165e094800 (a100 S) R3 Cmm
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SOLID–STATE COCKPIT VOICE RECORDER (SSCVR) MODEL A100S SSCVR CONTROL UNITS MODELS A150, A151, A152, A151B, A152B SSCVR MICROPHONE MODULES MODELS A55, A55B
RECORDER PART NUMBER
S100–0080– ( )
CONTROL UNIT PART NUMBERS
93A151– ( ) 93A152– ( )
PREAMPLIFIER MODULE
93A150–20
REMOTE MICROPHONE MODULES PART NUMBERS
93A055– ( )
REMOTE MICROPHONE MODULES PART NUMBERS
9300A165, –01
COMPONENT MAINTENANCE MANUAL WITH ILLUSTRATED PARTS LIST P/N: 165E0948–00
IN ACCORDANCE WITH FAA TSO–C84 (CONTROL UNITS, PREAMPS & MICS) FAA TSO–C123 (RECORDER) AND ARINC CHARACTERISTIC NO. 557
23-70-02 Rev. 03
Jul. 01/93 01/05 Feb.
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Solid–State Cockpit Voice Recorder (SSCVR) Control Boxes Microphones P/N: 165E0948–00 Rev 03 Jul. 01/05
EXPORT CONTROL STATEMENT SSCVR/SSFDR Parts: “This Solid State Fight Data/Cockpit Voice Recorder Products/ Technology is being exported from the United States in accordance with the Export Administration Regualtions (ECCN #7E994), No License Required (NLR). Diversion contrary to U.S. law is prohibited. In accordance with U.S. Law (Title 15 CFR Part 746 and Supplement No. 1 to Part 774; and Title 31 CFR) resale/reexport or transfer to certain designated countries is prohibited without the prior written consent of the U.S. Department of Commerce.”
ECopyright 2005 by L–3 Communications All rights reserved. No part of this manual may be reproduced or utilized in any form or by any means, electronic or mechanical, including photocopying, recording, or by information storage and retrieval system, without permission in writing. Inquiries should be addressed to: L–3 Communications Aviation Recorders Publications P. O. Box 3041 Sarasota, Florida 34230 Phone: (941) 371–0811 FAX: (941) 377–5591
23-70-02 Rev. 03 Jul. 01/05
Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
THE CONTENTS OF THE RECORDER CAN BE DAMAGED BY ELECTROSTATIC DISCHARGE. PROPER HANDLING MUST BE USED! GENERAL This product and related documentation must be reviewed for familiarization with safety markings and instructions before operation. This instrument was constructed in an ESD (electrostatic discharge) protected environment. This is because most of the semiconductor devices used in this instrument are susceptible to damage by static discharge. Depending on the magnitude of the charge, device substrates can be punctured or destroyed by contact or mere proximity of a static charge. The results can cause degradation of device performance, early failure, or immediate destruction. These charges are generated in numerous ways such as simple contact, separation of materials, and normal motions of persons working with static sensitive devices. When handling or servicing equipment containing static sensitive devices, adequate precautions must be taken to prevent device damage or destruction. Only those who are thoroughly familiar with industry accepted techniques for handling static sensitive devices should attempt to service circuitry within these devices. In all instances, measures must be taken to prevent static charge build–up on work surfaces and persons handling the devices.
BEFORE APPLYING POWER Verify that the product is set to match the available line voltage and the correct fuse is installed. Servicing instructions are for use by service–trained personnel only. To avoid dangerous electric shock, do not perform any servicing unless qualified to do so. Adjustments described in the manual are performed with power supplied to the instrument while protective covers are removed. Energy available at many points may, if contacted, result in personal injury.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SERVICE BULLETIN LIST SERVICE BULLETIN SSCVR001
DATE 09/01/93
INCORPORATES S100–0080–00
DESCRIPTION Software Product Improvement Modification Commencing with Unit Serial Number 254, manufactured 7/93, all newly manufactured A100S SSCVR units will have this modification. This modification is a product improvement, which requires a software revision to IC chip U5 located on the Store Processor PWA. It expands the SSCVR BITE circuitry from “READ–AFTER–WRITE” to include a Continuous Test of all bits within the solid– state memory. Failure of this Continuous Test would be indicated upon execution of the next Preflight Functional Check. This modification is optional. Note: This modification is identified by marking, using yellow paint, R1 on the unit Program Revision Plate.
SSCVR002
11/15/93
S100–0080–00
Alternate Supplier For Underwater Locator Beacons (ULDs) L3 approved Datasonics, Inc. as an alternate supplier of ULDs. Both Dukane and Datasonics ULDs are being installed on newly manufactured A100S recorders. Both ULD types are assigned the same L3 Part Number, 266E0305–00. Also, both ULD types are equipped with a Lithium battery with an expected service life of 6–years.
SSCVR003
02/23/94
S100–0080–00
Introduction Of The 8–Megabit Flash Crash Survivable Store Unit (FCSSU) and The New Type Store Processor PWA The new 8–Megabit FCSSU (P/N 253E0660–00) and Store Processor PWA (P/N 205E1027–00) have been phased into the production of the A100S SSCVR beginning with unit serial number 311, manufactured 12/93. It is not mandatory for an older SSCVR with a 2–Megabit FCSSU (P/N 253E0348– 03) and Store Processor PWA (P/N 205E0601–00) to incorporate this modification. However, should a failure occur in the older FCSSU, it must be replaced with the 8–Megabit FCSSU along with its associated Store Processor PWA. Note: This modification is identified by marking, using yellow paint, a 1 on the SSCVR Modification Plate (Mod Dot 1) and R2 on the Program Revision Plate.
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Service Bulletin List Rev 1 Page 1 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SERVICE BULLETIN LIST (Continued) SERVICE BULLETIN SSCVR004
DATE 06/21/94
INCORPORATES S100–0080–00
DESCRIPTION Notification of Defective Printed Wiring Board (PWB) In Certain Flash Crash Survivable Store Units (FCSSUs) Some 8–Megabit FCSSUs (P/N 253E0660–00) in the A100S SSCVR units (identified with Mod Dot 1) may fail due to a defective PWB furnished by a specific supplier. Beginning June 17, 1994, FCSSUs will be manufactured with PWBs supplied by selected vendors. A100S SSCVR units, beginning with serial number 00452, will have the new FCSSU installed; these units will be identified by a 3 on the SSCVR Modification Plate (Mod Dot 3). It is not recommended to retrofit an SSCVR containing a Mod Dot 1 FCSSU unless it fails. Note: Modification Dot 2 has been reserved by Engineering for a later release.
SSCVR005
03/17/95
S100–0080–00
Introduction of New Flash Crash Survivable Store Unit (FCSSU) Commencing with Unit Serial Number 00622, manufactured 11/94, all newly manufactured A100S SSCVR units will have this modification. To reduce the possibility of certain premature failures and enhance reliability, FCSSU assemblies have had modifications to the Printed Wiring Board (PWB) and to the thermal insulation material. This modification is not mandatory and is not recommended to change the current FCSSU assembly unless a FCSSU related failure occurs. Note: This modification is identified by marking, using yellow paint, a 4 on the SSCVR Modification Plate (Mod Dot 4).
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Service Bulletin List Rev 2 Page 2 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SERVICE BULLETIN LIST (Continued) SERVICE BULLETIN SSCVR006
DATE 06/15/96
INCORPORATES S100–0080–00
DESCRIPTION Introduction of 1–Hr. Fire Protection Flash Crash Survivable Store Unit (FCSSU) All A100S SSCVRs manufactured after 03/96 will have this modification. New FCSSU part numbers 253E1290–00 and 253E1293–00 have been designed to survive 1–hour fire at 1100 degrees Centigrade with a 50,000 British Thermal Units (BTUs) square foot hours thermal flux transfer, and 10 hours at 260 degrees Centigrade. Note: This modification is identified by marking, using yellow paint, a 5 on the SSCVR Modification Plate (Mod Dot 5).
SSCVR007
03/28/95
S100–0080–00
New Software Incorporated into Store Processor Printed Wiring Assembly Commencing with Unit Serial Number 00651, all newly manufactured A100S SSCVR units will have this modification. This modification prohibits the SSCVR from giving a false fault during rapid power cycling. This modification also ensures that all data is erased during a bulk erase. This modification is not mandatory and may be accomplished at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 3 on the Software Program Revision Plate.
SSCVR008
06/10/96
S100–0080–00
New Software Incorporated into Store Processor Printed Wiring Assembly Commencing with Unit Serial Number 00961, all newly manufactured A100S SSCVR units will have this modification. This modification ensures that the fault light is illuminated during a power recovery bulk erase cycle. This modification is not mandatory and may be accomplished at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 4 on the Software Program Revision Plate.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SERVICE BULLETIN LIST (Continued) SERVICE BULLETIN SSCVR009
DATE 07/01/96
INCORPORATES S100–0080–00
DESCRIPTION Introduction of Titanium Flash Crash Survivable Store Unit (FCSSU) All A100S SSCVRs manufactured after 04/96 will have this modification. New FCSSU part number 253E1293–00 reduces the weight of the FCSSU This modification is a product improvement and may be incorporated at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 2 on the SSCVR Modification Plate (Mod Dot 2).
SSCVR010
04/04/96
S100–0080–00
Introduction of a New Underwater Locator Beacon All A100S SSCVRs manufactured after 03/96 will have this modification. New Dukane Underwater Locator Beacon, p/n: DK120, maintains a six–year battery life and can be replaced in the field. Note: Beacons DK100 and DK120 can be identified by Dukane with these part numbers stamped on the beacon’s body.
SSCVR011
07/01/96
S100–0080–00
Addition of EMI Filter Circuit to Aircraft Interface Card All A100S SSCVRs manufactured after 03/96 will have this modification. Enhanced Electo–magnetic Interference filter characteristics by adding filter circuit consisting of L1–L3, and C35–C38 to the Aircraft Interface circuit board, p/n: 205E0597–00. Removed old capacitors C16 & C17 (p/n: 361–01–0001) from Aircraft Interface board. This modification is a product improvement and not a required modification, however it is recommended that this modification be incorporated at the unit’s next scheduled service visit. Note: This modification is identified by marking, using yellow paint, a 6 on the SSCVR Modification Plate (Mod Dot 6).
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Service Bulletin List Rev 2 Page 4 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SERVICE BULLETIN LIST (Continued) SERVICE BULLETIN SSCVR012
DATE 07/02/96
INCORPORATES S100–0080–00
DESCRIPTION Replaced Power Supply, U2, on Aircraft Interface Card
All A100S SSCVRs manufactured after 06/96 will have this modification. Replacement of power supply to enhance reliability. This modification is a product improvement and may be incorporated at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 7 on the SSCVR Modification Plate (Mod Dot 7). SSCVR013
06/15/96
S100–0080–00
New Software Program Incorporated into Store Processor Printed Wiring Assembly Beginning with serial number 1142, all newly manufactured A100S SSCVRs will have this modification. Added software logic for improved handling of SSCVR power down and restart conditions during excessive power interrupts. This modification is not a mandatory change and may be incorporated at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 5 on the Software Program Revision Plate.
SSCVR014 Rev. 01
07/01/97 02/07/97
S100–0080–00
New Software Program Incorporated into Store Processor Printed Wiring Assembly Beginning with serial number 1168, all newly manufactured A100S SSCVRs will have this modification. Enhanced Read–After–Write Reset and unit identification functions. Corrects occasional misidentification of an 8 Meg memory unit as a 2 Meg unit during power interupt conditions. Introduced a procedure for clearing Latched “Memory” faults and Latched “Pointer Not Saved” faults. This modification is not a required modification, and may be accomplished at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 6 on the Software Program Revision Plate.
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Service Bulletin List Rev 2 Page 5 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SERVICE BULLETIN LIST (Continued) SERVICE BULLETIN SSCVR015
DATE 10/01/96
INCORPORATES S100–0080–00
DESCRIPTION Modification to Store Processor Card
All A100S SSCVRs manufactured after 09/96 will have this modification. Modified Store Processor card, p/n: 205E1027–00 to reduce noise levels on the flash memory bus. Redesigned Store Processor by removing components C7 & C13, changing U4 and R10, and adding R18 and R19. Replacement of power supply to enhance reliability. This modification is a product improvement and not a required modification, however it is recommended that this modification be incorporated at the unit’s next scheduled service visit. Note: This modification is identified by marking, using yellow paint, a 8 on the SSCVR Modification Plate (Mod Dot 8).
SSCVR016
04/18/97
S100–0080–00 Only Units with Mod 5 Installed
Introduction of Refurbished FCSSU (253U1290–00) S100–0080–00 A100S SSCVRs (containing MOD5) manufactured after 09/96 will have this modification. FCSSU part number 253U1290–00 has been assigned to identify refurbished memory modules as an alternate replacement for P/N’s 253E1290–00.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
RECORD OF REVISIONS REV NO.
INSERTION DATE
BY
1
July 30/94
CM
2
Mar. 15/00
JG
3
Jul. 01/05
JG
REV NO.
INSERTION DATE
BY
REV NO
INSERTION DATE
BY
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
RECORD OF CHANGES ISSUE Initial
REVISION
DATE OF CHANGE
COMMENTS
00
Feb. 1/93
Initial issue of CMM. No changes have been issued via Service Bulletins (SB’s).
01
July 30/94
This revision includes information presented in SB’s: SSCVR 001, 002, 003 and 004. It also includes the deletion of all information given for the Audio Processor Extender PWA and the Model S151 and S251 Control Units including their respective IPL figures and listings. In addition, miscellaneous changes, updates and corrections were made to text wherever necessary.
02
Mar. 15/00
This revision includes information presented in SB’s: SSCVR 005, 006, 007, 008, 009, 010, 011, 012, 013, 014, 015, 016, and ECO 9282. Removed “Fairchild” from the mast– head. Moved Store Processor PWA to NHA. Updated ULD information. Corrected numerous errors in Numerical Index. Includes the addition of S100–0080–01 model configuration for titanium FCSSU assembly.
03
Jul. 01/05
This revision includes the addition of testing procedures for the Model A150 External Preamplifier. Updated ULD information.
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LIST OF EFFECTIVE PAGES Section
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Date
Title Page
Caution Sheet
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Service Bulletin List
Record of Revisions
Record of Changes
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Table of Contents
List of Illustrations
Introduction
Section
Page 2 3 4 5 6 7 8
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Description and Operation 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
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Page
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Section
Description and Operation (Con’t) 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48
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Testing and Troubleshooting 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124
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401 402 403 404
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Disassembly
Cleaning
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Checks 501 502
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601 602
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Repair
Assembly
Special Tools, Fixtures and Equipment 901 902 903 904
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Illustrated Parts List 1001 1002 1003 1004 1005 1006 1007 1008 1009 1010 1011 1012 1013 1014
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Section
Page 1015 1016 1017 1018 1019 1020 1021 1022 1023 1024 1025 1026 1027 1028 1029 1030 1031 1032 1033 1034 1035 1036 1037 1038 1039 1040 1041 1042 1043 1044 1045 1046 1047 1048 1049 1050 1051 1052 1053 1054
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Illustrated Parts List (Con’t) 1055 1056 1057 1058 1059 1060 1061 1062 1063 1064 1065 1066 1067 1068 1069 1070 1071 1072 1073 1074
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Appendix A Circuit and Wiring Diagrams A1 A2 A3 A4 A5 A6 A7 A8 A9 A10 A11 A12 A13 A14 A15 A16 A17 A18
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Section
Page
Date
A19 A20 A21 A22 A23 A24 A25 A26 A27 A28 A29 A30 A31 A32 A33 A34 A35 A36 A37 A38 A39 A40 A41 A42 A43 A44 A45 A46 A47 A48 A49 A50 A51 A52 A53 A54 A55 A56 A57 A58 A59 A60
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Appendix A Circuit and Wiring Diagrams (Con’t) A61 A62 A63 A64
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Section
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A65 A66 A67 A68 A69 A70
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
TABLE OF CONTENTS SUBJECT/DESCRIPTION
PAGE INTRODUCTION
1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
2. COMPONENT MAINTENANCE MANUAL (CMM) DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . .
2
A. Frontis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
B. Description And Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
C. Testing And Fault Isolation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
D. Disassembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
E. Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
F.
Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
G. Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
H. Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
I.
Special Tools and Test Fixtures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
J.
Illustrated Parts List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
K. Circuit and Wiring Diagrams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
3. DOCUMENT VERIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
4. RECORDER MODIFICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
5. CONTROL UNIT MODIFICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
DESCRIPTION AND OPERATION 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
2. SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
3. SPECIFICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
A. APPLICABLE DOCUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
B. PHYSICAL CHARACTERISTICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
C. ELECTRICAL CHARACTERISTICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
D. ENVIRONMENTAL CHARACTERISTICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
4. TECHNICAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5
A. SYSTEM OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5
B. DATA MONITORING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
C. STORAGE CAPACITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
D. DATA RETRIEVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
E. DATA REPRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
F.
7
BUILT–IN–TEST–EQUIPMENT (BITE) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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PAGE
G. FLASH CRASH SURVIVABLE STORE UNIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
H. CRASH AND FIRE PROTECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8
5. SUPPORT EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8
A. MODEL A860 COCKPIT VOICE RECORDER SYSTEM TEST PANEL . . . . . . . . . . . . . . .
8
B. MODEL A870 CALIBRATED SOUND SOURCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9
C. AUDIO MONITOR ADAPTER (AMA/1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9
6. PERIPHERAL EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10
A. CONTROL UNIT, MODEL A152B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
11
B. CONTROL UNIT, MODEL A151B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
11
C. MICROPHONE MODULES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
13
7. INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
15
A. Control Unit Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
15
B. Remote Microphone Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
15
8. THEORY OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
29
A. SYSTEM THEORY OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
29
(1) Aircraft Interface PWA, P/N 205E0597–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (2) Audio Processor PWA, P/N 205E0598–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (3) Store Processor PWA, P/N 205E0601–00, 205E1027–00 . . . . . . . . . . . . . . . . . . . . . . (4) Flash Crash Survivable Store Unit (FCSSU), P/N 253E0348–00, 253E0660–00 . . B. PWA THEORY OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
29 29 29 30 31
(1) (2) (3) (4)
Aircraft Interface PWA, P/N 205E0597–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Audio Processor PWA; P/N 205E0598–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Store Processor PWA; P/N 205E0601–00, 205E1027–00 . . . . . . . . . . . . . . . . . . . . . . Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
31 33 41 45
TESTING AND TROUBLESHOOTING 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
101
2. A100S RECORDER TESTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
101
3. MODEL A100S OPERATIONAL TEST PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
101
4. CONTROL UNIT, MODEL A151/A151B & A152/A152B TEST PROCEDURES . . . . . . . . . . . .
110
5. CONTROL UNIT, MODEL A151 & A152 WITH MODIFICATION 4 TEST PROCEDURES . .
114
A. FREQUENCY RESPONSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
114
6. CONTROL UNIT, MODEL A151 & A152 WITH MODIFICATION 5 TEST PROCEDURES . .
114
A. FREQUENCY RESPONSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
114
B. MICROPHONE GAIN ALIGNMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
115
7. MODEL A150 PREAMPLIFIER TEST PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
115
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PAGE
TESTING AND TROUBLESHOOTING (Continued) 8. CALIBRATION TEST FOR MODEL A055B REMOTE MICROPHONE MODULES . . . . . . . . .
118
A. PRELIMINARY SET–UP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
119
B. OUTPUT VERIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
119
C. ALTERATE METHOD (used when sound level source is not available) . . . . . . . . . . . . . . .
119
9. MODEL A100S SYSTEM TROUBLESHOOTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
120
10. MODEL A100S PRINTED WIRING ASSEMBLY (PWA) FAULT ISOLATION . . . . . . . . . . . . . .
126
A. AIRCRAFT INTERFACE PWA FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
126
B. AUDIO PROCESSOR PWA FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
127
(1) Audio Processor PWA Fault Isolation Test Set–up . . . . . . . . . . . . . . . . . . . . . . . . . . . . (2) Audio Processor PWA Input Gain Calibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (3) A100S Frequency Response Measurement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C. STORE PROCESSOR PWA FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
128 133 135 136
11. CONTROL UNIT FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
139
DISASSEMBLY 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
301
2. DISASSEMBLY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
301
A. UNDERWATER LOCATING DEVICE (BEACON) (See Figure 301 or IPL Figure 2) . . . .
302
B. MAIN CHASSIS DISASSEMBLY (See Figure 301 or IPL Figure 2) . . . . . . . . . . . . . . . . . . .
304
(1) Dust Cover (2–90) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (2) Front Panel Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (3) Audio Processor PWA Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (4) Store Processor PWA Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (5) Aircraft Interface PWA Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (6) Flash Crash Survivable Store Unit Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (7) FCSSU Elastomeric Shock Mounts, P/N AM003–7 Removal . . . . . . . . . . . . . . . . . . C. MODELS A151/A151B AND A152/A152B CONTROL UNIT DISASSEMBLY (See IPL Figure 7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
304 304 305 306 307 309 311
D. ELECTRONIC CIRCUIT BOARD DISASSEMBLY (See IPL Figures 3–12) . . . . . . . . . . . .
315
313
CLEANING 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
401
2. MATERIALS REQUIRED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
401
3. CLEANING PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
401
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PAGE CLEANING (Continued)
A. PRINTED WIRING ASSEMBLY CLEANING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402
B. CONNECTOR CLEANING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402
C. MACHINED METAL PARTS CLEANING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402
D. UNDERWATER LOCATING DEVICE (Beacon) CLEANING . . . . . . . . . . . . . . . . . . . . . . . . .
402
CHECKS 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501
2. CHECKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501
A. MECHANICAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501
B. MAIN RECORDER ASSEMBLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501
C. ELECTRICAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
502
D. UNDERWATER LOCATING DEVICE (ULD) INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . .
502
REPAIR 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
601
2. REPAIR PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602
A. PRINTED WIRING ASSEMBLIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602
ASSEMBLY 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
701
2. REQUIRED MATERIALS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
701
3. ASSEMBLY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
701
A. GENERAL ASSEMBLY TECHNIQUES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
701
B. GENERAL CIRCUIT BOARD ASSEMBLY (See applicable IPL Figures) . . . . . . . . . . . . . .
704
C. AIRCRAFT INTERFACE PWA, P/N 205E0597–00 (See IPL Figures 2 & 3) . . . . . . . . . . .
704
D. AUDIO PROCESSOR PWA, P/N 205E0598–00 (See IPL Figures 2 & 4) . . . . . . . . . . . . .
706
E. STORE PROCESSOR PWA, P/N 205E0601–00 and P/N 253E1027–00 (See IPL Figures 2, 5 & 6) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
706
F.
FLASH CRASH SURVIVABLE STORE UNIT, (FCSSU) P/N 253E0348–03 and P/N 253E0660–00 (See Figure 702 and IPL Figures 2, 5 & 6) . . . . . . . . . . . . . . . . . . . . .
707
G. FCSSU ELASTOMERIC SHOCK MOUNTS, P/N AM003–7 (See Figure 702 and IPL Figure 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
708
H. MODELS A151/A151B & A152/A152B CONTROL UNIT (See IPL Figure 7) . . . . . . . . . . .
711
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PAGE ASSEMBLY (Continued)
4. STORAGE INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
712
A. STORAGE IN ORIGINAL CONTAINERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
712
B. STORAGE WITHOUT ORIGINAL CONTAINERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
712
SPECIAL TOOLS, FIXTURES, & EQUIPMENT 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
901
A. COCKPIT VOICE RECORDER SYSTEM TEST PANEL, P/N 9300A860 . . . . . . . . . . . . . .
901
B. CALIBRATED SOUND SOURCE, P/N 9300A870 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
902
C. AUDIO MONITOR ADAPTER WITH MODIFICATION 1, P/N 17TES0200 . . . . . . . . . . . . .
902
ILLUSTRATED PARTS LIST 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1001
2. PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1001
3. ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1001
4. EQUIPMENT DESCIGNATOR INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1001
5. NUMERICAL INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1001
6. DETAILED PARTS LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1002
7. MANUFACTURER’S CODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1003
8. CONFIGURATION MATRIX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1007
APPENDIX A CIRCUIT AND WIRING DIAGRAMS 1. INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A1
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LIST OF ILLUSTRATIONS FIGURE NO.
PAGE
Description and Operation Figure 1
Model A100S Solid–State Cockpit Voice Recorder and Associated Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
Figure 2
Model A100S Outline & Dimension Drawing . . . . . . . . . . . . . . . . . . . . . . . . .
4
Figure 3
Model A100S Functional System Block Diagram . . . . . . . . . . . . . . . . . . . . .
6
Figure 4
Cockpit Voice Recorder System Test Panel, P/N 9300A860 . . . . . . . . . . .
8
Figure 5
Calibrated Sound Source, P/N 9300A870 . . . . . . . . . . . . . . . . . . . . . . . . . . .
9
Figure 6
Audio Monitor Adapter/Modification 1, P/N 17TES0200 . . . . . . . . . . . . . . .
10
Figure 7
Front Panel Controls and Indicators for Model A151, A151B, A152 and A152B Control Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
11
Figure 8
Model A151B and A152B Control Unit Configuration Matrix . . . . . . . . . . .
12
Figure 9
Model A55B Microphone Modules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
13
Figure 10
Remote Microphone Configuration Matrix for Model A151/A151B Control Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
14
Figure 11
Wiring Diagram for Model A55B Remote Microphone Assemblies . . . . . .
15
Figure 12
Interwiring Diagram, Recorder A100S, Control Units A151, A151B Remote Microphones A55, A55B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
16
Figure 13
Interwiring Diagram, Recorder A100S, Control Units A152, A152B . . . . .
17
Figure 14
Interwiring Diagram, Recorder A100S, Control Unit A150 . . . . . . . . . . . . .
18
Figure 15
Control Unit Assembly, Model A151, A151–1 and A151B Wiring Diagrams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
19
Figure 16
Control Unit, Model A152 (P/N 93A152–00) Wiring Diagram . . . . . . . . . . .
20
Figure 17
Control Units, Model A152–1 (P/N 93A152–01), Model A152–2 (P/N 93A152–02), Model A152–4 (P/N 93A152–04) Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
21
Control Unit, Model A152B (P/N 93A152–20) S/N 10000 through 10167 without Mod #1 Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . .
22
Control Unit, Model A152B (All P/N’s except 93A152–20), S/N 10000 through 10167 without Mod #1 Wiring Diagram . . . . . . . . . .
23
Control Unit, Model A152B (P/N 93A152–20 only), S/N 10000 through 10167 without Mod #1 and S/N 10168 and up Wiring Diagram . . . . . . .
24
Control Unit, Model A152B (All P/N’s except 93A152–20), S/N 10000 through 10167, without Mod # 1, and S/N 10168 and up Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
25
Control Unit, Model A152B (P/N 93A152–20, 93A152–25, 93A152–50, and 93A152–70) with Mod #1 and Mod #2 Wiring Diagram . . . . . . . . . .
26
Figure 18 Figure 19 Figure 20 Figure 21
Figure 22
23-70-02 List of Illustrations Rev 3 Page vi Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
LIST OF ILLUSTRATIONS (Continued) FIGURE NO.
PAGE
Description and Operation (Continued) Figure 23
Control Unit, Model A152B (P/N 93A152–20 only) S/N 10000 through 10167 without Mod #1 but with Mod #2, Wiring Diagram . . . . . . . . . . . . .
27
Figure 24
Model A150 External Preamplifier (P/N 93A150–00) Wiring Diagram . . .
28
Figure 25
Model A100S System Functional Block Diagram . . . . . . . . . . . . . . . . . . . . .
30
Figure 26
Aircraft Interface PWA Functional Block Diagram . . . . . . . . . . . . . . . . . . . .
31
Figure 27
Audio Processor PWA, PN 205E0598–00, Functional Block Diagram . . .
34
Figure 28
Computational Processor Signal Descriptions . . . . . . . . . . . . . . . . . . . . . . .
38
Figure 29
Store Processor PWA Functional Block Diagram . . . . . . . . . . . . . . . . . . . .
41
Figure 30
Exploded View of Control Unit Assembly,/ A152, A152B . . . . . . . . . . . . . .
45
Figure 31
Dynamic Microphone Preamplifier PWA, 93A263–02 . . . . . . . . . . . . . . . . .
47
Figure 32
Condenser Microphone Preamplifier PWA, 93A266–01 . . . . . . . . . . . . . . .
48
Testing and Troubleshooting Figure 101
Model A100S Operational Test Set–Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
103
Figure 102
Control Unit Test Set–up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
111
Figure 103
Control Unit Test and Adjustment Point . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
111
Figure 104
External Preamplifier, Model A150 (P/N 93A150–20) Assembly Diagram
115
Figure 105
Simulated Microphone Signal Input Test Connections to the Model A150 Preamplifier Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
116
Figure 106
Remote Microphone Test Setup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
119
Figure 107
Audio Processor PWA, P/N 205E0598–00, Component Layout Drawing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
134
Disassembly of Underwater Locating Device (ULD) and Dust Cover Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
302
Figure 302
Disassembly of ULD Cradle Assembly for Beacon Access . . . . . . . . . . . .
303
Figure 303
Disassembly of Model A100S Front Panel Assembly . . . . . . . . . . . . . . . . .
305
Figure 304
Removal of Audio Processor and Store Processor PWAs . . . . . . . . . . . . .
306
Figure 305
Removal of Store Processor PWA From The Flash Crash Survivable Storage Assembly (FCSSU) . . . . . . . . . . . . . . . . . . . . . . . . . . .
307
Figure 306
Removal of Aircraft Interface PWA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
308
Figure 307
Removal of Flash Crash Survivable Storage Unit (FCSSU) . . . . . . . . . . . .
310
Figure 308
Removal of FCSSU Elastomeric Shock Mounts, P/N AM003–7 . . . . . . . .
312
Figure 309
Disassembly of A151/A151B and A152/A152B Control Units . . . . . . . . . .
314
Disassembly Figure 301
23-70-02 List of Illustrations Rev 3 Page vii Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
LIST OF ILLUSTRATIONS (Continued) FIGURE NO.
PAGE
Cleaning Figure 401
Underwater Locating Device (ULD) Beacon Water Switch Location . . . .
403
Figure 701
Installation of Flash Crash Survivable Storage Unit (FCSSU) . . . . . . . . . .
709
Figure 702
Installation of FCSSU Elastomeric Shock Mounts, P/N AM003–7 . . . . . .
710
Assembly
Special Tools and Test Fixtures Figure 901
Cockpit Voice Recorder System Test Panel, P/N 9300A860 . . . . . . . . . . .
902
Figure 902
Calibrated Sound Source, P/N 9300A870 . . . . . . . . . . . . . . . . . . . . . . . . . . .
902
Figure 903
L3 Audio Monitor Adapter With Modification 1, P/N 17TES0200 . . . . . . . .
903
Figure 904
Model A100S SSCVR Typical Test Setup . . . . . . . . . . . . . . . . . . . . . . . . . . .
904
LIST OF TABLES TABLE NO.
PAGE
Introduction Table 1
Modification Descriptions For Model A100S SSCVR . . . . . . . . . . . . . . . . .
5
Table 2
Modification Descriptions For Model A151 And A152 Control Units . . . . .
7
Table 3
Modification Descriptions For Model A151B And A152B Control Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
Testing and Troubleshooting Table 101
Recommended Standard Test Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . .
102
Table 102
Model A100S Operational Test Procedures . . . . . . . . . . . . . . . . . . . . . . . . .
104
Table 103
Model A151 and A152 Control Units, Operational Test Procedure . . . . . .
110
Table 104
Model A150 Preamplifier Unit, Operational Test Procedure . . . . . . . . . . . .
116
Table 105
System Level Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
121
Table 106
Aircraft Interface PWA Fault Isolation Procedure . . . . . . . . . . . . . . . . . . . . .
126
Table 107
Audio Processor PWA Fault Isolation Procedure . . . . . . . . . . . . . . . . . . . . .
128
Table 108
Store Processor PWA Fault Isolation Procedure . . . . . . . . . . . . . . . . . . . . .
136
Table 109
System Level Troubleshooting Procedure for Control Units . . . . . . . . . . . .
139
Table 110
Troubleshooting Procedure for Microphone Preamplifiers 9300A030 and 93A263–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
140
Troubleshooting Procedure for Microphone Preamplifiers 93A263–02 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
140
Troubleshooting Procedure for Microphone Preamplifiers 9300A242, 93A266 and 93A266–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
141
Table 111 Table 112
23-70-02 List of Illustrations Rev 3 Page viii Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
LIST OF TABLES (Continued) TABLE NO.
PAGE
Cleaning Table 401
Cleaning Materials Required . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
401
Repair Materials Required . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
601
Required Assembly Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
702
Repair Table 601 Assembly Table 701
Special Tools and Test Fixtures Table 901
Model A100S Special Tools, Fixtures, and Equipment . . . . . . . . . . . . . . . .
901
ILLUSTRATED PARTS LIST FIGURE NO.
PAGE
Figure 1
SSCVR Configuration, Model A100S, P/N S100–0080–00 . . . . . . . . . . . .
1026
Figure 2
SSCVR Final Assembly, P/N 253E0600–00 . . . . . . . . . . . . . . . . . . . . . . . . .
1030
Figure 3
Aircraft Interface PWA, P/N 205E0598–00 . . . . . . . . . . . . . . . . . . . . . . . . . .
1036
Figure 4
Audio Processor PWA, P/N 205E0598–00 . . . . . . . . . . . . . . . . . . . . . . . . . .
1043
Figure 5
Flash Crash Survivable Store Unit (FCSSU), P/N 253E0348–03, P/N 253E0660–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1050
Figure 6
Store Processor PWA, P/N 205E0601–00, 205E1027–00 . . . . . . . . . . . . .
1052
Figure 7
Control Unit, P/N 93A151–XX, 93A152–XX . . . . . . . . . . . . . . . . . . . . . . . . .
1058
Figure 8
Microphone Preamplifier PWA, P/N 93A263–02 . . . . . . . . . . . . . . . . . . . . .
1062
Figure 9
Microphone Preamplifier PWA, P/N 93A266–01 . . . . . . . . . . . . . . . . . . . . .
1065
Figure 10
Remote Microphone Assembly, P/N 93A055–00, –03,–10, –20, –30, –50, –55 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1068
Remote Microphone Assembly, P/N 93A055–40, –45, –60, –65, –66, –67, –95 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1070
Remote Microphone Assembly, P/N 9300A165, –01 . . . . . . . . . . . . . . . . . .
1072
Figure 11 Figure 12
23-70-02 List of Illustrations Rev 3 Page ix Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
APPENDIX A CIRCUIT AND WIRING DIAGRAMS LIST OF TABLES TABLE NO. Table A1
PAGE Schematic Diagram List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A1
LIST OF ILLUSTRATIONS FIGURE NO. Figure A1 Figure A2 Figure A3 Figure A4 Figure A5 Figure A6 Figure A7 Figure A8
PAGE Model A100S Solid–State Cockpit Voice Recorder, P/N S100–0080–00, System Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . .
A2
Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram P/N 905E0597–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A7
Audio Processor PWA, 205E0598–00, Schematic Diagram P/N 905E0598–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A15
Store Processor PWA, 205E0601–01, Schematic Diagram P/N 905E0601–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A35
Store Processor PWA, 205E1027–00, Schematic Diagram P/N 905E1027–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A51
Dynamic Microphone Preamplifier PWA, P/N 93A263–01, Schematic Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A66
Dynamic Microphone Preamplifier PWA, P/N 93A263–02, Schematic Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A68
Condenser Microphone Preamplifier PWA, P/N 93A266–01, Schematic Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A70
23-70-02 List of Illustrations Rev 3 Page x Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
INTRODUCTION 1. GENERAL This Component Maintenance Manual (CMM) documents the operation of and suggested maintenance for the Model A100S Solid–State Cockpit Voice Recorder (SSCVR), hereinafter referred to as the A100S. This recorder is designed as a maintenance free recorder. There are no periodic adjustments required to maintain this unit. Also covered within this CMM, are the Model A151, A151B, A152 and A152B Control Units and the Model A55B series of condenser microphones. It should be noted that the Model A100S has been designed to take full advantage of all existing peripheral devices originally developed for use with the Model A100/A100A series of tape–based Cockpit Voice Recorders. The Model A100S is considered an “ON CONDITION LRU.” The Model A151B and A152B Control Units are identical to the earlier Model A151 and A152 Control Units, respectively, except that the “B” models use a Microphone Preamplifier PWA designed to operate with a condenser microphone. Also note that the Model A152 and A152B Control Units are equipped with a built–in microphone whereas the Model A151 and A151B are used with an externally mounted microphone. The Model A55B Remote Microphone Modules are condenser type microphones which operate using a low voltage received from its associated “B” model control unit. Information about the Model A151, A151B, A152 and A152B Control Units, the Model A150 Preamplifier, and the Model A55B series of condenser microphones is contained in the Models A100, A100A CMM, ATA No. 23–70–01 and in the Model A100S CMM, ATA No. 23–70–02. All units produced under the above model designations have been assigned configuration part numbers. The listings below can be used to determine the assigned configuration part number for a particular model control unit and microphone. CONTROL UNITS PART NUMBER
MODEL
PANEL COLOR
MICROPHONE
TEST METER ILLUMINATION
93A151–20 93A151–30 93A151–40 93A151–50
A151B A151B A151B A151B
Gray Black Brown (Boeing) Brown (ATR–42)
None None None None
None None None None
93A152–20 93A152–25 93A152–30 93A152–35 93A152–40 93A152–50 93A152–60 93A152–70
A152B A152B A152B A152B A152B A152B A152B A152B
Gray Gray Black Gray Gray Brown (Boeing) Brown (Boeing) Black
Condenser Condenser Condenser Condenser Condenser Condenser Condenser Condenser
None None 28V 28V 5V None 5V None
23–70–02 Introduction
Rev 2 Page 1 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
REMOTE MICROPHONE MODULES
PART NUMBER
MODEL
COLOR
CONNECTOR LOCATION
MICROPHONE
93A055–10
A55B
Black
Condenser
Rear
93A055–20
A55B
Black
Condenser
Side
93A055–30
A55B
Brown (Boeing)
Condenser
Rear
93A055–40
A55B
Gray
Mini–Condenser
Pigtail
93A055–45
A55B
Brown (ATR–42)
Mini–Condenser
Pigtail
93A055–50
A55B
Black
Condenser
Rear
93A055–55
A55B
Black
Condenser
Side
93A055–60
A55B
Gray
Condenser
Pigtail
93A055–65
A55B
Brown (ATR–42)
Condenser
Pigtail
93A055–66
A55B
Gray
Condenser
Pigtail
93A055–67
A55B
Black
Condenser
Pigtail
93A055–95
A55B
Black
Condenser
Pigtail
EXTERNAL PREAMPS PART NUMBER 93A150–20
MODEL A150
PANEL COLOR BLACK
2. COMPONENT MAINTENANCE MANUAL (CMM) DESCRIPTION This CMM consists of a single volume. The manual conforms to the intent and form of the Air Transport Association of America, ATA Specification 100. The manual is written for an audience of operators and both intermediate and depot level maintenance technicians. All functional, electrical and mechanical aspects of the Model A100S SSCVR, the Model A151, A151B, A152 and A152B Control Units and the Model A55B Series of Condenser Microphones are documented; i.e. description, specification, operation, testing, repair, etc. The CMM content is summarized as follows:
A. Frontis Frontis material consists of a title page, service bulletin list, record of revisions, record of changes, list of effective pages, table of contents and this introduction.
B. Description And Operation This section contains the description and operation information for the Model A100S SSCVR, the Model A151, A151B, A152 and A152B Control Units and the Model A55B series of condenser microphones. Line art is used to illustrate the units, their interconnections and functionality. This section also contains the Model A100S theory of operation and associated block diagram drawings.
23–70–02 Introduction
Rev 2 Page 2 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
C. Testing And Fault Isolation This section contains specific checks and tests required to determine the operational condition of a unit that has been removed from service. Also included in the section are tables of required test equipment, test set–up data, procedures and test parameters. Troubleshooting data is presented in a tabular form with each entry related to a specific test and fault isolation task. Component level fault analysis is also provided based upon test–point signal parameters and stage isolation. No Calibration of circuit boards is required within the Model A100S.
D. Disassembly This section provides all the information required to completely disassemble the A100S and its associated control units and remote microphone modules. The steps of each procedure are coordinated with the TESTING AND FAULT ISOLATION section such that no disassembly is dictated unless first proven as the probable cause of failure. All access to subassemblies within the A100S are described so that there is a minimal disturbance to other subassemblies. Each major disassembly task procedure is accompanied with a line art exploded–view of the subassembly area which are cross referenced to the applicable Illustrated Parts List (IPL) drawing for ordering replacement parts.
E. Cleaning This section contains a listing of all required cleaning materials, procedures for cleaning material use, and applicable warnings and cautions related to the use of prescribed cleaning solvents.
F.
Check This section contains the detailed check procedures that may be required during shop maintenance. References are made to fits and clearance for applicable wear tolerances.
G. Repair This section contains a tabular listing at the front of the section of required materials, tools, and fixtures. This section contains all information required to restore a worn or damaged part to a serviceable condition.
H. Assembly This section contains detailed step–by–step procedures describing the complete assembly of the Model A100S SSCVR and the Model A151, A151B, A152 and A152B Control Units. Special circuit component installation instructions along with any testing during assembly is also included as well as storage instructions after assembly.
I.
Special Tools and Test Fixtures This section provides a listing of all required tools, fixtures, and equipment which are not common maintenance tools.
23–70–02 Introduction
Rev 1 Page 3 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
J.
Illustrated Parts List This section contains exploded–view and circuit board component location diagrams along with detailed parts listings for the SSCVR, Control Units and Remote Microphone Assemblies.
K. Circuit and Wiring Diagrams This appendix provides the detailed schematic diagrams of the Model A100S printed wiring assemblies, the Control Unit Microphone Preamplifier PWAs.
3. DOCUMENT VERIFICATION All manual drawings, illustrations, wiring diagrams and schematics were validated against existing engineering source material. All operational and testing procedures have been verified against the actual performance of the unit under test conditions. Also, all procedural data has been previously verified by field usage of the preliminary component maintenance manual. Effectivity of the manual is based on effectivity dates and product serial number. Effectivity of the manual is identified by a list of effective pages in the front of the manual.
4. RECORDER MODIFICATIONS The Model A100S Solid–State Cockpit Voice Recorder may be upgraded and/or modified to provide increased performance and to reflect the most current component technology. Hardware modifications to the recorder are identified on the front panel Modification Plate whereas Software modifications are identified on the front panel Program Revision Plate. The hardware Modification Plate identifies the unit configuration at the time of production and after factory repair. Note: the Program Revision Plate identifies the software program revisions in numerical order; therefore, when a Program Revision Plate is marked REV. 3, it is to be assumed that revisions 1 and 2 have been incorporated. Table 1 provides a description of the Model A100S modifications performed up to the time of this publication as related to Field Service Bulletins.
5. CONTROL UNIT MODIFICATIONS The Model A151 and A152 CVR Control Units, through extensive field experience, have evolved over the years to reflect the most current in component technology. As such, the control units are identified with a Modification Label which identifies the unit configuration at the time of production and after factory repair. Table 2 provides a description of the Model A151 and Model A152 modifications as related to Field Service Bulletins. Table 3 provides a description of the Model A151B and Model A152B modifications as related to Field Service Bulletins.
23–70–02 Introduction
Rev 1 Page 4 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Modification Descriptions for Model A100S SSCVR Table 1
Modification Program Plate Rev. Plate
Field Service Bulletin No.
Description
R1
001
This modification expands the SSCVR Built–In–Test– Equipment (BITE) circuitry from “READ–AFTER–WRITE” to include Continuous Testing of all bits within the Flash Crash Survivable Store Unit (FCSSU) sometimes referred to as the solid–state memory. It requires a software revision to IC chip U5 (EPROM, part number 046E0285– 01E) located on the Store Processor PWA. No change in the A100S operation or Preflight testing is required.
R2
003
This modification introduces the 8–Megabit FCSSU, P/N 253E0660–00, and the new Store Processor PWA, P/N 205E1027–00.
3
004
This modification signals users of a premature failure rate in FCSSUs manufactured using PWBs supplied by a specific supplier. Since there are multiple PWB suppliers, it cannot be determined as to which PWB was used in a FCSSU. Beginning June 17, 1994, all SSCVRs will use FCSSUs manufactured with PWBs supplied by approved vendors. These units will be identified with Mod Dot 3. Note: Modification Dot 2 has been reserved for use by Engineering for a later release.
4
005
This modification introduces the new FCSSU, P/N 253E1245–00, with modifications to the Printed Wiring Board and to the thermal insulation material.
5
006
This modification introduces two new FCSSUs, P/N 253E1290–00 and 253E1293–00, which have been designed to survive 1–hour fire at 1100 degrees Centigrade with a 50,000 BTUs square foot hours thermal flux transfer, and 10 hours at 260 degrees Centigrade.
R3
007
This software modification prohibits the SSCVR from giving a false fault during rapid power cycling and ensures that all data is erased during a bulk erase.
R4
008
This software modification ensures that the fault light is illuminated during a power recovery bulk erase cycle.
1
23–70–02 Introduction
Rev 2 Page 5 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Modification Descriptions for Model A100S SSCVR (Continued) Table 1
Modification Program Plate Rev. Plate 2
Field Service Bulletin No.
Description
009
This modification introduces the Titanium FCSSU, P/N 253E1293–00, which reduces the weight of the FCSSU.
010
This modification introduces a new Dukane Underwater Locator Beacon, P/N DK120, with a 6–year battery life and field replaceability. Can be identified by the part number stamped on the beacon’s body.
6
011
This modification enhances electro–magnetic interference filter characteristics by adding filter circuit consisting of L1–L3 and C35–C38 to the Aircraft Interface circuit board, P/N 205E0597–00. This modification also removed old capacitors C16 & C17, P/N 361–01–0001, from the Aircraft Interface Board.
7
012
This modification replaces power supply U2 on Aircraft Interface Card.
R5
013
This software modification adds software logic for improved handling of SSCVR power down and restart conditions during excessive power interrupts.
R6
014
This software modification enhances Read–After–Write Reset and unit identification functions. Corrects occasional misidentification of an 8 Meg memory unit as a 2 Meg unit during power interrupt conditions. Introduces a procedure for clearing Latched “Memory” faults and Latched “Pointer Not Saved” faults.
015
This modification modifies Store Processor card, P/N 205E1027–00 to reduce noise levels on the flash memory bus. Redesigned Store Processor by removing components C7 & C13, changing U4 and R10, and adding R18 & R19. Replaces power supply to enhance reliability.
016
Informational Introduction of Refurbished FCSSU’s for 253E1290–00 (p/n: 253U1290–00).
8
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Modification Descriptions for Model A151 And A152 Control Units Table 2 MOD NUMBER
FSB
DESCRIPTION
1
101
Rewire Microphone per wirelist P/N 9300WD7.
2
102
Relocation of shield wire.
3
N/A
N/A
4
139
Increase Frequency Bandwidth on Microphone Preamplifier PWA P/N 9300A30.
5
142
Reinstituted Attenuation selection capability through modification of Microphone Preamplifier PWA P/N 9300A30 (Removes Mod 4).
Modification Descriptions for Model A151B And A152B Control Units Table 3 MOD NUMBER
FSB
DESCRIPTION
1
143
Replaces Microphone Preamplifier PWA P/N 93A242 with P/N 93A266.
2
146
Makes direct interchange from A152–02, dynamic, to A152–20, condenser.
151
Changes Microphone Preamplifier PWA P/N 93A266 to P/N 93A266–01: Models A151–50 and A152–35 are Mod 1. All other models are Mod 2.
1 or 2
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
DESCRIPTION AND OPERATION 1. GENERAL This Component Maintenance Manual (CMM) describes the Model A100S Solid–State Cockpit Voice Recorder (SSCVR), the Model A151B/A152B Control Units and the Model A55B series of remote condenser–type microphones. The Model A100S uses solid–state flash memory as the recording medium and is fully compatible with ARINC–557.
MODEL A100S SSCVR
MODEL AI51B CONTROL UNITS
MODEL AI52B CONTROL UNIT
(REMOTE MICROPHONE USED)
(BUILT-IN MICROPHONE)
MODEL A55B REMOTE MICROPHONES
CANISTER STYLE
MOUSE STYLE
FOR STANDARD INSTALLATIONS
FOR CUSTOM INSTALLATIONS
Model A100S Solid–State Cockpit Voice Recorder and Associated Units Figure 1
2. SYSTEM DESCRIPTION The Model A100S SSCVR is a Line Replaceable Unit (LRU) housed in a 1/2 ATR short ARINC 404 style box and weighs less than 23 pounds. It is a four channel high–fidelity recorder designed to continuously acquire and store audio data for a minimum of 30 minutes. It is able to reproduce each channel individually and provides a fifth output which is a combination of the four channels.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
The Model A100S is controlled via standard cockpit panel mounted control units (Models A151, A151B, A152 or A152B) and tested using the Cockpit Voice Recorder System Test Panel, P/N 9300A860. Incorporated into the Model A100S is a built–in–test–equipment (BITE) utility program which measures the frequency and amplitude of a given reference signal and provides a Go or No Go indication. The Model A100S accepts four channels of cockpit audio (Pilot, Co–pilot, Spare and Area microphones) and converts the audio signal to a digital format for storage in a crash protected solid–state memory. Data retrieval from the Model A100S can be accomplished using existing Model A100 & A100A CVR support equipment along with the Audio Monitor Adapter, Mod. 1 (AMA/1), P/N 17TES0200, which was specifically designed for use with the A100S. The Model A100S consists of a chassis and front panel, three Printed Wiring Assemblies (PWAs), and the Flash Crash Survivable Store Unit (FCSSU) which contains the solid–state flash memory used as the recording medium. An Underwater Locator Device (ULD), also referred to as an underwater beacon, is mounted on the front of the recorder.
3. SPECIFICATIONS Specifications for the Model A100S have been developed in close coordination with Aerospace Industry regulatory agencies. As such, the A100S meets or exceeds the requirements of technical standards TSO–C84, TSO–C123, EUROCAE ED–56 and EUROCAE ED–55 (crash protection).
A. APPLICABLE DOCUMENTS The following documents form a part of, or are referenced, within this CMM: (1)
TSO–C84
Federal Aviation Agency Technical Standard Order Minimum Performance Standard for Cockpit Voice Recorders.
(2)
TSO–C123
Federal Aviation Agency Technical Standard Order Minimum Performance Standard for Cockpit Voice Recorders.
(3)
EUROCAE MOPS ED–55
European Organization for Civil Aviation Electronics Minimum Operational Performance Specification for Flight Data Recorder Systems; establishes crash protection standards for all crash protected recorders.
(4)
EUROCAE MOPS ED–56
European Organization for Civil Aviation Electronics Minimum Operational Performance Specification for Cockpit Voice Recorder Systems.
(5)
ARINC Characteristic 557
Airborne Voice Recorder
(6)
RTCA DO–160C
Environmental Conditions and Test Procedures for Airborne Equipment.
(7)
RTCA DO–178A
Software Considerations in Airborne Systems to Level 3.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
B. PHYSICAL CHARACTERISTICS The Model A100S is housed in an ARINC 404 1/2 ATR short box. The A100S physical attributes are presented in the following listing. Refer to Figure 2 for the Model A100S outline and dimension drawing. (1)
Dimensions: (a)
Height: — 7.5 inches (including dust cover)
(b)
Width:
— 5.00 inches (front panel)
(c)
Depth:
— 12.5 inches (behind front panel 14.5 inches (including panel/handle)
(2)
Weight:
–00 –01
18.4 +/– .5 pounds 15.9 +/– .5 pounds
(3)
Case: Stainless Steel, International Orange, Reflective Striping, English/French Markings, Raised Lettering
(4)
Main Connector: DPX036571–0059
(5)
Front Panel Connector: 1/4 inch phone jack
(6)
Underwater Locating Device: Dukane Beacon (P/N: DK120) or Datasonics Beacon (P/N: ELP–362D). Both beacons have an expected battery life of six years and are directly interchangeable.
C. ELECTRICAL CHARACTERISTICS (1)
Power Requirements: 115 Volts, 400 Hz ac or +28 Volts dc.
(2)
Power Level: 12W, maximum.
(3)
Output Power: +18 Vdc Preamplifier power, 100 mA short–circuit protected.
(4)
Analog Inputs: Three crew microphones (150 to 3500 Hz bandwidth); One area microphone (150 to 5000 Hz bandwidth).
(5)
Analog Outputs Monitored:
(6)
Discrete Inputs: (a) (b) (c)
1) 600–ohm headphone (short–circuit protected); 2) Test Meter indicator and 3) Lamp Driver.
Bulk Erase (two), Test, Record Enable.
D. ENVIRONMENTAL CHARACTERISTICS (1)
Operating Temperature: –55 to +70
C
(2)
Non–Operating Temperature: –65 to +85 C
(3)
Altitude (Operating): –1000 to 55,000 feet
(4) (5)
Vibration (Operating): Doc. DO–160C, Para. 8.2.2 and 8.4; Fig. 8–6 Test Curve C, C’ Penetration: ED–55 – 500 lbs/10ft/1/4” probe
(6) (7) (8)
Static Crush: Fire Protection: Impact:
ED–55 – 5,000 lbs ED–55 – 50,000 BTUs/sq.ft./hours, 30 min. ED–55 – 3400 g’s., 6.5 ms
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
STANDARD HALF ATR SHORT CASE
C.G.
3.56
.156 .125 5.25
NAME PLATE
2.40
HANDLE
MONITOR
ULD MOUNTING BRACKET
UNDERWATER LOCATING DEVICE
C.G. CANNON CONNECTOR NO. DPXB-57-34P-0101 MODIFICATION RECORD PLATE
POLARIZING KEYS
PROGRAM REVISION PLATE
HOLD DOWN HOOKS PER ARINC SPEC. NO. 404
2.40 HOLD DOWN HOLES PER ARINC SPEC. NO. 404
Model A100S Outline & Dimension Drawing Figure 2
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
4. TECHNICAL DESCRIPTION The Model A100S is fully compatible with ARINC 557. As such, it is a direct replacement for all previous tape–based cockpit voice recorders.
A. SYSTEM OVERVIEW The Model A100S Cockpit Voice Recorder System is composed of the recorder and an externally mounted control unit utilizing either a built–in or externally mounted microphone (refer to Figure 3). Interconnection between the recorder and the control unit is accomplished using aircraft wiring. The A100S consists of the following four main assemblies: Aircraft Interface PWA, Audio Processor PWA, Store Processor PWA and the crash protected solid–state memory assembly which is designated as the Flash Crash Survivable Store Unit (FCSSU). The A100S is connected to aircraft wiring via a 57–pin, DPX style input connector and its Aircraft Interface PWA. The Aircraft Interface PWA provides for all input and output signals. The Model A100S provides for four microphone inputs which are connected as follows: the cockpit spare microphone input to Channel 1, the co–pilot microphone input to Channel 2, the pilot microphone input to Channel 3, and the area microphone input to Channel 4. The audio from the area microphone may originate at the control unit (built–in) or at a remote microphone; this audio has a bandwidth of 150 to 5000 Hertz. The other three channels are supplied audio from the pilot audio selectors and have a bandwidth of 150 to 3500 Hertz. The spare audio input applied to Channel 1 may be from a third crew member or from a PA system. The Audio Processor PWA receives the audio signals from the four channels and converts each to a digital byte oriented format for storage. The digital signals are applied to the Store Processor PWA for encoding and storage in the FCSSU. Incorporated into the A100S is a “record” jumper. During bench test of the A100S, the jumper enables the record function of the recorder to be turned off, thereby allowing playback of the recorded data. Once playback is initiated, the unit immediately begins replaying the recorded data. The A100S provides the control unit with +18 Vdc operating power, monitor audio, and an indicator signal. The monitor audio is accessible at the front panel of both the control unit and the A100S via a 600–ohm phone plug. The indicator signal is used to drive the test meter in the DO–160B control unit, Model A151 or Model A152. The +18 Vdc is a short–circuit protected 100 ma line. All control units (Model A151, A151B, A152 or A152B) provide the A100S with three control signals: Erase A, Erase C, and Push_To_Test. The Erase A and Erase C signals are used to initiate a bulk erasure of the crash protected solid–state memory. The bulk erase button must be pressed for more than two seconds, and then released, to initiate the bulk erase function. Additionally, landing gear and brake interlocks are provided in the aircraft wiring to prevent memory erasures during flight conditions. The Push_To_Test signal is activated as long as the “TEST” button on the control unit is pressed. During this time, a 640 Hz +20 Hz signal is generated which is used to test the throughput circuitry of all the audio channels. In turn, the A100S recorder provides an INDICATOR signal which drives the GO / NO GO display on the control unit.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
INDICATOR SIGNAL
ERASE A
MONITOR AUDIO
CONTROL UNIT
ERASE C AIRCRAFT WIRING INTERLOCKS (LANDING GEAR MUST BE DOWN AND BRAKE LOCKED TO ALLOW MEMORY TO BE ERASED)
PUSH_TO_TEST
GEAR
AREA MICROPHONE
BRAKE +18 V OPERATING POWER 5
RECORD LIGHTING AREA MICROPHONE PILOT MICROPHONE
CO-PILOT MICROPHONE SPARE MICROPHONE (TO 3RD CREW MEMBER OR PA SYSTEM)
CHANNEL 4 2
MONITOR AUDIO
CHANNEL 3
2
2 CHANNEL 2 2 CHANNEL 1 2
+18 V
AIRCRAFT INTERFACE PWA
2 INDICATOR 2
27.5 VDC OR 115 VAC
CHASSIS GROUND
AUDIO PROCESSOR PWA STORE PROCESSOR PWA FCSSU
(Flash Crash Survivable Store Unit)
ASSEMBLY
(AKA, CRASH PROTECTED SOLID-STATE MEMORY)
MODEL A100S Model A100S Functional System Block Diagram Figure 3
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
B. DATA MONITORING While mounted in the aircraft, previously recorded data cannot be monitored from the Model A100S. This is a security feature implemented to protect the rights of pilots and other flight crew members. The combined audio of the four channels can be monitored during recording using headsets plugged into the 1/4–inch, 600–ohm phone jack mounted on the front panel of either the A100S or its control unit. Also, when being tested at the standard cockpit test bench set up, combined playback data can be monitored using the speaker mounted within the Cockpit Voice Recorder System Test Panel, P/N 9300A860.
C. STORAGE CAPACITY The Model A100S storage media is designated as the Flash Crash Survivable Store Unit (FCSSU). The FCSSU contains CMOS Flash memory with enough storage capacity to allow a minimum of thirty minutes of continuous recording.
D. DATA RETRIEVAL The recorder must be removed from the aircraft and the dust cover removed to retrieve data from the recorder. With the dust cover removed, the Audio Monitor Adapter (AMA/1), P/N 17 TES0200, is plugged into the edge mounted Playback/Monitor connector (J6) on the Audio Processor PWA. This connection allows a user to monitor individual channel data or combined channel data. The fidelity of the A100S audio data output at the AMA/1 is such that only an external amplifier and speaker are required to allow quality analysis of the recorded data.
E. DATA REPRODUCTION A standard cassette or reel–to–reel tape recorder can be used to produce a high fidelity copy of the Model A100S recorded data. To do so, the inputs of the copy recorder are connected to any one of the 1/4–inch monophone jacks located on the Audio Monitor Adapter (AMA/1) front panel. Depending upon the type recorder used for copying, the A100S data can be copied one channel at a time, or all individual channels can be copied simultaneously.
F.
BUILT–IN–TEST–EQUIPMENT (BITE) Built–In–Test–Equipment (BITE) capability is provided to establish and monitor the mission fitness of the hardware. The built–in–test feature has been designed to perform a continuous test of all bits within the solid–state memory located in the Flash Crash Survivable Store Unit (FCSSU). The test tone used for unit verification is developed on the Audio Processor PWA and applied to each channel individually where it is processed, stored in memory, read from memory, and checked for expected frequency and amplitude. The built–in–test is initiated by pressing and holding the “TEST” push–button located on the front panel of the Model A151, A151B, A152 and the A152B Control Units. The GO /NO GO meter is also located on the front panel of these control units.
G. FLASH CRASH SURVIVABLE STORE UNIT The Flash Crash Survivable Store Unit (FCSSU) is the memory storage assembly of the Model A100S. Electrical interface to the FCSSU is made by the Store Processor via a single connector with 50 contacts. The Store Processor PWA is mounted to the FCSSU assembly. Dimensions of the FCSSU are: 7.37” x 7.28” x 4.73”. FCSSU P/N 253E0348–03, 253E0660–00, 253E0992–00 and 253E1290–00 weigh approximately 17 pounds. FCSSU P/N 253E1293–00 weighs approximately 13 pounds.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
H. CRASH AND FIRE PROTECTION The Flash Crash Survivable Store Unit (FCSSU) is triple protected by an inner casing of thermal insulation, the inner steel casing, and the outer stainless steel casing. The inner and outer cases for the light weight model FCSSU, P/N 253E1293–00, are comprised of titanium in place of steel. This construction enables the Model A100S to meet the rigorous crash protection requirements given in specification ED–55.
5. SUPPORT EQUIPMENT The Model A100S has been designed to take advantage of all existing cockpit voice recorder support equipment. Additionally, the Audio Monitor Adapter (AMA/1), P/N 17TES0200, has been specially designed for the A100S to allow connection to any one of the four audio output channels or to the combined audio output which is the sum of the four channels.
A. MODEL A860 COCKPIT VOICE RECORDER SYSTEM TEST PANEL The operation of the A100S is verified using the standard test panel originally designed for the test and calibration of the Model A100 series of tape–based cockpit voice recorders. Using the standard L3 Cockpit Voice Recorder System Test Panel, P/N 9300A860 (refer to Figure 4), audio signals can be applied to individual channels for testing and analysis. Additionally, the A860 Cockpit Voice Recorder System Test Panel can be used: 1) to activate the built–in–test utility of the Model A100S, 2) to initiate the Bulk Erase feature of the recorder, and 3) to replay previously recorded audio.
VOICE RECORDER FAIRCHILD COCKPIT SYSTEM TEST PANEL N O R M A L
A C T U A T E
BULK ERASE TEST
TEST
BIAS TRAP ADJUST
SYS UNIT
O U T P U T
MODE GND FAULT
700
1kHz
ROLL OFF I N P U T
GND SHORT
AII3 BULK ERASE
-6 dB
A T T E N U A T I O N
-12 dB
-24 dB
C.U.
EXT
1
A55
MIC
J2
ALL TEST
REC.
INT
O U T P U T
BULK ERASE
BYPASS REVERSED GND
HEADSET
VOLUME
LOCAL AMP AC
MIC CAL DC
2A
DC
OFF
3
4 SHORT
C.U.
CHANNEL SELECT RECORD BIAS
ON
POWER
2
-18VDC +18VDC
2A
I N P U T
AC
J3
CONTROL OFF UNIT
GTP PROBE (FOR GROUND TEST)
Cockpit Voice Recorder System Test Panel, P/N 9300A860 Figure 4
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
B. MODEL A870 CALIBRATED SOUND SOURCE Microphone performance can be evaluated through the use of the Model A870 Calibrated Sound Source, P/N 9300A870 (refer to Figure 5).
MICROPHONE
CALIBRATED SOUND SOURCE P/N 9300-A870
CALIBRATE
USE 1 kHz SET TO 0 dB
Calibrated Sound Source, P/N 9300A870 Figure 5 C. AUDIO MONITOR ADAPTER (AMA/1) The AMA with Modification1, P/N 17TES0200 (refer to Figure 6), is used along with the L3 Cockpit Voice Recorder System Test Panel to extract individual channel audio data from the Model A100S for sampling and/or copying to a portable recorder. The Model A100S must have its dust cover removed to allow access to the Audio Processor PWA. The AMA/1 cable connector is mated to the Audio Processor PWA Playback/Monitor connector (J6) which is located at the board’s outer edge just below center. This connection routes the four audio channels and the Combined Audio channel (summation of Channels 1 through 4) to the AMA/1 for output individually as follows: From SSCVR
To AMA/1
Signal Amplitude (see note)
Channel 3 (signal AUDIO_3)
PILOT jack
1 Vrms + 10%
Channel 2 (signal AUDIO_2)
CO–PILOT jack
1 Vrms + 10%
Channel 1 (signal AUDIO_1)
SPARE jack
1 Vrms + 10%
Channel 4 (signal AUDIO_4)
AREA jack
1 Vrms + 10%
Combined Audio Channel (signal COMBINED_AUDIO)
COMBINED jack
1.45 Vrms + 10%
Note: the signal amplitudes given are based on the A100S applied input of 3 Vrms for Channels 1, 2 and 3 and 2 Vrms for Channel 4. As a general rule, the signal amplitude available at the AMA/1 SPARE (Channel 1), CO–PILOT (Channel 2 ) and PILOT (Channel 3) jacks is 33% of the A100S applied input whereas the signal amplitude available at the AREA jack (Channel 4) is 50% of the unit applied input. The signal amplitude available at the AMA/1 COMBINED jack is approximately 1.45 times the highest individual channel amplitude present at the AMA/1. Also, the signal amplitude measured at the AMA/1 COMBINED jack should be identical to that measured at the Headset jack on both the Model A100S front panel or its associated Control Unit front panel.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
10 CONTACT CONNECTOR L3 P/N 0639800365 30-INCH FLAT-RIBBON CABLE
DIMENSIONS: HEIGHT - 7.55 INCHES WIDTH - 4.05 INCHES DEPTH - 1.72 INCHES CABLE - 30 INCHES
Audio Monitor Adapter/Modification 1, P/N 17TES0200 Figure 6 Because of the enhanced fidelity of the Model A100S, the AMA/1 along with an external amplifier and speaker are the only instruments required to provide quality analysis of the recorded audio. Individual channels are accessed at their respective jacks on the AMA/1 using a cable fitted with a 1/4–inch monophone jack at one end and an appropriate type connector for the device to be connected at the other. Copies of the A100S recorded audio may be made by connecting the cable to the input of a standard cassette recorder or similar device. After the desired connections have been made and before applying power to the A100S, verify that the CVR System Test Panel RECORD BIAS/OFF toggle switch is set to position OFF (down) to prevent writing over existing data. To play back the full 30 minutes of recorded audio, simply apply power to the A100S. To begin replaying the data recorded since the recorder was last powered–up, press the ALL TEST pushbutton on the CVR System Test Panel.
6. PERIPHERAL EQUIPMENT The Model A100S has been designed to take full advantage of all existing peripheral devices originally developed for use with the Model A100/A100A series of tape–based Cockpit Voice Recorders. In addition, the Model A100S has also been designed to accommodate the Model A151B and A152B Control Units which are DO–160B compliant. Each control unit is a standard ATR, panel–mounted unit that provides remote control of the Model A100S. These units include a Microphone Preamplifier PWA designed for use solely with condenser type microphones (Model A55B microphones). Except for the Microphone Preamplifier PWA designed to operate with a condenser microphone, the Model A151B and A152B Control Units are identical to the earlier Model A151 and A152 Control Units, respectively, which use a dynamic Microphone Preamplifier PWA and one of the Model A55 series of dynamic microphones. The main external difference to be noted between control unit models (see Figure 7) is that the Model A152 and A152B Control Units have a built–in microphone whereas the Model A151 and A151B units connect to an externally mounted microphone.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
A. CONTROL UNIT, MODEL A152B The Model A152B Control Unit, P/N 93A152–XX (refer to Figure 7), contains the area microphone (condenser), TEST switch, bulk ERASE switch, test meter, 600–ohm headset jack, and a Microphone Preamplifier PWA, P/N 93A266–01 (refer to Appendix A for schematic). The TEST switch and indicating test meter provide the capability to test the four channels and the headset jack provides a means to monitor the playback of all four recorded channels. The bulk ERASE switch is used to erase the stored audio data after a routine flight, and will only work when the landing gear is down, the weight of the plane is resting on the landing gear, and the parking brake is engaged. To prevent accidental erasures, a time–delay circuit makes it necessary to hold the switch down for two seconds to start the erasure process. The Control Unit utilizes aircraft wiring for connection to the recorder unit. As previously stated, the Model A152B Control Unit, P/N 93A152–XX, is easily identified by its built–in condenser microphone. The last two digits of the control unit part number identify the unit color and other pertinent features provided (refer to Figure 8 for the Model A152B Control Unit Configuration Matrix). MICROPHONE (A152/A152B ONLY)
2.250 +.000 -.030
FUNCTION SWITCHES
TEST METER
HEADSET JACK
 Â
TEST
ERASE + .002 1.125 -
HEADSET 600 OHMS
COCKPIT VOICE RECORDER +.015 5.375 + .000 5.750 - .020
+ .562 - .000 .015 .18
MODEL A152 AND A152B CONTROL UNIT FRONT PANEL ILLUSTRATED MODEL A151 AND A151B CONTROL UNITS SAME AS ABOVE EXCEPT NO BUILT–IN MICROPHONE
Front Panel Controls and Indicators for Model A151, A151B, A152 and A152B Control Units Figure 7 B. CONTROL UNIT, MODEL A151B The Model A151B Control Unit, P/N 93A151–XX, is identical to the Model A152B described above except that the built–in condenser microphone is eliminated and an externally mounted condenser microphone is used. This type control unit is used in installations where, due to space restrictions, its optimum mounting location would cause a built–in microphone to be ineffective. Refer to Figure 8 for the Model A151B Control Unit Configuration Matrix.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
PANEL COLOR
MICROPHONE
METER ILLUMINATION
PRODUCTION PART NUMBER 93A150-20 93A151-00 93A151-01 93A151-20 93A151-30 93A151-40 93A151-50 93A151-70 93A152-20 93A152-25 93A152-30 93A152-35 93A152-40 93A152-50 93A152-60 93A152-70
Model A151B and A152B Control Unit Configuration Matrix Figure 8
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
C. MICROPHONE MODULES Figure 9 illustrates the Model A55B Microphone Modules typically used with the Model A152B and A151B Control Unit. Also shown are two microphones used in some custom installations. These microphones are the electric condenser type microphones which operate using a low voltage, approximately +6.2V, received from its associated control unit Microphone Preamplifier PWA. Except for the two omni–directional models, P/N 93A055–40 and 93A055–45, all others are cardioid type directional microphones which have a heart–shaped response pattern that gives a nearly uniform response for a range of about 180 in one direction and a minimum response in the opposite direction. As illustrated, two basic styles of the microphone are offered. One is the canister style which is a panel mounted microphone with connection terminals at its side or rear. The other is the mouse style which comes with a pigtail for hard–wiring to the control unit. This smaller mouse type microphone is suitable for remote mounting on the glare shield or windshield post where panel space is not available for any other type installation. Note: various configurations of these microphones are available for unique installations; refer to Figure 10 for the Remote Microphone Configuration Matrix for specifics. CONDENSER MICROPHONES
CANISTER STYLE
93A055–10, –20, –30, –50, –55
MOUSE STYLE
93A055–40, –45, –60, –65, –66, –67, –95
USED IN MOST INSTALLATIONS
9300A165
9300A165–01
USED IN CUSTOM INSTALLATIONS
Model A55B Microphone Modules Figure 9
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE COLOR
MICROPHONE TYPE
CONNECTOR LOCATION
CURRENT PRODUCTION PART NUMBER 93A055-10 93A055-20 93A055-30 93A055-40 93A055-45 93A055-50 93A055-55 93A055-60 93A055-65 93A055-66 93A055-67 93A055-95
NOTES: 1. DIRECTIONAL MICROPHONES ARE THE CARDIOID TYPE WHICH HAS A HEART-SHAPED RESPONSE PATTERN THAT GIVES A NEARLY UNIFORM RESPONSE FOR A RANGE OF ABOUT 180 IN ONE DIRECTION AND A MINIMUM RESPONSE IN THE OPPOSITE DIRECTION. 2. MICROPHONES 93A055-40, -45 ARE OMNI-DIRECTIONAL TYPES.
Remote Microphone Configuration Matrix for Model A151/A151B Control Units Figure 10
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
7. INSTALLATION The Model A100S SSCVR is an environmentally hardened unit housed in an ARINC 404 1/2 ATR short box painted international orange. The A100S does not require external shock mounting for installation into the aircraft. The A100S is fully compatible with ARINC Specification 557 and is directly interchangeable with all existing cockpit voice recorder installations. The A100S is connected to its Control Unit by way of the aircraft wiring. As illustrated in Figure 12 and Figure 13, the A100S and the Control Unit electrical interconnections are standard with the only variation being with the Control Unit and whether it has an internal or external microphone.
A. Control Unit Wiring The Model A151B and the Model A152B Control Units are recommended for use in a new A100S system. The main difference between the two is the Model A152B has a built–in condenser microphone whereas the Model A151B utilizes an externally mounted condenser microphone. Other differences are in regard to front panel color and meter illumination input voltage. Refer to Figure 15 through Figure 23 for the Model A100S and associated Control Unit wiring diagrams.
B. Remote Microphone Wiring The wiring diagrams for the Model A55B series of remote microphones listed in Figure 10 and used in conjunction with the Model A151B Control Unit are shown in Figure 11. CONNECTOR AS VIEWED FROM SOLDER TERMINAL END
FLAT ON THREADS
MICROPHONES: 93A055-10 93A055-20 93A055-30 93A055-50 93A055-55
CONNECTOR SHELL
.75 REF
PIN 1 PIN 2 WHITE WIRE RED WIRE
BLACK WIRE
SHIELD
MICROPHONES: 93A055-40 93A055-45
ALPHA FIT-221-3/16 WHITE HEAT SHRINK TUBING 7/8" LONG
24 BLACK PLASTIC COVERED 7/32 STRAND WIRE. (MIL-W-16878D) MICROPHONE CABLE DETAIL
SPLICE BLACK WIRE WHITE WIRE
WHITE WIRE RED WIRE SHIELD
MICROPHONES: 93A055-60 93A055-65 93A055-67
WHITE WIRE BLACK WIRE
MICROPHONES: 93A055-66 93A055-95
WHITE WIRE BLACK WIRE
SHIELD
SHIELD
+DC SUPPLY (TO PIN P) - AUDIO OUT (TO PIN N) SHIELD
SIGNAL GND & SHIELD (TO PIN M)
DC SUPPLY (TO PIN P) SIGNAL OUTPUT (TO PIN N) SIGNAL GND & SHIELD (TO PIN M) DC SUPPLY (6V) SIGNAL OUTPUT SIGNAL GND
Wiring Diagrams for Model A55B Remote Microphone Assemblies Figure 11
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Description and Operation Rev 1 Page 15 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
VOICE RECORDER UNIT, ALL A100S MODELS
STANDARD INTERWIRING PER ARINC SPEC 557 TO 115 VAC HOT (400HZ) TO AC COLD
1 AMP
TO 27.5VDC
5 AMPS
*3
*4
CONTROL UNIT ALL MODELS A151 OR A151B PUSH_TO_TEST PRE-AMP POWER GND PRE-AMP POWER +18 VDC INDICATOR + INDICATOR CHASSIS GROUND ERASE SWITCH A" ERASE SWITCH C" OUTPUT - LOW OUTPUT - HIGH MIKE CABLE SHIELD MIKE INPUT - HI MIKE INPUT - LO FILTER COMMON FILTER 1.000 HZ
*5
AUDIO JACK - LO AUDIO JACK - HI
(RESERVED) (RESERVED) SUGGESTED SPARE NO. 1 SUGGESTED SPARE NO. 2 SUGGESTED SPARE NO. 3 6 DB ATTENUATION ATTENUATOR_ COMMON 12 DB ATTENUATION 24 DB ATTENUATION
A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k p q r s t
*4
SPARE MICROPHONE - TO 3RD CREW MEMBER OR PA SYSTEM
*7 TO CO-PILOT MICROPHONE
TO PILOT MICROPHONE
AREA MICROPHONE
*6 *4
MICROPHONE MODEL A55 OR A55B MIKE OUTPUT HI (AUDIO) MIKE OUTPUT LO ( DC IN ) MIKE SHIELD (CONNECTOR SHELL)
NOTES:
1 *2 *3 *4 *5 *6 *7 *8
*2
1 2
*7 *8
BRAKE
GEAR
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. 52. 53. 54. 55. 56. 57.
115 VAC HOT OUT 115 VAC HOT IN AC COMMON COLD
AUDIO OUT LO AUDIO OUT HI BIAS JUMPER BIAS JUMPER +27.5 Vdc INPUT (reserved) PUSH_TO_TEST PREAMP POWER GND PREAMP POWER +18 Vdc REG INDICATOR + INDICATOR CHASSIS GROUND (reserved) (reserved)
SUGGESTED SPARE NO. 1 SUGGESTED SPARE NO. 2 SUGGESTED SPARE NO. 3
LO CHANNEL 1 HI
LO
CHANNEL 2
HI
LO CHANNEL 3 HI LO HI
CHANNEL 4
ERASE A ERASE C
Recommended minimum wire size is #22; however, wire size #24 is acceptable except for long-run power leads where #18 wire is recommended (pins 2,3,17, & 19). Ground connection to be within 1 foot of pin 17. Only one power source to be wired per aircraft. If 115 Vac, 400 Hz is supplied, no connection is to be made to pin #9. If 27.5 Vdc is supplied, no connection is to be made to pin #3. Short pins 1 & 2. Single Ground Point. Short pins S & T for piston aircraft only. Wiring shown for standard fixed attenuation of 18 dB per ARINC 557. Control Units A151 or A152 to be used with Mike Modules A55 only. Control Units A151B or A152B to be used with Mike Modules A55B only. Model 40 Series & Model 60 Series microphone output cabling colors are reversed. On the Model 40 Series, the white wire is the high" (audio side); on the Model 60 Series, the white wire is the LO" (dc in ).
Interwiring Diagram, Recorder A100S, Control Units A151, A151B, Remote Microphones A55, A55B Figure 12
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Description and Operation Rev 1 Page 16 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
STANDARD INTERWIRING PER ARINC SPEC 557 TO 115 VAC HOT (400HZ) TO AC COLD
1 AMP
TO 27.5VDC
5 AMPS
VOICE RECORDER UNIT, ALL A100S MODELS
*3
*4
CONTROL UNIT, ALL MODELS A152 OR A152B PUSH_TO_TEST PRE-AMP POWER GND PRE-AMP POWER +18 VDC INDICATOR + INDICATOR CHASSIS GROUND ERASE SWITCH A" ERASE SWITCH C" OUTPUT - LOW OUTPUT - HIGH (RESERVED) MIKE INPUT - HI MIKE INPUT - LO FILTER COMMON FILTER 1.000 HZ
*6
AUDIO JACK - LO AUDIO JACK - HI 5V LAMP - HOT LAMP - COMMON/COLD 28V LAMP - HOT
INTERNAL MIKE - HIGH INTERNAL MIKE - LOW SUGGESTED SPARE NO. 1 SUGGESTED SPARE NO. 2 SUGGESTED SPARE NO. 3
6 DB ATTENUATION ATTENUATOR COMMON 12 DB ATTENUATION 24 DB ATTENUATION
A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s t
*4
*2
SPARE MICROPHONE - TO 3RD CREW MEMBER OR PA SYSTEM
*5
*8 TO CO-PILOT MICROPHONE
TO PILOT MICROPHONE
AREA MICROPHONE
*7 *4
BRAKE
NOTES:
1 *2 *3 *4 *5 *6 *7 *8
GEAR
1. 115 VAC HOT OUT 2. 115 VAC HOT IN 3. AC COMMON COLD 4. 5. AUDIO OUT LO 6. AUDIO OUT HI 7. BIAS JUMPER 8. BIAS JUMPER 9. +27.5 Vdc INPUT 10. (reserved) 11. 12. PUSH_TO_TEST 13. PREAMP POWER GND 14. PREAMP POWER +18 Vdc REG 15. INDICATOR + 16. INDICATOR 17. CHASSIS GROUND 18. (reserved) 19. (reserved) 20. 21. 22. 23. SUGGESTED SPARE NO. 1 24. SUGGESTED SPARE NO. 2 25. SUGGESTED SPARE NO. 3 26. 27. 28. 29. 30. LO 31. CHANNEL 1 32. HI 33. 34. 35.LO 36. CHANNEL 2 37.HI 38. 39. 40. 41.LO 42. CHANNEL 3 43.HI 44. 45.LO 46. CHANNEL 4 47.HI 48. 49. 50. 51. 52. 53. 54. 55.ERASE A 56. 57.ERASE C
Recommended minimum wire size is #22; however, wire size #24 is acceptable except for long-run power leads where #18 wire is recommended (pins 2,3,17, & 19). Ground connection to be within 1 foot of pin 17. Only one power source to be wired per aircraft. If 115 VAC, 400 Hz is supplied, no connection is to be made to pin #9. If 27.5 VDC is supplied, no connection is to be made to pin #3. Short pins 1 & 2. Single Ground Point. If meter illumination is included in Control Unit, supply voltage from lighting bus to proper pins. Short pins S & T for piston aircraft only. Wiring shown for standard fixed attenuation of 18 dB per ARINC 557. Jumper wires per ARINC 557, 1/2 inch, maximum length.
Interwiring Diagram, Recorder A100S, Control Units A152, A152B Figure 13
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Description and Operation Rev 1 Page 17 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
STANDARD INTERWIRING PER ARINC SPEC 557 EXTERNAL PREAMP A150 TO 115 VAC HOT (400HZ) TO AC COLD
VOICE RECORDER UNIT, ALL MODELS A100S
1 AMP
*3
TO 27.5 VDC
5 AMPS
*4
EXTERNAL PREAMP MODEL A150 PRE-AMP POWER (+18 VDC) PRE-AMP POWER GND PRE-AMP OUT - HI PRE-AMP OUT - LO ATTENUATION MASTER CHASSIS GROUND
J2
24 DB ATTENUATION 12 DB ATTENUATION 6 DB ATTENUATION
MIC SIGNAL INPUT MIC SUPPLY (+6.2 VDC) MIC SHIELD (GND)
J1
A B C D E F G H J K L M
*2
A B C
TO 3RD CREW MEMBER OR PA
MODEL A55B MICROPHONE (ANY PART MODEL) MIC 6 VDC SUPPLY MIC GND (SHIELD) MIC OUTPUT
*4
1
TO CO-PILOT
2
TO PILOT
AREA MICROPHONE
*4
NOTES:
1 *2 *3 *4
1 2 3 4 5 6 7 8 9 10 11
115 VAC HOT OUT 115 VAC HOT IN AC COMMON COLD
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
PUSH_TO_TEST PREAMP POWER GND PREAMP POWER +18 VDC REG INDICATOR + INDICATOR CHASSIS GROUND
42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57
AUDIO OUT LO AUDIO OUT HI BIAS JUMPER BIAS JUMPER +27.5 VDC INPUT (with inverter)
SUGGESTED SPARE NO. 1 SUGGESTED SPARE NO. 2 SUGGESTED SPARE NO. 3
LO HI
LO HI
CHANNEL 1
CHANNEL 2
LO HI LO HI
CHANNEL 3
CHANNEL 4
ERASE A ERASE C
Recommended minimum wire size is #22; however, #24 wire is acceptable except for long-run power leads where #18 wire is recommended (pins 2,3,17, & 19) Ground connection to be within 1 foot of pin 17. Only one power source to be wired per aircraft. If 115 VAC, 400 Hz is supplied, no connection is to be made to pin #9. If 27.5 VDC is supplied, no connection is to be made to pin #3. Short pins 1 & 2 and be sure inverter is used. Single Ground Point.
Interwiring Diagram, Recorder A100S, Control Unit A150 Figure 14
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Description and Operation Rev 1 Page 18 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
CONNECTOR A9300-241 GY RD
METER
BK GRN BK WH BK
E D M N P
WH/BK WH/BK VIO RD
B K L C
WH WH/RD WH/GRN BL
P r t q
WH/GR BK RD BL BRN GR
A F G H W V
+ F
PRE-AMP
5B
BK
TEST SWITCH
No Nc C
HEAD PHONE JACK
E
K
L
C
P
No Nc C
N P
B
q
BK
ERASE SWITCH
M
t r
Z b
BL
BK
RD GRN
MODEL A151B CONTROL UNIT, P/N 93A151-20, 93A151-30 and 93A151-50 Optional Wires METER
+ P M F
BK C B
PRE-AMP
HEAD PHONE JACK
K
5B
TEST SWITCH
ERASE SWITCH
N
L
T
No Nc C
S
p t
BK No Nc
BL
C
RD GRN
BK
r q
BK
GY BK BK BRN WH BK BK RD WH/BK WH/BK VIO YW OR WH WH/RD WH/GRN BL WH/GY BK BL RD BRN GY
PLUG PIN Z b E D N P M C B K L S T P r t q A F H G W V
MODEL A151, A151-1 CONTROL UNIT, P/N 93A151-00, and 93A151-01
Control Unit Assembly Model A151, A151–1 and A151B Wiring Diagrams Figure 15
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Description and Operation Page 19 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
CONNECTOR
MICROPHONE
METER
GY BK
Z b
RD WH
f g
BK
+
BK GRN
WH
N P
P.C. BOARD
BK
M
BK
GRN
RD
C B 5B S
K
L
T
No
WH WH/RD
r
WH/GRN BL
t q
C ERASE SWITCH
WH/BK WH/BK VIO YW OR
p
Nc
N P
**
M
F
BK
TEST SWITCH
E D
C B K L S T P r t q
BK WH/GY No
BK BL RD BRN GY
BL
Nc
BK
C
RD GRN
A F H G W V
**
PHONE JACK
MODEL A152 CONTROL UNIT, P/N 93A152-00 **
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152 (P/N 93A152–00) Wiring Diagram Figure 16
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Description and Operation Page 20 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
CONNECTOR
MICROPHONE
GY BK WH
Z b
*
METER WITH ILLUMINATION
+
BK GRN
RD
N P M
RD BK
WH BK
BK
BK
F
BK
RD WH/BK WH/BK VIO YL OR
C B
P.C. BOARD
5B
TEST SWITCH
S
K
L
T p r
No Nc
t
C
q
BK
ERASE SWITCH
No BK
Nc
BL RD
C GRN
E D
N P
**
M C B K L S T
WH WH/RD WH/GRN BL
P r t q
WH/GY BK BL RD BRN GY
A F H G W V
**
PHONE JACK
MODEL A152-1 CONTROL UNIT, P/N 93A152-01, MODEL A152-2 CONTROL UNIT, P/N 93A152-02, MODEL A152-4 CONTROL UNIT, P/N 93A152-04 *
METER ILLUMINATION A152-1 Pins Z & b (28 V) A152-2 Not Applicable A152-4 Pins Z & Y (5 V)
**
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Units Model A152–1 (P/N 93A152–01), Model A152–2 (P/N 93A152–02), Model A152–4 (P/N 93A152–04) Wiring Diagram Figure 17
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Description and Operation Page 21 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
CONNECTOR
MICROPHONE
METER
+
GY RD
Z b
WH RD
g f
BK GRN
BK
P.C. BOARD
P
J N E S
BK WH
M
E D P N
**
M
F RD
C 5B L
TEST SWITCH K
VI WH/BK
B
WH/BK
No
C L B K
Nc C BK
ERASE SWITCH
WH/GY No BK
C
BK BL RD BRN GY
BL
Nc RD GRN
A F H G W V
**
PHONE JACK
MODEL A152B CONTROL UNIT, P/N 93A152-20, S/N 10000 - 10167 WITHOUT MOD. #1 **
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (P/N 93A152–20) S/N 10000 through 10167 without Mod #1 Wiring Diagram Figure 18
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Description and Operation Page 22 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE WH RD
CONNECTOR
METER WITH ILLUMINATION
GY RD
+
BK GRN
RD
BK
BK
P
J N E S
WH
M
F
BK
RD
5B L K
*
E D P N
**
M
P.C. BOARD
C TEST SWITCH
Z b
VI WH/BK
B
WH/BK
No
C L B K
Nc C BK WH/GY ERASE SWITCH
No
BK BL RD BRN GY
BL
Nc
BK
C
RD GRN
A F H G W V
**
PHONE JACK
MODEL A152B CONTROL UNIT, ALL PART NUMBERS EXCEPT P/N 93A152-20, S/N 10000 - 10167 WITHOUT MOD. #1
*
METER ILLUMINATION 93A152-30 & 93A152-35 Pins Z & b (28 V) 93A152-40 & 93A152-60 Pins Z & Y (5 V) Other Part Numbers - Not Applicable
**
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (All P/N’s except 93A152–20) S/N 10000 through 10167 without Mod #1 Wiring Diagram Figure 19
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Description and Operation Page 23 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE CONNECTOR GY RD
METER
BK GRN
+
WH RD BK
F
WH
M
BK
N
P.C. BOARD
B 5B
E
BK
P WH/BK WH/BK VI
K L
TEST SWITCH
RD C
WH WH/RD
No p
Nc q
C
WH/GR
t
BL
r
ERASE SWITCH
WH/GY No
BK RD BL BRN GY
BL
Nc
BK
C
RD GRN
Z b E D g f M N
**
P B K L C p r t q
A F G H W V
**
PHONE JACK
MODEL A152B CONTROL UNIT, P/N 93A152-20 ONLY, S/N 10000 - 10167 WITHOUT MOD. #1 **
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (P/N 93A152–20 only) S/N 10000 through 10167 without Mod #1 and S/N 10168 and up Wiring Diagram Figure 20
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Description and Operation Page 24 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE
CONNECTOR GY BK
METER WITH ILLUMINATION
+
BK GRN GRN BK
F
RD
WH
M N
BK
E P
5B
B L
BK
BL WH/BK WH/BK
K
P.C. BOARD
VIO RD
C
TEST SWITCH q
WH WH/RD
P No
WH
t
WH/GRN BL
r
Z b
*
E D M N P
**
B K L C P r t q
Nc C WH/GY ERASE SWITCH
No BK
Nc
BK
BL
RD BL BRN GY
RD
C GRN
A F G H W V
PHONE JACK
MODEL A152B CONTROL UNIT, ALL EXCEPT P/N 93A152-20, S/N 10000 - 10167 WITHOUT MOD. #1 *
METER ILLUMINATION 93A152-30 & 93A152-35 Pins Z & b (28 V) 93A152-40 & 93A152-60 Pins Z & Y (5 V) Other Part Numbers - Not Applicable
**
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (All P/N’s except 93A152–20) S/N 10000 through 10167 without Mod # 1 and S/N 10168 and up Wiring Diagram Figure 21
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Description and Operation Page 25 Feb. 01/93
**
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE
CONNECTOR
METER
GY BK
+
BK GRN BK
F RD
M E
N
BK
P B L
5B
WH BK
WH WH/BK WH/BK
K
VIO RD
P.C. BOARD
C
WH WH/RD
TEST SWITCH
P q
No
WH/GRN BL
t r
Z b
E D M N
*
P B K L C P r t q
Nc C WH/GY
BK ERASE SWITCH
No BK
Nc
BK
BL
RD BL BRN GY
RD
C BK
A F G H W V
PHONE JACK
MODEL A152B CONTROL UNIT, P/N 93A152-20, P/N 93A152-25, P/N 93A152-50, P/N 93A152-70 S/N 10000 - 10167 WITH MOD. #1 AND MOD #2 *
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (P/N 93A152–20, 93A152–25, 93A152–50, and 93A152–70) with Mod #1 and #2 Wiring Diagram Figure 22
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Description and Operation Page 26 Feb. 01/93
*
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE WH RD
CONNECTOR
METER
GY RD
+
BK GRN
BK
BK WH
P
J N E S
M
BK
RD
C 5B L K
E D P N
*
M
P.C. BOARD
F
TEST SWITCH
Z b
VI WH/BK
B
WH/BK
C L B K
No Nc C
WH/GY
BK ERASE SWITCH
No BK
Nc
BK BL
BL RD BRN GY
RD
C GRN
A F H G W V
PHONE JACK
MODEL A152B CONTROL UNIT, P/N 93A152-20 ONLY, S/N 10000 - 10167 WITHOUT MOD. #1 BUT WITH MOD #2 *
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (P/N 93A152–20 only) S/N 10000 through 10167 without Mod #1 but with Mod #2, Wiring Diagram Figure 23
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Description and Operation Page 27 Feb. 01/93
*
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE PREAMPLIFIER PWA, P/N 93A266-01
GRN
CONNECTOR J1 GRN BLK WHT
M N
P
L
p q
WHT/BLK VIO VIO
K C
t r
MIC GND (SHIELD)
A
MIC SIGNAL
B
MIC SUPPLY (+6.2V)
B D
PRE-AMP PWR GND PRE-AMP OUT LOW
C
PRE-AMP OUT HI)
A
PRE-AMP PWR HI)
M K
6 dB ATTENUATION 12 dB ATTENUATION
H
24 dB ATTENUATION
E
ATT. COMMON
CONNECTOR J2 WHT/BLK
B
C
WHT WHT/RED WHT/GRN BLU
MODEL A150 EXTERNAL PREAMPLIFIER MODULE
Model A150 External Preamplifier (P/N 93A150–00) Wiring Diagram Figure 24
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Description and Operation Rev 1 Page 28 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
8. THEORY OF OPERATION The theory of operation given for the Model A100S describes the functionality of the A100S both at the system level and at the PWA level. System level theory of operation describes the general operation of the system as a whole. Refer to the Model A100S Functional Block Diagram given in Figure 25 during the following discussions. The PWA level theory of operation describes the electrical circuitry of the major functional groupings contained on the individual PWAs. Detailed PWA schematic diagrams are provided in Appendix A of this manual.
A. SYSTEM THEORY OF OPERATION The Model A100S SSCVR is composed of three PWAs and a Flash Crash Survivable Store Unit (FCSSU). The three PWAs are the Aircraft Interface PWA, the Audio Processor PWA, and the Store Processor PWA (refer to Figure 25). (1)
Aircraft Interface PWA, P/N 205E0597–00 The Aircraft Interface PWA connects the aircraft wiring to the A100S via its 57–pin connector J1. Power regulation, lightning protection, RF attenuation and discrete signal conditioning functions are performed on this PWA. The A100S operates from either a 115V, 400 Hz ac input or a 27.5V dc input. The input voltage is regulated to furnish +12V, –12V, + 5V, and +18V dc operating power. All regulated voltages are short–circuit protected. The Aircraft Interface PWA also generates a /LOW_LINE signal which is used to power down the unit in the case of a power failure. The Aircraft Interface PWA is mounted to the chassis using five screws with standoffs; its circuitry includes transformer T1 and the input/output 57–pin connector J1. Connections to the Spare PWA slot (J3), the Audio Processor PWA (J4), and the Store Processor PWA (J5) are made via connector J2/P2 which is a 50–pin, printed circuit board style connector that is hard–wired to the Aircraft Interface (ribbon) Cable Assembly (W1). Note: the Spare PWA slot is not used. The Aircraft Interface PWA measures 4.4 by 7.1 inches.
(2)
Audio Processor PWA, P/N 205E0598–00 The Audio Processor PWA accepts four channels of cockpit audio and converts the audio to a digital byte oriented format suitable for storage in the FCSSU solid–state memory. The four audio inputs are conditioned, amplified, and equalized as necessary. The resulting signals are converted to digital pulse code modulation (PCM). The PCM signals are passed to the Store Processor PWA via a FIFO (First–In–First–Out) memory. The process is reversed for playback. The Audio Processor PWA connects to the other PWAs when its 64–pin edge connector (P1) mates to connector J4 of the Aircraft Interface Cable Assembly (W1). The dimensions of the Audio Processor PWA are 4.4 by 7.1 inches.
(3)
Store Processor PWA, P/N 205E0601–00, 205E1027–00 The Store Processor PWA, using specially designed algorithms, encodes the data and routes it to the FCSSU for storage. In addition to data encoding, the Store Processor PWA provides functional controls for bulk erase, test and playback. The Store Processor PWA measures 4.8 by 5.3 inches and is mounted to the side of the FCSSU assembly using four screws. When mounted, it electrically connects to the other PWAs via a 6.5–inch, hard–wired ribbon cable assembly (W2) fitted with a 26–pin plug (P5) that mates to connector J5 of the Aircraft Interface Cable Assembly W1. It electrically connects to the FCSSU assembly via a 50–pin connector, designated J2.
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Description and and Operation Operation Description Page 29 29 Rev 2 Page Feb.15/00 01/93 Mar.
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
(4)
Flash Crash Survivable Store Unit (FCSSU), P/N 253E0348–03, 253E0660–00 The hardened memory array, comprised of devices known as CMOS Flash Memory, is electrically erasable and programmable. The nonvolatile memory is protected within a hardened, insulated metal housing to ensure survivability in the event of a crash.
FROM CONNECTOR P1 VIA AIRCRAFT WIRING
/FAULT
PUSH_TO_TEST
TEST
BIAS JUMPER IN
/LOW_LINE
ERASE “A”
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
/RECORD ERASE
CHANNEL 1 (LO)
CHANNEL 1 (LO)
CHANNEL 1 (HI)
CHANNEL 1 (HI) CHANNEL 2 (LO)
CHANNEL 2 (LO)
CHANNEL 2 (HI)
CHANNEL 2 (HI)
CHANNEL 3 (LO) CHANNEL 3 (LO) CHANNEL 3 (HI)
AIRCRAFT INTERFACE PWA P/N 205E0597–00
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
P5/W2 (CABLE W2
HARD WIRED TO STORE PROCESSOR
PWA; CONNECTS TO J5 OF AIRCRAFT INTERĆ FACE CABLE ASSEMBLY W1)
PLAYBACK / MONITOR EDGE– TEST CONNECTOR J6
AUDIO PROCESSOR PWA P/N 205E0598–00
J2/P2
DIGITAL AUDIO LINK
/OE
STORE PROCESSOR PWA (SEE NOTE)
/WE SEL (7..0) 8 ADR (20..0) 21 D (7..0)
CHANNEL 3 (HI) CHANNEL 4 (LO) CHANNEL 4 (HI)
CHANNEL 4 (LO) CHANNEL 4 (HI)
8 AIRCRAFT INTERFACE CABLE CONNECTOR J4
COMBINED_AUDIO
AIRCRAFT INTERFACE CABLE CONNECTOR J5
FLASH CRASH SURVIVABLE STORE UNIT (FCSSU) ASSEMBLY (SEE NOTE)
+5V
115 VAC IN (H)
+5V
+12V, 5%
AC COMMON (C)
+12V
CHASSIS GROUND
+27.5 VDC INPUT
–12V
CHASSIS GROUND
CHASSIS GROUND COMBINED_AUDIO
TO AIRCRAFT WIRING VIA CONNECTOR P1 BIAS JUMPER OUT ERASE “C” AUDIO OUT – LO AUDIO OUT – HI
J71 2
TO FRONT PANEL PHONE JACK
NOTES 1.
INDICATOR + INDICATOR –
PRE–AMP PWR GROUND PRE–AMP PWR +18VDC REG 2.
INITIAL MODEL A100S UNITS WERE EQUIPPED WITH A FCSSU, P/N 253E0348-03, WHICH USES 2-MBIT FLASH MEMORY CHIPS, AND A STORE PROCESSOR PWA, P/N 205E0601-00, DESIGNED TO INTERFACE WITH IT. BEGINNING 12/93, A NEW FCSSU, P/N 253E0660-00, WHICH USES 8-MBIT FLASH MEMORY CHIPS, AND A REDESIGNED STORE PROCESSOR PWA, P/N 205E1027-00, WERE MANUFACTURED. THESE ASSEMBLIES WERE FIRST INSTALLED IN UNIT SERIAL NUMBER 311. BEGINNING 03/96, TWO NEW FCSSUs, P/N 253E1290-00 AND 253E1293-00 WERE MANUFACTURED. THE NEW FCSSUs PROVIDE BETTER FIRE PROTECTION BEGINNING 04/96, A NEW FCSSU, P/N 253E1293-00, WHICH USES TITANIUM, REDUCING THE WEIGHT OF THE FCSSU. REFER TO FIGURE A1 IN APPENDIX A OF THIS MANUAL FOR DETAILED SYSTEM WIRING DIAGRAM.
Model A100S Functional Block Diagram Figure 25
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B. PWA THEORY OF OPERATION The A100S PWA theory of operation is presented as follows: Aircraft Interface PWA, Audio Processor PWA, and Store Processor PWA. The control units and Microphone Preamplifier PWAs follow. Detailed schematic diagrams of each A100S PWA and control unit Microphone Preamplifier PWA are given in Appendix A at the rear of this manual. Also, refer to the detail system wiring diagram, given in Figure A1. (1)
Aircraft Interface PWA, P/N 205E0597–XX (See Figure A2) The Aircraft Interface PWA connects the aircraft wiring to the A100S using a 57–pin DPX style connector designated J1. Power regulation, lightning protection, RF attenuation and discrete signal conditioning functions are performed on this PWA. (a)
DC Regulator; U2 The A100S operates from either 115V, 400 Hz ac power or 27.5V dc power (refer to Figure 26). Power circuits provide regulated +5V, +12V and –12V dc outputs. The –12V output is used to power a DC–to–DC “Up” Converter, U3, which generates +18V dc power for the A100S Control Unit. All regulated voltages are short–circuit protected. The unregulated 27.5V dc input is also used as the /LOW_LINE signal which is continually monitored to detect a power failure and thereby provide an early warning to allow circuitry to be properly powered down. /LOW_LINE TP4
27.5 VDC 115 VAC (H)
+5 VDC
TP2
+12 VDC
REGULATOR TP3
115 VAC (C)
–12 VDC
DISTRIBUTED TO OTHER PWAs TO PROVIDE EARLY WARNING OF A POWER FAILURE. REGULATED POWER DISTRIBUTED THROUGH–OUT A100S
U2 DC–DC “UP” CONVERTER
+18VDC
TO CONTROL UNIT
U3
CHANNEL 1 H/L CHANNEL 2 H/L CHANNEL 3 H/L
EMI FILTER 2 L1 – L3 C35 – C38
2
AUDIO CHANNEL CONDITIONING
2
CHANNEL 4 H/L
2
BIAS JUMPER IN
CR1 – CR8
PUSH_TO_TEST
TO AUDIO PROCESSOR PWA P/N 205E0597–XX
CHANNEL 3 H/L CHANNEL 4 H/L
TO AUDIO PROCESSOR PWA P/N 205E0597–XX
/RECORD ERASE TEST
DISCRETE SIGNAL CONDITIONER
ERASE “A”
CHANNEL 1 H/L CHANNEL 2 H/L
U4
COMBINED_AUDIO AUDIO FAULT DETECTOR
/FAULT TO FRONT PANEL PHONE JACK
AUDIO OUT (H) AUDIO OUT (L) 27.5 VDC
/NO FAULT U1, U4 INDICATOR DRIVER
INDICATOR +
E3
Q1
TO 1.0 mA CONTROL UNIT
Aircraft Interface PWA Functional Block Diagram Figure 26
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(b)
Audio Conditioner; CR1 – CR8 The four audio inputs are lightning protected by CR1 – CR8. The audio channels are routed to the Audio Processor PWA for conversion to a digital byte oriented format and subsequent storage, via the Store Processor PWA, in the crash protected solid– state memory.
(c)
Discrete Signal Conditioner; U4 Three discrete inputs; BIAS JUMPER IN, ERASE “A”, and PUSH_TO _TEST are lightning protected and converted to drive HCMOS type loads by U4 and associated circuitry. After conversion, the “BIAS JUMPER IN” signal is designated as /RECORD and is used to disable the record function when playback of the data is required. Signal /RECORD will be pulled up to +5V with no connection made to the BIAS JUMPER IN line. When the BIAS JUMPER IN line is connected to the BIAS JUMPER OUT line, /RECORD will be driven low. The Erase “A” signal is used to initiate the Bulk Erase function. When ERASE “A” is left floating, ERASE is driven low. When ERASE “A” is connected to ERASE “C” (Erase button on Control Unit depressed), ERASE will be pulled up to +5V. The Push_To_Test signal is used to activate the A100S built–in–test circuitry and enables the Audio Fault Detector, U1 and U4.
(d)
Audio Fault Detector; U1, U4 The audio fault detector is used to determine the status of the COMBINED_AUDIO signal and to generate a 1.0 milliampere signal to drive the control unit fault indicator. The Test Tone signal at COMBINED_AUDIO is attenuated by R1 and R2. This signal is then buffered and band–pass filtered (640 Hz) by U1 and associated circuitry. The filtered signal is then rectified and filtered by CR12 and C14 for comparison to the 2.5V reference by U4. This signal, /NO FAULT, turns on the current source for +INDICATOR. CR17 and CR18 provide level shifting and over–voltage protection for the comparator, U4.
(e)
Indicator Driver; Q1 The test indicator output (+INDICATOR) circuitry provides a 1 milliampere drive current for the standard Control Unit meter or a 28V incandescent lamp. This signal is present if the following conditions are met: /FAULT in the non–Fault state TEST active (PUSH_TO_TEST driven Low) Test Tone present at AUDIO OUT–HI
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(2)
Audio Processor PWA; P/N 205E0598–XX (See Figure A3) The primary function of the Audio Processor PWA is to digitize the four audio signals received from the Aircraft Interface PWA and to interface with the Store Processor PWA. In doing so, the Audio Processor PWA accepts four channels of cockpit audio and then converts the audio to a digital byte oriented format suitable for storage in the crash protected solid–state memory. Refer to Figure 27 during the following discussion. The Audio Processor PWA can be viewed as a series of conversion circuits which are enacted upon the four channels of audio signals coming from the cockpit. The conversions can be divided into two functional groupings: an analog section and a digital section. (a)
Analog Section The analog section consists of record circuits, playback circuits, and test tone circuits. 1)
Record Circuits; U6, U9, U10 The four audio channel inputs (CHANNEL_#_HI and CHANNEL_#_LO) are applied to separate signal transformers (T1, T2. T3, and T4) to provide an ungrounded differential input. The voltage ratio of the transformer is 1:1 and it is connected to invert the input signal which corrects for the inversion in the record shaping circuit. The transformer secondaries are terminated using a 10k ohm level control (trimmer) potentiometer as follows: T1/R1, T2/R3, T3/R2, and T4/R4. Each potentiometer is used to adjust the reference level for its respective channel. The adjusted output signals of the level control potentiometers and the test tone signals are applied to the input buffers. The buffers provide a non–inverting gain of 7.7. This gain allows the input level of each channel to be adjusted from 0.1 to 1V rms while providing a 0.5V rms signal level to the record signal shaping input. The input buffers also provide an inverting gain of one to the test tone signals. The record signal shaping circuits provide a bridged, twin tee notch for each channel. The notch is centered at 1 kHz and has an attenuation of 4 dB. Additionally, the shaping circuits for Channels 1, 2, and 3 contain high–pass filter circuits which peak the signals by 3.5 dB (nominal) at 3.5 kHz. This peaking is provided to compensate for the frequency response of the encoder/decoder filter. The record signal shaping circuits provide an output signal level of 0.315V rms at 1 kHz to the analog input of the encoder/decoders.
2)
Playback Circuits; U5, U4, U14 The encoder/decoders analog output provides a signal level of 1V rms at the output of the playback signal shaping circuits. The playback signal shaping circuits provide the inverse of the notch in the record shaping circuit.
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ANALOG SECTION PLAYBACK MONITOR J6 USED WITH AUDIO MONITOR ADAPTER (AMA/1) FOR TEST PURPOSES
AUDIO 1
AREA OUT
AUDIO 2
VOICE 1 OUT
AUDIO 3
SIGNAL SHAPING
AUDIO 4
AREA OUT
VOICE 2 OUT
COMBINED AUDIO U14
VOICE 3 OUT AREA IN
P4
COMBINED AUDIO
OUTPUT BUFFER
10k-OHM LEVEL CONTROL POTENTIOMETERS TO AIRCRAFT INTERFACE PWA
T1
CH 1 IN (LO/HI) TRANSFER AND LEVEL CONTROL CIRCUITS
CH 2 IN (LO/HI) CH 3 IN (LO/HI)
T2 T3
U5, U4, Q1, Q2
VOICE 1 OUT VOICE 2 OUT VOICE 3 OUT
R1 R3 R2
INPUT BUFFER
SIGNAL SHAPING
R4
CH 4 IN (LO/HI) T4
U6
U9, U10
VOICE 1 IN VOICE 2 IN VOICE 3 IN
TEST TONE 1 TEST TONE 2 TEST TONE 3 TEST TONE 4
TEST TONE SECTION
SWITCH
BUFFER
U7
U15
4
LOW PASS FILTER
LEVEL CONTROL
CR3, CR6
TEST TONE SQ WV (640HZ) TEST ENABLE
TEST
TEST
ERASE /RECORD TO AIRCRAFT INTERFACE PWA
ERASE /RECORD
+12V
+12V
–12V
–12V
+5V CHASSIS GROUND
+5V CHASSIS GROUND
Audio Processor PWA, PN 205E0598–00, Functional Block Diagram Figure 27 (sheet 1 of 2)
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DIGITAL SECTION
AREA CLK 12K FS 12K RFS 12K XFS
12K ENCODER/ DECODER
PCM–8 AREA IN/OUT
2
U25 PCM–8 VOICE 1 IN/OUT
12K FS
COMPUTATIONAL PROCESSOR (TRANSMIT & RECEIVE)
PLAYBACK DATA
U20, U21
9
ADPCM–2 IN/OUT
BYTE PACKETIZER
PCM–8 VOICE 2 IN/OUT
2
/RD
RECORD DATA
2 8K ENCODER/ DECODER
9
READ/ WRITE FIFO
CONTROL SIGNALS
COMPUTATIONAL PROCESSOR
DATA 9
/WRT
TO STORE PROCESSOR PWA
/SYSRST
PCM–8 VOICE 3 IN/OUT
2 U22, U23, U24
U17, U18, U19
AREA CLK
U11, U13
U12, U16
12K FS
MASTER CLK 8K FS
8K FS
VOICE CLK
/SYSRST 12.288 MHZ OSCILLATOR
TEST TIMING AND CONTROL
ERASE
U8
/RECORD U1, U2, U13
TEST TONE SQ WV (640HZ) TEST ENABLE
+12V
+12V
POWER DECOUPLING AND –5V REGULATOR
+5V
–12V
DISTRIBUTED WITHIN AUDIO PROCESSOR
–5V
+5V CHASSIS GROUND
–12V
U3
Audio Processor PWA, PN 205E0598–00, Functional Block Diagram Figure 27 (sheet 2 of 2)
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The output signals of the playback shaping circuits are connected through a 20 ohm resistor to the PLAYBACK/MONITOR connector, J6, for test and reproduction purposes. The output signals are also summed in the output buffer to provide the COMBINED_AUDIO output signal. The gain of the output buffer is set to provide a 1.45V rms output signal for each channel when the channel is driven with the reference signal. The COMBINED_AUDIO output can provide a maximum output signal of 8.03 volts peak into 622 ohms, which is the sum of the specified output load of 600 ohms and the 22 ohms on the Aircraft Interface Card. The COMBINED_AUDIO output signal is connected to the I/O connector, P4, and to the PLAYBACK/MONITOR connector, J6. A short circuit at the COMBINED_ AUDIO output will cause no damage to the Audio Processor PWA. 3)
Test Tone Circuits; U7, U15 The square wave test tone signal from the LCA, U13, is applied to a comparator in the test tone level control circuit. The output of the comparator drives two back–to–back Zener diodes to produce a 13.6V peak–to–peak signal. This signal is divided, filtered, and buffered to provide a nominal 0.34V rms fundamental signal to the test tone switch. The test tone switch, which is controlled by the test tone enable signals (/TT_EN_x), connects the test tone to one channel at a time. The amplitude level of the test tone signal at the COMBINED_AUDIO output is 1.0V rms for the voice channels and 1.2V rms for the area channel.
(b)
Digital Section The digital section consists of an encoding/decoding section, a computational section, a timing and sequencing section, an input/output section, and a programmable control section. 1)
Encoding/Decoding Section; U22 – U25 The encoder/decoder transmits encoding (record path) and receives decoding (playback path) at a sample rate of up to 16 kHz. Anti–aliasing and interpolation filters are also included in the device. The encoding produces an 8–bit serial PCM stream. The 8–bit word appears at the sampling rate which is synchronized by the FSX signal. The bit rate is determined by CLK R/X which also determines the bandwidth of the anti–aliasing and interpolation filters. The sign bit is transmitted first followed by seven magnitude bits in decreasing order of significance. The receive decoding operates in an analogous manner. The audio processor has four encoder/decoder devices, U22, U23, U24 and U25. The Pilot, Co–Pilot and Spare channels are collectively called voice channels and are processed via U22, U23 and U24. These encoder/decoders are all wired for the same sampling rate and bit rate. The Area Microphone channel is processed by U25 and has a higher sampling and bit rate. The PCM signals which are generated and received by the encoder/decoder are processed by the computational processors.
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2)
Computational Processors; U17 – U21 The Audio Processor PWA uses computational processors as the engine to reduce the required bit rate of the recorded data. These devices are mask ROM programmed specifically for the conversion of PCM data to and from ADPCM data. The processor uses two bit encoding. The master clock for the processor is 12.288 MHz (U8). This crystal controlled clock is also used to derive the bit rate clocks ACLK and VCLK (see PLD2). For the voice channels a single processor can process both the record and playback data for one channel. These processors are U17, U18, and U19. The Area Microphone channel requires a separate processor for the record and playback functions. The record function encoding is provided by U20 and the playback encoding is provided by U21. The XOUT pin of the four encoders which provide record function encoding are connected together to form the XADPCM single bit tri–state bus. This bus is input to the Logic Configurable Array (LCA) for conversion to byte wide packets. The bus is actively driven by each processor in response to the FSX signals which the LCA provides in a time multiplexed fashion. Similarly for playback, the LCA provides a RADPCM bus and FSR signals. Figure 28 illustrates the relationship between key processor signals and the corresponding encoder/decoder and audio processor signals.
3)
Timing and Sequencing Section; U11, U13 The timing and sequencing of the data flow on the audio processor is controlled by a Xilinx 3030 LCA (U13). The program for the LCA is contained in a special serial PROM (U11). This program is loaded at system reset time (/SYSRST) under the control of PLD1 (see PLD1). The logic of the LCA program can be examined in three sections, transmit, receive and test tone. A test mode is available which will allow complete operation of the Audio Processor circuits without interface to the Store Processor. — Transmit Section After system reset the transmit section is in continuous synchronous operation with fixed timing. This timing consists of the repetition of a one millisecond cycle. During one cycle the two bit ADPCM data from 24 voice samples (8 each from the 3 voice channels) and 12 area microphone samples are packed into a 9 byte packet of parallel data. This packet size represents the smallest number of whole bytes for which all the channels are sampled over an equal period (i.e. one millisecond). Each byte is written to the record FIFO as it is accumulated and the REC_SYNC flag is raised during the write of the first byte in the packet.
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Encoder/Decoder Signal
AP Signal
DS2165 Signal
Description
Clk R/X U3,U8,U9
VCLK
CLKX,CLKY U1,U4,U5
2.048 MHz square wave
Clk R/X U10
ACLK
ClKX U6 CLKY U7
3.072 MHz square wave
FSX U3 FSX U8 FSX U9
XV1_FS XV2_FS XV3_FS
FSX U1 FSX U4 FSX U5
8 kHz Pulse, 488 ns wide
FSX U10
XA_FS
FSX U6
12 kHz Pulse, 325 ns wide
FSR U3 FSR U8 FSR U9
RV1_FS RV2_FS RV3_FS
FSR U1 FSR U4 FSR U5
8 kHz Pulse, 488 ns wide
FSR U10
RA_FS
FSR U7
12 kHz Pulse, 325 ns wide
PCM OUT U3 PCM OUT U8 PCM OUT U9
XV1_PCM XV2_PCM XV3_PCM
XIN U1 XIN U4 XIN U5
2.048 MHz 8 bit PCM data
PCM OUT U10
XA_PCM
XIN U6
3.072 MHz 8 bit PCM data
PCM IN U3 PCM IN U8 PCM IN U9
RV1_PCM RV2_PCM RV3_PCM
YOUT U1 YOUT U4 YOUT U5
2.048 MHz 8 bit PCM data
PCM IN U10
RA_PCM
YOUT U7
3.072 MHz 8 bit PCM data
XADPCM
XOUT XOUT XOUT XOUT
Dual rate 2 bit PCM data (tri–state bus)
RADPCM
YIN U1 YIN U4 YIN U5 YIN U7
U1 U4 U5 U6
Dual rate 2 bit PCM data
Computational Processor Signal Descriptions Figure 28 The generation of the timing is based on the 3.072 MHz ACLK and the 2.048 MHz VCLK being synchronous with an exact three halves relationship (see PLD2). The ACLK is divided by 256 to provide 12 kHz time slots for the sampling of the area microphone channel. A three stage Johnson counter, clocked at twice this rate, provides time slots for sampling the three voice channels which do not interfere with the area channel slots.
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The individual voice channels are sampled at 8 kHz, which is consistent with the three halves relationship to the 12 kHz sampled area channel. Since VCLK is synchronous to ACLK, the clocking edges of VCLK are fixed in relation to the voice channel sampling slots. The rising edge of each sampling slot causes the generation of the appropriate sample pulse (FSX pulse) followed by two data clocking pulses. The sample pulses go to the corresponding encoder/decoders and ADPCM processors which then output data on the XADPCM bus. The clocking pulses shift this data into a serial to parallel shift register. When four samples (8 bits) have been accumulated in the shift register, the contents are written to the record FIFO. After nine bytes have been written to the FIFO the cycle is repeated. — Receive Section The receive section timing is similar to the transmit section timing except that operation is inhibited until the playback FIFO is half full and the cycles are synchronized to the incoming PLAY_SYNC signal. Synchronization is achieved by resetting the counters which control the 1 ms cycle if the first playback FIFO read of the cycle does not contain a PLAY_SYNC signal. In normal operation the first read after the playback FIFO is half full should contain the sync signal and no resynchronization should be required thereafter. The playback FIFO should remain about half full with slight variations due to the Store Processor operations. This half–full condition represents a playback delay of approximately 57 ms. The timing of the receive and transmit sections are independent of one another. — Test Tone Section The test tone section produces a 640 Hz square wave along with individual channel enables so that the tone may be added to the channels in response to the test signal. The 640 Hz tone is produced from a divide by 300 chain clocked by 192 kHz. The 192 kHz clock is a byproduct of the receive and transmit sections timing. The 640 Hz signal is further divided by 320 to produce 2 Hz. The 2 Hz signal drives a 2–bit counter which is decoded into four test–tone enable signals. These enable signals are active low for 0.5 seconds each. The 2–bit counter and the decoder are enabled by the rising edge the test signal. The individual channel enables and the test tone signal will persist while the test signal is present, or for 2.5 seconds which ever is longer. 4)
Input /Output Section; U12, U16 The Record FIFO (U16) and the Playback FIFO (U12) are 1K X 9 bit First In First Out memories. The write side of the Record FIFO and the read side of the Playback FIFO are controlled by the audio processor. Conversely the read side of the Record FIFO and the write side of the Playback FIFO are controlled by the Store Processor.
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Data bits 0–7 contain the packed audio data while data bit 8 contains the packet sync information. The output of the Record FIFO and the input of the Playback FIFO are connected together to form the Digital Audio Data bus (DAD 0–8). The input of the Record FIFO and the output of the Playback FIFO are separate. The Record FIFO input comes from the LCA (REC_DATA 0–7 and REC_SYNC). The Playback FIFO output is a LCA input (PLAY_DATA 0–7 and PLAY_SYNC). 5)
Programmable Control; U1, U2 — PLD1 The Programmable Logic Device 1 (PLD1), U1, is responsible for two functions. One is the robust resetting of the LCA, U13, in response to system reset (/SYSRST). This reset initiates a load of the LCA program from the serial PROM U11. Once the loading begins the LCA controls the load clock to the serial PROM. Upon completion of the load the LCA asserts the DONE signal. The initialization and loading process takes approximately 150 ms. The other function is the BITE monitoring of FIFO overflow which will also cause a robust LCA reset. The reset sequence proceeds as follows. The ADPCM processor and FIFO reset signal, /RESET, is held low while the input /SYSRST is active low. The rising edge of /SYSRST is synchronized to the 128 kHz clock (see PLD2). A three stage sequence of flip–flops then produce two 7.8 microsecond wide pulses separated by 7.8 microseconds. This pulse sequence is XRST which is connected to the /OE of U14 which is the LCA serial programming PROM. The signal is also used to pull down the open drain connection to the LCA Done pin. The inverse /XRST is connected to the LCA /Reset pin. This restart sequence is considered to be more robust than a simple rising edge reset signal. As part of the BITE function the PLD1 also monitors the Playback FIFO full condition. If the /PLAYFIFO_FULL pin goes active while /SYSRST is inactive a restart sequence is initiated. This condition may occur if the receive section of the LCA is not operating properly. After the /XRST pulse sequence is completed, signal /RESET is held low until the Done pin is pulled high by the LCA. This ensures a /RESET period of greater than 1 millisecond for the ADPCM processors. Another BITE feature is the monitoring of the Record FIFO full condition. If the /RECFIFO_FULL pin goes active while /SYSRST and ERASE signals are inactive then the open drain /NFG (Not Functioning Great) signal is pulled down. This causes a system fault indication. This condition may occur if the Store Processor is not operating properly. — PLD2 The Programmable Logic Device 2 (PLD2), U2, provides the clocks for the audio processor based upon the 12.288 MHz crystal controlled oscillator clock (MCLKI). MCLKI is first divided by two to produce a 6.144 MHz clock. This clock is divided by three to produce the 3.072 MHz ACLK and is divided by two to produce the 2.048 MHz VCLK. VCLK is divided by 16 to produce 128 kHz.
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(3)
Store Processor PWA; P/N 205E0601–01, 205E1027–00 (See Figures A4 and A5) The Store Processor PWA, using microprocessor U22, interfaces the flash memory to the Audio Processor PWA. In order to provide thirty minutes of continuous recording, the Store Processor aligns the solid–state memory array like a non–volatile circular buffer, which the Store Processor writes to at the head of the circular buffer and erases at the end of the buffer. The Store Processor can be functionally divided into a Control Management Section and an Interface Section. (a)
Control Management Section The control management activities consist of steering the inputs and outputs of its three interfaces (protected–memory, Aircraft Interface, and Audio Processor), as well as providing internal and external performance monitoring. 1)
Microprocessor; U22 The Store Processor uses a synchronous state mP, U22, whose timing is derived from a crystal controlled oscillator, Y1, which outputs a square wave at 32 MHz. This signal is named CLKIN and drives only the microprocessor’s clock input. The mP internally divides CLKIN by two yielding an output clock named CLKOUT of 16 MHz. All of the mP’s internal timing is synchronized to CLKOUT.
ADDRESS LATCHES
CLOCK
READ ONLY MEMORY
Y1
VOLATILE READ/WRITE MEMORY U17, U21
U5
U10, U14
NON–VOLATILE READ/WRITE MEMORY U24
ADDRESS BUS MICROPROCESSOR DATA BUS CONTROL BUS
U22 /RESET CONTROL LOGIC /LOW_LINE
POWER RESET AND WATCHDOG TIMER
U4 U20, U12
AUDIO PROCESSOR AND AIRCRAFT INTERFACE
2 /PWR_FAIL
VCC (+5V)
4 /FAULT
U8, U9, U11, U13, U15, U18
U6, U7, U12, U23
U2 /SYSRST
FLASH MEMORY INTERFACE
8
2
DATA CTRL SYNC STATUS TO AUDIO PROCESSOR PWA
10 CTRL
21
8 DATA
ADR
VCC VPP
TO STORE PROCESSOR PWA
+5V +12V
POWER MANAGEMENT
VEE (+5V) VPP (+12V)
U16, U3
AIRCRAFT INTERFACE
Store Processor PWA Functional Block Diagram Figure 29
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
2)
Address Latches; U10, U14 The mP’s 20–bit address bus is multiplexed with other signals and must be externally demultiplexed to generate a system address bus which remains stable throughout a bus cycle. Address latches, U10 and U14, are used to demultiplex the interface signals to generate the local address bus (ADR<19..0>). The mP’s Address Latch Enable (ALE) strobe clocks the latches.
3)
Power Reset and Watchdog Timer; U2 The resetting of the mP and its support circuitry is managed by a microprocessor supervisory circuit, U2. It provides an active low /RESET output which is directly connected to the mP’s /RESET input. The minimum duration of the reset pulse is 35 ms. U2 initiates a /RESET signal when it detects either: 1) the +5 Vdc power supply going out of limits or 2) a watch–dog time out. Upon powering up, /RESET remains low for 35 to 70 ms after Vcc raises above 4.75 volts. On powering down, signal /RESET goes low whenever Vcc falls below 4.5 volts. The reset threshold comparators have approximately 50 mV of hysteresis. The Watch–dog Timer (WDT) circuit forces a RESET pulse when no retrigger pulse occurs at its WDI pin within a time–out period of 1.0 second. The Store Processor causes the watch–dog timer to be retriggered every “read from” or “write to” the Audio Processor. This is accomplished by pulsing the watch–dog timer’s WDI pin with the Audio Processor’s chip select strobe, /PCS4.
4)
Control Logic; U20, U4 The Control Logic is composed of two programmable logic devices, U20 and U4, as well as a 13 nanosecond delay device, U19. This section generates the control signals that are used to read and write the data from the protected (flash) store memory and the Audio Processor PWA.
5)
Power Management; U16, U3 Power management circuitry performs three functions; power failure detection, EEPROM power, and protected (flash) memory power. Power failure detection is provided by an analog voltage sourced by the power supply section of the Aircraft Interface PWA. The signal, designated LOW_LINE, is an analog to the unregulated 28 Vdc (nominal) input to the power supply’s DC/DC converters. At power down, the /LOW_LINE signal begins to sag before the +5 and/or +12 volt supplies. In the Store Processor PWA, the /LOW_LINE signal is attenuated and compared to a 1.3 volt band–gap reference contained within U2. The comparator output, /PWR_FAIL, goes low to indicate power loss. This logic signal is polled by the mP every time it reads the Audio Processor input port. Signal / PWR_FAIL also directly controls the EEPROM power circuit.
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EEPROM power, Vee, is provided because of the need to save memory pointers and other state variables at power down. In order to guarantee accurate saving of state records, the +5 Vdc supply to non–volatile read/write memory, U24, must remain within specifications for 10.1 ms after the mP writes the last byte to be saved. Since the power supply cannot maintain Vcc to the whole PWA for that long of a period, an isolated +5 Vdc, Vee, is generated by U16. Protected (flash) memory requires a programming voltage, Vpp, of +12 Vdc +5%. The +12 Vdc provided by the Aircraft Interface PWA can only be regulated to +10%; consequently, a more tightly regulated voltage is provided by U3, which is located on the Store Processor PWA. 6)
Local Memory; U17, U21, U24 Local Memory (non–crash protected memory) consists of: Read Only Memory, U5; Volatile Read/Write Memory (RAM) U17 and U21; and Non–Volatile Memory, U24. This circuitry performs two functions; it is used as a buffer between the Audio Processor and the crash–protected memory, and to retain the memory pointers and other state variables at power down.
(b)
Interface Section The interface section consists of three interfaces; Aircraft Interface PWA, Audio Processor PWA, and the crash protected (flash) memory. Additionally, a local memory sub–section is used in the transfer of data from the Audio Processor to the protected– memory. 1)
Aircraft Interface to Store Processor Interface; U23 and U6 The Store Processor interface to the Aircraft Interface PWA consists of four data lines: TEST, ERASE, /RECORD, and /LOW_LINE. Refer to Page 32 for signal definitions.
2)
Audio Processor Interface; U6, U7 and U12 The logical interface to the Audio Processor consists of: a 9–bit bi–directional bus (data and sync); a 2–bit status bus (FIFO half–full and empty); and a 2–bit control bus (write and read strobes). The read and write control strobes which the Store Processor outputs to the Audio Processor are generated in PLD’s, U20 and U4. The physical interface to the Audio Processor consists of two ports, one read– only, the other write–only. Both are accessed whenever the mP asserts /PCS4. The input port is implemented with a pair of octal 3–state buffers (U6 and U7), which drive the mP’s data bus whenever /PCS4 and /RD are asserted. The port supplies data and status information from the Audio Processor (11 bits). Additionally, it supplies aircraft and recorder status information (5 bits).
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The output port is implemented with a 9–bit transparent 3–state latch, U12. The latch is transparent when /WR and /PCS4 are asserted. It latches data on the rising edge of /WR. The latch’s output are enabled while the latches are transparent, but remain enabled for an additional period after the rising edge of /WR to meet the Audio Processor’s write hold timing requirements. 3)
Crash Protected (Flash) Memory Interface; U8, U9, U11, U13, U15, U18 The performance requirements of the Store Processor with regard to concurrently recording audio data and erasing memory chips in preparation for subsequent recording are such that two page registers are required. One page register selects the device and area to which data is currently being written. The other page register selects the device and area currently being erased. The physical interface to the crash protected memory consists of : an 8–bit bi– directional data bus (FDAT<7..0>); a 3–bit (decoded to 8 lines) module select bus (SEL<7..0>); a 21–bit address bus (FADR<20..0>); and a 2–bit control bus (/OE, /WE). The data bus is buffered through an 8–bit bus transceiver, U18. The direction of the transceivers is controlled by the mP’s /RD strobe. The outputs of the transceivers are enabled by PLD U4. During a read from flash memory, the outputs of the transceivers are enabled while /MCSO and /RD are asserted by the mP. During a write to flash memory, the transceiver outputs are enabled while / MCSO and /WR are asserted by the mP, but they remain enabled for a period after the rising edge of /WR in order to meet the flash memory’s write hold timing requirement. The 15 least significant bits of the flash memory address bus (FADR<14..0>) are derived directly from the mP’s address bus. A pair of 8–bit, 3–state transparent latches, U10 and U14, are clocked by the mP’s ALE strobe to latch AD<15..0> on each address cycle. The 6 most significant bits of the flash memory address bus (FADR<20...15>) and the 8 module select lines (SEL<7...0>) are derived from a pair of 10–bit page registers, U8 and U9. The registers capture the 10 least significant bits of the mP’s data bus when it performs a write while asserting /PCSO. The registers’ clocks and output enables are generated by PLD U4. The level on ADR<1> determines which register is clocked. One of the two page registers’ outputs are enabled during any access to flash memory. The level of ADR<16> determines which register’s outputs are enabled. The 6 least significant output bits of the page registers become FADR<20...15> and drive the flash memory array directly. The next three most significant bits (FADR<23..21>) are decoded by a 1–0f–8 decoder, U11, generating the module select bus (SEL<7..0>).
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(4)
Control Unit The Control Unit (see Figure 7 and Figure 30) contains the TEST switch, bulk ERASE switch, indicating meter, headset jack, and a Microphone Preamplifier PWA and includes the area microphone (internally or externally mounted). The A151 and A151B Control Units connect to an externally mounted microphone. The A151 and A152 Control Units use Microphone Preamplifier PWA, P/N 93A263–02 which operates with a dynamic microphone while the A151B and A152B Control Units use Microphone Preamplifier PWA, P/N 93A266–01 which operates with a condenser microphone (refer to Appendix A for the schematic diagrams). The TEST switch and indicating meter provide the capability to test the four channels and the headset jack provides the means to monitor the playback of all four recorded channels. The bulk ERASE switch is used to erase the entire solid–state memory (FCSSU) after a routine flight, and will work only when: 1) the landing gear is down, 2) the weight of the plane is resting on the landing gear, and 3) the parking brake is engaged. To prevent accidental erasures, a time–delay circuit makes it necessary to hold the switch down for more than two seconds to start the erasure process.
TEST SWITCH
ERASE SWITCH MICROPHONE
METER
MICROPHONE PREAMPLIFIER PWA
Exploded View of Control Unit Assembly, A152, A152B Figure 30
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(a)
Microphone Preamplifier PWA, P/N 93A263–(XX) This PWA (refer to Figure 31) is used in Model A151 and A152 Control Units which function with a dynamic type microphone. The preamplifier (see the schematic diagram given in Figure A6 in Appendix A) receives the microphone low–level input signal at pins N and P. The low–level audio signal is amplified by Q1, gain adjusted by potentiometer R9, and further amplified by Q2. Pin selectable audio gain attenuation, in 6 dB steps from 0 to 24 dB, is provided via resistors R17, R29, R30, R32, and R31. A jumper/strap is required in the aircraft connector between pin q and the appropriate attenuation pin (s): p (6 db), r (12 db), or t (24 db). For example, a gain attenuation of 18 dB is enabled by connecting a jumper between pin q and p (6 db) and also between pin q and r (12 db). Transistor Q3 is another amplification stage and Q4 is an emitter–follower used to provide a low–impedance output at pin L (OUT), which is fed through the aircraft wiring to the Aircraft Interface PWA in the Model A100S recorder. Transistors Q5 and Q6 and associated circuitry form an automatic gain control circuit (AGC). Diode D4, R27, and C22 filter the supply voltage (B+18V) received from the A100S recorder. NOTE: Jumper pin 5B at the center of the PWA is used to disable the AGC circuitry when jumpered to the chassis.
(5)
Microphone Preamplifier PWA, P/N 93A266–(XX) This PWA (refer to Figure 32) is used in the Model A151B and A152B Control Units which connect, externally or internally, to a condenser microphone (Model A55B). The operation of this PWA is similar to that of Microphone Preamplifier PWA, P/N 93A263– (XX), but differs in that it provides a filtered 6.2V dc supply voltage required by the condenser microphones as a polarizing voltage. This voltage is furnished via resistor R20, Zener diode D3, and capacitor C15 (see the schematic diagram given in Figure A7 in Appendix A). Also, the preamplifier input is changed somewhat to accommodate the higher level audio signal. The microphone output signal is applied to the preamplifier input at pins N and M and amplified by Q1, gain adjusted by potentiometer R9, and further amplified by Q2. Pin selectable audio gain attenuation, in 6 dB steps from 0 to 24 dB, is provided via resistors R17, R29, R30, R32, and R31. A jumper is required in the aircraft connector between pin q and the appropriate attenuation pin (s): p (6 db), r (12 db), or t (24 db). For example, a gain attenuation of 18 dB is enabled by connecting a jumper between pin q and p (6 db) and also between pin q and r (12 db). Transistor Q3 is another amplification stage and Q4 is an emitter–follower used to provide a low–impedance output at pin L (OUT), which is fed through the aircraft wiring to the Aircraft Interface PWA in the Model A100S recorder. Low frequency response remains fixed at 150 Hz (–3 dB). Transistors Q5 and Q6 and associated circuitry form an automatic gain control circuit (AGC). Diode D4, R27, and C22 filter the supply voltage (B+18V) received from the A100S recorder. NOTE: Jumper pin 5B at the center of the PWA is used to disable the AGC circuitry when jumpered to the chassis.
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2.31"
R2
INPUT FROM MICROPHONE
C3
F
C1
GND M
C15 R7
C4
Q1
N
C2
R4
C7
P P
C22 R6
R3
B-18V
C5
C6
R5
R8
R10
3.5" Q6
GAIN POT. R9
K B
Q5
R9
L R11
AGC DISABLE JUMPER PIN
5B
R 27
AUDIO OUT
R28 C20
R 18
C11
C19 D 1
C8 C9
D C 2 14
R 19
D 4
B+18V
C12
R 13 R R 12 14
C
R22 R17
R26
R29 Q4 R 15
R C 25 17 Q2
C13
R16 R 30
C21
R 32
C10
q
R 21
p
R 31
r
C R 16 24
t
C 18
Q3
R23
AUDIO GAIN ATTENUATION JUMPER PINS Jumper p to q for 6 dB Jumper r to q for 12 dB Jumper t to q for 24 dB
Dynamic Microphone Preamplifier PWA, P/N 93A263–02 Figure 31
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2.31"
INPUT FROM MICROPHONE +
C3 –
+
C4
P
C7 + R6
Q1
C15
+ C6
+
C5
D 3
+ C22
R3 R5
6.2V TO MICROPHONE
N
C2 + R4
E
M R1
R7
GND
F
+ C1 –
R2
R 20
B-
R8
AUDIO OUT
R10 3.5"
Q6
GAIN POT. R9
+ R C 18 11 –
Q5 R11 R9
R 27
K B R28
L
C20
5B
AGC DISABLE JUMPER PIN
+
C8
C R C D1 D2 14 19 19 D – + 4
C9 +
B+ +
C12
R 13 R R 12 14
R26
R17 Q4
R29
R 15
C 13
R 30 R R C 32 31 16 +
Q2 + C 21 +
R22
C10 p q
C
R16 R 24 C 18 +
C R 17 R 25 + 21
Q3
t r
R23
AUDIO GAIN ATTENUATION JUMPER PINS Jumper p to q for 6 dB Jumper r to q for 12 dB Jumper t to q for 24 dB
Condenser Microphone Preamplifier PWA, P/N 93A266–01 Figure 32
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
TESTING AND TROUBLESHOOTING 1. GENERAL This section provides operational level testing and system troubleshooting procedures for the Model A100S recorder and associated control units and microphones. Testing for the A100S is based upon operational test procedures. The operational test procedures may serve as an acceptance criteria for the unit, as well as provide pointers to probable failures in the event that the unit is not functioning properly. There is no periodic testing required for the A100S. The A100S is a solid–state device which has no moving parts and provides a minimum of 30 minutes of recording time. As such, fault isolation is simplified in that it is confined to the three printed wiring assemblies which contain the processing and control electronics for the A100S.
2. A100S RECORDER TESTING The Model A100S has been designed as a direct line replaceable unit (LRU) for the existing L3 Cockpit Voice Recorders, Models A100 and A100A. As such, other than the Audio Monitor Adapter with Modification 1 (AMA/1), the Model A100S recorder uses the same test equipment and bench setup as the tape–based models. As with the Model A100 and A100A recorders, the Model A100S must be removed from the aircraft and placed on a test bench to be tested. Table 101 lists the standard test equipment that is recommended to be available at the test bench such as an oscilloscope, voltmeters and frequency counter. Special test equipment required consists of the following L3 units: Cockpit Voice Recorder System Test Panel Calibrated Sound Source Audio Monitor Adapter (AMA/1) Ultrasonic Test Set (Beacon Tester)
L3 P/N 9300A860 L3 P/N 9300A870 L3 P/N 17TES0200 L3 P/N 15977
3. MODEL A100S OPERATIONAL TEST PROCEDURE Figure 101 is a block diagram of the test equipment setup used to test the Model A100S. The operational test procedure used to verify the mission readiness of the Model A100S are given in Table 102. The A100S is tested using the L3 Cockpit Voice Recorder System Test Panel, P/N 9300A860, which is the same test panel used to test the Model A100 and A100A tape–based Cockpit Voice Recorders. Interface cables are included with the Test Panel, one (rectangular plug) to connect to the cockpit voice recorder and another (round plug) to connect to the control unit.
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Table 101 Recommended Standard Test Equipment Part No. or Model No.
Manufacturer
Name
Purpose
Model 54111D
Hewlett–Packard
Oscilloscope
Signal presentation
3400A
Hewlett–Packard
AC VTVM
Voltage measurement (VTVM)
651B
Hewlett–Packard
Audio Oscillator
Test signal injection for troubleshooting and alignment
W5MT3W (0–100 Watts, 600–400 Hz)
Technipower
Variac
Troubleshooting
4368B
Hewlett–Packard
Volt–Ohm– Milliammeter
Voltage measurements (VOM)
Model 3283 P/N 16315
Simpson
AC Volt Meter
Measuring input line voltage
5314A
Hewlett–Packard
Frequency Meter
Measuring input line frequency
This panel may be used in conjunction with the L3 Calibrated Sound Source, P/N 9300A870, which is used to generate a regulated sound source, via a speaker, to test and analyze the system microphones. The specifications for the A100S apply to the individual channel outputs accessed, via the Audio Monitor Adapter with Modification 1 (AMA/1), at the Playback Monitor connector (J6) located on the outer edge of the Audio Processor PWA. As such, the dust cover of the A100S must be removed if the desired level of test goes beyond the “ALL TEST” procedure given in Table 102. For an illustration of this test setup, refer Figure 904. NOTE:
The “ALL TEST” test procedure is sufficient to determine the mission readiness of the recorder.
System level troubleshooting for the Model A100S is provided in Table 105. Each step given in Table 105 corresponds to the respective step described in the Operational Test Procedure given in Table 102. That is, if an expected indication called for in the Operational Test Procedure is not correct, refer to the respective step in the System Level Troubleshooting table. System level troubleshooting restricts corrective maintenance to replacement of a PWA and/or the Flash Crash Survivable Storage Unit (FCSSU). However, fault isolation procedures are given for the Aircraft Interface PWA (Table 106), Audio Processor PWA (Table 107) and the Store Processor PWA (Table 108). To aid in troubleshooting, refer to the System Functional Block Diagram given in Figure 25, which is presented in the Description and Operation section. Also, refer to the detailed system wiring diagram (Figure A1) and PWA schematic diagrams given in Appendix A at the rear of this manual for additional troubleshooting aids. Frequency response and input gain calibration procedures are described in the Fault Isolation section for the Audio Processor PWA.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Variac Watt/AC Line Meter
115 + 1 VAC 400 Hz
Audio Oscillator
Scope
Frequency Meter Channel A
Frequency Meter Channel B
Input VTVM
Output VTVM Terminal Block TB1 Pin 1 – 115V – Hot Pin 2 – 115V – Gnd Recorder Input Terminals
RECORDER SIDE
Recorder Output Terminals
Power In Speaker
LOCAL AMP (Audio Amplifier) Switch
CHANNEL SELECT Switch
CONTROL UNIT SIDE
Rec. c.u.
Recorder Interface Connector J3
COCKPIT VOICE RECORDER SYSTEM TEST PANEL, P/N 9300A860
J2 Connection For Interface Cable To Control Unit, When Used
Interface Cable P1 Input
J1
Output
Model A100S Solid–State Cockpit Voice Recorder Under Test
Model A100S Operational Test Set–Up Figure 101
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Table 102 Model A100S Operational Test Procedure ITEM A.
PROCEDURE
REFERENCE
PRELIMINARY TEST SET–UP (1)
Test Set–Up Figure 101
Except for the Model A100S, connect all units as shown in Figure 101. At the A860 Cockpit Voice Recorder System Test Panel, hereinafter referred to as the Test Panel, set function switches as follows: POWER ON/OFF switch
— Set this toggle switch to position OFF (down).
POWER AC/DC switch
— Set this toggle switch to position AC (up).
CHANNEL SELECT switch — Set this switch to position CH1. RECORD BIAS/OFF switch
— Set the RECORD toggle switch to position BIAS (up).
LOCAL AMP switch
— Set this switch to position REC.
VOLUME control
— Set the VOLUME control at its mid–range position.
MODE SYS/UNIT select sw. — Set the SYS/UNIT switch to (Left top of panel) position SYS.
B.
(2)
Set output of generator to 3 Vrms @ 1 KHz output. Note the ac power consumption, if any.
(3)
Apply power to the Variac and adjust as needed for 115 +1 Vac output. Note the ac power consumption, if any.
POWER–ON TEST
Test Set–Up, Figure 101
This test checks the Model A100S ac power consumption and the power–up audible tone generated by the recorder. (1)
Connect the Model A100S and the Control Unit (if one is being used) to the Test Panel. NOTE: With the RECORD BIAS/OFF switch set to position BIAS, pre–recorded data will be overwritten.
(2)
At the Test Panel, while monitoring the Variac and listening for the start–up audible tone, set the POWER ON/OFF toggle switch to position ON. Note: at the instant that power is applied, the recorder will generate a brief audible tone. If no audible tone is heard, proceed to Table 105 for troubleshooting.
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Table 102 Model A100S Operational Test Procedure (Continued) ITEM (3)
C.
PROCEDURE
REFERENCE
Carefully readjust Variac to provide 115 + 1 Vac to the Test Panel. Note the ac power consumption. Subtract from this figure, the power consumption noted in step A.(2). The ac power consumed by the recorder should be12 watts or less. If not, proceed to Table 105 for troubleshooting.
ALL TEST
Test Set–Up, Figure 101
Sophisticated Built–In–Test–Equipment (BITE) has been designed into the A100S to allow a quick operational confidence check without removing the dust cover. This check can be accomplished at the test bench using the Test Panel. (1)
ALL TEST Using Test Panel: (a)
At the Test Panel, set the MODE switch to position UNIT.
(b)
At the Test Panel, press and hold the green ALL TEST pushbutton for approximately 1 minute to allow recorded data to be monitored in the playback mode.
(c)
While holding in the ALL TEST pushbutton, monitor the TEST meter directly above the ALL TEST pushbutton. The needle should remain in the green (GOOD) area.
(d)
At the Test Panel, monitor the speaker for the 640 Hertz test tone; if necessary, turn up the panel VOLUME control. The test tone will alternate between the channels and will always start a new cycle at Channel 1. If this is not the case, proceed to Table 105 for troubleshooting.
(e)
Control Unit Voltage Check: Measure the output of the Control Unit connectors on the A860 Control Panel and ensure a reading of 18 VDC + 15% with a 1 K ohm load across the output.
NOTE: If recorder does not pass All Test, check for fault conditions described in notes at end of this chapter. NOTE: CLEARING “MEMORY” LATCHED FAULT CONDITION The A100S Store Processor Card, p/n: 205E0602–00 or 205E1027–00, stores memory fault codes in nonvolatile EEPROM. Certain memory fault conditions must be reset by service personnel prior to returning the unit to normal operation. This “Memory” latched fault condition is indicated by the Fault Indicator, CR5, located on the Store Processor Card, being illuminated when the unit is powered up in the Record Mode of operation. The “Memory” Latched Fault Condition can be cleared as described in the procedure below.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Table 102 Model A100S Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
(1)
With the SSCVR connected to the A860 CVR Test Panel, power the A100S up in the Reproduce Mode. (Record/Bias Switch, S11, on the Test Panel to OFF.)
(2)
If the “Pointers Not Saved” condition has been latched, the Fault Indicator, CR5, on the Store Processor Card will flash 10 times.
(3)
Allow the flashing indication cycle to complete, or observe that the unit does not have this condition.
Note:
Since this procedure requires critical timing sequence for clearing the fault condition, read Steps (4) & (5) completely before performing.
(4)
To clear the “Memory” Latched Fault condition, first press and release the All Test Switch, S13, on the A860 CVR Test Panel. (This begins a 5–second interval in which the latched fault condition may be cleared.)
(5)
Immediately after pressing and releasing the All Test Switch, S13, press and hold the Bulk Erase Switch, S10, for at–least 3 seconds but not more than the 5 second interval.
(6)
Power down the recorder, place the unit into Record Mode by placing the CVR Test Panel switch S11 to Record/Bias position and reapply power to the recorder.
(7)
Observe that the Fault Indicator is no longer illuminated. Press All Test Switch and observe test meter is in green to verify proper operation of recorder.
(8)
If recorder fails to test good, or the Fault Indicator, CR5, is still illuminated, then repeat steps (3) – (7). If problem continues, return unit to L3AR for service.
(9)
If the “Pointers Not Saved” latched condition was observed in step (2) above, then proceed with the next procedure.
NOTE: “POINTERS NOT SAVED” LATCHED FAULT CONDITION The A100S is designed such that an impending loss of power is signaled to the CPU to preserve the current system pointers in nonvolatile (EEPROM) memory. Any interruption to this cycle might result in a corrupted set of pointers and cause a “Pointers Not Saved” latched fault condition. (1)
With the SSCVR connected to the A860 CVR Test Panel, power the A100S up in the Reproduce Mode. (Record/Bias Switch, S11, on the Test Panel to OFF.)
(2)
If the “Pointers Not Saved” condition has been latched, the Fault Indicator, CR5, on the Store Processor Card will flash 10 times.
(3)
Allow this flashing fault indication cycle to complete.
Note:
Since this procedure requires critical timing sequence for clearing the fault condition, read Steps (4) & (5) completely before performing.
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Table 102 Model A100S Operational Test Procedure (Continued) ITEM
(2)
D.
PROCEDURE
REFERENCE
(4)
Press and release the All Test Switch, S13, on the A860 CVR Test Panel. (This begins a 5–second interval in which the latched fault condition may be cleared.)
(5)
Immediately after pressing and releasing the All Test Switch, S13, press and hold the Bulk Erase Switch, S10, for at–least 3 seconds but not more than the 5–second interval. During the 3 seconds while the Bulk Erase Switch, S10, is being pressed, briefly press and release the All Test Switch, S13, again.
(6)
To verify that the fault has cleared, power down the recorder, then reapply power while in the Reproduce mode of operation and observe that the Fault Indicator, CR5, on the Store Processor Card briefly flashes but does not illuminate.
ALL TEST Using Associated Control Unit: (a)
At the Test Panel, set the MODE switch to position SYS.
(b)
At the Control Unit, press and hold the ALL TEST push– button for approximately 1 minute to allow recorded data to be monitored in the playback mode.
(c)
At the Control Unit, monitor the TEST meter. The needle should remain in the green (GOOD) area.
(d)
At the Control Unit with a suitable headset connected to the 1/4 inch phone jack, monitor the A100S test tone. The test tone should be an audible 640 Hertz tone and should alternate between channels. If this is not the case, proceed to Table 105 for troubleshooting.
PLAYBACK TEST
Test Set–Up, Figure 101
This test verifies the playback ability of the A100S recorder. (1)
At the System Test Panel, set the RECORD BIAS/OFF toggle switch to position OFF (down).
(2)
At the Test Panel, press the ALL TEST pushbutton. The recorder should automatically begin replaying the data recorded since the recorder was last powered–up. If this is not the case, proceed to Table 105 for troubleshooting.
(3)
Connect the headset to the recorder front panel jack to monitor the combined audio. The previously recorded test tone should be heard.
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Table 102 Model A100S Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
NOTE: The recorder test tone can also be heard via the Test Panel speaker and also by connecting to the HEADSET phone jack on the Control Unit. (4)
E.
At the Test Panel, place the RECORD BIAS/OFF toggle switch to position BIAS (up). The recorder will resume recording data at the point in memory where it had stopped when the PLAYBACK function was initiated.
BULK ERASE TEST
Test Set–Up, Figure 101
This test checks the capability of erasing the information stored in the A100S FCSSU (CMOS Flash memory). (1)
Bulk Erase Lock–Out:
NOTE: This portion of the test verifies that the Bulk Erase function will not be initiated by momentarily contacting the ERASE pushbutton (less than 2 seconds).
(2)
(a)
At the Test Panel, verify that the RECORD BIAS/OFF toggle switch is still set to position BIAS (up).
(b)
At the Test Panel (or the Control Unit if used), press and release the BULK ERASE pushbutton for less than 2 seconds.
(c)
This action should not have started the Bulk Erase function. If started, proceed to Table 105 for troubleshooting.
Bulk Erase:
NOTE: All previously recorded data will be erased during the Bulk Erase cycle. (a)
At the Test Panel (or the Control Unit if used), press and hold the ERASE pushbutton for more than two seconds and release.
(b)
Monitor the Test Panel speaker. For units equipped with 2–Megabit Memory Devices, the erase tone should be audible for approximately 13 seconds. For units equipped with 8–Megabit Memory Devices (Modification Dot 1), the erase tone should be audible for approximately 1 to 15 seconds. If the erase tone is not heard, proceed to Table 105 for troubleshooting.
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Table 102 Model A100S Operational Test Procedure (Continued) ITEM (3)
PROCEDURE
REFERENCE
Bulk Erase Verification:
This test verifies that all previously recorded information has been erased from the memory.
E.
(a)
At the Test Panel, verify that the RECORD BIAS/OFF toggle switch is still set to position OFF (down).
(b)
At the Test Panel, press the ALL TEST pushbutton. The recorder should automatically begin replaying the data recorded since the recorder was last powered–up.
BULK ERASE TEST (Continued) (c)
F.
Test Set–Up, Figure 101
When the unit is placed back into the playback mode after a Bulk Erase is performed, a sound similar to a “galloping horse” or “tapping fingers” is heard. This sound indicates that there is no data in memory. If nothing is heard, proceed to Table 105 for troubleshooting.
BEACON TEST This test verifies the proper operation of the beacon (Underwater Locating Device) mounted on the A100S front panel. (1)
Turn on the L3 Beacon Tester (P/N 15977).
(2)
Using a ground strap or similar conductive material, short the beacon center conductor, located on the underside of the beacon, to the cradle.
(3)
While the beacon is shorted to the cradle, an audible tone should be heard at the beacon test set. Once detected, remove the shorting jumper. If an audible tone is not detected, proceed to Table 105 for troubleshooting.
(4)
If the ULD is functioning properly, it will emit inaudible, ultrasonic soundwaves that the 42A12( ) will receive and reproduce at a lower, audible frequency. Proper operation of the ULD is indicated by a repetitive “beep” emanating from the 42A12( )’s speaker.
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4. CONTROL UNIT, MODEL A151/A151B & A152/A152B TEST PROCEDURES Table 103 provides the operational tests and alignment procedures for the Model A151/A151B and A152/A152B Control Units. Figure 102 is a diagram of the basic test setup to be used for testing either type Control Unit. Figure 103 shows the location of the Control Unit microphone input gain control (potentiometer R9 on the Microphone Preamplifier PWA).
Table 103 Model A151 and A152 Control Units, Operational Test Procedure ITEM
PROCEDURE
REFERENCE
A. PRELIMINARY TEST SET–UP (1)
Remove the dust cover from the Control Unit to be tested.
(2)
At the Control Unit, connect a jumper wire between pin 5B on the Microphone Preamplifier PWA and chassis; this con– nection disables the AGC circuitry (see Figure 31/Figure 32).
(3)
Connect all units as shown in Figure 102
(4)
At the Test Panel, set the function switches as follows: POWER AC/DC Switch
—
AC
POWER ON/OFF Switch
—
OFF
LOCAL AMP Switch
—
C.U. (Control Unit)
ROLL OFF Switch
—
700 Hertz
ATTENUATION Switches
—
–6 dB –12 dB –24 dB
MIC INT/EXT Switch
—
EXT
CHANNEL SELECT Switch —
CH1
Figure 102
– ON, (right) – ON, (right) – OFF (left)
NOTE: In Model A152/A152B Control Units, where the built–in microphone is wired internally to pins N (HI) and P (LO) of the Microphone Preamplifier PWA (see Figure 31/Figure 32), disconnect microphone leads and apply input signals using a properly shielded cable directly to circuit board pins N and P. In other units, the input signal should be applied to the test panel input with the MIC INT/EXT switch set to EXT. (5)
When testing Models A151 and A152, test signals may be applied to input terminals on the RECORDER side of the Test Panel. For Models 152–1, A152–2 and A152–4, remove the microphone wires from pins N and P on the printed circuit board and connect the test signal directly to pins N (HI) and P (LO). See Figure 901.
(6)
At the Test Panel, set the POWER ON/OFF switch to position ON.
(7)
Apply power to the Variac and adjust as needed for 115 +1 Vac power to the Test Panel input (TB1– 1 & 2). See Figure 102.
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Variac Watt/AC Line Meter
115 + 1 Vac 400 Hz
Freq Meter Channel A
Input VTVM
Terminal Block TB1 Pin 1 – 115V – Hot Pin 2 – 115V – Gnd
System Test Panel
Audio Oscillator
Control Unit Input
CONTROL UNIT SIDE
Speaker RECORDER SIDE
Freq Meter Channel B
Output VTVM
LOCAL AMP (Audio Amplifier) Switch
MIC. Select
C.U. Scope
Control Unit Output
Rec.
J2 Connection For Interface Cable To Control Unit Input
Output
Control Unit Under Test
Control Unit Test Set–up Figure 102
POTENTIOMETER R9
Control Unit Test and Adjustment Point Figure 103
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Table 103 Model A151 and A152 Control Units, Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
B. GAIN ALIGNMENT (1) (2)
Figure 102
NOTE: For Model A151 & A152 units with Mod. 5, refer to Section 6.B. At the Audio Oscillator, apply a 4 mV, 1 kHz signal to the Control Unit input terminals. Adjust Control Unit potentiometer R9 (location illustrated in Figure 103) for a 0.5V level as measured at the Output VTVM.
C. MAX OUTPUT TEST
Figure 102
(1)
At the Audio Oscillator, increase the Control Unit input signal level to approximately 12 mV.
(2)
Adjust the input signal level for a 2 volt level at the Output VTVM.
(3)
A sinewave output with no sign of clipping should be observed on the oscilloscope.
D. AGC TEST
Figure 102
(1)
At the Control Unit, remove the jumper connecting post 5B on the Microphone Preamplifier PWA to the chassis (installed in the PRELIMINARY TEST SET–UP).
(2)
Observe that the voltage level measured at the Output VTVM dropped to between 0.3 and 0.6 volt.
(3)
Reconnect the jumper between post 5B on the Microphone Preamplifier PWA and the chassis.
E. SIGNAL/NOISE RATIO
F.
Figure 102
(1)
At the Test Panel, short the input terminals and note the reading Output VTVM.
(2)
At the Output VTVM, the noise level should be less than10 mV.
(3)
At the Test Panel, remove the short.
FREQUENCY RESPONSE
Figure 102
NOTE: For Model A151 & A152 units with Mod. 4, refer to Section 5.A. For Model A151 & A152 units with Mod. 5, refer to Section 6.A. (1)
Set the Output VTVM to the 1 volt full–scale range.
(2)
Apply a 1–kHz input signal and adjust the input voltage level (at the audio oscillator) for a 0 dB reading on the Output VTVM.
(3)
Maintaining the above input level, adjust the audio oscillator for 700 Hz input signal and note the reading on the Output VTVM in dB. The meter should not deviate more than 0 to –6 dB.
(4)
Repeat step (3) with audio oscillator adjusted for both 300 Hz and 5 kHz.
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Table 103 Model A151 and A152 Control Units, Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
G. MICROPHONE GAIN ALIGNMENT
Figure 102
(1)
At the Test Panel, set the MIC INT/EXT switch to position INT.
(2)
Reconnect microphone if disconnected in the PRELIMINARY TEST SET–UP.
(3)
At the Calibrated Sound Source, P/N 9300A870, apply a 100 dB sound pressure level to the Control Unit microphone and adjust the position of the Control Unit to obtain a maximum reading.
(4)
At the Control Unit Microphone Preamplifier PWA, adjust potentiometer R9 (position illustrated in Figure 103) for a reading of 0.5 V on the Output VTVM.
H. TEST METER (1)
I.
J.
Figure 102
Remove jumper between Pin 5B and ground. Press TEST button of control unit test meter to read 9dB minimum.
BULK ERASE SWITCH
Figure 102
(1)
While monitoring both the NORMAL and the ACTUATE meters at the upper left corner of the Test Panel, press the ERASE button on the Control Unit.
(2)
At the Test Panel, the NORMAL meter should drop to mid–scale while the ACTUATE meter should rise to mid–scale.
GROUND SHORT TEST (1)
Figure 102
Switch test panel GND test switch to Position 1 (GND Short). GND test lamp should NOT light. If control unit under test has a short between signal ground and chassis GND test lamp will light indicating a fault.
K. REVERSED GROUND TEST
Figure 102
(1)
Switch test panel GND test switch to Position 2 (Reversed Ground). GND test lamp should NOT light. Touch the control unit’s chassis with the test panel probe. If control unit is properly grounded the GND test lamp will light.
(2)
For control units with internal microphone repeat above test touching microphone case.
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5. CONTROL UNIT, MODEL A151 & A152 WITH MODIFICATION 4 TEST PROCEDURES The test procedures for testing Control Units, Models A151 and A152, which include Modification 4, are the same as those without Modification 4 with the exception of the Frequency Response Test given below. The test setup given in Figure 102 is to be used for testing these Control Units. Also, refer to Figure 103 for the Control Unit preamplifier gain adjustment point.
A. FREQUENCY RESPONSE (1)
Set the Output VTVM to its 1 volt full–scale range.
(2)
Apply a 1 kHz input signal and adjust its input voltage level (at the oscillator) for an output signal level of 0 dB as measured on the Output VTVM.
(3)
Maintain the same input level. Switch through following frequencies and read dB outputs: 150 Hz 300 Hz 500 Hz 5000 Hz
–1 to –5 dB 0 to –3 dB 0 to –3 dB 0 to –4 dB
6. CONTROL UNIT, MODEL A151 & A152 WITH MODIFICATION 5 TEST PROCEDURES The test procedures for testing Control Units, Models A151 and A152, which include Modification 5, are the same as those without Modification 5 with the exceptions of the Frequency Response Test and the Microphone Gain Alignment given below. The test setup given in Figure 102 is to be used for testing these Control Units. Refer to Figure 103 for the Control Unit preamplifier gain adjustment point.
A. FREQUENCY RESPONSE (1)
Set the Output VTVM to its 1 volt full–scale range.
(2)
Apply a 1 kHz input signal and adjust the input voltage level (at the oscillator) for an output signal level of 0 dB as measured on the Output VTVM.
(3)
Maintain the same input voltage level set above. Switch through the following frequencies and note the dB outputs: 150 Hz 300 Hz 500 Hz 5000 Hz
–1 to –5 dB 0 to –3 dB 0 to –3 dB 0 to –4 dB
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B. MICROPHONE GAIN ALIGNMENT (1)
At the Test Panel, set the MIC INT/EXT switch to position INT. Set the Test Panel attenuator switches for –18 dB attenuation. This is performed by positioning the –6 dB and –12 dB attenuation switches to the right (enable) and the –24 dB attenuation switch to the left (disable) position.
(2)
Connect the microphone if not already connected.
(3)
At the Calibrated Sound Source, P/N 9300A870, apply a 100 dB sound pressure level to the Control Unit microphone and adjust the position of the Control Unit to obtain a maximum reading on the Output VTVM.
(4)
At the Control Unit Microphone Preamplifier PWA, adjust potentiometer R9 (shown in Figure 103) for an output of 0.5V as indicated on the Output VTVM.
7. MODEL A150 PREAMPLIFIER TEST PROCEDURES Table 104 provides the operational test procedure for the Model A150 Microphone Preamplifier Module. The Model A150 is designed to be used only with condenser-type microphones (Model A055). To test the operational performance of the A150 Preamplifier Module, use Test Cable Assembly, P/N 024E1285–00, along with the same test setup given in Figure 102 with one exception. A simulated microphone signal output from the HP33120B is routed through the A860 Test Panel, a banana jack – to – BNC adapter, and Cable 024E1877–00 to connector J1 on the A150 Preamplifier. The Test Cable Assembly, P/N 024E1285–00 connects between J2 on the A860 Test Panel and the 19–pin connector on Preamplifier A150 to furnish operating power for the preamplifier and to route the amplified simulated microphone output back to the A860 Test Panel.
Mic Connector J1
A
B D
C
K
E Signal Connector J2
A
M
C
J2
H
B J1
External Preamplifier, Model A150 (P/N 93A150-20) Assembly Diagram Figure 104
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
A150 PREAMPLIFIER MODULE
CABLE ASSEMBLY 024E1877–00
PWA TERMINALS
E5
MIC_NO.1_IN_HI
A
MIC_NO.1_BIAS
E4
MIC_NO.1_IN_LO
E6
P2
J1-
A
P1-
(BNC)
MIC SIGNAL (wHITE)
B
B NO CONNECT
C
C
CONNECT MIC CENTER CAL OUTPUT FROM A860 SHIELD TEST PANEL VIA BANANA JACK-TO-BNC ADAPTER.
MIC GND (SHIELD)
Simulated Microphone Signal Input Test Connections to the Model A150 Preamplifier Module Figure 105 Table 104 Model A150 Preamplifier Unit, Operational Test Procedure ITEM
PROCEDURE
REFERENCE
A. PRELIMINARY TEST SET–UP (1)
Remove the dust cover from the Preamplifier Unit to be tested.
(2)
At the Preamplifier Unit, connect a jumper wire between pin 5B on the Microphone Preamplifier PWA, p/n: 205E and chassis; this connection disables the AGC circuitry (Figure 32).
(3)
At the Test Panel, set the function switches as follows: POWER AC/DC Switch
—
AC
POWER ON/OFF Switch
—
OFF
LOCAL AMP Switch
—
C.U. (Control Unit)
ATTENUATION Switches
—
–6 dB –12 dB –24 dB
MIC INT/EXT Switch
—
EXT
CHANNEL SELECT Switch —
CH1
– ON, (right) – ON, (right) – OFF (left)
(4)
At the Test Panel, set the POWER ON/OFF switch to position ON.
(5)
Apply power to the Variac and adjust as needed for 115 +1 Vac power to the Test Panel input (TB1– 1 & 2). See Figure 102.
B. GAIN ADJUSTMENT (1)
At the Audio Oscillator, apply a 4 mVrms, 1 kHz signal to the Preamplifier Unit input terminals.
(2)
Adjust Preamplifier Unit potentiometer R9 (location illustrated in 32) for a 0.5V level as measured at the Output VTVM.
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Table 104 Model A150 Preamplifier Unit, Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
C. DISTORTION CHECK (1)
At the Audio Oscillator, increase the Preamplifier input signal level to approximately 12 mVrms.
(2)
Adjust the input signal level for a 2 volt level at the Output VTVM.
(3)
A sinewave output with no sign of clipping should be observed on the oscilloscope.
D. AGC TEST (1)
At the Preamplifier Unit, remove the jumper connecting post 5B on the Microphone Preamplifier PWA to the chassis (installed in the PRELIMINARY TEST SET–UP).
(2)
Observe that the voltage level measured at the Output VTVM dropped to between 0.3 and 0.6 volt.
(3)
Reconnect the jumper between post 5B on the Microphone Preamplifier PWA and the chassis.
E. SIGNAL/NOISE RATIO
F.
(1)
At the Test Panel, short the input terminals and note the reading Output VTVM.
(2)
At the Output VTVM, the noise level should be less than10 mV.
(3)
At the Test Panel, remove the short.
FREQUENCY RESPONSE (1)
Set the Output VTVM to the 1 volt full–scale range.
(2)
Apply a 1–kHz input signal and adjust the input voltage level (at the audio oscillator) for a 0 dB reading on the Output VTVM.
(3)
Measure the output level for each of the frequencies listed below and verify that the output levels are within the given specifications. Frequency Input 150 Hz 300 Hz 500 Hz 5,000 Hz
Output –2 to –10 dB 0 to –4dB 0 to –2dB 0 to –5dB
G. ATTENUATION CHECK (1)
Set all attenuator switches to OFF.
(2)
Apply a 1–kHz input siganal and adjust the input voltage level (at the audio oscillator) for a 0 dB reading on the Output VTVM.
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Table 104 Model A150 Preamplifier Unit, Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
(3)
Set the 6 dB switch to ON and note the level on the Output VTVM, it should read: –3 to –9 dB. Set the 6 dB switch to OFF.
(3)
Set the 12 dB switch to ON and note the level on the Output VTVM, it should read: –9 to –15 dB. Set the 12 dB switch to OFF.
(3)
Set the 24 dB switch to ON and note the level on the Output VTVM, it should read: –20 to –28 dB. Set the 24 dB switch to OFF.
H. GAIN Verification
I.
J.
(1)
At the Test Panel, set the attenuator switches as follows: 6 dB ON 12 dB ON 24 dB OFF
(2)
At the Audio Oscillator, apply a 4 mVrms, 1 kHz signal to the Preamplifier Unit input terminals.
(3)
Verify a 0.5V level as measured at the Output VTVM, if necessary, adjust Preamplifier Unit potentiometer R9 (location illustrated in 32).
(4)
Measure the voltage across C15. Voltage should be 6.0 V (+/– .6V).
GROUND TEST (1)
Switch Test Panel GND test switch to REVERSED GND position.
(2)
Touch the Preamp Unit chassis with the Test Panel probe. Verify that the GND FAULT lamp does not illuminate.
(3)
Set the Test Panel GND test switch to BYPASS position.
SYSTEM TEST (1)
Turn Test Panel Power OFF.
(2)
Reinstall Preamp Dust Cover.
(3)
Turn Test Panel Power ON.
(4)
Set Test Panel LOCAL AMP switch to C.U. Verify that a voice or 1-kHz tone can be heard through the Test Panel speaker as the VOLUME control is rotated clockwise.
8. CALIBRATION TEST FOR MODEL A055B REMOTE MICROPHONE MODULES This series of tests verifies the proper operation of the L3 Model A055B series of remote condenser type microphones, part numbers 93A055–10, –20, –30, –40, –45, –50, –55, –60, –65, –66, –67 and –95.
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A. PRELIMINARY SET–UP (1)
Set up for test as illustrated in Figure 106.
(2)
Position the Calibrated Sound Source, P/N 9300A870, approximately 6–inches from the microphone.
(3)
Connect microphone to Dumont: Model 701 oscilloscope and HP 400D AC VTVM, or equivalent. NOTE: If a sound level source and oscilloscope are not available, use the alternate method given in step C. to verify operation.
B. OUTPUT VERIFICATION (1)
Apply a 100 dB sound pressure level to the microphone.
(2)
The VTVM should indicate 12 mV + 6 dB.
(3)
The waveform displayed on the oscilloscope should be free from distortion.
C. ALTERNATE METHOD This method is to be used only when the Calibrated Sound Source is not available. (1)
At a normal voice level, speak into the microphone from a distance of approximately 6–inches.
(2)
The VTVM should fluctuate between 2 and 10 mV. *Remote Microphone Oscilloscope + 6Vdc Audio
Shield
+
Calibrated Sound Source P/N 9300A870 6 Volt + 1 Volt Battery or D.C. Power Supply 10K 1/4W Resistor
AC VTVM
* For P/N 93A055–40 & 45 remote microphones, the +6 Vdc line is black and the audio line is white. For P/N 93A055–60, 65, 66, 66, 67, & 95 remote microphones, the +6Vdc line is white and the audio line is black.
Remote Microphone Test Setup Figure 106
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9. MODEL A100S SYSTEM TROUBLESHOOTING System level troubleshooting for the Model A100S is provided in Table 105. Troubleshooting is based on the Operational Test Procedure described in the front of this section. That is, if an expected indication called for in the Operational Test Procedure is not correct, the troubleshooting procedure will direct the technician to the probable cause of the malfunction. System troubleshooting restricts corrective maintenance to replacement of a PWA and/or the Flash Crash Survivable Storage Unit (FCSSU). Each step given in Table 105 corresponds to the respective step described in the Operational Test Procedure. To aid in troubleshooting, refer to Figure 25, System Functional Block Diagram, presented in the Description and Operation section, Figure A1 the detailed system wiring diagram presented in Appendix A and to the detailed schematic diagrams of each PWA also provided in Appendix A. Board level troubleshooting follows the system troubleshooting and provides test point analysis, logic analyzer fault detection (Audio Processor PWA), and component level fault isolation. WARNING: VOLTAGES CAPABLE OF FATAL INJURY ARE PRESENT AT THE RECORDER INPUT CONNECTOR; ONLY QUALIFIED MAINTENANCE TECHNICIANS SHOULD PERFORM THE FOLLOWING MAINTENANCE. CAUTION: THE A100S PRINTED CIRCUIT ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL CIRCUIT BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
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Table 105 System Level Troubleshooting STEP
TEST DESCRIPTION
EXPECTED RESULTS
FAULT ISOLATION PROCEDURE
A.
Preliminary Set–up
N/A
N/A
B.
Power–On Test
A.) Brief Audible tone upon power–up
1)
Recheck test set–up and apply power to unit. If no brief audible tone is heard, turn off power and perform next step.
2)
Remove dust cover, turn on power and check if red FAULT LED (CR5) at the center of the Store Processor PWA, P/N 205E0601–00 and 205– E1027–00, is lit (refer to IPL Figure 6, item 20). This LED lights continu– ally whenever a fault exists in the A100S and, for a period of 5 seconds, whenever a Bulk Erase cycle is initiated.
3)
Check power supply voltages at the Aircraft Interface PWA, P/N 205E0597–00: TP2 – (+12 Vdc); TP3 – (–12 Vdc); TP4 – (+5 Vdc)
4)
If regulated voltages are incorrect, check input line voltage. If input is correct, turn power off and remove and replace Aircraft Interface PWA. To remove, refer to the Disassembly Section. For further troubleshooting, refer to Table 106.
5)
If input and regulated voltages are correct, remove and replace Audio Processor PWA, P/N 205E0598–00. To remove, refer to the Disassembly Section. For further troubleshooting, refer to Table 107.
6)
Apply power and check if red FAULT LED on Store Processor PWA is still lit. If so, remove and replace Store Processor PWA. To remove, refer to the Disassembly Section. For further trouble shooting, refer to Table 108.
NOTE Whenever power to the unit under test is removed and reapplied, the BULK ERASE pushbutton on the Test Panel must be pressed for approximately 3 to 4 seconds and released to clear a pre–existing memory fault condition.
NOTE Store Processor PWA, P/N 205E0601–00, is to be used only with FCSSU, P/N 253E0348–03. Store Processor PWA, P/N 205E1027–00, is intended to be used with FCSSU, P/N 253E0660–00 but may be used with either model FCSSU.
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Table 105 System Level Troubleshooting (Continued) STEP B.
TEST DESCRIPTION
EXPECTED RESULTS
Power–On Test (continued)
FAULT ISOLATION PROCEDURE 7)
If the red FAULT LED on the new Store Processor PWA lights upon powering up, turn power off and remove and replace the FCSSU. Refer to the Disassembly section.
8)
Apply power and check if red FAULT LED on Store Processor PWA lights after power up and memory cleared. If this is the case, assemble unit as first tested and return to factory for servicing and recertification.
1)
If power consumption is excessive, turn power off at the Test Panel.
2)
Disconnect the recorder from the Test Panel.
3)
Using an ohmmeter, measure the resistance between input connector, J1, pin 2 (115 Vac Hot), pin 3 (115 Vac cold), and J1 pin 17 (chassis ground). There should be an open between the power pins and chassis ground. If a power line is shorted to ground, remove and replace the Aircraft Interface PWA, P/N 205E0597–00. If no short is de– tected, perform next step.
4)
Disconnect Store Processor PWA Cable Assembly W2 (plug P5) from connector J5 of the Aircraft Interface Cable Assembly W1. Remove Audio Processor PWA from the recorder.
5)
Reconnect the recorder to the Test Panel and apply power.
6)
If power consumption is now within limits, turn power off, reconnect the Store Processor PWA Cable Assembly W2/P5 to connector J5 of the Aircraft Interface Cable Assembly W1.
NOTE Store Processor PWA, P/N 205E0601–00, is to be used only with FCSSU, P/N 253E0348–03. Store Processor PWA, P/N 205E1027–00, is intended to be used with FCSSU, P/N 253E0660–00 but may be used with either model FCSSU.
Power consumption less than 12 watts.
NOTE Whenever power to the unit under test is removed and reapplied, the BULK ERASE pushbutton on the Test Panel must be pressed for approximately 3 to 4 seconds and released to clear a pre–existing memory fault condition.
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Table 105 System Level Troubleshooting (Continued) STEP B.
TEST DESCRIPTION
EXPECTED RESULTS
Power–On Test (Continued)
NOTE Store Processor PWA, P/N 205E0601–00, is to be used only with FCSSU, P/N 253E0348–03. Store Processor PWA, P/N 205E1027–00, is intended to be used with FCSSU, P/N 253E0660–00 but may be used with either model FCSSU.
FAULT ISOLATION PROCEDURE 7)
Remove the four screws securing the Store Processor PWA to the FCSSU and disconnect the Store Processor PWA connector J2 from the FCSSU interface connector P2. Reapply power.
8)
If power consumption is excessive, turn power off and remove and replace the Store Processor PWA.
9)
If power consumption is within limits, turn power off and reconnect the Store Processor PWA J2 connector to the FCSSU connector P2 and using four screws secure in place.
10) Turn power on. If power drain is still excessive, remove and replace the FCSSU. 11) Reinstall Audio Processor PWA. Turn power on. If power consump– tion is excessive, remove and replace the Audio Processor PWA. 12) If power consumption remains excessive after performing the previous steps, turn power off and remove and replace the Aircraft Interface PWA.
C.
All Test indicates in the green
a.) ALL TEST meter
1)
Turn power off. Remove and replace the Audio Processor PWA.
“GOOD” area while ALL TEST button is pressed.
2)
If ALL TEST continues to fail, remove and replace the Store Processor PWA.
3)
If ALL TEST continues to fail, remove and replace the FCSSU.
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Table 105 System Level Troubleshooting (Continued) STEP C.
D.
E.
TEST DESCRIPTION
EXPECTED RESULTS
ALL Test (Continued)
Playback Test
Bulk Erase Test
a. Recorder begins playing back data since last power down once “RECORD BIAS” is turned off and the “ALL TEST” button is pressed.
a. Bulk Erase function started when Bulk Erase button is pressed less than two seconds
FAULT ISOLATION PROCEDURE 4)
If ALL TEST continues to fail, re– move and replace the Aircraft Inter face PWA.
5)
If ALL TEST continues to fail, inspect the test set–up.
1)
Check test set–up.
2)
Turn power off to the recorder. At the Test Panel, enable RECORD BIAS. Reapply power and perform an ALL TEST. Continue the ALL TEST for approximately one minute to provide a suitable test signal for the playback test.
3)
Disable the RECORD BIAS. Press the ALL TEST button and release.
4)
If the unit fails to playback the ALL TEST signal recorded since last power–up, remove power and remove and replace the Audio Processor PWA.
5)
If the test continues to fail, remove and replace the Store Processor PWA.
1)
Check test set–up and repeat test.
2)
If a bulk erasing cycle is initiated after pressing BULK ERASE button for less than two seconds, replace the Aircraft Interface PWA.
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Table 105 System Level Troubleshooting (Continued) STEP E.
F.
TEST DESCRIPTION Bulk Erase Test (Continued)
Beacon Test
EXPECTED RESULTS
FAULT ISOLATION PROCEDURE
b. Bulk Erase function 1) starts after pressing BULK ERASE button longer than 2 seconds; a bulk erase tone 2) (approx. 600 Hz) will be heard for 1 – 15 seconds in newer models (13 seconds 3) for older models).
Check test set–up and repeat test ensuring BULK ERASE button is pressed for at least 2 seconds.
c. After Bulk Erase is 1) performed, a sound similar to a “galloping horse” or “tapping 2) fingers” is heard when the unit is put in the playback mode.
If Bulk Erase test fails, remove and replace the Store Processor PWA.
a. When the center– 1) conductor at the underside (silver spot) of the beacon is shorted to the beacon 2) cradle, an audible beep is heard at the beacon test set, if incorporated; other– wise, perform step 2.
Check the battery expiration date printed on the beacon. If expired, replace the beacon.
If Bulk Erase test fails again, remove and replace the Store Processor PWA. If Bulk Erase test still fails, remove and replace the Aircraft Interface PWA.
If Bulk Erase continues to fail, remove and replace the Aircraft Interface PWA.
Remove the beacon and test on the L3 ULD Beacon Tester, P/N 15977. If defective, replace beacon.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
10. MODEL A100S PRINTED WIRING ASSEMBLY (PWA) FAULT ISOLATION Fault Isolation at the Printed Wiring Assembly (PWA) level has been developed for the Model A100S such that expected indications for key signals and test points are described along with the associated circuitry. As such, if an expected indication is not correct, the fault isolation chart will provide the circuitry which is the probable cause of failure for the signal under inspection. Once the probable circuitry is identified, the technician is expected to use common troubleshooting techniques to further isolate the fault to a particular circuit or component.
A. AIRCRAFT INTERFACE PWA FAULT ISOLATION The Aircraft Interface PWA, P/N 205E0597–00, connects the aircraft wiring to the A100S through a 57–pin DPX style connector designated J1. Power regulation, lightning protection, RF attenuation and discrete signal conditioning functions are also performed on this PWA. Refer to the Description and Operation Section, 8.B.(1), for an in–depth functional description of the Aircraft Interface PWA. The fault isolation procedure for the Aircraft Interface PWA is given in Table 106. Refer to the detailed system wiring diagram, Figure A1, and to the Aircraft Interface PWA detailed schematic diagram, Figure A2, given in Appendix A of this manual.
Table 106 Aircraft Interface PWA Fault Isolation Procedure Test Point TP1
Signal Nomenclature System Ground
Functional Description
Expected Possible Faulty Value Stage / Comp.
N/A
N/A
N/A
TP2
+12Vdc
+12V + 10%; <1% RMS ripple
+12V +10%
U2, C15, C16, C17, C18, C19, C22, CR13, CR14, CR15, CR16, CR19, CR24, CR25, T1
TP3
–12Vdc
–12V + 10%; <1% RMS ripple
–12V +10%
U2, C15, C16, C17, C18, C19, C22, CR13, CR14, CR15, CR16, CR19, CR24, CR25, T1
TP4
+5Vdc
+5V + 1%; <1% RMS ripple
+5V + 1%
U2, C15, C16, C17, C18, C19, C22, CR13, CR15 CR14, CR16, CR19, CR24, CR25, T1
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Table 106 Aircraft Interface PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Possible Faulty Value Stage / Comp.
TP5
TEST TONE
640 kHz; this signal is rectified by CR12 & C14 and applied to the 2.5V reference comparator, U4, which is used to develop the /NO FAULT signal, which turns on the +INDICATOR current source. This signal is only applied when the ALL TEST is enabled.
640 kHz sine wave; approx. 12V pk–pk
C12, C13, C20, R1, R2, R3, R4, U1
TP6
+18Vdc regulated (for units prior to S/N 1000, this value will be +30 VDC)
+18V + 15%;<0.1A; <1% rms ripple. The regulated +18V is used to power the Control Unit. The +18V is derived from the –12V.
+18V + 1%
U3, C28, C29, C30, CR20
J2 pin 23
/RECORD
This signal is pulled up to +5V when the RECORD BIAS is in the OFF position.
+5V
U4, C23, C25, R7, R8, R11, CR23, CR26
J2 pin 26
ERASE
This signal is pulled up to +5V when the Erase pushbutton on the test panel or the Control Unit is pressed.
+5V
U4, R7, R8, R15, C24, C26, CR21, CR22
J2 pin 24
TEST
This signal is pulled up to +5V when the ALL TEST button is pushed on the Test Panel or at the Control Unit.
+5V
U4, R7, R8, R12, C21, C27
B. AUDIO PROCESSOR PWA FAULT ISOLATION The primary function of the Audio Processor PWA, P/N 205E0598–00, is to digitize the four audio signals supplied via the Aircraft Interface PWA and to interface with the Store Processor PWA. In doing so, the Audio Processor accepts four channels of cockpit audio and then converts the audio to a digital byte oriented format suitable for storage in the solid–state crash protected memory (FCSSU). Refer to Description and Operation Section 8.B.(2) for an in–depth functional description of the Audio Processor PWA. The Logic Configurable Array (LCA), U13, on the Audio Processor provides a means to perform a closed–loop test, which isolates the Audio Processor PWA from the Store Processor PWA and the FCSSU. As such, component level fault isolation for the Audio Processor is described with the Audio Processor in the test mode.
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As with the Aircraft Interface PWA, fault isolation will be accomplished by listing key signals, describing the expected indications, and identifying the possible faulty circuitry. Once the probable circuitry is identified, the technician is expected to use traditional troubleshooting techniques to further isolate the fault. Set up the Audio Processor PWA for fault isolation as described below and refer to Table 107 for the Audio Processor PWA fault isolation procedure. Refer to the detailed schematic diagram of the Audio Processor PWA, Figure A3, given in Appendix A of this manual. (1)
Audio Processor PWA Fault Isolation Test Set–up This procedure is used to prepare the Audio Processor PWA for fault isolation. (a)
Place the Audio Processor PWA in a known good Model A100S recorder.
(b)
Connect the A100S to the Test Panel as illustrated in Figure 101.
(c)
Adjust the Audio Oscillator for a 3V rms, 1 kHz signal at the RECORDER INPUT terminals on the Test Panel right side when Channels 1, 2 or 3 are to be tested; when Channel 4 is to be tested, adjust for a 2V rms,1 kHz input signal.
(d)
At the Audio Processor PWA, connect point E40 to point E41. This will put the Audio Processor in the test mode.
(e)
Disconnect the connection between the Store Processor PWA Cable Assembly W2, plug P5 and the Aircraft Interface Cable Assembly W1, connector J5.
(f)
Turn power on at the Test Panel.
(g)
At the Audio Processor PWA, momentarily short point E38 to ground. This simulates the system reset pulse required to initiate the Audio Processor’s digital devices.
(h)
Using an oscilloscope, refer to Table 107 and check for the indications described in the fault isolation procedure. Be sure to perform the checks in the sequence described in the procedure. NOTE: Because of the complexity of the digital circuitry, the checks described in the fault isolation chart are not all encompassing; consequently, an identified check may measure as expected and the device might still be faulty at another output. As such, L3 recommends that if the technician cannot isolate a faulty Audio Processor PWA to the component level by following the fault isolation chart, the PWA should be sent back to the factory for repair.
Table 107 Audio Processor PWA Fault Isolation Procedure Test Point U3 pin 1
Signal Nomenclature VBB (–5V)
Functional Description –5V developed for use by the logic devices
Expected Value –5V +10%
Possible Faulty Stage / Comp. U3, C8, C14, C20, C23, C85
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Table 107 Audio Processor PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Value
Possible Faulty Stage / Comp.
U8 pin 5
MCLK1
MCLK1 is a 12.28 MHz crystal–oscillator generated signal applied to pin 1 & 2 of U2 to generate the various clocks required to drive the Audio Processor’s digital devices.
12.28 MHz square wave; approx. 5.0V pk–pk
U8, R6
U2 pin 8
kHz128
kHz128 is a square wave signal derived by U2 from the MCLKI signal. kHz128 is applied to pin 1 of PLD U1 as a clock.
128 kHz TTL level square wave
U2
U1 pin 10
DONE
DONE is a control signal applied to pin 4 of U11 and pin 55 of LCA U13.
Logic High (+5V)
U1, R42
U13 pin 75
XDCLK
XDCLK is an output clock from U13.
Logic Low U13 w/ high pulses
U16 pin 24
/RECFIFO_EMPTY
Control signal generated by FIFO, U16, and applied to the LCA, U13.
Logic High (+5V) High w/Neg. pulses
U16
U12 pin 24
/PLAYFIFO_EMPTY
Control signal generated by FIFO, U16, and applied to the LCA, U13.
square wave High w/Neg. Pulses
U12
U10 pin 8
V1IN
V1IN is the Channel 1 1 kHz analog input conditioned 1V pk–pk and buffered for application sine wave to the encoder/decoder U22.
NOTE: If the 1 kHz signal is present at pin 8, but the amplitude is incorrect perform the AP PWA Input, Gain Calibration procedure given in B.(2) on Page 133. U10 pin 7
V2IN
V2IN is the Ch. 2 analog 1 kHz input conditioned and 1V pk–pk buffered for application sine wave to the encoder/decoder U23.
NOTE: If the 1 kHz signal is present at pin 7, but the amplitude is incorrect perform the AP PWA Input, Gain Calibration procedure given in B.(2) on Page 133.
Adj. pot. R1, U6, U9, U10, T1, C1, C4, C6, C9, C10, C16, C25, C26, R17, R18, R19, R20, R21, R23, R24, R26, R28, R29, R30, R31, R32, R33, R34 Adj. pot. R3, U6, U9, U10, T2, C7, C11, C17, C21, C20, C32, C34, C35, R17, R18, R19, R20, R21, R23, R24, R26, R28, R29, R30, R31, R32, R33, R34
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Table 107 Audio Processor PWA Fault Isolation Procedure (Continued) Test Point U10 pin 14
Signal Nomenclature V3IN
Functional Description
Expected Value
V3IN is the Channel 3 1 kHz analog input conditioned 1V pk–pk and buffered for application sine wave to the encoder/decoder, U24. NOTE: If the 1 kHz signal is present at pin 14, but the amplitude is incorrect, perform the AP PWA Input Gain Calibration procedure given in B.(2) on Page 133.
U9 pin 1
AIN
AIN is the Channel 4 (AREA MIC) analog input conditioned and buffered for application to the encoder/decoder, U25.
Possible Faulty Stage / Comp. Adj. pot. R2, U6, U9, U10, T3, C2, C5, C12, C18, C19, C22, C34, C30, C31, R17, R18, R19, R20, R21, R23, R24, R26, R28, R29, R30, R31, R32, R33, R34
1 kHz 1V pk–pk sine wave
Adj. pot. R4, U6, U9, T4, C13, C5, C27, C33, C36, C37, R17, R18, R19, R21, R23, R29, R30, R31, R32, R33
NOTE: If the 1 kHz signal is present at pin 1, but the amplitude is incorrect, perform the AP PWA Input Gain Calibration procedure given in B.(2) on Page 133. U22 pin 2
V1OUT
V1OUT is the analog output of the encoder/decoder, U22. This signal is applied to summing amplifier network U14.
1 kHz sine wave approx. 2V pk–pk
U22, C28, R22, R25, R27, R36, R37
U23 pin 2
V2OUT
V2OUT is the analog output of the encoder/decoder, U23. This signal is applied to summing amplifier network U14.
1 kHz sine wave approx. 2V pk–pk
U22, C24, R22, R25, R27, R36, R37
U24 pin 2
V3OUT
V3OUT is the analog output of the encoder/decoder, U24. This signal is applied to summing amplifier network U14.
1 kHz sine wave approx. 2V pk–pk
U22, C15, R22, R25, R27, R36, R37
U25 pin 2
AOUT
AOUT is the analog output of the encoder/decoder, U25. This signal is applied to summing amplifier network U14.
1 kHz sine wave approx. 2V pk–pk
U22, C47, R22, R25, R27, R36, R37
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Table 107 Audio Processor PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Value
Possible Faulty Stage / Comp.
U14 pin 14
SUMMING_1
SUMMING_1 is the CH 1 equalized playback signal which is applied to summing amplifier network U5, U4, Q1 & Q2 to generate the COMBINED_AUDIO signal.
1 kHz approx. 3V pk–pk
U14, R35, R38, R39, R40, R41, R43, R46, C64, C66, C68, C71
U14 pin 1
SUMMING_2
SUMMING_2 is the CH 2 equalized playback signal which is applied to summing amplifier network U5, U4, Q1 & Q2 to generate the COMBINED_AUDIO signal.
1 kHz approx. 3V pk–pk
U14, R35, R38, R39, R40, R41, R43, R46, C67, C69, C70, C72
U14 pin 8
SUMMING_3
SUMMING_3 is the CH 3 equalized playback signal which is applied to summing amplifier network U5, U4, Q1 & Q2 to generate the COMBINED_AUDIO signal.
1 kHz approx. 3V pk–pk
U14, R35, R38, R39, R40, R41, R43, R46, C62, C63, C73, C75
U14 pin 7
SUMMING_A
SUMMING_A is the AREA MIC equalized playback signal which is applied to summing amplifier network U5, U4, Q1, & Q2 to generate the COMBINED_AUDIO signal.
1 kHz approx. 3V pk–pk
U14, R35, R38, R39, R40, R41, R43, R46, C65, C76, C78, C80
U4 pin 4
COMBINED_AUDIO COMBINED_AUDIO is the summation of the four audio input channels.
1 kHz sine wave approx. 10V pk–pk
U4, U5, Q1, Q2, CR4, CR5, R7, R10, R11, R12, R13, R15, R48 C81
U15 pin 8
TT_SQ
640 Hz sawtooth approx. 2V pk–pk
U13, U15, CR3, CR6, C77, R8, R9, R14, R16, R45
TT_SQ is only generated when the ALL TEST pushbutton is pressed on the Test Panel or the Control Unit. The Test Tone signal is a 640 Hz, + 20 Hz signal, generated by the LCA, U13.
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Table 107 Audio Processor PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Possible Faulty Value Stage / Comp.
U22 pin 13
XV1_PCM
XV1_PCM is the digitized output of encoder/decoder U22. This signal is applied to ADPCM Computational Processor, U17.
17.3 kHz sawtooth
U22
U23 pin 13
XV2_PCM
XV2_PCM is the digitized output of encoder/decoder U23. This signal is applied to ADPCM Computational Processor, U18.
17.3 kHz sawtooth
U23
U24 pin 13
XV3_PCM
XV2_PCM is the digitized output of encoder/decoder U23. This signal is applied to ADPCM Computational Processor, U19.
17.3 kHz sawtooth
U24
U25 pin 13
XA_PCM
XA_PCM is the digitized output of encoder/decoder U25. This signal is applied to ADPCM Computational Processors, U20 & U21.
17.3 kHz sawtooth
U25
U17 pin 24
RV1_PCM
RV1_PCM is the playback PCM from the Store Processor PWA and the FCSSU Memory. The signal is applied to encoder/ decoder U22 for conversion to an audio output.
17.3 kHz sawtooth
U18
U18 pin 24
RV2_PCM
RV2_PCM is the playback PCM from the Store Processor PWA and the FCSSU Memory. The signal is applied to encoder/ decoder U22 for conversion to an audio output.
17.3 kHz sawtooth
U18
U19 pin 24
RV3_PCM
RV1_PCM is the playback PCM from the Store Processor PWA and the FCSSU Memory. The signal is applied to encoder/ decoder U22 for conversion to an audio output.
17.3 kHz sawtooth
U18
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(2)
Audio Processor PWA Input Gain Calibration NOTE: This adjustment is factory calibrated and should not require field adjustment; however, the following procedure is provided in case it is felt that adjustment is necessary to troubleshoot the Audio Processor PWA. This procedure describes the adjustments of the input gain potentiometers for the four channels on the Audio Processor PWA. (a)
At the Test Panel, reset the test conditions according to that given in step (1) Audio Processor PWA Fault Isolation Test Set–up. Refer to Page 128.
(b)
At the Audio Processor PWA, connect the L3 Audio Monitor Adapter with Modification 1 (AMA/1), P/N 17TES0200, to connector J6 on the Audio Processor PWA (refer to Figure 107).
(c)
Using a “1/4–inch monophonic jack–to–BNC” test cable, connect the AC voltmeter to the respective AMA/1 jack for the A100S channel output to be adjusted. For Model A100S Channel 3
Connect To AMA/1 PILOT jack
Channel 2
CO–PILOT jack
Channel 1
SPARE jack
Channel 4
AREA jack
Combined Audio Channel
COMBINED jack
(d)
Set the Test Panel CHANNEL SELECT switch to the channel to be adjusted and proceed to step (e) or (g).
(e)
To adjust the gain of Channels 1, 2 or 3, verify that a 3V rms, 1 kHz input signal is applied from the Audio Oscillator to the Test Panel RECORDER INPUT terminals.
(f)
While monitoring the AC voltmeter, adjust the input gain for Channels 1, 2 and 3 on the Audio Processor PWA, so that a 1V rms +10% reading is obtained on the AC voltmeter; adjust channel controls as follows (refer to Figure 107 for location): Channel 1 – adjust potentiometer R1. Channel 2 – adjust potentiometer R3. Channel 3 – adjust potentiometer R2.
(g)
To adjust the gain of Channel 4, verify that a 2V rms, 1 kHz signal is applied from the Audio Oscillator to the Test Panel RECORDER INPUT terminals.
(h)
At the Audio Processor PWA, while monitoring the AC voltmeter, adjust the input gain for Channel 4 (Area Mic), using potentiometer R4 (refer to Figure 107), so that 1V rms +10% is obtained on the AC voltmeter.
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U11 CR2
R 5
R 6
C 44
U21
U12
U20
C 42
C41
U2
C 82
+ C 43
C40 U18
U13 U19
C 50
C88
U8 P1
U17 C 46 U1
C49 U16
J5
U24
U23
U22
P1
C 45
L1
U25 R44
J5
R42 CR1 C23
C20
C14
R37
R27
R25
R36
R43
R16 CR6
R39 C 77
R38
J6 J6
R 47
C15 C28
CR5
R41
R9
R40
R8
C72
C76
C68
C78
C63
C66
C65
C64
C67
C73
C69 C C 47 24
C8
C 58
R12
C 39
C30 R 34
U10
C 11
R11
R15 C R R 52 46 48
C81
Q2
U5 C7 C13 C2
R10
R R 21 23
C1
R33 T4
R29 C55
R4
C3 U3 T2
R2 U6 R3 R R 30 32
T3 R1
C60
U9 C37 C18 C35 C9 C61
C 79
U4 C 74
C36 C12 C34 C6 C C R 19 10 R 20 31
Q1
C 48
C C C C 27 31 21 26
C C 22 16 C51
C 38
U7
C C C C C R 17 R 80 71 62 70 C33 C5 C29 C4 22 C32 C25 R 26 R 28 24 C53
CR4
CR3
C75 C59
R13
C 57
U15
R7
R35
C86
R14 R45
C56
U14
C87
R49
R17
T1
R19 R18
R1 - R4
+
C C C 83 85 84
+ +
T1 - T4
Audio Processor PWA, P/N 205E0598–00, Component Layout Drawing Figure 107
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(3)
Model A100S Frequency Response Measurement NOTE 1:
The frequency response of the A100S, for all practical purposes, is guaranteed due to the digitizing process; however, this test, which is described as the frequency response test is often a helpful troubleshooting tool. The electronic circuitry of the Model A100S can be categorized into two general categories: the analog signal–in conditioning circuitry and the memory interface circuitry to include the crash protected memory. The electronics of the analog section can be further divided into individual channel sections which aid in overall troubleshooting.
NOTE 2:
If the frequency response measurement does not check correctly, it is probably due to the encoder/decoder devices located on the Audio Processor PWA (U22 – U25). If that is not the case, refer to the troubleshooting charts for further fault isolation procedures.
(a)
At the Test Panel, reset the test conditions according to that given in step (1) Audio Processor PWA Fault Isolation Test Set–up. Refer to Page 128.
(b)
At the Audio Processor PWA, connect the L3 Audio Monitor Adapter (AMA/1), P/N 17TES0200, to connector J6 on the Audio Processor PWA (refer to Figure 107).
(c)
To monitor Channel 1, connect the SPARE jack to the AC voltmeter using the “1/4–inch monophonic jack–to–BNC” test cable.
(d)
While monitoring the output of Channel 1 with an AC voltmeter, slowly adjust the audio oscillator from 150 to 3500 Hz. The dip–to–peak deviation in the output should be less than or equal to 6 dB.
(e)
Repeat step (d) for Channel 2 connecting the “1/4–inch monophonic jack–to–BNC” test cable to the CO–PILOT jack and to the AC voltmeter.
(f)
Repeat step (d) for Channel 3 connecting the “1/4–inch monophonic jack–to–BNC” test cable to the PILOT jack and to the AC voltmeter.
(g)
For Channel 4 (Area Mic), connect the “1/4–inch monophonic jack–to–BNC” test cable to the AREA jack and to the AC voltmeter. Then, adjust the audio oscillator from 150 to 5000 Hz. Like the other channels, the dip–to–peak deviation in the output should be less than or equal to 6 dB.
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C. STORE PROCESSOR PWA FAULT ISOLATION The Store Processor PWA, P/N 205E0601–00 and 205E1027–00, interfaces the solid–state memory to the Audio Processor PWA via microprocessor U22. In order to provide thirty minutes of continuous recording, the Store Processor aligns the solid–state memory array like a nonvolatile circular buffer, which the Store Processor PWA writes to at the head of the circular buffer and erases at the end of the buffer. The Store Processor PWA can be functionally broken into a control management section and an interface section. Refer to Description and Operation Section 8.B.(3) for an in–depth functional description of the Store Processor PWA. As with the other PWAs in the Model A100S, the fault isolation has been developed such that key test points and signals are described along with their expected indications. If a fault is detected, the fault isolation chart directs the technician to the circuitry which is the probable cause of failure. Once the probable circuitry is identified, the technician is expected to use traditional troubleshooting techniques to further isolate the failure. Refer to the Audio Processor PWA Fault Isolation Test Set–up given in Section (1), Page 128 and setup as directed. Complete the Audio Processor PWA fault isolation procedure successfully and then reconnect the Store Processor PWA Cable Assembly W2/P5, step (e), to the Aircraft Interface Cable Assembly W1 connector J5. Refer to Table 108 and check for the indications described in the Store Processor PWA fault isolation procedure. Detailed schematic diagrams of the two Store Processor PWAs, P/N 205E0601–00 and 205E1027–00, are given in Appendix A, as Figure A4 and Figure A5, respectively.
Table 108 Store Processor PWA Fault Isolation Procedure Test Point
Signal Nomenclature
Functional Description
Expected Possible Faulty Value Stage / Comp.
U16 pin 1
VEE
VEE is a +5V dc supply provided because of the need to save memory pointers and other state variables at power down. VEE is applied to U24, pin 32. U24 is the non–volatile local memory.
+5V + 10%
U16, L3, CR1, CR4, C3, C4,C5, C12
U3 pin 5 (See Pg. A-36)
VPP
VPP is a +12V dc, + 5% supply voltage which is provided to power the crash–protected memory (FCSSU).
+12V + 5%
U3, CR3, L1, R4, C2, C9, C11
Y1 pin 5
CLKIN
CLKIN is a 32 MHz signal provided to micro– processor U22 as a clock signal.
32 MHz square wave approx. 2.5V pk–pk
Y1, R1
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Table 108 Store Processor PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Possible Faulty Value Stage / Comp.
U22
CLKOUT
CLKOUT is the 16 MHz clock output of micro– processor U22.
16 MHz sine wave approx. 2.5V pk–pk
U22
U14
ADR(9...0)
ADR(9...0) is the 10 LSBs of the local address bus.
TTL Data
U14
U10
ADR(19...8)
ADR(19...8) is the10 MSBs of the local address bus.
TTL Data
U10
U20 pin 16
/REC_RD
/REC_RD is the control signal used to read the data from the Audio Processor PWA.
High with negative transitions
U20
U19 pin 5
DLYDCLK
DLYDCLK is the CLKOUT delayed by 13 nanoseconds
16 MHz square wave approx. 2.5V pk–pk
U19
U4 pin 8
/WR_FLASH
/WR_FLASH is the control signal used to read and write data from the crash– protected memory.
Logic High with negative transitions
U14
TP1
/PWR_FAIL
/PWR_FAIL is a power watchdog signal which provides a logic “low” when the LOW_LINE signal goes below acceptable limits.
Logic High
U1, U2, U23, R1, R2, R3, R5, C14
TP2
/RST
/RST is the system reset control signal derived from the condition of the regulated +5V dc. On power–up, /RESET remains low for 35 to 70 ms after Vcc raises above +4.75V. On power–down, /RESET goes low whenever Vcc falls below +4.5V.
Logic High
U1, U2, U23, R1, R2, R3, R5, C14
U6 pin11 – 18
AD(15...8)
AD(15...8) are address bits interfaced from the Audio Processor PWA.
TTL Data
U6, U23, R7, R11
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Table 108 Store Processor PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Value
Possible Faulty Stage / Comp.
U7 pin 11 – 18
AD(7...0)
AD(7...0) are address bits interfaced from the Audio Processor PWA.
TTL Data
U7
U12 pin 2 – 23
AD(8...0)
AD(8...0) are address bits interfaced from the Audio Processor PWA
TTL Data
U12
U15 pins 3, 5, 7, 9, 12, 14,16,18
FADR (14, 13, 11, 9, 7, 6, 4, 1)
These address signals are interfaced to the crash– protected (flash) memory.
TTL Data
U15
U13 pins 3, 5, 7, 12, 14, 16, 18
FADR (0, 2, 3, 5, 8, 10, 12)
These address signals are interfaced to the crash– protected (flash) memory.
TTL Data
U13
U18 pins 2–9, 11–18
AD(7...0) & D(7...0)
U18 buffers the least significant half of the data bus into and out of the crash–protected memory.
TTL Data
U18
U9 pins 2–11, 15–23
FADR(15...23)
Memory address lines
TTL Data
U9
U8 pins 2–11, 15–23
FADR(15...23)
Memory address lines
TTL Data
U8
U11 pins 7, 9–15
SEL(7...0)
Memory select lines
TTL Data
U11
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11. CONTROL UNIT FAULT ISOLATION The Model A100S has been developed to work in conjunction with all existing L3 Control Units. The history of the Control Units is such that there are several variations of the basic control unit. As with the A100S fault isolation procedures, the Control Unit’s fault isolation procedures are presented in tabular (chart) form. The troubleshooting approach for the Control Units differs from the Model A100S in that Control Unit troubleshooting is based on fault recognition versus expected indication as in the Model A100S. This is due to the immense field experience related to the Control Unit. The Control Unit consists of physical connections for a phone jack, primary input/output connector, a meter and various pushbuttons, as well as the MIcrophone Preamplifier PWA (dynamic/condenser). The microphone preamplifier circuitry consists of a series of four amplifier/buffer stages and an AGC circuit. L3 recommends “half–split” troubleshooting methods be used on the preamplifier, largely due to the “flow–thru” nature of the circuitry. Refer to Figure 15 through Figure 24, in the Description and Operation Section for wiring diagrams of the different versions of the L3’ Control Units. Table 109 provides the system level troubleshooting procedure for the Control Unit. Refer to Table 110 for the procedure to troubleshoot Control Unit Microphone Preamplifiers 9300A030 and 93A263–01, Table 111 for the procedure to troubleshoot Control Unit Microphone Preamplifier 93A263–02 and to Table 112 for the procedure to troubleshoot Microphone Preamplifiers 9300A242, 93A266 and 93A266–01. Refer to Appendix A for schematic diagrams of the Control Unit Microphone Preamplifier PWAs (Figures A6 and A7).
Table 109 System Level Troubleshooting Procedure for Control Units Trouble
Probable Cause
1. Control Unit (a) does not work
2. Meter and switches do not work 3. Microphone inoperative or garbled
Control Unit wiring har– ness with opened or shorted leads
Remedy (1)
Check out internal wiring connections and repair if necessary.
(2)
Repair wiring.
Refer to the System Level Troubleshooting given in Table 105 (a)
Defective microphone
(1)
Switch to external mike and feed in 4 mV at 1 kHz. The output should be 0.4 to 0.5 Vac.
(b)
Microphone preamplifier board defective
(1)
Switch to external mike. Measure the output of the microphone with a 10 dB sound source. Level at 1 kHz to be 3 to 6 mV.
(2)
Replace Microphone preamplifier board and calibrate.
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Table 110 Troubleshooting Procedure for Microphone Preamplifiers 9300A030 and 93A263–01 Trouble
Probable Cause
Correction
Low output, not distorted, no AGC
C21, Q5 shorted or R30, C5 open Q6 defective
Replace
Normal output, not distorted, no AGC
R28, C19, D3, R29 open, D2 or C20 shorted
Replace
No 1–kHz rolloff
C8 shorted or R10 open
Replace
No or improper attenuation
C11, C12 shorted, R15, R16, R17, R18, R19 open
Replace
No B+ at any transistor
D1 or R27 open or D1 reversed
Replace
Table 111 Troubleshooting Procedure for Microphone Preamplifiers 93A263–02 Trouble
Probable Cause
Correction
Low output, not distorted, no AGC
C8, Q5 or R10 shorted, C7 open Q6 defective
Replace
Normal output, not distorted, no AGC
R19, C14, D1, R18 open, D2 or C11 shorted
Replace
No 1-kHz rolloff
C5 shorted or R6 open
Replace
No or improper attenuation
C13, C16 shorted, R17, R29, R30, R31, R32 open
Replace
No B+ at any transistor
D4 or R27 open or D4 reversed
Replace
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Table 112 Troubleshooting Procedure for Microphone Preamplifiers 9300A242, 93A266 and 93A266–01 Trouble
Probable Cause
Correction
Low output, not distorted, no AGC
C8, Q5 shorted or R10, C7 open
Replace
Normal output, not distorted, no AGC
R19, C14, D1, R18 open, D2 or C11 open
Replace
No or improper attenuation
C13 or C16 shorted, R17, R29, R30, R31, R27 open
Replace
No B+ at any transistor
D4 or R27 open
Replace
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DISASSEMBLY 1. GENERAL This section contains all the information required to completely disassemble the Model A100S Solid– State Cockpit Voice Recorder and associated Control Units, Models A151/A151B and A152/A152B. This information is coordinated with the Testing and Fault Isolation section probable cause analysis. Access to subassemblies within the Model A100S is described such that there is minimal disturbance to other subassemblies. Loctite or other sealants are used at many places in this recorder. Exercise care when removing screws sealed with the adhesive. CAUTION: THE A100S PRINTED CIRCUIT ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL CIRCUIT BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
2. DISASSEMBLY INSTRUCTIONS Special tools, fixtures, and equipment needed to disassemble and repair the Model A100S are listed in Figure 901. NOTE: Numbers shown in parentheses in the following text and figures are the Illustrated Parts List (IPL) figure number followed by the IPL item number for a particular part; e.g., (7–100) for IPL Figure 7, Item 100. For items listed in the parts list but not illustrated, the item number is preceded by a “–”. In addition to the IPL figure references, each disassembly instruction is accompanied with an illustration showing specific assemblies in which the steps of procedure are related. The figures in this section contain the same figure/item number references identifying the piece parts of the assembly as the IPL figures, however, different views of the assemblies are provided to facilitate disassembly task actions.
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A. UNDERWATER LOCATING DEVICE (Beacon) (See Figure 301 or IPL Figure 2) The Underwater Locating Device (ULD) should be mounted on the A100S front panel so that the beacon water switch is facing to the down (refer to Figure 301, 2–160A and 2–160B). The ULD is equipped with a battery having a life expectancy of six years and may be manufactured by either the Dukane Corporation, P/N: DK120, or Benthos, P/N: ELP–362D. The two ULDs are identical in form, fit and function, so if a new replacement device is needed, it may be ordered directly from L–3 Aviation Recorders (L3AR). When ordering from L3AR, the L3AR part number must be used (Dukane: p/n 266E0305–01, Benthos: p/n 266E0305–02). 2-90 2-105
2-25
2-100
2-110 2-150
2-155
BOTTOM PLATE
2-160A 2-160B
2-155
Disassembly of Underwater Locating Device (ULD) and Dust Cover Assemblies Figure 301 As a general rule, the beacon should be removed from service on or before the expiration date printed on the beacon. The batteries installed in the beacons are field replaceable. Refer to service information provided from their respective manufacturers listed below for servicing and recertification. Dukane Corporation (Cage Code 94970) SeaCom Division, 2900 Dukane Drive St. Charles, IL 60174
Benthos (Cage Code 26858) 49 Edgerton Dr. North Falmouth, MA 02556
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BEACON REMOVAL PROCEDURE (1)
To remove the beacon (2–160A, 2–160B) from the Beacon Mount Assembly (2–150), use a 3/32” Allen hex-wrench, remove the four 8–32 screws (MS–51959–43) and #8 countersink lock-washers (MS–35336–17) that secure the cover plate to the bottom of the Beacon Mount Assembly (also refer to Figure 302). The beacon can now be removed through the bottom opening of the Beacon Mount Assembly (2–150).
(2)
If it is also necessary to remove the Beacon Mount Assembly (2–150), use a 3/16” Allen hex-wrench, remove the four 1/4–20, 3/4” hex-cap screws (2–155) that secure the Beacon Mount Assembly to the front panel (2–110).
(3)
If using the DK100 beacon, replacement of the beacon (2–125) battery should not be attempted in the field. The DK100 beacon should be returned to its respective manufacturer (address listed above) for battery replacement. A new replacement beacon (with six-year battery) may be ordered directly from Aviation Recorders using P/N 266E0305–01/–02.
NOTE:
The replacement beacon should always be inserted into the Beacon Mount Assembly (2–135) with the water switch end to the bottom and the battery replacement date facing to the front.
Beacon Mount Assembly
Cover Plate
Four #8 St. Steel 1508-00 Lockwashers MS-35336-17
Four HexĆcap Screws (2ć155)
Four 8ć32x3/8 Lg. Flat Head Screws MS-51959-43
Underwater Beacon Water Switch End
Disassembly of ULD Cradle Assembly for Beacon Access Figure 302
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B. MAIN CHASSIS DISASSEMBLY (See Figure 301 or IPL Figure 2) (1)
(2)
Dust Cover (2–90) (a)
If the unit is installed in the aircraft rack mount, loosen the lock–down nuts from the two front panel hold–down retainers and disconnect the power/signal input connector from rear panel assembly. Slide the A100S from rack assembly. For further details on the aircraft installation of the unit, refer to the Model A100S Installation and Operating Instructions contained in FAR 04611238.
(b)
Remove the two 5/16” pan–head screws (2–100) which secure the dust cover to the rear panel of the chassis assembly.
(c)
Remove the single 3/8” pan–head screw (2–105) from the top front of the dust cover and slide main chassis assembly (2–25) forward out of the dust cover.
Front Panel Assembly Removal (See Figure 303 or IPL Figure 2) (a)
To remove and disassemble the front panel assembly (2–110), first remove the ULD Cradle assembly as described in Paragraph A.
(b)
Remove four 1/2” pan–head screws (2–180), which secure the two hold–down assemblies (2–175) along with the two pan–head screws (2–115) and fiber washers (2–120) at the top of the front panel.
(c)
Remove the Name Plate (2–130) by the removing four pan–head screws (2–135) that attach it to the front panel.
(d)
Loosen and remove the nut which attaches the Jack Cover (2–195) to Phone Jack assembly (2–190), this is part of the Voice Monitor Cable Assembly W3.
(e)
Gently separate the Front Panel assembly from the Front Isolator Plate (2–70) taking care not to damage the Front Panel Gasket (2–125).
(f)
To remove the handle assembly (2–165), loosen two 1/2” flat–head screws (2–170) from back side of front panel.
NOTE: The Dust Cover assembly does not need to be removed to remove and disassemble the Front Panel assembly.
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2-190
2-125
2-110 2-120 2-115
2-195
2-130 2-70 2-170
2-175 2-180
2-135
2-165
Disassembly of Model A100S Front Panel Assembly Figure 303 (3)
Audio Processor PWA Removal (See Figure 304 or IPL Figure 2 ) (a)
Remove chassis assembly (2–25) from dust cover as described in Step B.(1) and gently lay chassis on its right side.
CAUTION: ELECTROSTATIC DISCHARGE (ESD) WARNING: PRIOR TO HANDLING A PRINTED WIRING ASSEMBLY, ENSURE PROPER PERSONNEL ESD GROUNDING TECHNIQUES ARE USED. ONCE REMOVED, ENSURE THAT THE PRINTED WIRING ASSEMBLY IS PLACED INTO A STATIC SHIELDING CONDUCTIVE BAG.
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(b)
To gain access to the Audio Processor PWA (2–280), remove the card retainer assembly (2–85) by removing the two 1/2” flat–head screws (2–80) which hold it in place.
(c)
To remove the Audio Processor PWA (2–280), pull up on the left and right card guide locks (2–30) and (2–35) and gently pull card out of its slot.
2-80 Aircraft Interface PWA 2-245
2-85 2-248
2-35
Audio Processor PWA (2-280)
P2/J2 (6-310) FCSSU (2-200) Store Processor PWA
2-30
W2 (6-295) 2-25
J5/P1 (6-305)
2-247
Removal of Audio Processor and Store Processor PWAs Figure 304 (4)
Store Processor PWA Removal (See Figure 304 or IPL Figures 2, 5 & 6) (a)
Because the Store Processor Interface Cable Assembly W2 (6–295) is soldered directly to the Store Processor circuit board (5–25), plug P5 (6–300) of the cable assembly (refer to Figure 306) must be removed from the Aircraft Interface Cable Assembly connector J5/W1 (3–245) which is mounted to the chassis (refer to Figure 306).
(b)
Remove the four 3/16” flat–head screws (2–248) which mount the Store Processor PWA (2–247) to the FCSSU unit (refer to Figure 305).
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(c)
Carefully unplug P2 on the FCSSU Unit (2–200 / 2–200A) from connector J2 (6–310) on the Store Processor PWA.
(d)
Gently lift the Store Processor PWA up and away from plug P2 and the FCSSU assembly.
PLUG P5 (6-300)
INTERFACE CABLE ASSEMBLY W2 (6-295)
P2 Four 3/16" Flat-head Screws (2-248)
J2
FCSSU (2-200 / 2-200A)
Store Processor PWA (2-247)
Removal of Store Processor PWA From The Flash Crash Survivable Store Unit (FCSSU) Figure 305 (5)
Aircraft Interface PWA Removal (See Figure 306 or IPL Figures 2, 3 & 6) (a)
After removal of the Dust Cover assembly as described in Step B.(1) place the chassis in its upright position.
(b)
To gain access to the Aircraft Interface PWA (2–245), remove the Audio Processor PWA as described in Step B.(3) above.
(c)
To remove the Aircraft Interface PWA from the Chassis (2–25), the Aircraft Interface Cable Assembly W1 (3–230) must also be removed since this cable assembly is soldered directly to the circuit board.
(d)
To remove the Aircraft Interface Cable Assembly, unplug P5 of the Store Processor Cable Assembly W2 (6–295) from J5 (3–245) of the Aircraft Interface Cable Assembly W1 (3–230).
(e)
Disconnect J5 of the Aircraft Interface Cable Assembly from the chassis by removing two Phillips–head screws (2–60) and self–locking nylon insert nuts (2–65).
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(f)
Disconnect J3 and J4 (2–240) of the Aircraft Interface Cable assembly from the Chassis assembly by removing four straight–slot screws (2–50) and low profile nuts (2–55).
(g)
The Aircraft Interface PWA is mounted to the rear of the chassis. To remove it, remove the five 1/4” flat–head screws (2–260) which mount the circuit board to the standoffs (2–265).
(h)
Remove the four 3/8” flat–head screws (2–255) which secure the Aircraft Interface main connector J1 to the rear of the chassis. Use caution that the three key mounting screws for J1 are not removed on the circuit board by mistake since these screws are accessible from the rear of the chassis and can be easily confused with the four intended mounting screws.
(i)
Disconnect the Aircraft Interface Transformer T1 (3–200) from the rear chassis panel by removing the single 1/4” flat–head screw (2–250). Once disconnected use care to support T1 so its connections to the circuit board are not damaged.
(j)
Carefully slide the Aircraft Interface PWA from the chassis assembly. The standoffs may cause the circuit board to jam between the chassis and closest card guide; consequently, exercise extreme care when removing it.
(k)
To remove the five mounting standoffs (2–265) from the Aircraft Interface PWA, loosen and remove the five 5/16” pan–head screws (2–270) and washers (2–275) from the non–component side of the circuit board. 2-60
J3/J4 of W1 3-240
J5/W1 3-245
2-50
Store Processor Interface Cable Assembly W2 (6-295) with Plug P5 (6-300)
2-25 2-65
2-260
Aircraft Interface Cable Assembly W1 (3-230)
2-250
2-255
2-55
Aircraft Interface PWA 2-265 2-245 2-270 2-275
Figure 306. Removal of Aircraft Interface PWA
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(6)
Flash Crash Survivable Store Unit Removal (See Figure 307 or IPL Figures 2, 5 & 6 )
CAUTION: THE FLASH CRASH SURVIVABLE STORE UNIT (FCSSU) IS A PRECISION ASSEMBLED UNIT WHICH MUST BE RETURNED TO THE FACTORY FOR SERVICING. ATTEMPTING TO DISMANTLE THE SEALED UNIT MAY CAUSE DAMAGE TO THE INTERNAL FLASH MEMORY BOARDS AND RESULT IN LOSS OF DATA. (a)
Remove the dust cover from the Chassis Assembly (2–25) as described in Step B.(1) and gently lay chassis on its right side.
(b)
Remove the Audio Processor PWA (2–280) from its card slot (J4) as described in Step B.(2) to gain access to the rear isolator plate.
(c)
Remove the Front Panel Assembly as previously described in Step B. (2) to gain access to the Front Isolator Plate (2–70); refer also to Figure 307.
NOTE: If it is not necessary to remove the Store Processor PWA along with the FCSSU (2–200), simply remove the four 3/16” flat–head screws (5–30) which secure the Store Processor PWA to the FCSSU (refer to Figure 305), disconnect P2 from J2, and carefully place the circuit board off to the side. If this is the case, omit the following step and proceed to step (e). (d)
To remove the Store Processor PWA with the FCSSU, the Store Processor Interface cable assembly W2 (6–295) plug P5 (6–300) must be disconnected from the Aircraft Interface Cable Assembly connector W1/J5 (3–245) located on the chassis as previously described in Step B.(4).
(e)
At the Front Isolator Panel (2–70), loosen and remove the two10–32 hex–head screws (2–240) and vibration mount spacers (2–235) used to secure the FCSSU to the two forward elastomeric shock mounts (2–205).
(f)
At the Rear Isolator Panel, loosen and remove the two 10–32 Phillips–head screws (2–230) that secure the FCSSU to the two rear elastomeric shock mounts (2–205). This will also detach one end of the grounding strap.
(g)
To remove the ground strap (2–5) from the Rear Isolator Panel, loosen and remove the single 5/16” pan–head screw (2–20) with washer (2–15) and hex nut (2–10).
(h)
Gently slide the FCSSU out from the chassis.
(i)
Return the FCSSU assembly to the factory for servicing.
NOTE: The two forward elastomeric shock mounts (2–205) and the two rear elastomeric shock mounts (2–205) should be carefully inspected at this time for wear and/or damage. If the elastomeric shock mounts need replacing, proceed to step (7).
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10-32 Phillips Screw (2-230)
Rear Isolator Panel
Elastomeric Shock Mount (2-205)
Front Isolator Panel (2-70) Store Processor PWA (See Note)
Vibration Mount Spacer (2-235)
10-32 Hex Screw (2-240)
FCSSU (2-200)
NOTE: Store Processor PWA, P/N 205E0601-00, is to be used only with FCSSU, P/N 253E0348-00. Store Processor PWA, P/N 205E1027-00, may be used with either FCSSU, P/N 253E0348-00, P/N253E0601-00 or 253E1293-00. Store Processor PWA, P/N 205E1027-01, may be used with either FCSSU, P/N 253E0992-00 or 253E1293-00.
Removal of Flash Crash Survivable Store Unit (FCSSU) Figure 307
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(7)
FCSSU Elastomeric Shock Mounts, P/N AM003–7 Removal (See Figure 308 and IPL Figure 2) (a)
Perform steps (a) through (h) of the FCSSU disassembly procedure.
(b)
Remove the damaged elastomeric shock mounts (2–205) from the front isolator panel by loosening and removing the two flat–head screws ((2–210) and nylon insert nuts (2–215).
(c)
Remove the damaged elastomeric shock mounts (2–205) from the rear isolator panel by loosening and removing the two pan–head screws ((2–220) from the captive nylon locking nuts (2–225).
(d)
Attach the new front and/or rear elastomeric shock mounts (2–205) to their respective isolator panel using the hardware removed in steps (2) and (3).
(e)
Return to the FCSSU assembly procedure F. (4) given in the Assembly Section for reinstalling the FCSSU.
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10-32 Phillips Screw (2-230)
Rear Isolator Panel
Elastomeric Shock Mount (2-205)
Front Isolator Panel (2-70) Vibration Mount Spacer (2-235)
(2-215)
Store Processor PWA (See Note)
10-32 Hex Screw (2-240)
(2-210) FCSSU (2-200)
(2-205)
(2-210)
Removal of FCSSU Elastomeric Shock Mounts, P/N AM003–7 Figure 308
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C. MODEL A151/A151B AND A152/A152B CONTROL UNIT DISASSEMBLY (See IPL Figure 7) NOTE:
(1)
This control unit disassembly procedure covers all models of the control unit used with the Model A100S. Disregard those steps and parts that do not pertain to the exact model of control unit being disassembled. For specific effectivity of parts to configuration, refer to the EFF Code column in IPL Figure 7.
Remove two 1/4” pan–head screws (7–65) with washers (7–60) and pull the dust cover (7–55) from the front panel assembly (7–15) and chassis assembly (7–90). NOTE: Do not perform the next step to remove the insulator unless replacement is necessary.
(2)
Remove insulator (7–70) from bottom of dust cover.
(3)
Remove Microphone Preamplifier PWA (7–155) from the chassis assembly by removing four 3/8” pan–head screws (7–160).
(4)
Remove front panel assembly (7–15) from chassis by removing four 3/8” pan–head screws (7–20).
(5)
Remove harness wires from the Microphone Preamplifier PWA (7–155), meter (7–25), switches (7–30 and 7–35), and phone jack (7–40). Remove microphone wires from harness assembly connector (7–80) or Microphone Preamplifier PWA (7–155) as appropriate for the type configuration.
(6)
Remove meter (7–25) by unscrewing the rear collar and pulling meter assembly from the face of the front panel assembly.
(7)
Remove green test switch (7–30) and red erase switch (7–35) by removing their associated nuts and washers and pulling the switches from the rear of the front panel assembly.
(8)
Remove the phone jack (7–40) by removing attaching plug (7–50), nut, washer and one shoulder washer (7–45) from the face of the front panel assembly while pulling the second shoulder washer (7–45) and phone jack (7–40) from the rear. NOTE: Perform the next step only if microphone or harness assembly replacement is necessary. The microphone is nested in a damper (7–105 and 7–135) and hum shield (7–115) which is cemented in place. Exercise caution when removing the microphone (7–110 and 7–140) and/or damper to prevent damage to the damper. Microphone cap (7–75), if installed in place of a microphone, may be removed at any time to facilitate disassembly, inspection, replacement or repair.
(9)
Remove the microphone (7–110 and 7–140) by removing the grommet (7–120) from the microphone damper assembly (7–105 and 7–135), loosen microphone cap (7–75) and washer (7–150) and pull free of microphone hum shield (7–115) from the face of the front panel assembly.
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ÀÀ ÀÀ ÀÀ
7-15 7-20
7-115 7-75
7-30 7-35 7-40
7-110 7-140
7-60 7-65
7-150 7-45 7-25 7-50
7-105 7-135 7-55
7-85 7-70 7-90 7-80
7-120 7-160
7-155
Disassembly of Model A151/A151B and A152/A152B Control Units Figure 309
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D. ELECTRONIC CIRCUIT BOARD DISASSEMBLY (See IPL Figures 3–16) The procedures listed in this section are general in nature. The components used on the A100S printed wiring assemblies are advanced electrical circuits protected by conformal coating and are very heat, static and shock sensitive. Extreme care should be exercised when repairing these circuit boards. It is highly recommended that a defective circuit board be returned to the factory for repair. CAUTION: THE A100S PRINTED CIRCUIT BOARDS CONTAIN DEVICES THAT ARE SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL PRINTED CIRCUIT BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
(1)
Remove any circuit board assembly which needs replacement or repair as described in the previous steps. All of these circuit board assemblies are shown in detail in the Illustrated Parts List with their accompanying schematic diagrams located in Appendix A.
(2)
To remove protective conformal coating on the circuit board, rub the area around the damaged component with a cotton swab soaked with alcohol. Any residual coating can be removed by the soldering iron prior to desoldering terminals.
(3)
Protect the component to be removed by using a heat–sink clamp between the soldering point and the component itself.
(4)
Using an Endeco Model 300 vacuum desoldering iron, or equivalent, heat the connection on the terminal in question until the solder becomes liquid and remove it with the vacuum bulb.
(5)
Straighten the bent lead using needle–nose pliers and pull the component lead from the board.
(6)
Repeat Steps 2 through 5 for each component to be replaced.
(7)
Refer to the Assembly section of this Component Maintenance Manual for any special instructions on installing components.
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CLEANING 1. GENERAL This section contains a list of all required cleaning materials, general cleaning procedures, applicable cautions and warnings related to the use of any cleaning material, and instructions for cleaning the Model A100S major assemblies.
2. MATERIALS REQUIRED Refer to Table 401 for a listing of required cleaning materials:
Table 401 Cleaning Materials Required Material
Specification
Dry–Cleaning Solvent Isopropyl Alcohol Soft–Bristle Brush Cotton Swabs Lint–Free Cotton Cloth
Federal Specification P–D–680
NOTE: Equivalent substitutes may be used for all cleaning materials. All materials and chemicals may be obtained from any commercial source.
3. CLEANING PROCEDURES WARNINGS:
1) OBSERVE ALL FIRE PRECAUTIONS WHEN USING FLAMMABLE MATERIALS FOR CLEANING PURPOSES. 2) PERFORM OPERATIONS INVOLVING CLEANING SOLVENT IN A WELL– VENTILATED AREA. AVOID PROLONGED BREATHING OF VAPORS OR CONTACT WITH SKIN.
CAUTION: THE A100S PRINTED CIRCUIT ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL CIRCUIT BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
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CAUTION: DO NOT IMMERSE ANY PRINTED WIRING ASSEMBLY MOUNTED ELECTRONIC PARTS IN THE CLEANING SOLVENT; OTHERWISE, CIRCUIT BOARD AND/OR COMPONENT DAMAGE MAY RESULT.
A. PRINTED WIRING ASSEMBLY CLEANING (1)
Remove dust, dirt, and foreign matter from all surfaces, using soft–bristle brush.
(2)
Wipe finished surfaces and contacts, using a cloth moistened in solvent.
(3)
After replacing any components, clean all solder joints with solvent prior to recoating the repaired area.
B. CONNECTOR CLEANING Wipe dust and dirt from connectors, using a lint–free cloth, moistened with solvent.
C. MACHINED METAL PARTS CLEANING (1)
Blow dust from surface, holes, and recesses with an ionized air nozzle.
(2)
Remove bulk of surface grease and dirt with rags.
(3)
Immerse metal parts in a washing bath of solvent and scrub until clean.
(4)
Remove parts from bath and permit to dry.
(5)
Immerse parts in a rinsing bath; rinse and remove from bath. Do not permit solution to remain trapped in holes and recesses during draining.
(6)
Dry in a dust–free area.
D. UNDERWATER LOCATING DEVICE (Beacon) CLEANING The Model A100S beacon water switch should be kept clean by wiping with a soft lint-free cloth at least once every 24 months (more frequently under high humidity conditions). The beacon cradle is positioned on the A100S front panel so that the water switch is facing down; refer to Figure 401 for manner of installation. The beacon cleaning procedure requires no disassembly and consists only of cleaning the center contact of the beacon water switch. Make sure the beacon case and water switch are free of dirt and/or grease film. If necessary, take the beacon out of the mounting bracket assembly as shown in Figure 401 and wipe clean with approved cleaning agent. The water switch end insulator must be free of dirt, lint, or moisture to prevent current from leaking across the switch. As an added note, there are two types of beacons used with the Model A100S. Each is equipped with a battery having an expected life of six years. The two approved beacons are the Dukane beacon, P/N DK120, and a Benthos beacon, P/N ELP–362D. The two beacons are identical in form, fit, and function but carry different part numbers. The Dukane beacon, p/n: 266E0305-01, and the Benthos beacon, p/n: 266E0305-02, may be ordered directly from Aviation Recorders using these numbers.
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As a general rule, the beacon should be removed from service on or before the expiration date printed on the beacon. The batteries installed in the DK120 or ELP–326D beacons are field replaceable. Refer to service information provided from their respective manufacturers listed below for servicing and recertification. Dukane Corporation
(Cage Code 94970) SeaCom Division, 2900 Dukane Drive St. Charles, IL 60174
Benthos (Cage Code 26858) 49 Edgerton Dr. North Falmouth, MA 02556
Beacon Mount Assembly
Cover Plate
Four #8 St. Steel 1508-00 Lockwashers MS-35336-17
Four HexĆcap Screws (2ć155)
Four 8ć32x3/8 Lg. Flat Head Screws MS-51959-43
Underwater Beacon Water Switch End
Underwater Locating Device (ULD) Beacon Water Switch Location Figure 401
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CHECKS 1. GENERAL This section contains the various checks that should be performed on the Model A100S Solid–State Cockpit Voice Recorder during shop maintenance. Check procedures are written in step–by–step procedures wherever practicable, and include specific methods, techniques, and equipment required. Electrical set up and checks are given in the Testing and Troubleshooting Section of this Component Maintenance Manual. There is no periodic maintenance requirements for the A100S SSCVR. CAUTION: THE A100S PRINTED CIRCUIT ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL CIRCUIT BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
2. CHECKS A. MAIN RECORDER ASSEMBLY (1)
Check the general physical integrity of the recorder; i.e. front panel switches, microphone jack, Underwater Locating Device and rear panel connector pins.
(2)
Check that dust cover is serviceable, exhibiting no undue deterioration and is properly painted.
B. MECHANICAL INSPECTION (1)
Remove the unit dust cover.
(2)
Inspect all parts for cracks, distortion, excessive wear, and proper finish.
(3)
Inspect all cast parts for cracks, especially at bosses, flanges, and other critical areas.
(4)
Inspect all terminal boards and connectors for loose terminals, pins, locking rings and screws, and cracks in the boards that may have been brought about by environmental conditions.
(5)
Check all wire leads for broken conductors, burnt or deteriorated installation, and loose connections.
(6)
Check the electronic circuit boards for broken parts and bad solder joints. Check for burnt parts. Check the boards for cracks and abrasions.
(7)
Inspect the nameplate for legibility.
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C. ELECTRICAL INSPECTION Perform all test set–up and testing per instructions given in the Testing and Troubleshooting Section of this Component Maintenance Manual.
D. UNDERWATER LOCATING DEVICE (ULD) INSPECTION The ULD beacon used in the A100S is equipped with a battery having an expected life of sixyears. Detailed procedures for testing the Underwater Locating Device are located in the Beacon section of Table 102. The beacon should be removed from service on or before the expiration date printed on the beacon. The batteries installed in the DK120 or ELP–326D beacons are field replaceable. Refer to service information provided from their respective manufacturers listed below for servicing and recertification. The ULD used with the Model A100S may be manufactured by either the Dukane Corporation (P/N DK120) or Benthos (P/N ELP–362D); their addresses are as follows: Dukane Corporation
(Cage Code 94970) SeaCom Division, 2900 Dukane Drive St. Charles, IL 60174
Benthos (Cage Code 26858) 49 Edgerton Dr. North Falmouth, MA 02556
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REPAIR 1. GENERAL This section is intended to contain information required to restore a worn or damaged part to a serviceable condition. Since the Model A100S is a completely solid–state device containing no electro– mechanical moving parts, the information presented herein applies only to the repair of a printed wiring assembly. The components used on the PWA circuit boards of the Model A100S are advanced electrical circuits protected by conformal coating and are heat, static and shock sensitive. Extreme care should be used when repairing these boards. It is highly recommended that a known bad circuit board be returned to the factory for repair. If in–field repair of a printed wiring assembly is necessary (such as board surface damage or replacing damaged electrical components such as capacitors, resistors, transistors, transformers, and integrated circuits), refer to the Disassembly Section if its removal is not obvious and to the Illustrated Parts List Section for its parts listing. Replace all components not meeting the requirements outlined in the Testing and Troubleshooting Section. Remove loose conductive material in accordance with the Cleaning Section. Table 601 lists the basic repair materials required.
Table 601 Repair Materials Required Item
Manufacturer and Specification
Use
1. Soldering iron
25–watt pencil tip and standard IC tips
PWA component removal
2. Solder
Tin lead rosin core 60/40 per QQ–S–571
To tin all component leads and wires
3. Adhesive
Methylene dichloride cracks and fractures
For repairing minor
CAUTION: THE MODEL A100S PRINTED WIRING ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE CIRCUIT BOARD USELESS. PRIOR TO HANDLING A CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, WHEN THE CIRCUIT BOARDS ARE TO BE STORED, ENSURE THAT THEY ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
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2. REPAIR PROCEDURES A. PRINTED WIRING ASSEMBLIES (Refer to applicable IPL Figures.) CAUTION:
(1)
USE A PAIR OF LONG–NOSED PLIERS OR OTHER SUITABLE HEAT SINK PROTECTION WHEN REMOVING HEAT–SENSITIVE COMPONENTS SUSPECTED OF BEING FAULTY. THE SAME APPLIES WHEN INSTALLING NEW HEAT–SENSITIVE COMPONENTS
Do not remove any component from the circuit board unless deemed faulty. To remove a component, unsolder the appropriate leads using a 25–watt pencil tip soldering iron. Tag the unsoldered leads to facilitate reassembly. Verify polarity and or orientation of the component. CAUTION:
IN ADDITION TO USING A PROPER HEAT SINK WHEN SOLDERING A SOLID–STATE DEVICE, EXERCISE EXTREME CARE TO USE A MINIMUM OF HEAT WHILE SOLDERING TO PREVENT DAMAGE TO THE CIRCUIT BOARD.
(2)
All components must be physically secured to the non–printed side of the circuit board by inserting the leads in the appropriate holes and bending the ends of the lead wires inward approximately 1/8 inch. The part should make physical contact with the board. Also, make certain all component markings or values face upward and are readable.
(3)
Make certain all connections are mechanically strong before attempting to solder. Solder per MIL–S–6872.
(4)
Remove any old or excessive solder as required.
(5)
Remove flux residue with Alpha No. 563 cleaner and flux remover. Perform final wash in clean solution of the same cleaner.
(6)
Apply protective coating (PC18 or PC29M manufactured by Hysol Division of Dexter Corporation or Conathane 1155 per MIL–I–46058 type PUR) to all reworked areas of the circuit board as follows: (a)
Ensure that printed circuit board is clean and dry.
NOTE: The protective coating is to be applied only to components that have been replaced. (b)
Coating may be sprayed or applied with a brush.
(c)
Cure coating per manufacturer instructions.
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ASSEMBLY 1. GENERAL This section contains detailed step–by–step procedures describing the complete assembly of the Model A100S Recorder. Any testing during assembly is also included as well as storage instructions after assembly.
2. REQUIRED MATERIALS Refer to Table 701 for a tabular listing of required assembly materials. There are no special tools or equipment required during assembly. Special equipment required for unit testing can be found in Table 901 of the Special Tools, Fixtures, and Equipment Section.
3. ASSEMBLY INSTRUCTIONS CAUTION: THE MODEL A100S PRINTED WIRING ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE CIRCUIT BOARD USELESS. PRIOR TO HANDLING A CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT THE CIRCUIT BOARD IS PLACED INTO A STATIC SHIELDING CONDUCTIVE BAG WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
A. GENERAL ASSEMBLY TECHNIQUES Though procedures listed in this section are general in nature, some of the circuit components require special handling and preparation before installation. The components used on the PWA circuit boards of the Model A100S are advanced electrical circuits protected by conformal coating and are heat, static and shock sensitive. Extreme care should be used when repairing these boards. It is highly recommended that a known bad circuit board be returned to the factory for repair. NOTE: Numbers shown in parentheses in the following text are the Illustrated Parts List (IPL) figure number followed by the IPL item number for a particular part; e.g., (8–115) for IPL Figure 8, Item 115. For items listed in the parts list but not illustrated, the item number is preceded by a “–”. (1)
Remove old solder and make connections mechanically secure before resoldering.
(2)
Sleeve component leads and jumper wires as required to prevent shorting.
(3)
Use 60/40 solder (Item 1, Table 701) throughout.
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Table 701 Required Assembly Materials (Sheet 1 of 2) Item
Manufacturing and Specification
Use
1. Solder
Resin core 60/40 per QQ–S–571
All Component leads and wires.
2. Protective coating
PC18 or PC29M manufactured by Hysol Division of Dexter Corp. [V04347], 211 Franklin St., Olean, NY 14760 or Conathane 1155 per MIL–I–46058 type PUR.
Printed wiring assembly coating and solder connections.
3. Cleaner/flux remover
Alpha No. 563
Clean new solder joints.
4. Primer
Loquic primer, Grade N No. 88–21 manufactured by Loctite Corp., 705 N. Mountain Rd., Newington, CT 06111 [V05972]
Primer for items 5, 6, 7, 8.
5. Adhesive
Loctite, Grade A manufactured by Loctite Corp., 705 N. Mountain Rd., Newington, CT 06111 [V05972]
Retain screws.
6. Adhesive
Loctite, Grade C No. 84–21 manufactured by Loctite Corp., 705 N. Mountain Rd., Newington, CT 06111 [V05972]
Retain screws.
7. Adhesive
Loctite, No. 222 Lock/sealant manufactured by Loctite Corp., 705 N. Mountain Rd., Newington, CT 06111 [V05972]
Retain screws.
8. Adhesive
Loctite, No. 242 Lock/sealant manufactured by Loctite Corp., 705 N. Mountain Rd., Newington, CT 06111 [V05972]
Retain screws.
9. Adhesive
Glyptal No. 1201 manufactured by General Electric Co., Silicone Products Business Dept., Waterford, NY 12188 [V01139]
Retain screws.
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Table 701 Required Assembly Materials (Sheet 2 of 2) Item
Manufacturing and Specification
Use
10.
Adhesive
Rubber cement No. EC847 manufactured by Minnesota Mining and Mfg. Co., Adhesive Coatings and Sealers Div., 3M Center, St. Paul, MN 55101 [V04963]
Secure gasket to cover.
11.
Adhesive
RTV–108, G. E.
Sealant, Gen. Purp.
12.
Adhesive
RTV 162 white
Secure components.
13.
Adhesive
RTV–106 red
Secure components.
14.
Tubing
Shrink tubing, black, 0.063 I.D. No. FIT–221–1/16 manufactured by Alpha Wire Corp, 711 Lidgerwood Ave., Elizabeth, NJ 07207 [V92194]
Insulate wire leads.
15.
Tubing
Shrink tubing, white 3/16 thermo–fit No. RNF–100–3/16–WHT manufactured by Raychem, [V06090]
Insulate wire leads.
16.
Wire
No. 26 AWG hook–up wire, TFE Teflon, 14/38 strand, 0.041 O.D., red
Electrical wiring.
17.
Wire
No. 26 AWG hook–up wire, TFE Teflon, 19/38 strand, 0.041 O.D., orange
Electrical wiring.
18.
Wire
No. 20 Stranded Wire, White 600 V.
Electrical wiring.
19.
Lubricant
810–346 manufactured by Dukane, Ultrasonic Division, St. Charles, IL 60174 [V94970]
Lubricate ULD O–ring and threads
20.
Sealant
Compound Silicon RBR Dow Corning
Sealant, Gen. Purp.
21.
Adhesive
RTV–3145, Corning
Sealant, Silicone Rbr.
22.
Jumper
Wire, #22 BUSS SOLID – L3 P/N 2769900008
Jumper Wire
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B. GENERAL CIRCUIT BOARD ASSEMBLY (See applicable IPL Figures) (1)
After removal of a defective component from a circuit board following the procedures described in DISASSEMBLY, the following procedures must be followed when replacing the electronic components. (a)
All components must be physically secured to the non–printed side of the circuit board by inserting the leads in the appropriate holes and bending the ends of the lead wires inward approximately 1/8 inch. The part should make physical contact with the board.
(b)
All terminal posts should be riveted in place before soldering.
(c)
Leads from components mounted to terminal posts must have a minimum 300 wraparound.
(d)
Component markings or values should face upward and be readable.
(e)
On all IPL and schematic drawings, the (square) pad indicates (+) positive end of capacitors, cathode end of diodes and mechanical orientation of symmetrical multi– leaded devices.
(2)
Solder components in place (following the appropriate schematic) with a small pencil iron rated at no more than 25 watts. Use rosin core 60/40 solder (Item 1, Table 701).
(3)
Remove flux residue with Alpha No. 563 cleaner and flux remover (Item 3, Table 701). Perform final wash in clean solution of the same cleaner.
(4)
Apply protective coating (Item 2, Table 701) to all repaired areas as follows: (a)
Ensure that printed wiring boards are clean and dry.
NOTE: Protective coatings are to be applied only to components that have been replaced. (b)
Coating may be sprayed, applied with a brush, or board may be dipped.
(c)
Cure coating per manufacturer instructions.
C. AIRCRAFT INTERFACE PWA, P/N 205E0597–00 (See IPL Figures 2 & 3) (1)
Special installation Instructions for components on this circuit board are as follows: (a)
Connect transformer T1 to the board per the following list using #20 stranded white wire (Item 18, Table 701) and cover terminals with white tubing (Item 15, Table 701). T1–1 T1–2 T1–3 T1–4
(b)
to to to to
E5 E6 E7 E8
After installing T1, generously apply silicon sealant (Item 20, Table 701) on the non– component side for 115 volt protection over the following pins: J1–2, J1–3, C16, C17, CR14, CR25, E5, E6, L1–L3, and C35–C38.
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(c)
Apply silicon sealant (Item 20, Table 701) generously as follows: under between
U2, U3, C19 and C22; CR7 & CR3, CR3 & CR4, CR4 & CR8, CR5 & CR6, CR6 & CR1, CR1 & CR2. at base of CR31.
(2)
(d)
When installing connector J1 (3–210) only use one of the mounting screws (3–220) and washers (3–215) where shown in IPL Figure 3. Apply locking compound (Item 7, Table 701) to threads of screw (3–220).
(e)
Install power supply (3–55) with washers (3–60) between part body and printed wiring board on each pin.
(f)
Install transistor pads (3–75/3–90) beneath CR3 (3–70) and Q1 (3–85), respectively.
(g)
Install the five mounting standoffs (2–265) to the Aircraft Interface board, using five 5/16” pan–head screws (2–270) and washers (2–275) on the non–component side of the board.
Installation of Aircraft Interface PWA into Chassis assembly: (a)
It is assumed that the Audio Processor PWA (2–280) is not in its card slot, J4, since this interface connector is an integral part of the Aircraft Interface Cable Assembly W1 (3–230).
(b)
To install the Aircraft Interface PWA into the Chassis (2–25), the Aircraft Interface Cable Assembly W1 (3–230) must also be installed since this assembly is hard soldered to the board.
(c)
Attach connectors J3 (2–240) and J4 (2–240) of the Aircraft Interface Cable Assembly W1 to the Chassis assembly by installing four straight–slot screws (2–50) and low profile nuts (2–55).
(d)
Attach J5 of the Aircraft Interface Cable Assembly W1 to the Chassis assembly by installing two Phillips screws (2–60) and self–lock nylon insert nuts (2–65).
(e)
Connect plug P5 of the Store Processor Cable Assembly W2 (6–300) to connector J5 (3–245) of the Aircraft Interface Cable Assembly W1 (3–230).
(f)
Carefully slide the Aircraft Interface PWA into the chassis assembly while supporting transformer T1. Exercise care while positioning the board in place since the board standoffs may cause it to jam between the chassis and the closest card guide; do not force board.
(g)
Mount the Aircraft Interface transformer T1 (3–200) to the rear chassis panel by installing the single 1/4” flat–head screw (2–250).
(h)
Attach the four 3/8” flat–head screws (2–255) which secure the Aircraft Interface main connector, J1, to the rear of the Chassis.
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(i)
Attach the five 1/4” flat–head screws (2–260) which mount the PWA to the standoffs (2–265).
(j)
Once the Aircraft Interface PWA is secured in place, install the Audio Processor PWA by sliding it into its card slot (Aircraft Interface Cable Assembly W1 connector J4) and securing it in place by pushing down on the left and right card guide locks (2–30) and (2–35).
(k)
Attach the card retainer assembly (2–85) by installing two 1/2” flat–head screws (2–80).
(l)
Slide the chassis assembly (2–25) into the dust cover (2–90 and attach with the single 3/8” pan–head screw (2–105) in the top front of the dust cover and with the two 5/16” pan–head screws (2–100) which secure the dust cover to the rear panel of the chassis assembly.
D. AUDIO PROCESSOR PWA, P/N 205E0598–00 (See IPL Figures 2 & 4) (1)
Special installation Instructions for components on this circuit board are as follows: (a)
(2)
Apply a thin coat of adhesive (Item 21, Table 701) to the inside of the transformer covers (4–360) which attach to T1–T4 (4–355).
Installation of Audio Processor PWA into the Chassis assembly: (a)
Install the Audio Processor PWA by sliding it in its card slot (connector J4 of the Aircraft Interface Cable Assembly W1) and securing it by pushing down on the left and right card guide locks (2–30) and (2–35).
(b)
Attach the card retainer assembly (2–85) by installing two 1/2” flat–head screws (2–80).
(c)
Slide the chassis assembly (2–25) into the dust cover (2–90 and attach with the single 3/8” pan–head screw (2–105) in the top front of the dust cover and with the two 5/16” pan–head screws (2–100) which secure the dust cover to the rear panel of the chassis assembly.
E. STORE PROCESSOR PWA, P/N 205E0601–00 and P/N 205E1027–00 (See IPL Figures 2, 5 & 6) (1)
Special installation instructions for circuit board, P/N 205E0601–00, are as follows: (a)
Install C8 (6–275) under U5 (6–45) between its socket strips (6–50).
(b)
Install C7 & C13 (6–285) under U4 (6–25) between its socket strips (6–30).
(c)
Install C10 (6–255) under U22’s (6–100) socket (6–105).
(d)
Install C15 (6–245) under Y1 (6–125).
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(2)
(e)
Install dip capacitors C1XX (6–225, 230, 235, 240, 250 & 260) in the same holes as their corresponding integrated circuits UXX. Note: the reference designators for the dip capacitors are similar to their corresponding IC’s plus 100. For example: C123 is located under U23, etc.
(f)
When installing C102 (6–250) under U2 (6–125) be sure to orient C102 correctly, the power pins for U2 are pins 2 and 3.
(g)
When installing U24’s (6–110) socket (6–115), remove pin 1 completely.
Installation of Store Processor PWA (5–5) onto the FCSSU (2–200). NOTE: Store Processor PWA, P/N 205E0601–00 is to only be used with FCSSU, P/N 253E0348–03 (2 megabit). Store Processor PWA, P/N 205E1027– 00 is intended for use with FCSSU P/N 253E0660–00 (8 megabit); however, it may be used with either FCSSU.
F.
(a)
Position the Store Processor PWA on the FCSSU and mate connector J2 (6–310) to FCSSU plug P2.
(b)
Using four 3/16” flat–head screws (5–30) secure the Store Processor PWA to the FCSSU.
(c)
Connect plug P5 (6–300) of the Store Processor Interface Cable Assembly, W2, (6–295) to connector J5 (3–245) of the Aircraft Interface Cable Assembly, W1.
FLASH CRASH SURVIVABLE STORE UNIT (FCSSU), P/N 253E0348–03, P/N 253E0660–00 and P/N 253E1293–00 (See Figure 701 and IPL Figures 2, 5 & 6) Prior to installing the FCSSU assembly (2–200) into the chassis, the Audio Processor circuit board and front panel assembly must be removed. (1)
Remove Chassis assembly (2–25) from dust cover as described in DISASSEMBLY Step B.(1).
(2)
Remove front panel assembly as previously described in DISASSEMBLY Step B.(2) to gain access to the front plate isolator panel (2–70).
(3)
Remove the Audio Processor PWA (2–280) from its card chassis slot as described in DISASSEMBLY Step B.(3) to gain access to the rear isolator plate. NOTE: The front and rear elastomeric shock mounts (2–205) should be checked at this time for possible damage. If it is necessary to replace an elastomeric shock mount (2–205), proceed to the instructions given in G. Otherwise, proceed to the next step herein.
(4)
If not already mounted, mount the Store Processor PWA to the FCSSU as instructed in previous Step E.(2). NOTE: Store Processor PWA, P/N 205E1027–00 may be used with either FCSSU (2 megabit or 8 megabit); however, Store Processor PWA, P/N 205E0601–00 can only be used with FCSSU P/N 253E0348–03 (2 megabit).
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(5)
If not already attached, attach the chassis end of the ground strap (2–5) to the rear isolator panel with the single 5/16” pan–head screw (2–20) with washer (2–15) and hex nut (2–10).
(6)
Carefully slide the FCSSU assembly (2–200) into its position in the chassis.
(7)
Secure the FCSSU to the front elastomeric shock mounts (2–205) using the two 10–32 hex–head screws and vibration mount spacers.
(8)
Secure the FCSSU to the rear elastomeric shock mounts (2–205) using the two 10–32 Phillips–head screws. Attach the grounding strap (2–5) to one of the Phillips–head screws.
(9)
Connect Store Processor Cable Assembly W2 (6–295) plug P5 (6–300) to connector J5 (6–300) on the Aircraft Interface Cable Assembly (3–245).
(10) Install the Audio Processor circuit board into its card slot (Aircraft Interface Cable Assembly W1 connector J4) and secure it in place by pushing down on the left and right card guide locks (2–30) and (2–35). (11) Attach the card retainer assembly (2–85) by installing two 1/2” flat–head screws (2–80). (12) Reinstall the front panel assembly. (13) Slide the chassis assembly (2–25) into the dust cover (2–90 and attach with the single 3/8” pan–head screw (2–105) in the top front of the dust cover and with the two 5/16” pan–head screws (2–100) which secure the dust cover to the rear panel of the chassis assembly.
G. FCSSU ELASTOMERIC SHOCK MOUNTS, P/N AM003–7 (See Figure 702 and IPL Figure 2) (1)
Perform steps (1) through (3) of the FCSSU procedure.
(2)
Remove the damaged elastomeric shock mounts (2–205) from the front isolator panel by loosening and removing the two flat–head screws ((2–210) and nylon insert nuts (2–215).
(3)
Remove the damaged elastomeric shock mounts (2–205) from the rear isolator panel by loosening and removing the two pan–head screws ((2–220) from the captive nylon locking nuts (2–225).
(4)
Attach the new front and/or rear elastomeric shock mounts (2–205) to their respective isolator panel using the hardware removed in steps (2) and (3).
(5)
Return to the FCSSU procedure for reinstalling the FCSSU.
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10-32 Phillips Screw (2-230)
Rear Isolator Panel
Elastomeric Shock Mount (2-205)
Front Isolator Panel (2-70) Store Processor PWA (See Note)
Vibration Mount Spacer (2-235)
10-32 Hex Screw (2-240)
FCSSU (2-200)
NOTE: Store Processor PWA, P/N 205E0601-00, is to be used only with FCSSU, P/N 253E0348-00. Store Processor PWA, P/N 205E1027-00, may be used with either FCSSU, P/N 253E0348-00, P/N253E0601-00 or 253E1293-00. Store Processor PWA, P/N 205E1027-01, may be used with either FCSSU, P/N 253E0992-00 or 253E1293-00.
Figure 701. Installation of Flash Crash Survivable Store Unit (FCSSU)
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10-32 Phillips Screw (2-230)
Rear Isolator Panel
Elastomeric Shock Mount (2-205)
Front Isolator Panel (2-70) Vibration Mount Spacer (2-235)
(2-215)
Store Processor PWA (See Note)
10-32 Hex Screw (2-240)
(2-210) FCSSU (2-200)
(2-205)
(2-210)
Installation of FCSSU Elastomeric Shock Mounts, P/N AM003–7 Figure 702
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H. MODEL A151/A151B & A152/A152B CONTROL UNITS (See IPL Figure 7) NOTE: This Control Unit assembly procedure covers the A151/A151B and A152/A152B and alternate models of the Control Unit used with the Model A100S. Disregard those steps and parts that do not pertain to the exact model of Control Unit under assembly. For specific effectivity of parts to configuration, refer to the EFF Code column in IPL Figure 7. (1)
Install the microphone (7–110/7–140) by threading the microphone cable through the grommet (7–125), microphone bracket assembly (7–90), microphone damper assembly (7–105/7–135) and hum shield assembly (7–115).
(2)
Install the phone jack (7–40) by attaching plug (7–50), nut, washer and one shoulder washer (7–45) to the face of the front panel assembly (7–15) while attaching the second shoulder washer (7–45) and phone jack (7–40) to the rear.
(3)
Attach green test switch (7–30) and red erase switch (7–35) by inserting the switches from the rear of the front panel assembly and installing their associated nuts and washers and the switches to front panel assembly.
(4)
Install meter (7–25) by inserting it from the rear of the front panel assembly and screwing the rear attaching collar.
(5)
Install the harness wires to the preamplifier assembly (7–155), meter (7–25), switches (7–30 and 7–35), and phone jack (7–40). Install microphone wires from harness assembly connector (7–80) or preamplifier assembly (7–155) as appropriate for the type configuration.
(6)
Attach front panel assembly (7–15) to chassis by installing four 3/8” pan–head screws (7–20).
(7)
Install preamplifier assembly (7–155) to the chassis assembly by inserting four 3/8” pan– head screws (7–160).
(8)
Ensure insulator (7–70) is attached to bottom of dust cover.
(9)
Attach front panel assembly (7–15) and chassis assembly (7–90) to the dust cover (7–55) by inserting two 1/4” pan–head screws (7–65) with washers (7–60) from the rear of the dust cover assembly.
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4. STORAGE INSTRUCTIONS NOTE: A bench test is required after storage of more than one year, refer to Testing and Troubleshooting section for specific test and check out procedures.
A. STORAGE IN ORIGINAL CONTAINERS When possible, the Model A100S system equipment should be stored in its original container(s). Provide adequate packing to ensure protection from damage during storage and shipment and ensure that adequate silica gel packages are packed in the container(s) to protect the equipment from moisture. Seal the container(s) to provide a moisture–proof package.
B. STORAGE WITHOUT ORIGINAL CONTAINERS If the original container(s) are not available, perform the following procedures to wrap the Model A100S system equipment for storage: (1)
Wrap the recorder unit in plain wrapping paper or newspaper of sufficient thickness to thoroughly cover all sharp corners and protrusions.
(2)
Enclose the unit in a polyethylene bag (3 mils thick, min.) with packages of silica gel sufficient to provide moisture protection and seal the bags.
(3)
Place the recorder unit in a suitably sized heavy construction cardboard box surrounded with packing material sufficient to protect it on all sides. Arrange packing material in such a way that the unit is protected and will not move around within the box.
(4)
Seal box(es) with fiberglass packing tape.
(5)
Mark boxes clearly as to contents.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SPECIAL TOOLS, FIXTURES, & EQUIPMENT 1. GENERAL This section provides a listing of all required tools, fixtures, and equipment which are not common maintenance tools. Refer to Table 901 for a listing of special test equipment required for testing the Model A100S system. Refer to the following paragraphs for a synopsis of equipment description and purpose. Refer to the applicable user manual for an in–depth explanation of the test equipment operation and configuration.
Table 901 Model A100S Special Tools, Fixtures, and Equipment Special L3 Fairchild Equipment and Type
Manufacturer
Cockpit Voice Recorder System Test Panel
L3 P/N 9300A860
Calibrated Sound Source
L3 P/N 9300A870
L3 Audio Monitor Adapter/ Mod.1
L3 P/N 17TES0200
Ultrasonic Test Set (Beacon Tester)
L3 P/N 15977
A. COCKPIT VOICE RECORDER SYSTEM TEST PANEL, P/N 9300A860 The operation of the Model A100S Recorder and associated control units may be verified using the standard Cockpit Voice Recorder System Test Panel, P/N 9300A860, originally designed for the test and calibration of the Model A100 series of tape–based Cockpit Voice Recorders (refer to Figure 901). Using this panel, audio signals can be applied to individual channels for test and analysis. Additionally, the test panel can be used to activate the Model A100S built–in–test utility, to initiate its Bulk erase feature, and to replay previously recorded data (combined audio). The Test Panel is divided into two section: RECORDER and CONTROL UNIT. The RECORDER section (right half) contains all the controls for test tone, bulk erase, bias trap and associated input/output points. The CONTROL UNIT (left half) section contains all the necessary controls to perform operational checks on all models of control units. Switches for attenuation (6, 12, and 24 db), and a 700 – 1K Hertz filter are included in this test panel to simulate actual conditions. The audio output from either the recorder or control unit section can be monitored, using a headset, at the HEADSET jack or by way of the front panel speaker. The Test Panel measures 19–inches wide, 8.75–inches high and 9.5–inches deep.
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VOICE RECORDER FAIRCHILD COCKPIT SYSTEM TEST PANEL N O R M A L
A C T U A T E
BULK ERASE TEST
TEST
BIAS TRAP ADJUST
SYS UNIT
O U T P U T
MODE GND FAULT
700
1kHz
ROLL OFF I N P U T
GND SHORT
AII3 BULK ERASE
-6 dB
A T T E N U A T I O N
-24 dB
C.U.
EXT
1
A55
MIC
J2
ALL TEST
REC.
INT
O U T P U T
BULK ERASE
-12 dB
BYPASS REVERSED GND
HEADSET
VOLUME
LOCAL AMP AC
MIC CAL DC
2A
DC
OFF
3
4 SHORT
C.U.
CHANNEL SELECT RECORD BIAS
ON
POWER
2
I N P U T
-18VDC +18VDC
2A
AC
J3
CONTROL OFF UNIT
GTP PROBE(FOR GROUND TEST)
Cockpit Voice Recorder System Test Panel, P/N 9300A860 Figure 901 B. CALIBRATED SOUND SOURCE, P/N 9300A870 Refer to Figure 902 for an illustration of the Calibrated Sound Source unit, P/N 9300A870 front panel. Using this panel in conjunction with the Cockpit Voice Recorder System Test Panel, audio signals can be applied to selective microphone devices for test and analysis.
MICROPHONE
CALIBRATE
CALIBRATED SOUND SOURCE P/N 9300-A870
USE 1 kHz SET TO 0 dB
Calibrated Sound Source, P/N 9300A870 Figure 902 C. AUDIO MONITOR ADAPTER / MODIFICATION 1, P/N: 17TES0200 Refer to Figure 903 for an illustration of the Audio Monitor Adapter with Modification 1 (AMA/1), P/N 17TES0200. The AMA/1 is used to extract selective channel audio data from the Model A100S. It may be used along with the L3 Cockpit Voice Recorder System Test Panel and the L3 Calibrated Sound Source Unit to verify proper operation of the Model A100S. A typical A100S unit under test is illustrated in Figure 904.
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10 CONTACT CONNECTOR L3 P/N 063-98-00365 30-INCH FLAT-RIBBON CABLE
UNIT DIMENSIONS: HEIGHT - 7.55 INCHES WIDTH - 4.05 INCHES DEPTH - 1.72 INCHES
L3 Audio Monitor Adapter With Modification 1, P/N 17TES0200 Figure 903 The AMA/1 along with an external amplifier and speaker are the only instruments required to provide quality analysis of the recorded audio data. To use the AMA/1, the recorder must be taken from the aircraft, placed on a test bench and its dust cover removed. The AMA/1 30–inch cable is mated, via its 10–pin connector, to the Playback Monitor connector designated J6 which is located on the Audio Processor PWA at its center outer edge (refer to Figure 904). This connection routes the four audio channels and the Combined Audio channel (summation of Channels 1 through 4) from the Model A100S to the AMA/1 for output individually, via 1/4–inch monophone jacks, as follows: From SSCVR
To AMA/1
Signal Amplitude
Channel 3 Channel 2 Channel 1 Channel 4 Combined Audio Channel
PILOT jack CO–PILOT jack SPARE jack AREA jack COMBINED jack
1 Vrms + 10% 1 Vrms + 10% 1 Vrms + 10% 1 Vrms + 10% 1.45 Vrms + 10%
The signal amplitudes available at the AMA/1 monophone jacks are based on the Model A100S having an applied input of 3 Vrms for Channels 1, 2 and 3 and 2 Vrms for Channel 4. As a general rule, the signal amplitude available at the AMA/1 SPARE (Channel 1), CO–PILOT (Channel 2 ) and PILOT (Channel 3) jacks is 33% of the A100S applied input whereas the signal amplitude available at the AREA jack (Channel 4) is 50% of the unit applied input. The signal amplitude available at the AMA/1 COMBINED jack is approximately 1.45 times the highest individual channel amplitude present at the AMA/1. Also, the signal amplitude measured at the AMA/1 COMBINED jack should be identical to that measured at the Headset jack on both the Model A100S front panel or its associated Control Unit front panel.
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CALIBRATED SOUND SOURCE P/N9300A870 FAIRCHILD
COCKPIT VOICE RECORDER SYSTEM TEST PANEL
COCKPIT VOICE RECORDER SYSTEM TEST PANEL, P/N 9300A860
J6
J6
TO MODEL A100S REAR PANEL CONNECTOR TO J6 ON AUDIO PROCESSOR PWA AUDIO MONITOR ADAPTER (AMA/1) Model A100S SSCVR Typical Test Setup Figure 904
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ILLUSTRATED PARTS LIST 1. GENERAL This section contains the following sections: Introduction, Equipment Designator List, Numerical Index, and Detailed Parts List. The Introduction describes usage of the Illustrated Parts List (IPL), a listing of abbreviations, and a list of vendor names, addresses, and codes per the current issue of “Federal Supply Code for Manufacturers”, catalog handbook H4–1. A configuration matrix listing the Model A100S Solid–State Cockpit Voice Recorder configurations is provided in paragraph 8. The Equipment Designator Index provides a cross reference from manufacture reference designator to manufacturing part number. The Numerical Index provides a numerical listing of all manufacturing part numbers.
2. PURPOSE The purpose of this Illustrated Parts List is to assist maintenance and supply personnel in requisitioning, storing, issuing and identifying parts to maintain the Model A100S recorder. This Illustrated Parts List is not to be taken as the authority for the procedure of assembly or disassembly. Overhaul or repair should be done by authorized personnel only.
3. ABBREVIATIONS The following abbreviations are used in this section:
Abbreviation AR NHA RF
Meaning As Required Next Higher Assembly Reference
4. EQUIPMENT DESIGNATOR INDEX The Equipment Designator Index is an index of designators assigned to electrical parts as shown in electrical wiring and schematic diagrams. Equipment designators are listed in alphanumerical sequence showing applicable figure and item numbers.
5. NUMERICAL INDEX The Numerical Index is a complete listing of parts included in the Detail Parts List, cross–referenced to the applicable figure and item number, L3’s part numbers, the manufacturer’s part numbers and total quantity required. Part numbers are arranged in a alphanumerical sequence beginning at the extreme left–hand position and continue from left to right, one position at a time. The order to precedence in beginning the part number arrangement is as follows: A. Letters A through Z (Alphabetical Os are considered as numerical zeros). B. Numerals 0 through 9. Part number entry is limited to a single line and does not exceed fifteen characters. The FIGURE number and ITEM number columns contain the figure and item number(s) for all parts listed. When more than one figure and item number are shown for the same part number, the part number is not repeated.
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6. DETAIL PARTS LIST The Detail Parts List consists of illustrations and columnar parts breakdown of the component and all assemblies, subassemblies, and parts that can be disassembled, repaired and reassembled, or replaced. Items that are riveted, welded or spun over are not listed. Parts made of bulk stock such as wire, tape or bonding braid are also not listed. Illustrations are each assigned a figure number, commencing with Figure 1 and progressing in sequence. The FIGURE AND INDEX NUMBER column reflects the assigned figure number of the illustration in which the item is shown and the item number listed on the illustration. Figure numbers are shown for the first entry of each figure and at the top of each subsequent column. When there is more than one type of subassembly for the same function additional figures are included with the same number, but followed by an additional alpha designator (such as A, B, etc.). Each part number listed in the Detail Parts List is assigned an index number. Index numbers begin with number 1 for each illustration and in broken sequence to facilitate the insertion of new items which are not variants of existing items. Items listed but not illustrated are identified by a dash to the left of the index number. Item Number Alpha variants are assigned consecutively, A through Z, for related part numbers to show Service bulletin related modifications, or configurational differences from the original item, Non– service bulletin related product improvement parts, or optional parts. The PART NUMBER column contains the manufacturer’s part number when the part is purchased from a source other than L–3 Communications, or the L3 part number for those parts which must be purchased from L3. When the manufacturer’s part number is used for any parts, the L3 number is also shown enclosed in parentheses, in the NOMENCLATURE column. When standard parts (such as MS, AN, RC, CP, etc.) are used, vendor codes are not assigned to these parts. However, for non–standard parts the vendor code is assigned in the NOMENCLATURE column and is preceded by the letter “V.” It corresponds to the Federal Supply Code for Manufacturers as listed in Cataloging Handbook H4–1. When a part has multiple vendors, all part numbers are listed in the PART NUMBER column. The first vendor will be assigned an item number and each subsequent part number is assigned the same item number with an alpha variant. The NOMENCLATURE column describes the part or assembly. Nomenclature wording is arranged so that the identifying noun or key word is always the first part of the description; this is followed by modifying words. Standard abbreviations are used as necessary. Assemblies which are not broken down within a listing but which are covered by a separate figure will carry the notation “(SEE FIG. – FOR DETAIL BREAKDOWN).” The listing of the assembly in the breakdown figure will carry the reference “(SEE FIG. – FOR NHA)”. If the vendor is not L3, the manufacturer’s vendor code may be included in parentheses in this column. The indenture system, provided by the numbers “1” through “6” in the heading, shows the relationship of one part to another; for example, a part listed under indenture “3” is a component of the assembly listed under indenture “2” immediately above it. Items used to attach parts or assemblies to each other are designated “ATTACHING PARTS” and are listed immediately following the item or items they attach. The symbol “* * *” denotes the end of attaching parts.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S The EFFECTIVITY CODE column establishes parts’ relationship with units or assemblies which are essentially the same but have variations. These units or assemblies are assigned reference letters such as A, B, C, D, etc. Parts which are not common to all configurations but are associated with one or more of the coded lead items carry the letter or letters assigned to the lead item with which it is associated. If a part is common to all lead items, the EFFECTIVITY CODE column is blank. The UNITS PER ASSY column lists the quantity of the item required in one assembly in which it is a component. It is, therefore, not necessarily the total quantity of the part required in the complete equipment; the equipment total can be found in the Numerical Index. The term “RF” denotes that the assembly has been previously listed in the parts breakdown, or in some instances engineering reference documentation associated with an assembly part.
7. MANUFACTURER’S CODE Code
Manufacturer
00141
PIC Design Corp. Subsidiary of Wells Benrus Co. Benrus Center P.O. Box 335 Ridgefield, CT 06877
01121
Allen Bradley Co. 1201 South 2nd St. Milwaukee, WI 53204
01295
Texas Instruments Inc. Semiconductor Group 13500 N. Central Expressway P.O. Box 225012 M/S 49 Dallas, TX 75265
02289
Hi–G Co. Inc. Spring St. and Rte. 75 Windsor Locks, CT 06096
03038
Long–Lok Fastener Corp. An Inlex Co. 13709 S. Normandie Ave. Gardena, CA 90249
04713
Motorola Inc. Semiconductor Group 5005 E. McDowell Rd. Phoenix, AZ 85008
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Code
Manufacturer
06288
Edal Industries Inc. 4 Short Beach Rd. East Haven, CT 06512
07263
Fairchild Camera and Instrument Corp. Semiconductor Division Mail Stop 14–1053 401 Ellis St. P.O. Box 7284 Mountain View, CA 94042
08842
Abacus Electronics Corp. Dobbs Ferry, NY
10581
Magnetico Inc. 182 Morris Ave. Holtsville, NY 11742
11983
Nortronics Co. Inc. 8101 10th Ave. N. Minneapolis, MN 55427
13511
Amphenol Cadre Division Bunker Ramo Corp. Los Gatos, CA
14752
Electrocube Inc. 1710 S. Del Mar Ave. San Gabriel, CA 91776
15755
Abbott Transistor Laboratories Inc. 5200 W. Jefferson Blvd. Los Angeles, CA 90016
16741
Triad Transformer Corp. Huntington, IN
22527
Fisher Scientific Co. 585 Alpha Dr. Pittsburgh, PA 15238
25140
TRW Inc. TRW Globe Motor Division 2275 Stanley Ave. Dayton, OH 45404
23-70-02 Illustrated Parts List
Page 1004 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Code
Manufacturer
26858
Benthos
49 Edgerton Dr. North Falmouth, MA 02556 27014
National Semiconductor Corp. 2900 Semiconductor Dr. Santa Clara, CA 95051
30655
Elastic Stop Nut Corp. of America Fastener Division Union, NJ 07083
34335
Advanced Micro Devices 901 Thompson Pl. Sunnyvale, CA 94086
46384
Penn Engineering and Manufacturing Corp. P.O. Box 311 Doylestown, PA 18901
51791
Statek Corp. 512 N. Main St. Orange, CA 92668
56289
Sprague Electric Co. 87 Marshall St. North Adams, MA 01247
71279
Cambridge Thermionic Corp. 445 Concord Ave. Cambridge, MA 02138
71460
ITT Canon Electric 666 E. Dyer Rd. Santa Ana, CA 92702
71643
Connecticut Hard Rubber Co. 407 East St. New Haven, CT 06509
71785
TRW Inc. TRW Cinch Connectors Division 1501 Morse Ave. Elk Grove Village, IL 60007
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Illustrated Parts List Rev 3 Page Page 1005 1005 Feb. Jul. 01/93 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Code
Manufacturer
72794
Dzus Fastener Co. Inc. 425 Union Blvd. West Islip, NY 11795
72982
Erie Technological Products Inc. 645 West 11th St. Erie, PA 16512
79136
Waldes Kohinoor Inc. 47–16 Austel Pl. Long Island City, NY 11101
80053
Beckman Instruments Inc. Electronic Instruments Division 3900 North River Rd. Schiller Park, IL 60176
81039
Plessey Dynamics Corp. 1 414 Chesnut Ave. Hillside, NJ 07205
81300
Dayco Corp. 333 W. 1st St. Dayton, OH 45402
83086
New Hampshire Ball Bearings Inc. Rt. 202 Peterborough, NH 03458
91146
ITT Cannon Electric Co. Salem Division Salem, MA
91506
Augat Inc. 33 Perry Ave. P.O. Box 779 Attleboro, MA 02703
94867
Churchill Corp. 344 Franklin St. Box G Melrose, MA 02167
94970
Dukane Corp. SeaCom Division 2900 Dukane Drive St. Charles, IL 60174
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Page 1006 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Code
Manufacturer
95238
Continental Connector Corp. 34–63 56th St. Woodside, NY 11377
95987
Weckesser Co. Inc. 4444 West Irving Park Rd. Chicago, IL 60641
98659
Computer Instruments 100 Madison Ave. Hempstead, NY 11550
8. CONFIGURATION MATRIX The Model A100S Solid–State Cockpit Voice Recorder currently has two configurations: S100–0080–00 and S100–0080–01 (the light weight version). The S100–0080–00 has three effectivities: the standard version has the 30 minute FCSSU (P/N: 253E0660–00) installed, version A has the 60 minute FCSSU (P/N: 253E1290–00) installed and version B has the titanium FCSSU (P/N: 253E1293–00) installed. The S100–0080–01 has two effectivities: the standard version has the 30 minute FCSSU (P/N: 253E0992–00) installed and verson A has the 60 minute FCSSU (P/N: 253E1293–00) installed.
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Illustrated Parts List Rev 2 Page 1007 Feb. 01/93 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
EQUIPMENT DESIGNATOR INDEX Equipment Designator CR1 CR1 CR1 CR2 CR2 CR2 CR3 CR3 CR3 CR4 CR4 CR4 CR5 CR5 CR5 CR6 CR6 CR7 CR8 CR9 CR10 CR11 CR12 CR13 CR14 CR15 CR16 CR17 CR18 CR19 CR20 CR21 CR22 CR23 CR24 CR25 CR26 CR27 CR28 CR29 CR30
Fig–Item 3– 4– 6– 3– 4– 6– 3– 4– 6– 3– 4– 6– 3– 4– 6– 3– 4– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3–
40 15 15 40 25 10 40 10 5 40 20 15 40 20 20 40 10 40 40 10 10 10 10 30 25 35 45 35 20 20 30 10 15 15 30 25 10 10 10 30 75
Equipment Designator CR31 CR32 CR33 CR34 C1 C1 C1 C1 C1 C2 C2 C2 C2 C2 C3 C3 C3 C3 C3 C4 C4 C4 C4 C4 C5 C5 C5 C5 C5 C5 C6 C6 C6 C6 C6 C7 C7 C7 C7 C7 C8
Fig–Item 3– 40 3– 10 3– 10 3– 5 3– 105 4– 330 6– 270 8– 50 9– 70 3– 110 4– 330 6– 220 8– 25 9– 30 3– 110 4– 350 6– 265 8– 55 9– 55 3– 110 4– 340 6– 280 8– 170 9– 50 3– 110 4– 340 9– 70 6– 220 8– 30 9– 35 3– 110 4– 340 6– 275 8– 20 9– 25 3– 110 4– 330 6– 285 8– 60 9– 60 3– 110
Equipment Designator C8 C8 C8 C8 C9 C9 C9 C9 C9 C10 C10 C10 C10 C10 C11 C11 C11 C11 C11 C12 C12 C12 C12 C12 C13 C13 C13 C13 C13 C14 C14 C14 C14 C14 C15 C15 C15 C15 C15 C16
Fig–Item 4– 350 6– 275 8– 70 9– 75 3– 110 4– 340 6– 290 8– 20 9– 25 3– 110 4– 335 6– 255 8– 40 9– 45 3– 110 4– 335 6– 275 8– 15 9– 20 3– 120 4– 340 6– 275 8– 30 9– 35 3– 120 4– 330 6– 285 8– 35 9– 40 3– 145 4– 350 6– 275 8– 20 9– 25 3– 110 4– 345 6– 245 8– 20 9– 80 3– 100
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
EQUIPMENT DESIGNATOR INDEX Equipment Designator C16 C16 C16 C16 C17 C17 C17 C17 C18 C18 C18 C18 C19 C19 C19 C19 C20 C20 C20 C20 C21 C21 C21 C21 C22 C22 C22 C22 C23 C23 C24 C24 C25 C25 C26 C26 C27 C27 C28 C28 C29
Fig–Item 4– 335 6– 270 8– 45 9– 50 3– 100 4– 335 8– 20 9– 25 3– 135 4– 340 8– 40 9– 45 3– 130 4– 335 8– 15 9– 20 3– 170 4– 350 8– 65 9– 65 3– 115 4– 325 8– 55 9– 55 3– 130 4– 335 8– 30 9– 35 3– 105 4– 350 3– 105 4– 345 3– 110 4– 345 3– 110 4– 325 3– 110 4– 325 3– 95 4– 345 3– 95
Equipment Designator C29 C30 C30 C31 C31 C32 C32 C33 C33 C34 C34 C35 C35 C36 C36 C37 C37 C38 C38 C39 C40 C41 C42 C43 C44 C45 C46 C47 C48 C49 C50 C51 C52 C53 C55 C56 C57 C59 C60 C61 C62
Fig–Item 4– 340 3– 110 4– 345 3– 110 4– 325 3– 105 4– 345 3– 105 4– 340 3– 105 4– 340 3– 122 4– 340 3– 112 4– 340 3– 112 4– 340 3– 102 4– 310 4– 310 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 345 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 320
Equipment Designator C63 C64 C65 C66 C67 C68 C69 C70 C71 C72 C73 C74 C75 C76 C77 C78 C79 C80 C81 C82 C83 C84 C85 C86 C87 C88 C101 C102 C106 C107 C108 C109 C110 C111 C112 C113 C114 C115 C117 C118 C120
Fig–Item 4– 340 4– 340 4– 340 4– 340 4– 340 4– 340 4– 340 4– 320 4– 320 4– 340 4– 340 4– 310 4– 340 4– 340 4– 340 4– 340 4– 310 4– 320 4– 315 4– 295 4– 300 4– 300 4– 295 4– 290 4– 290 4– 305 6– 235 6– 250 6– 235 6– 235 6– 240 6– 240 6– 240 6– 230 6– 240 6– 235 6– 240 6– 235 6– 260 6– 235 6– 225
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
EQUIPMENT DESIGNATOR INDEX Equipment Designator C123 D1 D1 D2 D2 D3 D4 D4 J1 J2 J2 J3 J4 J5 J5 J7 J8 L1 L1 L2 L2 L3 L3 P1 P1 P2 P4 P5 Q1 Q1 Q1 Q1 Q2 Q2 Q2 Q3 Q3 Q4 Q4 Q5 Q5
Fig–Item 6– 225 8– 10 9– 15 8– 10 9– 15 9– 10 8– 5 9– 5 3– 210 3– 250 6– 310 3– 240 3– 240 3– 245 6– 300 3– 225 2– 190 4– 5 6– 140 3–100A 6– 145 3–100A 6– 145 6– 50 4– 365 3– 250 4– 70 6– 45 3– 85 4– 125 8– 170 9– 190 4– 125 8– 175 9– 195 8– 175 9– 195 8– 180 9– 200 8– 180 8– 180
Equipment Designator Q5 Q6 Q6 R1 R1 R1 R1 R1 R2 R2 R2 R2 R2 R3 R3 R3 R3 R3 R4 R4 R4 R4 R4 R5 R5 R5 R5 R5 R6 R6 R6 R6 R6 R7 R7 R7 R7 R7 R8 R8 R8
Fig–Item 9– 200 8– 185 9– 205 3– 160 4– 235 6– 175 8– 115 9– 170 3– 150 4– 235 6– 210 8– 115 9– 95 3– 170 4– 235 6– 205 8– 90 9– 100 3– 185 4– 235 6– 200 8– 145 9– 160 3– 185 4– 260 6– 215 8– 80 9– 90 3– 145 4– 245 6– 190 8– 85 9– 95 3– 190 4– 280 6– 165 8– 80 9– 90 3– 195 4– 255 6– 170
Equipment Designator R8 R8 R9 R9 R9 R9 R9 R10 R10 R10 R10 R10 R11 R11 R11 R11 R11 R12 R12 R12 R12 R12 R13 R13 R13 R13 R14 R14 R14 R14 R15 R15 R15 R15 R15 R16 R16 R16 R16 R17 R17
Fig–Item 8– 160 9– 180 3– 155 4– 285 6– 170 8– 165 9– 140 3– 195 4– 245 6– 165 8– 160 9– 180 3– 165 4– 240 6– 185 8– 150 9– 165 3– 165 4– 270 6– 180 8– 120 9– 135 3– 195 4– 240 8– 145 9– 160 3– 150 4– 275 8– 130 9– 145 3– 165 4– 245 6– 195 8– 125 9– 140 4– 265 6– 180 8– 75 9– 85 4– 225 6– 195
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Illustrated Parts List Rev 2 Page 1010 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
EQUIPMENT DESIGNATOR INDEX Equipment Designator R17 R17 R18 R18 R18 R19 R19 R19 R19 R20 R20 R21 R21 R21 R22 R22 R22 R23 R23 R23 R24 R24 R24 R25 R25 R25 R26 R26 R27 R27 R27 R28 R28 R28 R29 R29 R29 R30 R30 R30 R31
Fig–Item 8– 80 9– 90 4– 150 8– 80 9– 90 3– 180 4– 150 8– 100 9– 110 3– 175 9– 120 4– 165 8– 85 9– 95 4– 215 8– 105 9– 115 4– 165 8– 135 9– 150 4– 230 8– 80 9– 90 4– 200 8– 75 9– 85 8– 100 9– 110 4– 150 8– 140 9– 155 4– 190 8– 110 9– 125 4– 175 8– 115 9– 130 4– 155 8– 115 9– 130 4– 185
Equipment Designator R31 R31 R32 R32 R32 R33 R34 R35 R36 R37 R38 R39 R40 R41 R42 R43 R44 R45 R46 R47 R48 R49 TP1 TP1 TP2 TP2 TP3 TP4 TP5 TP6 TP10 TP20 TP30 TP40 T1 T1 T2 T3 T4 U1 U1
Fig–Item 8– 115 9– 105 4– 170 8– 155 9– 175 4– 160 4– 155 4– 170 4– 150 4– 220 4– 165 4– 175 4– 160 4– 165 4– 145 4– 195 4– 145 4– 150 4– 155 4– 210 4– 200 4– 250 3– 205 6– 35 3– 205 6– 35 3– 205 3– 205 3– 205 3– 50 6– 155 6– 155 6– 155 6– 155 3– 200 4– 355 4– 355 4– 355 4– 355 3– 50 4– 35
Equipment Designator U1 U2 U2 U2 U3 U3 U3 U3 U4 U4 U4 U5 U5 U5 U6 U6 U7 U7 U8 U8 U9 U9 U10 U10 U11 U11 U12 U12 U13 U13 U14 U14 U15 U15 U16 U16 U17 U17 U18 U18 U19
Fig–Item 6– 130 3– 55 4– 45 6– 125 3– 65 3–65A 4– 100 6– 80 3– 70 4– 110 6– 25 3–65A 4– 55 6– 45 4– 105 6– 70 4– 115 6– 70 4– 120 6– 95 4– 55 6– 95 4– 55 6– 90 4– 30 6– 65 4– 90 6– 55 4– 60 6– 130 4– 105 6– 90 4– 105 6– 130 4– 90 6– 120 4– 80 6– 60 4– 80 6– 75 4– 80
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Illustrated Parts List Rev 2 Page 1011 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
EQUIPMENT DESIGNATOR INDEX Equipment Designator U19 U20 U20 U21 U21
Fig–Item 6– 135 4– 80 6– 35 4– 80 6– 60
Equipment Designator U22 U22 U23 U23 U24
Fig–Item 4– 70 6– 100 4– 70 6– 85 4– 70
Equipment Designator U24 U25 W1 W2 Y1
Fig–Item 6– 110 4– 70 3– 230 6– 40 6– 150
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Illustrated Parts List Rev 1 Page 1012 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER #515 AM003–7 AM29C821/BLA B191–20H BCDAT–2–619–5 CCR06CG104FR CCR06CG472FR CCR07CG333FR CCR07CG683FR CD54ACT238F3A CD54HCT14F CK05BX101K CK05BX102K CK05BX103K CK05BX104K
CK05BX561K CK06BX104K CK06BX105K CK06BX223K CK06BX274K CK06BX562K DD1032 DDU–8Z297 DG201AAK DS2165QN HLMP–1700–101 HLMP–7000–1S1 L–11 LH0002H LM136AH–2.5 LM139J MAX632AMJA MC1558U MD015C104KAA
AIRLINE PART NO.
FIG.
ITEM
TTL REQ
2 2 6 3 5 4 4 4 4 6 6 4 4 6 3 8 3 4 6 4 3 3 8 9 4 3 3 6 4 4 4 6 2 7 4 3 3 6 3 4
195 205 95 45 15 345A 335 340 345 65 85 320 315 290 110 50 105 310 275 325 112 115 55 55 330 120 135 135 115 80 25 20 190 40 110 75 70 80 50 350
1 4 2 1 1 7 6 25 7 1 1 5 1 1 17 2 6 4 5 4 1 1 2 2 1 2 1 1 1 5 1 1 1 1 1 1 1 1 1 26
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Illustrated Parts List Rev 2 Page 1013 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER MS15795–803 MS24693–C3 MS24693–C46 MS35333–70 MS35649–244 MS51957–5 MS51957–14
MS51957–27 MS51957–28 MS51957–45 MS51958–65 MS51959–13 MS51959–15 MS51959–17 MS51960–65 NMF0509S OP–27BZ OP–470AY PLC–440 PLC–832 RC07GF101J RC07GF102J RC07GF103J RC07GF125J RC07GF151J RC07GF152J RC07GF154J
AIRLINE PART NO.
FIG.
ITEM
7 2 2 2 2 2 3 2 2 2 2 2 2 2 2 2 2 2 2 3 4 4 2 2 8 9 8 9 8 9 8 9 8 9 8 9 8 9
60 210 250 15 275 10 220 20 220 270 100 105 145 180 230 260 255 80 170 65A 55 105 225 40 75 85 80 90 85 95 90 100 95 105 100 110 105 115
TTL REQ 2 4 1 1 5 1 3 1 4 5 2 1 4 4 2 5 4 2 2 2 1 5 4 6 1 2 5 5 2 3 1 1 1 1 2 2 1 1
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Illustrated Parts List Rev 2 Page 1014 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER RC07GF182J RC07GF221J RC07GF222J RC07GF224J RC07GF471J RC07GF472J RC07GF474J RC07GF510J RC07GF561J RC07GF562J RC07GF682J RC07GF821J RC07GF822J RNC50*DSCR RN60D22R1F SN54BCT2244J S100–0080–00 S100–0080–01 SP–310 SS020–01–TG TM7–3 VK200 V130LA5 016E0946–00 024E0526–00 024E0611–00 0448000001 0449800012 046E0280–01A 046E0281–01
AIRLINE PART NO.
FIG.
ITEM
9 8 9 8 9 8 9 8 9 8 9 8 9 8 9 8 9 8 9 9 8 9 8 9 6 3 6 1 1 4 6 3 4 3 2 2 3 3 3 4 4
120 110 125 115 130 120 135 125 140 130 145 135 150 140 155 145 160 150 165 170 155 175 160 180 190 180 130 1 1A 360 50 200 5 40 151 5 230 136 136A 30 35
TTL REQ 1 1 1 3 2 1 1 1 1 1 1 1 1 1 1 2 2 1 1 1 1 1 2 2 1 1 3 1 1 4 2 1 1 9 1 1 1 3 3 1 1
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Illustrated Parts List Rev 3 Page 1015 Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER
AIRLINE PART NO.
TTL REQ
FIG.
ITEM
046E0282–01 046E0283–01A 046E0284–01A 046E0285–01A 0469701469 0469701732 0469701736 0469701858 0469701861 0469701868 0469701883 0469701885 0469701888 0469701892 0469701896
4 6 6 6 6 6 4 4 4 4 6 6 6 6 6
45 25 35 45 55 60 60 70 90 100 90 100 110 120 125
1 1 1 1 1 2 1 1 2 1 2 1 1 1 1
0639800074 0639801522 075E0604–00 0884700024
3 4 2 4 6 3 3 8 9 3 8 9 4 9 6 4 3 6 3 3 3 6
210 365 90 15 10 25 30 10 15 10 5 5 20 10 5 10 15 15 20 35 5 40
1 1 1 1 1 2 5 2 2 12 1 1 2 1 1 2 1 2 1 1 1 1
1.5KE250CA 1.5KE68C 1N295 1N4148 1N4446 1N4614 1N4735,A 1N4761A 1N5234B 1N5256A, B 1N5819 1N5825 1N759A 1N914, A,B 1000200612
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Illustrated Parts List Rev 1 Page 1016 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER
AIRLINE PART NO.
TTL REQ
FIG.
ITEM
17D17–0618
3 3 4 4 8 9 6 6 6 6 3 10 3 8 9 3 2 7 2
80 90 130 140 190 210 225 230 235 240 240 45 102 195 215 100A 140 5 145
1 1 1 1 1 1 1 1 7 5 2 1 1 1 1 2 1 1 1
1829800193 1829800194 1829800195 1829800196 1829800197 1829800198 1829800199 1829800200 1829800201 1829800202 1829800203 1829800204 1829800206 1829800209 1829800210 1829800211 183DHL 1849700118 1849700119 189E0610–00 191E0607–00
4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 6 4 6 2 2
150 155 160 165 170 175 180 185 190 195 200 205 210 220 225 230 255 120 150 85 110
5 3 2 4 2 2 1 1 1 1 2 1 1 1 1 1 1 1 1 1 1
10042–DAP
10282–N 104JEV 104JEW 104JEX 104JEY 120–064–455F 150949–1002 158X104K 160–0021–020 167103J400A 17D17–0262
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Illustrated Parts List Rev 2 Page 1017 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 191E0953–00 196E0605–00 196E0608–00 2N2222A 2N2907A
2029800326 2029800391 205E0597–00 205E0598–00 205E0601–00 205E0660–00 205E1027–00 206E0597–00 2160 2290200398 2290200413 2299800197 2299800341 2299800417 2299800423 230E0947–00 2369800242 236C2110–10 239E0197–00 239E0630–00 24SX–2–6–3–L 24SX–2–6–3–R 25107 253E0348–03 253E0585–00 253E0600–00 253E0600–01
AIRLINE PART NO.
FIG.
ITEM
2 2 2 4 3 3 4 3 3 2 3 2 4 2 6 5 2 6 3 3 2 2 4 2 2 2 2 4 6 2 2 2 2 3 2 5 2 1 2 1 2
110A 130 70 125 85 135 135 55 55A 245 1 280 1 282A 1 1A 282B 1A 260 60 154 284 370 50 240 60 125A 75 30 235 45 35 30 65 200 1 150 5 1 5A 1A
TTL REQ 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 7 1 4 2 4 2 2 1 4 2 2 1 2 2 1 1 1 1 1 1 1 1
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Illustrated Parts List Rev 3 Page 1018 Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 253E0992–00 253E1290–00 253E1293–00 2559800205 2559800280 263D28 266E0305–01 266E0305–02 2739800090 2879800154 2879800162 2879800213 2979800257 3019822003 3370415004 3371139004 3371222004 3371315004 3392222005 3399–6026 3433–5302 3518 3611010001 3621215004 3623633004 3781312522 3926–0000T 39424 403DDC 408E0609–00 42285 4626–6300 4989–02–1822–F 502DFF 502DRC
AIRLINE PART NO.
FIG.
ITEM
2 5 2 5 2 5 6 3 6 2 2 4 2 2 4 2 4 8 9 4 3 4 6 6 6 3 6 3 6 6 3 6 6 6 4 2 6 3 4 6 6
200A 1B 200B 1C 200C 1D 155 205 260 160A 160B 375 55 65 380 265 290 60 60 295 95 300 220 300 310 255 315 100 265 270 125 280 305 145 305 75 140 245 215 245 250
TTL REQ 1 1 1 1 1 1 4 6 2 1 1 2 4 2 2 5 2 1 1 2 2 2 2 1 1 2 2 2 1 2 1 1 1 2 1 1 1 1 2 2 1
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Illustrated Parts List Rev 2 Page 1019 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 54ACTQ245DM 54FCT541DM 5602–55–32 6080102269 6080130902 6080905629 6080908669 6080910000 6080910001 6080910009 6080910701 6080912400 6080924900 6080929401 6080930100 6080930102 6080935700 6080949901 6080964900 6080968100 6080973200 6080988701 6112820001 619–24–CC–B.1 62650–1 6140116200 6140166508 68120–050 68WR10K 7447–1–P42 7473422005 750–101–R10K 750–101–R100K 750–101–R47K 750–83–R10K 750–83–R100K 750–83–R47
AIRLINE PART NO.
FIG.
ITEM
6 6 3 6 3 4 3 3 4 3 4 4 4 3 6 3 4 3 4 4 3 3 4 4 6 4 4 3 6 6 3 4 6 3 6 6 4 6 6 3 6
75 70 215 195 185 240 140 145 245 150 250 255 260 155 200 160 265 165 270 275 170 175 280 285 205 40 50 225 210 215 250 235 160 130 165 180 145 185 175 190 170
TTL REQ 1 2 3 2 1 2 1 1 3 2 1 1 1 1 1 1 1 3 1 1 1 1 1 1 1 1 1 1 1 1 1 4 2 2 2 2 2 1 1 1 2
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 750–83–R47K 754–01–001 7552110002 77103–050 79NM–40 821573–3 821574–1 821581–1 821665–1 89984 8AS23R3 8EP43R3 8EP44R3 8EP46R3 8EP46R5 9WES4 9–0649 9–1391 9–1504 9–1508 9–1539 9–1586–25 9–1586–26 9–1586–27 9–1586–28 9–1588 9–1589 9–1590 9–1889 93A055–00
AIRLINE PART NO.
FIG.
ITEM
TTL REQ
3 4 6 3 2 4 6 4 4 6 11 10 10 7 10 7 7 11 11 10 2 7 2 2 8 9 8 9 8 9 8 9 8 9 9 8 9 9
195 385 285 235 215 65 105 85 95 115 5A 70 35A 65 35 20 160 40 45 50 135 85 120 155 170 190 175 195 180 200 185 205 65 65 70 165 185 80
1 46 2 1 4 1 1 5 2 1 1 3 2 1 2 4 4 1 1 1 4 4 2 4 1 1 10 1 10 1 1 1 1 1 2 1 1 1
1 10
20 1
1 1
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 93A055–03 93A055–10 93A055–20 93A055–30 93A055–40 93A055–45 93A055–50 93A055–55 93A055–60 93A055–65 93A055–66 93A055–67 93A055–95 93A151–00 93A151–01 93A151–20 93A151–30 93A151–40 93A151–50 93A152–00
AIRLINE PART NO.
TTL REQ
FIG.
ITEM
1 10 1 10 1 10 1 10 1 11 1 11 1 10 1 10 1 11 1 11 1 11 1 11 1 11 1 7 1 7 1 7 1 7 1 7 1 7
20A 1A 20B 1B 20C 1C 20D 1D 25 1 25A 1A 20E 1E 20F 1F 25B 1B 25C 1C 25D 1D 25E 1E 25F 1F 10 1 10A 1A 10B 1B 10C 1C 10D 1D 10E 1E
1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1
1 7
15 1F
1 1
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 93A152–01 93A152–04 93A152–20 93A152–25 93A152–30 93A152–35 93A152–40 93A152–50 93A152–60 93A152–70 93A244 93A263–02 93A264 93A265 93A266–01 93A267 93A268 93A272 93A307
93–618 93–619–01 93–624 93–626–19 93–626–20 93–626–22 93–626–23
AIRLINE PART NO.
FIG.
ITEM
1 7 1 7 1 7 1 7 1 7 1 7 1 7 1 7 1 7 1 7 7 7 8 7 7 7 9 7 7 11 7 7 7 2 10 12 10 10 10 10 10
15A 1G 15B 1H 15C 1J 15D 1K 15E 1L 15F 1M 15G 1N 15H 1P 15J 1Q 15K 1R 125 155 1 80 80B 155A 1 80A 80C 5 90 100 130 125 5A 5A 55A 60B 60C 60 60A
TTL REQ 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1
23-70-02
Illustrated Parts List Rev 2 Page 1023 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 93–626–30 93–626–83 93–626–100 93–626–101 93–626–115 93–626–116 93–626–117 93–653 93–654 93–655 93–656 93–658–01 93–658–02 93–658–03 93–917–67 93–972 93–989 93–1021 93–1025 9300A014 9300A014–01 9300A014–02 9300A014–03 9300A033 9300A165 9300A165–01 9300A206 9300–177 9300–179–01 9300–179–02 9300–180 9300–195 9300–197
9300–204
AIRLINE PART NO.
FIG.
ITEM
11 11 11 11 11 10 10 11 11 11 11 11 11 11 11 9 8 10 7 11 7 7 7 7 7 1 12 1 12 12 2 7 7 2 7 7 10 12 7 7
30A 30 30B 30C 30D 60D 60E 15 35 25 10 10A 20 20A 20B 75 200 15A 45 5B 15 15A 15B 15C 95 30 1 30A 1A 5 165 30 35 175 55 155 10 10 105 135
TTL REQ 1 1 1 1 1 1 1 1 1 1 2 3 1 1 1 1 1 1 2 1 1 1 1 1 1 1 1 1 1 1 1 1 1 2 1 1 1 1 1 1
23-70-02
Illustrated Parts List Rev 1 Page 1024 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 9300–205 9300–233 9300–233–01 9300–233–04 9300–285 9300–286–01 9300–290 9300–301 9300–305 9300–307 9300–329 9300–334 9300–337 9300–344
9300–347 9300–348 9300–351 9300–352 9300–377 9300–382 9300–388 9300–534 9300–543 9300–581 9300–583 9300–583 9300–927 9300–928 933533617
AIRLINE PART NO.
FIG.
ITEM
7 10 7 7 7 8 9 4 8 9 8 9 8 9 8 9 7 10 7 7 10 12 10 10 10 10 7 7 10 7 8 9 12 2 8 9 10 10 2
110 5 25 25A 25B 15 20 355 20 25 25 30 30 35 35 40 70 55 75 115 20 15 25 30 65 40 120 145 15 50 40 45 20 152 45 50 65A 30A 154
TTL REQ 1 1 1 1 1 2 2 4 5 4 1 1 3 3 1 1 1 1 1 1 1 1 1 1 1 2 1 1 1 1 2 2 1 1 1 1 1 1 1
23-70-02
Illustrated Parts List Rev 3 Page 1025 Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
5 5A
10A–E 15 15A–K
20 20A–F
25 25A–F
30
30A
Solid–State Cockpit Voice Recorder Configuration, Model S100S, P/N: S100–0080–( ) Figure 1
23-70-02
Illustrated Parts List Rev 2 Page 1026 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM 1
PART NUMBER
AIRLINE PART NO.
NOMENCLATURE 1234567
EFF CODE
UNITS PER ASSY
1
S100–0080–00
SSCVR CONFIGURATION, A100S
A
RF
1A
S100–0080–01
SSCVR CONFIGURATION, A100S, TITANIUM FINAL ASSEMBLY, SSCVR (SEE FIG 2 FOR DETAIL BREAKDOWN) FINAL ASSEMBLY, SSCVR, TITANIUM (SEE FIG 2 FOR DETAIL BREAKDOWN) CONTROL ASSEMBY, A151–1, BLK, NO MICROPHONE CONTROL ASSEMBY, A151B, M2, GRAY, NO MICROPHONE CONTROL ASSEMBY, A151B, M2, BLK, NO MICROPHONE CONTROL ASSEMBY, A151B, BOEING BROWN, NO MICROPHONE CONTROL ASSEMBY, A151B, ATR BROWN, NO MICROPHONE CONTROL ASSEMBY, A152, GRAY, DYNAMIC MIC (SEE FIG 7 FOR DETAIL BREAKDOWN) CONTROL ASSEMBY, A152–1, BLACK, DYNAMIC MIC CONTROL ASSEMBY, A152–4, GRAY, DYNAMIC MIC CONTROL ASSEMBY, A152B, GRAY, CONDENSOR MICROPHONE CONTROL ASSEMBY, A152B, GRAY, CONDENSOR MICROPHONE CONTROL ASSEMBY, A152B, BLACK, CONDENSOR MICROPHONE CONTROL ASSEMBY, A152B, GRAY, CONDENSOR MICROPHONE CONTROL ASSEMBY, A152B, GRAY, CONDENSOR MICROPHONE CONTROL ASSEMBY, A152B, BOEING BROWN, CONDENSOR CONTROL ASSEMBY, A152B, BOEING BROWN, CONDENSOR CONTROL ASSEMBY, A152B, BLACK, CONDENSOR MICROPHONE
B
RF
A
1
B
1
5
253E0600–00
5A
253E0600–01
10A
93A15101
10B
93A15120
10C
93A15130
10D
93A15140
10E
93A15150
15
93A15200
15A
93A15201
15B
93A15204
15C
93A15220
15D
93A15225
15E
93A15230
15F
93A15235
15G
93A15240
15H
93A15250
15J
93A15260
15K
93A15270
1 1 1 1 1 1
1 1 1 1 1 1 1 1 1 1
23-70-02
Illustrated Parts List Rev 2 Page 1027 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM
PART NUMBER
1
20
93A055–00
20A
93A055–03
20B
93A055–10
20C
93A055–20
20D
93A055–30
20E
93A055–50
20F
93A055–55
25
93A055–40
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
MICROPHONE ASSEMBLY, REMOTE MODEL A55 (SEE FIG 10 for DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55 (SEE FIG 10 for DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BLACK, CONDENSOR, NON–MAGNETIC, DIRECTIONAL, REAR CONNECTOR (SEE FIG 10 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BLACK, CONDENSOR, NON–MAGNETIC, DIRECTIONAL, SIDE CONNECTOR (SEE FIG 10 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BROWN (BOENING), CONDENSOR, NON–MAGNETIC, DIRECTIONAL, REAR CONNECTOR (SEE FIG 10 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BLACK, CONDENSOR, NON–MAGNETIC, DIRECTIONAL, REAR CONNECTOR (SEE FIG 10 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BLACK, CONDENSOR, NON–MAGNETIC, DIRECTIONAL, SIDE CONNECTOR (SEE FIG 10 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, GRAY, MINI–CONDEN– SOR, PIGTAIL CONNECTOR, OMNI– DIRECTIONAL (SEE FIG 11 FOR DETAIL BREAKDOWN)
UNITS PER ASSY 1
1
1
1
1
1
1
1
23-70-02
Illustrated Parts List Rev 2 Page 1028 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM
PART NUMBER
1 25A
93A055–45
25B
93A055–60
25C
93A055–65
25D
93A055–66
25E
93A055–67
25F
93A055–95
30
9300A165
30A
9300A165–01
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BROWN (ATR–42), MINI–CONDENSOR, PIGTAIL CONNECTOR, OMNI–DIRECTIONAL (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, GRAY, MINI–CONDEN– SOR, NON–MAGNETIC, DIRECTIONAL, PIGTAIL CONNECTOR (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BROWN (ATR–42), MINI–CONDENSOR, NON–MAGNETIC, DIRECTIONAL, PIGTAIL CONNECTOR (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, GRAY, MINI–CONDEN– SOR, NON–MAGNETIC, DIRECTIONAL, PIGTAIL CONNECTOR (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BLACK, MINI–CONDEN– SOR, NON–MAGNETIC, DIRECTIONAL, PIGTAIL CONNECTOR (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBY, REMOTE MODEL A55B, BLACK, MINI–CONDEN– SOR, NON–MAGNETIC, DIRECTIONAL, PIGTAIL CONNECTOR (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBY, REMOTE (SEE FIG 12 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBY, REMOTE (SEE FIG 12 FOR DETAIL BREAKDOWN)
UNITS PER ASSY 1
1
1
1
1
1
1 1
23-70-02
Illustrated Parts List Rev 2 Page 1029 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
90
105 100
25
A 245
80 85 75
145
280 282 200 200A
140
Model A100S SSCVR Final Assembly, P/N: 253E0600–00 –01 Figure 2 (Sheet 1 of 2)
23-70-02 Illustrated Parts List Rev 2 Page 1030 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S 125 110 120 115
250 170
195 150 130
260
160A 160B
255
B 135 30
B
10 230
25
155
175
225
165 180
245 265 270 275
185 190
5 205
50 55 60 65
35
45 15 20
220
215
C 70 282 284
210 200 200A
205
C
235 240
A
Model A100S SSCVR Final Assembly, P/N: 253E0600–00, –01 Figure 2 (Sheet 2 of 2)
23-70-02 Illustrated Parts List Rev 2 Page 1031 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM 2
PART NUMBER 1
253E0600–00
1A
253E0600–01
5
024E0526–00
10
MS35649–244
15
MS35333–70
20
MS51957–14
25 30
042E0606–00 24SX–2–6–3–R
35
24SX–2–6–3–L
–40
PLC–832
45
239E0630–00
50 55 60 65
2299800341 2879800154 2299800423 2879800162
70 75
196E0608–00 408E0609–00
80
MS51959–17
85
189E0610–00
90 –93 95
075E0604–00 9030100047 9300A218
100
MS51957–27
AIRLINE PART NO.
NOMENCLATURE 1234567
RECORDER FINAL ASSEMBLY, A100S (SEE FIG 1 FOR NHA) RECORDER FINAL ASSEMBLY, A100S LIGHT WEIGHT (SEE FIG 1 FOR NHA) CABLE, GROUNDING ATTACHING PARTS NUT, HEX, 4–40 (V96906) (2870200002) WASHER, #4, INTERNAL TOOTH (V96906) (2730200025) SCREW,PAN HEAD,4–40 X5/16 (V96906) (2290200074) *** CHASSIS, SSCVR GUIDE, CARD, LOCK, RIGHT HAND, 3.0IN (V01121) (4019800042) GUIDE, CARD, LOCK, LEFT HAND, 3.0IN (V01121) (4019800043) NUT, CAPTIVE, 8–32, LOCKING, SST (2879800190) SPACER, CONNECTOR ATTACHING PARTS SCREW, M2X6, FLAT HEAD, SLOT NUT,HEX,LOW PROFILE,M2 SCREW, M2.5 X 14, FLAT HEAD,SST NUT,SELF–LOCK,NYL INSR *** PLATE, ISOLATOR, FRONT RETAINER, CARD ATTACHING PARTS SCREW, FLAT HEAD, 4–40 X 1/2 (V96906) (2290200189) PAD, CARD RETAINER *** DUST COVER, MODIFIED, SSCVR STATIC AWARENESS LABEL DELETED ATTACHING PARTS SCREW ,PAN HEAD, 6–32 X 5/16 (V96906) (2290200084)
EFF CODE
UNITS PER ASSY
A
RF
B
RF 1 1 1 1
1 2 2 6 1 4 4 2 2 1 1 2 1 1 1
2
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List Rev 23 Page 1032 Jul. 15/00 01/05 Mar.
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM
PART NUMBER
2
105
MS51957–28
110
191E0607–00
SCREW, PAN HEAD, 6–32 X 3/8 (V96906) (2290200085) *** PANEL, FRONT, SSCVR (SUPSD BY
191E0953–00
ITEM 110A, PRE ECO 07305) PANEL, FRONT, SSCVR (SUPSDS
110A
115
MS51957–45
120
9–1508
125
93–618
125A
230E0947–00
130
196E0605–00
135
9–1391
140 145 150
17D17–0262 17D17–0618 253E0585–00
151 152 153
016E0946–00 9300581 2290200398
154
933533617
155
9–1539
160A
266E0305–01
160B
266E0305–02
165
9300–177
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
UNITS PER ASSY 1
1 1
ITEM 110, POST ECO 07305) ATTACHING PARTS SCREW, PAN HEAD, 8–32 X 1/2 (V96906) (2290200102) FLAT FIBRE WASHER (V06141) (9391508) *** GASKET (OBSOLETE, SUPSD BY ITEM 125A), SEAL, FRONT PANEL (SUPSDS ITEM 125) NAMEPLATE, FRONT PANEL ATTACHING PARTS PAN HEAD SCREW (V06141) (9391391) *** MODIFICATION RECORD PLATE PROGRAM REVISION PLATE UNDERWATER LOCATOR DEVICE CRADLE ASSEMBLY BRKT, BEACON MOUNT COVER PLACE, ULD SCREW, CAP, SKT HD FLT 8–32 x 3/8 LOCKWASHER, #8 CSNK, SST ATTACHING PARTS HEX CP SC (LP62U040J12X2) (V06141) (9391539) *** BEACON,ACOUSTIC,UNDERWATER DUKANE (V94970) (DK–120) BEACON,ACOUSTIC,UNDERWATER RJE (V61257) (ELP–362D) HANDLE
2 2
1 1 1 4
1 1 1 1 1 1 1 4
1 1 1
23-70-02 Illustrated Parts List Rev 23 Page 1033 Jul. 15/00 01/05 Mar.
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM 2
PART NUMBER
170
MS51960–65
175
9300–180
180
MS51957–45
185
024E0616–00
190 195
L–11 #515
200
253E0348–03
200A
253E0992–00
200B
253E1290–00
200C
253E1293–00
205
AM003–7
210
MS24693–C3
215
79NM–40
220
MS51957–14
225
PLC–440
230
MS51958–65
235
239–E0197–00
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
ATTACHING PARTS SCREW, FLAT HEAD, 10–32 X 1/2 (V96906) (2290200043) *** HOLD–DOWN ATTACHING PARTS SCREW,PAN HEAD, 8–32 X 1/2 (V96906) (2290200102) *** CABLE ASSEMBLY, W3, VOICE MON ATTACHING PARTS PHONE JACK (9300384) JACK COVER (9300247) *** ASSEMBLY,FLASH CRASH SURVIVABLE STORE UNIT (SUPSD BY ITEM 200A, PRE FSB006) ASSEMBLY,FLASH CRASH SURVIVABLE STORE UNIT (SUPSD BY ITEM 200C, PRE FSB009) ASSEMBLY,FLASH CRASH SURVIVABLE STORE UNIT (SUPSDS ITEM 200, POST FSB006) ASSEMBLY,FLASH CRASH SURVIVABLE STORE UNIT (SUPSDS ITEM 200A, POST FSB009) MOUNT, ELASTOMERIC, SHOCK (1789800066) ATTACHING PARTS SCREW, FLAT HEAD, 4–40 X 5/16 (V96906) (2290200219) NUT 4–40 NYLON INSERT (2879800241) SCREW, PAN HEAD, 4–40 X 5/16 (V96906) (2290200074) NUT, CAPTIVE, NYLON LOCKING 4–40 (2879800191) SCREW, PAN HEAD, 10–32 X 3/4 (V96906) (2290200334) SPACER,VIBRATION MOUNT
UNITS PER ASSY 2
2 4
1 1 1 A
1
B
1
A
1
B
1
4
4 4 4 4 2 2
– ITEM NOT ILLUSTRATED - ITEM 200B U" PART NUMERS DESIGNATED REFURISHED WARRANTY REPAIR" FCSSU'S.
23-70-02 Illustrated Parts List Rev 2 Page 1034 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM
PART NUMBER
2
240
2299800417
245
205E0597–00
250 255
MS24693–C46 MS51959–15
260
MS51959–13
265
2979800257
270
MS51957–14
275
MS35333–70
280
205E0598–00
282A
205E0601–00
282B
205E1027–00
284 –285 –290 –295 –300 –305 –310 –315
2290200413 MS20470–AD2–2 LAC–440–2 2979800080 QQ–A–250/8 9–0527–03 905E0600–33 905E0600–19
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
SCREW, SHCAP, 10–32 X 1.125 LOW (V96906) (2290200365) PWA, AIRCRAFT INTERFACE A100S (SEE FIG 3 FOR DETAIL BREAKDOWN) ATTACHING PARTS SCREW, FLAT HEAD, 8–32 X 1/4 SCREW, FLAT HEAD, 4–40 X 3/8 (V96906) (2290200187) SCREW, FLAT HEAD, 4–40 X 1/4 (V96906) (2290200185) *** STAND OFF, 3/16 HEX, 4–40 X 1–1/31, (Mfg. UNICORP, No. P–343–M09–F09–440) SCREW, PAN HEAD, 4–40 X 5/16 (V96906) (2290200074) WASHER, #4, INTERNAL TOOTH (V96906) (2730200025) *** PWA, AUDIO PROCESSOR A100S (SEE FIG 4 FOR DETAIL BREAKDOWN) PWA, STORE PROCESSOR (SEE FIGURE 6 FOR DETAIL BREAKDOWN) PWA, STORE PROCESSOR, 8MB (SEE FIG 6 FOR DETAIL BREAKDOWN) ATTACHING PARTS SCREW, FLAT HEAD, 6–32 x 3/16 DELETED DELETED DELETED DELETED DELETED BLOCK DIAGRAM, PHYSICAL DRAWING TREE, SSCVR
UNITS PER ASSY 2 1
1 4 5
5
5 5
1 A
1
B
1
4 8 2 2 5 2 RF RF
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List Rev 2 Page 1035 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
AIRCRAFT INTERFACE PWA REAR PANEL 200 T1 T1
110
165
105
105
225 195
J7
70
15
CR9 CR17
CR12 CR 28
35
CR11
120
200
U1
C34
R4 C12 C13 CR12
T1 125 145
R6
+ + C29
C1 105
130
95
E8
U3
E7
C19 230 235
E6
195
E5
E1 E2 R 10
R 9
W1 CR 33 C 7
R 14 CR 32
85 90
C22
CR25
CR1 CR2
190 25 100
CR25 CR14 C16
CR7 CR3
R7 E4
CR4 C3
E3
C11
C8
C26 C10
C9 C4
C17 CR20
75 80
C15 C31 C6 C25 C2
C5 C27
J1
C30
5 175 135 130
CR24
CR6
40
45 150
CR C R 34 CR30 18 20
CR5
165
155 140
Q1
R12
115
20
CR 19
CR16
R13
U2 C 21
J2
10 250 110
10
C32
C28
65
A
C 33
C 14
CR10
CR18
10
SH2
CR R1 R2 26
U4
CR 27
185
50
CR32
R5 R3
R15 R11
R8
10
10 105
CR21
C24
C23
C 20
170 105
160 150 185
10
CR8 CR29
30 25 40
TP1 TP2
205
TP3
40
TP4
CR13
TP5
R19
TP6
205 110 30
205
CR31
30
180 110
55 60
210
215 220
110
40
Aircraft Interface PWA, P/N 205E0597–00 Figure 3 (Sheet 1 of 3)
23-70-02 Illustrated Parts List
Rev 2 Page 1036 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S AIRCRAFT INTERFACE PWA REAR PANEL 200 T1 T1
J7
R5 R3
R15 R11
CR R1 R2 26
R8 U4
CR 27
CR10
CR18
CR9 CR17
CR12 CR 28
A
CR21
C24
C23
C 20
CR11
CR32 C 33
C34 C 14
C32 U1 R4 C12 C13 CR12
T1
R6 C28
+
C1
+ C29 U3
65A
E8
102 C38
65A
SH2
E7
U5
E6
E5
E1 E2
C19 R 10
R 9
C 7
R 14 U2
CR 32
C 18 R 20 CR 34
J2 R12
R7
CR5
C22
CR6
CR2 CR25 CR14 L2 136
CR7 CR3
C37 E4 C36
CR4 C3
E3
C11
C8
C26 C10
C9 C4
L3 CR20
C5 C27 C30
J1
C15 C31 C6 C25 C2
L1
CR30
CR24 CR25
CR1
100A
CR16
R13
Q1
C 21
112
C35
W1 CR 33
CR 19
CR8 CR29
TP1 TP2 TP3 TP4
CR13
TP5
R19
TP6
CR31
Aircraft Interface PWA, P/N 205E0597–00 Post Mod Dot 6 Figure 3 (Sheet 2 of 3)
23-70-02 Illustrated Parts List
Rev 2 Page 1037 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S PIN 1
PIN 1
PIN 1
PIN 1
255 J5 STORE PROCESSOR PWA
245
P2 250 AIRCRAFT INTERFACE PWA
J3 240
A
SPARE PWA
J4 240 AUDIO PROCESSOR PWA
AIRCRAFT INTERFACE CABLE ASSEMBLY W1 (230)
Aircraft Interface PWA, P/N 205E0598–00 Figure 3 (Sheet 3 of 3)
23-70-02 Illustrated Parts List
Rev 1 Page 1038 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 3
PART NUMBER 1
205E0597–00
5
1N914, A, B
10
1N4148
15
1N5256A, B
20
1N5825
25
1.5KE250CA
30
1.5KE68C
35
1N759A
40
V130LA5
45 50 55
B191–20H MC1558U 2029800326
55A
2029800391
60
2160
65
25107
65A
NMF0509S
70
LM139J
75
LM136AH–2.5
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
PWA, AIRCRAFT INTERFACE A100S SSCVR (SEE FIG 2 FOR NHA) DIODE, SI, 75.0V, 75.0MA, SW (V16352) (0881009140) DIODE, SI, 100.0V, 300.0MA, SW (V16352) (0881041480) DIODE, SI, 30.0VZ, 4.2MA, ZENER (V04713) (0881052561) DIODE, SI, 40V, 5A, SCR (V04713) (0881058250) DIODE, SI, 250.0V, 5.0A, SUPRESSOR (V24444) (0889800034) DIODE, SI, 68.0V, 15.3A, SUPRESSOR (V24444) (0889800052) DIODE, SI, 12.0V, .1UA, ZENER (V06141) (0889900119) DVC, VRIS, 130VRMS, 20J, (1019800054) BRIDGE (V06288) (9391863) AMPLIFIER (V96906) (9391679) POWER SUPPLY, DC–DC, 15.5–42VIN (SUPSD BY ITEM 55A PRE SB012) POWER SUPPLY, DC–DC, 15.5–42VIN (SUPSDS ITEM 55 POST SB012) ATTACHING PARTS WASHER, #6, FIBRE .141 ID X (2739800041) *** POWER SUPPLY, DUAL, DC/DC CONV (V31669) (2029800308) (SUPSD BY ITEM 65A PRE ECO7977) POWER SUPPLY, DUAL, DC/DC CONV (V31669) (2029800360) (SUPSDS ITEM 65 POST ECO7977) INTEGRATED CIRCUIT, LINEAR , BIP, COMPARATOR, 14DIP, NH (V26014) (0469700905) INTEGRATED CIRCUIT, LINEAR , BIP, VREF, 3CAN, HNS (V26014) (0469701575)
UNITS PER ASSY RF 1 12 1 1 2 5 1 9 1 1 1 1
7
1
2
1
1
23-70-02 Illustrated Parts List
Rev 2 Page 1039 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
3
80
10042–DAP
85
2N2907A
90
10042–DAP
95 100
3371222004 3611010001
100A
167103J400A
102
158X104K
105
CK05BX104K
110
CK05BX103K
112
CK06BX104K
115
CK06BX105K
120
CK06BX562K
125
3781312522
130
7473422005
135
DD1032
136
0448900001
136A
0449800012
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
ATTACHING PARTS PAD, TRANSISTOR TO–18 OR 28, 4 PI (1899800002) TRANSISTOR, PNP SW 60V, HFE 100 (V07263) (2631029071) ATTACHING PARTS PAD, TRANSISTOR TO–18 OR 28, 4 PI (1899800002) *** CAPACITOR, STAN, 15V, 22UF, +10% CAPACITOR, PEM, 250V, 0.010 UF, 5%, (Mfg. MLRY, No. 167/.01/J/250/A) CAPACITOR, PEM, 400V, 0.01 UF, –5% (3610510001) (ADDED POST SB11) CAPACITOR, F, PEM, 250VAC, 0.10 UF, 10% (3164510002) (POST MOD DOT 6) CAPACITOR, 0.10 UF, 10%, 50V (V12294) (3631510002) CAPACITOR, 0.01 UF, 10%, 100V (V12294) (3633910001) CAPACITOR, CERAMIC, 0.10 UF, 10%, 100V (3695110002) (ADDED POST SB11) CAPACITOR, 1.0 UF, 10%, 50V (V51406) (3691510003) CAPACITOR, CERAMIC, 5600 PF, 10%, 200V (3693456000) CAPACITOR, FXD, 10 UF, 10%, 35V, (Mfg. UNION CARBID, No. T330C106K035AS) CAPACITOR, AL, 63V, 220 UF, +20%, (Mfg. SPR, No. 630D227M063FK5A) CAPACITOR 0.01 UF, 1 KV (V71279) (9391769) CHOKE ASSY, FERRITE, WB, 750 (SUPSD BY ITEM 136A PRE ECO8645) CHOKE ASSY, FERRITE, WB, .6K/50MHZ (SUPSDS ITEM 136 POST ECO8645)
UNITS PER ASSY 1 1
1
2 2
2
1
6 17 1
1 2 1
2 1 3 3
23-70-02 Illustrated Parts List
Rev 2 Page 1040 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
3
140 145 150 155 160 165 170 175 180
6080908669 6080910000 6080910001 6080924900 6080929401 6080930102 6080964900 6080968100 RN60D22R1F
185 190
6080130902 750–83–R100K
195
750–83R47K
200
TM7–3
205
2559800280
210
0639800074
215
5602–55–32
220
MS51957–5
225 230
62650–1 024E0611–00
235
77103–050
240
120–064–455F
245
4626–6300
250
68120–050
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
RESISTOR, 86.6 OHM, 1%, 1/10W RESISTOR. 1K, 1%, 1/10W RESISTOR. 10K, 1%, 1/10W RESISTOR, 2.49K, 1%, 1/10W RESISTOR, 29.4K, 1%, 1/10W RESISTOR. 301K, 1%, 1/10W RESISTOR, 6.49K, 1%, 1/10W RESISTOR. 6.81K, 1%, 1/10W RESISTOR, MF, 22.1 OHM, 0.5W, 1% (6140122100) RESISTOR, 309K, 1%, 1/10W, 100 PP NETWORK, RESISTOR, 4/100K OHM, 2% (V11236) (1829800135) NETWORK, RESISTOR, 4/47K OHM, 20W@ (V11236) (1829800192) TRANSFORMER, POWER 115V, 400 HZ INPUT (V01121) (2629800044) TERM, STAND OFF, 2 TURRET, NON–INS, (Mfg. CTC, No. 160–1558–03–01–00) CONNECTOR, 57–PIN, RACK & PANEL, (Mfg. CANNON, No. DPX036571–0059) ATTACHING PARTS WASHER, FIBRE, .10 IDX.190 (2739800038) SCREW, PAN HEAD, 2–56 X3/8 (V96906) (2290200067) *** CONNECTOR, PCB TAB (0639800709) CABLE ASSEMBLY, W1, AIRCRAFT INTERFACE ATTACHING PARTS SPRT, STRAIN RELIEF FOR (2799800018) *** CONNECTOR, 64–CONTACT, IDC FEMALE (0639801521) CONNECTOR, RECT, 26–CONTACT, PLUG (0639800696) CONNECTOR, PCB, 50CONT, TWO ROW (V53387) (0639801447)
UNITS PER ASSY 1 1 2 1 1 3 1 1 1 2 1 2 1 6
1
3 3
1 1
1
2 1 1
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List Page 1041 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
3
3518
255 –260 –265
206E0597–00 905E0597–01
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
INSERT, POLARIZNG KEY (V53387) (4219800026) BOARD, PRINTED WIRING SCHEMATIC, AIRCRAFT INTERFACE A100S
UNITS PER ASSY 2 1 AR
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List Page 1042 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
260
245
80 85
350
90 95
45 50
350
30
350
25
U11 CR2
R 5
350
R 6
C 44
U21
U12
U20
U18
+ 120
U19
U13
C 50
C88
C 46
C 45
70 75
U23
SH2
U22
U16
L1
5
U25 R44
J5
350
C23
195
C20
C14 R27
R25
R36
R39
175
R41
165 160 210 340
R 47
170 335
C76
C68
C78
C63
C66
C65
C64
C67
C73
C69
345
C C 47 24
215
345
C15 C28
230 345
U14
C59
C81
R 34
U10
C C R 19 10 R 20 31
C C C C 27 31 21 26
C51
105
240
R11
135 140
R10 R33
125 130
C7 C13 C2
R2
C3
R1 R17
C37 C18 C35 C9
U3
100
C C C 83 85 84
295
+
T3
+ +
T1
R19 R18
C61
330
T2
R3
C60
310
C1
350
R4
R R 30 32
110 370 375 380
T4
R29 C55
Q1
C 79
C 74
R R 21 23
U9
C C 22 16
155
10
CR3
U4
U6 C36 C12 C34 C6
R12
Q2
C 48
R7
C75
C 11
C 38
U5
270
CR4
R15 C R R 52 46 48
20
R13
C 57
U7
C56
240
C86
U15
C C C C C R 17 R 80 71 62 70 C33 C5 C29 C4 22 C32 C25 R 26 R 28 24 C53
C30
C 39
R9
R35
350 190
C 58
R8
C72
C87
R49 R14
CR5
R40
CR1
R45
R16 CR6
C 77
R38
A
C8
R37 R43
340
J6
290
R42
150 220 200
365 350 35 40
U1
C49 U24
370 375 380
U8 P1
U17
A
C 82
C41
U2
C 43
C40
80 85
295
C 42
180 350
335
205 185 320 325
350 105
340
155
170
225
355 360
150
300
Audio Processor PWA, P/N 205E0598–00 Figure 4 (Sheet 1 of 2)
23-70-02 Illustrated Parts List Rev 1 Page 1043 July 30/94 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
60 65
CR2
U11 R 5
R 6
C 44
U21
U18
U13 C88
U23
265
U22
U1
R44 145
R42
C23
C20
C14
A
C8
R37
R27
310
R25
R36
20
R43
285
R38
255
R9
R40
R8
350
C72
C76
105
C68
C78
C63
C66
C65
C64
R47
200 350 C C 47 24 R 22
C C 15 28
C73
C69
C75
R49
C 39
C59
U10
C 11
R C C 20 19 10 R 31
C C C C 27 31 21 26
C51
350
245 350
Q1
55 350
C 79
C 74 R33
280 C13 C2
R4
C1
245 160
R2
R1
R17
U3
T2 235 T3
T1
R19 R18
175 C3
R3
C60
310
C7
T4
R29 C55
U6
C61
165
Q2
C 48
C36 C12 C34 C6
C37 C18 C35 C9
310
R11
R10
R R 30 32
C C 22 16
C 38
C81
U9
105 115
CR3
U4
R C C C C C 21 R 23 17 R 80 71 62 70 C33 C5 C29 C4 C C R 26 32 25 28 R 24
350
CR4 R12
U7
U5
275 150
R13
C 57
R15 C R 46 R 52 48
250
C86
U15
R7
R35
C53 C 30 R 34
C67
C 58
C56
U14
C87
R45
CR5
R41
15
CR1 R14
R16 CR6
C 77
R39
155
L1
U25
10
315
U16
J5
J6
90 95
C45
C 49
350
U8
C 46
150
U24
+
P1
U17
A
C82
C41
U2
305
C 50
U19
150
C 42
C 43
C40 350
U12
U20
+
C C C 85 84 83
+ +
105
Audio Processor PWA, P/N 205E0598–00 Figure 4 (Sheet 2 of 2)
23-70-02 Illustrated Parts List Rev 2 Page 1044 Mar. 15/00 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 4
PART NUMBER 1
205E0598–00
5
VK200
10
1N5234B
15
0884700024
20
1N4614
25
HLMP–1700–101
30
046E0280–01A
35
046E0281–01
40
619–24–CC–B.1
45
046E0282–01
50
619–24–CC–B.1
55
OP–27BZ
60
0469701736
65
821573–3
70
0469701858
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
PWA, AUDIO PROCESSOR A100S SSCVR (SEE FIG 2 FOR NHA) CHOKE, FERRITE, .75K/50MHZ (V01121) (0449800006) DIODE, SI, .2VZ, 0.0MA, ENER (V16352) (0881052342) DIODE, SI, .0V, 0.0MA, DET, ] (Mfg. HP/TRW, No. 5082–2835/A2S835) DIODE, SI, .8VZ, 20MA, ENER, (V04713) (0881046140) INDICATOR, LED RED, –1, f TTL/CMOS (1379800088) INTEGRATED CIRCUIT, SERIAL PROM (V06141) (046E028001) INTEGRATED CIRCUIT, CHMOS, PLD, 24 DIP ATTACHING PARTS SOCKET INTEGRATED CIRCUIT 24 PIN W/DCPLG CAPACITOR, (V06141) (2369800248) *** INTEGRATED CIRCUIT, CHMOS, PLD, 24 DIP ATTACHING PARTS SOCKET INTEGRATED CIRCUIT 24 PIN W/DCPLG CAPACITOR, (V06141) (2369800248) *** INTEGRATED CIRCUIT, LINEAR, H BIP, OPAMP, 8 DIP, NS (V06141) (0464700009) INTEGRATED CIRCUIT, ARRAY, MOS, LCA, 84PLCC, Mfg. XLNX/MML, No. XC3030–70PC84W) ATTACHING PARTS SOCKET, PLCC, 4 CONT, /SOLDER (2369800291) *** INTEGRATED CIRCUIT, DIGITAL, G CMOS, INTERFACE, 0 DIP
UNITS PER ASSY RF 1 2 1
2 1 1 1
1
1
1
1
1
1
4
23-70-02 Illustrated Parts List Page 1045 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
4
75
2369800242
80
DS2165QN
85
821581–1
90
0469701861
95
821665–1
100
0469701868
105
OP470AY
110
LH0002H
115
DG201AAK
120
1849700118
125
2N2222A
130
10042–DAP
135
2N2907A
140
10042–DAP
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
ATTACHING PARTS SOCKET INTEGRATED CIRCUIT 20PIN W/DCPLG CAPACITOR *** INTEGRATED CIRCUIT, DIGITAL, CMOS, DSP, 28PLCC (V0B0A9) (0469701859) ATTACHING PARTS SOCKET, PLCC, 28CONT, SQUARE (2369800289) *** INTEGRATED CIRCUIT, MEMORY, HCMOS, FIFO, 1K X 9 ATTACHING PARTS SOCKET, PLCC, 32CONT, RECTANGLE (V00779) (2369800276) *** INTEGRATED CIRCUIT, LINEAR , BIP, VR, 3PP, NH, (Mfg. MOT, No. MC79LO5ABP*SCR–55/+85C) INTEGRATED CIRCUIT, LINEAR, BIP, OPAMP, 14DIP (0469701873) INTEGRATED CIRCUIT, LINEAR , BIP, AMP, 8CAN, HNS (V27014) (0469701881) INTEGRATED CIRCUIT, DIGITAL, CMOS, SW, 16DIP, HNS, (V1Y409) (0469701882) OSCILATOR, CRYSTAL, HCMOS, 12.288MHZ, (Mfg. CONW, No. H83G–12.288MHZ) TRANSISTOR, NPN, SI, SINGLE, 30VCE (V07263) (2631022221) ATTACHING PARTS PAD, TRANSISTOR TO–18 OR 28, 4 PI (1899800002) *** TRANSISTOR, PNP SW 60V, HFE 100 (V07263) (2631029071) ATTACHING PARTS PAD, TRANSISTOR TO–18 OR 28, 4 PI (1899800002) ***
UNITS PER ASSY 4
5
5
2
2
1
5 1
1
1
1
1
1
1
23-70-02 Illustrated Parts List Page 1046 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
4
145
750–101–R47K
150
1829800193
155
1829800194
160
1829800195
165
1829800196
170
1829800197
175
1829800198
180
1829800199
185
1829800200
190
1829800201
195
1829800202
200
1829800203
205
1829800204
210
1829800206
215
4989–02–1822F
220
1829800209
225
1829800210
230
1829800211
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
NETWORK, RESISTOR, 9/47K OHM, 2% (V11236) (1829800167) NETWORK, RESISTOR, 4/10KOHM, 1%, (Mfg. IRC, No. 4989–02–1002–F) NETWORK, RESISTOR, 4/1KOHM, 1%, (Mfg. IRC, No. 4989–02–1001–F) NETWORK, RESISTOR, 4/15KOHM, 1%, (Mfg. IRC, No. 4989–02–1502–F) NETWORK, RESISTOR, 4/7.5KOHM, 1%, (Mfg. IRC, No. 4989–02–7501–F) NETWORK, RESISTOR, 4/1.87KOHM 1%, (Mfg. IRC, No. 4989–02–1871–F) NETWORK, RESISTOR, 4/17.4KOHM, 1%, (Mfg. IRC, No. 4989–02–1742–F) NETWORK, RESISTOR, 4/6.19KOHM 1%, (Mfg. IRC, No. 4989–02–6191–F) NETWORK, RESISTOR, 4/13KOHM, 1%, (Mfg. IRC, No. 4989–02–1302–F) NETWORK, RESISTOR, 4/825OHM 1%, (Mfg. IRC, No. 4989–02–8250–F) NETWORK, RESISTOR, 4/11KOHM, 1%, (Mfg. IRC, No. 4989–02–1102–F) NETWORK, RESISTOR, 4/4.99KOHM, 1%, (Mfg. IRC, No. 4989–02–4991–F) NETWORK, RESISTOR, 4/604OHM, .25%, (Mfg. IRC, No. 4989–03–6040–C) NETWORK, RESISTOR, 4/20OHM 1%, (Mfg. IRC, No. 4989–02–20R0–F) NETWORK, RESISTOR, 4/18.2KOHM 1% (1829800207) NETWORK, RESISTOR, 4/20KOHM, 1%, (Mfg. IRC, No. 4989–02–2002–F) NETWORK, RESISTOR, 4/1.5KOHM 1%, (Mfg. IRC, No. 4989–02–1501–F) NETWORK, RESISTOR, 4/150KOHM, 0.25%, (Mfg. IRC, No. 4989–03–1503–C)
UNITS PER ASSY 2 5 3 2 4 2
2
1
1 1 1 2
1
1 1 1 1 1
23-70-02 Illustrated Parts List Page 1047 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
4
235
68WR10K
240 245 250 255 260 265 270 275 280 285 290
6080905629 6080910000 6080910009 6080910701 6080912400 6080930100 6080935700 6080949901 6080973200 6080988701 3019822003
295 300 305
3371139004 3371315004 403DDC
310
CK05BX104K
315
CK05BX102K
320
CKO5BX101K
325
CK05BX561K
330
CK06BX274K
335
CCR06CG472FR
340
CCR07CG333FR
345
CCR07CG683FR
345A
CCR07CG104FR
350
MD015C104KAA
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
POT, TRIMMER, 10K OHM, 10%, 0.5W (V01121) (2019800376) RESISTOR, 56.2 OHM, 1%, 0.1W RESISTOR, 1K OHM, 1%, 0.1W RESISTOR, 100.0 OHM, 1%, 0.1W RESISTOR, 10.7K OHM, 1%, 0.1W RESISTOR, 1.24K OHM, 1%, 0.1W RESISTOR, 3.01K OHM, 1%, 0.1W RESISTOR, 3.57K OHM, 1%, 0.1W RESISTOR, 49.9K OHM, 1%, 0.1W RESISTOR, 7.32K OHM, 1%, 0.1W RESISTOR, 88.7K OHM, 1%, 0.1W CAPACITOR, CERAMIC, 50V, 2.2 UF, +20%, (Mfg. MUER/MML, No. RPE117X7R225M50V) CAPACITOR, STAN, 10V, 39 UF, +10% CAPACITOR, STAN, 20V, 15 UF, +10% CAPACITOR, CERAMIC, DECOUPLING, .04UF X7R (3459800023) CAPACITOR, 0.10 UF, 10%, 50V (V12294) (3631510002) CAPACITOR, 1000 PF, 10%, 200V (3633410000) CAPACITOR, 100 PF, 10%, 200V (3633410009) CAPACITOR, 560 PF, 10%, 200V (3633456009) CAPACITOR, 0.27 UF, 10%, 50V (3691527002) CAPACITOR, CERAMIC, 0.0047UF, 1%, 100V (3990547000) CAPACITOR, FIX, CERAMIC, 0.033UF, 1%, 50V (3991133001) CAPACITOR, FIX, CERAMIC, .068 UF, 1%, 50V (3991168001) (SUPSD BY ITEM 345A PRE ECO9282) CAPACITOR, FIX, CERAMIC, .1 UF, 1%, 50V (3991110002) (SUPSDS ITEM 345 POST ECO9282) CAPACITOR, CERAMIC, 0.1UF, 50V, +10% (V96906) (7540110002)
UNITS PER ASSY 4 2 3 1 1 1 1 1 1 1 1 2
2 2 1 4 1 5 4 4 6 25 7
7
26
23-70-02 Illustrated Parts List Rev 2 Page 1048 Mar. 15/00 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
4
355
9300–286–01
360
SP–310
365
0639801522
370 375 380
2299800197 2739800090 2879800213
–385
75401–001
–390
905E0598–01
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
TRANSFORMER, SELECTED ATTACHING PARTS COVER, FOR SP–66 TRANSFORMER, (0759800054) *** CONNECTOR, 64 CONT, PIN HDR MALE, (Mfg. PAND, No. 120–064–053–00) ATTACHING PARTS SCREW, M2.5X12, PAN HEAD, SST WASHER, EXT TOOTH, M2.5, SST NUT, M2.5X.45 *** CONTROL, PIN .025SQ, .345L, (V01121) (0659800093) SCHEMATIC, AUDIO PROCESSOR. A100S
UNITS PER ASSY 4 4
1
2 2 2 46 AR
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List Page 1049 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
J2 P2
15
Flash Crash Survivable Store Unit (FCSSU), P/N 253E0348–03, P/N 253E0660–00, P/N 253E0992–00, P/N 253E1290–00, P/N 253E1293–00 Figure 5
23-70-02
Illustrated Parts List Rev 2 Page 1050 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 5
PART NUMBER
AIRLINE PART NO.
NOMENCLATURE 1234567
ASSEMBLY, FLASH CRASH SURVIVABLE STORE UNIT (SEE FIGURE 2 FOR NHA) OBSOLETE – REPLACED BY P/N 205E0660–00 FSB No. SSCVR 003 ASSEMBLY, FLASH CRASH SURVIVABLE STORE UNIT (SEE FIGURE 5 FOR NHA) THIS UNIT REPLACES ITEM NO. 1 AS PER FSB No. SSCVR 003
EFF CODE
UNITS PER ASSY
A
RF
B
RF
1
253E0348–03
1A
205E0660–00
1B
253E0992–00
ASSEMBLY, FLASH CRASH SURVIVABLE STORE UNIT (SEE FIGURE 5 FOR NHA) THIS UNIT IS AN IMPROVEMENT TO ITEM NO. 1 AS PER FSB No. SSCVR 006
RF
1B
253E1290–00
ASSEMBLY, FLASH CRASH SURVIVABLE STORE UNIT (SEE FIGURE 5 FOR NHA) THIS UNIT IS AN IMPROVEMENT TO ITEM NO. 1 AS PER FSB No. SSCVR 006
RF
1C
253E1293–00
ASSEMBLY, FLASH CRASH SURVIVABLE STORE UNIT (SEE FIGURE 5 FOR NHA) THIS UNIT IS AN IMPORVEMENT TO ITEM NO. 1 AS PER FSB No. SSCVR 006
RF
15
BCDAT–2–619–5
*** LABEL, BLANK 3.0 X .9 (9090100789)
AR
*** CAUTION *** THIS MODULE CAN ONLY BE SERVICED BY FACTORY TRAINED TECHNICIANS. OPENING MAY VOID WARRANTY. P/N 253–E0XXX–XX S/N XXXXX WT XXXXX Kg REV XX
23-70-02
Illustrated Parts List Rev 2 Page 1051 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
235 70
185
240 55
145
110 115
15
120
280
275
260 60
45 50
240 60
195
235 90
240 90
270
155
155 195
R11
300 305
U24
TP40
275
U7
J5
70 235
R 15
U12
C107
85 225
C112
165
L3
130 235
C113
C110
160
C16 C101
35 40
TP2
U6
U23
C8 C 123
U5
CR2 C1
C11
U18
C9
R4
C109
CR3
U11
R3
150 245
C118
135
R10 C C 13 7
R9
R8
C3
220
C10 U4
U9 C2
U13
C111
Y1 C6
C113
U2 C102
E1 E2
R2
L1
265
125 250
U19
C15
290 200
100 105 255
U22
C115
C108
C5
U3
275 160
U15
U8
270
20 (FAULT INDICATOR)
CR5
R6
TP1
180
R12
U20
L2
175
R1 R16
R 17
C 106
10 190
80
C114
TP10
U10
CR1 R7
145
C117
U14
U1
C 12
U16
U21
C4
W2
295
CR 4
U17
R5
J2
TP20
5
TP30
C14
210 215
140 275
95 240
155
205
170
65 230
310
165
170
315
130 235
75 235
130 285 155 235
25 30
275
Notes: 1. C8 is installed under IC chip U5; C7 and C13 are installed under U4; C10 is installed under the socket of U22; C15 is installed under Y1; C102 is installed under U2. 2. DIP CAPS (C1XX) share the same holes as their corresponding IC chip's (UXX). Reference designators for CAPS are similar to their corresponding IC chip plus 100. Example: C123 is located under U23, etc.
Store Processor PWA, P/N 205E0601–00, P/N 205E1027–00 Figure 6
23-70-02 Illustrated Parts List
Rev 1 Page 1052 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 6
PART NUMBER
1
205E0601–00
1A
205E1027–00
5
1N4761A
10
0884700024
15
1N5819
20
HLMP–7000–1S1
25
046E0283–01A
30
236–C2110–10
35
046E0284–01A
40
100–0200612
45
046E0285–01A
50
SS020–01–TG
55
0469701469
AIRLINE PART NO.
NOMENCLATURE 1234567
PWA, STORE PROCESSOR SSCVR (SEE FIGURE 2 FOR NHA) (SUPSD BY ITEM 1A PRE SB003) PWA, STORE PROCESSOR SSCVR (SEE FIGURE 2 FOR NHA) (SUPSDS ITEM 1 POST SB003) DIODE, SI, 75.0 VZ, 3.3 MA, ZENER (V04713) (0881047611) Deleted per Rev. C, ECO 0006654 (effectivity date 03–12–92). DIODE, SI, 8.0V, 10.0 MA, SDET, (Mfg. HP/TRW, No. 5082–2835/A2S835) DIODE, SI, 40.0V, 500.0 MA, SDET (V04713) (0889758190) DIODE, GAP, 3.0V, 5.0 MA, LED (V50434) (1379800099) INTEGRATED CIRCUIT, PLD, 20 DIP (V06141) (046E0283–01) ATTACHING PARTS SOCKET, STRIP, 10 PIN *** INTEGRATED CIRCUIT, PLD, 20 DIP (V06141) (046E0284–01) ATTACHING PARTS SOCKET,INTEGRATED CIRCUIT, DIP 20PIN,SLDR (236–98–00171) *** INTEGRATED CIRCUIT, EPROM,40 DIP (V06141) (046E0285–01) ATTACHING PARTS SOCKET, STRIP, 20 PIN, .100 (2369800136) *** INTEGRATED CIRCUIT, DIGITAL, CMOS, LATCH, 24 DIP, (Mfg. IDT, No. IDT54FCT843BDB) Deleted per Rev. F, ECO 0007628 (effectivity date 3–28–94).
EFF CODE
UNITS PER ASSY
A
RF
B
RF
A
1
1 2 1 1
2 1
1
1
2
1
23-70-02 Illustrated Parts Parts List List Illustrated
Rev 12 Page Page 1053 1053 Rev July Mar. 30/94 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
6 55A
0469702493
60
0469701732
65
CD54ACT238F3A
70
54FCT541DM
75
54ACTQ245DM
80
MAX632AMJA
80A
NMF0512S
85
CD54HCT14F
90
0469701883
95
AM29C821/BLA
100
0469701885
105
821574–1
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
INTEGRATED CIRCUIT, DIGITAL, CMOS, LATCH, 24 DIP, (Mfg. IDT, No. IDT54FCT841BD) Added per Rev. F, ECO 0007628 (effectivity date 3–28–94). INTEGRATED CIRCUIT, MEMORY, CMOS, SRAM, 32KX8, INTEGRATED CIRCUIT, DIGITAL, ACTMOS, DECODER/DEMUX (V34371) (046–97–01862) INTEGRATED CIRCUIT, DIGITAL, FCT, DRIVER, 20 DIP (V27014) (046–97–01863) INTEGRATED CIRCUIT,DIGITAL, ACTQ, TRANSCEIVER, 20 DIP, (V27014) (046–97–01865) INTEGRATED CIRCUIT, LINEAR, CMOS, VR, 8 DIP, HNS (V96906) (046–97–01870) Deleted per Rev. C, ECO 0006654 (effectivity date 03–12–92. POWER SUPPLY, DC/DC CONVERTER, 5 VDC, 8 DIP, (202–98–00322) Added per Rev. C ECO 0006654 (effectivity date 03–12–92. INTEGRATED CIRCUIT, DIGITAL, HCTMOS, ST, 14 DIP (V34371) (046–97–01871) INTEGRATED CIRCUIT, DIGITAL, CMOS, LATCH, 24 SDIP, (Mfg. AMD/MML, No. 5962–8760301LA) INTEGRATED CIRCUIT, DIGITAL, CMOS, REGULATOR, 24 SDIP (V34335) (046–97–01884) INTEGRATED CIRCUIT, DIGITAL, CMOS, MIPRCS, 68PLCC, (Mfg. AMD, No. N80C186–16*SCREEN) ATTACHING PARTS SOCKET, PLCC, 68 CONT, SQUARE, (V00779) (236–98–00270) ***
UNITS PER ASSY 1
2 A
1
2
1
A
1
A
1
1
2
2
1
1
23-70-02 Illustrated Parts List
Rev 1 Page 1054 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 6
PART NUMBER
110
0469701888
115
821665–1
120
0469701892
125
0469701896
130
SN54BCT2244J
135
DDU–8Z297
140
42285
145
39424
150
1849700119
155
2559800205
160
7447–1–P42
165
750–101–R10K
170
750–83–R47
175
750–83–R10K
180
750–101–R100K
185
750–101–R47K
190
RNC50*DSCR
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
INTEGRATED CIRCUIT, DIGITAL, CMOS, EEPROM, 32PLCC ATTACHING PARTS SOCKET, PLCC, 32CONT, RECTANGLE (V00779) (236–98–00276) *** INTEGRATED CIRCUIT, LINEAR , BIP, VR, 8 DIP, NH INTEGRATED CIRCUIT, DIGITAL, CMOS, MPSUP, 8 DIP, NH, (Mfg. LTEC, No. LTC690IN8*SCREEN) INTEGRATED CIRCUIT, DIGITAL, CMOS, BUFFER, 20 DIP, HNS (V9K523) (046–97–01905) DVC, DELAY UNIT, HCMOS, 8 DIP (V22519) (101–98–00077) INDUCTOR, DUAL, 500 UH, 660 MA, (055–98–00221) Deleted per Rev. C, ECO 0006654 (effectivity date 03–12–92). CHOKE, ASSEMBLY, FERRITE, WB, 750 (V06141) (044–89–00001) OSCILATOR, CRYSTAL, HCMOS, 32.0 MHZ, (Mfg. CONW, No. S83R–32.000 MHZ) TERMINAL PW, 2–TURRET, .062 BD, (Mfg. CTC/MML, No. 160–1558–02–05–00) TERMINAL, STAND OFF, NON–INSULATED, SWAGE (2559800255) NETWORK, RESISTOR, 9/10K OHM, 2% (V11236) (182–98–00076) NETWORK, RESISTOR, 4/47 OHM, 2% (V11236) (182–98–00085) NETWORK,RESISTOR, 4/10K OHM, 2% (V11236) (182–98–00095) NETWORK, RESISTOR, 9/100K OHM, 2% (V11236) (182–98–00111) NETWORK, RESISTOR, 9/47K OHM, 2% (V11236) (182–98–00167) RESISTOR, MF, 1.5K OHM, 1%, 0.1W (600–49–15000)
UNITS PER ASSY 1
1
1 1
3
1 1
2 1
4
2 2 2 1 2 1 1
23-70-02 Illustrated Parts List
Rev 1 Page 1055 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 6
PART NUMBER
195 200 205
6080102269 6080924900 6112820001
210
6140116200
215
6140166508
220
3392222005
220A
3392222005
221
3381347004
225
104JEV
230
104JEW
235
104JEX
240
104JEY
245
502DFF
250
502DRC
255
183DHL
260
263D28
265
3621215004
270
3623633004
275
CK05BX104K
280
3781312522
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
RESISTOR, 22.6 OHMS, 1%, 0.1W RESISTOR, 2.49K OHMS, 1%, 0.1W RESISTOR, MF, 20.0K OHM, 0.1% 0.1W, (Mfg. IRC, No. MAR5–T16–20.0K–.1%) RESISTOR, MF, 1.62K OHM, 0.1%, 10 PPM (Mfg. DALE, No. PTF–561K62BT–13) RESISTOR, MF, 66.5 OHM, 0.1%, 10 PPM, (Mfg. DALE, No. PTF–5666R5BT–13) CAPACITOR, STAN, 20V, 220 UF, +20%, (Mfg. SPR/MML, No. 152D227X9020S2) CAPACITOR, STAN, 20V, 220 UF, +20%, (Mfg. SPR/MML, No. 152D227X9020S2) C2 value changed per Rev. C, ECO 0006654 (effectivity date 03–12–92). See item 221. CAPACITOR, STAN, 20V, 47 UF, +20%, New C2 value per Rev. C. CAPACITOR, CERAMIC, 50V, 10 UF, +25% (345–98–00015) CAPACITOR, CERAMIC, 50V, 10 UF, +25% (345–98–00016) CAPACITOR, CERAMIC, DECOUPLING, 0.1 UF X7R (345–98–00018) CAPACITOR, CERAMIC, DECOUPLING, 0.1 UF X7R (345–98–00019) CAPACITOR, CERAMIC, DECOUPLING, 0.005 UF (345–98–00021) CAPACITOR, CERAMIC, .005UF, X7R, (345–98–00022) CAPACITOR, CERAMIC, DECOUPLING, 0.018 UF, X7R (345–98–00024) CAPACITOR, CERAMIC, DECOUPLING, 0.026 UF, X7R (345–98–00025) CAPACITOR, TEP, 20V, 15.0 UF, 20% (Mfg. KEMET, No. T370E156M020AS) CAPACITOR, TEP, 10V, 33.0 UF, 20%, (Mfg. KEMET, No. T330C336M010AS) CAPACITOR, 0.10 UF, 10%, 50V (V12294) (363–15–10002) CAPACITOR, FIXED, 10 UF, 10%, 35V, (Mfg. UNION CARBID, No. T330C106K035AS)
UNITS PER ASSY 2 1 1 1 1 2
A
1
A
1 1
A
1 7 5 2 1 1 2 1 2 5 1
23-70-02 Illustrated Parts List
Rev 1 Page 1056 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 6
PART NUMBER
285
7552110002
290
CK05BX102K
295
024–E0612–00
300
3399–6026
305
3926–0000T
310
3433–5302
315
3518
–320 –325 –330 –335
206E0601–00 905E0601–01 206E1027–00 905E1027–01
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
CAPACITOR, CERAMIC, 0.1 UF, 20%, 50V, X7R, (Mfg. KEMET, No. C420C104MR5RCA) CAPACITOR 0.001 UF, 200V (9305BX102K) Deleted per Rev. C, ECO 0006654 (effectivity date 03–12–92). CABLE ASSEMBLY, W2, STORE PROCESSOR CONNECTOR, RECT, 26–CONTACT, PLUG (V53387) (063–98–00367) CONNECTOR, RECT, 26–CONTACT PWB MT (063–98–01136) CONNECTOR, RECT, 50–CONTACT, RECEPTICLE HDR (063–98–00818) ATTACHING PARTS INSERT, POLARIZNG KEY (V53387) (421–98–00026) *** BOARD, PRINTED WIRING (2M) SCHEMATIC, STORE PROCESSOR (2M) BOARD, PRINTED WIRING (8M) SCHEMATIC, STORE PROCESSOR (8M)
UNITS PER ASSY 2
1
1 1 1 1
2
A A B B
1 AR 1 AR
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List
Rev 1 Page 1057 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
15
ÀÀ ÀÀ ÀÀ
20 115 75
30 35
110 140
40
150
65 45
60
5
50
10
25
105 135
55
85 70 90 95 100 125 130
80 120 145
155 160
MODEL AI51/A151B CONTROL UNITS (REMOTE MICROPHONE USED )
MODEL AI52/A152B CONTROL UNITS (BUILT-IN MICROPHONE)
Control Unit, P/N 93A151–XX, 93A152–XX Figure 7
23-70-02
Illustrated Parts List Rev 1 Page 1058 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 7
PART NUMBER 1
93A15100
1A
93A15101
1B
93A15120
1C
93A15130
1D 1E
93A15140 93A15150
1F
93A15200
1G
93A15201
1H
93A15204
1J
93A15220
1K
93A15225
1L
93A15230
1M
93A15235
1N
93A15240
1P
93A15250
1Q
93A15260
1R
93A15270
5 10 15
17D17–0262 93–624 9300A014
15A 15B 15C
9300A014–01 9300A014–02 9300A014–03
AIRLINE PART NO.
NOMENCLATURE 1234567
CONTROL UNIT ASSEMBLY MODEL A151,MOD (SEE FIG 1 FOR NHA) CONTROL UNIT ASSEMBLY MODEL A151–1, M CONTROL UNIT ASSEMBLY A151 B MODIFICATION 2 CONTROL UNIT ASSEMBLY A151B MODIFICATION 2 CONTROL UNIT ASSEMBLY A151B CONTROL UNIT ASSEMBLY A151B MODIFICATION 1 CONTROL UNIT ASSEMBLY. MODEL A152, MOD CONTROL UNIT ASSEMBLY MODEL A152–1 MOD CONTROL UNIT ASSEMBLY MODEL A152–4 MOD CONTROL UNIT ASSEMBLY A152 B MODIFICATION 2 CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 CONTROL UNIT ASSEMBLY MODEL A152B MOD CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 MODIFICATION RECORD PLATE NAMEPLATE FRONT PANEL ASSEMBLY – GRAY FRONT PANEL ASSEMBLY – BLACK FRONT PANEL ASSEMBLY–BROWN FRONT,PANEL ASSEMBLY–ATR 42 BROWN
EFF CODE
UNITS PER ASSY
A
RF
B
RF
C
RF
D
RF
E F
RF RF
G
RF
H
RF
J
RF
K
RF
L
RF
M
RF
N
RF
P
RF
Q
RF
R
RF
S
RF
A,C,G, J–L,N,P B,D,H,M,S E,Q,R F
1 1 1 1 1 1
23-70-02
Illustrated Parts List Rev 2 Page 1059 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
7
20
8EP46R3
25
9300–233
25A 25B 30 35 40
9300–233–01 9300–233–04 9300–179–01 9300–179–02 L–11
45 50
93–1021 9300–388
55
9300–195
60
MS15795–803
65
8EP44R3
70 75 80 80A
9300–329 9300–337 93A264 93A267
80B 80C
93A265 93A268
85
9–1504
90 95 100 105 110 115 120 125 130 135
93A307 9300–A033 93A307 9300–204 9300–205 9300–344 9300–377 93A244 93A307 9300–204
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
ATTACHING PARTS SCREW, PAN HEAD, 4–40 X 3/8 (V06141) (938EP46R3) *** METER
UNITS PER ASSY 4
METER METER SWITCH, GREEN SWITCH, RED PHONE JACK (9300384) ATTACHING PARTS SHOULDER WASHER PLUG *** .COVER, 2.12W X 5.00L X 2.50, AL ATTACHING PARTS WASHER, #4, FLAT ST STL (V96906) (2730200004) SCREW,PAN HEAD,4–40 X1/4 (V06141) (938EP44R3) *** INSULATOR PLUG HARNESS ASSEMBLY. HARNESS ASSEMBLY–CONTROL UNIT HARNESS ASSEMBLY. HARNESS ASSEMBLY–CONTROL UNIT ATTACHING PARTS NUT (79NM–40) (V06141) (9391504) *** CHASSIS ASSEMBLY, CONTROL UNIT BRACKET & MICROPHONE CHASSIS ASSEMBLY, CONTROL UNIT DAMPER, MICROPHONE MICROPHONE MICROPHONE HUM SHIELD GROMMET BRACKET & MICROPHONE ASSEMBLY CHASSIS ASSEMBLY, CONTROL UNIT DAMPER, MICROPHONE
A–G,K,L,Q, S H,M,N J,P,R
1 1 1 1 1 1 2 1 1
G,H,K–M, P–S
2 2
A–F A,B,G,H C–F, K–N,Q,S J P,R
1 1 1 1 1 1 4
A–F G–J G G–J G–J G–J G–J K–S K K–S
1 1 1 1 1 1 1 1 1 1
23-70-02
Illustrated Parts List Page 1060 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
7
140 145 150 155
93–619–01 9300–377 9300–197 93A263–02
155A
93A266–01
160
8EP46R3
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
MICROPHONE, NON–MAGNETIC GROMMET WASHER–MICROPHONE PWA MICROPHONE PREAMP (SEE FIG 8 FOR DETAIL BREAKDOWN) PWA, MICROPHONE PRE–AMP ASSEMBLY (SEE FIG 9 FOR DETAIL BREAKDOWN) ATTACHING PARTS SCREW, PAN HEAD, 4–40 X 3/8 (V06141) (938EP46R3) ***
UNITS PER ASSY
K–S K–S G–S A,B,G–J
1 1 1 1
C–F, K–S
1
4
23-70-02
Illustrated Parts List Page 1061 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
170
80
90 145
50
60
80
25
115
55
50
R2
GND M
C1 C15
R7 30
C22
Q6
185
R5
R8
K
R11
5B R 18
C8
C11 D 1
C9
20
80
C10
125
q
55
175
40
Q4
35
115
p
R3 2
30 105 100
R 31 r
155 115
C R 16 24
C 18
85 20
Q3
75
R23
t
95
180
R C R 25 17 21
R16 R 30
C21
5
R26
C13
Q2
D 4
C
R22
R29 R 15
R 19
100
20
R17
120 130
D C 2 14
C19
C12
R 13 R R 12 14
145
15
C20
80 70
10
R28
L
150
65
R 27
B
Q5
R9
165
15 110
R10
160
160
140
C5
C6
P
R6
R3 20
P
180
C7
C4
Q1
N
C2
R4
30
85
F
C3
200
20
175
45
80
135
40
75
Dynamic Microphone Preamplifier PWA, P/N 93A263–02 Figure 8
23-70-02
Illustrated Parts List Rev 1 Page 1062 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 8
PART NUMBER 1
93A263–02
5
1N4446
10 15 20 25 30 35 40 45 50
1N295 9300–285 9300–290 9300–301 9300–305 9300–307 9300–534 9300–583 CK05BX103K
55 60 65
CK06BX223K 3370415004 9–1588
70
9391767
75
RC07GF101J
80
RC07GF102J
85
RC07GF103J
90
RC07GF125J
95
RC07GF151J
100
RC07GF152J
105
RC07GF154J
110
RC07GF221J
115
RC07GF222J
120
RC07GF224J
125
RC07GF471J
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
PWA MICROPHONE PREAMP (SEE FIG. 7 FOR NHA) SILICON DIODE (V06141) (9300272) GERMANIUM DIODE (9300292) CAPACITOR, 4.7 UF, 35V CAPACITOR, 1.0 UF, 35V CAPACITOR, 10 UF, 20V CAPACITOR, 47 UF, 20V CAPACITOR, 4.7 UF, 20V CAPACITOR, 0.01 UF, 100V CAPACITOR, 0.22 UF, 20V CAPACITOR, 0.01 UF, 100V (V06141) (9305BX103K) CAPACITOR, (V06141) (9306BX223K) CAPACITOR, STAN, 20V, 15UF, +5% CAPACITOR, 0.022 UF 50V (V06141) (9391588) CAPACITOR, 150UF, 30V, (Mfg. SPRAGUE, No. 109D157X0030F2) RESISTOR, CC, 100 OHM, 1/4W, 5% (V01121) (9307GF101J) RESISTOR, CC, 1.0K OHM, 1/4W, 5% (V01121) (9307GF102J) RESISTOR, CC, 10.0K OHM, 1/4W, 5% (V01121) (9307GF103J) RESISTOR, CC, 1.2M OHM, 1/4W, 5% (V01121) (9307GF125J) RESISTOR, 150 OHM, 1/4W, 5% (V01121) (9307GF151J) RESISTOR, 1.5K OHM, 1/4W, 5% (V01121) (9307GF152J) RESISTOR, 0.15M OHM, 1/4W, 5% (V01121) (9307GF154J) RESISTOR, 220 OHM, 1/4W, 5% (V01121) (9307GF221J) RESISTOR, 2.2K OHM, 1/4W, 5% (V01121) (9307GF222J) RESISTOR, 220.0K OHM, 1/4W, 5% (V01121) (9307GF224J) RESISTOR, 470 OHM, 1/4W, 5% (V01121) (9307GF471J)
UNITS PER ASSY RF 1 2 2 5 1 3 1 2 1 2 2 1 1 1 2 5 2 1 1 2 1 1 3 1 1
23-70-02
Illustrated Parts List Rev 1 Page 1063 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
8
130
RC07GF472J
135
RC07GF474J
140
RC07GF510J
145
RC07GF561J
150
RC07GF562J
155
RC07GF821J
160
RC07GF822J
165
9–1590
170
9–1586–25
175
9–1586–26
180
9–1586–27
185
9–1586–28
–190
10282–N
–195 200
160–0021–020 93–972
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
RESISTOR, 4.7K OHM, 1/4W, 5% (V01121) (9307GF472J) RESISTOR, 470K OHM, 1/4W, 5% (V01121) (9307GF474J) RESISTOR, 51 OHM, 1/4W, 5% (V01121) (9307GF510J) RESISTOR, 560 OHM, 1/4W, 5% (V01121) (9307GF561J) RESISTOR, 5,600 OHM, 1/4W, 5% (V01121) (9307GF562J) RESISTOR, 820 OHM, 1/4W, 5% (V01121) (9307GF821J) RESISTOR, 8,200 OHM 1/4W, 5% (V01121) (9307GF822J) RESISTOR ,10K OHM POTENTIOMETER (V06141) (9391590) TRANSISTOR, 2N2483 B30–500 (V06141) (939158625) TRANSISTOR, MATCHED PAIR, NPN SI, (V06141) (939158626) TRANSISTOR, MATCHED PAIR, NPN SI, (V06141) (939158627) TRANSISTOR, NPN SI, HF, LOW POWER (V06141) (939158628) INSULATION, TRANSISTOR, NYLON (1409800028) MINI–PIN TERMINAL (9391543) BOARD, PRINTED WIRING
UNITS PER ASSY 1 1 1 2 1 1 2 1 1 10 10 1 1 1 1
– ITEM NOT ILLUSTRATED
23-70-02
Illustrated Parts List Page 1064 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
90
70
160
95
60 30
70
55
170
+ C3 -
1
F
+ C1 -
R2
R7 C4
35
+
R4
C7
+ C15
R3
25 + C6
205
R5
+
C5
200 R11
R9
165 185 215
35 180
C22 R 20
120 90 20
160
C12 R R 12 14
Q2
140 C 21 +
145
+
R 30 R R C1 32 31 6 +
+
C10 p
195
q
15 20 110 25
C
R22
35
R26
R17 C1 3
65
C20
5
Q4
R29
R 15
125
R28
L
D C1 R C1 D 2 4 19 9 D 1 + 4
+
C9 + R 13
155
R 27
K
B
5B
C8
135
80
+
R8
+ R C1 18 1 -
Q5
90
25
D 3
R10 Q6
75
10
P
R6
Q1
180
E N
C2 +
190
95
M
R1
100
GND
110 C1 R 7 R 25 + 21
R16
R 24 C1 8 +
115 200 95
Q3
t r
25
R23
85
55 45
40 130
175
105
50 90 45
150
130
90
195
85
Condenser Microphone Preamplifier PWA, P/N 93A266–01 Figure 9
23-70-02
Illustrated Parts List Rev 1 Page 1065 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 9
PART NUMBER 1
93A266–01
5
1N4446
10
1N4735,A
15 20 25 30 35 40 45 50 55 60 65
1N295 9300–285 9300–290 9300–301 9300–305 9300–307 9300–534 9300–583 CK06BX223K 3370415004 9–1588
70
9–1589
75
93–917–67
80 85
9–1889 RC07GF101J
90
RC07GF102J
95
RC07GF103J
100
RC07GF125J
105
RC07GF151J
110
RC07GF152J
115
RC07GF154J
120
RC07GF182J
125
RC07GF221J
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
MICROPHONE PRE–AMP ASSEMBLY MODIFIED (SEE FIG 7 FOR NHA) SILICON DIODE (V06141) (9300272) DIODE, ZENER IN4735 (V04713) (939032405) GERMANIUM DIODE (9300292) CAPACITOR, 4.7 UF, 35V CAPACITOR, 1.0 UF, 35V CAPACITOR, 10 UF, 20V CAPACITOR, 47 UF, 20V CAPACITOR, 4.7 UF, 20V CAPACITOR, 0.01 UF, 100V CAPACITOR, 0.22 UF, 20V CAPACITOR, (V06141) (9306BX223K) CAPACITOR, STAN, 20V, 15UF, +5% CAPACITOR, 0.022 UF 50V (V06141) (9391588) CAPACITOR, 0.0022 UF, 100V (V06141) (9391589) CAPACITOR, 150 UF, 30V (Mfg. SPRAGUE, No. 109D157X0030F2) CAPACITOR, (V06141) (9391889) RESISTOR, CC, 100 OHM, 1/4W, 5% (V01121) (9307GF101J) RESISTOR, CC, 1.0K OHM, 1/4W, 5% (V01121) (9307GF102J) RESISTOR, CC, 10.0K OHM, 1/4W, 5% (V01121) (9307GF103J) RESISTOR, CC, 1.2M OHM, 1/4W, 5% (V01121) (9307GF125J) RESISTOR, 150 OHM, 1/4W, 5% (V01121) (9307GF151J) RESISTOR, 1.5K OHM, 1/4W, 5% (V01121) (9307GF152J) RESISTOR, 0.15M OHM, 1/4W, 5% (V01121) (9307GF154J) RESISTOR, 1.8K OHM, 1/4W, 5% (V01121) (9307GF182J) RESISTOR, 220 OHM, 1/4W, 5% (V01121) (9307GF221J)
UNITS PER ASSY RF 1 1 2 2 4 1 3 1 2 1 2 1 1 2 1 1 2 5 3 1 1 2 1 1 1
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Illustrated Parts List Page 1066 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
9
130
RC07GF222J
135
RC07GF224J
140
RC07GF471J
145
RC07GF472J
150
RC07GF474J
155
RC07GF510J
160
RC07GF561J
165
RC07GF562J
170
RC07GF682J
175
RC07GF821J
180
RC07GF822J
185
9–1590
190
9–1586–25
195
9–1586–26
200
9–1586–27
205
9–1586–28
–210 215
10282–N 160–0021–020
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
RESISTOR, 2.2K OHM, 1/4W, 5% (V01121) (9307GF222J) RESISTOR, 220.0K OHM, 1/4W, 5% (V01121) (9307GF224J) RESISTOR, 470 OHM, 1/4W, 5% (V01121) (9307GF471J) RESISTOR, 4.7K OHM, 1/4W, 5% (V01121) (9307GF472J) RESISTOR, 470K OHM, 1/4W, 5% (V01121) (9307GF474J) RESISTOR, 51 OHM, 1/4W, 5% (V01121) (9307GF510J) RESISTOR, 560 OHM, 1/4W, 5% (V01121) (9307GF561J) RESISTOR, 5,600 OHM, 1/4W, 5% (V01121) (9307GF562J) RESISTOR, 6,800 OHM, 1/4W, 5% (V01121) (9307GF682J) RESISTOR, 820 OHM, 1/4W, 5% (V01121) (9307GF821J) RESISTOR, 8,200 OHM, 1/4W, 5% (V01121) (9307GF822J) RESISTOR, 10K OHM POTENTIOMETER (V06141) (9391590) TRANSISTOR, 2N2483 B30–500 (V06141) (939158625) TRANSISTOR, MATCHED PAIR, NPN SI, (V06141) (939158626) TRANSISTOR, MATCHED PAIR, NPN SI, (V06141) (939158627) TRANSISTOR, NPN SI, HF, LOW POWER (V06141) (939158628) INSULATION, TRANSISTOR, NYLON (1409800028) MINI–PIN TERMINAL (9391543)
UNITS PER ASSY 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 1 1
– ITEM NOT ILLUSTRATED
23-70-02
Illustrated Parts List Page 1067 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
25
20 15 10
5 45 55
35
70 65 30
45
50
35
60 70 40
65
55 60
30
40
Remote Microphone Assembly, P/N 93A055–00, –03, –10, –20, –30, –50, –55 Figure 10
23-70-02 Illustrated Parts List Page 1068 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 10
PART NUMBER 1
93A055–00
1A 1B 1C 1D 1E 1F 5 5A 10 15 15A 20 25 30 30A
93A055–03 93A055–10 93A055–20 93A055–30 93A055–50 93A055–55 9300–205 93–619–01 9300–197 9300–382 93–989 9300–344 9300–347 9300–348 9300–928
35
8EP44R3
35A
8EP43R3
40
9300–352
45
150949–1002
50
9–0649
55 55A 60 60A 60B 60C 60D 60E 65 65A 70
9300–334 93–624 93–626–22 93–626–23 93–626–19 93–626–20 93–626–116 93–626–117 9300–351 9300–927 8AS23R3
AIRLINE PART NO.
NOMENCLATURE 1234567
REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY REMOTE MICROPHONE ASSEMBLY REMOTE MICROPHONE ASSEMBLY REMOTE MICROPHONE ASSEMBLY REMOTE MICROPHONE ASSEMBLY REMOTE MICROPHONE ASSEMBLY MICROPHONE MICROPHONE, NON–MAGNETIC WASHER–MICROPHONE MICROPHONE MOUNT MICROPHONE MOUNT, BROWN MICROPHONE HUM SHIELD DAMPER–MICROPHONE CONNECTOR PLATE CONNECTOR PLATE ATTACHING PARTS SCREW, PAN HEAD, 4–40 X 1/4 (V06141) (938EP44R3) SCREW, PAN HEAD, 4–40 X 3/16 (V06141) (938EP43R3) PEM NUT *** CONNECTOR (9300349) ATTACHING PARTS TERMINAL LUG (V06141) (9390649) *** NAMEPLATE NAMEPLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE DUST COVER DUST COVER ATTACHING PARTS SCREW, FLAT HEAD, 2–56 X 3/16 (V06141) (938AS23R3)
EFF CODE
UNITS PER ASSY
A
RF
B C D E F G A,B C–G
A,C,E,F B,D,G
RF RF RF RF RF RF 1 1 1 1 1 1 1 1 1
A,C–G
2
B
2
A,C,E,F
2
A–D,F,G E A,B
1 1 A,B C–G A B C D,G E F A,C,E,F B,D,G
1 1 1 1 1 1 1 1 1 1 3
23-70-02 Illustrated Illustrated Parts Parts List List
Rev 2 Page Page 1069 1069 Feb. Mar. 01/93 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
5 30 15
5 20 10
35 25
45 40
Remote Microphone Assembly, P/N 93A055–40, –45, –60, –65, –66, –67, –95 Figure 11
23-70-02 Illustrated Parts List Page 1070 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 11
PART NUMBER 1
93A055–40
1A
93A055–45
1B
93A055–60
1C
93A055–65
1D
93A055–66
1E
93A055–67
1F
93A055–95
5 5A
93A272 89984
5B
93–1025
10 10A 15 20 20A
93–656 93–656 93–653 93–658–01 93–658–02
20B
93–658–03
25 30 30A 30B 30C 30D 35
93–655 93–626–83 93–626–30 93–626–100 93–626–101 93–626–115 93–654
40
8EP46R5
45
9WES4
AIRLINE PART NO.
NOMENCLATURE 1234567
REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) MICROPHONE ASSEMBLY MICROPHONE, MINI DIRECTIONAL (93959) MICROPHONE, MINI, DIRECTIONAL, EXTENDED WASHER WASHER SLEEVE–REMOTE MICROPHONE HOLDER REMOTE MICROPHONE HOLDER, REMOTE MICROPHONE (ATR–42, BROWN) HOLDER, REMOTE MICROPHONE, BLACK NAMEPLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CABLE RETAINER ATTACHING PARTS .4–40 X 3/8 PHIL.PAN HEAD.SC (V06141) (938EP46R5) LOCK WASHER, EXT CRES #4 B (V06141) (939WES4) ***
EFF CODE
UNITS PER ASSY
A
RF
B
RF
C
RF
D
RF
E
RF
F
RF
G
RF
A,B C,D,F,G
1 1
E
1
A,B C–G A,B A,C,E B,D
2 3 1 1 1
F,G
1
A B C D F
1 1 1 1 1 1 1 1 1
23-70-02 Illustrated Parts List Rev 2 Page 1071 Mar. Feb. 15/00 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
15 10
5
20
Remote Microphone Assembly, 9300A165 and 9300A165–01 Figure 12
23-70-02 Illustrated Parts List Page 1072 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 12
PART NUMBER 1
1A 5 5A 10 15 20
9300A165 9300A165–01 9300A206 93–619–01 9300–197 9300–344 9300–543
AIRLINE PART NO.
NOMENCLATURE 1234567
REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY MICROPHONE / CABLE ASSEMBLY MICROPHONE, NON–MAGNETIC WASHER–MICROPHONE MICROPHONE HUM SHIELD DAMPER–MICROPHONE
EFF CODE
UNITS PER ASSY
A
RF
B A B
RF 1 1 1 1 1
A
23-70-02 Illustrated Parts List Page 1073 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
THIS PAGE INTENTIONALLY LEFT BLANK
23-70-02 Illustrated Parts List Page 1074 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
APPENDIX A CIRCUIT AND WIRING DIAGRAMS 1. INTRODUCTION This appendix contains the wiring and schematic diagrams for the L3 Fairchild Model A100S Solid– State Cockpit Voice Recorder. Each schematic diagram is preceded by a revision reference sheet which is used as a historical record of changes to the schematic drawings. Refer to Table A1 for a listing of the schematic diagrams included in this section.
Table A1 Schematic Diagram List Assembly / Part Number
Schematic Part Number
Figure Number
Page Number
Model A100S SSCVR: System Wiring Diagram
N/A
Figure A1
Page A2
Aircraft Interface P/N 205E0597–00
905E0597–01
Figure A2
Page A7
Audio Processor P/N 205E0598–00
905E0598–01
Figure A3
Page A15
Store Processor P/N 205E0601–00
905E0601–01
Figure A4
Page A35
Store Processor P/N 205E1027–00
905E1027–01
Figure A5
Page A51
93A263–02
Figure A7
Page A66
93A266–01
Figure A8
Page A68
Control Units: Model A151 & A152 Dynamic Microphone Preamplifier PWA Model A151B & A152B Condenser Microphone Preamplifier PWA
23-70-02
Circuit and Wiring Diagrams Rev 1 Page A1 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S +5V +12V -12V REARPANEL CONNECTOR
P1 9 2 3
8 55 12 30 32
+27.5 VDC INPUT 115 VAC IN (H) AC COMMON (C)
BIAS JUMPER IN ERASE A" PUSH_TO_TEST CHANNEL 1 (LO) CHANNEL 1 (HI)
J1 9 2 3
17,18 27,29
20
22
AIRCRAFT INTERFACE PWA P/N 205E0597-00
16 25
8
23
55
26
12
24
30
37 38
32
39 35 37
41 43
45 TO FRONT PANEL PHONE JACK
47
CHANNEL 2 (LO) CHANNEL 2 (HI)
CHANNEL 3 (LO) CHANNEL 3 (HI)
CHANNEL 4 (LO) CHANNEL 4 (HI) AUDIO OUT - HI / LO
6 5
14 13
AUDIO OUT - HI AUDIO OUT - LO
PRE-AMP PWR +18VDC PRE-AMP PWR GND /BIAS JUMPER OUT
7 23 15 16 17
57
INDICATOR + INDICATOR + INDICATOR CHASSIS GROUND
ERASE C"
(+12V)
35 37
41 43
45
PWA CONNECTOR J2 HARDWIRED TO PLUG P2 OF AIRCRAFT INTERFACE CABLE ASSEMBLY W1
40 41 42 43 44 45 46
47
47
J7-1/2
48 15
6
B9, B14 A10 A9, B15
J2/P2 /LOW LINE
A8
/FAULT /RECORD ERASE TEST CHANNEL 1 (LO) CHANNEL 1 (HI) GROUND CHANNEL 2 (LO) CHANNEL 2 (HI) GROUND CHANNEL 3 (LO) CHANNEL 3 (HI) GROUND CHANNEL 4 (LO) CHANNEL 4 (HI) GROUND /SYSRST
5 35
14
36
13
1 7 23 15 16 17
57
19 E3 E4
21 28 30
COMBINED_AUDIO GROUND GROUND
A11
SPARE PWA (NOT USED)
A8
B13
B13
B12
B12
A13
A13
A12
A12
B19
B19
A19
A19
B20
B20
A20
A20
B21
B21
A21
A21
B22
B22
A22
A22
B23
B23
A23
A23
AIRCRAFT INTERFACE A24 CABLE ASSEMBLY B8 W1 CARD CONNECTOR J3 B24
B24 A24 B8
B18
B18
A18
A18
/LOW LINE /FAULT /RECORD ERASE TEST CHANNEL 1 (LO) CHANNEL 1 (HI) GROUND CHANNEL 2 (LO) CHANNEL 2 (HI) GROUND CHANNEL 3 (LO) CHANNEL 3 (HI) GROUND CHANNEL 4 (LO) CHANNEL 4 (HI) GROUND /SYSRST
COMBINED_AUDIO GROUND
B1
GROUND GROUND GROUND GROUND
B10
B10
B11
B11
A14
A14
A15
A15
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
GROUND GROUND GROUND GROUND
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
Model A100S Solid–State Cockpit Voice Recorder, P/N S100–0080–00, System Wiring Diagram Figure A1 (sheet 1 of 3)
23-70-02
Circuit and Wiring Diagrams Rev 1 Page A2 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S +5V +12V
J2/P2
-12V
B9, B14 A9, B15
/LOW_LINE
/RECORD ERASE TEST
CHANNEL 1 (HI) GROUND
CHANNEL 2 (HI) GROUND
CHANNEL 3 (HI) GROUND CHANNEL 4 (LO) CHANNEL 4 (HI) GROUND
GROUND GROUND GROUND
A13 A12 B1
A19
A20 B21
B22
A1 B2 A2 B3 A3 B4 A4 B5 A5 B6 A6
A22
B7
A21
A7
A23
B8
B24
B8
COMBINED_AUDIO
GROUND
A13
A24
/SYSRST
GROUND
B12
A21
CHANNEL 3 (LO)
GROUND
B12
B20
CHANNEL 2 (LO)
A8 B13
B19
P5 17 18
B13
A12
CHANNEL 1 (LO)
A11
AUDIO PROCESSOR PWA P/N 205E0598-00
A8
/FAULT
A10
/LOW_LINE /FAULT /RECORD ERASE TEST /REC_RD GROUND DAD 0 DAD 1 DAD 2 DAD 3 DAD 4 DAD 5 DAD 6 DAD 7 SYNC /RECFIFO_HF /REC_EMPTY /PLAY_WR /SYSRST
20
PLUG P5 PART OF CABLE ASSEMBLY W2
22
16 25 23
1 2
26
3 4
24
5
1
6
2
7
3
8
4 5 6
9 10 11
7
12
8
13 14
9 10 11
15 16 17 18 19 20
12 13 14
AIRCRAFT INTERFACE CABLE ASSEMBLY W1 CARD CONNECTOR J5 (26 PIN)
15
21 22 23 24 25 26
/REC_RD GROUND
AIRCRAFT INTERFACE CABLE B10 ASSEMBLY B11 W1 CARD A14 CONNECTOR A15 J4 (64 PIN) A24
DAD 1 DAD 2 DAD 3 DAD 4 DAD 5 DAD 6 DAD 7 SYNC /RECFIFO_HF /REC_EMPTY /PLAY_WR /SYSRST /LOW_LINE +5V +5V GROUND +12V GROUND -12V /RECORD TEST /FAULT ERASE
RIBBON CABLE ASSEMBLY W2 IS HARD WIRED TO STORE PROCESSOR PWA)
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
(SEE NOTE AT BOTTOM OF PAGE)
DAD 0
B18 A18
STORE PROCESSOR PWA P/N 205E0601-00 MOUNTED ONTO FCSSU
NOTE REFER TO SHEET 3 FOR STORE PROCESSOR PWA, P/N 205E1027-00 WIRING TO FCSSU, 253E0660-00
18 48
18 48
17
17
47 16
47 16
19
19
20 45 46 49 50 23 10
20 45 46 49 50 23 10
7
7
22 13
22 13
21 11 9 32 33 37 39 41 42
21 11 9 32 33 37 39 41 42
43 44
43 44
14
14
31 2 34 30 1
31 2 34 30 1
5 8
5 8
6 35
6 35
28 36
28 36
38
38
40 15
40 15
29 27 12 26
29 27 12 26
25 24 3
25 24 3
4
4
+5V +5V +12V +12V GND GND GND GND GND GND GND D<0> D<1> D<2> D<3> D<4> D<5> D<6> D<7> SEL<0> SEL<1> SEL<2> SEL<3> SEL<4> SEL<5>
FCSSU P/N 253E0348-03 (SEE NOTE AT BOTTOM OF PAGE)
SEL<6> SEL<7> FADR<20> FADR<19> FADR<18> FADR<17> FADR<16> FADR<15> FADR<14> FADR<13> FADR<12> FADR<11> FADR<10> FADR<9> FADR<8> FADR<7> FADR<6> FADR<5> FADR<4> FADR<3> FADR<2> FADR<1> FADR<0> /OE /WE
NOTE INITIAL MODEL A100S UNITS WERE EQUIPPED WITH FCSSU, P/N 253E0348-03, WHICH USES 2-MBIT FLASH MEMORY CHIPS, AND STORE PROCESSOR PWA, P/N 205E0601-00, DEĆ SIGNED TO INTERFACE WITH IT. BEGINNING 12/93, THE NEW FCSSU, P/N 253E0660-00, WHICH USES 8-MBIT FLASH MEMORY CHIPS, AND A REDESIGNED STORE PROCESSOR PWA, P/N 205E1027-00, WERE MANUFACĆ TURED. THESE ASSEMBLIES WERE FIRST INSTALLED IN MODĆ EL A100S UNIT SERIAL NUMBER 311.
Model A100S Solid–State Cockpit Voice Recorder, P/N S100–0080–00, System Wiring Diagram Figure A1 (sheet 2 of 3)
23-70-02
Circuit and Wiring Diagrams Rev 1 Page A3 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S +5V +12V
J2/P2
-12V
STORE PROCESSOR PWA P/N 205E1027-00
P5 17 18
/LOW_LINE /FAULT /RECORD ERASE TEST /REC_RD GROUND DAD 0 DAD 1 DAD 2 DAD 3 DAD 4 DAD 5 DAD 6 DAD 7 SYNC /RECFIFO_HF /REC_EMPTY /PLAY_WR /SYSRST
20
PLUG P5 PART OF CABLE ASSEMBLY W2
22
16 25 23
1 2
26
3 4
24
5
1
6
2
7
3
8
4
9 10
5 6
11
7
12
8
13 14 15
9 10
16 17 18 19 20
11 12 13 14
AIRCRAFT INTERFACE CABLE ASSEMBLY W1 CARD CONNECTOR J5 (26 PIN)
15
21 22 23 24 25 26
MOUNTED ONTO FCSSU (SEE NOTE AT BOTTOM OF PAGE)
/REC_RD GROUND DAD 0 DAD 1 DAD 2 DAD 3 DAD 4 DAD 5 DAD 6 DAD 7 SYNC /RECFIFO_HF /REC_EMPTY /PLAY_WR /SYSRST /LOW_LINE +5V +5V GROUND +12V GROUND -12V /RECORD TEST /FAULT ERASE
RIBBON CABLE ASSEMBLY W2 IS HARD WIRED TO STORE PROCESSOR PWA)
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
18 48
18 48
17 47 16
17 47 16
19
19
20
20
45 46 49 50 23 10
45 46 49 50 23 10
7 22 13
7 22 13
21 11 9 32 33 37 39 41 42
21 11 9 32 33 37 39 41 42
43 44 14
43 44 14
31 2 34 30 1
31 2 34 30 1
5 8 6 35
5 8
28 36 38
28 36
40 15
40 15
29
29 27 12 26
27 12 26 25 24 3 4
6 35
38
25 24 3 4
+5V +5V +12V +12V GND GND GND GND GND GND GND D<0>
FCSSU P/N 253E0660-00
D<1> D<2> D<3> D<4> D<5> D<6> D<7> FADR<21> FADR<22> FADR<23> FADR<24> FADR<25> FADR<26> /CE_FLASH /PWRDWN
(SEE NOTE AT BOTTOM OF PAGE)
NOTE SIGNAL CHANGES
FADR<20> FADR<19> FADR<18> FADR<17> FADR<16> FADR<15> FADR<14> FADR<13> FADR<12> FADR<11> FADR<10> FADR<9> FADR<8> FADR<7> FADR<6> FADR<5> FADR<4> FADR<3> FADR<2> FADR<1> FADR<0> /OE /WE
SIGNAL MNEMONIC CHANGES BETWEEN STORE PROCESSOR PWA, P/N 205E1027-00, AND FCSSU, P/N 253E0660-00
NOTE THE ABOVE REFLECTS THE NEW FCSSU, P/N 253E0660- 00, WHICH USES 8-MBIT FLASH MEMORY CHIPS, AND STORE PROCESSOR PWA, P/N 205E1027-00 MANUFACTURED BEGINĆ NING 12/93. THESE ASSEMBLIES WERE FIRST INSTALLED IN UNIT SERIAL NUMBER 311.
Model A100S Solid–State Cockpit Voice Recorder, P/N S100–0080–00, System Wiring Diagram Figure A1 (sheet 3 of 3)
23-70-02
Circuit and Wiring Diagrams Rev 1 Page A4 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code Rev. 02 Rev. 02 Rev. 02
Serial Number Effectivity
Revision Description Replaced U3 and added U5 per ECO 7977. Replaced U2 per SB SSCVR012 Removed C16 and C17, added L1-L3 and C35-C38 per SB SSCVR011.
00761 and above.
Revision Reference Sheet for Figure A2 Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram, P/N 905E0597–01 (Sheets 1 through 4)
23–70–02
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
REVISIONS SYM.
A B C
DESCRIPTION
ECO 0006293 CHNG SHT 2 ECO 0007977 CHNG SHT 1 ECO 0008291 CHNG SHTS 1,2
EFFECTIVITY
DATE
APPROVED
9–04–91 9–14–91 3–29–95 4–02–95 3–06–96 7–02–96
REV. 02
Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram, P/N 905E0597–01 Figure A2 (sheet 1 of 4)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
REV. 02
REV. 02
Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram, P/N 905E0597–01 Figure A2 (sheet 2 of 4)
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Circuit and Wiring Diagrams Rev 2 Page A8 Mar. 01/93 15/00 Feb.
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram, P/N 905E0597–01 Figure A2 (sheet 2 of 4 continued)
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Circuit and Wiring Diagrams Page A9 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram, P/N 905E0597–01 Figure A2 (sheet 3 of 4)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram, P/N 905E0597–01 Figure A2 (sheet 3 of 4 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram, P/N 905E0597–01 Figure A2 (sheet 4 of 4)
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Circuit and Wiring Diagrams Page A12 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code Rev. 02
Revision Description
Serial Number Effectivity
Replaced C15, C24, C25, C28, C30, C32, and C47 per ECO 9282.
Revision Reference Sheet for Figure A3 Audio Processor, P/N 205E0598–00, Schematic Diagram, P/N 905E0598–01, (Sheets 1 through 11)
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Circuit Circuit and and Wiring Wiring Diagrams Diagrams Rev 2 Page Page A13 A13 Mar. Feb. 15/00 01/93
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
A
ECO 0006215: UPDATE SHTS 1,3,4
7/26/91
7/26/91
B
ECO 0006919: UPDATE SHTS 1,4
7/12/91
9/26/91
C
ECO 0006445: REV SHTS 1,5,6; ADD NOTE 5
D
ECO 0009282: REV SHTS 5,6,8,9
11/6/91 8/24/00
11/8/91 8/28/00
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 1 of 11)
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Circuit and Wiring Diagrams Page A15 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 2 of 11)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 2 of 11 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 3 of 11)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NC
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 3 of 11 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 4 of 11)
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Circuit and Wiring Diagrams Page A20 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 4 of 11 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
0.1 REV. 02
0.1 REV. 02
0.1 REV. 02
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 5 of 11)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 5 of 11 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
0.1
REV. 02
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 6 of 11)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 7 of 11)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 8 of 11)
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0.1 REV. 02
0.1 REV. 02
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 8 of 11 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 9 of 11)
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0.1 REV. 02
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 9 of 11 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 10 of 11)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 10 of 11 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 11 of 11)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
COMBINED_AUDIO AUDIO_1 AUDIO_2
PLAYBACK MONITOR CONNECTOR
AUDIO_3 AUDIO_4
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 11 of 11 continued)
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Circuit and Wiring Diagrams Page A33 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code
Revision Description
Serial Number Effectivity
Revision Reference Sheet for Figure A4 Store Processor, P/N 205E0601–XX, Schematic Diagram P/N 905E0601–01 (Sheets 1 through 8)
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Circuit and Wiring Diagrams Rev 1 Page A34 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
D E F
75 9 71 1 9
762 8
&2 3 & 8 3 &8 & 8
3 6 1 3
12 02 29 11
2 2 3 4
3 6 2 3
25 26 25 28
2 2 3 4
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 1 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
VCC
REVISION C INCORPORATED PER ECO 0006654 WITH AN EFFECTIVITY DATE OF 3-12-92 REPLACED THE ABOVE BLOCKED CIRCUITRY WITH THE DC/DC CONVERTER POWER SUPPLY (5 VDC IN / - 12 VDC OUT AT 83 MA, 1W) SHOWN HERE.
VIN N/C
NMF0512S
CTRL
GND
+OUT -OUT
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 2 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 2 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
LSB
LSB
MSB MSB
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 3 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
MSB
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 3 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 4 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 4 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 5 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 5 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 6 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
MSB LSB
FCT841 MSB
LSB LSB
D9 D8 D7 D6 D5 D4 D3 D2 D1 D0 LE
Y9 Y8 Y7 Y6 Y5 Y4 Y3 Y2 Y1 Y0
MSB
LSB
OE
REV. F
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 6 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E0601–01, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 7 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E0601–01, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 7 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E0601–01, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 8 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code
Revision Description
Serial Number Effectivity
Revision Reference Sheet for Figure A5 Store Processor, P/N 205E1027–XX, Schematic Diagram, P/N 905E1027–01 (Sheets 1 through 8)
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Circuit and Wiring Diagrams Rev 1 Page A50 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
7628
CHG U12 ON SHT 6
3 /11 / 94
3 / 25 / 94
0
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 1 of 8)
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Circuit and Wiring Diagrams Rev 1 Page A51 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
VCC
VIN N/C
NMF0512S
CTRL
GND
+OUT -OUT
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 2 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 2 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
LSB
LSB
MSB MSB
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 3 of 8)
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Circuit and Wiring Diagrams Rev 1 Page A54 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
J2 43
MSB
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 3 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 4 of 8)
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Circuit and Wiring Diagrams Rev 1 Page A56 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 4 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 5 of 8)
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Circuit and Wiring Diagrams Rev 1 Page A58 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 5 of 8 continued)
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Circuit and Wiring Diagrams Rev 1 Page A59 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 6 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
MSB LSB
FCT841 MSB
LSB
D9 D8 D7 D6 D5 D4 D3 D2 D1 D0 LE
Y9 Y8 Y7 Y6 Y5 Y4 Y3 Y2 Y1 Y0
MSB
LSB
OE
REV. A
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 6 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 7 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 7 of 8 continued)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
/PWRDWN FADR<24> FADR<23>
FADR<22> FADR<21> FADR<20> FADR<19> FADR<18> FADR<17> FADR<16> FADR<15> FADR<26> FADR<25>
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 8 of 8)
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Circuit and Wiring Diagrams Rev 1 Page A64 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code
Revision Description
Serial Number Effectivity
Revision Reference Sheet for Figure A6 Dynamic Microphone Preamplifier, P/N 93A263–01, Schematic Diagram (Sheet 1 of 1)
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Circuit and Wiring Diagrams Page A65 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
R6 1.0K
R3 150 C1 N 1.0 35V C2 .01 200V
C3
C8 47 20V
R5 10K
+
+
+
560 10 C4 20V .01 R1 200V 2.2K
3
Q1 2N2483
1
R12 R8 10.0K
C9
+
2
R11 C10 .01 200V
R9 5.6K
+ C5 60 6V
R4 1.0K
R13
R7 8.2K
C7
1.0 35V
R2
D1 1N4446
R27
C (B+ 18V)
100 C13 47 20V
R23 10K
C11
R16
4.7 20V Q2
1K
2.2K
R15 2.2K
R17 820
6 p DS
12 DS
R14 470
C12 +
R18
r
q
R19 150 t
24 DS C14. .01 200V
R24 150K
R21 470 R20 1.0K
Q4
C15 1.0 35V
C16 4.7 35V +
Q3 R22 100
R26
L (OUT)
220 R25
C17 .022 200V
P C18 C22 .033 200V
M
R30 8.2K Q6
D3
R29
+
Q5
1.0K
C21 47 20V
5B
CHASSIS
NOTES: 1. UNLESS OTHERWISE SPECIFIED: RESISTOR VALUES ARE IN OHMS, 1/4 WATT, 5% CAPACITOR VALUES ARE IN MICROFARADS. 2. Q2 AND Q3 - P/N 939158626 3. Q4 AND Q5 - P/N 939158627 4. Q6 - P/N 939158628
C20 4.7 35V
R28
1.0 35V
1.5K
+
1N295 +
C19
K (OUT) B (B- 18V)
D2 1N295 CHASSIS
P/N 93A263-01
Dynamic Microphone Preamplifier, P/N 93A263–01, Schematic Diagram Figure A6
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Circuit and Wiring Diagrams Page A66 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code
Revision Description
Serial Number Effectivity
Revision Reference Sheet for Figure A7 Dynamic Microphone Preamplifier, P/N 93A263–02, Schematic Diagram (Sheet 1 of 1)
23-70-02
Circuit and Wiring Diagrams Page A67 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
R5 1.0K
R16 100
51
C22 + 47 20V
R6 10.0K R3 1.2M
N
C2 +
C15 + 1.0 35V
10 20V
C1 0.01 100V
R2 2.2K
R14 4.7K
R8 8.2K
C5 + 47 20V C6 +
3 R9 10.0K
2
1
C9 +
R13
1.0 35V
560 + C10 0.01 100V
R11 5.6K
R7 1.0K
4.7 20V Q2 9-1586 -26
R17
R29
1.0K
2.2K
+ C16 0.22 20V
R30 2.2K
R32 820
R31 150
p
r
t
6DB
R15 470
R21 10.0K
C12 47 20V
C13 +
220K
Q1 9-1586 -25
560 C4 0.01 100V
+
R12
1.0 35V
R4
D4 1N4446
R27
12DB
R23 470K R24 1.0K
q
R22 150K
+ C17 1.0 35V
Q4 9-1586 -27
Q3 9-1586 -26 C18 0.01 100V
24DB
R25 100
R26 1.5K
C19 +
R28
4.7 35V
220
L
(OUT)
K
P +
M
C
(B+ 18V)
C3 CK06BX223K
Q6 9-1586 -28
(OUT)
C7 15 20V
B
(B- 18V)
R10 8.2K
CHASSIS
+
R18
Q5 9-1586 -27 C8 150 30V
C20 0.022 50V
D1 1N295
+
1.0K +
5B
C11 4.7 35V
D2 1N295
C14 1.0 35V
R19 C21
1.5K
CK06BX223K
CHASSIS
NOTES: UNLESS OTHERWISE SPECIFIED: RESISTOR VALUES ARE IN OHMS, 1/4 WATT, 5% CAPACITOR VALUES ARE IN MICROFARADS.
Dynamic Microphone Preamplifier, P/N 93A263–02, Schematic Diagram Figure A7
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Circuit and Wiring Diagrams Rev 1 Page A68 July 01/93 30/94 Feb.
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code
Revision Description
Serial Number Effectivity
Revision Reference Sheet for Figure A8 Condenser Microphone Preamplifier, P/N 93A266–01, Schematic Diagram (Sheet 1 of 1)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
R20
P
1.8K
6.2V OUT
+
C15
D3 1N4735A
E
+ R6 10.0K + C6 1.0 Q1 35V 9-158625 + C5
R3 1.2M
N
R1 6.8K C1 0.0022 100V
C2 10.0 + 20V R2 10.0K
R4 560 C4 0.0022 100V R7 1.0K
+ C7
R27 51
R16 100
R5 1.0K
R8 8.2K
2 1
47 20V
C9 + 1.0 35V R11 5.6K
220.0K R13 560 C10 0.01 100V
+
R29 2.2K
R32 820
p
R15 470
15 20V
R21 10.0K R17 1.0K
Q2 9-1586 R30 -26 2.2K
C
(B+ 18V)
C12 47 20V
C13 4.7 20V +
R12 3
R9 10K
+
R14 4.7K
C22 47 20V
D4 1N4446
q
C16 +
R23 470K
0.22 20V
R24 1.0K
R31 150
r
t
C18 0.01 100V
+ R25 100
R22 150K C17 +
Q4 1.0 9-1586-27 35V Q3 R28 9-1586-26 C19 220 + R26 1.5K
L (OUT)
4.7 35V C20 0.022 50V
K
M
(OUT) C3
F
C21
R10 8.2K
R18 1.0K
Q5 9-1586-27
Q6
1N295
9-1586-28 CHASSIS
C8 150 30V
D1
+
5B
C11 4.7 35V
+
D2 1N295
+ C14 1.0 35V
+
R19 1.5K
CHASSIS
NOTES: UNLESS OTHERWISE SPECIFIED: RESISTOR VALUES ARE IN OHMS, 1/4 WATT, 5% CAPACITOR VALUES ARE IN MICROFARADS.
Condenser Microphone Preamplifier PWA, P/N 93A266–01 Schematic Diagram Figure A8
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Circuit and Wiring Diagrams Rev 1 Page A70 July 01/93 30/94 Feb.
B (B- 18V)
SOLID–STATE COCKPIT VOICE RECORDER (SSCVR) MODEL A100S SSCVR CONTROL UNITS MODELS A150, A151, A152, A151B, A152B SSCVR MICROPHONE MODULES MODELS A55, A55B
RECORDER PART NUMBER
S100–0080– ( )
CONTROL UNIT PART NUMBERS
93A151– ( ) 93A152– ( )
PREAMPLIFIER MODULE
93A150–20
REMOTE MICROPHONE MODULES PART NUMBERS
93A055– ( )
REMOTE MICROPHONE MODULES PART NUMBERS
9300A165, –01
COMPONENT MAINTENANCE MANUAL WITH ILLUSTRATED PARTS LIST P/N: 165E0948–00
IN ACCORDANCE WITH FAA TSO–C84 (CONTROL UNITS, PREAMPS & MICS) FAA TSO–C123 (RECORDER) AND ARINC CHARACTERISTIC NO. 557
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Solid–State Cockpit Voice Recorder (SSCVR) Control Boxes Microphones P/N: 165E0948–00 Rev 03 Jul. 01/05
EXPORT CONTROL STATEMENT SSCVR/SSFDR Parts: “This Solid State Fight Data/Cockpit Voice Recorder Products/ Technology is being exported from the United States in accordance with the Export Administration Regualtions (ECCN #7E994), No License Required (NLR). Diversion contrary to U.S. law is prohibited. In accordance with U.S. Law (Title 15 CFR Part 746 and Supplement No. 1 to Part 774; and Title 31 CFR) resale/reexport or transfer to certain designated countries is prohibited without the prior written consent of the U.S. Department of Commerce.”
ECopyright 2005 by L–3 Communications All rights reserved. No part of this manual may be reproduced or utilized in any form or by any means, electronic or mechanical, including photocopying, recording, or by information storage and retrieval system, without permission in writing. Inquiries should be addressed to: L–3 Communications Aviation Recorders Publications P. O. Box 3041 Sarasota, Florida 34230 Phone: (941) 371–0811 FAX: (941) 377–5591
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
THE CONTENTS OF THE RECORDER CAN BE DAMAGED BY ELECTROSTATIC DISCHARGE. PROPER HANDLING MUST BE USED! GENERAL This product and related documentation must be reviewed for familiarization with safety markings and instructions before operation. This instrument was constructed in an ESD (electrostatic discharge) protected environment. This is because most of the semiconductor devices used in this instrument are susceptible to damage by static discharge. Depending on the magnitude of the charge, device substrates can be punctured or destroyed by contact or mere proximity of a static charge. The results can cause degradation of device performance, early failure, or immediate destruction. These charges are generated in numerous ways such as simple contact, separation of materials, and normal motions of persons working with static sensitive devices. When handling or servicing equipment containing static sensitive devices, adequate precautions must be taken to prevent device damage or destruction. Only those who are thoroughly familiar with industry accepted techniques for handling static sensitive devices should attempt to service circuitry within these devices. In all instances, measures must be taken to prevent static charge build–up on work surfaces and persons handling the devices.
BEFORE APPLYING POWER Verify that the product is set to match the available line voltage and the correct fuse is installed. Servicing instructions are for use by service–trained personnel only. To avoid dangerous electric shock, do not perform any servicing unless qualified to do so. Adjustments described in the manual are performed with power supplied to the instrument while protective covers are removed. Energy available at many points may, if contacted, result in personal injury.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SERVICE BULLETIN LIST SERVICE BULLETIN SSCVR001
DATE 09/01/93
INCORPORATES S100–0080–00
DESCRIPTION Software Product Improvement Modification Commencing with Unit Serial Number 254, manufactured 7/93, all newly manufactured A100S SSCVR units will have this modification. This modification is a product improvement, which requires a software revision to IC chip U5 located on the Store Processor PWA. It expands the SSCVR BITE circuitry from “READ–AFTER–WRITE” to include a Continuous Test of all bits within the solid– state memory. Failure of this Continuous Test would be indicated upon execution of the next Preflight Functional Check. This modification is optional. Note: This modification is identified by marking, using yellow paint, R1 on the unit Program Revision Plate.
SSCVR002
11/15/93
S100–0080–00
Alternate Supplier For Underwater Locator Beacons (ULDs) L3 approved Datasonics, Inc. as an alternate supplier of ULDs. Both Dukane and Datasonics ULDs are being installed on newly manufactured A100S recorders. Both ULD types are assigned the same L3 Part Number, 266E0305–00. Also, both ULD types are equipped with a Lithium battery with an expected service life of 6–years.
SSCVR003
02/23/94
S100–0080–00
Introduction Of The 8–Megabit Flash Crash Survivable Store Unit (FCSSU) and The New Type Store Processor PWA The new 8–Megabit FCSSU (P/N 253E0660–00) and Store Processor PWA (P/N 205E1027–00) have been phased into the production of the A100S SSCVR beginning with unit serial number 311, manufactured 12/93. It is not mandatory for an older SSCVR with a 2–Megabit FCSSU (P/N 253E0348– 03) and Store Processor PWA (P/N 205E0601–00) to incorporate this modification. However, should a failure occur in the older FCSSU, it must be replaced with the 8–Megabit FCSSU along with its associated Store Processor PWA. Note: This modification is identified by marking, using yellow paint, a 1 on the SSCVR Modification Plate (Mod Dot 1) and R2 on the Program Revision Plate.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SERVICE BULLETIN LIST (Continued) SERVICE BULLETIN SSCVR004
DATE 06/21/94
INCORPORATES S100–0080–00
DESCRIPTION Notification of Defective Printed Wiring Board (PWB) In Certain Flash Crash Survivable Store Units (FCSSUs) Some 8–Megabit FCSSUs (P/N 253E0660–00) in the A100S SSCVR units (identified with Mod Dot 1) may fail due to a defective PWB furnished by a specific supplier. Beginning June 17, 1994, FCSSUs will be manufactured with PWBs supplied by selected vendors. A100S SSCVR units, beginning with serial number 00452, will have the new FCSSU installed; these units will be identified by a 3 on the SSCVR Modification Plate (Mod Dot 3). It is not recommended to retrofit an SSCVR containing a Mod Dot 1 FCSSU unless it fails. Note: Modification Dot 2 has been reserved by Engineering for a later release.
SSCVR005
03/17/95
S100–0080–00
Introduction of New Flash Crash Survivable Store Unit (FCSSU) Commencing with Unit Serial Number 00622, manufactured 11/94, all newly manufactured A100S SSCVR units will have this modification. To reduce the possibility of certain premature failures and enhance reliability, FCSSU assemblies have had modifications to the Printed Wiring Board (PWB) and to the thermal insulation material. This modification is not mandatory and is not recommended to change the current FCSSU assembly unless a FCSSU related failure occurs. Note: This modification is identified by marking, using yellow paint, a 4 on the SSCVR Modification Plate (Mod Dot 4).
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SERVICE BULLETIN LIST (Continued) SERVICE BULLETIN SSCVR006
DATE 06/15/96
INCORPORATES S100–0080–00
DESCRIPTION Introduction of 1–Hr. Fire Protection Flash Crash Survivable Store Unit (FCSSU) All A100S SSCVRs manufactured after 03/96 will have this modification. New FCSSU part numbers 253E1290–00 and 253E1293–00 have been designed to survive 1–hour fire at 1100 degrees Centigrade with a 50,000 British Thermal Units (BTUs) square foot hours thermal flux transfer, and 10 hours at 260 degrees Centigrade. Note: This modification is identified by marking, using yellow paint, a 5 on the SSCVR Modification Plate (Mod Dot 5).
SSCVR007
03/28/95
S100–0080–00
New Software Incorporated into Store Processor Printed Wiring Assembly Commencing with Unit Serial Number 00651, all newly manufactured A100S SSCVR units will have this modification. This modification prohibits the SSCVR from giving a false fault during rapid power cycling. This modification also ensures that all data is erased during a bulk erase. This modification is not mandatory and may be accomplished at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 3 on the Software Program Revision Plate.
SSCVR008
06/10/96
S100–0080–00
New Software Incorporated into Store Processor Printed Wiring Assembly Commencing with Unit Serial Number 00961, all newly manufactured A100S SSCVR units will have this modification. This modification ensures that the fault light is illuminated during a power recovery bulk erase cycle. This modification is not mandatory and may be accomplished at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 4 on the Software Program Revision Plate.
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SERVICE BULLETIN LIST (Continued) SERVICE BULLETIN SSCVR009
DATE 07/01/96
INCORPORATES S100–0080–00
DESCRIPTION Introduction of Titanium Flash Crash Survivable Store Unit (FCSSU) All A100S SSCVRs manufactured after 04/96 will have this modification. New FCSSU part number 253E1293–00 reduces the weight of the FCSSU This modification is a product improvement and may be incorporated at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 2 on the SSCVR Modification Plate (Mod Dot 2).
SSCVR010
04/04/96
S100–0080–00
Introduction of a New Underwater Locator Beacon All A100S SSCVRs manufactured after 03/96 will have this modification. New Dukane Underwater Locator Beacon, p/n: DK120, maintains a six–year battery life and can be replaced in the field. Note: Beacons DK100 and DK120 can be identified by Dukane with these part numbers stamped on the beacon’s body.
SSCVR011
07/01/96
S100–0080–00
Addition of EMI Filter Circuit to Aircraft Interface Card All A100S SSCVRs manufactured after 03/96 will have this modification. Enhanced Electo–magnetic Interference filter characteristics by adding filter circuit consisting of L1–L3, and C35–C38 to the Aircraft Interface circuit board, p/n: 205E0597–00. Removed old capacitors C16 & C17 (p/n: 361–01–0001) from Aircraft Interface board. This modification is a product improvement and not a required modification, however it is recommended that this modification be incorporated at the unit’s next scheduled service visit. Note: This modification is identified by marking, using yellow paint, a 6 on the SSCVR Modification Plate (Mod Dot 6).
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SERVICE BULLETIN LIST (Continued) SERVICE BULLETIN SSCVR012
DATE 07/02/96
INCORPORATES S100–0080–00
DESCRIPTION Replaced Power Supply, U2, on Aircraft Interface Card
All A100S SSCVRs manufactured after 06/96 will have this modification. Replacement of power supply to enhance reliability. This modification is a product improvement and may be incorporated at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 7 on the SSCVR Modification Plate (Mod Dot 7). SSCVR013
06/15/96
S100–0080–00
New Software Program Incorporated into Store Processor Printed Wiring Assembly Beginning with serial number 1142, all newly manufactured A100S SSCVRs will have this modification. Added software logic for improved handling of SSCVR power down and restart conditions during excessive power interrupts. This modification is not a mandatory change and may be incorporated at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 5 on the Software Program Revision Plate.
SSCVR014 Rev. 01
07/01/97 02/07/97
S100–0080–00
New Software Program Incorporated into Store Processor Printed Wiring Assembly Beginning with serial number 1168, all newly manufactured A100S SSCVRs will have this modification. Enhanced Read–After–Write Reset and unit identification functions. Corrects occasional misidentification of an 8 Meg memory unit as a 2 Meg unit during power interupt conditions. Introduced a procedure for clearing Latched “Memory” faults and Latched “Pointer Not Saved” faults. This modification is not a required modification, and may be accomplished at the discretion of the operator. Note: This modification is identified by marking, using yellow paint, a 6 on the Software Program Revision Plate.
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SERVICE BULLETIN LIST (Continued) SERVICE BULLETIN SSCVR015
DATE 10/01/96
INCORPORATES S100–0080–00
DESCRIPTION Modification to Store Processor Card
All A100S SSCVRs manufactured after 09/96 will have this modification. Modified Store Processor card, p/n: 205E1027–00 to reduce noise levels on the flash memory bus. Redesigned Store Processor by removing components C7 & C13, changing U4 and R10, and adding R18 and R19. Replacement of power supply to enhance reliability. This modification is a product improvement and not a required modification, however it is recommended that this modification be incorporated at the unit’s next scheduled service visit. Note: This modification is identified by marking, using yellow paint, a 8 on the SSCVR Modification Plate (Mod Dot 8).
SSCVR016
04/18/97
S100–0080–00 Only Units with Mod 5 Installed
Introduction of Refurbished FCSSU (253U1290–00) S100–0080–00 A100S SSCVRs (containing MOD5) manufactured after 09/96 will have this modification. FCSSU part number 253U1290–00 has been assigned to identify refurbished memory modules as an alternate replacement for P/N’s 253E1290–00.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
RECORD OF REVISIONS REV NO.
INSERTION DATE
BY
1
July 30/94
CM
2
Mar. 15/00
JG
3
Jul. 01/05
JG
REV NO.
INSERTION DATE
BY
REV NO
INSERTION DATE
BY
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RECORD OF CHANGES ISSUE Initial
REVISION
DATE OF CHANGE
COMMENTS
00
Feb. 1/93
Initial issue of CMM. No changes have been issued via Service Bulletins (SB’s).
01
July 30/94
This revision includes information presented in SB’s: SSCVR 001, 002, 003 and 004. It also includes the deletion of all information given for the Audio Processor Extender PWA and the Model S151 and S251 Control Units including their respective IPL figures and listings. In addition, miscellaneous changes, updates and corrections were made to text wherever necessary.
02
Mar. 15/00
This revision includes information presented in SB’s: SSCVR 005, 006, 007, 008, 009, 010, 011, 012, 013, 014, 015, 016, and ECO 9282. Removed “Fairchild” from the mast– head. Moved Store Processor PWA to NHA. Updated ULD information. Corrected numerous errors in Numerical Index. Includes the addition of S100–0080–01 model configuration for titanium FCSSU assembly.
03
Jul. 01/05
This revision includes the addition of testing procedures for the Model A150 External Preamplifier. Updated ULD information.
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LIST OF EFFECTIVE PAGES Section
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Caution Sheet
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Service Bulletin List
Record of Revisions
Record of Changes
List of Effective Pages 1 2 3 4 5 6
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Table of Contents
List of Illustrations
Introduction
Section
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Description and Operation 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
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Section
Description and Operation (Con’t) 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48
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Testing and Troubleshooting 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124
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Disassembly
Cleaning
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Checks 501 502
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Repair
Assembly
Special Tools, Fixtures and Equipment 901 902 903 904
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Illustrated Parts List 1001 1002 1003 1004 1005 1006 1007 1008 1009 1010 1011 1012 1013 1014
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Page 1015 1016 1017 1018 1019 1020 1021 1022 1023 1024 1025 1026 1027 1028 1029 1030 1031 1032 1033 1034 1035 1036 1037 1038 1039 1040 1041 1042 1043 1044 1045 1046 1047 1048 1049 1050 1051 1052 1053 1054
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Illustrated Parts List (Con’t) 1055 1056 1057 1058 1059 1060 1061 1062 1063 1064 1065 1066 1067 1068 1069 1070 1071 1072 1073 1074
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Appendix A Circuit and Wiring Diagrams A1 A2 A3 A4 A5 A6 A7 A8 A9 A10 A11 A12 A13 A14 A15 A16 A17 A18
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A19 A20 A21 A22 A23 A24 A25 A26 A27 A28 A29 A30 A31 A32 A33 A34 A35 A36 A37 A38 A39 A40 A41 A42 A43 A44 A45 A46 A47 A48 A49 A50 A51 A52 A53 A54 A55 A56 A57 A58 A59 A60
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Appendix A Circuit and Wiring Diagrams (Con’t) A61 A62 A63 A64
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A65 A66 A67 A68 A69 A70
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TABLE OF CONTENTS SUBJECT/DESCRIPTION
PAGE INTRODUCTION
1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
2. COMPONENT MAINTENANCE MANUAL (CMM) DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . .
2
A. Frontis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
B. Description And Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
C. Testing And Fault Isolation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
D. Disassembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
E. Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
F.
Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
G. Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
H. Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
I.
Special Tools and Test Fixtures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
J.
Illustrated Parts List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
K. Circuit and Wiring Diagrams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
3. DOCUMENT VERIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
4. RECORDER MODIFICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
5. CONTROL UNIT MODIFICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
DESCRIPTION AND OPERATION 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
2. SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
3. SPECIFICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
A. APPLICABLE DOCUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
B. PHYSICAL CHARACTERISTICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
C. ELECTRICAL CHARACTERISTICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
D. ENVIRONMENTAL CHARACTERISTICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
4. TECHNICAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5
A. SYSTEM OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5
B. DATA MONITORING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
C. STORAGE CAPACITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
D. DATA RETRIEVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
E. DATA REPRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
F.
7
BUILT–IN–TEST–EQUIPMENT (BITE) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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PAGE
G. FLASH CRASH SURVIVABLE STORE UNIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
H. CRASH AND FIRE PROTECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8
5. SUPPORT EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8
A. MODEL A860 COCKPIT VOICE RECORDER SYSTEM TEST PANEL . . . . . . . . . . . . . . .
8
B. MODEL A870 CALIBRATED SOUND SOURCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9
C. AUDIO MONITOR ADAPTER (AMA/1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9
6. PERIPHERAL EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10
A. CONTROL UNIT, MODEL A152B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
11
B. CONTROL UNIT, MODEL A151B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
11
C. MICROPHONE MODULES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
13
7. INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
15
A. Control Unit Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
15
B. Remote Microphone Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
15
8. THEORY OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
29
A. SYSTEM THEORY OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
29
(1) Aircraft Interface PWA, P/N 205E0597–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (2) Audio Processor PWA, P/N 205E0598–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (3) Store Processor PWA, P/N 205E0601–00, 205E1027–00 . . . . . . . . . . . . . . . . . . . . . . (4) Flash Crash Survivable Store Unit (FCSSU), P/N 253E0348–00, 253E0660–00 . . B. PWA THEORY OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
29 29 29 30 31
(1) (2) (3) (4)
Aircraft Interface PWA, P/N 205E0597–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Audio Processor PWA; P/N 205E0598–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Store Processor PWA; P/N 205E0601–00, 205E1027–00 . . . . . . . . . . . . . . . . . . . . . . Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
31 33 41 45
TESTING AND TROUBLESHOOTING 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
101
2. A100S RECORDER TESTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
101
3. MODEL A100S OPERATIONAL TEST PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
101
4. CONTROL UNIT, MODEL A151/A151B & A152/A152B TEST PROCEDURES . . . . . . . . . . . .
110
5. CONTROL UNIT, MODEL A151 & A152 WITH MODIFICATION 4 TEST PROCEDURES . .
114
A. FREQUENCY RESPONSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
114
6. CONTROL UNIT, MODEL A151 & A152 WITH MODIFICATION 5 TEST PROCEDURES . .
114
A. FREQUENCY RESPONSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
114
B. MICROPHONE GAIN ALIGNMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
115
7. MODEL A150 PREAMPLIFIER TEST PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
115
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PAGE
TESTING AND TROUBLESHOOTING (Continued) 8. CALIBRATION TEST FOR MODEL A055B REMOTE MICROPHONE MODULES . . . . . . . . .
118
A. PRELIMINARY SET–UP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
119
B. OUTPUT VERIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
119
C. ALTERATE METHOD (used when sound level source is not available) . . . . . . . . . . . . . . .
119
9. MODEL A100S SYSTEM TROUBLESHOOTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
120
10. MODEL A100S PRINTED WIRING ASSEMBLY (PWA) FAULT ISOLATION . . . . . . . . . . . . . .
126
A. AIRCRAFT INTERFACE PWA FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
126
B. AUDIO PROCESSOR PWA FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
127
(1) Audio Processor PWA Fault Isolation Test Set–up . . . . . . . . . . . . . . . . . . . . . . . . . . . . (2) Audio Processor PWA Input Gain Calibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (3) A100S Frequency Response Measurement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C. STORE PROCESSOR PWA FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
128 133 135 136
11. CONTROL UNIT FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
139
DISASSEMBLY 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
301
2. DISASSEMBLY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
301
A. UNDERWATER LOCATING DEVICE (BEACON) (See Figure 301 or IPL Figure 2) . . . .
302
B. MAIN CHASSIS DISASSEMBLY (See Figure 301 or IPL Figure 2) . . . . . . . . . . . . . . . . . . .
304
(1) Dust Cover (2–90) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (2) Front Panel Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (3) Audio Processor PWA Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (4) Store Processor PWA Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (5) Aircraft Interface PWA Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (6) Flash Crash Survivable Store Unit Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (7) FCSSU Elastomeric Shock Mounts, P/N AM003–7 Removal . . . . . . . . . . . . . . . . . . C. MODELS A151/A151B AND A152/A152B CONTROL UNIT DISASSEMBLY (See IPL Figure 7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
304 304 305 306 307 309 311
D. ELECTRONIC CIRCUIT BOARD DISASSEMBLY (See IPL Figures 3–12) . . . . . . . . . . . .
315
313
CLEANING 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
401
2. MATERIALS REQUIRED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
401
3. CLEANING PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
401
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PAGE CLEANING (Continued)
A. PRINTED WIRING ASSEMBLY CLEANING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402
B. CONNECTOR CLEANING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402
C. MACHINED METAL PARTS CLEANING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402
D. UNDERWATER LOCATING DEVICE (Beacon) CLEANING . . . . . . . . . . . . . . . . . . . . . . . . .
402
CHECKS 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501
2. CHECKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501
A. MECHANICAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501
B. MAIN RECORDER ASSEMBLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501
C. ELECTRICAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
502
D. UNDERWATER LOCATING DEVICE (ULD) INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . .
502
REPAIR 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
601
2. REPAIR PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602
A. PRINTED WIRING ASSEMBLIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
602
ASSEMBLY 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
701
2. REQUIRED MATERIALS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
701
3. ASSEMBLY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
701
A. GENERAL ASSEMBLY TECHNIQUES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
701
B. GENERAL CIRCUIT BOARD ASSEMBLY (See applicable IPL Figures) . . . . . . . . . . . . . .
704
C. AIRCRAFT INTERFACE PWA, P/N 205E0597–00 (See IPL Figures 2 & 3) . . . . . . . . . . .
704
D. AUDIO PROCESSOR PWA, P/N 205E0598–00 (See IPL Figures 2 & 4) . . . . . . . . . . . . .
706
E. STORE PROCESSOR PWA, P/N 205E0601–00 and P/N 253E1027–00 (See IPL Figures 2, 5 & 6) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
706
F.
FLASH CRASH SURVIVABLE STORE UNIT, (FCSSU) P/N 253E0348–03 and P/N 253E0660–00 (See Figure 702 and IPL Figures 2, 5 & 6) . . . . . . . . . . . . . . . . . . . . .
707
G. FCSSU ELASTOMERIC SHOCK MOUNTS, P/N AM003–7 (See Figure 702 and IPL Figure 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
708
H. MODELS A151/A151B & A152/A152B CONTROL UNIT (See IPL Figure 7) . . . . . . . . . . .
711
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PAGE ASSEMBLY (Continued)
4. STORAGE INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
712
A. STORAGE IN ORIGINAL CONTAINERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
712
B. STORAGE WITHOUT ORIGINAL CONTAINERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
712
SPECIAL TOOLS, FIXTURES, & EQUIPMENT 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
901
A. COCKPIT VOICE RECORDER SYSTEM TEST PANEL, P/N 9300A860 . . . . . . . . . . . . . .
901
B. CALIBRATED SOUND SOURCE, P/N 9300A870 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
902
C. AUDIO MONITOR ADAPTER WITH MODIFICATION 1, P/N 17TES0200 . . . . . . . . . . . . .
902
ILLUSTRATED PARTS LIST 1. GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1001
2. PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1001
3. ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1001
4. EQUIPMENT DESCIGNATOR INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1001
5. NUMERICAL INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1001
6. DETAILED PARTS LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1002
7. MANUFACTURER’S CODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1003
8. CONFIGURATION MATRIX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1007
APPENDIX A CIRCUIT AND WIRING DIAGRAMS 1. INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A1
23-70-02
Table of Contents Rev 3 Page v Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
LIST OF ILLUSTRATIONS FIGURE NO.
PAGE
Description and Operation Figure 1
Model A100S Solid–State Cockpit Voice Recorder and Associated Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
Figure 2
Model A100S Outline & Dimension Drawing . . . . . . . . . . . . . . . . . . . . . . . . .
4
Figure 3
Model A100S Functional System Block Diagram . . . . . . . . . . . . . . . . . . . . .
6
Figure 4
Cockpit Voice Recorder System Test Panel, P/N 9300A860 . . . . . . . . . . .
8
Figure 5
Calibrated Sound Source, P/N 9300A870 . . . . . . . . . . . . . . . . . . . . . . . . . . .
9
Figure 6
Audio Monitor Adapter/Modification 1, P/N 17TES0200 . . . . . . . . . . . . . . .
10
Figure 7
Front Panel Controls and Indicators for Model A151, A151B, A152 and A152B Control Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
11
Figure 8
Model A151B and A152B Control Unit Configuration Matrix . . . . . . . . . . .
12
Figure 9
Model A55B Microphone Modules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
13
Figure 10
Remote Microphone Configuration Matrix for Model A151/A151B Control Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
14
Figure 11
Wiring Diagram for Model A55B Remote Microphone Assemblies . . . . . .
15
Figure 12
Interwiring Diagram, Recorder A100S, Control Units A151, A151B Remote Microphones A55, A55B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
16
Figure 13
Interwiring Diagram, Recorder A100S, Control Units A152, A152B . . . . .
17
Figure 14
Interwiring Diagram, Recorder A100S, Control Unit A150 . . . . . . . . . . . . .
18
Figure 15
Control Unit Assembly, Model A151, A151–1 and A151B Wiring Diagrams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
19
Figure 16
Control Unit, Model A152 (P/N 93A152–00) Wiring Diagram . . . . . . . . . . .
20
Figure 17
Control Units, Model A152–1 (P/N 93A152–01), Model A152–2 (P/N 93A152–02), Model A152–4 (P/N 93A152–04) Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
21
Control Unit, Model A152B (P/N 93A152–20) S/N 10000 through 10167 without Mod #1 Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . .
22
Control Unit, Model A152B (All P/N’s except 93A152–20), S/N 10000 through 10167 without Mod #1 Wiring Diagram . . . . . . . . . .
23
Control Unit, Model A152B (P/N 93A152–20 only), S/N 10000 through 10167 without Mod #1 and S/N 10168 and up Wiring Diagram . . . . . . .
24
Control Unit, Model A152B (All P/N’s except 93A152–20), S/N 10000 through 10167, without Mod # 1, and S/N 10168 and up Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
25
Control Unit, Model A152B (P/N 93A152–20, 93A152–25, 93A152–50, and 93A152–70) with Mod #1 and Mod #2 Wiring Diagram . . . . . . . . . .
26
Figure 18 Figure 19 Figure 20 Figure 21
Figure 22
23-70-02 List of Illustrations Rev 3 Page vi Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
LIST OF ILLUSTRATIONS (Continued) FIGURE NO.
PAGE
Description and Operation (Continued) Figure 23
Control Unit, Model A152B (P/N 93A152–20 only) S/N 10000 through 10167 without Mod #1 but with Mod #2, Wiring Diagram . . . . . . . . . . . . .
27
Figure 24
Model A150 External Preamplifier (P/N 93A150–00) Wiring Diagram . . .
28
Figure 25
Model A100S System Functional Block Diagram . . . . . . . . . . . . . . . . . . . . .
30
Figure 26
Aircraft Interface PWA Functional Block Diagram . . . . . . . . . . . . . . . . . . . .
31
Figure 27
Audio Processor PWA, PN 205E0598–00, Functional Block Diagram . . .
34
Figure 28
Computational Processor Signal Descriptions . . . . . . . . . . . . . . . . . . . . . . .
38
Figure 29
Store Processor PWA Functional Block Diagram . . . . . . . . . . . . . . . . . . . .
41
Figure 30
Exploded View of Control Unit Assembly,/ A152, A152B . . . . . . . . . . . . . .
45
Figure 31
Dynamic Microphone Preamplifier PWA, 93A263–02 . . . . . . . . . . . . . . . . .
47
Figure 32
Condenser Microphone Preamplifier PWA, 93A266–01 . . . . . . . . . . . . . . .
48
Testing and Troubleshooting Figure 101
Model A100S Operational Test Set–Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
103
Figure 102
Control Unit Test Set–up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
111
Figure 103
Control Unit Test and Adjustment Point . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
111
Figure 104
External Preamplifier, Model A150 (P/N 93A150–20) Assembly Diagram
115
Figure 105
Simulated Microphone Signal Input Test Connections to the Model A150 Preamplifier Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
116
Figure 106
Remote Microphone Test Setup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
119
Figure 107
Audio Processor PWA, P/N 205E0598–00, Component Layout Drawing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
134
Disassembly of Underwater Locating Device (ULD) and Dust Cover Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
302
Figure 302
Disassembly of ULD Cradle Assembly for Beacon Access . . . . . . . . . . . .
303
Figure 303
Disassembly of Model A100S Front Panel Assembly . . . . . . . . . . . . . . . . .
305
Figure 304
Removal of Audio Processor and Store Processor PWAs . . . . . . . . . . . . .
306
Figure 305
Removal of Store Processor PWA From The Flash Crash Survivable Storage Assembly (FCSSU) . . . . . . . . . . . . . . . . . . . . . . . . . . .
307
Figure 306
Removal of Aircraft Interface PWA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
308
Figure 307
Removal of Flash Crash Survivable Storage Unit (FCSSU) . . . . . . . . . . . .
310
Figure 308
Removal of FCSSU Elastomeric Shock Mounts, P/N AM003–7 . . . . . . . .
312
Figure 309
Disassembly of A151/A151B and A152/A152B Control Units . . . . . . . . . .
314
Disassembly Figure 301
23-70-02 List of Illustrations Rev 3 Page vii Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
LIST OF ILLUSTRATIONS (Continued) FIGURE NO.
PAGE
Cleaning Figure 401
Underwater Locating Device (ULD) Beacon Water Switch Location . . . .
403
Figure 701
Installation of Flash Crash Survivable Storage Unit (FCSSU) . . . . . . . . . .
709
Figure 702
Installation of FCSSU Elastomeric Shock Mounts, P/N AM003–7 . . . . . .
710
Assembly
Special Tools and Test Fixtures Figure 901
Cockpit Voice Recorder System Test Panel, P/N 9300A860 . . . . . . . . . . .
902
Figure 902
Calibrated Sound Source, P/N 9300A870 . . . . . . . . . . . . . . . . . . . . . . . . . . .
902
Figure 903
L3 Audio Monitor Adapter With Modification 1, P/N 17TES0200 . . . . . . . .
903
Figure 904
Model A100S SSCVR Typical Test Setup . . . . . . . . . . . . . . . . . . . . . . . . . . .
904
LIST OF TABLES TABLE NO.
PAGE
Introduction Table 1
Modification Descriptions For Model A100S SSCVR . . . . . . . . . . . . . . . . .
5
Table 2
Modification Descriptions For Model A151 And A152 Control Units . . . . .
7
Table 3
Modification Descriptions For Model A151B And A152B Control Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7
Testing and Troubleshooting Table 101
Recommended Standard Test Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . .
102
Table 102
Model A100S Operational Test Procedures . . . . . . . . . . . . . . . . . . . . . . . . .
104
Table 103
Model A151 and A152 Control Units, Operational Test Procedure . . . . . .
110
Table 104
Model A150 Preamplifier Unit, Operational Test Procedure . . . . . . . . . . . .
116
Table 105
System Level Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
121
Table 106
Aircraft Interface PWA Fault Isolation Procedure . . . . . . . . . . . . . . . . . . . . .
126
Table 107
Audio Processor PWA Fault Isolation Procedure . . . . . . . . . . . . . . . . . . . . .
128
Table 108
Store Processor PWA Fault Isolation Procedure . . . . . . . . . . . . . . . . . . . . .
136
Table 109
System Level Troubleshooting Procedure for Control Units . . . . . . . . . . . .
139
Table 110
Troubleshooting Procedure for Microphone Preamplifiers 9300A030 and 93A263–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
140
Troubleshooting Procedure for Microphone Preamplifiers 93A263–02 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
140
Troubleshooting Procedure for Microphone Preamplifiers 9300A242, 93A266 and 93A266–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
141
Table 111 Table 112
23-70-02 List of Illustrations Rev 3 Page viii Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
LIST OF TABLES (Continued) TABLE NO.
PAGE
Cleaning Table 401
Cleaning Materials Required . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
401
Repair Materials Required . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
601
Required Assembly Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
702
Repair Table 601 Assembly Table 701
Special Tools and Test Fixtures Table 901
Model A100S Special Tools, Fixtures, and Equipment . . . . . . . . . . . . . . . .
901
ILLUSTRATED PARTS LIST FIGURE NO.
PAGE
Figure 1
SSCVR Configuration, Model A100S, P/N S100–0080–00 . . . . . . . . . . . .
1026
Figure 2
SSCVR Final Assembly, P/N 253E0600–00 . . . . . . . . . . . . . . . . . . . . . . . . .
1030
Figure 3
Aircraft Interface PWA, P/N 205E0598–00 . . . . . . . . . . . . . . . . . . . . . . . . . .
1036
Figure 4
Audio Processor PWA, P/N 205E0598–00 . . . . . . . . . . . . . . . . . . . . . . . . . .
1043
Figure 5
Flash Crash Survivable Store Unit (FCSSU), P/N 253E0348–03, P/N 253E0660–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1050
Figure 6
Store Processor PWA, P/N 205E0601–00, 205E1027–00 . . . . . . . . . . . . .
1052
Figure 7
Control Unit, P/N 93A151–XX, 93A152–XX . . . . . . . . . . . . . . . . . . . . . . . . .
1058
Figure 8
Microphone Preamplifier PWA, P/N 93A263–02 . . . . . . . . . . . . . . . . . . . . .
1062
Figure 9
Microphone Preamplifier PWA, P/N 93A266–01 . . . . . . . . . . . . . . . . . . . . .
1065
Figure 10
Remote Microphone Assembly, P/N 93A055–00, –03,–10, –20, –30, –50, –55 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1068
Remote Microphone Assembly, P/N 93A055–40, –45, –60, –65, –66, –67, –95 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1070
Remote Microphone Assembly, P/N 9300A165, –01 . . . . . . . . . . . . . . . . . .
1072
Figure 11 Figure 12
23-70-02 List of Illustrations Rev 3 Page ix Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
APPENDIX A CIRCUIT AND WIRING DIAGRAMS LIST OF TABLES TABLE NO. Table A1
PAGE Schematic Diagram List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A1
LIST OF ILLUSTRATIONS FIGURE NO. Figure A1 Figure A2 Figure A3 Figure A4 Figure A5 Figure A6 Figure A7 Figure A8
PAGE Model A100S Solid–State Cockpit Voice Recorder, P/N S100–0080–00, System Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . .
A2
Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram P/N 905E0597–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A7
Audio Processor PWA, 205E0598–00, Schematic Diagram P/N 905E0598–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A15
Store Processor PWA, 205E0601–01, Schematic Diagram P/N 905E0601–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A35
Store Processor PWA, 205E1027–00, Schematic Diagram P/N 905E1027–01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A51
Dynamic Microphone Preamplifier PWA, P/N 93A263–01, Schematic Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A66
Dynamic Microphone Preamplifier PWA, P/N 93A263–02, Schematic Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A68
Condenser Microphone Preamplifier PWA, P/N 93A266–01, Schematic Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
A70
23-70-02 List of Illustrations Rev 3 Page x Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
INTRODUCTION 1. GENERAL This Component Maintenance Manual (CMM) documents the operation of and suggested maintenance for the Model A100S Solid–State Cockpit Voice Recorder (SSCVR), hereinafter referred to as the A100S. This recorder is designed as a maintenance free recorder. There are no periodic adjustments required to maintain this unit. Also covered within this CMM, are the Model A151, A151B, A152 and A152B Control Units and the Model A55B series of condenser microphones. It should be noted that the Model A100S has been designed to take full advantage of all existing peripheral devices originally developed for use with the Model A100/A100A series of tape–based Cockpit Voice Recorders. The Model A100S is considered an “ON CONDITION LRU.” The Model A151B and A152B Control Units are identical to the earlier Model A151 and A152 Control Units, respectively, except that the “B” models use a Microphone Preamplifier PWA designed to operate with a condenser microphone. Also note that the Model A152 and A152B Control Units are equipped with a built–in microphone whereas the Model A151 and A151B are used with an externally mounted microphone. The Model A55B Remote Microphone Modules are condenser type microphones which operate using a low voltage received from its associated “B” model control unit. Information about the Model A151, A151B, A152 and A152B Control Units, the Model A150 Preamplifier, and the Model A55B series of condenser microphones is contained in the Models A100, A100A CMM, ATA No. 23–70–01 and in the Model A100S CMM, ATA No. 23–70–02. All units produced under the above model designations have been assigned configuration part numbers. The listings below can be used to determine the assigned configuration part number for a particular model control unit and microphone. CONTROL UNITS PART NUMBER
MODEL
PANEL COLOR
MICROPHONE
TEST METER ILLUMINATION
93A151–20 93A151–30 93A151–40 93A151–50
A151B A151B A151B A151B
Gray Black Brown (Boeing) Brown (ATR–42)
None None None None
None None None None
93A152–20 93A152–25 93A152–30 93A152–35 93A152–40 93A152–50 93A152–60 93A152–70
A152B A152B A152B A152B A152B A152B A152B A152B
Gray Gray Black Gray Gray Brown (Boeing) Brown (Boeing) Black
Condenser Condenser Condenser Condenser Condenser Condenser Condenser Condenser
None None 28V 28V 5V None 5V None
23–70–02 Introduction
Rev 2 Page 1 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
REMOTE MICROPHONE MODULES
PART NUMBER
MODEL
COLOR
CONNECTOR LOCATION
MICROPHONE
93A055–10
A55B
Black
Condenser
Rear
93A055–20
A55B
Black
Condenser
Side
93A055–30
A55B
Brown (Boeing)
Condenser
Rear
93A055–40
A55B
Gray
Mini–Condenser
Pigtail
93A055–45
A55B
Brown (ATR–42)
Mini–Condenser
Pigtail
93A055–50
A55B
Black
Condenser
Rear
93A055–55
A55B
Black
Condenser
Side
93A055–60
A55B
Gray
Condenser
Pigtail
93A055–65
A55B
Brown (ATR–42)
Condenser
Pigtail
93A055–66
A55B
Gray
Condenser
Pigtail
93A055–67
A55B
Black
Condenser
Pigtail
93A055–95
A55B
Black
Condenser
Pigtail
EXTERNAL PREAMPS PART NUMBER 93A150–20
MODEL A150
PANEL COLOR BLACK
2. COMPONENT MAINTENANCE MANUAL (CMM) DESCRIPTION This CMM consists of a single volume. The manual conforms to the intent and form of the Air Transport Association of America, ATA Specification 100. The manual is written for an audience of operators and both intermediate and depot level maintenance technicians. All functional, electrical and mechanical aspects of the Model A100S SSCVR, the Model A151, A151B, A152 and A152B Control Units and the Model A55B Series of Condenser Microphones are documented; i.e. description, specification, operation, testing, repair, etc. The CMM content is summarized as follows:
A. Frontis Frontis material consists of a title page, service bulletin list, record of revisions, record of changes, list of effective pages, table of contents and this introduction.
B. Description And Operation This section contains the description and operation information for the Model A100S SSCVR, the Model A151, A151B, A152 and A152B Control Units and the Model A55B series of condenser microphones. Line art is used to illustrate the units, their interconnections and functionality. This section also contains the Model A100S theory of operation and associated block diagram drawings.
23–70–02 Introduction
Rev 2 Page 2 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
C. Testing And Fault Isolation This section contains specific checks and tests required to determine the operational condition of a unit that has been removed from service. Also included in the section are tables of required test equipment, test set–up data, procedures and test parameters. Troubleshooting data is presented in a tabular form with each entry related to a specific test and fault isolation task. Component level fault analysis is also provided based upon test–point signal parameters and stage isolation. No Calibration of circuit boards is required within the Model A100S.
D. Disassembly This section provides all the information required to completely disassemble the A100S and its associated control units and remote microphone modules. The steps of each procedure are coordinated with the TESTING AND FAULT ISOLATION section such that no disassembly is dictated unless first proven as the probable cause of failure. All access to subassemblies within the A100S are described so that there is a minimal disturbance to other subassemblies. Each major disassembly task procedure is accompanied with a line art exploded–view of the subassembly area which are cross referenced to the applicable Illustrated Parts List (IPL) drawing for ordering replacement parts.
E. Cleaning This section contains a listing of all required cleaning materials, procedures for cleaning material use, and applicable warnings and cautions related to the use of prescribed cleaning solvents.
F.
Check This section contains the detailed check procedures that may be required during shop maintenance. References are made to fits and clearance for applicable wear tolerances.
G. Repair This section contains a tabular listing at the front of the section of required materials, tools, and fixtures. This section contains all information required to restore a worn or damaged part to a serviceable condition.
H. Assembly This section contains detailed step–by–step procedures describing the complete assembly of the Model A100S SSCVR and the Model A151, A151B, A152 and A152B Control Units. Special circuit component installation instructions along with any testing during assembly is also included as well as storage instructions after assembly.
I.
Special Tools and Test Fixtures This section provides a listing of all required tools, fixtures, and equipment which are not common maintenance tools.
23–70–02 Introduction
Rev 1 Page 3 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
J.
Illustrated Parts List This section contains exploded–view and circuit board component location diagrams along with detailed parts listings for the SSCVR, Control Units and Remote Microphone Assemblies.
K. Circuit and Wiring Diagrams This appendix provides the detailed schematic diagrams of the Model A100S printed wiring assemblies, the Control Unit Microphone Preamplifier PWAs.
3. DOCUMENT VERIFICATION All manual drawings, illustrations, wiring diagrams and schematics were validated against existing engineering source material. All operational and testing procedures have been verified against the actual performance of the unit under test conditions. Also, all procedural data has been previously verified by field usage of the preliminary component maintenance manual. Effectivity of the manual is based on effectivity dates and product serial number. Effectivity of the manual is identified by a list of effective pages in the front of the manual.
4. RECORDER MODIFICATIONS The Model A100S Solid–State Cockpit Voice Recorder may be upgraded and/or modified to provide increased performance and to reflect the most current component technology. Hardware modifications to the recorder are identified on the front panel Modification Plate whereas Software modifications are identified on the front panel Program Revision Plate. The hardware Modification Plate identifies the unit configuration at the time of production and after factory repair. Note: the Program Revision Plate identifies the software program revisions in numerical order; therefore, when a Program Revision Plate is marked REV. 3, it is to be assumed that revisions 1 and 2 have been incorporated. Table 1 provides a description of the Model A100S modifications performed up to the time of this publication as related to Field Service Bulletins.
5. CONTROL UNIT MODIFICATIONS The Model A151 and A152 CVR Control Units, through extensive field experience, have evolved over the years to reflect the most current in component technology. As such, the control units are identified with a Modification Label which identifies the unit configuration at the time of production and after factory repair. Table 2 provides a description of the Model A151 and Model A152 modifications as related to Field Service Bulletins. Table 3 provides a description of the Model A151B and Model A152B modifications as related to Field Service Bulletins.
23–70–02 Introduction
Rev 1 Page 4 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Modification Descriptions for Model A100S SSCVR Table 1
Modification Program Plate Rev. Plate
Field Service Bulletin No.
Description
R1
001
This modification expands the SSCVR Built–In–Test– Equipment (BITE) circuitry from “READ–AFTER–WRITE” to include Continuous Testing of all bits within the Flash Crash Survivable Store Unit (FCSSU) sometimes referred to as the solid–state memory. It requires a software revision to IC chip U5 (EPROM, part number 046E0285– 01E) located on the Store Processor PWA. No change in the A100S operation or Preflight testing is required.
R2
003
This modification introduces the 8–Megabit FCSSU, P/N 253E0660–00, and the new Store Processor PWA, P/N 205E1027–00.
3
004
This modification signals users of a premature failure rate in FCSSUs manufactured using PWBs supplied by a specific supplier. Since there are multiple PWB suppliers, it cannot be determined as to which PWB was used in a FCSSU. Beginning June 17, 1994, all SSCVRs will use FCSSUs manufactured with PWBs supplied by approved vendors. These units will be identified with Mod Dot 3. Note: Modification Dot 2 has been reserved for use by Engineering for a later release.
4
005
This modification introduces the new FCSSU, P/N 253E1245–00, with modifications to the Printed Wiring Board and to the thermal insulation material.
5
006
This modification introduces two new FCSSUs, P/N 253E1290–00 and 253E1293–00, which have been designed to survive 1–hour fire at 1100 degrees Centigrade with a 50,000 BTUs square foot hours thermal flux transfer, and 10 hours at 260 degrees Centigrade.
R3
007
This software modification prohibits the SSCVR from giving a false fault during rapid power cycling and ensures that all data is erased during a bulk erase.
R4
008
This software modification ensures that the fault light is illuminated during a power recovery bulk erase cycle.
1
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Modification Descriptions for Model A100S SSCVR (Continued) Table 1
Modification Program Plate Rev. Plate 2
Field Service Bulletin No.
Description
009
This modification introduces the Titanium FCSSU, P/N 253E1293–00, which reduces the weight of the FCSSU.
010
This modification introduces a new Dukane Underwater Locator Beacon, P/N DK120, with a 6–year battery life and field replaceability. Can be identified by the part number stamped on the beacon’s body.
6
011
This modification enhances electro–magnetic interference filter characteristics by adding filter circuit consisting of L1–L3 and C35–C38 to the Aircraft Interface circuit board, P/N 205E0597–00. This modification also removed old capacitors C16 & C17, P/N 361–01–0001, from the Aircraft Interface Board.
7
012
This modification replaces power supply U2 on Aircraft Interface Card.
R5
013
This software modification adds software logic for improved handling of SSCVR power down and restart conditions during excessive power interrupts.
R6
014
This software modification enhances Read–After–Write Reset and unit identification functions. Corrects occasional misidentification of an 8 Meg memory unit as a 2 Meg unit during power interrupt conditions. Introduces a procedure for clearing Latched “Memory” faults and Latched “Pointer Not Saved” faults.
015
This modification modifies Store Processor card, P/N 205E1027–00 to reduce noise levels on the flash memory bus. Redesigned Store Processor by removing components C7 & C13, changing U4 and R10, and adding R18 & R19. Replaces power supply to enhance reliability.
016
Informational Introduction of Refurbished FCSSU’s for 253E1290–00 (p/n: 253U1290–00).
8
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Modification Descriptions for Model A151 And A152 Control Units Table 2 MOD NUMBER
FSB
DESCRIPTION
1
101
Rewire Microphone per wirelist P/N 9300WD7.
2
102
Relocation of shield wire.
3
N/A
N/A
4
139
Increase Frequency Bandwidth on Microphone Preamplifier PWA P/N 9300A30.
5
142
Reinstituted Attenuation selection capability through modification of Microphone Preamplifier PWA P/N 9300A30 (Removes Mod 4).
Modification Descriptions for Model A151B And A152B Control Units Table 3 MOD NUMBER
FSB
DESCRIPTION
1
143
Replaces Microphone Preamplifier PWA P/N 93A242 with P/N 93A266.
2
146
Makes direct interchange from A152–02, dynamic, to A152–20, condenser.
151
Changes Microphone Preamplifier PWA P/N 93A266 to P/N 93A266–01: Models A151–50 and A152–35 are Mod 1. All other models are Mod 2.
1 or 2
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
DESCRIPTION AND OPERATION 1. GENERAL This Component Maintenance Manual (CMM) describes the Model A100S Solid–State Cockpit Voice Recorder (SSCVR), the Model A151B/A152B Control Units and the Model A55B series of remote condenser–type microphones. The Model A100S uses solid–state flash memory as the recording medium and is fully compatible with ARINC–557.
MODEL A100S SSCVR
MODEL AI51B CONTROL UNITS
MODEL AI52B CONTROL UNIT
(REMOTE MICROPHONE USED)
(BUILT-IN MICROPHONE)
MODEL A55B REMOTE MICROPHONES
CANISTER STYLE
MOUSE STYLE
FOR STANDARD INSTALLATIONS
FOR CUSTOM INSTALLATIONS
Model A100S Solid–State Cockpit Voice Recorder and Associated Units Figure 1
2. SYSTEM DESCRIPTION The Model A100S SSCVR is a Line Replaceable Unit (LRU) housed in a 1/2 ATR short ARINC 404 style box and weighs less than 23 pounds. It is a four channel high–fidelity recorder designed to continuously acquire and store audio data for a minimum of 30 minutes. It is able to reproduce each channel individually and provides a fifth output which is a combination of the four channels.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
The Model A100S is controlled via standard cockpit panel mounted control units (Models A151, A151B, A152 or A152B) and tested using the Cockpit Voice Recorder System Test Panel, P/N 9300A860. Incorporated into the Model A100S is a built–in–test–equipment (BITE) utility program which measures the frequency and amplitude of a given reference signal and provides a Go or No Go indication. The Model A100S accepts four channels of cockpit audio (Pilot, Co–pilot, Spare and Area microphones) and converts the audio signal to a digital format for storage in a crash protected solid–state memory. Data retrieval from the Model A100S can be accomplished using existing Model A100 & A100A CVR support equipment along with the Audio Monitor Adapter, Mod. 1 (AMA/1), P/N 17TES0200, which was specifically designed for use with the A100S. The Model A100S consists of a chassis and front panel, three Printed Wiring Assemblies (PWAs), and the Flash Crash Survivable Store Unit (FCSSU) which contains the solid–state flash memory used as the recording medium. An Underwater Locator Device (ULD), also referred to as an underwater beacon, is mounted on the front of the recorder.
3. SPECIFICATIONS Specifications for the Model A100S have been developed in close coordination with Aerospace Industry regulatory agencies. As such, the A100S meets or exceeds the requirements of technical standards TSO–C84, TSO–C123, EUROCAE ED–56 and EUROCAE ED–55 (crash protection).
A. APPLICABLE DOCUMENTS The following documents form a part of, or are referenced, within this CMM: (1)
TSO–C84
Federal Aviation Agency Technical Standard Order Minimum Performance Standard for Cockpit Voice Recorders.
(2)
TSO–C123
Federal Aviation Agency Technical Standard Order Minimum Performance Standard for Cockpit Voice Recorders.
(3)
EUROCAE MOPS ED–55
European Organization for Civil Aviation Electronics Minimum Operational Performance Specification for Flight Data Recorder Systems; establishes crash protection standards for all crash protected recorders.
(4)
EUROCAE MOPS ED–56
European Organization for Civil Aviation Electronics Minimum Operational Performance Specification for Cockpit Voice Recorder Systems.
(5)
ARINC Characteristic 557
Airborne Voice Recorder
(6)
RTCA DO–160C
Environmental Conditions and Test Procedures for Airborne Equipment.
(7)
RTCA DO–178A
Software Considerations in Airborne Systems to Level 3.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
B. PHYSICAL CHARACTERISTICS The Model A100S is housed in an ARINC 404 1/2 ATR short box. The A100S physical attributes are presented in the following listing. Refer to Figure 2 for the Model A100S outline and dimension drawing. (1)
Dimensions: (a)
Height: — 7.5 inches (including dust cover)
(b)
Width:
— 5.00 inches (front panel)
(c)
Depth:
— 12.5 inches (behind front panel 14.5 inches (including panel/handle)
(2)
Weight:
–00 –01
18.4 +/– .5 pounds 15.9 +/– .5 pounds
(3)
Case: Stainless Steel, International Orange, Reflective Striping, English/French Markings, Raised Lettering
(4)
Main Connector: DPX036571–0059
(5)
Front Panel Connector: 1/4 inch phone jack
(6)
Underwater Locating Device: Dukane Beacon (P/N: DK120) or Datasonics Beacon (P/N: ELP–362D). Both beacons have an expected battery life of six years and are directly interchangeable.
C. ELECTRICAL CHARACTERISTICS (1)
Power Requirements: 115 Volts, 400 Hz ac or +28 Volts dc.
(2)
Power Level: 12W, maximum.
(3)
Output Power: +18 Vdc Preamplifier power, 100 mA short–circuit protected.
(4)
Analog Inputs: Three crew microphones (150 to 3500 Hz bandwidth); One area microphone (150 to 5000 Hz bandwidth).
(5)
Analog Outputs Monitored:
(6)
Discrete Inputs: (a) (b) (c)
1) 600–ohm headphone (short–circuit protected); 2) Test Meter indicator and 3) Lamp Driver.
Bulk Erase (two), Test, Record Enable.
D. ENVIRONMENTAL CHARACTERISTICS (1)
Operating Temperature: –55 to +70
C
(2)
Non–Operating Temperature: –65 to +85 C
(3)
Altitude (Operating): –1000 to 55,000 feet
(4) (5)
Vibration (Operating): Doc. DO–160C, Para. 8.2.2 and 8.4; Fig. 8–6 Test Curve C, C’ Penetration: ED–55 – 500 lbs/10ft/1/4” probe
(6) (7) (8)
Static Crush: Fire Protection: Impact:
ED–55 – 5,000 lbs ED–55 – 50,000 BTUs/sq.ft./hours, 30 min. ED–55 – 3400 g’s., 6.5 ms
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
STANDARD HALF ATR SHORT CASE
C.G.
3.56
.156 .125 5.25
NAME PLATE
2.40
HANDLE
MONITOR
ULD MOUNTING BRACKET
UNDERWATER LOCATING DEVICE
C.G. CANNON CONNECTOR NO. DPXB-57-34P-0101 MODIFICATION RECORD PLATE
POLARIZING KEYS
PROGRAM REVISION PLATE
HOLD DOWN HOOKS PER ARINC SPEC. NO. 404
2.40 HOLD DOWN HOLES PER ARINC SPEC. NO. 404
Model A100S Outline & Dimension Drawing Figure 2
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
4. TECHNICAL DESCRIPTION The Model A100S is fully compatible with ARINC 557. As such, it is a direct replacement for all previous tape–based cockpit voice recorders.
A. SYSTEM OVERVIEW The Model A100S Cockpit Voice Recorder System is composed of the recorder and an externally mounted control unit utilizing either a built–in or externally mounted microphone (refer to Figure 3). Interconnection between the recorder and the control unit is accomplished using aircraft wiring. The A100S consists of the following four main assemblies: Aircraft Interface PWA, Audio Processor PWA, Store Processor PWA and the crash protected solid–state memory assembly which is designated as the Flash Crash Survivable Store Unit (FCSSU). The A100S is connected to aircraft wiring via a 57–pin, DPX style input connector and its Aircraft Interface PWA. The Aircraft Interface PWA provides for all input and output signals. The Model A100S provides for four microphone inputs which are connected as follows: the cockpit spare microphone input to Channel 1, the co–pilot microphone input to Channel 2, the pilot microphone input to Channel 3, and the area microphone input to Channel 4. The audio from the area microphone may originate at the control unit (built–in) or at a remote microphone; this audio has a bandwidth of 150 to 5000 Hertz. The other three channels are supplied audio from the pilot audio selectors and have a bandwidth of 150 to 3500 Hertz. The spare audio input applied to Channel 1 may be from a third crew member or from a PA system. The Audio Processor PWA receives the audio signals from the four channels and converts each to a digital byte oriented format for storage. The digital signals are applied to the Store Processor PWA for encoding and storage in the FCSSU. Incorporated into the A100S is a “record” jumper. During bench test of the A100S, the jumper enables the record function of the recorder to be turned off, thereby allowing playback of the recorded data. Once playback is initiated, the unit immediately begins replaying the recorded data. The A100S provides the control unit with +18 Vdc operating power, monitor audio, and an indicator signal. The monitor audio is accessible at the front panel of both the control unit and the A100S via a 600–ohm phone plug. The indicator signal is used to drive the test meter in the DO–160B control unit, Model A151 or Model A152. The +18 Vdc is a short–circuit protected 100 ma line. All control units (Model A151, A151B, A152 or A152B) provide the A100S with three control signals: Erase A, Erase C, and Push_To_Test. The Erase A and Erase C signals are used to initiate a bulk erasure of the crash protected solid–state memory. The bulk erase button must be pressed for more than two seconds, and then released, to initiate the bulk erase function. Additionally, landing gear and brake interlocks are provided in the aircraft wiring to prevent memory erasures during flight conditions. The Push_To_Test signal is activated as long as the “TEST” button on the control unit is pressed. During this time, a 640 Hz +20 Hz signal is generated which is used to test the throughput circuitry of all the audio channels. In turn, the A100S recorder provides an INDICATOR signal which drives the GO / NO GO display on the control unit.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
INDICATOR SIGNAL
ERASE A
MONITOR AUDIO
CONTROL UNIT
ERASE C AIRCRAFT WIRING INTERLOCKS (LANDING GEAR MUST BE DOWN AND BRAKE LOCKED TO ALLOW MEMORY TO BE ERASED)
PUSH_TO_TEST
GEAR
AREA MICROPHONE
BRAKE +18 V OPERATING POWER 5
RECORD LIGHTING AREA MICROPHONE PILOT MICROPHONE
CO-PILOT MICROPHONE SPARE MICROPHONE (TO 3RD CREW MEMBER OR PA SYSTEM)
CHANNEL 4 2
MONITOR AUDIO
CHANNEL 3
2
2 CHANNEL 2 2 CHANNEL 1 2
+18 V
AIRCRAFT INTERFACE PWA
2 INDICATOR 2
27.5 VDC OR 115 VAC
CHASSIS GROUND
AUDIO PROCESSOR PWA STORE PROCESSOR PWA FCSSU
(Flash Crash Survivable Store Unit)
ASSEMBLY
(AKA, CRASH PROTECTED SOLID-STATE MEMORY)
MODEL A100S Model A100S Functional System Block Diagram Figure 3
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
B. DATA MONITORING While mounted in the aircraft, previously recorded data cannot be monitored from the Model A100S. This is a security feature implemented to protect the rights of pilots and other flight crew members. The combined audio of the four channels can be monitored during recording using headsets plugged into the 1/4–inch, 600–ohm phone jack mounted on the front panel of either the A100S or its control unit. Also, when being tested at the standard cockpit test bench set up, combined playback data can be monitored using the speaker mounted within the Cockpit Voice Recorder System Test Panel, P/N 9300A860.
C. STORAGE CAPACITY The Model A100S storage media is designated as the Flash Crash Survivable Store Unit (FCSSU). The FCSSU contains CMOS Flash memory with enough storage capacity to allow a minimum of thirty minutes of continuous recording.
D. DATA RETRIEVAL The recorder must be removed from the aircraft and the dust cover removed to retrieve data from the recorder. With the dust cover removed, the Audio Monitor Adapter (AMA/1), P/N 17 TES0200, is plugged into the edge mounted Playback/Monitor connector (J6) on the Audio Processor PWA. This connection allows a user to monitor individual channel data or combined channel data. The fidelity of the A100S audio data output at the AMA/1 is such that only an external amplifier and speaker are required to allow quality analysis of the recorded data.
E. DATA REPRODUCTION A standard cassette or reel–to–reel tape recorder can be used to produce a high fidelity copy of the Model A100S recorded data. To do so, the inputs of the copy recorder are connected to any one of the 1/4–inch monophone jacks located on the Audio Monitor Adapter (AMA/1) front panel. Depending upon the type recorder used for copying, the A100S data can be copied one channel at a time, or all individual channels can be copied simultaneously.
F.
BUILT–IN–TEST–EQUIPMENT (BITE) Built–In–Test–Equipment (BITE) capability is provided to establish and monitor the mission fitness of the hardware. The built–in–test feature has been designed to perform a continuous test of all bits within the solid–state memory located in the Flash Crash Survivable Store Unit (FCSSU). The test tone used for unit verification is developed on the Audio Processor PWA and applied to each channel individually where it is processed, stored in memory, read from memory, and checked for expected frequency and amplitude. The built–in–test is initiated by pressing and holding the “TEST” push–button located on the front panel of the Model A151, A151B, A152 and the A152B Control Units. The GO /NO GO meter is also located on the front panel of these control units.
G. FLASH CRASH SURVIVABLE STORE UNIT The Flash Crash Survivable Store Unit (FCSSU) is the memory storage assembly of the Model A100S. Electrical interface to the FCSSU is made by the Store Processor via a single connector with 50 contacts. The Store Processor PWA is mounted to the FCSSU assembly. Dimensions of the FCSSU are: 7.37” x 7.28” x 4.73”. FCSSU P/N 253E0348–03, 253E0660–00, 253E0992–00 and 253E1290–00 weigh approximately 17 pounds. FCSSU P/N 253E1293–00 weighs approximately 13 pounds.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
H. CRASH AND FIRE PROTECTION The Flash Crash Survivable Store Unit (FCSSU) is triple protected by an inner casing of thermal insulation, the inner steel casing, and the outer stainless steel casing. The inner and outer cases for the light weight model FCSSU, P/N 253E1293–00, are comprised of titanium in place of steel. This construction enables the Model A100S to meet the rigorous crash protection requirements given in specification ED–55.
5. SUPPORT EQUIPMENT The Model A100S has been designed to take advantage of all existing cockpit voice recorder support equipment. Additionally, the Audio Monitor Adapter (AMA/1), P/N 17TES0200, has been specially designed for the A100S to allow connection to any one of the four audio output channels or to the combined audio output which is the sum of the four channels.
A. MODEL A860 COCKPIT VOICE RECORDER SYSTEM TEST PANEL The operation of the A100S is verified using the standard test panel originally designed for the test and calibration of the Model A100 series of tape–based cockpit voice recorders. Using the standard L3 Cockpit Voice Recorder System Test Panel, P/N 9300A860 (refer to Figure 4), audio signals can be applied to individual channels for testing and analysis. Additionally, the A860 Cockpit Voice Recorder System Test Panel can be used: 1) to activate the built–in–test utility of the Model A100S, 2) to initiate the Bulk Erase feature of the recorder, and 3) to replay previously recorded audio.
VOICE RECORDER FAIRCHILD COCKPIT SYSTEM TEST PANEL N O R M A L
A C T U A T E
BULK ERASE TEST
TEST
BIAS TRAP ADJUST
SYS UNIT
O U T P U T
MODE GND FAULT
700
1kHz
ROLL OFF I N P U T
GND SHORT
AII3 BULK ERASE
-6 dB
A T T E N U A T I O N
-12 dB
-24 dB
C.U.
EXT
1
A55
MIC
J2
ALL TEST
REC.
INT
O U T P U T
BULK ERASE
BYPASS REVERSED GND
HEADSET
VOLUME
LOCAL AMP AC
MIC CAL DC
2A
DC
OFF
3
4 SHORT
C.U.
CHANNEL SELECT RECORD BIAS
ON
POWER
2
-18VDC +18VDC
2A
I N P U T
AC
J3
CONTROL OFF UNIT
GTP PROBE (FOR GROUND TEST)
Cockpit Voice Recorder System Test Panel, P/N 9300A860 Figure 4
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
B. MODEL A870 CALIBRATED SOUND SOURCE Microphone performance can be evaluated through the use of the Model A870 Calibrated Sound Source, P/N 9300A870 (refer to Figure 5).
MICROPHONE
CALIBRATED SOUND SOURCE P/N 9300-A870
CALIBRATE
USE 1 kHz SET TO 0 dB
Calibrated Sound Source, P/N 9300A870 Figure 5 C. AUDIO MONITOR ADAPTER (AMA/1) The AMA with Modification1, P/N 17TES0200 (refer to Figure 6), is used along with the L3 Cockpit Voice Recorder System Test Panel to extract individual channel audio data from the Model A100S for sampling and/or copying to a portable recorder. The Model A100S must have its dust cover removed to allow access to the Audio Processor PWA. The AMA/1 cable connector is mated to the Audio Processor PWA Playback/Monitor connector (J6) which is located at the board’s outer edge just below center. This connection routes the four audio channels and the Combined Audio channel (summation of Channels 1 through 4) to the AMA/1 for output individually as follows: From SSCVR
To AMA/1
Signal Amplitude (see note)
Channel 3 (signal AUDIO_3)
PILOT jack
1 Vrms + 10%
Channel 2 (signal AUDIO_2)
CO–PILOT jack
1 Vrms + 10%
Channel 1 (signal AUDIO_1)
SPARE jack
1 Vrms + 10%
Channel 4 (signal AUDIO_4)
AREA jack
1 Vrms + 10%
Combined Audio Channel (signal COMBINED_AUDIO)
COMBINED jack
1.45 Vrms + 10%
Note: the signal amplitudes given are based on the A100S applied input of 3 Vrms for Channels 1, 2 and 3 and 2 Vrms for Channel 4. As a general rule, the signal amplitude available at the AMA/1 SPARE (Channel 1), CO–PILOT (Channel 2 ) and PILOT (Channel 3) jacks is 33% of the A100S applied input whereas the signal amplitude available at the AREA jack (Channel 4) is 50% of the unit applied input. The signal amplitude available at the AMA/1 COMBINED jack is approximately 1.45 times the highest individual channel amplitude present at the AMA/1. Also, the signal amplitude measured at the AMA/1 COMBINED jack should be identical to that measured at the Headset jack on both the Model A100S front panel or its associated Control Unit front panel.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
10 CONTACT CONNECTOR L3 P/N 0639800365 30-INCH FLAT-RIBBON CABLE
DIMENSIONS: HEIGHT - 7.55 INCHES WIDTH - 4.05 INCHES DEPTH - 1.72 INCHES CABLE - 30 INCHES
Audio Monitor Adapter/Modification 1, P/N 17TES0200 Figure 6 Because of the enhanced fidelity of the Model A100S, the AMA/1 along with an external amplifier and speaker are the only instruments required to provide quality analysis of the recorded audio. Individual channels are accessed at their respective jacks on the AMA/1 using a cable fitted with a 1/4–inch monophone jack at one end and an appropriate type connector for the device to be connected at the other. Copies of the A100S recorded audio may be made by connecting the cable to the input of a standard cassette recorder or similar device. After the desired connections have been made and before applying power to the A100S, verify that the CVR System Test Panel RECORD BIAS/OFF toggle switch is set to position OFF (down) to prevent writing over existing data. To play back the full 30 minutes of recorded audio, simply apply power to the A100S. To begin replaying the data recorded since the recorder was last powered–up, press the ALL TEST pushbutton on the CVR System Test Panel.
6. PERIPHERAL EQUIPMENT The Model A100S has been designed to take full advantage of all existing peripheral devices originally developed for use with the Model A100/A100A series of tape–based Cockpit Voice Recorders. In addition, the Model A100S has also been designed to accommodate the Model A151B and A152B Control Units which are DO–160B compliant. Each control unit is a standard ATR, panel–mounted unit that provides remote control of the Model A100S. These units include a Microphone Preamplifier PWA designed for use solely with condenser type microphones (Model A55B microphones). Except for the Microphone Preamplifier PWA designed to operate with a condenser microphone, the Model A151B and A152B Control Units are identical to the earlier Model A151 and A152 Control Units, respectively, which use a dynamic Microphone Preamplifier PWA and one of the Model A55 series of dynamic microphones. The main external difference to be noted between control unit models (see Figure 7) is that the Model A152 and A152B Control Units have a built–in microphone whereas the Model A151 and A151B units connect to an externally mounted microphone.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
A. CONTROL UNIT, MODEL A152B The Model A152B Control Unit, P/N 93A152–XX (refer to Figure 7), contains the area microphone (condenser), TEST switch, bulk ERASE switch, test meter, 600–ohm headset jack, and a Microphone Preamplifier PWA, P/N 93A266–01 (refer to Appendix A for schematic). The TEST switch and indicating test meter provide the capability to test the four channels and the headset jack provides a means to monitor the playback of all four recorded channels. The bulk ERASE switch is used to erase the stored audio data after a routine flight, and will only work when the landing gear is down, the weight of the plane is resting on the landing gear, and the parking brake is engaged. To prevent accidental erasures, a time–delay circuit makes it necessary to hold the switch down for two seconds to start the erasure process. The Control Unit utilizes aircraft wiring for connection to the recorder unit. As previously stated, the Model A152B Control Unit, P/N 93A152–XX, is easily identified by its built–in condenser microphone. The last two digits of the control unit part number identify the unit color and other pertinent features provided (refer to Figure 8 for the Model A152B Control Unit Configuration Matrix). MICROPHONE (A152/A152B ONLY)
2.250 +.000 -.030
FUNCTION SWITCHES
TEST METER
HEADSET JACK
 Â
TEST
ERASE + .002 1.125 -
HEADSET 600 OHMS
COCKPIT VOICE RECORDER +.015 5.375 + .000 5.750 - .020
+ .562 - .000 .015 .18
MODEL A152 AND A152B CONTROL UNIT FRONT PANEL ILLUSTRATED MODEL A151 AND A151B CONTROL UNITS SAME AS ABOVE EXCEPT NO BUILT–IN MICROPHONE
Front Panel Controls and Indicators for Model A151, A151B, A152 and A152B Control Units Figure 7 B. CONTROL UNIT, MODEL A151B The Model A151B Control Unit, P/N 93A151–XX, is identical to the Model A152B described above except that the built–in condenser microphone is eliminated and an externally mounted condenser microphone is used. This type control unit is used in installations where, due to space restrictions, its optimum mounting location would cause a built–in microphone to be ineffective. Refer to Figure 8 for the Model A151B Control Unit Configuration Matrix.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
PANEL COLOR
MICROPHONE
METER ILLUMINATION
PRODUCTION PART NUMBER 93A150-20 93A151-00 93A151-01 93A151-20 93A151-30 93A151-40 93A151-50 93A151-70 93A152-20 93A152-25 93A152-30 93A152-35 93A152-40 93A152-50 93A152-60 93A152-70
Model A151B and A152B Control Unit Configuration Matrix Figure 8
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
C. MICROPHONE MODULES Figure 9 illustrates the Model A55B Microphone Modules typically used with the Model A152B and A151B Control Unit. Also shown are two microphones used in some custom installations. These microphones are the electric condenser type microphones which operate using a low voltage, approximately +6.2V, received from its associated control unit Microphone Preamplifier PWA. Except for the two omni–directional models, P/N 93A055–40 and 93A055–45, all others are cardioid type directional microphones which have a heart–shaped response pattern that gives a nearly uniform response for a range of about 180 in one direction and a minimum response in the opposite direction. As illustrated, two basic styles of the microphone are offered. One is the canister style which is a panel mounted microphone with connection terminals at its side or rear. The other is the mouse style which comes with a pigtail for hard–wiring to the control unit. This smaller mouse type microphone is suitable for remote mounting on the glare shield or windshield post where panel space is not available for any other type installation. Note: various configurations of these microphones are available for unique installations; refer to Figure 10 for the Remote Microphone Configuration Matrix for specifics. CONDENSER MICROPHONES
CANISTER STYLE
93A055–10, –20, –30, –50, –55
MOUSE STYLE
93A055–40, –45, –60, –65, –66, –67, –95
USED IN MOST INSTALLATIONS
9300A165
9300A165–01
USED IN CUSTOM INSTALLATIONS
Model A55B Microphone Modules Figure 9
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Description and Operation Rev 1 Page 13 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE COLOR
MICROPHONE TYPE
CONNECTOR LOCATION
CURRENT PRODUCTION PART NUMBER 93A055-10 93A055-20 93A055-30 93A055-40 93A055-45 93A055-50 93A055-55 93A055-60 93A055-65 93A055-66 93A055-67 93A055-95
NOTES: 1. DIRECTIONAL MICROPHONES ARE THE CARDIOID TYPE WHICH HAS A HEART-SHAPED RESPONSE PATTERN THAT GIVES A NEARLY UNIFORM RESPONSE FOR A RANGE OF ABOUT 180 IN ONE DIRECTION AND A MINIMUM RESPONSE IN THE OPPOSITE DIRECTION. 2. MICROPHONES 93A055-40, -45 ARE OMNI-DIRECTIONAL TYPES.
Remote Microphone Configuration Matrix for Model A151/A151B Control Units Figure 10
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Description and Operation Rev 2 Page 14 Feb. 15/00 01/93 Mar.
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
7. INSTALLATION The Model A100S SSCVR is an environmentally hardened unit housed in an ARINC 404 1/2 ATR short box painted international orange. The A100S does not require external shock mounting for installation into the aircraft. The A100S is fully compatible with ARINC Specification 557 and is directly interchangeable with all existing cockpit voice recorder installations. The A100S is connected to its Control Unit by way of the aircraft wiring. As illustrated in Figure 12 and Figure 13, the A100S and the Control Unit electrical interconnections are standard with the only variation being with the Control Unit and whether it has an internal or external microphone.
A. Control Unit Wiring The Model A151B and the Model A152B Control Units are recommended for use in a new A100S system. The main difference between the two is the Model A152B has a built–in condenser microphone whereas the Model A151B utilizes an externally mounted condenser microphone. Other differences are in regard to front panel color and meter illumination input voltage. Refer to Figure 15 through Figure 23 for the Model A100S and associated Control Unit wiring diagrams.
B. Remote Microphone Wiring The wiring diagrams for the Model A55B series of remote microphones listed in Figure 10 and used in conjunction with the Model A151B Control Unit are shown in Figure 11. CONNECTOR AS VIEWED FROM SOLDER TERMINAL END
FLAT ON THREADS
MICROPHONES: 93A055-10 93A055-20 93A055-30 93A055-50 93A055-55
CONNECTOR SHELL
.75 REF
PIN 1 PIN 2 WHITE WIRE RED WIRE
BLACK WIRE
SHIELD
MICROPHONES: 93A055-40 93A055-45
ALPHA FIT-221-3/16 WHITE HEAT SHRINK TUBING 7/8" LONG
24 BLACK PLASTIC COVERED 7/32 STRAND WIRE. (MIL-W-16878D) MICROPHONE CABLE DETAIL
SPLICE BLACK WIRE WHITE WIRE
WHITE WIRE RED WIRE SHIELD
MICROPHONES: 93A055-60 93A055-65 93A055-67
WHITE WIRE BLACK WIRE
MICROPHONES: 93A055-66 93A055-95
WHITE WIRE BLACK WIRE
SHIELD
SHIELD
+DC SUPPLY (TO PIN P) - AUDIO OUT (TO PIN N) SHIELD
SIGNAL GND & SHIELD (TO PIN M)
DC SUPPLY (TO PIN P) SIGNAL OUTPUT (TO PIN N) SIGNAL GND & SHIELD (TO PIN M) DC SUPPLY (6V) SIGNAL OUTPUT SIGNAL GND
Wiring Diagrams for Model A55B Remote Microphone Assemblies Figure 11
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Description and Operation Rev 1 Page 15 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
VOICE RECORDER UNIT, ALL A100S MODELS
STANDARD INTERWIRING PER ARINC SPEC 557 TO 115 VAC HOT (400HZ) TO AC COLD
1 AMP
TO 27.5VDC
5 AMPS
*3
*4
CONTROL UNIT ALL MODELS A151 OR A151B PUSH_TO_TEST PRE-AMP POWER GND PRE-AMP POWER +18 VDC INDICATOR + INDICATOR CHASSIS GROUND ERASE SWITCH A" ERASE SWITCH C" OUTPUT - LOW OUTPUT - HIGH MIKE CABLE SHIELD MIKE INPUT - HI MIKE INPUT - LO FILTER COMMON FILTER 1.000 HZ
*5
AUDIO JACK - LO AUDIO JACK - HI
(RESERVED) (RESERVED) SUGGESTED SPARE NO. 1 SUGGESTED SPARE NO. 2 SUGGESTED SPARE NO. 3 6 DB ATTENUATION ATTENUATOR_ COMMON 12 DB ATTENUATION 24 DB ATTENUATION
A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k p q r s t
*4
SPARE MICROPHONE - TO 3RD CREW MEMBER OR PA SYSTEM
*7 TO CO-PILOT MICROPHONE
TO PILOT MICROPHONE
AREA MICROPHONE
*6 *4
MICROPHONE MODEL A55 OR A55B MIKE OUTPUT HI (AUDIO) MIKE OUTPUT LO ( DC IN ) MIKE SHIELD (CONNECTOR SHELL)
NOTES:
1 *2 *3 *4 *5 *6 *7 *8
*2
1 2
*7 *8
BRAKE
GEAR
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. 52. 53. 54. 55. 56. 57.
115 VAC HOT OUT 115 VAC HOT IN AC COMMON COLD
AUDIO OUT LO AUDIO OUT HI BIAS JUMPER BIAS JUMPER +27.5 Vdc INPUT (reserved) PUSH_TO_TEST PREAMP POWER GND PREAMP POWER +18 Vdc REG INDICATOR + INDICATOR CHASSIS GROUND (reserved) (reserved)
SUGGESTED SPARE NO. 1 SUGGESTED SPARE NO. 2 SUGGESTED SPARE NO. 3
LO CHANNEL 1 HI
LO
CHANNEL 2
HI
LO CHANNEL 3 HI LO HI
CHANNEL 4
ERASE A ERASE C
Recommended minimum wire size is #22; however, wire size #24 is acceptable except for long-run power leads where #18 wire is recommended (pins 2,3,17, & 19). Ground connection to be within 1 foot of pin 17. Only one power source to be wired per aircraft. If 115 Vac, 400 Hz is supplied, no connection is to be made to pin #9. If 27.5 Vdc is supplied, no connection is to be made to pin #3. Short pins 1 & 2. Single Ground Point. Short pins S & T for piston aircraft only. Wiring shown for standard fixed attenuation of 18 dB per ARINC 557. Control Units A151 or A152 to be used with Mike Modules A55 only. Control Units A151B or A152B to be used with Mike Modules A55B only. Model 40 Series & Model 60 Series microphone output cabling colors are reversed. On the Model 40 Series, the white wire is the high" (audio side); on the Model 60 Series, the white wire is the LO" (dc in ).
Interwiring Diagram, Recorder A100S, Control Units A151, A151B, Remote Microphones A55, A55B Figure 12
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Description and Operation Rev 1 Page 16 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
STANDARD INTERWIRING PER ARINC SPEC 557 TO 115 VAC HOT (400HZ) TO AC COLD
1 AMP
TO 27.5VDC
5 AMPS
VOICE RECORDER UNIT, ALL A100S MODELS
*3
*4
CONTROL UNIT, ALL MODELS A152 OR A152B PUSH_TO_TEST PRE-AMP POWER GND PRE-AMP POWER +18 VDC INDICATOR + INDICATOR CHASSIS GROUND ERASE SWITCH A" ERASE SWITCH C" OUTPUT - LOW OUTPUT - HIGH (RESERVED) MIKE INPUT - HI MIKE INPUT - LO FILTER COMMON FILTER 1.000 HZ
*6
AUDIO JACK - LO AUDIO JACK - HI 5V LAMP - HOT LAMP - COMMON/COLD 28V LAMP - HOT
INTERNAL MIKE - HIGH INTERNAL MIKE - LOW SUGGESTED SPARE NO. 1 SUGGESTED SPARE NO. 2 SUGGESTED SPARE NO. 3
6 DB ATTENUATION ATTENUATOR COMMON 12 DB ATTENUATION 24 DB ATTENUATION
A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s t
*4
*2
SPARE MICROPHONE - TO 3RD CREW MEMBER OR PA SYSTEM
*5
*8 TO CO-PILOT MICROPHONE
TO PILOT MICROPHONE
AREA MICROPHONE
*7 *4
BRAKE
NOTES:
1 *2 *3 *4 *5 *6 *7 *8
GEAR
1. 115 VAC HOT OUT 2. 115 VAC HOT IN 3. AC COMMON COLD 4. 5. AUDIO OUT LO 6. AUDIO OUT HI 7. BIAS JUMPER 8. BIAS JUMPER 9. +27.5 Vdc INPUT 10. (reserved) 11. 12. PUSH_TO_TEST 13. PREAMP POWER GND 14. PREAMP POWER +18 Vdc REG 15. INDICATOR + 16. INDICATOR 17. CHASSIS GROUND 18. (reserved) 19. (reserved) 20. 21. 22. 23. SUGGESTED SPARE NO. 1 24. SUGGESTED SPARE NO. 2 25. SUGGESTED SPARE NO. 3 26. 27. 28. 29. 30. LO 31. CHANNEL 1 32. HI 33. 34. 35.LO 36. CHANNEL 2 37.HI 38. 39. 40. 41.LO 42. CHANNEL 3 43.HI 44. 45.LO 46. CHANNEL 4 47.HI 48. 49. 50. 51. 52. 53. 54. 55.ERASE A 56. 57.ERASE C
Recommended minimum wire size is #22; however, wire size #24 is acceptable except for long-run power leads where #18 wire is recommended (pins 2,3,17, & 19). Ground connection to be within 1 foot of pin 17. Only one power source to be wired per aircraft. If 115 VAC, 400 Hz is supplied, no connection is to be made to pin #9. If 27.5 VDC is supplied, no connection is to be made to pin #3. Short pins 1 & 2. Single Ground Point. If meter illumination is included in Control Unit, supply voltage from lighting bus to proper pins. Short pins S & T for piston aircraft only. Wiring shown for standard fixed attenuation of 18 dB per ARINC 557. Jumper wires per ARINC 557, 1/2 inch, maximum length.
Interwiring Diagram, Recorder A100S, Control Units A152, A152B Figure 13
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Description and Operation Rev 1 Page 17 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
STANDARD INTERWIRING PER ARINC SPEC 557 EXTERNAL PREAMP A150 TO 115 VAC HOT (400HZ) TO AC COLD
VOICE RECORDER UNIT, ALL MODELS A100S
1 AMP
*3
TO 27.5 VDC
5 AMPS
*4
EXTERNAL PREAMP MODEL A150 PRE-AMP POWER (+18 VDC) PRE-AMP POWER GND PRE-AMP OUT - HI PRE-AMP OUT - LO ATTENUATION MASTER CHASSIS GROUND
J2
24 DB ATTENUATION 12 DB ATTENUATION 6 DB ATTENUATION
MIC SIGNAL INPUT MIC SUPPLY (+6.2 VDC) MIC SHIELD (GND)
J1
A B C D E F G H J K L M
*2
A B C
TO 3RD CREW MEMBER OR PA
MODEL A55B MICROPHONE (ANY PART MODEL) MIC 6 VDC SUPPLY MIC GND (SHIELD) MIC OUTPUT
*4
1
TO CO-PILOT
2
TO PILOT
AREA MICROPHONE
*4
NOTES:
1 *2 *3 *4
1 2 3 4 5 6 7 8 9 10 11
115 VAC HOT OUT 115 VAC HOT IN AC COMMON COLD
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
PUSH_TO_TEST PREAMP POWER GND PREAMP POWER +18 VDC REG INDICATOR + INDICATOR CHASSIS GROUND
42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57
AUDIO OUT LO AUDIO OUT HI BIAS JUMPER BIAS JUMPER +27.5 VDC INPUT (with inverter)
SUGGESTED SPARE NO. 1 SUGGESTED SPARE NO. 2 SUGGESTED SPARE NO. 3
LO HI
LO HI
CHANNEL 1
CHANNEL 2
LO HI LO HI
CHANNEL 3
CHANNEL 4
ERASE A ERASE C
Recommended minimum wire size is #22; however, #24 wire is acceptable except for long-run power leads where #18 wire is recommended (pins 2,3,17, & 19) Ground connection to be within 1 foot of pin 17. Only one power source to be wired per aircraft. If 115 VAC, 400 Hz is supplied, no connection is to be made to pin #9. If 27.5 VDC is supplied, no connection is to be made to pin #3. Short pins 1 & 2 and be sure inverter is used. Single Ground Point.
Interwiring Diagram, Recorder A100S, Control Unit A150 Figure 14
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Description and Operation Rev 1 Page 18 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
CONNECTOR A9300-241 GY RD
METER
BK GRN BK WH BK
E D M N P
WH/BK WH/BK VIO RD
B K L C
WH WH/RD WH/GRN BL
P r t q
WH/GR BK RD BL BRN GR
A F G H W V
+ F
PRE-AMP
5B
BK
TEST SWITCH
No Nc C
HEAD PHONE JACK
E
K
L
C
P
No Nc C
N P
B
q
BK
ERASE SWITCH
M
t r
Z b
BL
BK
RD GRN
MODEL A151B CONTROL UNIT, P/N 93A151-20, 93A151-30 and 93A151-50 Optional Wires METER
+ P M F
BK C B
PRE-AMP
HEAD PHONE JACK
K
5B
TEST SWITCH
ERASE SWITCH
N
L
T
No Nc C
S
p t
BK No Nc
BL
C
RD GRN
BK
r q
BK
GY BK BK BRN WH BK BK RD WH/BK WH/BK VIO YW OR WH WH/RD WH/GRN BL WH/GY BK BL RD BRN GY
PLUG PIN Z b E D N P M C B K L S T P r t q A F H G W V
MODEL A151, A151-1 CONTROL UNIT, P/N 93A151-00, and 93A151-01
Control Unit Assembly Model A151, A151–1 and A151B Wiring Diagrams Figure 15
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Description and Operation Page 19 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
CONNECTOR
MICROPHONE
METER
GY BK
Z b
RD WH
f g
BK
+
BK GRN
WH
N P
P.C. BOARD
BK
M
BK
GRN
RD
C B 5B S
K
L
T
No
WH WH/RD
r
WH/GRN BL
t q
C ERASE SWITCH
WH/BK WH/BK VIO YW OR
p
Nc
N P
**
M
F
BK
TEST SWITCH
E D
C B K L S T P r t q
BK WH/GY No
BK BL RD BRN GY
BL
Nc
BK
C
RD GRN
A F H G W V
**
PHONE JACK
MODEL A152 CONTROL UNIT, P/N 93A152-00 **
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152 (P/N 93A152–00) Wiring Diagram Figure 16
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Description and Operation Page 20 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
CONNECTOR
MICROPHONE
GY BK WH
Z b
*
METER WITH ILLUMINATION
+
BK GRN
RD
N P M
RD BK
WH BK
BK
BK
F
BK
RD WH/BK WH/BK VIO YL OR
C B
P.C. BOARD
5B
TEST SWITCH
S
K
L
T p r
No Nc
t
C
q
BK
ERASE SWITCH
No BK
Nc
BL RD
C GRN
E D
N P
**
M C B K L S T
WH WH/RD WH/GRN BL
P r t q
WH/GY BK BL RD BRN GY
A F H G W V
**
PHONE JACK
MODEL A152-1 CONTROL UNIT, P/N 93A152-01, MODEL A152-2 CONTROL UNIT, P/N 93A152-02, MODEL A152-4 CONTROL UNIT, P/N 93A152-04 *
METER ILLUMINATION A152-1 Pins Z & b (28 V) A152-2 Not Applicable A152-4 Pins Z & Y (5 V)
**
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Units Model A152–1 (P/N 93A152–01), Model A152–2 (P/N 93A152–02), Model A152–4 (P/N 93A152–04) Wiring Diagram Figure 17
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Description and Operation Page 21 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
CONNECTOR
MICROPHONE
METER
+
GY RD
Z b
WH RD
g f
BK GRN
BK
P.C. BOARD
P
J N E S
BK WH
M
E D P N
**
M
F RD
C 5B L
TEST SWITCH K
VI WH/BK
B
WH/BK
No
C L B K
Nc C BK
ERASE SWITCH
WH/GY No BK
C
BK BL RD BRN GY
BL
Nc RD GRN
A F H G W V
**
PHONE JACK
MODEL A152B CONTROL UNIT, P/N 93A152-20, S/N 10000 - 10167 WITHOUT MOD. #1 **
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (P/N 93A152–20) S/N 10000 through 10167 without Mod #1 Wiring Diagram Figure 18
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Description and Operation Page 22 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE WH RD
CONNECTOR
METER WITH ILLUMINATION
GY RD
+
BK GRN
RD
BK
BK
P
J N E S
WH
M
F
BK
RD
5B L K
*
E D P N
**
M
P.C. BOARD
C TEST SWITCH
Z b
VI WH/BK
B
WH/BK
No
C L B K
Nc C BK WH/GY ERASE SWITCH
No
BK BL RD BRN GY
BL
Nc
BK
C
RD GRN
A F H G W V
**
PHONE JACK
MODEL A152B CONTROL UNIT, ALL PART NUMBERS EXCEPT P/N 93A152-20, S/N 10000 - 10167 WITHOUT MOD. #1
*
METER ILLUMINATION 93A152-30 & 93A152-35 Pins Z & b (28 V) 93A152-40 & 93A152-60 Pins Z & Y (5 V) Other Part Numbers - Not Applicable
**
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (All P/N’s except 93A152–20) S/N 10000 through 10167 without Mod #1 Wiring Diagram Figure 19
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Description and Operation Page 23 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE CONNECTOR GY RD
METER
BK GRN
+
WH RD BK
F
WH
M
BK
N
P.C. BOARD
B 5B
E
BK
P WH/BK WH/BK VI
K L
TEST SWITCH
RD C
WH WH/RD
No p
Nc q
C
WH/GR
t
BL
r
ERASE SWITCH
WH/GY No
BK RD BL BRN GY
BL
Nc
BK
C
RD GRN
Z b E D g f M N
**
P B K L C p r t q
A F G H W V
**
PHONE JACK
MODEL A152B CONTROL UNIT, P/N 93A152-20 ONLY, S/N 10000 - 10167 WITHOUT MOD. #1 **
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (P/N 93A152–20 only) S/N 10000 through 10167 without Mod #1 and S/N 10168 and up Wiring Diagram Figure 20
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Description and Operation Page 24 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE
CONNECTOR GY BK
METER WITH ILLUMINATION
+
BK GRN GRN BK
F
RD
WH
M N
BK
E P
5B
B L
BK
BL WH/BK WH/BK
K
P.C. BOARD
VIO RD
C
TEST SWITCH q
WH WH/RD
P No
WH
t
WH/GRN BL
r
Z b
*
E D M N P
**
B K L C P r t q
Nc C WH/GY ERASE SWITCH
No BK
Nc
BK
BL
RD BL BRN GY
RD
C GRN
A F G H W V
PHONE JACK
MODEL A152B CONTROL UNIT, ALL EXCEPT P/N 93A152-20, S/N 10000 - 10167 WITHOUT MOD. #1 *
METER ILLUMINATION 93A152-30 & 93A152-35 Pins Z & b (28 V) 93A152-40 & 93A152-60 Pins Z & Y (5 V) Other Part Numbers - Not Applicable
**
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (All P/N’s except 93A152–20) S/N 10000 through 10167 without Mod # 1 and S/N 10168 and up Wiring Diagram Figure 21
23-70-02
Description and Operation Page 25 Feb. 01/93
**
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE
CONNECTOR
METER
GY BK
+
BK GRN BK
F RD
M E
N
BK
P B L
5B
WH BK
WH WH/BK WH/BK
K
VIO RD
P.C. BOARD
C
WH WH/RD
TEST SWITCH
P q
No
WH/GRN BL
t r
Z b
E D M N
*
P B K L C P r t q
Nc C WH/GY
BK ERASE SWITCH
No BK
Nc
BK
BL
RD BL BRN GY
RD
C BK
A F G H W V
PHONE JACK
MODEL A152B CONTROL UNIT, P/N 93A152-20, P/N 93A152-25, P/N 93A152-50, P/N 93A152-70 S/N 10000 - 10167 WITH MOD. #1 AND MOD #2 *
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (P/N 93A152–20, 93A152–25, 93A152–50, and 93A152–70) with Mod #1 and #2 Wiring Diagram Figure 22
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Description and Operation Page 26 Feb. 01/93
*
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE WH RD
CONNECTOR
METER
GY RD
+
BK GRN
BK
BK WH
P
J N E S
M
BK
RD
C 5B L K
E D P N
*
M
P.C. BOARD
F
TEST SWITCH
Z b
VI WH/BK
B
WH/BK
C L B K
No Nc C
WH/GY
BK ERASE SWITCH
No BK
Nc
BK BL
BL RD BRN GY
RD
C GRN
A F H G W V
PHONE JACK
MODEL A152B CONTROL UNIT, P/N 93A152-20 ONLY, S/N 10000 - 10167 WITHOUT MOD. #1 BUT WITH MOD #2 *
OPTIONAL COLORS FOR SHIELDED PAIRS Pins G & N Red or White Pins H & P Blue or Black
Control Unit, Model A152B (P/N 93A152–20 only) S/N 10000 through 10167 without Mod #1 but with Mod #2, Wiring Diagram Figure 23
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Description and Operation Page 27 Feb. 01/93
*
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
MICROPHONE PREAMPLIFIER PWA, P/N 93A266-01
GRN
CONNECTOR J1 GRN BLK WHT
M N
P
L
p q
WHT/BLK VIO VIO
K C
t r
MIC GND (SHIELD)
A
MIC SIGNAL
B
MIC SUPPLY (+6.2V)
B D
PRE-AMP PWR GND PRE-AMP OUT LOW
C
PRE-AMP OUT HI)
A
PRE-AMP PWR HI)
M K
6 dB ATTENUATION 12 dB ATTENUATION
H
24 dB ATTENUATION
E
ATT. COMMON
CONNECTOR J2 WHT/BLK
B
C
WHT WHT/RED WHT/GRN BLU
MODEL A150 EXTERNAL PREAMPLIFIER MODULE
Model A150 External Preamplifier (P/N 93A150–00) Wiring Diagram Figure 24
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Description and Operation Rev 1 Page 28 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
8. THEORY OF OPERATION The theory of operation given for the Model A100S describes the functionality of the A100S both at the system level and at the PWA level. System level theory of operation describes the general operation of the system as a whole. Refer to the Model A100S Functional Block Diagram given in Figure 25 during the following discussions. The PWA level theory of operation describes the electrical circuitry of the major functional groupings contained on the individual PWAs. Detailed PWA schematic diagrams are provided in Appendix A of this manual.
A. SYSTEM THEORY OF OPERATION The Model A100S SSCVR is composed of three PWAs and a Flash Crash Survivable Store Unit (FCSSU). The three PWAs are the Aircraft Interface PWA, the Audio Processor PWA, and the Store Processor PWA (refer to Figure 25). (1)
Aircraft Interface PWA, P/N 205E0597–00 The Aircraft Interface PWA connects the aircraft wiring to the A100S via its 57–pin connector J1. Power regulation, lightning protection, RF attenuation and discrete signal conditioning functions are performed on this PWA. The A100S operates from either a 115V, 400 Hz ac input or a 27.5V dc input. The input voltage is regulated to furnish +12V, –12V, + 5V, and +18V dc operating power. All regulated voltages are short–circuit protected. The Aircraft Interface PWA also generates a /LOW_LINE signal which is used to power down the unit in the case of a power failure. The Aircraft Interface PWA is mounted to the chassis using five screws with standoffs; its circuitry includes transformer T1 and the input/output 57–pin connector J1. Connections to the Spare PWA slot (J3), the Audio Processor PWA (J4), and the Store Processor PWA (J5) are made via connector J2/P2 which is a 50–pin, printed circuit board style connector that is hard–wired to the Aircraft Interface (ribbon) Cable Assembly (W1). Note: the Spare PWA slot is not used. The Aircraft Interface PWA measures 4.4 by 7.1 inches.
(2)
Audio Processor PWA, P/N 205E0598–00 The Audio Processor PWA accepts four channels of cockpit audio and converts the audio to a digital byte oriented format suitable for storage in the FCSSU solid–state memory. The four audio inputs are conditioned, amplified, and equalized as necessary. The resulting signals are converted to digital pulse code modulation (PCM). The PCM signals are passed to the Store Processor PWA via a FIFO (First–In–First–Out) memory. The process is reversed for playback. The Audio Processor PWA connects to the other PWAs when its 64–pin edge connector (P1) mates to connector J4 of the Aircraft Interface Cable Assembly (W1). The dimensions of the Audio Processor PWA are 4.4 by 7.1 inches.
(3)
Store Processor PWA, P/N 205E0601–00, 205E1027–00 The Store Processor PWA, using specially designed algorithms, encodes the data and routes it to the FCSSU for storage. In addition to data encoding, the Store Processor PWA provides functional controls for bulk erase, test and playback. The Store Processor PWA measures 4.8 by 5.3 inches and is mounted to the side of the FCSSU assembly using four screws. When mounted, it electrically connects to the other PWAs via a 6.5–inch, hard–wired ribbon cable assembly (W2) fitted with a 26–pin plug (P5) that mates to connector J5 of the Aircraft Interface Cable Assembly W1. It electrically connects to the FCSSU assembly via a 50–pin connector, designated J2.
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(4)
Flash Crash Survivable Store Unit (FCSSU), P/N 253E0348–03, 253E0660–00 The hardened memory array, comprised of devices known as CMOS Flash Memory, is electrically erasable and programmable. The nonvolatile memory is protected within a hardened, insulated metal housing to ensure survivability in the event of a crash.
FROM CONNECTOR P1 VIA AIRCRAFT WIRING
/FAULT
PUSH_TO_TEST
TEST
BIAS JUMPER IN
/LOW_LINE
ERASE “A”
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
/RECORD ERASE
CHANNEL 1 (LO)
CHANNEL 1 (LO)
CHANNEL 1 (HI)
CHANNEL 1 (HI) CHANNEL 2 (LO)
CHANNEL 2 (LO)
CHANNEL 2 (HI)
CHANNEL 2 (HI)
CHANNEL 3 (LO) CHANNEL 3 (LO) CHANNEL 3 (HI)
AIRCRAFT INTERFACE PWA P/N 205E0597–00
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
P5/W2 (CABLE W2
HARD WIRED TO STORE PROCESSOR
PWA; CONNECTS TO J5 OF AIRCRAFT INTERĆ FACE CABLE ASSEMBLY W1)
PLAYBACK / MONITOR EDGE– TEST CONNECTOR J6
AUDIO PROCESSOR PWA P/N 205E0598–00
J2/P2
DIGITAL AUDIO LINK
/OE
STORE PROCESSOR PWA (SEE NOTE)
/WE SEL (7..0) 8 ADR (20..0) 21 D (7..0)
CHANNEL 3 (HI) CHANNEL 4 (LO) CHANNEL 4 (HI)
CHANNEL 4 (LO) CHANNEL 4 (HI)
8 AIRCRAFT INTERFACE CABLE CONNECTOR J4
COMBINED_AUDIO
AIRCRAFT INTERFACE CABLE CONNECTOR J5
FLASH CRASH SURVIVABLE STORE UNIT (FCSSU) ASSEMBLY (SEE NOTE)
+5V
115 VAC IN (H)
+5V
+12V, 5%
AC COMMON (C)
+12V
CHASSIS GROUND
+27.5 VDC INPUT
–12V
CHASSIS GROUND
CHASSIS GROUND COMBINED_AUDIO
TO AIRCRAFT WIRING VIA CONNECTOR P1 BIAS JUMPER OUT ERASE “C” AUDIO OUT – LO AUDIO OUT – HI
J71 2
TO FRONT PANEL PHONE JACK
NOTES 1.
INDICATOR + INDICATOR –
PRE–AMP PWR GROUND PRE–AMP PWR +18VDC REG 2.
INITIAL MODEL A100S UNITS WERE EQUIPPED WITH A FCSSU, P/N 253E0348-03, WHICH USES 2-MBIT FLASH MEMORY CHIPS, AND A STORE PROCESSOR PWA, P/N 205E0601-00, DESIGNED TO INTERFACE WITH IT. BEGINNING 12/93, A NEW FCSSU, P/N 253E0660-00, WHICH USES 8-MBIT FLASH MEMORY CHIPS, AND A REDESIGNED STORE PROCESSOR PWA, P/N 205E1027-00, WERE MANUFACTURED. THESE ASSEMBLIES WERE FIRST INSTALLED IN UNIT SERIAL NUMBER 311. BEGINNING 03/96, TWO NEW FCSSUs, P/N 253E1290-00 AND 253E1293-00 WERE MANUFACTURED. THE NEW FCSSUs PROVIDE BETTER FIRE PROTECTION BEGINNING 04/96, A NEW FCSSU, P/N 253E1293-00, WHICH USES TITANIUM, REDUCING THE WEIGHT OF THE FCSSU. REFER TO FIGURE A1 IN APPENDIX A OF THIS MANUAL FOR DETAILED SYSTEM WIRING DIAGRAM.
Model A100S Functional Block Diagram Figure 25
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B. PWA THEORY OF OPERATION The A100S PWA theory of operation is presented as follows: Aircraft Interface PWA, Audio Processor PWA, and Store Processor PWA. The control units and Microphone Preamplifier PWAs follow. Detailed schematic diagrams of each A100S PWA and control unit Microphone Preamplifier PWA are given in Appendix A at the rear of this manual. Also, refer to the detail system wiring diagram, given in Figure A1. (1)
Aircraft Interface PWA, P/N 205E0597–XX (See Figure A2) The Aircraft Interface PWA connects the aircraft wiring to the A100S using a 57–pin DPX style connector designated J1. Power regulation, lightning protection, RF attenuation and discrete signal conditioning functions are performed on this PWA. (a)
DC Regulator; U2 The A100S operates from either 115V, 400 Hz ac power or 27.5V dc power (refer to Figure 26). Power circuits provide regulated +5V, +12V and –12V dc outputs. The –12V output is used to power a DC–to–DC “Up” Converter, U3, which generates +18V dc power for the A100S Control Unit. All regulated voltages are short–circuit protected. The unregulated 27.5V dc input is also used as the /LOW_LINE signal which is continually monitored to detect a power failure and thereby provide an early warning to allow circuitry to be properly powered down. /LOW_LINE TP4
27.5 VDC 115 VAC (H)
+5 VDC
TP2
+12 VDC
REGULATOR TP3
115 VAC (C)
–12 VDC
DISTRIBUTED TO OTHER PWAs TO PROVIDE EARLY WARNING OF A POWER FAILURE. REGULATED POWER DISTRIBUTED THROUGH–OUT A100S
U2 DC–DC “UP” CONVERTER
+18VDC
TO CONTROL UNIT
U3
CHANNEL 1 H/L CHANNEL 2 H/L CHANNEL 3 H/L
EMI FILTER 2 L1 – L3 C35 – C38
2
AUDIO CHANNEL CONDITIONING
2
CHANNEL 4 H/L
2
BIAS JUMPER IN
CR1 – CR8
PUSH_TO_TEST
TO AUDIO PROCESSOR PWA P/N 205E0597–XX
CHANNEL 3 H/L CHANNEL 4 H/L
TO AUDIO PROCESSOR PWA P/N 205E0597–XX
/RECORD ERASE TEST
DISCRETE SIGNAL CONDITIONER
ERASE “A”
CHANNEL 1 H/L CHANNEL 2 H/L
U4
COMBINED_AUDIO AUDIO FAULT DETECTOR
/FAULT TO FRONT PANEL PHONE JACK
AUDIO OUT (H) AUDIO OUT (L) 27.5 VDC
/NO FAULT U1, U4 INDICATOR DRIVER
INDICATOR +
E3
Q1
TO 1.0 mA CONTROL UNIT
Aircraft Interface PWA Functional Block Diagram Figure 26
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(b)
Audio Conditioner; CR1 – CR8 The four audio inputs are lightning protected by CR1 – CR8. The audio channels are routed to the Audio Processor PWA for conversion to a digital byte oriented format and subsequent storage, via the Store Processor PWA, in the crash protected solid– state memory.
(c)
Discrete Signal Conditioner; U4 Three discrete inputs; BIAS JUMPER IN, ERASE “A”, and PUSH_TO _TEST are lightning protected and converted to drive HCMOS type loads by U4 and associated circuitry. After conversion, the “BIAS JUMPER IN” signal is designated as /RECORD and is used to disable the record function when playback of the data is required. Signal /RECORD will be pulled up to +5V with no connection made to the BIAS JUMPER IN line. When the BIAS JUMPER IN line is connected to the BIAS JUMPER OUT line, /RECORD will be driven low. The Erase “A” signal is used to initiate the Bulk Erase function. When ERASE “A” is left floating, ERASE is driven low. When ERASE “A” is connected to ERASE “C” (Erase button on Control Unit depressed), ERASE will be pulled up to +5V. The Push_To_Test signal is used to activate the A100S built–in–test circuitry and enables the Audio Fault Detector, U1 and U4.
(d)
Audio Fault Detector; U1, U4 The audio fault detector is used to determine the status of the COMBINED_AUDIO signal and to generate a 1.0 milliampere signal to drive the control unit fault indicator. The Test Tone signal at COMBINED_AUDIO is attenuated by R1 and R2. This signal is then buffered and band–pass filtered (640 Hz) by U1 and associated circuitry. The filtered signal is then rectified and filtered by CR12 and C14 for comparison to the 2.5V reference by U4. This signal, /NO FAULT, turns on the current source for +INDICATOR. CR17 and CR18 provide level shifting and over–voltage protection for the comparator, U4.
(e)
Indicator Driver; Q1 The test indicator output (+INDICATOR) circuitry provides a 1 milliampere drive current for the standard Control Unit meter or a 28V incandescent lamp. This signal is present if the following conditions are met: /FAULT in the non–Fault state TEST active (PUSH_TO_TEST driven Low) Test Tone present at AUDIO OUT–HI
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(2)
Audio Processor PWA; P/N 205E0598–XX (See Figure A3) The primary function of the Audio Processor PWA is to digitize the four audio signals received from the Aircraft Interface PWA and to interface with the Store Processor PWA. In doing so, the Audio Processor PWA accepts four channels of cockpit audio and then converts the audio to a digital byte oriented format suitable for storage in the crash protected solid–state memory. Refer to Figure 27 during the following discussion. The Audio Processor PWA can be viewed as a series of conversion circuits which are enacted upon the four channels of audio signals coming from the cockpit. The conversions can be divided into two functional groupings: an analog section and a digital section. (a)
Analog Section The analog section consists of record circuits, playback circuits, and test tone circuits. 1)
Record Circuits; U6, U9, U10 The four audio channel inputs (CHANNEL_#_HI and CHANNEL_#_LO) are applied to separate signal transformers (T1, T2. T3, and T4) to provide an ungrounded differential input. The voltage ratio of the transformer is 1:1 and it is connected to invert the input signal which corrects for the inversion in the record shaping circuit. The transformer secondaries are terminated using a 10k ohm level control (trimmer) potentiometer as follows: T1/R1, T2/R3, T3/R2, and T4/R4. Each potentiometer is used to adjust the reference level for its respective channel. The adjusted output signals of the level control potentiometers and the test tone signals are applied to the input buffers. The buffers provide a non–inverting gain of 7.7. This gain allows the input level of each channel to be adjusted from 0.1 to 1V rms while providing a 0.5V rms signal level to the record signal shaping input. The input buffers also provide an inverting gain of one to the test tone signals. The record signal shaping circuits provide a bridged, twin tee notch for each channel. The notch is centered at 1 kHz and has an attenuation of 4 dB. Additionally, the shaping circuits for Channels 1, 2, and 3 contain high–pass filter circuits which peak the signals by 3.5 dB (nominal) at 3.5 kHz. This peaking is provided to compensate for the frequency response of the encoder/decoder filter. The record signal shaping circuits provide an output signal level of 0.315V rms at 1 kHz to the analog input of the encoder/decoders.
2)
Playback Circuits; U5, U4, U14 The encoder/decoders analog output provides a signal level of 1V rms at the output of the playback signal shaping circuits. The playback signal shaping circuits provide the inverse of the notch in the record shaping circuit.
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ANALOG SECTION PLAYBACK MONITOR J6 USED WITH AUDIO MONITOR ADAPTER (AMA/1) FOR TEST PURPOSES
AUDIO 1
AREA OUT
AUDIO 2
VOICE 1 OUT
AUDIO 3
SIGNAL SHAPING
AUDIO 4
AREA OUT
VOICE 2 OUT
COMBINED AUDIO U14
VOICE 3 OUT AREA IN
P4
COMBINED AUDIO
OUTPUT BUFFER
10k-OHM LEVEL CONTROL POTENTIOMETERS TO AIRCRAFT INTERFACE PWA
T1
CH 1 IN (LO/HI) TRANSFER AND LEVEL CONTROL CIRCUITS
CH 2 IN (LO/HI) CH 3 IN (LO/HI)
T2 T3
U5, U4, Q1, Q2
VOICE 1 OUT VOICE 2 OUT VOICE 3 OUT
R1 R3 R2
INPUT BUFFER
SIGNAL SHAPING
R4
CH 4 IN (LO/HI) T4
U6
U9, U10
VOICE 1 IN VOICE 2 IN VOICE 3 IN
TEST TONE 1 TEST TONE 2 TEST TONE 3 TEST TONE 4
TEST TONE SECTION
SWITCH
BUFFER
U7
U15
4
LOW PASS FILTER
LEVEL CONTROL
CR3, CR6
TEST TONE SQ WV (640HZ) TEST ENABLE
TEST
TEST
ERASE /RECORD TO AIRCRAFT INTERFACE PWA
ERASE /RECORD
+12V
+12V
–12V
–12V
+5V CHASSIS GROUND
+5V CHASSIS GROUND
Audio Processor PWA, PN 205E0598–00, Functional Block Diagram Figure 27 (sheet 1 of 2)
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DIGITAL SECTION
AREA CLK 12K FS 12K RFS 12K XFS
12K ENCODER/ DECODER
PCM–8 AREA IN/OUT
2
U25 PCM–8 VOICE 1 IN/OUT
12K FS
COMPUTATIONAL PROCESSOR (TRANSMIT & RECEIVE)
PLAYBACK DATA
U20, U21
9
ADPCM–2 IN/OUT
BYTE PACKETIZER
PCM–8 VOICE 2 IN/OUT
2
/RD
RECORD DATA
2 8K ENCODER/ DECODER
9
READ/ WRITE FIFO
CONTROL SIGNALS
COMPUTATIONAL PROCESSOR
DATA 9
/WRT
TO STORE PROCESSOR PWA
/SYSRST
PCM–8 VOICE 3 IN/OUT
2 U22, U23, U24
U17, U18, U19
AREA CLK
U11, U13
U12, U16
12K FS
MASTER CLK 8K FS
8K FS
VOICE CLK
/SYSRST 12.288 MHZ OSCILLATOR
TEST TIMING AND CONTROL
ERASE
U8
/RECORD U1, U2, U13
TEST TONE SQ WV (640HZ) TEST ENABLE
+12V
+12V
POWER DECOUPLING AND –5V REGULATOR
+5V
–12V
DISTRIBUTED WITHIN AUDIO PROCESSOR
–5V
+5V CHASSIS GROUND
–12V
U3
Audio Processor PWA, PN 205E0598–00, Functional Block Diagram Figure 27 (sheet 2 of 2)
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The output signals of the playback shaping circuits are connected through a 20 ohm resistor to the PLAYBACK/MONITOR connector, J6, for test and reproduction purposes. The output signals are also summed in the output buffer to provide the COMBINED_AUDIO output signal. The gain of the output buffer is set to provide a 1.45V rms output signal for each channel when the channel is driven with the reference signal. The COMBINED_AUDIO output can provide a maximum output signal of 8.03 volts peak into 622 ohms, which is the sum of the specified output load of 600 ohms and the 22 ohms on the Aircraft Interface Card. The COMBINED_AUDIO output signal is connected to the I/O connector, P4, and to the PLAYBACK/MONITOR connector, J6. A short circuit at the COMBINED_ AUDIO output will cause no damage to the Audio Processor PWA. 3)
Test Tone Circuits; U7, U15 The square wave test tone signal from the LCA, U13, is applied to a comparator in the test tone level control circuit. The output of the comparator drives two back–to–back Zener diodes to produce a 13.6V peak–to–peak signal. This signal is divided, filtered, and buffered to provide a nominal 0.34V rms fundamental signal to the test tone switch. The test tone switch, which is controlled by the test tone enable signals (/TT_EN_x), connects the test tone to one channel at a time. The amplitude level of the test tone signal at the COMBINED_AUDIO output is 1.0V rms for the voice channels and 1.2V rms for the area channel.
(b)
Digital Section The digital section consists of an encoding/decoding section, a computational section, a timing and sequencing section, an input/output section, and a programmable control section. 1)
Encoding/Decoding Section; U22 – U25 The encoder/decoder transmits encoding (record path) and receives decoding (playback path) at a sample rate of up to 16 kHz. Anti–aliasing and interpolation filters are also included in the device. The encoding produces an 8–bit serial PCM stream. The 8–bit word appears at the sampling rate which is synchronized by the FSX signal. The bit rate is determined by CLK R/X which also determines the bandwidth of the anti–aliasing and interpolation filters. The sign bit is transmitted first followed by seven magnitude bits in decreasing order of significance. The receive decoding operates in an analogous manner. The audio processor has four encoder/decoder devices, U22, U23, U24 and U25. The Pilot, Co–Pilot and Spare channels are collectively called voice channels and are processed via U22, U23 and U24. These encoder/decoders are all wired for the same sampling rate and bit rate. The Area Microphone channel is processed by U25 and has a higher sampling and bit rate. The PCM signals which are generated and received by the encoder/decoder are processed by the computational processors.
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2)
Computational Processors; U17 – U21 The Audio Processor PWA uses computational processors as the engine to reduce the required bit rate of the recorded data. These devices are mask ROM programmed specifically for the conversion of PCM data to and from ADPCM data. The processor uses two bit encoding. The master clock for the processor is 12.288 MHz (U8). This crystal controlled clock is also used to derive the bit rate clocks ACLK and VCLK (see PLD2). For the voice channels a single processor can process both the record and playback data for one channel. These processors are U17, U18, and U19. The Area Microphone channel requires a separate processor for the record and playback functions. The record function encoding is provided by U20 and the playback encoding is provided by U21. The XOUT pin of the four encoders which provide record function encoding are connected together to form the XADPCM single bit tri–state bus. This bus is input to the Logic Configurable Array (LCA) for conversion to byte wide packets. The bus is actively driven by each processor in response to the FSX signals which the LCA provides in a time multiplexed fashion. Similarly for playback, the LCA provides a RADPCM bus and FSR signals. Figure 28 illustrates the relationship between key processor signals and the corresponding encoder/decoder and audio processor signals.
3)
Timing and Sequencing Section; U11, U13 The timing and sequencing of the data flow on the audio processor is controlled by a Xilinx 3030 LCA (U13). The program for the LCA is contained in a special serial PROM (U11). This program is loaded at system reset time (/SYSRST) under the control of PLD1 (see PLD1). The logic of the LCA program can be examined in three sections, transmit, receive and test tone. A test mode is available which will allow complete operation of the Audio Processor circuits without interface to the Store Processor. — Transmit Section After system reset the transmit section is in continuous synchronous operation with fixed timing. This timing consists of the repetition of a one millisecond cycle. During one cycle the two bit ADPCM data from 24 voice samples (8 each from the 3 voice channels) and 12 area microphone samples are packed into a 9 byte packet of parallel data. This packet size represents the smallest number of whole bytes for which all the channels are sampled over an equal period (i.e. one millisecond). Each byte is written to the record FIFO as it is accumulated and the REC_SYNC flag is raised during the write of the first byte in the packet.
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Encoder/Decoder Signal
AP Signal
DS2165 Signal
Description
Clk R/X U3,U8,U9
VCLK
CLKX,CLKY U1,U4,U5
2.048 MHz square wave
Clk R/X U10
ACLK
ClKX U6 CLKY U7
3.072 MHz square wave
FSX U3 FSX U8 FSX U9
XV1_FS XV2_FS XV3_FS
FSX U1 FSX U4 FSX U5
8 kHz Pulse, 488 ns wide
FSX U10
XA_FS
FSX U6
12 kHz Pulse, 325 ns wide
FSR U3 FSR U8 FSR U9
RV1_FS RV2_FS RV3_FS
FSR U1 FSR U4 FSR U5
8 kHz Pulse, 488 ns wide
FSR U10
RA_FS
FSR U7
12 kHz Pulse, 325 ns wide
PCM OUT U3 PCM OUT U8 PCM OUT U9
XV1_PCM XV2_PCM XV3_PCM
XIN U1 XIN U4 XIN U5
2.048 MHz 8 bit PCM data
PCM OUT U10
XA_PCM
XIN U6
3.072 MHz 8 bit PCM data
PCM IN U3 PCM IN U8 PCM IN U9
RV1_PCM RV2_PCM RV3_PCM
YOUT U1 YOUT U4 YOUT U5
2.048 MHz 8 bit PCM data
PCM IN U10
RA_PCM
YOUT U7
3.072 MHz 8 bit PCM data
XADPCM
XOUT XOUT XOUT XOUT
Dual rate 2 bit PCM data (tri–state bus)
RADPCM
YIN U1 YIN U4 YIN U5 YIN U7
U1 U4 U5 U6
Dual rate 2 bit PCM data
Computational Processor Signal Descriptions Figure 28 The generation of the timing is based on the 3.072 MHz ACLK and the 2.048 MHz VCLK being synchronous with an exact three halves relationship (see PLD2). The ACLK is divided by 256 to provide 12 kHz time slots for the sampling of the area microphone channel. A three stage Johnson counter, clocked at twice this rate, provides time slots for sampling the three voice channels which do not interfere with the area channel slots.
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The individual voice channels are sampled at 8 kHz, which is consistent with the three halves relationship to the 12 kHz sampled area channel. Since VCLK is synchronous to ACLK, the clocking edges of VCLK are fixed in relation to the voice channel sampling slots. The rising edge of each sampling slot causes the generation of the appropriate sample pulse (FSX pulse) followed by two data clocking pulses. The sample pulses go to the corresponding encoder/decoders and ADPCM processors which then output data on the XADPCM bus. The clocking pulses shift this data into a serial to parallel shift register. When four samples (8 bits) have been accumulated in the shift register, the contents are written to the record FIFO. After nine bytes have been written to the FIFO the cycle is repeated. — Receive Section The receive section timing is similar to the transmit section timing except that operation is inhibited until the playback FIFO is half full and the cycles are synchronized to the incoming PLAY_SYNC signal. Synchronization is achieved by resetting the counters which control the 1 ms cycle if the first playback FIFO read of the cycle does not contain a PLAY_SYNC signal. In normal operation the first read after the playback FIFO is half full should contain the sync signal and no resynchronization should be required thereafter. The playback FIFO should remain about half full with slight variations due to the Store Processor operations. This half–full condition represents a playback delay of approximately 57 ms. The timing of the receive and transmit sections are independent of one another. — Test Tone Section The test tone section produces a 640 Hz square wave along with individual channel enables so that the tone may be added to the channels in response to the test signal. The 640 Hz tone is produced from a divide by 300 chain clocked by 192 kHz. The 192 kHz clock is a byproduct of the receive and transmit sections timing. The 640 Hz signal is further divided by 320 to produce 2 Hz. The 2 Hz signal drives a 2–bit counter which is decoded into four test–tone enable signals. These enable signals are active low for 0.5 seconds each. The 2–bit counter and the decoder are enabled by the rising edge the test signal. The individual channel enables and the test tone signal will persist while the test signal is present, or for 2.5 seconds which ever is longer. 4)
Input /Output Section; U12, U16 The Record FIFO (U16) and the Playback FIFO (U12) are 1K X 9 bit First In First Out memories. The write side of the Record FIFO and the read side of the Playback FIFO are controlled by the audio processor. Conversely the read side of the Record FIFO and the write side of the Playback FIFO are controlled by the Store Processor.
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Data bits 0–7 contain the packed audio data while data bit 8 contains the packet sync information. The output of the Record FIFO and the input of the Playback FIFO are connected together to form the Digital Audio Data bus (DAD 0–8). The input of the Record FIFO and the output of the Playback FIFO are separate. The Record FIFO input comes from the LCA (REC_DATA 0–7 and REC_SYNC). The Playback FIFO output is a LCA input (PLAY_DATA 0–7 and PLAY_SYNC). 5)
Programmable Control; U1, U2 — PLD1 The Programmable Logic Device 1 (PLD1), U1, is responsible for two functions. One is the robust resetting of the LCA, U13, in response to system reset (/SYSRST). This reset initiates a load of the LCA program from the serial PROM U11. Once the loading begins the LCA controls the load clock to the serial PROM. Upon completion of the load the LCA asserts the DONE signal. The initialization and loading process takes approximately 150 ms. The other function is the BITE monitoring of FIFO overflow which will also cause a robust LCA reset. The reset sequence proceeds as follows. The ADPCM processor and FIFO reset signal, /RESET, is held low while the input /SYSRST is active low. The rising edge of /SYSRST is synchronized to the 128 kHz clock (see PLD2). A three stage sequence of flip–flops then produce two 7.8 microsecond wide pulses separated by 7.8 microseconds. This pulse sequence is XRST which is connected to the /OE of U14 which is the LCA serial programming PROM. The signal is also used to pull down the open drain connection to the LCA Done pin. The inverse /XRST is connected to the LCA /Reset pin. This restart sequence is considered to be more robust than a simple rising edge reset signal. As part of the BITE function the PLD1 also monitors the Playback FIFO full condition. If the /PLAYFIFO_FULL pin goes active while /SYSRST is inactive a restart sequence is initiated. This condition may occur if the receive section of the LCA is not operating properly. After the /XRST pulse sequence is completed, signal /RESET is held low until the Done pin is pulled high by the LCA. This ensures a /RESET period of greater than 1 millisecond for the ADPCM processors. Another BITE feature is the monitoring of the Record FIFO full condition. If the /RECFIFO_FULL pin goes active while /SYSRST and ERASE signals are inactive then the open drain /NFG (Not Functioning Great) signal is pulled down. This causes a system fault indication. This condition may occur if the Store Processor is not operating properly. — PLD2 The Programmable Logic Device 2 (PLD2), U2, provides the clocks for the audio processor based upon the 12.288 MHz crystal controlled oscillator clock (MCLKI). MCLKI is first divided by two to produce a 6.144 MHz clock. This clock is divided by three to produce the 3.072 MHz ACLK and is divided by two to produce the 2.048 MHz VCLK. VCLK is divided by 16 to produce 128 kHz.
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(3)
Store Processor PWA; P/N 205E0601–01, 205E1027–00 (See Figures A4 and A5) The Store Processor PWA, using microprocessor U22, interfaces the flash memory to the Audio Processor PWA. In order to provide thirty minutes of continuous recording, the Store Processor aligns the solid–state memory array like a non–volatile circular buffer, which the Store Processor writes to at the head of the circular buffer and erases at the end of the buffer. The Store Processor can be functionally divided into a Control Management Section and an Interface Section. (a)
Control Management Section The control management activities consist of steering the inputs and outputs of its three interfaces (protected–memory, Aircraft Interface, and Audio Processor), as well as providing internal and external performance monitoring. 1)
Microprocessor; U22 The Store Processor uses a synchronous state mP, U22, whose timing is derived from a crystal controlled oscillator, Y1, which outputs a square wave at 32 MHz. This signal is named CLKIN and drives only the microprocessor’s clock input. The mP internally divides CLKIN by two yielding an output clock named CLKOUT of 16 MHz. All of the mP’s internal timing is synchronized to CLKOUT.
ADDRESS LATCHES
CLOCK
READ ONLY MEMORY
Y1
VOLATILE READ/WRITE MEMORY U17, U21
U5
U10, U14
NON–VOLATILE READ/WRITE MEMORY U24
ADDRESS BUS MICROPROCESSOR DATA BUS CONTROL BUS
U22 /RESET CONTROL LOGIC /LOW_LINE
POWER RESET AND WATCHDOG TIMER
U4 U20, U12
AUDIO PROCESSOR AND AIRCRAFT INTERFACE
2 /PWR_FAIL
VCC (+5V)
4 /FAULT
U8, U9, U11, U13, U15, U18
U6, U7, U12, U23
U2 /SYSRST
FLASH MEMORY INTERFACE
8
2
DATA CTRL SYNC STATUS TO AUDIO PROCESSOR PWA
10 CTRL
21
8 DATA
ADR
VCC VPP
TO STORE PROCESSOR PWA
+5V +12V
POWER MANAGEMENT
VEE (+5V) VPP (+12V)
U16, U3
AIRCRAFT INTERFACE
Store Processor PWA Functional Block Diagram Figure 29
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2)
Address Latches; U10, U14 The mP’s 20–bit address bus is multiplexed with other signals and must be externally demultiplexed to generate a system address bus which remains stable throughout a bus cycle. Address latches, U10 and U14, are used to demultiplex the interface signals to generate the local address bus (ADR<19..0>). The mP’s Address Latch Enable (ALE) strobe clocks the latches.
3)
Power Reset and Watchdog Timer; U2 The resetting of the mP and its support circuitry is managed by a microprocessor supervisory circuit, U2. It provides an active low /RESET output which is directly connected to the mP’s /RESET input. The minimum duration of the reset pulse is 35 ms. U2 initiates a /RESET signal when it detects either: 1) the +5 Vdc power supply going out of limits or 2) a watch–dog time out. Upon powering up, /RESET remains low for 35 to 70 ms after Vcc raises above 4.75 volts. On powering down, signal /RESET goes low whenever Vcc falls below 4.5 volts. The reset threshold comparators have approximately 50 mV of hysteresis. The Watch–dog Timer (WDT) circuit forces a RESET pulse when no retrigger pulse occurs at its WDI pin within a time–out period of 1.0 second. The Store Processor causes the watch–dog timer to be retriggered every “read from” or “write to” the Audio Processor. This is accomplished by pulsing the watch–dog timer’s WDI pin with the Audio Processor’s chip select strobe, /PCS4.
4)
Control Logic; U20, U4 The Control Logic is composed of two programmable logic devices, U20 and U4, as well as a 13 nanosecond delay device, U19. This section generates the control signals that are used to read and write the data from the protected (flash) store memory and the Audio Processor PWA.
5)
Power Management; U16, U3 Power management circuitry performs three functions; power failure detection, EEPROM power, and protected (flash) memory power. Power failure detection is provided by an analog voltage sourced by the power supply section of the Aircraft Interface PWA. The signal, designated LOW_LINE, is an analog to the unregulated 28 Vdc (nominal) input to the power supply’s DC/DC converters. At power down, the /LOW_LINE signal begins to sag before the +5 and/or +12 volt supplies. In the Store Processor PWA, the /LOW_LINE signal is attenuated and compared to a 1.3 volt band–gap reference contained within U2. The comparator output, /PWR_FAIL, goes low to indicate power loss. This logic signal is polled by the mP every time it reads the Audio Processor input port. Signal / PWR_FAIL also directly controls the EEPROM power circuit.
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EEPROM power, Vee, is provided because of the need to save memory pointers and other state variables at power down. In order to guarantee accurate saving of state records, the +5 Vdc supply to non–volatile read/write memory, U24, must remain within specifications for 10.1 ms after the mP writes the last byte to be saved. Since the power supply cannot maintain Vcc to the whole PWA for that long of a period, an isolated +5 Vdc, Vee, is generated by U16. Protected (flash) memory requires a programming voltage, Vpp, of +12 Vdc +5%. The +12 Vdc provided by the Aircraft Interface PWA can only be regulated to +10%; consequently, a more tightly regulated voltage is provided by U3, which is located on the Store Processor PWA. 6)
Local Memory; U17, U21, U24 Local Memory (non–crash protected memory) consists of: Read Only Memory, U5; Volatile Read/Write Memory (RAM) U17 and U21; and Non–Volatile Memory, U24. This circuitry performs two functions; it is used as a buffer between the Audio Processor and the crash–protected memory, and to retain the memory pointers and other state variables at power down.
(b)
Interface Section The interface section consists of three interfaces; Aircraft Interface PWA, Audio Processor PWA, and the crash protected (flash) memory. Additionally, a local memory sub–section is used in the transfer of data from the Audio Processor to the protected– memory. 1)
Aircraft Interface to Store Processor Interface; U23 and U6 The Store Processor interface to the Aircraft Interface PWA consists of four data lines: TEST, ERASE, /RECORD, and /LOW_LINE. Refer to Page 32 for signal definitions.
2)
Audio Processor Interface; U6, U7 and U12 The logical interface to the Audio Processor consists of: a 9–bit bi–directional bus (data and sync); a 2–bit status bus (FIFO half–full and empty); and a 2–bit control bus (write and read strobes). The read and write control strobes which the Store Processor outputs to the Audio Processor are generated in PLD’s, U20 and U4. The physical interface to the Audio Processor consists of two ports, one read– only, the other write–only. Both are accessed whenever the mP asserts /PCS4. The input port is implemented with a pair of octal 3–state buffers (U6 and U7), which drive the mP’s data bus whenever /PCS4 and /RD are asserted. The port supplies data and status information from the Audio Processor (11 bits). Additionally, it supplies aircraft and recorder status information (5 bits).
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The output port is implemented with a 9–bit transparent 3–state latch, U12. The latch is transparent when /WR and /PCS4 are asserted. It latches data on the rising edge of /WR. The latch’s output are enabled while the latches are transparent, but remain enabled for an additional period after the rising edge of /WR to meet the Audio Processor’s write hold timing requirements. 3)
Crash Protected (Flash) Memory Interface; U8, U9, U11, U13, U15, U18 The performance requirements of the Store Processor with regard to concurrently recording audio data and erasing memory chips in preparation for subsequent recording are such that two page registers are required. One page register selects the device and area to which data is currently being written. The other page register selects the device and area currently being erased. The physical interface to the crash protected memory consists of : an 8–bit bi– directional data bus (FDAT<7..0>); a 3–bit (decoded to 8 lines) module select bus (SEL<7..0>); a 21–bit address bus (FADR<20..0>); and a 2–bit control bus (/OE, /WE). The data bus is buffered through an 8–bit bus transceiver, U18. The direction of the transceivers is controlled by the mP’s /RD strobe. The outputs of the transceivers are enabled by PLD U4. During a read from flash memory, the outputs of the transceivers are enabled while /MCSO and /RD are asserted by the mP. During a write to flash memory, the transceiver outputs are enabled while / MCSO and /WR are asserted by the mP, but they remain enabled for a period after the rising edge of /WR in order to meet the flash memory’s write hold timing requirement. The 15 least significant bits of the flash memory address bus (FADR<14..0>) are derived directly from the mP’s address bus. A pair of 8–bit, 3–state transparent latches, U10 and U14, are clocked by the mP’s ALE strobe to latch AD<15..0> on each address cycle. The 6 most significant bits of the flash memory address bus (FADR<20...15>) and the 8 module select lines (SEL<7...0>) are derived from a pair of 10–bit page registers, U8 and U9. The registers capture the 10 least significant bits of the mP’s data bus when it performs a write while asserting /PCSO. The registers’ clocks and output enables are generated by PLD U4. The level on ADR<1> determines which register is clocked. One of the two page registers’ outputs are enabled during any access to flash memory. The level of ADR<16> determines which register’s outputs are enabled. The 6 least significant output bits of the page registers become FADR<20...15> and drive the flash memory array directly. The next three most significant bits (FADR<23..21>) are decoded by a 1–0f–8 decoder, U11, generating the module select bus (SEL<7..0>).
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(4)
Control Unit The Control Unit (see Figure 7 and Figure 30) contains the TEST switch, bulk ERASE switch, indicating meter, headset jack, and a Microphone Preamplifier PWA and includes the area microphone (internally or externally mounted). The A151 and A151B Control Units connect to an externally mounted microphone. The A151 and A152 Control Units use Microphone Preamplifier PWA, P/N 93A263–02 which operates with a dynamic microphone while the A151B and A152B Control Units use Microphone Preamplifier PWA, P/N 93A266–01 which operates with a condenser microphone (refer to Appendix A for the schematic diagrams). The TEST switch and indicating meter provide the capability to test the four channels and the headset jack provides the means to monitor the playback of all four recorded channels. The bulk ERASE switch is used to erase the entire solid–state memory (FCSSU) after a routine flight, and will work only when: 1) the landing gear is down, 2) the weight of the plane is resting on the landing gear, and 3) the parking brake is engaged. To prevent accidental erasures, a time–delay circuit makes it necessary to hold the switch down for more than two seconds to start the erasure process.
TEST SWITCH
ERASE SWITCH MICROPHONE
METER
MICROPHONE PREAMPLIFIER PWA
Exploded View of Control Unit Assembly, A152, A152B Figure 30
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(a)
Microphone Preamplifier PWA, P/N 93A263–(XX) This PWA (refer to Figure 31) is used in Model A151 and A152 Control Units which function with a dynamic type microphone. The preamplifier (see the schematic diagram given in Figure A6 in Appendix A) receives the microphone low–level input signal at pins N and P. The low–level audio signal is amplified by Q1, gain adjusted by potentiometer R9, and further amplified by Q2. Pin selectable audio gain attenuation, in 6 dB steps from 0 to 24 dB, is provided via resistors R17, R29, R30, R32, and R31. A jumper/strap is required in the aircraft connector between pin q and the appropriate attenuation pin (s): p (6 db), r (12 db), or t (24 db). For example, a gain attenuation of 18 dB is enabled by connecting a jumper between pin q and p (6 db) and also between pin q and r (12 db). Transistor Q3 is another amplification stage and Q4 is an emitter–follower used to provide a low–impedance output at pin L (OUT), which is fed through the aircraft wiring to the Aircraft Interface PWA in the Model A100S recorder. Transistors Q5 and Q6 and associated circuitry form an automatic gain control circuit (AGC). Diode D4, R27, and C22 filter the supply voltage (B+18V) received from the A100S recorder. NOTE: Jumper pin 5B at the center of the PWA is used to disable the AGC circuitry when jumpered to the chassis.
(5)
Microphone Preamplifier PWA, P/N 93A266–(XX) This PWA (refer to Figure 32) is used in the Model A151B and A152B Control Units which connect, externally or internally, to a condenser microphone (Model A55B). The operation of this PWA is similar to that of Microphone Preamplifier PWA, P/N 93A263– (XX), but differs in that it provides a filtered 6.2V dc supply voltage required by the condenser microphones as a polarizing voltage. This voltage is furnished via resistor R20, Zener diode D3, and capacitor C15 (see the schematic diagram given in Figure A7 in Appendix A). Also, the preamplifier input is changed somewhat to accommodate the higher level audio signal. The microphone output signal is applied to the preamplifier input at pins N and M and amplified by Q1, gain adjusted by potentiometer R9, and further amplified by Q2. Pin selectable audio gain attenuation, in 6 dB steps from 0 to 24 dB, is provided via resistors R17, R29, R30, R32, and R31. A jumper is required in the aircraft connector between pin q and the appropriate attenuation pin (s): p (6 db), r (12 db), or t (24 db). For example, a gain attenuation of 18 dB is enabled by connecting a jumper between pin q and p (6 db) and also between pin q and r (12 db). Transistor Q3 is another amplification stage and Q4 is an emitter–follower used to provide a low–impedance output at pin L (OUT), which is fed through the aircraft wiring to the Aircraft Interface PWA in the Model A100S recorder. Low frequency response remains fixed at 150 Hz (–3 dB). Transistors Q5 and Q6 and associated circuitry form an automatic gain control circuit (AGC). Diode D4, R27, and C22 filter the supply voltage (B+18V) received from the A100S recorder. NOTE: Jumper pin 5B at the center of the PWA is used to disable the AGC circuitry when jumpered to the chassis.
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2.31"
R2
INPUT FROM MICROPHONE
C3
F
C1
GND M
C15 R7
C4
Q1
N
C2
R4
C7
P P
C22 R6
R3
B-18V
C5
C6
R5
R8
R10
3.5" Q6
GAIN POT. R9
K B
Q5
R9
L R11
AGC DISABLE JUMPER PIN
5B
R 27
AUDIO OUT
R28 C20
R 18
C11
C19 D 1
C8 C9
D C 2 14
R 19
D 4
B+18V
C12
R 13 R R 12 14
C
R22 R17
R26
R29 Q4 R 15
R C 25 17 Q2
C13
R16 R 30
C21
R 32
C10
q
R 21
p
R 31
r
C R 16 24
t
C 18
Q3
R23
AUDIO GAIN ATTENUATION JUMPER PINS Jumper p to q for 6 dB Jumper r to q for 12 dB Jumper t to q for 24 dB
Dynamic Microphone Preamplifier PWA, P/N 93A263–02 Figure 31
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2.31"
INPUT FROM MICROPHONE +
C3 –
+
C4
P
C7 + R6
Q1
C15
+ C6
+
C5
D 3
+ C22
R3 R5
6.2V TO MICROPHONE
N
C2 + R4
E
M R1
R7
GND
F
+ C1 –
R2
R 20
B-
R8
AUDIO OUT
R10 3.5"
Q6
GAIN POT. R9
+ R C 18 11 –
Q5 R11 R9
R 27
K B R28
L
C20
5B
AGC DISABLE JUMPER PIN
+
C8
C R C D1 D2 14 19 19 D – + 4
C9 +
B+ +
C12
R 13 R R 12 14
R26
R17 Q4
R29
R 15
C 13
R 30 R R C 32 31 16 +
Q2 + C 21 +
R22
C10 p q
C
R16 R 24 C 18 +
C R 17 R 25 + 21
Q3
t r
R23
AUDIO GAIN ATTENUATION JUMPER PINS Jumper p to q for 6 dB Jumper r to q for 12 dB Jumper t to q for 24 dB
Condenser Microphone Preamplifier PWA, P/N 93A266–01 Figure 32
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
TESTING AND TROUBLESHOOTING 1. GENERAL This section provides operational level testing and system troubleshooting procedures for the Model A100S recorder and associated control units and microphones. Testing for the A100S is based upon operational test procedures. The operational test procedures may serve as an acceptance criteria for the unit, as well as provide pointers to probable failures in the event that the unit is not functioning properly. There is no periodic testing required for the A100S. The A100S is a solid–state device which has no moving parts and provides a minimum of 30 minutes of recording time. As such, fault isolation is simplified in that it is confined to the three printed wiring assemblies which contain the processing and control electronics for the A100S.
2. A100S RECORDER TESTING The Model A100S has been designed as a direct line replaceable unit (LRU) for the existing L3 Cockpit Voice Recorders, Models A100 and A100A. As such, other than the Audio Monitor Adapter with Modification 1 (AMA/1), the Model A100S recorder uses the same test equipment and bench setup as the tape–based models. As with the Model A100 and A100A recorders, the Model A100S must be removed from the aircraft and placed on a test bench to be tested. Table 101 lists the standard test equipment that is recommended to be available at the test bench such as an oscilloscope, voltmeters and frequency counter. Special test equipment required consists of the following L3 units: Cockpit Voice Recorder System Test Panel Calibrated Sound Source Audio Monitor Adapter (AMA/1) Ultrasonic Test Set (Beacon Tester)
L3 P/N 9300A860 L3 P/N 9300A870 L3 P/N 17TES0200 L3 P/N 15977
3. MODEL A100S OPERATIONAL TEST PROCEDURE Figure 101 is a block diagram of the test equipment setup used to test the Model A100S. The operational test procedure used to verify the mission readiness of the Model A100S are given in Table 102. The A100S is tested using the L3 Cockpit Voice Recorder System Test Panel, P/N 9300A860, which is the same test panel used to test the Model A100 and A100A tape–based Cockpit Voice Recorders. Interface cables are included with the Test Panel, one (rectangular plug) to connect to the cockpit voice recorder and another (round plug) to connect to the control unit.
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Table 101 Recommended Standard Test Equipment Part No. or Model No.
Manufacturer
Name
Purpose
Model 54111D
Hewlett–Packard
Oscilloscope
Signal presentation
3400A
Hewlett–Packard
AC VTVM
Voltage measurement (VTVM)
651B
Hewlett–Packard
Audio Oscillator
Test signal injection for troubleshooting and alignment
W5MT3W (0–100 Watts, 600–400 Hz)
Technipower
Variac
Troubleshooting
4368B
Hewlett–Packard
Volt–Ohm– Milliammeter
Voltage measurements (VOM)
Model 3283 P/N 16315
Simpson
AC Volt Meter
Measuring input line voltage
5314A
Hewlett–Packard
Frequency Meter
Measuring input line frequency
This panel may be used in conjunction with the L3 Calibrated Sound Source, P/N 9300A870, which is used to generate a regulated sound source, via a speaker, to test and analyze the system microphones. The specifications for the A100S apply to the individual channel outputs accessed, via the Audio Monitor Adapter with Modification 1 (AMA/1), at the Playback Monitor connector (J6) located on the outer edge of the Audio Processor PWA. As such, the dust cover of the A100S must be removed if the desired level of test goes beyond the “ALL TEST” procedure given in Table 102. For an illustration of this test setup, refer Figure 904. NOTE:
The “ALL TEST” test procedure is sufficient to determine the mission readiness of the recorder.
System level troubleshooting for the Model A100S is provided in Table 105. Each step given in Table 105 corresponds to the respective step described in the Operational Test Procedure given in Table 102. That is, if an expected indication called for in the Operational Test Procedure is not correct, refer to the respective step in the System Level Troubleshooting table. System level troubleshooting restricts corrective maintenance to replacement of a PWA and/or the Flash Crash Survivable Storage Unit (FCSSU). However, fault isolation procedures are given for the Aircraft Interface PWA (Table 106), Audio Processor PWA (Table 107) and the Store Processor PWA (Table 108). To aid in troubleshooting, refer to the System Functional Block Diagram given in Figure 25, which is presented in the Description and Operation section. Also, refer to the detailed system wiring diagram (Figure A1) and PWA schematic diagrams given in Appendix A at the rear of this manual for additional troubleshooting aids. Frequency response and input gain calibration procedures are described in the Fault Isolation section for the Audio Processor PWA.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Variac Watt/AC Line Meter
115 + 1 VAC 400 Hz
Audio Oscillator
Scope
Frequency Meter Channel A
Frequency Meter Channel B
Input VTVM
Output VTVM Terminal Block TB1 Pin 1 – 115V – Hot Pin 2 – 115V – Gnd Recorder Input Terminals
RECORDER SIDE
Recorder Output Terminals
Power In Speaker
LOCAL AMP (Audio Amplifier) Switch
CHANNEL SELECT Switch
CONTROL UNIT SIDE
Rec. c.u.
Recorder Interface Connector J3
COCKPIT VOICE RECORDER SYSTEM TEST PANEL, P/N 9300A860
J2 Connection For Interface Cable To Control Unit, When Used
Interface Cable P1 Input
J1
Output
Model A100S Solid–State Cockpit Voice Recorder Under Test
Model A100S Operational Test Set–Up Figure 101
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Table 102 Model A100S Operational Test Procedure ITEM A.
PROCEDURE
REFERENCE
PRELIMINARY TEST SET–UP (1)
Test Set–Up Figure 101
Except for the Model A100S, connect all units as shown in Figure 101. At the A860 Cockpit Voice Recorder System Test Panel, hereinafter referred to as the Test Panel, set function switches as follows: POWER ON/OFF switch
— Set this toggle switch to position OFF (down).
POWER AC/DC switch
— Set this toggle switch to position AC (up).
CHANNEL SELECT switch — Set this switch to position CH1. RECORD BIAS/OFF switch
— Set the RECORD toggle switch to position BIAS (up).
LOCAL AMP switch
— Set this switch to position REC.
VOLUME control
— Set the VOLUME control at its mid–range position.
MODE SYS/UNIT select sw. — Set the SYS/UNIT switch to (Left top of panel) position SYS.
B.
(2)
Set output of generator to 3 Vrms @ 1 KHz output. Note the ac power consumption, if any.
(3)
Apply power to the Variac and adjust as needed for 115 +1 Vac output. Note the ac power consumption, if any.
POWER–ON TEST
Test Set–Up, Figure 101
This test checks the Model A100S ac power consumption and the power–up audible tone generated by the recorder. (1)
Connect the Model A100S and the Control Unit (if one is being used) to the Test Panel. NOTE: With the RECORD BIAS/OFF switch set to position BIAS, pre–recorded data will be overwritten.
(2)
At the Test Panel, while monitoring the Variac and listening for the start–up audible tone, set the POWER ON/OFF toggle switch to position ON. Note: at the instant that power is applied, the recorder will generate a brief audible tone. If no audible tone is heard, proceed to Table 105 for troubleshooting.
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Table 102 Model A100S Operational Test Procedure (Continued) ITEM (3)
C.
PROCEDURE
REFERENCE
Carefully readjust Variac to provide 115 + 1 Vac to the Test Panel. Note the ac power consumption. Subtract from this figure, the power consumption noted in step A.(2). The ac power consumed by the recorder should be12 watts or less. If not, proceed to Table 105 for troubleshooting.
ALL TEST
Test Set–Up, Figure 101
Sophisticated Built–In–Test–Equipment (BITE) has been designed into the A100S to allow a quick operational confidence check without removing the dust cover. This check can be accomplished at the test bench using the Test Panel. (1)
ALL TEST Using Test Panel: (a)
At the Test Panel, set the MODE switch to position UNIT.
(b)
At the Test Panel, press and hold the green ALL TEST pushbutton for approximately 1 minute to allow recorded data to be monitored in the playback mode.
(c)
While holding in the ALL TEST pushbutton, monitor the TEST meter directly above the ALL TEST pushbutton. The needle should remain in the green (GOOD) area.
(d)
At the Test Panel, monitor the speaker for the 640 Hertz test tone; if necessary, turn up the panel VOLUME control. The test tone will alternate between the channels and will always start a new cycle at Channel 1. If this is not the case, proceed to Table 105 for troubleshooting.
(e)
Control Unit Voltage Check: Measure the output of the Control Unit connectors on the A860 Control Panel and ensure a reading of 18 VDC + 15% with a 1 K ohm load across the output.
NOTE: If recorder does not pass All Test, check for fault conditions described in notes at end of this chapter. NOTE: CLEARING “MEMORY” LATCHED FAULT CONDITION The A100S Store Processor Card, p/n: 205E0602–00 or 205E1027–00, stores memory fault codes in nonvolatile EEPROM. Certain memory fault conditions must be reset by service personnel prior to returning the unit to normal operation. This “Memory” latched fault condition is indicated by the Fault Indicator, CR5, located on the Store Processor Card, being illuminated when the unit is powered up in the Record Mode of operation. The “Memory” Latched Fault Condition can be cleared as described in the procedure below.
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Table 102 Model A100S Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
(1)
With the SSCVR connected to the A860 CVR Test Panel, power the A100S up in the Reproduce Mode. (Record/Bias Switch, S11, on the Test Panel to OFF.)
(2)
If the “Pointers Not Saved” condition has been latched, the Fault Indicator, CR5, on the Store Processor Card will flash 10 times.
(3)
Allow the flashing indication cycle to complete, or observe that the unit does not have this condition.
Note:
Since this procedure requires critical timing sequence for clearing the fault condition, read Steps (4) & (5) completely before performing.
(4)
To clear the “Memory” Latched Fault condition, first press and release the All Test Switch, S13, on the A860 CVR Test Panel. (This begins a 5–second interval in which the latched fault condition may be cleared.)
(5)
Immediately after pressing and releasing the All Test Switch, S13, press and hold the Bulk Erase Switch, S10, for at–least 3 seconds but not more than the 5 second interval.
(6)
Power down the recorder, place the unit into Record Mode by placing the CVR Test Panel switch S11 to Record/Bias position and reapply power to the recorder.
(7)
Observe that the Fault Indicator is no longer illuminated. Press All Test Switch and observe test meter is in green to verify proper operation of recorder.
(8)
If recorder fails to test good, or the Fault Indicator, CR5, is still illuminated, then repeat steps (3) – (7). If problem continues, return unit to L3AR for service.
(9)
If the “Pointers Not Saved” latched condition was observed in step (2) above, then proceed with the next procedure.
NOTE: “POINTERS NOT SAVED” LATCHED FAULT CONDITION The A100S is designed such that an impending loss of power is signaled to the CPU to preserve the current system pointers in nonvolatile (EEPROM) memory. Any interruption to this cycle might result in a corrupted set of pointers and cause a “Pointers Not Saved” latched fault condition. (1)
With the SSCVR connected to the A860 CVR Test Panel, power the A100S up in the Reproduce Mode. (Record/Bias Switch, S11, on the Test Panel to OFF.)
(2)
If the “Pointers Not Saved” condition has been latched, the Fault Indicator, CR5, on the Store Processor Card will flash 10 times.
(3)
Allow this flashing fault indication cycle to complete.
Note:
Since this procedure requires critical timing sequence for clearing the fault condition, read Steps (4) & (5) completely before performing.
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Table 102 Model A100S Operational Test Procedure (Continued) ITEM
(2)
D.
PROCEDURE
REFERENCE
(4)
Press and release the All Test Switch, S13, on the A860 CVR Test Panel. (This begins a 5–second interval in which the latched fault condition may be cleared.)
(5)
Immediately after pressing and releasing the All Test Switch, S13, press and hold the Bulk Erase Switch, S10, for at–least 3 seconds but not more than the 5–second interval. During the 3 seconds while the Bulk Erase Switch, S10, is being pressed, briefly press and release the All Test Switch, S13, again.
(6)
To verify that the fault has cleared, power down the recorder, then reapply power while in the Reproduce mode of operation and observe that the Fault Indicator, CR5, on the Store Processor Card briefly flashes but does not illuminate.
ALL TEST Using Associated Control Unit: (a)
At the Test Panel, set the MODE switch to position SYS.
(b)
At the Control Unit, press and hold the ALL TEST push– button for approximately 1 minute to allow recorded data to be monitored in the playback mode.
(c)
At the Control Unit, monitor the TEST meter. The needle should remain in the green (GOOD) area.
(d)
At the Control Unit with a suitable headset connected to the 1/4 inch phone jack, monitor the A100S test tone. The test tone should be an audible 640 Hertz tone and should alternate between channels. If this is not the case, proceed to Table 105 for troubleshooting.
PLAYBACK TEST
Test Set–Up, Figure 101
This test verifies the playback ability of the A100S recorder. (1)
At the System Test Panel, set the RECORD BIAS/OFF toggle switch to position OFF (down).
(2)
At the Test Panel, press the ALL TEST pushbutton. The recorder should automatically begin replaying the data recorded since the recorder was last powered–up. If this is not the case, proceed to Table 105 for troubleshooting.
(3)
Connect the headset to the recorder front panel jack to monitor the combined audio. The previously recorded test tone should be heard.
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Table 102 Model A100S Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
NOTE: The recorder test tone can also be heard via the Test Panel speaker and also by connecting to the HEADSET phone jack on the Control Unit. (4)
E.
At the Test Panel, place the RECORD BIAS/OFF toggle switch to position BIAS (up). The recorder will resume recording data at the point in memory where it had stopped when the PLAYBACK function was initiated.
BULK ERASE TEST
Test Set–Up, Figure 101
This test checks the capability of erasing the information stored in the A100S FCSSU (CMOS Flash memory). (1)
Bulk Erase Lock–Out:
NOTE: This portion of the test verifies that the Bulk Erase function will not be initiated by momentarily contacting the ERASE pushbutton (less than 2 seconds).
(2)
(a)
At the Test Panel, verify that the RECORD BIAS/OFF toggle switch is still set to position BIAS (up).
(b)
At the Test Panel (or the Control Unit if used), press and release the BULK ERASE pushbutton for less than 2 seconds.
(c)
This action should not have started the Bulk Erase function. If started, proceed to Table 105 for troubleshooting.
Bulk Erase:
NOTE: All previously recorded data will be erased during the Bulk Erase cycle. (a)
At the Test Panel (or the Control Unit if used), press and hold the ERASE pushbutton for more than two seconds and release.
(b)
Monitor the Test Panel speaker. For units equipped with 2–Megabit Memory Devices, the erase tone should be audible for approximately 13 seconds. For units equipped with 8–Megabit Memory Devices (Modification Dot 1), the erase tone should be audible for approximately 1 to 15 seconds. If the erase tone is not heard, proceed to Table 105 for troubleshooting.
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Table 102 Model A100S Operational Test Procedure (Continued) ITEM (3)
PROCEDURE
REFERENCE
Bulk Erase Verification:
This test verifies that all previously recorded information has been erased from the memory.
E.
(a)
At the Test Panel, verify that the RECORD BIAS/OFF toggle switch is still set to position OFF (down).
(b)
At the Test Panel, press the ALL TEST pushbutton. The recorder should automatically begin replaying the data recorded since the recorder was last powered–up.
BULK ERASE TEST (Continued) (c)
F.
Test Set–Up, Figure 101
When the unit is placed back into the playback mode after a Bulk Erase is performed, a sound similar to a “galloping horse” or “tapping fingers” is heard. This sound indicates that there is no data in memory. If nothing is heard, proceed to Table 105 for troubleshooting.
BEACON TEST This test verifies the proper operation of the beacon (Underwater Locating Device) mounted on the A100S front panel. (1)
Turn on the L3 Beacon Tester (P/N 15977).
(2)
Using a ground strap or similar conductive material, short the beacon center conductor, located on the underside of the beacon, to the cradle.
(3)
While the beacon is shorted to the cradle, an audible tone should be heard at the beacon test set. Once detected, remove the shorting jumper. If an audible tone is not detected, proceed to Table 105 for troubleshooting.
(4)
If the ULD is functioning properly, it will emit inaudible, ultrasonic soundwaves that the 42A12( ) will receive and reproduce at a lower, audible frequency. Proper operation of the ULD is indicated by a repetitive “beep” emanating from the 42A12( )’s speaker.
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4. CONTROL UNIT, MODEL A151/A151B & A152/A152B TEST PROCEDURES Table 103 provides the operational tests and alignment procedures for the Model A151/A151B and A152/A152B Control Units. Figure 102 is a diagram of the basic test setup to be used for testing either type Control Unit. Figure 103 shows the location of the Control Unit microphone input gain control (potentiometer R9 on the Microphone Preamplifier PWA).
Table 103 Model A151 and A152 Control Units, Operational Test Procedure ITEM
PROCEDURE
REFERENCE
A. PRELIMINARY TEST SET–UP (1)
Remove the dust cover from the Control Unit to be tested.
(2)
At the Control Unit, connect a jumper wire between pin 5B on the Microphone Preamplifier PWA and chassis; this con– nection disables the AGC circuitry (see Figure 31/Figure 32).
(3)
Connect all units as shown in Figure 102
(4)
At the Test Panel, set the function switches as follows: POWER AC/DC Switch
—
AC
POWER ON/OFF Switch
—
OFF
LOCAL AMP Switch
—
C.U. (Control Unit)
ROLL OFF Switch
—
700 Hertz
ATTENUATION Switches
—
–6 dB –12 dB –24 dB
MIC INT/EXT Switch
—
EXT
CHANNEL SELECT Switch —
CH1
Figure 102
– ON, (right) – ON, (right) – OFF (left)
NOTE: In Model A152/A152B Control Units, where the built–in microphone is wired internally to pins N (HI) and P (LO) of the Microphone Preamplifier PWA (see Figure 31/Figure 32), disconnect microphone leads and apply input signals using a properly shielded cable directly to circuit board pins N and P. In other units, the input signal should be applied to the test panel input with the MIC INT/EXT switch set to EXT. (5)
When testing Models A151 and A152, test signals may be applied to input terminals on the RECORDER side of the Test Panel. For Models 152–1, A152–2 and A152–4, remove the microphone wires from pins N and P on the printed circuit board and connect the test signal directly to pins N (HI) and P (LO). See Figure 901.
(6)
At the Test Panel, set the POWER ON/OFF switch to position ON.
(7)
Apply power to the Variac and adjust as needed for 115 +1 Vac power to the Test Panel input (TB1– 1 & 2). See Figure 102.
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Variac Watt/AC Line Meter
115 + 1 Vac 400 Hz
Freq Meter Channel A
Input VTVM
Terminal Block TB1 Pin 1 – 115V – Hot Pin 2 – 115V – Gnd
System Test Panel
Audio Oscillator
Control Unit Input
CONTROL UNIT SIDE
Speaker RECORDER SIDE
Freq Meter Channel B
Output VTVM
LOCAL AMP (Audio Amplifier) Switch
MIC. Select
C.U. Scope
Control Unit Output
Rec.
J2 Connection For Interface Cable To Control Unit Input
Output
Control Unit Under Test
Control Unit Test Set–up Figure 102
POTENTIOMETER R9
Control Unit Test and Adjustment Point Figure 103
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Table 103 Model A151 and A152 Control Units, Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
B. GAIN ALIGNMENT (1) (2)
Figure 102
NOTE: For Model A151 & A152 units with Mod. 5, refer to Section 6.B. At the Audio Oscillator, apply a 4 mV, 1 kHz signal to the Control Unit input terminals. Adjust Control Unit potentiometer R9 (location illustrated in Figure 103) for a 0.5V level as measured at the Output VTVM.
C. MAX OUTPUT TEST
Figure 102
(1)
At the Audio Oscillator, increase the Control Unit input signal level to approximately 12 mV.
(2)
Adjust the input signal level for a 2 volt level at the Output VTVM.
(3)
A sinewave output with no sign of clipping should be observed on the oscilloscope.
D. AGC TEST
Figure 102
(1)
At the Control Unit, remove the jumper connecting post 5B on the Microphone Preamplifier PWA to the chassis (installed in the PRELIMINARY TEST SET–UP).
(2)
Observe that the voltage level measured at the Output VTVM dropped to between 0.3 and 0.6 volt.
(3)
Reconnect the jumper between post 5B on the Microphone Preamplifier PWA and the chassis.
E. SIGNAL/NOISE RATIO
F.
Figure 102
(1)
At the Test Panel, short the input terminals and note the reading Output VTVM.
(2)
At the Output VTVM, the noise level should be less than10 mV.
(3)
At the Test Panel, remove the short.
FREQUENCY RESPONSE
Figure 102
NOTE: For Model A151 & A152 units with Mod. 4, refer to Section 5.A. For Model A151 & A152 units with Mod. 5, refer to Section 6.A. (1)
Set the Output VTVM to the 1 volt full–scale range.
(2)
Apply a 1–kHz input signal and adjust the input voltage level (at the audio oscillator) for a 0 dB reading on the Output VTVM.
(3)
Maintaining the above input level, adjust the audio oscillator for 700 Hz input signal and note the reading on the Output VTVM in dB. The meter should not deviate more than 0 to –6 dB.
(4)
Repeat step (3) with audio oscillator adjusted for both 300 Hz and 5 kHz.
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Table 103 Model A151 and A152 Control Units, Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
G. MICROPHONE GAIN ALIGNMENT
Figure 102
(1)
At the Test Panel, set the MIC INT/EXT switch to position INT.
(2)
Reconnect microphone if disconnected in the PRELIMINARY TEST SET–UP.
(3)
At the Calibrated Sound Source, P/N 9300A870, apply a 100 dB sound pressure level to the Control Unit microphone and adjust the position of the Control Unit to obtain a maximum reading.
(4)
At the Control Unit Microphone Preamplifier PWA, adjust potentiometer R9 (position illustrated in Figure 103) for a reading of 0.5 V on the Output VTVM.
H. TEST METER (1)
I.
J.
Figure 102
Remove jumper between Pin 5B and ground. Press TEST button of control unit test meter to read 9dB minimum.
BULK ERASE SWITCH
Figure 102
(1)
While monitoring both the NORMAL and the ACTUATE meters at the upper left corner of the Test Panel, press the ERASE button on the Control Unit.
(2)
At the Test Panel, the NORMAL meter should drop to mid–scale while the ACTUATE meter should rise to mid–scale.
GROUND SHORT TEST (1)
Figure 102
Switch test panel GND test switch to Position 1 (GND Short). GND test lamp should NOT light. If control unit under test has a short between signal ground and chassis GND test lamp will light indicating a fault.
K. REVERSED GROUND TEST
Figure 102
(1)
Switch test panel GND test switch to Position 2 (Reversed Ground). GND test lamp should NOT light. Touch the control unit’s chassis with the test panel probe. If control unit is properly grounded the GND test lamp will light.
(2)
For control units with internal microphone repeat above test touching microphone case.
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5. CONTROL UNIT, MODEL A151 & A152 WITH MODIFICATION 4 TEST PROCEDURES The test procedures for testing Control Units, Models A151 and A152, which include Modification 4, are the same as those without Modification 4 with the exception of the Frequency Response Test given below. The test setup given in Figure 102 is to be used for testing these Control Units. Also, refer to Figure 103 for the Control Unit preamplifier gain adjustment point.
A. FREQUENCY RESPONSE (1)
Set the Output VTVM to its 1 volt full–scale range.
(2)
Apply a 1 kHz input signal and adjust its input voltage level (at the oscillator) for an output signal level of 0 dB as measured on the Output VTVM.
(3)
Maintain the same input level. Switch through following frequencies and read dB outputs: 150 Hz 300 Hz 500 Hz 5000 Hz
–1 to –5 dB 0 to –3 dB 0 to –3 dB 0 to –4 dB
6. CONTROL UNIT, MODEL A151 & A152 WITH MODIFICATION 5 TEST PROCEDURES The test procedures for testing Control Units, Models A151 and A152, which include Modification 5, are the same as those without Modification 5 with the exceptions of the Frequency Response Test and the Microphone Gain Alignment given below. The test setup given in Figure 102 is to be used for testing these Control Units. Refer to Figure 103 for the Control Unit preamplifier gain adjustment point.
A. FREQUENCY RESPONSE (1)
Set the Output VTVM to its 1 volt full–scale range.
(2)
Apply a 1 kHz input signal and adjust the input voltage level (at the oscillator) for an output signal level of 0 dB as measured on the Output VTVM.
(3)
Maintain the same input voltage level set above. Switch through the following frequencies and note the dB outputs: 150 Hz 300 Hz 500 Hz 5000 Hz
–1 to –5 dB 0 to –3 dB 0 to –3 dB 0 to –4 dB
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B. MICROPHONE GAIN ALIGNMENT (1)
At the Test Panel, set the MIC INT/EXT switch to position INT. Set the Test Panel attenuator switches for –18 dB attenuation. This is performed by positioning the –6 dB and –12 dB attenuation switches to the right (enable) and the –24 dB attenuation switch to the left (disable) position.
(2)
Connect the microphone if not already connected.
(3)
At the Calibrated Sound Source, P/N 9300A870, apply a 100 dB sound pressure level to the Control Unit microphone and adjust the position of the Control Unit to obtain a maximum reading on the Output VTVM.
(4)
At the Control Unit Microphone Preamplifier PWA, adjust potentiometer R9 (shown in Figure 103) for an output of 0.5V as indicated on the Output VTVM.
7. MODEL A150 PREAMPLIFIER TEST PROCEDURES Table 104 provides the operational test procedure for the Model A150 Microphone Preamplifier Module. The Model A150 is designed to be used only with condenser-type microphones (Model A055). To test the operational performance of the A150 Preamplifier Module, use Test Cable Assembly, P/N 024E1285–00, along with the same test setup given in Figure 102 with one exception. A simulated microphone signal output from the HP33120B is routed through the A860 Test Panel, a banana jack – to – BNC adapter, and Cable 024E1877–00 to connector J1 on the A150 Preamplifier. The Test Cable Assembly, P/N 024E1285–00 connects between J2 on the A860 Test Panel and the 19–pin connector on Preamplifier A150 to furnish operating power for the preamplifier and to route the amplified simulated microphone output back to the A860 Test Panel.
Mic Connector J1
A
B D
C
K
E Signal Connector J2
A
M
C
J2
H
B J1
External Preamplifier, Model A150 (P/N 93A150-20) Assembly Diagram Figure 104
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
A150 PREAMPLIFIER MODULE
CABLE ASSEMBLY 024E1877–00
PWA TERMINALS
E5
MIC_NO.1_IN_HI
A
MIC_NO.1_BIAS
E4
MIC_NO.1_IN_LO
E6
P2
J1-
A
P1-
(BNC)
MIC SIGNAL (wHITE)
B
B NO CONNECT
C
C
CONNECT MIC CENTER CAL OUTPUT FROM A860 SHIELD TEST PANEL VIA BANANA JACK-TO-BNC ADAPTER.
MIC GND (SHIELD)
Simulated Microphone Signal Input Test Connections to the Model A150 Preamplifier Module Figure 105 Table 104 Model A150 Preamplifier Unit, Operational Test Procedure ITEM
PROCEDURE
REFERENCE
A. PRELIMINARY TEST SET–UP (1)
Remove the dust cover from the Preamplifier Unit to be tested.
(2)
At the Preamplifier Unit, connect a jumper wire between pin 5B on the Microphone Preamplifier PWA, p/n: 205E and chassis; this connection disables the AGC circuitry (Figure 32).
(3)
At the Test Panel, set the function switches as follows: POWER AC/DC Switch
—
AC
POWER ON/OFF Switch
—
OFF
LOCAL AMP Switch
—
C.U. (Control Unit)
ATTENUATION Switches
—
–6 dB –12 dB –24 dB
MIC INT/EXT Switch
—
EXT
CHANNEL SELECT Switch —
CH1
– ON, (right) – ON, (right) – OFF (left)
(4)
At the Test Panel, set the POWER ON/OFF switch to position ON.
(5)
Apply power to the Variac and adjust as needed for 115 +1 Vac power to the Test Panel input (TB1– 1 & 2). See Figure 102.
B. GAIN ADJUSTMENT (1)
At the Audio Oscillator, apply a 4 mVrms, 1 kHz signal to the Preamplifier Unit input terminals.
(2)
Adjust Preamplifier Unit potentiometer R9 (location illustrated in 32) for a 0.5V level as measured at the Output VTVM.
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Table 104 Model A150 Preamplifier Unit, Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
C. DISTORTION CHECK (1)
At the Audio Oscillator, increase the Preamplifier input signal level to approximately 12 mVrms.
(2)
Adjust the input signal level for a 2 volt level at the Output VTVM.
(3)
A sinewave output with no sign of clipping should be observed on the oscilloscope.
D. AGC TEST (1)
At the Preamplifier Unit, remove the jumper connecting post 5B on the Microphone Preamplifier PWA to the chassis (installed in the PRELIMINARY TEST SET–UP).
(2)
Observe that the voltage level measured at the Output VTVM dropped to between 0.3 and 0.6 volt.
(3)
Reconnect the jumper between post 5B on the Microphone Preamplifier PWA and the chassis.
E. SIGNAL/NOISE RATIO
F.
(1)
At the Test Panel, short the input terminals and note the reading Output VTVM.
(2)
At the Output VTVM, the noise level should be less than10 mV.
(3)
At the Test Panel, remove the short.
FREQUENCY RESPONSE (1)
Set the Output VTVM to the 1 volt full–scale range.
(2)
Apply a 1–kHz input signal and adjust the input voltage level (at the audio oscillator) for a 0 dB reading on the Output VTVM.
(3)
Measure the output level for each of the frequencies listed below and verify that the output levels are within the given specifications. Frequency Input 150 Hz 300 Hz 500 Hz 5,000 Hz
Output –2 to –10 dB 0 to –4dB 0 to –2dB 0 to –5dB
G. ATTENUATION CHECK (1)
Set all attenuator switches to OFF.
(2)
Apply a 1–kHz input siganal and adjust the input voltage level (at the audio oscillator) for a 0 dB reading on the Output VTVM.
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Table 104 Model A150 Preamplifier Unit, Operational Test Procedure (Continued) ITEM
PROCEDURE
REFERENCE
(3)
Set the 6 dB switch to ON and note the level on the Output VTVM, it should read: –3 to –9 dB. Set the 6 dB switch to OFF.
(3)
Set the 12 dB switch to ON and note the level on the Output VTVM, it should read: –9 to –15 dB. Set the 12 dB switch to OFF.
(3)
Set the 24 dB switch to ON and note the level on the Output VTVM, it should read: –20 to –28 dB. Set the 24 dB switch to OFF.
H. GAIN Verification
I.
J.
(1)
At the Test Panel, set the attenuator switches as follows: 6 dB ON 12 dB ON 24 dB OFF
(2)
At the Audio Oscillator, apply a 4 mVrms, 1 kHz signal to the Preamplifier Unit input terminals.
(3)
Verify a 0.5V level as measured at the Output VTVM, if necessary, adjust Preamplifier Unit potentiometer R9 (location illustrated in 32).
(4)
Measure the voltage across C15. Voltage should be 6.0 V (+/– .6V).
GROUND TEST (1)
Switch Test Panel GND test switch to REVERSED GND position.
(2)
Touch the Preamp Unit chassis with the Test Panel probe. Verify that the GND FAULT lamp does not illuminate.
(3)
Set the Test Panel GND test switch to BYPASS position.
SYSTEM TEST (1)
Turn Test Panel Power OFF.
(2)
Reinstall Preamp Dust Cover.
(3)
Turn Test Panel Power ON.
(4)
Set Test Panel LOCAL AMP switch to C.U. Verify that a voice or 1-kHz tone can be heard through the Test Panel speaker as the VOLUME control is rotated clockwise.
8. CALIBRATION TEST FOR MODEL A055B REMOTE MICROPHONE MODULES This series of tests verifies the proper operation of the L3 Model A055B series of remote condenser type microphones, part numbers 93A055–10, –20, –30, –40, –45, –50, –55, –60, –65, –66, –67 and –95.
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A. PRELIMINARY SET–UP (1)
Set up for test as illustrated in Figure 106.
(2)
Position the Calibrated Sound Source, P/N 9300A870, approximately 6–inches from the microphone.
(3)
Connect microphone to Dumont: Model 701 oscilloscope and HP 400D AC VTVM, or equivalent. NOTE: If a sound level source and oscilloscope are not available, use the alternate method given in step C. to verify operation.
B. OUTPUT VERIFICATION (1)
Apply a 100 dB sound pressure level to the microphone.
(2)
The VTVM should indicate 12 mV + 6 dB.
(3)
The waveform displayed on the oscilloscope should be free from distortion.
C. ALTERNATE METHOD This method is to be used only when the Calibrated Sound Source is not available. (1)
At a normal voice level, speak into the microphone from a distance of approximately 6–inches.
(2)
The VTVM should fluctuate between 2 and 10 mV. *Remote Microphone Oscilloscope + 6Vdc Audio
Shield
+
Calibrated Sound Source P/N 9300A870 6 Volt + 1 Volt Battery or D.C. Power Supply 10K 1/4W Resistor
AC VTVM
* For P/N 93A055–40 & 45 remote microphones, the +6 Vdc line is black and the audio line is white. For P/N 93A055–60, 65, 66, 66, 67, & 95 remote microphones, the +6Vdc line is white and the audio line is black.
Remote Microphone Test Setup Figure 106
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9. MODEL A100S SYSTEM TROUBLESHOOTING System level troubleshooting for the Model A100S is provided in Table 105. Troubleshooting is based on the Operational Test Procedure described in the front of this section. That is, if an expected indication called for in the Operational Test Procedure is not correct, the troubleshooting procedure will direct the technician to the probable cause of the malfunction. System troubleshooting restricts corrective maintenance to replacement of a PWA and/or the Flash Crash Survivable Storage Unit (FCSSU). Each step given in Table 105 corresponds to the respective step described in the Operational Test Procedure. To aid in troubleshooting, refer to Figure 25, System Functional Block Diagram, presented in the Description and Operation section, Figure A1 the detailed system wiring diagram presented in Appendix A and to the detailed schematic diagrams of each PWA also provided in Appendix A. Board level troubleshooting follows the system troubleshooting and provides test point analysis, logic analyzer fault detection (Audio Processor PWA), and component level fault isolation. WARNING: VOLTAGES CAPABLE OF FATAL INJURY ARE PRESENT AT THE RECORDER INPUT CONNECTOR; ONLY QUALIFIED MAINTENANCE TECHNICIANS SHOULD PERFORM THE FOLLOWING MAINTENANCE. CAUTION: THE A100S PRINTED CIRCUIT ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL CIRCUIT BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
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Table 105 System Level Troubleshooting STEP
TEST DESCRIPTION
EXPECTED RESULTS
FAULT ISOLATION PROCEDURE
A.
Preliminary Set–up
N/A
N/A
B.
Power–On Test
A.) Brief Audible tone upon power–up
1)
Recheck test set–up and apply power to unit. If no brief audible tone is heard, turn off power and perform next step.
2)
Remove dust cover, turn on power and check if red FAULT LED (CR5) at the center of the Store Processor PWA, P/N 205E0601–00 and 205– E1027–00, is lit (refer to IPL Figure 6, item 20). This LED lights continu– ally whenever a fault exists in the A100S and, for a period of 5 seconds, whenever a Bulk Erase cycle is initiated.
3)
Check power supply voltages at the Aircraft Interface PWA, P/N 205E0597–00: TP2 – (+12 Vdc); TP3 – (–12 Vdc); TP4 – (+5 Vdc)
4)
If regulated voltages are incorrect, check input line voltage. If input is correct, turn power off and remove and replace Aircraft Interface PWA. To remove, refer to the Disassembly Section. For further troubleshooting, refer to Table 106.
5)
If input and regulated voltages are correct, remove and replace Audio Processor PWA, P/N 205E0598–00. To remove, refer to the Disassembly Section. For further troubleshooting, refer to Table 107.
6)
Apply power and check if red FAULT LED on Store Processor PWA is still lit. If so, remove and replace Store Processor PWA. To remove, refer to the Disassembly Section. For further trouble shooting, refer to Table 108.
NOTE Whenever power to the unit under test is removed and reapplied, the BULK ERASE pushbutton on the Test Panel must be pressed for approximately 3 to 4 seconds and released to clear a pre–existing memory fault condition.
NOTE Store Processor PWA, P/N 205E0601–00, is to be used only with FCSSU, P/N 253E0348–03. Store Processor PWA, P/N 205E1027–00, is intended to be used with FCSSU, P/N 253E0660–00 but may be used with either model FCSSU.
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Table 105 System Level Troubleshooting (Continued) STEP B.
TEST DESCRIPTION
EXPECTED RESULTS
Power–On Test (continued)
FAULT ISOLATION PROCEDURE 7)
If the red FAULT LED on the new Store Processor PWA lights upon powering up, turn power off and remove and replace the FCSSU. Refer to the Disassembly section.
8)
Apply power and check if red FAULT LED on Store Processor PWA lights after power up and memory cleared. If this is the case, assemble unit as first tested and return to factory for servicing and recertification.
1)
If power consumption is excessive, turn power off at the Test Panel.
2)
Disconnect the recorder from the Test Panel.
3)
Using an ohmmeter, measure the resistance between input connector, J1, pin 2 (115 Vac Hot), pin 3 (115 Vac cold), and J1 pin 17 (chassis ground). There should be an open between the power pins and chassis ground. If a power line is shorted to ground, remove and replace the Aircraft Interface PWA, P/N 205E0597–00. If no short is de– tected, perform next step.
4)
Disconnect Store Processor PWA Cable Assembly W2 (plug P5) from connector J5 of the Aircraft Interface Cable Assembly W1. Remove Audio Processor PWA from the recorder.
5)
Reconnect the recorder to the Test Panel and apply power.
6)
If power consumption is now within limits, turn power off, reconnect the Store Processor PWA Cable Assembly W2/P5 to connector J5 of the Aircraft Interface Cable Assembly W1.
NOTE Store Processor PWA, P/N 205E0601–00, is to be used only with FCSSU, P/N 253E0348–03. Store Processor PWA, P/N 205E1027–00, is intended to be used with FCSSU, P/N 253E0660–00 but may be used with either model FCSSU.
Power consumption less than 12 watts.
NOTE Whenever power to the unit under test is removed and reapplied, the BULK ERASE pushbutton on the Test Panel must be pressed for approximately 3 to 4 seconds and released to clear a pre–existing memory fault condition.
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Table 105 System Level Troubleshooting (Continued) STEP B.
TEST DESCRIPTION
EXPECTED RESULTS
Power–On Test (Continued)
NOTE Store Processor PWA, P/N 205E0601–00, is to be used only with FCSSU, P/N 253E0348–03. Store Processor PWA, P/N 205E1027–00, is intended to be used with FCSSU, P/N 253E0660–00 but may be used with either model FCSSU.
FAULT ISOLATION PROCEDURE 7)
Remove the four screws securing the Store Processor PWA to the FCSSU and disconnect the Store Processor PWA connector J2 from the FCSSU interface connector P2. Reapply power.
8)
If power consumption is excessive, turn power off and remove and replace the Store Processor PWA.
9)
If power consumption is within limits, turn power off and reconnect the Store Processor PWA J2 connector to the FCSSU connector P2 and using four screws secure in place.
10) Turn power on. If power drain is still excessive, remove and replace the FCSSU. 11) Reinstall Audio Processor PWA. Turn power on. If power consump– tion is excessive, remove and replace the Audio Processor PWA. 12) If power consumption remains excessive after performing the previous steps, turn power off and remove and replace the Aircraft Interface PWA.
C.
All Test indicates in the green
a.) ALL TEST meter
1)
Turn power off. Remove and replace the Audio Processor PWA.
“GOOD” area while ALL TEST button is pressed.
2)
If ALL TEST continues to fail, remove and replace the Store Processor PWA.
3)
If ALL TEST continues to fail, remove and replace the FCSSU.
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Table 105 System Level Troubleshooting (Continued) STEP C.
D.
E.
TEST DESCRIPTION
EXPECTED RESULTS
ALL Test (Continued)
Playback Test
Bulk Erase Test
a. Recorder begins playing back data since last power down once “RECORD BIAS” is turned off and the “ALL TEST” button is pressed.
a. Bulk Erase function started when Bulk Erase button is pressed less than two seconds
FAULT ISOLATION PROCEDURE 4)
If ALL TEST continues to fail, re– move and replace the Aircraft Inter face PWA.
5)
If ALL TEST continues to fail, inspect the test set–up.
1)
Check test set–up.
2)
Turn power off to the recorder. At the Test Panel, enable RECORD BIAS. Reapply power and perform an ALL TEST. Continue the ALL TEST for approximately one minute to provide a suitable test signal for the playback test.
3)
Disable the RECORD BIAS. Press the ALL TEST button and release.
4)
If the unit fails to playback the ALL TEST signal recorded since last power–up, remove power and remove and replace the Audio Processor PWA.
5)
If the test continues to fail, remove and replace the Store Processor PWA.
1)
Check test set–up and repeat test.
2)
If a bulk erasing cycle is initiated after pressing BULK ERASE button for less than two seconds, replace the Aircraft Interface PWA.
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Table 105 System Level Troubleshooting (Continued) STEP E.
F.
TEST DESCRIPTION Bulk Erase Test (Continued)
Beacon Test
EXPECTED RESULTS
FAULT ISOLATION PROCEDURE
b. Bulk Erase function 1) starts after pressing BULK ERASE button longer than 2 seconds; a bulk erase tone 2) (approx. 600 Hz) will be heard for 1 – 15 seconds in newer models (13 seconds 3) for older models).
Check test set–up and repeat test ensuring BULK ERASE button is pressed for at least 2 seconds.
c. After Bulk Erase is 1) performed, a sound similar to a “galloping horse” or “tapping 2) fingers” is heard when the unit is put in the playback mode.
If Bulk Erase test fails, remove and replace the Store Processor PWA.
a. When the center– 1) conductor at the underside (silver spot) of the beacon is shorted to the beacon 2) cradle, an audible beep is heard at the beacon test set, if incorporated; other– wise, perform step 2.
Check the battery expiration date printed on the beacon. If expired, replace the beacon.
If Bulk Erase test fails again, remove and replace the Store Processor PWA. If Bulk Erase test still fails, remove and replace the Aircraft Interface PWA.
If Bulk Erase continues to fail, remove and replace the Aircraft Interface PWA.
Remove the beacon and test on the L3 ULD Beacon Tester, P/N 15977. If defective, replace beacon.
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10. MODEL A100S PRINTED WIRING ASSEMBLY (PWA) FAULT ISOLATION Fault Isolation at the Printed Wiring Assembly (PWA) level has been developed for the Model A100S such that expected indications for key signals and test points are described along with the associated circuitry. As such, if an expected indication is not correct, the fault isolation chart will provide the circuitry which is the probable cause of failure for the signal under inspection. Once the probable circuitry is identified, the technician is expected to use common troubleshooting techniques to further isolate the fault to a particular circuit or component.
A. AIRCRAFT INTERFACE PWA FAULT ISOLATION The Aircraft Interface PWA, P/N 205E0597–00, connects the aircraft wiring to the A100S through a 57–pin DPX style connector designated J1. Power regulation, lightning protection, RF attenuation and discrete signal conditioning functions are also performed on this PWA. Refer to the Description and Operation Section, 8.B.(1), for an in–depth functional description of the Aircraft Interface PWA. The fault isolation procedure for the Aircraft Interface PWA is given in Table 106. Refer to the detailed system wiring diagram, Figure A1, and to the Aircraft Interface PWA detailed schematic diagram, Figure A2, given in Appendix A of this manual.
Table 106 Aircraft Interface PWA Fault Isolation Procedure Test Point TP1
Signal Nomenclature System Ground
Functional Description
Expected Possible Faulty Value Stage / Comp.
N/A
N/A
N/A
TP2
+12Vdc
+12V + 10%; <1% RMS ripple
+12V +10%
U2, C15, C16, C17, C18, C19, C22, CR13, CR14, CR15, CR16, CR19, CR24, CR25, T1
TP3
–12Vdc
–12V + 10%; <1% RMS ripple
–12V +10%
U2, C15, C16, C17, C18, C19, C22, CR13, CR14, CR15, CR16, CR19, CR24, CR25, T1
TP4
+5Vdc
+5V + 1%; <1% RMS ripple
+5V + 1%
U2, C15, C16, C17, C18, C19, C22, CR13, CR15 CR14, CR16, CR19, CR24, CR25, T1
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Table 106 Aircraft Interface PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Possible Faulty Value Stage / Comp.
TP5
TEST TONE
640 kHz; this signal is rectified by CR12 & C14 and applied to the 2.5V reference comparator, U4, which is used to develop the /NO FAULT signal, which turns on the +INDICATOR current source. This signal is only applied when the ALL TEST is enabled.
640 kHz sine wave; approx. 12V pk–pk
C12, C13, C20, R1, R2, R3, R4, U1
TP6
+18Vdc regulated (for units prior to S/N 1000, this value will be +30 VDC)
+18V + 15%;<0.1A; <1% rms ripple. The regulated +18V is used to power the Control Unit. The +18V is derived from the –12V.
+18V + 1%
U3, C28, C29, C30, CR20
J2 pin 23
/RECORD
This signal is pulled up to +5V when the RECORD BIAS is in the OFF position.
+5V
U4, C23, C25, R7, R8, R11, CR23, CR26
J2 pin 26
ERASE
This signal is pulled up to +5V when the Erase pushbutton on the test panel or the Control Unit is pressed.
+5V
U4, R7, R8, R15, C24, C26, CR21, CR22
J2 pin 24
TEST
This signal is pulled up to +5V when the ALL TEST button is pushed on the Test Panel or at the Control Unit.
+5V
U4, R7, R8, R12, C21, C27
B. AUDIO PROCESSOR PWA FAULT ISOLATION The primary function of the Audio Processor PWA, P/N 205E0598–00, is to digitize the four audio signals supplied via the Aircraft Interface PWA and to interface with the Store Processor PWA. In doing so, the Audio Processor accepts four channels of cockpit audio and then converts the audio to a digital byte oriented format suitable for storage in the solid–state crash protected memory (FCSSU). Refer to Description and Operation Section 8.B.(2) for an in–depth functional description of the Audio Processor PWA. The Logic Configurable Array (LCA), U13, on the Audio Processor provides a means to perform a closed–loop test, which isolates the Audio Processor PWA from the Store Processor PWA and the FCSSU. As such, component level fault isolation for the Audio Processor is described with the Audio Processor in the test mode.
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As with the Aircraft Interface PWA, fault isolation will be accomplished by listing key signals, describing the expected indications, and identifying the possible faulty circuitry. Once the probable circuitry is identified, the technician is expected to use traditional troubleshooting techniques to further isolate the fault. Set up the Audio Processor PWA for fault isolation as described below and refer to Table 107 for the Audio Processor PWA fault isolation procedure. Refer to the detailed schematic diagram of the Audio Processor PWA, Figure A3, given in Appendix A of this manual. (1)
Audio Processor PWA Fault Isolation Test Set–up This procedure is used to prepare the Audio Processor PWA for fault isolation. (a)
Place the Audio Processor PWA in a known good Model A100S recorder.
(b)
Connect the A100S to the Test Panel as illustrated in Figure 101.
(c)
Adjust the Audio Oscillator for a 3V rms, 1 kHz signal at the RECORDER INPUT terminals on the Test Panel right side when Channels 1, 2 or 3 are to be tested; when Channel 4 is to be tested, adjust for a 2V rms,1 kHz input signal.
(d)
At the Audio Processor PWA, connect point E40 to point E41. This will put the Audio Processor in the test mode.
(e)
Disconnect the connection between the Store Processor PWA Cable Assembly W2, plug P5 and the Aircraft Interface Cable Assembly W1, connector J5.
(f)
Turn power on at the Test Panel.
(g)
At the Audio Processor PWA, momentarily short point E38 to ground. This simulates the system reset pulse required to initiate the Audio Processor’s digital devices.
(h)
Using an oscilloscope, refer to Table 107 and check for the indications described in the fault isolation procedure. Be sure to perform the checks in the sequence described in the procedure. NOTE: Because of the complexity of the digital circuitry, the checks described in the fault isolation chart are not all encompassing; consequently, an identified check may measure as expected and the device might still be faulty at another output. As such, L3 recommends that if the technician cannot isolate a faulty Audio Processor PWA to the component level by following the fault isolation chart, the PWA should be sent back to the factory for repair.
Table 107 Audio Processor PWA Fault Isolation Procedure Test Point U3 pin 1
Signal Nomenclature VBB (–5V)
Functional Description –5V developed for use by the logic devices
Expected Value –5V +10%
Possible Faulty Stage / Comp. U3, C8, C14, C20, C23, C85
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Table 107 Audio Processor PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Value
Possible Faulty Stage / Comp.
U8 pin 5
MCLK1
MCLK1 is a 12.28 MHz crystal–oscillator generated signal applied to pin 1 & 2 of U2 to generate the various clocks required to drive the Audio Processor’s digital devices.
12.28 MHz square wave; approx. 5.0V pk–pk
U8, R6
U2 pin 8
kHz128
kHz128 is a square wave signal derived by U2 from the MCLKI signal. kHz128 is applied to pin 1 of PLD U1 as a clock.
128 kHz TTL level square wave
U2
U1 pin 10
DONE
DONE is a control signal applied to pin 4 of U11 and pin 55 of LCA U13.
Logic High (+5V)
U1, R42
U13 pin 75
XDCLK
XDCLK is an output clock from U13.
Logic Low U13 w/ high pulses
U16 pin 24
/RECFIFO_EMPTY
Control signal generated by FIFO, U16, and applied to the LCA, U13.
Logic High (+5V) High w/Neg. pulses
U16
U12 pin 24
/PLAYFIFO_EMPTY
Control signal generated by FIFO, U16, and applied to the LCA, U13.
square wave High w/Neg. Pulses
U12
U10 pin 8
V1IN
V1IN is the Channel 1 1 kHz analog input conditioned 1V pk–pk and buffered for application sine wave to the encoder/decoder U22.
NOTE: If the 1 kHz signal is present at pin 8, but the amplitude is incorrect perform the AP PWA Input, Gain Calibration procedure given in B.(2) on Page 133. U10 pin 7
V2IN
V2IN is the Ch. 2 analog 1 kHz input conditioned and 1V pk–pk buffered for application sine wave to the encoder/decoder U23.
NOTE: If the 1 kHz signal is present at pin 7, but the amplitude is incorrect perform the AP PWA Input, Gain Calibration procedure given in B.(2) on Page 133.
Adj. pot. R1, U6, U9, U10, T1, C1, C4, C6, C9, C10, C16, C25, C26, R17, R18, R19, R20, R21, R23, R24, R26, R28, R29, R30, R31, R32, R33, R34 Adj. pot. R3, U6, U9, U10, T2, C7, C11, C17, C21, C20, C32, C34, C35, R17, R18, R19, R20, R21, R23, R24, R26, R28, R29, R30, R31, R32, R33, R34
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Table 107 Audio Processor PWA Fault Isolation Procedure (Continued) Test Point U10 pin 14
Signal Nomenclature V3IN
Functional Description
Expected Value
V3IN is the Channel 3 1 kHz analog input conditioned 1V pk–pk and buffered for application sine wave to the encoder/decoder, U24. NOTE: If the 1 kHz signal is present at pin 14, but the amplitude is incorrect, perform the AP PWA Input Gain Calibration procedure given in B.(2) on Page 133.
U9 pin 1
AIN
AIN is the Channel 4 (AREA MIC) analog input conditioned and buffered for application to the encoder/decoder, U25.
Possible Faulty Stage / Comp. Adj. pot. R2, U6, U9, U10, T3, C2, C5, C12, C18, C19, C22, C34, C30, C31, R17, R18, R19, R20, R21, R23, R24, R26, R28, R29, R30, R31, R32, R33, R34
1 kHz 1V pk–pk sine wave
Adj. pot. R4, U6, U9, T4, C13, C5, C27, C33, C36, C37, R17, R18, R19, R21, R23, R29, R30, R31, R32, R33
NOTE: If the 1 kHz signal is present at pin 1, but the amplitude is incorrect, perform the AP PWA Input Gain Calibration procedure given in B.(2) on Page 133. U22 pin 2
V1OUT
V1OUT is the analog output of the encoder/decoder, U22. This signal is applied to summing amplifier network U14.
1 kHz sine wave approx. 2V pk–pk
U22, C28, R22, R25, R27, R36, R37
U23 pin 2
V2OUT
V2OUT is the analog output of the encoder/decoder, U23. This signal is applied to summing amplifier network U14.
1 kHz sine wave approx. 2V pk–pk
U22, C24, R22, R25, R27, R36, R37
U24 pin 2
V3OUT
V3OUT is the analog output of the encoder/decoder, U24. This signal is applied to summing amplifier network U14.
1 kHz sine wave approx. 2V pk–pk
U22, C15, R22, R25, R27, R36, R37
U25 pin 2
AOUT
AOUT is the analog output of the encoder/decoder, U25. This signal is applied to summing amplifier network U14.
1 kHz sine wave approx. 2V pk–pk
U22, C47, R22, R25, R27, R36, R37
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Table 107 Audio Processor PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Value
Possible Faulty Stage / Comp.
U14 pin 14
SUMMING_1
SUMMING_1 is the CH 1 equalized playback signal which is applied to summing amplifier network U5, U4, Q1 & Q2 to generate the COMBINED_AUDIO signal.
1 kHz approx. 3V pk–pk
U14, R35, R38, R39, R40, R41, R43, R46, C64, C66, C68, C71
U14 pin 1
SUMMING_2
SUMMING_2 is the CH 2 equalized playback signal which is applied to summing amplifier network U5, U4, Q1 & Q2 to generate the COMBINED_AUDIO signal.
1 kHz approx. 3V pk–pk
U14, R35, R38, R39, R40, R41, R43, R46, C67, C69, C70, C72
U14 pin 8
SUMMING_3
SUMMING_3 is the CH 3 equalized playback signal which is applied to summing amplifier network U5, U4, Q1 & Q2 to generate the COMBINED_AUDIO signal.
1 kHz approx. 3V pk–pk
U14, R35, R38, R39, R40, R41, R43, R46, C62, C63, C73, C75
U14 pin 7
SUMMING_A
SUMMING_A is the AREA MIC equalized playback signal which is applied to summing amplifier network U5, U4, Q1, & Q2 to generate the COMBINED_AUDIO signal.
1 kHz approx. 3V pk–pk
U14, R35, R38, R39, R40, R41, R43, R46, C65, C76, C78, C80
U4 pin 4
COMBINED_AUDIO COMBINED_AUDIO is the summation of the four audio input channels.
1 kHz sine wave approx. 10V pk–pk
U4, U5, Q1, Q2, CR4, CR5, R7, R10, R11, R12, R13, R15, R48 C81
U15 pin 8
TT_SQ
640 Hz sawtooth approx. 2V pk–pk
U13, U15, CR3, CR6, C77, R8, R9, R14, R16, R45
TT_SQ is only generated when the ALL TEST pushbutton is pressed on the Test Panel or the Control Unit. The Test Tone signal is a 640 Hz, + 20 Hz signal, generated by the LCA, U13.
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Table 107 Audio Processor PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Possible Faulty Value Stage / Comp.
U22 pin 13
XV1_PCM
XV1_PCM is the digitized output of encoder/decoder U22. This signal is applied to ADPCM Computational Processor, U17.
17.3 kHz sawtooth
U22
U23 pin 13
XV2_PCM
XV2_PCM is the digitized output of encoder/decoder U23. This signal is applied to ADPCM Computational Processor, U18.
17.3 kHz sawtooth
U23
U24 pin 13
XV3_PCM
XV2_PCM is the digitized output of encoder/decoder U23. This signal is applied to ADPCM Computational Processor, U19.
17.3 kHz sawtooth
U24
U25 pin 13
XA_PCM
XA_PCM is the digitized output of encoder/decoder U25. This signal is applied to ADPCM Computational Processors, U20 & U21.
17.3 kHz sawtooth
U25
U17 pin 24
RV1_PCM
RV1_PCM is the playback PCM from the Store Processor PWA and the FCSSU Memory. The signal is applied to encoder/ decoder U22 for conversion to an audio output.
17.3 kHz sawtooth
U18
U18 pin 24
RV2_PCM
RV2_PCM is the playback PCM from the Store Processor PWA and the FCSSU Memory. The signal is applied to encoder/ decoder U22 for conversion to an audio output.
17.3 kHz sawtooth
U18
U19 pin 24
RV3_PCM
RV1_PCM is the playback PCM from the Store Processor PWA and the FCSSU Memory. The signal is applied to encoder/ decoder U22 for conversion to an audio output.
17.3 kHz sawtooth
U18
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(2)
Audio Processor PWA Input Gain Calibration NOTE: This adjustment is factory calibrated and should not require field adjustment; however, the following procedure is provided in case it is felt that adjustment is necessary to troubleshoot the Audio Processor PWA. This procedure describes the adjustments of the input gain potentiometers for the four channels on the Audio Processor PWA. (a)
At the Test Panel, reset the test conditions according to that given in step (1) Audio Processor PWA Fault Isolation Test Set–up. Refer to Page 128.
(b)
At the Audio Processor PWA, connect the L3 Audio Monitor Adapter with Modification 1 (AMA/1), P/N 17TES0200, to connector J6 on the Audio Processor PWA (refer to Figure 107).
(c)
Using a “1/4–inch monophonic jack–to–BNC” test cable, connect the AC voltmeter to the respective AMA/1 jack for the A100S channel output to be adjusted. For Model A100S Channel 3
Connect To AMA/1 PILOT jack
Channel 2
CO–PILOT jack
Channel 1
SPARE jack
Channel 4
AREA jack
Combined Audio Channel
COMBINED jack
(d)
Set the Test Panel CHANNEL SELECT switch to the channel to be adjusted and proceed to step (e) or (g).
(e)
To adjust the gain of Channels 1, 2 or 3, verify that a 3V rms, 1 kHz input signal is applied from the Audio Oscillator to the Test Panel RECORDER INPUT terminals.
(f)
While monitoring the AC voltmeter, adjust the input gain for Channels 1, 2 and 3 on the Audio Processor PWA, so that a 1V rms +10% reading is obtained on the AC voltmeter; adjust channel controls as follows (refer to Figure 107 for location): Channel 1 – adjust potentiometer R1. Channel 2 – adjust potentiometer R3. Channel 3 – adjust potentiometer R2.
(g)
To adjust the gain of Channel 4, verify that a 2V rms, 1 kHz signal is applied from the Audio Oscillator to the Test Panel RECORDER INPUT terminals.
(h)
At the Audio Processor PWA, while monitoring the AC voltmeter, adjust the input gain for Channel 4 (Area Mic), using potentiometer R4 (refer to Figure 107), so that 1V rms +10% is obtained on the AC voltmeter.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
U11 CR2
R 5
R 6
C 44
U21
U12
U20
C 42
C41
U2
C 82
+ C 43
C40 U18
U13 U19
C 50
C88
U8 P1
U17 C 46 U1
C49 U16
J5
U24
U23
U22
P1
C 45
L1
U25 R44
J5
R42 CR1 C23
C20
C14
R37
R27
R25
R36
R43
R16 CR6
R39 C 77
R38
J6 J6
R 47
C15 C28
CR5
R41
R9
R40
R8
C72
C76
C68
C78
C63
C66
C65
C64
C67
C73
C69 C C 47 24
C8
C 58
R12
C 39
C30 R 34
U10
C 11
R11
R15 C R R 52 46 48
C81
Q2
U5 C7 C13 C2
R10
R R 21 23
C1
R33 T4
R29 C55
R4
C3 U3 T2
R2 U6 R3 R R 30 32
T3 R1
C60
U9 C37 C18 C35 C9 C61
C 79
U4 C 74
C36 C12 C34 C6 C C R 19 10 R 20 31
Q1
C 48
C C C C 27 31 21 26
C C 22 16 C51
C 38
U7
C C C C C R 17 R 80 71 62 70 C33 C5 C29 C4 22 C32 C25 R 26 R 28 24 C53
CR4
CR3
C75 C59
R13
C 57
U15
R7
R35
C86
R14 R45
C56
U14
C87
R49
R17
T1
R19 R18
R1 - R4
+
C C C 83 85 84
+ +
T1 - T4
Audio Processor PWA, P/N 205E0598–00, Component Layout Drawing Figure 107
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
(3)
Model A100S Frequency Response Measurement NOTE 1:
The frequency response of the A100S, for all practical purposes, is guaranteed due to the digitizing process; however, this test, which is described as the frequency response test is often a helpful troubleshooting tool. The electronic circuitry of the Model A100S can be categorized into two general categories: the analog signal–in conditioning circuitry and the memory interface circuitry to include the crash protected memory. The electronics of the analog section can be further divided into individual channel sections which aid in overall troubleshooting.
NOTE 2:
If the frequency response measurement does not check correctly, it is probably due to the encoder/decoder devices located on the Audio Processor PWA (U22 – U25). If that is not the case, refer to the troubleshooting charts for further fault isolation procedures.
(a)
At the Test Panel, reset the test conditions according to that given in step (1) Audio Processor PWA Fault Isolation Test Set–up. Refer to Page 128.
(b)
At the Audio Processor PWA, connect the L3 Audio Monitor Adapter (AMA/1), P/N 17TES0200, to connector J6 on the Audio Processor PWA (refer to Figure 107).
(c)
To monitor Channel 1, connect the SPARE jack to the AC voltmeter using the “1/4–inch monophonic jack–to–BNC” test cable.
(d)
While monitoring the output of Channel 1 with an AC voltmeter, slowly adjust the audio oscillator from 150 to 3500 Hz. The dip–to–peak deviation in the output should be less than or equal to 6 dB.
(e)
Repeat step (d) for Channel 2 connecting the “1/4–inch monophonic jack–to–BNC” test cable to the CO–PILOT jack and to the AC voltmeter.
(f)
Repeat step (d) for Channel 3 connecting the “1/4–inch monophonic jack–to–BNC” test cable to the PILOT jack and to the AC voltmeter.
(g)
For Channel 4 (Area Mic), connect the “1/4–inch monophonic jack–to–BNC” test cable to the AREA jack and to the AC voltmeter. Then, adjust the audio oscillator from 150 to 5000 Hz. Like the other channels, the dip–to–peak deviation in the output should be less than or equal to 6 dB.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
C. STORE PROCESSOR PWA FAULT ISOLATION The Store Processor PWA, P/N 205E0601–00 and 205E1027–00, interfaces the solid–state memory to the Audio Processor PWA via microprocessor U22. In order to provide thirty minutes of continuous recording, the Store Processor aligns the solid–state memory array like a nonvolatile circular buffer, which the Store Processor PWA writes to at the head of the circular buffer and erases at the end of the buffer. The Store Processor PWA can be functionally broken into a control management section and an interface section. Refer to Description and Operation Section 8.B.(3) for an in–depth functional description of the Store Processor PWA. As with the other PWAs in the Model A100S, the fault isolation has been developed such that key test points and signals are described along with their expected indications. If a fault is detected, the fault isolation chart directs the technician to the circuitry which is the probable cause of failure. Once the probable circuitry is identified, the technician is expected to use traditional troubleshooting techniques to further isolate the failure. Refer to the Audio Processor PWA Fault Isolation Test Set–up given in Section (1), Page 128 and setup as directed. Complete the Audio Processor PWA fault isolation procedure successfully and then reconnect the Store Processor PWA Cable Assembly W2/P5, step (e), to the Aircraft Interface Cable Assembly W1 connector J5. Refer to Table 108 and check for the indications described in the Store Processor PWA fault isolation procedure. Detailed schematic diagrams of the two Store Processor PWAs, P/N 205E0601–00 and 205E1027–00, are given in Appendix A, as Figure A4 and Figure A5, respectively.
Table 108 Store Processor PWA Fault Isolation Procedure Test Point
Signal Nomenclature
Functional Description
Expected Possible Faulty Value Stage / Comp.
U16 pin 1
VEE
VEE is a +5V dc supply provided because of the need to save memory pointers and other state variables at power down. VEE is applied to U24, pin 32. U24 is the non–volatile local memory.
+5V + 10%
U16, L3, CR1, CR4, C3, C4,C5, C12
U3 pin 5 (See Pg. A-36)
VPP
VPP is a +12V dc, + 5% supply voltage which is provided to power the crash–protected memory (FCSSU).
+12V + 5%
U3, CR3, L1, R4, C2, C9, C11
Y1 pin 5
CLKIN
CLKIN is a 32 MHz signal provided to micro– processor U22 as a clock signal.
32 MHz square wave approx. 2.5V pk–pk
Y1, R1
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Table 108 Store Processor PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Possible Faulty Value Stage / Comp.
U22
CLKOUT
CLKOUT is the 16 MHz clock output of micro– processor U22.
16 MHz sine wave approx. 2.5V pk–pk
U22
U14
ADR(9...0)
ADR(9...0) is the 10 LSBs of the local address bus.
TTL Data
U14
U10
ADR(19...8)
ADR(19...8) is the10 MSBs of the local address bus.
TTL Data
U10
U20 pin 16
/REC_RD
/REC_RD is the control signal used to read the data from the Audio Processor PWA.
High with negative transitions
U20
U19 pin 5
DLYDCLK
DLYDCLK is the CLKOUT delayed by 13 nanoseconds
16 MHz square wave approx. 2.5V pk–pk
U19
U4 pin 8
/WR_FLASH
/WR_FLASH is the control signal used to read and write data from the crash– protected memory.
Logic High with negative transitions
U14
TP1
/PWR_FAIL
/PWR_FAIL is a power watchdog signal which provides a logic “low” when the LOW_LINE signal goes below acceptable limits.
Logic High
U1, U2, U23, R1, R2, R3, R5, C14
TP2
/RST
/RST is the system reset control signal derived from the condition of the regulated +5V dc. On power–up, /RESET remains low for 35 to 70 ms after Vcc raises above +4.75V. On power–down, /RESET goes low whenever Vcc falls below +4.5V.
Logic High
U1, U2, U23, R1, R2, R3, R5, C14
U6 pin11 – 18
AD(15...8)
AD(15...8) are address bits interfaced from the Audio Processor PWA.
TTL Data
U6, U23, R7, R11
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Table 108 Store Processor PWA Fault Isolation Procedure (Continued) Test Point
Signal Nomenclature
Functional Description
Expected Value
Possible Faulty Stage / Comp.
U7 pin 11 – 18
AD(7...0)
AD(7...0) are address bits interfaced from the Audio Processor PWA.
TTL Data
U7
U12 pin 2 – 23
AD(8...0)
AD(8...0) are address bits interfaced from the Audio Processor PWA
TTL Data
U12
U15 pins 3, 5, 7, 9, 12, 14,16,18
FADR (14, 13, 11, 9, 7, 6, 4, 1)
These address signals are interfaced to the crash– protected (flash) memory.
TTL Data
U15
U13 pins 3, 5, 7, 12, 14, 16, 18
FADR (0, 2, 3, 5, 8, 10, 12)
These address signals are interfaced to the crash– protected (flash) memory.
TTL Data
U13
U18 pins 2–9, 11–18
AD(7...0) & D(7...0)
U18 buffers the least significant half of the data bus into and out of the crash–protected memory.
TTL Data
U18
U9 pins 2–11, 15–23
FADR(15...23)
Memory address lines
TTL Data
U9
U8 pins 2–11, 15–23
FADR(15...23)
Memory address lines
TTL Data
U8
U11 pins 7, 9–15
SEL(7...0)
Memory select lines
TTL Data
U11
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
11. CONTROL UNIT FAULT ISOLATION The Model A100S has been developed to work in conjunction with all existing L3 Control Units. The history of the Control Units is such that there are several variations of the basic control unit. As with the A100S fault isolation procedures, the Control Unit’s fault isolation procedures are presented in tabular (chart) form. The troubleshooting approach for the Control Units differs from the Model A100S in that Control Unit troubleshooting is based on fault recognition versus expected indication as in the Model A100S. This is due to the immense field experience related to the Control Unit. The Control Unit consists of physical connections for a phone jack, primary input/output connector, a meter and various pushbuttons, as well as the MIcrophone Preamplifier PWA (dynamic/condenser). The microphone preamplifier circuitry consists of a series of four amplifier/buffer stages and an AGC circuit. L3 recommends “half–split” troubleshooting methods be used on the preamplifier, largely due to the “flow–thru” nature of the circuitry. Refer to Figure 15 through Figure 24, in the Description and Operation Section for wiring diagrams of the different versions of the L3’ Control Units. Table 109 provides the system level troubleshooting procedure for the Control Unit. Refer to Table 110 for the procedure to troubleshoot Control Unit Microphone Preamplifiers 9300A030 and 93A263–01, Table 111 for the procedure to troubleshoot Control Unit Microphone Preamplifier 93A263–02 and to Table 112 for the procedure to troubleshoot Microphone Preamplifiers 9300A242, 93A266 and 93A266–01. Refer to Appendix A for schematic diagrams of the Control Unit Microphone Preamplifier PWAs (Figures A6 and A7).
Table 109 System Level Troubleshooting Procedure for Control Units Trouble
Probable Cause
1. Control Unit (a) does not work
2. Meter and switches do not work 3. Microphone inoperative or garbled
Control Unit wiring har– ness with opened or shorted leads
Remedy (1)
Check out internal wiring connections and repair if necessary.
(2)
Repair wiring.
Refer to the System Level Troubleshooting given in Table 105 (a)
Defective microphone
(1)
Switch to external mike and feed in 4 mV at 1 kHz. The output should be 0.4 to 0.5 Vac.
(b)
Microphone preamplifier board defective
(1)
Switch to external mike. Measure the output of the microphone with a 10 dB sound source. Level at 1 kHz to be 3 to 6 mV.
(2)
Replace Microphone preamplifier board and calibrate.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Table 110 Troubleshooting Procedure for Microphone Preamplifiers 9300A030 and 93A263–01 Trouble
Probable Cause
Correction
Low output, not distorted, no AGC
C21, Q5 shorted or R30, C5 open Q6 defective
Replace
Normal output, not distorted, no AGC
R28, C19, D3, R29 open, D2 or C20 shorted
Replace
No 1–kHz rolloff
C8 shorted or R10 open
Replace
No or improper attenuation
C11, C12 shorted, R15, R16, R17, R18, R19 open
Replace
No B+ at any transistor
D1 or R27 open or D1 reversed
Replace
Table 111 Troubleshooting Procedure for Microphone Preamplifiers 93A263–02 Trouble
Probable Cause
Correction
Low output, not distorted, no AGC
C8, Q5 or R10 shorted, C7 open Q6 defective
Replace
Normal output, not distorted, no AGC
R19, C14, D1, R18 open, D2 or C11 shorted
Replace
No 1-kHz rolloff
C5 shorted or R6 open
Replace
No or improper attenuation
C13, C16 shorted, R17, R29, R30, R31, R32 open
Replace
No B+ at any transistor
D4 or R27 open or D4 reversed
Replace
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
Table 112 Troubleshooting Procedure for Microphone Preamplifiers 9300A242, 93A266 and 93A266–01 Trouble
Probable Cause
Correction
Low output, not distorted, no AGC
C8, Q5 shorted or R10, C7 open
Replace
Normal output, not distorted, no AGC
R19, C14, D1, R18 open, D2 or C11 open
Replace
No or improper attenuation
C13 or C16 shorted, R17, R29, R30, R31, R27 open
Replace
No B+ at any transistor
D4 or R27 open
Replace
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
DISASSEMBLY 1. GENERAL This section contains all the information required to completely disassemble the Model A100S Solid– State Cockpit Voice Recorder and associated Control Units, Models A151/A151B and A152/A152B. This information is coordinated with the Testing and Fault Isolation section probable cause analysis. Access to subassemblies within the Model A100S is described such that there is minimal disturbance to other subassemblies. Loctite or other sealants are used at many places in this recorder. Exercise care when removing screws sealed with the adhesive. CAUTION: THE A100S PRINTED CIRCUIT ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL CIRCUIT BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
2. DISASSEMBLY INSTRUCTIONS Special tools, fixtures, and equipment needed to disassemble and repair the Model A100S are listed in Figure 901. NOTE: Numbers shown in parentheses in the following text and figures are the Illustrated Parts List (IPL) figure number followed by the IPL item number for a particular part; e.g., (7–100) for IPL Figure 7, Item 100. For items listed in the parts list but not illustrated, the item number is preceded by a “–”. In addition to the IPL figure references, each disassembly instruction is accompanied with an illustration showing specific assemblies in which the steps of procedure are related. The figures in this section contain the same figure/item number references identifying the piece parts of the assembly as the IPL figures, however, different views of the assemblies are provided to facilitate disassembly task actions.
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A. UNDERWATER LOCATING DEVICE (Beacon) (See Figure 301 or IPL Figure 2) The Underwater Locating Device (ULD) should be mounted on the A100S front panel so that the beacon water switch is facing to the down (refer to Figure 301, 2–160A and 2–160B). The ULD is equipped with a battery having a life expectancy of six years and may be manufactured by either the Dukane Corporation, P/N: DK120, or Benthos, P/N: ELP–362D. The two ULDs are identical in form, fit and function, so if a new replacement device is needed, it may be ordered directly from L–3 Aviation Recorders (L3AR). When ordering from L3AR, the L3AR part number must be used (Dukane: p/n 266E0305–01, Benthos: p/n 266E0305–02). 2-90 2-105
2-25
2-100
2-110 2-150
2-155
BOTTOM PLATE
2-160A 2-160B
2-155
Disassembly of Underwater Locating Device (ULD) and Dust Cover Assemblies Figure 301 As a general rule, the beacon should be removed from service on or before the expiration date printed on the beacon. The batteries installed in the beacons are field replaceable. Refer to service information provided from their respective manufacturers listed below for servicing and recertification. Dukane Corporation (Cage Code 94970) SeaCom Division, 2900 Dukane Drive St. Charles, IL 60174
Benthos (Cage Code 26858) 49 Edgerton Dr. North Falmouth, MA 02556
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BEACON REMOVAL PROCEDURE (1)
To remove the beacon (2–160A, 2–160B) from the Beacon Mount Assembly (2–150), use a 3/32” Allen hex-wrench, remove the four 8–32 screws (MS–51959–43) and #8 countersink lock-washers (MS–35336–17) that secure the cover plate to the bottom of the Beacon Mount Assembly (also refer to Figure 302). The beacon can now be removed through the bottom opening of the Beacon Mount Assembly (2–150).
(2)
If it is also necessary to remove the Beacon Mount Assembly (2–150), use a 3/16” Allen hex-wrench, remove the four 1/4–20, 3/4” hex-cap screws (2–155) that secure the Beacon Mount Assembly to the front panel (2–110).
(3)
If using the DK100 beacon, replacement of the beacon (2–125) battery should not be attempted in the field. The DK100 beacon should be returned to its respective manufacturer (address listed above) for battery replacement. A new replacement beacon (with six-year battery) may be ordered directly from Aviation Recorders using P/N 266E0305–01/–02.
NOTE:
The replacement beacon should always be inserted into the Beacon Mount Assembly (2–135) with the water switch end to the bottom and the battery replacement date facing to the front.
Beacon Mount Assembly
Cover Plate
Four #8 St. Steel 1508-00 Lockwashers MS-35336-17
Four HexĆcap Screws (2ć155)
Four 8ć32x3/8 Lg. Flat Head Screws MS-51959-43
Underwater Beacon Water Switch End
Disassembly of ULD Cradle Assembly for Beacon Access Figure 302
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
B. MAIN CHASSIS DISASSEMBLY (See Figure 301 or IPL Figure 2) (1)
(2)
Dust Cover (2–90) (a)
If the unit is installed in the aircraft rack mount, loosen the lock–down nuts from the two front panel hold–down retainers and disconnect the power/signal input connector from rear panel assembly. Slide the A100S from rack assembly. For further details on the aircraft installation of the unit, refer to the Model A100S Installation and Operating Instructions contained in FAR 04611238.
(b)
Remove the two 5/16” pan–head screws (2–100) which secure the dust cover to the rear panel of the chassis assembly.
(c)
Remove the single 3/8” pan–head screw (2–105) from the top front of the dust cover and slide main chassis assembly (2–25) forward out of the dust cover.
Front Panel Assembly Removal (See Figure 303 or IPL Figure 2) (a)
To remove and disassemble the front panel assembly (2–110), first remove the ULD Cradle assembly as described in Paragraph A.
(b)
Remove four 1/2” pan–head screws (2–180), which secure the two hold–down assemblies (2–175) along with the two pan–head screws (2–115) and fiber washers (2–120) at the top of the front panel.
(c)
Remove the Name Plate (2–130) by the removing four pan–head screws (2–135) that attach it to the front panel.
(d)
Loosen and remove the nut which attaches the Jack Cover (2–195) to Phone Jack assembly (2–190), this is part of the Voice Monitor Cable Assembly W3.
(e)
Gently separate the Front Panel assembly from the Front Isolator Plate (2–70) taking care not to damage the Front Panel Gasket (2–125).
(f)
To remove the handle assembly (2–165), loosen two 1/2” flat–head screws (2–170) from back side of front panel.
NOTE: The Dust Cover assembly does not need to be removed to remove and disassemble the Front Panel assembly.
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2-190
2-125
2-110 2-120 2-115
2-195
2-130 2-70 2-170
2-175 2-180
2-135
2-165
Disassembly of Model A100S Front Panel Assembly Figure 303 (3)
Audio Processor PWA Removal (See Figure 304 or IPL Figure 2 ) (a)
Remove chassis assembly (2–25) from dust cover as described in Step B.(1) and gently lay chassis on its right side.
CAUTION: ELECTROSTATIC DISCHARGE (ESD) WARNING: PRIOR TO HANDLING A PRINTED WIRING ASSEMBLY, ENSURE PROPER PERSONNEL ESD GROUNDING TECHNIQUES ARE USED. ONCE REMOVED, ENSURE THAT THE PRINTED WIRING ASSEMBLY IS PLACED INTO A STATIC SHIELDING CONDUCTIVE BAG.
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(b)
To gain access to the Audio Processor PWA (2–280), remove the card retainer assembly (2–85) by removing the two 1/2” flat–head screws (2–80) which hold it in place.
(c)
To remove the Audio Processor PWA (2–280), pull up on the left and right card guide locks (2–30) and (2–35) and gently pull card out of its slot.
2-80 Aircraft Interface PWA 2-245
2-85 2-248
2-35
Audio Processor PWA (2-280)
P2/J2 (6-310) FCSSU (2-200) Store Processor PWA
2-30
W2 (6-295) 2-25
J5/P1 (6-305)
2-247
Removal of Audio Processor and Store Processor PWAs Figure 304 (4)
Store Processor PWA Removal (See Figure 304 or IPL Figures 2, 5 & 6) (a)
Because the Store Processor Interface Cable Assembly W2 (6–295) is soldered directly to the Store Processor circuit board (5–25), plug P5 (6–300) of the cable assembly (refer to Figure 306) must be removed from the Aircraft Interface Cable Assembly connector J5/W1 (3–245) which is mounted to the chassis (refer to Figure 306).
(b)
Remove the four 3/16” flat–head screws (2–248) which mount the Store Processor PWA (2–247) to the FCSSU unit (refer to Figure 305).
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(c)
Carefully unplug P2 on the FCSSU Unit (2–200 / 2–200A) from connector J2 (6–310) on the Store Processor PWA.
(d)
Gently lift the Store Processor PWA up and away from plug P2 and the FCSSU assembly.
PLUG P5 (6-300)
INTERFACE CABLE ASSEMBLY W2 (6-295)
P2 Four 3/16" Flat-head Screws (2-248)
J2
FCSSU (2-200 / 2-200A)
Store Processor PWA (2-247)
Removal of Store Processor PWA From The Flash Crash Survivable Store Unit (FCSSU) Figure 305 (5)
Aircraft Interface PWA Removal (See Figure 306 or IPL Figures 2, 3 & 6) (a)
After removal of the Dust Cover assembly as described in Step B.(1) place the chassis in its upright position.
(b)
To gain access to the Aircraft Interface PWA (2–245), remove the Audio Processor PWA as described in Step B.(3) above.
(c)
To remove the Aircraft Interface PWA from the Chassis (2–25), the Aircraft Interface Cable Assembly W1 (3–230) must also be removed since this cable assembly is soldered directly to the circuit board.
(d)
To remove the Aircraft Interface Cable Assembly, unplug P5 of the Store Processor Cable Assembly W2 (6–295) from J5 (3–245) of the Aircraft Interface Cable Assembly W1 (3–230).
(e)
Disconnect J5 of the Aircraft Interface Cable Assembly from the chassis by removing two Phillips–head screws (2–60) and self–locking nylon insert nuts (2–65).
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
(f)
Disconnect J3 and J4 (2–240) of the Aircraft Interface Cable assembly from the Chassis assembly by removing four straight–slot screws (2–50) and low profile nuts (2–55).
(g)
The Aircraft Interface PWA is mounted to the rear of the chassis. To remove it, remove the five 1/4” flat–head screws (2–260) which mount the circuit board to the standoffs (2–265).
(h)
Remove the four 3/8” flat–head screws (2–255) which secure the Aircraft Interface main connector J1 to the rear of the chassis. Use caution that the three key mounting screws for J1 are not removed on the circuit board by mistake since these screws are accessible from the rear of the chassis and can be easily confused with the four intended mounting screws.
(i)
Disconnect the Aircraft Interface Transformer T1 (3–200) from the rear chassis panel by removing the single 1/4” flat–head screw (2–250). Once disconnected use care to support T1 so its connections to the circuit board are not damaged.
(j)
Carefully slide the Aircraft Interface PWA from the chassis assembly. The standoffs may cause the circuit board to jam between the chassis and closest card guide; consequently, exercise extreme care when removing it.
(k)
To remove the five mounting standoffs (2–265) from the Aircraft Interface PWA, loosen and remove the five 5/16” pan–head screws (2–270) and washers (2–275) from the non–component side of the circuit board. 2-60
J3/J4 of W1 3-240
J5/W1 3-245
2-50
Store Processor Interface Cable Assembly W2 (6-295) with Plug P5 (6-300)
2-25 2-65
2-260
Aircraft Interface Cable Assembly W1 (3-230)
2-250
2-255
2-55
Aircraft Interface PWA 2-265 2-245 2-270 2-275
Figure 306. Removal of Aircraft Interface PWA
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(6)
Flash Crash Survivable Store Unit Removal (See Figure 307 or IPL Figures 2, 5 & 6 )
CAUTION: THE FLASH CRASH SURVIVABLE STORE UNIT (FCSSU) IS A PRECISION ASSEMBLED UNIT WHICH MUST BE RETURNED TO THE FACTORY FOR SERVICING. ATTEMPTING TO DISMANTLE THE SEALED UNIT MAY CAUSE DAMAGE TO THE INTERNAL FLASH MEMORY BOARDS AND RESULT IN LOSS OF DATA. (a)
Remove the dust cover from the Chassis Assembly (2–25) as described in Step B.(1) and gently lay chassis on its right side.
(b)
Remove the Audio Processor PWA (2–280) from its card slot (J4) as described in Step B.(2) to gain access to the rear isolator plate.
(c)
Remove the Front Panel Assembly as previously described in Step B. (2) to gain access to the Front Isolator Plate (2–70); refer also to Figure 307.
NOTE: If it is not necessary to remove the Store Processor PWA along with the FCSSU (2–200), simply remove the four 3/16” flat–head screws (5–30) which secure the Store Processor PWA to the FCSSU (refer to Figure 305), disconnect P2 from J2, and carefully place the circuit board off to the side. If this is the case, omit the following step and proceed to step (e). (d)
To remove the Store Processor PWA with the FCSSU, the Store Processor Interface cable assembly W2 (6–295) plug P5 (6–300) must be disconnected from the Aircraft Interface Cable Assembly connector W1/J5 (3–245) located on the chassis as previously described in Step B.(4).
(e)
At the Front Isolator Panel (2–70), loosen and remove the two10–32 hex–head screws (2–240) and vibration mount spacers (2–235) used to secure the FCSSU to the two forward elastomeric shock mounts (2–205).
(f)
At the Rear Isolator Panel, loosen and remove the two 10–32 Phillips–head screws (2–230) that secure the FCSSU to the two rear elastomeric shock mounts (2–205). This will also detach one end of the grounding strap.
(g)
To remove the ground strap (2–5) from the Rear Isolator Panel, loosen and remove the single 5/16” pan–head screw (2–20) with washer (2–15) and hex nut (2–10).
(h)
Gently slide the FCSSU out from the chassis.
(i)
Return the FCSSU assembly to the factory for servicing.
NOTE: The two forward elastomeric shock mounts (2–205) and the two rear elastomeric shock mounts (2–205) should be carefully inspected at this time for wear and/or damage. If the elastomeric shock mounts need replacing, proceed to step (7).
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10-32 Phillips Screw (2-230)
Rear Isolator Panel
Elastomeric Shock Mount (2-205)
Front Isolator Panel (2-70) Store Processor PWA (See Note)
Vibration Mount Spacer (2-235)
10-32 Hex Screw (2-240)
FCSSU (2-200)
NOTE: Store Processor PWA, P/N 205E0601-00, is to be used only with FCSSU, P/N 253E0348-00. Store Processor PWA, P/N 205E1027-00, may be used with either FCSSU, P/N 253E0348-00, P/N253E0601-00 or 253E1293-00. Store Processor PWA, P/N 205E1027-01, may be used with either FCSSU, P/N 253E0992-00 or 253E1293-00.
Removal of Flash Crash Survivable Store Unit (FCSSU) Figure 307
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(7)
FCSSU Elastomeric Shock Mounts, P/N AM003–7 Removal (See Figure 308 and IPL Figure 2) (a)
Perform steps (a) through (h) of the FCSSU disassembly procedure.
(b)
Remove the damaged elastomeric shock mounts (2–205) from the front isolator panel by loosening and removing the two flat–head screws ((2–210) and nylon insert nuts (2–215).
(c)
Remove the damaged elastomeric shock mounts (2–205) from the rear isolator panel by loosening and removing the two pan–head screws ((2–220) from the captive nylon locking nuts (2–225).
(d)
Attach the new front and/or rear elastomeric shock mounts (2–205) to their respective isolator panel using the hardware removed in steps (2) and (3).
(e)
Return to the FCSSU assembly procedure F. (4) given in the Assembly Section for reinstalling the FCSSU.
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10-32 Phillips Screw (2-230)
Rear Isolator Panel
Elastomeric Shock Mount (2-205)
Front Isolator Panel (2-70) Vibration Mount Spacer (2-235)
(2-215)
Store Processor PWA (See Note)
10-32 Hex Screw (2-240)
(2-210) FCSSU (2-200)
(2-205)
(2-210)
Removal of FCSSU Elastomeric Shock Mounts, P/N AM003–7 Figure 308
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C. MODEL A151/A151B AND A152/A152B CONTROL UNIT DISASSEMBLY (See IPL Figure 7) NOTE:
(1)
This control unit disassembly procedure covers all models of the control unit used with the Model A100S. Disregard those steps and parts that do not pertain to the exact model of control unit being disassembled. For specific effectivity of parts to configuration, refer to the EFF Code column in IPL Figure 7.
Remove two 1/4” pan–head screws (7–65) with washers (7–60) and pull the dust cover (7–55) from the front panel assembly (7–15) and chassis assembly (7–90). NOTE: Do not perform the next step to remove the insulator unless replacement is necessary.
(2)
Remove insulator (7–70) from bottom of dust cover.
(3)
Remove Microphone Preamplifier PWA (7–155) from the chassis assembly by removing four 3/8” pan–head screws (7–160).
(4)
Remove front panel assembly (7–15) from chassis by removing four 3/8” pan–head screws (7–20).
(5)
Remove harness wires from the Microphone Preamplifier PWA (7–155), meter (7–25), switches (7–30 and 7–35), and phone jack (7–40). Remove microphone wires from harness assembly connector (7–80) or Microphone Preamplifier PWA (7–155) as appropriate for the type configuration.
(6)
Remove meter (7–25) by unscrewing the rear collar and pulling meter assembly from the face of the front panel assembly.
(7)
Remove green test switch (7–30) and red erase switch (7–35) by removing their associated nuts and washers and pulling the switches from the rear of the front panel assembly.
(8)
Remove the phone jack (7–40) by removing attaching plug (7–50), nut, washer and one shoulder washer (7–45) from the face of the front panel assembly while pulling the second shoulder washer (7–45) and phone jack (7–40) from the rear. NOTE: Perform the next step only if microphone or harness assembly replacement is necessary. The microphone is nested in a damper (7–105 and 7–135) and hum shield (7–115) which is cemented in place. Exercise caution when removing the microphone (7–110 and 7–140) and/or damper to prevent damage to the damper. Microphone cap (7–75), if installed in place of a microphone, may be removed at any time to facilitate disassembly, inspection, replacement or repair.
(9)
Remove the microphone (7–110 and 7–140) by removing the grommet (7–120) from the microphone damper assembly (7–105 and 7–135), loosen microphone cap (7–75) and washer (7–150) and pull free of microphone hum shield (7–115) from the face of the front panel assembly.
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ÀÀ ÀÀ ÀÀ
7-15 7-20
7-115 7-75
7-30 7-35 7-40
7-110 7-140
7-60 7-65
7-150 7-45 7-25 7-50
7-105 7-135 7-55
7-85 7-70 7-90 7-80
7-120 7-160
7-155
Disassembly of Model A151/A151B and A152/A152B Control Units Figure 309
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
D. ELECTRONIC CIRCUIT BOARD DISASSEMBLY (See IPL Figures 3–16) The procedures listed in this section are general in nature. The components used on the A100S printed wiring assemblies are advanced electrical circuits protected by conformal coating and are very heat, static and shock sensitive. Extreme care should be exercised when repairing these circuit boards. It is highly recommended that a defective circuit board be returned to the factory for repair. CAUTION: THE A100S PRINTED CIRCUIT BOARDS CONTAIN DEVICES THAT ARE SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL PRINTED CIRCUIT BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
(1)
Remove any circuit board assembly which needs replacement or repair as described in the previous steps. All of these circuit board assemblies are shown in detail in the Illustrated Parts List with their accompanying schematic diagrams located in Appendix A.
(2)
To remove protective conformal coating on the circuit board, rub the area around the damaged component with a cotton swab soaked with alcohol. Any residual coating can be removed by the soldering iron prior to desoldering terminals.
(3)
Protect the component to be removed by using a heat–sink clamp between the soldering point and the component itself.
(4)
Using an Endeco Model 300 vacuum desoldering iron, or equivalent, heat the connection on the terminal in question until the solder becomes liquid and remove it with the vacuum bulb.
(5)
Straighten the bent lead using needle–nose pliers and pull the component lead from the board.
(6)
Repeat Steps 2 through 5 for each component to be replaced.
(7)
Refer to the Assembly section of this Component Maintenance Manual for any special instructions on installing components.
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CLEANING 1. GENERAL This section contains a list of all required cleaning materials, general cleaning procedures, applicable cautions and warnings related to the use of any cleaning material, and instructions for cleaning the Model A100S major assemblies.
2. MATERIALS REQUIRED Refer to Table 401 for a listing of required cleaning materials:
Table 401 Cleaning Materials Required Material
Specification
Dry–Cleaning Solvent Isopropyl Alcohol Soft–Bristle Brush Cotton Swabs Lint–Free Cotton Cloth
Federal Specification P–D–680
NOTE: Equivalent substitutes may be used for all cleaning materials. All materials and chemicals may be obtained from any commercial source.
3. CLEANING PROCEDURES WARNINGS:
1) OBSERVE ALL FIRE PRECAUTIONS WHEN USING FLAMMABLE MATERIALS FOR CLEANING PURPOSES. 2) PERFORM OPERATIONS INVOLVING CLEANING SOLVENT IN A WELL– VENTILATED AREA. AVOID PROLONGED BREATHING OF VAPORS OR CONTACT WITH SKIN.
CAUTION: THE A100S PRINTED CIRCUIT ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL CIRCUIT BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
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CAUTION: DO NOT IMMERSE ANY PRINTED WIRING ASSEMBLY MOUNTED ELECTRONIC PARTS IN THE CLEANING SOLVENT; OTHERWISE, CIRCUIT BOARD AND/OR COMPONENT DAMAGE MAY RESULT.
A. PRINTED WIRING ASSEMBLY CLEANING (1)
Remove dust, dirt, and foreign matter from all surfaces, using soft–bristle brush.
(2)
Wipe finished surfaces and contacts, using a cloth moistened in solvent.
(3)
After replacing any components, clean all solder joints with solvent prior to recoating the repaired area.
B. CONNECTOR CLEANING Wipe dust and dirt from connectors, using a lint–free cloth, moistened with solvent.
C. MACHINED METAL PARTS CLEANING (1)
Blow dust from surface, holes, and recesses with an ionized air nozzle.
(2)
Remove bulk of surface grease and dirt with rags.
(3)
Immerse metal parts in a washing bath of solvent and scrub until clean.
(4)
Remove parts from bath and permit to dry.
(5)
Immerse parts in a rinsing bath; rinse and remove from bath. Do not permit solution to remain trapped in holes and recesses during draining.
(6)
Dry in a dust–free area.
D. UNDERWATER LOCATING DEVICE (Beacon) CLEANING The Model A100S beacon water switch should be kept clean by wiping with a soft lint-free cloth at least once every 24 months (more frequently under high humidity conditions). The beacon cradle is positioned on the A100S front panel so that the water switch is facing down; refer to Figure 401 for manner of installation. The beacon cleaning procedure requires no disassembly and consists only of cleaning the center contact of the beacon water switch. Make sure the beacon case and water switch are free of dirt and/or grease film. If necessary, take the beacon out of the mounting bracket assembly as shown in Figure 401 and wipe clean with approved cleaning agent. The water switch end insulator must be free of dirt, lint, or moisture to prevent current from leaking across the switch. As an added note, there are two types of beacons used with the Model A100S. Each is equipped with a battery having an expected life of six years. The two approved beacons are the Dukane beacon, P/N DK120, and a Benthos beacon, P/N ELP–362D. The two beacons are identical in form, fit, and function but carry different part numbers. The Dukane beacon, p/n: 266E0305-01, and the Benthos beacon, p/n: 266E0305-02, may be ordered directly from Aviation Recorders using these numbers.
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As a general rule, the beacon should be removed from service on or before the expiration date printed on the beacon. The batteries installed in the DK120 or ELP–326D beacons are field replaceable. Refer to service information provided from their respective manufacturers listed below for servicing and recertification. Dukane Corporation
(Cage Code 94970) SeaCom Division, 2900 Dukane Drive St. Charles, IL 60174
Benthos (Cage Code 26858) 49 Edgerton Dr. North Falmouth, MA 02556
Beacon Mount Assembly
Cover Plate
Four #8 St. Steel 1508-00 Lockwashers MS-35336-17
Four HexĆcap Screws (2ć155)
Four 8ć32x3/8 Lg. Flat Head Screws MS-51959-43
Underwater Beacon Water Switch End
Underwater Locating Device (ULD) Beacon Water Switch Location Figure 401
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CHECKS 1. GENERAL This section contains the various checks that should be performed on the Model A100S Solid–State Cockpit Voice Recorder during shop maintenance. Check procedures are written in step–by–step procedures wherever practicable, and include specific methods, techniques, and equipment required. Electrical set up and checks are given in the Testing and Troubleshooting Section of this Component Maintenance Manual. There is no periodic maintenance requirements for the A100S SSCVR. CAUTION: THE A100S PRINTED CIRCUIT ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL CIRCUIT BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
2. CHECKS A. MAIN RECORDER ASSEMBLY (1)
Check the general physical integrity of the recorder; i.e. front panel switches, microphone jack, Underwater Locating Device and rear panel connector pins.
(2)
Check that dust cover is serviceable, exhibiting no undue deterioration and is properly painted.
B. MECHANICAL INSPECTION (1)
Remove the unit dust cover.
(2)
Inspect all parts for cracks, distortion, excessive wear, and proper finish.
(3)
Inspect all cast parts for cracks, especially at bosses, flanges, and other critical areas.
(4)
Inspect all terminal boards and connectors for loose terminals, pins, locking rings and screws, and cracks in the boards that may have been brought about by environmental conditions.
(5)
Check all wire leads for broken conductors, burnt or deteriorated installation, and loose connections.
(6)
Check the electronic circuit boards for broken parts and bad solder joints. Check for burnt parts. Check the boards for cracks and abrasions.
(7)
Inspect the nameplate for legibility.
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C. ELECTRICAL INSPECTION Perform all test set–up and testing per instructions given in the Testing and Troubleshooting Section of this Component Maintenance Manual.
D. UNDERWATER LOCATING DEVICE (ULD) INSPECTION The ULD beacon used in the A100S is equipped with a battery having an expected life of sixyears. Detailed procedures for testing the Underwater Locating Device are located in the Beacon section of Table 102. The beacon should be removed from service on or before the expiration date printed on the beacon. The batteries installed in the DK120 or ELP–326D beacons are field replaceable. Refer to service information provided from their respective manufacturers listed below for servicing and recertification. The ULD used with the Model A100S may be manufactured by either the Dukane Corporation (P/N DK120) or Benthos (P/N ELP–362D); their addresses are as follows: Dukane Corporation
(Cage Code 94970) SeaCom Division, 2900 Dukane Drive St. Charles, IL 60174
Benthos (Cage Code 26858) 49 Edgerton Dr. North Falmouth, MA 02556
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REPAIR 1. GENERAL This section is intended to contain information required to restore a worn or damaged part to a serviceable condition. Since the Model A100S is a completely solid–state device containing no electro– mechanical moving parts, the information presented herein applies only to the repair of a printed wiring assembly. The components used on the PWA circuit boards of the Model A100S are advanced electrical circuits protected by conformal coating and are heat, static and shock sensitive. Extreme care should be used when repairing these boards. It is highly recommended that a known bad circuit board be returned to the factory for repair. If in–field repair of a printed wiring assembly is necessary (such as board surface damage or replacing damaged electrical components such as capacitors, resistors, transistors, transformers, and integrated circuits), refer to the Disassembly Section if its removal is not obvious and to the Illustrated Parts List Section for its parts listing. Replace all components not meeting the requirements outlined in the Testing and Troubleshooting Section. Remove loose conductive material in accordance with the Cleaning Section. Table 601 lists the basic repair materials required.
Table 601 Repair Materials Required Item
Manufacturer and Specification
Use
1. Soldering iron
25–watt pencil tip and standard IC tips
PWA component removal
2. Solder
Tin lead rosin core 60/40 per QQ–S–571
To tin all component leads and wires
3. Adhesive
Methylene dichloride cracks and fractures
For repairing minor
CAUTION: THE MODEL A100S PRINTED WIRING ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE CIRCUIT BOARD USELESS. PRIOR TO HANDLING A CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, WHEN THE CIRCUIT BOARDS ARE TO BE STORED, ENSURE THAT THEY ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
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2. REPAIR PROCEDURES A. PRINTED WIRING ASSEMBLIES (Refer to applicable IPL Figures.) CAUTION:
(1)
USE A PAIR OF LONG–NOSED PLIERS OR OTHER SUITABLE HEAT SINK PROTECTION WHEN REMOVING HEAT–SENSITIVE COMPONENTS SUSPECTED OF BEING FAULTY. THE SAME APPLIES WHEN INSTALLING NEW HEAT–SENSITIVE COMPONENTS
Do not remove any component from the circuit board unless deemed faulty. To remove a component, unsolder the appropriate leads using a 25–watt pencil tip soldering iron. Tag the unsoldered leads to facilitate reassembly. Verify polarity and or orientation of the component. CAUTION:
IN ADDITION TO USING A PROPER HEAT SINK WHEN SOLDERING A SOLID–STATE DEVICE, EXERCISE EXTREME CARE TO USE A MINIMUM OF HEAT WHILE SOLDERING TO PREVENT DAMAGE TO THE CIRCUIT BOARD.
(2)
All components must be physically secured to the non–printed side of the circuit board by inserting the leads in the appropriate holes and bending the ends of the lead wires inward approximately 1/8 inch. The part should make physical contact with the board. Also, make certain all component markings or values face upward and are readable.
(3)
Make certain all connections are mechanically strong before attempting to solder. Solder per MIL–S–6872.
(4)
Remove any old or excessive solder as required.
(5)
Remove flux residue with Alpha No. 563 cleaner and flux remover. Perform final wash in clean solution of the same cleaner.
(6)
Apply protective coating (PC18 or PC29M manufactured by Hysol Division of Dexter Corporation or Conathane 1155 per MIL–I–46058 type PUR) to all reworked areas of the circuit board as follows: (a)
Ensure that printed circuit board is clean and dry.
NOTE: The protective coating is to be applied only to components that have been replaced. (b)
Coating may be sprayed or applied with a brush.
(c)
Cure coating per manufacturer instructions.
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ASSEMBLY 1. GENERAL This section contains detailed step–by–step procedures describing the complete assembly of the Model A100S Recorder. Any testing during assembly is also included as well as storage instructions after assembly.
2. REQUIRED MATERIALS Refer to Table 701 for a tabular listing of required assembly materials. There are no special tools or equipment required during assembly. Special equipment required for unit testing can be found in Table 901 of the Special Tools, Fixtures, and Equipment Section.
3. ASSEMBLY INSTRUCTIONS CAUTION: THE MODEL A100S PRINTED WIRING ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A CIRCUIT BOARD SHOULD COMPLY WITH PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE CIRCUIT BOARD USELESS. PRIOR TO HANDLING A CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT THE CIRCUIT BOARD IS PLACED INTO A STATIC SHIELDING CONDUCTIVE BAG WHEN HANDLING OR STORING. ESD WARNING SYMBOL
SYMBOL FOR ESD GROUND CONNECTING POINT
A. GENERAL ASSEMBLY TECHNIQUES Though procedures listed in this section are general in nature, some of the circuit components require special handling and preparation before installation. The components used on the PWA circuit boards of the Model A100S are advanced electrical circuits protected by conformal coating and are heat, static and shock sensitive. Extreme care should be used when repairing these boards. It is highly recommended that a known bad circuit board be returned to the factory for repair. NOTE: Numbers shown in parentheses in the following text are the Illustrated Parts List (IPL) figure number followed by the IPL item number for a particular part; e.g., (8–115) for IPL Figure 8, Item 115. For items listed in the parts list but not illustrated, the item number is preceded by a “–”. (1)
Remove old solder and make connections mechanically secure before resoldering.
(2)
Sleeve component leads and jumper wires as required to prevent shorting.
(3)
Use 60/40 solder (Item 1, Table 701) throughout.
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Table 701 Required Assembly Materials (Sheet 1 of 2) Item
Manufacturing and Specification
Use
1. Solder
Resin core 60/40 per QQ–S–571
All Component leads and wires.
2. Protective coating
PC18 or PC29M manufactured by Hysol Division of Dexter Corp. [V04347], 211 Franklin St., Olean, NY 14760 or Conathane 1155 per MIL–I–46058 type PUR.
Printed wiring assembly coating and solder connections.
3. Cleaner/flux remover
Alpha No. 563
Clean new solder joints.
4. Primer
Loquic primer, Grade N No. 88–21 manufactured by Loctite Corp., 705 N. Mountain Rd., Newington, CT 06111 [V05972]
Primer for items 5, 6, 7, 8.
5. Adhesive
Loctite, Grade A manufactured by Loctite Corp., 705 N. Mountain Rd., Newington, CT 06111 [V05972]
Retain screws.
6. Adhesive
Loctite, Grade C No. 84–21 manufactured by Loctite Corp., 705 N. Mountain Rd., Newington, CT 06111 [V05972]
Retain screws.
7. Adhesive
Loctite, No. 222 Lock/sealant manufactured by Loctite Corp., 705 N. Mountain Rd., Newington, CT 06111 [V05972]
Retain screws.
8. Adhesive
Loctite, No. 242 Lock/sealant manufactured by Loctite Corp., 705 N. Mountain Rd., Newington, CT 06111 [V05972]
Retain screws.
9. Adhesive
Glyptal No. 1201 manufactured by General Electric Co., Silicone Products Business Dept., Waterford, NY 12188 [V01139]
Retain screws.
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Table 701 Required Assembly Materials (Sheet 2 of 2) Item
Manufacturing and Specification
Use
10.
Adhesive
Rubber cement No. EC847 manufactured by Minnesota Mining and Mfg. Co., Adhesive Coatings and Sealers Div., 3M Center, St. Paul, MN 55101 [V04963]
Secure gasket to cover.
11.
Adhesive
RTV–108, G. E.
Sealant, Gen. Purp.
12.
Adhesive
RTV 162 white
Secure components.
13.
Adhesive
RTV–106 red
Secure components.
14.
Tubing
Shrink tubing, black, 0.063 I.D. No. FIT–221–1/16 manufactured by Alpha Wire Corp, 711 Lidgerwood Ave., Elizabeth, NJ 07207 [V92194]
Insulate wire leads.
15.
Tubing
Shrink tubing, white 3/16 thermo–fit No. RNF–100–3/16–WHT manufactured by Raychem, [V06090]
Insulate wire leads.
16.
Wire
No. 26 AWG hook–up wire, TFE Teflon, 14/38 strand, 0.041 O.D., red
Electrical wiring.
17.
Wire
No. 26 AWG hook–up wire, TFE Teflon, 19/38 strand, 0.041 O.D., orange
Electrical wiring.
18.
Wire
No. 20 Stranded Wire, White 600 V.
Electrical wiring.
19.
Lubricant
810–346 manufactured by Dukane, Ultrasonic Division, St. Charles, IL 60174 [V94970]
Lubricate ULD O–ring and threads
20.
Sealant
Compound Silicon RBR Dow Corning
Sealant, Gen. Purp.
21.
Adhesive
RTV–3145, Corning
Sealant, Silicone Rbr.
22.
Jumper
Wire, #22 BUSS SOLID – L3 P/N 2769900008
Jumper Wire
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B. GENERAL CIRCUIT BOARD ASSEMBLY (See applicable IPL Figures) (1)
After removal of a defective component from a circuit board following the procedures described in DISASSEMBLY, the following procedures must be followed when replacing the electronic components. (a)
All components must be physically secured to the non–printed side of the circuit board by inserting the leads in the appropriate holes and bending the ends of the lead wires inward approximately 1/8 inch. The part should make physical contact with the board.
(b)
All terminal posts should be riveted in place before soldering.
(c)
Leads from components mounted to terminal posts must have a minimum 300 wraparound.
(d)
Component markings or values should face upward and be readable.
(e)
On all IPL and schematic drawings, the (square) pad indicates (+) positive end of capacitors, cathode end of diodes and mechanical orientation of symmetrical multi– leaded devices.
(2)
Solder components in place (following the appropriate schematic) with a small pencil iron rated at no more than 25 watts. Use rosin core 60/40 solder (Item 1, Table 701).
(3)
Remove flux residue with Alpha No. 563 cleaner and flux remover (Item 3, Table 701). Perform final wash in clean solution of the same cleaner.
(4)
Apply protective coating (Item 2, Table 701) to all repaired areas as follows: (a)
Ensure that printed wiring boards are clean and dry.
NOTE: Protective coatings are to be applied only to components that have been replaced. (b)
Coating may be sprayed, applied with a brush, or board may be dipped.
(c)
Cure coating per manufacturer instructions.
C. AIRCRAFT INTERFACE PWA, P/N 205E0597–00 (See IPL Figures 2 & 3) (1)
Special installation Instructions for components on this circuit board are as follows: (a)
Connect transformer T1 to the board per the following list using #20 stranded white wire (Item 18, Table 701) and cover terminals with white tubing (Item 15, Table 701). T1–1 T1–2 T1–3 T1–4
(b)
to to to to
E5 E6 E7 E8
After installing T1, generously apply silicon sealant (Item 20, Table 701) on the non– component side for 115 volt protection over the following pins: J1–2, J1–3, C16, C17, CR14, CR25, E5, E6, L1–L3, and C35–C38.
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(c)
Apply silicon sealant (Item 20, Table 701) generously as follows: under between
U2, U3, C19 and C22; CR7 & CR3, CR3 & CR4, CR4 & CR8, CR5 & CR6, CR6 & CR1, CR1 & CR2. at base of CR31.
(2)
(d)
When installing connector J1 (3–210) only use one of the mounting screws (3–220) and washers (3–215) where shown in IPL Figure 3. Apply locking compound (Item 7, Table 701) to threads of screw (3–220).
(e)
Install power supply (3–55) with washers (3–60) between part body and printed wiring board on each pin.
(f)
Install transistor pads (3–75/3–90) beneath CR3 (3–70) and Q1 (3–85), respectively.
(g)
Install the five mounting standoffs (2–265) to the Aircraft Interface board, using five 5/16” pan–head screws (2–270) and washers (2–275) on the non–component side of the board.
Installation of Aircraft Interface PWA into Chassis assembly: (a)
It is assumed that the Audio Processor PWA (2–280) is not in its card slot, J4, since this interface connector is an integral part of the Aircraft Interface Cable Assembly W1 (3–230).
(b)
To install the Aircraft Interface PWA into the Chassis (2–25), the Aircraft Interface Cable Assembly W1 (3–230) must also be installed since this assembly is hard soldered to the board.
(c)
Attach connectors J3 (2–240) and J4 (2–240) of the Aircraft Interface Cable Assembly W1 to the Chassis assembly by installing four straight–slot screws (2–50) and low profile nuts (2–55).
(d)
Attach J5 of the Aircraft Interface Cable Assembly W1 to the Chassis assembly by installing two Phillips screws (2–60) and self–lock nylon insert nuts (2–65).
(e)
Connect plug P5 of the Store Processor Cable Assembly W2 (6–300) to connector J5 (3–245) of the Aircraft Interface Cable Assembly W1 (3–230).
(f)
Carefully slide the Aircraft Interface PWA into the chassis assembly while supporting transformer T1. Exercise care while positioning the board in place since the board standoffs may cause it to jam between the chassis and the closest card guide; do not force board.
(g)
Mount the Aircraft Interface transformer T1 (3–200) to the rear chassis panel by installing the single 1/4” flat–head screw (2–250).
(h)
Attach the four 3/8” flat–head screws (2–255) which secure the Aircraft Interface main connector, J1, to the rear of the Chassis.
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(i)
Attach the five 1/4” flat–head screws (2–260) which mount the PWA to the standoffs (2–265).
(j)
Once the Aircraft Interface PWA is secured in place, install the Audio Processor PWA by sliding it into its card slot (Aircraft Interface Cable Assembly W1 connector J4) and securing it in place by pushing down on the left and right card guide locks (2–30) and (2–35).
(k)
Attach the card retainer assembly (2–85) by installing two 1/2” flat–head screws (2–80).
(l)
Slide the chassis assembly (2–25) into the dust cover (2–90 and attach with the single 3/8” pan–head screw (2–105) in the top front of the dust cover and with the two 5/16” pan–head screws (2–100) which secure the dust cover to the rear panel of the chassis assembly.
D. AUDIO PROCESSOR PWA, P/N 205E0598–00 (See IPL Figures 2 & 4) (1)
Special installation Instructions for components on this circuit board are as follows: (a)
(2)
Apply a thin coat of adhesive (Item 21, Table 701) to the inside of the transformer covers (4–360) which attach to T1–T4 (4–355).
Installation of Audio Processor PWA into the Chassis assembly: (a)
Install the Audio Processor PWA by sliding it in its card slot (connector J4 of the Aircraft Interface Cable Assembly W1) and securing it by pushing down on the left and right card guide locks (2–30) and (2–35).
(b)
Attach the card retainer assembly (2–85) by installing two 1/2” flat–head screws (2–80).
(c)
Slide the chassis assembly (2–25) into the dust cover (2–90 and attach with the single 3/8” pan–head screw (2–105) in the top front of the dust cover and with the two 5/16” pan–head screws (2–100) which secure the dust cover to the rear panel of the chassis assembly.
E. STORE PROCESSOR PWA, P/N 205E0601–00 and P/N 205E1027–00 (See IPL Figures 2, 5 & 6) (1)
Special installation instructions for circuit board, P/N 205E0601–00, are as follows: (a)
Install C8 (6–275) under U5 (6–45) between its socket strips (6–50).
(b)
Install C7 & C13 (6–285) under U4 (6–25) between its socket strips (6–30).
(c)
Install C10 (6–255) under U22’s (6–100) socket (6–105).
(d)
Install C15 (6–245) under Y1 (6–125).
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(2)
(e)
Install dip capacitors C1XX (6–225, 230, 235, 240, 250 & 260) in the same holes as their corresponding integrated circuits UXX. Note: the reference designators for the dip capacitors are similar to their corresponding IC’s plus 100. For example: C123 is located under U23, etc.
(f)
When installing C102 (6–250) under U2 (6–125) be sure to orient C102 correctly, the power pins for U2 are pins 2 and 3.
(g)
When installing U24’s (6–110) socket (6–115), remove pin 1 completely.
Installation of Store Processor PWA (5–5) onto the FCSSU (2–200). NOTE: Store Processor PWA, P/N 205E0601–00 is to only be used with FCSSU, P/N 253E0348–03 (2 megabit). Store Processor PWA, P/N 205E1027– 00 is intended for use with FCSSU P/N 253E0660–00 (8 megabit); however, it may be used with either FCSSU.
F.
(a)
Position the Store Processor PWA on the FCSSU and mate connector J2 (6–310) to FCSSU plug P2.
(b)
Using four 3/16” flat–head screws (5–30) secure the Store Processor PWA to the FCSSU.
(c)
Connect plug P5 (6–300) of the Store Processor Interface Cable Assembly, W2, (6–295) to connector J5 (3–245) of the Aircraft Interface Cable Assembly, W1.
FLASH CRASH SURVIVABLE STORE UNIT (FCSSU), P/N 253E0348–03, P/N 253E0660–00 and P/N 253E1293–00 (See Figure 701 and IPL Figures 2, 5 & 6) Prior to installing the FCSSU assembly (2–200) into the chassis, the Audio Processor circuit board and front panel assembly must be removed. (1)
Remove Chassis assembly (2–25) from dust cover as described in DISASSEMBLY Step B.(1).
(2)
Remove front panel assembly as previously described in DISASSEMBLY Step B.(2) to gain access to the front plate isolator panel (2–70).
(3)
Remove the Audio Processor PWA (2–280) from its card chassis slot as described in DISASSEMBLY Step B.(3) to gain access to the rear isolator plate. NOTE: The front and rear elastomeric shock mounts (2–205) should be checked at this time for possible damage. If it is necessary to replace an elastomeric shock mount (2–205), proceed to the instructions given in G. Otherwise, proceed to the next step herein.
(4)
If not already mounted, mount the Store Processor PWA to the FCSSU as instructed in previous Step E.(2). NOTE: Store Processor PWA, P/N 205E1027–00 may be used with either FCSSU (2 megabit or 8 megabit); however, Store Processor PWA, P/N 205E0601–00 can only be used with FCSSU P/N 253E0348–03 (2 megabit).
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(5)
If not already attached, attach the chassis end of the ground strap (2–5) to the rear isolator panel with the single 5/16” pan–head screw (2–20) with washer (2–15) and hex nut (2–10).
(6)
Carefully slide the FCSSU assembly (2–200) into its position in the chassis.
(7)
Secure the FCSSU to the front elastomeric shock mounts (2–205) using the two 10–32 hex–head screws and vibration mount spacers.
(8)
Secure the FCSSU to the rear elastomeric shock mounts (2–205) using the two 10–32 Phillips–head screws. Attach the grounding strap (2–5) to one of the Phillips–head screws.
(9)
Connect Store Processor Cable Assembly W2 (6–295) plug P5 (6–300) to connector J5 (6–300) on the Aircraft Interface Cable Assembly (3–245).
(10) Install the Audio Processor circuit board into its card slot (Aircraft Interface Cable Assembly W1 connector J4) and secure it in place by pushing down on the left and right card guide locks (2–30) and (2–35). (11) Attach the card retainer assembly (2–85) by installing two 1/2” flat–head screws (2–80). (12) Reinstall the front panel assembly. (13) Slide the chassis assembly (2–25) into the dust cover (2–90 and attach with the single 3/8” pan–head screw (2–105) in the top front of the dust cover and with the two 5/16” pan–head screws (2–100) which secure the dust cover to the rear panel of the chassis assembly.
G. FCSSU ELASTOMERIC SHOCK MOUNTS, P/N AM003–7 (See Figure 702 and IPL Figure 2) (1)
Perform steps (1) through (3) of the FCSSU procedure.
(2)
Remove the damaged elastomeric shock mounts (2–205) from the front isolator panel by loosening and removing the two flat–head screws ((2–210) and nylon insert nuts (2–215).
(3)
Remove the damaged elastomeric shock mounts (2–205) from the rear isolator panel by loosening and removing the two pan–head screws ((2–220) from the captive nylon locking nuts (2–225).
(4)
Attach the new front and/or rear elastomeric shock mounts (2–205) to their respective isolator panel using the hardware removed in steps (2) and (3).
(5)
Return to the FCSSU procedure for reinstalling the FCSSU.
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10-32 Phillips Screw (2-230)
Rear Isolator Panel
Elastomeric Shock Mount (2-205)
Front Isolator Panel (2-70) Store Processor PWA (See Note)
Vibration Mount Spacer (2-235)
10-32 Hex Screw (2-240)
FCSSU (2-200)
NOTE: Store Processor PWA, P/N 205E0601-00, is to be used only with FCSSU, P/N 253E0348-00. Store Processor PWA, P/N 205E1027-00, may be used with either FCSSU, P/N 253E0348-00, P/N253E0601-00 or 253E1293-00. Store Processor PWA, P/N 205E1027-01, may be used with either FCSSU, P/N 253E0992-00 or 253E1293-00.
Figure 701. Installation of Flash Crash Survivable Store Unit (FCSSU)
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10-32 Phillips Screw (2-230)
Rear Isolator Panel
Elastomeric Shock Mount (2-205)
Front Isolator Panel (2-70) Vibration Mount Spacer (2-235)
(2-215)
Store Processor PWA (See Note)
10-32 Hex Screw (2-240)
(2-210) FCSSU (2-200)
(2-205)
(2-210)
Installation of FCSSU Elastomeric Shock Mounts, P/N AM003–7 Figure 702
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H. MODEL A151/A151B & A152/A152B CONTROL UNITS (See IPL Figure 7) NOTE: This Control Unit assembly procedure covers the A151/A151B and A152/A152B and alternate models of the Control Unit used with the Model A100S. Disregard those steps and parts that do not pertain to the exact model of Control Unit under assembly. For specific effectivity of parts to configuration, refer to the EFF Code column in IPL Figure 7. (1)
Install the microphone (7–110/7–140) by threading the microphone cable through the grommet (7–125), microphone bracket assembly (7–90), microphone damper assembly (7–105/7–135) and hum shield assembly (7–115).
(2)
Install the phone jack (7–40) by attaching plug (7–50), nut, washer and one shoulder washer (7–45) to the face of the front panel assembly (7–15) while attaching the second shoulder washer (7–45) and phone jack (7–40) to the rear.
(3)
Attach green test switch (7–30) and red erase switch (7–35) by inserting the switches from the rear of the front panel assembly and installing their associated nuts and washers and the switches to front panel assembly.
(4)
Install meter (7–25) by inserting it from the rear of the front panel assembly and screwing the rear attaching collar.
(5)
Install the harness wires to the preamplifier assembly (7–155), meter (7–25), switches (7–30 and 7–35), and phone jack (7–40). Install microphone wires from harness assembly connector (7–80) or preamplifier assembly (7–155) as appropriate for the type configuration.
(6)
Attach front panel assembly (7–15) to chassis by installing four 3/8” pan–head screws (7–20).
(7)
Install preamplifier assembly (7–155) to the chassis assembly by inserting four 3/8” pan– head screws (7–160).
(8)
Ensure insulator (7–70) is attached to bottom of dust cover.
(9)
Attach front panel assembly (7–15) and chassis assembly (7–90) to the dust cover (7–55) by inserting two 1/4” pan–head screws (7–65) with washers (7–60) from the rear of the dust cover assembly.
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4. STORAGE INSTRUCTIONS NOTE: A bench test is required after storage of more than one year, refer to Testing and Troubleshooting section for specific test and check out procedures.
A. STORAGE IN ORIGINAL CONTAINERS When possible, the Model A100S system equipment should be stored in its original container(s). Provide adequate packing to ensure protection from damage during storage and shipment and ensure that adequate silica gel packages are packed in the container(s) to protect the equipment from moisture. Seal the container(s) to provide a moisture–proof package.
B. STORAGE WITHOUT ORIGINAL CONTAINERS If the original container(s) are not available, perform the following procedures to wrap the Model A100S system equipment for storage: (1)
Wrap the recorder unit in plain wrapping paper or newspaper of sufficient thickness to thoroughly cover all sharp corners and protrusions.
(2)
Enclose the unit in a polyethylene bag (3 mils thick, min.) with packages of silica gel sufficient to provide moisture protection and seal the bags.
(3)
Place the recorder unit in a suitably sized heavy construction cardboard box surrounded with packing material sufficient to protect it on all sides. Arrange packing material in such a way that the unit is protected and will not move around within the box.
(4)
Seal box(es) with fiberglass packing tape.
(5)
Mark boxes clearly as to contents.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
SPECIAL TOOLS, FIXTURES, & EQUIPMENT 1. GENERAL This section provides a listing of all required tools, fixtures, and equipment which are not common maintenance tools. Refer to Table 901 for a listing of special test equipment required for testing the Model A100S system. Refer to the following paragraphs for a synopsis of equipment description and purpose. Refer to the applicable user manual for an in–depth explanation of the test equipment operation and configuration.
Table 901 Model A100S Special Tools, Fixtures, and Equipment Special L3 Fairchild Equipment and Type
Manufacturer
Cockpit Voice Recorder System Test Panel
L3 P/N 9300A860
Calibrated Sound Source
L3 P/N 9300A870
L3 Audio Monitor Adapter/ Mod.1
L3 P/N 17TES0200
Ultrasonic Test Set (Beacon Tester)
L3 P/N 15977
A. COCKPIT VOICE RECORDER SYSTEM TEST PANEL, P/N 9300A860 The operation of the Model A100S Recorder and associated control units may be verified using the standard Cockpit Voice Recorder System Test Panel, P/N 9300A860, originally designed for the test and calibration of the Model A100 series of tape–based Cockpit Voice Recorders (refer to Figure 901). Using this panel, audio signals can be applied to individual channels for test and analysis. Additionally, the test panel can be used to activate the Model A100S built–in–test utility, to initiate its Bulk erase feature, and to replay previously recorded data (combined audio). The Test Panel is divided into two section: RECORDER and CONTROL UNIT. The RECORDER section (right half) contains all the controls for test tone, bulk erase, bias trap and associated input/output points. The CONTROL UNIT (left half) section contains all the necessary controls to perform operational checks on all models of control units. Switches for attenuation (6, 12, and 24 db), and a 700 – 1K Hertz filter are included in this test panel to simulate actual conditions. The audio output from either the recorder or control unit section can be monitored, using a headset, at the HEADSET jack or by way of the front panel speaker. The Test Panel measures 19–inches wide, 8.75–inches high and 9.5–inches deep.
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VOICE RECORDER FAIRCHILD COCKPIT SYSTEM TEST PANEL N O R M A L
A C T U A T E
BULK ERASE TEST
TEST
BIAS TRAP ADJUST
SYS UNIT
O U T P U T
MODE GND FAULT
700
1kHz
ROLL OFF I N P U T
GND SHORT
AII3 BULK ERASE
-6 dB
A T T E N U A T I O N
-24 dB
C.U.
EXT
1
A55
MIC
J2
ALL TEST
REC.
INT
O U T P U T
BULK ERASE
-12 dB
BYPASS REVERSED GND
HEADSET
VOLUME
LOCAL AMP AC
MIC CAL DC
2A
DC
OFF
3
4 SHORT
C.U.
CHANNEL SELECT RECORD BIAS
ON
POWER
2
I N P U T
-18VDC +18VDC
2A
AC
J3
CONTROL OFF UNIT
GTP PROBE(FOR GROUND TEST)
Cockpit Voice Recorder System Test Panel, P/N 9300A860 Figure 901 B. CALIBRATED SOUND SOURCE, P/N 9300A870 Refer to Figure 902 for an illustration of the Calibrated Sound Source unit, P/N 9300A870 front panel. Using this panel in conjunction with the Cockpit Voice Recorder System Test Panel, audio signals can be applied to selective microphone devices for test and analysis.
MICROPHONE
CALIBRATE
CALIBRATED SOUND SOURCE P/N 9300-A870
USE 1 kHz SET TO 0 dB
Calibrated Sound Source, P/N 9300A870 Figure 902 C. AUDIO MONITOR ADAPTER / MODIFICATION 1, P/N: 17TES0200 Refer to Figure 903 for an illustration of the Audio Monitor Adapter with Modification 1 (AMA/1), P/N 17TES0200. The AMA/1 is used to extract selective channel audio data from the Model A100S. It may be used along with the L3 Cockpit Voice Recorder System Test Panel and the L3 Calibrated Sound Source Unit to verify proper operation of the Model A100S. A typical A100S unit under test is illustrated in Figure 904.
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10 CONTACT CONNECTOR L3 P/N 063-98-00365 30-INCH FLAT-RIBBON CABLE
UNIT DIMENSIONS: HEIGHT - 7.55 INCHES WIDTH - 4.05 INCHES DEPTH - 1.72 INCHES
L3 Audio Monitor Adapter With Modification 1, P/N 17TES0200 Figure 903 The AMA/1 along with an external amplifier and speaker are the only instruments required to provide quality analysis of the recorded audio data. To use the AMA/1, the recorder must be taken from the aircraft, placed on a test bench and its dust cover removed. The AMA/1 30–inch cable is mated, via its 10–pin connector, to the Playback Monitor connector designated J6 which is located on the Audio Processor PWA at its center outer edge (refer to Figure 904). This connection routes the four audio channels and the Combined Audio channel (summation of Channels 1 through 4) from the Model A100S to the AMA/1 for output individually, via 1/4–inch monophone jacks, as follows: From SSCVR
To AMA/1
Signal Amplitude
Channel 3 Channel 2 Channel 1 Channel 4 Combined Audio Channel
PILOT jack CO–PILOT jack SPARE jack AREA jack COMBINED jack
1 Vrms + 10% 1 Vrms + 10% 1 Vrms + 10% 1 Vrms + 10% 1.45 Vrms + 10%
The signal amplitudes available at the AMA/1 monophone jacks are based on the Model A100S having an applied input of 3 Vrms for Channels 1, 2 and 3 and 2 Vrms for Channel 4. As a general rule, the signal amplitude available at the AMA/1 SPARE (Channel 1), CO–PILOT (Channel 2 ) and PILOT (Channel 3) jacks is 33% of the A100S applied input whereas the signal amplitude available at the AREA jack (Channel 4) is 50% of the unit applied input. The signal amplitude available at the AMA/1 COMBINED jack is approximately 1.45 times the highest individual channel amplitude present at the AMA/1. Also, the signal amplitude measured at the AMA/1 COMBINED jack should be identical to that measured at the Headset jack on both the Model A100S front panel or its associated Control Unit front panel.
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CALIBRATED SOUND SOURCE P/N9300A870 FAIRCHILD
COCKPIT VOICE RECORDER SYSTEM TEST PANEL
COCKPIT VOICE RECORDER SYSTEM TEST PANEL, P/N 9300A860
J6
J6
TO MODEL A100S REAR PANEL CONNECTOR TO J6 ON AUDIO PROCESSOR PWA AUDIO MONITOR ADAPTER (AMA/1) Model A100S SSCVR Typical Test Setup Figure 904
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ILLUSTRATED PARTS LIST 1. GENERAL This section contains the following sections: Introduction, Equipment Designator List, Numerical Index, and Detailed Parts List. The Introduction describes usage of the Illustrated Parts List (IPL), a listing of abbreviations, and a list of vendor names, addresses, and codes per the current issue of “Federal Supply Code for Manufacturers”, catalog handbook H4–1. A configuration matrix listing the Model A100S Solid–State Cockpit Voice Recorder configurations is provided in paragraph 8. The Equipment Designator Index provides a cross reference from manufacture reference designator to manufacturing part number. The Numerical Index provides a numerical listing of all manufacturing part numbers.
2. PURPOSE The purpose of this Illustrated Parts List is to assist maintenance and supply personnel in requisitioning, storing, issuing and identifying parts to maintain the Model A100S recorder. This Illustrated Parts List is not to be taken as the authority for the procedure of assembly or disassembly. Overhaul or repair should be done by authorized personnel only.
3. ABBREVIATIONS The following abbreviations are used in this section:
Abbreviation AR NHA RF
Meaning As Required Next Higher Assembly Reference
4. EQUIPMENT DESIGNATOR INDEX The Equipment Designator Index is an index of designators assigned to electrical parts as shown in electrical wiring and schematic diagrams. Equipment designators are listed in alphanumerical sequence showing applicable figure and item numbers.
5. NUMERICAL INDEX The Numerical Index is a complete listing of parts included in the Detail Parts List, cross–referenced to the applicable figure and item number, L3’s part numbers, the manufacturer’s part numbers and total quantity required. Part numbers are arranged in a alphanumerical sequence beginning at the extreme left–hand position and continue from left to right, one position at a time. The order to precedence in beginning the part number arrangement is as follows: A. Letters A through Z (Alphabetical Os are considered as numerical zeros). B. Numerals 0 through 9. Part number entry is limited to a single line and does not exceed fifteen characters. The FIGURE number and ITEM number columns contain the figure and item number(s) for all parts listed. When more than one figure and item number are shown for the same part number, the part number is not repeated.
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6. DETAIL PARTS LIST The Detail Parts List consists of illustrations and columnar parts breakdown of the component and all assemblies, subassemblies, and parts that can be disassembled, repaired and reassembled, or replaced. Items that are riveted, welded or spun over are not listed. Parts made of bulk stock such as wire, tape or bonding braid are also not listed. Illustrations are each assigned a figure number, commencing with Figure 1 and progressing in sequence. The FIGURE AND INDEX NUMBER column reflects the assigned figure number of the illustration in which the item is shown and the item number listed on the illustration. Figure numbers are shown for the first entry of each figure and at the top of each subsequent column. When there is more than one type of subassembly for the same function additional figures are included with the same number, but followed by an additional alpha designator (such as A, B, etc.). Each part number listed in the Detail Parts List is assigned an index number. Index numbers begin with number 1 for each illustration and in broken sequence to facilitate the insertion of new items which are not variants of existing items. Items listed but not illustrated are identified by a dash to the left of the index number. Item Number Alpha variants are assigned consecutively, A through Z, for related part numbers to show Service bulletin related modifications, or configurational differences from the original item, Non– service bulletin related product improvement parts, or optional parts. The PART NUMBER column contains the manufacturer’s part number when the part is purchased from a source other than L–3 Communications, or the L3 part number for those parts which must be purchased from L3. When the manufacturer’s part number is used for any parts, the L3 number is also shown enclosed in parentheses, in the NOMENCLATURE column. When standard parts (such as MS, AN, RC, CP, etc.) are used, vendor codes are not assigned to these parts. However, for non–standard parts the vendor code is assigned in the NOMENCLATURE column and is preceded by the letter “V.” It corresponds to the Federal Supply Code for Manufacturers as listed in Cataloging Handbook H4–1. When a part has multiple vendors, all part numbers are listed in the PART NUMBER column. The first vendor will be assigned an item number and each subsequent part number is assigned the same item number with an alpha variant. The NOMENCLATURE column describes the part or assembly. Nomenclature wording is arranged so that the identifying noun or key word is always the first part of the description; this is followed by modifying words. Standard abbreviations are used as necessary. Assemblies which are not broken down within a listing but which are covered by a separate figure will carry the notation “(SEE FIG. – FOR DETAIL BREAKDOWN).” The listing of the assembly in the breakdown figure will carry the reference “(SEE FIG. – FOR NHA)”. If the vendor is not L3, the manufacturer’s vendor code may be included in parentheses in this column. The indenture system, provided by the numbers “1” through “6” in the heading, shows the relationship of one part to another; for example, a part listed under indenture “3” is a component of the assembly listed under indenture “2” immediately above it. Items used to attach parts or assemblies to each other are designated “ATTACHING PARTS” and are listed immediately following the item or items they attach. The symbol “* * *” denotes the end of attaching parts.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S The EFFECTIVITY CODE column establishes parts’ relationship with units or assemblies which are essentially the same but have variations. These units or assemblies are assigned reference letters such as A, B, C, D, etc. Parts which are not common to all configurations but are associated with one or more of the coded lead items carry the letter or letters assigned to the lead item with which it is associated. If a part is common to all lead items, the EFFECTIVITY CODE column is blank. The UNITS PER ASSY column lists the quantity of the item required in one assembly in which it is a component. It is, therefore, not necessarily the total quantity of the part required in the complete equipment; the equipment total can be found in the Numerical Index. The term “RF” denotes that the assembly has been previously listed in the parts breakdown, or in some instances engineering reference documentation associated with an assembly part.
7. MANUFACTURER’S CODE Code
Manufacturer
00141
PIC Design Corp. Subsidiary of Wells Benrus Co. Benrus Center P.O. Box 335 Ridgefield, CT 06877
01121
Allen Bradley Co. 1201 South 2nd St. Milwaukee, WI 53204
01295
Texas Instruments Inc. Semiconductor Group 13500 N. Central Expressway P.O. Box 225012 M/S 49 Dallas, TX 75265
02289
Hi–G Co. Inc. Spring St. and Rte. 75 Windsor Locks, CT 06096
03038
Long–Lok Fastener Corp. An Inlex Co. 13709 S. Normandie Ave. Gardena, CA 90249
04713
Motorola Inc. Semiconductor Group 5005 E. McDowell Rd. Phoenix, AZ 85008
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Code
Manufacturer
06288
Edal Industries Inc. 4 Short Beach Rd. East Haven, CT 06512
07263
Fairchild Camera and Instrument Corp. Semiconductor Division Mail Stop 14–1053 401 Ellis St. P.O. Box 7284 Mountain View, CA 94042
08842
Abacus Electronics Corp. Dobbs Ferry, NY
10581
Magnetico Inc. 182 Morris Ave. Holtsville, NY 11742
11983
Nortronics Co. Inc. 8101 10th Ave. N. Minneapolis, MN 55427
13511
Amphenol Cadre Division Bunker Ramo Corp. Los Gatos, CA
14752
Electrocube Inc. 1710 S. Del Mar Ave. San Gabriel, CA 91776
15755
Abbott Transistor Laboratories Inc. 5200 W. Jefferson Blvd. Los Angeles, CA 90016
16741
Triad Transformer Corp. Huntington, IN
22527
Fisher Scientific Co. 585 Alpha Dr. Pittsburgh, PA 15238
25140
TRW Inc. TRW Globe Motor Division 2275 Stanley Ave. Dayton, OH 45404
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Code
Manufacturer
26858
Benthos
49 Edgerton Dr. North Falmouth, MA 02556 27014
National Semiconductor Corp. 2900 Semiconductor Dr. Santa Clara, CA 95051
30655
Elastic Stop Nut Corp. of America Fastener Division Union, NJ 07083
34335
Advanced Micro Devices 901 Thompson Pl. Sunnyvale, CA 94086
46384
Penn Engineering and Manufacturing Corp. P.O. Box 311 Doylestown, PA 18901
51791
Statek Corp. 512 N. Main St. Orange, CA 92668
56289
Sprague Electric Co. 87 Marshall St. North Adams, MA 01247
71279
Cambridge Thermionic Corp. 445 Concord Ave. Cambridge, MA 02138
71460
ITT Canon Electric 666 E. Dyer Rd. Santa Ana, CA 92702
71643
Connecticut Hard Rubber Co. 407 East St. New Haven, CT 06509
71785
TRW Inc. TRW Cinch Connectors Division 1501 Morse Ave. Elk Grove Village, IL 60007
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Code
Manufacturer
72794
Dzus Fastener Co. Inc. 425 Union Blvd. West Islip, NY 11795
72982
Erie Technological Products Inc. 645 West 11th St. Erie, PA 16512
79136
Waldes Kohinoor Inc. 47–16 Austel Pl. Long Island City, NY 11101
80053
Beckman Instruments Inc. Electronic Instruments Division 3900 North River Rd. Schiller Park, IL 60176
81039
Plessey Dynamics Corp. 1 414 Chesnut Ave. Hillside, NJ 07205
81300
Dayco Corp. 333 W. 1st St. Dayton, OH 45402
83086
New Hampshire Ball Bearings Inc. Rt. 202 Peterborough, NH 03458
91146
ITT Cannon Electric Co. Salem Division Salem, MA
91506
Augat Inc. 33 Perry Ave. P.O. Box 779 Attleboro, MA 02703
94867
Churchill Corp. 344 Franklin St. Box G Melrose, MA 02167
94970
Dukane Corp. SeaCom Division 2900 Dukane Drive St. Charles, IL 60174
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Code
Manufacturer
95238
Continental Connector Corp. 34–63 56th St. Woodside, NY 11377
95987
Weckesser Co. Inc. 4444 West Irving Park Rd. Chicago, IL 60641
98659
Computer Instruments 100 Madison Ave. Hempstead, NY 11550
8. CONFIGURATION MATRIX The Model A100S Solid–State Cockpit Voice Recorder currently has two configurations: S100–0080–00 and S100–0080–01 (the light weight version). The S100–0080–00 has three effectivities: the standard version has the 30 minute FCSSU (P/N: 253E0660–00) installed, version A has the 60 minute FCSSU (P/N: 253E1290–00) installed and version B has the titanium FCSSU (P/N: 253E1293–00) installed. The S100–0080–01 has two effectivities: the standard version has the 30 minute FCSSU (P/N: 253E0992–00) installed and verson A has the 60 minute FCSSU (P/N: 253E1293–00) installed.
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
EQUIPMENT DESIGNATOR INDEX Equipment Designator CR1 CR1 CR1 CR2 CR2 CR2 CR3 CR3 CR3 CR4 CR4 CR4 CR5 CR5 CR5 CR6 CR6 CR7 CR8 CR9 CR10 CR11 CR12 CR13 CR14 CR15 CR16 CR17 CR18 CR19 CR20 CR21 CR22 CR23 CR24 CR25 CR26 CR27 CR28 CR29 CR30
Fig–Item 3– 4– 6– 3– 4– 6– 3– 4– 6– 3– 4– 6– 3– 4– 6– 3– 4– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3– 3–
40 15 15 40 25 10 40 10 5 40 20 15 40 20 20 40 10 40 40 10 10 10 10 30 25 35 45 35 20 20 30 10 15 15 30 25 10 10 10 30 75
Equipment Designator CR31 CR32 CR33 CR34 C1 C1 C1 C1 C1 C2 C2 C2 C2 C2 C3 C3 C3 C3 C3 C4 C4 C4 C4 C4 C5 C5 C5 C5 C5 C5 C6 C6 C6 C6 C6 C7 C7 C7 C7 C7 C8
Fig–Item 3– 40 3– 10 3– 10 3– 5 3– 105 4– 330 6– 270 8– 50 9– 70 3– 110 4– 330 6– 220 8– 25 9– 30 3– 110 4– 350 6– 265 8– 55 9– 55 3– 110 4– 340 6– 280 8– 170 9– 50 3– 110 4– 340 9– 70 6– 220 8– 30 9– 35 3– 110 4– 340 6– 275 8– 20 9– 25 3– 110 4– 330 6– 285 8– 60 9– 60 3– 110
Equipment Designator C8 C8 C8 C8 C9 C9 C9 C9 C9 C10 C10 C10 C10 C10 C11 C11 C11 C11 C11 C12 C12 C12 C12 C12 C13 C13 C13 C13 C13 C14 C14 C14 C14 C14 C15 C15 C15 C15 C15 C16
Fig–Item 4– 350 6– 275 8– 70 9– 75 3– 110 4– 340 6– 290 8– 20 9– 25 3– 110 4– 335 6– 255 8– 40 9– 45 3– 110 4– 335 6– 275 8– 15 9– 20 3– 120 4– 340 6– 275 8– 30 9– 35 3– 120 4– 330 6– 285 8– 35 9– 40 3– 145 4– 350 6– 275 8– 20 9– 25 3– 110 4– 345 6– 245 8– 20 9– 80 3– 100
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EQUIPMENT DESIGNATOR INDEX Equipment Designator C16 C16 C16 C16 C17 C17 C17 C17 C18 C18 C18 C18 C19 C19 C19 C19 C20 C20 C20 C20 C21 C21 C21 C21 C22 C22 C22 C22 C23 C23 C24 C24 C25 C25 C26 C26 C27 C27 C28 C28 C29
Fig–Item 4– 335 6– 270 8– 45 9– 50 3– 100 4– 335 8– 20 9– 25 3– 135 4– 340 8– 40 9– 45 3– 130 4– 335 8– 15 9– 20 3– 170 4– 350 8– 65 9– 65 3– 115 4– 325 8– 55 9– 55 3– 130 4– 335 8– 30 9– 35 3– 105 4– 350 3– 105 4– 345 3– 110 4– 345 3– 110 4– 325 3– 110 4– 325 3– 95 4– 345 3– 95
Equipment Designator C29 C30 C30 C31 C31 C32 C32 C33 C33 C34 C34 C35 C35 C36 C36 C37 C37 C38 C38 C39 C40 C41 C42 C43 C44 C45 C46 C47 C48 C49 C50 C51 C52 C53 C55 C56 C57 C59 C60 C61 C62
Fig–Item 4– 340 3– 110 4– 345 3– 110 4– 325 3– 105 4– 345 3– 105 4– 340 3– 105 4– 340 3– 122 4– 340 3– 112 4– 340 3– 112 4– 340 3– 102 4– 310 4– 310 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 345 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 350 4– 320
Equipment Designator C63 C64 C65 C66 C67 C68 C69 C70 C71 C72 C73 C74 C75 C76 C77 C78 C79 C80 C81 C82 C83 C84 C85 C86 C87 C88 C101 C102 C106 C107 C108 C109 C110 C111 C112 C113 C114 C115 C117 C118 C120
Fig–Item 4– 340 4– 340 4– 340 4– 340 4– 340 4– 340 4– 340 4– 320 4– 320 4– 340 4– 340 4– 310 4– 340 4– 340 4– 340 4– 340 4– 310 4– 320 4– 315 4– 295 4– 300 4– 300 4– 295 4– 290 4– 290 4– 305 6– 235 6– 250 6– 235 6– 235 6– 240 6– 240 6– 240 6– 230 6– 240 6– 235 6– 240 6– 235 6– 260 6– 235 6– 225
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
EQUIPMENT DESIGNATOR INDEX Equipment Designator C123 D1 D1 D2 D2 D3 D4 D4 J1 J2 J2 J3 J4 J5 J5 J7 J8 L1 L1 L2 L2 L3 L3 P1 P1 P2 P4 P5 Q1 Q1 Q1 Q1 Q2 Q2 Q2 Q3 Q3 Q4 Q4 Q5 Q5
Fig–Item 6– 225 8– 10 9– 15 8– 10 9– 15 9– 10 8– 5 9– 5 3– 210 3– 250 6– 310 3– 240 3– 240 3– 245 6– 300 3– 225 2– 190 4– 5 6– 140 3–100A 6– 145 3–100A 6– 145 6– 50 4– 365 3– 250 4– 70 6– 45 3– 85 4– 125 8– 170 9– 190 4– 125 8– 175 9– 195 8– 175 9– 195 8– 180 9– 200 8– 180 8– 180
Equipment Designator Q5 Q6 Q6 R1 R1 R1 R1 R1 R2 R2 R2 R2 R2 R3 R3 R3 R3 R3 R4 R4 R4 R4 R4 R5 R5 R5 R5 R5 R6 R6 R6 R6 R6 R7 R7 R7 R7 R7 R8 R8 R8
Fig–Item 9– 200 8– 185 9– 205 3– 160 4– 235 6– 175 8– 115 9– 170 3– 150 4– 235 6– 210 8– 115 9– 95 3– 170 4– 235 6– 205 8– 90 9– 100 3– 185 4– 235 6– 200 8– 145 9– 160 3– 185 4– 260 6– 215 8– 80 9– 90 3– 145 4– 245 6– 190 8– 85 9– 95 3– 190 4– 280 6– 165 8– 80 9– 90 3– 195 4– 255 6– 170
Equipment Designator R8 R8 R9 R9 R9 R9 R9 R10 R10 R10 R10 R10 R11 R11 R11 R11 R11 R12 R12 R12 R12 R12 R13 R13 R13 R13 R14 R14 R14 R14 R15 R15 R15 R15 R15 R16 R16 R16 R16 R17 R17
Fig–Item 8– 160 9– 180 3– 155 4– 285 6– 170 8– 165 9– 140 3– 195 4– 245 6– 165 8– 160 9– 180 3– 165 4– 240 6– 185 8– 150 9– 165 3– 165 4– 270 6– 180 8– 120 9– 135 3– 195 4– 240 8– 145 9– 160 3– 150 4– 275 8– 130 9– 145 3– 165 4– 245 6– 195 8– 125 9– 140 4– 265 6– 180 8– 75 9– 85 4– 225 6– 195
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
EQUIPMENT DESIGNATOR INDEX Equipment Designator R17 R17 R18 R18 R18 R19 R19 R19 R19 R20 R20 R21 R21 R21 R22 R22 R22 R23 R23 R23 R24 R24 R24 R25 R25 R25 R26 R26 R27 R27 R27 R28 R28 R28 R29 R29 R29 R30 R30 R30 R31
Fig–Item 8– 80 9– 90 4– 150 8– 80 9– 90 3– 180 4– 150 8– 100 9– 110 3– 175 9– 120 4– 165 8– 85 9– 95 4– 215 8– 105 9– 115 4– 165 8– 135 9– 150 4– 230 8– 80 9– 90 4– 200 8– 75 9– 85 8– 100 9– 110 4– 150 8– 140 9– 155 4– 190 8– 110 9– 125 4– 175 8– 115 9– 130 4– 155 8– 115 9– 130 4– 185
Equipment Designator R31 R31 R32 R32 R32 R33 R34 R35 R36 R37 R38 R39 R40 R41 R42 R43 R44 R45 R46 R47 R48 R49 TP1 TP1 TP2 TP2 TP3 TP4 TP5 TP6 TP10 TP20 TP30 TP40 T1 T1 T2 T3 T4 U1 U1
Fig–Item 8– 115 9– 105 4– 170 8– 155 9– 175 4– 160 4– 155 4– 170 4– 150 4– 220 4– 165 4– 175 4– 160 4– 165 4– 145 4– 195 4– 145 4– 150 4– 155 4– 210 4– 200 4– 250 3– 205 6– 35 3– 205 6– 35 3– 205 3– 205 3– 205 3– 50 6– 155 6– 155 6– 155 6– 155 3– 200 4– 355 4– 355 4– 355 4– 355 3– 50 4– 35
Equipment Designator U1 U2 U2 U2 U3 U3 U3 U3 U4 U4 U4 U5 U5 U5 U6 U6 U7 U7 U8 U8 U9 U9 U10 U10 U11 U11 U12 U12 U13 U13 U14 U14 U15 U15 U16 U16 U17 U17 U18 U18 U19
Fig–Item 6– 130 3– 55 4– 45 6– 125 3– 65 3–65A 4– 100 6– 80 3– 70 4– 110 6– 25 3–65A 4– 55 6– 45 4– 105 6– 70 4– 115 6– 70 4– 120 6– 95 4– 55 6– 95 4– 55 6– 90 4– 30 6– 65 4– 90 6– 55 4– 60 6– 130 4– 105 6– 90 4– 105 6– 130 4– 90 6– 120 4– 80 6– 60 4– 80 6– 75 4– 80
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EQUIPMENT DESIGNATOR INDEX Equipment Designator U19 U20 U20 U21 U21
Fig–Item 6– 135 4– 80 6– 35 4– 80 6– 60
Equipment Designator U22 U22 U23 U23 U24
Fig–Item 4– 70 6– 100 4– 70 6– 85 4– 70
Equipment Designator U24 U25 W1 W2 Y1
Fig–Item 6– 110 4– 70 3– 230 6– 40 6– 150
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NUMERICAL INDEX
PART NUMBER #515 AM003–7 AM29C821/BLA B191–20H BCDAT–2–619–5 CCR06CG104FR CCR06CG472FR CCR07CG333FR CCR07CG683FR CD54ACT238F3A CD54HCT14F CK05BX101K CK05BX102K CK05BX103K CK05BX104K
CK05BX561K CK06BX104K CK06BX105K CK06BX223K CK06BX274K CK06BX562K DD1032 DDU–8Z297 DG201AAK DS2165QN HLMP–1700–101 HLMP–7000–1S1 L–11 LH0002H LM136AH–2.5 LM139J MAX632AMJA MC1558U MD015C104KAA
AIRLINE PART NO.
FIG.
ITEM
TTL REQ
2 2 6 3 5 4 4 4 4 6 6 4 4 6 3 8 3 4 6 4 3 3 8 9 4 3 3 6 4 4 4 6 2 7 4 3 3 6 3 4
195 205 95 45 15 345A 335 340 345 65 85 320 315 290 110 50 105 310 275 325 112 115 55 55 330 120 135 135 115 80 25 20 190 40 110 75 70 80 50 350
1 4 2 1 1 7 6 25 7 1 1 5 1 1 17 2 6 4 5 4 1 1 2 2 1 2 1 1 1 5 1 1 1 1 1 1 1 1 1 26
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NUMERICAL INDEX
PART NUMBER MS15795–803 MS24693–C3 MS24693–C46 MS35333–70 MS35649–244 MS51957–5 MS51957–14
MS51957–27 MS51957–28 MS51957–45 MS51958–65 MS51959–13 MS51959–15 MS51959–17 MS51960–65 NMF0509S OP–27BZ OP–470AY PLC–440 PLC–832 RC07GF101J RC07GF102J RC07GF103J RC07GF125J RC07GF151J RC07GF152J RC07GF154J
AIRLINE PART NO.
FIG.
ITEM
7 2 2 2 2 2 3 2 2 2 2 2 2 2 2 2 2 2 2 3 4 4 2 2 8 9 8 9 8 9 8 9 8 9 8 9 8 9
60 210 250 15 275 10 220 20 220 270 100 105 145 180 230 260 255 80 170 65A 55 105 225 40 75 85 80 90 85 95 90 100 95 105 100 110 105 115
TTL REQ 2 4 1 1 5 1 3 1 4 5 2 1 4 4 2 5 4 2 2 2 1 5 4 6 1 2 5 5 2 3 1 1 1 1 2 2 1 1
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NUMERICAL INDEX
PART NUMBER RC07GF182J RC07GF221J RC07GF222J RC07GF224J RC07GF471J RC07GF472J RC07GF474J RC07GF510J RC07GF561J RC07GF562J RC07GF682J RC07GF821J RC07GF822J RNC50*DSCR RN60D22R1F SN54BCT2244J S100–0080–00 S100–0080–01 SP–310 SS020–01–TG TM7–3 VK200 V130LA5 016E0946–00 024E0526–00 024E0611–00 0448000001 0449800012 046E0280–01A 046E0281–01
AIRLINE PART NO.
FIG.
ITEM
9 8 9 8 9 8 9 8 9 8 9 8 9 8 9 8 9 8 9 9 8 9 8 9 6 3 6 1 1 4 6 3 4 3 2 2 3 3 3 4 4
120 110 125 115 130 120 135 125 140 130 145 135 150 140 155 145 160 150 165 170 155 175 160 180 190 180 130 1 1A 360 50 200 5 40 151 5 230 136 136A 30 35
TTL REQ 1 1 1 3 2 1 1 1 1 1 1 1 1 1 1 2 2 1 1 1 1 1 2 2 1 1 3 1 1 4 2 1 1 9 1 1 1 3 3 1 1
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER
AIRLINE PART NO.
TTL REQ
FIG.
ITEM
046E0282–01 046E0283–01A 046E0284–01A 046E0285–01A 0469701469 0469701732 0469701736 0469701858 0469701861 0469701868 0469701883 0469701885 0469701888 0469701892 0469701896
4 6 6 6 6 6 4 4 4 4 6 6 6 6 6
45 25 35 45 55 60 60 70 90 100 90 100 110 120 125
1 1 1 1 1 2 1 1 2 1 2 1 1 1 1
0639800074 0639801522 075E0604–00 0884700024
3 4 2 4 6 3 3 8 9 3 8 9 4 9 6 4 3 6 3 3 3 6
210 365 90 15 10 25 30 10 15 10 5 5 20 10 5 10 15 15 20 35 5 40
1 1 1 1 1 2 5 2 2 12 1 1 2 1 1 2 1 2 1 1 1 1
1.5KE250CA 1.5KE68C 1N295 1N4148 1N4446 1N4614 1N4735,A 1N4761A 1N5234B 1N5256A, B 1N5819 1N5825 1N759A 1N914, A,B 1000200612
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER
AIRLINE PART NO.
TTL REQ
FIG.
ITEM
17D17–0618
3 3 4 4 8 9 6 6 6 6 3 10 3 8 9 3 2 7 2
80 90 130 140 190 210 225 230 235 240 240 45 102 195 215 100A 140 5 145
1 1 1 1 1 1 1 1 7 5 2 1 1 1 1 2 1 1 1
1829800193 1829800194 1829800195 1829800196 1829800197 1829800198 1829800199 1829800200 1829800201 1829800202 1829800203 1829800204 1829800206 1829800209 1829800210 1829800211 183DHL 1849700118 1849700119 189E0610–00 191E0607–00
4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 6 4 6 2 2
150 155 160 165 170 175 180 185 190 195 200 205 210 220 225 230 255 120 150 85 110
5 3 2 4 2 2 1 1 1 1 2 1 1 1 1 1 1 1 1 1 1
10042–DAP
10282–N 104JEV 104JEW 104JEX 104JEY 120–064–455F 150949–1002 158X104K 160–0021–020 167103J400A 17D17–0262
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NUMERICAL INDEX
PART NUMBER 191E0953–00 196E0605–00 196E0608–00 2N2222A 2N2907A
2029800326 2029800391 205E0597–00 205E0598–00 205E0601–00 205E0660–00 205E1027–00 206E0597–00 2160 2290200398 2290200413 2299800197 2299800341 2299800417 2299800423 230E0947–00 2369800242 236C2110–10 239E0197–00 239E0630–00 24SX–2–6–3–L 24SX–2–6–3–R 25107 253E0348–03 253E0585–00 253E0600–00 253E0600–01
AIRLINE PART NO.
FIG.
ITEM
2 2 2 4 3 3 4 3 3 2 3 2 4 2 6 5 2 6 3 3 2 2 4 2 2 2 2 4 6 2 2 2 2 3 2 5 2 1 2 1 2
110A 130 70 125 85 135 135 55 55A 245 1 280 1 282A 1 1A 282B 1A 260 60 154 284 370 50 240 60 125A 75 30 235 45 35 30 65 200 1 150 5 1 5A 1A
TTL REQ 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 7 1 4 2 4 2 2 1 4 2 2 1 2 2 1 1 1 1 1 1 1 1
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NUMERICAL INDEX
PART NUMBER 253E0992–00 253E1290–00 253E1293–00 2559800205 2559800280 263D28 266E0305–01 266E0305–02 2739800090 2879800154 2879800162 2879800213 2979800257 3019822003 3370415004 3371139004 3371222004 3371315004 3392222005 3399–6026 3433–5302 3518 3611010001 3621215004 3623633004 3781312522 3926–0000T 39424 403DDC 408E0609–00 42285 4626–6300 4989–02–1822–F 502DFF 502DRC
AIRLINE PART NO.
FIG.
ITEM
2 5 2 5 2 5 6 3 6 2 2 4 2 2 4 2 4 8 9 4 3 4 6 6 6 3 6 3 6 6 3 6 6 6 4 2 6 3 4 6 6
200A 1B 200B 1C 200C 1D 155 205 260 160A 160B 375 55 65 380 265 290 60 60 295 95 300 220 300 310 255 315 100 265 270 125 280 305 145 305 75 140 245 215 245 250
TTL REQ 1 1 1 1 1 1 4 6 2 1 1 2 4 2 2 5 2 1 1 2 2 2 2 1 1 2 2 2 1 2 1 1 1 2 1 1 1 1 2 2 1
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 54ACTQ245DM 54FCT541DM 5602–55–32 6080102269 6080130902 6080905629 6080908669 6080910000 6080910001 6080910009 6080910701 6080912400 6080924900 6080929401 6080930100 6080930102 6080935700 6080949901 6080964900 6080968100 6080973200 6080988701 6112820001 619–24–CC–B.1 62650–1 6140116200 6140166508 68120–050 68WR10K 7447–1–P42 7473422005 750–101–R10K 750–101–R100K 750–101–R47K 750–83–R10K 750–83–R100K 750–83–R47
AIRLINE PART NO.
FIG.
ITEM
6 6 3 6 3 4 3 3 4 3 4 4 4 3 6 3 4 3 4 4 3 3 4 4 6 4 4 3 6 6 3 4 6 3 6 6 4 6 6 3 6
75 70 215 195 185 240 140 145 245 150 250 255 260 155 200 160 265 165 270 275 170 175 280 285 205 40 50 225 210 215 250 235 160 130 165 180 145 185 175 190 170
TTL REQ 1 2 3 2 1 2 1 1 3 2 1 1 1 1 1 1 1 3 1 1 1 1 1 1 1 1 1 1 1 1 1 4 2 2 2 2 2 1 1 1 2
23-70-02
Illustrated Parts List Rev 1 Page 1020 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 750–83–R47K 754–01–001 7552110002 77103–050 79NM–40 821573–3 821574–1 821581–1 821665–1 89984 8AS23R3 8EP43R3 8EP44R3 8EP46R3 8EP46R5 9WES4 9–0649 9–1391 9–1504 9–1508 9–1539 9–1586–25 9–1586–26 9–1586–27 9–1586–28 9–1588 9–1589 9–1590 9–1889 93A055–00
AIRLINE PART NO.
FIG.
ITEM
TTL REQ
3 4 6 3 2 4 6 4 4 6 11 10 10 7 10 7 7 11 11 10 2 7 2 2 8 9 8 9 8 9 8 9 8 9 9 8 9 9
195 385 285 235 215 65 105 85 95 115 5A 70 35A 65 35 20 160 40 45 50 135 85 120 155 170 190 175 195 180 200 185 205 65 65 70 165 185 80
1 46 2 1 4 1 1 5 2 1 1 3 2 1 2 4 4 1 1 1 4 4 2 4 1 1 10 1 10 1 1 1 1 1 2 1 1 1
1 10
20 1
1 1
23-70-02
Illustrated Parts List Rev 2 Page 1021 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 93A055–03 93A055–10 93A055–20 93A055–30 93A055–40 93A055–45 93A055–50 93A055–55 93A055–60 93A055–65 93A055–66 93A055–67 93A055–95 93A151–00 93A151–01 93A151–20 93A151–30 93A151–40 93A151–50 93A152–00
AIRLINE PART NO.
TTL REQ
FIG.
ITEM
1 10 1 10 1 10 1 10 1 11 1 11 1 10 1 10 1 11 1 11 1 11 1 11 1 11 1 7 1 7 1 7 1 7 1 7 1 7
20A 1A 20B 1B 20C 1C 20D 1D 25 1 25A 1A 20E 1E 20F 1F 25B 1B 25C 1C 25D 1D 25E 1E 25F 1F 10 1 10A 1A 10B 1B 10C 1C 10D 1D 10E 1E
1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1
1 7
15 1F
1 1
23-70-02
Illustrated Parts List Rev 2 Page 1022 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 93A152–01 93A152–04 93A152–20 93A152–25 93A152–30 93A152–35 93A152–40 93A152–50 93A152–60 93A152–70 93A244 93A263–02 93A264 93A265 93A266–01 93A267 93A268 93A272 93A307
93–618 93–619–01 93–624 93–626–19 93–626–20 93–626–22 93–626–23
AIRLINE PART NO.
FIG.
ITEM
1 7 1 7 1 7 1 7 1 7 1 7 1 7 1 7 1 7 1 7 7 7 8 7 7 7 9 7 7 11 7 7 7 2 10 12 10 10 10 10 10
15A 1G 15B 1H 15C 1J 15D 1K 15E 1L 15F 1M 15G 1N 15H 1P 15J 1Q 15K 1R 125 155 1 80 80B 155A 1 80A 80C 5 90 100 130 125 5A 5A 55A 60B 60C 60 60A
TTL REQ 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1
23-70-02
Illustrated Parts List Rev 2 Page 1023 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 93–626–30 93–626–83 93–626–100 93–626–101 93–626–115 93–626–116 93–626–117 93–653 93–654 93–655 93–656 93–658–01 93–658–02 93–658–03 93–917–67 93–972 93–989 93–1021 93–1025 9300A014 9300A014–01 9300A014–02 9300A014–03 9300A033 9300A165 9300A165–01 9300A206 9300–177 9300–179–01 9300–179–02 9300–180 9300–195 9300–197
9300–204
AIRLINE PART NO.
FIG.
ITEM
11 11 11 11 11 10 10 11 11 11 11 11 11 11 11 9 8 10 7 11 7 7 7 7 7 1 12 1 12 12 2 7 7 2 7 7 10 12 7 7
30A 30 30B 30C 30D 60D 60E 15 35 25 10 10A 20 20A 20B 75 200 15A 45 5B 15 15A 15B 15C 95 30 1 30A 1A 5 165 30 35 175 55 155 10 10 105 135
TTL REQ 1 1 1 1 1 1 1 1 1 1 2 3 1 1 1 1 1 1 2 1 1 1 1 1 1 1 1 1 1 1 1 1 1 2 1 1 1 1 1 1
23-70-02
Illustrated Parts List Rev 1 Page 1024 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
NUMERICAL INDEX
PART NUMBER 9300–205 9300–233 9300–233–01 9300–233–04 9300–285 9300–286–01 9300–290 9300–301 9300–305 9300–307 9300–329 9300–334 9300–337 9300–344
9300–347 9300–348 9300–351 9300–352 9300–377 9300–382 9300–388 9300–534 9300–543 9300–581 9300–583 9300–583 9300–927 9300–928 933533617
AIRLINE PART NO.
FIG.
ITEM
7 10 7 7 7 8 9 4 8 9 8 9 8 9 8 9 7 10 7 7 10 12 10 10 10 10 7 7 10 7 8 9 12 2 8 9 10 10 2
110 5 25 25A 25B 15 20 355 20 25 25 30 30 35 35 40 70 55 75 115 20 15 25 30 65 40 120 145 15 50 40 45 20 152 45 50 65A 30A 154
TTL REQ 1 1 1 1 1 2 2 4 5 4 1 1 3 3 1 1 1 1 1 1 1 1 1 1 1 2 1 1 1 1 2 2 1 1 1 1 1 1 1
23-70-02
Illustrated Parts List Rev 3 Page 1025 Jul. 01/05
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
5 5A
10A–E 15 15A–K
20 20A–F
25 25A–F
30
30A
Solid–State Cockpit Voice Recorder Configuration, Model S100S, P/N: S100–0080–( ) Figure 1
23-70-02
Illustrated Parts List Rev 2 Page 1026 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM 1
PART NUMBER
AIRLINE PART NO.
NOMENCLATURE 1234567
EFF CODE
UNITS PER ASSY
1
S100–0080–00
SSCVR CONFIGURATION, A100S
A
RF
1A
S100–0080–01
SSCVR CONFIGURATION, A100S, TITANIUM FINAL ASSEMBLY, SSCVR (SEE FIG 2 FOR DETAIL BREAKDOWN) FINAL ASSEMBLY, SSCVR, TITANIUM (SEE FIG 2 FOR DETAIL BREAKDOWN) CONTROL ASSEMBY, A151–1, BLK, NO MICROPHONE CONTROL ASSEMBY, A151B, M2, GRAY, NO MICROPHONE CONTROL ASSEMBY, A151B, M2, BLK, NO MICROPHONE CONTROL ASSEMBY, A151B, BOEING BROWN, NO MICROPHONE CONTROL ASSEMBY, A151B, ATR BROWN, NO MICROPHONE CONTROL ASSEMBY, A152, GRAY, DYNAMIC MIC (SEE FIG 7 FOR DETAIL BREAKDOWN) CONTROL ASSEMBY, A152–1, BLACK, DYNAMIC MIC CONTROL ASSEMBY, A152–4, GRAY, DYNAMIC MIC CONTROL ASSEMBY, A152B, GRAY, CONDENSOR MICROPHONE CONTROL ASSEMBY, A152B, GRAY, CONDENSOR MICROPHONE CONTROL ASSEMBY, A152B, BLACK, CONDENSOR MICROPHONE CONTROL ASSEMBY, A152B, GRAY, CONDENSOR MICROPHONE CONTROL ASSEMBY, A152B, GRAY, CONDENSOR MICROPHONE CONTROL ASSEMBY, A152B, BOEING BROWN, CONDENSOR CONTROL ASSEMBY, A152B, BOEING BROWN, CONDENSOR CONTROL ASSEMBY, A152B, BLACK, CONDENSOR MICROPHONE
B
RF
A
1
B
1
5
253E0600–00
5A
253E0600–01
10A
93A15101
10B
93A15120
10C
93A15130
10D
93A15140
10E
93A15150
15
93A15200
15A
93A15201
15B
93A15204
15C
93A15220
15D
93A15225
15E
93A15230
15F
93A15235
15G
93A15240
15H
93A15250
15J
93A15260
15K
93A15270
1 1 1 1 1 1
1 1 1 1 1 1 1 1 1 1
23-70-02
Illustrated Parts List Rev 2 Page 1027 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM
PART NUMBER
1
20
93A055–00
20A
93A055–03
20B
93A055–10
20C
93A055–20
20D
93A055–30
20E
93A055–50
20F
93A055–55
25
93A055–40
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
MICROPHONE ASSEMBLY, REMOTE MODEL A55 (SEE FIG 10 for DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55 (SEE FIG 10 for DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BLACK, CONDENSOR, NON–MAGNETIC, DIRECTIONAL, REAR CONNECTOR (SEE FIG 10 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BLACK, CONDENSOR, NON–MAGNETIC, DIRECTIONAL, SIDE CONNECTOR (SEE FIG 10 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BROWN (BOENING), CONDENSOR, NON–MAGNETIC, DIRECTIONAL, REAR CONNECTOR (SEE FIG 10 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BLACK, CONDENSOR, NON–MAGNETIC, DIRECTIONAL, REAR CONNECTOR (SEE FIG 10 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BLACK, CONDENSOR, NON–MAGNETIC, DIRECTIONAL, SIDE CONNECTOR (SEE FIG 10 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, GRAY, MINI–CONDEN– SOR, PIGTAIL CONNECTOR, OMNI– DIRECTIONAL (SEE FIG 11 FOR DETAIL BREAKDOWN)
UNITS PER ASSY 1
1
1
1
1
1
1
1
23-70-02
Illustrated Parts List Rev 2 Page 1028 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM
PART NUMBER
1 25A
93A055–45
25B
93A055–60
25C
93A055–65
25D
93A055–66
25E
93A055–67
25F
93A055–95
30
9300A165
30A
9300A165–01
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BROWN (ATR–42), MINI–CONDENSOR, PIGTAIL CONNECTOR, OMNI–DIRECTIONAL (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, GRAY, MINI–CONDEN– SOR, NON–MAGNETIC, DIRECTIONAL, PIGTAIL CONNECTOR (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BROWN (ATR–42), MINI–CONDENSOR, NON–MAGNETIC, DIRECTIONAL, PIGTAIL CONNECTOR (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, GRAY, MINI–CONDEN– SOR, NON–MAGNETIC, DIRECTIONAL, PIGTAIL CONNECTOR (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBLY, REMOTE MODEL A55B, BLACK, MINI–CONDEN– SOR, NON–MAGNETIC, DIRECTIONAL, PIGTAIL CONNECTOR (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBY, REMOTE MODEL A55B, BLACK, MINI–CONDEN– SOR, NON–MAGNETIC, DIRECTIONAL, PIGTAIL CONNECTOR (SEE FIG 11 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBY, REMOTE (SEE FIG 12 FOR DETAIL BREAKDOWN) MICROPHONE ASSEMBY, REMOTE (SEE FIG 12 FOR DETAIL BREAKDOWN)
UNITS PER ASSY 1
1
1
1
1
1
1 1
23-70-02
Illustrated Parts List Rev 2 Page 1029 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
90
105 100
25
A 245
80 85 75
145
280 282 200 200A
140
Model A100S SSCVR Final Assembly, P/N: 253E0600–00 –01 Figure 2 (Sheet 1 of 2)
23-70-02 Illustrated Parts List Rev 2 Page 1030 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S 125 110 120 115
250 170
195 150 130
260
160A 160B
255
B 135 30
B
10 230
25
155
175
225
165 180
245 265 270 275
185 190
5 205
50 55 60 65
35
45 15 20
220
215
C 70 282 284
210 200 200A
205
C
235 240
A
Model A100S SSCVR Final Assembly, P/N: 253E0600–00, –01 Figure 2 (Sheet 2 of 2)
23-70-02 Illustrated Parts List Rev 2 Page 1031 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM 2
PART NUMBER 1
253E0600–00
1A
253E0600–01
5
024E0526–00
10
MS35649–244
15
MS35333–70
20
MS51957–14
25 30
042E0606–00 24SX–2–6–3–R
35
24SX–2–6–3–L
–40
PLC–832
45
239E0630–00
50 55 60 65
2299800341 2879800154 2299800423 2879800162
70 75
196E0608–00 408E0609–00
80
MS51959–17
85
189E0610–00
90 –93 95
075E0604–00 9030100047 9300A218
100
MS51957–27
AIRLINE PART NO.
NOMENCLATURE 1234567
RECORDER FINAL ASSEMBLY, A100S (SEE FIG 1 FOR NHA) RECORDER FINAL ASSEMBLY, A100S LIGHT WEIGHT (SEE FIG 1 FOR NHA) CABLE, GROUNDING ATTACHING PARTS NUT, HEX, 4–40 (V96906) (2870200002) WASHER, #4, INTERNAL TOOTH (V96906) (2730200025) SCREW,PAN HEAD,4–40 X5/16 (V96906) (2290200074) *** CHASSIS, SSCVR GUIDE, CARD, LOCK, RIGHT HAND, 3.0IN (V01121) (4019800042) GUIDE, CARD, LOCK, LEFT HAND, 3.0IN (V01121) (4019800043) NUT, CAPTIVE, 8–32, LOCKING, SST (2879800190) SPACER, CONNECTOR ATTACHING PARTS SCREW, M2X6, FLAT HEAD, SLOT NUT,HEX,LOW PROFILE,M2 SCREW, M2.5 X 14, FLAT HEAD,SST NUT,SELF–LOCK,NYL INSR *** PLATE, ISOLATOR, FRONT RETAINER, CARD ATTACHING PARTS SCREW, FLAT HEAD, 4–40 X 1/2 (V96906) (2290200189) PAD, CARD RETAINER *** DUST COVER, MODIFIED, SSCVR STATIC AWARENESS LABEL DELETED ATTACHING PARTS SCREW ,PAN HEAD, 6–32 X 5/16 (V96906) (2290200084)
EFF CODE
UNITS PER ASSY
A
RF
B
RF 1 1 1 1
1 2 2 6 1 4 4 2 2 1 1 2 1 1 1
2
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List Rev 23 Page 1032 Jul. 15/00 01/05 Mar.
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM
PART NUMBER
2
105
MS51957–28
110
191E0607–00
SCREW, PAN HEAD, 6–32 X 3/8 (V96906) (2290200085) *** PANEL, FRONT, SSCVR (SUPSD BY
191E0953–00
ITEM 110A, PRE ECO 07305) PANEL, FRONT, SSCVR (SUPSDS
110A
115
MS51957–45
120
9–1508
125
93–618
125A
230E0947–00
130
196E0605–00
135
9–1391
140 145 150
17D17–0262 17D17–0618 253E0585–00
151 152 153
016E0946–00 9300581 2290200398
154
933533617
155
9–1539
160A
266E0305–01
160B
266E0305–02
165
9300–177
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
UNITS PER ASSY 1
1 1
ITEM 110, POST ECO 07305) ATTACHING PARTS SCREW, PAN HEAD, 8–32 X 1/2 (V96906) (2290200102) FLAT FIBRE WASHER (V06141) (9391508) *** GASKET (OBSOLETE, SUPSD BY ITEM 125A), SEAL, FRONT PANEL (SUPSDS ITEM 125) NAMEPLATE, FRONT PANEL ATTACHING PARTS PAN HEAD SCREW (V06141) (9391391) *** MODIFICATION RECORD PLATE PROGRAM REVISION PLATE UNDERWATER LOCATOR DEVICE CRADLE ASSEMBLY BRKT, BEACON MOUNT COVER PLACE, ULD SCREW, CAP, SKT HD FLT 8–32 x 3/8 LOCKWASHER, #8 CSNK, SST ATTACHING PARTS HEX CP SC (LP62U040J12X2) (V06141) (9391539) *** BEACON,ACOUSTIC,UNDERWATER DUKANE (V94970) (DK–120) BEACON,ACOUSTIC,UNDERWATER RJE (V61257) (ELP–362D) HANDLE
2 2
1 1 1 4
1 1 1 1 1 1 1 4
1 1 1
23-70-02 Illustrated Parts List Rev 23 Page 1033 Jul. 15/00 01/05 Mar.
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM 2
PART NUMBER
170
MS51960–65
175
9300–180
180
MS51957–45
185
024E0616–00
190 195
L–11 #515
200
253E0348–03
200A
253E0992–00
200B
253E1290–00
200C
253E1293–00
205
AM003–7
210
MS24693–C3
215
79NM–40
220
MS51957–14
225
PLC–440
230
MS51958–65
235
239–E0197–00
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
ATTACHING PARTS SCREW, FLAT HEAD, 10–32 X 1/2 (V96906) (2290200043) *** HOLD–DOWN ATTACHING PARTS SCREW,PAN HEAD, 8–32 X 1/2 (V96906) (2290200102) *** CABLE ASSEMBLY, W3, VOICE MON ATTACHING PARTS PHONE JACK (9300384) JACK COVER (9300247) *** ASSEMBLY,FLASH CRASH SURVIVABLE STORE UNIT (SUPSD BY ITEM 200A, PRE FSB006) ASSEMBLY,FLASH CRASH SURVIVABLE STORE UNIT (SUPSD BY ITEM 200C, PRE FSB009) ASSEMBLY,FLASH CRASH SURVIVABLE STORE UNIT (SUPSDS ITEM 200, POST FSB006) ASSEMBLY,FLASH CRASH SURVIVABLE STORE UNIT (SUPSDS ITEM 200A, POST FSB009) MOUNT, ELASTOMERIC, SHOCK (1789800066) ATTACHING PARTS SCREW, FLAT HEAD, 4–40 X 5/16 (V96906) (2290200219) NUT 4–40 NYLON INSERT (2879800241) SCREW, PAN HEAD, 4–40 X 5/16 (V96906) (2290200074) NUT, CAPTIVE, NYLON LOCKING 4–40 (2879800191) SCREW, PAN HEAD, 10–32 X 3/4 (V96906) (2290200334) SPACER,VIBRATION MOUNT
UNITS PER ASSY 2
2 4
1 1 1 A
1
B
1
A
1
B
1
4
4 4 4 4 2 2
– ITEM NOT ILLUSTRATED - ITEM 200B U" PART NUMERS DESIGNATED REFURISHED WARRANTY REPAIR" FCSSU'S.
23-70-02 Illustrated Parts List Rev 2 Page 1034 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL MODEL A100S
FIG. ITEM
PART NUMBER
2
240
2299800417
245
205E0597–00
250 255
MS24693–C46 MS51959–15
260
MS51959–13
265
2979800257
270
MS51957–14
275
MS35333–70
280
205E0598–00
282A
205E0601–00
282B
205E1027–00
284 –285 –290 –295 –300 –305 –310 –315
2290200413 MS20470–AD2–2 LAC–440–2 2979800080 QQ–A–250/8 9–0527–03 905E0600–33 905E0600–19
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
SCREW, SHCAP, 10–32 X 1.125 LOW (V96906) (2290200365) PWA, AIRCRAFT INTERFACE A100S (SEE FIG 3 FOR DETAIL BREAKDOWN) ATTACHING PARTS SCREW, FLAT HEAD, 8–32 X 1/4 SCREW, FLAT HEAD, 4–40 X 3/8 (V96906) (2290200187) SCREW, FLAT HEAD, 4–40 X 1/4 (V96906) (2290200185) *** STAND OFF, 3/16 HEX, 4–40 X 1–1/31, (Mfg. UNICORP, No. P–343–M09–F09–440) SCREW, PAN HEAD, 4–40 X 5/16 (V96906) (2290200074) WASHER, #4, INTERNAL TOOTH (V96906) (2730200025) *** PWA, AUDIO PROCESSOR A100S (SEE FIG 4 FOR DETAIL BREAKDOWN) PWA, STORE PROCESSOR (SEE FIGURE 6 FOR DETAIL BREAKDOWN) PWA, STORE PROCESSOR, 8MB (SEE FIG 6 FOR DETAIL BREAKDOWN) ATTACHING PARTS SCREW, FLAT HEAD, 6–32 x 3/16 DELETED DELETED DELETED DELETED DELETED BLOCK DIAGRAM, PHYSICAL DRAWING TREE, SSCVR
UNITS PER ASSY 2 1
1 4 5
5
5 5
1 A
1
B
1
4 8 2 2 5 2 RF RF
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List Rev 2 Page 1035 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
AIRCRAFT INTERFACE PWA REAR PANEL 200 T1 T1
110
165
105
105
225 195
J7
70
15
CR9 CR17
CR12 CR 28
35
CR11
120
200
U1
C34
R4 C12 C13 CR12
T1 125 145
R6
+ + C29
C1 105
130
95
E8
U3
E7
C19 230 235
E6
195
E5
E1 E2 R 10
R 9
W1 CR 33 C 7
R 14 CR 32
85 90
C22
CR25
CR1 CR2
190 25 100
CR25 CR14 C16
CR7 CR3
R7 E4
CR4 C3
E3
C11
C8
C26 C10
C9 C4
C17 CR20
75 80
C15 C31 C6 C25 C2
C5 C27
J1
C30
5 175 135 130
CR24
CR6
40
45 150
CR C R 34 CR30 18 20
CR5
165
155 140
Q1
R12
115
20
CR 19
CR16
R13
U2 C 21
J2
10 250 110
10
C32
C28
65
A
C 33
C 14
CR10
CR18
10
SH2
CR R1 R2 26
U4
CR 27
185
50
CR32
R5 R3
R15 R11
R8
10
10 105
CR21
C24
C23
C 20
170 105
160 150 185
10
CR8 CR29
30 25 40
TP1 TP2
205
TP3
40
TP4
CR13
TP5
R19
TP6
205 110 30
205
CR31
30
180 110
55 60
210
215 220
110
40
Aircraft Interface PWA, P/N 205E0597–00 Figure 3 (Sheet 1 of 3)
23-70-02 Illustrated Parts List
Rev 2 Page 1036 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S AIRCRAFT INTERFACE PWA REAR PANEL 200 T1 T1
J7
R5 R3
R15 R11
CR R1 R2 26
R8 U4
CR 27
CR10
CR18
CR9 CR17
CR12 CR 28
A
CR21
C24
C23
C 20
CR11
CR32 C 33
C34 C 14
C32 U1 R4 C12 C13 CR12
T1
R6 C28
+
C1
+ C29 U3
65A
E8
102 C38
65A
SH2
E7
U5
E6
E5
E1 E2
C19 R 10
R 9
C 7
R 14 U2
CR 32
C 18 R 20 CR 34
J2 R12
R7
CR5
C22
CR6
CR2 CR25 CR14 L2 136
CR7 CR3
C37 E4 C36
CR4 C3
E3
C11
C8
C26 C10
C9 C4
L3 CR20
C5 C27 C30
J1
C15 C31 C6 C25 C2
L1
CR30
CR24 CR25
CR1
100A
CR16
R13
Q1
C 21
112
C35
W1 CR 33
CR 19
CR8 CR29
TP1 TP2 TP3 TP4
CR13
TP5
R19
TP6
CR31
Aircraft Interface PWA, P/N 205E0597–00 Post Mod Dot 6 Figure 3 (Sheet 2 of 3)
23-70-02 Illustrated Parts List
Rev 2 Page 1037 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S PIN 1
PIN 1
PIN 1
PIN 1
255 J5 STORE PROCESSOR PWA
245
P2 250 AIRCRAFT INTERFACE PWA
J3 240
A
SPARE PWA
J4 240 AUDIO PROCESSOR PWA
AIRCRAFT INTERFACE CABLE ASSEMBLY W1 (230)
Aircraft Interface PWA, P/N 205E0598–00 Figure 3 (Sheet 3 of 3)
23-70-02 Illustrated Parts List
Rev 1 Page 1038 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 3
PART NUMBER 1
205E0597–00
5
1N914, A, B
10
1N4148
15
1N5256A, B
20
1N5825
25
1.5KE250CA
30
1.5KE68C
35
1N759A
40
V130LA5
45 50 55
B191–20H MC1558U 2029800326
55A
2029800391
60
2160
65
25107
65A
NMF0509S
70
LM139J
75
LM136AH–2.5
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
PWA, AIRCRAFT INTERFACE A100S SSCVR (SEE FIG 2 FOR NHA) DIODE, SI, 75.0V, 75.0MA, SW (V16352) (0881009140) DIODE, SI, 100.0V, 300.0MA, SW (V16352) (0881041480) DIODE, SI, 30.0VZ, 4.2MA, ZENER (V04713) (0881052561) DIODE, SI, 40V, 5A, SCR (V04713) (0881058250) DIODE, SI, 250.0V, 5.0A, SUPRESSOR (V24444) (0889800034) DIODE, SI, 68.0V, 15.3A, SUPRESSOR (V24444) (0889800052) DIODE, SI, 12.0V, .1UA, ZENER (V06141) (0889900119) DVC, VRIS, 130VRMS, 20J, (1019800054) BRIDGE (V06288) (9391863) AMPLIFIER (V96906) (9391679) POWER SUPPLY, DC–DC, 15.5–42VIN (SUPSD BY ITEM 55A PRE SB012) POWER SUPPLY, DC–DC, 15.5–42VIN (SUPSDS ITEM 55 POST SB012) ATTACHING PARTS WASHER, #6, FIBRE .141 ID X (2739800041) *** POWER SUPPLY, DUAL, DC/DC CONV (V31669) (2029800308) (SUPSD BY ITEM 65A PRE ECO7977) POWER SUPPLY, DUAL, DC/DC CONV (V31669) (2029800360) (SUPSDS ITEM 65 POST ECO7977) INTEGRATED CIRCUIT, LINEAR , BIP, COMPARATOR, 14DIP, NH (V26014) (0469700905) INTEGRATED CIRCUIT, LINEAR , BIP, VREF, 3CAN, HNS (V26014) (0469701575)
UNITS PER ASSY RF 1 12 1 1 2 5 1 9 1 1 1 1
7
1
2
1
1
23-70-02 Illustrated Parts List
Rev 2 Page 1039 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
3
80
10042–DAP
85
2N2907A
90
10042–DAP
95 100
3371222004 3611010001
100A
167103J400A
102
158X104K
105
CK05BX104K
110
CK05BX103K
112
CK06BX104K
115
CK06BX105K
120
CK06BX562K
125
3781312522
130
7473422005
135
DD1032
136
0448900001
136A
0449800012
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
ATTACHING PARTS PAD, TRANSISTOR TO–18 OR 28, 4 PI (1899800002) TRANSISTOR, PNP SW 60V, HFE 100 (V07263) (2631029071) ATTACHING PARTS PAD, TRANSISTOR TO–18 OR 28, 4 PI (1899800002) *** CAPACITOR, STAN, 15V, 22UF, +10% CAPACITOR, PEM, 250V, 0.010 UF, 5%, (Mfg. MLRY, No. 167/.01/J/250/A) CAPACITOR, PEM, 400V, 0.01 UF, –5% (3610510001) (ADDED POST SB11) CAPACITOR, F, PEM, 250VAC, 0.10 UF, 10% (3164510002) (POST MOD DOT 6) CAPACITOR, 0.10 UF, 10%, 50V (V12294) (3631510002) CAPACITOR, 0.01 UF, 10%, 100V (V12294) (3633910001) CAPACITOR, CERAMIC, 0.10 UF, 10%, 100V (3695110002) (ADDED POST SB11) CAPACITOR, 1.0 UF, 10%, 50V (V51406) (3691510003) CAPACITOR, CERAMIC, 5600 PF, 10%, 200V (3693456000) CAPACITOR, FXD, 10 UF, 10%, 35V, (Mfg. UNION CARBID, No. T330C106K035AS) CAPACITOR, AL, 63V, 220 UF, +20%, (Mfg. SPR, No. 630D227M063FK5A) CAPACITOR 0.01 UF, 1 KV (V71279) (9391769) CHOKE ASSY, FERRITE, WB, 750 (SUPSD BY ITEM 136A PRE ECO8645) CHOKE ASSY, FERRITE, WB, .6K/50MHZ (SUPSDS ITEM 136 POST ECO8645)
UNITS PER ASSY 1 1
1
2 2
2
1
6 17 1
1 2 1
2 1 3 3
23-70-02 Illustrated Parts List
Rev 2 Page 1040 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
3
140 145 150 155 160 165 170 175 180
6080908669 6080910000 6080910001 6080924900 6080929401 6080930102 6080964900 6080968100 RN60D22R1F
185 190
6080130902 750–83–R100K
195
750–83R47K
200
TM7–3
205
2559800280
210
0639800074
215
5602–55–32
220
MS51957–5
225 230
62650–1 024E0611–00
235
77103–050
240
120–064–455F
245
4626–6300
250
68120–050
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
RESISTOR, 86.6 OHM, 1%, 1/10W RESISTOR. 1K, 1%, 1/10W RESISTOR. 10K, 1%, 1/10W RESISTOR, 2.49K, 1%, 1/10W RESISTOR, 29.4K, 1%, 1/10W RESISTOR. 301K, 1%, 1/10W RESISTOR, 6.49K, 1%, 1/10W RESISTOR. 6.81K, 1%, 1/10W RESISTOR, MF, 22.1 OHM, 0.5W, 1% (6140122100) RESISTOR, 309K, 1%, 1/10W, 100 PP NETWORK, RESISTOR, 4/100K OHM, 2% (V11236) (1829800135) NETWORK, RESISTOR, 4/47K OHM, 20W@ (V11236) (1829800192) TRANSFORMER, POWER 115V, 400 HZ INPUT (V01121) (2629800044) TERM, STAND OFF, 2 TURRET, NON–INS, (Mfg. CTC, No. 160–1558–03–01–00) CONNECTOR, 57–PIN, RACK & PANEL, (Mfg. CANNON, No. DPX036571–0059) ATTACHING PARTS WASHER, FIBRE, .10 IDX.190 (2739800038) SCREW, PAN HEAD, 2–56 X3/8 (V96906) (2290200067) *** CONNECTOR, PCB TAB (0639800709) CABLE ASSEMBLY, W1, AIRCRAFT INTERFACE ATTACHING PARTS SPRT, STRAIN RELIEF FOR (2799800018) *** CONNECTOR, 64–CONTACT, IDC FEMALE (0639801521) CONNECTOR, RECT, 26–CONTACT, PLUG (0639800696) CONNECTOR, PCB, 50CONT, TWO ROW (V53387) (0639801447)
UNITS PER ASSY 1 1 2 1 1 3 1 1 1 2 1 2 1 6
1
3 3
1 1
1
2 1 1
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List Page 1041 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
3
3518
255 –260 –265
206E0597–00 905E0597–01
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
INSERT, POLARIZNG KEY (V53387) (4219800026) BOARD, PRINTED WIRING SCHEMATIC, AIRCRAFT INTERFACE A100S
UNITS PER ASSY 2 1 AR
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List Page 1042 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
260
245
80 85
350
90 95
45 50
350
30
350
25
U11 CR2
R 5
350
R 6
C 44
U21
U12
U20
U18
+ 120
U19
U13
C 50
C88
C 46
C 45
70 75
U23
SH2
U22
U16
L1
5
U25 R44
J5
350
C23
195
C20
C14 R27
R25
R36
R39
175
R41
165 160 210 340
R 47
170 335
C76
C68
C78
C63
C66
C65
C64
C67
C73
C69
345
C C 47 24
215
345
C15 C28
230 345
U14
C59
C81
R 34
U10
C C R 19 10 R 20 31
C C C C 27 31 21 26
C51
105
240
R11
135 140
R10 R33
125 130
C7 C13 C2
R2
C3
R1 R17
C37 C18 C35 C9
U3
100
C C C 83 85 84
295
+
T3
+ +
T1
R19 R18
C61
330
T2
R3
C60
310
C1
350
R4
R R 30 32
110 370 375 380
T4
R29 C55
Q1
C 79
C 74
R R 21 23
U9
C C 22 16
155
10
CR3
U4
U6 C36 C12 C34 C6
R12
Q2
C 48
R7
C75
C 11
C 38
U5
270
CR4
R15 C R R 52 46 48
20
R13
C 57
U7
C56
240
C86
U15
C C C C C R 17 R 80 71 62 70 C33 C5 C29 C4 22 C32 C25 R 26 R 28 24 C53
C30
C 39
R9
R35
350 190
C 58
R8
C72
C87
R49 R14
CR5
R40
CR1
R45
R16 CR6
C 77
R38
A
C8
R37 R43
340
J6
290
R42
150 220 200
365 350 35 40
U1
C49 U24
370 375 380
U8 P1
U17
A
C 82
C41
U2
C 43
C40
80 85
295
C 42
180 350
335
205 185 320 325
350 105
340
155
170
225
355 360
150
300
Audio Processor PWA, P/N 205E0598–00 Figure 4 (Sheet 1 of 2)
23-70-02 Illustrated Parts List Rev 1 Page 1043 July 30/94 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
60 65
CR2
U11 R 5
R 6
C 44
U21
U18
U13 C88
U23
265
U22
U1
R44 145
R42
C23
C20
C14
A
C8
R37
R27
310
R25
R36
20
R43
285
R38
255
R9
R40
R8
350
C72
C76
105
C68
C78
C63
C66
C65
C64
R47
200 350 C C 47 24 R 22
C C 15 28
C73
C69
C75
R49
C 39
C59
U10
C 11
R C C 20 19 10 R 31
C C C C 27 31 21 26
C51
350
245 350
Q1
55 350
C 79
C 74 R33
280 C13 C2
R4
C1
245 160
R2
R1
R17
U3
T2 235 T3
T1
R19 R18
175 C3
R3
C60
310
C7
T4
R29 C55
U6
C61
165
Q2
C 48
C36 C12 C34 C6
C37 C18 C35 C9
310
R11
R10
R R 30 32
C C 22 16
C 38
C81
U9
105 115
CR3
U4
R C C C C C 21 R 23 17 R 80 71 62 70 C33 C5 C29 C4 C C R 26 32 25 28 R 24
350
CR4 R12
U7
U5
275 150
R13
C 57
R15 C R 46 R 52 48
250
C86
U15
R7
R35
C53 C 30 R 34
C67
C 58
C56
U14
C87
R45
CR5
R41
15
CR1 R14
R16 CR6
C 77
R39
155
L1
U25
10
315
U16
J5
J6
90 95
C45
C 49
350
U8
C 46
150
U24
+
P1
U17
A
C82
C41
U2
305
C 50
U19
150
C 42
C 43
C40 350
U12
U20
+
C C C 85 84 83
+ +
105
Audio Processor PWA, P/N 205E0598–00 Figure 4 (Sheet 2 of 2)
23-70-02 Illustrated Parts List Rev 2 Page 1044 Mar. 15/00 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 4
PART NUMBER 1
205E0598–00
5
VK200
10
1N5234B
15
0884700024
20
1N4614
25
HLMP–1700–101
30
046E0280–01A
35
046E0281–01
40
619–24–CC–B.1
45
046E0282–01
50
619–24–CC–B.1
55
OP–27BZ
60
0469701736
65
821573–3
70
0469701858
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
PWA, AUDIO PROCESSOR A100S SSCVR (SEE FIG 2 FOR NHA) CHOKE, FERRITE, .75K/50MHZ (V01121) (0449800006) DIODE, SI, .2VZ, 0.0MA, ENER (V16352) (0881052342) DIODE, SI, .0V, 0.0MA, DET, ] (Mfg. HP/TRW, No. 5082–2835/A2S835) DIODE, SI, .8VZ, 20MA, ENER, (V04713) (0881046140) INDICATOR, LED RED, –1, f TTL/CMOS (1379800088) INTEGRATED CIRCUIT, SERIAL PROM (V06141) (046E028001) INTEGRATED CIRCUIT, CHMOS, PLD, 24 DIP ATTACHING PARTS SOCKET INTEGRATED CIRCUIT 24 PIN W/DCPLG CAPACITOR, (V06141) (2369800248) *** INTEGRATED CIRCUIT, CHMOS, PLD, 24 DIP ATTACHING PARTS SOCKET INTEGRATED CIRCUIT 24 PIN W/DCPLG CAPACITOR, (V06141) (2369800248) *** INTEGRATED CIRCUIT, LINEAR, H BIP, OPAMP, 8 DIP, NS (V06141) (0464700009) INTEGRATED CIRCUIT, ARRAY, MOS, LCA, 84PLCC, Mfg. XLNX/MML, No. XC3030–70PC84W) ATTACHING PARTS SOCKET, PLCC, 4 CONT, /SOLDER (2369800291) *** INTEGRATED CIRCUIT, DIGITAL, G CMOS, INTERFACE, 0 DIP
UNITS PER ASSY RF 1 2 1
2 1 1 1
1
1
1
1
1
1
4
23-70-02 Illustrated Parts List Page 1045 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
4
75
2369800242
80
DS2165QN
85
821581–1
90
0469701861
95
821665–1
100
0469701868
105
OP470AY
110
LH0002H
115
DG201AAK
120
1849700118
125
2N2222A
130
10042–DAP
135
2N2907A
140
10042–DAP
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
ATTACHING PARTS SOCKET INTEGRATED CIRCUIT 20PIN W/DCPLG CAPACITOR *** INTEGRATED CIRCUIT, DIGITAL, CMOS, DSP, 28PLCC (V0B0A9) (0469701859) ATTACHING PARTS SOCKET, PLCC, 28CONT, SQUARE (2369800289) *** INTEGRATED CIRCUIT, MEMORY, HCMOS, FIFO, 1K X 9 ATTACHING PARTS SOCKET, PLCC, 32CONT, RECTANGLE (V00779) (2369800276) *** INTEGRATED CIRCUIT, LINEAR , BIP, VR, 3PP, NH, (Mfg. MOT, No. MC79LO5ABP*SCR–55/+85C) INTEGRATED CIRCUIT, LINEAR, BIP, OPAMP, 14DIP (0469701873) INTEGRATED CIRCUIT, LINEAR , BIP, AMP, 8CAN, HNS (V27014) (0469701881) INTEGRATED CIRCUIT, DIGITAL, CMOS, SW, 16DIP, HNS, (V1Y409) (0469701882) OSCILATOR, CRYSTAL, HCMOS, 12.288MHZ, (Mfg. CONW, No. H83G–12.288MHZ) TRANSISTOR, NPN, SI, SINGLE, 30VCE (V07263) (2631022221) ATTACHING PARTS PAD, TRANSISTOR TO–18 OR 28, 4 PI (1899800002) *** TRANSISTOR, PNP SW 60V, HFE 100 (V07263) (2631029071) ATTACHING PARTS PAD, TRANSISTOR TO–18 OR 28, 4 PI (1899800002) ***
UNITS PER ASSY 4
5
5
2
2
1
5 1
1
1
1
1
1
1
23-70-02 Illustrated Parts List Page 1046 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
4
145
750–101–R47K
150
1829800193
155
1829800194
160
1829800195
165
1829800196
170
1829800197
175
1829800198
180
1829800199
185
1829800200
190
1829800201
195
1829800202
200
1829800203
205
1829800204
210
1829800206
215
4989–02–1822F
220
1829800209
225
1829800210
230
1829800211
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
NETWORK, RESISTOR, 9/47K OHM, 2% (V11236) (1829800167) NETWORK, RESISTOR, 4/10KOHM, 1%, (Mfg. IRC, No. 4989–02–1002–F) NETWORK, RESISTOR, 4/1KOHM, 1%, (Mfg. IRC, No. 4989–02–1001–F) NETWORK, RESISTOR, 4/15KOHM, 1%, (Mfg. IRC, No. 4989–02–1502–F) NETWORK, RESISTOR, 4/7.5KOHM, 1%, (Mfg. IRC, No. 4989–02–7501–F) NETWORK, RESISTOR, 4/1.87KOHM 1%, (Mfg. IRC, No. 4989–02–1871–F) NETWORK, RESISTOR, 4/17.4KOHM, 1%, (Mfg. IRC, No. 4989–02–1742–F) NETWORK, RESISTOR, 4/6.19KOHM 1%, (Mfg. IRC, No. 4989–02–6191–F) NETWORK, RESISTOR, 4/13KOHM, 1%, (Mfg. IRC, No. 4989–02–1302–F) NETWORK, RESISTOR, 4/825OHM 1%, (Mfg. IRC, No. 4989–02–8250–F) NETWORK, RESISTOR, 4/11KOHM, 1%, (Mfg. IRC, No. 4989–02–1102–F) NETWORK, RESISTOR, 4/4.99KOHM, 1%, (Mfg. IRC, No. 4989–02–4991–F) NETWORK, RESISTOR, 4/604OHM, .25%, (Mfg. IRC, No. 4989–03–6040–C) NETWORK, RESISTOR, 4/20OHM 1%, (Mfg. IRC, No. 4989–02–20R0–F) NETWORK, RESISTOR, 4/18.2KOHM 1% (1829800207) NETWORK, RESISTOR, 4/20KOHM, 1%, (Mfg. IRC, No. 4989–02–2002–F) NETWORK, RESISTOR, 4/1.5KOHM 1%, (Mfg. IRC, No. 4989–02–1501–F) NETWORK, RESISTOR, 4/150KOHM, 0.25%, (Mfg. IRC, No. 4989–03–1503–C)
UNITS PER ASSY 2 5 3 2 4 2
2
1
1 1 1 2
1
1 1 1 1 1
23-70-02 Illustrated Parts List Page 1047 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
4
235
68WR10K
240 245 250 255 260 265 270 275 280 285 290
6080905629 6080910000 6080910009 6080910701 6080912400 6080930100 6080935700 6080949901 6080973200 6080988701 3019822003
295 300 305
3371139004 3371315004 403DDC
310
CK05BX104K
315
CK05BX102K
320
CKO5BX101K
325
CK05BX561K
330
CK06BX274K
335
CCR06CG472FR
340
CCR07CG333FR
345
CCR07CG683FR
345A
CCR07CG104FR
350
MD015C104KAA
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
POT, TRIMMER, 10K OHM, 10%, 0.5W (V01121) (2019800376) RESISTOR, 56.2 OHM, 1%, 0.1W RESISTOR, 1K OHM, 1%, 0.1W RESISTOR, 100.0 OHM, 1%, 0.1W RESISTOR, 10.7K OHM, 1%, 0.1W RESISTOR, 1.24K OHM, 1%, 0.1W RESISTOR, 3.01K OHM, 1%, 0.1W RESISTOR, 3.57K OHM, 1%, 0.1W RESISTOR, 49.9K OHM, 1%, 0.1W RESISTOR, 7.32K OHM, 1%, 0.1W RESISTOR, 88.7K OHM, 1%, 0.1W CAPACITOR, CERAMIC, 50V, 2.2 UF, +20%, (Mfg. MUER/MML, No. RPE117X7R225M50V) CAPACITOR, STAN, 10V, 39 UF, +10% CAPACITOR, STAN, 20V, 15 UF, +10% CAPACITOR, CERAMIC, DECOUPLING, .04UF X7R (3459800023) CAPACITOR, 0.10 UF, 10%, 50V (V12294) (3631510002) CAPACITOR, 1000 PF, 10%, 200V (3633410000) CAPACITOR, 100 PF, 10%, 200V (3633410009) CAPACITOR, 560 PF, 10%, 200V (3633456009) CAPACITOR, 0.27 UF, 10%, 50V (3691527002) CAPACITOR, CERAMIC, 0.0047UF, 1%, 100V (3990547000) CAPACITOR, FIX, CERAMIC, 0.033UF, 1%, 50V (3991133001) CAPACITOR, FIX, CERAMIC, .068 UF, 1%, 50V (3991168001) (SUPSD BY ITEM 345A PRE ECO9282) CAPACITOR, FIX, CERAMIC, .1 UF, 1%, 50V (3991110002) (SUPSDS ITEM 345 POST ECO9282) CAPACITOR, CERAMIC, 0.1UF, 50V, +10% (V96906) (7540110002)
UNITS PER ASSY 4 2 3 1 1 1 1 1 1 1 1 2
2 2 1 4 1 5 4 4 6 25 7
7
26
23-70-02 Illustrated Parts List Rev 2 Page 1048 Mar. 15/00 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
4
355
9300–286–01
360
SP–310
365
0639801522
370 375 380
2299800197 2739800090 2879800213
–385
75401–001
–390
905E0598–01
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
TRANSFORMER, SELECTED ATTACHING PARTS COVER, FOR SP–66 TRANSFORMER, (0759800054) *** CONNECTOR, 64 CONT, PIN HDR MALE, (Mfg. PAND, No. 120–064–053–00) ATTACHING PARTS SCREW, M2.5X12, PAN HEAD, SST WASHER, EXT TOOTH, M2.5, SST NUT, M2.5X.45 *** CONTROL, PIN .025SQ, .345L, (V01121) (0659800093) SCHEMATIC, AUDIO PROCESSOR. A100S
UNITS PER ASSY 4 4
1
2 2 2 46 AR
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List Page 1049 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
J2 P2
15
Flash Crash Survivable Store Unit (FCSSU), P/N 253E0348–03, P/N 253E0660–00, P/N 253E0992–00, P/N 253E1290–00, P/N 253E1293–00 Figure 5
23-70-02
Illustrated Parts List Rev 2 Page 1050 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 5
PART NUMBER
AIRLINE PART NO.
NOMENCLATURE 1234567
ASSEMBLY, FLASH CRASH SURVIVABLE STORE UNIT (SEE FIGURE 2 FOR NHA) OBSOLETE – REPLACED BY P/N 205E0660–00 FSB No. SSCVR 003 ASSEMBLY, FLASH CRASH SURVIVABLE STORE UNIT (SEE FIGURE 5 FOR NHA) THIS UNIT REPLACES ITEM NO. 1 AS PER FSB No. SSCVR 003
EFF CODE
UNITS PER ASSY
A
RF
B
RF
1
253E0348–03
1A
205E0660–00
1B
253E0992–00
ASSEMBLY, FLASH CRASH SURVIVABLE STORE UNIT (SEE FIGURE 5 FOR NHA) THIS UNIT IS AN IMPROVEMENT TO ITEM NO. 1 AS PER FSB No. SSCVR 006
RF
1B
253E1290–00
ASSEMBLY, FLASH CRASH SURVIVABLE STORE UNIT (SEE FIGURE 5 FOR NHA) THIS UNIT IS AN IMPROVEMENT TO ITEM NO. 1 AS PER FSB No. SSCVR 006
RF
1C
253E1293–00
ASSEMBLY, FLASH CRASH SURVIVABLE STORE UNIT (SEE FIGURE 5 FOR NHA) THIS UNIT IS AN IMPORVEMENT TO ITEM NO. 1 AS PER FSB No. SSCVR 006
RF
15
BCDAT–2–619–5
*** LABEL, BLANK 3.0 X .9 (9090100789)
AR
*** CAUTION *** THIS MODULE CAN ONLY BE SERVICED BY FACTORY TRAINED TECHNICIANS. OPENING MAY VOID WARRANTY. P/N 253–E0XXX–XX S/N XXXXX WT XXXXX Kg REV XX
23-70-02
Illustrated Parts List Rev 2 Page 1051 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
235 70
185
240 55
145
110 115
15
120
280
275
260 60
45 50
240 60
195
235 90
240 90
270
155
155 195
R11
300 305
U24
TP40
275
U7
J5
70 235
R 15
U12
C107
85 225
C112
165
L3
130 235
C113
C110
160
C16 C101
35 40
TP2
U6
U23
C8 C 123
U5
CR2 C1
C11
U18
C9
R4
C109
CR3
U11
R3
150 245
C118
135
R10 C C 13 7
R9
R8
C3
220
C10 U4
U9 C2
U13
C111
Y1 C6
C113
U2 C102
E1 E2
R2
L1
265
125 250
U19
C15
290 200
100 105 255
U22
C115
C108
C5
U3
275 160
U15
U8
270
20 (FAULT INDICATOR)
CR5
R6
TP1
180
R12
U20
L2
175
R1 R16
R 17
C 106
10 190
80
C114
TP10
U10
CR1 R7
145
C117
U14
U1
C 12
U16
U21
C4
W2
295
CR 4
U17
R5
J2
TP20
5
TP30
C14
210 215
140 275
95 240
155
205
170
65 230
310
165
170
315
130 235
75 235
130 285 155 235
25 30
275
Notes: 1. C8 is installed under IC chip U5; C7 and C13 are installed under U4; C10 is installed under the socket of U22; C15 is installed under Y1; C102 is installed under U2. 2. DIP CAPS (C1XX) share the same holes as their corresponding IC chip's (UXX). Reference designators for CAPS are similar to their corresponding IC chip plus 100. Example: C123 is located under U23, etc.
Store Processor PWA, P/N 205E0601–00, P/N 205E1027–00 Figure 6
23-70-02 Illustrated Parts List
Rev 1 Page 1052 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 6
PART NUMBER
1
205E0601–00
1A
205E1027–00
5
1N4761A
10
0884700024
15
1N5819
20
HLMP–7000–1S1
25
046E0283–01A
30
236–C2110–10
35
046E0284–01A
40
100–0200612
45
046E0285–01A
50
SS020–01–TG
55
0469701469
AIRLINE PART NO.
NOMENCLATURE 1234567
PWA, STORE PROCESSOR SSCVR (SEE FIGURE 2 FOR NHA) (SUPSD BY ITEM 1A PRE SB003) PWA, STORE PROCESSOR SSCVR (SEE FIGURE 2 FOR NHA) (SUPSDS ITEM 1 POST SB003) DIODE, SI, 75.0 VZ, 3.3 MA, ZENER (V04713) (0881047611) Deleted per Rev. C, ECO 0006654 (effectivity date 03–12–92). DIODE, SI, 8.0V, 10.0 MA, SDET, (Mfg. HP/TRW, No. 5082–2835/A2S835) DIODE, SI, 40.0V, 500.0 MA, SDET (V04713) (0889758190) DIODE, GAP, 3.0V, 5.0 MA, LED (V50434) (1379800099) INTEGRATED CIRCUIT, PLD, 20 DIP (V06141) (046E0283–01) ATTACHING PARTS SOCKET, STRIP, 10 PIN *** INTEGRATED CIRCUIT, PLD, 20 DIP (V06141) (046E0284–01) ATTACHING PARTS SOCKET,INTEGRATED CIRCUIT, DIP 20PIN,SLDR (236–98–00171) *** INTEGRATED CIRCUIT, EPROM,40 DIP (V06141) (046E0285–01) ATTACHING PARTS SOCKET, STRIP, 20 PIN, .100 (2369800136) *** INTEGRATED CIRCUIT, DIGITAL, CMOS, LATCH, 24 DIP, (Mfg. IDT, No. IDT54FCT843BDB) Deleted per Rev. F, ECO 0007628 (effectivity date 3–28–94).
EFF CODE
UNITS PER ASSY
A
RF
B
RF
A
1
1 2 1 1
2 1
1
1
2
1
23-70-02 Illustrated Parts Parts List List Illustrated
Rev 12 Page Page 1053 1053 Rev July Mar. 30/94 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
6 55A
0469702493
60
0469701732
65
CD54ACT238F3A
70
54FCT541DM
75
54ACTQ245DM
80
MAX632AMJA
80A
NMF0512S
85
CD54HCT14F
90
0469701883
95
AM29C821/BLA
100
0469701885
105
821574–1
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
INTEGRATED CIRCUIT, DIGITAL, CMOS, LATCH, 24 DIP, (Mfg. IDT, No. IDT54FCT841BD) Added per Rev. F, ECO 0007628 (effectivity date 3–28–94). INTEGRATED CIRCUIT, MEMORY, CMOS, SRAM, 32KX8, INTEGRATED CIRCUIT, DIGITAL, ACTMOS, DECODER/DEMUX (V34371) (046–97–01862) INTEGRATED CIRCUIT, DIGITAL, FCT, DRIVER, 20 DIP (V27014) (046–97–01863) INTEGRATED CIRCUIT,DIGITAL, ACTQ, TRANSCEIVER, 20 DIP, (V27014) (046–97–01865) INTEGRATED CIRCUIT, LINEAR, CMOS, VR, 8 DIP, HNS (V96906) (046–97–01870) Deleted per Rev. C, ECO 0006654 (effectivity date 03–12–92. POWER SUPPLY, DC/DC CONVERTER, 5 VDC, 8 DIP, (202–98–00322) Added per Rev. C ECO 0006654 (effectivity date 03–12–92. INTEGRATED CIRCUIT, DIGITAL, HCTMOS, ST, 14 DIP (V34371) (046–97–01871) INTEGRATED CIRCUIT, DIGITAL, CMOS, LATCH, 24 SDIP, (Mfg. AMD/MML, No. 5962–8760301LA) INTEGRATED CIRCUIT, DIGITAL, CMOS, REGULATOR, 24 SDIP (V34335) (046–97–01884) INTEGRATED CIRCUIT, DIGITAL, CMOS, MIPRCS, 68PLCC, (Mfg. AMD, No. N80C186–16*SCREEN) ATTACHING PARTS SOCKET, PLCC, 68 CONT, SQUARE, (V00779) (236–98–00270) ***
UNITS PER ASSY 1
2 A
1
2
1
A
1
A
1
1
2
2
1
1
23-70-02 Illustrated Parts List
Rev 1 Page 1054 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 6
PART NUMBER
110
0469701888
115
821665–1
120
0469701892
125
0469701896
130
SN54BCT2244J
135
DDU–8Z297
140
42285
145
39424
150
1849700119
155
2559800205
160
7447–1–P42
165
750–101–R10K
170
750–83–R47
175
750–83–R10K
180
750–101–R100K
185
750–101–R47K
190
RNC50*DSCR
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
INTEGRATED CIRCUIT, DIGITAL, CMOS, EEPROM, 32PLCC ATTACHING PARTS SOCKET, PLCC, 32CONT, RECTANGLE (V00779) (236–98–00276) *** INTEGRATED CIRCUIT, LINEAR , BIP, VR, 8 DIP, NH INTEGRATED CIRCUIT, DIGITAL, CMOS, MPSUP, 8 DIP, NH, (Mfg. LTEC, No. LTC690IN8*SCREEN) INTEGRATED CIRCUIT, DIGITAL, CMOS, BUFFER, 20 DIP, HNS (V9K523) (046–97–01905) DVC, DELAY UNIT, HCMOS, 8 DIP (V22519) (101–98–00077) INDUCTOR, DUAL, 500 UH, 660 MA, (055–98–00221) Deleted per Rev. C, ECO 0006654 (effectivity date 03–12–92). CHOKE, ASSEMBLY, FERRITE, WB, 750 (V06141) (044–89–00001) OSCILATOR, CRYSTAL, HCMOS, 32.0 MHZ, (Mfg. CONW, No. S83R–32.000 MHZ) TERMINAL PW, 2–TURRET, .062 BD, (Mfg. CTC/MML, No. 160–1558–02–05–00) TERMINAL, STAND OFF, NON–INSULATED, SWAGE (2559800255) NETWORK, RESISTOR, 9/10K OHM, 2% (V11236) (182–98–00076) NETWORK, RESISTOR, 4/47 OHM, 2% (V11236) (182–98–00085) NETWORK,RESISTOR, 4/10K OHM, 2% (V11236) (182–98–00095) NETWORK, RESISTOR, 9/100K OHM, 2% (V11236) (182–98–00111) NETWORK, RESISTOR, 9/47K OHM, 2% (V11236) (182–98–00167) RESISTOR, MF, 1.5K OHM, 1%, 0.1W (600–49–15000)
UNITS PER ASSY 1
1
1 1
3
1 1
2 1
4
2 2 2 1 2 1 1
23-70-02 Illustrated Parts List
Rev 1 Page 1055 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 6
PART NUMBER
195 200 205
6080102269 6080924900 6112820001
210
6140116200
215
6140166508
220
3392222005
220A
3392222005
221
3381347004
225
104JEV
230
104JEW
235
104JEX
240
104JEY
245
502DFF
250
502DRC
255
183DHL
260
263D28
265
3621215004
270
3623633004
275
CK05BX104K
280
3781312522
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
RESISTOR, 22.6 OHMS, 1%, 0.1W RESISTOR, 2.49K OHMS, 1%, 0.1W RESISTOR, MF, 20.0K OHM, 0.1% 0.1W, (Mfg. IRC, No. MAR5–T16–20.0K–.1%) RESISTOR, MF, 1.62K OHM, 0.1%, 10 PPM (Mfg. DALE, No. PTF–561K62BT–13) RESISTOR, MF, 66.5 OHM, 0.1%, 10 PPM, (Mfg. DALE, No. PTF–5666R5BT–13) CAPACITOR, STAN, 20V, 220 UF, +20%, (Mfg. SPR/MML, No. 152D227X9020S2) CAPACITOR, STAN, 20V, 220 UF, +20%, (Mfg. SPR/MML, No. 152D227X9020S2) C2 value changed per Rev. C, ECO 0006654 (effectivity date 03–12–92). See item 221. CAPACITOR, STAN, 20V, 47 UF, +20%, New C2 value per Rev. C. CAPACITOR, CERAMIC, 50V, 10 UF, +25% (345–98–00015) CAPACITOR, CERAMIC, 50V, 10 UF, +25% (345–98–00016) CAPACITOR, CERAMIC, DECOUPLING, 0.1 UF X7R (345–98–00018) CAPACITOR, CERAMIC, DECOUPLING, 0.1 UF X7R (345–98–00019) CAPACITOR, CERAMIC, DECOUPLING, 0.005 UF (345–98–00021) CAPACITOR, CERAMIC, .005UF, X7R, (345–98–00022) CAPACITOR, CERAMIC, DECOUPLING, 0.018 UF, X7R (345–98–00024) CAPACITOR, CERAMIC, DECOUPLING, 0.026 UF, X7R (345–98–00025) CAPACITOR, TEP, 20V, 15.0 UF, 20% (Mfg. KEMET, No. T370E156M020AS) CAPACITOR, TEP, 10V, 33.0 UF, 20%, (Mfg. KEMET, No. T330C336M010AS) CAPACITOR, 0.10 UF, 10%, 50V (V12294) (363–15–10002) CAPACITOR, FIXED, 10 UF, 10%, 35V, (Mfg. UNION CARBID, No. T330C106K035AS)
UNITS PER ASSY 2 1 1 1 1 2
A
1
A
1 1
A
1 7 5 2 1 1 2 1 2 5 1
23-70-02 Illustrated Parts List
Rev 1 Page 1056 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 6
PART NUMBER
285
7552110002
290
CK05BX102K
295
024–E0612–00
300
3399–6026
305
3926–0000T
310
3433–5302
315
3518
–320 –325 –330 –335
206E0601–00 905E0601–01 206E1027–00 905E1027–01
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
CAPACITOR, CERAMIC, 0.1 UF, 20%, 50V, X7R, (Mfg. KEMET, No. C420C104MR5RCA) CAPACITOR 0.001 UF, 200V (9305BX102K) Deleted per Rev. C, ECO 0006654 (effectivity date 03–12–92). CABLE ASSEMBLY, W2, STORE PROCESSOR CONNECTOR, RECT, 26–CONTACT, PLUG (V53387) (063–98–00367) CONNECTOR, RECT, 26–CONTACT PWB MT (063–98–01136) CONNECTOR, RECT, 50–CONTACT, RECEPTICLE HDR (063–98–00818) ATTACHING PARTS INSERT, POLARIZNG KEY (V53387) (421–98–00026) *** BOARD, PRINTED WIRING (2M) SCHEMATIC, STORE PROCESSOR (2M) BOARD, PRINTED WIRING (8M) SCHEMATIC, STORE PROCESSOR (8M)
UNITS PER ASSY 2
1
1 1 1 1
2
A A B B
1 AR 1 AR
– ITEM NOT ILLUSTRATED
23-70-02 Illustrated Parts List
Rev 1 Page 1057 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
15
ÀÀ ÀÀ ÀÀ
20 115 75
30 35
110 140
40
150
65 45
60
5
50
10
25
105 135
55
85 70 90 95 100 125 130
80 120 145
155 160
MODEL AI51/A151B CONTROL UNITS (REMOTE MICROPHONE USED )
MODEL AI52/A152B CONTROL UNITS (BUILT-IN MICROPHONE)
Control Unit, P/N 93A151–XX, 93A152–XX Figure 7
23-70-02
Illustrated Parts List Rev 1 Page 1058 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 7
PART NUMBER 1
93A15100
1A
93A15101
1B
93A15120
1C
93A15130
1D 1E
93A15140 93A15150
1F
93A15200
1G
93A15201
1H
93A15204
1J
93A15220
1K
93A15225
1L
93A15230
1M
93A15235
1N
93A15240
1P
93A15250
1Q
93A15260
1R
93A15270
5 10 15
17D17–0262 93–624 9300A014
15A 15B 15C
9300A014–01 9300A014–02 9300A014–03
AIRLINE PART NO.
NOMENCLATURE 1234567
CONTROL UNIT ASSEMBLY MODEL A151,MOD (SEE FIG 1 FOR NHA) CONTROL UNIT ASSEMBLY MODEL A151–1, M CONTROL UNIT ASSEMBLY A151 B MODIFICATION 2 CONTROL UNIT ASSEMBLY A151B MODIFICATION 2 CONTROL UNIT ASSEMBLY A151B CONTROL UNIT ASSEMBLY A151B MODIFICATION 1 CONTROL UNIT ASSEMBLY. MODEL A152, MOD CONTROL UNIT ASSEMBLY MODEL A152–1 MOD CONTROL UNIT ASSEMBLY MODEL A152–4 MOD CONTROL UNIT ASSEMBLY A152 B MODIFICATION 2 CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 CONTROL UNIT ASSEMBLY MODEL A152B MOD CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 CONTROL UNIT ASSEMBLY A152B MODIFICATION 2 MODIFICATION RECORD PLATE NAMEPLATE FRONT PANEL ASSEMBLY – GRAY FRONT PANEL ASSEMBLY – BLACK FRONT PANEL ASSEMBLY–BROWN FRONT,PANEL ASSEMBLY–ATR 42 BROWN
EFF CODE
UNITS PER ASSY
A
RF
B
RF
C
RF
D
RF
E F
RF RF
G
RF
H
RF
J
RF
K
RF
L
RF
M
RF
N
RF
P
RF
Q
RF
R
RF
S
RF
A,C,G, J–L,N,P B,D,H,M,S E,Q,R F
1 1 1 1 1 1
23-70-02
Illustrated Parts List Rev 2 Page 1059 Mar. 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
7
20
8EP46R3
25
9300–233
25A 25B 30 35 40
9300–233–01 9300–233–04 9300–179–01 9300–179–02 L–11
45 50
93–1021 9300–388
55
9300–195
60
MS15795–803
65
8EP44R3
70 75 80 80A
9300–329 9300–337 93A264 93A267
80B 80C
93A265 93A268
85
9–1504
90 95 100 105 110 115 120 125 130 135
93A307 9300–A033 93A307 9300–204 9300–205 9300–344 9300–377 93A244 93A307 9300–204
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
ATTACHING PARTS SCREW, PAN HEAD, 4–40 X 3/8 (V06141) (938EP46R3) *** METER
UNITS PER ASSY 4
METER METER SWITCH, GREEN SWITCH, RED PHONE JACK (9300384) ATTACHING PARTS SHOULDER WASHER PLUG *** .COVER, 2.12W X 5.00L X 2.50, AL ATTACHING PARTS WASHER, #4, FLAT ST STL (V96906) (2730200004) SCREW,PAN HEAD,4–40 X1/4 (V06141) (938EP44R3) *** INSULATOR PLUG HARNESS ASSEMBLY. HARNESS ASSEMBLY–CONTROL UNIT HARNESS ASSEMBLY. HARNESS ASSEMBLY–CONTROL UNIT ATTACHING PARTS NUT (79NM–40) (V06141) (9391504) *** CHASSIS ASSEMBLY, CONTROL UNIT BRACKET & MICROPHONE CHASSIS ASSEMBLY, CONTROL UNIT DAMPER, MICROPHONE MICROPHONE MICROPHONE HUM SHIELD GROMMET BRACKET & MICROPHONE ASSEMBLY CHASSIS ASSEMBLY, CONTROL UNIT DAMPER, MICROPHONE
A–G,K,L,Q, S H,M,N J,P,R
1 1 1 1 1 1 2 1 1
G,H,K–M, P–S
2 2
A–F A,B,G,H C–F, K–N,Q,S J P,R
1 1 1 1 1 1 4
A–F G–J G G–J G–J G–J G–J K–S K K–S
1 1 1 1 1 1 1 1 1 1
23-70-02
Illustrated Parts List Page 1060 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
7
140 145 150 155
93–619–01 9300–377 9300–197 93A263–02
155A
93A266–01
160
8EP46R3
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
MICROPHONE, NON–MAGNETIC GROMMET WASHER–MICROPHONE PWA MICROPHONE PREAMP (SEE FIG 8 FOR DETAIL BREAKDOWN) PWA, MICROPHONE PRE–AMP ASSEMBLY (SEE FIG 9 FOR DETAIL BREAKDOWN) ATTACHING PARTS SCREW, PAN HEAD, 4–40 X 3/8 (V06141) (938EP46R3) ***
UNITS PER ASSY
K–S K–S G–S A,B,G–J
1 1 1 1
C–F, K–S
1
4
23-70-02
Illustrated Parts List Page 1061 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
170
80
90 145
50
60
80
25
115
55
50
R2
GND M
C1 C15
R7 30
C22
Q6
185
R5
R8
K
R11
5B R 18
C8
C11 D 1
C9
20
80
C10
125
q
55
175
40
Q4
35
115
p
R3 2
30 105 100
R 31 r
155 115
C R 16 24
C 18
85 20
Q3
75
R23
t
95
180
R C R 25 17 21
R16 R 30
C21
5
R26
C13
Q2
D 4
C
R22
R29 R 15
R 19
100
20
R17
120 130
D C 2 14
C19
C12
R 13 R R 12 14
145
15
C20
80 70
10
R28
L
150
65
R 27
B
Q5
R9
165
15 110
R10
160
160
140
C5
C6
P
R6
R3 20
P
180
C7
C4
Q1
N
C2
R4
30
85
F
C3
200
20
175
45
80
135
40
75
Dynamic Microphone Preamplifier PWA, P/N 93A263–02 Figure 8
23-70-02
Illustrated Parts List Rev 1 Page 1062 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 8
PART NUMBER 1
93A263–02
5
1N4446
10 15 20 25 30 35 40 45 50
1N295 9300–285 9300–290 9300–301 9300–305 9300–307 9300–534 9300–583 CK05BX103K
55 60 65
CK06BX223K 3370415004 9–1588
70
9391767
75
RC07GF101J
80
RC07GF102J
85
RC07GF103J
90
RC07GF125J
95
RC07GF151J
100
RC07GF152J
105
RC07GF154J
110
RC07GF221J
115
RC07GF222J
120
RC07GF224J
125
RC07GF471J
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
PWA MICROPHONE PREAMP (SEE FIG. 7 FOR NHA) SILICON DIODE (V06141) (9300272) GERMANIUM DIODE (9300292) CAPACITOR, 4.7 UF, 35V CAPACITOR, 1.0 UF, 35V CAPACITOR, 10 UF, 20V CAPACITOR, 47 UF, 20V CAPACITOR, 4.7 UF, 20V CAPACITOR, 0.01 UF, 100V CAPACITOR, 0.22 UF, 20V CAPACITOR, 0.01 UF, 100V (V06141) (9305BX103K) CAPACITOR, (V06141) (9306BX223K) CAPACITOR, STAN, 20V, 15UF, +5% CAPACITOR, 0.022 UF 50V (V06141) (9391588) CAPACITOR, 150UF, 30V, (Mfg. SPRAGUE, No. 109D157X0030F2) RESISTOR, CC, 100 OHM, 1/4W, 5% (V01121) (9307GF101J) RESISTOR, CC, 1.0K OHM, 1/4W, 5% (V01121) (9307GF102J) RESISTOR, CC, 10.0K OHM, 1/4W, 5% (V01121) (9307GF103J) RESISTOR, CC, 1.2M OHM, 1/4W, 5% (V01121) (9307GF125J) RESISTOR, 150 OHM, 1/4W, 5% (V01121) (9307GF151J) RESISTOR, 1.5K OHM, 1/4W, 5% (V01121) (9307GF152J) RESISTOR, 0.15M OHM, 1/4W, 5% (V01121) (9307GF154J) RESISTOR, 220 OHM, 1/4W, 5% (V01121) (9307GF221J) RESISTOR, 2.2K OHM, 1/4W, 5% (V01121) (9307GF222J) RESISTOR, 220.0K OHM, 1/4W, 5% (V01121) (9307GF224J) RESISTOR, 470 OHM, 1/4W, 5% (V01121) (9307GF471J)
UNITS PER ASSY RF 1 2 2 5 1 3 1 2 1 2 2 1 1 1 2 5 2 1 1 2 1 1 3 1 1
23-70-02
Illustrated Parts List Rev 1 Page 1063 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
8
130
RC07GF472J
135
RC07GF474J
140
RC07GF510J
145
RC07GF561J
150
RC07GF562J
155
RC07GF821J
160
RC07GF822J
165
9–1590
170
9–1586–25
175
9–1586–26
180
9–1586–27
185
9–1586–28
–190
10282–N
–195 200
160–0021–020 93–972
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
RESISTOR, 4.7K OHM, 1/4W, 5% (V01121) (9307GF472J) RESISTOR, 470K OHM, 1/4W, 5% (V01121) (9307GF474J) RESISTOR, 51 OHM, 1/4W, 5% (V01121) (9307GF510J) RESISTOR, 560 OHM, 1/4W, 5% (V01121) (9307GF561J) RESISTOR, 5,600 OHM, 1/4W, 5% (V01121) (9307GF562J) RESISTOR, 820 OHM, 1/4W, 5% (V01121) (9307GF821J) RESISTOR, 8,200 OHM 1/4W, 5% (V01121) (9307GF822J) RESISTOR ,10K OHM POTENTIOMETER (V06141) (9391590) TRANSISTOR, 2N2483 B30–500 (V06141) (939158625) TRANSISTOR, MATCHED PAIR, NPN SI, (V06141) (939158626) TRANSISTOR, MATCHED PAIR, NPN SI, (V06141) (939158627) TRANSISTOR, NPN SI, HF, LOW POWER (V06141) (939158628) INSULATION, TRANSISTOR, NYLON (1409800028) MINI–PIN TERMINAL (9391543) BOARD, PRINTED WIRING
UNITS PER ASSY 1 1 1 2 1 1 2 1 1 10 10 1 1 1 1
– ITEM NOT ILLUSTRATED
23-70-02
Illustrated Parts List Page 1064 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
90
70
160
95
60 30
70
55
170
+ C3 -
1
F
+ C1 -
R2
R7 C4
35
+
R4
C7
+ C15
R3
25 + C6
205
R5
+
C5
200 R11
R9
165 185 215
35 180
C22 R 20
120 90 20
160
C12 R R 12 14
Q2
140 C 21 +
145
+
R 30 R R C1 32 31 6 +
+
C10 p
195
q
15 20 110 25
C
R22
35
R26
R17 C1 3
65
C20
5
Q4
R29
R 15
125
R28
L
D C1 R C1 D 2 4 19 9 D 1 + 4
+
C9 + R 13
155
R 27
K
B
5B
C8
135
80
+
R8
+ R C1 18 1 -
Q5
90
25
D 3
R10 Q6
75
10
P
R6
Q1
180
E N
C2 +
190
95
M
R1
100
GND
110 C1 R 7 R 25 + 21
R16
R 24 C1 8 +
115 200 95
Q3
t r
25
R23
85
55 45
40 130
175
105
50 90 45
150
130
90
195
85
Condenser Microphone Preamplifier PWA, P/N 93A266–01 Figure 9
23-70-02
Illustrated Parts List Rev 1 Page 1065 Feb. 01/93 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 9
PART NUMBER 1
93A266–01
5
1N4446
10
1N4735,A
15 20 25 30 35 40 45 50 55 60 65
1N295 9300–285 9300–290 9300–301 9300–305 9300–307 9300–534 9300–583 CK06BX223K 3370415004 9–1588
70
9–1589
75
93–917–67
80 85
9–1889 RC07GF101J
90
RC07GF102J
95
RC07GF103J
100
RC07GF125J
105
RC07GF151J
110
RC07GF152J
115
RC07GF154J
120
RC07GF182J
125
RC07GF221J
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
MICROPHONE PRE–AMP ASSEMBLY MODIFIED (SEE FIG 7 FOR NHA) SILICON DIODE (V06141) (9300272) DIODE, ZENER IN4735 (V04713) (939032405) GERMANIUM DIODE (9300292) CAPACITOR, 4.7 UF, 35V CAPACITOR, 1.0 UF, 35V CAPACITOR, 10 UF, 20V CAPACITOR, 47 UF, 20V CAPACITOR, 4.7 UF, 20V CAPACITOR, 0.01 UF, 100V CAPACITOR, 0.22 UF, 20V CAPACITOR, (V06141) (9306BX223K) CAPACITOR, STAN, 20V, 15UF, +5% CAPACITOR, 0.022 UF 50V (V06141) (9391588) CAPACITOR, 0.0022 UF, 100V (V06141) (9391589) CAPACITOR, 150 UF, 30V (Mfg. SPRAGUE, No. 109D157X0030F2) CAPACITOR, (V06141) (9391889) RESISTOR, CC, 100 OHM, 1/4W, 5% (V01121) (9307GF101J) RESISTOR, CC, 1.0K OHM, 1/4W, 5% (V01121) (9307GF102J) RESISTOR, CC, 10.0K OHM, 1/4W, 5% (V01121) (9307GF103J) RESISTOR, CC, 1.2M OHM, 1/4W, 5% (V01121) (9307GF125J) RESISTOR, 150 OHM, 1/4W, 5% (V01121) (9307GF151J) RESISTOR, 1.5K OHM, 1/4W, 5% (V01121) (9307GF152J) RESISTOR, 0.15M OHM, 1/4W, 5% (V01121) (9307GF154J) RESISTOR, 1.8K OHM, 1/4W, 5% (V01121) (9307GF182J) RESISTOR, 220 OHM, 1/4W, 5% (V01121) (9307GF221J)
UNITS PER ASSY RF 1 1 2 2 4 1 3 1 2 1 2 1 1 2 1 1 2 5 3 1 1 2 1 1 1
23-70-02
Illustrated Parts List Page 1066 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM
PART NUMBER
9
130
RC07GF222J
135
RC07GF224J
140
RC07GF471J
145
RC07GF472J
150
RC07GF474J
155
RC07GF510J
160
RC07GF561J
165
RC07GF562J
170
RC07GF682J
175
RC07GF821J
180
RC07GF822J
185
9–1590
190
9–1586–25
195
9–1586–26
200
9–1586–27
205
9–1586–28
–210 215
10282–N 160–0021–020
AIRLINE PART NO.
NOMENCLATURE
EFF CODE
1234567
RESISTOR, 2.2K OHM, 1/4W, 5% (V01121) (9307GF222J) RESISTOR, 220.0K OHM, 1/4W, 5% (V01121) (9307GF224J) RESISTOR, 470 OHM, 1/4W, 5% (V01121) (9307GF471J) RESISTOR, 4.7K OHM, 1/4W, 5% (V01121) (9307GF472J) RESISTOR, 470K OHM, 1/4W, 5% (V01121) (9307GF474J) RESISTOR, 51 OHM, 1/4W, 5% (V01121) (9307GF510J) RESISTOR, 560 OHM, 1/4W, 5% (V01121) (9307GF561J) RESISTOR, 5,600 OHM, 1/4W, 5% (V01121) (9307GF562J) RESISTOR, 6,800 OHM, 1/4W, 5% (V01121) (9307GF682J) RESISTOR, 820 OHM, 1/4W, 5% (V01121) (9307GF821J) RESISTOR, 8,200 OHM, 1/4W, 5% (V01121) (9307GF822J) RESISTOR, 10K OHM POTENTIOMETER (V06141) (9391590) TRANSISTOR, 2N2483 B30–500 (V06141) (939158625) TRANSISTOR, MATCHED PAIR, NPN SI, (V06141) (939158626) TRANSISTOR, MATCHED PAIR, NPN SI, (V06141) (939158627) TRANSISTOR, NPN SI, HF, LOW POWER (V06141) (939158628) INSULATION, TRANSISTOR, NYLON (1409800028) MINI–PIN TERMINAL (9391543)
UNITS PER ASSY 2 1 1 1 1 1 2 1 1 1 2 1 1 1 1 1 1 1
– ITEM NOT ILLUSTRATED
23-70-02
Illustrated Parts List Page 1067 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
25
20 15 10
5 45 55
35
70 65 30
45
50
35
60 70 40
65
55 60
30
40
Remote Microphone Assembly, P/N 93A055–00, –03, –10, –20, –30, –50, –55 Figure 10
23-70-02 Illustrated Parts List Page 1068 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 10
PART NUMBER 1
93A055–00
1A 1B 1C 1D 1E 1F 5 5A 10 15 15A 20 25 30 30A
93A055–03 93A055–10 93A055–20 93A055–30 93A055–50 93A055–55 9300–205 93–619–01 9300–197 9300–382 93–989 9300–344 9300–347 9300–348 9300–928
35
8EP44R3
35A
8EP43R3
40
9300–352
45
150949–1002
50
9–0649
55 55A 60 60A 60B 60C 60D 60E 65 65A 70
9300–334 93–624 93–626–22 93–626–23 93–626–19 93–626–20 93–626–116 93–626–117 9300–351 9300–927 8AS23R3
AIRLINE PART NO.
NOMENCLATURE 1234567
REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY REMOTE MICROPHONE ASSEMBLY REMOTE MICROPHONE ASSEMBLY REMOTE MICROPHONE ASSEMBLY REMOTE MICROPHONE ASSEMBLY REMOTE MICROPHONE ASSEMBLY MICROPHONE MICROPHONE, NON–MAGNETIC WASHER–MICROPHONE MICROPHONE MOUNT MICROPHONE MOUNT, BROWN MICROPHONE HUM SHIELD DAMPER–MICROPHONE CONNECTOR PLATE CONNECTOR PLATE ATTACHING PARTS SCREW, PAN HEAD, 4–40 X 1/4 (V06141) (938EP44R3) SCREW, PAN HEAD, 4–40 X 3/16 (V06141) (938EP43R3) PEM NUT *** CONNECTOR (9300349) ATTACHING PARTS TERMINAL LUG (V06141) (9390649) *** NAMEPLATE NAMEPLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE DUST COVER DUST COVER ATTACHING PARTS SCREW, FLAT HEAD, 2–56 X 3/16 (V06141) (938AS23R3)
EFF CODE
UNITS PER ASSY
A
RF
B C D E F G A,B C–G
A,C,E,F B,D,G
RF RF RF RF RF RF 1 1 1 1 1 1 1 1 1
A,C–G
2
B
2
A,C,E,F
2
A–D,F,G E A,B
1 1 A,B C–G A B C D,G E F A,C,E,F B,D,G
1 1 1 1 1 1 1 1 1 1 3
23-70-02 Illustrated Illustrated Parts Parts List List
Rev 2 Page Page 1069 1069 Feb. Mar. 01/93 15/00
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
5 30 15
5 20 10
35 25
45 40
Remote Microphone Assembly, P/N 93A055–40, –45, –60, –65, –66, –67, –95 Figure 11
23-70-02 Illustrated Parts List Page 1070 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 11
PART NUMBER 1
93A055–40
1A
93A055–45
1B
93A055–60
1C
93A055–65
1D
93A055–66
1E
93A055–67
1F
93A055–95
5 5A
93A272 89984
5B
93–1025
10 10A 15 20 20A
93–656 93–656 93–653 93–658–01 93–658–02
20B
93–658–03
25 30 30A 30B 30C 30D 35
93–655 93–626–83 93–626–30 93–626–100 93–626–101 93–626–115 93–654
40
8EP46R5
45
9WES4
AIRLINE PART NO.
NOMENCLATURE 1234567
REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) MICROPHONE ASSEMBLY MICROPHONE, MINI DIRECTIONAL (93959) MICROPHONE, MINI, DIRECTIONAL, EXTENDED WASHER WASHER SLEEVE–REMOTE MICROPHONE HOLDER REMOTE MICROPHONE HOLDER, REMOTE MICROPHONE (ATR–42, BROWN) HOLDER, REMOTE MICROPHONE, BLACK NAMEPLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CONFIGURATION P/N PLATE CABLE RETAINER ATTACHING PARTS .4–40 X 3/8 PHIL.PAN HEAD.SC (V06141) (938EP46R5) LOCK WASHER, EXT CRES #4 B (V06141) (939WES4) ***
EFF CODE
UNITS PER ASSY
A
RF
B
RF
C
RF
D
RF
E
RF
F
RF
G
RF
A,B C,D,F,G
1 1
E
1
A,B C–G A,B A,C,E B,D
2 3 1 1 1
F,G
1
A B C D F
1 1 1 1 1 1 1 1 1
23-70-02 Illustrated Parts List Rev 2 Page 1071 Mar. Feb. 15/00 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
15 10
5
20
Remote Microphone Assembly, 9300A165 and 9300A165–01 Figure 12
23-70-02 Illustrated Parts List Page 1072 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
FIG. ITEM 12
PART NUMBER 1
1A 5 5A 10 15 20
9300A165 9300A165–01 9300A206 93–619–01 9300–197 9300–344 9300–543
AIRLINE PART NO.
NOMENCLATURE 1234567
REMOTE MICROPHONE ASSEMBLY (SEE FIG 1 FOR NHA) REMOTE MICROPHONE ASSEMBLY MICROPHONE / CABLE ASSEMBLY MICROPHONE, NON–MAGNETIC WASHER–MICROPHONE MICROPHONE HUM SHIELD DAMPER–MICROPHONE
EFF CODE
UNITS PER ASSY
A
RF
B A B
RF 1 1 1 1 1
A
23-70-02 Illustrated Parts List Page 1073 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
THIS PAGE INTENTIONALLY LEFT BLANK
23-70-02 Illustrated Parts List Page 1074 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
APPENDIX A CIRCUIT AND WIRING DIAGRAMS 1. INTRODUCTION This appendix contains the wiring and schematic diagrams for the L3 Fairchild Model A100S Solid– State Cockpit Voice Recorder. Each schematic diagram is preceded by a revision reference sheet which is used as a historical record of changes to the schematic drawings. Refer to Table A1 for a listing of the schematic diagrams included in this section.
Table A1 Schematic Diagram List Assembly / Part Number
Schematic Part Number
Figure Number
Page Number
Model A100S SSCVR: System Wiring Diagram
N/A
Figure A1
Page A2
Aircraft Interface P/N 205E0597–00
905E0597–01
Figure A2
Page A7
Audio Processor P/N 205E0598–00
905E0598–01
Figure A3
Page A15
Store Processor P/N 205E0601–00
905E0601–01
Figure A4
Page A35
Store Processor P/N 205E1027–00
905E1027–01
Figure A5
Page A51
93A263–02
Figure A7
Page A66
93A266–01
Figure A8
Page A68
Control Units: Model A151 & A152 Dynamic Microphone Preamplifier PWA Model A151B & A152B Condenser Microphone Preamplifier PWA
23-70-02
Circuit and Wiring Diagrams Rev 1 Page A1 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S +5V +12V -12V REARPANEL CONNECTOR
P1 9 2 3
8 55 12 30 32
+27.5 VDC INPUT 115 VAC IN (H) AC COMMON (C)
BIAS JUMPER IN ERASE A" PUSH_TO_TEST CHANNEL 1 (LO) CHANNEL 1 (HI)
J1 9 2 3
17,18 27,29
20
22
AIRCRAFT INTERFACE PWA P/N 205E0597-00
16 25
8
23
55
26
12
24
30
37 38
32
39 35 37
41 43
45 TO FRONT PANEL PHONE JACK
47
CHANNEL 2 (LO) CHANNEL 2 (HI)
CHANNEL 3 (LO) CHANNEL 3 (HI)
CHANNEL 4 (LO) CHANNEL 4 (HI) AUDIO OUT - HI / LO
6 5
14 13
AUDIO OUT - HI AUDIO OUT - LO
PRE-AMP PWR +18VDC PRE-AMP PWR GND /BIAS JUMPER OUT
7 23 15 16 17
57
INDICATOR + INDICATOR + INDICATOR CHASSIS GROUND
ERASE C"
(+12V)
35 37
41 43
45
PWA CONNECTOR J2 HARDWIRED TO PLUG P2 OF AIRCRAFT INTERFACE CABLE ASSEMBLY W1
40 41 42 43 44 45 46
47
47
J7-1/2
48 15
6
B9, B14 A10 A9, B15
J2/P2 /LOW LINE
A8
/FAULT /RECORD ERASE TEST CHANNEL 1 (LO) CHANNEL 1 (HI) GROUND CHANNEL 2 (LO) CHANNEL 2 (HI) GROUND CHANNEL 3 (LO) CHANNEL 3 (HI) GROUND CHANNEL 4 (LO) CHANNEL 4 (HI) GROUND /SYSRST
5 35
14
36
13
1 7 23 15 16 17
57
19 E3 E4
21 28 30
COMBINED_AUDIO GROUND GROUND
A11
SPARE PWA (NOT USED)
A8
B13
B13
B12
B12
A13
A13
A12
A12
B19
B19
A19
A19
B20
B20
A20
A20
B21
B21
A21
A21
B22
B22
A22
A22
B23
B23
A23
A23
AIRCRAFT INTERFACE A24 CABLE ASSEMBLY B8 W1 CARD CONNECTOR J3 B24
B24 A24 B8
B18
B18
A18
A18
/LOW LINE /FAULT /RECORD ERASE TEST CHANNEL 1 (LO) CHANNEL 1 (HI) GROUND CHANNEL 2 (LO) CHANNEL 2 (HI) GROUND CHANNEL 3 (LO) CHANNEL 3 (HI) GROUND CHANNEL 4 (LO) CHANNEL 4 (HI) GROUND /SYSRST
COMBINED_AUDIO GROUND
B1
GROUND GROUND GROUND GROUND
B10
B10
B11
B11
A14
A14
A15
A15
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
GROUND GROUND GROUND GROUND
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
Model A100S Solid–State Cockpit Voice Recorder, P/N S100–0080–00, System Wiring Diagram Figure A1 (sheet 1 of 3)
23-70-02
Circuit and Wiring Diagrams Rev 1 Page A2 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S +5V +12V
J2/P2
-12V
B9, B14 A9, B15
/LOW_LINE
/RECORD ERASE TEST
CHANNEL 1 (HI) GROUND
CHANNEL 2 (HI) GROUND
CHANNEL 3 (HI) GROUND CHANNEL 4 (LO) CHANNEL 4 (HI) GROUND
GROUND GROUND GROUND
A13 A12 B1
A19
A20 B21
B22
A1 B2 A2 B3 A3 B4 A4 B5 A5 B6 A6
A22
B7
A21
A7
A23
B8
B24
B8
COMBINED_AUDIO
GROUND
A13
A24
/SYSRST
GROUND
B12
A21
CHANNEL 3 (LO)
GROUND
B12
B20
CHANNEL 2 (LO)
A8 B13
B19
P5 17 18
B13
A12
CHANNEL 1 (LO)
A11
AUDIO PROCESSOR PWA P/N 205E0598-00
A8
/FAULT
A10
/LOW_LINE /FAULT /RECORD ERASE TEST /REC_RD GROUND DAD 0 DAD 1 DAD 2 DAD 3 DAD 4 DAD 5 DAD 6 DAD 7 SYNC /RECFIFO_HF /REC_EMPTY /PLAY_WR /SYSRST
20
PLUG P5 PART OF CABLE ASSEMBLY W2
22
16 25 23
1 2
26
3 4
24
5
1
6
2
7
3
8
4 5 6
9 10 11
7
12
8
13 14
9 10 11
15 16 17 18 19 20
12 13 14
AIRCRAFT INTERFACE CABLE ASSEMBLY W1 CARD CONNECTOR J5 (26 PIN)
15
21 22 23 24 25 26
/REC_RD GROUND
AIRCRAFT INTERFACE CABLE B10 ASSEMBLY B11 W1 CARD A14 CONNECTOR A15 J4 (64 PIN) A24
DAD 1 DAD 2 DAD 3 DAD 4 DAD 5 DAD 6 DAD 7 SYNC /RECFIFO_HF /REC_EMPTY /PLAY_WR /SYSRST /LOW_LINE +5V +5V GROUND +12V GROUND -12V /RECORD TEST /FAULT ERASE
RIBBON CABLE ASSEMBLY W2 IS HARD WIRED TO STORE PROCESSOR PWA)
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
(SEE NOTE AT BOTTOM OF PAGE)
DAD 0
B18 A18
STORE PROCESSOR PWA P/N 205E0601-00 MOUNTED ONTO FCSSU
NOTE REFER TO SHEET 3 FOR STORE PROCESSOR PWA, P/N 205E1027-00 WIRING TO FCSSU, 253E0660-00
18 48
18 48
17
17
47 16
47 16
19
19
20 45 46 49 50 23 10
20 45 46 49 50 23 10
7
7
22 13
22 13
21 11 9 32 33 37 39 41 42
21 11 9 32 33 37 39 41 42
43 44
43 44
14
14
31 2 34 30 1
31 2 34 30 1
5 8
5 8
6 35
6 35
28 36
28 36
38
38
40 15
40 15
29 27 12 26
29 27 12 26
25 24 3
25 24 3
4
4
+5V +5V +12V +12V GND GND GND GND GND GND GND D<0> D<1> D<2> D<3> D<4> D<5> D<6> D<7> SEL<0> SEL<1> SEL<2> SEL<3> SEL<4> SEL<5>
FCSSU P/N 253E0348-03 (SEE NOTE AT BOTTOM OF PAGE)
SEL<6> SEL<7> FADR<20> FADR<19> FADR<18> FADR<17> FADR<16> FADR<15> FADR<14> FADR<13> FADR<12> FADR<11> FADR<10> FADR<9> FADR<8> FADR<7> FADR<6> FADR<5> FADR<4> FADR<3> FADR<2> FADR<1> FADR<0> /OE /WE
NOTE INITIAL MODEL A100S UNITS WERE EQUIPPED WITH FCSSU, P/N 253E0348-03, WHICH USES 2-MBIT FLASH MEMORY CHIPS, AND STORE PROCESSOR PWA, P/N 205E0601-00, DEĆ SIGNED TO INTERFACE WITH IT. BEGINNING 12/93, THE NEW FCSSU, P/N 253E0660-00, WHICH USES 8-MBIT FLASH MEMORY CHIPS, AND A REDESIGNED STORE PROCESSOR PWA, P/N 205E1027-00, WERE MANUFACĆ TURED. THESE ASSEMBLIES WERE FIRST INSTALLED IN MODĆ EL A100S UNIT SERIAL NUMBER 311.
Model A100S Solid–State Cockpit Voice Recorder, P/N S100–0080–00, System Wiring Diagram Figure A1 (sheet 2 of 3)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S +5V +12V
J2/P2
-12V
STORE PROCESSOR PWA P/N 205E1027-00
P5 17 18
/LOW_LINE /FAULT /RECORD ERASE TEST /REC_RD GROUND DAD 0 DAD 1 DAD 2 DAD 3 DAD 4 DAD 5 DAD 6 DAD 7 SYNC /RECFIFO_HF /REC_EMPTY /PLAY_WR /SYSRST
20
PLUG P5 PART OF CABLE ASSEMBLY W2
22
16 25 23
1 2
26
3 4
24
5
1
6
2
7
3
8
4
9 10
5 6
11
7
12
8
13 14 15
9 10
16 17 18 19 20
11 12 13 14
AIRCRAFT INTERFACE CABLE ASSEMBLY W1 CARD CONNECTOR J5 (26 PIN)
15
21 22 23 24 25 26
MOUNTED ONTO FCSSU (SEE NOTE AT BOTTOM OF PAGE)
/REC_RD GROUND DAD 0 DAD 1 DAD 2 DAD 3 DAD 4 DAD 5 DAD 6 DAD 7 SYNC /RECFIFO_HF /REC_EMPTY /PLAY_WR /SYSRST /LOW_LINE +5V +5V GROUND +12V GROUND -12V /RECORD TEST /FAULT ERASE
RIBBON CABLE ASSEMBLY W2 IS HARD WIRED TO STORE PROCESSOR PWA)
AIRCRAFT INTERFACE CABLE ASSEMBLY W1
18 48
18 48
17 47 16
17 47 16
19
19
20
20
45 46 49 50 23 10
45 46 49 50 23 10
7 22 13
7 22 13
21 11 9 32 33 37 39 41 42
21 11 9 32 33 37 39 41 42
43 44 14
43 44 14
31 2 34 30 1
31 2 34 30 1
5 8 6 35
5 8
28 36 38
28 36
40 15
40 15
29
29 27 12 26
27 12 26 25 24 3 4
6 35
38
25 24 3 4
+5V +5V +12V +12V GND GND GND GND GND GND GND D<0>
FCSSU P/N 253E0660-00
D<1> D<2> D<3> D<4> D<5> D<6> D<7> FADR<21> FADR<22> FADR<23> FADR<24> FADR<25> FADR<26> /CE_FLASH /PWRDWN
(SEE NOTE AT BOTTOM OF PAGE)
NOTE SIGNAL CHANGES
FADR<20> FADR<19> FADR<18> FADR<17> FADR<16> FADR<15> FADR<14> FADR<13> FADR<12> FADR<11> FADR<10> FADR<9> FADR<8> FADR<7> FADR<6> FADR<5> FADR<4> FADR<3> FADR<2> FADR<1> FADR<0> /OE /WE
SIGNAL MNEMONIC CHANGES BETWEEN STORE PROCESSOR PWA, P/N 205E1027-00, AND FCSSU, P/N 253E0660-00
NOTE THE ABOVE REFLECTS THE NEW FCSSU, P/N 253E0660- 00, WHICH USES 8-MBIT FLASH MEMORY CHIPS, AND STORE PROCESSOR PWA, P/N 205E1027-00 MANUFACTURED BEGINĆ NING 12/93. THESE ASSEMBLIES WERE FIRST INSTALLED IN UNIT SERIAL NUMBER 311.
Model A100S Solid–State Cockpit Voice Recorder, P/N S100–0080–00, System Wiring Diagram Figure A1 (sheet 3 of 3)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code Rev. 02 Rev. 02 Rev. 02
Serial Number Effectivity
Revision Description Replaced U3 and added U5 per ECO 7977. Replaced U2 per SB SSCVR012 Removed C16 and C17, added L1-L3 and C35-C38 per SB SSCVR011.
00761 and above.
Revision Reference Sheet for Figure A2 Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram, P/N 905E0597–01 (Sheets 1 through 4)
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REVISIONS SYM.
A B C
DESCRIPTION
ECO 0006293 CHNG SHT 2 ECO 0007977 CHNG SHT 1 ECO 0008291 CHNG SHTS 1,2
EFFECTIVITY
DATE
APPROVED
9–04–91 9–14–91 3–29–95 4–02–95 3–06–96 7–02–96
REV. 02
Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram, P/N 905E0597–01 Figure A2 (sheet 1 of 4)
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REV. 02
Aircraft Interface PWA, P/N 205E0597–00, Schematic Diagram, P/N 905E0597–01 Figure A2 (sheet 2 of 4)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code Rev. 02
Revision Description
Serial Number Effectivity
Replaced C15, C24, C25, C28, C30, C32, and C47 per ECO 9282.
Revision Reference Sheet for Figure A3 Audio Processor, P/N 205E0598–00, Schematic Diagram, P/N 905E0598–01, (Sheets 1 through 11)
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A
ECO 0006215: UPDATE SHTS 1,3,4
7/26/91
7/26/91
B
ECO 0006919: UPDATE SHTS 1,4
7/12/91
9/26/91
C
ECO 0006445: REV SHTS 1,5,6; ADD NOTE 5
D
ECO 0009282: REV SHTS 5,6,8,9
11/6/91 8/24/00
11/8/91 8/28/00
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 1 of 11)
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NC
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 3 of 11 continued)
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0.1 REV. 02
0.1 REV. 02
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 5 of 11)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
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REV. 02
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 6 of 11)
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0.1 REV. 02
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
COMBINED_AUDIO AUDIO_1 AUDIO_2
PLAYBACK MONITOR CONNECTOR
AUDIO_3 AUDIO_4
Audio Processor PWA, 205E0598–00, Schematic Diagram, P/N 905E0598–01 Figure A3 (sheet 11 of 11 continued)
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Revision Code
Revision Description
Serial Number Effectivity
Revision Reference Sheet for Figure A4 Store Processor, P/N 205E0601–XX, Schematic Diagram P/N 905E0601–01 (Sheets 1 through 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
D E F
75 9 71 1 9
762 8
&2 3 & 8 3 &8 & 8
3 6 1 3
12 02 29 11
2 2 3 4
3 6 2 3
25 26 25 28
2 2 3 4
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 1 of 8)
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
VCC
REVISION C INCORPORATED PER ECO 0006654 WITH AN EFFECTIVITY DATE OF 3-12-92 REPLACED THE ABOVE BLOCKED CIRCUITRY WITH THE DC/DC CONVERTER POWER SUPPLY (5 VDC IN / - 12 VDC OUT AT 83 MA, 1W) SHOWN HERE.
VIN N/C
NMF0512S
CTRL
GND
+OUT -OUT
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 2 of 8)
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LSB
LSB
MSB MSB
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 3 of 8)
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MSB
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 3 of 8 continued)
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MSB LSB
FCT841 MSB
LSB LSB
D9 D8 D7 D6 D5 D4 D3 D2 D1 D0 LE
Y9 Y8 Y7 Y6 Y5 Y4 Y3 Y2 Y1 Y0
MSB
LSB
OE
REV. F
Store Processor PWA, P/N 205E0601–00, Schematic Diagram P/N 905E0601–01 Figure A4 (sheet 6 of 8 continued)
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Revision Code
Revision Description
Serial Number Effectivity
Revision Reference Sheet for Figure A5 Store Processor, P/N 205E1027–XX, Schematic Diagram, P/N 905E1027–01 (Sheets 1 through 8)
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7628
CHG U12 ON SHT 6
3 /11 / 94
3 / 25 / 94
0
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 1 of 8)
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VCC
VIN N/C
NMF0512S
CTRL
GND
+OUT -OUT
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 2 of 8)
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LSB
LSB
MSB MSB
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 3 of 8)
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J2 43
MSB
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 3 of 8 continued)
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MSB LSB
FCT841 MSB
LSB
D9 D8 D7 D6 D5 D4 D3 D2 D1 D0 LE
Y9 Y8 Y7 Y6 Y5 Y4 Y3 Y2 Y1 Y0
MSB
LSB
OE
REV. A
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AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
/PWRDWN FADR<24> FADR<23>
FADR<22> FADR<21> FADR<20> FADR<19> FADR<18> FADR<17> FADR<16> FADR<15> FADR<26> FADR<25>
Store Processor PWA, P/N 205E1027–00, Schematic Diagram, P/N 905E1027–01 Figure A5 (sheet 8 of 8)
23-70-02
Circuit and Wiring Diagrams Rev 1 Page A64 July 30/94
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code
Revision Description
Serial Number Effectivity
Revision Reference Sheet for Figure A6 Dynamic Microphone Preamplifier, P/N 93A263–01, Schematic Diagram (Sheet 1 of 1)
23-70-02
Circuit and Wiring Diagrams Page A65 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
R6 1.0K
R3 150 C1 N 1.0 35V C2 .01 200V
C3
C8 47 20V
R5 10K
+
+
+
560 10 C4 20V .01 R1 200V 2.2K
3
Q1 2N2483
1
R12 R8 10.0K
C9
+
2
R11 C10 .01 200V
R9 5.6K
+ C5 60 6V
R4 1.0K
R13
R7 8.2K
C7
1.0 35V
R2
D1 1N4446
R27
C (B+ 18V)
100 C13 47 20V
R23 10K
C11
R16
4.7 20V Q2
1K
2.2K
R15 2.2K
R17 820
6 p DS
12 DS
R14 470
C12 +
R18
r
q
R19 150 t
24 DS C14. .01 200V
R24 150K
R21 470 R20 1.0K
Q4
C15 1.0 35V
C16 4.7 35V +
Q3 R22 100
R26
L (OUT)
220 R25
C17 .022 200V
P C18 C22 .033 200V
M
R30 8.2K Q6
D3
R29
+
Q5
1.0K
C21 47 20V
5B
CHASSIS
NOTES: 1. UNLESS OTHERWISE SPECIFIED: RESISTOR VALUES ARE IN OHMS, 1/4 WATT, 5% CAPACITOR VALUES ARE IN MICROFARADS. 2. Q2 AND Q3 - P/N 939158626 3. Q4 AND Q5 - P/N 939158627 4. Q6 - P/N 939158628
C20 4.7 35V
R28
1.0 35V
1.5K
+
1N295 +
C19
K (OUT) B (B- 18V)
D2 1N295 CHASSIS
P/N 93A263-01
Dynamic Microphone Preamplifier, P/N 93A263–01, Schematic Diagram Figure A6
23-70-02
Circuit and Wiring Diagrams Page A66 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code
Revision Description
Serial Number Effectivity
Revision Reference Sheet for Figure A7 Dynamic Microphone Preamplifier, P/N 93A263–02, Schematic Diagram (Sheet 1 of 1)
23-70-02
Circuit and Wiring Diagrams Page A67 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
R5 1.0K
R16 100
51
C22 + 47 20V
R6 10.0K R3 1.2M
N
C2 +
C15 + 1.0 35V
10 20V
C1 0.01 100V
R2 2.2K
R14 4.7K
R8 8.2K
C5 + 47 20V C6 +
3 R9 10.0K
2
1
C9 +
R13
1.0 35V
560 + C10 0.01 100V
R11 5.6K
R7 1.0K
4.7 20V Q2 9-1586 -26
R17
R29
1.0K
2.2K
+ C16 0.22 20V
R30 2.2K
R32 820
R31 150
p
r
t
6DB
R15 470
R21 10.0K
C12 47 20V
C13 +
220K
Q1 9-1586 -25
560 C4 0.01 100V
+
R12
1.0 35V
R4
D4 1N4446
R27
12DB
R23 470K R24 1.0K
q
R22 150K
+ C17 1.0 35V
Q4 9-1586 -27
Q3 9-1586 -26 C18 0.01 100V
24DB
R25 100
R26 1.5K
C19 +
R28
4.7 35V
220
L
(OUT)
K
P +
M
C
(B+ 18V)
C3 CK06BX223K
Q6 9-1586 -28
(OUT)
C7 15 20V
B
(B- 18V)
R10 8.2K
CHASSIS
+
R18
Q5 9-1586 -27 C8 150 30V
C20 0.022 50V
D1 1N295
+
1.0K +
5B
C11 4.7 35V
D2 1N295
C14 1.0 35V
R19 C21
1.5K
CK06BX223K
CHASSIS
NOTES: UNLESS OTHERWISE SPECIFIED: RESISTOR VALUES ARE IN OHMS, 1/4 WATT, 5% CAPACITOR VALUES ARE IN MICROFARADS.
Dynamic Microphone Preamplifier, P/N 93A263–02, Schematic Diagram Figure A7
23-70-02
Circuit and Wiring Diagrams Rev 1 Page A68 July 01/93 30/94 Feb.
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
Revision Code
Revision Description
Serial Number Effectivity
Revision Reference Sheet for Figure A8 Condenser Microphone Preamplifier, P/N 93A266–01, Schematic Diagram (Sheet 1 of 1)
23-70-02
Circuit and Wiring Diagrams Page A69 Feb. 01/93
AVIATION RECORDERS COMPONENT MAINTENANCE MANUAL FAIRCHILD MODEL A100S
R20
P
1.8K
6.2V OUT
+
C15
D3 1N4735A
E
+ R6 10.0K + C6 1.0 Q1 35V 9-158625 + C5
R3 1.2M
N
R1 6.8K C1 0.0022 100V
C2 10.0 + 20V R2 10.0K
R4 560 C4 0.0022 100V R7 1.0K
+ C7
R27 51
R16 100
R5 1.0K
R8 8.2K
2 1
47 20V
C9 + 1.0 35V R11 5.6K
220.0K R13 560 C10 0.01 100V
+
R29 2.2K
R32 820
p
R15 470
15 20V
R21 10.0K R17 1.0K
Q2 9-1586 R30 -26 2.2K
C
(B+ 18V)
C12 47 20V
C13 4.7 20V +
R12 3
R9 10K
+
R14 4.7K
C22 47 20V
D4 1N4446
q
C16 +
R23 470K
0.22 20V
R24 1.0K
R31 150
r
t
C18 0.01 100V
+ R25 100
R22 150K C17 +
Q4 1.0 9-1586-27 35V Q3 R28 9-1586-26 C19 220 + R26 1.5K
L (OUT)
4.7 35V C20 0.022 50V
K
M
(OUT) C3
F
C21
R10 8.2K
R18 1.0K
Q5 9-1586-27
Q6
1N295
9-1586-28 CHASSIS
C8 150 30V
D1
+
5B
C11 4.7 35V
+
D2 1N295
+ C14 1.0 35V
+
R19 1.5K
CHASSIS
NOTES: UNLESS OTHERWISE SPECIFIED: RESISTOR VALUES ARE IN OHMS, 1/4 WATT, 5% CAPACITOR VALUES ARE IN MICROFARADS.
Condenser Microphone Preamplifier PWA, P/N 93A266–01 Schematic Diagram Figure A8
23-70-02
Circuit and Wiring Diagrams Rev 1 Page A70 July 01/93 30/94 Feb.
B (B- 18V)
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