shape of the associated bearing display - station identification or frequency - tuning mode (nothing : automatically tuned, M : manually tuned and R : if tuned by the RMP).

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-53-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 17 Feb 01/10

R R

ADF - Data and Warning Displays Figure 004B

  R EFF : 251-299,  34-53-00    CES

 

Page 18 May 01/09

A single pointer on the heading dial shows the bearing of the ADF 1 (item 2). All these data are shown in green except the tuning mode which is shown in white. (b) In ROSE NAV and ARC modes If you push the NDB pushbutton switch on the EFIS control section of the FCU, triangle symbols show the ADF stations (item 1). (c) In case of No Computed Data (NCD), the station characteristics and associated pointer go out of view. (d) In case of ADF fault, a red ADF warning message is shown in place of the station characteristics. **ON A/C 106-149, 201-249, 301-399, 401-499, (2) On the VOR/ADF/DME RMI If you set the VOR/ADF selector switches (item 4) to ADF, the RMI indicates the ADF bearings : - a single pointer indicates the ADF 1 bearing (item 5) - a double pointer indicates the ADF 2 bearing (item 6). A warning flag comes into view to indicate system malfunction (item 7) . In this case, the related pointer is at the last valid position (item 8). If No Computed Data (NCD), the warning flag comes into view and the related pointer stays at the position corresponding to the last correct data. R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, (3) Audio control (a) The ADF receiver applies its audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the ADF1 (ADF2) pushbutton switch and adjust the related potentiometer to the correct audio level. (b) Only with NDB stations modulated in A1 mode (in automatic or manual mode) it is necessary to select the BFO function on the MCDU in order to hear clearly its Morse identification signal.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-53-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 19 Feb 01/10

(c) In emergency mode, the BFO function is selected on the RMP when : - you push the STBY NAV/ADF pushbutton switch - you push the STBY NAV/BFO pushbutton switch. (d) It is possible to select the broadcast station on the RMP and the MCDU (manual mode only). In this case, the BFO selection is not necessary. (e) With the ATIS message trasmission by the NDB station, with the BFO active : it is necessary to push the ON VOICE pushbutton switch on one ACP in order to hear clearly this information without Morse signal. D. Warning R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, (Ref. Fig. 004) **ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 004A)

R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, The warnings related to the ADF are only the local warnings shown on the NDs. The warnings are detected by the BITE function of the receiver. **ON A/C 251-299, (3) Audio control (a) The ADF receiver applies its audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the ADF1 pushbutton switch and adjust the related potentiometer to the correct audio level. (b) Only with NDB stations modulated in A1 mode (in automatic or manual mode) it is necessary to select the BFO function on the MCDU in order to hear clearly its Morse identification signal.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-53-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 20 Feb 01/10

(c) In emergency mode, the BFO function is selected on the RMP when : - you push the STBY NAV/ADF pushbutton switch - you push the STBY NAV/BFO pushbutton switch. (d) It is possible to select the broadcast station on the RMP and the MCDU (manual mode only). In this case, the BFO selection is not necessary. (e) With the ATIS message trasmission by the NDB station, with the BFO active : it is necessary to push the ON VOICE pushbutton switch on one ACP in order to hear clearly this information without Morse signal. D. Warning (Ref. Fig. 004B) The warnings related to the ADF are only the local warnings shown on the NDs. The warnings are detected by the BITE function of the receiver. **ON A/C ALL 4. ____________ Power Supply R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, **ON A/C 001-004, 051-060, (Ref. Fig. 002) **ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 002A)

R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, Post SB

34-1147 For A/C 001-004,051-060,

(Ref. Fig. 002C) R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, Energization of the system is through 115VAC 400 Hz buses :

  EFF : ALL  34-53-00    CES

 

Page 21 Feb 01/10

**ON A/C 251-299, (Ref. Fig. 002B) Energization of the system is through 115VAC 400 Hz buses : **ON A/C ALL - 115VAC SHED ESS BUS 801XP via circuit breaker 1RP1 - 115VAC BUS 2 202XP via circuit breaker 1RP2 **ON A/C 106-149, 201-249, 301-399, 401-499, The 115VAC ESS BUS 401XP energizes the VOR/ADF/DME RMI via circuit breaker 12FN. **ON A/C ALL 5. _____________________ Component Description R

**ON A/C 001-049, 101-105, 151-199, A. ADF Receiver (1) Characteristics - Frequency range : 150 to 1799 KHz in 0.5 KHz steps - Electrical power supply: 115VAC, 400 Hz, 30 watts - Tuning accuracy: selected frequency plus or minus 250 Hz - ADF accuracy: plus or minus 2 deg. - Sensivity: 30 % modulation - ADF mode: 50 microV/m field strength at 400 Hz for 6 dB signal to noise ratio. (2) External description (Ref. Fig. 005) The face of the receiver is fitted with a handle, two attaching parts, two momentary pushbutton switches and a front panel Liquid Crystal Display (LCD). The LCD is used as a fault display and as an operator interface during certain modes. The front panel display also provides user interfaces for test and troubleshooting. The front panel contains two momentary pushbutton switches for interfacing with the LCD pages.

  EFF : ALL  34-53-00    CES

 

Page 22 Nov 01/09

An RS-232 maintenace access port is provided on the front panel. This port is compatible with RS-232 serial ports on Personal Computers (PC). The back is equipped with one ARINC 600 size one connector, which includes three plugs: - Top Plug (TP): is not used - Middle Plug (MP): used for aircraft connections ts - Bottom Plug (BP): used for input power. (a) Not Applicable R R

**ON A/C 051-051, 053-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, A. ADF Receiver (1) Characteristics - Frequency range : 190 to 1799 KHz in 0.5 KHz steps - Electrical power supply: 115VAC, 400 Hz, 45 VA - Tuning accuracy: selected frequency plus or minus 250 Hz - ADF accuracy: plus or minus 2 deg. - Sensivity: 30 % modulation - ADF mode: 50 microV/m field strength at 400 Hz for 6 dB signal to noise ratio. (2) External description The ADF receiver conforms with the ARINC specification 600. The case size is 2MCU. (a) Receiver face (Ref. Fig. 005A) The face of the receiver is fitted with a handle, one lug, a TEST pushbutton switch and two LEDs. The name, color and function of the two LEDs are as follows: - LRU STATUS (red): indicates that a malfunction is detected during the self test of the ADF receiver. - LRU STATUS (green): indicates that no faults are detected during the self test of the ADF receiver. - CONTROL FAIL (red): indicates that an ARINC input data is faulty. The back is equipped with one ARINC 600 size one connector which includes three plugs: - Top Plug (TP): connection with the automatic test circuit - Middle Plug (MP): connection with the antenna and peripheral circuits - Bottom Plug (BP): connection with the power supply circuit. Index pin code is 05.

  R EFF : 001-049, 051-051, 053-099, 101-149,  34-53-00 151-199, 201-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 23 Feb 01/10

ADF - Receiver Figure 005 (SHEET 1)   R EFF : 001-049, 101-105, 151-199,  34-53-00    CES

 

Page 24 Nov 01/09

ADF - Receiver Figure 005 (SHEET 2)   R EFF : 001-049, 101-105, 151-199,  34-53-00    CES

 

Page 25 Nov 01/09

ADF - Receiver Figure 005A   R EFF : 051-051, 053-099, 106-149, 201-249,  34-53-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 26 Feb 01/10

**ON A/C 052-052, A. ADF Receiver (1) External description (Ref. Fig. 005B) The face of the receiver is fitted with a handle, one attaching part, a TEST pushbutton switch and three LEDs. The name, color and function of the three LEDs are as follows: - CONTROL INPUT/FAIL (red) indicates that the receiver is not receiving any information at the input ports, during self-test - LRU STATUS/PASS (green) indicates that no faults are detected during the self-test sequence - LRU STATUS/FAIL (red) indicates that a fault is detected during the self-test sequence. The back of the ADF receiver contains an ARINC 600, shell size connector to provide electrical connections to the aircraft wiring via mount. Contact grouping is as follows : - Top contact set - ATE interface - Center contact set - System interconnections - Bottom contact set - Power supply and bonding (2) Not Applicable R

**ON A/C 001-049, 101-105, 151-199, (3) Internal description (Ref. Fig. 006) The ADF receiver includes: - an RF module, - a main processor assembly, - a power supply assembly, - a rear interconnect module, - a front panel display module, - a memory card interface module. (a) RF module The RF module contains receiver and synthesizer circuits to amplify and connvert the antenna derived sense, sine and cosine signals to baseband signals for digital signal processing. The RF receiver receives three signals from the combined sense/loop antenna, sense signal from the sense portion of the antenna and sine and cosine signals from the two bar-loops.

  R EFF : 001-049, 052-052, 101-105, 151-199,  34-53-00    CES

 

Page 27 Nov 01/09

ADF - Receiver Figure 005B   R EFF : 052-052,  34-53-00    CES

 

Page 28 Aug 01/09

ADF Receiver - Simplified Block Diagram Figure 006   R EFF : 001-049, 101-105, 151-199,  34-53-00    CES

 

Page 29 Nov 01/09

The sense signal is coupled to a buffer amplifier that provides +4 to +6 dB gain and improves the voltage to noise figure of the receiver. The buffer amplifier also prevents loop modulation backward towards to sense antenna. The sense signal is summed in quadrature with the 105 Hz phase modulated sine and cosine signals. This composite signal is then upconverted to 10.7 MHz where a cristal filter provides selectivity. The signal is then amplified and detected for processing by the digital signal processor. The synthesiser provides local oscillator injection to upconvert the ADF RF signals to 10.7 MHz. The upconverted signal is passed through an IF filter and an IF amplifier. The signal is then down converted to 140 kHz. The 140 kHz IF signal is then amplified and sampled by the Analog/Didital (A/D) and sent to the DSP via the FIFO. Tuning (band switching) is accomplished by utilizing a 7 - band RF filter in conjunction with a band switching circuit. Essentially the tuning range of the ADF receiver is separated into seven discrete bands. (b) Main Processor Module The Main Processor Board serves as the heart of the ADF reciver. The analog signals from the RF module are processed and used to generate the ADF audio and bearing outputs. All aircraft interfaces are controlled by this board. All information on the front panel display is provided by this board. The board includes three major sections: - DSP section, - DP (microprocessor) section, - I/O section. 1 _

DSP section The DSP section is used to process the analog outputs from the RF Module and to generate automatic gain control and other receiver commands as well as test signals to the RF Module. The DSP performs the bearing computations, Automatic Gain Control (AGC), Audio Filtering, Morse Code Tone detection, part of the BITE monitoring and RF module control. The DSP programs the synthesizer using the data from the DP. The composite ADF signal from the RF Module is digitized using an A/D converter. The A/D converter is also used to monitor signals from the BITE test points on the power supply voltages. The digitized data from the A/D converter is stored in a FIFO which is accessed by the DSP. Programmable Logic Devices (PLD) are used by the DSP to generate the control signals for the ADF frequency synthesizer. A Digital/Analog (D/A) converter generates the

  R EFF : 001-049, 101-105, 151-199,  34-53-00    CES

 

Page 30 Nov 01/09

AGC and test control signals for the RF Module. A second D/A converter generates the audio outputs which are amplified to provide up to 50mW into a load ranging from 200 Ohms to 600 Ohms. A D/A converter generates the AGC, lateral and longitudinal modulations as well as the Audio signal. Data is exchanged with the CPU Section through a dual-port RAM, providing maximum throughput of both processors. The DSP provides the DP with the ADF bearing outputs periodically (every 50 ms) via the shared memory interface. The Main DSP also provides morse code report via the shared memory interface. In addition the DSP provides the audio outputs via the D/A. 2 _

DP section (Intel 80486) The DP section is used to process the BIT data from the DSP section, to provide information to the front panel display and to provide the data and control signals to the I/O section. The microprocessor in the DP section controls all major functions of the ADF. Programmable Logic Devices serve as the microprocessor controller and provide the interfaces to the memory devices, the data recorder/data loader flash card, and the front panel display driver. The DP receives the ADF bearing reports from the DSP every 50 ms. The DP sends the ADF receiver frequency band select, operational mode select and receiver synthesizer tuning code to the DSP upon the receipt of an external frequency change command. The DP performs the QEC and TOP/BOTTOM compensation on the bearing data received from the DSP prior to outputing the bearing data to external systems. Data is exchanged with the DSP section through a dual-port RAM.

3 _

I/O section The I/O section provides the interfaces with other aircraft systems including the centralized Fault Display Interface Unit (CFDIU), Control Panel(s), displays and the AFCS. ARINC 429 inputs from the data loader, CFDIU and the tuning control panel(s) are processed by the ARINC 429 Large Scale Integrated (LSI). This LSI also provides the ARINS 429 data loader, CFDIU and deviation outputs. External buffers are used to satisfy the ARINC 429 characteristics for the transmitters. All discrete inputs external to the ADF Receiver are processed by the I/O section. This section also generates the external discrete outputs. The I/O section also contains an RS-232C test interface.

  R EFF : 001-049, 101-105, 151-199,  34-53-00    CES

 

Page 31 Nov 01/09

(c) Power Supply Module The 115 VAC, 400 Hz aircraft power is converted by the Power Supply into the DC operating voltages required by the various modules within the ADF receiver. A self-contained, high efficiency switching power supply is used to minimize power dissipation. Five voltages (+5, +12, -12, +20 and +24V) are supplied and a Power Down Interrupt that provides avanced notice of a power loss allowing the processors to temporarily retain their status. A switching circuitry is provided for the power supply to switch its operating frequency in order to prevent a degradation of the receiver sensitivity. (d) HIRF/Rear Interconnect Module The signal and power cables are on the rear interconnect located inside this High Intensity Radiated Field (HIRF) compartment. The filtered lines are then fed to the appropriate points in the unit. The filtering is accomplished using discrete and distributed shunt capacitance for HIRF filtering. The series resistance, required to limit lightning-induced currents, also forms a series element to HIRF filtering. (e) Front Panel Display The front panel contains a low-power Liquid Crystal Display (LCD) used as a fault display and as an operator interface during certain modes and display drivers. The front panel display also provides user interfaces for test and troubleshooting. (f) Memory Card Interface Module The ADF receiver is provided with an interface for a Personal Computing Memory Card Interface Adapter (PCMCIA) flash card which gives the capability to record data or be configured for read only memory (means to load new software without opening the unit to replace Programmable Read Only Memory (PROM), maintenance and problem installations). (4) Not Applicable R R

**ON A/C 051-051, 053-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (3) Internal description The receiver determines the relative bearing to any selected transmitter operating between 190 and 1799 KHz. This bearing data is converted into ARINC 429 format and transmitted through ARINC buses to the NDs via the DMCs. In addition the AM modulation of the carrier wave is detected and applied to the audio integrating system. The

  R EFF : 001-049, 051-051, 053-099, 101-149,  34-53-00 151-199, 201-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 32 Feb 01/10

receiver is housed in an ARINC 2MCU case and consists of the following interconnected assemblies: (a) An ARINC interconnect assembly which provides filtering against HIRF and noise entry or exit. (b) A digital instrumentation assembly which contains the system processor and signal processor: 1 _

The function of the system processor is to: - format the ADF data from the signal processor into an ARINC 429 bearing word - provide frequency tuning for the ADF receiver - perform functional test and self-test functions - provide diagnostic data to the maintenance processor - transmit data generated by the system processor and maintenance processor - store calibration constants (as received from the signal processor) in the system processor Non-Volatile Memory during the calibration mode - monitor the power-down warning signal from the power supply to provide warm start capability - monitor system voltages and discretes for fault conditions.

2 _

The function of the signal processor is to: - compute and output, to the system processor, the ADF bearing derived from the ADF detector - determine the presence of the ADF detector signal and flag the bearing data accordingly - detect the presence of a 400Hz or 1020Hz identification tone (or BFO mode) and output a tone present discrete to the maintenance processor - monitor ADF signal level status and output maintenance data to the system processor - output sin mode and cosine mode to the loop modulators via their respective D/A converters - process the ADF detector signal to provide filtered and amplitude controlled audio information to the aircraft audio system.

(c) A maintenance processor assembly the primary function of which is the logging of maintenance information and secondarily, decoding the morse binary data stream into ASCII characters. (d) A power supply assembly which provides +12VDC, -12VDC and -5VDC from 115VAC at 400Hz.

  R EFF : 051-051, 053-099, 106-149, 201-249,  34-53-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 33 Feb 01/10

(e) A tuner/synthesizer assembly 1 _

The tuner combines the sense and loop signals from the antenna, amplifies and filters them and then provides the detected audio information to the signal processor.

2 _

The synthesizer receives frequency information from the system processor and provides fixed and variable oscillator signals for the mixers in the tuner.

(4) Operation (Ref. Fig. 006A) The operation of the receiver is initiated when the desired frequency is selected by the FMGCs or RMPs. Frequency and function data are received via an interface. This data is used to activate the desired function, set the receive band and tune a Voltage Controlled Oscillator (VCO) for converting the received signal to the IF. Sense and loop signals from the antenna are applied to the loop modulators where they are modulated with 95Hz control signals from the signal processor. The summed output of the loops is corrected for the antenna loop gain and phase and then summed with the sense channel. The composite output of the summing circuit is passed through a band select filter, which output feeds the first mixer. The VCO is mixed with the input to generate a first IF of 15MHz. The signal is filtered and amplified and then applied to the second mixer where 18.6MHz mixes it down to a second IF of 3.6Mhz. It is once again filtered and amplified before application to a coherent detector. The output of the coherent detector is used to derive the AGC control for the IF. The composite audio is sampled and processed by audio and bearing algorithms in a Digital Signal Processor (DSP) in the signal processor area. The DSP filters the audio, and sets the output level and returns it to an audio amplifier stage, and then to the aircraft audio system. The DSP also applies a separate narrow audio filter and then detects the audio tone for MORSE ident. This binary data stream is sent to the maintenance processor for decoding into ASCII characters. The bearing is determined in the null-seeking algorithm by the DSP continuously adjusting the ratio of the 95Hz loop modulation applied to the sine and cosine modulators. When the ratio is properly adjusted, the amount of 95Hz present in the coherent detector output is minimized. The ratio of the loop modulation is then directly proportional to the raw bearing. The raw bearing is corrected for Quandrantal Error and calibration factors.

  R EFF : 051-051, 053-099, 106-149, 201-249,  34-53-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 34 Feb 01/10

ADF Receiver - Simplified Block Diagram Figure 006A   R EFF : 051-051, 053-099, 106-149, 201-249,  34-53-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 35 Feb 01/10

The signal processor then converts this corrected bearing to ARINC word format and relays it to the system processor for transmission on the ARINC bus. In addition to its receiver control functions, the system processor continuously monitors receiver health and passes radio health information to the maintenance processor. It also initiates functional tests when conditions allow it. The maintenance processor processes commands from the CFDIU and stores faults detected by the system processor. It also decodes the MORSE ident data stream passed by the signal processor. **ON A/C 052-052, (3) Internal description The receiver determines the relative bearing to any selected transmitter operating between 190 and 1750 kHz. This bearing data is converted into ARINC 429 format and transmitted through ARINC buses to the DMCs. In addition the AM modulation of the carrier wave is detected and applied to the audio integrating system. The receiver is housed in an ARINC 2MCU case and consists of an aluminum chassis which contains: (a) A tuner which modulates, combines and amplifies the IF signals received from the loop and sense antenna. The tuner also includes a detector and audio processing circuits. (b) A synthesizer which produces fixed and variable frequencies used in the receiver. (c) A backplate which provides interface between the rear connector and the other assemblies. (d) An input/output assembly for interface with the aircraft circuits. (e) A processor which generates the basic clock signals used and converts the analog bearing into digital data for the input/output assembly. (f) A preprocessor which generates the 96 Hz reference signal used to modulate the signals from the loop antenna. (g) A power supply assembly which converts the 115VAC aircraft supply into the various voltages used by the internal circuits of the receiver.

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-53-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 36 Feb 01/10

(4) Operation (Ref. Fig. 006B) The loop antenna outputs are amplitude modulated by 96 Hz signals which are shifted 90⁰ with respect to the other. The modulated outputs are then combined to produce a composite signal. The phase relationship between this composite signal and the 96 Hz modulation is proportional to the bearing of the received station but with a phase shift of 180⁰. The phase shift is eliminated by combining the composite signal with the output from the sense antenna. The combined output is then filtered and mixed with an injected input from the synthesizer to produce a 15 MHz IF output. The injected input to the mixer is tunable over the range 15.19 to 16.75 MHz corresponding to the receiver tuning range of 190 to 1750 kHz. The 15 MHz output is then mixed with a fixed 18.6 MHz signal from the synthesizer to produce a 3.6 MHz IF signal which is filtered and applied to a coherent detector which provides: - an audio output to the aircraft audio integrating system - an Automatic Gain Control (AGC) signal for the IF stages - a composite audio output which is applied to the signal processor through an A/D converter. The signal processor determines the phase relationship between the 96 Hz signal and the composite audio output. The phase data, after correction for quadrantal error, is the station bearing data which is applied to the input/output processor for transmission through ARINC 429 data buses to the DMCs. **ON A/C ALL (5) Digital outputs This table contains all the output parameters in the digital form. ---------------------------------------| LABEL | PARAMETER DEFINITION | ---------------------------------------| 032 | ADF FREQUENCY | ---------------------------------------| 162 | ADF BEARING | ---------------------------------------| 254 | ADF IDENTIFIER WORD 1 | ---------------------------------------| 255 | ADF IDENTIFIER WORD 2 | ---------------------------------------| 377 | EQUIPEMENT IDENTIFIER | ---------------------------------------| 356 | MAINTENANCE STATUS | ----------------------------------------

  R EFF : ALL  34-53-00    CES

 

Page 37 Aug 01/09

ADF Receiver - Simplified Block Diagram Figure 006B   R EFF : 052-052,  34-53-00    CES

 

Page 38 Aug 01/09

B. Loop and Sense Antenna (Ref. Fig. 007) The combined loop and sense antenna operates in the 190 to 1750 kHz frequency range and consists of the following components enclosed in a fiberglass housing: - a vertically polarized sense antenna which is omnidirectional in the horizontal plane - two horizontally polarized orthogonal loop antennas which are directional in the horizontal plane - a test loop which enables a self-test of the antenna - a printed circuit board which contains three pre-amplifiers used to amplify the loop and sense antennas signals. The pre-amplifiers are energized by plus or minus 12VDC form the ADF receiver. The output impedance of the antenna is 78 Ohms and the Voltage Standing Wave Ratio (VSWR) 1.2:1. 6. Operation _________ R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, **ON A/C 001-004, 051-060, (Ref. Fig. 002) **ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 002A)

R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, Post SB

34-1147 For A/C 001-004,051-060,

(Ref. Fig. 002C) R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, NOTE : The two ADF systems are independent. The operating mode is identical ____ for ADF 1 and ADF 2. - The FMGC 1 sends a management bus to the ADF receiver 1 through the RMP1.

  EFF : ALL  34-53-00    CES

 

Page 39 Feb 01/10

ADF - Antenna Figure 007   EFF : ALL  34-53-00   R  CES

 

Page 40 Aug 01/09

- In normal operation, the FMGC 1 tunes the ADF receiver 1 either automatically or manually by means of the MCDU. In this case, the RMP 1 operates as a relay which sends the frequency information from the FMGC 1 to the ADF receiver 1. - By a second port, the ADF receiver 1 receives a second management bus directly from the FMGC 2. The FMGC 2 becomes active when the ADF receiver 1 receives a failure signal from the FMGC 1. - With RMP 1 internal failures the RMP 1 is transparent to data and discrete from the FMGC 1. - In emergency configuration (failure of the FMGC 1 and 2), the RMP 1 can control the ADF receiver 1 after ON NAV mode selection. - In emergency configuration (failure of the FMGC 1 and 2), the RMP 2 can control the ADF receiver 2 after on NAV mode selection. (Ref. Fig. 008) **ON A/C 251-299, (Ref. Fig. 002B) - The FMGC 1 sends a management bus to the ADF receiver 1 through the RMP 1. - In normal operation, the FMGC 1 tunes the ADF receiver 1 either automatically or manually by means of the MCDU. In this case, the RMP 1 operates as a relay which sends the frequency information from the FMGC 1 to the ADF receiver 1. - By a second port, the ADF receiver 1 receives a second management bus directly from the FMGC 2. The FMGC 2 becomes active when the ADF receiver 1 receives a fault signal from the FMGC 1. - With RMP 1 internal faults the RMP 1 is transparent to data and discrete from the FMGC 1. - In emergency configuration (fault of the FMGC 1 and 2), the RMP 1 can control the ADF receiver 1 after ON NAV mode selection. (Ref. Fig. 008) **ON A/C ALL 7. Test ____ R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, A. Maintenance Test **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 009)

  EFF : ALL  34-53-00    CES

 

Page 41 Feb 01/10

ADF - Frequency Selection in Emergency Mode Figure 008   EFF : ALL  34-53-00   R  CES

 

Page 42 Aug 01/09

ADF - Maintenance Test Procedure Figure 009   R EFF : 001-049, 101-105, 151-199,  34-53-00    CES

 

Page 43 Aug 01/09

R

**ON A/C 051-051, 053-099, 501-509, 511-526, 528-599, (Ref. Fig. 009A) **ON A/C 052-052, (Ref. Fig. 009B)

R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, It is possible to do the maintenance tests with the Centralized Fault Display System (CFDS). The primary components of the CFDS are : - the MCDU - the CFDIU - the Built-In Test Equipment (BITE) internal to the ADF receiver. It is possible to perform these tests on the ground only. The access to the ADF 1 (2) menu is through : - selection of the SYSTEM REPORT/TEST item on the CFDS menu - then, selection of the relevant ADF on the NAV menu. The test sequence starts when you push the line key adjacent to the TEST indication on the ADF1(2) menu. **ON A/C 106-149, 201-249, 301-399, 401-499, A. Maintenance Test (Ref. Fig. 009A) It is possible to do the maintenance tests with the Centralized Fault Display System (CFDS). The primary components of the CFDS are : - the MCDU - the CFDIU - the Built-In Test Equipment (BITE) internal to the ADF receiver. It is possible to perform these tests on the ground only. The access to the ADF 1 (2) menu is through : - selection of the SYSTEM REPORT/TEST item on the CFDS menu - then, selection of the relevant ADF on the NAV menu. A self-test of the system causes the receiver to transmit a test signal to the VOR/ADF/DME RMI and ND. On the VOR/ADF/DME RMI, if you set the VOR/ADF selector switches (item 4) to ADF. The test sequence starts when you push the line key adjacent to the TEST indication on the ADF1(2) menu.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-53-00 201-249, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 44 Feb 01/10

ADF - Maintenance Test Procedure Figure 009A   R EFF : 051-051, 053-099, 106-149, 201-249,  34-53-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 45 Feb 01/10

ADF - Maintenance Test Procedure Figure 009B   R EFF : 052-052,  34-53-00    CES

 

Page 46 Aug 01/09

**ON A/C 251-299, A. Maintenance Test (Ref. Fig. 009C) It is possible to do the maintenance tests with the Centralized Fault Display System (CFDS). The primary components of the CFDS are : - the MCDU - the CFDIU - the Built-In Test Equipment (BITE) internal to the ADF receiver. It is possible to perform these tests on the ground only. The access to the ADF 1 menu is through : - selection of the SYSTEM REPORT/TEST item on the CFDS menu - then, selection of the relevant ADF on the NAV menu. The test sequence starts when you push the line key adjacent to the TEST indication on the ADF1 menu. R R

**ON A/C 001-049, 051-051, 053-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, B. CFDIU Interface **ON A/C 001-004, 051-051, 053-060, (Ref. Fig. 002) **ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 002A) **ON A/C 251-299, (Ref. Fig. 002B)

R R

**ON A/C 001-049, 051-051, 053-099, 101-105, 151-199, 501-509, 511-526, 528-599, Post SB 34-1147 For A/C 001-004,051-051,053-060, (Ref. Fig. 002C)

  R EFF : 001-049, 051-051, 053-099, 101-149,  34-53-00 151-199, 201-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 47 Feb 01/10

ADF - Maintenance Test Procedure Figure 009C   R EFF : 251-299,  34-53-00    CES

 

Page 48 Nov 01/09

R R

**ON A/C 001-049, 051-051, 053-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the ADF system. The BITE of the ADF receiver is connected to the CFDIU (Ref. 31-32-00). The unit tested is the ADF receiver. The BITE: - transmits continuously ADF system status and its identification message to the CFDIU - memorizes the failures which occurred during the last 63 flight segments - monitors data inputs from the various peripherals (RMP and CFDIU) - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the menu mode. (a) Normal mode During the normal mode the BITE monitors cyclically the status of the ADF system. It transmits its information to the CFDIU during the concerned flight. In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 50 - 250 ms by an ARINC 429 message with label 356. (b) Menu mode: The menu mode can only be activated on the ground. This mode enables communication between the CFDIU and the ADF receiver BITE by means of the MCDU. The ADF menu mode is composed of: - LAST LEG REPORT - PREVIOUS LEGS REPORT - LRU IDENTIFICATION - GROUND SCANNING - TROUBLE SHOOTING DATA - CLASS 3 FAULTS - GROUND REPORT - TEST.

  R EFF : 001-049, 051-051, 053-099, 101-149,  34-53-00 151-199, 201-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 49 Feb 01/10

(2) Interactive function The interactive mode can be activated on the ground only, using the line key adjacent to the ADF indication on the SYSTEM REPORT/TEST page of any MCDU (Ref. 22-82-00). This mode enables communication between the CFDIU and the BITE of the ADF receiver by means of the MCDU. **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 009) R R

**ON A/C 051-051, 053-099, 106-149, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 009A) **ON A/C 251-299, (Ref. Fig. 009C)

R R

**ON A/C 001-049, 051-051, 053-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, The interactive mode is composed of: - LAST LEG REPORT: This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the last flight leg. **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 010)

R R

**ON A/C 051-051, 053-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 010A)

R R

**ON A/C 001-049, 051-051, 053-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, - PREVIOUS LEGS REPORT:

  R EFF : 001-049, 051-051, 053-099, 101-149,  34-53-00 151-199, 201-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 50 Feb 01/10

ADF - Last Leg Report, Previous Legs Report and LRU IDENT Figure 010   R EFF : 001-049, 101-105, 151-199,  34-53-00    CES

 

Page 51 Nov 01/09

ADF - Last Leg Report, Previous Legs Report and LRU IDENT Figure 010A   R EFF : 051-051, 053-099, 106-149, 201-249,  34-53-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 52 Feb 01/10

This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 010) R R

**ON A/C 051-051, 053-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 010A)

R R

**ON A/C 001-049, 051-051, 053-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, - LRU IDENTIFICATION: Allows to display the P/N and the S/N of the equipment. **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 010)

R R

**ON A/C 051-051, 053-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 010A)

R R

**ON A/C 001-049, 051-051, 053-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, - GROUND SCANNING: **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 011)

R R

**ON A/C 051-051, 053-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 011A)

  R EFF : 001-049, 051-051, 053-099, 101-149,  34-53-00 151-199, 201-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 53 Feb 01/10

ADF - GROUND SCANNING and Trouble Shooting Data Figure 011   R EFF : 001-049, 101-105, 151-199,  34-53-00    CES

 

Page 54 Nov 01/09

ADF - GROUND SCANNING and Trouble Shooting Data Figure 011A   R EFF : 051-051, 053-099, 106-149, 201-249,  34-53-00 251-299, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 55 Feb 01/10

R R

**ON A/C 001-049, 051-051, 053-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. By pressing the line key adjacent to the failure message, the operator is allowed to the corresponding Trouble Shooting Data. The peripheral monitoring and ADF internal cyclic tests are used to detect transient failures. - TROUBLE SHOOTING DATA **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 011)

R R

**ON A/C 051-051, 053-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 011A)

R R

**ON A/C 001-049, 051-051, 053-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599,

-

-

-

-

Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT. CLASS 3 FAULTS (Ref. Fig. 012) Allows to display the class 3 faults recorded during the last flight leg. GROUND REPORT (Ref. Fig. 012) Allows to present the class 1, 2 or 3 internal failures detected on ground. These failures differ from those displayed on the LAST LEG REPORT and CLASS 3 FAULTS. By pressing the line key adjacent to the failure message, the operator is allowed to access to the corresponding Trouble Shooting Data. TEST (Ref. Fig. 013) Allows a check of the correct operation of the ADF on the ground. This test can be performed by: either selecting the test function on the face of the ADF receiver by pressing the TEST pushbutton switch

  R EFF : 001-049, 051-051, 053-099, 101-149,  34-53-00 151-199, 201-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 56 Feb 01/10

ADF - CLASS 3 FAULTS and Ground Report Figure 012   R EFF : 001-049, 051-051, 053-099, 101-149,  34-53-00 151-199, 201-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 57 Feb 01/10

ADF - TEST Figure 013 (SHEET 1)   R EFF : 001-049, 051-051, 053-099, 101-149,  34-53-00 151-199, 201-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 58 Feb 01/10

ADF - TEST Figure 013 (SHEET 2)   R EFF : 001-049, 051-051, 053-099, 101-149,  34-53-00 151-199, 201-249, 251-299, 301-399, 401-499,  501-509, 511-526, 528-599, CES

 

Page 59 Feb 01/10

- or through the Centralized Fault Display System (CFDS) by selecting, on the MCDU, the test function on the ADF main menu page. All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00). R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, C. Power-up Tests Initialization and Cockpit Repercussions (1) Conditions of power-up tests initialization - How long the computer must be de-energized: 2 s. - A/C configuration: - whatever the A/C configuration on ground (2) Progress of power-up tests (a) Duration: 2 s. (b) Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - if ADF selected on FCU - ND ADF 1 or 2 in red - if ADF RMI option available - ADF RMI display ADF flag during 2 s. (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). (a) Tests pass: - if ADF selected on FCU - ND ADF 1 or 2 in green - if ADF RMI option available - ADF RMI display ADF flag no longer displayed (b) Tests failed: - if ADF selected on FCU - ND ADF 1 or 2 red indications flash - if ADF RMI option available - ADF RMI display

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-53-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 60 Feb 01/10

ADF flag **ON A/C 251-299, C. Power-up Tests Initialization and Cockpit Repercussions (1) Conditions of power-up tests initialization - How long the computer must be de-energized: 2 s. - A/C configuration: - whatever the A/C configuration on ground (2) Progress of power-up tests (a) Duration: 2 s. (b) Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - if ADF selected on FCU - ND ADF 1 in red - if ADF RMI option available - ADF RMI display ADF flag during 2 s. (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). (a) Tests pass: - if ADF selected on FCU - ND ADF 1 in green - if ADF RMI option available - ADF RMI display ADF flag no longer displayed (b) Tests failed: - if ADF selected on FCU - ND ADF 1 red indications flash - if ADF RMI option available - ADF RMI display ADF flag

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-53-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 61 Feb 01/10

ADF - ADJUSTMENT/TEST _____________________ TASK 34-53-00-740-003 BITE Test of the ADF WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-004 34-10-00-860-005 R R

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure IR Alignment Procedure ADIRS Stop Procedure

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-53-00-991-002

Fig. 501

  EFF : ALL  34-53-00    CES

 

Page 501 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, Subtask 34-53-00-860-053 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (4) On the EFIS control sections of the FCU: - set the ADF/VOR selector switches to ADF - set the mode selector switches to ROSE/NAV. (5) On the center pedestal, on the MCDU: - get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010) - push the NEXT PAGE function key. (6) On the center pedestal, on the RMP1 (RMP2): - set the ON/OFF switch to ON - push the NAV pushbutton switch (the green LED on this pushbutton switch comes on) - tune ADF1 and ADF2 to a non local station (frequency more than 750 KHz). (Ref. Fig. 501/TASK 34-53-00-991-002)

  EFF : ALL  34-53-00    CES

 

Page 502 Feb 01/10

ADF-Frequency Selection Figure 501/TASK 34-53-00-991-002   EFF : ALL  34-53-00    CES

 

Page 503 Feb 01/98

R

**ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-53-00-860-053-A A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (4) On the EFIS control sections of the FCU: - set the ADF/VOR selector switches to ADF. - set the mode selector switches to ROSE/NAV. (5) On the center pedestal, on the MCDU: - get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010) - push the NEXT PAGE function key. (6) On the center pedestal, on the RMP1 (RMP2): - set the ON/OFF switch to ON - push the NAV pushbutton switch (the green LED on this pushbutton switch comes on) - tune ADF1 and ADF2 to a non local station (frequency more than 750 KHz). (Ref. Fig. 501/TASK 34-53-00-991-002) (7) On the VOR/ADF/DME RMI: - set the VOR/ADF selector switches to ADF.

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-53-00    CES

 

Page 504 Nov 01/08

R

**ON A/C 251-299,

R

Subtask 34-53-00-860-053-B

R

A. Aircraft Maintenance Configuration

R R

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002).

R

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

R R

(3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

R R R

(4) On the EFIS control sections of the FCU: - set the ADF/VOR selector switches to ADF - set the mode selector switches to ROSE/NAV.

R R R R

(5) On the center pedestal, on the MCDU: - get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010) - push the NEXT PAGE function key.

R R R R R R

(6) On the center pedestal, on the RMP1 (RMP2): - set the ON/OFF switch to ON - push the NAV pushbutton switch (the green LED on this pushbutton switch comes on) - tune ADF1 to a non local station (frequency more than 750KHz). (Ref. Fig. 501/TASK 34-53-00-991-002)

  R EFF : 251-299,  34-53-00    CES

 

Page 505 May 01/09

**ON A/C ALL Subtask 34-53-00-865-055 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 49VU NAV/VOR/DME/RMI

12FN

F13

**ON A/C ALL 49VU NAV/ADF/1 R R

1RP1

H14

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/ADF/2

1RP2

K02

**ON A/C ALL 4. Procedure _________ R R

**ON A/C 001-049, 051-051, 053-099, 101-105, 151-199, 501-509, 511-526, 528-599, Subtask 34-53-00-740-050 A. BITE Test of the ADF NOTE : During the BITE TEST (ADF1 or 2) by the MCDU, the indications ____ related to the two receivers (Capt and F/O) are shown at the same time.This has no effect on the test or component.

  EFF : ALL  34-53-00    CES

 

Page 506 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the ADF1 (ADF2) indication.

- the ADF1 (ADF2) page comes into view.

- push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (page 1 to 3). NOTE : Ignore all the checks to be done ____ on the DDRMI.

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 13S indication comes into view. From 0 to 6s: - On the CAPT and F/O NDs: * the ADF1 (ADF2) pointer dissapears. * the RED ADF1 (ADF2) warning message comes into view. From 6 to 13s: - On the CAPT and F/O NDs: * the ADF1 (ADF2) pointer comes into view, moves to a relative bearing of 135⁰.

On the MCDU:

On the MCDU:

- push the line key adjacent to the YES indication.

the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication.

The test procedure stops.

  R EFF : 001-049, 051-051, 053-099, 101-105,  34-53-00 151-199, 501-509, 511-526, 528-599,   CES

 

Page 507 Feb 01/10

**ON A/C 052-052, Subtask 34-53-00-740-050-C A. BITE Test of the ADF ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU: - push the line key adjacent to the ADF1 (ADF2) indication.

The ADF1 (ADF2) page comes into view.

- push the line key adjacent to the TEST indication.

A fault indication comes into view for 3 seconds: - on the CAPT and F/O NDs: . the ADF red indication comes into view. . the ADF pointer is not in view. An NCD indication comes into view for 3 seconds: - on the CAPT and F/O NDs: . the ADF red indication goes out of view. An ADF heading indication comes into view for 7 seconds: - on the CAPT and F/O NDs: . the ADF1 (ADF2) pointer comes into view and moves to a relative bearing of 135 deg. At the end of the test: - on the CAPT and F/O NDs: . the ADF1 (ADF2) pointer goes out of view. - on the MCDU: . the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication.

- the MCDU MENU page comes into view.

  R EFF : 052-052,  34-53-00    CES

 

Page 508 May 01/09

**ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-53-00-740-050-B A. BITE Test of the ADF NOTE : During the BITE TEST (ADF1 or 2) by the MCDU ,the indications ____ related to the two receivers (Capt and F/O) are shown at the same time.This has no effect on the test or component operation. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the ADF1 (ADF2) indication.

- the ADF1 (ADF2) page comes into view.

- push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (page 1 to 3).

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 13S indication comes into view. From 0 to 6s: - On the CAPT and F/O NDs: * the ADF1 (ADF2) pointer disappears. * the RED ADF1 (ADF2) warning message comes into view. - On the VOR/ADF/DME RMI: * the ADF1 (ADF2) pointer stays at the last valid position on DDRMI NOTE : Disregard MCDU display test ____ result. * the ADF1 (ADF2) warning flag comes into view during 3s. From 6 to 13s: - On the CAPT and F/O NDs: * the ADF1 (ADF2) pointer comes into view, moves to a relative bearing of 135⁰. - On the VOR/ADF/DME RMI:

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-53-00    CES

 

Page 509 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------* the ADF1 (ADF2) pointer moves to a relative bearing of 135⁰. On the MCDU:

On the MCDU:

- push the line key adjacent to the YES indication.

the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication.

The test procedure stops.

R

**ON A/C 251-299,

R

Subtask 34-53-00-740-050-D

R

A. BITE Test of the ADF

R R R

------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------

R

1. On the MCDU:

On the MCDU:

R R

- push the line key adjacent to the ADF1 indication.

- the ADF1 page comes into view.

R R

- push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (page 1 to 3).

R R

NOTE : Ignore all the checks to be done ____ on the DDRMI.

R R

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 13S indication comes into view.

R R R R R

From 0 to 6s: - On the CAPT and F/O NDs: * the ADF1 pointer dissapears. * the RED ADF1 warning message comes into view.

R R

From 6 to 13s: - On the CAPT and F/O NDs:

  R EFF : 106-149, 201-249, 251-299, 301-399,  34-53-00 401-499,   CES

 

Page 510 May 01/09

R R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------* the ADF1 pointer comes into view, moves to a relative bearing of 135⁰.

R

On the MCDU:

On the MCDU:

R R

- push the line key adjacent to the YES indication.

the TEST OK indication comes into view.

R R

- push the line key adjacent to the RETURN indication.

The test procedure stops.

**ON A/C ALL 5. Close-up ________ Subtask 34-53-00-860-054 A. Put the aircraft back to its initial configuration. (1) On the EFIS control sections of the FCU, set the ADF/VOR selector switches to OFF. (2) Do the ADIRS STOP procedure (Ref. TASK 34-10-00-860-005) (3) On the center pedestal, on the RMP: - push the NAV pushbutton switch (the green LED on this pushbutton switch goes off). - set the ON/OFF switch to OFF. (4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (5) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-53-00    CES

 

Page 511 May 01/09

TASK 34-53-00-710-002 Operational Test of the ADF WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Test of ADF Identification and Reception 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-10-00-860-002 34-10-00-860-004 34-10-00-860-005 R R

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power ADIRS Start Procedure IR Alignment Procedure ADIRS Stop Procedure

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-53-00-991-002

Fig. 501

  EFF : ALL  34-53-00    CES

 

Page 512 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up R R

**ON A/C 001-049, 051-099, 101-105, 151-199, 251-299, 501-509, 511-526, 528-599, Subtask 34-53-00-860-051 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (4) On the EFIS control sections of the FCU: - set the ADF/VOR selector switches to ADF - set the mode selector switches to ROSE/NAV. (5) On the center pedestal, on the RMP1 (RMP2): - set the ON/OFF switch to ON. - push the NAV pushbutton switch (the green LED on this pushbutton switch comes on). **ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-53-00-860-051-A A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (4) On the EFIS control sections of the FCU: - set the ADF/VOR selector switches to ADF - set the mode selector switches to ROSE/NAV.

  EFF : ALL  34-53-00    CES

 

Page 513 Feb 01/10

(5) On the center pedestal, on the RMP1 (RMP2): - set the ON/OFF switch to ON - push the NAV pushbutton switch (the green LED on this pushbutton switch comes on). (6) On the VOR/ADF/DME RMI: - set the VOR/ADF selector switches to ADF. **ON A/C ALL Subtask 34-53-00-865-054 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/ADF/1 1RP1 H14 R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/ADF/2

1RP2

  EFF : ALL  34-53-00    CES

 

K02

Page 514 Feb 01/10

**ON A/C ALL 4. Procedure _________ R

**ON A/C 001-049, 051-099, 101-105, 151-199, 501-509, 511-526, 528-599, Subtask 34-53-00-710-056 A. Operational Test of the ADF ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center pedestal, on one ACP: - push the ADF1 (ADF2) pushbutton switch. 2. On the RMP1 (RMP2): - set the ON/OFF selector switch to ON - set an ADF local frequency . (Ref. Fig. 501/TASK 34-53-00991-002)

On the CAPT and F/O NDs: - the ADF1 (ADF2) pointer moves and shows the station direction. - the station identification or frequency comes into view in the left lower corner. In the loudspeakers: - if the station set is a A1 station, you cannot hear the identification signal. Do step 3 - if the station set is a A2 station, you can hear the identification signal. Go to step 4

3. On the RMP1 (RMP2):

  EFF : ALL  34-53-00    CES

 

Page 515 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set the BF0 function. In the loudspeakers, you can hear the (Ref. Fig. 501/TASK 34-53-00991-002) identification signal but it is weaker. 4. On the RMP1 (RMP2): - set a non local ADF station. (Ref. Fig. 501/TASK 34-53-00991-002)

On the CAPT and F/O NDs, the ADF1 (ADF2) pointer goes out of view. In the loudspeakers, no signal is heard.

**ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-53-00-710-056-A A. Operational Test of the ADF ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the center pedestal, on one ACP: - push the ADF1 (ADF2) pushbutton switch. 2. On the RMP1 (RMP2): - set the ON/OFF selector switch to ON. - set an ADF local frequency . (Ref. Fig. 501/TASK 34-53-00991-002)

On the CAPT and F/O ND : - the ADF1 (ADF2) pointer moves and shows the station direction. - the station identification or frequency comes into view in the left lower corner.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-53-00 201-249, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 516 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------In the loudspeakers: - if the station set is a A1 station, you cannot hear the identification signal. Do step 3 - if the station set is a A2 station, you can hear the identification signal. Go to step 4 On the VOR/ADF/DME RMI : - the ADF1 (ADF2) warning flag goes out of view. - the ADF1 (ADF2) pointer indicates the direction of the station set. 3. On the RMP1 (RMP2): - set the BF0 function. (Ref. Fig. 501/TASK 34-53-00991-002)

In the loudspeakers, you can hear the identification signal but it is weaker.

4. On the RMP1 (RMP2): - set a non local ADF station. (Ref. Fig. 501/TASK 34-53-00991-002)

On the CAPT and F/O ND, the ADF1 (ADF2) pointer goes out of view. In the loudspeakers, no signal is heard. On the VOR/ADF/DME RMI, the ADF1 (ADF2) pointer stays at the position related to the last correct data and the warning flag comes into view.

  EFF : 106-149, 201-249, 301-399, 401-499,  34-53-00    CES

 

Page 517 May 01/09

R

**ON A/C 251-299,

R

Subtask 34-53-00-710-056-B

R

A. Operational Test of the ADF

R R R

------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------

R R R R R

1. On the center pedestal, on one ACP: - push the ADF1 pushbutton switch.

R

2. On the RMP:

R R

- set an ADF local frequency . (Ref. Fig. 501/TASK 34-53-00991-002)

On the CAPT and F/O NDs:

R R R R R R

- the ADF1 pointer moves and shows the station direction. - the station identification or frequency comes into view in the left lower corner.

R R R R R R R R

In the loudspeakers: - if the station set is a A1 station, you cannot hear the identification signal. Do step 3 - if the station set is a A2 station, you can hear the identification signal. Go to step 4.

R

3. On the RMP1 (RMP2):

R R

- set the BF0 function. (Ref. Fig. 501/TASK 34-53-00991-002)

R R R

- in the loudspeakers, you can hear the identification signal but it is weaker.

  EFF : 251-299,  34-53-00    CES

 

Page 518 May 01/09

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------4. On the RMP1 (RMP2): - set a non local ADF station. (Ref. Fig. 501/TASK 34-53-00991-002)

On the CAPT and F/O NDs, the ADF1 pointer goes out of view. In the loudspeakers, no signal is heard.

**ON A/C ALL 5. Close-up ________ R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, Subtask 34-53-00-860-052 A. Put the aircraft back to its initial configuration. (1) On the EFIS control sections of the FCU, set the ADF/VOR selector switches to OFF. (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) On the center pedestal, on the RMP: - push the NAV pushbutton switch (the green LED on this pushbutton switch goes off) - set the ON/OFF switch to OFF. (4) On the center pedestal, on the ACP, release the ADF1 (ADF2) pushbutton switch. (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002). (6) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-53-00    CES

 

Page 519 Feb 01/10

R

**ON A/C 251-299,

R

Subtask 34-53-00-860-052-A

R

A. Put the aircraft back to its initial configuration.

R R

(1) On the EFIS control sections of the FCU, set the ADF/VOR selector switches to OFF.

R

(2) DO the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

R R R R

(3) On the center pedestal, on the RMP: - push the NAV pushbutton switch (the green LED on this pushbutton switch goes off) - set the ON/OFF switch to OFF.

R R

(4) On the center pedestal, on the ACP, release the ADF1 pushbutton switch.

R R

(5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

R R

(6) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : 251-299,  34-53-00    CES

 

Page 520 May 01/09

ANTENNA - ADF LOOP AND SENSE (3RP1,3RP2) - REMOVAL/INSTALLATION _______________________________________________________________ TASK 34-53-11-000-001 Removal of the ADF Loop and Sense Antenna 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No No

specific specific specific specific specific

blanking caps circuit breaker(s) safety clip(s) masking tape nonmetallic scraper access platform 6.0 m (19 ft. 8 in.)

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 11-010

USA TT-I-735 GRADE A ISOPROPYL ALCOHOL (Ref. 20-31-00)

C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-42-00-861-001 R R

Energize the Ground Service Network from the External Power

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 501-509, 511-526, 528-599, 34-53-11-991-001

Fig. 401

  EFF : ALL  34-53-11    CES

 

Page 401 Feb 01/10

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 151-199, 401-499, 34-53-11-991-001-A

Fig. 401A

**ON A/C 301-399, 34-53-11-991-001-B

Fig. 401B

**ON A/C ALL 3. __________ Job Set-up Subtask 34-53-11-861-050 A. Energize the ground service network (Ref. TASK 24-42-00-861-001). Subtask 34-53-11-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/ADF/1 1RP1 H14 R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/ADF/2

1RP2

K02

**ON A/C ALL 4. Procedure _________ R R

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 501-509, 511-526, 528-599, (Ref. Fig. 401/TASK 34-53-11-991-001)

  EFF : ALL  34-53-11    CES

 

Page 402 Feb 01/10

ADF Loop and Sense Antennas. Figure 401/TASK 34-53-11-991-001   R EFF : 001-049, 051-099, 101-149, 201-249,  34-53-11 251-299, 501-509, 511-526, 528-599,   CES

 

Page 403 Feb 01/10

**ON A/C 151-199, 401-499, (Ref. Fig. 401A/TASK 34-53-11-991-001-A) **ON A/C 301-399, (Ref. Fig. 401B/TASK 34-53-11-991-001-B) **ON A/C ALL Subtask 34-53-11-010-050 A. Get Access (1) Put the access platform in position. (2) Safety Precautions WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL _______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. Subtask 34-53-11-020-051 B. Removal of the ADF Loop and Sense Antenna (1) Remove the bolts (1) from the antenna (2). (2) Lift the antenna (2) until you can see the coaxial cable connector (5). (3) Disconnect the coaxial cable connector (5) from the antenna connector. NOTE : The coaxial cable (6) must not go into the fuselage. ____ (4) Remove and discard the O-ring (3).

  R EFF : ALL  34-53-11    CES

 

Page 404 Aug 01/09

ADF Loop and Sense Antennas. Figure 401A/TASK 34-53-11-991-001-A   R EFF : 151-199, 401-499,  34-53-11    CES

 

Page 405 May 01/09

R R

ADF Loop and Sense Antennas. Figure 401B/TASK 34-53-11-991-001-B

  R EFF : 301-399,  34-53-11    CES

 

Page 406 May 01/04

(5) Remove the antenna (2) and the gasket (4). R

(6) Put blanking caps on the disconnected electrical connector(s). (7) Put masking tape around the coaxial cable (6) and attach it to the fuselage. (8) Remove the sealant with a nonmetallic scraper and clean the fuselage structure with the CLEANING AGENTS (Material No. 11-010).

  EFF : ALL  34-53-11    CES

 

Page 407 Feb 01/10

TASK 34-53-11-400-001 Installation of the ADF Loop and Sense Antenna WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN. _______ IF YOU DO: - RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH - WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

lint free cloth access platform 6.0 m (19 ft. 8 in.) Torque Wrench : range 0.00 to 1.20 m.daN (0.00 to 9.00 lbf.ft)

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 07-001 Material No. 09-008 R Material No. 09-016 Material No. 11-004

NO LONGER AVAILABLE RPLD BY 07001B/D/F (Ref. 20-31-00) USA MIL-S-8802 CLASS A NO LONGER AVAILABLE (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) USA MIL-T-81533 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM) (Ref. 20-31-00)

  EFF : ALL  34-53-11    CES

 

Page 408 Aug 01/08

------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 16-021

F ASNB70720 FLEXIBLE POLYURETHANE (Ref. 20-31-00)

C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-912-005 24-42-00-861-001 24-42-00-862-001

Electrical Bonding of Antennas With Conductive Bolts. Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Operational Test of the ADF Repair of the Sealing

34-53-00-710-002 51-76-11-300-001 R R

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 501-509, 511-526, 528-599, 34-53-11-991-001

Fig. 401

**ON A/C 151-199, 401-499, 34-53-11-991-001-A

Fig. 401A

**ON A/C 301-399, 34-53-11-991-001-B

Fig. 401B

  EFF : ALL  34-53-11    CES

 

Page 409 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-53-11-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001). (2) Make sure that the access platform is in position. (3) Make sure that the aircraft is in the same configuration as for the removal task. (4) Make sure that the parts retained from the removed component are clean and in the correct condition. **ON A/C 301-399, Subtask 34-53-11-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/ADF/1 1RP1 H14 121VU COM NAV/ADF/2 1RP2 K02 **ON A/C ALL 4. Procedure _________ R R

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 501-509, 511-526, 528-599, (Ref. Fig. 401/TASK 34-53-11-991-001)

  EFF : ALL  34-53-11    CES

 

Page 410 Feb 01/10

**ON A/C 151-199, 401-499, (Ref. Fig. 401A/TASK 34-53-11-991-001-A) **ON A/C 301-399, (Ref. Fig. 401B/TASK 34-53-11-991-001-B) **ON A/C ALL Subtask 34-53-11-420-051 A. Installation of the ADF Loop and Sense Antenna WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL _______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE THE SPECIAL _______ MATERIAL. THIS MATERIAL IS DANGEROUS. (1) Clean the component interface and/or the adjacent area with CLEANING AGENTS (Material No. 11-004) and lint free cloth. (2) Do an inspection of the component interface and/or the adjacent area. R

(3) Remove the blanking caps from the electrical connector(s). (4) Make sure that the electrical connectors are clean and in the correct condition. (5) Put the new o-ring (3) in the correct position on the antenna. (6) Put the new gasket (4) on the fuselage and align the bolts hole. (7) Remove the masking tape from the coaxial cable (6) and connect the cable connector (5) to the antenna connector.

  EFF : ALL  34-53-11    CES

 

Page 411 Feb 01/10

(8) Install the antenna (2) to the fuselage structure with the bolts (1).Torque the bolts (1) in a diagonally opposite sequence to 0.375 m.daN (33.18 lbf.in). NOTE : The antenna mounting bolts (1) and the holes (8) provide the ____ electrical bonding. (9) Make sure that the bonding contact resistance between the antenna (2) and the fuselage structure is not higher than 5 milliohms (Ref. TASK 20-28-00-912-005). (10) Apply a bead of SEALANTS (Material No. 09-016) (7) or use as an alternative SEALANTS (Material No. 09-008) around the antenna (2) (Ref. TASK 51-76-11-300-001) and the fuselage. R R

(11) Fill the recess of the bolts (1) with SEALANTS (Material No. 09-016) or as an alternative SEALANTS (Material No. 09-008). (12) Make the contour of the sealant on the bolts (1) and around the antenna (2) smooth. (13) Let the sealant cure. (14) Apply STRUCTURE PAINTS (Material No. 16-021) to the sealant around the base of the antenna (2). (15) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001) to the sealant on the head of the bolts (1). NOTE : It is not mandatory to paint the sealant around the base of ____ the antenna and on the head of the screws. Subtask 34-53-11-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1RP1, 1RP2 Subtask 34-53-11-710-050 C. Do the operational test of the ADF system (Ref. TASK 34-53-00-710-002).

  EFF : ALL  34-53-11    CES

 

Page 412 May 01/09

5. Close-up ________ Subtask 34-53-11-410-052 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the access platform(s). Subtask 34-53-11-862-050 B. De-energize the ground service network (Ref. TASK 24-42-00-862-001).

  EFF : ALL  34-53-11    CES

 

Page 413 May 01/04

RECEIVER - ADF (2RP1,2RP2) - REMOVAL/INSTALLATION _________________________________________________ TASK 34-53-31-000-002 Removal of the ADF Receiver (2RP1, 2RP2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, 34-53-31-991-001

Fig. 401

**ON A/C 251-299, 34-53-31-991-001-A

Fig. 401A

  EFF : ALL  34-53-31    CES

 

Page 401 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-53-31-865-052 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/ADF/1 1RP1 H14 R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/ADF/2

1RP2

K02

**ON A/C ALL Subtask 34-53-31-010-050 B. Get Access (1) Put the access platform in position at the access door 824 in zone 128. (2) Open the access door 824. 4. Procedure _________ R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401/TASK 34-53-31-991-001) **ON A/C 251-299, (Ref. Fig. 401A/TASK 34-53-31-991-001-A)

  EFF : ALL  34-53-31    CES

 

Page 402 Feb 01/10

ADF Receivers Figure 401/TASK 34-53-31-991-001   R EFF : 001-049, 051-099, 101-149, 151-199,  34-53-31 201-249, 301-399, 401-499, 501-509, 511-526,  528-599, CES

 

Page 403 Feb 01/10

R R

ADF Receiver Figure 401A/TASK 34-53-31-991-001-A

  R EFF : 251-299,  34-53-31    CES

 

Page 404 May 01/09

R

**ON A/C ALL Subtask 34-53-31-020-050 A. Removal of the ADF Receiver (1) Loosen the nut (4). (2) Lower the nut (4). (3) Pull the ADF receiver (1) on its rack (3) to disconnect the electrical connectors (2). (4) Remove the ADF receiver (1) from its rack (3). (5) Put blanking caps on the disconnected electrical connectors (2).

  EFF : ALL  34-53-31    CES

 

Page 405 May 01/09

TASK 34-53-31-400-002 Installation of the ADF Receiver (2RP1, 2RP2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-53-00-740-003 52-41-00-410-002 R R

BITE Test of the ADF Close the Avionics Compartment Doors after Access

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, 34-53-31-991-001

Fig. 401

**ON A/C 251-299, 34-53-31-991-001-A

Fig. 401A

  EFF : ALL  34-53-31    CES

 

Page 406 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-53-31-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at the access door 824 in zone 128. (2) Make sure that the access door 824 is open. Subtask 34-53-31-865-053 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/ADF/1 1RP1 H14 R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, 121VU COM NAV/ADF/2

1RP2

K02

**ON A/C ALL 4. Procedure _________ R R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 401/TASK 34-53-31-991-001) **ON A/C 251-299, (Ref. Fig. 401A/TASK 34-53-31-991-001-A)

  EFF : ALL  34-53-31    CES

 

Page 407 Feb 01/10

R

**ON A/C ALL Subtask 34-53-31-420-050 A. Installation of the ADF Receiver (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (2). (4) Make sure that the electrical connectors (2) are clean and in the correct condition. (5) Install the ADF Receiver (1) on its rack (3). (6) Push the ADF Receiver (1) on its rack (3) to connect the electrical connectors (2). (7) Engage the nut (4) and the lug (5) and tighten. Subtask 34-53-31-865-054 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1RP1, 1RP2 Subtask 34-53-31-740-050 C. Do the BITE test of the ADF (Ref. TASK 34-53-00-740-003). 5. Close-up ________ Subtask 34-53-31-410-050 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the access door 824 (Ref. TASK 52-41-00-410-002). (3) Remove the access platform(s).

  EFF : ALL  34-53-31    CES

 

Page 408 May 01/09

VOR/MARKER - DESCRIPTION AND OPERATION ______________________________________ 1. General _______ R

**ON A/C 001-004, 051-060, A. Foreword The VOR/MARKER comprises two independent systems in a same receiver : - a VOR system for the radio navigation phase - a MARKER (MKR) system for the landing approach phase. The two VOR/MKR receivers are interchangeable but only one marker system is installed on the aircraft. B. VOR System The VOR system is a radio aid to medium-range navigation. The aircraft is equipped with two VOR systems which can accept ground station signals in the frequency range of 108 MHz to 117.95 MHz. These signals are processed and conditioned to provide the crew with : - identification of a selected ground station - indication of the aircraft position with respect to the station (bearing information) - indication of the aircraft angular deviation from a selected course. C. MARKER System The marker system is a radio navigation aid. It is normally used together with the Instrument Landing System (ILS) during an ILS approach. The system determines the distance between the aircraft and the runway threshold. The marker system also marks particular airway and holding points. The system provides visual and aural indications of the passage of the aircraft over the marker transmitters located on the ground. **ON A/C ALL

R

Post SB

34-1147 For A/C 001-004,051-060,

A. Foreword The VOR/MARKER comprises two independent systems in a same receiver: - a VOR system for the radio navigation phase, - a MARKER (MKR) system for the landing approach phase. The two VOR/MKR receivers are interchangeable but only one marker system is installed on the aircraft.

  EFF : ALL  34-55-00    CES

 

Page 1 May 01/05

B. VOR System The VOR system is a radio aid to medium-range navigation. The aircraft is equipped with two VOR systems which can accept ground station signals in the frequency range of 108 MHz to 117.95 MHz. These signals are processed and conditioned to provide the crew with: - identification of a selected ground station, - indication of the aircraft position with respect to the station (bearing information), - indication of the aircraft angular deviation from a selected course. C. MARKER System The marker system is a radio navigation aid. It is normally used together with the Instrument Landing System (ILS) portion of the Multi-Mode Receiver (MMR) during an ILS approach. The system determines the distance between the aircraft and the runway threshold. The marker system also marks particular airway and holding points. The system provides visual and aural indications of the passage of the aircraft over the marker transmitters located on the ground. **ON A/C ALL 2. __________________ Component Location R R

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 501-509, 511-526, 528-599, (Ref. Fig. 001) **ON A/C 151-199, 401-499, (Ref. Fig. 001A) **ON A/C 301-399, (Ref. Fig. 001B)

  EFF : ALL  34-55-00    CES

 

Page 2 Feb 01/10

VOR/Marker - Component Location Figure 001   R EFF : 001-049, 051-099, 101-149, 201-249,  34-55-00 251-299, 501-509, 511-526, 528-599,   CES

 

Page 3 Feb 01/10

VOR/Marker - Component Location Figure 001A   R EFF : 151-199, 401-499,  34-55-00    CES

 

Page 4 Aug 01/05

R R

VOR/Marker - Component Location Figure 001B

  R EFF : 301-399,  34-55-00    CES

 

Page 5 May 01/04

**ON A/C ALL ------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. ------------------------------------------------------------------------------1RS ANTENNA-MARKER 133 34-55-18 3RS1 RECEIVER-VOR/MKR, 1 81VU 127 824 34-55-31 3RS2 RECEIVER-VOR/MKR, 2 82VU 128 824 34-55-31 4RS ANTENNA-VOR 1/2 324 324AT 34-55-11 3. __________________ System Description R

**ON A/C 001-049, 051-099, 101-105, 151-199, A. Principle (1) VOR system The principle of the VOR navigation is a comparison between a reference phase signal and a variable phase signal. The ground station generates these two signals. The phase difference between the reference and the variable phase is a function of the position of the aircraft with respect to the ground station. Furthermore, the ground station provides a Morse identification. (2) Marker system There are three marker transmitters positioned on the ground at known distances from the runway threshold : - the outer marker at approx. 4 N miles - the middle marker at 0.6 N miles - the inner marker at the runway threshold. The markers transmit a modulated 75 MHz signal to provide a marker position. When the aircraft passes through the beam of a marker, the modulating frequency is detected. Then, the system provides aural and visual indications to the flight crew. B. System Architecture (Ref. Fig. 002) (1) VOR system The VOR system comprises two independent systems. Each system consists of : - one VOR/MKR receiver 1(2) 3RS1 (3RS2) - one VOR 1/2 antenna 4RS

  EFF : ALL  34-55-00    CES

 

Page 6 May 01/05

VOR/Marker - Block Diagram Figure 002   R EFF : 001-049, 051-099, 101-105, 151-199,  34-55-00    CES

 

Page 7 May 01/05

- one VOR/DME Radio Magnetic Indicator (VOR/DME RMI) 11FN. The components given after control the VOR system: (Ref. Fig. 003) - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio Management Unit (AMU) 1RN for audio control - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2) and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection - the MCDU 1(2) and the Centralized Fault-Display Interface-Unit (CFDIU) 1TW for test purposes. (2) Marker system The marker system consists of one system only. The receiver is part of the VOR/MKR receiver 1. The system comprises : - one VOR/MKR receiver 1 3RS1 - one marker antenna 1RS. All the data are shown on the CAPT and F/O Primary Flight Displays (PFD). C. Utilization Technical Data (1) Data display (Ref. Fig. 004) (a) VOR system 1 _

On the Navigation Display (ND) In ROSE and ARC modes. If you set the ADF/VOR/OFF switch on the EFIS control section of the Flight Control Unit (FCU) to VOR, this causes : display of the characteristics of the VOR 1 and/or VOR 2 stations in the L and/or R lower corner of the ND (item 7) : - type of station (VOR 1, VOR 2) - shape of the associated bearing display - station identification - mode of tuning : nothing : automatically tuned by the FMGC M : manually tuned through the MCDU R : tuned through the RMP. A single pointer on the heading dial shows the bearing of the VOR 1 (item 5), a double pointer that of the VOR 2 (item 1). All these data are shown in white. In case of VOR system fault, all the corresponding data go out of view and the VOR indication turns to red.

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-55-00    CES

 

Page 8 May 01/05

VOR/Marker - Block Diagram Figure 002A   R EFF : 106-149, 201-249, 301-399, 401-499,  34-55-00    CES

 

Page 9 Nov 01/08

VOR/Marker - Block Diagram Figure 002B   R EFF : 251-299, 501-509, 511-526, 528-599,  34-55-00    CES

 

Page 10 Feb 01/10

VOR/Marker - Control and Indicating Figure 003  R EFF : 001-049, 051-099, 101-105, 151-199,  34-55-00     CES

 

Page 11/12 May 01/05

VOR/Marker - Control and Indicating Figure 003A  R EFF : 106-149, 201-249, 301-399, 401-499,  34-55-00     CES

 

Page 13/14 Nov 01/08

VOR/Marker - Control and Indicating Figure 003B   R EFF : 251-299, 501-509, 511-526, 528-599,  34-55-00    CES

 

Page 15 Feb 01/10

VOR/Marker - Data and Warning Displays Figure 004   EFF : 001-049, 051-099, 101-105, 151-199,  34-55-00   R  CES

 

Page 16 Nov 01/07

In ROSE VOR mode, the data below are shown : - a dagger-shaped pointer points to the selected VOR course (cyan) (item 6) - the lateral deviation bar which represents the VOR deviation is shown with an arrow for the TO FROM indication (cyan) (item 2) - in the R top corner, the VOR characteristics come into view: VOR 1 or 2, frequency, selected course (item 4), identification (cyan). In case of VOR system fault ,all these data go out of view and the VOR 1 or 2 indication turns to red. If the VOR approach is selected, the VOR APP message comes into view in the center top section of the ND (item 3). In ROSE NAV and ARC modes, the characteristics and location of the VOR stations which are not already included in the flight plan, can be shown when you push the VOR-D pushbutton switch on the EFIS control section of the FCU : - cross symbol for the VOR station (item 8) - circle plus cross symbol for the VOR/DME station (item 9). 2 _

On the VOR/DME RMI The RMI indicates the VOR bearings : - a single pointer indicates the VOR 1 bearing (item 11) - a double pointer indicates the VOR 2 bearing. A warning flag comes into view to indicate system malfunction (item 12). In this case, the corresponding pointer is in the 3 oclock position (item 13). In case of No Computed Data (NCD), no warning flag appears but the corresponding pointer remains in the 3 oclock position.

(b) Marker system The MKR data are shown on the PFD, in approach at the intersection of the G/S and LOC scales (item 14). When the aircraft overflies the corresponding marker, the data given after come into view on the PFD : - OM for the outer marker (blue) - MM for the middle marker (amber) - AWY for the inner marker (white). (2) Audio control (a) VOR system 1 _

The VOR/MKR receivers apply their VOR audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-55-00    CES

 

Page 17 Nov 01/07

pilot must push the VOR 1 (2) pushbutton switch and adjust the related potentiometer to the correct audio level. 2 _

In case of ATIS message transmission by the VOR station : - it is necessary to push the ON VOICE pushbutton switch on one ACP in order to hear clearly this information without Morse signal.

(b) Marker system The VOR/MKR receiver 1 applies its marker audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the MKR pushbutton switch and adjust the related potentiometer to the correct audio level. D. Warning (Ref. Fig. 004) The warning related to the VOR is the local warning shown on the VOR/DME RMI. In case of VOR fault, a corresponding VOR flag comes into view on the VOR/DME RMI. R

**ON A/C 106-149, 201-249, 301-399, 401-499, A. Principle (1) VOR system The principle of the VOR navigation is a comparison between a reference phase signal and a variable phase signal. The ground station generates these two signals. The phase difference between the reference and the variable phase is a function of the position of the aircraft with respect to the ground station. Furthermore, the ground station provides a Morse identification. (2) Marker system There are three marker transmitters positioned on the ground at known distances from the runway threshold : - the outer marker at approx. 4 N miles - the middle marker at 0.6 N miles - the inner marker at the runway threshold. The markers transmit a modulated 75 MHz signal to provide a marker position. When the aircraft passes through the beam of a marker, the modulating frequency is detected. Then, the system provides aural and visual indications to the flight crew.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-55-00 201-249, 301-399, 401-499,   CES

 

Page 18 Nov 01/08

B. System Architecture (Ref. Fig. 002A) (1) VOR system The VOR comprises two independent systems. Each system consists of : - one VOR/MKR receiver 1(2) 3RS1 (3RS2) - one VOR 1/2 antenna 4RS - one VOR/ADF/DME Radio Magnetic Indicator (VOR/ADF/DME RMI) 21FN. The components given after control the VOR system : (Ref. Fig. 003A) - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio Management Unit (AMU) 1RN for audio control - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2) and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection - the MCDU 1(2) and the Centralized Fault-Display Interface-Unit (CFDIU) 1TW for test purposes. (2) Marker system The marker system consists of one system only. The receiver is part of the VOR/MKR receiver 1. The system comprises : - one VOR/MKR receiver 1 3RS1 - one marker antenna 1RS. All the data are shown on the CAPT and F/O Primary Flight Displays (PFD). C. Utilization Technical Data (1) Data display (Ref. Fig. 004A) (a) VOR system 1 _

On the Navigation Display (ND) In ROSE and ARC modes. If you set the ADF/VOR/OFF switch on the EFIS control section of the Flight Control Unit (FCU) to VOR, this causes : display of the characteristics of the VOR 1 and/or VOR 2 stations in the L and/or R lower corner of the ND (item 7) : - type of station (VOR 1, VOR 2) - shape of the associated bearing display - station identification - mode of tuning: nothing : automatically tuned by the FMGC M : manually tuned through the MCDU

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-55-00    CES

 

Page 19 Nov 01/08

VOR/Marker - Data and Warning Displays Figure 004A   R EFF : 106-149, 201-249, 301-399, 401-499,  34-55-00    CES

 

Page 20 Nov 01/08

R : tuned through the RMP. A single pointer on the heading dial shows the bearing of the VOR 1 (item 5), a double pointer that of the VOR 2 (item 1). All these data are shown in white. in case of VOR system fault, all the corresponding data go out of view and the VOR indication turns to red. In ROSE VOR mode, the data below are shown: - a dagger-shaped pointer points to the selected VOR course (cyan) (item 6) - the lateral deviation bar which represents the VOR deviation is shown with an arrow for the TO FROM indication (cyan) (item 2) - in the R top corner, the VOR characteristics come into view: VOR 1 or 2, frequency, selected course (item 4), identification (cyan). In case of VOR system fault, all these data go out of view and the VOR 1 or 2 indication turns to red. If the VOR approach is selected, the VOR APP message comes into view in the center top section of the ND (item 3). In ROSE NAV and ARC modes, the characteristics and location of the VOR stations which are not already included in the flight plan, can be shown when you push the VOR-D pushbutton switch on the EFIS control section of the FCU : - cross symbol for the VOR station (item 8) - circle plus cross symbol for the VOR/DME station (item 9). 2 _

On the VOR/ADF/DME RMI Set the VOR/ADF selector switches to ADF. The RMI indicates the VOR bearings : - a single pointer indicates the VOR 1 bearing (item 11) - a double pointer indicates the VOR 2 bearing. A warning flag comes into view to indicate system malfunction (item 12). In this case, the corresponding pointer is in the 3 oclock position (item 13). If No Computed Data (NCD), the warning flag comes into view and the related pointer stays at the position corresponding to the last correct data.

(b) Marker system The MKR data are shown on the PFD, in approach at the intersection of the G/S and LOC scales (item 14). When the aircraft overflies the corresponding marker, the data given after come into view on the PFD : - OM for the outer marker (blue) - MM for the middle marker (amber) - AWY for the inner marker (white).

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-55-00    CES

 

Page 21 Nov 01/08

(2) Audio control (a) VOR system 1 _

The VOR/MKR receivers apply their VOR audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the VOR 1 (2) pushbutton switch and adjust the related potentiometer to the correct audio level.

2 _

In case of ATIS message transmission by the VOR station : - it is necessary to push the ON VOICE pushbutton switch on one ACP in order to hear clearly this information without Morse signal.

(b) Marker system The VOR/MKR receiver 1 applies its marker audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the MKR pushbutton switch and adjust the related potentiometer to the correct audio level. D. Warning (Ref. Fig. 004A) The warning related to the VOR is the local warning shown on the VOR/ADF/DME RMI. In case of VOR fault, a flag comes into view on the VOR/ADF/DME RMI. R

**ON A/C 251-299, 501-509, 511-526, 528-599, A. Principle (1) VOR system The principle of the VOR navigation is a comparison between a reference phase signal and a variable phase signal. The ground station generates these two signals. The phase difference between the reference and the variable phase is a function of the position of the aircraft with respect to the ground station. Furthermore, the ground station provides a Morse identification.

  R EFF : 106-149, 201-249, 251-299, 301-399,  34-55-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 22 Feb 01/10

(2) Marker system There are three marker transmitters positioned on the ground at known distances from the runway threshold : - the outer marker at approx. 4 N miles - the middle marker at 0.6 N miles - the inner marker at the runway threshold. The markers transmit a modulated 75 MHz signal to provide a marker position. When the aircraft passes through the beam of a marker, the modulating frequency is detected. Then, the system provides aural and visual indications to the flight crew. B. System Architecture (Ref. Fig. 002B) (1) VOR system The VOR system comprises two independent systems. Each system consists of : - one VOR/MKR receiver 1(2) 3RS1 (3RS2) - one VOR 1/2 antenna 4RS The components given after control the VOR system: (Ref. Fig. 003B) - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio Management Unit (AMU) 1RN for audio control - the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2) and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection - the MCDU 1(2) and the Centralized Fault-Display Interface-Unit (CFDIU) 1TW for test purposes. (2) Marker system The marker system consists of one system only. The receiver is part of the VOR/MKR receiver 1. The system comprises : - one VOR/MKR receiver 1 3RS1 - one marker antenna 1RS. All the data are shown on the CAPT and F/O Primary Flight Displays (PFD).

  R EFF : 251-299, 501-509, 511-526, 528-599,  34-55-00    CES

 

Page 23 Feb 01/10

C. Utilization Technical Data (1) Data display (Ref. Fig. 004B) (a) VOR system 1 _

On the Navigation Display (ND) In ROSE and ARC modes. If you set the ADF/VOR/OFF switch on the EFIS control section of the Flight Control Unit (FCU) to VOR, this causes : display of the characteristics of the VOR 1 and/or VOR 2 stations in the L and/or R lower corner of the ND (item 7) : - type of station (VOR 1, VOR 2) - shape of the associated bearing display - station identification - mode of tuning : nothing : automatically tuned by the FMGC M : manually tuned through the MCDU R : tuned through the RMP. A single pointer on the heading dial shows the bearing of the VOR 1 (item 5), a double pointer that of the VOR 2 (item 1). All these data are shown in white. In case of VOR system fault, all the corresponding data go out of view and the VOR indication turns to red. In ROSE VOR mode, the data below are shown : - a dagger-shaped pointer points to the selected VOR course (cyan) (item 6) - the lateral deviation bar which represents the VOR deviation is shown with an arrow for the TO FROM indication (cyan) (item 2) - in the R top corner, the VOR characteristics come into view: VOR 1 or 2, frequency, selected course (item 4), identification (cyan). In case of VOR system fault ,all these data go out of view and the VOR 1 or 2 indication turns to red. If the VOR approach is selected, the VOR APP message comes into view in the center top section of the ND (item 3). In ROSE NAV and ARC modes, the characteristics and location of the VOR stations which are not already included in the flight plan, can be shown when you push the VOR-D pushbutton switch on the EFIS control section of the FCU : - cross symbol for the VOR station (item 8) - circle plus cross symbol for the VOR/DME station (item 9).

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Page 24 Feb 01/10

VOR/Marker - Data and Warning Displays Figure 004B   R EFF : 251-299, 501-509, 511-526, 528-599,  34-55-00    CES

 

Page 25 Feb 01/10

R R R R R R R R

(b) Marker system The MKR data are shown on the PFD, in approach at the intersection of the G/S and LOC scales (item 10). When the aircraft overflies the corresponding marker, the data given after come into view on the PFD : - OM for the outer marker (blue) - MM for the middle marker (amber) - AWY for the inner marker (white).

R

(2) Audio control

R

(a) VOR system

R R R R R R

1 _

The VOR/MKR receivers apply their VOR audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the VOR 1 (2) pushbutton switch and adjust the related potentiometer to the correct audio level.

R R R R

2 _

In case of ATIS message transmission by the VOR station : - it is necessary to push the ON VOICE pushbutton switch on one ACP in order to hear clearly this information without Morse signal.

R R R R R R R

(b) Marker system The VOR/MKR receiver 1 applies its marker audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the MKR pushbutton switch and adjust the related potentiometer to the correct audio level.

R

D. Not Applicable **ON A/C ALL 4. ____________ Power Supply

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Page 26 Nov 01/07

**ON A/C 001-049, 051-099, 101-105, 151-199, (Ref. Fig. 002) Energization of each system is through 115VAC 400Hz buses : - 115VAC ESS BUS 401XP via circuit breaker 2RS1 for system 1 - 115VAC BUS 2 204XP via circuit breaker 2RS2 for system 2. The 115VAC ESS BUS 401XP energizes the VOR/DME RMI via circuit breaker 12FN. **ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 002A) Energization of each system is through 115VAC 400Hz buses : - 115VAC ESS BUS 401XP via circuit breaker 2RS1 for system 1 - 115VAC BUS 2 204XP via circuit breaker 2RS2 for system 2. The 115VAC ESS BUS 401XP energizes the VOR/ADF/DME RMI via circuit breaker 12FN. R

**ON A/C 251-299, 501-509, 511-526, 528-599, (Ref. Fig. 002B) Energization of each system is through 115VAC 400Hz buses : - 115VAC ESS BUS 401XP via circuit breaker 2RS1 for system 1 - 115VAC BUS 2 204XP via circuit breaker 2RS2 for system 2. **ON A/C ALL 5. _____________________ Component Description **ON A/C 001-049, 101-105, 151-199, A. VOR/MKR Receiver (1) External description (Ref. Fig. 005) The front panel of the VOR receiver contains the following items: - Two pushbutton switches to enter the functional test mode with various LCD screen menus or messages. - A RS232 Port Connector as external interface with a keyboard an terminal display. - A Liquid Cristal Display (LCD) used to display faults and as an operator interface for certain modes.

  EFF : ALL  34-55-00    CES

 

Page 27 Feb 01/10

VOR/MKR Receiver Figure 005   R EFF : 001-049, 101-105, 151-199,  34-55-00    CES

 

Page 28 Nov 01/09

The back of the VOR/MKR receiver contains an ARINC 600, shell size connector to provide electrical connections to the aircraft wiring via mount. Contact grouping is as follows: - Top Plug (TP): connection with the automatic test circuit - Middle Plug (MP): connection with the peripheral circuits - Bottom Plug (BP): connection with the power supply circuit and the antennas. R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, A. VOR/MKR Receiver (1) External description (Ref. Fig. 005A) The face of the receiver is fitted with a handle, two lugs, a TEST pushbutton switch and test LEDs. The name, color and function of the LEDs are as follows: - CONTROL FAIL (red) indicates that the control input data are faulty - LRU STATUS (green) indicates that no faults are detected during the self-test sequence - LRU STATUS (red) indicates that a fault is detected during the self-test sequence. The back of the VOR /MKR receiver contains an ARINC 600, shell size connector to provide electrical connections to the aircraft wiring via mount. Contact grouping is as follows: - Top plug (TP): connection with the automatic test circuit - Middle plug (MP): connection with the peripheral circuits - Bottom plug (BP): connection with the power supply circuit and the antennas. **ON A/C ALL (2) Internal description **ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 006)

R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 006A)

  EFF : ALL  34-55-00    CES

 

Page 29 Feb 01/10

VOR/MKR Receiver Figure 005A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-55-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 30 Feb 01/10

VOR/MKR Receiver - General Architecture Figure 006   R EFF : 001-049, 101-105, 151-199,  34-55-00    CES

 

Page 31 Nov 01/09

VOR/MKR Receiver - General Architecture Figure 006A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-55-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 32 Feb 01/10

**ON A/C ALL The microprocessor-based receiver processes and conditions signals within the frequency range of 108 MHz to 117.95 MHz, to produce digital bearing and identification word outputs and an audio output. The receiver comprises: (a) A VOR RF receiver module which converts, conditions, filters and amplifies the received VOR signal. (b) A marker beacon receiver module which converts, conditions, filters and amplifies the received marker beacon signal. (c) A digital instrumentation module which processes VOR and marker beacon detector signals into ARINC-711 NAV receiver outputs. This module contains a signal processor and system processor. The signal processor is used in computing VOR bearing information. The system processor is used in interfacing with the aircraft and also communicates with the maintenance processor. (d) A maintenance processor module which monitors the health of the VOR and marker beacon receivers, power supply and signal and system processor faults. (e) A power supply module which converts aircraft 115VAC, 400 Hz power to supplies used by the internal circuits. R

**ON A/C 001-049, 101-105, 151-199, (3) Operation (Ref. Fig. 007) (a) VOR operation The VOR receiver is a single-conversion superheterodyne design. The receiver frequency and gain are controlled by the DSP section of the main processor board. The VOR antenna receives signals transmitted by the VOR ground station in the 108.00 MHz to 117.95 MHz frequency range. The received VOR signal is modulated with audio tones, which provide a digital bearing word output in accordance with ARINC specification format. The signal from the antenna is applied to the preselector, which is tuned to the selected VOR channel by a tuning voltage provided by the digital signal processor (DSP).

  EFF : ALL  34-55-00    CES

 

Page 33 Nov 01/09

VOR Receiver - Simplified Block Diagram Figure 007   R EFF : 001-049, 101-105, 151-199,  34-55-00    CES

 

Page 34 Nov 01/09

A frequency synthesizer, which is tuned by the DSP, supplies the local oscillator signal for injection into a balanced mixer. The mixer subtracts the local oscillator frequency from the preselector localizer signal to produce an 18.1 MHz intermediate frequency (i-f) signal. The preselector, in conjunction with the balanced mixer, provides rejection of undesired signals and immunity to cross-modulation and inter-modulation effects. The 18.1 MHz i-f signal from the mixer is amplified, and then filtered by a highly selective 18.1 MHz crystal filter prior to additional amplification and filtering. The amplified and filtered i-f signal is then applied to a detector stage where the audio signals are recovered as composite audio output levels for processing. A carrier-proportional dc voltage is also provided for Automatic Gain Control (AGC) operation. The DSP removes all audio information and provides the AGC control signals to the i-f amplifiers. AGC is used to provide a constant receiver output level over a carrier input level range of less than 5 microvolts to greater than 100 millivolts. Functional test is accomplished by injecting a test oscillator signal into the receiver and modulating the signal by the BITE. During normal operation, signals from the local oscillator, synthesizer, and AGC are monitored by the DSP. (b) MARKER operation (Ref. Fig. 008) The marker antenna receives a 75 MHz signal from one of the three marker beacon transmitters. The received signal is modulated with a 400 Hz, 1300 Hz, or 3000 Hz tone, depending upon whether the outer, middle, or inner marker is being crossed. The received 75 MHz signal is applied to a 4-pole crystal filter through an antenna monitor circuit which determines whether or not the antenna is connected to the receiver. The crystal filter provides the necessary selectivity and rejection of spurious or undesired frequencies. The output from the 4-pole 75 MHz crystal filter is applied to a variable gain rf amplifier through a switchable attenuator which either adds or does not add 14 dB of attenuation, as determined by the presence of absence of a buffered sensitivity select signal from the main processor. The main processor through a temperature compensated AGC amplifier. AGC is used to provide a constant receiver output level during variations in carrier input level.

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Page 35 Nov 01/09

VOR Receiver - Simplified Block Diagram Figure 007A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-55-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 36 Feb 01/10

MARKER Receiver - Simplified Block Diagram Figure 008   R EFF : 001-049, 101-105, 151-199,  34-55-00    CES

 

Page 37 Nov 01/09

The output from the variable gain rf amplifier is applied to a 2-pole crystal filter through a cascode amplifier which provides the required impedance match between the RF amplifier and the filter. The output of the filter is then applied to the audio detector through a buffer amplifier which presents a constant load to the filter and isolates the varying input impedance of the detector circuit. The recovered marker audio is then amplified and passed through an anti-alias (low-pass) filter to reduce harmonics before it is output to the main processor for analog-to-digital conversion. Functional testing is accomplished by applying a test enable signal through a buffer which provides a constant voltage to the base of the test oscillator transistors to prevent variation in the power levels of the test oscillators. The test oscillator injects a 75 MHz signal into the receiver through an adjustable pad which is used to set the output power level for maximum receiver sensitivity. (c) Instrumentation The CPU section is used to process the data from the DSP section, to provide information to the front panel display and to provide the data and control signals to the I/O section. The microprocessor in the CPU section controls all major functions of the VOR Receiver. ASICs an PLDs serve as the microprocessor controller and provides the interfaces with the memory devices (boot routine, program, fault and data), the data loader/recorder card, and the front panel display driver. Data is exchanged with the DSP section through a dual-port RAM. (d) LRU monitoring The maintenance processor, monitors the health of the VOR and marker beacon receivers. The maintenance processor provides all the BITE functions for the LRU. BITE information is transferred to the system processor for communications to the aircraft maintenance functions include: 1 _

Receive data from the ARINC maintenance bus and store the time, data, aircraft IDENT, aircraft configuration and process the maintenance control word.

2 _

Process data received from the system processor for storage in the Non-Volatile fault Memory (NVM).

3 _

Monitor discrete inputs.

4 _

Determine the validity of the maintenance input control word.

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Page 38 Nov 01/09

R R

5 _

Format the fault summary word and transfer it to the system processor.

6 _

Transfer all OMS interactive mode data and normal mode data words to the system processor.

7 _

Provide maintenance menus in the aircraft.

8 _

Provide extended interactive mode support for troubleshooting when the LRU is in the maintenance mode.

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (3) Operation (a) VOR operation (Ref. Fig. 007A) The antenna applies the composite signal transmitted by the ground station to an RF receiver. In the receiver, the signal passes through a low-pass filter, a bandpass filter (preselector) and an RF switch to an RF amplifier. The output of the amplifier passes through one of two bandpass filters, depending on the RF frequency of the station being received, to the first mixer. The mixer combines the RF signal with a Local Oscillator (LO) to produce a first Intermediate Frequency (IF) of 20.05 MHz. The first LO injects a frequency 20.05 MHz below the desired RF frequency. The mixer output is filtered by a crystal filter and passed through a two-stage IF amplifier. Following the IF amplifier, the signal is mixed with a 20.505 MHz second LO to produce a second IF of 455 MHz. The second IF signal is demodulated using a precision AM peak detector. The VOR detector signal is processed by the signal processor on the instrumentation module. The filtered VOR detector signal is output to the rear interconnect module where it is amplified and output to the aircraft.

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Page 39 Feb 01/10

(b) MARKER operation (Ref. Fig. 008A) The RF signal is filtered through a low-pass and a 75 MHz bandpass filter. Following the bandpass filter, the signal passes through an RF switch. This switch selects the incoming signal or the functional test signal. After the switch, an RF amplifier provides 12 dB of gain. Following the RF amplifier, the signal is further filtered by another 75 MHz bandpass filter. The output of the second filter goes to a mixer, where it is mixed with an 85.700 MHz Local Oscillator signal to produce an IF of 10.7 MHz. This IF signal is filtered, amplified and demodulated. The detector output is applied to three tone filters. The filter outputs are rectified and checked against a reference level by a comparator. Each comparator output is sent to the instrumentation module. The marker beacon receiver module also contains the functional test generator circuits. These circuits generate the 75 MHz test signal for the marker beacon receiver and VOR test signal for the VOR receiver. (c) Instrumentation The instrumentation module contains two processors. The signal processor, takes the VOR detector signal and separates the two 30 Hz signals (variable and reference). From these two signals, the signal processor computes the station bearing. The second processor on the module, the system processor, is used to communicate the bearing information to the aircraft. The system processor handles the signal interface with the aircraft. (d) LRU monitoring The maintenance processor, monitors the health of the VOR and marker beacon receivers. The maintenance processor provides all the BITE functions for the LRU. BITE information is transferred to the system processor for communications to the aircraft. Maintenance functions include: 1 _

Receive data from the ARINC maintenance bus and store the time, data, aircraft IDENT, aircraft configuration and process the maintenance control word.

2 _

Process data received from the system processor for storage in the Non-Volatile fault Memory (NVM).

3 _

Monitor discrete inputs.

4 _

Determine the validity of the maintenance input control word.

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Page 40 Feb 01/10

MARKER Receiver - Simplified Block Diagram Figure 008A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-55-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 41 Feb 01/10

5 _

Format the fault summary word and transfer it to the system processor.

6 _

Transfer all OMS interactive mode data and normal mode data words to the system processor.

7 _

Provide maintenance menus in the aircraft.

8 _

Provide extended interactive mode support for troubleshooting when the LRU is in the maintenance mode.

**ON A/C 001-049, 101-105, 151-199, (4) Digital outputs This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives: - EQ.SYS.LAB.SDI: (SDAC,FWC,DMC...) output label for which the parameter is available - PARAMETER DEFINITION: parameter name - WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds - CODE : BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-55-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 42 Feb 01/10

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| .034. |VOR 1 FREQ| 108/117.95 |MHZ | | 4 |2560|BCD | | | | | | 0.01 | | | | | | | | | |VOR 2 FREQ| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | .100. |SEL | 180 |DEG | | 10 | |BNR | | | | |COURSE 1 | 0.0439 | | | | | | | | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | .222. |OMNI | 180 |DEG | | 13 | |HYB | | | | |BEARING | 0.0439 | | | | | | | | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | .242. |VOR 1 | | | | | |HYB | | | | |IDENT | | | | | | | | | | |WORD 1 | | | | | | | | | | | | | | | | | | | | | |VOR 2 | | | | | | | | | | |IDENT | | | | | | | | | | |WORD 1 | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | .244. |VOR 1 | | | | | |HYB | | | | |IDENT | | | | | | | | | | |WORD 2 | | | | | | | | | | | | | | | | | | | | | |VOR 2 | | | | | | | | | | |IDENT | | | | | | | | | | |WORD 2 | | | | | | | | | ------------------------------------------------------------------------------R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (4) Digital outputs This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives : - EQ.SYS.LAB.SDI: (SDAC,FWC,DMC...) output label for which the parameter is available

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Page 43 Feb 01/10

- PARAMETER DEFINITION: parameter name - WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy - UNIT: unit in which the digital value is transmitted - SIG BIT: indicates whether a sign bit is available - BITS: number of bits used by the parameter in the label - XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds - CODE : BNR: binary data word BCD: binary coded decimal data word ISO: data word coded in ISO5 code DIS: discrete data word HEX: hexadecimal coded HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code - SOURCE ORIGIN: parameter source computer or system. ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------| .034. |VOR 1 FREQ| 108/117.95 |MHZ | | 4 |2560|BCD | | | | | | 0.01 | | | | | | | | | |VOR 2 FREQ| | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | .100. |SEL | 180 |DEG | | 12 | |BNR | | | | |COURSE 1 | 0.0439 | | | | | | | | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | .222. |OMNI | 180 |DEG | | 12 | |HYB | | | | |BEARING | 0.0439 | | | | | | | | | | | | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | .242. |VOR 1 | | | | | |HYB | | | | |IDENT | | | | | | | | | | |WORD 1 | | | | | | | | | | | | | | | | | | | | | |VOR 2 | | | | | | | | | | |IDENT | | | | | | | | | | |WORD 1 | | | | | | | | |

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-55-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 44 Feb 01/10

------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------|--------------|----------|------------|----|----|----|----|----|-----|-------| | .244. |VOR 1 | | | | | |HYB | | | | |IDENT | | | | | | | | | | |WORD 2 | | | | | | | | | | | | | | | | | | | | | |VOR 2 | | | | | | | | | | |IDENT | | | | | | | | | | |WORD 2 | | | | | | | | | ------------------------------------------------------------------------------**ON A/C ALL B. Antennas (1) MARKER antenna (Ref. Fig. 009) A low-drag, lightweight antenna, located in the longitudinal axis of the aircraft below the fuselage, is provided for the reception of the 75 MHz marker signals. The dielectric, foam-filled, white polyester fiberglass housing, fitted with a metal leading edge, protects against moisture and erosion. The antenna is horizontally polarized, has an impedance of 50 ohms. (2) VOR antenna (Ref. Fig. 010) The VOR antenna is an airborne antenna sunk into the fin and used to receive VOR signals in the 108-118 MHz range. It is a small-sized half-wave folded dipole type. The antenna has two independent RF connectors used to feed two items of equipment. The antenna is horizontally polarized, has an impedance of 50 ohms.

  EFF : ALL  34-55-00   R  CES

 

Page 45 Nov 01/07

MARKER - Antenna Figure 009   EFF : ALL  34-55-00   R  CES

 

Page 46 Nov 01/07

VOR - Antenna Figure 010   EFF : ALL  34-55-00   R  CES

 

Page 47 Nov 01/07

6. Operation _________ **ON A/C 001-049, 051-099, 101-105, 151-199, (Ref. Fig. 002) **ON A/C 106-149, 201-249, 301-399, 401-499, (Ref. Fig. 002A) R

**ON A/C 251-299, 501-509, 511-526, 528-599, (Ref. Fig. 002B) **ON A/C ALL A. Control (1) VOR system - Each VOR/MKR receiver is connected to one RMP. The VOR/MKR receiver 1 is connected to the RMP 1, (the VOR/MKR receiver 2 to the RMP 2). The RMP 1 also receives the management bus from the FMGC 1 (the RMP 2 from the FMGC 2). - In normal operation, the FMGC 1(2) tunes the VOR/MKR receiver 1(2) either automatically or manually by means of the MCDU 1(2). In this case the RMP 1(2) operates as a relay which sends the frequency and course information from the FMGC 1(2) to the VOR/MKR receiver 1(2). - By a second port, the VOR/MKR receiver 1(2) receives a second management bus directly from the FMGC 2(1). The receiver selects one of the two port functions by a discrete signal from the FMGC 1(2) through the RMP 1(2). - In case of one FMGC fault, the other FMGC can control the two VOR/MKR receivers, one directly, the other through its RMP. - In case of the RMP 1(2) or two RMPs fault, the concerned RMP is transparent to data and discrete from the FMGC. - In emergency configuration (in case of two FMGCs fault) the RMP 1 can control the VOR/MKR receiver 1 after ON NAV mode selection. Same possibility for the RMP 2 (VOR/MKR receiver 2). (Ref. Fig. 011)

  EFF : ALL  34-55-00    CES

 

Page 48 Feb 01/10

VOR - Frequency Selection in Emergency Mode Figure 011   R EFF : ALL  34-55-00    CES

 

Page 49 Nov 01/07

(2) Marker system The marker receiver is contained in the VOR/MKR receiver. In normal operation, the VOR/MKR receiver receives a signal when the aircraft overflies the corresponding marker. B. Reconfiguration Switching In normal utilization, both VOR 1 and 2 data are shown on the CAPT (F/O) ND through their respective Display Management Computer (DMC 1(2)). The marker data are shown on the CAPT (F/O) PFD through the DMC 1(2). In case of the DMC 1(2) fault, it is possible to switch over to the DMC 3 with the EIS DMC selector switch. This selector switch is located on panel 8VU on the center pedestal. In this case the DMC 3 totally replaces the DMC 1(2) through the stage of the output switching relay of the failed DMC. In case of PFD fault, there is an automatic transfer of the PFD image into the ND. In case of ND fault: - you obtain the transfer of the ND image onto the PFD when you push the PFD/ND XFR pushbutton switch on panel 301VU (501VU). When you set the PFD potentiometer to OFF on panel 301VU (501VU), this causes : - deactivation of the PFD - transfer of the PFD image onto the ND. 7. _____________ BITE Function R

**ON A/C 001-049, 101-105, 151-199, (Ref. Fig. 012) A. Access to the VOR/MKR Sub-menu Functions It is possible to select the maintenance functions of the VOR/MKR receiver 1 (2) on the MCDU1 (2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant VOR on the NAV menu. After these actions, the VOR 1 (2) provides its own menu page and the sub-menu functions can then be chosen by the operator. B. Activation of the Test Function The test function can be activated in ground conditions only. The VOR/MARKER test can be activated from any of the following sources: - the tuning frequency words SSM set to TEST - the front panel pushbutton - via the ARINC 429 CFDIU Data Bus (on the ground only) - the CFDS interactive menu.

  EFF : ALL  34-55-00    CES

 

Page 50 Nov 01/09

VOR/Marker - Maintenance Test Procedure Figure 012   EFF : ALL  34-55-00   R  CES

 

Page 51 Nov 01/07

(1) The SSM must be continuously updated and must reflect the current states of the BITE. If any failures are present the SMM must be set to FAIL. If no failures are present, then the SMM must be set to TEST. (2) Not Applicable R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, (Ref. Fig. 012) A. Access to the VOR/MKR Sub-menu Functions It is possible to select the maintenance functions of the VOR/MKR receiver 1 (2) on the MCDU1 (2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant VOR on the NAV menu. After these actions, the VOR 1 (2) provides its own menu page and the sub-menu functions can then be chosen by the operator. B. Activation of the Test Function The test function can be activated in ground conditions only. (1) Marker test The marker test can be activated by pressing the line key adjacent to the TEST indication on the VOR 1 maintenance sub-menu or by pressing the pushbutton switch on the face of the receiver. (2) VOR test The VOR test can be activated by pressing the line key adjacent to the TEST indication on the VOR 1(2) maintenance sub-menu or by pressing the pushbutton switch on the face of the receiver. **ON A/C 001-049, 101-105, 151-199, 8. _________ BITE Test A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the VOR system. The BITE of the VOR receiver is connected to the CFDIU (Ref. 31-32-00). The unit tested is the VOR receiver. The BITE:

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-55-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 52 Feb 01/10

- transmits permanently VOR system status and its identification message to the CFDIU - memorizes the failures which occurred during the last 63 flight segments - monitors data inputs from the various peripherals (FMGC, RMP and CFDIU) - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the menu mode. (a) Normal mode During the normal mode the BITE monitors cyclically the status of the VOR system. It transmits its information to the CFDIU during the concerned flight. In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 50 to 250 ms by an ARINC 429 message with label 356. (b) Menu mode: The menu mode can only be activated on the ground. This mode enables communication between the CFDIU and the VOR receiver BITE by means of the MCDU. The VOR menu mode is composed of: - LAST LEG REPORT (Ref. Fig. 013) This menu permits to display two failures per page. These may be any combination of class 1 and /or class 2 faults. - PREVIOUS LEGS REPORT (Ref. Fig. 013) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. - LRU IDENTIFICATION (Ref. Fig. 013) Allows to display the P/N and S/N of the equipment. - GROUND SCANNING (Ref. Fig. 014) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. - TROUBLE SHOOTING DATA (Ref. Fig. 014)

  EFF : 001-049, 101-105, 151-199,  34-55-00   R  CES

 

Page 53 Nov 01/07

VOR - Maintenance Test Procedure - VOR Menu Figure 013   R EFF : 001-049, 101-105, 151-199,  34-55-00    CES

 

Page 54 Nov 01/09

VOR - Maintenance Test Procedure - VOR Menu Figure 013A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-55-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 55 Feb 01/10

VOR - Maintenance Test Procedure - VOR Menu Figure 014   R EFF : ALL  34-55-00    CES

 

Page 56 Nov 01/07

Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEG REPORT. - CLASS 3 FAULT (Ref. Fig. 015) Allows to display the class 3 faults recorded during the last flight leg. - GROUND REPORT (Ref. Fig. 015) Allows to present the class 1, 2 or 3 internal failures detected on ground. These failures differ from those displayed on the LAST LEG REPORT and CLASS 3 FAULTS. - TEST (Ref. Fig. 016, 017) Allows a check of the correct operation of the VOR/MKR on ground. R R

**ON A/C 051-099, 106-149, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 8. _________ BITE Test A. CFDIU Interface (1) BITE description The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the VOR system. The BITE of the VOR receiver is connected to the CFDIU (Ref. 31-32-00). The unit tested is the VOR receiver. The BITE: - transmits permanently VOR system status and its identification message to the CFDIU - memorizes the failures which occurred during the last 63 flight segments - monitors data inputs from the various peripherals (FMGC, RMP and CFDIU) - transmits to the CFDIU the result of the tests performed and self-tests - can communicate with the CFDIU through the menus. The BITE can operate in two modes: - the normal mode - the menu mode.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-55-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 57 Feb 01/10

VOR - Maintenance Test Procedure - VOR Menu Figure 015   R EFF : ALL  34-55-00    CES

 

Page 58 Nov 01/07

VOR - Maintenance Test Procedure - VOR Menu Figure 016   R EFF : 001-049, 101-105, 151-199,  34-55-00    CES

 

Page 59 Nov 01/07

VOR - Maintenance Test Procedure - VOR Menu Figure 016A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-55-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 60 Feb 01/10

VOR - Maintenance Test Procedure - VOR Menu Figure 017   EFF : 001-049, 101-105, 151-199,  34-55-00    CES

 

Page 61 Nov 01/07

(a) Normal mode During the normal mode the BITE monitors cyclically the status of the VOR system. It transmits its information to the CFDIU during the concerned flight. In case of fault detection the BITE stores the information in the fault memories. These items of information are transmitted to the CFDIU every 50 to 250 ms by an ARINC 429 message with label 356. (b) Menu mode: The menu mode can only be activated on the ground. This mode enables communication between the CFDIU and the VOR receiver BITE by means of the MCDU. The VOR menu mode is composed of: - LAST LEG REPORT (Ref. Fig. 013A) This menu permits to display two failures per page. These may be any combination of class 1 and /or class 2 faults. - PREVIOUS LEGS REPORT (Ref. Fig. 013A) This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. - LRU IDENTIFICATION (Ref. Fig. 013A) Allows to display the P/N and S/N of the equipment. - GROUND SCANNING (Ref. Fig. 014) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. - TROUBLE SHOOTING DATA (Ref. Fig. 014) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEG REPORT. - CLASS 3 FAULT (Ref. Fig. 015) Allows to display the class 3 faults recorded during the last flight leg. - GROUND REPORT (Ref. Fig. 015) Allows to present the class 1, 2 or 3 internal failures detected on ground. These failures differ from those displayed on the LAST LEG REPORT and CLASS 3 FAULTS. - TEST

  R EFF : 051-099, 106-149, 201-249, 251-299,  34-55-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 62 Feb 01/10

(Ref. Fig. 016A, 017A, 018) Allows a check of the correct operation of the VOR/MKR on ground. **ON A/C ALL B. Power-up Tests Initialization and Cockpit Repercussions (1) Conditions of power-up tests initialization - How long the computer must be de-energized: 3 s. - A/C configuration: - whatever the A/C configuration on ground (2) Progress of power-up tests (a) Duration: 3 s. (b) Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - if VOR selected on FCU - ND VOR 1 or 2 in red Bearing of VOR 1 or VOR 2 rotates to 360 deg. (3) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed). (a) Tests pass: - if VOR selected on FCU - ND VOR 1 or 2 in white (b) Tests failed: - if VOR selected on FCU - ND VOR 1 or 2 in red VOR 1 or 2 bearing in red

  EFF : ALL  34-55-00   R  CES

 

Page 63 Feb 01/10

VOR - Maintenance Test Procedure - VOR Menu Figure 017A   R EFF : 051-099, 106-149, 201-249, 251-299,  34-55-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 64 Feb 01/10

VOR - Maintenance Test Procedure - VOR Menu Figure 018   R EFF : 051-099, 106-149, 201-249, 251-299,  34-55-00 301-399, 401-499, 501-509, 511-526, 528-599,   CES

 

Page 65 Feb 01/10

VOR/MARKER - ADJUSTMENT/TEST ____________________________ TASK 34-55-00-740-002 BITE Test of the VOR/MKR WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 31-32-00-860-010 34-10-00-860-002 34-10-00-860-004 34-10-00-860-005 R R

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Procedure to Get Access to the SYSTEM REPORT/TEST NAV Page ADIRS Start Procedure IR Alignment Procedure ADIRS Stop Procedure

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-55-00-991-001

Fig. 501

  EFF : ALL  34-55-00    CES

 

Page 501 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up R R

**ON A/C 001-049, 051-099, 101-105, 151-199, 251-299, 501-509, 511-526, 528-599, Subtask 34-55-00-860-054-B A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the ADIRS Start procedure (Ref. TASK 34-10-00-860-002) (3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004) (4) On the EFIS control sections of the FCU: - set the ADF/VOR selector switches to VOR - set the mode selector switches to ROSE/VOR. - push the ILS pushbutton switches. (5) On the center pedestral, on one MCDU: - get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010). - push the NEXT PAGE function key. (6) On the center pedestal, on the RMP1 (RMP2): - set the ON/OFF switch to ON - push the NAV and VOR pushbutton switches (the green LED on these pushbutton switches comes on) - set the non local VOR1 and VOR2 stations and a course of 190⁰. (Ref. Fig. 501/TASK 34-55-00-991-001) **ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-55-00-860-054-C A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

  EFF : ALL  34-55-00    CES

 

Page 502 Feb 01/10

VOR-Frequency and Course Selection Figure 501/TASK 34-55-00-991-001   EFF : ALL  34-55-00    CES

 

Page 503 Feb 01/98

(3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (4) On the EFIS control sections of the FCU : - set the ADF/VOR selector switches to VOR - set the mode selector switches to ROSE/VOR. - push the ILS pushbutton switches. (5) On the center pedestal, on one MCDU: - get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010) - push the NEXT PAGE function key. (6) On the center pedestal, on the RMP1 (RMP2): - set the ON/OFF switch to ON - push the NAV and VOR pushbutton switches (the green LED on these pushbutton switches comes on) - set the non local VOR1 and VOR2 stations and a course of 190⁰ (Ref. Fig. 501/TASK 34-55-00-991-001) (7) On the VOR/ADF/DME RMI : - set the VOR/ADF selector switches to VOR. **ON A/C ALL Subtask 34-55-00-865-054 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 49VU NAV/VOR/DME/RMI

12FN

F13

**ON A/C ALL 49VU NAV/VOR/1 121VU COM NAV/VOR/2

2RS1 2RS2

  EFF : ALL  34-55-00    CES

 

G13 K08

Page 504 Nov 01/08

4. Procedure _________ **ON A/C 001-049, 101-105, 151-199, Subtask 34-55-00-740-051-C A. BITE Test of the VOR/MARKER NOTE : During the BITE TEST (VOR1 or 2) by the MCDU, the indications ____ related to the two receivers (CAPT and F/O) are shown at the same time. This has no effect on the test or component operation. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the VOR1 (VOR2) indication.

- the VOR1 (VOR2) page comes into view.

- push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (pages 1 to 3).

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 11 S indication comes into view On the CAPT and F/O PFDs (for the VOR1 test only): - the OM indication comes into view until the end of the test. From 0 to 3 S: - on the CAPT and F/O NDs: . the VOR1 (VOR2) warning flags come into view. - on the VOR/DME RMI: . the VOR1 (VOR2) warning flag comes into view. From 3 to 6 s: - on the CAPT and F/O NDs: . the VOR1 (VOR2) pointer is not shown. - on the VOR/DME RMI:

  R EFF : ALL  34-55-00    CES

 

Page 505 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------. the VOR pointers stay in the 3 oclock position. From 6 to 11 s: - on the CAPT and F/O NDs: . the VOR1 (VOR2) pointer comes into view and shows 180 deg. - on the VOR/DME RMI: . the VOR1 (VOR2) pointer shows 180 deg. - on the CAPT and F/O PFDs (for the VOR1 test only): . the OM indication is shown. - push the line key adjacent to the YES indication.

- the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication.

The test procedure stops.

**ON A/C 051-099, Subtask 34-55-00-740-051 A. BITE Test of the VOR/MARKER NOTE : During the BITE TEST (VOR1 or 2) by the MCDU, the indications ____ related to the two receivers (CAPT and F/O) are shown at the same time. This has no effect on the test or component operation. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the VOR1 (VOR2) indication.

- the VOR1 (VOR2) page comes into view.

- push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (pages 1 to 3).

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-55-00    CES

 

Page 506 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the TEST IN PROGRESS 11 S indication the START TEST indication. comes into view On the CAPT and F/O PFDs (for the VOR1 test only): - the OM indication comes into view until the end of the test. From 0 to 3 S: - on the CAPT and F/O NDs: . the VOR1 (VOR2) warning flags come into view. - on the VOR/DME RMI: . the VOR1 (VOR2) warning flag comes into view. From 3 to 6 s: - on the CAPT and F/O NDs: . the VOR1 (VOR2) pointer is not shown. - on the VOR/DME RMI: . the VOR pointers stay in the 3 oclock position. From 6 to 11 s: - on the CAPT and F/O NDs: . the VOR1 (VOR2) pointer comes into view and shows 180 deg. - on the VOR/DME RMI: . the VOR1 (VOR2) pointer shows 180 deg. - on the CAPT and F/O PFDs (for the VOR1 test only): . the OM indication is shown. - push the line key adjacent to the YES indication (for the VOR1 test only).

On the MCDU: - the MARKER AURAL TONE OK indication comes into view (for the VOR1 test only).

- push the line key adjacent to the YES indication.

- the TEST OK indication comes into view.

  R EFF : 051-099,  34-55-00    CES

 

Page 507 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to The test procedure stops. the RETURN indication. R

**ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-55-00-740-051-A A. BITE Test of the VOR/MARKER NOTE : During the BITE TEST (VOR1 or 2) by the MCDU, the indications ____ related to the two receivers (CAPT and F/O) are shown at the same time. This has no effect on the test or component operation. ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the VOR1 (VOR2) indication.

- the VOR1 (VOR2) page comes into view.

- push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (pages 1 to 3).

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 11 S indication comes into view On the CAPT and F/O PFDs (for the VOR1 test only): - the OM indication comes into view until the end of the test. From 0 to 3s: - on the CAPT and F/O NDs: . the VOR1 (VOR2) warning flags come into view. - on the VOR/ADF/DME RMI: . the VOR1 (VOR2) warning flag comes into view. From 3 to 6s: - on the CAPT and F/O NDs:

  R EFF : 051-099, 106-149, 201-249, 301-399,  34-55-00 401-499,   CES

 

Page 508 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------. the VOR1 (VOR2) pointer is not shown. - on the VOR/ADF/DME RMI: . the VOR pointers stay at the last valid position. NOTE : Disregard MCDU display test ____ result. From 6 to 11s: - on the CAPT and F/O NDs: . the VOR1 (VOR2) pointer comes into view and shows 180 deg. - on the VOR/ADF/DME RMI: . the VOR1 (VOR2) pointer shows 180 deg. - on the CAPT and F/O PFDs (for the VOR1 test only): . the OM indication is shown.

R

- push the line key adjacent to the YES indication (for the VOR1 test only).

On the MCDU: - the MARKER AURAL TONE OK indication comes into view (for the VOR1 test only).

- push the line key adjacent to the YES indication.

- the TEST OK indication comes into view.

- push the line key adjacent to the RETURN indication.

The test procedure stops.

**ON A/C 251-299, 501-509, 511-526, 528-599, Subtask 34-55-00-740-051-D A. BITE Test of the VOR/MARKER NOTE : During the BITE TEST (VOR1 or 2) by the MCDU, the indications ____ related to the two receivers (CAPT and F/O) are shown at the same time. This has no effect on the test or component operation.

  R EFF : 106-149, 201-249, 251-299, 301-399,  34-55-00 401-499, 501-509, 511-526, 528-599,   CES

 

Page 509 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the MCDU:

On the MCDU:

- push the line key adjacent to the VOR1 (VOR2) indication.

- the VOR1 (VOR2) page comes into view.

- push the line key adjacent to the TEST indication.

- the INITIAL CONDITIONS are shown (pages 1 to 3). NOTE : Ignore all the checks to be done ____ on the DDRMI.

- push the line key adjacent to the START TEST indication.

- the TEST IN PROGRESS 11 S indication comes into view On the CAPT and F/O PFDs (for the VOR1 test only): - the OM indication comes into view until the end of the test. From 0 to 3 S: - on the CAPT and F/O NDs: . the VOR1 (VOR2) warning flags come into view. From 3 to 6 s: - on the CAPT and F/O NDs: . the VOR1 (VOR2) pointer is not shown. From 6 to 11 s: - on the CAPT and F/O NDs: . the VOR1 (VOR2) pointer comes into view and shows 180 deg. - on the CAPT and F/O PFDs (for the VOR1 test only): . the OM indication is shown.

- push the line key adjacent to the YES indication (for the VOR1 test only).

On the MCDU: - the MARKER AURAL TONE OK indication comes into view (for the VOR1 test only).

  R EFF : 251-299, 501-509, 511-526, 528-599,  34-55-00    CES

 

Page 510 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the line key adjacent to - the TEST OK indication comes into the YES indication. view. - push the line key adjacent to the RETURN indication.

The test procedure stops.

**ON A/C ALL 5. Close-up ________ Subtask 34-55-00-860-055-A A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) On the EFIS control sections of the FCU: - set the ADF/VOR selector switches to OFF. - release the ILS pushbutton switches. (3) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (4) On the center pedestal, on the RMP: - push the NAV and VOR pushbutton switches (the green LED on these pushbutton switches goes off). - set the ON/OFF switch to OFF. (5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002) (6) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-55-00   R  CES

 

Page 511 Nov 01/08

TASK 34-55-00-710-001 Operational Test of the VOR/MKR WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1. __________________ Reason for the Job Reception Test of the VOR beacon. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-55-00-991-001

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Fig. 501

3. __________ Job Set-up Subtask 34-55-00-860-050 A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002) (2) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switches to ON.

  EFF : ALL  34-55-00   R  CES

 

Page 512 Nov 01/07

Subtask 34-55-00-865-051 B. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------R

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 49VU NAV/VOR/DME/RMI

12FN

F13

**ON A/C ALL 49VU NAV/VOR/1 121VU COM NAV/VOR/2

2RS1 2RS2

G13 K08

4. Procedure _________ Subtask 34-55-00-710-055 A. Operational Test of the VOR/MKR ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the RMP1 (RMP2): - push the NAV pushbutton switch.

On the RMP, the green LED on this pushbutton switch comes on.

- set the frequency of the VOR1 (2) local station (Ref. Fig. 501/TASK 34-55-00991-001)

The frequency comes into view in the left window of the RMP

2. On the center pedestal, on one ACP : - set the VOR1 reception.

In the loud speakers, you must hear the Morse signal of the set station.

3. On the RMP1 (RMP2):

  EFF : ALL  34-55-00    CES

 

Page 513 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- push the NAV pushbutton switch. The green LED on this pushbutton switch goes off. 5. Close-up ________ Subtask 34-55-00-860-051 A. Put the aircraft back to its initial configuration. (1) On the center pedestal, on the RMP, set the ON/OFF switch to OFF. (2) On the center pedestal, on the ACP, release the VOR1 pushbutton switch. (3) De-energize the aircraft electrical circuits. (Ref. TASK 24-41-00-862-002) (4) Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-55-00   R  CES

 

Page 514 Nov 01/07

TASK 34-55-00-720-001 Functional Test of the VOR/MKR WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE _______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. NOTE : You can do the MKR test only at the end of the VOR1 test. ____ 1. __________________ Reason for the Job To make sure that the VOR and MKR systems operate correctly. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

ground test unit

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 34-10-00-860-002 34-10-00-860-004 34-10-00-860-005 R R

Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power ADIRS Start Procedure IR Alignment Procedure ADIRS Stop Procedure

**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 501-509, 511-526, 528-599, 34-55-00-991-001

Fig. 501

  EFF : ALL  34-55-00    CES

 

Page 515 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-55-00-865-053 A. Make sure that this(these) circuit breaker(s) is(are) closed: ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 301-399, 401-499, 49VU NAV/VOR/DME/RMI

12FN

F13

**ON A/C ALL 49VU NAV/VOR/1 121VU COM NAV/VOR/2 R R

2RS1 2RS2

G13 K08

**ON A/C 001-049, 051-099, 101-105, 151-199, 251-299, 501-509, 511-526, 528-599, Subtask 34-55-00-860-052 B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002) (2) Install the ground test unit near the VOR or MKR antenna as shown in the installation instructions. (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (5) On the EFIS control sections of the FCU: - set the ADF/VOR selector switches to VOR and the mode selector switches to ROSE/VOR. - push the ILS pushbutton switches.

  EFF : ALL  34-55-00    CES

 

Page 516 Feb 01/10

(6) On the center pedestal, on one ACP, set the VOR1 (2) or MKR reception. (7) On the center pedestal, on the RMP1 and RMP2: - set the ON/OFF selector switch to ON. **ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-55-00-860-052-A B. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861002) (2) Install the ground test unit near the VOR or MKR antenna as shown in the installation instructions. (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002). (4) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004). (5) On the EFIS control sections of the FCU: - set the ADF/VOR selector switches to VOR and the mode selector switches to ROSE/VOR. - push the ILS pushbutton switches. (6) On the center pedestal, on one ACP, set the VOR1 (2) or MKR reception. (7) On the center pedestal, on the RMP1 and RMP2: - set the ON/OFF selector switch to ON. (8) On the VOR/ADF/DME RMI: - set the VOR/ADF selector switches to VOR.

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-55-00 201-249, 251-299, 301-399, 401-499, 501-509,  511-526, 528-599, CES

 

Page 517 Feb 01/10

**ON A/C ALL 4. Procedure _________ **ON A/C 001-049, 051-099, 101-105, 151-199, Subtask 34-55-00-720-050 A. Test of the VOR Reception and Identification ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the test unit: - set the frequency of the VOR test unit and then set a bearing of 0⁰. 2. On the RMP1 (RMP2): - push the NAV pushbutton switch.

On the RMP, the green LED on this pushbutton switch comes on.

- push the VOR pushbutton switch.

On the RMP, the green LED on this pushbutton switch comes on.

- set the VOR1 (VOR2) frequency of the VOR test unit and then set a course of C000 . (Ref. Fig. 501/TASK 34-55-00991-001)

On the RMP1 (RMP2): - the frequency comes into view in the left window. - the course comes into view in the right window. On the CAPT and F/O NDs: - the VOR1 (VOR2) frequency and the CRS 000 indications come into view in the top right corner. - the VOR1 (VOR2) indication and the VOR1 (VOR2) frequency come into view in the left (right) lower corner. - the outline of the pointer comes into view in the left (right) lower corner.

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Page 518 Nov 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the dagger shaped pointer (course pointer) shows 0⁰. - the VOR1 (VOR2) pointer comes into view and shows 0⁰. - the lateral deviation bar and the arrow that shows the TO indication come into view and are on the same axis as the dagger shaped pointer (course pointer). On the VOR/DME RMI: - the VOR1 (VOR2) pointer shows 0⁰. - set a course of C005 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 5⁰ and the lateral deviation bar moves to the left and stops on the first dot.

- set a course of C010 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 10⁰ and the lateral deviation bar moves to the left and stops on the second dot.

- set a course of C355 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 355⁰ and the lateral deviation bar moves to the right and stops on the first dot.

- set a course of C350 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 350⁰ and the lateral deviation bar moves to the right and stops on the second dot.

3. On the test unit: - set a bearing of 135⁰.

On the CAPT and F/O NDs: - the VOR1 (VOR2) pointer shows 135⁰. - the lateral deviation bar moves to the right and the arrow indicates FROM. On the VOR/DME RMI: - the VOR1 (VOR2) pointer shows 135⁰.

4. On the RMP1 (RMP2):

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Page 519 Nov 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set a course of C135. On the CAPT and F/O NDs: - the CRS 135⁰ indication comes into view in the top right corner. - the set dagger shaped pointer (course pointer) shows 135⁰. - the lateral deviation bar moves to the center and the arrow indicates TO. - set a course of C315.

5. On the test unit: - set the test unit in the OFF position

On the CAPT and F/O NDs: - the CRS 315⁰ indication comes into view in the top right corner. - the set dagger shaped pointer (course pointer) shows 315⁰. - the lateral deviation bar moves and then returns to the center and the arrow indicates FROM. On the CAPT ND: - the VOR1 (VOR2) pointer goes out of view - the lateral deviation bar and the arrow that indicates FROM/TO go out of view. On the F/O ND: - the VOR1 (VOR2) pointer goes out of view On the VOR/DME RMI: - the VOR1 (VOR2) pointer goes to the 3 oclock position.

6. On the test unit: - set the test unit on the ON position and set the transmission of the identification signal.

In the loudspeaker, you can hear the audio signal.

7. On the ACP: - adjust the volume until you get the required level.

The adjustment is continuous and no unwanted noise is heard.

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Page 520 Nov 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------8. On the test unit: - cancel the transmission of the audio signal.

You cannot hear the signal.

9. On the RMP1 (RMP2): - push the NAV pushbutton switch. R

On the RMP, the green LED on this pushbutton switch goes off.

**ON A/C 106-149, 201-249, 301-399, 401-499, Subtask 34-55-00-720-050-A A. Test of the VOR Reception and Identification ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the test unit: - set the frequency of the VOR test unit and then set a bearing of 0⁰. 2. On the RMP1 (RMP2): - push the NAV pushbutton switch.

On the RMP, the green LED on this pushbutton switch comes on.

- push the VOR pushbutton switch.

On the RMP, the green LED on this pushbutton switch comes on.

- set the VOR1 (VOR2) frequency of the VOR test unit and then set a course of C000 . (Ref. Fig. 501/TASK 34-55-00991-001)

On the RMP1 (RMP2): - the frequency comes into view in the left window. - the course comes into view in the right window. On the CAPT and F/O NDs:

  R EFF : 001-049, 051-099, 101-149, 151-199,  34-55-00 201-249, 301-399, 401-499,   CES

 

Page 521 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the VOR1 (VOR2) frequency and the CRS 000 indications come into view in the top right corner. - the VOR1 (VOR2) indication and the VOR1 (VOR2) frequency come into view in the left (right) lower corner. - the outline of the pointer comes into view in the left (right) lower corner. - the dagger shaped pointer (course pointer) shows 0⁰. - the VOR1 (VOR2) pointer comes into view and shows 0⁰. - the lateral deviation bar and the arrow that shows the TO indication come into view and are on the same axis as the dagger shaped pointer (course pointer). On the VOR/ADF/DME RMI: - the VOR1 (VOR2) pointer shows 0⁰. - set a course of C005 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 5⁰ and the lateral deviation bar moves to the left and stops on the first dot.

- set a course of C010 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 10⁰ and the lateral deviation bar moves to the left and stops on the second dot.

- set a course of C355 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 355⁰ and the lateral deviation bar moves to the right and stops on the first dot.

- set a course of C350 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 350⁰ and the lateral deviation bar moves to the right and stops on the second dot.

3. On the test unit: - set a bearing of 135⁰.

On the CAPT and F/O NDs:

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Page 522 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- the VOR1 (VOR2) pointer shows 135⁰. - the lateral deviation bar moves to the right and the arrow indicates FROM. On the VOR/ADF/DME RMI: - the VOR1 (VOR2) pointer shows 135⁰. 4. On the RMP1 (RMP2): - set a course of C135.

On the CAPT and F/O NDs: - the CRS 135⁰ indication comes into view in the top right corner. - the set dagger shaped pointer (course pointer) shows 135⁰. - the lateral deviation bar moves to the center and the arrow indicates TO.

- set a course of C315.

On the CAPT and F/O NDs: - the CRS 315⁰ indication comes into view in the top right corner. - the set dagger shaped pointer (course pointer) shows 315⁰. - the lateral deviation bar moves and then returns to the center and the arrow indicates FROM.

5. On the test unit: - set the test unit in the OFF position

On the CAPT ND: - the VOR1 (VOR2) pointer goes out of view - the lateral deviation bar and the arrow that indicates FROM/TO go out of view. On the F/O ND: - the VOR1 (VOR2) pointer goes out of view On the VOR/ADF/DME RMI: - the flag VOR1 (VOR2) comes into view.

6. On the test unit:

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Page 523 Nov 01/08

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set the test unit on the ON In the loudspeaker, you can hear the position and set the audio signal. transmission of the identification signal. 7. On the ACP: - adjust the volume until you get the required level.

The adjustment is continuous and no unwanted noise is heard.

8. On the test unit: - cancel the transmission of the audio signal.

You cannot hear the signal.

9. On the RMP1 (RMP2): - push the NAV pushbutton switch. R

On the RMP, the green LED on this pushbutton switch goes off.

**ON A/C 251-299, 501-509, 511-526, 528-599, Subtask 34-55-00-720-050-B A. Test of the VOR Reception and Identification ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the test unit: - set the frequency of the VOR test unit and then set a bearing of 0⁰. 2. On the RMP1 (RMP2): - push the NAV pushbutton switch.

On the RMP, the green LED on this pushbutton switch comes on.

- push the VOR pushbutton switch.

On the RMP, the green LED on this pushbutton switch comes on.

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Page 524 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set the VOR1 (VOR2) frequency On the RMP1 (RMP2): of the VOR test unit and then - the frequency comes into view in the set a course of C000 . left window. (Ref. Fig. 501/TASK 34-55-00991-001) - the course comes into view in the right window. On the CAPT and F/O NDs: - the VOR1 (VOR2) frequency and the CRS 000 indications come into view in the top right corner. - the VOR1 (VOR2) indication and the VOR1 (VOR2) frequency come into view in the left (right) lower corner. - the outline of the pointer comes into view in the left (right) lower corner. - the dagger shaped pointer (course pointer) shows 0⁰. - the VOR1 (VOR2) pointer comes into view and shows 0⁰. - the lateral deviation bar and the arrow that shows the TO indication come into view and are on the same axis as the dagger shaped pointer (course pointer). - set a course of C005 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 5⁰ and the lateral deviation bar moves to the left and stops on the first dot.

- set a course of C010 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 10⁰ and the lateral deviation bar moves to the left and stops on the second dot.

- set a course of C355 .

On the CAPT and F/O NDs the dagger shaped (course pointer) shows 355⁰ and the lateral deviation bar moves to the right and stops on the first dot.

  R EFF : 251-299, 501-509, 511-526, 528-599,  34-55-00    CES

 

Page 525 Feb 01/10

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- set a course of C350 . On the CAPT and F/O NDs the dagger shaped (course pointer) shows 350⁰ and the lateral deviation bar moves to the right and stops on the second dot. 3. On the test unit: - set a bearing of 135⁰.

On the CAPT and F/O NDs: - the VOR1 (VOR2) pointer shows 135⁰. - the lateral deviation bar moves to the right and the arrow indicates FROM.

4. On the RMP1 (RMP2): - set a course of C135.

On the CAPT and F/O NDs: - the CRS 135⁰ indication comes into view in the top right corner. - the set dagger shaped pointer (course pointer) shows 135⁰. - the lateral deviation bar moves to the center and the arrow indicates TO.

- set a course of C315.

On the CAPT and F/O NDs: - the CRS 315⁰ indication comes into view in the top right corner. - the set dagger shaped pointer (course pointer) shows 315⁰. - the lateral deviation bar moves and then returns to the center and the arrow indicates FROM.

5. On the test unit: - set the test unit in the OFF position

On the CAPT ND: - the VOR1 (VOR2) pointer goes out of view - the lateral deviation bar and the arrow that indicates FROM/TO go out of view. On the F/O ND: - the VOR1 (VOR2) pointer goes out of view

  R EFF : 251-299, 501-509, 511-526, 528-599,  34-55-00    CES

 

Page 526 Feb 01/10

R

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------6. On the test unit:

R R R R R

- set the test unit on the ON position and set the transmission of the identification signal. 7. On the ACP:

R R R

- adjust the volume until you get the required level.

The adjustment is continuous and no unwanted noise is heard.

8. On the test unit:

R R R

In the loudspeaker, you can hear the audio signal.

- cancel the transmission of the audio signal.

You cannot hear the signal.

9. On the RMP1 (RMP2):

R R

- push the NAV pushbutton switch.

On the RMP, the green LED on this pushbutton switch goes off.

**ON A/C ALL Subtask 34-55-00-720-051 B. Test of the MKR Reception and Identification ------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------1. On the test unit: - set a frequency of 75 MHz with a signal modulation of 400Hz (OM signal).

On the CAPT and F/O PFDs: - the OM indication comes into view on the right. In the loudspeaker, you can hear the audio signal.

2. On the ACP:

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Page 527 Nov 01/07

------------------------------------------------------------------------------ACTION RESULT ------------------------------------------------------------------------------- adjust the volume until you get In the loudspeaker, the adjustment is the required level. continuous and no unwanted noise can be heard. 3. On the test unit: - modulate the signal to 1300Hz (MM signal).

On the CAPT and F/O PFDs: - the MM indication comes into view on the right. In the loudspeaker, you can hear the audio signal.

- modulate the signal to 3000Hz (AWY signal).

On the CAPT and F/O PFDs: - the AWY indication comes into view on the right. In the loudspeaker, you can hear the audio signal.

- cancel the 75MHz frequency.

On the CAPT and F/O PFDs: the last MKR indication goes out of view. In the loudspeaker, you cannot hear the transmission of the audio signal.

5. Close-up ________ Subtask 34-55-00-860-053 A. Put the aircraft back to its initial configuration. (1) On the EFIS control sections of the FCU: - set the ADF/VOR selector switches to OFF. - release the ILS pushbutton switches. (2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005). (3) On the center pedestal, on the RMP, set the ON/OFF switch to OFF. (4) On the center pedestal, on the ACP, release the VOR1 (2) or MKR pushbutton switch. (5) Stop the test unit.

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Page 528 Nov 01/07

(6) De-energize the aircraft electrical circuits. (Ref. TASK 24-41-00-862-002) (7) Make sure that the work area is clean and clear of tool(s) and other items.

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Page 529 Nov 01/07

ANTENNA - VOR (4RS) - REMOVAL/INSTALLATION __________________________________________ TASK 34-55-11-000-001 Removal of the VOR Antenna 4RS 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No No

specific specific specific specific specific

blanking caps circuit breaker(s) safety clip(s) nonmetallic scraper warning notice access platform 12 m (39 ft. 4 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-42-00-861-001 R

55-34-11-000-001 34-55-11-991-001

Energize the Ground Service Network from the External Power Removal of the Vertical Stabilizer Tip Fig. 401

3. __________ Job Set-up Subtask 34-55-11-861-050 A. Energize the ground service network (Ref. TASK 24-42-00-861-001)

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Page 401 May 01/05

Subtask 34-55-11-865-050 B. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/VOR/1 2RS1 G13 121VU COM NAV/VOR/2 2RS2 K08 Subtask 34-55-11-010-050 C. Get Access (1) Put the warning notice in the cockpit to tell persons not to operate the flight controls. (2) Put the access platform in position at Zone 324. (3) Remove the vertical stabilizer tip 324AT (Ref. TASK 55-34-11-000-001) 4. Procedure _________ (Ref. Fig. 401/TASK 34-55-11-991-001) Subtask 34-55-11-020-051 A. Removal of the VOR Antenna (1) Solution 1 (VOR antenna S/N 001-331): - disconnect the coaxial cable connectors (2) from the antenna connectors (6). - remove sealant from the head of the screws (3) with a nonmetallic scraper. - remove the screws (3), the washers (5) and the antenna (1). (2) Solution 2 (VOR antenna S/N 332 and subsequent): - disconnect the coaxial cable connectors (2) from the antenna connectors (6). - remove the sealant from the head of the screws (3) with a nonmetallic scraper. - remove the screws (3), the washers (5), the isolation washers (7) and the antenna (1). NOTE : The isolation washers have a tendancy to stick to the bottom ____ of the VOR antenna. They must be removed.

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Page 402 May 01/05

VOR Antenna 4RS. Solution 1 (S/N 001-331) / Solution 2 (S/N 332 and subsequent). Figure 401/TASK 34-55-11-991-001  EFF : ALL  Page 403   Feb 01/98   CES 



34-55-11

(3) Put blanking caps on the disconnected electrical connectors.

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Page 404 Feb 01/98

TASK 34-55-11-400-001 Installation of the VOR Antenna 4RS WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN. _______ IF YOU DO: - RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH - WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER. R R R

WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------

R R

No specific No specific No specific

nonmetallic scraper Lint-free cloth Torque Wrench : range 0.00 to 1.20 m.daN (0.00 to 9.00 lbf.ft)

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Page 405 May 01/05

B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 07-001 R R Material No. 09-016 Material No. 11-010 Material No. 16-003

NO LONGER AVAILABLE RPLD BY 07001B/D/F (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) USA TT-I-735 GRADE A ISOPROPYL ALCOHOL (Ref. 20-31-00) F ASNB70720 COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------20-28-00-912-005 24-42-00-861-001 24-42-00-862-001 34-55-00-720-001 55-34-11-000-001 55-34-11-400-001 34-55-11-991-001

Electrical Bonding of Antennas With Conductive Bolts. Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Functional Test of the VOR/MKR Removal of the Vertical Stabilizer Tip Installation of the Vertical Stabilizer Tip Fig. 401

3. __________ Job Set-up Subtask 34-55-11-860-050 A. Aircraft Maintenance Configuration Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001) (1) Make sure that the warning notices are in position in the cockpit to tell persons not to operate the flight controls. (2) Make sure that the access platform is in position at Zone 324.

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Page 406 May 01/07

(3) Make sure that the vertical stabilizer 324AT (Ref. TASK 55-34-11-000001) is removed. Subtask 34-55-11-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/VOR/1 2RS1 G13 121VU COM NAV/VOR/2 2RS2 K08 4. Procedure _________ (Ref. Fig. 401/TASK 34-55-11-991-001) WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE THE SPECIAL _______ MATERIAL. THIS MATERIAL IS DANGEROUS. Subtask 34-55-11-140-050 A. Preparation for Installation (1) Remove the used sealant from the antenna support with a nonmetallic scraper. R R

(2) Clean the component interface and/or the adjacent area with CLEANING AGENTS (Material No. 11-010) and a Lint-free cloth. (3) Do an inspection of the component interface and/or the adjacent area. NOTE : Make sure that the antenna-attachment points have no signs of ____ paint, corrosion or sealant. Subtask 34-55-11-420-050 B. Installation of the VOR Antenna (1) Solution 1 ( VOR antenna S/N 001-331): - put the antenna (1) in position and install the screws (3) and the washers (5). - TORQUE the screws (3) to between 0.35 and 0.45 m.daN (30.97 and 39.82 lbf.in). - connect the cable connector (2) to the antenna connector (6).

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Page 407 May 01/00

(2) Solution 2 ( VOR antenna S/N 332 and subsequent): - put the antenna (1) in position and install the isolation washers (7), the - screws (3) and the washers (5). - TORQUE the screws (3) to between 0.35 and 0.45 m.daN (30.97 and 39.82 lbf.in). (3) Remove the blanking caps from the electrical connectors. (4) Make sure that the electrical connectors are clean and in the correct condition. (5) Connect the cable connector (2) to the antenna connector (6). (6) Make sure that the bonding contact resistance between the antenna (1) and the fuselage structure is not higher than 5 milliohms (Ref. TASK 20-28-00-912-005). (7) Apply SEALANTS (Material No. 09-016) around the antenna electrical bonding points and the screws (3). (8) Let the sealant cure. (9) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the electrical bonding points. R R

(10) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001) to the sealant on the head of the screws (3). Subtask 34-55-11-865-052 C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 2RS1, 2RS2 Subtask 34-55-11-720-050 D. Do the functional test of the VOR system (Ref. TASK 34-55-00-720-001).

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Page 408 May 01/00

5. Close-up ________ Subtask 34-55-11-410-052 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the vertical stabilizer tip 324AT (Ref. TASK 55-34-11-400001). (3) Remove the access platform(s). (4) Remove the warning notice(s). Subtask 34-55-11-862-050 B. De-energize the ground service network (Ref. TASK 24-42-00-862-001)

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Page 409 Feb 01/98

ANTENNA - MARKER (1RS) - REMOVAL/INSTALLATION _____________________________________________ TASK 34-55-18-000-001 Removal of the Marker Antenna (1RS) WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

blanking caps circuit breaker(s) safety clip(s)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R R

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 301-399, 501-509, 511-526, 528-599, 34-55-18-991-001

Fig. 401

**ON A/C 151-199, 401-499, 34-55-18-991-001-A

Fig. 401A

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Page 401 Feb 01/10

**ON A/C ALL 3. __________ Job Set-up Subtask 34-55-18-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/VOR/1 2RS1 G13 4. Procedure _________ R R

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 301-399, 501-509, 511-526, 528-599, (Ref. Fig. 401/TASK 34-55-18-991-001) **ON A/C 151-199, 401-499, (Ref. Fig. 401A/TASK 34-55-18-991-001-A) **ON A/C ALL Subtask 34-55-18-020-050 A. Removal of the Marker Antenna (1) Remove the sealant from the heads of the screws (4). (2) Remove the screws (4). (3) Put the antenna (3) away from the fuselage (2). (4) Disconnect the coaxial connector (1). (5) Remove and discard the seal (6). (6) Remove the antenna (3). (7) Put blanking caps on the disconnected coaxial connectors (1) and (5).

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Page 402 Feb 01/10

Marker Antenna Figure 401/TASK 34-55-18-991-001   R EFF : 001-049, 051-099, 101-149, 201-249,  34-55-18 251-299, 301-399, 501-509, 511-526, 528-599,   CES

 

Page 403 Feb 01/10

Marker Antenna Figure 401A/TASK 34-55-18-991-001-A   R EFF : 151-199, 401-499,  34-55-18    CES

 

Page 404 Aug 01/05

TASK 34-55-18-400-001 Installation of the Marker Antenna (1RS) WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS _______ ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No. 05-013

D TV-53-3507/73 RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)

Material No. 07-001B R Material No. 09-016 Material No. 09-019 Material No. 11-003 Material No. 16-003

ELECTRICAL BOND VARNISH (Ref. 20-31-00) USA MIL-PRF-81733D TYPE II CLASS B CORROSION INHIBITING FILLET CONSISTENCY (Ref. 20-31-00) USA AMS 3267/3 NO LONGER AVAILABLE (Ref. 20-31-00) USA ASTM D 740 METHYL-ETHYL-KETONE (Ref. 20-31-00) F ASNB70720 COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

B. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------6 6

seal seal

34-55-18 01 -010 34-55-18 01A-010

  EFF : ALL  34-55-18    CES

 

Page 405 Feb 01/09

C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-55-00-720-001 R R

Functional Test of the VOR/MKR

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 301-399, 501-509, 511-526, 528-599, 34-55-18-991-001

Fig. 401

**ON A/C 151-199, 401-499, 34-55-18-991-001-A

Fig. 401A

**ON A/C ALL 3. __________ Job Set-up Subtask 34-55-18-865-051 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/VOR/1 2RS1 G13 4. Procedure _________ R R

**ON A/C 001-049, 051-099, 101-149, 201-249, 251-299, 301-399, 501-509, 511-526, 528-599, (Ref. Fig. 401/TASK 34-55-18-991-001)

  EFF : ALL  34-55-18    CES

 

Page 406 Feb 01/10

**ON A/C 151-199, 401-499, (Ref. Fig. 401A/TASK 34-55-18-991-001-A) **ON A/C ALL Subtask 34-55-18-420-050 A. Installation of the Marker Antenna WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: _______ - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. NOTE : If you install the same antenna it is necessary to clean it with ____ CLEANING AGENTS (Material No. 11-003) (1) Remove the used sealant from the fuselage with CLEANING AGENTS (Material No. 11-003). (2) Apply SPECIAL MATERIALS (Material No. 05-013) on the antenna (3) mount and on the fuselage (2). (3) Apply SEALANTS (Material No. 09-019) on the antenna (3) mount and on the fuselage (2). NOTE : Make sure that there is no sealant in the screw holes. ____ (4) Remove the blanking caps from the coaxial connectors (1) and (5). (5) Install a new seal (6). (6) Connect the coaxial connector (1) to the antenna (3). (7) Put the antenna (3) in position on the fuselage (2). (8) Attach the antenna (3) with the screws (4). (9) Remove the sealant which is not necessary. (10) Apply a sealing bead with SEALANTS (Material No. 09-016) around the antenna (3). (11) Apply SEALANTS (Material No. 09-016) on the screw (4) heads.

  EFF : ALL  34-55-18   R  CES

 

Page 407 May 01/07

(12) Make the contour of the screws (4) and the antenna (3) smooth. (13) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the base of the antenna (3). (14) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07001B) to the sealant on the heads of the screws (4). R R

NOTE : It is not mandatory to paint the sealant around the base of ____ the antenna and on the head of the screws. Subtask 34-55-18-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 2RS1 Subtask 34-55-18-720-050 C. Do the functional test of the VOR/MKR (para. MKR Identification and Reception test) (Ref. TASK 34-55-00-720-001). 5. Close-up ________ Subtask 34-55-18-860-050 A. Make sure that the work area is clean and clear of tool(s) and other items.

  EFF : ALL  34-55-18    CES

 

Page 408 Aug 01/07

RECEIVER - VOR/MARKER (3RS1,3RS2) - REMOVAL/INSTALLATION ________________________________________________________ TASK 34-55-31-000-001 Removal of the VOR/MKR Receiver (3RS1, 3RS2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific

blanking caps circuit breaker(s) safety clip(s) access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-55-31-991-001

Fig. 401

3. __________ Job Set-up Subtask 34-55-31-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3RS1 49VU NAV/VOR/1 2RS1 G13 FOR 3RS2 121VU COM NAV/VOR/2 2RS2 K08

  EFF : ALL  34-55-31    CES

 

Page 401 Feb 01/98

Subtask 34-55-31-010-050 B. Get Access (1) Put the access platform in position at the access door 824 in zone 128. (2) Open the access door 824. 4. Procedure _________ (Ref. Fig. 401/TASK 34-55-31-991-001) Subtask 34-55-31-020-050 A. Removal of the VOR/MKR Receiver (1) Loosen the nuts (4). (2) Lower the nuts (4). (3) Pull the VOR/MKR receiver (1) on its rack (3) to disconnect the electrical connectors (2). (4) Remove the VOR/MKR receiver (1) from its rack (3). (5) Put blanking caps on the disconnected electrical connectors (2).

  EFF : ALL  34-55-31    CES

 

Page 402 Feb 01/98

VOR/MKR Receiver Figure 401/TASK 34-55-31-991-001   EFF : ALL  34-55-31    CES

 

Page 403 Feb 01/98

TASK 34-55-31-400-001 Installation of the VOR/MKR Receiver (3RS1, 3RS2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific

access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R

34-55-00-740-002 52-41-00-410-002 34-55-31-991-001

BITE Test of the VOR/MKR Close the Avionics Compartment Doors after Access Fig. 401

3. __________ Job Set-up Subtask 34-55-31-860-050 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position at the access door 824 in zone 128. (2) Make sure that the access door 824 is open.

  EFF : ALL  34-55-31    CES

 

Page 404 Feb 01/02

Subtask 34-55-31-865-051 B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 3RS1 49VU NAV/VOR/1 2RS1 G13 FOR 3RS2 121VU COM NAV/VOR/2 2RS2 K08 4. Procedure _________ (Ref. Fig. 401/TASK 34-55-31-991-001) Subtask 34-55-31-420-050 A. Installation of the VOR/MKR Receiver (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (2). (4) Make sure that the electrical connectors (2) are clean and in the correct condition. (5) Install the VOR/MKR receiver (1) on its rack (3). (6) Push the VOR/MKR receiver (1) on its rack (3) to connect the electrical connectors (2). (7) Engage the nuts (4) on the lugs (5) and tighten. Subtask 34-55-31-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 3RS1 2RS1 FOR 3RS2 2RS2

  EFF : ALL  34-55-31    CES

 

Page 405 Feb 01/98

Subtask 34-55-31-710-050-A C. Do the BITE test of the VOR/MKR (Ref. TASK 34-55-00-740-002). 5. Close-up ________ Subtask 34-55-31-860-051 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 34-55-31-410-050 B. Close Access R

(1) Close the access door 824 (Ref. TASK 52-41-00-410-002). (2) Remove the access platform(s).

  EFF : ALL  34-55-31    CES

 

Page 406 Feb 01/02

RMI - VOR/DME (11FN) - REMOVAL/INSTALLATION ___________________________________________ TASK 34-57-22-000-001 Removal of the VOR/DME RMI (11FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

blanking caps circuit breaker(s) safety clip(s)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-57-22-991-001

Fig. 401

3. __________ Job Set-up Subtask 34-57-22-865-050 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/VOR/DME/RMI 12FN F13 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 Subtask 34-57-22-010-050 B. Remove the thermoformed cover from the center instrument panel.

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-57-22 Page 401   Config-1 May 01/05  CES

 

4. Procedure _________ (Ref. Fig. 401/TASK 34-57-22-991-001) Subtask 34-57-22-020-050 A. Removal of the VOR/DME RMI (1) Loosen the screws (1), do not remove them. (2) Disengage the VOR/DME RMI (2) from its housing. (3) Disconnect the electrical connector (4). (4) Remove the VOR/DME RMI (2). (5) Put blanking caps on the disconnected electrical connectors (3) and (4).

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-57-22 Page 402   Config-1 May 01/05  CES

 

R

VOR/DME RMI Figure 401/TASK 34-57-22-991-001

  EFF : 001-049, 051-099, 101-105, 151-199,  34-57-22 Page 403   Config-1 May 01/07  CES

 

TASK 34-57-22-400-001 Installation of the VOR/DME RMI (11FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------33-13-00-710-001 34-14-00-740-001

Operational Test of the Instrument and Panel Integral Lighting Interface Test of the IR

3. __________ Job Set-up Subtask 34-57-22-865-051 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/VOR/DME/RMI 12FN F13 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 4. Procedure _________ Subtask 34-57-22-420-050 A. Installation of the VOR/DME RMI (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (3) and (4).

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-57-22 Page 404   Config-1 May 01/05  CES

 

(4) Make sure that the electrical connectors are clean and in the correct condition. (5) Connect the electrical connector (4) to the VOR/DME RMI (2). (6) Install the VOR/DME RMI (2) in its housing. (7) Tighten the screws (1). Subtask 34-57-22-865-052 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 12FN, 8FP, 4LF Subtask 34-57-22-710-050 C. Test of the VOR/DME RMI (1) Do the BITE test of the IR1 and IR3 systems (but read only the heading value on the RMI). (Ref. TASK 34-14-00-740-001) (2) Do the operational test of the instrument and panel integral lighting (Ref. TASK 33-13-00-710-001). 5. Close-up ________ Subtask 34-57-22-410-050 A. Put the aircraft back to its initial configuration. (1) Install the thermoformed cover on the center instrument panel. (2) Make sure that the work area is clean and clear of tool(s) and other items.

  R EFF : 001-049, 051-099, 101-105, 151-199,  34-57-22 Page 405   Config-1 May 01/05  CES

 

RMI - VOR/ADF/DME (21FN) - REMOVAL/INSTALLATION _______________________________________________ TASK 34-57-22-000-002 Removal of the VOR/ADF/DME RMI (21FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific

blanking caps circuit breaker(s) safety clip(s)

B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------34-57-22-991-002

Fig. 401

3. __________ Job Set-up Subtask 34-57-22-865-053 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/VOR/DME/RMI 12FN F13 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 Subtask 34-57-22-010-051 B. Remove the thermoformed cover from the center instrument panel.

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-57-22 Page 401   Config-2 Nov 01/08  CES

 

4. Procedure _________ (Ref. Fig. 401/TASK 34-57-22-991-002) Subtask 34-57-22-020-051 A. Removal of the VOR/ADF/DME RMI (1) Loosen the screws (1), do not remove them. (2) Disengage the VOR/ADF/DME RMI (2) from its housing. (3) Disconnect the electrical connector (4). (4) Remove the VOR/ADF/DME RMI (2). (5) Put blanking caps on the disconnected electrical connectors (3) and (4).

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-57-22 Page 402   Config-2 Nov 01/08  CES

 

VOR/ADF/DME RMI Figure 401/TASK 34-57-22-991-002   R EFF : 106-149, 201-249, 301-399, 401-499,  34-57-22 Page 403   Config-2 Nov 01/08  CES

 

TASK 34-57-22-400-002 Installation of the VOR/ADF/DME RMI (21FN) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------33-13-00-710-001 34-14-00-740-001

Operational Test of the Instrument and Panel Integral Lighting Interface Test of the IR

3. __________ Job Set-up Subtask 34-57-22-865-054 A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------49VU NAV/VOR/DME/RMI 12FN F13 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04 4. Procedure _________ Subtask 34-57-22-420-051 A. Installation of the VOR/ADF/DME RMI (1) Clean the component interface and/or the adjacent area. (2) Do an inspection of the component interface and/or the adjacent area. (3) Remove the blanking caps from the electrical connectors (3) and (4).

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-57-22 Page 404   Config-2 Nov 01/08  CES

 

(4) Make sure that the electrical connectors are clean and in the correct condition. (5) Connect the electrical connector (4) to the VOR/ADF/DME RMI (2). (6) Install the VOR/ADF/DME RMI (2) in its housing. (7) Tighten the screws (1). Subtask 34-57-22-865-055 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 12FN, 8FP, 4LF Subtask 34-57-22-710-052 C. Test of the VOR/ADF/DME RMI (21FN) (1) Do the BITE test of the IR system (but read only the heading value on the RMI). (Ref. TASK 34-14-00-740-001) (2) Do the operational test of the instrument and panel integral lighting (Ref. TASK 33-13-00-710-001) 5. Close-up ________ Subtask 34-57-22-410-051 A. Put the aircraft back to its initial configuration. (1) Install the thermoformed cover on the center instrument panel. (2) Make sure that the work area is clean and clear of tool(s) and other items.

  R EFF : 106-149, 201-249, 301-399, 401-499,  34-57-22 Page 405   Config-2 Nov 01/08  CES

 

**ON A/C ALL R

Post SB

34-1147 For A/C 001-004,051-060, SATELLITE NAVIGATION - DESCRIPTION AND OPERATION ________________________________________________

1. _______ General Not applicable. The GPS function is included in the Multi-Mode Receiver (MMR). The GPS is described in AMM 34-36-00 ILS/MMR.

  EFF : ALL  34-58-00    CES

 

Page 1 May 01/05

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