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C F M 56-5B __________ HIGHLIGHTS REVISION NO. 48 Feb 01/10 Pages which have been revised are outlined below, together with the Highlights of the Revision -------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------CHAPTER 72 __________
L.E.P. 1- 9 REVISED TO REFLECT THIS REVISION INDICATING NEW,REVISED, AND/OR DELETED PAGES T. OF C. REVISED TO REFLECT THIS REVISION 5 72-00-00 LAYOUT IMPROVED OR EFFECTIVITY UPDATED 224 72-00-00 311, 322
TOOL DESIGNATION(S) DATA UPDATED
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-00-00 610, 665676, 685A612
CORRECTION/ADDITION/AMPLIFICATION UPDATE CRITERIA
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-00-00 701
WARNING/NOTE/REASON FOR THE JOB AMENDED
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-21-00 402- 403, 406
CORRECTION/ADDITION/AMPLIFICATION ADDED POST CFM SB 72-0193 CONFIGURATION AND ALTERNATIV
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-21-00 601
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
72-23-00 444
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
72-23-00 610, 613, 616
CORRECTION/ADDITION/AMPLIFICATION ADDED MAX SERVICEABLE LIMITS FOR WEAR ON B1 FLANGE RADIUS
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-31-00 601- 602, 620- 631
CORRECTION/ADDITION/AMPLIFICATION SERVICEABLE LIMIT A. SHOULD READ, A. CRACKS ONE LOCK WITH A CRACK IS PERMITTED
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 72-HIGHLIGHTS Page REVISION NO. 48
CES
1 of 2 Feb 01/10
C F M 56-5B -------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------WITH REMARKS SEE LIMIT EXTENSIONS 72-00-00-200-005 AND B. LOOSENESS NOT SERVICEABLE WITH REMARKS SEE LIMIT EXTENSIONS 72-00-00-200-005 72-31-00 801, 808
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
72-56-00 427, 433438
EFFECTIVITY UPDATED CORRECTION/ADDITION/AMPLIFICATION ADDED DAMPING OIL TUBE INSTALLATION BEST PRACTICES
72-62-00 418
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
72-63-00 201
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
72-63-00 802- 810, 814, 823
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-HIGHLIGHTS Page REVISION NO. 48 CES
2 of 2 Feb 01/10
C F M 56-5B CHAPTER 72 __________ ENGINE LIST OF EFFECTIVE PAGES _______________________ N, R or D indicates pages which are New, Revised or Deleted respectively Remove and insert the affected pages and complete the Record of Revisions and the Record of Temporary Revisions as necessary CH/SE/SU
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RECORD OF TEMP. REVISION L.E.P. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. T. of C. 72-00-00 72-00-00 72-00-00
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CH/SE/SU 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00
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DATE Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09
CH/SE/SU 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00
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CH/SE/SU 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-21-00 72-21-00
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DATE Feb01/10 Nov01/08 Nov01/08 Nov01/08 Aug01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Nov01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Nov01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09
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72-L.E.P. Page 2 Feb 01/10 CES
C F M 56-5B CH/SE/SU C PAGE 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00
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DATE Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Feb01/10 Nov01/09 Feb01/09 Feb01/10 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 May01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/98 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 May01/09 May01/09 Nov01/08 Nov01/08 Nov01/08
CH/SE/SU 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00
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DATE Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 May01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/02 Nov01/08 Nov01/08 Nov01/08 Nov01/08 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09
CH/SE/SU 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-22-00 72-22-00
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DATE May01/09 Aug01/09 May01/09 May01/09 May01/09 Nov01/08 Nov01/08 Aug01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 May01/09 May01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08
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CH/SE/SU 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00
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438 439 440 441 442 443 444 445 446 447 448 449 450 451 452 453 454 455 456 457 458 459 460 461 462 463 464 465 466 467 468 469 470 471 472 473 474 475 476 477 478 479 601 602 603 604 605 606 607 608 609
DATE Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09 Nov01/09 Feb01/09 Feb01/09 Feb01/09 Nov01/09 Feb01/09 Feb01/09 Feb01/09 Nov01/09 Feb01/09 Feb01/09 Feb01/09 Feb01/09 Nov01/09 Aug01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08
CH/SE/SU 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00
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DATE Feb01/10 Nov01/08 May01/09 Feb01/10 May01/09 Aug01/09 Feb01/10 May01/09 May01/09 May01/09 Nov01/09 Nov01/09 Nov01/09 May01/09 May01/09 May01/09 May01/09 Nov01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 Nov01/09 May01/09 May01/09 May01/09 May01/09 May01/09 Feb01/09 Feb01/09 Feb01/09 May01/09 May01/09 Aug01/09 May01/09 May01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Feb01/09 Feb01/09
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661 662 801 802 803 804 805 806 807 808 809 810 811 812 813 814 815 816 817 818 819 820 821 822 823 824 825 826 827 828 829 830 831 832 833 834 835 836 837 838 839 840 841 842 843 844 845 846 847 848
DATE Feb01/09 Feb01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09 Nov01/08 Nov01/08 Feb01/09 Feb01/09 Feb01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09 Feb01/09 Nov01/08 Feb01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09
CH/SE/SU
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72-30-00 72-30-00 72-30-00 72-30-00
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DATE Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Aug01/09 Nov01/08 Nov01/09 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09
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C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT ENGINE - GENERAL ________________ DESCRIPTION AND OPERATION
________ CH/SE/SU 72-00-00
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PAGE ___________ ____ EFFECTIVITY 1
General
1
Engine Modules
1
Fan/Booster Rotor
1
Fan/Booster Stator
1
Fan Frame
6
Compressor Rotor
6
Compressor Stator
6
Combustor
6
High Pressure Turbine
6
Low Pressure Turbine
6
Turbine Frame
7
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 Page 1 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Accessories and Accessory Drives
Bearings and Seals
Bearings
Oil Distribution
Seals Arrangement
Bearing Functions
Engine Boroscope Inspection Port Provisions, Location and Identification On the Inner Wall (Fairing) of the Fan Bypass Duct On the High Pressure Compressor (HPC) Front and Rear Casings On the Combustion Case
On the Low Pressure Turbine Case
C _
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 11 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 11 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 11 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 11 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 15 001-049, 051-099 101-149, 151-199 201-249, 251-299 72-CONTENTS
R CES
Page 2 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
_________________ ENGINE - GENERAL MAINTENANCE PRACTICES
CH/SE/SU ________
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499
72-00-00 201
Engine Tubes, Hoses, and Fittings
201
Air Flow Check of the Forward Sump Oil Supply Circuit
214
Air Flow Check of the AGB/TGB Oil Supply Circuit
219
Air Flow Check of the Aft Sump Oil Supply Circuit
224
_________________ ENGINE - GENERAL SERVICING
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299
72-00-00 301
Recommendations for Engine Preservation
301
Preservation for a Period of up to 30 Days
304
Preservation for a Period of up to 90 Days
308
Preservation for a Period of 30 to 365 Days.
311
72-CONTENTS R CES
Page 3 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Preservation Renewal Requirements.
Procedure for Exceeded Long Term Preservation Period. Depreservation
_________________ ENGINE - GENERAL INSPECTION/CHECK
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 326 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 328 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 329 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-00-00 601
Inspection/Check of Foreign Object Damage (FOD) (Bird Strike Included)
601
Procedure After Engine Fire or Use of Fire-Extinguishing Agents
613
Procedure after Halogen Products Contamination
618
Procedure after Volcanic Ash, Dust, or Sand Ingestion
622
Inspection/Check After the Engine has Exceeded the Operational Limits
628
Off-Schedule Vane Replacement
647
Over-Serviceable-Limit Extensions
650
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 Page 4 Nov 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Over-Serviceable-Limit Extensions
Inspection/Check of the PS3 Line
Visual Inspection of the Fan Section after Engine Operation in Severe Icing Condition Monitor the Engine EGT for Possible Engine Performance Deterioration
_________________ ENGINE - GENERAL CLEANING/PAINTING
C _
PAGE EFFECTIVITY ____ ___________ 201-249, 251-299 301-399, 401-499 677 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 699 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 A608 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 A610 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-00-00 701
Engine Dry-out and Re lubrication
701
Engine Washing Requirements
714
Hand Cleaning of the Fan Gas Path and Fan Blades
718
Washing of the Engine Gas Path with Pure Water
722
Washing of the Engine Gas Path with Cleaning Agent
733
External Cleaning
744
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 Page 5 Feb 01/10
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
FAN AND BOOSTER ASSEMBLY DESCRIPTION AND OPERATION
72-21-00
General
Fan and booster assembly
Description
C _
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 1
1
1
1
Spinner Front Cone
1
Spinner Rear Cone
1
Fan Disk
1
Fan Blades
5
Booster Rotor
5
Booster Vane Assemblies
5
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 Page 6 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______ FAN AND BOOSTER ASSEMBLY REMOVAL/INSTALLATION
CH/SE/SU ________
C _
PAGE ___________ ____ EFFECTIVITY
72-21-00 401
Removal of the Spinner Front Cone
401
Installation of the Spinner Front Cone
404
Removal of the Spinner Rear Cone
407
Installation of the Spinner Rear Cone
409
Removal of the Fan Rotor Blades
414
Installation of the Fan Rotor Blades
420
Replacement of Fan Rotor Blades in Pairs
426
Replacement of Individual Fan Blades
442
Discard Fan Disc and Booster Spool
447
Discard Fan Shaft
448
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 Page 7 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Removal of the Stage 1 Booster Vane Assembly
CH/SE/SU ________
Installation of the Stage 1 Booster Vane Assembly
FAN AND BOOSTER ASSEMBLY INSPECTION/CHECK
C _
____ EFFECTIVITY PAGE ___________ 449 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 453 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-21-00 601
Inspection/Check of the Spinner Cone
601
Borescope Inspection of the Booster Rotor Blades, Stages 2, 3, 4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5 Inspect Fan Rotor Blades Installed on the Fan Disk
606
Inspect Fan Rotor Blades Removed from the Fan Disk.
633
Inspection/Check of the Stage 1 Booster Vane, Fan Disk, Fan Blades Spacers and Booster Spool.
644
Detailed Inspection and Relubrication of Fan Blade Dovetails, Midspan Shrouds, Retainers, Spacers, Dampers and Fan Disk Dovetail Slots
655
FAN AND BOOSTER ASSEMBLY REPAIRS
617
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-21-00 801
001-049, 051-099 101-149, 151-199 201-249, 251-299
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
Page 8 May 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Replacement of the Crimped Self-Locking Nuts on the Spinner Rear Cone Correction of the Static Imbalance
Blending of Fan Rotor Blades
Blending of the Stage 1 Booster Vane Assembly Angular Distribution for a Replacement of 3 to 18 Pairs of fan Rotor Blades Manual Method NO.1 AND NO.2 BEARING SUPPORT ASSEMBLY DESCRIPTION AND OPERATION
General
No. 1 and no. 2 bearing support module Description
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 801 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 804 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 810 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 825 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 829 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-22-00 1
1
1
1
No. 1 Bearing Support
1
No. 1 Ball Bearing
7
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 Page 9 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________ No. 2 Bearing Support
No. 2 Roller Bearing
Oil Manifold Assembly
External Piping
Fan Shaft
Forward Stationary Air/Oil Seal
FAN FRAME ASSEMBLY DESCRIPTION AND OPERATION
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 8 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 8 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 8 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-23-00 1
General
1
Fonctions
1
Fan Frame.
1
Fan Inlet Case.
1
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 Page 10 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Description
Fan Frame Assembly
Fan Inlet Case Assembly
FAN FRAME ASSEMBLY REMOVAL/INSTALLATION
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 6 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 6 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-23-00 401
Removal of the Fan Outlet Guide Vane (OGV) Doublets
401
Installation of the Fan Outlet Guide Vane (OGV) Doublets
405
Removal of the Forward Acoustical Panels of the Fan
409
Installation of the Forward Acoustical Panels of the Fan
412
Removal of the Mid Acoustical Panels
415
Installation of the Mid Acoustical Panels
418
Removal of the Aft Acoustical Panels
422
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 Page 11 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______ Installation of the Aft Acoustical Panels Removal of the Fan Duct Panels
Installation of the Fan Duct Panels Removal of the Splitter Fairing
Installation of the Splitter Fairing Removal of the PS13 Line
Installation of the PS13 Line
Removal of the PS12 Line
Installation of the PS12 Line
Installation of Acoustical Panels Attachment Screw/Nut Locking Installation of Acoustical Panels Attachment Screw Locking
CH/SE/SU ________
C _
PAGE EFFECTIVITY ____ ___________ 201-249, 251-299 301-399, 401-499 426 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 432 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 436 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 440 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 444 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 448 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 453 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 457 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 467 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 471 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 475 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 72-CONTENTS
R CES
Page 12 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______ FAN FRAME ASSEMBLY INSPECTION/CHECK
CH/SE/SU ________
C _
PAGE ___________ ____ EFFECTIVITY
72-23-00 601
Visual Inspection of the Fan Frame Assembly
601
Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material
616
Inspection/Check of the PS13 Line
627
Inspection/Check of the PS12 line
634
Inspection of Forward Acoustical Panels
643
Inspection of Mid Acoustical Panels
650
Inspection of Aft Acoustical Panels
655
Visual Inspection of the Junction Box
660
FAN FRAME ASSEMBLY REPAIRS
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499
72-23-00 801
72-CONTENTS R CES
Page 13 Aug 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Local Reconditioning of the Abradable Material- Defects less than 0.12 in. (3 mm) deep and 0.50 in.2 (3.2 cm2) Removal of Rust from the Fan Frame Casing
CH/SE/SU ________
Repair of Fan Duct Panel
Repair of the Abradable (material) Shroud with Circular Patches Repair of Forward, Mid and Aft Acoustical Panels when Unbounded Cup Replacement of the Riveted Self Locking Nuts for the Attachment of the Forward Acoustical Panels Replacement of Lateral Bracket Plate on the Junction Box
_____________________ HP COMPRESSOR SECTION DESCRIPTION AND OPERATION
Discard Life Limited HP Compressor
____ EFFECTIVITY PAGE ___________ 801 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 806 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 811 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 815 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 825 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 831 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 840 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-30-00 1
General
______________________ HP COMPRESSOR SECTION REMOVAL/INSTALLATION
C _
1
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049,
051-099 151-199 251-299 401-499 051-099
72-30-00 401
401
72-CONTENTS R CES
Page 14 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT rotating parts
CH/SE/SU ________
HPC ROTOR ASSEMBLY DESCRIPTION AND OPERATION
72-31-00
C _
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 1
General
1
Description
1
Front Shaft
1
Disk and Spools
1
Blades
1
Rear Seal
1
HPC ROTOR ASSEMBLY INSPECTION/CHECK
Inspection of the High Pressure Compressor Rotor Assembly
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-31-00 601
601
72-CONTENTS R CES
Page 15 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT HPC ROTOR ASSEMBLY REPAIRS
________ CH/SE/SU 72-31-00
C _
PAGE ___________ ____ EFFECTIVITY 801
Repair of Broken Borescope Plug
801
Blend Repair of the High Pressure Compressor (HPC) Rotor Blades Stages 1-9
808
HPC FRONT STATOR ASSEMBLY DESCRIPTION AND OPERATION
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499
72-32-00 1
General
1
Description
1
Front Stator Casing
1
Vanes
1
Variable Vane Actuation
1
HPC FRONT STATOR ASSEMBLY INSPECTION/CHECK
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-32-00 601
72-CONTENTS R CES
Page 16 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Inspection/Check of the HPC Front Stator Assembly
HPC FRONT STATOR ASSEMBLY REPAIRS
CH/SE/SU ________
C _
____ EFFECTIVITY PAGE ___________ 601 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-32-00 801
Removal of the Inlet Guide Vane (IGV) and Stage 3 Vane Lever Arms or Bushings
801
Installation of the Inlet Guide Vane (IGV) and Stage 3 Vane Lever Arms or Bushings
806
Removal of the Actuation Ring Connecting Links
810
Installation of the Actuation Ring Connecting Links
814
Replacement of the Actuation Ring Flanged Bushing (Stages 1 and 2)
819
HPC REAR STATOR ASSEMBLY DESCRIPTION AND OPERATION
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099
72-33-00 1
General
1
Description
1
Casing
1
72-CONTENTS R CES
Page 17 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Vanes
__________________ COMBUSTION SECTION DESCRIPTION AND OPERATION
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-40-00 1
General
COMBUSTION CASE ASSEMBLY DESCRIPTION AND OPERATION
C _
1
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499
72-41-00 1
General
1
Description
1
Components
1
Ports
1
COMBUSTION CASE ASSEMBLY INSPECTION/CHECK
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-41-00 601
72-CONTENTS R CES
Page 18 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Borescope Inspection of the Combustion Chamber Liners, Dome Areas, HPT Nozzle Vanes and Shrouds (as far as visible through two opposite ports) Inspection/Check of the Combustion Case Assembly
COMBUSTION CASE ASSEMBLY REPAIRS
CH/SE/SU ________
____ EFFECTIVITY PAGE ___________ 601 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 603
001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499
801
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-41-00
Repairs of the Combustion Case Assembly
COMBUSTION CHAMBER ASSEMBLY DESCRIPTION AND OPERATION
C _
801
72-42-00 1
General
1
Description
1
Dome
1
Cowl
1
Liners
1
72-CONTENTS R CES
Page 19 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
COMBUSTION CHAMBER ASSEMBLY INSPECTION/CHECK
C _
PAGE ___________ ____ EFFECTIVITY
72-42-00 601
Borescope Inspection of the Combustion Chamber Liners and Dome Area
601
Borescope Inspection of the Outer Side of the Combustion Chamber Outer Liners
621
Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD
626
Borescope Inspection of the Inner Cowl Bolts of the Combustion Chamber
634
_______________ TURBINE SECTION DESCRIPTION AND OPERATION
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-50-00 1
General
1
High pressure turbine module
1
Low pressure turbine module
1
________________ TURBINE SECTION REMOVAL/INSTALLATION
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-50-00 401
001-049, 051-099 101-149, 151-199
72-CONTENTS R CES
Page 20 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Discard Life Limited Parts of HPT and LPT
HPT NOZZLE ASSEMBLY DESCRIPTION AND OPERATION
C _
PAGE EFFECTIVITY ____ ___________ 201-249, 251-299 301-399, 401-499 401 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-51-00 1
General
1
Description
1
Nozzle Segments
1
Inner Support
1
Aft Outer Support and Seal
1
HPT NOZZLE ASSEMBLY INSPECTION/CHECK
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299
72-51-00 601
Borescope Inspection of High-Pressure Turbine Nozzle Assembly
601
Borescope Inspection of High-Pressure Turbine Nozzle Assembly
612
72-CONTENTS R CES
Page 21 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
HPT ROTOR ASSEMBLY DESCRIPTION AND OPERATION
72-52-00
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 1
General
1
Description
1
Front Shaft
1
Disk
1
Rear Shaft
1
Front Outer Seal
1
Blades
1
HPT ROTOR ASSEMBLY INSPECTION/CHECK
Borescope Inspection of HPT Blades (from the front and the rear)
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-52-00 601
601
72-CONTENTS R CES
Page 22 Nov 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Borescope Inspection of HPT Blades (from the front and the rear)
CH/SE/SU ________
Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) HPT SHROUD AND STAGE 1 LPT NOZZLE ASSEMBLY DESCRIPTION AND OPERATION
1
1
HPT shroud and stage 1 LPT nozzle assembly
1
Description
1
HPT shroud and stage 1 LPT nozzle assembly
Borescope/Inspection of the Stage 1 Low-Pressure Turbine Nozzle Assembly
____ EFFECTIVITY PAGE ___________ 616 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 630 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 640 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-53-00
General
HPT SHROUD AND STAGE 1 LPT NOZZLE ASSEMBLY INSPECTION/CHECK
C _
1
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
051-099 151-199 251-299 401-499 051-099 151-199 251-299
72-53-00 601
601
72-CONTENTS R CES
Page 23 Nov 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Borescope/Inspection of the High-Pressure Turbine Shroud
LPT ROTOR/STATOR ASSEMBLY DESCRIPTION AND OPERATION
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 609 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-54-00 1
General
1
The low pressure turbine (LPT) module is a 4-stage axial-flow turbine.
1
Description
1
LPT Stator Assembly
1
LPT Rotor Assembly
4
LPT ROTOR/STATOR ASSEMBLY INSPECTION/CHECK
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-54-00 601
Inspection of the Stage 1-3 Blades
601
Inspection of the Stage 4 Blades
622
72-CONTENTS R CES
Page 24 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Inspection of the Stage 2-4 Nozzle Segments
CH/SE/SU ________
Inspection of the Stage 2-4 Nozzle Segments Inspection of the Stage 1-4 Stationary Air Seals Optional Visual Inspection of the Stage 4 Blades from the Rear of the Engine Inspection of the Turbine Case
Inspection of the Turbine Case
General Visual Inspection of Piping of LPT Case Air Cooling General Visual Inspection of Piping of LPT Case Air Cooling
LPT ROTOR/STATOR ASSEMBLY REPAIRS
____ EFFECTIVITY PAGE ___________ 631 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 638 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 653 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 660 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 669 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 675 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 681 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 685 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-54-00 801
Replacement of the Broken Studs of EGT (T49.5) Sensor Bracket Assy
LPT SHAFT DESCRIPTION AND OPERATION
C _
801
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-55-00 1
001-049, 051-099
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
Page 25 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
General
Low pressure turbine shaft
Description
Low pressure Turbine Shaft
No. 4 Bearing
No. 5 Bearing
LPT SHAFT MAINTENANCE PRACTICES
Inspection/Check of the Low
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 5 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 5 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-55-00 201
Replacement of LPT Shaft Plug O-rings
LPT SHAFT INSPECTION/CHECK
C _
201
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049,
051-099 151-199 251-299 401-499 051-099
72-55-00 601
601
72-CONTENTS R CES
Page 26 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Pressure Turbine Shaft Assembly
CH/SE/SU ________
TURBINE FRAME ASSEMBLY DESCRIPTION AND OPERATION
72-56-00
C _
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 1
Turbine Frame with Radial Struts
1
No. 5 Bearing Support for Turbine Frame with Radial Struts
10
Turbine Frame with Tangential Non Symetrical Section Struts No. 5 Bearing Support for Turbine Frame with Tangential Non Symetrical Section Struts Turbine Frame with Tangential Symetrical Section Struts
10
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-105, 201-207, 001-049, 101-105, 201-207, 051-051,
14
051-051,
16
No. 5 Bearing Support for Turbine Frame with Tangential Symetrical Section Struts
17
106-149, 208-249, 301-399, 106-149, 208-249, 301-399,
155-199 251-299 401-499 155-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099
General
1
Description
1
TURBINE FRAME ASSEMBLY REMOVAL/INSTALLATION
CES
052-099 151-154
72-56-00 401
Removal of the Flame Arrestor and Flange Assembly
401
Installation of the Flame Arrestor
408
72-CONTENTS R
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 052-099 151-154
Page 27 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT and Flange Assembly
CH/SE/SU ________
Removal of the Oil Inlet Cover Assembly Installation of the Oil Inlet Cover Assembly
TURBINE FRAME ASSEMBLY INSPECTION/CHECK
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 414 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 427 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-56-00 601
Inspection/Check of the Turbine Frame Assembly
TURBINE FRAME ASSEMBLY CLEANING/PAINTING
C _
601
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-56-00 701
Cleaning of the Oil Inlet Cover
701
Cleaning of the Aft Sump Oil Supply Tube
705
Cleaning of the Aft Sump Oil Scavenge Tube
710
TURBINE FRAME ASSEMBLY REPAIRS
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-56-00 801
001-049, 051-099 101-149, 151-199
72-CONTENTS R CES
Page 28 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Replacement of Defective Studs
Replacement of Defective or Missing Thermal Insulation Blankets (On Radial Struts TRF Only) Replacement of the Oil Supply Tube Assembly
_______________________ ACCESSORY DRIVE SECTION DESCRIPTION AND OPERATION
PAGE EFFECTIVITY ____ ___________ 201-249, 251-299 301-399, 401-499 801 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 805 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 811 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-60-00 1
General
INLET GEARBOX ASSEMBLY DESCRIPTION AND OPERATION
C _
1
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-61-00 1
General
1
Description
1
Horizontal Bevel Gear
1
Radial Bevel Gear
1
72-CONTENTS R CES
Page 29 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________ Thrust Bearing (No. 3 Ball)
Roller Bearing (No. 3 Roller)
TRANSFER GEARBOX ASSEMBLY DESCRIPTION AND OPERATION
C _
____ EFFECTIVITY PAGE ___________ 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-62-00 1
General
1
Description
1
Radial Drive Shaft Assembly
1
TGB Assembly
1
TRANSFER GEARBOX ASSEMBLY REMOVAL/INSTALLATION
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-62-00 401
Removal of the Transfer Gearbox Module
401
Installation of the Transfer Gearbox Module
418
72-CONTENTS R CES
Page 30 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
TRANSFER GEARBOX ASSEMBLY INSPECTION/CHECK
PAGE ___________ ____ EFFECTIVITY
72-62-00 601
Inspection/check of the Transfer Gearbox Assembly
ACCESSORY GEARBOX ASSEMBLY DESCRIPTION AND OPERATION
C _
601
1
1
Description
1
Horizontal Drive Shaft Assembly
1
AGB Housing
1
Gear Train
8
Disengagement/Engagement of the Horizontal Drive Shaft
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
051-099 151-199 251-299 401-499 051-099 151-199 251-299
72-63-00
General
ACCESSORY GEARBOX ASSEMBLY MAINTENANCE PRACTICES
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-63-00 201
201
72-CONTENTS R CES
Page 31 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
ACCESSORY GEARBOX ASSEMBLY REMOVAL/INSTALLATION
CH/SE/SU ________
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499
72-63-00 401
Removal of the Handcranking Drive Cover
401
Installation of the Handcranking Drive Cover
408
Removal of the Accessory Gearbox Assembly
412
Installation of the Accessory Gearbox Assembly
441
ACCESSORY GEARBOX ASSEMBLY INSPECTION/CHECK
Replacement of a Sealol Seal (Typical)
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-63-00 601
Inspection/Check of the Accessory Gearbox Assembly
ACCESSORY GEARBOX ASSEMBLY REPAIRS
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
601
72-63-00 801
801
72-CONTENTS R CES
Page 32 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Replacement of a Magnetic Seal (Typical) Replacement of a Magnetic Seal (IDG and Starter Drive Pads).
CH/SE/SU ________
C _
____ EFFECTIVITY PAGE ___________ 813 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 822 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-CONTENTS CES
Page 33 Feb 01/09
C F M 56-5B ENGINE - GENERAL - DESCRIPTION AND OPERATION ____________________________________________ 1. _______ General (Ref. Fig. 001, 002, 003, 004) The engine is a dual-rotor, variable stator, high bypass ratio turbo fan power plant. The 9 stage high pressure compressor is driven by 1 stage high pressure turbine, and the integrated front fan and booster is driven by 4 stage low pressure turbine. An annular combustor converts fuel and compressor discharge air into energy to provide engine thrust part through primary exhaust and to drive the turbines. The accessory drive system extracts energy from the high pressure rotor to drive the engine accessories and the engine mounted aircraft accessories. Reverse thrust for braking the aircraft after landing is supplied by an integrated system which acts on the fan discharge airflow (Ref. 78-00-00). 2. Engine ______________ Modules The principal modules of the engine are fan and booster, high pressure compressor, combustor chamber, high pressure turbine, low pressure turbine and accessory drive gearbox. Detailed descriptions of the components of each section are given in corresponding sections of this document. The description of each engine module is as follows: A. Fan/Booster Rotor The fan rotor consists of one full diameter booster for the secondary flow single stage fan and a smaller 4 Stage booster for the core engine flow. The fan and the booster are mounted on a common internal concentric shaft driven by the fan pressure turbine. Two bearings support the fan assembly in the frame. B. Fan/Booster Stator Fixed stator vanes are provided for both, the fan and booster rotor. The fan casing, in which the stator is mounted has provision for blade containment forward of and in the plan of the fan rotor. The casing is supported by the fan frame and supports the accessory drive gearbox.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Engine LH Side Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Engine RH Side Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
Engine Schematic Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
Major External Dimensions Figure 004 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B C. Fan Frame The fan frame is one of the major structural and aerodynamic components of the engine. Aerodynamically the fan frame forms the inner and outer flow passage of the fan airstream as well as the core airstream. Structurally, it carries inlet cowl loads, supports the fan casing, the two fan bearings and the core engine forward bearing; it contains the forward engine mount, it houses the accessory drive power take off gearbox and radial drive shaft; it contains the variable bypass valves between the booster and high pressure compressor; it supports the transfer and accessory gearboxes; and provides the mounting surfaces for fan-stream acoustic panels. The fan frame also serves as the forward support for the compressor. D. Compressor Rotor The compressor is a nine stage axial flow assembly. The rotor consists of the stage 1 and 2 discs which form a spool, a separately attached stage 3 disc and a spool containing stage 4 - 9 discs. Stage 1, 2 and 3 have axial dovetail slots and stage 4 - 9 blades are retained in circumferential slots. All blades are individually replaceable without spool disassembly. E. Compressor Stator All 9 stages of the compressor stator are shrouded. The Inlet Guide Vanes (IGV) and the first 3 stages of the compressor are variable. The casing is composed of two semi cylindrical halves, permitting a quick access to the core engine compressor. F. Combustor A step diffuser is incorporated upstream of the combustor for reduction of the combustor sensitivity to the compressor velocity profile. The combustor can be replaced without disturbing the fuel nozzles. The combustor casing provides structural support for the combustor, the compressor Outlet Guide Vanes (OGV) the High Pressure (HP) stator and shrouds, and the seals for Compressor Discharge Pressure (CDP). G. High Pressure Turbine The High Pressure Turbine (HPT) is an air cooled single stage high energy turbine. Rotor blades are individually replaceable without the need for rotor disassembly or rebalancing. H. Low Pressure Turbine The Low Pressure Turbine (LPT) consists of 4 and half stages of blades and vanes. The first stage nozzle vane is cooled and provides cooling air for the high pressure and low pressure turbine discs. The LPT drives the fan rotor through the inner concentric shaft and is aerodynamically coupled to the high pressure system. The LPT casing is a 360 degrees design to provide structural continuity.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 6 Nov 01/08
C F M 56-5B J. Turbine Frame The turbine frame is located aft the LPT. It contains the aft LPT bearing, and supports the primary exhaust system. It contains the engine rear mount fitting. K. Accessories and Accessory Drives Engine and aircraft accessories are mounted on the accessory gearbox which is located on the outside of the lower part of the casing and driven through a radial shaft at 6 oclock position. Power for the engine and aircraft accessories is extracted from the HPC rotor shaft through an inlet gearbox and the radial drive shaft. Quick Attach/Detach (QAD) accessory mounting flanges are provided for the engine accessories. 3. Bearings __________________ and Seals (Ref. Fig. 005, 006, 007) A. Bearings The engine rotors are supported by bearings installed in the sump cavities provided by the two frames. The forward sump is in the fan frame and is the location of bearings No. 1, No. 2 (fan/booster shaft) and No. 3 (HP shaft forward part). The aft sump is in the turbine rear frame where are bearings No. 4 (HP shaft aft part) and No. 5 (LP shaft aft part). B. Oil Distribution The bearings must be lubricated and oil is distributed to these components by nozzles. However, the oil must be retained within the engine, so seals of various types are provided to confine the oil and direct its recirculation. C. Seals Arrangement The arrangement of oil and air seals, the provisions for oil supply, oil scavenge, seal pressurization, sump vent subsystems produce a system known as a dry sump. Engine sumps are vented to ambient pressure through the center-vent tube which is contained in the LP shaft. D. Bearing Functions Bearings provide reduced rolling friction, support the rotors axially and radially within the engine structure, and position the rotors relative to the stators. The bearing must control the forces of gravity weight aerodynamic loads of pumping and turbine driving and gyroscopic loads due to aircraft maneuvers.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 7 Nov 01/08
C F M 56-5B
Forward Sump Figure 005 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 8 Nov 01/08
C F M 56-5B
Aft Sump Figure 006 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 9 Nov 01/08
C F M 56-5B
Sump Venting System Figure 007 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 10 Nov 01/08
C F M 56-5B 4. ________________________________________________________________________ Engine Boroscope Inspection Port Provisions, Location and Identification (Ref. Fig. 008, 009, 010) There is a total of 22 borescope port provisions along the engine. The most important number of them is found on the engine right side, mostly between the 4 and 5 oclock positions, aft looking forward. Their location and identification are as follows: A. On the Inner Wall (Fairing) of the Fan Bypass Duct (Ref. Fig. 008) There are two (8 mm dia) borescope port provisions. From front to rear, the first port, identified S03, is just below the 3 oclock position, between two OGVs. The second port, identified S05, is near the 4 oclock position, just in front of the Variable Bleed Valves (VBVs) plane. Refer to ATA 72-21-00 for the internal parts and areas you can fully or partially see through these two borescope port provisions. B. On the High Pressure Compressor (HPC) Front and Rear Casings (Ref. Fig. 009, 010) There are nine (8 and 10 mm dia) borescope port provisions, located between the 4 and 5 oclock positions, aft looking forward. From the HPC inlet plane IGV to the last stage (ninth) of the HPC, they are identified as follows: - S1, S2, S3, S4, S5, S6, S7, S8 and S9. Refer to ATA 72-31-00 for the internal parts and airfoil areas you can see through these 9 borescope port provisions. C. On the Combustion Case (Ref. Fig. 008, 009, 010) There are six borescope port provisions around the combustion case: - S12, S13, S14, S15, located in the same plane, at the 1, 3, 6 and 10 oclock positions respectively, and immediately in front of the fuel manifold, - S16 and S17, located in the same plane, at approximately the 5:30 and 8:30 oclock positions respectively, and immediately in front of the combustion case aft flange. The two ports which install the two spark igniters on the combustion case can also be used as borescope port provisions. These ports are identified as S10 and S11. They are in the same plane, at the 4 and 8 oclock positions respectively. The S10, S11, S12, S13, S14 and S15 ports permit the borescope inspection of the HPT rotor blades (S10 and S11), the combustion chamber and the HPT nozzle. The S16 and S17 ports permit the borescope inspection of the HPT shrouds, the stage 1 LPT nozzle segments and leading edge of stage 1 LPT rotor blades.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 11 Nov 01/08
C F M 56-5B
Engine Borescope Port Provisions - Location and Identification on Left Side Figure 008 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 12 Nov 01/08
C F M 56-5B
Engine Borescope Port Provisions - Location and Identification on Right Side Figure 009 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 13 Nov 01/08
C F M 56-5B
Borescope Port Provisions - Location and Engine Station Figure 010 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 14 Nov 01/08
C F M 56-5B Refer to ATA 72-41-00, 72-42-00, 72-51-00, 72-52-00 and 72-53-00 for the internal parts and the areas you can, fully or partially, see through the six normal borescope port provisions of the combustion case and the two spark igniter ports. NOTE : The use of the spark igniter ports as borescope provisions (S10 ____ and S11) necessitates the removal of the spark igniters (Refer to ATA 74-21-30). D. On the Low Pressure Turbine Case (Ref. Fig. 009, 010) There are three borescope port provisions on the LPT case. Location at the 5 oclock position approximately. From front to rear, they are identified S18, S19 and S20. Refer to ATA 72-54-00 for the internal parts and areas you can, fully or partially, see through these borescope port provisions. NOTE : The borescope ports S16 and S17 must be used to inspect: ____ - the LPT nozzle, stage 1 (Refer to ATA 72-53-00), - the leading edge and tip shroud of LPT rotor blades, stage 1 (Ref. to ATA 72-54-00).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 15 Nov 01/08
C F M 56-5B ENGINE - GENERAL - MAINTENANCE PRACTICES ________________________________________ TASK 72-00-00-917-002 Engine Tubes, Hoses, and Fittings 1. __________________ Reason for the Job This section gives the general inspection and removal/installation instructions for engine tubes, hoses, and fittings. NOTE : Assemblies covered by this task do not contain parts that have a ____ regular replacement or inspection schedule. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific
container protective caps protective closures
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
Material No.
CP5070
Material No.
CP8001
Material No.
CP8002
* engine oil (Ref. 70-30-00) * vaseline (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 201 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-21-00-918-002 71-00-00-710-006 73-11-30-200-002 72-00-00-991-314 72-00-00-991-315 72-00-00-991-316
Seals (Preformed Packings and O-rings) and Gaskets Minimum Idle Check Inspection/Check of the Fuel Manifold Assembly Fig. 201 Fig. 202 Fig. 203
3. __________ Job Set-up Subtask 72-00-00-869-076 A. Not Applicable 4. Procedure _________ (Ref. Fig. 201/TASK 72-00-00-991-314, 202/TASK 72-00-00-991-315, 203/TASK 72-00-00-991-316) Subtask 72-00-00-210-073 A. If a tube, hose, or fitting on the engine has apparent damage, do the inspection that follows: NOTE : The limits in this table are general and they do not replace the ____ limits on components given in this manual. NOTE : The inspection of the fuel manifold is given in (Ref. TASK 73-11____ 30-200-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 202 Nov 01/08
C F M 56-5B
Tube and Hose Seating Surfaces Figure 201/TASK 72-00-00-991-314 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 203 Nov 01/08
C F M 56-5B
Swivel Flanged Connectors Figure 202/TASK 72-00-00-991-315 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 204 Nov 01/08
C F M 56-5B
Hose Assembly Inspection Areas Figure 203/TASK 72-00-00-991-316 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 205 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Tubing for: A. Splits, cracks or kinks
Not serviceable
Replace tube.
B. Dents or flat areas
Any amount when the contour is not more than 20 percent of original tube OD
Replace tube.
C. Nicks or scores on drain lines, drain shrouds, and scavenge lines, does not include aft sump oil scavenge line
Max. depth not more than 0.010 in. (0.25 mm) after blending
Blend the nicks or scores.
D. Nicks or scores on all other fuel, air and oil lines and aft sump oil scavenge line
Max. depth not more than 0.005 in. (0.13 mm) after blending
Blend the nicks or scores.
A. Scratches in circumference areas A and C
Any amount to 0.005 in. (0.13 mm) after removal of high metal
Remove high metal.
B. Scratches in circumference area B
Any amount not detectable using a 0.040 in. (1.02 mm) radius ball scribe
Remove high metal.
C. Axial scratches areas A and C
Any amount to 0.005 in. (0.13 mm) after removal of high metal
Remove high metal.
2. Seating surfaces of the fitting for: (Ref. Fig. 201/TASK 72-00-00-991-314)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 206 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------D. Axial scratches Not serviceable Replace tube. area B E. Nicks and pits area C
Any amount not more than 0.03 in. (0.8 mm) deep after blending
Blend depressions.
F. Nicks and pits areas A and B
Not serviceable
Replace tube.
G. Score marks in circumference of silver plated seating (mating) surfaces
Any amount when score mark does not go through parent metal
Replace tube.
H. Deformation in circumference (spreading) of tube/ferrule
Any amount when nut is free to turn
Replace tube.
J. Deformation in circumference (spreading) of flare nut
Any amount when nut is free to turn
Replace tube.
K. Axial deformation (dishing) of spherical seat fitting surface
Any amount if depth is constant and less than 0.005 (0.13 mm) to the initial surface
Replace tube.
A. Damaged corners
Any amount when the correct torque can be applied
Replace tube or hose.
B. Damaged thread
Total of one full thread or one continuous thread may be missing after chasing threads
Chase threads.
3. Tube and hose fitting nuts for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 207 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Lockwire hole torn Serviceable if one hole Replace tube or hose. out is still there 4. Swivel flange fittings for: (Ref. Fig. 202/TASK 72-00-00-991-315) A. Nicks or scratches on seating surface (surface B)
Not serviceable
Replace tube.
B. Nicks or scratches on mating surfaces (surfaces A and C)
Any nick or scratch not more than 0.020 in. (0.51 mm) deep after removal of high metal
Remove high metal.
C. Cracks
Not serviceable
Replace tube.
D. Seating surface (surface B) out-of-flat
0.006 in. (0.15 mm) out-of-flat
Replace tube.
E. Cracks that extend out from bolt holes
Permitted when not more than 2 bolt holes are cracked
Replace tube.
F. Weld joint cracks
Not serviceable
Replace tube.
Not serviceable
Replace tube or hose.
3 broken wires per plait and no more than 6 broken wires per assembly or per lineal foot (0.3 m) of hose
Replace hose.
5. Tube and hose assembly for: A. Leakage 6. Hose assemblies for: (Ref. Fig. 203/TASK 72-00-00-991-316) A. Broken hose braid
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 208 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Crimps Not serviceable Replace hose. C. Internal obstructions
Not serviceable
Remove obstruction or replace hose.
D. Cuts in fire sleeve areas A and B
Up to 3 cuts that do not cross per hose section if the length is not more than 0.20 in. (5.1 mm)
Replace hose.
NOTE : Area A is defined as follows L = 2.5 times the hose outer diameter ____ at both ends of the hose. Area B is the length between the two Areas A E. Tears in fire sleeve material area A
Not serviceable
Replace hose.
F. Tears in fire sleeve material area B
1 per hose section if the depth is not more than 0.010 in. (0.25 mm) and total area is not more than 0.40 in.2 (10.2 mm2)
Replace hose.
7. Tube mechanical joints (ferrules) for: A. Wear on end face
Any amount when O-ring retention flange is not deformed.
B. Nicks, dents and scratches on end face
Any amount when O-ring retention flange is not deformed after removal of high metal.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 209 Nov 01/08
C F M 56-5B Subtask 72-00-00-917-052 B. If necessary, replace the damaged tube as follows: WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE YOUR _______ CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. (1) Disassemble the connection. NOTE : Tubes can have oil or fuel in them as they are removed. Drain ____ the fluid into a container. (2) Install protective closures and protective caps on drilled passages, fuel lines, oil lines, air lines and open engine ports when parts are removed. (3) Use protection on the machined surfaces to prevent damage. (4) Remove and discard O-ring, if necessary. (5) Remove and do an inspection of the gaskets or seals, if necessary (Ref. TASK 70-21-00-918-002). (6) Do an inspection of the mating and threaded surfaces for cleanliness, contamination, scratches, dents, or other surface defects. (7) Do an inspection of the tube for satisfactory general condition and make sure that no damage has occurred. (8) Remove the closures and caps used for protection immediately before installation. (9) Lubricate new O-rings with vaseline (Material No. CP5070). (10) Apply a thin layer of engine oil (Material No. CP2442) to the gaskets and seals. (11) Install new O-rings, or serviceable gaskets, or seals, as necessary. (12) Install the tube but do not use force. A small elastic distortion is permitted to engage the connections.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 210 Nov 01/08
C F M 56-5B (13) Tightening method: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Tighten all end fittings and clamps with your hands. After a system is installed, torque the clamps first, then torque the end fittings. (14) Do not chafe tubes when you install the clamps. Attach the tube loosely with a clamp and position the tube to get the best clearance, then tighten the clamps. (15) Use the correct size clamps for the tube you install (16) Make sure there is clearance between the tube and each adjacent part. Correct minimum clearances are given in the table that follows: R R R R R R R R R R R R R R R R R R
------------------------------------------------------------------------------| | MINIMUM | | | AFFECTED EQUIPMENT | CLEARANCE | REMARKS | ------------------------------------------------------------------------------| STRUCTURE: | 0.25 in. | Not less than 0.06 in. | | Frames, bolts, | (6.4 mm) | (1.5 mm) clearance in | | rivets, webs, etc. | | 1 in. (25.4 mm) or | | | | less of clamping | | | | points | ------------------------------------------------------------------------------| MECHANISM: | 0.5 in. | Keep the clearance | | Actuators, linkages, etc. | (12.7 mm) | during the full | | | | travel of the | | | | mechanism | ------------------------------------------------------------------------------| GROUPED TUBING: | 0.19 in. | Clamp lines that | | Parallel runs, | (4.8 mm) | go across each other | | intersections, | | to get minimum | | etc. | | clearance of 0.12 in. | | | | (3.0 mm) | ------------------------------------------------------------------------------(17) Coupling nuts must turn freely by hand. (18) The mating surfaces of the flanges of the tube must be installed at 90 degrees to each other.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 211 Nov 01/08
C F M 56-5B (19) Make sure that fasteners are installed correctly when tightened to the specified value. (20) Safety the connection with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). Subtask 72-00-00-917-053 C. If necessary, replace the damaged hose as follows: WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE YOUR _______ CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. (1) Disassemble the connection. NOTE : Hoses can have oil or fuel in them as they are removed. Drain ____ the fluid into a container. (2) Install protective closures and protective caps on drilled passages, fuel lines, oil lines, air lines and open engine ports when parts are removed. (3) Remove and discard O-rings, if necessary. (4) Remove and do an inspection of the gaskets or seals, if necessary (Ref. TASK 70-21-00-918-002). (5) Do an inspection of the mating and threaded surfaces for cleanliness, contamination, scratches, dents or other surface defects. (6) Do an inspection of the hose for satisfactory general condition and make sure that no damage has occurred. (7) Remove the protective closures and caps immediately before installation. (8) Lubricate new O-rings with vaseline (Material No. CP5070). (9) Apply a thin layer of engine oil (Material No. CP2442) to the gaskets and seals. (10) Install new O-rings, or serviceable gaskets, or seals, as necessary. (11) Do not bend or try to make the preformed hoses straight.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 212 Nov 01/08
C F M 56-5B (12) Tightening method: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Tighten all the end fittings and clamps with your hand. After a system is installed, torque the clamps first, then torque the end fittings. (13) Do not chafe hoses when you install the clamps. Attach the tube loosely with a clamp and position the hose to get the best clearance, then tighten the clamps. (14) Use the correct size clamps for the hose you install. A clamp that is too large will cause chafing. A clamp that is too small will cause a restriction. (15) Make sure there is clearance between the hose and each adjacent part. (16) Coupling nuts must turn freely by hand. (17) The mating surfaces of the flanges of the hose must be installed at 90 degrees to each other. (18) Make sure that fasteners are installed correctly when tightened to the specified value. (19) Safety the connection with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). Subtask 72-00-00-710-051 D. If fuel or oil lines were disconnected, do a minimum idle leak check and check for leaks (Ref. TASK 71-00-00-710-006).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 213 Nov 01/08
C F M 56-5B TASK 72-00-00-820-004 Air Flow Check of the Forward Sump Oil Supply Circuit 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
container of 0.5 USgal (2 l.) test rig warning notice Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) 1 ADAPTER, TEST RIG - AIR FLOW CHECK
856A3267
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP8001
Material No.
CP8002
* lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 214 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 71-00-00-000-042 71-00-00-400-042 71-00-00-710-006 71-00-00-820-002 71-13-00-010-040 71-13-00-410-040 72-00-00-991-317
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Removal of the Power Plant Installation of the Power Plant Minimum Idle Check Oil Circuit Air Flow Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Fig. 204
3. __________ Job Set-up Subtask 72-00-00-941-106 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-148 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 215 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 204/TASK 72-00-00-991-317) Subtask 72-00-00-280-070 A. Forward Sump Air Flow Check WARNING : USE PROTECTIVE GLOVES AND BE CAREFUL WITH OIL SPLASHES WHEN YOU _______ DISCONNECT OIL TUBES. HOT OIL CAN CAUSE DEEP BURNS. (1) Put a container of 0.5 USgal (2 l.) under the junction of the oil supply tube (10) and oil supply hose (20). (2) Cut and remove the lockwire which safeties the union nut of the oil supply hose (20) to the oil supply tube (10). (3) Disconnect the oil supply hose. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Disconnect the oil supply hose (20) from the oil supply tube (10). (4) Connect the test rig equipped with ADAPTER, TEST RIG - AIR FLOW CHECK (856A3267G02), to the oil supply tube (10). (5) TORQUE the union nut to between 225 and 275 lbf.in (2.54 and 3.10 m.daN). (6) Do the check of the forward sump oil supply circuit (Ref. TASK 71-0000-820-002). (7) If the measured flow rate is not within the limits, replace the power plant (Ref. TASK 71-00-00-000-042) and (Ref. TASK 71-00-00-400-042). (8) Disconnect the test rig from the oil supply tube (10). (9) Connect the oil supply hose (20) to the oil supply tube (10). (10) TORQUE the union nut to between 450 and 550 lbf.in (5.08 and 6.21 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 216 Nov 01/08
C F M 56-5B
Air Flow Check of the Forward Sump Oil Supply Circuit Figure 204/TASK 72-00-00-991-317 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 217 Nov 01/08
C F M 56-5B (11) Safety the union nut with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). Subtask 72-00-00-710-059 B. Do an idle check (Ref. TASK 71-00-00-710-006) and check for leaks. Subtask 72-00-00-610-053 C. Do a check of the oil level (Ref. TASK 12-13-79-610-002). 5. Close-up ________ Subtask 72-00-00-410-147 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 218 Nov 01/08
C F M 56-5B TASK 72-00-00-820-005 Air Flow Check of the AGB/TGB Oil Supply Circuit 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R R R
No No No No
specific specific specific specific
container of 0.5 USgal (2 l.) test rig warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) 1 ADAPTER, TEST RIG - AIR FLOW CHECK
No specific 856A3267
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
* graphite grease (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 219 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 71-00-00-710-006 71-00-00-820-002 71-13-00-010-040 71-13-00-410-040 72-63-00-000-003 72-63-00-400-003 72-00-00-991-318
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Minimum Idle Check Oil Circuit Air Flow Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Accessory Gearbox Assembly Installation of the Accessory Gearbox Assembly Fig. 205
3. __________ Job Set-up Subtask 72-00-00-941-107 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-149 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 220 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 205/TASK 72-00-00-991-318) Subtask 72-00-00-280-071 A. AGB/TGB Air Flow Check WARNING : USE PROTECTIVE GLOVES AND BE CAREFUL WITH OIL SPLASHES WHEN YOU _______ DISCONNECT OIL TUBES. HOT OIL CAN CAUSE DEEP BURNS. (1) Remove bolt (50), outer spring clip (20), inner spring clip (40), and plastic bushings (30), which attach the AGB/TGB oil supply tube (10) to the AGB bracket. (2) Put a container of 0.5 USgal (2 l.) under the junctions of the oil supply tube (10) to the AGB and to the lubrication unit. (3) Disconnect the oil supply tube. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Disconnect the oil supply tube (10) from the nipples of the AGB and lubrication unit. (4) Connect the test rig, equipped with ADAPTER, TEST RIG - AIR FLOW CHECK (856A3267G02), to the AGB nipple. (5) TORQUE the union nut to between 225 and 275 lbf.in (2.54 and 3.10 m.daN). (6) Do the check of the the AGB/TGB oil supply circuit (Ref. TASK 71-0000-820-002). (7) If the measured flow rate is not within the limits, replace the accessory gearbox module (Ref. TASK 72-63-00-000-003) and (Ref. TASK 72-63-00-400-003). (8) Disconnect the test rig from the AGB nipple. (9) Connect the AGB/TGB oil supply tube (10) to the AGB and lubrication unit nipples. Tighten by hand.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 221 Nov 01/08
C F M 56-5B
Air Flow Check of the AGB/TGB Oil Supply Circuit Figure 205/TASK 72-00-00-991-318 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 222 Nov 01/08
C F M 56-5B (10) Lubricate the threads of bolt (50) with graphite grease (Material No. CP2101). (11) Attach the AGB/TGB oil supply tube (10) to AGB bracket with plastic bushings (30), inner spring clip (40), outer spring clip (20) and bolt (50). (12) Make sure that the EGB/TGB oil supply tube (10) is not strained. (13) TORQUE the bolt (50) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (14) TORQUE the union nuts to between 450 and 550 lbf.in (5.08 and 6.21 m.daN). Subtask 72-00-00-710-060 B. Do an idle check (Ref. TASK 71-00-00-710-006) and check for leaks. Subtask 72-00-00-610-054 C. Do a check of the oil level (Ref. TASK 12-13-79-610-002). 5. Close-up ________ Subtask 72-00-00-410-148 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 223 Nov 01/08
C F M 56-5B TASK 72-00-00-820-006 Air Flow Check of the Aft Sump Oil Supply Circuit 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No
specific specific specific specific specific
access platform container of 0.5 USgal (2 l.) test rig warning notice Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) 1 ADAPTER, TEST RIG - AIR FLOW CHECK
No specific 856A3267
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 224 Feb 01/10
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 71-00-00-710-006 71-00-00-820-002 71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-00-00-991-319
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Minimum Idle Check Oil Circuit Air Flow Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 206
3. __________ Job Set-up Subtask 72-00-00-941-108 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 225 Nov 01/08
C F M 56-5B Subtask 72-00-00-010-150 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-00-00-040-082 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-151 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 206/TASK 72-00-00-991-319) Subtask 72-00-00-820-051 A. Aft Sump Air Flow Check WARNING : USE PROTECTIVE GLOVES AND BE CAREFUL WITH OIL SPLASHES WHEN YOU _______ DISCONNECT OIL TUBES. HOT OIL CAN CAUSE DEEP BURNS. (1) Put a container of 0.5 USgal (2 l.) under the junctions of the oil supply tube (20). (2) Remove nuts (60) and (180), bolts (70) and (160) which attach clamps (80) and (170) to the oil supply tube (20). (3) Remove clamps (80), (170) and shields (90) and (190).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 226 Nov 01/08
C F M 56-5B (4) Remove the aft sump oil supply tube as follows: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Remove the bolt (130) which attaches the clamps (120) and (140) to the bracket (150) on flange T. (b) Remove the nut (50) and the bolt (30) which attaches the clamps (40) and (110) to the bracket (100) on flange S. (c) Disconnect the oil supply tube (20) from the oil supply tube (10) and from the aft sump oil supply tube (30). (d) Remove oil supply tube (20). (5) Install a fitting reducer 0.750-16 and 0.5625-18 THD (19 and 14.3 mm) to the end of the aft sump oil supply tube (30). (6) Connect the test rig equipped with ADAPTER, TEST RIG - AIR FLOW CHECK (856A3267G02), to the fitting reducer. (7) TORQUE the union nuts to between to between 225 and 275 lbf.in (2.54 and 3.10 m.daN). (8) Do the check of the aft sump oil supply circuit (Ref. TASK 71-00-00820-002). (9) If the measured flow rate is not within the limits, do the cleaning of the oil inlet cover, and do the cleaning of the aft sump oil supply tube. (10) Disconnect the test rig from the fitting reducer. (11) Remove the fitting reducer from the aft sump oil supply tube (30). (12) Install the aft sump oil supply tube (20) as follows: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Connect the oil supply tube (20) to the oil supply tube (10) and to the aft sump oil supply tube (30).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 227 Nov 01/08
C F M 56-5B
Air Flow Check of the Aft Sump Oil Supply Circuit Figure 206/TASK 72-00-00-991-319- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 228 Nov 01/08
C F M 56-5B
Air Flow Check of the Aft Sump Oil Supply Circuit Figure 206/TASK 72-00-00-991-319- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 229 Nov 01/08
C F M 56-5B
Air Flow Check of the Aft Sump Oil Supply Circuit Figure 206/TASK 72-00-00-991-319- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 230 Nov 01/08
C F M 56-5B (b) Tighten the coupling nuts by hand. (c) Install clamps (120) and (170) on the oil supply tube (20). (d) Lubricate threads of bolt (30) and (130) with graphite grease (Material No. CP2101). (e) Attach clamps (120) and (140) to the bracket (150) on flange T, with bolt (130). (f) Attach clamps (40) and (110) to the bracket (100) on flange S, with bolt (30) and nut (50). (g) Make sure that the oil tube (20) is not strained. (h) TORQUE the bolt (30) and (130) to to between 45 and 50 lbf.in (0.50 and 0.56 m.daN). (i) TORQUE the coupling nuts of tubes (20) and (30) to to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (j) Lubricate threads of bolt (70) and (160) with graphite grease (Material No. CP2101). (k) Install shields (90) and (190) on couplings of the oil tube (20), with clamps (80) and (170), bolts (70) and (160), and nuts (60) and (180). NOTE : The nut (180) must be installed on the turbine frame side. ____ (l) TORQUE the nuts (60) and (180) to to between 45 and 50 lbf.in (0.50 and 0.56 m.daN). 5. Close-up ________ Subtask 72-00-00-410-149 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 231 Nov 01/08
C F M 56-5B Subtask 72-00-00-710-061 B. Do an idle check (Ref. TASK 71-00-00-710-006) and check for leaks. Subtask 72-00-00-610-055 C. Do a check of the oil level (Ref. TASK 12-13-79-610-002). Subtask 72-00-00-440-082 D. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-150 E. Close-up (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s). (3) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 232 Nov 01/08
C F M 56-5B ENGINE - GENERAL - SERVICING ____________________________ TASK 72-00-00-600-026 Recommendations for Engine Preservation 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-600-006 72-00-00-600-007 72-00-00-600-008 72-00-00-600-009 72-00-00-600-025 72-00-00-600-027 75-31-20-820-001
Preservation for a Period of up to 30 Days Preservation for a Period of 30 to 365 Days. Preservation Renewal Requirements. Procedure for Exceeded Long Term Preservation Period. Preservation for a Period of up to 90 Days Depreservation Set the Variable Bleed Valve Assembly to the Closed position
3. __________ Job Set-up Subtask 72-00-00-869-073 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-620-062 A. Engine preservation (1) The procedures that follow are recommended as the necessary minimum, to protect the CFM56 engine against corrosion, liquid and debris which go into the engine, and atmospheric conditions during periods of storage, and inactivity ; or which follow an engine-out ferry, or landing which follows an In Flight Shut Down (IFSD). These procedures are also recommended for installed engines on an inoperative aircraft or an engine not to be operated for more than thirty days.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 301 Nov 01/08
C F M 56-5B (2) Preservation Tasks The recommended procedure for preservation of the engine changes depending upon the duration of inactivity, the type of preservation used, and if the engine is operable or non-operable. NOTE : Engines that can be started are considered operable. Engines ____ that for any reason cannot be started are considered non-operable. Preservation renewal procedures are also covered in this instruction. (3) Select the preservation procedure and use the schedule that follows: (a) Up to 30 days (Ref. TASK 72-00-00-600-006). (b) Up to 90 days (Ref. TASK 72-00-00-600-025). (c) 30 to 365 days (Ref. TASK 72-00-00-600-007). (d) Preservation renewal requirements (Ref. TASK 72-00-00-600-008). (e) Procedure for exceeded long term preservation (Ref. TASK 72-0000-600-009). (f) Depreservation (Ref. TASK 72-00-00-600-027). NOTE : There is no restriction on the number of times you can do ____ the preservation procedure again, as long as it is accomplished each year. (4) Preservation Program The preservation procedures in this section are recommended as a guide to determine what precautions must be applied to give the engine sufficient protection from the elements during periods of storage and inactivity. Engine preservation is a flexible program that should be implemented in such a manner as to conform with particular weather and storage conditions. You must pay more attention to the preservation program for inactive engines exposed to high humidity and/or large temperature changes, especially if they are near a salt water area. These definitely require more attention to preservation needs than those inactive engines stored in drier climates or less severe weather conditions. The preservation program for spare and/or stored engines must be scheduled before you implement the preservation renewal requirements and monitored regularly to make sure that the necessary action is implemented before expiration of the preservation period. Depending upon weather conditions and the condition of the engine protection equipment covers, the effectiveness of the preservation protection
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 302 Nov 01/08
C F M 56-5B must be analysed and modified in order to keep the engine in serviceable condition. NOTE : You cannot preserve and place engines in storage and then ____ forget them. A correct plan (as given for an engine in revenue service) must be scheduled and then implemented. When you use desiccants they must be changed on a regular basis, based on the environmental conditions, to maintain the desiccant with a good protection life. It is recommended that the variable bleed valves (VBV) must be closed when the engine is to be preserved and stored or when you do maintenance in this area. This prevents the possibility of foreign objects going into the core engine inlet through the VBVs. For closure of the VBV doors, refer to (Ref. TASK 75-31-20-820-001).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 303 Nov 01/08
C F M 56-5B TASK 72-00-00-600-006 Preservation for a Period of up to 30 Days 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A2930
forklift start cart 1 COVER-FITTED BARE QECD ENGINE SHIPPING
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2098
Material No.
CP2160
USA MIL-D-3464 desiccant bags (Ref. 70-30-00) USA MIL-LP-378 vapor barrier film (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-003 71-00-00-710-028 72-00-00-100-007 75-31-20-820-001 78-31-00-710-042 80-11-00-040-045
Engine Automatic Start Engine Shutdown Engine Dry-out and Re lubrication Set the Variable Bleed Valve Assembly to the Closed position Operational Test of the Thrust Reverser System Manually Operate the Starter Valve
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 304 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-00-00-869-070 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-620-057 A. Preservation for a Period of up to 30 days. CAUTION : IF ENGINE WAS FERRIED OR SUBJECTED TO AN IN FLIGHT SHUTDOWN _______ (IFSD), ENGINE MUST BE DRIED OUT AND RELUBRICATED WITHIN 24 HOURS PER DRY OUT PROCEDURE OF THIS SECTION. CAUTION : UNDER NO CIRCUMSTANCES SHALL PRESERVATIVE OIL OR EQUIVALENT BE _______ SPRAYED INTO THE ENGINE INLET, CORE COMPRESSOR OR TURBINE, OR ENGINE EXHAUST. DIRT PARTICLES DEPOSITED ON THE WETTED BLADES AND VANES MAY ADVERSELY AFFECT ENGINE PERFORMANCE DURING SUBSEQUENT OPERATION. (1) Operable Engine Preservation. (a) On-wing installed engines. 1 _
Start the engines (Ref. TASK 71-00-00-710-003) and let them become stable at ground idle for 15 to 20 minutes, followed by a thrust reverser cycle (Ref. TASK 78-31-00-710-042) then stop the engines (Ref. TASK 71-00-00-710-028). NOTE : You can ignore this step if it was done during the last ____ engine operation (flight cycle). Under these conditions, consider the engine is preserved for 30 days from time of last operation.
2 _
Cover entrance to fan cowling and exit openings.
(b) Engines installed on stand. CAUTION : OPERATION SHOULD BE CARRIED OUT IN A CONFINED SPACE _______ WITH SUFFICIENT VENTILATION AND ON A FLAT HORIZONTAL SURFACE. CAUTION : MAXIMUM TOWING SPEED IS 3MPH (5KM/H). _______
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 305 Nov 01/08
C F M 56-5B 1 _
Tow stand base (dolly) to an area with sufficient ventilation and a flat surface.
2 _
Carefully raise stand base with a forklift.
3 _
Remove the pins, raise and stow the four caster wheels of stand base.
4 _
Lower stand base to level surface, remove the forklift.
5 _
Attach the forward and aft caster wheels with pins.
6 _
Remove COVER-FITTED BARE QECD ENGINE SHIPPING (856A2930G01) or (856A2930G02) from the engine.
7 _
Do the engine motoring procedure at max motoring speed for 4 minutes and shut down. NOTE : When you do the engine motoring procedure on stand, you ____ can connect a start cart hose to the starter shutoff valve with a locally manufactured adapter (Ref. TASK 80-11-00-040-045).
8 _
Make sure that VBV doors are closed (Ref. TASK 75-31-20-820001).
9 _
Cover VBV grills with vapor barrier film (Material No. CP2160).
10 __
Cap or cover all strut, piping, accessory openings and electrical connections.
11 __
Seal front and back openings/exposed areas with vapor barrier film (Material No. CP2160). It is recommended that desiccant bags (Material No. CP2098) be placed on either side of the engine, but not in contact with the engine hardware.
12 __
Cover full engine with COVER-FITTED BARE QECD ENGINE SHIPPING (856A2930G01) and attach tightly in place.
13 __
Raise stand base with a forklift.
14 __
Deploy, lower and pin caster wheels of stand base.
15 __
Lower stand base, remove forklift.
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Page 306 Nov 01/08
C F M 56-5B 16 __
Tow stand base CAUTION : MAXIMUM TOWING SPEED IS 3MPH (5KM/H). _______ a _
Tow stand base (dolly) with engine to storage area.
(2) Preservation - Non-operable Engines (a) Dry out and relubricate engine (Ref. TASK 72-00-00-100-007) if engine was ferried or subjected to an IFSD. (b) If engine is non-operable, consider the engine is preserved for 30 days from time of last operation. (3) Make sure that VBV doors are closed (Ref. TASK 75-31-20-820-001). (4) Cover VBV grills with vapor barrier film (Material No. CP2160). (5) Cap or cover all strut, piping and accessory openings and electrical connections. (6) Seal front and back openings/exposed areas with vapor barrier film (Material No. CP2160). It is recommended that desiccant bags (Material No. CP2098) be placed on either side of the engine, but not in contact with the engine hardware. (7) Cover full engine with COVER-FITTED BARE QECD ENGINE SHIPPING (856A2782G01/G02), and attach tightly in place if in a trailer or stand. If on wing, cover entrance of fan cowling and exit opening of tailpipe.
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Page 307 Nov 01/08
C F M 56-5B TASK 72-00-00-600-025 Preservation for a Period of up to 90 Days 1. __________________ Reason for the Job You must do the preservation procedure at the end of engine operation or not earlier than one day before an engine return to shop, when the engine must not operate for a period up to 90 days. This procedure is only applicable to on-wing installed engines. 2. ______________________ Job Set-up Information A. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
Material No.
CP5067
Material No.
CP5075
* engine oil (Ref. 70-30-00) * lubrication system corrosion preventive oil (Ref. 70-30-00) * corrosion preventive additive (Ref. 70-30-00)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 71-00-00-710-003 71-00-00-710-028 78-31-00-710-042
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Engine Automatic Start Engine Shutdown Operational Test of the Thrust Reverser System
3. __________ Job Set-up Subtask 72-00-00-869-067 A. Not Applicable
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Page 308 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-00-00-620-058 A. Preservation for a Period of up to 90 days. CAUTION : IF ENGINE WAS FERRIED OR SUBJECTED TO AN IN FLIGHT SHUTDOWN _______ (IFSD), ENGINE MUST BE DRIED OUT AND RELUBRICATED WITHIN 24 HOURS PER DRY OUT PROCEDURE OF THIS SECTION. CAUTION : UNDER NO CIRCUMSTANCES SHALL PRESERVATIVE OIL OR EQUIVALENT BE _______ SPRAYED INTO THE ENGINE INLET, CORE COMPRESSOR OR TURBINE, OR ENGINE EXHAUST. DIRT PARTICLES DEPOSITED ON THE WETTED BLADES AND VANES MAY ADVERSELY AFFECT ENGINE PERFORMANCE DURING SUBSEQUENT OPERATION. Subtask 72-00-00-620-068 B. Operable Engine Preservation - Period of Up to 90 days. (1) Do the servicing of the oil tank with an approved mixture of engine oil (Material No. CP2442) and at least 5 percent of lubrication system corrosion preventive oil (Material No. CP5067) or, as an alternative, 7 percent corrosion preventive additive (Material No. CP5075) by volume (Ref. TASK 12-13-79-610-002). NOTE : In both cases, a minimum of 19 l (5 USgal) of oil mixture is ____ necessary for preservation motoring. (2) Start the engine (Ref. TASK 71-00-00-710-003) and let it become stable at ground idle for 15-20 minutes, followed by a thrust reverser cycle (Ref. TASK 78-31-00-710-042) then stop the engine (Ref. TASK 71-00-00-710-028). (3) Cover the entrance to fan inlet cowl and exit openings. NOTE : For a period of up to 90 days, the preservation of the fuel ____ system is not necessary.
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Page 309 Nov 01/08
C F M 56-5B Subtask 72-00-00-620-069 C. Alternative Procedure. Operable Engine Preservation one Day before the Preservation Plan-Period of Up to 90 days. (1) Do the servicing of the oil tank with an approved mixture of engine oil (Material No. CP2442) and at least 5 percent of lubrication system corrosion preventive oil (Material No. CP5067) by volume (Ref. TASK 12-13-79-610-002). NOTE : In this case a minimum of 19l (5 US gal) of oil mixture is ____ necessary for preservation motoring. NOTE : It is not permitted to use corrosion preventive additive ____ (Material No. CP5075) for this procedure. NOTE : In this case, it is not necessary to do the ground idle run. ____ (2) Cover the entrance to fan inlet cowl and exit openings. NOTE : For a period of up to 90 days, the preservation of the fuel ____ system is not necessary.
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Page 310 Nov 01/08
C F M 56-5B TASK 72-00-00-600-007 Preservation for a Period of 30 to 365 Days. 1. __________________ Reason for the Job The preservation procedures are applied at the end of engine operation, before the engine goes back to the shop, and when the engine does not operate for a period of 30 to 365 days. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No No No No No R
specific specific specific specific specific specific specific specific
caps circuit breaker(s) safety clip(s) container 26.5 USgal (100 l) container 4 US gal (16 l) oil pressurizing cart plugs soft nose pliers Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 FADEC-ENGINE PRESERVATION FALSE METERING VALVE SIGNAL 1 COVER-FITTED BARE QECD ENGINE SHIPPING
856A1480 856A2930
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2098
Material No.
CP2160
Material No.
CP2442
Material No.
CP5066
Material No.
CP5067
USA MIL-D-3464 desiccant bags (Ref. 70-30-00) USA MIL-LP-378 vapor barrier film (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * fuel system corrosion preventive oil (Ref. 70-30-00) * lubrication system corrosion preventive oil (Ref. 70-30-00)
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Page 311 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP5075
* corrosion preventive additive (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-003 12-13-79-610-004 70-21-00-918-002 71-00-00-710-001 71-00-00-710-002 73-11-10-000-003 75-31-20-820-001 72-00-00-991-310 72-00-00-991-311 72-00-00-991-312
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Oil Tank Draining Draining of the Accessory Drive Section Seals (Preformed Packings and O-rings) and Gaskets Dry Motoring Check Wet Motoring Check Removal of the Fuel Pump and Filter Assembly Set the Variable Bleed Valve Assembly to the Closed position Fig. 301 Fig. 302 Fig. 303
3. __________ Job Set-up Subtask 72-00-00-865-054 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 1000EM1 49VU FUEL/LP VALVE/MOT1/ENG1 1QG A08 121VU FUEL/LP VALVE/MOT2/ENG1 3QG M25 FOR 1000EM2 49VU FUEL/LP VALVE/MOT1/ENG2 2QG A09 121VU FUEL/LP VALVE/MOT2/ENG2 4QG M26
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Page 312 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 301/TASK 72-00-00-991-310, 302/TASK 72-00-00-991-311, 303/TASK 72-00-00-991-312) Subtask 72-00-00-620-059 A. Preservation for a Period of 30 to 365 Days. CAUTION : IF ENGINE WAS FERRIED OR SUBJECTED TO AN IN FLIGHT SHUTDOWN _______ (IFSD), ENGINE MUST BE DRIED OUT AND RELUBRICATED WITHIN 24 HOURS PER DRY OUT PROCEDURE OF THIS SECTION. CAUTION : UNDER NO CIRCUMSTANCES SHALL PRESERVATIVE OIL OR EQUIVALENT BE _______ SPRAYED INTO THE ENGINE INLET, CORE COMPRESSOR OR TURBINE, OR ENGINE EXHAUST. DIRT PARTICLES DEPOSITED ON THE WETTED BLADES AND VANES MAY ADVERSELY AFFECT ENGINE PERFORMANCE DURING SUBSEQUENT OPERATION. (1) Operable Engine Preservation. CAUTION : DO NOT USE SILICONE BASE OILS IN THE FUEL SYSTEM. DAMAGE TO _______ THE ENGINE CAN BE CAUSED. (a) Drain the oil tank (Ref. TASK 12-13-79-610-003). (b) Do the servicing of the oil tank with a mixture of approved engine oil (Material No. CP2442) and 7 percent (by volume) corrosion preventive additive (Material No. CP5075) or with a mixture of approved engine oil (Material No. CP2442) and 5 percent (by volume) lubrication system corrosion preventive oil (Material No. CP5067) (Ref. TASK 12-13-79-610-002). A minimum of 19 l (5 USgal) of oil is necessary to do the motoring procedure of the engine during preservation. (c) When you do the engine motoring procedure without the accessories installed, make sure that the items that follow are installed. 1 _
Pad covers and gaskets on pads where accessories are normally installed.
2 _
Caps on the pad cavity drains to prevent the loss of engine oil.
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C F M 56-5B
Fuel Pump Inlet, PCR Port and LPTCC Fuel Supply Hose Location Figure 301/TASK 72-00-00-991-310 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 314 Nov 01/08
C F M 56-5B
Fuel Draining Figure 302/TASK 72-00-00-991-311 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 315 Nov 01/08
C F M 56-5B
Location of Fuel Pump Discharge Pressure Ports and Lubrication Unit Filters Drain Figure 303/TASK 72-00-00-991-312- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, Page 316 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-00-00
C F M 56-5B
Location of Fuel Pump Discharge Pressure Ports and Lubrication Unit Filters Drain Figure 303/TASK 72-00-00-991-312- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, Page 317 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-00-00
C F M 56-5B (d) Disconnect the fuel pump inlet tube. 1 _
Put a container 4 US gal (16 l) under the fuel pump inlet tube.
2 _
Remove the 4 bolts and the 4 washers which attach the fuel inlet tube to the fuel manifold duct. Let the fuel drain into the container.
3 _
Keep the gasket.
(e) Install a temporary line to the fuel pump inlet tube. Use the line to supply oil fuel system corrosion preventive oil (Material No. CP5066) at 50 psi (3.5 bar) maximum pressure. - The line is to be locally manufactured. For details: (Ref. Fig. 303/TASK 72-00-00-991-312) (f) Disconnect: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING _______ NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. 1 _
Disconnect the line from the PCR port on the HMU.
(g) Install a temporary hose drain line 118 in. (3 m) long from the HMU PCR port and put the hose to drain in a container 26.5 USgal (100 l) capacity. Attach the hose to prevent spillage. - The drain line is to be locally manufactured with a coupling tube welding P/N J382P06 (0.5625-18 diameter UNJF-3A Threads/material AMS 5645). (h) Do a dry motoring check for 30 seconds (Ref. TASK 71-00-00-710001). 1 _
Stop the engine motoring. Let the engine coast down.
(i) Remove the temporary drain line from the PCR port on the HMU.
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C F M 56-5B (j) Tighten coupling nut: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING _______ NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. 1 _
Install the PCR line to the PCR port. Torque coupling nut to between 180 and 200 lbf.in (2.03 and 2.26 m.daN).
(k) Do a wet motoring check for 5 seconds (Ref. TASK 71-00-00-710002) or until you see sprayed preservation fluid come out of the engine exhaust nozzle. Move the ENG MASTER control switch to OFF and motor for 2 minutes. NOTE : A minimum of 20 quarts (19 liters) of fuel system ____ corrosion preventive oil (Material No. CP5066) is necessary for preservation motoring. (l) Stop the engine motoring. Let the engine coast down. (m) Turn the fan rotor: WARNING : DO NOT TURN THE FAN ROTOR BY HAND UNLESS YOU ARE _______ WEARING HEAVY PROTECTIVE GLOVES. MAKE SURE YOU DO NOT SLIP WHEN YOU TURN THE FAN ROTOR. INJURY TO PERSONS CAN BE CAUSED. 1 _
Pull the fan rotor through a minimum of 2 complete turns if it did not turn during motoring.
(n) Remove the temporary oil supply line from the fuel pump inlet tube. (o) Make sure that the gasket is clean and serviceable (Ref. TASK 7021-00-918-002). (p) Install the 4 washers and the 4 bolts which attach the fuel inlet tube to the fuel manifold duct. (q) TORQUE the bolts to between 65 and 85 lbf.in (0.73 and 0.96 m.daN). (r) Make sure that VBV doors are closed (Ref. TASK 75-31-20-820-001).
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Page 319 Nov 01/08
C F M 56-5B (s) Install vapor barrier film (Material No. CP2160) on all open areas. (t) Install caps or plugs on all open engine areas, such as struts, pipes and accessory pads. (u) Put desiccant bags (Material No. CP2098) on either side of the engine. Do not allow the desiccant to touch the engine surfaces. NOTE : Replace the desiccant at regular times based on ____ atmospheric and weather conditions. Put the desiccant in the engine so that it will give sufficient protection. Install it so that you will have to move a minimum quantity of engine protective covers. (v) Put COVER-FITTED BARE QECD ENGINE SHIPPING (856A2930G01/GO2) over all of the engine. Make sure it is tight. (w) Put a tag on the engine to show the engine is preserved. (2) Non-operable Engine Preservation. (a) Drain the fuel system as follows. Collect the fuel in a satisfactory container. 1 _
Disconnect the filter upstream (inlet) pressure sensing tube from the fuel filter housing (this is the lower sensing tube connected to the fuel filter differential pressure switch at its other end). Let the fuel drain from the disconnected port.
2 _
Disconnect the fuel supply line. Install a cap on the fuel pump inlet tube.
3 _
Remove the fuel filter drain plug. Let the fuel drain from the filter.
4 _
Remove the fuel pump drain plug. Let the fuel drain from the pump.
5 _
Remove the fuel filter element. Discard the element (Ref. TASK 73-11-10-000-003).
(b) Preserve the engine as follows: CAUTION : DO NOT USE SILICONE BASE OILS IN THE FUEL SYSTEM. _______ DAMAGE TO THE ENGINE CAN BE CAUSED.
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Page 320 Nov 01/08
C F M 56-5B 1 _
Remove the PBP port plug from the fuel pump. Connect an oil pressurizing cart that contains fuel system corrosion preventive oil (Material No. CP5066) to the boost discharge pressure (PBP) port on the fuel pump. TORQUE the connector to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
2 _
Pump filtered (10 micron) oil into the fuel pump until it flows out of the fuel filter inlet pressure port and filter housing. Continue to pump the oil into the fuel pump until the oil that flows out does not have fuel mixed with it.
3 _
Connect the tube to the fuel filter inlet pressure port. TORQUE the coupling nut to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
4 _
Install a new fuel filter element. Install the bowl cover and drain plug. TORQUE the drain plug to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
5 _
Remove the fuel pump discharge (PHP) port plug.
6 _
Pump filtered (10 micron) oil into the PBP port until it flows out of the PHP port. Continue to pump the oil into the PBP port until the oil that flows out does not have fuel mixed with it.
7 _
Disconnect the cart from the PBP port.
8 _
Install the PBP port plug. TORQUE the plug to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
9 _
Connect the cart to the fuel pump discharge (PHP) port. TORQUE the connector to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
10 __
Disconnect: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE _______ COUPLING NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. a _
11 __
Disconnect the line (hose) from the HMU PCR port.
Install a temporary line to the PCR port and let it drain into the container.
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Page 321 Nov 01/08
C F M 56-5B 12 __
R R
R R
Disconnect the HJ8 electrical harness from the receptacle connector identified CHANNEL B on the HMU. Use soft nose pliers, if necessary.
13 __
Connect the FADEC-ENGINE PRESERVATION FALSE METERING VALVE SIGNAL (856A1480G01) to the HMU receptacle identified CHANNEL B in order to open the Fuel Metering Valve (FMV) in the HMU and allow the preservation oil to flow to the fuel nozzles.
14 __
Pump filtered (10 micron) oil through the PHP port until it flows out of the PCR temporary line. Continue to pump oil through the PHP port until the oil that flows out does not have fuel mixed with it.
15 __
Remove TOOL FADEC-ENGINE PRESERVATION FALSE METERING VALVE SIGNAL (856A1480G01) from the HMU receptacle connector, CHANNEL B.
16 __
Remove the temporary drain line from the PCR port of the HMU.
17 __
Tighten coupling nut: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE _______ COUPLING NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. a _
Re-connect the PCR line to the HMU PCR port. TORQUE coupling nut to between 180 and 200 lbf.in (2.03 and 2.26 m.daN).
18 __
Re-connect the HJ8 electrical harness to the HMU receptacle connector identified CHANNEL B.
19 __
Disconnect: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE _______ COUPLING NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. a _
Disconnect the LPTCC fuel supply hose from the HMU.
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C F M 56-5B 20 __
Install a temporary line to the LPTCC port of the HMU and let it drain into the container. Pump filtered (10 micron) oil through the PHP port until it flows out of the LPTCC temporary line. Continue to pump oil through the PHP port until the oil that flows out does not have fuel mixed with it.
21 __
Disconnect the cart from the PHP port.
22 __
Re-install the PHP port plug on the fuel pump. TORQUE plug to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
23 __
Tighten coupling nut: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE _______ COUPLING NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. a _
24 __
Remove the temporary line. Re-connect the LPTCC fuel supply hose to the HMU. TORQUE the coupling nut to between 180 and 200 lbf.in (2.03 and 2.26 m.daN).
Install caps on all fuel system ports. Make sure that all lines are connected and do not leak.
(c) Close the VBV doors (Ref. TASK 75-31-20-820-001). (d) Install vapor barrier film (Material No. CP2160) over the VBV bleed grills. (e) Drain the engine oil from the areas that follow: 1 _
Oil tank (Ref. TASK 12-13-79-610-003).
2 _
Accessory gearbox (AGB) (Ref. TASK 12-13-79-610-004).
3 _
Transfer gearbox (TGB) (Ref. TASK 12-13-79-610-004)
4 _
Supply filter on lubrication unit.
5 _
The oil supply lines between the lubrication unit and the sumps and gearboxes.
6 _
The scavenge oil lines between the sumps and gearboxes and the lubrication unit.
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Page 323 Nov 01/08
C F M 56-5B 7 _
Drain the oil from the oil supply or scavenge lines that have caps installed and that do not connect back to the lubrication unit. Install the caps after the oil has been drained.
(f) Preserve the lubrication system as follows: 1 _
R R R R R
Pump a mixture of approved engine oil (Material No. CP2442) and 7 percent (by volume) corrosion preventive additive (Material No. CP5075) or a mixture of approved engine oil (Material No. CP2442) and 5 percent (by volume) lubrication system corrosion preventive oil (Material No. CP5067) into the areas that follow. Use a cart or hand pump equipped with a volume measuring device and pump the oil at a maximum pressure of 50 psi (3.5 bar). Turn the fan and core rotors by hand while you pump the oil in. Continue to turn the rotors for 1 minute after all of the oil is added.
----------------------------------------------------------------------------| LOCATION | OIL QUANTITY | ----------------------------------------------------------------------------| Oil supply to the AGB | 6 qt (6 liters) | ----------------------------------------------------------------------------| Oil supply to the TGB | 1 qt (1 liter) | ----------------------------------------------------------------------------| Oil supply to the forward sump | 2 qt (2 liters) | ----------------------------------------------------------------------------| Oil supply to the aft sump | 1 qt (1 liter) | ----------------------------------------------------------------------------| Oil tank | 18 qt (17 liters) | ----------------------------------------------------------------------------| Lube and scavenge pumps | Wet parts | | (Oil supply and scavenge discharge) | |
R ----------------------------------------------------------------------------2 _
Install caps on all of the lube system ports, pipes, drains, vents, etc.
(g) Install vapor barrier film (Material No. CP2160) on all of the open engine sections. (h) Install a tag on each section of the engine to show that the lubrication and fuel system is preserved.
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C F M 56-5B (i) Put COVER-FITTED BARE QECD ENGINE SHIPPING (856A2782G01/G02) over the engine. Make sure that it is tight to keep unwanted material out of the engine. 5. Close-up ________ Subtask 72-00-00-865-055 A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 1000EM1 1QG, 3QG FOR 1000EM2 2QG, 4QG
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Page 325 Nov 01/08
C F M 56-5B TASK 72-00-00-600-008 Preservation Renewal Requirements. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-100-007 72-00-00-600-006 72-00-00-600-007 72-00-00-600-025
Engine Dry-out and Preservation for a Preservation for a Preservation for a
Re lubrication Period of up to 30 Days Period of 30 to 365 Days. Period of up to 90 Days
3. __________ Job Set-up Subtask 72-00-00-869-069 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-620-060 A. Preservation renewal requirements (1) Period up to 30 Days- Operable Engine (a) Two (2) renewals are allowed (Ref. TASK 72-00-00-600-006). (2) Period up to 30 Days - Non-operable engine NOTE : No renewal is allowed, the engine components should be ____ preserved (Ref. TASK 72-00-00-600-025) (Split engine or Engine Modules).
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C F M 56-5B (3) Period up to 90 Days - Operable Engine NOTE : Before represervation, it is recommended to prelubricate ____ engine sumps by hand-pumping oil through disconnected oil supply lines at lube unit and prelubricate lube unit by hand-pumping oil (Ref. TASK 72-00-00-100-007). (a) One (1) renewal is allowed (Ref. TASK 72-00-00-600-025). (4) Period 30 to 365 days - Operable Engine (a) Repeat the full procedure. Refer to the original 30 to 365 days preservation procedure (Ref. TASK 72-00-00-600-007). 1 _
Make sure that the engine is safely attached and protective cover is correctly in place.
(5) Period 30 to 365 days. Non-operable Engine (a) No renewal is allowed, engine must be serviced and operable.
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Page 327 Nov 01/08
C F M 56-5B TASK 72-00-00-600-009 Procedure for Exceeded Long Term Preservation Period. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information Not Applicable 3. __________ Job Set-up Subtask 72-00-00-869-071 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-620-061 A. If the engine preservation period is expired, refer to your CFMI Representative for instruction. NOTE : An engineering analysis must be used to analyse the situation ____ applicable to each special case. Some parameters are to be analysed such as total time after the preservation time limit, engine storage location and condition, humidity level, temperature variation, dessicant replacement interval, etc...
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 328 Nov 01/08
C F M 56-5B TASK 72-00-00-600-027 Depreservation 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 12-13-79-610-003 12-13-79-610-004 71-00-00-710-001 71-00-00-710-002
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Oil Tank Draining Draining of the Accessory Drive Section Dry Motoring Check Wet Motoring Check
3. __________ Job Set-up Subtask 72-00-00-869-072 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-630-051 A. Depreservation (1) Remove all moisture barrier material, seals, caps, covers, etc., as applicable, from the engine. (2) Connect fuel supply to the engine, and reconnect oil supply and scavenge lines if applicable. (3) Drain oil tank (Ref. TASK 12-13-79-610-003). NOTE : For an operable engine which is preserved for a period of up ____ to 90 days, this step is not necessary.
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Page 329 Nov 01/08
C F M 56-5B (4) Drain accessory drive assembly (Ref. TASK 12-13-79-610-004). NOTE : For an operable engine which is preserved for a period of up ____ to 90 days, this step is not necessary. (5) Fill the oil tank (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-1379-610-002). NOTE : For an operable engine which is preserved for a period of up ____ to 90 days, do a check for oil tank level and fill the tank, if necessary (Ref. TASK 12-13-79-610-002). (6) Do a wet motoring of the engine (Ref. TASK 71-00-00-710-002). (7) Do one or more dry motoring operations to remove the remaining fuel (Ref. TASK 71-00-00-710-001).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 330 Nov 01/08
C F M 56-5B ENGINE - GENERAL - INSPECTION/CHECK ___________________________________ TASK 72-00-00-200-006 Inspection/Check of Foreign Object Damage (FOD) (Bird Strike Included) WARNING : THERE IS A POSSIBLE HEALTH RISK TO PERSONNEL WHO DO MAINTENANCE TASKS _______ AFTER A BIRD STRIKE. THE SAFETY MEASURES THAT FOLLOW ARE RECOMMENDED: - USE DISPOSABLE GLOVES. - USE A DISPOSABLE COVERALL IF THERE IS A RISK OF BODY CONTACT WITH THE BIRD REMAINS. - DO NOT USE PRESSURIZED AIR OR WATER TO CLEAN THE PARTS WHICH WERE IN CONTACT WITH THE BIRD. - REMOVE THE BIRD REMAINS AND PUT THEM IN A PLASTIC BAG. - DO NOT TOUCH YOUR FACE, EYES, NOSE, ETC. WITH YOUR GLOVES. - REMOVE THE GLOVES AND THE DISPOSABLE COVERALL AND PUT THEM IN THE SAME PLASTIC BAG AS THE REMAINS. SEAL THE BAG. - DISCARD THE BAG AS YOU DO FOR USUAL GARBAGE. - CAREFULLY WASH YOUR HANDS WITH SOAP AND WATER. NOTE : In any case, operators and maintenance personnel should comply with the ____ recommendations of the local medical authorities. The requirements of the relevant medical authority take precedence over any CFM guidelines in these matters and their advice must always be sought. 1. __________________ Reason for the Job You must do a visual inspection and, when applicable, a borescope inspection when unwanted materials (foreign objects) have gone into the engine. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
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Page 601 Nov 01/08
C F M 56-5B B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-008 71-13-00-010-040 71-13-00-410-040 72-21-00-210-005 72-21-00-210-009 72-21-00-290-003 72-23-00-210-004 72-31-00-290-002 72-42-00-290-005 72-54-00-290-006 73-21-40-210-002 78-30-00-081-041 78-30-00-481-041
R
78-36-00-010-040 78-36-00-410-040 72-00-00-991-313
Power Assurance Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Inspection/Check of the Spinner Cone Inspect Fan Rotor Blades Installed on the Fan Disk Borescope Inspection of the Booster Rotor Blades, Stages 2,3,4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5 Visual Inspection of the Fan Frame Assembly Inspection of the High Pressure Compressor Rotor Assembly Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD Inspection of the Stage 4 Blades Visual Inspection of the T12 Temperature Sensor Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601
3. __________ Job Set-up Subtask 72-00-00-941-067 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
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Page 602 Feb 01/09
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-074 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-059 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-079 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-00-00-210-062 A. Visual Inspection NOTE : Visual inspection must be done without part removal. ____ (1) Possible damage to the spinner front and rear cones (Ref. TASK 72-2100-210-005). (2) General condition of the fan rotor blades (Ref. TASK 72-21-00-210009). (3) Wear of abradable material in fan inlet case (Ref. TASK 72-23-00-210004). (4) Condition of acoustical panels that may have been damaged as a result of interference with blade tip (Ref. TASK 72-23-00-210-004). (5) Condition of splitter fairing and booster inlet guide vanes (IGV) (Ref. TASK 72-23-00-210-004) and (Ref. TASK 72-21-00-210-005).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B (6) Condition of fan outlet guide vanes (OGV) and seals of fan OGV inner shroud (Ref. TASK 72-23-00-210-004). (7) Damage to T12 sensor probe (Ref. TASK 73-21-40-210-002). (8) Condition of exhaust and stage 4 LP turbine blades (Ref. TASK 72-5400-290-006). Subtask 72-00-00-280-057 B. Gaspath Inspection (1) FOD associated with normal engine parameters. NOTE : The borescope inspection may be delayed 25 hours or 10 cycles ____ (whichever comes first) provided FOD did not result in missing material to the fan blades. Service extension is only permitted on one engine in the event of a dual engine FOD. (a) Do the step that follows if one or more of these conditions apply: - FOD event has resulted in fan blade missing material/fan blade damage beyond serviceable limits. - FOD event struck fan blades radially inward of mid span shroud. - Evidence of debris has entered the booster inlet, ie: damage or debris on spinner front and rear cones, stage 1 booster vane or splitter fairing. 1 _
Do a borescope inspection of the HPC stages 1, 3 and 8 (Ref. TASK 72-31-00-290-002).
2 _
If damage is found inspect the other stages (Ref. TASK 72-3100-290-002).
3 _
Do a borescope of the combustion chamber dome assembly after a bird strike/ingestion event (Ref. TASK 72-42-00-290-005).
4 _
If the engine is PRE CFM SB 72-0418, do a borescope inspection of the stage 5 booster blades (Ref. TASK 72-21-00-290-003). Examine carefully the concave and convex sides of stage 5 booster blades in area E. (Ref. Fig. 601/TASK 72-00-00-991-313) Examine carefully blades around blade locks area.
R R R R R R R
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Page 604 Feb 01/09
C F M 56-5B
INTENTIONALLY BLANK
R 72-00-00 CES
Page 605 Nov 01/09
C F M 56-5B
PS3 Line Figure 601/TASK 72-00-00-991-313- 14 (SHEET 1)
R
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Page 606 Feb 01/09
C F M 56-5B
PS3 Line Figure 601/TASK 72-00-00-991-313- 24 (SHEET 2)
R
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Page 607 Feb 01/09
C F M 56-5B
PS3 Line Figure 601/TASK 72-00-00-991-313- 34 (SHEET 3)
R
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Page 608 Feb 01/09
C F M 56-5B
PS3 Line Figure 601/TASK 72-00-00-991-313- 44 (SHEET 4)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Feb 01/09
C F M 56-5B (2) FOD associated with abnormal engine parameters. (a) If FOD event was associated with surge, stall or flameout, do the steps which follow: 1 _
Do a borescope inspection of the booster (Ref. TASK 72-21-00290-003). - If the engine is PRE CFM SB 72-0418, do a borescope inspection of the stage 5 examine carefully the concave and convex sides of stage 5 booster blades in area E (Ref. Fig. 601/TASK 72-00-00-991-313) and blades around blade locks area.
2 _
Do a borescope inspection of the HPC stages 1, 3 and 8 (Ref. TASK 72-31-00-290-002).
3 _
If damage is found inspect the other stages (Ref. TASK 72-3100-290-002).
4 _
Do a borescope inspection of the combustion chamber dome area (Ref. TASK 72-42-00-290-005).
5 _
Do a Maximum Power Assurance check (Ref. TASK 71-00-00-710008).
R Subtask 72-00-00-210-063 C. Birdstrike Inspection NOTE : Before this inspection, perform steps 4.A Visual Inspection and ____ 4.B Gaspath Inspection. (1) Examine the external portions of the nacelle inlet at the point of impact and look for: (a) Cracks. (b) Signs of distortion. (c) Loose or missing fasteners.
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Page 610 Feb 01/10
C F M 56-5B (2) Examine the inlet cowl structure for secondary damage and look for: (a) Cracks. (b) Signs of distortion. (c) Delamination. (d) Loose or missing fasteners. (3) Examine all open ports in the inlet and look for: (a) Blockage. (4) If the FOD went through the inlet cowl structure, look for: (a) Damage to internal structure. (b) Damage to internal equipment. (5) If there is an indication of engine imbalance, examine the following nacelle components for signs of damage: (a) Inlet cowl. (b) Exhaust nozzle. (c) Fan cowl hinges and surrounding structure. (d) Fan cowl latches and surrounding structure. (e) Centerbody attachment rings and fasteners. 5. Close-up ________ Subtask 72-00-00-410-073 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 611 Nov 01/09
C F M 56-5B Subtask 72-00-00-440-059 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-078 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 612 Nov 01/09
C F M 56-5B TASK 72-00-00-200-007 Procedure After Engine Fire or Use of Fire-Extinguishing Agents WARNING : A LARGE NUMBER OF O-RINGS, GASKETS AND OTHER TYPES OF SEALS ARE MADE _______ OF VITON MATERIAL. VITON MATERIAL DECOMPOSES WHEN THE TEMPERATURE IS MORE THAN 750 DEG.F (400 DEG.C). ONE OF THE BY-PRODUCTS OF THIS DECOMPOSITION IS HYDROFLUORIC ACID. THIS ACID CAN CAUSE BAD BURNS. THUS, USE ACID-RESISTANT GLOVES IF YOU MUST REPLACE A VITON SEAL DURING MAINTENANCE AFTER A FIRE. 1. __________________ Reason for the Job You must do this procedure when fire-extinguishing agents have been used. NOTE : After any fire damage, the removal of the engine from the aircraft ____ for inspection is necessary. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
vacuum cleaner warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2155
USA MIL-C-25779D ardrox 6025 (Ref. 70-30-00)
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Page 613 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------29-00-00-280-006 71-00-00-000-042 71-00-00-710-001 71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 ESM 720000
Check of the Green or Yellow Hydraulic System after Operation in a Possible Cavitation Condition of the Engine Pump Removal of the Power Plant Dry Motoring Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-00-00-941-068 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
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Page 614 Nov 01/09
C F M 56-5B Subtask 72-00-00-010-075 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-060 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-080 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-00-00-280-072 A. If the crew closed the fire shut-off valve during operation of the fire extinguishers, do the check of the hydraulic system after Operation of the engine pumps in possible starvation or cavitation condition: (Ref. TASK 29-00-00-280-006). Check of the Green or Yellow Hydraulic System after Operation in a Possible Cavitation Condition of the Engine Pump. Subtask 72-00-00-280-058 B. Fire Extinguishing Agents Applied Externally NOTE : Do as soon as possible to avoid soak of contamination on engine ____ hardware. (1) If the engine has been exposed to fire extinguishing agents on external surfaces, perform the following where appropriate: (a) Carbon dioxide (CO2) contamination: 1 _
Cold sections: parts not exposed to heat require no maintenance action.
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Page 615 Nov 01/09
C F M 56-5B 2 _
Hot sections: engine parts which were at elevated temperatures when exposed to CO2 must be removed and checked.
(b) Chemical foam contamination: CAUTION : DO NOT ALLOW FOAM TO ENTER ANY ENGINE CAVITIES AS FOAM _______ RESIDUES MAY CAUSE CORROSION DAMAGE. 1 _
Wash exposed areas using clean, running water.
2 _
Scrub to remove all foam agents.
(c) Dry chemical powders contamination: CAUTION : DO NOT USE WATER. DRY AGENT COMBINES WITH WATER TO FORM _______ AN EVEN MORE CORROSIVE COMPOUND. DO NOT ALLOW AGENT TO ENTER ANY ENGINE CAVITIES. RESIDUES WILL CAUSE CORROSION DAMAGE. 1 _
Remove all powder residues from engine by utilizing vacuum cleaner and compressed air at 30-40 psi (205-275 kPa) as required.
2 _
If powder has turned to glaze due to elevated temperatures, scrub with ardrox 6025 (Material No. CP2155).
Subtask 72-00-00-280-059 C. Fire Extinguishing Agents Applied Internally (1) If the engine has been exposed to fire extinguishing agents on internal surfaces, perform the following where appropriate: (a) Carbon dioxide (CO2) contamination: Remove parts exposed to CO2 for inspection. (b) Chemical foam contamination. NOTE : Do as soon as possible to avoid soak of contamination on ____ engine hardware. 1 _
Flush with clean water and motor engine (if practicable) to remove foam residues.
2 _
Remove engine for disassembly, inspection and cleaning.
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Page 616 Nov 01/09
C F M 56-5B (c) Dry chemical powder contamination: 1 _
Remove all accessible loose powder using vacuum cleaner and compressed air at 30-40 psi (205-275 kPa).
2 _
If powder has turned to glaze due to elevated temperatures, rinse with ardrox 6025 (Material No. CP2155).
3 _
Dry-motor to clear and dry engine (Ref. TASK 71-00-00-710001).
4 _
Remove engine for disassembly and cleaning (Ref. TASK 71-0000-000-042) and (Ref. ESM 720000).
5. Close-up ________ Subtask 72-00-00-410-074 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-060 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-079 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
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Page 617 Nov 01/09
C F M 56-5B TASK 72-00-00-200-042 Procedure after Halogen Products Contamination 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
* engine oil (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 12-13-79-610-003 12-13-79-610-004 71-00-00-710-003 71-00-00-710-028 71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Oil Tank Draining Draining of the Accessory Drive Section Engine Automatic Start Engine Shutdown Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors
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Page 618 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-36-00-410-040
Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-00-00-941-132 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-172 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-090 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-173 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
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Page 619 Nov 01/09
C F M 56-5B 4. Procedure _________ Subtask 72-00-00-280-076 A. Halogen Products Contamination CAUTION : THE ENGINE CONTAINS NUMEROUS TITANIUM PARTS, THEREFORE HALOGEN _______ SUBSTANCES MUST NOT BE USED. (1) In flight: Use of nacelle extinguishing equipment (fire confirmed or not). No maintenance action. (2) On ground: (a) Use of nacelle extinguishing equipment only: open nacelle doors immediately to disperse halogen vapors. No further maintenance action is required. (b) If halogen fluids have been sprayed in the engine (in undetermined quantity), do the following steps. 1 _
If the engine can be restarted within 30 minutes. - Perform a ground run at Idle for 10 minutes (Ref. TASK 7100-00-710-003). - Drain oil tank (Ref. TASK 12-13-79-610-003). - Drain accessory gearbox (AGB) (Ref. TASK 12-13-79-610-004). - Reservice oil tank with new engine oil (Material No. CP2442) (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-13-79-610002).
2 _
If reignition and ground run cannot be performed before 30 minutes, perform as soon as possible, and within one hour, the following: - Start and motor the engine for 5 minutes (Ref. TASK 71-0000-710-003). - Stop motoring for 5 to 10 minutes (Ref. TASK 71-00-00-710028). - Re-start and motor engine for 5 minutes (Ref. TASK 71-00-00710-003). - Drain oil tank (Ref. TASK 12-13-79-610-003). - Drain accessory gearbox (AGB) (Ref. TASK 12-13-79-610-004). - Reservice oil tank with new engine oil (Material No. CP2442) (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-13-79-610002). - Perform a ground run at idle for 10 minutes within 3 hours (Ref. TASK 71-00-00-710-003).
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Page 620 Nov 01/09
C F M 56-5B 3 _
If motoring the engine is impossible within 3 hours, remove and return engine to shop for disassembly, cleaning and inspection.
5. Close-up ________ Subtask 72-00-00-410-175 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-090 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-176 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
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Page 621 Nov 01/09
C F M 56-5B TASK 72-00-00-200-043 Procedure after Volcanic Ash, Dust, or Sand Ingestion 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 12-13-79-610-003 12-13-79-610-004 12-13-79-610-005 71-00-00-710-001 71-13-00-010-040 71-13-00-410-040 72-31-00-290-002 72-42-00-290-005 72-51-00-290-004 R R R R
72-52-00-290-001 72-52-00-290-001 72-52-00-290-004 72-52-00-290-004
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Oil Tank Draining Draining of the Accessory Drive Section Flushing of Oil System Dry Motoring Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Inspection of the High Pressure Compressor Rotor Assembly Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD Borescope Inspection of High-Pressure Turbine Nozzle Assembly Borescope Inspection of HPT Blades (from the front and the rear) Borescope Inspection of HPT Blades (from the front and the rear) Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------73-21-40-210-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 79-21-10-920-002 TSM 77 PB 101
Visual Inspection of the T12 Temperature Sensor Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Remove and Discard Supply Filter
3. __________ Job Set-up Subtask 72-00-00-941-133 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-174 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-091 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 623 Nov 01/09
C F M 56-5B Subtask 72-00-00-010-175 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-00-00-280-077 A. Volcanic Ash, Dust, or Sand Inspection (1) The following requirements are subsequent to incidents of engines flown or operated in volcanic ash, dust, or sand. (a) Visually check engine inlet and exhaust areas for evidence of damage or excessive erosion. (b) Borescope inspect High Pressure Compressor and High Pressure Turbine for evidence of the following (Ref. TASK 72-31-00-290002), (Ref. TASK 72-42-00-290-005), (Ref. TASK 72-51-00-290-004), (Ref. TASK 72-52-00-290-001) or (Ref. TASK 72-52-00-290-001), (Ref. TASK 72-52-00-290-004) or (Ref. TASK 72-52-00-290-004): NOTE : Inspect all stages of the HPC. The aft stages of the HPC ____ will be most effected by erosion. NOTE : Inspect the HPT nozzle vanes and the HPT blades for ____ erosion and accumulation of solidified material. Sufficient amounts of material accumulation on the HPT nozzle vanes can cause a reduced engine stall margin. 1 _
Excessive erosion.
2 _
Foreign object damage (FOD).
3 _
Build-up of ash, dust, or sand deposits that have solidified on the HPT nozzle vanes and HPT blades. a _
If material has solidified on the HPT vanes or blades, contact CFM.
(c) Oil system. 1 _
Replace scavenge oil filter (Ref. TASK 79-21-10-920-002).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 624 Nov 01/09
C F M 56-5B 2 _
Drain oil (Ref. TASK 12-13-79-610-003) and (Ref. TASK 12-1379-610-004).
3 _
Replace oil (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-1379-610-002).
(d) Monitor engine operation to determine if a shift in performance parameters has occurred. If parameters are abnormal, (Ref. TSM 77 PB 101). (e) Check for proper cooling of ignition leads. (f) Check condition of T12 temperature sensor (Ref. TASK 73-21-40210-002). (g) Flush accessory and transfer gearboxes (Ref. TASK 12-13-79-610005). (h) Check for fouling of LPT case air cooling Scoop and precooler Scoop on Thrust Reverser (T/R). (2) The following requirements are subsequent to incidents of engines NOT flown or operated in volcanic ash, dust, or sand, but have been exposed to volcanic ash, dust, or sand on the ground. NOTE : Do not water wash an engine that has been exposed to volcanic ____ ash, dust, or sand. Particles may accumulate in the HPT nozzle vanes and HPT blade cooling paths. Material may accumulate in the HPC rotor spools and cause rotor imbalance. (a) Inspect the engine inlet and exhaust for accumulation of ash, dust, or sand particles. 1 _
Vacuum any particles from accessible areas of the inlet and exhaust.
2 _
Dry motor the engine for two minutes (Ref. TASK 71-00-00-710001).
3 _
Borescope the HPC and HPT at 6o clock positions to inpect for ash, dust, or sand (Ref. TASK 72-31-00-290-002), (Ref. TASK 72-42-00-290-005), (Ref. TASK 72-51-00-290-004), (Ref. TASK 72-52-00-290-001) or (Ref. TASK 72-52-00-290-001), (Ref. TASK 72-52-00-290-004) or (Ref. TASK 72-52-00-290-004).
4 _
If loose material is still present in the engine flow path, dry motor the engine for two more minutes.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 625 Nov 01/09
C F M 56-5B 5 _
Repeat the borescope inspection and dry motoring until all material has been removed.
(b) Oil System. 1 _
Replace scavenge oil filter (Ref. TASK 79-21-10-920-002).
2 _
Drain oil (Ref. TASK 12-13-79-610-003) and (Ref. TASK 12-1379-610-004).
3 _
Replace oil (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-1379-610-002).
(c) Monitor engine operation to determine if a shift in performance parameters has occured. If parameters are abnormal, (Ref.TSM 77 PB 101). (3) Do a one time repeat borescope inspection at an A-check or 400-800 cycles to ensure HPT nozzle vane and HPT blade integrity. 5. Close-up ________ Subtask 72-00-00-410-177 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-091 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 626 Nov 01/09
C F M 56-5B Subtask 72-00-00-410-178 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 627 Nov 01/09
C F M 56-5B TASK 72-00-00-200-008 Inspection/Check After the Engine has Exceeded the Operational Limits 1. __________________ Reason for the Job If an exceedance occurs, the DMC memorizes in its memory the maximum value reached during the last flight leg for N1, N2 and EGT. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 12-13-79-610-003 12-13-79-610-004 71-00-00-710-001 71-00-00-710-008 71-13-00-010-040 71-13-00-410-040 72-00-00-100-008 72-21-00-210-005 72-21-00-290-003 72-23-00-210-003 72-23-00-210-004 72-31-00-290-002 R R
72-52-00-290-001
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Oil Tank Draining Draining of the Accessory Drive Section Dry Motoring Check Power Assurance Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Engine Washing Requirements Inspection/Check of the Spinner Cone Borescope Inspection of the Booster Rotor Blades, Stages 2,3,4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5 Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material Visual Inspection of the Fan Frame Assembly Inspection of the High Pressure Compressor Rotor Assembly Borescope Inspection of HPT Blades (from the front and the rear)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 628 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-52-00-290-004 72-54-00-290-005 72-56-00-210-002 77-00-00-710-042 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 TSM 73-00-00-810-865 TSM 73-00-00-810-866 TSM 77-00-00-810-849 TSM 77-00-00-810-850 TSM 79-00-00-810-805 TSM 79-00-00-810-818 TSM 79-00-00-810-836 TSM 79-00-00-810-837 72-00-00-991-305 72-00-00-991-306 72-00-00-991-307 72-00-00-991-323 72-00-00-991-324
Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) Inspection of the Stage 1-3 Blades Inspection/Check of the Turbine Frame Assembly Reset of the N1, N2 and EGT Max Pointers Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Engine 1 or 2 Stall/Surge Stall of the engine 1 or 2 / Audible stall / Engine surge EGT Overlimit on Engine 1 or 2 N1 Overlimit on Engine 1 or 2 Abnormal Oil Temperature on Engine 1 or on Engine 2 Incorrect Oil Quantity Level on Engine 1 Low Oil Pressure Indication on Engine 1 Low Oil Pressure Indication on Engine 2 Fig. 602 Fig. 603 Fig. 604 Fig. 605 Fig. 606
3. __________ Job Set-up Subtask 72-00-00-941-069 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 629 Nov 01/09
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-076 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-061 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-081 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 602/TASK 72-00-00-991-305, 603/TASK 72-00-00-991-306, 604/TASK 72-00-00-991-307) Subtask 72-00-00-290-052 A. Checks to be Done after a Hot Start NOTE : Starting exhaust gas temperature (EGT) (T495) limits are given. ____ (1) Area A: EGT (T495) is more than 725 deg.C but less than or equal to 750 deg.C for a period of less than 30 seconds. (a) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight (Ref. TSM TASK 7700-00-810-849). (b) A maximum service extension of 5 flight cycles is permitted before you must correct the problem.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 630 Nov 01/09
C F M 56-5B
Operational EGT (T495) Limits for Ground Starting and Sub-Idle Operation Figure 602/TASK 72-00-00-991-305 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 631 Nov 01/09
C F M 56-5B
Operational EGT (T495) Limits Above Idle Figure 603/TASK 72-00-00-991-306 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 632 Nov 01/09
C F M 56-5B
Oil Pressure Versus Core Speed (N2) Figure 604/TASK 72-00-00-991-307 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 633 Nov 01/09
C F M 56-5B (2) Area B: EGT (T495) is more than 750 deg.C but less than or equal to 800 deg.C for less than 10 seconds. (a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope ports S16 and S17) (Ref. TASK 72-54-00-290-005) and (Ref. TASK 72-52-00-290-004). (b) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight (Ref. TSM TASK 7700-00-810-849). (c) A maximum service extension of one start is permitted and, if that start is satisfactory, 1 cycle is permitted before you must correct the problem. (3) Area C: Stop the start and do these checks before you try to start the engine again. CAUTION : HPT BLADES THAT HAVE HAD ENGINE EGT MORE THAN 990 DEG.C _______ (1814 DEG.F) CANNOT BE REPAIRED. THE ENGINE MUST BE REMOVED AND RETURNED TO SHOP FACILITY TO EXAMINE FOR DAMAGE. (a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope ports S16 and S17). (Ref. TASK 72-52-00-290004) and (Ref. TASK 72-54-00-290-005) (b) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight (Ref. TSM TASK 7700-00-810-849). (4) If EGT is more than 950 deg.C reset the EGT max pointer after you correct the problem (Ref. TASK 77-00-00-710-042). Subtask 72-00-00-290-053 B. Checks to be Done if an Overtemperature Condition Occurs at all Engine Ratings other than Starting (Ref. Fig. 603/TASK 72-00-00-991-306) NOTE : There can be many causes for an EGT overtemperature condition, ____ such as: - engine warm up before take off is not sufficient - full rated takeoff in hot day condition - dirty compressor airfoils, engine deterioration (low remaining EGT margin), engine bleed selected during take off after throttle push
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 634 Nov 01/09
C F M 56-5B - FOD, engine system malfunction (for example: VBV actuation), or engine hardware malfunction (for example: airfoil failure, hot air leak, etc.). NOTE : Some positive EGT margin can result by doing an engine gas path ____ water wash (Ref. TASK 72-00-00-100-008). This makes engine performance better but is temporary. It is not a long term repair for high EGT or engine deterioration. Read the DMU Exceedance Report, the DMC Max Value Report and/or the ECU data by the Menu Mode Specific Data Report (if available) to find the maximum EGT value that was recorded during the event, as well as the amount of time of the overtemperature condition. If none of these reports are available, get the data from the AIDS or DFDR. (1) Follow these instructions for the applicable power range where the engine overtemperature occurred: (a) Takeoff (Ref. Fig. 605/TASK 72-00-00-991-323) NOTE : Consider EGT indicated max value and physical max time ____ value, as printed out from PWR SETTING MAX VALUES report. 1 _
Find if there was an Area A, B or C takeoff exceedance.
(b) Climb, Cruise or Max Continuous (Ref. Fig. 606/TASK 72-00-00-991-324) NOTE : Consider EGT indicated max value and physical max time ____ value, as printed out from PWR SETTING MAX VALUES report. NOTE : If the flight crew has logged an EGT indication above the ____ 915 degrees C climb, cruise, or max continuous power limit, maintenance personnel should be concerned with the total time the engine was at 915 degrees C or above regardless of the time that has elapsed since takeoff power was reduced to climb, cruise or max continuous power.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 635 Nov 01/09
C F M 56-5B
Operational EGT (T495) Limits at Take Off Figure 605/TASK 72-00-00-991-323 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 636 Nov 01/09
C F M 56-5B
Operational EGT (T495) Limits at Climb, Cruise or MAX Continuous Figure 606/TASK 72-00-00-991-324 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 637 Nov 01/09
C F M 56-5B (2) Area A: (Unusual Operation) (a) If the EGT overtemperature condition is identified to be caused by not having sufficient engine warm-up before take off: 1 _
No troubleshooting is necessary. NOTE : Warm-up time is not sufficient if engine is as follows: ____ - shut down for more than 4 hours - operated at idle or above for less than 15 minutes
(b) If the EGT overtemperature condition is identified to be caused by engine deterioration (low remaining EGT margin), or engine bleed selected during take off after throttle push: 1 _
No troubleshooting is necessary.
(c) If the cause of the EGT overtemperature condition cannot be identified by the above, or you think it could have been caused by FOD or engine hardware failure: 1 _
Do troubleshooting for EGT OVERLIMIT . (Ref. TSM TASK 77-0000-810-849)
2 _
Troubleshooting can be deferred for five overtemperature conditions in Area A but can not go over 25 cycles after the first overtemperature condition. NOTE : There are known engine malfunctions that can lead to an ____ EGT overtemperature condition and thus a Class 1 ECAM warning message. These malfunctions require troubleshooting prior to engine operation. (Example: VBV ACT, HMU , CHECK HOT AIR LEAKS, NAC TEMP SENSOR, etc.).
(d) You can have a maximum of 20 overtemperature conditions in Area A, before engine removal is required and sent to a shop for a full performance overhaul workscope.
R R R R R R R R
NOTE : EGT exceedences above the EGT red line limit will make ____ maintenance troubleshooting actions necessary. The EGT exceedance may be caused by a system related problem or a performance deterioration. In case of performance deterioration related exceedance, engine must be sent to shop for performance overhaul.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 638 Nov 01/09
C F M 56-5B (3) Area B: (Unusual Operation) (a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope port S17) (Ref. TASK 72-52-00-290-001) and (Ref. TASK 72-54-00-290-005). (b) Do troubleshooting for EGT OVERLIMIT (Ref. TSM TASK 77-00-00810-849). 1 _
Troubleshooting can be deferred for 10 cycles unless the fault repeats.
(c) You can have a maximum of 20 overtemperature conditions in Areas A and B together or 10 overtemperature conditions in Area B alone, before engine removal is required and sent to a shop for a full performance overhaul workscope.
R R R R R R R R
NOTE : EGT exceedences above the EGT red line limit will make ____ maintenance troubleshooting actions necessary. The EGT exceedance may be caused by a system related problem or a performance deterioration. In case of performance deterioration related exceedance, engine must be sent to shop for performance overhaul. (4) Area C: (Unserviceable) (a) Remove and return engine to a shop facility to examine damage. (b) One non-revenue flight for fly-back is permitted before the engine must be removed, if there is no damage above the serviceable limits: 1 _
Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope port S17) (Ref. TASK 72-52-00-290-001) and (Ref. TASK 72-54-00-290-005).
2 _
Do a troubleshooting for EGT OVERLIMIT (Ref. TSM TASK 77-0000-810-849).
(5) If the maximum EGT is more than 950 deg.C, the EGT maximum pointer must be set again after the corrective action is done (Ref. TASK 7700-00-710-042).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 639 Nov 01/09
C F M 56-5B Subtask 72-00-00-280-062 C. Checks to be Performed when Abnormal Rotation Speeds are Reached (1) Overspeed (a) The speed limits are as follows: 1 _
Fan speed (N1): 104 percent
2 _
Core speed (N2): 105 percent
(b) Fan (N1) overspeed inspections: 1 _
If fan is operated at speeds from 104 percent to 105.8 percent, the engine must be inspected as follows: - Review available data to understand reason for the overspeed. - Correct the cause. Troubleshoot. (Ref. TSM TASK 77-00-00810-850) - Visually inspect the engine inlet, the fan blades, the exhaust nozzle, and the stage 4 LPT blades. - Check the fan rotor for freedom of rotation and shingling of blades (Ref. TASK 72-21-00-210-005). - Inspect abradable material in fan inlet case for rubbing (Ref. TASK 72-23-00-210-003). - Borescope inspect the stage 5 of booster rotor blades (borescope port S05 at 3:30 oclock location and at the rear end of booster) (Ref. TASK 72-21-00-290-003). - Borescope inspect stage 1 LPT blades (borescope ports S16 and S17) (Ref. TASK 72-54-00-290-005).
2 _
If fan speed exceeds 105.8 percent, remove engine and return to shop for overspeed inspection.
3 _
If fan speed has exceeded 104 percent the N1 max pointer must be reset after corrective action has been performed (Ref. TASK 77-00-00-710-042).
(c) Core engine (N2) overspeed inspections: 1 _
If core engine rotor is operated at speeds from 105 percent to 105.8 percent the engine must be inspected as follows: - Inspect exhaust nozzles for particles. - Borescope inspect stages 1, 3, and 8 HPC blades (borescope ports S2, S4 and S9) (Ref. TASK 72-31-00-290-002).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 640 Nov 01/09
C F M 56-5B - Borescope inspect HPT blades (borescope ports S16 and S17) (Ref. TASK 72-52-00-290-004). 2 _
If core engine rotation speed exceeds 105.8 percent, shutdown, remove engine and return to shop for overspeed inspections.
3 _
If core engine rotation speed has exceeded 105 percent the N2 max pointer must be reset after corrective action has been performed (Ref. TASK 77-00-00-710-042).
Subtask 72-00-00-210-064 D. Checks Required after Lubrication System Operation Limits are Exceeded (1) Oil pressure (a) The Figure gives the relation between oil pressure and N2 speed. (b) Critical zone A, with oil pressure lower than 13 psi (0,90 bar). 1 _
If engine operation with no oil or very low pressure has exceeded any one of the following, remove engine and return to shop. - Take-off power for 10 seconds. - Cruise power for 10 seconds. - Idle (flight or ground) for 30 seconds.
2 _
If engine not exceeding time limits per step 1_ has been operated with no oil pressure or very low pressure, remove all oil filters, screens, magnetic plug and chip detectors, and check for presence of metal/debris. If no suspect metal debris is observed, troubleshoot (Ref. TSM TASK 79-00-00-810-836) or (Ref. TSM TASK 79-00-00-810-837).
(c) Zones B and/or D: Troubleshoot (Ref. TSM TASK 79-00-00-810-836) or (Ref. TSM TASK 79-00-00-810-837). (2) Supply Oil Temperature (a) Maximum oil temperature for continuous engine operation is 140 deg.C (284 deg.F). (b) Engine operation with oil between 140 deg.C (284 deg.F) and 155 deg.C (311 deg.F) is allowed for 15 minutes.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 641 Nov 01/09
C F M 56-5B (c) Above 155 deg.C (311 deg.F) the oil system must be drained (Ref. TASK 12-13-79-610-003) and (Ref. TASK 12-13-79-610-004) and serviced (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-13-79-610002). Troubleshoot (Ref. TSM TASK 79-00-00-810-805). (d) After abnormally high oil temperature, check that the supply filter, common scavenge filter and chip detectors of lube unit are free of metal particles. If metal particles are present, remove and disassemble the engine for inspection. (3) Oil Consumption (a) Normal oil consumption is not expected to exceed 0.57 l.hr (approximately 0.6 quart.hr) (0.15 USgal.hr). (b) As soon as one of the following cases occur, Troubleshooting (Ref. TSM TASK 79-00-00-810-818) or (Ref. TSM TASK 79-00-00-810818) must be performed: - Oil consumption exceeds 0.85 l.hr (approximately 0.9 quart.hr) (0.22 USgal.hr). - Oil consumption substantially exceeds that of the other operating engines. - Oil consumption indicates a gradual increasing trend. - Oil consumption indicates sudden step increase. (c) The maximum serviceable oil consumption rate is limited to 1.5 l.hr (approximately 1.5 quart.hr) (0.40 USgal.hr). Consumption monitoring. - Troubleshooting (Ref. TSM TASK 79-00-00-810-818) or (Ref. TSM TASK 79-00-00-810-818) must be performed as soon as the oil consumption rate overshoots the limit. - If the result of the troubleshooting is not conclusive and no action can be taken to reduce the oil consumption rate, the engine has to be replaced. Subtask 72-00-00-210-104 E. IFSD time limitation (1) Dry-out the engine if you can not restart within 24 hours and after each ferry flight.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 642 Nov 01/09
C F M 56-5B Subtask 72-00-00-210-065 F. Checks Required after Rough Landing Limits are Exceeded (1) General (a) The following procedure is to be used following a rough landing. (2) Visual Inspection/Checks. Inspect the following: (a) Wear of abradable material in fan inlet case at the 6 and 12 oclock positions (Ref. TASK 72-23-00-210-003). (b) Engine mounting pads forward and aft (Ref. TASK 72-23-00-210-004) and (Ref. TASK 72-56-00-210-002). (c) Accessory and hardware attachments for metal fractures or excessive distortion. (d) Piping connections for leaks. (e) Lines, tubing for possible interferences. (f) Turbine frame aft flange (Ref. TASK 72-56-00-210-002). (3) Borescope Inspection/Checks. Inspect the following: (a) Stages 1, 3, and 8 HPC blades (borescope ports S2, S4, and S9). (Ref. TASK 72-31-00-290-002). Subtask 72-00-00-210-066 G. Inspection after Stall (1) General (a) If a stall or suspected stall has occurred, the following inspection and troubleshooting must be done (Ref. TSM TASK 73-0000-810-865) or (Ref. TSM TASK 73-00-00-810-866). (2) Visual Inspection/Checks. Inspect the following: (a) Fan rotor and abradable material (Ref. TASK 72-21-00-210-005) and (Ref. TASK 72-23-00-210-003).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 643 Nov 01/09
C F M 56-5B (3) Borescope Inspection/Checks. Inspect the following: (a) For engine stalls in the start region, or for off-idle stalls which result in engine rollback into sub-idle N2 range: 1 _
If the start region EGT limit of 725 deg.C was exceeded, borescope inspect HPT blades and stage 1 LPT blades (borescope ports S16 and S17) (Ref. TASK 72-52-00-290-004) and (Ref. TASK 72-54-00-290-005). (Ref. Fig. 602/TASK 72-00-00-991-305)
2 _
If the cause of the stall is not known, borescope inspect stages 1, 3 and 8 HPC blades (borescope ports S2, S4 and S9) (Ref. TASK 72-31-00-290-002).
(b) For engine stalls at or above idle which do not result in engine rollback into sub-idle N2: 1 _
Borescope inspect HPT blades and stage 1 LPT blades (borescope ports S16 and S17) (Ref. TASK 72-52-00-290-004) and (Ref. TASK 72-54-00-290-005). (Ref. Fig. 603/TASK 72-00-00-991-306)
2 _
If the cause of the stall is not known, borescope inspect stage 5 of booster rotor blades (borescope port S05 at 3:30 oclock location and at the rear end of booster) (Ref. TASK 72-21-00-290-003) and stages 1, 3 and 8 HPC blades (borescope ports S2, S4 and S9) (Ref. TASK 72-31-00-290-002).
Subtask 72-00-00-210-067 H. Excessive Vertical Loading Greater than the Specified Limits (1) General (a) Engine suspected of experiencing excessive g loading during transportation must be given the following inspection. The inspection consists of visual and manual checks followed by a functional check. (2) Check engine for obvious damage as follows: (a) Visually inspect for buckling, deformation or cracking in engine skin and flange areas around transportation mounts.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 644 Nov 01/09
C F M 56-5B (b) To turn fan rotor by hand: WARNING : USE CARE TO AVOID PERSONAL INJURY WHEN YOU MANUALLY _______ TURN THE FAN ROTOR. ASSURE SAFE FOOTING.USE HEAVY PROTECTIVE GLOVES 1 _
Turn fan rotor by hand ; check for bearing roughness, unusual noises and binding. Clear indications of this type of damage require engine disassembly. NOTE : Light rubbing of seals and shrouds is normal. ____
(c) If seal or shroud interference is found and appears minimal, the engine can be considered serviceable after completing a successful dry motoring check (Ref. TASK 71-00-00-710-001) and power assurance check (Ref. TASK 71-00-00-710-008). (d) After functional test run, check scavenge screens and master magnetic chip detector for the presence of metal particles caused by bearing damage. Return engine to shop for inspection if unusual deposits are found. 5. Close-up ________ Subtask 72-00-00-410-075 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-061 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 645 Nov 01/09
C F M 56-5B Subtask 72-00-00-410-080 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 646 Nov 01/09
C F M 56-5B TASK 72-00-00-200-009 Off-Schedule Vane Replacement 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-00-00-941-070 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 647 Nov 01/09
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-077 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-062 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-082 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-00-00-210-070 A. Vane scheduling errors can occur if the lever arms which control the compressor stator vanes are damaged or disassembled. (1) When the vane scheduling errors are greater than 4 degrees, you must replace all HPC blades on one stage forward of and 2 stages aft of the stage which has off-schedule vanes.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 648 Nov 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-00-00-410-076 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-062 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-081 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 649 Nov 01/09
C F M 56-5B TASK 72-00-00-200-025 Over-Serviceable-Limit Extensions 1. __________________ Reason for the Job This TASK is applicable to NON /P engines. It can occur that specific defects do not agree with the Maximum Serviceable Limits, and that the maintenance facilities, at a given location, are not sufficient to do the necessary corrective actions. In these circumstances, limit extensions will permit to send the engine where correction is possible, or to schedule the necessary maintenance in the extension period. NOTE : The limit extensions are one-time extensions only. Applicable ____ hardware action is necessary at the completion of the extended serviceable period. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-210-006 72-21-00-210-009 72-23-00-210-003 79-00-00-210-003 72-00-00-991-308 72-00-00-991-309 72-00-00-991-321
Inspect Fan Rotor Blades Removed from the Fan Disk. Inspect Fan Rotor Blades Installed on the Fan Disk Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material Visual Inspection of the Oil System Fig. 607 Fig. 608 Fig. 609
3. __________ Job Set-up Subtask 72-00-00-941-071 A. Not applicable
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 650 Nov 01/09
C F M 56-5B 4. Procedure _________ (Ref. Fig. 607/TASK 72-00-00-991-308, 608/TASK 72-00-00-991-309, 609/TASK 72-00-00-991-321) Subtask 72-00-00-210-071 A. Over-serviceable-limit Extensions ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------1. Fan and booster A. Spinner front cone (1) Damaged surface protection greater than 50 percent of total surface
50 cycles
(2) Corrosion marks (white mushroom pattern) before part removal
A continuation in service of 100 cycles maximum is permitted
B. Spinner rear cone (1) Oil wetting at inner of spinner cone or fan disk or forward fan shaft
50 cycles
(2) Seal ring tear: any number if cumulated length is more than 0.4 in. (10 mm)
50 cycles
C. Fan blade (1) Fully missing molydag on inner faces of the platforms
250 cycles
(2) Flaking of Cu.Ni.In coating on blade dovetail pressure faces (contact areas), up to 10 percent if there is no indication of wear on base material
Examine blades for serviceability. (Ref. TASK 72-2100-210-006) 1200 cycles after relubrication. Repeat extension is permitted
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 651 Nov 01/09
C F M 56-5B
Booster Rotor and Stator Damage Extended Figure 607/TASK 72-00-00-991-308 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 652 Nov 01/09
C F M 56-5B
INTENTIONALLY BLANK
R 72-00-00 CES
Page 653 Nov 01/09
C F M 56-5B
Extended Vanes Damage Limits Figure 608/TASK 72-00-00-991-309- 12 (SHEET 1) EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 654 Nov 01/09
C F M 56-5B
Extended Vanes Damage Limits Figure 608/TASK 72-00-00-991-309- 22 (SHEET 2) EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 655 Nov 01/09
C F M 56-5B
Inspection/Check of the Fan Outlet Guide Vanes (OGV) Figure 609/TASK 72-00-00-991-321- 13 (SHEET 1) EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 656 Nov 01/09
C F M 56-5B
Inspection/Check of the Fan Outlet Guide Vanes (OGV) Figure 609/TASK 72-00-00-991-321- 23 (SHEET 2) EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 657 Nov 01/09
C F M 56-5B
Inspection/Check of the Fan Outlet Guide Vanes (OGV) Figure 609/TASK 72-00-00-991-321- 33 (SHEET 3) EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 658 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Flaking of Cu.Ni.In coating on blade dovetail 400 cycles after pressure faces (contact areas), more than 10 relubrication. percent and less than 50 percent if there is Repeat extension is no indication of wear on base material not permitted (4) Shingling at mid span shrouds
Turn the shingled blades to the 12 oclock position and unshingle with hand force or by using a piece of wood. Examine blades for serviceability (Ref. TASK 72-2100-210-009). Remove and send the shingled blades to a shop for a dimensional and an F.P.I. inspection in less than 50 cycles.
(5) Nicks, dents, scratches and sheared edges on midspan shroud surfaces up to 0.035 in. (0.89 mm) deep if defects are not in the midspan shroud to airfoil fillet radius
50 cycles
(6) Missing or damaged hard coating on midspan shroud pressure faces more than 20 percent but less than 40 percent of coated area
50 cycles
D. Fan disk (1) Wear greater than 50 percent of area on disk dovetail pressure faces
100 cycles
E. Booster rotor blade for: (1) Piece missing:
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 659 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------any number in area G, at leading edge and 50 cycles/75 hours trailing edge tip corners, 0.8 in. (20 mm) radial and 0.5 in. (12.5 mm) axial (2) Cracks and tears in area G, 0.8 in. (20 mm) from tip: any number, less than 0.8 in. (20 mm) radial and less than 0.492 in. (12.5 mm) axial
50 cycles/75 hours
(3) Wear or local distortion of T/E and L/E tips if less than 15 blades, 0.984 in. (25 mm) radial and 0.59 in. (15 mm) axial
100 cycles/150 hours
(4) Nicks, dents, scratches for area E: any number, less than 0.059 in. (1.5 mm) in diameter, protrusion acceptable, not thru
50 cycles/75 hours
(5) Nicks, dents, scratches for airfoil out of area E, not L/E and T/E: any number, less than 0.236 in. (6 mm) in diameter, protrusion acceptable
50 cycles/75 hours
(6) Nicks, dents, scratches out of area E on L/E and T/E: maximum axial length less than 0.059 in. (1.49 mm)
50 cycles/75 hours
(7) Distorted L/E and T/E, out of area E, maximum circumference equals 0.275 in. (6.98 mm) radial length equals 0.708 in. (17.98 mm)
50 cycles/75 hours
F. Booster vanes (stage 1 only) for: (1) Piece missing: maximum 20 blades more than 0.256 in. (6.5 mm) axial, 0.728 in. (18.49 mm) radial, no cracks starting from damage area allowed in areasA and B
50 cycles/75 hours
(2) Cracks and tears in than 0.256 in. (6.5 (1.98 mm) axial. In more than 0.128 in. 0.039 in. (0.99 mm)
10 cycles/15 hours
area C, any number, more mm) radial and 0.078 in. areas A and B, any number (3.25 mm) radial and axial
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 660 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Distortion of T/E and L/E: any number, if the 50 cycles/75 hours length L is not more than 1 in. (25.4 mm) and the maximum dimension X along the chord width is not more than 0.492 in. (12.5 mm). (4) Nicks, dents, scratches for areas A and B: any number, less than 0.157 in. (3.99 mm) in diameter, protrusion permitted
10 cycles/15 hours
(5) Nicks, dents, scratches for area C: any number, less than 0.295 in. (7.49 mm) in diameter, protrusion permitted
50 cycles/75 hours
(6) Nicks, dents, scratches L/E and T/E maximum axial length less than 0.118 in. (2.99 mm) in diameter
20 cycles/30 hours
(7) Cracked inner shroud: Maximum of 4 cracks extending from the L/E to the T/E of the inner shroud (passing through a recess) are permitted if there is a minimum separation of 3 non-cracked vane recesses between 2 cracked recesses.
3000 hours/C check
A sound check (see note below) done on the vanes at, and adjacent to the cracked inner shroud area, must demonstrate no difference in tonality.
This extension may be used again indefinitely in intervals of 3000 hours as long as there is no further deterioration of these conditions.
NOTE : Sound Tonality Check Recommendation ____ A sound tonality check must be done to detect if the abradable material inside the inner shroud is still in contact with the root of the vane. Use a smooth-ended cylindrical tool made of steel with diameter of approximately 0.5 in. (12.6999 mm). (For example, a ratchet wrench extension bar). Tools made of aluminium, plastic or wood do not permit the detection of significant variation in the sound tone from one vane to the next. Removal of 2 or 3 fan blades gives a better accessibility to do the check.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 661 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------Be careful to not use a tool or excessive force during the check. This would damage the vanes. Do the check on an area including 3 or 4 vanes on each side of the vane where the cracked inner shroud is located. Place the tool on the leading edge mid-span of the counterclockwise most vane. Lightly stroke the vane and subsequent vanes in the clockwise direction using a constant speed. Note any variations in the sound tone from one vane to the next. If there is a difference between the vane where the recess is cracked and the other vanes, the stage 1 vane assembly is unserviceable. (8) Vane leading and trailing edges - Nicks, dents and scratches on LE/TE in areas B and C with a maximum axial length less than 0.117 in. (2.97 mm) - Nicks, dents and scratches on LE/TE in area A with a maximum axial length of 0.117 in. (2.97 mm)
10 cycles/50 hours
2 cycles/10 hours
2. Fan frame A. Fan frame (1) Cracks, any number if max length of 0.16 in. (4.06 mm) and min. separation of 1 in. (25.4 mm)
10 cycles or 25 hours
(2) Nicks and dents, any number
10 cycles or 25 hours
B. Fan inlet case (1) Cracks: any number, if max length of 0.16 in. (4.06 mm) and min. separation of 1 in. (25.4 mm)
10 cycles or 25 hours
(2) Nicks and scratches: any number
10 cycles or 25 hours
(3) Crater in abradable liner (length<5x width) and damage other than crack rub and
50 cycles or 125 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 662 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------circumferential defect: if the damage is within the maximum serviceable limit (Ref. TASK 72-23-00-210-003), but the fan case parent metal is exposed and is confirmed via visual inspection to be undamaged. (4) Grooves in abradable liner (oriented within 0 deg. to 80 deg. from engine axis and length>5x width: if the damage is within the maximum serviceable limit, (Ref. TASK 72-2300-210-003) but the fan case parent metal is exposed and is confirmed via visual inspection to be undamaged
50 cycles or 125 hours.
(5) Circumferential defect in abradable liner (360 deg. or oriented within 80 deg. to 90 deg. from engine axis): For one or a cumulated defect less than 2 in. (50.8 mm) if the fan case parent metal remains not damaged under visual inspection.
50 cycles or 125 hours.
C. Outlet Guide Vanes (OGV) for: (Ref. Fig. 609/TASK 72-00-00-991-321) (1) Broken vane: not serviceable, if vane is replaced
10 cycles extension
(2) Missing vane: One doublet missing
10 cycles extension
(3) Cracks Outer platform: cracks from or along the airfoil are defined (Ref. Fig. 609/TASK 72-00-00-991-321)
50 cycles extension
(4) Metal leading edge missing: up to 0.78 in. (20 mm) in height and 0.39 in. (10 mm)
100 cycles extension
(5) Nicks and/or dents, on leading edge (metallic leading edge), if damage between 0.12 in. (3 mm) and 0.19 in. (5 mm) deep
A maximum service extension of 100 cycles
(6) Erosion of composite material, any amount
50 cycles or 125 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 663 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------D. OGV inner shroud (1) Cracks, cut or torn seal at mating with OGV, any amount
25 cycles or 50 hours
E. Fan duct panels (1) One fan duct panel missing is permitted, if you make sure that the VBV area is free of unwanted object before the first aircraft release of the day.
10 cycles
(2) Missing lowers on panel
50 cycles with 3 missing lowers maximum
F. Splitter fairing (1) Cracks: any amount
10 cycles or 25 hours
G. Mid acoustical panels
20 cycles
(1) Disbonded damper more than 20 percent of the total surface 3. Compressor rotor A. Compressor rotor blades NOTE : The depth of a defect such as a nick is measured along the axis of ____ the damage unless otherwise noted. (1) Stages 1-4 radial cracks within 0.30 in. (7.6 mm) of the leading and trailing edges more than 0.25 in. (6.4 mm) but less than 0.40 in. (10.2 mm) in length.
10 cycles or 25 hours
(2) Stages 1-4 chord-wise cracks more than 0.20 in. (5.1 mm) but less than 0.30 in. (7.6 mm) in length.
10 cycles or 25 hours
(3) Stages 1-4 nicks, missing material and erosion on the leading and trailing edges
10 cycles or 25 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 664 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------found in Dim. B more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm). (4) Stages 1-4 dents on the leading and trailing edges found in Dim. B more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm) in depth, or less than 0.06 in. (1.5 mm) deflection from the original contour.
10 cycles or 25 hours
(5) Stages 1 nicks, dents and tears on the leading and trailing edge in Dim. A more than 0.25 in. (6.4 mm) but less than 0.30 in. (7.6 mm) in depth.
10 cycles or 25 hours
(6) Stages 1-4 missing material and erosion at the leading and trailing edge tip corners more than 0.30 in. (7.6 mm) but less than 0.40 in. (10.1 mm).
10 cycles or 25 hours
R R R R
(7) Stage 2, more than 4 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
R R R R
(8) Stage 3, more than 5 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
R R R R
(9) Stage 4, more than 6 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
R
(10) Stages 1-4 nicks, dents and missing material on the leading and trailing edges of the lower 25% of the airfoil (but not the root radius) more than 0.03 in. (0.76 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R
(11) Nicks, dents, wear and scratches of the trailing edge root radius of stage 2 and stage 3 of more than 0.03 in. (0.8 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R R
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 665 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(12) Stages 5-9 radial cracks that are no more 10 cycles or 25 than 0.20 in. (5.1 mm) from the leading or hours trailing edge and more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm) in length.
R
(13) Stages 5-9 chord-wise cracks that are no more than 0.20 in. (5.1 mm) from the tip and are more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm) in length.
10 cycles or 25 hours
R
(14) Stages 5-9 nicks, tears, missing material and erosion on the leading and trailing edges found in Dim. B that are more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R
(15) Stages 5-9 dents on the leading and trailing edges found in Dim. B that are more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm) in depth or less than 0.06 in. (1.5 mm) deflection from the original contour.
10 cycles or 25 hours
R
(16) Stages 5-9 nicks, dents and tears on the leading and trailing edges found in Dim. A that are more than 0.15 in. (3.8 mm) but than less 0.20 in. (5.1 mm).
10 cycles or 25 hours
R
(17) Stages 5-9 missing material and erosion at the leading and trailing edge tip corners if the damage is more than 0.20 in. (5.1 mm) but less than 0.30 in. (7.6 mm).
10 cycles or 25 hours
R
(18) Stages 5-9 curl on the end of the airfoil when the blade chord is more than 50% but less than 75% of the chord maximum radial length, 0.3 in. (7.6 mm), when it does not engage the stationary parts during operation.
10 cycles or 25 hours
R
(19) Stages 5-9 nicks, dents and missing material edges found in the lower 25% of the airfoil (but not the root radius) more than 0.03 in. (0.76 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 666 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(20) Stages 2-3 trailing edge root radius nicks, 10 cycles or 25 dents and scratches more than 0.03 in. (7.6 hours mm) but less than 0.08 in. (2.0mm) in depth. 4. Compressor front stator A. Casing cracks 0.17 in. (4.32 mm) max length in skin
10 cycles or 25 hours
B. Casing nicks, pits, scores or scratches, any amount, any depth
10 cycles or 25 hours
C. Broken actuation ring connector, one side only, if connector is replaced
5 cycles
D. Vane actuation ring cracks, distortion, bends, twists or distress, provided ring has not separated
5 cycles
E. Loose vane assemblies with metal-to-metal contact on up to 50 percent of vanes
10 cycles or 25 hours
5. Combustion case A. Forward and aft flange radial cracks inward from bolt holes
10 cycles
B. Midflange radial cracks
10 cycles
C. Maximum of 10 broken midflange bolts with no more than 4 broken bolts in any group of 20
25 cycles
D. High pressure turbine (HPT) shroud cooling and compressor discharge pressure (CDP) pad cracks more than 0.06 in. (1.52 mm) from bolt holes
10 cycles
6. Combustion chamber A. Dome assembly (1) Radial crack in spectacle plate
25 hours
Any number up to 2.5 inches (63.5 mm) in length and not connected to each other
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 667 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(2) Circumferential crack in spectacle plate 25 hours Any number up to 3.6 inches (91 mm) in length separated by 4.8 inches (125 mm) (3) Connected cracks in spectacle plate
25 hours
Not more than (1) radial crack 2.5 in. (50.8 mm) long with (1) circumferential crack 3.6 in. (91 mm) long, separated by 4.8 in. (125 mm) (4) Missing material from spectacle plate
25 hours
The damage is more then the given limits (5) Radial crack in deflector or sleeve
25 cycles
Any number up to 0.6 in. (16 mm) in length (6) Circumferential cracks in deflector or sleeve
25 cycles
Any number up to 0.9 in. (23 mm) in length (7) Connected cracks in deflector or sleeve
25 cycles
Connection of any radial and circumferential cracks within limits of (5) and (6) above. Limit is exceeded when third crack connects (8) Missing material from overhangs on deflector or sleeve
50 cycles
Any amount up to 0.240 in. (6.10 mm) maximum depth (9) Burn through holes
25 cycles
3 per dome 1.2 in. (30mm) x 1.2 in. (30 mm) maximum B. Inner and outer liners (1) Outer liner axial cracks
100 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 668 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------Up to 5 cracks across more than one panel, and a crack can go across up to 5 panels in sequence (2) Outer liner axial cracks (from outer side borescope)
25 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 5 panels. At least one of the cooling ribs (3, 4, 5, or 6) does not have cracks that extend through to the outer side. Rib 1 is not cracked through. (3) Inner liner axial cracks
100 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 4 panels in sequence (4) Circumferential cracks
25 cycles
Any number up to 3 dilution lands in length separated by 3 non-cracked dilution lands (5) Connected cracks
100 cycles
Connection of any axial and circumferential cracks up to max limits of paragraphs (1), (2), (3), and (4) (6) Burn through or missing material
100 cycles
There are not more than 8 areas that are not more than 2 times the diameter of a dilution hole. There are not more than 2 areas that are not more than 3 times the diameter of a dilution hole. There are not more than one area that is not more than 4 times the size of a dilution hole. There are not more than 3 areas in adjacent panels that are aligned axially if they have a separation of a minimum of 3 dilution lands that are not damaged.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 669 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(7) Missing overhangs 25 cycles Per liner: 17 areas each twice the size of a dilution hole, providing max axial alignment of distress is 3 adjacent panels (8) Distortion
25 cycles
Any amount within 0.7 in. (17.8 mm) of original contour C. Combustor inner cowl bolts (1) Missing bolt: Maximum of 3 bolts are missing with 4 bolts intact between 2 missing bolts. All other bolts are tight with tack welds intact
50 cycles for next check, then repeat BSI every 400 cycles
(2) Bolt tack weld cracked but bolt is not loose: If a maximum of 5 tack welds are cracked, no more than two consecutive, with 4 tack welds intact between two cracked tack welds
25 cycles for first check, 50 cycles for second check, repeat BSI check every 100 cycles
(3) Bolt tack weld is cracked and bolt is loose: If one or more bolts are loose
5 cycles
7. Fuel Nozzles A. Fuel nozzles with dislodged wear sleeves or wear sleeves with 4 interrupted weld designs
5 cycles
8. HPT nozzle A. Leading edge missing material, from cracking or burn-through, up to 0.5 in. (12.7 mm) X 0.5 in. (12.7 mm) per vane. Maximum of 4 vanes per 90 degree arc
25 cycles
B. Concave surfaces of airfoil missing material, from cracking or burn-through, up to 0.75 in. (19.04 mm) diameter per vane
25 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 670 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------C. Convex side missing panel 25 cycles provided HPT blades are within limits D. Inner and outer platforms missing material, from cracking or burn-through, up to 0.5 in. (12.7 mm) diameter per segment
25 cycles
E. Trailing edge missing material up to 0.75 in. (19 mm)in axial direction
25 cycles
F. Baffle missing material, any amount.
10 cycles
9. HPT rotor blade A. Trailing edge cracks in Area A less than 0.2 in. (5.08 mm) long
10 cycles
B. Trailing edge cracks and convex airfoil cracks within 0.5 in. (12.7 mm) of trailing edge (10 blades maximum) in Area B less than 0.3 in. (7.62 mm) long
25 cycles
C. Radial tip cracks less than 0.35 in. (8.89 mm) long
10 cycles
D. Leading edge cracks in Area A less than 0.1 in. (2.54 mm) long
10 cycles
E. Axial nose or gill hole cracks in Area B less than 0.05 in. (1.27 mm) long
10 cycles
F. Radial nose or gill hole cracks in Area B less than 0.06 in. (1.52 mm) long
10 cycles
G. Radial nose or gill hole cracks in Area C less than 0.03 in. (0.76 mm) long
10 cycles
H. Leading edge missing material in areas A and B. Any amount provided cavity 2 is not exposed (any number of blades)
25 cycles
J. Airfoil distortion or evidence of burning or melting (10 blades maximum)
25 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 671 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------10. HPT shroud and stage 1 low pressure turbine (LPT) nozzle A. HPT shrouds (1) Circumferential cracks that connect and are more than 1 in. (25.3999 mm) long.
25 cycles
(2) Circumferential cracks more than 0.25 in. (6.3499 mm) long that connect to axial cracks in Area B.
25 cycles
(3) Burn through of shroud rub land
25 cycles
B. Stage 1 LPT nozzle (1) Cracks in all areas up to 1.4 in. (35 mm) long provided not more than 2 adjacent airfoils per segment
10 cycles
(2) One crack permitted on each airfoil, from leading edge to trailing edge, if there is no missing material.
100 cycles
(3) Burns, erosion, corrosion and missing metal up to 1 in.2 (645.16 mm2) per airfoil and no cracks extending from distressed area
5 cycles
11. LPT Rotor A. LPT blades (all stages) (1) Blade pretwist - Total gap, for stage 1, up to 0.1 in. (2.54 mm)
5 cycles
- Stages 2-4 gaps such that adjacent interlocks do not contact each other
5 cycles
(2) 0.08 in. (2.03 mm) max. deflection over a length 10 times longer max, only for stage 1 LPT blades distorted leading edges, due to overtemperature
15 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 672 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Stages 1, 2, 3 blades - Area E: Any amount of impact damage/rubbing provided there is no missing material or cracks
5 cycles or 10 hours
- Other areas: Any amount of impact damage such as bending, nicks and/or dents is allowed provided there is no missing material or cracks exceeding 50 percent of chord width
5 cycles or 10 hours
(4) Stage 4 blades - Any amount of tip shroud interlock wear allowed
25 cycles or 50 hours
- Blades tip shroud protrusion not to exceed 0.04 in. (1.01 mm)
10 cycles or 25 hours
- Area E: Any amount of impact damage such as nicks and/or dents is allowed provided there is no missing material or cracks
5 cycles or 10 hours
- Other areas: Any amount of impact damage. One complete airfoil and any number of tip shrouds with associated airfoil tips may be missing provided engine vibration is not excessive
5 cycles or 10 hours
- Blades tip shrouds shingled or unlatched provided rotor turns freely and engine vibration is not excessive
5 cycles or 10 hours in shingled condition.
B. Nozzle segments 2 to 4 (1) Three cracks maximum for each nozzle segment if cracks are more than 0.5 in. (12.7 mm) (1/3 of the chord width) and less than 1.0 in. (25.4 mm) (2/3 of the chord width) if the
200 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 673 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------adjacent nozzle segments have no more than two cracks more than 0.5 in. (12.7 mm) (1/3 of the chord width) and less than 1.0 in. (25.4 mm) (2/3 of the chord width). (2) One crack maximum for each nozzle segment that is more than 1.0 in. (25.4 mm) (2/3 of the chord width) including open airfoil.
200 cycles
(3) One full chord crack on two airfoils for each segment if the adjacent nozzle segments have no more than one airfoil with a full chord crack.
25 cycles
(4) Nicks, dents, tears, missing pieces up to 2 in.2 (1290.32 mm2) on nonadjacent vanes provided there are no cracks extending from distressed areas
10 cycles
(5) Burned areas with missing material or melted
25 cycles
C. Stage 4 shroud abradable material (1) Worn, jagged or crushed sealing surface exceeding 50 percent of the honeycomb height provided sectors of the shroud abradable material are not missing
10 cycles
12. LPT Casing A. Forward and aft flanges (1) One crack connecting 2 bolt holes without penetrating pressure vessel outer skin
10 cycles
(2) One crack into skin 0.4 in. (10.16 mm) long maximum
10 cycles
B. External surface of the casing (1) One crack 0.4 in. (10.16 mm) long maximum C. Cooling air tube and manifold assemblies
10 cycles 10 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 674 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(1) One separated circumferential tube (2) 3 in. (76.2 mm) cumulative cooling air manifold crack (3) One separated cooling air tube support D. Thread ports and bosses (1) One crack 0.5 in. (12.7 mm) maximum providing there is no leakage
10 cycles
13. Turbine frame A. Forward and aft flanges
10 cycles
(1) One circumferential crack connecting two bolt holes (2) One crack into skin 0.5 in. (12.7 mm) maximum B. Engine mounting lug areas airframe attach points only
10 cycles
(1) One crack out of one mount lug bolt hole 0.25 in. (6.35 mm) maximum (2) Skin crack 0.25 in. (6.35 mm) maximum. C. Threaded parts and bosses
10 cycles
(1) One crack 0.5 in. (12.7 mm) long providing there is no fluid or air leakage D. Stud on the aft face of the inner hub. (1) Missing/broken/loose stud(s): - One (1) or two (2) studs:
500hrs/500cyc
- Three (3) studs: *If not adjacent to each other:
500hrs/500cyc
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 675 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------*If two (2) non-serviceable studs are 500hrs/500cyc adjacent, but the third one is separated from them by two (2) serviceable studs: *If not:
Replace studs
- Four (4) studs or more:
Replace studs
E. Thermal insulation blankets
100 cycles
(1) Missing or protruding blankets F. Other areas
10 cycles
(1) One crack 0.25 in. (6.35 mm) maximum 14. Accessory gearbox A. Two opposite keylock studs missing provided there is no leakage at flange
3 cycles or 30 hours
B. Oil leakage from AGB/Starter carbon seal (Ref. TASK 79-00-00-210-003)
10 cycles provided seal drain line is disconnected and drain cavity is capped
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 676 Feb 01/10
C F M 56-5B TASK 72-00-00-200-025- 01 Over-Serviceable-Limit Extensions 1. __________________ Reason for the Job This TASK is applicable to /P engines and /3 engines. It can occur that specific defects do not agree with the Maximum Serviceable Limits, and that the maintenance facilities, at a given location, are not sufficient to do the necessary corrective actions. In these circumstances, limit extensions will permit to send the engine where correction is possible, or to schedule the necessary maintenance in the extension period. NOTE : The limit extensions are one-time extensions only. Applicable ____ hardware action is necessary at the completion of the extended serviceable period. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-210-006 72-21-00-210-009 72-23-00-210-003 79-00-00-210-003 72-00-00-991-308 72-00-00-991-309 72-00-00-991-321 72-00-00-991-320
Inspect Fan Rotor Blades Removed from the Fan Disk. Inspect Fan Rotor Blades Installed on the Fan Disk Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material Visual Inspection of the Oil System Fig. 607 Fig. 608 Fig. 609 Fig. 610
3. __________ Job Set-up Subtask 72-00-00-941-105 A. Not applicable
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 677 Nov 01/09
C F M 56-5B 4. Procedure _________ (Ref. Fig. 607/TASK 72-00-00-991-308, 608/TASK 72-00-00-991-309, 609/TASK 72-00-00-991-321, 610/TASK 72-00-00-991-320) Subtask 72-00-00-210-101 A. Over-serviceable-limit Extensions ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------1. Fan and booster A. Spinner front cone (1) Damaged surface protection greater than 50 percent of total surface
50 cycles
(2) Corrosion marks (white mushroom pattern) before part removal
A continuation in service of 100 cycles maximum is permitted
B. Spinner rear cone (1) Oil wetting at inner of spinner cone or fan disk or forward fan shaft
50 cycles
(2) Seal ring tear: any number if cumulated length is more than 0.4 in. (10 mm)
50 cycles
C. Fan blade (1) Fully missing molydag on inner faces of the platforms
250 cycles
(2) Flaking of Cu.Ni.In coating on blade dovetail pressure faces (contact areas), up to 10 percent if there is no indication of wear on base material
Examine blades for serviceability. (Ref. TASK 72-2100-210-006) 1200 cycles after relubrication. Repeat extension is permitted
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 678 Nov 01/09
C F M 56-5B
HPT Blade Inspection (Only Applicable /P Engines) Figure 610/TASK 72-00-00-991-320 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 679 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Flaking of Cu.Ni.In coating on blade dovetail 400 cycles after pressure faces (contact areas), more than 10 relubrication. percent and less than 50 percent if there is Repeat extension is no indication of wear on base material not permitted (4) Shingling at mid span shrouds
Turn the shingled blades to the 12 oclock position and unshingle with hand force or by using a piece of wood. Examine blades for serviceability (Ref. TASK 72-2100-210-009) Remove and send the shingled blades to a shop for a dimensional and an F.P.I. inspection in less than 50 cycles
(5) Nicks, dents, scratches and sheared edges on midspan shroud surfaces up to 0.035 in. (0.89 mm) deep if defects are not in the midspan shroud to airfoil fillet radius
50 cycles
(6) Missing or damaged hard coating on midspan shroud pressure faces more than 20 percent but less than 40 percent of coated area
50 cycles
D. Fan disk (1) Wear greater than 50 percent of area on disk dovetail pressure faces
100 cycles
E. Booster rotor blade for: (1) Piece missing:
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 680 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------any number in area G, at leading edge and 50 cycles/75 hours trailing edge tip corners, 0.8 in. (20 mm) radial and 0.5 in. (12.5 mm) axial (2) Cracks and tears in area G, 0.8 in. (20 mm) from tip : any number less than 0.8 in. (20 mm) radial and less than 0.492 in. (12.5 mm) axial
50 cycles/75 hours
(3) Wear or local distortion of T/E and L/E tips if less than 15 blades 0.984 in. (25 mm) radial and 0.59 in. (15 mm) axial
100 cycles/150 hours
(4) Nicks, dents, scratches for area E: any number, less than 0.059 in. (1.5 mm) in diameter, protrusion acceptable, not thru
50 cycles/75 hours
(5) Nicks, dents, scratches for airfoil out of area E, not L/E and T/E: any number, less than 0.236 in. (6 mm) in diameter, protrusion acceptable
50 cycles/75 hours
(6) Nicks, dents, scratches out of area E on L/E and T/E: maximum axial length less than 0.059 in. (1.49 mm)
50 cycles/75 hours
(7) Distorted L/E and T/E, out of area E maximum circumference equals 0.275 in. (6.98 mm) radial length equals 0.708 in. (17.98 mm)
50 cycles/75 hours
F. Booster vanes (stage 1 only) for: (1) Piece missing: maximum 20 blades more than 0.256 in. (6.5 mm) axial, 0.728 in. (18.49 mm) radial, no cracks starting from damage area allowed in areas A and B
50 cycles/75 hours
(2) Cracks and tears in than 0.256 in. (6.5 (1.98 mm) axial. In more than 0.128 in. 0.039 in. (0.99 mm)
10 cycles/15 hours
area C, any number, more mm) radial and 0.078 in. areas A and B, any number (3.25 mm) radial and axial
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 681 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Distortion of T/E and L/E: any number, if the 50 cycles/75 hours length L is no more than 1 in. (25.4mm) and the maximum dimension X along the chord width is not more than 0.492 in. (12.5mm) (4) Nicks, dents, scratches for areas A and B ; any number, less than 0.157 in. (3.99 mm) in diameter, protrusion permitted
10 cycles/15 hours
(5) Nicks, dents, scratches for area C: any number, less than 0.295 in. (7.49 mm) in diameter, protrusion permitted
50 cycles/75 hours
(6) Nicks, dents, scratches L/E and T/E maximum axial length less than 0.118 in. (2.99 mm) in diameter
20 cycles/30 hours
(7) Cracked inner shroud: Maximum of 4 cracks extending from the L/E to the T/E of the inner shroud (passing through a recess) are permitted if there is a minimum separation of 3 non-cracked vane recesses between 2 cracked recesses.
3000 hours/C check
A sound check (see note below) done on the vanes at, and adjacent to the cracked inner shroud area, must demonstrate no difference in tonality.
This extension may be used again indefinitely in intervals of 3000 hours as long as there is no further deterioration of these conditions.
NOTE : Sound Tonality Check Recommendation: ____ A sound tonality check must be done to detect if the abradable material inside the inner shroud is still in contact with the root of the vane. Use a smooth-ended cylindrical tool made of steel with diameter of approximately 0.5 in. (12.6999 mm). (For example, a ratchet wrench extension bar). Tools made of aluminium, plastic or wood do not permit the detection of significant variation in the sound tone from one vane to the next. Removal of 2 or 3 fan blades gives a better accessibility to do the check.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 682 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------Be careful to not use a tool or excessive force during the check. This would damage the vanes. Do the check on an area including 3 or 4 vanes on each side of the vane where the cracked inner shroud is located. Place the tool on the leading edge mid-span of the couterclockwise most vane. Lightly stroke the vane and subsequent vanes in the clockwise direction using a constant speed. Note any variations in the sound tone from one vane to the next. If there is a difference between the vane where the recess is cracked and the other vanes, the stage 1 vane assembly is unserviceable. (8) Vane leading and trailing edges - Nicks, dents and scratches on LE/TE in areas B and C with a maximum axial length less than 0.117 in. (2.97 mm) - Nicks, dents and scratches on LE/TE in area A with a maximum axial length of 0.117 in. (2.97 mm)
10 cycles/50 hours
2 cycles/10 hours
2. Fan frame A. Fan frame (1) Cracks, any number if max length of 0.16 in. (4.06 mm) and min. separation of 1 in. (25.4 mm)
10 cycles or 25 hours
(2) Nicks and dents, any number
10 cycles or 25 hours
B. Fan inlet case (1) Cracks: any number, if max length of 0.16 in. (4.06 mm) and min. separation of 1 in. (25.4 mm)
10 cycles or 25 hours
(2) Nicks and scratches: any number
10 cycles or 25 hours
(3) Crater in abradable liner (length<5x width) and damage other than crack rub and
50 cycles or 125 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 683 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------circumferential defect : If the damage is within the maximum serviceable limit, (Ref. TASK 72-23-00-210-003), but the fan case parent metal is exposed and is confirmed via visual inspection to be undamaged. (4) Grooves in abradable liner (oriented within 0 deg. to 80 deg. from engine axis and length>5x width : If the damage is within the maximum serviceable limit, (Ref. TASK 72-2300-210-003) but the fan case parent metal is exposed and is confirmed via visual inspection to be undamaged
50 cycles or 125 hours
(5) Circumferential defect in abradable liner (360 deg. or oriented within 80 deg. to 90 deg. from engine axis) : for one or a cumulated defect less than 2 in. (50.8 mm) if the fan case parent metal remains not damaged under visual inspection.
50 cycles or 125 hours.
C. Outlet Guide Vanes (OGV) for: (Ref. Fig. 609/TASK 72-00-00-991-321) (1) Broken vane: Not serviceable, if vane is replaced
10 cycles extension
(2) Missing vane: One doublet missing
10 cycles extension
(3) Crack Outer platform: cracks from or along the airfoil are defined (Ref. Fig. 609/TASK 72-00-00-991-321)
50 cycles extension
(4) Metal leading edge missing: up to 0.78 in. (20 mm) in height and 0.39 in. (10 mm)
100 cycles extension
(5) Nicks and/or dents, on leading edge (metallic leading edge), if damage between 0.12 in. (3 mm) and 0.19 in. (5 mm) deep
A maximum service extension of 100 cycles
(6) Erosion of composite material, any amount
50 cycles or 125 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 684 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------D. OGV inner shroud (1) Cracks, cut or torn seal at mating with OGV, any amount
25 cycles or 50 hours
E. Fan duct panels (1) One fan duct panel missing is permitted, if you make sure that the VBV area is free of unwanted object before the first aircraft release of the day.
10 cycles
(2) Missing lowers on panel
50 cycles with 3 missing lowers maximum
F. Splitter fairing (1) Cracks: any amount
10 cycles or 25 hours
G. Mid acoustical panels
20 cycles
(1) Disbonded damper more than 20 percent of the total surface 3. Compressor rotor A. Compressor rotor blades NOTE : The depth of a defect such as a nick is measured along the axis of ____ the damage unless otherwise noted. (1) Stages 1-4 radial cracks within 0.30 in. (7.6 mm) of the leading and trailing edges more than 0.25 in. (6.4 mm) but less than 0.40 in. (10.2 mm) in length.
10 cycles or 25 hours
(2) Stages 1-4 chord-wise cracks more than 0.20 in. (5.1 mm) but less than 0.30 in. (7.6 mm) in length.
10 cycles or 25 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 685 Feb 01/10
R R R
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Stages 1-4 nicks, missing material and 10 cycles or 25 erosion on the leading and trailing edges hours found in Dim. B more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm), if the HPC blade is NOT a Tech Insertion stage 4 blade (PN P394XXX).
R R R R R R
(4) Stages 1-4 nicks, missing material and erosion on the leading and trailing edges found in Dim. B more than 0.03 in. (1.0 mm) in depth but less than 0.08 in. (2.0 mm) in depth, if the HPC blade is a Tech insertion stage 4 blade (PN P394XXX).
10 cycles or 25 hours
R
(5) Stages 1-4 dents on the leading and trailing edges found in Dim. B more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm) in depth, or less than 0.06 in. (1.5 mm) deflection from the original contour.
10 cycles or 25 hours
R
(6) Stages 1-4 nicks, dents and tears on the leading and trailing edge in Dim. A more than 0.25 in. (6.4 mm) but less than 0.30 in. (7.6 mm) in depth.
10 cycles or 25 hours
R R
(7) Stages 1 missing material and erosion at the leading and trailing edge tip corners more than 0.30 in. (7.6 mm) but less than 0.40 in. (10.1 mm).
10 cycles or 25 hours
R R R R
(8) Stage 2, more than 4 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
R R R R
(9) Stage 3, more than 5 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
R R R R
(10) Stage 4, more than 6 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 686 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(11) Stages 1-4 nicks, dents and missing material 10 cycles or 25 on the leading and trailing edges of the hours lower 25% of the airfoil (but not the root radius) more than 0.03 in. (0.76 mm) but less than 0.08 in. (2.0 mm).
R
(12) Nicks, dents, wear and scratches of the trailing edge root radius of stage 2 and stage 3 of more than 0.03 in. (0.8 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R
(13) Stages 5-9 radial cracks that are no more than 0.20 in. (5.1 mm) from the leading or trailing edge and more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm) in length.
10 cycles or 25 hours
R
(14) Stages 5-9 chord-wise cracks that are no more than 0.20 in. (5.1 mm) from the tip and are more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm) in length.
10 cycles or 25 hours
R
(15) Stages 5-9 nicks, tears, missing material and erosion on the leading and trailing edges found in Dim. B that are more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R
(16) Stages 5-9 dents on the leading and trailing edges found in Dim. B that are more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm) in depth or less than 0.06 in. (1.5 mm) deflection from the original contour.
10 cycles or 25 hours
R
(17) Stages 5-9 nicks, dents and tears on the leading and trailing edges found in Dim. A that are more than 0.15 in. (3.8 mm) but less 0.20 in. (5.1 mm).
10 cycles or 25 hours
R
(18) Stages 5-9 missing material and erosion at the leading and trailing edge tip corners if the damage is more than 0.20 in. (5.1 mm) but less than 0.30 in.
10 cycles or 25 hours
Stages 5-9 curl on the end of the airfoil when the blade chord is more than 50%
10 cycles or 25 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 687 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(19) but less than 75% of the chord maximum radial length, 0.3 in. (7.6 mm), when it does not engage the stationary parts during operation.
R
(20) Stages 5-9 nicks, dents and missing material edges found in the lower 25% of the airfoil (but not the root radius) more than 0.03 in. (0.76 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R
(21) Stages 2-3 trailing edge root radius nicks, dents and scratches more than 0.03 in. (7.6 mm) but less than 0.08 in. (2.0 mm) in depth.
10 cycles or 25 hours
R
(22) Stages 4-9 blade locks with two cracks.
10 cycles or 25 hours
R
(23) Stages 4-9 blade locks that are loose.
25 cycles or 100 hours
4. Compressor front stator A. Casing cracks 0.17 in. (4.32 mm) max length in skin
10 cycles or 25 hours
B. Casing nicks, pits, scores or scratches, any amount, any depth
10 cycles or 25 hours
C. Broken actuation ring connector, one side only, if connector is replaced
5 cycles
D. Vane actuation ring cracks, distortion, bends, twists or distress, provided ring has not separated
5 cycles
E. Loose vane assemblies with metal-to-metal contact on up to 50 percent of vanes
10 cycles or 25 hours
5. Combustion case A. Forward and aft flange radial cracks inward from bolt holes
10 cycles
B. Midflange radial cracks
10 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 688 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------C. Maximum of 10 broken midflange bolts with no more 25 cycles than 4 broken bolts in any group of 20 D. High pressure turbine (HPT) shroud cooling and compressor discharge pressure (CDP) pad cracks more than 0.06 in. (1.52 mm) from bolt holes
10 cycles
6. Combustion chamber A. Dome assembly (1) Radial crack in spectacle plate
25 hours
Any number up to 2.5 inches (63.5 mm) in length and not connected to each other. (2) Circumferential crack in spectacle plate
25 hours
Any number up to 3.6 inches (91 mm) in length separated by 4.8 inches (125 mm) (3) Connected cracks in spectacle plate
25 hours
Not more than (1) radial crack 2.5 in. (50.8 mm) long with (1) circumferential crack 3.6 in. (91 mm) long, separated by 4.8 in. (125 mm) (4) Missing material from spectacle plate
25 hours
The damage is more then the given limits (5) Radial crack in deflector or sleeve
25 cycles
Any number up to 0.6 in. (16 mm) in length (6) Circumferential cracks in deflector or sleeve
25 cycles
Any number up to 0.9 in. (23 mm) in length (7) Connected cracks in deflector or sleeve
25 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 689 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------Connection of any radial and circumferential cracks within limits of (5) and (6) above. Limit is exceeded when third crack connects (8) Missing material from overhangs on deflector or sleeve
50 cycles
Any amount up to 0.240 in. (6.10 mm) maximum depth (9) Burn through holes
25 cycles
3 per dome 1.2 in. (30mm) x 1.2 in. (30 mm) maximum. B. Inner and outer liners (1) Outer liner axial cracks
100 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 5 panels in sequence (2) Outer liner axial cracks (from outer side borescope)
25 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 5 panels. At least one of the cooling ribs (3, 4, 5, or 6) does not have cracks that extend through to the outer side. Rib 1 is not cracked through. (3) Inner liner axial cracks
100 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 4 panels in sequence (4) Circumferential cracks
25 cycles
Any number up to 3 dilution lands in length separated by 3 non-cracked dilution lands (5) Connected cracks
100 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 690 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------Connection of any axial and circumferential cracks up to max limits of paragraphs (1), (2), (3), and (4) (6) Burn through or missing material
100 cycles
There are not more than 8 areas that are not more than 2 times the diameter of a dilution hole. There are not more than 2 areas that are not more than 3 times the diameter of a dilution hole. There are not more than one area that is not more than 4 times the size of a dilution hole. There are not more than 3 areas in adjacent panels that are aligned axially if they have a separation of a minimum of 3 dilution lands that are not damaged. (7) Missing overhangs
25 cycles
Per liner: 17 areas each twice the size of a dilution hole, providing max axial alignment of distress is 3 adjacent panels (8) Distortion
25 cycles
Any amount within 0.7 in. (17.8 mm) of original contour C. Combustor inner cowl bolts (1) Missing bolt: Maximum of 3 bolts are missing with 4 bolts intact between 2 missing bolts. All other bolts are tight with tack welds intact
50 cycles for next check, then repeat BSI every 400 cycles
(2) Bolt tack weld cracked but bolt is not loose: If a maximum of 5 tack welds are cracked, no more than two consecutive, with 4 tack welds intact between two cracked tack welds
25 cycles for first check, 50 cycles for second check, repeat BSI check 100 cycles
(3) Bolt tack weld is cracked and bolt is loose: If one or more bolts are loose
5 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 691 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------7. HPT nozzle A. Leading edge missing material, from cracking or burn-through, up to 0.5 in. (12.7 mm) X 0.5 in. (12.7 mm) per vane. Maximum of 4 vanes per 90 degree arc
25 cycles
B. Concave surfaces of airfoil missing material, from cracking or burn-through, up to 0.75 in. (19.0 mm) diameter per vane
25 cycles
C. Convex surfaces of airfoil missing material from cracking or burn-through, up to 0.75 in. (19.0 mm) diameter per vane
25 cycles
D. Inner and outer platforms missing material, from cracking or burn-through, up to 0.5 in. (12.7 mm) diameter per segment
25 cycles
E. Trailing edge missing material up to 0.75 in. (19 mm)in axial direction
25 cycles if HPT blades are within limits
F. Baffle missing material, any amount.
10 cycles
8. HPT rotor blade (Ref. Fig. 610/TASK 72-00-00-991-320) A. Trailing edge cracks in Area A less than 0.2 in. (5.08 mm) long
40 cycles
B. Convex airfoil cracks within 0.5 in. (12.7 mm) of trailing edge (10 blades maximum) in Area B less than 0.3 in. (7.62 mm) long
25 cycles
C. Trailing edge cracks in Areas B and C less than 0.30 in. (7.62 mm) long
40 cycles
D. Radial tip cracks on the convex side not within 0.5 in. (12.7 mm) of the trailing edge, less than 0.35 in. (8.9 mm) long
50 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 692 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------E. Radial tip cracks on the concave side not within 50 cycles 0.5 in. (12.7 mm) of the trailing edge, less than 1.0 in. (25.4 mm) long F. Leading edge cracks in Area A less than 0.1 in. (2.54 mm) long
10 cycles
G. Axial nose or gill hole cracks in Areas B and C less than 0.05 in. (1.27 mm) long
10 cycles
H. Radial nose or gill hole cracks in Area B less than 0.06 in. (1.52 mm) long
10 cycles
J. Radial nose or gill hole cracks in Area C less than 0.03 in. (0.76 mm) long
10 cycles
K. Missing material at trailing edge tip and Area A up to 0.5 in. x 0.75 in. (12.7 mm x 19 mm)
50 cycles
L. Leading edge missing material in areas A and B. Any amount provided cavity 2 is not exposed (any number of blades)
25 cycles
M. Airfoil distortion or evidence of burning or melting (10 blades maximum)
25 cycles
N. Airfoil tip bent, curled, or missing material if the missing material below the tip shelf is less than 0.05 in. (1.27 mm) in diameter
10 cycles
P. Airfoil convex and concave surface nicks or dents in Areas A, B and C if no cracks or missing material
25 cycles
9. HPT shroud and stage 1 low pressure turbine (LPT) nozzle A. HPT shrouds (1) Circumferential cracks that connect and are more than 1 in. (25.3999 mm) long.
25 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 693 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(2) Circumferential cracks more than 0.25 in. 25 cycles (6.3499 mm) long that connect to axial cracks in Area B. (3) Burn through of shroud rub land
25 cycles
B. Stage 1 LPT nozzle (1) Cracks in all areas up to 1.4 in. (35 mm) long provided not found on 2 adjacent airfoil segments
10 cycles
(2) One crack permitted on each airfoil, from leading edge to trailing edge, if there is no missing material.
100 cycles
(3) Burns, erosion, corrosion and missing metal up to 1 in.2 (645.16 mm2) per airfoil and no cracks extending from distressed area
5 cycles
(4) Cracks in outer and inner platforms up to 1.0 in. (25 mm) provided not found on 2 adjacent airfoil segments
100 cycles
10. LPT Rotor A. LPT blades (all stages) (1) Blade pretwist - Total gap, for stage 1, up to 0.1 in. (2.54 mm)
5 cycles
- Stage 2-4 gaps such that adjacent interlocks do not contact each other
5 cycles
(2) 0.08 in. (2.03 mm) max. deflection over a length 10 times longer max, only for stage 1 LPT blades distorted leading edges, due to overtemperature
15 cycles
(3) Stage 1, 2, 3 blades
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 694 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------- Area E: 5 cycles or 10 Any amount of impact damage/rubbing hours provided there is no missing material or cracks - Other areas: Any amount of impact damage such as bending, nicks and/or dents is allowed provided there is no missing material or cracks exceeding 50 percent of chord width
5 cycles or 10 hours
(4) Stage 4 blades - Any amount of tip shroud interlock wear allowed
25 cycles or 50 hours
- Blade tip shroud protrusion not to exceed 0.04 in. (1.01 mm)
10 cycles or 25 hours
- Area E: Any amount of impact damage such as nicks and/or dents is allowed provided there is no missing material or cracks
5 cycles or 10 hours
- Other areas: Any amount of impact damage. One complete airfoil and any number of tip shrouds with associated airfoil tips may be missing provided engine vibration is not excessive
5 cycles or 10 hours
- Blade tip shrouds shingled or unlatched provided rotor turns freely and engine vibration is not excessive
5 cycles or 10 hours in shingled condition.
B. Nozzle segments 2 to 4 (1) Three cracks maximum for each nozzle segment if cracks are more than 0.5 in. (12.7 mm) (1/3 of the chord width) and less than 1.0 in. (25.4 mm) (2/3 of the chord width) if the adjacent nozzle segments have no more than two cracks more than 0.5 in. (12.7 mm) (1/3
200 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 695 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------of the chord width) and less than 1.0 in. (25.4 mm) (2/3 of the chord width). (2) One crack maximum for each nozzle segment that is more than 1.0 in. (25.4 mm) (2/3 of the chord width) including open airfoil.
200 cycles
(3) One full chord crack on two airfoils for each segment if the adjacent nozzle segments have no more than one airfoil with a full chord crack.
25 cycles
(4) Nicks, dents, tears, missing pieces up to 2 in.2 (1290.32 mm2) on nonadjacent vanes provided there are no cracks extending from distressed areas
10 cycles
(5) Burned areas with missing material or melted
25 cycles
C. Stage 4 shroud abradable material (1) Worn, jagged or crushed sealing surface exceeding 50 percent of the honeycomb height provided sectors of the shroud abradable material are not missing
10 cycles
11. LPT Casing A. Forward and aft flanges (1) One crack connecting 2 bolt holes without penetrating pressure vessel outer skin
10 cycles
(2) One crack into skin 0.4 in. (10.16 mm) long maximum
10 cycles
B. External surface of the casing (1) One crack 0.4 in. (10.16 mm) long maximum C. Cooling air tube and manifold assemblies
10 cycles 10 cycles
(1) One separated circumferential tube
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 696 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(2) 3 in. (76.2 mm) cumulative cooling air manifold crack (3) One separated cooling air tube support D. Thread ports and bosses (1) One crack 0.5 in. (12.7 mm) maximum providing there is no leakage
10 cycles
12. Turbine frame A. Forward and aft flanges
10 cycles
(1) One circumferential crack connecting two bolt holes (2) One crack into skin 0.5 in. (12.7 mm) maximum B. Engine mounting lug areas airframe attach points only
10 cycles
(1) One crack out of one mount lug bolt hole 0.25 in. (6.35 mm) maximum (2) Skin crack 0.25 in. (6.35 mm) maximum. C. Threaded parts and bosses
10 cycles
(1) One crack 0.5 in. (12.7 mm) long providing there is no fluid or air leakage D. Stud on the aft face of the inner hub. (1) Missing/broken/loose stud(s): - One (1) or two (2) studs:
500hrs/500cyc
- Three (3) studs: *If not adjacent to each other:
500hrs/500cyc
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 697 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------*If two (2) non-serviceable studs are 500hrs/500cyc adjacent, but the third one is separated from them by two (2) serviceable studs: *If not:
Replace studs
- Four (4) studs or more:
Replace studs
E. Thermal insulation blankets
100 cycles
(1) Missing or protruding blankets F. Other areas
10 cycles
(1) One crack 0.25 in. (6.35 mm) maximum 13. Accessory gearbox A. Two opposite keylock studs missing provided there is no leakage at flange
3 cycles or 30 hours
B. Oil leakage from AGB/Starter carbon seal (Ref. TASK 79-00-00-210-003)
10 cycles provided seal drain line is disconnected and drain cavity is capped
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 698 Feb 01/10
C F M 56-5B TASK 72-00-00-200-026 Inspection/Check of the PS3 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific
plastic wire warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN)
No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddart solvent (Ref. 70-30-00) * graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 699 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP8001
Material No.
CP8002
* lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------36-11-49-000-044 36-11-49-400-044 71-13-00-010-040 71-13-00-410-040 72-00-00-991-313
Removal of the High Pressure Tee Duct Installation of the High Pressure Tee Duct Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Fig. 601
3. __________ Job Set-up Subtask 72-00-00-941-072 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A600 Feb 01/10
C F M 56-5B Subtask 72-00-00-010-086 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-00-00-991-313) CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO HOLD _______ THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. Subtask 72-00-00-210-068 A. Visual Inspection of the PS3 Line (1) Inspect the PS3 line as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. The tubes for: - cracks
Not serviceable
Replace the tube
- dents
4 per lineal foot, spaced at least 1 in. (25,4 mm) apart, provided depht of each dent does not exceed 20 percent of tube outer diameter for straight section or 10 percent of tube outer diameter for bend section
- flat areas
Lenght shall not be greater than 3 times the tube outer diameter, and contour change shall not exceed 20 percent of
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A601 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------tube outer diameter for straight section or 10 percent of tube outer diameter for bend section - nicks, scratches
0.005 in. (0,13 mm) max. depht
The hose for: - broken hose braid
3 broken wires per plait, and no more than 6 broken wires per assembly, or per lineal 12 in. (305 mm) of hose
- chafing on hose
Not serviceable
Replace the hose
- crimps
Not serviceable
Replace the hose
- cuts, tears, chafing on fire sleeves
Any number, provided maximum depth does not exceed one-half of sleeve thickness
Subtask 72-00-00-280-063 B. Dry out and Cleaning of the PS3 Line (1) Cut and remove the lockwire. (2) Disconnect the PS3 hose (20) from the ECU. (3) Disconnect the PS3 tube from the core engine as follows: (a) If necessary, get access to the PS3 restrictor: Remove the High Pressure Tee Duct (Ref. TASK 36-11-49-000-044). (b) Remove the nut (160), the bolt (190) and the clamp (180) which attach the PS3 tube (170) to the bracket (150), on flange P, at the 8 oclock position (Detail F).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A602 Feb 01/10
C F M 56-5B (c) Cut and remove the lockwires. (d) Disconnect the PS3 tube (170) from the restrictor (200). (e) Remove the restrictor from the engine. (4) Cut and remove the lockwires. (5) Disconnect the PS3 hose (20) from the ECU and from the PS3 tube (10). (6) Check the hose for blockage blocked hose is not serviceable: Replace the hose (20). (7) Blow clean dry air into the PS3 tube (10) end to remove any dirt or water accumulation in the PS3 line. Subtask 72-00-00-020-052 C. Removal of the PS3 Line Connections NOTE : Do the steps which follows only if you suspect leakage. ____ (1) Cut and remove the lockwire which safeties the PS3 tube (10) to the tube bundle. (2) Disconnect the PS3 tube (10) from the tube bundle. (3) Remove the parts which attach the PS3 tube (10) to the engine as follows: ---------------------------------------------------------------------------| REMOVE | FROM | NOTE | ---------------------------------------------------------------------------|Nut (70) | Bracket (40) and P25 | At the 6:30 oclock | |Bolt (30) | tube on flange G | position (Detail C) | |Outer spring clip (60) | | | |Inner spring clip (50) | | | |Plastic bushing (80) | | | ---------------------------------------------------------------------------|Nut (130) | Bracket (120) and P25 | At the 5 oclock | |Bolt (90) | on flange G | position (Detail C) | |Outer spring clip (100) | | | |Inner spring clip (110) | | | |Plastic bushing (140) | | | ---------------------------------------------------------------------------(4) Remove the PS3 tube (10) from the engine.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A603 Feb 01/10
C F M 56-5B Subtask 72-00-00-210-069 D. Inspection of the PS3 Line Connection (1) Inspect the connecting parts as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fitting nuts for: - damaged corners
Any amount, provided proper torque can be obtained
- damaged threads
Any amount, provided effective threads are not reduced by more than one after chasing
- safetywire hole deformation and wear
Serviceable, provided metal around hole is not cracked or torn
Chase the threads
2. Fittings and restrictor (200) seating surfaces for: - circumferential scratches
Any amount not detectable with a 0.04 in. (1 mm) radius ball scribe
- axial scratches
Not serviceable
Replace the tube or the part
- nicks, pits
Not serviceable
Replace the tube or the part
(2) If necessary, clean the parts with: stoddart solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A604 Feb 01/10
C F M 56-5B (3) If necessary, remove the dirt from the ECU nipple with a plastic wire. Take care to not introduce dirt into the ECU. (4) Check the tube bundle weep hole for clogging or dirt accumulation. (5) If necessary, clean the tube bundle weep hole with stoddart solvent (Material No. CP2011) or acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) and a plastic wire. Subtask 72-00-00-420-056 E. Installation of the PS3 Line CAUTION : DURING INSTALLATION, MAKE SURE THAT THE PS3 LINE DOES NOT TOUCH _______ THE LOWER STARTER DUCT OR OTHER PARTS IN THIS AREA. IF IT DOES, CHAFING OF THE PS3 HOSE CAN OCCUR. (1) Install the reducer (200) on the core engine. (2) TORQUE the reducer to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (3) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (4) Connect the PS3 tube (170) to the reducer on core engine. (5) TORQUE the connecting nut to between 135 and 150 lbf.in (1.52 and 1.69 m.daN). (6) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (7) Lubricate the threads of the bolt (190) with graphite grease (Material No. CP2101). (8) Install the clamp (180), the bolt (190) and the nut (160) which secure the PS3 tube (170) to the bracket (150) on flange M, at the 8 Oclock position (Detail F). (9) TORQUE the nut (160) to between 55 and 70 lbf.in (0.62 and 0.79 m.daN).
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Page A605 Feb 01/10
C F M 56-5B (10) If necessary, install the High Pressure Tee Duct (Ref. TASK 36-11-49400-044). (11) Lubricate the threads of the tube bundle tube. (12) Connect the PS3 tube (10) to the tube bundle tube nipple by hand. (13) Install the parts which secure the PS3 tube (10) to the engine as follows: ----------------------------------------------------------------------------| INSTALL | ON | NOTE | ----------------------------------------------------------------------------| Nut (70) | Bracket (40) and P25 | At the 6:30 Oclock | | Bolt (30) | tube on flange G | position (Detail C) | | Outer spring clip (60) | | | | Inner spring clip (50) | | | | Plastic bushing (80) | | | ----------------------------------------------------------------------------| Nut (130) | Bracket (120) and P25 | At the 5 Oclock | | Bolt (90) | tube on flange G | position (Detail C) | | Outer spring clip (100)| | | | Inner spring clip (110)| | | | Plastic bushing (140) | | | ----------------------------------------------------------------------------(14) TORQUE the PS3 tube (10) connecting nut to the tube bundle to between 135 and 150 lbf.in (1.52 and 1.69 m.daN). (15) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (16) TORQUE the nuts (70), (130) to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). (17) Lubricate the ECU and PS3 tube (10) nipples with engine fuel. (18) Connect the PS3 hose (20) to the ECU and to the PS3 tube (10). (19) TORQUE the PS3 hose connecting nuts to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (20) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). NOTE : The PS3 and the PS12 connecting nuts are safetied together. ____
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Page A606 Feb 01/10
C F M 56-5B 5. Close-up ________ Subtask 72-00-00-410-086 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
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Page A607 Feb 01/10
C F M 56-5B TASK 72-00-00-200-028 Visual Inspection of the Fan Section after Engine Operation in Severe Icing Condition 1. __________________ Reason for the Job You must do a visual inspection of the fan section area (primarily, the front end of the fan section) after the engines have operated in bad icing conditions. NOTE : This inspection can be done with the fan cowl and thrust reverser ____ cowl doors closed. If necessary, use an electric torch (flashlight) to look rearwards through the fan rotor blades. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
electric torch (flashlight) rubber mat, or equivalent floor protection
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-210-005 72-21-00-210-009 72-23-00-210-004
Inspection/Check of the Spinner Cone Inspect Fan Rotor Blades Installed on the Fan Disk Visual Inspection of the Fan Frame Assembly
3. __________ Job Set-up Subtask 72-00-00-941-073 A. Put a rubber mat, or equivalent floor protection, in the powerplant inlet cowl before you go into it to do this inspection. If necessary, use an electric torch (flashlight) for a better lighting aft of the fan rotor blades.
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Page A608 Feb 01/10
C F M 56-5B 4. Procedure _________ Subtask 72-00-00-210-072 A. Visual Inspection (1) Look for possible damage to the spinner front and rear cones exposed areas (Ref. TASK 72-21-00-210-005). (2) Examine the general condition of the fan rotor blades (Ref. TASK 7221-00-210-009). (3) Look for possible damage to the fan forward acoustical panels (Ref. TASK 72-23-00-210-004). (4) Through the fan rotor blades, look for possible damage to: NOTE : If necessary, (dim lighting conditions) use an electric torch ____ (flashlight). (a) The leading edge of fan outlet guide vanes (OGVs), (b) Splitter fairing, (c) Fan mid acoustical panels (located between the fan rotor blades and the OGV assembly), (Ref. TASK 72-23-00-210-004). 5. Close-up ________ Subtask 72-00-00-869-074 A. Put the aircraft back to its initial configuration. (1) Remove the rubber mat, or equivalent floor protection from the powerplant inlet cowl. (2) Make sure the inlet cowl area is clean and clear of tool(s) and other items.
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Page A609 Feb 01/10
C F M 56-5B TASK 72-00-00-280-002 Monitor the Engine EGT for Possible Engine Performance Deterioration 1. __________________ Reason for the Job PRE SB CFM56-5B 72-182 This TASK is applicable for /P engines. POST SB CFM56-5B 72-182 After SB CFM56-5b 72-182 is done with the 2D stage 9 blades, this TASK is no longer needed. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 TSM
77-00-00-810-849
Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EGT Overlimit on Engine 1 or 2
3. __________ Job Set-up Subtask 72-00-00-861-054 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 72-00-00-869-085 B. Get the engine takeoff EGT data, with the use of the MCDU or DAR/QAR data.
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Page A610 Feb 01/10
C F M 56-5B 4. Procedure _________ Subtask 72-00-00-280-065 A. Do this procedure to get engine EGT trend information. (1) Takeoff EGT data must be recorded and evaluated as follows: (a) Once each month during usual conditions. (b) Once each week if the calculated EGT margin (see EGT Calculation Procedure paragraph) becomes 20 deg.C (36.00 deg.F), or less. (c) Once each day if the calculated EGT margin (see EGT Calculation Procedure paragraph) becomes 10 deg.C (18.00 deg.F), or less. (d) The next flight immediately after an unusual condition that can cause engine deterioration such as: 1 _
a bird strike,
2 _
other unwanted materials that have gone into the engine,
3 _
engine vibration advisory warning.
(2) After an unusual condition, if the data shows an EGT margin more than the 20 deg.C level, examine the data once each month. After an unusual condition, if the data shows an EGT margin between the 10 deg.C and 20 deg.C levels, examine the data once each week. Subtask 72-00-00-970-050 B. EGT Calculation Procedure (1) Do the procedure that follows to calculate the EGT margin. (a) Use the CFMI trend monitoring programs (GEM or ADEPT) and process the recorded takeoff data. (b) Calculate 5B/P EGTMARGIN as follows: EGTMARGIN=EGTMAR+EGTADJ where: EGTMAR=EGT margin output from GEM or ADEPT and EGTADJ=adjustment shown in Table as compared to engine rating
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Page A611 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------| Engine Model Rating | ------------------------------------------------------------------------------| | 5B1/P | 5B2/P | 5B3/P | 5B4/P | 5B5/P | 5B6/P | | | or | or | or | or | or | or | | | 5B1/2P | 5B2/2P | 5B3/2P | 5B4/2P | 5B5/2P | 5B6/2P | ------------------------------------------------------------------------------| EGTADJ⁰C | -34 | -20 | -3 | -23 | -66 | -48 | ------------------------------------------------------------------------------(2) If the EGTMARGIN calculated becomes negative, do the correction procedures that follow: (a) Troubleshoot the engine (Ref. TSM TASK 77-00-00-810-849). (b) If no errors are found or a cause that can be corrected is not found, the engine must be removed after not more than five flights. (c) If EGT or data systems errors are found, they must be corrected and the EGT must continue to be monitored. 5. Close-up ________ Subtask 72-00-00-862-054 A. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).
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Page A612 Feb 01/10
C F M 56-5B ENGINE - GENERAL - CLEANING/PAINTING ____________________________________ TASK 72-00-00-100-007 Engine Dry-out and Re lubrication 1. __________________ Reason for the Job It is recommended to do this procedure as soon as possible after landing in the event of: - An In-Flight Shutdown (IFSD). - An engine was ferried. You can ignore this procedure if the engine is to be operated in the limit of 24 hours after landing. In this case, run the engine for a minimum of 15 to 20 minutes at ground idle power.
R R R R R
2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 856A2320 856A2659 856A2718 856A2796 856A3810
1 1 1 1 1
hot air hose hot air source warning notice TOOL SET,DRYING AND RELUBRICATION-ENGINE SUMPS FILTER ADAPTER TOOL SET,R/I-DRIVE SHAFTS SAFETY PROTECTOR _ HANDCRANKING PAD ADAPTER, AIR - DRY OUT ENGINE SUMPS
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
Material No.
CP5067
Material No.
CP5075
* engine oil (Ref. 70-30-00) * lube system corrosion preventive oil (Ref. 70-30-00) * corrosion preventive additive (Ref. 70-30-00)
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Page 701 Feb 01/10
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-63-00-000-002 72-63-00-400-002 78-36-00-410-040 79-00-00-281-003 72-00-00-991-300 72-00-00-991-301 72-00-00-991-302 72-00-00-991-303
Opening of the Fan Cowl Doors Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Closing of the Thrust Reverser Doors Check of FWD, AFT Sump, AGB, and TGB scavenge screens Fig. 701 Fig. 702 Fig. 703 Fig. 704
3. __________ Job Set-up Subtask 72-00-00-941-063 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-071 B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 702 Nov 01/08
C F M 56-5B Subtask 72-00-00-160-052 C. Material Requirements: (1) Hot air source characteristics: (a) Output: 120-130 lb/min (54-59 kg/min) (b) Temperature: 300-325 deg. F (150-163 deg. C) (c) Supply pressure: 30-44 psi (207-303 kPa) (2) Air filter characteristics: (a) Filtration : 25 microns absolute (b) Temperature: 300-325 deg. F (150-163 deg. C) (c) Min. flow capacity: 2 lb/sec (0.9 kg/sec) (d) Differential pressure: 10 psi (69 kPa) (e) Working pressure: 70 psi (5 bar) (f) Proof pressure: 105 psi (7 bar) (3) Air circulation: (a) The hot air flows through the exhaust nozzle, aft and forward sumps, TGB and AGB assemblies, engine flow path, and open scavenge circuits of the lubrication unit. Subtask 72-00-00-020-051 D. Preparation before the job (1) Remove the scavenge screen plugs. (2) If the core engine can turn, remove the handcranking drive cover (Ref. TASK 72-63-00-000-002). (3) Fill the oil container of the TOOL SET,DRYING AND RELUBRICATIONENGINE SUMPS (856A2320G02) as follows: (a) When you use the lube system corrosion preventive oil (Material No. CP5067), put 0.8 l (0.21 USgal) of oil in the container.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 703 Nov 01/08
C F M 56-5B (b) When you use corrosion preventive additive (Material No. CP5075), mix a solution of 0.4 l (0.11 USgal) of product with an equal quantity of engine oil (Material No. CP2442) in the container. 4. Procedure _________ (Ref. Fig. 701/TASK 72-00-00-991-300, 702/TASK 72-00-00-991-301, 703/TASK 72-00-00-991-302, 704/TASK 72-00-00-991-303) Subtask 72-00-00-480-051 A. Installation of the Dry Out and Relubrication Tools WARNING : WEAR HEAVY PROTECTIVE GLOVES TO HANDLE THE HOT AIR HOSES, _______ FILTER AND SOURCE WHEN THEY ARE HOT. (1) Install the TOOL SET,DRYING AND RELUBRICATION-ENGINE SUMPS (856A2320G02) as follows: (a) Install the sleeves (10) in the lubrication unit. (b) Tighten the sleeves, and make the sleeves openings face together, as shown in (Ref. Fig. 701/TASK 72-00-00-991-300) (c) Lubricate the o-rings of the tool body and of the knurled knobs (20) with engine oil (Material No. CP2442). (d) Install the tool body and attach it to the sleeves (10) with the knurled knobs (20). (e) Tighten the knurled knobs. (2) Install the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01) as follows: (a) Install the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01) in position on the exhaust nozzle end. (b) Attach the jaws (70) to the exhaust nozzle end with bolts (90) and nuts (80). (c) Tighten the nuts (80). (d) Tighten the nuts (60).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 704 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-00-00 CES
Page 705 Aug 01/09
C F M 56-5B
Engine Sumps Relubrication Tool Setup Figure 701/TASK 72-00-00-991-300- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 706 Nov 01/08
C F M 56-5B
Engine Sumps Relubrication Tool Setup Figure 701/TASK 72-00-00-991-300- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 707 Nov 01/08
C F M 56-5B
Dry Out Air Adapter Attachment to Rear End of Exhaust Plug Figure 702/TASK 72-00-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 708 Nov 01/08
C F M 56-5B
Engine Dry-out Figure 703/TASK 72-00-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 709 Nov 01/08
C F M 56-5B
Engine Relubrication Figure 704/TASK 72-00-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 710 Nov 01/08
C F M 56-5B (3) If the core engine can turn, install the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01) as follows: (a) Put the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01) in position on the AGB. (b) Tighten the bolts. (c) Lubricate the seal of the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01) with engine oil (Material No. CP2442). (d) Engage the wrench, part of TOOL SET,R/I-DRIVE SHAFTS (856A2718G02/P04) in the handcranking drive, throught the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01). (4) Connect the hot air source and the FILTER ADAPTER (856A2659G01) to the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01). Subtask 72-00-00-160-053 B. Dry-out of the engine WARNING : STAY CLEAR OF THE LUBRICATION UNIT BY 20 FEET BECAUSE HOT AIR _______ WILL BE BLOWN FROM THE TOOL SET-RELUBE ENG. SUMPS. (1) Turn on the hot air source. (2) Increase the air temperature slowly and continuously 150 deg.C (302 deg.F) to 163 deg.C (325 deg.F) . (3) Blowing: WARNING : WEAR HEAVY PROTECTIVE GLOVES TO AVOID INJURY WHEN MANUALLY _______ TURNING THE FAN ROTOR. (a) Blow hot air into the engine for 20 minutes. (4) During this period, turn the fan rotor 3-4 times by hand, and if possible, turn the core engine 3-4 times with the wrench, part of TOOL SET,R/I-DRIVE SHAFTS (856A2718G02/P18). (5) Turn on the hot air source off. (6) Disconnect the hot air hose from the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01) and connect it to the TOOL SET,DRYING AND RELUBRICATION-ENGINE SUMPS (856A2320G02).
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Page 711 Aug 01/09
C F M 56-5B Subtask 72-00-00-640-051 C. Relubrication of the engine WARNING : STAY CLEAR FROM THE EXHAUST NOZZLE NOT TO BREATHE OIL MIST. _______ (1) Turn on the hot air source. (2) Increase the air temperature slowly and continuously 150 deg.C (320 deg.F) 163 deg.C (325 deg.F) . (3) Open the oil supply valve (30). (4) Turn the fan rotor and the core engine: WARNING : WEAR HEAVY PROTECTIVE GLOVES TO AVOID INJURY WHEN MANUALLY _______ TURNING THE FAN ROTOR. (a) Turn the fan rotor and the core engine (if possible) approximately once every minute, until the oil container is empty (5-6 minutes). (5) Turn the hot air source off. (6) Disconnect the hot air hose from the TOOL SET,DRYING AND RELUBRICATION-ENGINE SUMPS (856A2320G02). (7) Let the engine temperature decrease to the ambiant temperature. Subtask 72-00-00-080-051 D. Removal of the tools (1) Remove the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01) as follows. (a) Loosen the nuts (60). (b) Loosen the nuts (80). (c) Disengage the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01) from the exhaust nozzle end. (2) Remove the TOOL SET,DRYING AND RELUBRICATION-ENGINE SUMPS (856A2320G02) from the lubrication unit as follows: (a) Make sure that the oil supply valve is closed.
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Page 712 Aug 01/09
C F M 56-5B (b) Disconnect the oil supply and air pressure supply lines from the oil container. (c) Loosen the knurled knobs (20). (d) Remove the tool body from the sleeves (10). (e) Remove the sleeves (10) from the lubrication unit. (3) If installed, remove the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01) as follows: (a) Disengage the wrench, part of TOOL SET,R/I-DRIVE SHAFTS (856A2718G02/P04) from the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01). (b) Remove the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01) from the AGB. 5. Close-up ________ Subtask 72-00-00-420-054 A. Procedure after the job (1) If necessary, install the handcranking drive cover (Ref. TASK 72-6300-400-002). (2) Make sure that the scavenge screens are clean and serviceable (Ref. TASK 79-00-00-281-003). (3) Install the scavenge screen plugs. Subtask 72-00-00-410-071 B. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the warning notice(s).
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Page 713 Aug 01/09
C F M 56-5B TASK 72-00-00-100-008 Engine Washing Requirements CAUTION : DO NOT USE METHANOL OR ENGINE TITANIUM PARTS COULD BE DAMAGED. _______ CAUTION : DO NOT WASH AN ENGINE WHICH HAS BEEN EXPOSED TO DRY CHEMICAL FIRE _______ EXTINGUISHING AGENTS. CAUTION : DO NOT WASH AN ENGINE UNLESS THE EGT IS BELOW 150 DEG.F (66 DEG.C). _______ CAUTION : DO NOT WASH AN ENGINE AT TEMPERATURE BELOW 14 DEG.F (-10 DEG.C). _______ 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
Material No.
CP5060
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * gas path cleaner (Ref. 70-30-00)
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Page 714 Aug 01/09
C F M 56-5B B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-100-026 72-00-00-100-028
Washing of the Engine Gas Path with Pure Water Washing of the Engine Gas Path with Cleaning Agent
3. __________ Job Set-up Subtask 72-00-00-869-075 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-110-061 A. Engine Washing Requirements (1) General (a) You can wash the engine either with pure water only (Ref. TASK 72-00-00-100-026), or with a solution of gas path cleaner (Material No. CP5060) (Ref. TASK 72-00-00-100-028). 1 _
For EGT margin recovery, it is recommended to perform the engine gas path water wash with pure water only (without cleaning agent) (Ref. TASK 72-00-00-100-026). Pure water (without detergent) is effective in most situations depending on the engine operating environment and the gas path cleaning program implemented by the operator.
2 _
An engine gas path water wash using detergent (Ref. TASK 7200-00-100-028) provides the most effective method for cleaning the engine compressors. However, the use of detergent requires the strict application of the engine rinsing and bleed system cycling per AMM procedures to thus prevent fumes in the cabin when the aircraft resumes revenue service operation. Consideration should be given to accomplishing gas path cleaning with detergent if any of the following conditions are met: - organic debris or oil deposits are observed on compressor airfoil. - the engine has less than 10 deg. C EGT margin left.
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Page 715 Aug 01/09
C F M 56-5B (b) In both cases, you can use isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) as anti-freeze agent, if necessary. (2) Water (a) Water properties 1 _
Do not use water with more than 100 parts per million total solids.
2 _
Do not use water with more than 25 parts per million sodium plus potassium (Na+K), and with a pH of 6.8-8.0 (potable water usually meets these requirements).
3 _
Hot water 150 deg.F (66 deg.C) to 200 deg.F (93 deg.C) is more effective for cleaning or rinsing.
(b) Water flow CAUTION : DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) _______ PER MINUTE. IF NOT, THEN ENGINE DAMAGE CAN OCCUR. 1 _
Apply a water flow between 5 USgal (19 l) and 6 USgal (23 l) per minute.
(c) Water temperature 1 _
For best results, increase the temperature of the water to 150 deg.F (66 deg.C) to 200 deg.F (93 deg.C).
2 _
Hot water 150 deg.F (66 deg.C) to 200 deg.F (93 deg.C) will wash and rinse the gas path with more efficiency than cold water.
(3) Cleaning solution (if required) WARNING : USE RUBBER GLOVES AND EYE PROTECTION WHEN HANDLING LIQUID _______ DETERGENT. LIQUID DETERGENT AND ANTI-FREEZE SOLVENT HAVE LOW FLASHPOINTS. KEEP AWAY FROM HEAT AND OPEN FLAME. PROVIDE ADEQUATE VENTILATION. STAND AT LEAST 3 FEET (1M) AWAY FROM COWLING INLET WHEN SPRAYING LIQUIDS INTO ENGINE TO AVOID PERSONAL INJURY.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 716 Aug 01/09
C F M 56-5B (a) Mix 20 to 25 percent of gas path cleaner (Material No. CP5060) with 75 to 80 percent water. (4) Anti-freeze mixtures WARNING : USE RUBBER GLOVES AND EYE PROTECTION WHEN HANDLING LIQUID _______ DETERGENT. LIQUID DETERGENT AND ANTI-FREEZE SOLVENT HAVE LOW FLASHPOINTS. KEEP AWAY FROM HEAT AND OPEN FLAME. PROVIDE ADEQUATE VENTILATION. STAND AT LEAST 3 FEET (1M) AWAY FROM COWLING INLET WHEN SPRAYING LIQUIDS INTO ENGINE TO AVOID PERSONAL INJURY. CAUTION : USE ONLY ISOPROPYL ALCOHOL AS AN ANTI-FREEZE MIXTURE. _______ METHANOL CAN CAUSE CORROSION OF THE TITANIUM PARTS OF THE ENGINE. (a) Use anti-freeze mixtures at temperatures below 40 deg.F (5 deg.C). (b) Prepare mixtures as follows: 1 _
For temperatures of 40 deg.F (5 deg.C) to 23 deg.F (-5 deg.C), mix 25 percent of isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) to 75 percent of water.
2 _
For temperatures of 23 deg.F (-5 deg.C) to 14 deg.F (-10 deg.C), mix 35 percent of isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) to 65 percent of water.
(c) Do not use anti-freeze mixtures at temperatures below 14 deg.F (-10 deg.C).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 717 Aug 01/09
C F M 56-5B TASK 72-00-00-100-025 Hand Cleaning of the Fan Gas Path and Fan Blades 1. __________________ Reason for the Job This cleaning procedure gives instructions to remove the contamination from the fan blades, the Outlet Guide Vanes (OGV) and the acoustical panels of an engine, by hand washing. NOTE : It is recommended that you clean the fan blades and the gas path at ____ the same time. NOTE : This task can contribute to fuel savings. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R R
Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2240
Material No.
CP2279
Material No.
CP2470
Material No.
CP2559
Material No.
CP2560
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * scotch brite type A CFS (Ref. 70-30-00) * scotch brite type S CFS (Ref. 70-30-00) * TURCO 5948 DPM (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 718 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
Material No.
CP5060
* mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * gas path cleaner (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-100-008
Engine Washing Requirements
3. __________ Job Set-up Subtask 72-00-00-941-064 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 719 Aug 01/09
C F M 56-5B 4. Procedure _________ Subtask 72-00-00-110-062 A. Hand Cleaning of the Fan Gas Path CAUTION : DO NOT USE METHANOL OR ENGINE TITANIUM PARTS COULD BE DAMAGED. _______ (1) Mix 20 percent of gas path cleaner (Material No. CP5060) with 80 percent of water. (2) Spraying CAUTION : DO NOT SPRAY CLEANING SOLUTION DIRECTLY INTO BOOSTER (LPC) _______ INLET. IF THE CLEANING SOLUTION IS PUT INTO THE BOOSTER INLET, THE ENGINE MUST BE OPERATED TO DRY OUT THE SOLUTION, OR ENGINE DAMAGE CAN OCCUR. (a) Use anti-freeze mixture, if necessary (Ref. TASK 72-00-00-100008). (b) Spray the blades, the Outlet Guide Vanes (OGV), the acoustical panels and the fan inlet and outlet with the wash solution. Do not spray the fan wash solution into the Low Pressure Compressor (LPC) inlet. NOTE : Apply the solution to the two sides of the blade at the 6 ____ oclock position. This will decrease the amount of solution that touches the blade dovetails. The solution will remove the lubricant. If you wipe the blades, do it in the down direction, away from the rotor. (3) Rub the sprayed areas with a cloth. (4) Rinse the blades with water. Subtask 72-00-00-110-063 B. Fan Blades Cleaning (1) If the blades stay dirty, do the procedure which follows: CAUTION : DO NOT USE THIS SOLVENT NEAR FLAMES OR HEAT, BECAUSE THIS _______ SOLVENT IS FLAMMABLE. DO NOT BREATHE THE GASES RELEASED FROM SOLVENT, DO NOT LET IT TOUCH YOUR SKIN OR CLOTHING AND MAKE SURE YOU HAVE A GOOD FLOW OF AIR, BECAUSE THIS SOLVENT IS DANGEROUS TO YOUR SKIN, EYES AND LUNGS.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 720 Aug 01/09
R R R R
C F M 56-5B (a) Remove light deposits with soft cloth and acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041) or TURCO 5948 DPM (Material No. CP2470). (b) Remove heavy stubborn deposits with scotch brite type A CFS (Material No. CP2240) or scotch brite type S CFS (Material No. CP2279) and acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041) or TURCO 5948 DPM (Material No. CP2470).
R R R R
(c) Rinse thoroughly with water. 5. Close-up ________ Subtask 72-00-00-869-064 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-00-00-942-052 B. Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 721 Aug 01/09
C F M 56-5B TASK 72-00-00-100-026 Washing of the Engine Gas Path with Pure Water CAUTION : IF CLEANING AGENT IS USED, PROPER AIRCRAFT MAINTENANCE CONFIGURATION, _______ ENGINE RINSING AND POST ENGINE WASH TEST MUST BE COMPLETED TO PREVENT THE POSSIBILITY OF FUMES IN THE CABIN WHEN AIRCRAFT RESUMES REVENUE FLIGHT OPERATION. 1. __________________ Reason for the Job For Exhaust Gas Temperature (EGT) margin recovery, it is recommended to perform the engine gas path water wash with pure water only. NOTE : This task can contribute to fuel savings. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN)
No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP5067
Material No.
CP5075
Material No.
CP8001
Material No.
CP8002
* lube system corrosion preventive oil (Ref. 70-30-00) * corrosion preventive additive (Ref. 70-30-00) * lockwire (Ref. 70-30-00) * lockwire (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 722 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 21-00-00-615-003 21-00-00-615-004 24-41-00-861-002 24-41-00-862-002 71-00-00-710-001 71-00-00-710-003 71-00-00-710-028 71-13-00-010-040 71-13-00-410-040 72-00-00-100-008 72-00-00-991-325 72-00-00-991-304
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Decontamination of the Environmental Control System (ECS) when the Temperature is below 24 deg.C (Engine/s) Decontamination of the Environmental Control System (ECS) when the Temperature is above 24 deg.C (Engine/s) Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Dry Motoring Check Engine Automatic Start Engine Shutdown Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Engine Washing Requirements Fig. 705 Fig. 706
3. __________ Job Set-up Subtask 72-00-00-941-065 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ENG/FADEC GND PWR/1(2) pushbutton switch is OFF (the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 723 Aug 01/09
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-072 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ Subtask 72-00-00-110-057 A. Preparation of the Engine for Washing (1) For engine washing requirements (Ref. TASK 72-00-00-100-008). NOTE : The disconnection of P25 line is only available for engines ____ equipped with PMUX option. (2) Disconnect PS3 line and P25 line (if installed) from the Electronic Control Unit (ECU). (3) Plug the open tubes and ports of the ECU with standard protective covers. (4) Disconnect the rigid anti-ice servo pressure line (25) from the nacelle anti-ice valve (NAI). (Ref. Fig. 705/TASK 72-00-00-991-325) NOTE : Let the rigid anti-ice servo pressure line free (not plugged) ____ during the washing of the engine. (5) Install a standard protective cover on the anti-ice servo pressure line port of the NAI valve. (6) Prepare an anti-freeze mixture, if necessary, as defined in engine washing requirements (Ref. TASK 72-00-00-100-008). CAUTION : CORROSION PREVENTIVE ADDITIVE SHOULD BE USED. HOWEVER, IF _______ NONE OF THE CORROSION PREVENTIVE PRODUCTS SPECIFIED (REFER TO CHAPTER B. CONSUMABLE MATERIALS) IS AVAILABLE, THE ENGINE MUST RESUME REVENUE SERVICE OPERATION WITHIN 24 HOURS FOLLOWING THE POST ENGINE WASH TEST.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 724 Aug 01/09
C F M 56-5B
Rigid Anti-Ice Muscle Line Figure 705/TASK 72-00-00-991-325 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 725 Aug 01/09
C F M 56-5B (7) Service the oil tank with one quart (one liter) of lube system corrosion preventive oil (Material No. CP5067) or corrosion preventive additive (Material No. CP5075) (Ref. TASK 12-13-79-610002). NOTE : The oil tank must be topped off up to the window mark. ____ Subtask 72-00-00-861-051 B. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 72-00-00-860-051 C. Aircraft Maintenance Configuration (1) On the ANTI ICE section of panel 25VU, make sure that the ANTI ICE/ENG 1(2) pushbutton switch is OFF (the ON legend of the ANTI ICE/ENG 1(2) pushbutton switch is off). (2) On the AIR COND panel 30VU, make sure that ENG 1(2) BLEED pushbutton switch is OFF (the OFF legend of the ENG1(2) BLEED is on). (3) On the AIR COND panel 30VU, make sure that PACK 1 and PACK 2 pushbutton switches are OFF (the OFF legend of the PACK 1 and the PACK 2 pushbutton switches are on). Subtask 72-00-00-110-058 D. Engine Washing CAUTION : DO NOT WASH AN ENGINE WHICH HAS BEEN EXPOSED TO DRY CHEMICAL _______ FIRE EXTINGUISHING AGENTS. CAUTION : DO NOT WASH AN ENGINE UNLESS THE EGT IS BELOW 150 DEG.F (66 _______ DEG.C). CAUTION : DO NOT WASH AN ENGINE AT TEMPERATURE BELOW 14 DEG.F (-10 _______ DEG.C). CAUTION : THE FUEL PUMP AND HYDRO-MECHANICAL UNIT (HMU) ARE FUEL _______ LUBRICATED. DO NOT MOTOR, START, OR OPERATE ENGINE UNLESS A POSITIVE FUEL INLET PRESSURE IS INDICATED ON THE LOWER ECAM (FUEL SYSTEM PAGE). DAMAGE TO COMPONENTS MAY RESULT. CAUTION : DO NOT EXCEED STARTER DUTY CYCLE. STARTER DAMAGE MAY RESULT. _______
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 726 Aug 01/09
C F M 56-5B CAUTION : MAKE SURE THE N1 ROTOR TURNS FREELY THROUGHOUT WASHING TO _______ PREVENT OIL SYSTEM CONTAMINATION. CAUTION : DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) PER _______ MINUTE. IF NOT, THEN ENGINE DAMAGE CAN OCCUR. CAUTION : DRY MOTOR CYCLE DURATIONS MUST NOT EXCEED 2 MINUTES (REFER TO _______ AMM TASK 71-00-00-710-001). (1) Dry motor the engine for two minutes (Ref. TASK 71-00-00-710-001). (2) After 10 seconds of motoring with a positive fan rotation, inject the water at 1 oclock position (aft view) on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LP compressor inlet if a specific rig is used). (3) Stop the water injection before the end of the engine motoring. (4) Let the engine soak for 5 minutes. (5) Repeat steps (1) to (4). (6) Let the engine soak for 5 minutes. (7) Dry motor the engine again (Ref. TASK 71-00-00-710-001). NOTE : Water can potentially drain out of the disconnected rigid ____ anti-ice servo pressure line. If water drains out, continue to dry motor the engine until there is no more water draining out of the line. Subtask 72-00-00-420-055 E. Installation of PS3 Line and P25 Line (1) Remove the plugs from the PS3 and P25 lines and from the ECU. CAUTION : DO NOT BLOW COMPRESSED AIR OR NITROGEN INTO THE ECU AS _______ DAMAGE TO THE ECU CAN OCCUR. (2) Blow PS3 and P25 lines clear of water using compressed air or nitrogen. CAUTION : DURING INSTALLATION, MAKE SURE THAT THE PS3 LINE DOES NOT _______ TOUCH THE LOWER STARTER DUCT OR OTHER PARTS IN THIS AREA. IF IT DOES, CHAFING OF THE PS3 HOSE CAN OCCUR.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 727 Aug 01/09
C F M 56-5B (3) Connect PS3 line to ECU, TORQUE to between 270 and 300 lbf.in (3.05 and 3.39 m.daN) and safety with lockwire (Material No. CP8001) or lockwire (Material No. CP8002). (4) Connect P25 line to ECU, TORQUE to between 180 and 200 lbf.in (2.03 and 2.26 m.daN) and safety with lockwire (Material No. CP8001) or lockwire (Material No. CP8002). (5) Remove the standard protective cover from the nacelle anti-ice line port of the NAI valve. (6) Connect the rigid anti-ice servo pressure line (25) to nacelle anti-ice valve (4000 DN). TORQUE the forward hose nut to between 135 and 150 lbf.in (1.52 and 1.69 m.daN) . Subtask 72-00-00-410-085 F. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the following engine fan cowl doors (Ref. TASK 71-13-00-410040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-620-063 G. Post Engine Wash Test (Ref. Fig. 706/TASK 72-00-00-991-304) (1) On the AIR COND panel 30VU, make sure that: - The crossbleed valve selector switch is in the OPEN position. (2) Start the engine within 2 hours (or 30 minutes in icing condition) of the last wash cycle to purge the lube/sump system of any water ingestion (Ref. TASK 71-00-00-710-003). NOTE : APU bleed valve must be closed (the ON legend of the APU bleed ____ pushbutton switch is OFF) after engine start, to avoid the supply of air to the wing anti-ice systems from the APU.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 728 Aug 01/09
C F M 56-5B
Engine Cleaning (Washing with Pure Water) Figure 706/TASK 72-00-00-991-304 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 729 Aug 01/09
C F M 56-5B NOTE : This engine run is done to ensure that the bleed system is ____ free from contaminant. Smoke/Smell in the cabin and Starter Air Valve (SAV) contamination can result if contaminant enters the bleed system. NOTE : Corrosion preventive products (refer to chapter B. Consumable ____ Materials) must be used if not done already. If none of the corrosion preventive products specified above are available, the engine must resume Revenue Service operation within 24 hours following this Post Wash Test. (a) Let the engine run at idle for 5 minutes. (b) After 5 minutes from engine start, do the following: 1 _
Press the ENG 1(2) BLEED pushbutton switch to operate the engine bleed system.
2 _
Make sure that the OFF legend of the ENG1 (2) BLEED pushbutton switch goes off when the engine bleed system operates.
3 _
Press the ANTI ICE/WING pushbutton switch to operate the wing anti-ice system. NOTE : The aim is to purge water potentially trapped in High ____ Pressure (HP) bleed ducts and HP engine bleed chambers.
4 _
Make sure that the ON legend of the ANTI ICE/WING pushbutton switch goes on when the wing anti-ice system operates. NOTE : The Wing Anti-Ice (WAI) valves will automatically close ____ 30 seconds after the Wing Anti-Ice system is selected ON. This is to prevent wing slats overheat. However, the ON legend remains illuminated until the switch is deselected.
5 _
Make sure that Pressure Regulating Valve (PRV) and High Pressure Valve (HPV) are open on ECAM BLEED page with engine running at this speed while WAI valve is open.
6 _
Once WAI valve is closed, let the engine run at idle for 5 minutes. NOTE : Do not actuate WAI systems before the 5-minute period ____ at idle is over in order to avoid WAI systems overheat.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 730 Aug 01/09
C F M 56-5B 7 _
Increase and stabilize engine thrust to at least 60 percent Fan (N1).
8 _
Press twice the ANTI ICE/WING pushbutton switch to operate the Wing Anti-Ice system once more. NOTE : The aim is to purge water potentially trapped in IP ____ bleed ducts and IP engine bleed chambers. NOTE : If the Wing Anti-Ice ON legend is still on, pressing ____ twice the WAI pushbutton switch enables a second WAI cycle of 30 seconds to be started. NOTE : Do not perform more than two attempts with a minimum of ____ 5 minutes between the two attempts, in order to avoid WAI systems overheat.
9 _
Make sure that the ON legend of the ANTI ICE/WING pushbutton switch comes on when the wing anti-ice system operates.
10 __
Make sure that PRV is open and HPV is closed on ECAM BLEED page with engine running at this speed while the WAI valve is open.
(c) Once the WAI valve is closed, pull the throttle to stabilize the engine thrust at idle for 5 minutes. (d) After 15 minutes from engine start, do the following: 1 _
Press the ANTI ICE/WING pushbutton switch and make sure that the ON legend of the ANTI ICE/WING pushbutton switch goes off.
2 _
Turn the crossbleed valve selector switch to the AUTO position.
3 _
Press the PACK 1 (2) pushbutton switch to operate the air conditioning pack.
4 _
Make sure that the OFF legend of the PACK 1 (2) pushbutton switch goes off.
5 _
Check for evidence of anti-freeze mixture odor/smoke in the cabin. - If evidence is found, continue to operate the engine at idle until no odor/smoke remains in the cabin.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 731 Aug 01/09
C F M 56-5B - After 10 minutes engine running, if continuous odor/smoke remains in the cabin, shut down the engine (Ref. TASK 71-0000-710-028) and decontaminate the Environmental Control System (ECS). Note that APU Bleed valve must be open before engine shutdown - When Ambient Air Temperature is below 75.2 Deg F (24 Deg C) (Ref. TASK 21-00-00-615-003) - When Ambient Air Temperature is above 75.2 Deg F (24 Deg C) (Ref. TASK 21-00-00-615-004) - If no evidence is found, shut down the engine (Ref. TASK 7100-00-710-028). 5. Close-up ________ Subtask 72-00-00-869-065 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-00-00-862-051 B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). Subtask 72-00-00-942-053 C. Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 732 Aug 01/09
C F M 56-5B TASK 72-00-00-100-028 Washing of the Engine Gas Path with Cleaning Agent 1. __________________ Reason for the Job Engine washing with cleaning agent is preferred when organic debris or oil deposits are present or remaining EGT margin is less than 5 deg. C. NOTE : When cleaning agent is used, proper Aircraft Maintenance ____ Configuration, engine rinsing and post engine wash test must be completed to prevent the possibility of fumes in the cabin when Aircraft resumes revenue flight operation. NOTE : The engine bleed system must be operative prior to proceeding with ____ engine washing with cleaning agent. Check that there is no failure message on the engine bleed system. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN)
No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP5067
Material No.
CP5075
Material No.
CP8001
Material No.
CP8002
* lube system corrosion preventive oil (Ref. 70-30-00) * corrosion preventive additive (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) DIA (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) DIA (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 733 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 21-00-00-615-003 21-00-00-615-004 24-41-00-861-002 24-41-00-862-002 71-00-00-710-001 71-00-00-710-001 71-00-00-710-003 71-00-00-710-028 71-13-00-010-040 71-13-00-410-040 72-00-00-100-008 72-00-00-991-325 72-00-00-991-322
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Decontamination of the Environmental Control System (ECS) when the Temperature is below 24 deg.C (Engine/s) Decontamination of the Environmental Control System (ECS) when the Temperature is above 24 deg.C (Engine/s) Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Dry Motoring Check Dry Motoring Check Engine Automatic Start Engine Shutdown Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Engine Washing Requirements Fig. 705 Fig. 707
3. __________ Job Set-up Subtask 72-00-00-941-101 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 734 Aug 01/09
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-138 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ Subtask 72-00-00-110-079 A. Preparation of the Engine for Washing CAUTION : CORROSION PREVENTIVE ADDITIVE SHOULD BE USED. HOWEVER, IF NONE _______ OF THE CORROSION PREVENTIVE PRODUCTS SPECIFIED (REFER TO CHAPTER B. CONSUMABLE MATERIALS) IS AVAILABLE, THE ENGINE MUST RESUME REVENUE SERVICE OPERATION WITHIN 24 HOURS FOLLOWING THE POST ENGINE WASH TEST. (1) For engine washing requirements (Ref. TASK 72-00-00-100-008). NOTE : The disconnection of the P25 line is only available for ____ engines equipped with the PMUX option. (2) Disconnect PS3 line and P25 line (if installed) from the Electronic Control Unit (ECU). (3) Plug the open tubes and ports of the ECU with standard protective covers. (4) Disconnect the rigid anti-ice servo pressure line (25) from the nacelle anti-ice valve (NAI). (Ref. Fig. 705/TASK 72-00-00-991-325) NOTE : Let the rigid anti-ice servo pressure line free (not plugged) ____ during the washing of the engine. (5) Install a standard protective cover on the anti-ice servo pressure line port of the NAI valve. (6) Prepare an anti-freeze mixture, if necessary, as defined in engine washing requirements (Ref. TASK 72-00-00-100-008).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 735 Aug 01/09
C F M 56-5B (7) Service the oil tank with one quart (one liter) of lube system corrosion preventive oil (Material No. CP5067) or corrosion preventive additive (Material No. CP5075) (Ref. TASK 12-13-79-610002). NOTE : The oil tank must be topped off up to the window mark. ____ Subtask 72-00-00-410-137 B. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-861-053 C. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 72-00-00-860-052 D. Aircraft Maintenance Configuration (1) On the overhead control and indicating panel 25VU, make sure that the ON legend of the ANTI-ICE/ENG 1(2) pushbutton switch is off. (2) On the AIR COND panel 30VU, make sure that the OFF legend of the ENG 1(2) BLEED pushbutton switch is on. (3) On the AIR COND panel 30VU, make sure that the OFF legends of the PACK 1 and the PACK 2 pushbutton switches are on. Subtask 72-00-00-110-081 E. Engine Washing CAUTION : DO NOT WASH AN ENGINE WHICH HAS BEEN EXPOSED TO DRY CHEMICAL _______ FIRE EXTINGUISHING AGENTS. CAUTION : DO NOT WASH AN ENGINE UNLESS THE EGT IS BELOW 150 DEG.F (66 _______ DEG.C).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 736 Aug 01/09
C F M 56-5B CAUTION : DO NOT WASH AN ENGINE AT TEMPERATURE BELOW 14 DEG.F (-10 _______ DEG.C). CAUTION : THE FUEL PUMP AND HYDRO-MECHANICAL UNIT (HMU) ARE FUEL _______ LUBRICATED. DO NOT MOTOR, START, OR OPERATE ENGINE UNLESS A POSITIVE FUEL INLET PRESSURE IS INDICATED ON THE LOWER ECAM (FUEL SYSTEM PAGE). DAMAGE TO COMPONENTS MAY RESULT. CAUTION : DO NOT EXCEED STARTER DUTY CYCLE. STARTER DAMAGE MAY RESULT. _______ CAUTION : MAKE SURE THE N1 ROTOR TURNS FREELY THROUGHOUT WASHING TO _______ PREVENT OIL SYSTEM CONTAMINATION. CAUTION : DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) PER _______ MINUTE. IF NOT, THEN ENGINE DAMAGE CAN OCCUR. (1) Dry motor the engine for two minutes (Ref. TASK 71-00-00-710-001). (2) After 30 seconds in motoring, inject the cleaning solution at 1 oclock position on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LP compressor inlet if a specific rig is used). (3) Stop the cleaning solution injection before the end of the engine motoring. (4) After two minutes in motoring, release the ENG/MAN START/1 (2) pushbutton switch. (5) Let the engine soak for 5 minutes. (6) Repeat steps (1) to (5) if extreme organic debris or oil deposits were present or if remaining EGT margin prior to the water wash was less than 10 deg. C. Subtask 72-00-00-110-082 F. Engine Rinsing CAUTION : DO NOT RINSE THE ENGINE EXPOSED TO DRY CHEMICAL EXTINGUISHING _______ AGENT. DO NOT RINSE THE ENGINE UNLESS THE EGT IS BELOW 150 DEG.F (66 DEG.C.). DO NOT RINSE THE ENGINE AT TEMPERATURE BELOW 14 DEG. F (-10 DEG.C.).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 737 Aug 01/09
C F M 56-5B CAUTION : THE FUEL PUMP AND HYDRO-MECHANICAL UNIT (HMU) ARE FUEL _______ LUBRICATED. DO NOT MOTOR, START, OR OPERATE ENGINE UNLESS A POSITIVE FUEL INLET PRESSURE IS INDICATED ON THE LOWER ECAM (FUEL SYSTEM PAGE). DAMAGE TO COMPONENTS MAY RESULT. CAUTION : DO NOT EXCEED STARTER DUTY CYCLE. STARTER DAMAGE MAY RESULT. _______ CAUTION : MAKE SURE THAT THE N1 ROTOR TURNS FREELY THROUGHOUT RINSING TO _______ PREVENT OIL SYSTEM CONTAMINATION. CAUTION : DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) PER _______ MINUTE. IF NOT, THEN ENGINE DAMAGE CAN OCCUR. (1) Dry motor the engine for two minutes (Ref. TASK 71-00-00-710-001). (2) After 10 seconds in motoring with positive fan rotation, inject the water at 1 oclock position on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LP compressor inlet if a specific rig is used). (3) Stop the water injection before the end of the engine motoring. (4) Let the engine soak for 5 minutes. (5) Dry motor the engine again for two minutes (Ref. TASK 71-00-00-710001). (6) After 10 seconds in motoring with positive fan rotation, inject the water, at 1 oclock position on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LP compressor inlet if a specific rig is used). (7) Stop the water injection before the end of the engine motoring. (8) Let the engine soak for 5 minutes. (9) Dry motor the engine again for two minutes (Ref. TASK 71-00-00-710001). (10) After 10 seconds in motoring with positive fan rotation, inject the water, at 1 oclock position on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LP compressor inlet if a specific rig is used). (11) Stop the water injection before the end of the engine motoring.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 738 Aug 01/09
C F M 56-5B (12) If water still drains out of the disconnected rigid anti-ice muscle line, dry motor the engine again until no water drains out (Ref. TASK 71-00-00-710-001). Subtask 72-00-00-010-139 G. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-420-064 H. Installation of PS3 Line and P25 Line CAUTION : DO NOT BLOW COMPRESSED AIR OR NITROGEN INTO THE ECU AS DAMAGE _______ TO THE ECU CAN OCCUR. CAUTION : DURING INSTALLATION, MAKE SURE THAT THE PS3 LINE DOES NOT TOUCH _______ THE LOWER STARTER DUCT OR OTHER PARTS IN THIS AREA. IF IT DOES, CHAFING OF THE PS3 HOSE CAN OCCUR. (1) Remove the plugs from the PS3 and P25 lines and from the ECU. (2) Blow PS3 and P25 lines clear of water with compressed air or nitrogen. (3) Connect PS3 line to ECU, TORQUE to between 270 and 300 lbf.in (3.05 and 3.39 m.daN) and safety with lockwire 0.032 in. (0.8 mm) DIA (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) DIA (Material No. CP8002). (4) Connect P25 line to ECU, TORQUE to between 180 and 200 lbf.in (2.03 and 2.26 m.daN) and safety with lockwire 0.032 in. (0.8 mm) DIA (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) DIA (Material No. CP8002). (5) Remove the standard protective cover from the nacelle anti-ice port of the NAI valve. (6) Connect the rigid anti-ice servo pressure line (25) to nacelle anti-ice valve, torque the forward hose nut to between 135 and 150 lbf.in (1.52 and 1.69 m.daN).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 739 Aug 01/09
C F M 56-5B Subtask 72-00-00-410-138 J. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-620-065 K. Post Engine Wash Test (Ref. Fig. 707/TASK 72-00-00-991-322) (1) On the AIR COND panel 30VU, make sure that: - The OFF legend of the PACK 1 and the PACK 2 pushbutton switches are on prior to start the procedure. - The cross bleed valve rotary selector is on OPEN position. (2) Start the engine within 2 hours (or 30 minutes if icing condition) of the last wash cycle to purge the lube/sump system of any water ingestion (Ref. TASK 71-00-00-710-003). NOTE : APU Bleed Valve must be closed (the ON legend of APU ____ pushbutton switch is off) after engine start, to avoid the supply of the air to the Wing-Anti-ice Systems from APU. NOTE : This engine run is done to ensure that the bleed system is ____ free from contaminant. Smoke/smell in cabin can result if contaminant enters in the bleed system. NOTE : Corrosion preventive products should be used. If none of the ____ corrosion preventive products specified above is available, the aircraft must resume Revenue Service operation within 24 hours following this Post Wash Test. (a) Let the engine run at idle for 5 minutes. (b) After 5 minutes from engine start, do the following: 1 _
Press the ANTI-ICE/ENG 1(2) pushbutton switch to operate the engine anti-ice system.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 740 Aug 01/09
C F M 56-5B
Engine Cleaning (Washing with Cleaning Agent) Figure 707/TASK 72-00-00-991-322 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 741 Aug 01/09
C F M 56-5B 2 _
Make sure that the ON legend of the ANTI-ICE/ENG 1(2) pushbutton switch comes on when the engine anti-ice system operates. CAUTION : AFTER 30 MINUTES FROM ENGINES START, ANTI-ICE/ENG _______ 1(2) PUSHBUTTON SWITCH SHOULD BE PRESSED OFF TO DEACTIVATE THE ENGINE ANTI-ICE SYSTEM. IF NOT, DAMAGE TO THE ENGINE COULD OCCUR.
3 _
Press the ENG 1(2) BLEED pushbutton switch to operate the engine bleed system.
4 _
Make sure that the OFF legend of the ENG 1(2) BLEED pushbutton switch goes off when the engine bleed anti-ice system operates.
5 _
Press the ANTI-ICE/WING pushbutton switch to operate the wing anti-ice system.
6 _
Make sure that the ON legend of the ANTI-ICE/WING pushbutton switch comes on when the wing anti-ice system operates.
7 _
Increase and stabilize engine thrust to at least 60 percent Fan (N1) Speed until HPV is closed while PRV is open on ECAM BLEED page.
8 _
Make sure that HPV is closed and PRV opened on ECAM BLEED page with engine running at this speed.
(c) Let the engine run this stabilized Fan (N1) Speed for 10 minutes. (d) Pull throttle to stabilize engine thrust at idle for 5 minutes. (e) After 20 minutes from engine start, do the following: 1 _
Press the ANTI-ICE/ENG and ANTI-ICE/WING pushbutton switches to turn off both anti ice systems.
2 _
Make sure that the ON legend of the ANTI-ICE/ENG and ANTI-ICE/WING pushbutton switches goes off.
3 _
Turn the cross bleed valve rotary selector to AUTO position.
4 _
Press the PACK 1 (2) pushbutton switch to operate the air conditioning pack.
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Page 742 Aug 01/09
C F M 56-5B 5 _
Make sure that the ON legend of the pushbutton switch comes on.
6 _
Check for evidence of cleaning agent or anti-freeze mixture odor/smoke in the cabin. - if evidence is found, continue to operate the engine at idle until no odor/smoke remains in the cabin. - after 10 minutes engine running, if continuous odor/smoke remains in the cabin, shut down the engine (Ref. TASK 71-0000-710-028) and decontaminate the Environmental Control System (ECS). . When Ambient Air Temperature is below 24 deg. C (Ref. TASK 21-00-00-615-003). . When Ambient Air Temperature is above 24 deg. C (Ref. TASK 21-00-00-615-004). - if no evidence is found, shut down the engine (Ref. TASK 7100-00-710-028).
5. Close-up ________ Subtask 72-00-00-869-084 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-00-00-942-059 B. Remove the warning notice(s). Subtask 72-00-00-862-053 C. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 743 Aug 01/09
C F M 56-5B TASK 72-00-00-100-027 External Cleaning 1. __________________ Reason for the Job NOTE : This task can contribute to fuel savings. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No
specific specific specific specific
clean cloth soaked rag soft bristle brush warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2010
Material No.
CP2011
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * white spirit (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 744 Aug 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 SPM 732113160001
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-00-00-941-066 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-084 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 745 Aug 01/09
C F M 56-5B Subtask 72-00-00-040-064 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-085 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-00-00-110-059 A. Engine external cleaning (1) Hydrocarbon method WARNING : HYDROCARBONS ARE FLAMMABLE AND TOXIC. _______ AVOID PROLONGED CONTACT WITH THE SKIN, AND OBSERVE PRECAUTIONS AGAINST FIRE. CAUTION : SOME PLASTICS AND RUBBER-BASE MATERIALS ARE ATTACKED BY _______ HYDROCARBON SOLVENTS. - stoddard solvent (Material No. CP2011) or acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or magchem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or white spirit (Material No. CP2010) is recommended. Light accumulations of grease, oil, gum, and dirt may be removed with hydrocarbon solvent. This method is not effective in removing baked-on oil deposits. (a) Apply solvent by spraying or using soaked rag. NOTE : A soft bristle brush may be used to remove stubborn ____ accumulations. (b) Wipe thoroughly to remove accumulation and dry with a clean cloth or rinse with water.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 746 Aug 01/09
C F M 56-5B (2) Steam cleaning method (a) Steam cleaning is a superficial cleaning process that is useful when it is not desireable to remove paint and surface coatings. NOTE : Do not use steam cleaning compounds. ____ (3) Cap all tube ends, manifold openings and air extraction ports to prevent entry of any contaminants or foreign objects. (a) Handling of the plugs: WARNING : FIRING TIPS OF IGNITER PLUGS WITH SPECIAL HANDLING _______ MARKINGS CONTAIN BERYLLIUM OXIDE. INHALATION OR INGESTION OF, OR CONTACT WITH BERYLLIUM OXYDE DUST IS HARMFUL TO YOUR HEALTH ; DO NOT GRIND, CLEAN OR MACHINE. HOLD PLUG BY INPUT CONNECTOR ONLY. TO AVOID PERSONAL INJURY, DO NOT HANDLE FIRING TIP. IF FITING TIP OF PLUG IS CONTACTED, AVOID TOUCHING OTHER AREAS OF YOUR BODY, AND WASH HANDS WITH SOAP AND WARM WATER. USED PLUGS SHOULD BE PLACED IN A PLASTIC ZIP LOC BAG FOR STORAGE OF SERVICEABLE PARTS AND/OR ACCUMULATION FOR DISPOSAL. SCRAP PLUGS MUST BE PLACED IN A SEALED CONTAINER AND BURIED IN THE EARTH PER RECOMMENDATIONS OF THE NATIONAL INSTITUTE FOR OCCUPATIONAL SAFETY AND HEALTH. LOCAL GOVERNMENT REQUIREMENTS OR LOCAL STANDARDS (IF THEY ARE MORE RESTRICTIVE) WILL BE THE ONLY AUTHORIZATION FOR DEVIATION FROM THESE REQUIREMENTS. (4) Steam clean the accessible exterior surfaces of the engine in accordance with (Ref. SPM 732113160001). To prevent damage to exposed plastic parts, avoid dwelling of steam on such parts to minimize excessive build-up of heat. (5) Remove covers installed above.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 747 Aug 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-00-00-410-083 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-064 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-084 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 748 Aug 01/09
C F M 56-5B FAN AND BOOSTER ASSEMBLY - DESCRIPTION AND OPERATION ____________________________________________________ 1. _______ General (Ref. Fig. 001) A. Fan and booster assembly (1) The fan and booster assembly consists of a single-stage fan rotor and a 4-stage axial booster, cantilever-mounted at the rear of the fan disk. (2) The fan and booster assembly consists of the following sections: (a) The fan section. It consists of: - spinner rear and front cones. - fan disk. - fan blades. (b) The booster section. It consists of: - booster rotor which is a spool with 4 stages of blades - booster stator which contains 5 stages of vane assemblies. 2. ___________ Description (Ref. Fig. 002, 003) A. Spinner Front Cone The spinner front cone is made of composite material. Its design precludes the need for an engine nose anti-icing system. The front cone is bolted to the rear cone. B. Spinner Rear Cone The spinner rear cone is made of aluminum alloy. Its rear flange is bolted to the fan disk and is part of the fan blades retention system. The outer rim of rear flange is provided with tapped holes for trim balance bolts. The front flange provides for attachment of the spinner front cone. C. Fan Disk The fan disk is a titanium alloy forging. Its inner rear flange provides attachement for the fan shaft and its outer rear flange is bolted to the booster rotor. The outer front flange provides attachment for the spinner rear cone. The disk outer rim has 36 recesses designed for fan blade retention.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Fan and Booster Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Fan and Booster Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
Booster Rotor and Stator Assembly Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B D. Fan Blades There are 36 titanium alloy, mid-span shrouded fan blades approximately 23 in. (0.58 m) long. Each of the blades has a dovetail base that engages in disk rim recess. Blades are individually retained by a spacer that limits radial movement. A retainer lug, machined at the rear end of each blade root, engages the forward flange of the booster spool and limits the forward and rearward axial movements. E. Booster Rotor (Ref. Fig. 003) The booster rotor consists of the booster spool and 4 stages of blades. (1) The booster spool is forged and machined from titanium and is cantilever-mounted on the rear of the fan disk. The inner front flange, bolted to the fan disk, acts as a stop for the fan blade spacers and blades. The 4-stage spool has circumferential slots that retain the stages 2, 3, 4 and 5 rotor blades, locking lugs and balance weights. Stage 2 has 64 blades, stage 3 and 4 have 70 blades and stage 5 has 68 blades. Rotating air seal serrations are machined between each stage on the outer diameter of spool. A forward rotating air seal, integral with the front web of the booster spool, provides (partial) sealing between the fan rotor stage and the inner shroud of booster stator stage 1 and (partial) pressurization of the engine forward sump. (2) The booster blades are approximately 3.5 to 4.2 in. (89 to 107 mm) long and serve primarily to supercharge the compressor. Blades are held in the dovetail slots by locking lugs. F. Booster Vane Assemblies (1) The stacked vane assemblies are cantilever-mounted on the fan frame front face. The entire assembly is composed of 5 stages of similar design. Each vane assembly consists of : (a) An outer shroud which, depending on its assembly location, is fitted with one or 2 mounting flanges at its ends. The outer shroud inner face of stages 1, 3, 4 and 5 vanes assemblies is lined with an abradable material facing, respectively, the 1, 2, 3 and 4 rotor blades. (b) An inner shroud, whose inner face is lined with abradable material facing the seal serrations machined on the booster spool.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B (c) Individual vanes of the stage 1 and stage 5 vane assemblies are welded to the outer shroud. Individual vanes of the stages 2, 3 and 4 vane assemblies are bolted to the outer shroud. (d) Stator vanes are retained on the inner shroud by the abradable material. Stage one vane assembly has 100 vanes, stage 2 vane assembly has 122 vanes, stage 3 vane assembly has 122 vanes stage 4 vane assembly has 116 vanes and stage 5 vane has 96 vanes. (2) The outer shroud rear flange of stage 5 vane assembly is bolted to the front face of the fan frame. The inner shroud rear flange is rabbeted to form an interference fit with a corresponding flange on the fan frame. (3) The outer shroud of booster stage 3 and of stage 5 vane assemblies has an orifice at the 3:30 oclock position to permit the borescope inspection of the booster mid and rear stages rotor blades (full view) and of the related vane assemblies (partial view only). These borescope orifices are designed SO3 and SO5, respectively in the chapter which follows.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 6 Nov 01/08
C F M 56-5B FAN AND BOOSTER ASSEMBLY - REMOVAL/INSTALLATION _______________________________________________ TASK 72-21-00-000-005 Removal of the Spinner Front Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1130
warning notice access platform 1 m (3 ft. 3 in.) 1 TOOL SET - JACK SCREW
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-991-300
Fig. 401
3. __________ Job Set-up Subtask 72-21-00-941-067 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put the access platform in position. 4. Procedure _________ (Ref. Fig. 401/TASK 72-21-00-991-300) Subtask 72-21-00-020-063 A. Removal of the Spinner Front Cone: CAUTION : BE CAREFUL NOT TO LOOSE THE WASHERS WHEN YOU REMOVE THE _______ ATTACHMENT BOLTS. NORMALLY, THEY ARE STUCK ON THE FRONT CONE. PRE CFM SB 72-0193 (1) Remove the bolts (40) which attach the spinner front cone (50) to the spinner rear cone (20). END OF PRE CFM SB 72-0193 POST CFM SB 72-0193 R R R
(2) Alternative Procedure Available. Remove the bolts (40) and the washers (35) which attach the spinner front cone P/N 338-00-204-0 (50) to the spinner rear cone (20).
R R
(3) Alternative Procedure. Remove the bolts (40) which attach the spinner front cone P/N 338-085-204-0 (50) to the spinner rear cone (20). END OF POST CFM SB 72-0193
R
(4) Move the Spinner Front Cone: CAUTION : BE CAREFUL NOT TO LET THE SPINNER FRONT CONE FALL DOWN WHEN _______ YOU DETACH IT FROM THE REAR CONE. (a) Move the spinner front cone (50) apart from the spinner rear cone (20) with the 3 jackscrews (P08) from the tool set TOOL SET JACK SCREW, (856A1130G02/G06)
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Feb 01/10
C F M 56-5B
R
Spinner Front and Rear Cones Figure 401/TASK 72-21-00-991-300
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 403 Feb 01/10
C F M 56-5B TASK 72-21-00-400-005 Installation of the Spinner Front Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
heat gun warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 PIN,GUIDE-SPINNER REAR CONE
856A3409
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
* engine oil (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-991-300
Fig. 401
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 404 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-860-054 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. 4. Procedure _________ (Ref. Fig. 401/TASK 72-21-00-991-300) Subtask 72-21-00-480-057 A. Install the guide pins as follows: (1) Apply a thin layer of engine oil (Material No. CP2442) to the 3 PIN,GUIDE-SPINNER REAR CONE (856A3409G01). (2) Install the guide pins on the flange of the spinner rear cone. Install one of the pins in the offset hole. Subtask 72-21-00-420-066 B. Prepare and Install the Spinner Cone: R R
WARNING : USE HEAT INSULATED GLOVES WHEN YOU TOUCH CHILLED OR HOTS PARTS _______ TO PREVENT INJURY (1) Increase the temperature of the front flange of the spinner rear cone to approximately 80 deg.C (176 deg.F) with a heat gun. (2) Install the Spinner Front Cone. CAUTION : DURING INSTALLATION, MAKE SURE THERE IS A WASHER, BONDED OR _______ NOT, UNDER EACH BOLT HEAD. (a) Install the spinner front cone (50) on the spinner rear cone (20). Carefully align the offset holes. Subtask 72-21-00-080-053 C. Remove the guide pins.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 405 Feb 01/09
C F M 56-5B Subtask 72-21-00-420-073 D. Attach the Spinner Front Cone. (1) Apply a thin layer of engine oil (Material No. CP2442) to the threads of the 6 bolts (40). PRE CFM SB 72-0193 (2) Attach the spinner front cone (50) to the spinner rear cone (20) with the bolts (40). END OF PRE CFM SB 72-0193 POST CFM SB 72-0193 R R R
(3) Alternative Procedure Available. Attach the spinner front cone P/N 338-001-204-0 (50) to the spinner rear cone (20) with the bolts (40) and the washers (35).
R R
(4) Alternative Procedure. Attach the spinner front cone P/N 338-085-204-0 (50) to the spinner rear cone (20) with the bolts (40). END OF POST CFM SB 72-0193
R
(5) Tighten the bolts (40) by hand, and let the mating parts return to the ambient temperature.
R
(6) TORQUE the bolts (40) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). 5. Close-up ________ Subtask 72-21-00-869-062 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-061 B. Close Access (1) Remove the warning notice(s). (2) Remove the access platform(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 406 Feb 01/10
C F M 56-5B TASK 72-21-00-000-006 Removal of the Spinner Rear Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1130
warning notice access platform 1 m (3 ft. 3 in.) 1 TOOL SET - JACK SCREW
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-991-300
Removal of the Spinner Front Cone Fig. 401
3. __________ Job Set-up Subtask 72-21-00-941-068 A. Safety Precautions (1) Put the access platform in position. (2) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (3) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 407 Nov 01/08
C F M 56-5B (4) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). 4. Procedure _________ (Ref. Fig. 401/TASK 72-21-00-991-300) Subtask 72-21-00-020-064 A. Remove the Spinner Rear Cone: CAUTION : BE CAREFUL NOT TO LET THE SPINNER FRONT CONE FALL DOWN WHEN YOU _______ DETACH IT FROM THE REAR CONE. (1) Remove spinner front cone (Ref. TASK 72-21-00-000-005) (2) Remove the bolts (30) and the washers (10) which attach the spinner rear cone (20) to the fan disk. (3) Remove the spinner rear cone from the fan disk with the 6 jackscrews from the TOOL SET - JACK SCREW (856A1130G02/G06).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 408 Nov 01/08
C F M 56-5B TASK 72-21-00-400-006 Installation of the Spinner Rear Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No
specific specific specific specific specific
feeler gage set heat gun warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 PIN,GUIDE-SPINNER REAR CONE
856A3409
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2442
* graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-006 72-21-00-400-005 72-21-00-991-300 72-21-00-991-301
Removal of the Spinner Rear Cone Installation of the Spinner Front Cone Fig. 401 Fig. 402
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 409 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-860-055 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position. (2) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (3) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). 4. Procedure _________ (Ref. Fig. 401/TASK 72-21-00-991-300, 402/TASK 72-21-00-991-301) Subtask 72-21-00-480-058 A. Install guide pins as follows: (1) Apply a thin layer of engine oil (Material No. CP2442) to the 3 PIN,GUIDE-SPINNER REAR CONE (856A3409G01). (2) Install the 3 guide pins, equally spaced, on the forward flange of the fan disk. Install one of the pins in the offset hole of the flange. Subtask 72-21-00-420-067 B. Install the spinner rear cone as follows: (1) Apply a thin layer of graphite grease (Material No. CP2101) to the threads of the bolts (30). (2) Safety precautions WARNING : USE HEAT INSULATED GLOVES WHEN YOU TOUCH CHILLED OR HOTS _______ PARTS TO PREVENT INJURY (a) Increase the temperature of the aft flange of spinner rear cone (20) to 60 deg.C (140.00 deg.F) with a heat gun.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 410 Nov 01/08
C F M 56-5B
Post Installation checks of the Spinner Rear Cone Figure 402/TASK 72-21-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 411 Nov 01/08
C F M 56-5B (3) Install the spinner rear cone. CAUTION : TAKE CARE NOT TO LET THE SPINNER REAR CONE FALL WHEN YOU _______ INSTALL IT ON THE FAN DISK. DAMAGE TO THE CONE COULD RESULT. (a) Install the spinner rear cone on the fan disk forward flange as follows: 1 _
Align the offset holes NOTE : The offset hole in the spinner rear cone is identified ____ by a spherical indentation on its rear flange.
2 _
Install three equally-spaced bolts (30) and washers (10) and tighten them until the rear cone comes fully against the forward flange of fan disk. While you do this, make sure that the lip of the rear cone seal engages correctly under the front edge of the fan blade platforms.
(4) Let the assembly return to ambient temperature. Then remove the 3 guide pins PIN,GUIDE-SPINNER REAR CONE (856A3409G01). (5) Install the remaining bolts (30) and washers (10). (6) TORQUE all the bolts (30) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). Subtask 72-21-00-220-056 C. Do a check of the spinner rear cone to fan disk for correct installation as follows: (Ref. Fig. 402/TASK 72-21-00-991-301) (1) Make a check of the Gap F34 over 360 degrees with a feeler gage set. NOTE : The gap F34 is the blueprint clearance, or gap, between the ____ aft edge of the spinner rear cone and the front edge of the fan blade platforms after installation. (a) The gap F34 must measure between: (0.020 in. (0.5 mm) to 0.051 in. (1.3 mm) (b) If this gap F34 is out of limits at any location of the circumference, remove the rear cone (Ref. TASK 72-21-00-000-006) find the cause (see the NOTE) and correct it.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 412 Nov 01/08
C F M 56-5B NOTE : The cause might be a mis-installed blade on the fan disk, ____ a FOD damaged blade in the platform area, or a out-of-shape aft flange of the spinner rear cone, for example. (2) Make a check of the seating of the spinner rear cone on the fan disk flange at location A. (a) Do this check at 6 locations at least, and radially to the flange scallops. (b) The seating is correct if you cannot engage a feeler gage of 0.001 in. (0.02 mm) maximum thickness between two flange scallops at the specified 6 locations marked A. (c) If you can engage the 0.001 in. (0.02 mm) feeler gage at two or three consecutive locations, the seating is incorrect in the related sector. Before to do anything else, make sure the bolts in this sector are correctly torqued. If after this check the seating remains incorrect, remove the spinner rear cone (Ref. TASK 72-21-00-000-006), find the cause and correct it. Subtask 72-21-00-410-060 D. Install spinner front cone (Ref. TASK 72-21-00-400-005) 5. Close-up ________ Subtask 72-21-00-869-063 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-062 B. Close Access (1) Remove the warning notice(s). (2) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 413 Nov 01/08
C F M 56-5B TASK 72-21-00-000-007 Removal of the Fan Rotor Blades CAUTION : ALL FAN ROTOR BLADES SHALL BE MATCHMARKED OR NUMBERED FOR ASSEMBLY IN _______ ORIGINAL ALIGNMENT AND POSITION USING ONLY APPROVED MARKING MATERIAL. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 856A2631
rubber mat or foam material flooring warning notice access platform 1 m (3 ft. 3 in.) 1 STAND,STORAGE-FAN BLADES
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP5061
* temporary marking (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-991-302
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Fig. 403
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 414 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-941-069 A. Safety Precautions (1) Put the access platform in position. (2) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (3) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (4) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-21-00-010-058 B. Preparation for Removal of the Fan Blades: (1) Install a rubber mat or foam material flooring in the inlet cowl before you go into it. (2) Remove spinner front cone. (Ref. TASK 72-21-00-000-005) (3) Remove spinner rear cone. (Ref. TASK 72-21-00-000-006) NOTE : Removal will be easier if fan blade to be removed is placed at ____ the 12 oclock position.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 415 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 403/TASK 72-21-00-991-302) Subtask 72-21-00-020-065 A. Removal of the fan blades: CAUTION : USE ONLY APPROVED MARKING MATERIAL TO PREVENT DAMAGE TO THE _______ BLADES. (1) Temporarily mark each blade (80) from 1 to 36 on their convex side. Use a temporary marking (Material No. CP5061). Blade No. 1 will be the blade immediately above the offset hole in the fan disk bolt flange. Numbering is counter-clockwise (CCW), forward locking aft. (2) Removal of the first and second fan blades circled 1 and 2. NOTE : The removal of blades (80) is counterclockwise (CCW) after the ____ first blade removed. NOTE : Put the first blade to be removed at the 12 oclock position ____ to ease the removal. (a) Remove spacer (70) from the fan blade circled 2 located immediately at left of the first blade circled 1 you want to remove. Carefully lower blade circled 2 in its dovetail recess (this unlocks it from its engagement on the booster spool), and move it at a slope (inclined) to the left. Do not try to remove it now. (b) Remove spacer (70) from the first blade circled 1 to be removed. (c) Lower blade circled 1 in its dovetail recess (this unlocks it), and carrefully pul it forward while you move its left midspan shroud above the right midspan shroud of the (sloped) blade circled 2 at left. Remove blade circled 1. (d) Remove blade. (3) Removal of the 3rd to the 36th blades: (a) The removal of the following blades is easier, done CCW, and as follows for each blade: 1 _
Remove spacer (70)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 416 Nov 01/08
C F M 56-5B 2 _
Remove blade (80).
(4) Put spacer (70) and fan blades from 1 through 36 in their related compartements on STAND,STORAGE-FAN BLADES (865A2631G01)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 417 Nov 01/08
C F M 56-5B
Removal of Fan Blades Figure 403/TASK 72-21-00-991-302- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 418 Nov 01/08
C F M 56-5B
Removal of Fan Blades Figure 403/TASK 72-21-00-991-302- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 419 Nov 01/08
C F M 56-5B TASK 72-21-00-400-007 Installation of the Fan Rotor Blades CAUTION : ALL FAN ROTOR BLADES SHALL BE MATCHMARKED OR NUMBERED FOR ASSEMBLY IN _______ ORIGINAL ALIGNMENT AND POSITION USING ONLY APPROVED MARKING MATERIAL. CAUTION : DO NOT DISSOCIATE FAN BLADE PAIRS MATCHED DURING ORIGINAL ASSEMBLY. _______ BLADES FROM A SAME PAIR MUST ALWAYS BE LOCATED 180 DEGREES APART. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A2631
warning notice access platform 1 m (3 ft. 3 in.) 1 STAND,STORAGE-FAN BLADES
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2104
Material No.
CP5062
* molykote g rapid (Ref. 70-30-00) * MoS2 dry film lubricant (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-400-005 72-21-00-400-006 72-21-00-991-303 72-21-00-991-304
Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Fig. 404 Fig. 405
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 420 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-860-056 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position. (2) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (3) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). 4. Procedure _________ (Ref. Fig. 404/TASK 72-21-00-991-303, 405/TASK 72-21-00-991-304) Subtask 72-21-00-420-068 A. Preparation and Installation of the Fan Rotor Blades: (1) Preparation for Installation of Fan Rotor Blades. CAUTION : THE FAN BLADES ARE KEPT IN NUMERICAL ORDER ON THE STORAGE _______ STAND AND MUST BE INSTALLED ACCORDINGLY ON THE FAN DISK. BLADE N⁰1 IS INSTALLED IN FRONT OF THE OFFSET BOLT OF THE FAN DISK. NUMBERS ARE GIVEN COUNTERCLOCKWISE, FORWARD LOOKING AFT. NOTE : Installation will be easier if the fan disk blade recess into ____ which the blade is to be installed is placed at the 6 Oclock position. (a) Get the fan blades (80) from STAND,STORAGE-FAN BLADES (856A2631G01). NOTE : Put the fan disk dovetail slot, where you want to install ____ blade No. 1 at the 6 Oclock position. This will help installation of the blades on the fan disk.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 421 Nov 01/08
C F M 56-5B
Installation of the First Fan Blade at 6 Oclock Figure 404/TASK 72-21-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 422 Nov 01/08
C F M 56-5B
Installation of the 2 Last Fan Blades at 12 Oclock Figure 405/TASK 72-21-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 423 Nov 01/08
C F M 56-5B (b) Apply lubricant MoS2 dry film lubricant (Material No. CP5062) or molykote g rapid (Material No. CP2104) to the disk slots, the spacers, the blade roots (dovetails), the blade platforms and lateral surfaces of these platforms, and the midspan shroud mating surfaces, before you install the blades. NOTE : You must apply a large quantity of lubricant to all the ____ dovetail and slot pressure faces. Brush application is prefered. If you use spray application , a minimum of 4 to 6 passes is necessary to supply all the pressure faces with sufficient lubrication. Let the lubricant become dry to a dull opaque finish before you install the blades in the disk slots. (2) Installation of the Fan Rotor Blades. (a) Position the fan blade No. 1 correctly (leading edge forward) and engage (dovetail lug first) in the fan disk slot No. 1 immediately below the offset hole in the fan disk bolt flange. (b) Push the blade in full position. (c) Pull down the fan blade to engage the lug into the booster spool recess. (d) Install the spacer (70) between the fan blade No. 1 and the disk. Push the spacer fully in position against the front frange of the booster spool. (e) Continue COUNTERCLOCKWISE, forward locking aft and use the same procedure as for fan blade No. 1 to install blades No. 2 through No. 34 in their related slots. NOTE : The midspan shroud section of each blade will engage and ____ mate with the related midspan shroud sections of adjacent blades. (f) Install the 2 last fan blades 35 and 36 at the 12 Oclock position, as follows: 1 _
Fully engage blade 36, in its dovetail recess. Let its dovetail root touch the bottom of the recess. Do not install its spacer.
2 _
Carefully engage blade 35, in its dovetail recess and install its spacer (70).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 424 Nov 01/08
C F M 56-5B 3 _
Install the spacer (70) of blade 36.
(g) Make sure that all the blades and spacers are correctly installed. (h) Install the spinner rear cone. (Ref. TASK 72-21-00-400-006) (i) Install the spinner front cone. (Ref. TASK 72-21-00-400-005) (j) Remove the rubber pad or foam material flooring from the inlet cowl. 5. Close-up ________ Subtask 72-21-00-869-064 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-063 B. Close Access (1) Remove the warning notice(s). (2) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 425 Nov 01/08
C F M 56-5B TASK 72-21-00-300-028 Replacement of Fan Rotor Blades in Pairs 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 CFMI SOFTWARE FOR BLADE MAPPING
856A3770
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
Material No.
CP5061
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * temporary marking (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 426 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-009 71-00-00-750-001 72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-300-009 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-21-00-991-327 72-21-00-991-341 72-21-00-991-342 72-21-00-991-343 72-21-00-991-344 72-21-00-991-345 72-21-00-991-346
Vibration Check Fan Trim Balance - 1 sensor 3 speed Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Correction of the Static Imbalance Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Fig. 406 Fig. 407 Fig. 408 Fig. 409 Fig. 410 Fig. 411 Fig. 412
3. __________ Job Set-up Subtask 72-21-00-941-085 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 427 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 406/TASK 72-21-00-991-327, 407/TASK 72-21-00-991-341, 408/TASK 72-21-00-991-342, 409/TASK 72-21-00-991-343, 410/TASK 72-21-00-991-344) Subtask 72-21-00-869-079 A. Remove the fan blades before record moment weight. CAUTION : DO NOT MIX PAIR OF BLADES PRE CFM SB 72-0057 AND POST CFM SB _______ 72-0057 ON THE SAME FAN DISK. NOTE : The spare blades are grouped in pairs so that the difference ____ between the moment weights is not more than 80 in.g (200 cm.g). If the result of the fan blade plotting is not correct, you must do the checks and corrections given below before and after blade installation to make sure the engine imbalance is not more than the limits. This will also optimize the engine operation. Four conditions can exist, refer to the logic diagram. (Ref. Fig. 406/TASK 72-21-00-991-327)
R R R R R
NOTE : In all replacement cases: 1,2,3.....N pairs of fan blades and for ____ individual fan blade replacement, a vibration survey can be performed (Ref. TASK 71-00-00-710-009). Results from the vibration survey will determine if a trim balance is necessary. In this last case, do a trim balance operation (Ref. TASK 71-00-00-750-001) if the aircraft is at the main base or as soon as the aircraft returns to the base. (1) Put a rubber mat in the air intake cowl. (2) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (3) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (4) Record location of each blade to be replaced and of each blade opposite. (5) Remove fan blades (Ref. TASK 72-21-00-000-007)
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 428 May 01/09
C F M 56-5B
R
Diagram for Fan Blade Change Figure 406/TASK 72-21-00-991-327
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Page 429 Nov 01/08
C F M 56-5B
Fan Blade Replacement Figure 407/TASK 72-21-00-991-341 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 430 Nov 01/08
C F M 56-5B
Replacement of Several Pairs of Fan Blades Figure 408/TASK 72-21-00-991-342 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 431 Nov 01/08
C F M 56-5B
Fan Blades, Balance Screw Location Chart and Vectorial Diagram Figure 409/TASK 72-21-00-991-343 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 432 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
72-21-00 CES
Page 433 Nov 01/98
C F M 56-5B
Various Balance Screw Arrangements for Given Moment Weights Figure 410/TASK 72-21-00-991-344- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 434 Nov 01/08
C F M 56-5B
Various Balance Screw Arrangements for Given Moment Weights Figure 410/TASK 72-21-00-991-344- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 435 Nov 01/08
C F M 56-5B (6) Write moment weight on base of blades that you remove using temporary marking (Material No. CP5061). (Ref. Fig. 407/TASK 72-21-00-991-341) NOTE : Grease deposits can mask the moment weight indication. If ____ necessary, clean blade base with isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656). Subtask 72-21-00-420-081 B. Record moment weight on base of spare blades. CAUTION : FOR EACH PAIR OF FAN BLADES, INSTALL THE HEAVIER SPARE BLADE AT _______ THE POSITION OF THE HEAVIER BLADE TO BE REMOVED. (1) Write the moment weight on base of the spare blades with temporary marking (Material No. CP5061). (2) Install spare blades (Ref. TASK 72-21-00-400-007). Subtask 72-21-00-820-053 C. Determine the balance screws to be installed. (1) Determine the resultant vector length and direction, then select balance screws to provide a correction returning the fan to its initial balance condition as follows. NOTE : It is advisable to limit the number of balance screws on the ____ spinner due the complexity and the risk of confusion when performing further corrections, and to install only one set of balance screws. This requires the construction of a vector diagram for determining the sum of the corrections. An example is given in (Ref. TASK 72-21-00-300-009). (a) Assume the following blades with the moment weights indicated are to be removed: No. 01: 164832 cm.g (64894 in.g) No. 36: 163245 cm.g (64270 in.g) No. 03: 162510 cm.g (63980 in.g) No. 35: 164185 cm.g (64640 in.g)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 436 Nov 01/08
C F M 56-5B (b) Assume the moment weights of the opposite blades are as follows: No. 19: 164647 cm.g (64823 in.g) No. 18: 163405 cm.g (64333 in.g) No. 21: 162650 cm.g (64035 in.g) No. 17: 164160 cm.g (64630 in.g) (c) Calculate differences between moment weights D1: (No. 01/19) = 164832 - 164647 = 185 cm.g D2: (No. 18/36) = 163405 - 163245 = 160 cm.g D3: (No. 21/03) = 162650 - 162510 = 140 cm.g D4: (No. 35/17) = 164185 - 164160 = 025 cm.g (d) Calculate blades as D1: (No. D2: (No. D3: (No. D4: (No.
moment below: 01/19) 18/36) 21/03) 35/17)
as below: (73 in.g) (63 in.g) (55 in.g) (10 in.g)
weight differences corresponding to spare fan = = = =
162905 161205 164570 163825
-
162730 161185 164545 163630
= = = =
175 020 025 195
cm.g cm.g cm.g cm.g
(69 (08 (10 (77
in.g) in.g) in.g) in.g)
(e) Calculate differences between removed blades and spare blades as below: D1 - D1 = 185 - 175 = 010 cm.g (04 in.g) = F1 D2 - D2 = 160 - 020 = 140 cm.g (55 in.g) = F2 D3 - D3 = 140 - 025 = 115 cm.g (45 in.g) = F3 D4 - D4 = 195 - 025 = 170 cm.g (67 in.g) = F4 (f) Determine the direction of corrections as follows: NOTE : When D is greater than D the balance weight should be ____ added close to the heavier blade. When D is lighter than D the balance weight should be added close to the lighter blade. 1 _
For blades No. 1 and 19, D1 is greater than D1 and the balance weight should therefore be added close to the heavier blade: No. 1.
2 _
For blades No. 18 and 36, D2 is greater than D2 and the balance weight should therefore be added close to the heavier blade: No. 18.
3 _
For blades No. 21 and 3, D3 is greater than D3 and the balance weight should therefore be added close to the heavier blade: No. 21.
4 _
For blades No. 35 and 17, D4 is less than D4 and the balance weight should ore be added close to the lighter blade: No. 17.
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Page 437 Nov 01/08
C F M 56-5B (g) Construct vectorial diagram as follows: (Ref. Fig. 408/TASK 72-21-00-991-342, 409/TASK 72-21-00-991-343) 1 _
On a polar diagram draw vectors corresponding to moment weight difference calculated in (e) and orientated as in (f). (Ref. Fig. 409/TASK 72-21-00-991-343)
2 _
Draw the resultant Fr representing the correction required from F1, F2, F3 and F4. NOTE : In this example, Fr is approximately 405 cm.g (159 ____ in.g) and orientated close to the balance screw No. 18. NOTE : When resultant imbalance direction is between 2 holes, ____ the screw given in fifth column of referenced figures must be placed in the nearest hole.
(h) Select balance screws as follows: (Ref. Fig. 410/TASK 72-21-00-991-344) 1 _
Find in the tables the values of the resultant Fr calculated in paragraph (g). This indicates which balance screw must be installed. The screw in the fifth column of the table must be installed at location calculated in paragraph (g). NOTE : In this example, for a resultant Fr of 405 cm.g (159 ____ in.g), one centered screw P01 installed in hole No. 18 and two lateral screw P02 installed in holes No. 17 and No. 19 provide a correction returning the fan to its initial balance condition. NOTE : Balance screws are identified by a number corresponding ____ to their moment weight (P01-P02-P03-P04-P05-P06-P07) engraved on screw head. As it may be difficult to read the numbers due to erosion and pollution, the relationship between the screw reference and screw length is shown in. (Ref. Fig. 411/TASK 72-21-00-991-345)
(2) Install balance screws. TORQUE the screws to between 65 and 75 lbf.in (0.73 and 0.84 m.daN). (3) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (4) Install the spinner front cone (Ref. TASK 72-21-00-400-005).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 438 Nov 01/08
C F M 56-5B
Balance Screws Figure 411/TASK 72-21-00-991-345 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 439 Nov 01/08
C F M 56-5B (5) Remove the rubber mat from the air intake cowl. (6) Do a vibration check (Ref. TASK 71-00-00-710-009) if resultant is greater than 400 cm.g (157.5 in.g). (Ref. Fig. 412/TASK 72-21-00-991-346) (a) If the vibration level is out of the limits, do a trim balance (Ref. TASK 71-00-00-750-001) with CFMI SOFTWARE FOR BLADE MAPPING. 5. Close-up ________ Subtask 72-21-00-869-080 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-078 B. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 440 Nov 01/08
C F M 56-5B
Diagram for Fan Blade Change in Individual Figure 412/TASK 72-21-00-991-346 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 441 Nov 01/08
C F M 56-5B TASK 72-21-00-300-029 Replacement of Individual Fan Blades 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 CFMI SOFTWARE FOR BLADE MAPPING
856A3770
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
* graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-009 71-00-00-750-001 72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-21-00-991-341 72-21-00-991-344
Vibration Check Fan Trim Balance - 1 sensor 3 speed Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Fig. 407 Fig. 410
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 442 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-991-345 72-21-00-991-346
Fig. 411 Fig. 412
3. __________ Job Set-up Subtask 72-21-00-941-086 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put an access platform in position. 4. Procedure _________ (Ref. Fig. 407/TASK 72-21-00-991-341, 410/TASK 72-21-00-991-344, 411/TASK 72-21-00-991-345, 412/TASK 72-21-00-991-346) Subtask 72-21-00-020-076 A. Record moment weight of blades. CAUTION : DO NOT MIX PAIR OF BLADES PRE CFM SB 72-0057 AND POST CFM SB _______ 72-0057 ON THE SAME FAN DISK. NOTE : If pairs of fan blades are not available as spare, you can replace ____ one blade individually. If the result of the fan blade plotting is not correct, you must do the inspections and corrections given below before and after the fan blade installation to make sure the engine imbalance is not more than the limits. This will also
R R R
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 443 May 01/09
C F M 56-5B optimize the engine operation. Two conditions can exist, refer to the logic dynamic. (Ref. Fig. 412/TASK 72-21-00-991-346) NOTE : In all cases of individual blade replacement, remove its opposite ____ to record the moment weight of the opposite blade. (1) Put a rubber mat in the air intake cowl. (2) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (3) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (4) Record moment weight of removed blade. (5) Remove fan blade (Ref. TASK 72-21-00-000-007) (6) Record moment weight of blade to be installed. Subtask 72-21-00-420-082 B. Install fan blade (Ref. TASK 72-21-00-400-007) Subtask 72-21-00-750-055 C. Calculate difference between moment weights of both blades. (1) If difference between moment weights D is greater than 200 cm.g (80 in.g), correct the imbalance as in the example which follows: NOTE : If you change only one fan blade and if the moment weight with ____ the opposite blade is less than 200 cm.g (80 in.g), no correction is necessary. NOTE : If you change more than one fan blade, a vectoriel diagram ____ must be done in order to identify the resultant imbalance. Apply the procedure as shown in the following example. (2) Assume a blade with moment weight of 162750 cm.g (64075 in.g) is to be replaced in any position. (3) A spare blade is provided with moment weight of 163296 cm.g (64290 in.g). (4) Calculate the difference between the moment weights as below: 163296 - 162750 = 546 cm.g (215 in.g).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 444 May 01/09
C F M 56-5B (5) Select balance screws as follows: (a) To determine the solutions closest to above difference of 546 cm.g (215 in.g). One centered screw P05 and 2 lateral screws P01 = 541 cm.g (213 in.g). This solution permits a satisfactory correction for returning the fan close to its initial balance condition. (Ref. Fig. 410/TASK 72-21-00-991-344) (6) Locate balance screws as follows: (a) As the new blade is heavier than the removed blade, install balance screws close to the opposite blade. NOTE : If the new blade is lighter than the removed blade, ____ install balance screw close to the removed blade. (7) Install balance screws lightly coated with graphite grease (Material No. CP2101). TORQUE screws to between 65 and 75 lbf.in (0.73 and 0.84 m.daN). NOTE : Balance screws are identified by a number corresponding to ____ their moment weight (P01-P02-P03-P04-P05-P06-P07) engraved on screw head. As it may be difficult to read the numbers due to erosion and pollution, the relationship between the screw reference and screw length is shown in. (Ref. Fig. 411/TASK 72-21-00-991-345) (8) Install the spinner rear cone (Ref. TASK 72-21-00-400-005). (9) Install the spinner front cone (Ref. TASK 72-21-00-400-006). (10) Remove the rubber mat from the inlet cowl. (11) Do a vibration-check (Ref. TASK 71-00-00-710-009) if resultant is greater than 400 cm.g (157.5 in.g). (Ref. Fig. 412/TASK 72-21-00-991-346) (a) If the vibration level is out of the limits, do a trim balance (Ref. TASK 71-00-00-750-001) with CFMI SOFTWARE FOR BLADE MAPPING .
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Page 445 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-21-00-869-081 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-079 B. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 446 Nov 01/08
C F M 56-5B TASK 72-21-00-920-001 Discard Fan Disc and Booster Spool 1. __________________ Reason for the Job Refer to the MPD TASK: 722100-C1 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-00-00-400-042 ESM 722100
Removal of the Power Plant Installation of the Power Plant
3. __________ Job Set-up Subtask 72-21-00-010-062 A. Remove the engine (Ref. TASK 71-00-00-000-042). 4. Procedure _________ Subtask 72-21-00-020-077 A. Remove and discard fan disk and booster spool (Ref. ESM 722100). Subtask 72-21-00-420-083 B. Install new fan disc and booster spool (Ref. ESM 722100). 5. Close-up ________ Subtask 72-21-00-410-064 A. Install the engine (Ref. TASK 71-00-00-400-042).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 447 Nov 01/08
C F M 56-5B TASK 72-21-00-920-002 Discard Fan Shaft 1. __________________ Reason for the Job Refer to the MPD TASK: 722100-C2 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-00-00-400-042 ESM 722200
Removal of the Power Plant Installation of the Power Plant
3. __________ Job Set-up Subtask 72-21-00-010-063 A. Remove the engine (Ref. TASK 71-00-00-000-042). 4. Procedure _________ Subtask 72-21-00-020-078 A. Remove and discard fan shaft (Ref. ESM 722200). Subtask 72-21-00-420-084 B. Install fan shaft (Ref. ESM 722200). 5. Close-up ________ Subtask 72-21-00-410-065 A. Install the engine (Ref. TASK 71-00-00-400-042).
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Page 448 Nov 01/08
C F M 56-5B TASK 72-21-00-000-008 Removal of the Stage 1 Booster Vane Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific 856A1130
warning notice 1 TOOL SET - JACK SCREW
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-23-00-000-028 72-21-00-991-305 72-21-00-991-306
Removal of Removal of Removal of Removal of Fig. 413 Fig. 414
the the the the
Spinner Front Cone Spinner Rear Cone Fan Rotor Blades Splitter Fairing
3. __________ Job Set-up Subtask 72-21-00-941-070 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 449 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). 4. Procedure _________ (Ref. Fig. 413/TASK 72-21-00-991-305, 414/TASK 72-21-00-991-306) Subtask 72-21-00-020-071 A. Preparation for Removal of the Stage 1 Booster Vane Assembly: (1) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (2) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (3) Remove all the fan blades (Ref. TASK 72-21-00-000-007). (4) Remove the splitter fairing (Ref. TASK 72-23-00-000-028). Subtask 72-21-00-020-066 B. Removal of the Stage 1 Booster Vane Assembly: (1) Remove the 24 bolts that secure the stage 1 vane assembly to the stage 2 vane (2) Move apart stage 1 vane assembly from the stage 2 vane assembly, using jackscrews, P13, from the TOOL SET - JACK SCREW (856A1130G02/G06), on the equally spaced threaded holes located on the rear flange of the stage 1 vane assembly.
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Page 450 Nov 01/08
C F M 56-5B
Stage 1 Booster Vane Assembly Figure 413/TASK 72-21-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 451 Nov 01/08
C F M 56-5B
Installation of Stage 1 Booster Vane Assembly Figure 414/TASK 72-21-00-991-306 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 452 Nov 01/08
C F M 56-5B TASK 72-21-00-400-008 Installation of the Stage 1 Booster Vane Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
heat gun warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 GUIDE PINS - BOOSTER VANE ASSY
856A2916
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
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Page 453 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-23-00-400-028 72-21-00-991-305 72-21-00-991-306
Installation Installation Installation Installation Fig. 413 Fig. 414
of of of of
the the the the
Spinner Front Cone Spinner Rear Cone Fan Rotor Blades Splitter Fairing
3. __________ Job Set-up Subtask 72-21-00-860-057 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). 4. Procedure _________ (Ref. Fig. 413/TASK 72-21-00-991-305, 414/TASK 72-21-00-991-306) Subtask 72-21-00-480-059 A. Install the 3 guide pins, GUIDE PINS - BOOSTER VANE ASSY (856A2916G01), equally spaced on vane assembly, stage 2. Subtask 72-21-00-110-053 B. Clean the Making Faces: WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY SHOULD _______ BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 454 Nov 01/08
C F M 56-5B (1) Thoroughly clean the mating faces of the stage 1 and stage 2 vanes assemblies with acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041). Subtask 72-21-00-420-069 C. Preparation and Installation of the Stage 1 Vane Assembly: (1) Increase the temperature of the forward flange of stage 2 vane assembly to between 75 deg.C (167.00 deg.F) and 85 deg.C (185.00 deg.F) with a heat gun. (2) Install the stage 1 vane assembly WARNING : WEAR THERMAL INSULATED GLOVES WHEN HANDLING HEATED OR _______ CHILLED PARTS TO PREVENT INJURY TO HANDS. (a) Align the offset holes and use the 3 guide pins, to install the stage 1 vane assembly on the booster assembly. Subtask 72-21-00-080-054 D. Remove the guide pins, GUIDE PINS - BOOSTER VANE ASSY (856A2916G01), apply a thin layer of graphite grease (Material No. CP2101) on the threads of bolts and seat the stage 1 vane assembly with 24 bolts. Subtask 72-21-00-220-053 E. Do a check of the seating of the stage 1 vane assembly on the stage 2 vane assembly with 0.001 in. (0.02 mm) feeler gage. Subtask 72-21-00-420-074 F. Install the Fan Components: (1) Let the parts return to ambient temperature and TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN) (2) Install the splitter fairing (Ref. TASK 72-23-00-400-028). (3) Install all the fan blades (Ref. TASK 72-21-00-400-007). (4) Install the spinner rear cone (Ref. TASK 72-21-00-400-006).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 455 Nov 01/08
C F M 56-5B (5) Install the spinner front cone (Ref. TASK 72-21-00-400-005). 5. Close-up ________ Subtask 72-21-00-869-065 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-064 B. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 456 Nov 01/08
C F M 56-5B FAN AND BOOSTER ASSEMBLY - INSPECTION/CHECK ___________________________________________ TASK 72-21-00-210-005 Inspection/Check of the Spinner Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2216
* Loctite 496 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-200-025 72-00-00-200-025 72-21-00-000-005 72-21-00-000-006 72-21-00-300-001 72-21-00-400-005 72-21-00-400-006 72-55-00-960-002
Over-Serviceable-Limit Extensions Over-Serviceable-Limit Extensions Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Replacement of the Crimped Self-Locking Nuts on the Spinner Rear Cone Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Replacement of LPT Shaft Plug O-rings
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Feb 01/10
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-941-078 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-21-00-020-072 B. Remove the Spinner Cone. (1) Remove the spinner front cone (Ref. TASK 72-21-00-000-005) (2) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006) 4. Procedure _________ Subtask 72-21-00-210-055 A. Inspection of the spinner cone ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Spinner front cone for: A. Cracks
Not serviceable.
Install a new or serviceable spinner front cone (Ref. TASK 72-21-00400-005).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Nicks, dents and No limited quantity scratches C. Damaged or missing surface protection for aluminium spinner front cone.
No limit if not greater than 50 percent of total surface
If more than 50 percent of total surface, install a new or serviceable spinner front cone (Ref. TASK 7221-00-400-005)
D. Loose or missing bonded washer.
Not serviceable.
Reinstall washer using Loctite 496 (Material No. CP2216) and hold it in pressure
E. Tip erosion.
No limit if radius is not greater than 0.28 in. (7.1 mm) after blending.
Do blending procedure to maximum serviceable limits or install a new serviceable spinner front cone (Ref. TASK 72-21-00400-005).
F. Missing anti-erosion paint.
Any amount is permitted.
G. Corrosion marks (white mushroom pattern) before part removal.
These corrosion marks are not serviceable.
Refer to over serviceable (Ref. TASK 72-00-00-200025).
A. Cracks
Not serviceable
Install a new or serviceable spinner rear cone (Ref. TASK 72-21-00400-006).
B. Dents
No limited quantity
C. Damaged surface protection.
No limit if not greater than 10 percent of total surface
2. Spinner rear cone for:
If more than 10 percent of total surface, install a new or serviceable spinner
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------rear cone (Ref. TASK 7221-00-400-006). D. Missing self-locking nuts
Not serviceable
Replace nuts (Ref. TASK 72-21-00-300-001) or install a new or serviceable spinner rear cone (Ref. TASK 72-21-00400-006).
E. Self-locking nuts with loss of self-locking quality
Not serviceable if running torque is less than to 4 lbf.in (0.04 m.daN)
Replace nuts (Ref. TASK 72-21-00-300-001) or install a new or serviceable spinner rear cone (Ref. TASK 72-21-00400-006).
F. Self-locking nuts with axial looseness
Not more than 0.008 in. (0.2 mm)
Crimp again (no crack permitted) or replace nuts (Ref. TASK 72-21-00-300001)
G. Self-locking nuts with lateral looseness
Not more than 0.008 in. (0.2 mm)
Replace nuts (Ref. TASK 72-21-00-300-001) or install a new or serviceable spinner rear cone (Ref. TASK 72-21-00400-006).
H. Oil wetting at inner of spinner cone or fan disk or forward fan shaft
None permitted
Refer to limit extensions (Ref. TASK 72-00-00-200025) or (Ref. TASK 72-0000-200-025). Replace O-rings on the LPT shaft plug (Ref. TASK 72-55-00960-002).
J. Seal ring tears
Maximum cumulated length 0.4 in. (10 mm)
Refer to limit extensions (Ref. TASK 72-00-00-200025) or (Ref. TASK 72-0000-200-025). Install a new or serviceable spinner
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------rear cone (Ref. TASK 7221-00-400-006). NOTE : Whenever serviceable limits for the following are exceeded, refer ____ to the over-serviceable limit extension if necessary (Ref. TASK 72-00-00-200-025) or (Ref. TASK 72-00-00-200-025) . 5. Close-up ________ Subtask 72-21-00-420-076 A. Install the Spinner Cone. (1) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (2) Install the spinner front cone (Ref. TASK 72-21-00-400-005). Subtask 72-21-00-869-073 B. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-072 C. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B TASK 72-21-00-290-003 Borescope Inspection of the Booster Rotor Blades, Stages 2,3,4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1320 856A1322
warning notice access platform 1 m (3 ft. 3 in.) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-21-00-991-307 72-21-00-991-308 72-21-00-991-309 72-21-00-991-310 72-21-00-991-313
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603 Fig. 604 Fig. 605
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-941-079 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-21-00-010-059 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-21-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-21-00-010-060 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-21-00-991-307, 602/TASK 72-21-00-991-308, 603/TASK 72-21-00-991-309, 604/TASK 72-21-00-991-310, 605/TASK 72-21-00-991-313) Subtask 72-21-00-290-053 A. Borescope Inspection Methods (1) Inspection of booster rotor blades through the borescope ports SO3 and SO5 and booster inlet. (a) There are 2 borescope ports (SO3 and SO5) located (approximately) at the 3.30 oclock position at the periphery of the booster section and almost radially in line with the stages 3 and 4 of the booster stator. Through these ports, you can see the leading and trailing edges of the booster stage 3, 4 and 5 rotor blades. Through the booster inlet, you can get a borescope view of the booster rotor blades, stage 2. (b) To do the inspection of the booster stages 2, 3, 4 and 5 rotor blades: 1 _
Use BORESCOPE-KIT (856A1320P04/P05) (field of view 60 deg., angle of vision 90 deg.) with a long right angle extension.
2 _
Use BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08) NOTE : It is necessary to index and turn the fan rotor. You ____ can turn the fan and booster rotor assembly by hand from the engine inlet.
Subtask 72-21-00-480-060 B. Installation of the borescope. CAUTION : MAKE SURE THAT THE INPUT VOLTAGE OF THE BORESCOPE LIGHT SOURCE _______ SET CORRESPONDS TO THAT OF THE POWER SUPPLY. CAUTION : MAKE SURE THAT : _______ THE ON-OFF SWITCH IS IN THE OFF POSITION. THE LIGHT INTENSITY CONTROL IS SET TO THE MINIMUM BEFORE YOU CONNECT THE BOROSCOPE LIGHT-SOURCE SET TO THE POWER SUPPLY. MAKE SURE THAT THE LIGHT SOURCE AND THE POWER SUPPLY ARE CORRECTLY GROUNDED.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B
Booster Borescope Ports Figure 601/TASK 72-21-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B
Borescope Inspection of the Stage 2 Booster Blades Figure 602/TASK 72-21-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B
Borescope Inspection of the Stage 3 and 4 Booster Blades Figure 603/TASK 72-21-00-991-309 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B
R
Borescope Inspection of the Stage 5 Booster Blades Figure 604/TASK 72-21-00-991-310
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/09
C F M 56-5B
Booster Rotor Blades Damage Inspection (All stages) Figure 605/TASK 72-21-00-991-313 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B (1) Connect the BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08) to a grounded power supply. (a) Connect the fiber light cable to the BORESCOPE-KIT (856A1320P04/P05) and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). (b) Turn the light source on. Engage the borescope and the long right-angle extension, and set it as necessary for inspection. Subtask 72-21-00-290-054 C. Borescope Inspection of the booster blades. WARNING : USE CARE TO AVOID PERSONAL INJURY WHEN YOU MANUALLY TURN THE _______ FAN ROTOR. ASSURE SAFE FOOTING.USE HEAVY PROTECTIVE GLOVES NOTE : Any amount of erosion/flaking of abradable lining material on the ____ outer shroud is permitted on booster vane stages 3,4 & 5. (1) Do an borescope inspection of the booster blades while you turn the fan rotor clockwise (aft looking forward) to complete the procedure. ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Booster rotor blades (all stages) for: A. Missing piece on tip corner
Axial or radial depth 0.25 in. (6.35 mm) max.
B. Cracks
Not serviceable
C. Wear or local deformation (blade tip corner on leading and/or trailing edges
Axial depth 0.5 in. (12.7 mm) and 0.8 in. (20.32 mm) radial max.
D. Nicks, dents on concave and/or convex sides located in area E
No limited quantity if not deeper than 0.01 in. (0.25 mm)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------E. Nicks, dents on No limited quantity if concave and/or not deeper than 0.04 in. convex sides not (1.02 mm) located in area E F. Nicks, dents, on leading and/or mex trailing edges
Axial depth 0.02 in. (0.5 mm) max.
NOTE : If any damage is found, do a borescope inspection of all booster ____ downstream stages and compressor. G. Distorted leading and/or trailing edges not located in area E
Circumferential displacement 0.2 in. (5 mm) maximum NOTE : Whenever ____ serviceable limits for the following are exceeded, refer to the over-serviceable limit extension if necessary (Ref. TASK 72-0000-200-025).
(2) When the inspection is completed, turn the switch off. Leave the main light source blower on for a while to cool the lamp and the housing.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-21-00-410-061 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-21-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-21-00-410-062 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/08
C F M 56-5B TASK 72-21-00-210-009 Inspect Fan Rotor Blades Installed on the Fan Disk 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice 1 ACCESS PLATFORM 1M(3 FT)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 72-00-00-200-025 72-21-00-000-007 72-21-00-300-028 72-21-00-300-029 72-21-00-320-003 72-21-00-400-007 72-23-00-210-003 72-21-00-991-314 72-21-00-991-315
Fluorescent-Penetrant Inspection-Portable-Water Washable Over-Serviceable-Limit Extensions Removal of the Fan Rotor Blades Replacement of Fan Rotor Blades in Pairs Replacement of Individual Fan Blades Blending of Fan Rotor Blades Installation of the Fan Rotor Blades Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material Fig. 606 Fig. 607
3. __________ Job Set-up Subtask 72-21-00-941-087 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (c) Put the ACCESS PLATFORM 1M(3 FT) in position. 4. Procedure _________ (Ref. Fig. 606/TASK 72-21-00-991-314, 607/TASK 72-21-00-991-315) Subtask 72-21-00-210-059 A. Inspection of the fan blades (in situ, installed on the fan disk) NOTE : If pairs of fan blades are not available as spare for replacement ____ (Ref. TASK 72-21-00-300-028), you can replace one blade individually (Ref. TASK 72-21-00-300-029), when the difference between the moment weight of the blade removed and its opposite is not more than 800 cm.g (315 in.g). However, you must do the inspections and corrections given in the replacement procedure with the conditions of the referenced procedure, thus, to make sure the engine vibration is not more than the limits. This also optimizes the operation of the engine. ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fan rotor blades for:
Not serviceable.
Replace pair of matched
A. Cracks or Tears.
blades (Ref. TASK 72-21-
(1) Operational cracks. (2) FOD caused cracks or tears.
00-300-028). Not serviceable
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-21-00 CES
Page 619 May 01/09
C F M 56-5B
Fan Rotor Blades - Blend Limits Figure 606/TASK 72-21-00-991-314- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/08
C F M 56-5B
Fan Rotor Blades - Blend Limits Figure 606/TASK 72-21-00-991-314- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 621 Nov 01/08
C F M 56-5B
Fan Rotor Blades - Blend Limits Figure 606/TASK 72-21-00-991-314- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-21-00 CES
Page 623 Nov 01/02
C F M 56-5B
Fan Rotor Blades - Local Distortions Figure 607/TASK 72-21-00-991-315- 14 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 624 Nov 01/08
C F M 56-5B
Fan Rotor Blades - Local Distortions Figure 607/TASK 72-21-00-991-315- 24 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 625 Nov 01/08
C F M 56-5B
Fan Rotor Blades - Local Distortions Figure 607/TASK 72-21-00-991-315- 34 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 626 Nov 01/08
C F M 56-5B
Fan Rotor Blades - Local Distortions Figure 607/TASK 72-21-00-991-315- 44 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------(Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity. B. Nicks, dents and scratches on contour surfaces of root area, and full airfoil out of midspan shroud
No limited quantity, if not deeper than 0.003 in.(0.08 mm) after removal of high metal.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007) or blend the defects if damage is within the blending limit of figure (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
C. Nicks, dents and scratches on leading edge of root area, Area A.
No limited quantity, if not deeper than 0.006 in.(0.15 mm)
Do blending procedure (Ref. TASK 72-21-00-320003)
D. Nicks, dents and scratches on trailing edge, Area D
No limited quantity, if not deeper than 0.006 in. (0.15 mm).
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007) or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
critical area.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 628 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------E. Nicks, dents and No limited quantity, if Replace blade (Ref. TASK scratches on not deeper than 0.03 in. 72-21-00-000-007) and leading edge in (0.76 mm), with 0.40 in. (Ref. TASK 72-21-00-400Area B. (10.16 mm) max length 007) or blend the defectts for scratches after (Ref. TASK 72-21-00-320removal of high metal. 003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity. F. Localized distortion on leading and trailing edges of root area, Area A.
Not serviceable.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007).
G. Leading and trailing edges distortion in Areas B and D (out of root area trailing edge).
Two areas may be distorted up to 0.34 in. (8.64 mm) out of contour provided there are no sharp corners and the minimum length L is six times the depth of the distortion.
Do a spot fluorescent-penetrant inspection (Ref. TASK 7051-00-230-002).
H. Blade tip (Area C) for:
Tip curl must not extend more than dimension
Replace pair of blades if not in the limits
(1) Leading edge tip curl
X1=0.5 in. (13 mm) across the blade tip and not more than dimension X=0.5 in. (13 mm), along the leading edge. Maximum deflection from original contour is dimension Y=0.25 in. (6.35 mm).
(Ref. TASK 72-21-00-300028) No continued in-service extension is permitted.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 629 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A maximum of 6 blades can have tip curl up to dimension X1=1.3 in. (33 mm) across the blade tip and dimension X=2 in. (51 mm) along the leading edge with maximum deflection from original contour dimension Y=0.6 in. (15 mm). Not more than 3 blades to these increased limits can be adjacent. In all cases, deflection tip angle must not be more than 60 degrees from original airfoil. (2) Trailing edge tip curl.
Tip curl must not extend more than dimension Z1=0.5 in. (13 mm) across the blade tip and not more than dimension Z=0.5 in. (13 mm) along the trailing edge, with maximum deflection from original contour dimension Y1=0.25 in. (6.35 mm). A maximum of 5 blades can have tip curl up to dimension Z1=1 in. (25.4 mm) across the blade tip and up to dimension Z=1 in.(25.4mm) along the trailing edge with maximum deflection from original contour dimension Y1=0.3 in. (7.62 mm).
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028). No continued in-service extention is permitted.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 630 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------No more than 3 blades to these increased limits can be adjacent. (3) Nicks and dents.
No limited quantity if not deeper than 0.04 in. (1.02 mm) and not longer than 0.25 in. (6.35 mm).
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007) or blend the defects (Ref. TASK 72-21-00-320003) if damage is within limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
J. Nicks, dents and scratches on surface of blade platform (excluding fillet and recess area).
For scratches: no limited quantity, if not deeper than 0.02 in. (0.5 mm) and not longer than 0.40 in. (10.16 mm). For nicks and dents, no limit on diameter after removal of high metal.
Do blending procedure (Ref. TASK 72-21-00-320003).
K. Pits
No limited quantity if not deeper than 0.005 in. (0.13 mm). No limits as regards diameter or spacing.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
L. Wear due to shingling on midspan shroud.
Any amount up to 0.005 in. (0.13 mm) deep.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
M. High metal caused by shingling on midspan shroud.
Any amount after smoothing of high metal.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 631 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------N. Shingled midspan Not serviceable. Refer to over serviceable shrouds. limit extensions (Ref. TASK 72-00-00-200025). P. Fan blade(s) tip seizure in fan case abradable shroud
Not serviceable.
Release the blade(s) with hand force to move the seized blade(s) tip forward and circumferentially. Then, do an inspection of the blade(s) as told in this procedure and abradable shroud (Ref. TASK 72-23-00-210003) for serviceability. Make sure that there is free rotation of N1 rotor system.
Subtask 72-21-00-010-064 B. If necessary, remove the fan blades for full inspection (Ref. TASK 72-2100-000-007) 5. Close-up ________ Subtask 72-21-00-410-066 A. Close access. (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the warning notice(s). (3) Remove the access platform(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 632 May 01/09
C F M 56-5B TASK 72-21-00-210-006 Inspect Fan Rotor Blades Removed from the Fan Disk. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A5817
warning notice 1 ACCESS PLATFORM 1M(3 FT) 1 TOOL,CHECK-FAN BLADE SHANK
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 72-00-00-200-025 72-21-00-000-007 72-21-00-210-004 72-21-00-300-028 72-21-00-300-029 72-21-00-320-003 72-21-00-400-007 72-21-00-991-314 72-21-00-991-315
Fluorescent-Penetrant Inspection-Portable-Water Washable Over-Serviceable-Limit Extensions Removal of the Fan Rotor Blades Detailed Inspection and Relubrication of Fan Blade Dovetails, Midspan Shrouds, Retainers, Spacers, Dampers and Fan Disk Dovetail Slots Replacement of Fan Rotor Blades in Pairs Replacement of Individual Fan Blades Blending of Fan Rotor Blades Installation of the Fan Rotor Blades Fig. 606 Fig. 607
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 633 May 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-941-080 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (c) Put an ACCESS PLATFORM 1M(3 FT) in position. 4. Procedure _________ (Ref. Fig. 606/TASK 72-21-00-991-314, 607/TASK 72-21-00-991-315) Subtask 72-21-00-210-056 A. Full inspection of the fan blades (removed from fan disk) (Ref. Fig. 606/TASK 72-21-00-991-314, 607/TASK 72-21-00-991-315) CAUTION : DO NOT CLEAN TITANIUM PARTS WITH COMPOUNDS WHICH CONTAIN _______ HALOGEN. HALOGEN DECREASES THE STRENGTH OF TITANIUM. NOTE : The removal of the fan blades is necessary to do a full inspection ____ of those blades (Ref. TASK 72-21-00-000-007). NOTE : If pairs of fan blades are not available as spare for replacement ____ (Ref. TASK 72-21-00-300-028), you can replace one blade individually (Ref. TASK 72-21-00-300-029), when the difference between the moment weight of the blade removed and its opposite is not more than 800 cm.g (315 in.g). However, you must do the inspections and corrections given in the replacement procedure with the conditions of the referenced procedure, thus, to make sure the engine vibration is not more than the limits. This also optimizes the operation of the engine.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 634 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fan rotor blades for: A. Cracks or tears. (1) Operational cracks.
Not serviceable.
Replace pair of matched blades (Ref. TASK 72-2100-300-028).
(2) FOD caused cracks or tears.
Not serviceable.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
B. Nicks, dents and scratches on contour surfaces of root area, and full airfoil out of midspan shroud critical area.
No limited quantity if no deeper than 0.003 in. (0.08 mm) after removal of high metal.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
C. Nicks, dents and scratches on leading edge of root area, Area A.
No limited quantity if not deeper than 0.006 in. (0.15 mm).
Do blending procedure (Ref. TASK 72-21-00-320003).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 635 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------D. Nicks, dents and No limited quantity if Replace blade (Ref. TASK scratches on not deeper than 0.006 72-21-00-000-007) and trailing edge, in. (0.15 mm). (Ref. TASK 72-21-00-400Area D. 007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity. E. Nicks, dents and scratches on leading edge in Area B.
No limited quantity if not deeper than 0.03 in. (0.76 mm), with 0.40 in. (10.16 mm) max length for scratches after removal of high metal.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
F. Localized distortion on leading and trailing edges of root area, Area A.
Not serviceable.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007).
G. Leading and trailing edges distortion in Areas B and D (out of root area trailing edge).
Two areas may be distorted up to 0.34 in. (8.64 mm) out of contour provided there are no sharp corners and the minimum length L is six
Do a spot fluorescent penetrant inspection (Ref. TASK 70-51-00-230002).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 636 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------times the depth of the distortion. H. Blade tip (Area C) for: (1) Leading edge tip curl.
(2) Trailing edge tip curl.
Tip curl must not extend more than dimension X1 = 0.5 in. (13 mm) across the blade tip and not more than dimension X = 0.5 in. (13 mm) along the leading edge, with maximum deflection from original contour dimension X1 = 0.25 in. (6.35 mm).
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028). No continued in-service extension is permitted.
A maximum of 6 blades can have tip curl up to dimension X1 = 1.3 in. (33 mm) across the blade tip and dimension X = 2 in. (51 mm) along the leading edge with maximum deflection from original contour dimension Y = 0.6 in. (15 mm). No more than 3 blades to these increased limits can be adjacent. In all cases, deflection tip angle must not be more than 60 degrees from original airfoil.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028). No continue in-service extension is permitted.
Tip curl must not extend more than dimension Z1 = 0.5 in. (13 mm) across the blade tip and not more than dimension Z = 0.5 in. (13 mm) along
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028). No continued in-service extension is permitted.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 637 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------the trailing edge, with maximum deflection from original contour dimension Y1= 0.25 in. (6.35 mm). A maximum of 5 blades can have tip curl up to dimension Z1 = 1 in. (25.4 mm) across the blade tip and up to dimension Z = 1 in. (25.4 mm) along the trailing edge with maximum deflection from original contour dimension Y1= 0.3 in. (7.62 mm). No more than 3 blades to these increased limits can be adjacent.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028). No continued in-service extension is permitted.
(3) Nicks and dents.
No limited quantity if not deeper than 0.03 in. (0.76 mm) and no longer than 0.25 in. (6.35 mm).
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
J. Nicks, dents and scratches on surface of blade platform (excluding fillet and recess area).
For scratches: no limited quantity,if not deeper than 0.02 in. (0.5 mm) and, not longer than 0.40 in. (10.16 mm).
Do blending procedure (Ref. TASK 72-21-00-320003).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 638 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------For nicks and dents, no limit on diameter after removal of high metal. K. Missing Molydag coating on dovetail pressure faces.
Missing Molydag coating is permitted on 100 percent of the surface if parent material is not damaged.
(1) Worn or missing Cu.Ni.In coating in the non-contact area (Area 1).
Any amount if parent material is not damaged.
(2) Worn or missing Cu.Ni.In coating in the contact area (Area 2) of the dovetail pressure face.
Flaking of Cu.Ni.In up to 10 percent is permitted if coating adherence is correct in adjacent areas and if there is no evidence of wear on base material.
See over serviceable limit extension (Ref. TASK 7200-00-200-025) and examine blades for serviceability. Make sure that MoS2 dry film lubricant is applied to disk slots, the blade roots (dovetails), the blade platforms and lateral surfaces of those platforms, and the midspan shroud mating surfaces before blade installation (Ref. TASK 72-21-00-210004).
Flaking of Cu.Ni.In over 10 percent and less than 50 percent is permitted if coating adherence is correct in adjacent areas and if there is no evidence of wear on base material.
See over serviceable limit extension (Ref. TASK 7200-00-200-025) and examine blades for serviceability. Make sure that MoS2 dry film lubricant is applied to disk slots, the blade roots (dovetails), the blade platforms and lateral surfaces of those
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 639 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------platforms, and the midspan shroud mating surfaces before blade installation (Ref. TASK 72-21-00-210004) . L. Missing coating on inner faces of platform.
Any amount.
M. Fretting on dovetail pressure faces.
Not serviceable.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
N. Nicks, dents and scratches in dovetail fillet radius.
Not serviceable.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
P. Pits.
No limited quantity if not deeper than 0.005 in. (0.13 mm). No limits as regards diameter or spacing.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
Q. Nicks, dents and scratches on midspan shroud.
No limited quantity if not deeper than 0.010 in. (0.25 mm). No limited length for scratches, and 0.5 in. (12.7 mm) diameter for dents. None permitted in midspan shroud critical
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
area.
R. Missing hard coating from
Flaking of hard coating is permitted if coating
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 640 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------midspan shroud not adherence is correct in exceeding 10 adjacent areas. percent of the midspan shroud mating face. Missing hard coating from midspan shroud exceeding 10 percent but less than 20 percent of the midspan shroud mating face.
Flaking of hard coating is permitted if coating adherence is correct in adjacent areas.
Monitor every 1500 cycles. Remove and examine blades for serviceability (Ref. TASK 72-21-00-000007). Make sure that MoS2 dry film lubricant is applied to disk slots, the blade roots (dovetails), the blade platforms and lateral surfaces of those platforms, and the midspan shroud mating surfaces before blade installation (Ref. TASK 72-21-00-400007).
Missing hard coat from midspan shroud exceeding 20 percent of the midspan shroud mating face.
Not serviceable.
See over serviceable limit extensions (Ref. TASK 7200-00-200-025).
S. Wear due to shingling on midspan shroud.
Any amount up to 0.005 in. (0.13 mm) deep.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
T. High metal caused by shingling on midspan shroud.
Any amount after smoothing of high metal.
U. Fretting on:
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 641 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------WARNING : YOU MUST _______ CLEAN THE FAN BLADE SHANKS WITH ISOPROPY ALCOHOL (MATERIA No. CP1041) BEFORE YOU DO THE INSPECTI NOTE : It is ____ necessary to do the wear depth measurement on all fan blade shanks with the tool TOOL,CHECKFAN BLADE SHANK. (1) Aft side of shank.
No limit if not deeper than 0.003 in. (0.08 mm).
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
(2) Lateral sides of shank
No limit if not deeper than 0.012 in. (0.30 mm) (concave side) and 0.008 in. (0.20 mm) (convex side) on the area referenced by X for length and Y for width.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 642 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------(3) Forward face No limit if not deeper Replace pair of blades if of dovetail. than 0.003 in. (0.08 not in the limits mm). (Ref. TASK 72-21-00-300028). (4) Slide edges of platform.
No limit if not deeper than 0.013 in. (0.33 mm).
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
V. Shingled midspan shrouds.
Not serviceable.
See over serviceable limit extensions (Ref. TASK 7200-00-200-025).
W. Fan blade(s) tip seizure in fan case abradable shroud.
Not serviceable.
Release the blade(s) with hand force to move the seized blade(s) tip forward and circumferentially. Then, do an inspection of the blade(s) and abradable shroud for serviceability. Make sure that there is free N1 rotation.
5. Close-up ________ Subtask 72-21-00-942-075 A. Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the warning notice(s). (3) Remove the access platform(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 643 May 01/09
C F M 56-5B TASK 72-21-00-210-007 Inspection/Check of the Stage 1 Booster Vane, Fan Disk, Fan Blades Spacers and Booster Spool. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R
72-00-00-200-025 72-21-00-000-007 72-21-00-000-008 72-21-00-320-004 72-21-00-400-007 72-21-00-400-008 72-21-00-991-317 72-21-00-991-318 72-21-00-991-319 72-21-00-991-336
Over-Serviceable-Limit Extensions Removal of the Fan Rotor Blades Removal of the Stage 1 Booster Vane Assembly Blending of the Stage 1 Booster Vane Assembly Installation of the Fan Rotor Blades Installation of the Stage 1 Booster Vane Assembly Fig. 608 Fig. 609 Fig. 610 Fig. 611
3. __________ Job Set-up Subtask 72-21-00-941-081 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 644 Aug 01/09
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-21-00-020-073 B. Remove the fan blades (Ref. TASK 72-21-00-000-007). 4. Procedure _________ (Ref. Fig. 608/TASK 72-21-00-991-317, 609/TASK 72-21-00-991-318, 610/TASK 72-21-00-991-319) Subtask 72-21-00-210-057 A. Do this visual inspection: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Stage 1 booster vanes for: (Ref. Fig. 610/TASK 72-21-00-991-319) A. Piece missing:
Maximum number 20 blades up to 0.25 in. (6.5 mm) axial, 0.73 in. (18.5 mm) radial on all airfoil surfaces, except top/bottom 0.4 in. (10 mm).
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
B. Broken vane:
Not serviceable
Replace stage 1 booster vane (Ref. TASK 72-21-00000-008) and (Ref. TASK 72-21-00-400-008)
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 645 May 01/09
C F M 56-5B
Inspection of Fan Disk Figure 608/TASK 72-21-00-991-317 EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 646 May 01/09
C F M 56-5B
Fan Blades Spacer Figure 609/TASK 72-21-00-991-318 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 647 May 01/09
C F M 56-5B
Stage 1 Booster Vane Damage Limits Figure 610/TASK 72-21-00-991-319- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 648 Nov 01/08
C F M 56-5B
Stage 1 Booster Vane Damage Limits Figure 610/TASK 72-21-00-991-319- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 649 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Disengagement from Not serviceable Replace stage 1 booster inner shroud: vane (Ref. TASK 72-21-00000-008) and (Ref. TASK 72-21-00-400-008) In area C, any number, less than 0.25 in. (6.5 mm) radial less than 0.08 in. (2 mm) axial.
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
E. Distortion of trailing edge and leading edge:
Any number, if the length L is not more than 0.709 in. (18 mm) and the maximum dimension X along the chord width is not more than 0.256 in. (6.5 mm)
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
F. Nicks, dents, scratches for areas A and B:
Any number, less than 0.09 in. (2.29 mm) in diameter protrusion.
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
G. Nicks, dents, scratches for area C:
Any number, less than 0.197 in. (5 mm) in diameter protrusion acceptable, not through
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
H. Nicks, dents, scratches on leading edge and trailing edge
Maximum axial length less than 0.08 in. (2 mm) in diameter protrusion acceptable, not thru.
For L/E, repair the stage 1 booster vane (Ref. TASK 72-21-00-320-004) Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
J. Deposits and erosion:
Any amount.
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
K. Cracked inner shroud
Not serviceable.
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025).
R R R R R R
D. Cracks and tears:
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 650 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------L. Erosion of Any amount. abradable lining on outer shroud M. Flaking of abradable lining on outer shroud
Any number, maximum surface affected less than 52.70 sq.in (340 cm2) for CFM56-5B/P & CFM56-5B/2P engines. Any number, maximum surface affected less than 15.50 sq.in (100 cm2) for CFM56-5B engine.
2. Fan disk for: (Ref. Fig. 608/TASK 72-21-00-991-317) A. Cracks
Not serviceable.
B. Wear on dovetail slot pressure faces.
No limit, if less than 50 percent of area is damaged. If the maximum affected surface, even only on one side of one slot, is greater than or equal to 50%, any amount if less than 0.152 mm (0.0059 in.) deep.
C. Nicks and scratches.
No limited quantity, if not deeper than 0.01 in. (0.25 mm) after removal of high metal. None permitted within 0.5 in. (12.7 mm) of dovetail slots disk bore and aft surface of web.
See limit extensions (Ref. TASK 72-00-00-200025)
3. Fan blade spacer for: (Ref. Fig. 609/TASK 72-21-00-991-318)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 651 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Cracks Not serviceable. Replace blade spacer B. Fretting
No limit, if the damage is not more than 0.005 in. (0.125 mm) deep.
Replace blade spacer
C. Corrosion, pitting
No limit for the damage less than 0.0098 in. (0.25 mm) deep, if the surface protection is not damaged.
Replace blade spacer
D. Damaged Surface protection
No limit for the damage less than 20 percent of total surface if parent material is found without corrosion pitting in the damaged area.
Replace blade spacer
E. Scratches
No limit for the damage 0.005 in. (0,125 mm) deep maximum after the removal of high metal.
Replace blade spacer
4. Booster spool for: (Ref. Fig. 611/TASK 72-21-00-991-336) A. Wear on front flange
No limit if not deeper than 0.001 in. (0.0254 mm) for wear due to contact with the rear surface of the fan blade shank.
B. Dents, nicks and scratches on front surface of seal tooth
Any amount if less than 0.003 in. (0.08 mm) deep.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 652 Nov 01/08
C F M 56-5B
Booster Spool Figure 611/TASK 72-21-00-991-336 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 653 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Plugs on surface A A maximum of 8 plug See limit extensions missing is permitted. (Ref. TASK 72-00-00-200025) 5. Close-up ________ Subtask 72-21-00-420-077 A. Install the fan blades (Ref. TASK 72-21-00-400-007). Subtask 72-21-00-869-075 B. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-073 C. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 654 Nov 01/08
C F M 56-5B TASK 72-21-00-210-004 Detailed Inspection and Relubrication of Fan Blade Dovetails, Midspan Shrouds, Retainers, Spacers, Dampers and Fan Disk Dovetail Slots 1. __________________ Reason for the Job Refer to the MPD TASK: 722000-C2 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
soft bristle brush warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2104
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
Material No.
CP5062
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * molykote G rapid (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * MoS2 dry film lubricant (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 655 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-007 72-21-00-210-006 72-21-00-210-007 R
72-21-00-400-007 72-23-00-280-006 72-21-00-991-335
Removal of the Fan Rotor Blades Inspect Fan Rotor Blades Removed from the Fan Disk. Inspection/Check of the Stage 1 Booster Vane, Fan Disk, Fan Blades Spacers and Booster Spool. Installation of the Fan Rotor Blades Inspection of Mid Acoustical Panels Fig. 612
3. __________ Job Set-up Subtask 72-21-00-941-089 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-21-00-020-079 B. Remove the fan blades (Ref. TASK 72-21-00-000-007). Subtask 72-21-00-110-056 C. CLean the fan blade dovetails. WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY SHOULD _______ BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 656 May 01/09
C F M 56-5B (1) Clean the fan blade dovetails and midspan shrouds, the fan blade spacers and the fan disk dovetail slots with isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656). Use a soft bristle brush if necessary, to remove dirt build-ups. 4. Procedure _________ (Ref. Fig. 612/TASK 72-21-00-991-335) Subtask 72-21-00-210-061 A. Do an inspection/check of the items which follow: (1) Fan blade airfoils, midspan shrouds and dovetails (Ref. TASK 72-2100-210-006). (2) Fan blade spacers and fan dovetails slots (Ref. TASK 72-21-00-210007). R
Subtask 72-21-00-210-062
R R
B. Do a tap test inspection for the mid acoustical panel delamination (Ref. TASK 72-23-00-280-006) 5. Close-up ________ Subtask 72-21-00-640-052 A. Apply MoS2 dry film lubricant (Material No. CP5062) or molykote G rapid (Material No. CP2104): - the fan disk dovetail slots, - the blade spacers, - the blade dovetails, - the blade midspan shrouds, before the re-installion of the blades. Lubricant should be applied liberally to all dovetail and slot pressure faces. Brush application is preferred. Allow the lubricant to dry to a dull opaque finish before installation of blades in disk slots. Subtask 72-21-00-420-085 B. Install fan blades (Ref. TASK 72-21-00-400-007).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 657 May 01/09
C F M 56-5B
Fan Blade, Blade Spacer and Disk Areas to Be Inspected after Cleaning for Removal of Lubricant from Pressure Faces Figure 612/TASK 72-21-00-991-335 R EFF : 001-049, 051-099, 101-149, 151-199, Page 658 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-21-00
C F M 56-5B Subtask 72-21-00-942-080 C. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 659 Nov 01/08
C F M 56-5B FAN AND BOOSTER ASSEMBLY - REPAIRS __________________________________ TASK 72-21-00-300-001 Replacement of the Crimped Self-Locking Nuts on the Spinner Rear Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-400-005 72-21-00-400-006 SPM 704251350018
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Installation of the Spinner Front Cone Installation of the Spinner Rear Cone
3. __________ Job Set-up Subtask 72-21-00-941-071 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put an access platform in position. 4. Procedure _________ Subtask 72-21-00-020-067 A. Removal of the defective cimpred Nut(s). (1) Remove the spinner front cone (Ref. TASK 72-21-00-000-005) (2) If necessary, remove the spinner rear cone (Ref. TASK 72-21-00-000006) (3) Remove the defective crimped self-locking nut(s) from the spinner rear cone. (Ref. SPM 704251350018) Subtask 72-21-00-420-070 B. Crimping of the New Self-Locking Nuts. CAUTION : BE CAREFUL NOT TO CAUSE DAMAGE TO THE SURFACE PROTECTION AROUND _______ THE NUTS DURING NUT INSTALLATION. (1) Crimp the new self-locking nut(s). (Ref. SPM 704251350018) NOTE : No radial or end play is permitted in the installation of the ____ crimped self-locking nuts type B. (2) Install the spinner front cone. (Ref. TASK 72-21-00-400-005) (3) Install the spinner rear cone. (Ref. TASK 72-21-00-400-006)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-21-00-942-065 A. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B TASK 72-21-00-300-009 Correction of the Static Imbalance 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-009 71-00-00-750-001 72-21-00-991-324 72-21-00-991-328
Vibration Check Fan Trim Balance - 1 sensor 3 speed Fig. 801 Fig. 802
3. __________ Job Set-up Subtask 72-21-00-941-074 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). 1(2). (4) Put an access platform in position. 4. Procedure _________ (Ref. Fig. 801/TASK 72-21-00-991-324, 802/TASK 72-21-00-991-328) Subtask 72-21-00-750-053 A. Example of static imbalance correction on a spinner still equipped with balance screws other than P07. (Ref. Fig. 802/TASK 72-21-00-991-328) (1) Assume a balance weight Fc = 480 cm.g (189 in.g) orientated toward balance screw No. 24, is to be installed on the spinner which is still equipped with balance screws P02 in screw positions No. 18 and 19, and P05 in screw position No. 22. (2) Both screws P02 have a total moment weight F1 of 327 cm.g (129 in.g) acting along an axis between both screws. (3) Screw P05, installed in position No. 22, has a moment weight F2 of 375 cm.g (148 in.g) acting along an axis going through the screw location. (4) Vectorial sum corresponding to the 3 balance screws has a resultant F3 of approximately 656 cm.g (258 in.g). (5) Fc and F3 have a vectorial sum Ft of 1072 cm.g (422 in.g) acting along an axis close to balance screw No. 22. (6) Shows that 1 centered screw P04 and 2 lateral screws P05 provide a total moment weight of 1048 cm.g (413 in.g). (Ref. Fig. 801/TASK 72-21-00-991-324) (7) One balance screw P04 must be installed in position 22 and 2 lateral screws P04 must be installed in position 21 and 23, instead of screws previously installed. NOTE : As vectorial sum Ft defined in paragraph A(5) is greater than ____ 400 cm.g (157 in.g), static correction must be followed by a trim balance operation (Ref. TASK 71-00-00-750-001).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/08
C F M 56-5B
Various Balance Screw Arrangements For Given Moment Weights Figure 801/TASK 72-21-00-991-324- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/08
C F M 56-5B
Various Balance Screw Arrangements For Given Moment Weights Figure 801/TASK 72-21-00-991-324- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B
Static Imbalance Correction Figure 802/TASK 72-21-00-991-328 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Nov 01/08
C F M 56-5B NOTE : you can do a vibration check (Ref. TASK 71-00-00-710-009) when ____ you replace the fan blade(s) or when you install the same fan blade set again. The results of the the survey will show if it is necessary to do a fan trim balance or if the installation is correct (Ref. TASK 71-00-00-750-001). 5. Close-up ________ Subtask 72-21-00-869-069 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-068 B. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B TASK 72-21-00-320-003 Blending of Fan Rotor Blades 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific 856A2682G01 856A2949
magnifying glass power 10x to 20x soft file warning notice Light source - white 1 EDDY CURRENT INSTRUMENT 1 TEMPLATE, CHECKING - FAN BLADE LEADING EDGE
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2189
Material No.
CP2191
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * durite G422 (Ref. 70-30-00) * durite G421 (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2656
* mag-chem skysol (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 70-52-00-250-002 72-21-00-000-007 SPM 704111 SPM 704112 72-21-00-991-329 72-21-00-991-333 72-21-00-991-334
Fluorescent-Penetrant Inspection-Portable-Water Washable Eddy Current Inspection of the Fan Blade Leading Edge Removal of the Fan Rotor Blades Fig. 803 Fig. 804 Fig. 805
3. __________ Job Set-up Subtask 72-21-00-941-075 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 803/TASK 72-21-00-991-329, 804/TASK 72-21-00-991-333, 805/TASK 72-21-00-991-334) Subtask 72-21-00-020-069 A. Remove the damaged fan blades, if necessary (Ref. TASK 72-21-00-000-007). Subtask 72-21-00-220-054 B. Examine the fan blades. (1) Leading edge and trailing edge in the critical root area. (a) Find the critical root area. 1 _
The root area longitudinal dimension is 2.32 in. (60 mm).
(2) Mid span shroud area. (a) Find the critical area for the mid span shroud. 1 _
The critical areas are at 1.57 in. (40 mm) from the leading edge and at 1.18 in. (30 mm) on each side of the mid span shroud.
2 _
The critical areas are at 0.63 in. (16 mm) from the bottom of the mid span shroud and at 0.39 in. (10 mm) from the mid span shroud trailing edge.
(3) Leading edge and trailing edge repair in non critical areas. (a) The leading edge dimensions. 1 _
Taper the blend repair for area A and area B as follows: a _
In area A the blend repair is not more than 0.08 in. (2 mm).
b _
In area B the blend repair is not more than 0.339 in. (8.6 mm).
c _
When the distance (Dim. O) between two blend repairs is less than or equal to five times the depth of the smallest of these blends, tangentially blend out the bottom of the two blends.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B
Blend Repair of the Fan Rotor Blade Airfoil Figure 803/TASK 72-21-00-991-329 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/08
C F M 56-5B
Fan Blade Blending Repair limits Figure 804/TASK 72-21-00-991-333- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Nov 01/08
C F M 56-5B
Fan Blade Blending Repair limits Figure 804/TASK 72-21-00-991-333- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B
Fan Blade Blending Repair limits Figure 804/TASK 72-21-00-991-333- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B
Typical Examples of Unacceptable Leading Edges Contours Figure 805/TASK 72-21-00-991-334 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
C F M 56-5B d _
The total length of blend repairs permitted on the leading edge is equal to 2.76 in. (70 mm) per blade.
(b) The leading edge (area A and B) blend repairs are permitted with these limits. 1 _
Make sure that after you do the blending repair, the edge thickness is not less than the initial thickness.
2 _
The longitudinal direction of the repair for area A must be equal to or more than ten times the depth (Dim. P) of the damage.
3 _
The longitudinal direction of the repair for area B must be equal to or more than eight times the depth (Dim. P) of the damage.
4 _
The minimum radius R4 is equal to or more than fifteen times of depth (Dim. P) for area A.
5 _
The minimum radius R4 is equal to or more than ten times of depth (Dim. P) for area B.
6 _
The radius R3 for the blend repair on either side of the initial damage is a minimum radius blend of 0.2 in. (5 mm) and a maximum radius blend of 0.31 in. (8 mm).
7 _
If the distance (Dim. O1) between the blend repair and the blade tip is not more than two times the depth (Dim. P) of the repair, do the step: a _
Blend the bottom area of the repair tangentially from the depth of the area to the blade tip and blend the tip to the blending tip radius R1 with a minimum radius blend of 0.02 in. (0.5 mm) and a maximum radius blend of 0.67 in. (17 mm) at R1 minimum possible value.
(c) The trailing edge dimensions. 1 _
Taper the blend repair as follows: a _
The blend repair is not more than 0.059 in. (1.5 mm).
b _
When the distance (Dim. O) between two blend repairs is less than or equal to five times the depth of the smaller repair area, blend the two repairs together to a depth of a line which tangentially connects the bottom areas.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B c _
The total length of blend repairs permitted on the trailing edge is equal to 1.77 in. (45 mm) per blade.
(d) Trailing edge blend repairs are permitted with these limits. 1 _
Make sure that after you do the blending repair, the edge thickness is not less than the initial thickness.
2 _
The longitudinal direction of the repair must be equal to or more than ten times the depth (Dim. P) of the damage.
3 _
The minimum radius R4 is equal to or more than fifteen times the depth (Dim. P).
4 _
The radius R3 for the blend repair on either side of the initial damage is a minimum radius blend of 0.2 in. (5 mm) and a maximum radius blend of 0.31 in. (8 mm).
5 _
If the distance (Dim. O1) between the blend repair and the blade tip is not more than two times the depth (Dim. P) of the repair, do this step: a _
Blend the bottom area of the repair tangentially from the depth of the area to the blade tip and blend the tip to the blending tip radius R2 with a minimum radius blend of 0.02 in. (0.5 mm) and a maximum radius blend of 0.43 in. (11 mm) at R2 minimum possible value.
(4) Leading edge and trailing edge repair in critical areas. (a) The leading edge and trailing edge dimensions. 1 _
Taper the blend repair as follows: a _
The blend repair for the leading edge is not more than 0.04 in. (1 mm).
b _
The blend repair for the trailing edge is not more than 0.059 in. (1.5 mm).
(b) The leading edge and trailing edge blend repairs are permitted with these limits. 1 _
Taper the blend repair as follows: a _
The longitudinal direction of the repair must be equal to or more than twenty times the depth (Dim. P) of the damage.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 819 Nov 01/08
C F M 56-5B b _
The minimum radius R4 is equal to or more than thirty times the depth (Dim P).
(5) Blade tip repair (area C). (a) The blend repair does not extend more than 0.04 in. (1 mm). (b) The chordal direction of the repair must be equal to or more than eight times the depth (Dim. P) of the damage. (c) The minimum radius R4 is equal to or more than ten times the depth (Dim. P) of the damage. (d) The radius R3 for the blend repair on either side of the initial damage is a minimum radius blend of 0.2 in. (5 mm) and a maximum radius blend of 0.31 in. (8 mm). (e) The radius R1 blend repair between the leading edge and the tip is not less than 0.02 in. (0.5 mm) and not more than 0.67 in. (17 mm). (f) The radius R2 blend repair between the trailing edge and the tip is not less than 0.02 in. (0.5 mm) and not more than 0.43 in. (11 mm). (g) When the distance (Dim. O) between two blend repairs is less than or equal to five times the depth (Dim. P) of the repair, blend the two repairs together to a line which tangentially connects the bottom areas. (h) If the distance (Dim. O1) between the blend tip repair and the blade leading edge is less than two times the depth (Dim. P) of the repair, do this step: 1 _
Blend the bottom of the repair tangentially across to the blade leading edge and blend the tip to the blending tip radius R1 minimum possible value.
(i) If the distance (Dim. O1) between the blend tip repair and the blade trailing edge is less than two times the depth (Dim. P) of the repair, do this step: 1 _
Blend the bottom of the repair tangentially across to the blade trailing edge and blend the tip to the blending tip radius R2 minimum possible value.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 820 Nov 01/08
C F M 56-5B (j) The total chordal length of the blend repairs permitted on the blade tip is equal to 0.8 in. (20 mm) per blade. (6) Fan blade airfoil blend repairs. (a) The convex or concave blend repair. 1 _
Repairs are permitted on the surface with this limit: a _
2 _
Do not repair inside the blade critical areas.
If the distance (Dim. U) is not less than 0.079 in. (2 mm), do this step: a _
The convex or concave blend repair depth becomes not more than 0.024 in. (0.6 mm).
3 _
The concave or convex blend repair minimum radius R5 is not less than five times the depth (Dim. K).
4 _
The concave or convex blend repair area length is the sum of dimensions (Dim. S) and (Dim. T). a _
The total length of (Dim. S) and (Dim. T) for a blend repair is not more than 0.425 in. (10.8 mm).
b _
The chordal length (Dim. S) for a blade is six times the repair length (Dim. K).
c _
The maximun longitudinal length (Dim. T) is two times the length (Dim. S).
d _
The distance (Dim. O2) between two blend repairs must be more than the blend repair length (Dim. S) + (Dim. T) of the largest blend.
e _
The total length (Dim. S) + (Dim. T) of all blend repairs on the convex side must not be more than 1.3 in. (33 mm).
f _
The total length (Dim. S) + (Dim. T) of all blend repairs on the concave side must not be more than 1.3 in. (33 mm).
(7) Mid span shroud blend repair. (a) The distance (Dim. D) between two blend repairs must be more than five times the two defects largest blend.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 821 Nov 01/08
C F M 56-5B (b) The distance (Dim. V) for a blend repair is not more than 0.02 in. (0.5 mm). (c) The longitudinal direction (Dim. W) for a blend repair must be equal to or more than eight times the depth (Dim. V). (d) The minimum radius R6 is equal to or more than ten times the depth (Dim. V). (e) The radius R3 for the blend repair on either side of the damage is a minimum radius blend of 0.2 in. (5 mm) and a maximum radius blend of 0.31 in. (8 mm). (f) The minimum distance (Dim. M) is equal to or more than six times the depth (Dim. V). (g) The maximum distance (Dim. N) is two times the length (Dim. M). (h) The total length of (Dim. M) and (Dim. N) for a blend repair is not more than 0.35 in. (9 mm). (i) The distance (Dim. X) between two blend repairs, located either on the same or opposite sides, must be more than 0.177 in. (4.5 mm). (j) The total length (Dim. W) of all blend repairs must not be more than 0.16 in. (4 mm). Subtask 72-21-00-320-052 C. Do the blending operation as follows: CAUTION : EXCESSIVE HEAT CREATED DURING BLENDING CAN WEAKEN BLADE. TO _______ AVOID EXCESSIVE HEAT WHEN POWER GRINDING OR BLENDING TOOLS ARE USED, CHECK FOR HEAT BUILDING BY TOUCHING OCCASIONALLY WITH BARE HAND. IF BLADE BECOMES TOO HOT TO TOUCH, ALLOW MATERIAL TO COOL BEFORE CONTINUING REPAIR. NOTE : If five or more fan blades have been subject to this blending ____ repair, perform trim balance operation. It is recommended that location of repaired blades be recorded to perform trim balance operation.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 822 Nov 01/08
C F M 56-5B (1) Remove the surface damage from the blade airfoil per (Ref. SPM 704111) using a soft file or strips of durite G422 (Material No. CP2189) or durite G421 (Material No. CP2191) grade 150 or 180, used dry. The blended areas must make a smooth transition into the surrounding areas. NOTE : To prevent axial scratches, always do the blending in a ____ longitudinal direction, parallel with the length of the blade. (2) Complete the blending with strips of durite G422 (Material No. CP2189) grade 400 or 800, used dry. The surface finish (roughness) on blended areas must be as close as pratical to the original finish. (3) If a large or deep blend is required, a low speed power tool equipped with an appropriate titanium grinding tool may be used to shorten the time required to remove the metal per (Ref. SPM 704112) but you must complete with hand blending as told above. NOTE : Reworked contour must conform to original contour. ____ (Ref. Fig. 805/TASK 72-21-00-991-334) Subtask 72-21-00-110-054 D. Clean the blade: CAUTION : TITANIUM PARTS REQUIRE THE USE OF NON-HALOGENATED SOLVENTS. _______ (1) Clean blade using isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) . Subtask 72-21-00-230-052 E. Do an Inspection of Blended Area: (1) Do a fluorescent inspection (Ref. TASK 70-51-00-230-002) or an eddy current inspection with EDDY CURRENT INSTRUMENT (856A2682G01) (Ref. TASK 70-52-00-250-002) of blended area for cracks. No crack is permitted. NOTE : If you did the blending operation on the leading edge in area ____ B, you can delay the fluorescent-penetrant inspection by 10 flight cycles or 25 flight hours.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 823 Nov 01/08
C F M 56-5B In this case, you must do a visual inspection with a magnifying glass power 10x to 20x under Light source - white, to make sure sure that the damage is fully removed. (a) If necessary, repeat blending and inspection until no crack is detected. Refer paragraph A. to paragraph E. (1). (2) If you have a template, TEMPLATE, CHECKING - FAN BLADE LEADING EDGE (856A2949G01), use it after the blending of the leading edge as follows: (a) Put it on the leading edge of the blade on concave side so that the tabs touch the leading edge and the midspan shroud fillet radius with airfoil. 5. Close-up ________ Subtask 72-21-00-869-070 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-069 B. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 824 Nov 01/08
C F M 56-5B TASK 72-21-00-320-004 Blending of the Stage 1 Booster Vane Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific
soft file warning notice access platform 0.5 m (1 ft. 8 in.)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2189
Material No.
CP2191
* durite G422 (Ref. 70-30-00) * durite G421 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 72-21-00-000-007 72-21-00-400-007 72-21-00-991-330
Fluorescent-Penetrant Inspection-Portable-Water Washable Removal of the Fan Rotor Blades Installation of the Fan Rotor Blades Fig. 806
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 825 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-941-076 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). 1(2). (4) Put an access platform in position. 4. Procedure _________ (Ref. Fig. 806/TASK 72-21-00-991-330) Subtask 72-21-00-020-074 A. Remove the Fan rotor blades (Ref. TASK 72-21-00-000-007). Subtask 72-21-00-220-055 B. Check for dimensions and location of defects on edge and compare with repair limits. (Ref. Fig. 806/TASK 72-21-00-991-330) Subtask 72-21-00-320-053 C. Perform blending of defects using a soft file or strips of durite G422 (Material No. CP2189) or durite G421 (Material No. CP2191), used dry. (1) Remove a minimum of 0.01 in. (0.25 mm) of base metal in addition to depth of defect.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 826 Nov 01/08
C F M 56-5B
Blending of a Stage 1 Vane Assembly Leading Edge Figure 806/TASK 72-21-00-991-330 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 827 Nov 01/08
C F M 56-5B Subtask 72-21-00-230-053 D. Fluorescent penetrant inspect reworked area (Ref. TASK 70-51-00-230-002). No crack is allowed. 5. Close-up ________ Subtask 72-21-00-420-078 A. Install the fan rotor blades (Ref. TASK 72-21-00-400-007). Subtask 72-21-00-869-071 B. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-070 C. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 828 Nov 01/08
C F M 56-5B TASK 72-21-00-300-025 Angular Distribution for a Replacement of 3 to 18 Pairs of fan Rotor Blades Manual Method 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-991-331
Fig. 807
3. __________ Job Set-up Subtask 72-21-00-941-077 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 829 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put an access platform in position. 4. Procedure _________ (Ref. Fig. 807/TASK 72-21-00-991-331) Subtask 72-21-00-350-051 A. Manual Distribution Method. (1) Put the blades in decreasing order of moment weights. The moment weight of each blade is marked under the blade root. (2) Temporarily give numbers to the blades from 1 to 36, blade No. 1 is the haviest, blade No. 36 is the lightest. (3) Make the angular distribution of blades as shown in table of referenced figure. (Ref. Fig. 807/TASK 72-21-00-991-331) (4) Calculate the resulting (static) moment of the imbalance of the blades. (5) Decrease the calculated resultant to the lowest possible amount. To do this, change the location of the blades as necessary. NOTE : The moment weight difference between 2 blades 180-degree apart ____ must be kept within 200 g.cm. The resultant moment of imbalance must be less than 80 g.cm. 5. Close-up ________ Subtask 72-21-00-869-072 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-071 B. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
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Page 830 Nov 01/08
C F M 56-5B
Angular Distribution and Installation of Blades on Fan Disk Figure 807/TASK 72-21-00-991-331 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 831 Nov 01/08
C F M 56-5B NO.1 AND NO.2 BEARING SUPPORT ASSEMBLY - DESCRIPTION AND OPERATION __________________________________________________________________ 1. _______ General (Ref. Fig. 001) A. No. 1 and no. 2 bearing support module (1) The No. 1 and No. 2 bearing support module is bolted to the fan frame front face and supports both the fan and booster rotor assemblies. (2) The bearing support consists of the following major parts : (a) No. 1 bearing support. (b) No. 1 ball bearing. (c) No. 2 bearing support. (d) No. 2 roller bearing. (e) Oil manifold assembly. (f) External piping. (g) Fan shaft. (h) Forward stationary air/oil seal. 2. ___________ Description (Ref. Fig. 002, 003, 004, 005) A. No. 1 Bearing Support (Ref. Fig. 002, 003) The No. 1 bearing support is a titanium weldment. The rear outer flange of the support is bolted to the fan frame. The front flange of the support carries the No. 1 ball bearing housing. The rear inner flange carries the No. 2 bearing support. The outer casing is provided with a flange onto which is attached the No. 1 bearing stationary air/oil seal. The bottom rear of the casing has an orifice providing for oil draining through the fan frame hub. The forward casing has holes for oil and air venting into the No. 1 bearing air/oil seal and from there, to the front engine sump via a vent tube.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
No.1 and No.2 Bearing Support Module Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
No.1 and No.2 Bearing Support and Oil Manifold Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
No.1 Bearing Support Assembly Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
No.2 Bearing Support Assembly Figure 004 R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B
No.1 and No.2 Bearing Support External Piping Figure 005 R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 6 Nov 01/08
C F M 56-5B B. No. 1 Ball Bearing (Ref. Fig. 002, 003) The No. 1 ball bearing is a thrust bearing which carries the axial loads generated by the low pressure rotor system. Its one-piece outer race is located in the bearing housing. Its inner race has 2 halves attached by a nut to the No. 1 bearing sleeve which is installed on the fan shaft. The bearing sleeve is provided with an oil baffle upstream of No. 1 bearing. The bearing sleeve has provisions for locking the No. 1 bearing, locating the oil baffle forward of the No. 1 bearing, and integral with the sleeve, the No. 1 bearing rotating air/oil seal. C. No. 2 Bearing Support (Ref. Fig. 002, 004) The No. 2 bearing support is a steel alloy assembly. Its front flange is bolted to the No. 1 bearing support. Its rear flange accommodates the No. 2 roller bearing outer race. Holes are provided in this support for internal pressure equalization purposes in the forward oil sump. It also has an integral sleeve, at the 4 oclock position, providing for N1 speed sensor installation. There are holes at the 9 oclock position for oil supply to the oil manifold assembly and for installing the No. 2 bearing oil nozzle. D. No. 2 Roller Bearing (Ref. Fig. 002, 004) The No. 2 roller bearing takes the radial loads from the fan and booster rotor. Its inner race is mounted on the fan shaft and the outer race is bolted to the No. 2 bearing support. The N1 speed sensor ring, mounted on the fan shaft, will take up the radial loads in case of No. 2 bearing failure and, in addition, acts as a pulse generating rotor for the N1 speed sensor. The rear rotating air/oil seal is mounted at the rear of the fan shaft and provides for sealing of the engine forward sump. E. Oil Manifold Assembly (Ref. Fig. 001, 002) The oil manifold is installed inside of the No. 1 bearing support. It has one tube assembly which supplies oil to the dual oil nozzle at the No. 1 bearing and another tube assembly which supplies oil to the single oil nozzle at the No. 2 bearing. The manifold is connected to the oil supply line of fan frame through an oil coupling connection located at the 9 oclock position of the bearing support.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 7 Nov 01/08
C F M 56-5B F. External Piping (Ref. Fig. 002, 005) The external piping consists of 5 tubes mounted externally relative to the No. 1 bearing support. These tubes connect the forward stationary air/oil seal rear face to the fan frame front face. There are 3 air pressurization tubes for the No. 1 bearing dual stationary air/oil seal at the 3:30, 8:30, and 11:30 oclock positions. There is one oil scavenge tube at 6 oclock position from the forward oil sump and one oil drain tube at 5 oclock position, in case of failure of the dual stationary air/oil seal. G. Fan Shaft (Ref. Fig. 002) The fan shaft is a steel alloy forging. It is supported by the No. 1 and No. 2 bearings. Its front flange provides for attachment with the fan disk. Mechanical coupling with the low pressure turbine (LPT) shaft is provided by inner drive splines and an inner shoulder for axial retention. The shaft is fitted with a rotating air/oil separator, mounted between the No. 1 and No. 2 bearings, which removes oil particles from the forward sump air vented overboard. H. Forward Stationary Air/Oil Seal (Ref. Fig. 003) The stationary air/oil seal is a composite material assembly. It limits the engine forward sump at its front end, and is used to duct pressurization air to labyrinths provided on the No. 1 bearing sleeve. Space located between the seal inner and outer skin is divided into independent compartments for pressurization, drainage and oil scavenge.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 8 Nov 01/08
C F M 56-5B FAN FRAME ASSEMBLY - DESCRIPTION AND OPERATION ______________________________________________ 1. _______ General (Ref. Fig. 001, 002, 003) The fan frame module provides front handling mounts and is the main forward support for mounting the engine to the aircraft. Its purpose is to support the fan, booster and high pressure compressor (HPC) rotors, and to provide ducting for primary and secondary airflows. The fan frame module consists of the following major assemblies: - Fan frame assembly. - Fan Inlet Case assembly. 2. _________ Fonctions The Fan Frame and Fan Inlet Case perform the following primary functions: A. Fan Frame. (1) An inlet airflow path to the core engine. (2) A support for loads of the fan stator, fan rotor and fan reverser. (3) Containment of accessory drive power take off gears (inlet gearbox) and radial drive shaft arrangement. (4) A variable bypass bleed valve system. (5) Housing for the oil pressure, scavenge, drain lines and venting/pressurisation/sealing system associated with the bearings and gears located in the engine forward sump. B. Fan Inlet Case. (1) Provides for attachment of the engine inlet cowl and the support and transmission of attachment loads from this point to the fan frame. (2) Provides fan blade containment. (3) Provides attachment points for acoustical panels, and fan OGV. (4) Provides an abradable lining for fan blade tips.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Fan Frame Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Fan Frame Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
Fan Frame Assembly Figure 003 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
Fan Frame Assembly Figure 003 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B 3. Description ___________ (Ref. Fig. 002, 003) A. Fan Frame Assembly The fan frame assembly is a fabricated structural weldment made of concentric rings connected by radial struts. It consists of the basic fan frame structure and the fan inlet case assembly. (1) The basic fan frame structure is made of steel alloy. It consists of a hub, mid box structure and outer casing interconnected through 4 thick and 8 thin radial struts. (a) Structural strength for the fan frame is obtained from the 12 struts. The struts are hollow and provide passage for the following equipment : 1 _
No. 1 bearing vibration sensor cable (No. 4 strut).
2 _
N1 speed sensor and drain cavity (No. 6 strut).
3 _
Transfer gearbox (TGB) radial drive shaft and scavenge tube (No. 7 strut).
4 _
Forward sump oil supply tube (No. 10 strut).
(b) The hub front face supports the No. 1 and No. 2 bearing support. The rear face supports, from front to rear, the IGB and No. 3 bearing module and the rear stationary air/oil seal together with its pressurization air supply ring. The hub outer surface, which is also the inner wall of the primary airflow annulus, has orifices for bleed air requirements. (c) The mid box structure is located radially between the primary and secondary airflows. It houses the 11 variable bleed valve (VBV) ballscrew actuators and the VBV master ballscrew actuator , and air scoops for the LPT active clearance control system (LPTACC). The front flange of the structure supports the rear outer flanges of the stage 5 booster vane assembly, and the fan OGV inner shroud. The structure rear flange supports the HPC forward case, the VBV hydraulic fuel gear motor and provides for engine mounting. (d) The outercasing makes up the outer wall of the secondary airflow. Located on the outer surface of the casing are the 2 ground handling mounts and the TGB mounting pad. The fan inlet case mounts to the outer casing front flange, and the fan discharge duct mounts to the outer casing rear face.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 6 Nov 01/08
C F M 56-5B (e) An adapter ring, with a V-groove, is bolted to the outer casing rear flange to adapt the outer cowl of the engine (fan) thrust reverser (Ref. 78-30-00). 4. Fan _______________________ Inlet Case Assembly (Ref. Fig. 001, 002) The fan inlet case assembly is composed of the 2 parts which follows: - The upstream fan case - The downstream fan case The upstream fan case is a structural weldment made of alloy steel. The outer rear flange is bolted to the downstream fan case outer front flange. The downstream fan case is made of aluminium. The outer rear flange is bolted to the outer front flange of the fan frame. The outer surface of the fan inlet case assembly has flanges and ribs to provide additional strength to the case during engine operation. It also has 2 hoisting points for engine ground handling purposes (2 and 10 oclock positions), 2 accessory gearbox (AGB) mounts and various other mounting provisions for engine equipment. The inner surface houses an abradable shroud located radially in line with the fan rotor blades, 6 fan forward acoustical panels, 6 fan mid acoustical panels, the fan OGV assembly and 12 aft acoustical panels. The engine air inlet cowl is attached to the front flange of the fan inlet case. The fan outlet guide vanes (OGV) are made of composite material. The fan OGV inner shroud rear flange is bolted to the fan frame. Its forward outer surface contains 35 apertures to allow passage of the vane inner platforms and two borescope inspection ports. The fan splitter fairing is attached to the forward end of the fan OGV inner shroud. The fan OGV assembly has 35 twin vanes (or vane doublets). The vane inner platform are axially retained by the inner face of the fan (OGV) inner shroud. The vane outer platforms are bolted to the fan inlet case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 7 Nov 01/08
C F M 56-5B FAN FRAME ASSEMBLY - REMOVAL/INSTALLATION _________________________________________ TASK 72-23-00-000-008 Removal of the Fan Outlet Guide Vane (OGV) Doublets 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-23-00-000-026 78-30-00-481-041 78-36-00-010-040 72-23-00-991-300
Opening of the Fan Cowl Doors Removal of the Aft Acoustical Panels Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Fig. 401
3. __________ Job Set-up Subtask 72-23-00-941-071 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-083 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-23-00-040-061 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-094 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 401/TASK 72-23-00-991-300) Subtask 72-23-00-020-059 A. Removal of the Fan Outlet Guide Vane (OGV) Doublets (Rearward) (1) Remove the aft acoustical panels (Ref. TASK 72-23-00-000-026) (2) Remove the sealant which covers the three bolts (20) and (30) in the outer platform recesses. If necessary only. (3) Remove the three bolts (20) and (30) which attach the OGV doublet (10) platform.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Nov 01/08
C F M 56-5B
Removal and Installation of the Fan Outlet Guide Vane Doublets Figure 401/TASK 72-23-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 403 Nov 01/08
C F M 56-5B (4) Lower the OGV doublet (10) inner platform down into the OGV inner shroud. (5) Move the OGV doublet (10) outer platform rearward at the necessary angle to disengage the inner platform from its recess. (6) Remove the OGV doublet (10). (7) Remove the sealant which remains on the acoustical panels.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 404 Nov 01/08
C F M 56-5B TASK 72-23-00-400-008 Installation of the Fan Outlet Guide Vane (OGV) Doublets 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2242
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * RTV 732 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-400-026 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Installation of the Aft Acoustical Panels Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 405 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------SPM 706612 72-23-00-991-300
Fig. 401
3. __________ Job Set-up Subtask 72-23-00-860-058 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-23-00-010-093 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-040-065 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 406 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 401/TASK 72-23-00-991-300) Subtask 72-23-00-420-059 A. Installation of the Fan Outlet Guide Vane (OGV) Doublets (Rearward) (1) Engage the OGV inner platform into the OGV inner shroud recess. (2) Push the OGV outer platform forward between the adjacent OGV doublets and up against the inner diameter of the fan case. (3) Apply a thin layer of graphite grease (Material No. CP2101) to the threads of the three bolts (20) and (30), and attach the OGV doublet with the 3 bolts. NOTE : You must install the longer bolt (20) to the aft end of the ____ OGV outer platform. (4) TORQUE the bolts to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). (5) Apply RTV 732 (Material No. CP2242) all around the OGV(s) outer(s) platform(s) recesses. (6) Fill the sealant per (Ref. SPM 706612) to smooth the fan duct outer wall. (7) Install the aft acoustical panels (Ref. TASK 72-23-00-400-026). 5. Close-up ________ Subtask 72-23-00-410-077 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 407 Nov 01/08
C F M 56-5B Subtask 72-23-00-440-058 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-087 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 408 Nov 01/08
C F M 56-5B TASK 72-23-00-000-009 Removal of the Forward Acoustical Panels of the Fan 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-991-301
Fig. 402
3. __________ Job Set-up Subtask 72-23-00-941-072 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 409 Nov 01/08
C F M 56-5B (4) Put a warning notice to tell persons not to start the engine 1(2). (5) Put an access platform in position at the front of the engine. 4. Procedure _________ (Ref. Fig. 402/TASK 72-23-00-991-301) Subtask 72-23-00-020-060 A. Remove the fan forward acoustical panels (70) as follows: CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO UNTORQUE AND LOOSEN ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. (1) Remove the screws (80) which attach the forward panel (70) located in fan case. NOTE : If one screw is found untorqued, it must be discarded and ____ replaced for re-installation. (2) Disengage and remove the panel (70) from the case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 410 Nov 01/08
C F M 56-5B
Fan Forward Acoustical Panel Figure 402/TASK 72-23-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 411 Nov 01/08
C F M 56-5B TASK 72-23-00-400-009 Installation of the Forward Acoustical Panels of the Fan 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-280-005 72-23-00-300-045 72-23-00-400-043 72-23-00-400-044
Inspection of Forward Acoustical Panels Replacement of the Riveted Self Locking Nuts for the Attachment of the Forward Acoustical Panels Installation of Acoustical Panels Attachment Screw/Nut Locking Installation of Acoustical Panels Attachment Screw Locking
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 412 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-860-061 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. 4. Procedure _________ Subtask 72-23-00-420-060 A. Install the fan forward acoustical panels as follows: CAUTION : MAKE SURE THAT THE PS12 INSTRUMENTATION NIPPLE WHICH COMES OUT _______ OF THE FAN INLET CASE IS CORRECTLY ENGAGED IN THE PANEL. CAUTION : COATING SCREWS IS MANDATORY. _______ (1) Apply a layer of graphite grease (Material No. CP2101) to the threads of all the screws that attach the acoustical panels and to the contact faces below the screw heads. (2) Do a visual inspection of the forward acoustical panel cup (Ref. TASK 72-23-00-280-005) (3) If panel cup is found pierced (Ref. TASK 72-23-00-400-044). (4) Install the panel assy on the forward case, and attach it with 6 screws (80). CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO TORQUE ALL ACOUSTICAL _______ PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 413 Nov 01/08
C F M 56-5B (5) Measure the self locking nut torque of each nut when you start to tighten the screw. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO TORQUE ALL ACOUSTICAL _______ PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : Whenever possible, start the torque with the screws in the ____ center of the acoustical panels. NOTE : Make sure that the screws are not damaged, replace them if ____ necessary. (a) If the self locking nut torque is less than 4.5 lbf.in (0.05 m.daN), (Ref. TASK 72-23-00-400-043). (b) If the self locking nut torque is more than 4.5 lbf.in (0.05 m.daN), but less than 31 lbf.in (0.35 m.daN), TORQUE the screws to between 84 and 93 lbf.in (0.94 and 1.05 m.daN). R R R
(c) If the self locking nut torque is more than 31 lbf.in (0.35 m.daN) replace the self locking nut (Ref. TASK 72-23-00-300-045). 5. Close-up ________ Subtask 72-23-00-410-090 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 414 Feb 01/09
C F M 56-5B TASK 72-23-00-000-025 Removal of the Mid Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-23-00-991-302
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Fig. 403
3. __________ Job Set-up Subtask 72-23-00-941-073 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 415 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-084 B. Get Access (1) Put an access platform in position at the front of the engine. (2) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (3) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (4) Temporarily mark each fan blade from 1 to 36. (5) Remove 3 consecutive fan blades (Ref. TASK 72-21-00-000-007). To compensate for imbalance caused by the removal of 3 blades, it is recommended to remove 3 blades 180 degrees opposed to those previously removed. 4. Procedure _________ (Ref. Fig. 403/TASK 72-23-00-991-302) Subtask 72-23-00-020-061 A. Remove the Mid Acoustical Panels as follows: CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO UNTORQUE AND LOOSEN ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. (1) Remove the short screws (100) and the long screws (101) which attach the mid acoustical panels (110). NOTE : If one screw is found untorqued, it must be discarded and ____ replaced for re-installation. (2) Disengage panels from case and remove.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 416 Nov 01/08
C F M 56-5B
Mid Acoustical Panel Figure 403/TASK 72-23-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 417 Nov 01/08
C F M 56-5B TASK 72-23-00-400-025 Installation of the Mid Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-23-00-280-006 72-23-00-400-043 72-23-00-400-044 ESM 722302300008 72-23-00-991-302
Removal of the Power Plant Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Inspection of Mid Acoustical Panels Installation of Acoustical Panels Attachment Screw/Nut Locking Installation of Acoustical Panels Attachment Screw Locking Fig. 403
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 418 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-860-062 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. 4. Procedure _________ (Ref. Fig. 403/TASK 72-23-00-991-302) Subtask 72-23-00-420-061 A. Install the Mid Acoustical Panels as follows: CAUTION : COATING SCREWS IS MANDATORY. _______ (1) Coat with graphite grease (Material No. CP2101) screw threads and contact faces under screw heads. (2) Do a visual inspection of the mid acoustical panel cup (Ref. TASK 7223-00-280-006). (3) If panel cup is found pierced (Ref. TASK 72-23-00-400-044). (4) Install the panel assy on the forward case, and attach it with 3 short screws (100) and 3 long screws (101). CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : The longest screws have to be re-installed at the aft end of ____ panel.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 419 Nov 01/08
C F M 56-5B (5) Measure the self locking nut torque of each nut when you start to tighten the screw. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO TORQUE ALL ACOUSTICAL _______ PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : Whenever possible, start to torque with the screws in the ____ center of the acoustical panels. NOTE : Make sure that the screws are not damaged, replace them if ____ necessary. (a) If the self locking nut torque is less than 4.5 lbf.in (0.05 m.daN), (Ref. TASK 72-23-00-400-043). (b) If the self locking nut torque is within 4.5 lbf.in (0.05 m.daN) and 31 lbf.in (0.35 m.daN), torque the screws to between 84 and 93 lbf.in (0.94 and 1.05 m.daN) (c) If the self locking nut torque is more than 31 lbf.in (0.35 m.daN) but less than 49 lbf.in (0.55 m.daN), torque the screws at the running torque value and add 44 lbf.in (0.5 m.daN). (d) If the self locking torque is more than 49 lbf.in (0.55 m.daN), remove the engine (Ref. TASK 71-00-00-000-042) and do the engine shop repair procedure to replace the self locking nut (Ref. ESM 722302300008). 5. Close-up ________ Subtask 72-23-00-410-078 A. Close Access (1) Install the fan rotor blades at the locations recorded at the removal (Ref. TASK 72-21-00-400-007). (2) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (3) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (4) Make sure that the work area is clean and clear of tool(s) and other items. (5) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 420 Nov 01/08
C F M 56-5B (6) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 421 Nov 01/08
C F M 56-5B TASK 72-23-00-000-026 Removal of the Aft Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 78-30-00-481-041 78-36-00-010-040 72-23-00-991-303
Opening of the Fan Cowl Doors Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Fig. 404
3. __________ Job Set-up Subtask 72-23-00-941-074 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 422 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-085 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-23-00-040-062 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-095 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 404/TASK 72-23-00-991-303) Subtask 72-23-00-020-062 A. Remove the Aft Acoustical Panels as follows (typical, any panel): CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO UNTORQUE AND LOOSEN ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 423 Nov 01/08
C F M 56-5B
Aft Acoustical Panel (Configuration 1 and Configuration 2) Figure 404/TASK 72-23-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 424 Nov 01/08
C F M 56-5B (1) Remove the screws (130) that attach the aft acoustical panel (140). NOTE : If one screw is found untorqued, it must be discarded and ____ replaced for re-installation. PRE SB 72-071 (Configuration One) (2) Disengage panel (140) from case and T/R adapter ring. Remove the panel (140) which comes with its two lateral bonded seals. POST SB 72-071 (Conguration Two) (3) Disengage panel (140) from case and T/R adapter ring. Remove the panel (140). This panel will come without its U-shaped seal (145). Let the seal (145) squeezed between the two struts and adjacent aft acoustical panels that frame the panel you remove. Remove the seal (145) and thus, the two adjacent panels, only if this seal is badly damaged.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 425 Nov 01/08
C F M 56-5B TASK 72-23-00-400-026 Installation of the Aft Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-13-00-010-040 71-13-00-410-040 72-23-00-210-004 72-23-00-280-007 72-23-00-400-043 72-23-00-400-044 78-30-00-081-041
Removal of the Power Plant Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Visual Inspection of the Fan Frame Assembly Inspection of Aft Acoustical Panels Installation of Acoustical Panels Attachment Screw/Nut Locking Installation of Acoustical Panels Attachment Screw Locking Make the Thrust Reverser Serviceable after Maintenance
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 426 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 ESM 722302300008 72-23-00-991-303
Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 404
3. __________ Job Set-up Subtask 72-23-00-860-059 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-23-00-010-099 B. Get Access (1) Make sure that the fan cowl doors are open (Ref. TASK 71-13-00-010040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Make sure that the thrust reverser doors are open (Ref. TASK 78-3600-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 427 Nov 01/08
C F M 56-5B Subtask 72-23-00-040-068 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041). 4. Procedure _________ (Ref. Fig. 404/TASK 72-23-00-991-303) Subtask 72-23-00-420-062 A. Install the Aft Acoustical Panels as follows (typical, any panel): CAUTION : COATING SCREWS IS MANDATORY. _______ NOTE : The 12 aft acoustical panels are attached both to the fan inlet ____ case and to the T/R adapter ring, at their aft end. (1) Apply a layer of graphite grease (Material No. CP2101) to the threads of all the screws that attach the acoustical panels and to contact faces below the screw heads. PRE SB 72-071 (2) Visually inspect the aft acoustical panel cup (Ref. TASK 72-23-00280-007). (3) If panel cup is found pierced (Ref. TASK 72-23-00-400-044). (4) Install the panel assy on the forward case, an attach it with seven screws (130). (5) Before the installation, do a visual inspection of the panel (140) (Ref. TASK 72-23-00-210-004). Make sure that the two lateral bonded seals are in position. Although it is not at this time mandatory to obey the inspection criterion related to these bonded seals, we recommended they are in position, in good condition and fully bonded to the panel. (6) Put the panel (140), with its two bonded seals, on the fan case and the T/R adapter ring. Attach it loosely with the seven screws (130). CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 428 Nov 01/08
C F M 56-5B NOTE : You must install the 3 longest screws (130) at the aft of the ____ panel. (7) Measure the self locking nut torque of each nut when you start to tighten the screw. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : Whenever possible, start to torque with the screws in the ____ center ot the acoustical panels. NOTE : Make sure that the screws are not damaged, replace them if ____ necessary. (a) If the self locking nut torque is less than 4.5 lbf.in (0.05 m.daN) (Ref. TASK 72-23-00-400-043). (b) If the self locking nut torque is within 4.5 lbf.in (0.05 m.daN) and 31 lbf (0.35 m.daN), TORQUE the screws to between 66 and 75 lbf.in (0.74 and 0.84 m.daN). (c) If the self locking nut torque is more than 31 lbf.in (0.35 m.daN) but less than 49 lbf.in (0.55 m.daN), TORQUE the screws at the running torque value and add 44 lbf.in (0.5 m.daN). (d) If the self locking torque is more than 49 lbf.in (0.55 m.daN), remove the engine (Ref. TASK 71-00-00-000-042) and do the engine shop repair procedure to replace the self locking nut (Ref. ESM 722302300008). END OF SB 72-071 POST SB 72-071 (8) Before the installation, do a visual inspection of the panel (140) (Ref. TASK 72-23-00-210-004). Make sure that the two U-shaped seals (145) that are in stand-by on the two (non-removed and adjacent) fan aft acoustical panels are in good condition. If not, remove the panel(s) which hold the damaged seal(s) and install a new seal. See note below. NOTE : Refer to the PPIPC (72-23-00) when it is necessary to replace ____ a seal (145). Because of the different strut sizes and clock positions, the seals (145) do not all have the same pre-formed shapes and can thus have different part numbers.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 429 Nov 01/08
C F M 56-5B (9) Put the panel (140) in its approximate position on the fan case and the T/R adapter ring. Engage one seal (145) first, against one of the panel edges, then engage the other seal (145) against the opposite panel edge. Make sure that the seals (145) are correctly compressed between the panel and the adjacent struts around the panel. NOTE : It is not easy to get access to some (panel) clock locations. ____ External aid will possibly be necessary to install the seal (145) correctly between the panel and the related struss. (10) Push and hold the panel (140) against the fan case and attach it loosely with the seven srews (130). CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : You must install the 3 longest screws (130) at the aft of the ____ panel. (11) Measure the self locking nut torque of each nut when you start to tighten the screw. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : When possible, start the torque with the screws in the center ____ of the acoustical panels. NOTE : Make sure that the screws are not damaged, replace them if ____ necessary. (a) If the self locking nut torque is less than 4.5 lbf.in (0.05 m.daN) (Ref. TASK 72-23-00-400-043). (b) If the self locking nut torque is within 4.5 lbf.in (0.05 m.daN) and 31 lbf (0.35 m.daN), TORQUE the screws to between 66 and 75 lbf.in (0.74 and 0.84 m.daN) (c) If the self locking nut torque is more than 31 lbf.in (0.35 m.daN) but less than 49 lbf.in (0.55 m.daN), TORQUE the screws at the running torque value and add 44 lbf.in (0.5 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 430 Nov 01/08
C F M 56-5B (d) If the self locking torque is more than 49 lbf.in (0.55 m.daN), remove the engine (Ref. TASK 71-00-00-000-042) and do the engine shop repair procedure to replace the self locking nut (Ref. ESM 722302300008). END OF SB 72-071 5. Close-up ________ Subtask 72-23-00-410-079 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-059 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-088 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 431 Nov 01/08
C F M 56-5B TASK 72-23-00-000-027 Removal of the Fan Duct Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 78-30-00-481-041 78-36-00-010-040 72-23-00-991-305
Opening of the Fan Cowl Doors Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Fig. 405
3. __________ Job Set-up Subtask 72-23-00-941-075 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 432 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-086 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-23-00-040-063 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-096 D. Open the thrust reverser cowl doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 405/TASK 72-23-00-991-305) Subtask 72-23-00-020-063 A. Removal of the fan duct panels. CAUTION : DURING REMOVAL OF FAN DUCT PANELS, DO NOT FULLY REMOVE CAPTIVE _______ SCREWS FROM PANEL. THESE SCREWS ARE HELD IN PLACE BY A RETAINING BUSHING ON THE BACK SIDE OF THE PANELS WHICH MAY FALL INTO THE VBV CAVITY IF SCREWS ARE FULLY REMOVED. AFTER REMOVAL OF EACH PANEL, IT MUST BE VERIFIED THAT BUSHINGS ARE STILL WITH PANEL AND NOT IN VBV CAVITY.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 433 Nov 01/08
C F M 56-5B
Fan Duct Panel Figure 405/TASK 72-23-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 434 Nov 01/08
C F M 56-5B (1) Loosen the captive screws (150), and remove the panel (160). (2) Unscrew and remove the retaining bushings (170) from the screws (150). (3) Remove the washers (180) from the screws (150).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 435 Nov 01/08
C F M 56-5B TASK 72-23-00-400-027 Installation of the Fan Duct Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 436 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-23-00-991-305
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 405
3. __________ Job Set-up Subtask 72-23-00-860-060 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-23-00-010-100 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 437 Nov 01/08
C F M 56-5B (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-040-069 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041). 4. Procedure _________ (Ref. Fig. 405/TASK 72-23-00-991-305) Subtask 72-23-00-420-063 A. Installation of the fan duct panels. (1) Clean the fan frame cavity and the fan duct panels with acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or magchem skysol (Material No. CP2656) at the RTV contact area between the fan frame /fan duct panel. (2) Install the captive screw (150) the washers (180) and the retaining bushings (170) on the fan duct panel (160). (3) Apply a thin layer of graphite grease (Material No. CP2101) to the threads of the screws (150), and install the new panel (160). (4) Install the panel on the bleed valve cavity and attach it with captive screws. (5) TORQUE screws to between 85 and 95 lbf.in (0.96 and 1.07 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 438 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-080 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser door: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-060 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-089 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 439 Nov 01/08
C F M 56-5B TASK 72-23-00-000-028 Removal of the Splitter Fairing 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific 856A2663
rubber mat slide hammer warning notice access platform 1 m (3 ft. 3 in.) 1 ADAPTER, PULLER - SPLITTER FAIRING
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-23-00-991-306 72-23-00-991-307
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Fig. 406 Fig. 407
3. __________ Job Set-up Subtask 72-23-00-941-076 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 440 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put an access platform in position. Subtask 72-23-00-010-087 B. Removal of the Spinner Cone, the Spinner Rear Cone and the Fan Blades. (1) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (2) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (3) Remove the fan blades (Ref. TASK 72-21-00-000-007). 4. Procedure _________ (Ref. Fig. 406/TASK 72-23-00-991-306, 407/TASK 72-23-00-991-307) Subtask 72-23-00-020-064 A. Removal of the Splitter Fairing. CAUTION : INSTALL A RUBBER MAT IN THE FAN INLET CASE TO PREVENT DAMAGE TO _______ THE ACOUSTICAL PANELS. (1) Install a rubber mat in the fan inlet case. (2) Remove the countersunk head screws (20) which attach the splitter fairing (10) to the inner shroud of the fan outlet guide vane (OGV) assembly. (3) Pull out the splitter fairing (10) with a slide hammer (856A2663G01) attached to the ADAPTER, PULLER - SPLITTER FAIRING. (Ref. Fig. 407/TASK 72-23-00-991-307) alternatively positioned in each splitter fairing extraction slot. Remove the splitter fairing (10). (4) Remove the rubber mat from the fan inlet case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 441 Nov 01/08
C F M 56-5B
Splitter Fairing Figure 406/TASK 72-23-00-991-306 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 442 Nov 01/08
C F M 56-5B
Removal of the Splitter Fairing Figure 407/TASK 72-23-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 443 Nov 01/08
C F M 56-5B TASK 72-23-00-400-028 Installation of the Splitter Fairing 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No
specific specific specific specific specific
heat gun rubber mat warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 444 Feb 01/10
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-23-00-991-306
Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Fig. 406
3. __________ Job Set-up Subtask 72-23-00-860-063 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. 4. Procedure _________ (Ref. Fig. 406/TASK 72-23-00-991-306) Subtask 72-23-00-420-064 A. Installation of the splitter fairing CAUTION : INSTALL A RUBBER MAT IN THE FAN INLET CASE TO PREVENT DAMAGE TO _______ THE ACOUSTICAL PANELS. (1) Install a rubber mat in the fan inlet case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 445 Nov 01/08
C F M 56-5B (2) Clean the mating surfaces: WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL _______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. (a) Fully clean the mating surfaces of the splitter fairing front flange with acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99R (Material No. CP2584) or mag-chem skysol (Material No. CP2656). (3) Put the splitter fairing (10) on the inner shroud of the fan outlet guide vane (OGV) assembly and on the outer shroud of the stage 1 vane assembly. (4) Heat the front flange of the splitter fairing with a heat gun to approximately 140 deg.F (60 deg.C) until it can be fully engaged in the OGV inner shroud rabbet diameter. (5) Lubricate the threads of the countersunk head screws (20) with graphite grease (Material No. CP2101). (6) Install screws (20). TORQUE to between 40 and 45 lbf.in (0.45 and 0.50 m.daN). (7) Remove the rubber mat from the fan inlet case. 5. Close-up ________ Subtask 72-23-00-410-081 A. Close Access (1) Installation of the Fan Blades, the Spinner Rear Cone and the Spinner Front Cone. (2) Install the fan rotor blades (Ref. TASK 72-21-00-400-007). (3) Install the spinner rear cone (Ref. TASK 72-21-00-400-006).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 446 Nov 01/08
C F M 56-5B (4) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (5) Make sure that the work area is clean and clear of tool(s) and other items. (6) Remove the access platform(s). (7) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 447 Nov 01/08
C F M 56-5B TASK 72-23-00-000-029 Removal of the PS13 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1.5 m (4 ft. 11 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-23-00-991-315
Opening of the Fan Cowl Doors Fig. 408
3. __________ Job Set-up Subtask 72-23-00-941-086 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 448 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-103 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. 4. Procedure _________ (Ref. Fig. 408/TASK 72-23-00-991-315) Subtask 72-23-00-020-065 A. Removal of the PS13 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Cut and remove the lockwire. (2) Disconnect the PS13 line from the PS13 boss on the fan frame. (3) Cut and remove the lockwire. (4) Disconnect the PS13 line from the ECU.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 449 Nov 01/08
C F M 56-5B
Removal/Installation of the PS13 Line Figure 408/TASK 72-23-00-991-315- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 450 Nov 01/08
C F M 56-5B
Removal/Installation of the PS13 Line Figure 408/TASK 72-23-00-991-315- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 451 Nov 01/08
C F M 56-5B (5) Remove the parts which attach the PS13 line to the fan frame as follows: R R R R R R R R R R R R R R R R R R R R R R R R R
------------------------------------------------------------------------------| REMOVE | FROM | NOTE | ------------------------------------------------------------------------------| Nut (10) | Bracket (20) on flange F | At the 4:45 oclock | | Bolt (40) | | position (Detail B) | ------------------------------------------------------------------------------| Nut (80) | Bracket (60) on flange F | At the 4:30 oclock | | Bolt (50) | | position (Detail C) | | Clamp (70) | | | ------------------------------------------------------------------------------| Nut (120) | Bracket (110) on flange F | At the 4 oclock | | Bolt (90) | | position (Detail D) | | Clamp (100) | | | ------------------------------------------------------------------------------| Nut (140) | Bracket (150) on flange F | At the 3:45 oclock | | Bolt (130) | | position (Detail E) | | Clamp (160) | | | ------------------------------------------------------------------------------| Nuts (200) | Brackets (180) on flange G | At the 3 oclock, | | Bolts (170) | | 2 oclock and 1:30 oclock | | Clamps (190) | | positions (3 locations) | | | | (Detail F) | ------------------------------------------------------------------------------| Nut (240) | Bracket (220) on flange G | At the 2:30 oclock | | Bolt (210) | | position (Detail G) | | Clamp (230) | | | -------------------------------------------------------------------------------
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 452 Nov 01/08
C F M 56-5B TASK 72-23-00-400-029 Installation of the PS13 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1.5 m (4 ft. 11 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-991-315
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Fig. 408
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 453 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-860-064 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-23-00-010-105 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 408/TASK 72-23-00-991-315) Subtask 72-23-00-420-065 A. Installation of the PS13 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Lubricate the ECU and the fan frame boss nipples with engine fuel. (2) Connect the PS13 line to the ECU and to the fan frame boss by hand. (3) Lubricate the threads of the bolts (40), (50), (90), (130), (170), (210) with graphite grease (Material No. CP2101).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 454 Nov 01/08
C F M 56-5B (4) Install the parts which attach the PS13 line as follows: R R R R R R R R R R R R R R R R R R R R R R R R R
------------------------------------------------------------------------------| INSTALL | ON | NOTE | ------------------------------------------------------------------------------| Nut (10) | Bracket (20) on flange F | At the 4:45 oclock | | Bolt (40) | | position (Detail B) | ------------------------------------------------------------------------------| Nut (80) | Bracket (60) on flange F | At the 4:30 oclock | | Bolt (50) | | position (Detail C) | | Clamp (70) | | | ------------------------------------------------------------------------------| Nut (120) | Bracket (110) on flange F | At the 4 oclock | | Bolt (90) | | position (Detail D) | | Clamp (100) | | | ------------------------------------------------------------------------------| Nut (140) | Bracket (150) on flange F | At the 3:45 oclock | | Bolt (130) | | position (Detail E) | | Clamp (160) | | | ------------------------------------------------------------------------------| Nuts (200) | Brackets (180) on flange G | At the 3 oclock, | | Bolts (170) | | 2 oclock and 1:30 oclock | | Clamps (190) | | positions (3 locations) | | | | (Detail F) | ------------------------------------------------------------------------------| Nut (240) | Bracket (220) on flange G | At the 2:30 oclock | | Bolt (210) | | position (Detail G) | | Clamp (230) | | | ------------------------------------------------------------------------------(5) TORQUE the PS13 connection to the ECU to between 180 and 200 lbf.in (2.03 and 2.26 m.daN). (6) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (7) TORQUE the PS13 connection to the fan frame boss to between 135 and 150 lbf.in (1.52 and 1.69 m.daN). (8) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 455 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-095 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s). (4) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 456 Nov 01/08
C F M 56-5B TASK 72-23-00-000-040 Removal of the PS12 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1.5 m (4 ft. 11 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-23-00-991-316
Opening of the Fan Cowl Doors Fig. 409
3. __________ Job Set-up Subtask 72-23-00-941-083 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 457 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-106 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. 4. Procedure _________ (Ref. Fig. 409/TASK 72-23-00-991-316) Subtask 72-23-00-020-066 A. Removal of the PS12 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Cut and remove the lockwire. (2) Disconnect the PS12 line from the ECU. (3) Cut and remove the lockwires. (4) Disconnect the PS12 line from the 3 fan frame bosses.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 458 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-23-00 CES
Page 459 Feb 01/09
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 16 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 460 Nov 01/08
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 26 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 461 Nov 01/08
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 36 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 462 Nov 01/08
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 46 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 463 Nov 01/08
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 56 (SHEET 5) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 464 Nov 01/08
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 66 (SHEET 6) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 465 Nov 01/08
C F M 56-5B (5) Remove the parts which attach the PS12 Line as follows: ------------------------------------------------------------------------------| REMOVE | FROM | NOTE | ------------------------------------------------------------------------------| Nut (30) | Bracket (40) on flange G | At the 5 oclock | | Bolt (10) | | position (Detail C) | ------------------------------------------------------------------------------| Nut (70) | Bracket (80) on flange E | At the 4:45 oclock | | Bolt (50) | | position (Detail D) | | Clamp (60) | | | ------------------------------------------------------------------------------| Nut (110) | Bracket (120) on flange C | At the 4:30 oclock | | Bolt (90) | | position (Detail E) | | Clamp (100) | | | ------------------------------------------------------------------------------| Nut (150) | Bracket (140) on flange C | At the 4 oclock | | Bolt (130) | | position (Detail F) | ------------------------------------------------------------------------------| Nuts (180) | Brackets (170) on flange C | From the 3:30 oclock | | Bolts (190) | | to the 1:45 Oclock | | Clamps (160) | | positions (Detail G) | | | | (5 locations) | ------------------------------------------------------------------------------| Nut (230) | Bracket (220) on flange C | From the 1 oclock | | Bolt (200) | | to the 8:15 oclock | | Clamp (210) | | positions (Detail H) | | | | (12 locations) | ------------------------------------------------------------------------------| Nut (260) | Bracket (250) on flange C | At the 11:45 oclock | | Bolt (240) | | position (Detail J) | ------------------------------------------------------------------------------| Nut (290) | Bracket (280) on flange C | At the 8 oclock | | Bolt (270) | | position (Detail K) | ------------------------------------------------------------------------------(6) remove the PS12 line (20) from the Engine.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 466 Feb 01/09
C F M 56-5B TASK 72-23-00-400-040 Installation of the PS12 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1.5 m (4 ft. 11 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-991-316
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Fig. 409
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 467 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-860-065 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-23-00-010-104 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 409/TASK 72-23-00-991-316) Subtask 72-23-00-420-066 A. Installation of the PS12 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Install the PS12 line (20) in position on the engine. (2) Lubricate the threads of the fan frame bosses and ECU nipples with engine fuel. (3) Connect the PS12 line to the 3 fan frame bosses and to the ECU. (4) Tighten the connecting nuts by hand.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 468 Feb 01/09
C F M 56-5B (5) Lubricate the threads of the bolts with graphite grease (Material No. CP2101). (6) Install the parts which attach the PS12 line as follows: ------------------------------------------------------------------------------| INSTALL | ON | NOTE | ------------------------------------------------------------------------------| Bolt (10) | Bracket (40) on flange G | At the 5 oclock | | Nut (30) | | position (Detail C) | ------------------------------------------------------------------------------| Clamp (60) | Bracket (80) on flange E | At the 4:45 oclock | | Bolt (50) | | position (Detail D) | | Nut (70) | | | ------------------------------------------------------------------------------| Clamp (100) | Bracket (120) on flange C | At the 4:30 oclock | | Bolt (90) | | position (Detail D) | | Nut (110) | | | ------------------------------------------------------------------------------| Bolt (130) | Bracket (140) on flange C | At the 4 oclock | | Nut (150) | | position (Detail F) | ------------------------------------------------------------------------------| Clamps (160) | Brackets (170) on flange C | From the 3:30 oclock | | Bolts (190) | | to the 1:45 oclock | | Nuts (180) | | positions (Detail G) | | | | (5 locations) | ------------------------------------------------------------------------------| Clamps (210) | Bracket (220) on flange C | From the 1 oclock | | Bolts (200) | | to the 8:15 oclock | | Nuts (230) | | positions (Detail H) | | | | (12 locations) | ------------------------------------------------------------------------------| Bolt (240) | Bracket (250) on flange C | At the 11:45 oclock | | Nut (260) | | position (Detail J) | ------------------------------------------------------------------------------| Bolt (270) | Bracket (280) on flange C | At the 8 oclock | | Nut (290) | | position (Detail K) | ------------------------------------------------------------------------------(7) Distribute the slack all along the line. (8) TORQUE the nuts (30), (70), (110), (150), (180), (230), (260), (290) to to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (9) TORQUE the fan frame bosses and ECU connections to to between 135 and 150 lbf.in (1.52 and 1.69 m.daN).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 469 Feb 01/09
C F M 56-5B (10) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). NOTE : The PS3 and the PS12 connecting nuts are safetied together. ____ 5. Close-up ________ Subtask 72-23-00-410-096 A. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s). Remove the access platform(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 470 Feb 01/09
C F M 56-5B TASK 72-23-00-400-043 Installation of Acoustical Panels Attachment Screw/Nut Locking 1. __________________ Reason for the Job This procedure gives task to lock acoustical panel screws when the corresponding self locking nut torque is smaller than the AMM limits. This procedure applies to any acoustical panel screws: fwd, mid and aft. Any screws and corresponding riveted self locking nuts locked per this procedure will have to be changed at first shop visit opportunity. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2242
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-A-46106A RTV (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 471 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2656
* mag-chem skysol (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-23-00-941-093 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 472 Feb 01/09
C F M 56-5B Subtask 72-23-00-010-116 B. Get Access (1) Open the fan cowls: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-23-00-040-071 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-117 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-23-00-420-069 A. Locking of Acoustical Panels. (1) Remove the screws if the torque of the related self locking nut is less than the AMM limits. (2) Clean the screws and the nuts with acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or magchem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041). (3) Apply RTV (Material No. CP2242) or equivalent on screw threads and below the screw heads. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH AND TORQUE _______ ALL ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 473 Feb 01/09
C F M 56-5B (4) Re-install the acoustical panels and screws. (a) TORQUE the screws of the forward and mid panels to between 84 and 93 lbf.in (0.94 and 1.05 m.daN) (b) TORQUE the screws of the aft panels to between 66 and 75 lbf.in (0.74 and 0.84 m.daN). 5. Close-up ________ Subtask 72-23-00-410-107 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-065 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041) Subtask 72-23-00-410-108 C. Close Access (1) Close the fan cowls: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 474 Feb 01/09
C F M 56-5B TASK 72-23-00-400-044 Installation of Acoustical Panels Attachment Screw Locking 1. __________________ Reason for the Job This procedure tells you how to lock acoustical panel screws when the panel cup examined has a hole caused by the screw head. This procedure applies to all acoustical panel screws: fwd, mid and aft. It is necessary to replace panels with damaged cups re-installed by this procedure at the subsequent shop visit. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2242
Material No.
CP2266
Material No.
CP2431
USA MIL-T-5544 graphite grease (Ref. 70-30-00) USA MIL-A-4610A RTV 732 (Ref. 70-30-00) * RTV 102 (Ref. 70-30-00) * RTV 730 (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 475 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-13-00-010-040 71-13-00-410-040 72-23-00-300-045 72-23-00-400-043 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 ESM 722302300008 SPM 702111
Removal of the Power Plant Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Replacement of the Riveted Self Locking Nuts for the Attachment of the Forward Acoustical Panels Installation of Acoustical Panels Attachment Screw/Nut Locking Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-23-00-941-094 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 476 Feb 01/09
C F M 56-5B Subtask 72-23-00-010-118 B. Get Access (1) Open the fan cowls: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-23-00-040-072 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-119 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-23-00-420-070 A. Locking of Acoustical Panels CAUTION : COATING SCREWS IS MANDATORY. _______ (1) If panel cup(s) found pierced, do the procedure that follows: WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL _______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. (a) Remove the bolt. (b) Clean all damaged cups (Ref. SPM 702111).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 477 Feb 01/09
C F M 56-5B (c) Fill all damaged cups with RTV 732 (Material No. CP2242) or RTV 102 (Material No. CP2266) or RTV 730 (Material No. CP2431) NOTE : You must install the screw, with only a light layer of ____ graphite grease (Material No. CP2101), a short time after you apply the RTV (before polymerisation). (2) Apply a layer of graphite grease (Material No. CP2101) to the threads of all the screws that attach the acoustical panels. (3) Re-install the acoustical panels and screws. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. (4) Measure the self locking nut torque of each nut when you start to tighten the screw. NOTE : Make sure that the screws are not damaged, replace them if ____ necessary. (a) If the self locking nut torque is less than 4.5 lbf.in (0.05 m.daN), (Ref. TASK 72-23-00-400-043). (b) If the self locking nut torque is more than 4.5 lbf.in (0.05 m.daN), but less than 31 lbf.in (0.35 m.daN), TORQUE the screws of fwd and mid panels to between 84 and 93 lbf.in (0.94 and 1.05 m.daN) and TORQUE screws of the aft panels to between 66 and 75 lbf.in (0.74 and 0.84 m.daN). (c) If the self locking nut torque is more than 31 lbf.in (0.35 m.daN), but less than 49 lbf.in (0.55 m.daN), TORQUE screws at the running torque value and add 44 lbf.in (0.5 m.daN). (d) If the self locking nut torque is more than 49 lbf.in (0.55 m.daN): - replace the self locking nut of the fwd panels (Ref. TASK 7223-00-300-045). - remove the engine (Ref. TASK 71-00-00-000-042) and do the engine shop repair procedure (Ref. ESM 722302300008) to replace the self locking of the mid and aft panels.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 478 Feb 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-109 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-066 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041) Subtask 72-23-00-410-110 C. Close Access (1) Close the fan cowls: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 479 Feb 01/09
C F M 56-5B FAN FRAME ASSEMBLY - INSPECTION/CHECK _____________________________________ TASK 72-23-00-210-004 Visual Inspection of the Fan Frame Assembly CAUTION : TITANIUM PARTS REQUIRE THE USE OF NON-HALOGENATED SOLVENTS. _______ 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-21-00-320-003 72-23-00-000-027 72-23-00-000-028 72-23-00-280-005 72-23-00-280-006 72-23-00-280-007 72-23-00-300-042 72-23-00-350-002 72-23-00-400-027 72-23-00-400-028 78-30-00-081-041 78-30-00-481-041
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Blending of Fan Rotor Blades Removal of the Fan Duct Panels Removal of the Splitter Fairing Inspection of Forward Acoustical Panels Inspection of Mid Acoustical Panels Inspection of Aft Acoustical Panels Repair of Fan Duct Panel Removal of Rust from the Fan Frame Casing Installation of the Fan Duct Panels Installation of the Splitter Fairing Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-36-00-010-040 78-36-00-410-040 72-23-00-991-308 72-23-00-991-309 72-23-00-991-328 72-23-00-991-326
Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603 Fig. 604
3. __________ Job Set-up Subtask 72-23-00-941-077 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-088 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-23-00-040-066 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 602 Aug 01/09
C F M 56-5B Subtask 72-23-00-010-101 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-23-00-991-308, 602/TASK 72-23-00-991-309) Subtask 72-23-00-210-057 A. Visual inspection of the fan Frame Assembly ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fan frame casing for: (Ref. Fig. 601/TASK 72-23-00-991-308) A. Cracks
No limits in quantity if 0.08 in. (2,03 mm) max. length and a minimum of 1 in. (25,40 mm) apart.
B. Dents or nicks on struts
No limits in quantity if, 0.08 in. (2.03 mm) max. depth
C. Corrosion (discoloration)
No limits in quantity
D. Scaling or pitting
Not serviceable
At the first opportunity remove rust (Ref. TASK 7223-00-350-002)
2. Inlet case on B1 and B3 upstream bracket location for: (Ref. Fig. 601/TASK 72-23-00-991-308)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check Figure 601/TASK 72-23-00-991-308- 15 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check Figure 601/TASK 72-23-00-991-308- 25 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check Figure 601/TASK 72-23-00-991-308- 35 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check Figure 601/TASK 72-23-00-991-308- 45 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check Figure 601/TASK 72-23-00-991-308- 55 (SHEET 5) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B
Fan Duct Panels Figure 602/TASK 72-23-00-991-309 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Wear of flanges Two expanded adjacent Remove the inlet case. holes oversized holes are permitted if: - Each expanded hole is not more than 0.315 in. (8 mm) width and not more than 0.6 in. (15 mm) long. - 5 holes minimum in good condition are on both sides of expanded holes. B. Wear, fretting, chafing of flange holes.
If 0.008 in. (0,20 mm) max. depth or If 0.02 in. (0,5 mm) max. depth and 0.155 sq.in. (100 sq.mm) max. surface.
10 cycles serviceable extension is allowed.
C. Wear, fretting, chafing on the top of flange holes.
If 0.02 in. (0,5 mm) max. width and 0.8 in. (20 mm) max. length.
10 cycles serviceable extension is allowed.
D. Washer impression around flange holes
If 0.032 in. (0,81 mm) max. depth and 0.60 in. (15,25 mm) max. diameter.
10 cycles serviceable extension is allowed. Do blending (Ref. TASK 72-2100-320-003) until high metal is removed.
3. Fan inlet case on B1 upstream bracket location (Ref. Fig. 603/TASK 72-23-00-991-328) R R
A. Wear on B1 flange radius. (Ref. Fig. 604/TASK 72-23-00991-326)
R R
For damage that measures (X) from the B1 flange,
a maximum depth of wear (A) is permitted
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Feb 01/10
C F M 56-5B
Fan Inlet Case on B1 upstream bracket location Figure 603/TASK 72-23-00-991-328 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B
R R
Wear on B1 Flange Radius Figure 604/TASK 72-23-00-991-326
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------4. Inlet case on B4 upstream fan case: A. Expanded holes
Two expanded adjacent holes are permitted if: - Each expanded hole is not more than 0.315 in. (8 mm) width and not more than 0.39 in. (10 mm) long. - 5 holes minimum in good condition are on both sides of expanded holes.
B. Wear, fretting, chafing around flange holes.
If 0.031 in. (0.8 mm) max. depth and 0.155 sq.in. (100 sq.mm) max. surface.
10 cycles serviceable extension is permitted.
5. Inlet case on B4 downstream fan case: A. Expanded holes
Two expanded adjacent holes are permitted if: - Each expanded hole is not more than 0.315 in. (8 mm) width and not more than 0.39 in. (10 mm) long. - 5 holes minimum in good condition are on both sides of expanded holes.
B. Wear, fretting, chafing around flange holes.
If 0.024 in. (0.6 mm) max. depth and 0.155 sq.in. (100 sq.mm) max. surface.
10 cycles serviceable extension is permitted.
6. Fan FWD acoustical panel (Ref. TASK 7223-00-280-005)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 613 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------7. Fan MID acoustical panel (Ref. TASK 7223-00-280-006)
R
8. Fan aft acoustical panels (Ref. TASK 7223-00-280-007)
R
9. Splitter fairing for
R
A. Cracks
Not serviceable
B. Damaged protective coating
No limits in quantity
C. Erosion
No limits in quantity
Replace the fairing (Ref. TASK 72-23-00-000028) and (Ref. TASK 72-2300-400-028)
10. Fan duct panels for: (Ref. Fig. 602/TASK 72-23-00-991-309) A. Missing louver
1 missing louver permitted per panel if no more than 4 panels have this damage
Replace panel (Ref. TASK 72-23-00-000-027) and (Ref. TASK 72-23-00-400027).
B. Nicks, dents or scratches
No limits
C. Loose bolts
Not serviceable
Make sure that washers are installed and torque bolts to between 85 and 95 lbf.in (0.96 and 1.07 m.daN)
D. Cracks in screw hole area
One for each screw hole max length 0.25 in. (6,35 mm)
Replace panel (Ref. TASK 72-23-00-000-027) and (Ref. TASK 72-23-00-400027)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------E. Cracks in flanged Not serviceable Repair panel (Ref. TASK edges 72-23-00-300-042) 2 cracks permitted on the same panel
Repair panel (Ref. TASK 72-23-00-300-042)
G. Fan duct panel missing
Not serviceable
Install fan duct panel(s) (Ref. TASK 72-23-00-400027)
R R
F. Cracks on louver and area adjacent to louver
R R R
Refer to over serviceable limit extension (Ref. TASK 72-00-00-200-025) 5. Close-up ________ Subtask 72-23-00-410-082 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-061 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-093 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Aug 01/09
C F M 56-5B TASK 72-23-00-210-003 Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material 1. __________________ Reason for the Job R
Refer to the MPD TASK: 722000-C1 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-21-00-210-009 72-23-00-000-008 72-23-00-300-040 72-23-00-300-043 72-23-00-400-008 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-23-00-991-308 72-23-00-991-310
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Inspect Fan Rotor Blades Installed on the Fan Disk Removal of the Fan Outlet Guide Vane (OGV) Doublets Local Reconditioning of the Abradable MaterialDefects less than 0.12 in. (3 mm) deep and 0.50 in.2 (3.2 cm2) Repair of the Abradable (material) Shroud with Circular Patches Installation of the Fan Outlet Guide Vane (OGV) Doublets Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 605
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Feb 01/10
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-080 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-090 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-23-00-040-067 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-102 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 617 May 01/09
C F M 56-5B 4. Procedure _________ R
(Ref. Fig. 601/TASK 72-23-00-991-308, 605/TASK 72-23-00-991-310) Subtask 72-23-00-210-058 A. Detailed Visual Inspection of the Engine Inlet, Fan Blades, Fan Outlet and Abradable Material ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Inlet case for: (Ref. Fig. 601/TASK 72-23-00-991-308) A. Cracks
Not permitted.
B. Cracks or crazing in the rubber of AGB mount
Any amount.
C. Nicks
On area A, if 0.012 in. (0,30 mm) max. depth and 0.046 sq.in. (30 sq.mm) max. surface. On area B, if 0.008 in. (0,20 mm) max. depth and 0.046 sq.in. (30 sq.mm) max. surface. On area C, if 0.012 in. (0,30 mm) max. depth and 0.077 sq.in. (50 sq.mm) max. surface
50 cycles serviceable extension is allowed.
D. Scratches
0.008 in. (0,20 mm) max. depth and 1.968 in. (50 mm) max. length
50 cycles serviceable extension is allowed.
E. Dents
On area A, if 0.002 in. (0,5 mm) max. depth and 0.124 sq.in. (80 sq.mm) max. surface. On area B, if 0.008 in. (0,20 mm) max. depth and
50 cycles serviceable extension is allowed.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------0.124 sq.in. (80 sq.mm) max. surface. On area C, if 0.02 in. (0,5 mm) max. depth and 0.155 sq.in. (100 sq.mm) max. surface. F. Wear
On area A and B, if 0.004 in. (0,10 mm) max. depth and 0.465 sq.in. (300 sq.mm) max. surface. On area C, if 0.004 in. (0,10 mm) max. depth and 0.62 sq.in. (400 sq.mm) max. surface.
50 cycles serviceable extension is allowed.
2. Fan rotor blades: (Ref. TASK 72-21-00210-009) 3. Abradable for: (Ref. Fig. 601/TASK 72-23-00-991-308) A. Cracks
Any amount
B. Rubs
Any amount
C. Crater (length<5x width) and damage other than crack rub and circumferential defect
Cumulated damage more than 160 in.2 (1032,25 cm2) with no one area larger than 30 in.2 (193,54 cm2) and : a) The maximum axial width (parallel to engine axis) is less than 2.5 in. (63.5 mm) b) The minimum distance between the areas is equal to the maximum dimension of the nearest damaged area.
For defect above those limits : local reconditioning : (Ref. TASK 72-23-00-300040) circular patch : (Ref. TASK 72-23-00-300043) refer to limits : (Ref. TASK 72-00-00-200025)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 619 May 01/09
C F M 56-5B
R
Inspection/Check of the Fan-Outlet Guide Vanes (OGV) Figure 605/TASK 72-23-00-991-310- 13 (SHEET 1)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/09
C F M 56-5B
R
Inspection/Check of the Fan-Outlet Guide Vanes (OGV) Figure 605/TASK 72-23-00-991-310- 23 (SHEET 2)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 621 Nov 01/09
C F M 56-5B
R
Inspection/Check of the Fan-Outlet Guide Vanes (OGV) Figure 605/TASK 72-23-00-991-310- 33 (SHEET 3)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------c) The fan case parent metal does not show through.
R
D. Grooves (orientated within 0 deg. and 80 deg. from engine axis and length>5x width)
All damage is permitted if : a) The maximum width of one groove is not more than 0.32 in. (8.12 mm). b) A maximum of total width of 1.25 in. (31.75 mm) of groove is with a minimum separation of 0.1 in. (2.54 mm). c) The fan case parent metal does not show through.
For defect above those limits : local reconditioning : (Ref. TASK 72-23-00-300040) refer to limits : (Ref. TASK 72-00-00-200025)
E. Circumferential defect (360 deg. or orientated within 80 deg. to 90 deg. from engine axis
All damage is permitted if : a) The maximum axial width (parallel to engine axis) of one or cumulated defect is less than 1.5 in. (38.1 mm) b) Fan case parent metal does not show through.
For defect above those limits : local reconditioning : (Ref. TASK 72-23-00-300040) refer to limits : (Ref. TASK 72-00-00-200025)
A. Broken vane
Not serviceable
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
B. Missing vane
One doublet missing
10 cycles extension allowed with one doublet missing. Complete set inspection required when new doublet fitted.
4. Outlet Guide Vanes (OGV) for: (Ref. Fig. 605/TASK 72-23-00-991-310)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 623 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008). C. Cracks airfoil
Not serviceable
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
outer platform
Cracks from or along the airfoil are defined on fig.604
50 cycles extension allowed if cracks are found out of tolerance. Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
D. Delamination
Not serviceable
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
E. Eroded surface (glass film)
50 percent of airfoil
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
F. Unbonding of metal leading edge
Up to 0.31 sqare in. (200 square mm) serviceable if no parent composite material.
Replace the vane doublet (Ref. AMM TASK 72-23-00-000-008) and (Ref. AMM TASK 72-23-00-400-008).
Over 0.31 square in. (200 square mm).
Remove the unbonding area. Refer to paragraph G.Metal leading edge missing
Up to 0.78 in. (20 mm) height and 0.39 in. (10 mm) wide.
100 cycles extension allowed if missing material is over criteria.
G. Metal leading edge missing
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 624 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------Speed tape (CP2516) usage is recommended when missing metal on leading edge to preserve repair possibility, avoiding any damage on composite material. H. Outer and inner platform debonding
Not serviceable
Replace the vane doublet (Ref. AMM TASK 72-23-00-000-008) and (Ref. AMM TASK 72-23-00-400-008).
J. Nick and/or dents, on leading edge (metallic leading edge)
Any amount of damage less than 0.12 in. (3 mm) deep and metal not torn : serviceable. If damage less than 0.12 in. (3mm) deep and metal torn, refer to paragraph G..
A maximum service extension of 100 cycles is allowed if damage is between 0.12 in. (3mm) and 0.19 in. (5mm) deep.
K. Nick and/or dents, on trailing edge
No limited number if less than 0.01 in. (0.25 mm) depth
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
L. Nick and/or dent on concave or convex side
No limited number if less than 0.02 in. (0.51 mm) depth
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
M. Nick and/or dent on inner or outer platform
No limited number if less than 0.02 in. (0.51 mm) depth
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 625 May 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-084 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-063 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-094 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 626 May 01/09
C F M 56-5B TASK 72-23-00-280-001 Inspection/Check of the PS13 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
plastic wire warning notice access platform 1.5 m (4 ft. 11 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2010
Material No.
CP8001
Material No.
CP8002
* white spirit (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-000-029 72-23-00-400-029 72-23-00-991-320
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the PS13 Line Installation of the PS13 Line Fig. 606
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-084 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-107 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. 4. Procedure _________ R
(Ref. Fig. 606/TASK 72-23-00-991-320) Subtask 72-23-00-210-062 A. Visual Inspection of the PS13 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 628 May 01/09
C F M 56-5B (1) Inspect the PS13 line as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Inspect the hose for: - broken hose braid
3 broken wires per plait, and no more than 6 broken wires per assembly, or per lineal 12 in. (305 mm) of hose.
- crimps
Not serviceable
Replace the PS13 line (Ref. TASK 72-23-00-000029) and (Ref. TASK 72-2300-400-029).
Subtask 72-23-00-210-060 B. Visual Inspection of the PS13 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Inspect the PS13 hose connections as follows: (a) Cut and remove the lockwires. (b) Disconnect the PS13 hose from the ECU and from the fan frame boss.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 629 May 01/09
C F M 56-5B
PS13 Line Figure 606/TASK 72-23-00-991-320- 12 (SHEET 1)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 630 May 01/09
C F M 56-5B
PS13 Line Figure 606/TASK 72-23-00-991-320- 22 (SHEET 2)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 631 May 01/09
C F M 56-5B (c) Inspect the connections as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fitting nuts for: - damaged corners
Any amount, provided proper torque can be obtained.
- damaged threads
Any amount, provided effective threads are not reduced by more than one after chasing.
- safetywire hole deformation and wear.
Serviceable, provided metal around hole is not cracked or torn.
Chase the threads.
2. Fittings seating surfaces for: - circumferential scratches
Any amount not detectable with a 0.04 in. (1 mm) radius ball scribe.
- axial scratches
Not serviceable
Replace the hose or the part.
- nicks, pits
Not serviceable
Replace the hose or the part.
(2) Clean the weep hole with white spirit (Material No. CP2010) and a plastic wire. (3) Blow clean dry air into the PS13 connection to ECU to remove any dirt or water accumulation. Blocked hose is not serviceable. If necessary, replace the hose (Ref. TASK 72-23-00-000-029) and (Ref. TASK 72-2300-400-029). (4) Check the ECU nipple for dirt. If necessary, remove the dirt with a plastic wire. Take care to not introduce dirt inside the ECU.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 632 May 01/09
C F M 56-5B (5) Check the fan frame boss for dirt. If necessary, remove the dirt with stoddart solvent and a plastic wire. Blow clean dry air into the fan frame boss nipple. (6) Lubricate the ECU and the fan frame boss nipples with engine fuel. (7) Connect the PS13 line to the ECU and to the fan frame boss. (8) TORQUE the ECU connection to between 180 and 200 lbf.in (2.03 and 2.26 m.daN). (9) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (10) TORQUE the fan frame boss connection to between 135 and 150 lbf.in (1.52 and 1.69 m.daN). (11) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). 5. Close-up ________ Subtask 72-23-00-410-097 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s). (4) Remove the access platform(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 633 May 01/09
C F M 56-5B TASK 72-23-00-280-002 Inspection/Check of the PS12 line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
plastic wire warning notice access platform 1.5 m (4 ft. 11 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2010
Material No.
CP8001
Material No.
CP8002
* white spirit (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-000-040 72-23-00-400-040 72-23-00-991-321
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the PS12 Line Installation of the PS12 Line Fig. 607
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 634 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-085 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-108 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. 4. Procedure _________ R
(Ref. Fig. 607/TASK 72-23-00-991-321) Subtask 72-23-00-210-063 A. Visual Inspection of the PS12 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 635 May 01/09
C F M 56-5B
PS12 Line Figure 607/TASK 72-23-00-991-321- 14 (SHEET 1)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 636 May 01/09
C F M 56-5B
PS12 Line Figure 607/TASK 72-23-00-991-321- 24 (SHEET 2)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 637 May 01/09
C F M 56-5B
PS12 Line Figure 607/TASK 72-23-00-991-321- 34 (SHEET 3)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 638 May 01/09
C F M 56-5B
PS12 Line Figure 607/TASK 72-23-00-991-321- 44 (SHEET 4)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 639 May 01/09
C F M 56-5B (1) Inspect the PS12 line as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Inspect the hose for: - broken hose braid
3 broken wires per plait, and no more than 6 broken wires per assembly, or per lineal 12 in. (305 mm) of hose.
- crimps
Not serviceable
Replace the PS12 line (Ref. TASK 72-23-00-000040) and (Ref. TASK 72-2300-400-040).
Subtask 72-23-00-210-061 B. Visual Inspection of the PS12 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Inspect the PS12 hose connections as follows: (a) Cut and remove the lockwires. (b) Disconnect the PS12 hose from the ECU and from the fan frame bosses.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 640 Feb 01/09
C F M 56-5B (c) Inspect the connections as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fitting nuts for: - damaged corners
Any amount, provided proper torque can be obtained.
- damaged threads
Any amount, provided effective threads are not reduced by more than one after chasing.
- safetywire hole deformation and wear.
Serviceable, provided metal around hole is not cracked or torn.
Chase the threads.
2. Fittings seating surfaces for: - circumferential scratches
Any amount not detectable with a 0.04 in. (1 mm) radius ball scribe.
- axial scratches
Not serviceable
Replace the hose or the part.
- nicks, pits
Not serviceable
Replace the hose or the part.
(2) Clean the weep holes with white spirit (Material No. CP2010) and plastic wire. (3) Blow clean dry air into the PS12 connection to ECU to remove any dirt or water accumulation. Blocked hose is not serviceable. If necessary, replace the hose (Ref. TASK 72-23-00-000-040) and (Ref. TASK 72-2300-400-040). (4) Check the ECU nipple for dirt. If necessary, remove the dirt with plastic wire. Take care to not introduce dirt inside the ECU.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 641 Feb 01/09
C F M 56-5B (5) Check the fan frame bosses for dirt. If necessary, remove the dirt with stoddart solvent and a plastic wire. Blow clean dry air into the fan frame bosses nipples. (6) Lubricate the ECU and the fan frame bosses nipples with engine fuel. (7) Connect the PS12 line to the ECU and to the fan frame bosses. (8) TORQUE the PS12 connections to between 135 and 150 lbf.in (1.52 and 1.69 m.daN). (9) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). 5. Close-up ________ Subtask 72-23-00-410-098 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the access platform(s). (4) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 642 Feb 01/09
C F M 56-5B TASK 72-23-00-280-005 Inspection of Forward Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-000-009 72-23-00-300-044 72-23-00-400-009 72-23-00-400-044 R
72-23-00-991-311
Removal of the Forward Acoustical Panels of the Fan Repair of Forward, Mid and Aft Acoustical Panels when Unbounded Cup Installation of the Forward Acoustical Panels of the Fan Installation of Acoustical Panels Attachment Screw Locking Fig. 608
3. __________ Job Set-up Subtask 72-23-00-941-090 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 643 May 01/09
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put a warning notice to tell persons not to start the engine 1(2). (5) Put an access platform in position at the front of the engine. 4. Procedure _________ R
(Ref. Fig. 608/TASK 72-23-00-991-311) Subtask 72-23-00-350-058 A. Inspection of FWD Acoustical Panels ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. FWD acoustical panels A. Dents, marks, indentations caused by screw head.
No limits
B. Pierced cups caused by screw head.
Not serviceable
Install the panel (Ref. TASK 72-23-00-400044)
C. Unbonded cups.
Not serviceable
Repair the panel (Ref. TASK 72-23-00-300044) and re-install the panel immediately (Ref. TASK 72-23-00-400009).
D. Missing cups.
Not serviceable
Replace the panel (Ref. TASK 72-23-00-000009) and (Ref. TASK 72-2300-400-009).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 644 May 01/09
C F M 56-5B
INTENTIONALLY BLANK
R 72-23-00 CES
Page 645 Aug 01/09
C F M 56-5B
Fan Acoustical Panels Figure 608/TASK 72-23-00-991-311- 12 (SHEET 1)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 646 May 01/09
C F M 56-5B
Fan Acoustical Panels Figure 608/TASK 72-23-00-991-311- 22 (SHEET 2)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 647 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------E. Missing insert No limits thread F. Missing panel
Not serviceable
G. Loose bolts
Not serviceable
H. Local collapse of panel inner surface
No limits
J. Subsurface linear impressions or wrinkles
No limits
Serviceable criteria applied on new parts
K. Voids
Five per panel, 2 in. (50.8 mm) apart, 0.12 in. (3 mm) Dia max, 0.012 in. (0.3 mm) max depth
Serviceable criteria applied on new parts
(1) Missing
No limits
Remove the loose material with a sharp blade.
(2) Defects (dents, nicks, tears, flaking) that let show the inner skin
No limits
Remove the loose material with a sharp blade.
No limits with a total surface area less than 4 square in. (2580 sq mm)
Remove the loose material with a sharp blade.
Tighten bolts
L. Defects in the protective coating (initial Tedlar film, or paint) such as:
M. Inner skin defects, such as: (1) Superficial defects (dents, nicks,
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 648 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------tears, impacts per panel marks) not through the skin (2) Defects (tears, cracks, punctures) through the skin
Not serviceable
Replace panel(s) (Ref. TASK 72-23-00-000009) and (Ref. TASK 72-2300-400-009).
5. Close-up ________ Subtask 72-23-00-410-103 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 649 Aug 01/09
C F M 56-5B TASK 72-23-00-280-006 Inspection of Mid Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-200-025 72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-23-00-000-025 72-23-00-300-044 72-23-00-400-025 72-23-00-400-044 72-23-00-991-311
Over-Serviceable-Limit Extensions Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Removal of the Mid Acoustical Panels Repair of Forward, Mid and Aft Acoustical Panels when Unbounded Cup Installation of the Mid Acoustical Panels Installation of Acoustical Panels Attachment Screw Locking Fig. 608
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 650 Aug 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-091 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-113 B. Get Access (1) Put an access platform in position at the front of the engine. (2) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (3) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (4) Put temporary mark on each fan blade from 1 to 36. (5) Remove 3 consecutive fan blades (Ref. TASK 72-21-00-000-007). To compensate for imbalance caused by the removal of 3 blades, it is recommended to remove 3 blades 180 degrees opposite to those removed before.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 651 Aug 01/09
C F M 56-5B 4. Procedure _________ (Ref. Fig. 608/TASK 72-23-00-991-311) Subtask 72-23-00-350-059 A. Inspection of Mid Acoustical Panels ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Leading edge delamination
Not serviceable
Replace panel (Ref. TASK 72-23-00-000-025) and (Ref. TASK 72-23-00-400025)
2. Inner skin delamination in acoustical area
20 percent of acoustical area
Above 20 percent, replace panel (Ref. TASK 72-23-00000-025) and (Ref. TASK 72-23-00-400-025)
3. Mid acoustical panel cups A. Dents, marks, indentations caused by screw head
No limits
B. Pierced cups caused by screw head
No limits
(Ref. TASK 72-23-00-400044)
C. Unbonded cups
Not serviceable
(Ref. TASK 72-23-00-300044)
D. Missing cups.
Not serviceable
(Ref. TASK 72-23-00-300044)
4. Missing panel
Not serviceable
5. Loose bolts
Not serviceable
Tighten bolts
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 652 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------6. Subsurface linear No limits Serviceable criteria impressions or applied on new parts wrinkles 7. Voids
Five per panel, 2 in. (50.8 mm) apart, 0.12 in. (3 mm) Dia max, 0.012 in. (0.3 mm) max depth
Serviceable criteria applied on new parts
A. Missing
No limits
Remove the loose material with a sharp blade
B. Defects (dents, nicks, tears, flaking) that let show the inner skin
No limits
Remove the loose material with a sharp blade
A. Superficial defects (dents, nicks, tears, impact marks) not through the skin
No limits with a total surface area less than 4 square in. (2580 sq mm) per panel
Remove the loose material with a sharp blade
B. Defects (tears, cracks, punctures) through the skin
Not serviceable
Replace panel(s) (Ref. TASK 72-23-00-000025) and (Ref. TASK 72-2300-400-025)
C. Stiffener delamination under panel leading edge
Sound not constant with adjacent area by tap test control. Do the tap test control on the first 0.83 in. (21 mm)
Replace panel(s) (Ref. TASK 72-23-00-000025) and (Ref. TASK 72-2300-400-025)
8. Defects in the protective coating (initial Tedlar film, or paint) such as:
9. Inner skin defects, such as:
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 653 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------area from the leading edge on assembled panels 10. Damper A. Cracks (if panel removed)
Any amount
B. Disbonded damper (if panel removed)
Any amount not more than 20 percent of the total bonded surface
Replace mid acoustical panel of not in the limits (Ref. TASK 72-23-00-000025) and (Ref. TASK 72-2300-400-025) Refer to the over-serviceable limit extensions (Ref. TASK 7200-00-200-025)
5. Close-up ________ Subtask 72-23-00-410-104 A. Close Access (1) Install the fan rotor blades at the locations recorded at the removal (Ref. TASK 72-21-00-400-007). (2) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (3) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (4) Make sure that the work area is clean and clear of tool(s) and other items. (5) Remove the access platform(s). (6) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 654 Aug 01/09
C F M 56-5B TASK 72-23-00-280-007 Inspection of Aft Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-000-026 72-23-00-300-044 72-23-00-400-026 72-23-00-400-044 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-23-00-991-311
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Aft Acoustical Panels Repair of Forward, Mid and Aft Acoustical Panels when Unbounded Cup Installation of the Aft Acoustical Panels Installation of Acoustical Panels Attachment Screw Locking Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 608
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 655 Aug 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-095 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-120 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-23-00-040-073 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-121 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 656 Aug 01/09
C F M 56-5B 4. Procedure _________ (Ref. Fig. 608/TASK 72-23-00-991-311) Subtask 72-23-00-350-060 A. Inspection of Aft Acoustical Panels ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Aft acoustical panel cups A. Dents, marks, indentations caused by screw head.
No limits
(Ref. TASK 72-23-00-400026) for re-installation.
B. Pierced cups caused by screw head.
Not serviceable
(Ref. TASK 72-23-00-400044)
C. Unbonded cups.
Not serviceable
(Ref. TASK 72-23-00-300044)
D. Missing cups.
Not serviceable
(Ref. TASK 72-23-00-300044)
No limits unless the whole seal is missing
Replace seal if missing
Not serviceable
Install the seal correctly, or install a new U-shaped seal (Ref. TASK 72-23-00-000026) or (Ref. TASK 72-2300-400-026)
PRE SB 72-071 E. Damaged or missing bonded seal(s) END OF PRE SB 72-071 POST SB 72-071 F. Mis-installed, badly damaged or missing U-shaped seal (removable)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 657 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------END OF SB 72-071 G. Missing panel
Not serviceable
H. Loose bolts
Not serviceable
Tighten bolts
J. Subsurface linear impressions or wrinkles
No limits
Serviceable criteria applied on new parts
K. Voids
Five per panels, 2 in. (50.8 mm) apart, 0.12 in. (3 mm) Dia max, 0.012 in. (0.3 mm) max depth
Serviceable criteria applied on new parts
(1) Missing
No limits
Remove the loose material with a sharp blade
(2) Defects (dents, nicks, tears, flaking) that let show the inner skin
No limits
Remove the loose material with a sharp blade
No limits with a total surface area less than 4 square in. (2580 sq mm) per panel
Remove the loose material with a sharp blade
L. Defects in the protective coating (initial Tedlar film, or paint) such as:
M. Inner skin defects, such as: (1) Superficial defects (dents, nicks, tears, impact marks) not through the skin
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 658 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------(2) Defects Not serviceable Replace panel(s) (tears, (Ref. TASK 72-23-00-000cracks, 026) and (Ref. TASK 72-23punctures) 00-400-026) through the skin 5. Close-up ________ Subtask 72-23-00-410-111 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-067 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-112 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 659 Feb 01/09
C F M 56-5B TASK 72-23-00-210-007 Visual Inspection of the Junction Box 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2242
USA MIL-A-46106A RTV 732 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-300-046
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Replacement of Lateral Bracket Plate on the Junction Box
3. __________ Job Set-up Subtask 72-23-00-941-097 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 660 Feb 01/09
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-123 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ Subtask 72-23-00-210-067 A. Visual Inspection of the Junction Box ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------Crack on the two lateral bracket plates.
One crack 0.78 in. (20 mm) max length.
Stop crack by drilling a 0.12 in. (3 mm) hole at each ends of the crack. Clean the part.Apply RTV 732 (Material No. CP2242) or equivalent on the inner face of the affected area
Any amount
Replace the damaged lateral bracket plate (Ref. TASK 72-23-00-300046).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 661 Feb 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-115 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 662 Feb 01/09
C F M 56-5B FAN FRAME ASSEMBLY - REPAIRS ____________________________ TASK 72-23-00-300-040 Local Reconditioning of the Abradable Material- Defects less than 0.12 in. (3 mm) deep and 0.50 in.2 (3.2 cm2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No No No
specific specific specific specific specific specific
heat gun or a infra-red lamp protective mats spatula vacuum cleaner warning notice access platform 0.5 m (1 ft. 8 in.)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2239
Material No.
CP2297
Material No.
CP2298
Material No.
CP2559
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * abrasive cloth (Ref. 70-30-00) * base RTV 147 A (Ref. 70-30-00) * catalyst (hardener) RTV 147 B (black color) (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades
3. __________ Job Set-up Subtask 72-23-00-941-078 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B Subtask 72-23-00-010-089 B. Get Access (1) Put an access platform in position. (2) Install protective mats in the lower half of the inlet cowl. (3) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (4) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (5) Remove a sufficient number of fan blades to get access to repair area (Ref. TASK 72-21-00-000-007). 4. Procedure _________ Subtask 72-23-00-320-053 A. Prepare the Repair Area (1) Remove the damaged area from the abradable shroud, until only an area without damage is there. NOTE : All oil contaminated areas must be removed. ____ (2) Make the surface of the repair area rough with an abrasive cloth (Material No. CP2239) (3) Blow the dust out of the shroud or vacuum cleaner. Subtask 72-23-00-110-052 B. Degrease the Area WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY SHOULD _______ BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING. (1) Clean the area to be repaired with acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or magchem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B Subtask 72-23-00-340-051 C. Prepare the Base and Hardener for the Repair WARNING : PUT ON PROTECTIVE GLOVES WHEN YOU USE THE BASE AND HARDENER. IF _______ YOU DO NOT OBEY THIS PRECAUTION, INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR. (1) Mix, by weight, 100 parts of the base RTV 147 A (Material No. CP2297) and 10 parts of the catalyst (hardener) RTV 147 B (black color) (Material No. CP2298). (2) Stir the mixture by hand or mechanically until it becomes a homogenous compound. NOTE : The compound has a pot life of 2 hours after mixing, at ____ ambient temperature. (3) Apply the compound with a spatula. Lighthy hit the compound to remove the air bubbles (if any). Subtask 72-23-00-350-052 D. Cure the Compound with a heat gun or a infra-red lamp as follows: (1) 1 hour at 210 deg.F (98.9 deg.C). (2) 1/2 hour at 200 deg.F (93.3 deg.C). Subtask 72-23-00-320-054 E. Complete the Repair as follows: (1) Make sure the cured compound is constant in color. Make sure it does not contain air bubbles. (2) Use an abrasive cloth (Material No. CP2239) to make the repaired surface smooth with all adjacent areas of the abradable shroud. (3) Clean the repair area and the inlet cowl with a vacuum cleaner.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-083 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the fan blades (Ref. TASK 72-21-00-400-007). (3) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (4) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (5) Remove the protective mats from the inlet cowl. (6) Remove the access platform(s). (7) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/08
C F M 56-5B TASK 72-23-00-350-002 Removal of Rust from the Fan Frame Casing 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific
brush warning notice access platform 1 m (3 ft. 3 in.)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2189
Material No.
CP2208
Material No.
CP2442
* durite G422 (Ref. 70-30-00) * 3M-361 tape (Ref. 70-30-00) * engine oil (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-991-313
Fig. 801
3. __________ Job Set-up Subtask 72-23-00-941-081 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-097 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-23-00-040-064 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B Subtask 72-23-00-010-098 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 801/TASK 72-23-00-991-313) Subtask 72-23-00-140-051 A. Protect the fan duct panels with 3M-361 tape (Material No. CP2208). CAUTION : DAMAGE CAN RESULT IF ENGINE OIL IS SPREAD ON VARIABLE STATOR _______ VANE BUSHINGS OF THE COMPRESSOR FRONT STATOR. (1) Remove loose rust on hub and struts using a cloth. (2) If rust is still present, polish struts (radially) and hub using durite G422 (Material No. CP2189). (3) Coat the cleaned areas with engine oil (Material No. CP2442) using a cloth or brush. (4) Remove the masking tape from fan duct panels. 5. Close-up ________ Subtask 72-23-00-410-091 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-062 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Nov 01/08
C F M 56-5B
Fan Frame Casing - Rust Removal Figure 801/TASK 72-23-00-991-313 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B Subtask 72-23-00-410-092 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
C F M 56-5B TASK 72-23-00-300-042 Repair of Fan Duct Panel 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP5006
* austenite stainless steel wire - 321SS (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-000-027 72-23-00-400-027 SPM 70-32-11-23000500 SPM 70-41-11-35000900 SPM 70-45-11-31000200 72-23-00-991-314
Removal of the Fan Duct Panels Installation of the Fan Duct Panels
Fig. 802
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-082 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-092 B. Remove the fan duct panel (Ref. TASK 72-23-00-000-027). 4. Procedure _________ (Ref. Fig. 802/TASK 72-23-00-991-314) NOTE : This repair procedure provides instruction for reconditioning cracked ____ fan duct panels by weld buildup. Subtask 72-23-00-310-052 A. Stop the crack by drilling a 0.079 in. (2 mm) dia. hole at both ends. (1) Weld up the crack under argon atmosphere, and using weld wire austenite stainless steel wire - 321SS (Material No. CP5006). (Ref. SPM 70-45-11-31000200). (2) Check the welded area (Ref. SPM 70-32-11-23000500). (3) Flush the weld bead (Ref. SPM 70-41-11-35000900). (4) Perform a fluorescent inspection of the weld bead (Ref. SPM 70-32-1123000500).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B
Fan Duct Panels Figure 802/TASK 72-23-00-991-314 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-086 A. Close Access (1) Install the fan duct panel (Ref. TASK 72-23-00-400-027). (2) Make sure that the work area is clean and clear of tool(s) and other items. (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Nov 01/08
C F M 56-5B TASK 72-23-00-300-043 Repair of the Abradable (material) Shroud with Circular Patches CAUTION : THIS REPAIR MUST NOT BE DONE IN A HUMID ATMOSPHERE. THIS COULD AFFECT _______ THE QUALITY OF THE BONDING COMPOUND. THE MINIMUM AMBIENT TEMPERATURE MUST BE 60 DEG.F (15 DEG.C). 1. __________________ Reason for the Job General Defect more than 0.12 in. (3 mm) deep and 0.50 in.2 (3.2 cm2) and with fan case base metal exposed. This task refers to a procedure for the in-place of the abradable shroud by installation of circular patches 1.968 in. (50 mm) maximum diameter. NOTE : The following patch repair is estimated to take less than 3 hours in ____ the hangar when done by skilled mechanics familiarized with the procedure. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No No No No No
specific specific specific specific specific specific specific specific
clean, white cloth heat gun or infrared lamp or heatings panels paint brush protective mats scalpel vacuum cleaner warning notice access platform 0.5 m (1 ft. 8 in.)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2239
Material No.
CP2244
Material No.
CP2297
Material No.
CP2298
Material No.
CP2306
Material No.
CP2339
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * abrasive cloth 3 M 301D grit size 80 or 120 (Ref. 70-30-00) * Primer 1200 (Ref. 70-30-00) * base RTV 147 A (Ref. 70-30-00) * catalyst (hardener) RTV 147B (black color) (Ref. 70-30-00) * heat-resistant tape 3 M No. 5490 (Ref. 70-30-00) * RTV 630 (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-23-00-991-317
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Fig. 803
3. __________ Job Set-up Subtask 72-23-00-941-088 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-110 B. Get Access (1) Put an access platform in position. (2) Intall protective mats in the lower half of the inlet cowl. (3) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (4) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
C F M 56-5B (5) Remove a sufficient number of fan blades to get access to the repair area (Ref. TASK 72-21-00-000-007). 4. Procedure _________ (Ref. Fig. 803/TASK 72-23-00-991-317) Subtask 72-23-00-320-059 A. Repair of the Abradable Shroud with Circular Patches (1) Remove the unwanted pieces of abradable liner. (a) Punch out the abradable material to the base metal, at the location of the defect, maximum diameter 1.968 in. (50 mm). (b) Use a scalpel and abrasive cloth 3 M 301D grit size 80 or 120 (Material No. CP2239) to remove all pieces of the abradable material. (c) Blow the part clean with shop air. Subtask 72-23-00-110-054 B. Degrease Area WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY SHOULD _______ BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING. (1) Use the acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or magchem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) to remove the grease from the area to be repaired.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-23-00 CES
Page 819 Feb 01/09
C F M 56-5B
Repair of the Abradable Shroud With Circular Patches Figure 803/TASK 72-23-00-991-317- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 820 Nov 01/08
C F M 56-5B
Repair of the Abradable Shroud With Circular Patches Figure 803/TASK 72-23-00-991-317- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 821 Nov 01/08
C F M 56-5B Subtask 72-23-00-340-053 C. Apply the Abradable Liner Patch (1) Remove grease from the part with a clean, white cloth soaked in acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or magchem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656). (2) Prepare the bonding compound as follows: WARNING : PUT ON PROTECTIVE GLOVES WHEN YOU USE THE BASE AND _______ HARDENER. IF YOU DO NOT OBEY THIS PRECAUTION, INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR. NOTE : You must use the compound within 2 hours after it is mixed ____ (a) Mix 100 parts of base RTV 147 A (Material No. CP2297) with 10 parts of catalyst (hardener) RTV 147B (black color) (Material No. CP2298) or use RTV 630 (Material No. CP2339), at ambient temperature. (b) Stir the mixture manually or mechanically until it is fully mixed. (3) Apply the primer as follows: (a) Remove grease from the area to be repaired. (b) Apply the Primer 1200 (Material No. CP2244) on the degreased area of fan case with a clean, white cloth or a paint brush. (c) Allow to dry at ambient temperature for 45 minutes. NOTE : Too much primer will reduce adherence. Also do not touch ____ the primer after it is applied. (4) Prepare the abradable liner patch as follows: (a) From a (spare) new fan inlet case abradable cartridge (Ref. PIPC 72230065375), punch out a circular patch at the equivalent size of the defect. NOTE : In this repair, the maximum diameter dimension of the ____ patch is set at 1.968 inch (50 mm).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 822 Feb 01/09
C F M 56-5B (b) Lightly sand the underside and the edges of the patch with abrasive cloth 3 M 301D grit size 80 or 120 (Material No. CP2239). (c) Punch one hole with a diameter 0.118 inch (3 mm) at the center of the patch. Keep the 0.118 in. (3 mm) diameter piece of abradable. It will be used as a cap after the final application of the repair patch. NOTE : The hole of the center of the patch will do as a vent hole ____ during the application of the patch on the fan inlet case. (d) Degrease. WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY _______ SHOULD BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING. 1 _
Remove the grease with acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) .
2 _
Apply bonding compound on the case, on the underside and edges of the patch.
(e) Bond the patch. 1 _
Press strongly all around the little hole to remove unwanted compound and any air below the patch.
2 _
After the final application, plug the central hole with the cap.
3 _
Remove the mixture from the part surface with a white cloth before polymerization.
4 _
Hold the patch in place with heat-resistant tape 3 M No. 5490 (Material No. CP2306).
Subtask 72-23-00-350-055 D. Do the Polymerization as follows: (1) With an heat gun or infrared lamp or heatings panels heat the patch for 2 hours 15 minutes at 158 deg.F (70 deg.C) or 1 hour at 212 deg.F (100 deg.C) to cure the bonding compound.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 823 Feb 01/09
C F M 56-5B Subtask 72-23-00-210-065 E. Do a Last Check of the Abradable Liner (1) When you do the visual check, examine all joints and patch areas to make sure there are no defects as porosity or trapped air bubbles. (2) If you see defects, you do the repair again. Subtask 72-23-00-320-060 F. Complete the Repair as follows: (1) Hand finish the abradable liner. (a) Hand finish the reconditioned area to put it back to the contour and dimensions of the adjacent areas. (b) Sand lightly with an abrasive cloth 3 M 301D grit size 80 or 120 (Material No. CP2239). (2) Remove the abradable material dust and hand sanding residues from the repair area with a vacuum cleaner. 5. Close-up ________ Subtask 72-23-00-410-100 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the fan blades (Ref. TASK 72-21-00-400-007). (3) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (4) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (5) Remove the mats from the lower half from the inlet cowl. (6) Remove the access platform(s). (7) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 824 Feb 01/09
C F M 56-5B TASK 72-23-00-300-044 Repair of Forward, Mid and Aft Acoustical Panels when Unbounded Cup 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1040
Material No.
CP2242
Material No.
CP2266
Material No.
CP2431
* methyl-ethyl-ketone (Ref. 70-30-00) * RTV732 (Ref. 70-30-00) * RTV102 (Ref. 70-30-00) * RTV730 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-000-009 72-23-00-000-025 72-23-00-000-026 72-23-00-400-009 72-23-00-400-025 72-23-00-400-026 72-23-00-991-318
Removal of the Forward Acoustical Panels of the Fan Removal of the Mid Acoustical Panels Removal of the Aft Acoustical Panels Installation of the Forward Acoustical Panels of the Fan Installation of the Mid Acoustical Panels Installation of the Aft Acoustical Panels Fig. 804
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 825 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-098 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put a warning notice to tell persons not to start the engine 1(2). (5) Put an access platform in position at the front of the engine. Subtask 72-23-00-010-124 B. Remove the forward or mid or aft acoustical panel (Ref. TASK 72-23-00000-009) or (Ref. TASK 72-23-00-000-025) or (Ref. TASK 72-23-00-000-026) 4. Procedure _________ (Ref. Fig. 804/TASK 72-23-00-991-318) Subtask 72-23-00-350-061 A. Repair the unbounded cup (1) Clean the repair area with methyl-ethyl-ketone (Material No. CP1040). (2) Apply RTV732 (Material No. CP2242) or RTV102 (Material No. CP2266) or RTV730 (Material No. CP2431) on the panel cup surface. (3) Install the cup on the forward or mid or aft acoustical panel. NOTE : You must install the acoustical panel in a short time after ____ you apply the RTV (before polymerisation).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 826 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-116 A. Close Access (1) Install the forward or mid or aft acoustical panel (Ref. TASK 72-2300-400-009) or (Ref. TASK 72-23-00-400-025) or (Ref. TASK 72-23-00400-026). NOTE : You must install the acoustical panel in a short time after ____ you apply the RTV (before polymerisation). (2) Make sure that the work area is clean and clear of tool(s) and other items. (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 827 Nov 01/08
C F M 56-5B
Fan Acoustical Panels Figure 804/TASK 72-23-00-991-318- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 828 Nov 01/08
C F M 56-5B
Fan Acoustical Panels Figure 804/TASK 72-23-00-991-318- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 829 Nov 01/08
C F M 56-5B
Fan Acoustical Panels Figure 804/TASK 72-23-00-991-318- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 830 Nov 01/08
C F M 56-5B TASK 72-23-00-300-045 Replacement of the Riveted Self Locking Nuts for the Attachment of the Forward Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------70 70 80 80 90 90 90 90 90
self-locking self-locking self-locking self-locking self-locking self-locking self-locking self-locking self-locking
nuts nuts nuts nuts nuts nuts nuts nuts nuts
72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
25 25 25 25 25 25 25 25 25
-020 -020A -040 -040A -060 -060A -060B -060C -060D
Page 831 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-400-005 72-21-00-400-006 72-23-00-000-009 72-23-00-400-009 72-23-00-400-028 SPM 704311390003 SPM 704331390005 SPM 704450320006 72-23-00-991-319 72-23-00-991-322
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Removal of the Forward Acoustical Panels of the Fan Installation of the Forward Acoustical Panels of the Fan Installation of the Splitter Fairing
Fig. 805 Fig. 806
3. __________ Job Set-up Subtask 72-23-00-941-099 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 832 Nov 01/08
C F M 56-5B Subtask 72-23-00-010-125 B. Get Access (1) Put an access platform in position. (2) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (3) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006) (4) Remove a sufficient number of fan blades to get access to the repair area (Ref. TASK 72-21-00-000-007). (5) Remove the forward acoustical panel (Ref. TASK 72-23-00-000-009). 4. Procedure _________ (Ref. Fig. 805/TASK 72-23-00-991-319) Subtask 72-23-00-350-062 A. Replacement of the Riveted Self-Locking Nuts (Ref. Fig. 806/TASK 72-23-00-991-322) NOTE : If necessary, for the repair size rivets, drill at the same time ____ the rivet holes in the new nut you install and the rivet holes on the containment case (Ref. SPM 704311390003) or (Ref. SPM 704331390005). (1) Remove the rivet head with a 0.094 in. (2,4 mm) diameter drill (Ref. SPM 704450320006). (2) If you cannot remove the rivet head, use a 0.125 in. (3,2 mm) diameter drill related to the repair size rivet (Ref. SPM 704331390005) or (Ref. SPM 704450320006). (3) Do a check of the rivet holes (Ref. SPM 704331390005). (4) Install the new self-locking nuts self-locking nuts (70) or selflocking nuts (80) or self-locking nuts (90) on the containment case with new rivets (10) or (20) or (30) or (40) or (50) or (60) (Ref. SPM 704331390005).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 833 Nov 01/08
C F M 56-5B
Replacement of the Self Locking Nuts Figure 805/TASK 72-23-00-991-319 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 834 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-23-00 CES
Page 835 Nov 01/08
C F M 56-5B
Dimensional Information for the Replacement of the Self Locking Nuts Figure 806/TASK 72-23-00-991-322- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 836 Nov 01/08
C F M 56-5B
Dimensional Information for the Replacement of the Self Locking Nuts Figure 806/TASK 72-23-00-991-322- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 837 Nov 01/08
C F M 56-5B
Dimensional Information for the Replacement of the Self Locking Nuts Figure 806/TASK 72-23-00-991-322- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 838 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-117 A. Close Access (1) Install the forward acoustical panel (Ref. TASK 72-23-00-400-009). (2) Install the fan blades (Ref. TASK 72-23-00-400-028). (3) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (4) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (5) Make sure that the work area is clean and clear of tool(s) and other items. (6) Remove the access platform(s). (7) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 839 Nov 01/08
C F M 56-5B TASK 72-23-00-300-046 Replacement of Lateral Bracket Plate on the Junction Box 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific R
warning notice
B. Expendable Parts
R R R
------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN -------------------------------------------------------------------------------
R R
40 40
R
bracket plate bracket plate
72-00-00 05 -061 72-00-00 05 -062
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 SPM 70-21-12-110-003 SPM 70-32-21-230-010 SPM 70-41-11-350-009 SPM 70-43-11-390-003 SPM 70-43-32-390-006 72-23-00-991-323 72-23-00-991-324 72-23-00-991-325
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors
Fig. 807 Fig. 808 Fig. 809
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 840 Feb 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-106 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice in position to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-133 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): - FOR 1000EM1 437AL, 438AR - FOR 1000EM2 447AL, 448AR. 4. Procedure _________ (Ref. Fig. 807/TASK 72-23-00-991-323) Subtask 72-23-00-390-051 A. Removal of the Damaged Bracket Plate WARNING : METAL PARTICLES FROM DRILLING CAN CAUSE DAMAGE, INJURY OR _______ IRRITATION TO YOU. USE PERSONAL PROTECTION EQUIPMENT. (1) Drill to remove rivets from the riveted bracket plate (Ref. SPM 7043-32-390-006). (2) Do a visual inspection of the junction box. No crack is permitted.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 841 Feb 01/09
C F M 56-5B
R R
Replacement of Lateral Bracket Plate Figure 807/TASK 72-23-00-991-323
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 842 Nov 01/08
C F M 56-5B (3) Remove the riveted nuts (20) from the bracket plate you remove. WARNING : METAL PARTICLES FROM DRILLING CAN CAUSE DAMAGE, INJURY OR _______ IRRITATION TO YOU. USE PERSONAL PROTECTION EQUIPMENT. (a) Drill to remove the rivets (10) which attach the riveted nuts (20) (Ref. SPM 70-43-11-390-003). NOTE : Be careful not to damage the riveted nut. If the riveted ____ nut is damaged, install a new one. Subtask 72-23-00-420-073 B. Installation of the New Bracket Plate (1) Install the riveted nut (20) on the new bracket plate. (a) Do a visual inspection of the rivet holes in the tube bundle junction box (Ref. SPM 70-43-11-390-003). (Ref. Fig. 808/TASK 72-23-00-991-324) (b) Drill the rivet holes and the riveted nut. WARNING : METAL PARTICLES FROM DRILLING CAN CAUSE DAMAGE, INJURY _______ OR IRRITATION TO YOU. USE PERSONAL PROTECTION EQUIPMENT. 1 _
If necessary, drill again at the same time the rivet holes in the junction box and in the riveted nut you are to rivet (Ref. SPM 70-43-11-390-003). (Ref. Fig. 808/TASK 72-23-00-991-324)
(c) Put the riveted nut (20) in position and rivet it with two rivets (10) (Ref. SPM 70-43-11-390-003). NOTE : Make sure that the rivet head does not come out of its ____ recess. If necessary, grind it smooth with the surface. (2) Put the new bracket plate (40) in position on the junction box. (Ref. Fig. 808/TASK 72-23-00-991-324) and (Ref. Fig. 809/TASK 72-23-00-991-325) (3) Drill the rivet holes and the riveted nut. WARNING : METAL PARTICLES FROM DRILLING CAN CAUSE DAMAGE, INJURY OR _______ IRRITATION TO YOU. USE PERSONAL PROTECTION EQUIPMENT.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 843 Feb 01/09
C F M 56-5B
R R
Location of the Riveted Holes Figure 808/TASK 72-23-00-991-324- 13 (SHEET 1)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 844 Nov 01/08
C F M 56-5B
R R
Location of the Riveted Holes Figure 808/TASK 72-23-00-991-324- 23 (SHEET 2)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 845 Nov 01/08
C F M 56-5B
R R
Location of the Riveted Holes Figure 808/TASK 72-23-00-991-324- 33 (SHEET 3)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 846 Nov 01/08
C F M 56-5B
R R
Dimension Information of Position Figure 809/TASK 72-23-00-991-325
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 847 Nov 01/08
C F M 56-5B (a) Drill at the same time the rivet holes in the junction box and in the bracket plate (40) (Ref. SPM 70-43-32-390-006). (Ref. Fig. 808/TASK 72-23-00-991-324) (4) Do a fluorescent inspection of the holes (Ref. SPM 70-32-21-230-010). No crack is permitted. (5) Do a hand blending of the contact areas (Ref. SPM 70-41-11-350-009). (6) Remove the grease from the junction box contact area and the bracket plate (Ref. SPM 70-21-12-110-003). (7) Put the new bracket plate (40) in position and rivet it with six rivets (30) (Ref. SPM 70-43-32-390-006). 5. Close-up ________ Subtask 72-23-00-410-126 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): - FOR 1000EM1 437AL, 438AR - FOR 1000EM2 447AL, 448AR. (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 848 Feb 01/09
C F M 56-5B HP COMPRESSOR SECTION - DESCRIPTION AND OPERATION _________________________________________________ 1. _______ General (Ref. Fig. 001) The major components of the compressor are : compressor rotor and compressor stator. The front of the compressor stator is supported by the fan frame and the front of the compressor rotor is supported by the No.3 bearing in the fan frame. The rear of the compressor stator is attached to the combustion case and the rear of the compressor rotor is attached to the HPT rotor to form the core rotor. The rear of the core rotor is supported by the No.4 bearing. A portion of the fan discharge airflow passes thru the booster to the compressor. Compression is progressive as the primary airflow moves from stage through the axial compressor. Air passes through successive stages of compressor rotor blades and compressor stator vanes, being compressed as it passes from stage to stage. After passing through 9 stages of blades, the air has been compressed. The inlet guide vanes and the first 3 stages of the stator are variable, and change their angular position as a function of compressor inlet temperature and engine speed. The purpose of this variability is to optimize efficiency and stall margin for engine speed, compressor inlet temperature and pressure conditions.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-30-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
HP Compressor Section Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-30-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B HP COMPRESSOR SECTION - REMOVAL/INSTALLATION ____________________________________________ TASK 72-30-00-920-001 Discard Life Limited HP Compressor rotating parts 1. __________________ Reason for the Job Refer to the MPD TASK: 723000-C1 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-00-00-400-042 ESM 051102 ESM 723104 ESM 723105 ESM 723106 ESM 723107 ESM 723108
Removal of the Power Plant Installation of the Power Plant
3. __________ Job Set-up Subtask 72-30-00-010-052 A. Remove the engine (Ref. TASK 71-00-00-000-042). 4. Procedure _________ Subtask 72-30-00-020-052 A. Remove and discard life - (Ref. ESM 723104) for - (Ref. ESM 723105) for - (Ref. ESM 723106) for - (Ref. ESM 723107) for - (Ref. ESM 723108) for
limited the HPC the HPC the HPC the HPC the HPC
parts of the high pressure compressor: Stage 1-2 Spool Stage 3 Disk Stage 4-9 Spool rotor Shaft CDP Seal
NOTE : (Ref. ESM 051102) for time limits. ____
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Page 401 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-30-00-410-052 A. Install the engine (Ref. TASK 71-00-00-400-042).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-30-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Nov 01/08
C F M 56-5B HPC ROTOR ASSEMBLY - DESCRIPTION AND OPERATION ______________________________________________ 1. _______ General (Ref. Fig. 001) The compressor rotor (C/R) is a 9-stage, high-speed, unitized spool-disk structure. The rotor consists of 5 major parts : front shaft, stages 1-2 spool, stage 3 disk, stages 4-9 spool, and C/R rear (compressor discharge pressure (CDP)) rotating air seal. Spools are assembled by inertia welding. The front shaft, disk, and spools are joined at a single bolted joint to form a smooth, rigid unit. Interfering rabbeted diameters are used for proper positioning of parts and for rotor stability. 2. ___________ Description (Ref. Fig. 001, 002) A. Front Shaft The front shaft is bolted between stages 1-2 spool and stage 3 disk, and is the forward support for the rotor. The shaft is splined to and secured to the inlet gearbox (IGB) horizontal bevel gear by a coupling nut. The IGB contains the thrust bearing for the core engine. The front shaft is made of titanium alloy. B. Disk and Spools The stages 1-2 spool and stage 3 disk are made of titanium alloy forgings and retain the stages 1, 2, and 3 blades in axial slots. The stages 4-9 spool is made of a nickel alloy and retains stages 4 through 9 blades in circumferential grooves. The disk and stages 4-9 spool are internally cooled by low pressure compressor (booster) discharge air which enters the rotor through holes in the front shaft. Abrasive coated seals between the rotor blade stages improve compressor performance. C. Blades Blades in stages 1, 2 and 3 are made of a titanium alloy. Blades in stages 4 through 9 are made of a nickel alloy. The first 3 stages of blades are secured in the disk and spool axial slots by retaining rings ; blades in the stages 4-9 spool are secured in the circumferential grooves by locking lugs. All blades are replaceable without disassembling the rotor. D. Rear Seal The compressor rotor rear rotating (CDP) air seal is a one-piece nickel alloy forged part with abrasive, protective-coated sealing teeth. The seal is mounted to the aft flange of the stages 4-9 spool by a tight fitting rabbet diameter and is axially clamped by the bolts and nuts securing the forward flange of the high pressure turbine rotor to the compressor.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Compressor Rotor Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
HP Compressor Rotor Section Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B HPC ROTOR ASSEMBLY - INSPECTION/CHECK _____________________________________ TASK 72-31-00-290-002 Inspection of the High Pressure Compressor Rotor Assembly 1. __________________ Reason for the Job Inspection of a high pressure compressor rotor (HPCR) with the stator case installed is limited to those areas that can be seen with a rigid borescope. There are nine borescope ports (S1 through S9) in the compressor stator case, between the 4 and 5 oclock position, aft looking forward. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No No
specific specific specific specific specific specific
No specific No specific 856A1084 856A1320 856A1321 856A1322 856A1323 856A1488
1 1 1 1 1 1
caps on the cart hoses container warning notice 0.75 in. square drive socket 2ft. long breaker bar Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) CART-STATOR ACTUATOR BORESCOPE-KIT FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE MOTOR, DRIVE - CORE ENGINE ROTATION
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Feb 01/10
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R
71-00-00-710-001 71-00-00-710-006 71-13-00-010-040 71-13-00-410-040 72-00-00-200-005 72-00-00-200-025 72-31-00-300-002 72-31-00-300-004 72-63-00-000-002 72-63-00-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-000-002 80-11-10-400-002 NTM 720000 72-31-00-991-300 72-31-00-991-301 72-31-00-991-302 72-31-00-991-309 72-31-00-991-306 72-31-00-991-307 72-31-00-991-308
Dry Motoring Check Minimum Idle Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Over-Serviceable-Limit Extensions Repair of Broken Borescope Plug Blend Repair of the High Pressure Compressor (HPC) Rotor Blades Stages 1-9 Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. Fig. Fig. Fig. Fig. Fig. Fig.
601 602 603 604 605 606 607
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-31-00-991-310 72-31-00-991-315
Fig. 608 Fig. 609
3. __________ Job Set-up Subtask 72-31-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-31-00-010-055 B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. Subtask 72-31-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-31-00-010-056 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-31-00-991-300, 602/TASK 72-31-00-991-301, 603/TASK 72-31-00-991-302, 604/TASK 72-31-00-991-309, 605/TASK 72-31-00-991-306, 606/TASK 72-31-00-991-307, 607/TASK 72-31-00-991-308, 608/TASK 72-31-00-991310) Subtask 72-31-00-410-055 A. Do a borescope installation: (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure that the borescope or fiberscope and light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Install the tools to turn the core engine. NOTE : The core engine may be turned using a breaker bar (see step ____ (a)) or with a drive motor (see step (b)). (a) To turn the core manually with a breaker bar, do the steps that follow: 1 _
Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter. (Ref. TASK 72-63-00-000-002)
2 _
Install a 0.75 in. square drive socket with a 2ft. long breaker bar into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward). NOTE : To turn the core engine CW, the handcranking drive must ____ be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 _
Remove the starter (Ref. TASK 80-11-10-000-002).
2 _
Install the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P0/P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad drive shaft and engage the splines. NOTE : The tool must be installed in the horizontal position ____ with the air hoses to the rear.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
Core Rotation Drive Motor Installation Figure 601/TASK 72-31-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
VSV System Connections at the HMU Figure 602/TASK 72-31-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Borescope Ports of the High-Pressure Compressor Figure 603/TASK 72-31-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B
Removal of IGV Borescope Plug (S1) Figure 604/TASK 72-31-00-991-309 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B
HPC Rotor Indexing to Zero Figure 605/TASK 72-31-00-991-306 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B
Locally Manufactured Alignment Rod Figure 606/TASK 72-31-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B
Locally Manufactured Deep Socket Wrench Figure 607/TASK 72-31-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B
Compressor Blades Inspection Figure 608/TASK 72-31-00-991-310- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B
Compressor Blades Inspection Figure 608/TASK 72-31-00-991-310- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B 3 _
Turn the tool until the captive bolts align with the gearbox bolt holes.
4 _
Tighten the two captive bolts by hand.
5 _
Install the clamp to secure the drive motor.
6 _
Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 _
Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(3) Actuate the VSV system to the full open position as follows: WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE YOUR _______ CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. CAUTION : USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE NIPPLE _______ WHEN YOU DISCONNECT/CONNECT FUEL LINES ON NIPPLES. NOTE : Put a container under the HMU to catch fuel released when fuel ____ lines are disconnected. NOTE : If the CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) is ____ not available, the VSV system may be actuated to the full open position on an exceptional basis by dry motoring the engine (Ref. TASK 71-00-00-710-001). (a) Disconnect the VSV rod-end and head-end flex-hoses from the hydromechanical unit (HMU). (b) Remove the caps from the CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04). (c) Attach the rod-end and head-end hoses from the cart to rod-end and head-end connectors of the rod-end and head-end hoses you disconnected from the HMU. (d) Actuate the variable stator system CAUTION : DO NOT LET THE PRESSURE BE MORE THAN 300PSI (20.68BAR) _______ OR YOU WILL CAUSE DAMAGE TO ENGINE PARTS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B 1 _
Pump the actuator until the VSV system is at the open position (actuator rod retracted).
(e) Disconnect the CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04). WARNING : PRESSURE OF UP TO 300 PSI. (20.68 BAR) EXISTS IN THE _______ SUPPLY LINES. RELIEVE PRESSURE TO PREVENT INJURY WHEN DISCONNECTING FITTINGS. 1 _
Follow the instructions for use of the CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) to relieve any static pressure existing in the supply hoses. Gages on the CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) should read zero and the selector valve should be in the OFF position.
2 _
Disconnect the hoses of the cart from the rod-end and head-end hoses.
3 _
Install the caps on the cart hoses.
(f) Connect the rod-end and head-end hoses to the HMU. CAUTION : USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE _______ NIPPLE WHEN YOU DISCONNECT/CONNECT FUEL LINES ON NIPPLES. 1 _
TORQUE the head-end hose to between 450 and 550 lbf.in (5.08 and 6.21 m.daN).
2 _
TORQUE the rod-end hose to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
(4) Remove the borescope plugs from the stages to be inspected as follows. Tag each borescope plug to identify the stage from which it was removed: NOTE : The borescope plugs are located along the compressor case ____ between the 4 and 5 oclock positions, aft looking forward. (a) Cut and remove the lockwire from the borescope plugs to be removed. (b) Remove the IGV borescope plug (S1), if necessary, as follows: 1 _
Remove the two screws (20) that attach the borescope access blanking plate (10) at 5 oclock, aft looking forward, on the fan frame inner flange.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B 2 _
Remove the borescope access blanking plate (10).
3 _
Remove the IGV borescope plug (S1).
4 _
Tag the plug to ensure it will be reinstalled in the correct port.
(c) Remove the stage 1 through stage 5 borescope plugs (S2 through S6), as necessary. Tag each plug to ensure it will be reinstalled in the correct port. (d) Remove the stage 6, 7 and 8 borescope plugs (S7 through S9), as necessary, as follows: CAUTION : DO NOT PUT MORE THAN 280 lbf.in. (31.64 m.daN) OF _______ TORQUE ON THE 6TH, 7TH AND 8TH STAGE BOROSCOPE PLUGS WHEN YOU REMOVE THEM, OR THE INNER PLUG SHAFT COULD BREAK. 1 _
Loosen the outer borescope plug.
2 _
Pull the outer borescope plug straight out as far as possible to engage the internal shaft spline.
3 _
Remove the borescope plug.
4 _
Tag each plug to ensure it will be reinstalled in the correct port.
5 _
If the borescope plug is broken or if the inner plug does not come out with the outer plug, remove the broken inner plug with a deep socket wrench (Ref. TASK 72-31-00-300-002).
(5) Connect the fiber light cable to the fiberscope (green or blue band) from the BORESCOPE-KIT (856A1320P04 or P05) and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P01 through P07). Turn the light source on. (6) If you use the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02) to turn the core engine, do an inspection of the compressor blades as follows. If you use the breaker bar to turn the core, go to step (7). (a) Index the core engine to zero as follows: 1 _
Put the fiberscope into the stage 3 borescope port (S4) and look aft to the stage 4 compressor blade platform.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/08
C F M 56-5B 2 _
While you look in the fiberscope turn the core clockwise (CW), as seen from the front of the engine, using the MOTOR, DRIVE CORE ENGINE ROTATION (856A1488P01 or P02).
3 _
Turn the core until you see the first blade slot locking lug.
4 _
Continue to turn the core until you see the second locking lug. The second locking lug is 2 blades past the first locking lug.
5 _
Align the leading edge of the first blade past the second locking lug with the leading edge of the nearest stage 4 vane. This is the zero index point and blade number 1.
6 _
Set the pointer on the protractor to the zero degree mark. The core engine is now set to the zero index point for inspection of all stages of the compressor rotor.
(b) Do an inspection of stage 4 compressor blades while you turn the core engine using the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02). (c) Use the limits found in step 4.B. (d) Remove the fiberscope (e) Insert the fiberscope in the borescope plug of the next stage to be inspected and repeat step (b) thru (d) for the other stages to be inspected. (f) If the vane segments in stages 6, 7 and 8 have moved to partially cover the borescope port, do step (8). (7) If you use the breaker bar to turn the core engine, do an inspection of the compressor blades as follows. (a) Insert the fiberscope in the borescope port of the stage you want to inspect. (b) Do an inspection of the compressor blade you see. Use the limits found in the inspection table. (c) Rotate the core engine so that you can see the next blade. Use the breaker bar to turn the core engine clockwise (CW). NOTE : To turn the core engine CW, the handcranking drive must be ____ turned counterclockwise (CCW).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Nov 01/08
C F M 56-5B (d) Repeat steps (b) and (c) until you have inspected all of the blades in that stage. Count the blades as you inspect them to make sure all of the compressor blades are inspected. The number of blades in each stage is: 1 _
Stage 1 : 38 blades
2 _
Stage 2 : 53 blades
3 _
Stage 3 : 60 blades
4 _
Stage 4 : 68 blades
5 _
Stage 5 : 75 blades
6 _
Stage 6 : 82 blades
7 _
Stage 7 : 82 blades
8 _
Stage 8 : 80 blades
9 _
Stage 9 : 76 blades
(e) Repeat steps (a) thru (d) for the other stages to be inspected. (f) If the vane segments in stages 6, 7 and 8 have moved to partially cover the borescope holes (S7 through S9), do step (8). (8) To inspect the stages 6, 7, 8 and 9 blades when the vane segments have moved to partially cover the borescope holes, use the alternatives that follow: CAUTION : MAKE SURE THE FLEXIBLE BORESCOPE DOES NOT GET CAUGHT IN THE _______ BLADES WHILE YOU TURN THE CORE. (a) If the diameter of the borescope holes are larger than 0.24 in. (6.01 mm) , do the borescope inspection using the FIBERSCOPE SET (856A1321P01 through P03). (b) If the diameter of the borescope holes are less than 0.24 in. (6.01 mm) , do the following steps: 1 _
Put a tapered rod in the borescope hole. The rod must be made from 0.37 in. (9.40 mm) diameter aluminum, 18 in. (0.46 mm) long, with a 4 in. (101.60 mm) taper at one end. The tapered end must be rounded to 0.062 in. (1.57 mm) radius, accurate radius not necessary.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
C F M 56-5B 2 _
Apply a light downward force on the end of the tapered rod to move the vane segments.
(c) If the stage 7 borescope hole (S8) is not fully open, inspect the aft part of the compressor through the stage 8 borescope hole (S9). If the stage 8 borescope hole (S9) is not fully open, try to do the inspection through the stage 6 borescope port (S7). Subtask 72-31-00-290-051 B. Inspect the blades to the limits that follow: (Ref. Fig. 608/TASK 72-31-00-991-310, 609/TASK 72-31-00-991-315) NOTE : If you find airfoil damage, we recommend that you do a borescope ____ inspection of the stage 5 booster blades and the abradable (Refer to CFM SB 72-03910). NOTE : The depth of a defect such as a nick is measured along the axis of ____ the damage unless otherwise noted. NOTE : Unless otherwise identified, all damage limits for high pressure ____ compressor blades are the same for the different blade configurations. ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Stages 1-4 compressor blades: A. Cracks in Dim. A and tip
Any number of radial cracks within 0.30 in. (7.6 mm) of the leading or trailing edge, up to 0.25 in. (6.4 mm) in length are serviceable
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
Any number of radial cracks more than 0.30 in. (7.6 mm) from the leading or trailing edge, up to 0.10 in. (2.5 mm) in length are serviceable
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Page 619 Nov 01/08
C F M 56-5B
R
Stage 1-3 VSV Shroud Rubbing Figure 609/TASK 72-31-00-991-315
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------Any number of chord-wise See limit extensions cracks, up to 0.30 in. (Ref. TASK 72-00-00-200(7.6 mm) from the tip, 025) or repair (Ref. TASK up to 0.2 in. (5.1 mm) 72-31-00-300-004). in length are serviceable B. Missing or chipped erosion coating
Any amount
C. Tears on the leading and trailing edge found in Dim. B
Not serviceable
See repair (Ref. TASK 7231-00-300-004).
Any number if the damage is less than 0.04 in. (1.0 mm)
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
R R R R R
D. Nicks, missing material and erosion on the leading and trailing edge found in Dim. B, il the HPC blade is not a Tech Insertion Stage 4 blade (PN P394XXX)
R R R R R R R R R R
E. Nicks, missing material and erosion on the leading and trailing edge found in Dim. B, if the HPC blade is a Tech Insertion Stage 4 blade (PN P394XXX)
Any number, if the damage is less than 0.030 in. (0.8 mm) in depth
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004)
R
F. Dents on the leading or trailing edge found in Dim. B
Any amount if the damage is less than 0.04 in. (1.0 mm) in depth or up to 0.06 in. (1.5 mm) deflection from the original contour
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 621 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Nicks, dents and Any number if less than See limit extensions tears on the 0.25 in. (6.4 mm) in (Ref. TASK 72-00-00-200leading and depth 025). trailing edge tip corners in Dim. A
R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R
H. Missing material and erosion at the leading and trailing edge tip corners in Dim. A and tip
a) Individual blades with missing material more than 0.30 x 0.30 inch (7.6 x 7.6 mm) on both leading and trailing edges are not permitted. b) Any number of blades for each stage 1 thru 4, up to 0.30 x 0.30 inch (7.6 x 7.6 mm) if the downstream damage is serviceable. c) For stage 2, a maximum of 4 blades up to 0.40 x 0.40 inch (10.2 x 10.2mm), and 46 blades up to 0.30 x 0.30 inch (7.6 x 7.6mm) for total of 50 blades with missing tip corners. d) For stage 3, a maximum of 5 blades up to 0.40 x 0.40 inch (10.2 x 10.2mm) and 51 blades up to 0.30 x 0.30 inch (7.6 x 7.6 mm) for a total of total of 56 blades with missing tip corners.
See limit extensions (Ref. TASK 72-00-00-200025).
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Feb 01/10
R R R R R R R R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------e) For stage 4, maximum of 6 blades up to 0.40 x 0.40 inch (10.2 x 10.2mm) and 57 blades up to 0.30 x 0.30 inch (7.6 x 7.6 mm) for a total of total of 63 blades with missing tip corners
R
J. Curl on the end of the airfoil
Up to 25% of chord, maximum radial length of 0.30 in. (7.6 mm) when it does not engage the stationary parts during operation
R
K. Nicks, dents and scratches of the airfoil root radius (does not include the trailing edge root radius of stage 2 and stage 3).
Any amount, if less than 0.003 in. (0.08 mm) in depth. Scratches parallel with the platform are not serviceable.
R
L. Nicks, dents and scratches of the trailing edge root radius of stage 2 and stage 3.
Any amount, if less than 0.03 in. (0.8mm) in depth.
R
M. Tears on the leading and trailing edge found in the lower 25% of the airfoil (but not the root radius)
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025).
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 623 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------N. Nicks, dents and Any amount if the damage See limit extensions missing material is less than 0.03 in. (Ref. TASK 72-00-00-200on the leading and (0.76 mm) in depth. 025). trailing edge of the lower 25% of the airfoil (but not the root radius) Wear or scratches on trailing edge platform of stages 2 and 3
Any amount, if less than 0.03 in. (0.8 mm) in depth.
See limit extensions (Ref. TASK 72-00-00-200025).
Up to 25% of the blades across stages 5 through 9 can have radial cracks that are within 0.20 in. (5.1 mm) from the leading or trailing edge. These cracks can be up to 0.15 in. (3.8 mm) in length.
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
2. Stages 5-9 compressor blades: A. Cracks in Dim. A and tip
Radial cracks more than 0.20 in. (5.1 mm) from the leading or trailing edge are not serviceable Up to 25% of the blades across stages 5 through 9 can have chord-wise cracks that are no more than 0.20 in. (5.1 mm) from the tip. These cracks can be up to 0.15 in. (3.8 mm) in length B. Missing or chipped erosion coating
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
Any amount
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 624 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Nicks, tears, Any number if the damage See limit extensions missing material is less than 0.04 in. (Ref. TASK 72-00-00-200and erosion on the (1.0 mm) 025) or repair (Ref. TASK leading and 72-31-00-300-004). trailing edge found in Dim. B D. Dents on the leading and trailing edge found in Dim. B
Any number if the damage is less than 0.04 in. (1.0 mm) in depth or 0.06 in. (1.5 mm) deflection from the original contour
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
E. Nicks, dents and tears on the leading and trailing edge found in Dim. A
Any number is serviceable if the damage is less than 0.15 in. (3.8 mm)
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
F. Missing material and erosion at the leading and trailing edge tip corners
All blades, up to 0.15 x 0.15 in. (3.8 x 3.8 mm), if downstream damage is serviceable. A maximum of 25 blades across stages 5 through 9 up to 0.2 x 0.2 in. (5 x 5 mm).
See limit extensions (Ref. TASK 72-00-00-200025).
G. Curl on the end of the airfoil
Up to 50% of chord maximum radial length 0.30 in. (7.6 mm) when it does not engage the stationary parts during operation
See limit extensions (Ref. TASK 72-00-00-200025).
H. Nicks, dents and scratches on the airfoil root radius
Any amount if less than 0.003 in. (0.10 mm) in depth. Scratches parallel with the platform are not serviceable.
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, R CES
Page 625 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------J. Tears on the Not serviceable leading and trailing edge found in the lower 25% of the airfoil (but not the root radius) K. Nicks, dents and missing material on the leading and trailing edge of the lower 25% of the airfoil (but not the root radius)
Any amount if the damage is less than 0.03 in. (0.76 mm)
See limit extensions (Ref. TASK 72-00-00-200025).
3. Stages 1-9 compressor blade tips: A. Tears, nicks, dents, missing material, erosion, bending and burrs
Any number or amount is serviceable
NOTE : The blade tip is the top 0.10 in. (2.5 mm) of the blade. ____ B. Nick and dents on the airfoil center panel
Any number if the damage is not cracked on the opposite side of the airfoil
C. Erosion and scratches on the airfoil center panel
Any amount
D. Material on the blade
Any amount
4. Platform of stages 4-9 locking blades.
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, R CES
Page 626 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Clearance between Serviceable the blade platforms B. Distortion on the blades
Any amount
C. Cracks
Not serviceable
D. Shingling
Not serviceable
5. Blade locks for stages 4-9 blades: R R R
A. Cracks
One lock with a crack is permitted
See limit extensions (Ref. TASK 72-00-00-200005)
R R R R
B. Looseness
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200005)
6. Stator flow path: A. Missing rub coating
Any amount
B. Cracks which are crazed
Any amount
NOTE : The area adjacent to the borescope ports is the only rub coat you ____ can examine. 7. Stages 1 through 3 compressor stator variable vane shrouds A. Wear caused by rubbing on vanes
Any amount
8. HPC Inner Shroud Lip for:
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Wear from Any amount rotor-stator contact Subtask 72-31-00-010-057 C. Remove the borescope equipment (1) When inspection is complete, turn the lamp switch off. Keep the main light source blower on until the lamp and housing cools down. (2) Before you install the borescope plugs, put the 0.37 in. (9.40 mm) diameter tapered rod into the borescope hole. This will make sure the hole is open. (3) Install the IGV borescope plug (S1) as follows: (a) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads and pressure face of the borescope plug. (b) Put the borescope plug in the correct borescope port. Tighten the plug by hand. (c) TORQUE the plug to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (d) Wirelock the plugs with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (e) Install the borescope access blanking plate (10) using the two screws (20). (4) Install the stage 1 through 5 borescope plugs (S2 through S6) as follows: (a) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads and pressure face of the borescope plugs. (b) Install the borescope plug in the borescope port. Tighten the borescope plug by hand.
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, R CES
Page 628 Feb 01/10
C F M 56-5B (c) TORQUE the borescope plugs to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (d) Wirelock the borescope plugs. Use lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (5) Install the stage 6, 7 and 8 borescope plugs (S7, S8 and S9) as follows: CAUTION : MAKE SURE YOU FULLY SCREW THE INNER CAP IN. IF NOT FULLY _______ SCREWED IN, THE INNER CAP OF THE BORESCOPE PLUG WILL DEFLECT THE COMPRESSOR REAR CASE AS THE OUTER CAP IS TIGHTENED. THIS WILL CAUSE BINDING OF THE COMPRESSOR ROTOR. (a) Make sure the borescope port is open. Insert the 0.37 in. (9.40 mm) diameter tapered rod in the borescope port. (b) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads and pressure face of the borescope plugs. (c) Put the plug in the correct borescope port and tighten the inner plug by hand. Use the outer plug to turn the inner plug. (d) TORQUE the inner plug to between 90 and 100 lbf.in (1.01 and 1.13 m.daN). Loosen half a turn and RETORQUE to between 15 and 20 lbf.in (0.16 and 0.22 m.daN) more than the running torque. (e) Compress the plug spring and tighten the outer plug by hand. NOTE : If the inner plug is correctly installed and the threads ____ are not damaged, you can install the outer plug by hand. If the outer plug cannot be fully installed by hand, the inner plug is not correctly installed. Remove the plug and repeat steps (c), (d) and (e). (f) TORQUE the outer plug to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (g) Wirelock all 3 outer plugs together with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002).
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, R CES
Page 629 Feb 01/10
C F M 56-5B (6) Remove the tools used to rotate the core as follows: NOTE : If the breaker bar is installed, see steps (a) and (b). If the ____ drive motor is installed, see steps (c) and (d). (a) Remove the 0.75 in. square drive socket and 2ft. long breaker bar from the handcranking drive pad. (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002). (c) Remove the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02) from the starter pad of the AGB. (d) Install the starter (Ref. TASK 80-11-10-400-002). 5. Close-up ________ Subtask 72-31-00-410-057 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-31-00-710-054 B. If fuel or oil lines were disconnected, do a minimum idle leak check (Ref. TASK 71-00-00-710-006) and check for leaks. Subtask 72-31-00-440-052 C. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 630 Feb 01/10
C F M 56-5B Subtask 72-31-00-410-058 D. Close Access (1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 631 Feb 01/10
C F M 56-5B HPC ROTOR ASSEMBLY - REPAIRS ____________________________ TASK 72-31-00-300-002 Repair of Broken Borescope Plug 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No R R
specific specific specific specific
deep socket wrench warning notice T-handle 0.37 in. (9.40mm) diameter tapered Rod (locally purchased) access platform 1 m (3 ft. 3 in.) Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
No specific No specific No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
* graphite grease (Ref. 70-30-00) * Never seez-pure (Ref. 70-30-00) * Safetywire 0.032 in.(0.8 mm) dia. (Ref. 70-30-00) * Safetywire 0.032 in.(0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Feb 01/10
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-31-00-991-304 72-31-00-991-305
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 801 Fig. 802
3. __________ Job Set-up Subtask 72-31-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-31-00-010-058 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B (2) Put the access platform in position. Subtask 72-31-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-31-00-010-059 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 801/TASK 72-31-00-991-304, 802/TASK 72-31-00-991-305) Subtask 72-31-00-300-051 A. Remove the broken borescope plug as follows: (1) Remove the retaining ring, if necessary. (2) Install the locally manufactured deep socket wrench on the inner plug. (Ref. Fig. 802/TASK 72-31-00-991-305) (3) Install a T-handle on the socket wrench. (4) Remove the borescope plug. Subtask 72-31-00-420-064 B. Install a replacement borescope plug as follows: (1) Install the stage 1 through 5 borescope plugs (S1 through S5) as follows: (a) Apply graphite grease (Material No. CP2101) Never seez-pure (Material No. CP2619) to the threads and pressure face of the borescope plug. (b) Install the borescope plug in the borescope port. Tighten the borescope plug by hand.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B
Locally Manufactured Deep Socket Wrench Figure 801/TASK 72-31-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B
Broken Borescope Plug Removal Figure 802/TASK 72-31-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/08
C F M 56-5B (c) TORQUE the borescope plug to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (d) Wirelock the borescope plug. Use Safetywire 0.032 in.(0.8 mm) dia. (Material No. CP8001) or Safetywire 0.032 in.(0.8 mm) dia. (Material No. CP8002). (2) Install the stage 6, 7 and 8 borescope plugs (S6, S7 and S8) as follows: CAUTION : MAKE SURE YOU FULLY SCREW THE INNER CAP IN. IF NOT FULLY _______ SCREWED IN, THE INNER CAP OF THE BORESCOPE PLUG WILL DEFLECT THE COMPRESSOR REAR CASE AS THE OUTER CAP IS TIGHTENED. THIS WILL CAUSE BINDING OF THE COMPRESSOR ROTOR. (a) Make sure the borescope port is open. Insert 0.37 in. (9.40mm) diameter tapered Rod (locally purchased) in the borescope port. (b) Apply graphite grease (Material No. CP2101) or Never seez-pure (Material No. CP2619) to the threads and pressure face of the borescope plug. (c) Put the plug in the correct borescope port and tighten the inner plug by hand. Use the outer plug to turn the inner plug. (d) Torque the inner plug to between 75 and 85 lbf.in (0.84 and 0.96 m.daN). Loosen half a turn and RETORQUE to between 15 and 20 lbf.in (0.16 and 0.22 m.daN). (e) Compress the plug spring and tighten the outer plug by hand. NOTE : If the inner plug is correctly installed and the threads ____ are not damged, you can install the outer plug by hand. If the outer plug cannot be fully installed by hand , the inner plug is not correctly installed. Remove the plug and repeat steps (c), (d) and (e). (f) TORQUE the outer plug to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (g) Wirelock all 3 outer plugs together with Safetywire 0.032 in.(0.8 mm) dia. (Material No. CP8001) or Safetywire 0.032 in.(0.8 mm) dia. (Material No. CP8002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-31-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-31-00-440-053 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-31-00-410-059 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B TASK 72-31-00-300-004 Blend Repair of the High Pressure Compressor (HPC) Rotor Blades Stages 1-9 1. __________________ Reason for the Job This TASK is the blend repair of the HPC rotor blades with a borescope blend tool. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific R R
warning notice CCD video camera and monitor (Wolf Compatible) HPC, blade, borescope, blending tool (Wolf tool 5.08036.00) access platform 1 m (3 ft. 3 in.) Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
No specific No specific No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Feb 01/10
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-006 71-13-00-010-040 71-13-00-410-040 72-63-00-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-400-002 72-31-00-991-311 72-31-00-991-312 72-31-00-991-313 72-31-00-991-314
Minimum Idle Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Installation of the Handcranking Drive Cover Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Installation of the Pneumatic Starter Fig. 803 Fig. 804 Fig. 805 Fig. 806
3. __________ Job Set-up Subtask 72-31-00-941-057 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B Subtask 72-31-00-010-064 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-31-00-040-055 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-31-00-010-065 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 803/TASK 72-31-00-991-311, 804/TASK 72-31-00-991-312, 805/TASK 72-31-00-991-313, 806/TASK 72-31-00-991-314) Subtask 72-31-00-220-050 A. Blending Limits R R R R R R R R R R R R R R
------------------------------------------------------------------------------| INSPECT/CHECK | MAXIMUM | | | BLENDABLE LIMITS | ------------------------------------------------------------------------------| (1) Tears, nicks, dents, missing material | | | and erosion on the leading and trailing | | | edge of stages 1-4 compressor blade found | | | in Dim. B of the airfoil. | | ------------------------------------------------------------------------------| NOTE: Blend repair of the leading and trailing edges can not extend into | | the lower 25 percent of the airfoil length. | | NOTE: More than one blend in the same area is permitted if the total | | material removed from the initial contour is not more than the limit | | that can be repaired. |
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R
C F M 56-5B ------------------------------------------------------------------------------| INSPECT/CHECK | MAXIMUM | | | BLENDABLE LIMITS | ------------------------------------------------------------------------------------------------------------------------------------------------------------| (a) No maximum number of blended damage | Maximum depth is 0.060 in. | | areas. | (1.52 mm) after you blend. | ------------------------------------------------------------------------------| (2) Tears, nicks, dents, missing material | | | and erosion on the leading and trailing | | | edge of stages 1-4 compressor blade | | | found in Dim. A. | | ------------------------------------------------------------------------------| NOTE: More than one blend in the same area is permitted if the total | | material removed from the initial contour is not more than the limit | | that can be repaired. | ------------------------------------------------------------------------------| (a) No maximum number of blended damage | Maximum blended area is 0.30 | | areas. | x 0.30 in. (7.6 x 7.6 mm) | | | after you blend. | ------------------------------------------------------------------------------| (b) No maximum number of dents. | Maximum depth is 0.080 in. | | | (2.03 mm). | | | Maximum deflection from | | | initial contour is 0.080 in. | | | (2.03 mm). | ------------------------------------------------------------------------------| (c) No maximum number of missing tip | Maximum depth is 0.300 in. | | corners. | (7.62 mm). | | | Maximum length is 0.300 in. | | | (7.62 mm). | ------------------------------------------------------------------------------| (3) Tears, nicks, dents, missing material | | | and erosion on the leading and trailing | | | edge of stages 5-9 compressor blade | | | found in dimension Dim. B of the airfoil| | ------------------------------------------------------------------------------| (a) No maximum number of blended damage | Maximum blendable limits: | | areas. | 0.060 in. (1.52 mm) max | | | depth after you blend. | ------------------------------------------------------------------------------| (4) Tears, nicks, dents, missing material | | | and erosion on the leading and trailing | | | edge of stages 5-9 compressor blade | | | found in area Dim. A. | | ------------------------------------------------------------------------------| (a) Up to 20 percent of the blades in each| Maximum area is 0.20 x 0.20 |
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B
HPC Blade Borescope Blending Tool Figure 803/TASK 72-31-00-991-311- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B
HPC Blade Borescope Blending Tool Figure 803/TASK 72-31-00-991-311- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/08
C F M 56-5B
Blend Area Example Figure 804/TASK 72-31-00-991-312 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Nov 01/08
C F M 56-5B
Borescope Blend Tool Tip Selection/Blend Tip Installation Figure 805/TASK 72-31-00-991-313 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B
Compressor Blades Inspection Areas Figure 806/TASK 72-31-00-991-314- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B
Compressor Blades Inspection Areas Figure 806/TASK 72-31-00-991-314- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
R R R R R R R R R
C F M 56-5B ------------------------------------------------------------------------------| INSPECT/CHECK | MAXIMUM | | | BLENDABLE LIMITS | ------------------------------------------------------------------------------| stage can have tears, nicks, erosion | in. (5.1 x 5.1 mm) after you | | and material that is not there. | blend. | ------------------------------------------------------------------------------| (b) No maximum number of dents. | Maximum depth is 0.080 in. | | | (2.03 mm). | | | Maximum deflection from | | | initial contour is 0.080 in. | | | (2.03 mm). | ------------------------------------------------------------------------------Subtask 72-31-00-320-053 B. Perform Blade Blending NOTE : Equivalent substitutes for the HPC, blade, borescope, blending ____ tool (Wolf tool 5.08036.00) and CCD video camera and monitor (Wolf Compatible) are not permitted unless approved by CFMI. (1) Measure the damaged area as follows: NOTE : Do not install or remove the tool tip from the drive shaft ____ head with the drive shaft head in the zero degree position. If you remove the tool tip with the drive shaft head in the zero degree position, the drive belt will disengage. (a) Put the drive shaft head (2) in the 90 degree position. Install the measuring grid tip (5) onto the drive shaft head (2) and tighten the lockscrew. This will prevent damage to the rotor blades or the blend tool. (b) Put the measuring grid tip (5) in the zero degree position and put the tool (4) into the borescope port. (c) Monitor the measuring grid tip (5), and position the drive shaft head (2) to the 90 degree position. (d) Put the measuring grid tip (5) near the HPC blade damage area. NOTE : Each square on the grid is 0.039 x 0.039 in. (1.00 x 1.00 ____ mm). The overall grid size is 0.197 x 0.197 in. (5.00 x 5.00 mm).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B (e) Write down the damage result such as defect size and location. (f) Compare the recorded blade damage against the permitted blend limits. NOTE : Make sure the blade damage is less than the permitted ____ blend limits. (g) If the damage is less than permitted limits, find the length of the blend necessary to keep the minimum blend radius. (h) Calculate the minimum blend radius at eight times the depth of the defect, or four times on both sides of the center of the blade defect. (i) Put the drive shaft head (2) in the zero degree position, and remove the tool from the borescope port. (j) Put the drive shaft head (2) in the 90 degree position. Loosen the lockscrew, and remove the measuring grid tip (5) from the drive shaft head. (2) Blade blending procedure NOTE : Do not blend into the lower 25 percent of the airfoil length ____ (L). NOTE : When blending rotor blades, blend in a radial direction in ____ relation to the engine centerline. Avoid removing metal from leading and trailing edges of airfoil sections in such a way that the edges become thin or sharp; blend so as to maintain approximately the original contour. NOTE : The finish on the blended area must be as close to the ____ original finish as possible. (a) Put the drive shaft head (2) in the 90 degree position, and use the applicable grind tip to blend the HPC stage damaged. NOTE : Use longer blend tool tips for the forward blades, and ____ shorter blend tool tips for the aft blades.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 819 Nov 01/08
C F M 56-5B (b) Apply the light source to the blend tool. NOTE : Do not install or remove a tool tip from the drive shaft ____ head with the drive shaft head in the zero degree position. If you remove the tool tip with the drive shaft head in the zero degree position, the drive belt will disengage. NOTE : Make sure the blend tip is pointed away from the operator ____ in the 90 degree position. Start the drive motor and make sure the tip rotates in the clockwise direction. If the direction of rotation is counter clockwise, check the drive belt for possible twisted installation. (3) Put the blend tool tip in the zero degree position. Put the blend tool tip into the compressor, through the borescope access port. (4) Put the primary blade edge grinding tip (1) in the borescope port, view the tool tip and move the tool tip from the zero degree to the 90 degree position. (5) Put the primary blade edge grinding tip (1) near the HPC blade defect. (6) Align the blend tool tip with the blade defect and check for correct movement across the total length of the area to be blended. NOTE : Do not start the drive motor (14) at this time. ____ NOTE : Make sure the blend tool tip correctly touches across the ____ total area to be blended. (7) Use the primary blade edge grinding tip (1) and mark the two sides of the blade defect. NOTE : The minimum blend radius should be eight times the depth of ____ the defect, or four times on both sides of the center of the blade defect. (8) Start the drive motor (14) and apply pressure to the grid tip (1) at the defect area. (a) After sufficient practice with the grind tip (1) on the blade leading edge surface, turn on the motor using the on/off switch (16) and use the motor speed control (6) to increase speed.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 820 Nov 01/08
C F M 56-5B NOTE : If the grind tip (1) does not turn freely, apply less ____ pressure to the blade edge surface. (9) During blending, make sure that you put a contour on the edge of the blade and remove the sharp edges. (10) Stop the drive motor (14). (11) Put the grind tip (1) in the zero degree position. (12) Remove the grind tip (1) from the borescope access port. (13) Put the grind tip (1) in the 90 degree position. (14) Loosen the lockscrew and remove the grind tip (1) from the drive shaft head (2). NOTE : Do not install or remove a tool tip from the drive shaft head ____ with the drive shaft head in the zero degree position. If you remove the tool tip with the drive shaft head in the zero degree position, the drive belt will disengage. (15) Install the polishing ball tip (4) onto the drive shaft head (2) and tighten the lockscrew. This will prevent damage to the rotor blades or the blend tool. NOTE : Do not install or remove a tool tip from the drive shaft head ____ with the drive shaft head in the zero degree position. If you remove the tool tip with the drive shaft head in the zero degree position, the drive belt will disengage. (16) Put the polishing ball tip (4) in the zero degree position and put it into the borescope access port. Next, put the drive shaft head (2) in the 90 degree position. (17) Polish the blended surface and stop the drive motor (14). (18) Put the polishing ball tip (4) in the zero degree position and remove from the borescope port. (19) Use the standard borescope probe 1 configuration (magnified 1 : 1 at 7 in. (177 mm)) and inspect the blended blades to make sure you removed all the defect.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 821 Nov 01/08
C F M 56-5B Subtask 72-31-00-290-052 C. Follow-Up Inspection after the Borescope Blending (1) A one-time inspection of the blended area(s) no sooner than 25 cycles and not later than 100 cycles is required. (a) No follow-up inspection is required if all blending was confirmed in Area A and on tip. 5. Close-up ________ Subtask 72-31-00-410-066 A. Close Access (1) Install the stage 1 thru 5 borescope plugs (S1 thru S5) as follows: (a) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads and pressure face of the borescope plugs. (b) Install the borescope plug in the borescope port. Tighten the borescope plug by hand. (c) TORQUE the borescope plugs to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (d) Wirelock the borescope plugs. Use lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (2) Install the stage 6, 7 and 8 borescope plugs (S6, S7 and S8) as follows: CAUTION : MAKE SURE YOU FULLY SCREW THE INNER CAP IN. IF NOT FULLY _______ SCREWED IN, THE INNER CAP OF THE BORESCOPE PLUG WILL DEFLECT THE COMPRESSOR REAR CASE AS THE OUTER CAP IS TIGHTENED. THIS WILL CAUSE BINDING OF THE COMPRESSOR ROTOR. (a) Make sure the borescope port is open. Insert the 0.37 in. (9.40 mm) diameter tapered rod in the borescope port. (b) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads and pressure face of the borescope plugs.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 822 Nov 01/08
C F M 56-5B (c) Put the plug in the correct borescope port and tighten the inner plug by hand. Use the outer plug to turn the inner plug. (d) TORQUE the inner plug to between 90 and 100 lbf.in (1.01 and 1.13 m.daN). Loosen half a turn and RETORQUE to between 15 and 20 lbf.in (0.16 and 0.22 m.daN) more than the running torque. (e) Compress the plug spring and tighten the outer plug by hand. NOTE : If the inner plug is correctly installed and the threads ____ are not damaged, you can install the outer plug by hand. If the outer plug cannot be fully installed by hand, the inner plug is not correctly installed. Remove the plug and repeat steps (c), (d) and (e). (f) TORQUE the outer plug to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (g) Wirelock all 3 outer plugs together with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (3) Remove the tool used to rotate the core. (a) Remove the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02) from the starter pad of the AGB if installed. (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002) if removed. (c) Install the starter (Ref. TASK 80-11-10-400-002) if removed. (4) Make sure that the work area is clean and clear of tool(s) and other items. (5) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-31-00-440-055 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 823 Nov 01/08
C F M 56-5B Subtask 72-31-00-710-051 C. Test CAUTION : DO NOT OPERATE THE ENGINE WITHOUT A CORRECTLY INSTALLED COVER _______ ON THE N2 HANDCRANKING DRIVE PAD. IF THE COVER IS NOT INSTALLED CORRECTLY, THE ENGINE CAN HAVE OIL LEAKAGE. THIS CAN CAUSE ENGINE FAILURE. (1) Do a minimum idle check (Ref. TASK 71-00-00-710-006) and check for leaks. Subtask 72-31-00-410-067 D. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 824 Nov 01/08
C F M 56-5B HPC FRONT STATOR ASSEMBLY - DESCRIPTION AND OPERATION _____________________________________________________ 1. _______ General The compressor front stator consists of the front casing halves, the inlet guide vanes (IGV), and the first 5 stages of stator vanes. 2. ___________ Description (Ref. Fig. 001, 002) A. Front Stator Casing The front case halves are made from M152 steel forging. The stage 1-5 flowpath is a machined, integral part of the case, instead of liners. The lower halves of the front casing have ports for the inspection of the internal areas. The front stator forms the load carrying structure between the fan frame and the combustion case. Bleed air is taken from the pads on the front case for the use of the customer. The bleed air is also used for high pressure turbine cooling and clearance control and for low pressure turbine cooling. B. Vanes The IGV and the stages 1 through 3 vanes are variable ; the stages 4 and 5 vanes are fixed. All vanes are made of steel. The fixed vanes, in stages 4 and 5, are fabricated into segments consisting of several vanes each. All stages of vanes have honeycomb shrouds on their inner diameter. The shrouds together with the rotor seal teeth, form interstage seals to prevent flowpath recirculation. C. Variable Vane Actuation Actuation of the variable vanes is accomplished with hydraulically actuated bellcrank assemblies mounted on the front compressor stator at the 2 and 8 oclock positions. Fixed linkages connect the bellcranks to actuation rings. Lever arms attached to the variable vanes connect to the actuation rings. Fuel from the hydromechanical unit (HMU) operates the hydraulic actuators.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Compressor Front Stator Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
HP Compressor Stator Section Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B HPC FRONT STATOR ASSEMBLY - INSPECTION/CHECK ____________________________________________ TASK 72-32-00-210-002 Inspection/Check of the HPC Front Stator Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-13-00-010-040 71-13-00-410-040 72-00-00-200-009 72-00-00-200-025 72-32-00-000-004 72-32-00-400-004 72-32-00-960-002 75-32-10-000-002 75-32-10-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-32-00-991-300 72-32-00-991-304
Removal of the Power Plant Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Off-Schedule Vane Replacement Over-Serviceable-Limit Extensions Removal of the Actuation Ring Connecting Links Installation of the Actuation Ring Connecting Links Replacement of the Actuation Ring Flanged Bushing (Stages 1 and 2) Removal of the Variable Stator Vane (VSV) Actuators Installation of the Variable Stator Vane (VSV) Actuators Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-32-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-32-00-010-058 B. Get access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-32-00-040-055 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-32-00-010-059 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-32-00-991-300, 602/TASK 72-32-00-991-304) Subtask 72-32-00-210-052 A. Inspection/Check of the HPC Front Stator Assembly CAUTION : LEVER ARM DISTRESS OR MISASSEMBLY RESULTING IN VANE SCHEDULING _______ ERRORS IN EXCESS OF 4 DEGREES REQUIRES SPECIAL INSPECTION/ DISPOSITION OF COMPRESSOR ROTOR BLADES. R
(1) Inspect the following areas: (a) If vane scheduling errors occur (Ref. TASK 72-00-00-200-009). ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Casing for : - Cracks
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
- Nicks, pits, scores and scratches
Any number, any length, 0.010 in. (0.25 mm) deep after removal of high metal
See limit extensions (Ref. TASK 72-00-00-200025).
- Cracks (or broken)
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
- Distortion, bends, twists or distress
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
- Separation
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025).
2. Vane actuation rings for :
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Aug 01/09
C F M 56-5B
Compressor Front Stator Assembly-Inspection Figure 601/TASK 72-32-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-32-00 CES
Page 605 Nov 01/03
C F M 56-5B
Stator Vane ID to Rotor Contact Figure 602/TASK 72-32-00-991-304- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Stator Vane ID to Rotor Contact Figure 602/TASK 72-32-00-991-304- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Damaged or broken Bushing body is intact lever arm bushing and provides 360 degrees support to lever arm pin - Missing bushings on Stages 1 and 2
Not serviceable
- Missing or broken bushing legs
Any amount
See Repair Procedures (Ref. TASK 72-32-00-960002)
3. Actuation ring connector for : - Cracks (or broken) one side only
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
- Cracks (or broken) both sides
Not serviceable
R R R
- Bushings with broken or missing legs
Any amount
R R R
- Missing bushings
Not serviceable
Replace actuation ring (Ref. TASK 72-32-00-000004) and (Ref. TASK 72-3200-400-004)
- Broken or bent
Not serviceable
Remove engine for replacement of HPC rotor blades in one stage forward of and 2 stages aft of stage with defective lever arms
- Cracked
Not serviceable
Replace lever arm (Ref. TASK 72-32-00-000-
4. Vane lever arms, IGVs and stage 3 for :
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------004) and (Ref. TASK 72-3200-400-004) - Nicks, dents and scratches
Area A not serviceable Area B 0.010 in. (0.25 mm) after removal of high metal provided bottom of defect is not sharp pointed. Area C (not including pin) 0.002 in. (0.05 mm) deep.
5. Vane lever arms, stage 1 and 2 for : (Ref. Fig. 601/TASK 72-32-00-991-300) - Broken or bent
Not serviceable
Remove engine for replacement of HPC rotor blades in one stage forward of and 2 stages aft of stage with defective lever arms
- Cracked
Not serviceable
Remove engine for replacement of cracked lever arm
- Nicks, dents and scratches
Area A not serviceable Area B 0.010 in. (0.25 mm) after removal of high metal provided bottom of defect is not sharp pointed. Area C (not including pin) 0.002 in. ( 0.05 mm) deep.
6. Vane assembly, IGVs and stage 3 for : - Looseness
Any amount of radial and side movement provided bushing not missing. No metal to metal contact allowed. (Listen for
See limit extensions (Ref. TASK 72-00-00-200025)
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, R CES
Page 609 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------metallic sound while shaking vane stem) 7. Vane assembly, stages 1 and 2 for : - Looseness
Any amount of radial and side movement provided bushing not missing. No metal to metal contact allowed. (Listen for metallic sound while shaking vane stem)
See limit extensions (Ref. TASK 72-00-00-200025)
- Cracks
Not serviceable
Remove the engine for the replacement of the bellcrank assembly (Ref. TASK 71-00-00-000042) or Replace vane actuation assembly (Ref. TASK 75-3210-000-002) and (Ref. TASK 75-32-10-400-002)
- Nicks, pits, scores and scratches
Any number, any length 0.030 in. (0.76 mm) deep after removal of high metal
Replace vane actuation system (Ref. TASK 75-3210-000-002) and (Ref. TASK 75-32-10-400-002)
0.010 in. (0.25 mm) diametral
Remove the engine for the replacement of the bellcrank assembly (Ref. TASK 71-00-00-000042)
8. Vane actuation system (bellcrank assembly) for :
9. Spherical bearings for : - Looseness of ball in race
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, R CES
Page 610 Nov 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-32-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-32-00-440-053 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-32-00-410-057 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B HPC FRONT STATOR ASSEMBLY - REPAIRS ___________________________________ TASK 72-32-00-000-003 Removal of the Inlet Guide Vane (IGV) and Stage 3 Vane Lever Arms or Bushings 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1012 856A1051
warning notice access platform 1 m (3 ft. 3 in.) 1 LEVER,COUNTERTORQUE-CPRSR STATOR VANE ACTUATION ARM 1 PULLER,ARM-COMPRESSOR STATOR ACTUATION
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 78-30-00-481-041 78-36-00-010-040 72-32-00-991-301 72-32-00-991-302
Opening of the Fan Cowl Doors Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Fig. 801 Fig. 802
3. __________ Job Set-up Subtask 72-32-00-941-054 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-32-00-010-060 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-32-00-040-056 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-32-00-010-061 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 801/TASK 72-32-00-991-301, 802/TASK 72-32-00-991-302) Subtask 72-32-00-020-052 A. Remove the IGV and stage 3 lever arms and bushings. (1) Hold the lever arm with LEVER,COUNTERTORQUE-CPRSR STATOR VANE ACTUATION ARM (856A1012G01), while you loosen the vane stem nut. Do not let the vane turn.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B
Replacement of Lever Arm and/or Vane Bushing Figure 801/TASK 72-32-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B
IGV and Stage 3 Lever Arm Engaged Correctly and Incorrectly Figure 802/TASK 72-32-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B (2) Remove the nut and washer from the vane. (3) Remove the lever arm from the vane with PULLER,ARM-COMPRESSOR STATOR ACTUATION (856A1051G01). (4) Remove the bushing from the stator case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/08
C F M 56-5B TASK 72-32-00-400-003 Installation of the Inlet Guide Vane (IGV) and Stage 3 Vane Lever Arms or Bushings 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific 856A1012
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 LEVER,COUNTERTORQUE-CPRSR STATOR VANE ACTUATION ARM
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-32-00-991-301 72-32-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 801 Fig. 802
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-32-00-860-052 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-32-00-010-064 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-32-00-040-058 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-32-00-420-052 A. Install the IGV and stage 3 lever arms. CAUTION : CORRECTLY ALIGN THE WITNESS MARK ON THE VANE STEM WITH THE _______ LEVER ARM. BLADE DAMAGE CAN OCCUR IF THE VANE STEM IS NOT CORRECTLY ALIGNED. (1) Install the replacement bushing in the stator case. (2) Install the replacement lever arms on the vane while you engage the lever arm pin into the actuation ring. (3) Make sure the lever arm fully engages the vane stem flats. (4) Install the washer and nut on the vane stem. Hold the lever arm with LEVER,COUNTERTORQUE-CPRSR STATOR VANE ACTUATION ARM (856A1012G01), while you tighten the nut. (5) TORQUE the nut to between 55 and 70 lbf.in (0.62 and 0.79 m.daN). Do not let the vane turn. Subtask 72-32-00-210-053 B. Do a visual check. (1) The lever arm must fully engage the vane stem flats. (Ref. Fig. 801/TASK 72-32-00-991-301) (2) A minimum of 2 vane stem threads must be above the nut. (Ref. Fig. 802/TASK 72-32-00-991-302)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-32-00-410-058 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-32-00-440-054 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-32-00-410-059 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B TASK 72-32-00-000-004 Removal of the Actuation Ring Connecting Links 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 78-30-00-481-041 78-36-00-010-040 72-32-00-991-303
Opening of the Fan Cowl Doors Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Fig. 803
3. __________ Job Set-up Subtask 72-32-00-941-055 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-32-00-010-062 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-32-00-040-057 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-32-00-010-063 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 803/TASK 72-32-00-991-303) Subtask 72-32-00-020-053 A. Remove the connecting link. (1) Disconnect the tie rod from the clevis of the defective connecting link as follows: NOTE : Do not adjust the tie rod. ____ (a) Remove the nut.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B
Replacement of the Actuation Ring Connecting Links Figure 803/TASK 72-32-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B (b) Remove the D-head bolt. (2) Cut and remove lockire, remove the bolts that hold the connecting link to the actuation ring. NOTE : There is a locating pin at each end of the connecting link. ____ The straight pin stays in the actuation ring segment. The pin with the head comes out with the connecting link.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/08
C F M 56-5B TASK 72-32-00-400-004 Installation of the Actuation Ring Connecting Links 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2365
Material No.
CP8001
USA MIL-T-5544 Graphite grease (Ref. 70-30-00) USA MIL-S-22473 Grade A Loctite 290 (Ref. 70-30-00) * Lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-32-00-991-303
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 803
3. __________ Job Set-up Subtask 72-32-00-860-053 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-32-00-010-065 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-32-00-040-059 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041). 4. Procedure _________ (Ref. Fig. 803/TASK 72-32-00-991-303) Subtask 72-32-00-420-053 A. Install the connecting link. (1) If the straight pin comes out with the connecting link, apply Loctite 290 (Material No. CP2365) to the end of the straight pin that goes in the actuation ring. (2) Install the straight pin in the actuation ring. NOTE : On the right side, the pin goes in the top segment of the ____ actuation ring. On the left side, the pin goes in the lower segment of the actuation ring. (3) Install the connecting link to the actuation ring segments. Make sure the straight pin fully engages the hole in the actuation ring and the lever arms are correctly engaged in the connecting link bushings. (4) Install the headed pin in the connecting link and actuation ring segment. (5) Apply Graphite grease (Material No. CP2101) to the threads and friction surface of the bolts. (6) Install the bolts. TORQUE the bolts to between 55 and 70 lbf.in (0.62 and 0.79 m.daN). (7) Make sure that the straight pin is correctly installed in the actuation ring. Use lockwire through the inspection hole of the connecting link to feel for the pin.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B (8) Do a visual check: CAUTION : BLADE DAMAGE CAN OCCUR IF THE LEVER ARMS ARE NOT CORRECTLY _______ ENGAGED. (a) Make sure all of the lever arms are correctly engaged in the connecting link bushings. (9) Wirelock the bolts: CAUTION : MAKE SURE THE D-HEAD BOLT IS SEATED IN THE RECESS OF THE _______ CONNECTING LINK. (a) Use the Lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001). (10) Apply Graphite grease (Material No. CP2101) to the threads of the D-head bolt. (11) Install the tie rod in the connecting link with the D-head bolt and nut. The bolt head goes aft for IVG and forward for stages 1, 2, and 3. (12) Install the nut and TORQUE to between 105 and 115 lbf.in (1.18 and 1.29 m.daN). NOTE : Do not adjust the tie rod. ____ 5. Close-up ________ Subtask 72-32-00-410-060 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-32-00-440-055 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
C F M 56-5B Subtask 72-32-00-410-061 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the warning notice(s). (3) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B TASK 72-32-00-960-002 Replacement of the Actuation Ring Flanged Bushing (Stages 1 and 2) 1. __________________ Reason for the Job To replace missing actuation ring bushings. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2267
* RTV 106 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-32-00-991-305
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 804
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 819 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-32-00-941-057 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-32-00-010-068 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-32-00-040-061 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-32-00-010-069 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 820 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 804/TASK 72-32-00-991-305) CAUTION : DO NOT REMOVE THE LEVER ARMS TO COMPLETE THIS REPAIR. _______ Subtask 72-32-00-420-055 A. Install the new actuation ring lever arm bushing (1) If necessary, clean the pieces of old bushing from the ring. NOTE : The new bushing cannot be inserted onto the lever arm with the ____ legs attached. NOTE : The actuation ring is assembled with different types of ____ bushings. Be sure to select the correct bushing from the Illustrated Parts Catalog. (2) Carefully, break the 4 legs off of the new bushing. (3) Install the new bushing from outboard side of actuation ring (Ref. Fig. 804/TASK 72-32-00-991-305) WARNING : RTV 106 IS TOXIC AND FLAMMABLE. USE PERSONAL PROTECTION _______ EQUIPMENT. USE IN A WELL-VENTILATED AREA. (4) Apply approximately 0.125 in. (3.18 mm) RTV 106 (Material No. CP2267) to the outer flange of the bushing. (5) Permit the RTV 106 to cure for not less than 24 hours before you operate the engine. 5. Close-up ________ Subtask 72-32-00-410-064 A. Close access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 821 Nov 01/08
C F M 56-5B
Replacement of the Stages 1 and 2 Actuation Ring Flanged Bushing Figure 804/TASK 72-32-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 822 Nov 01/08
C F M 56-5B Subtask 72-32-00-440-057 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-32-00-410-065 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 823 Nov 01/08
C F M 56-5B HPC REAR STATOR ASSEMBLY - DESCRIPTION AND OPERATION ____________________________________________________ 1. _______ General (Ref. Fig. 001) The compressor rear stator consists of the rear casing halves, 3 stages of fixed vanes, and interstage honeycomb seals. The halves are attached together at the 3 and 9 oclock splitline with bolts. The rear stator assembly is found inside the front stator assembly and is cantilever mounted to the rear stator support. The outer flange of the rear stator support is installed between the front stator of the compressor and the combustion case. The rear flange has rabbets for close tolerance concentricity with the combustion case. The forward end is radially restrained by manifold supports attached to the front case to maintain concentricity. 2. Description ___________ A. Casing The rear casing halves are a matched set machined from an incoloy forging. The casings have internally machined circumferential slots that retain stages 6, 7, and 8 stator vane segments. Stage 6, 7, 8, and 9 rub lands are hard-coated. The casing contains ports for borescope inspection of internal area. B. Vanes The vanes in stages 6,7, and 8 are made into segments consisting of several vanes each. These segments are installed in circumferential slots in the casing. Each stage of vanes has shrouds with removable honeycomb seal segments attached to the inner platforms.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-33-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Compressor Rear Stator Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-33-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B COMBUSTION SECTION - DESCRIPTION AND OPERATION ______________________________________________ 1. _______ General (Ref. Fig. 001) The combustion of fuel takes place in the combustor installed in the compressor rear frame. The controlled release of energy of combustion through the turbine nozzles drive the engine rotors. (HP rotor for self sustaining operation and the LP rotor to develop airflow through the fan exhaust nozzle and to provide gases to the core engine exhaust nozzle for additional thrust).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-40-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Combustion Chamber Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-40-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B COMBUSTION CASE ASSEMBLY - DESCRIPTION AND OPERATION ____________________________________________________ 1. _______ General (Ref. Fig. 001) The combustion case is a fabricated structural weldment located between the high pressure compressor (HPC) and the low pressure turbine (LPT). It provides the structural interface, transmits the engine axial load, and provides gas flow path between the compressor and LPT. The case incorporates the compressor outlet guide vanes (OGV) and a diffuser for the reduction of combustion chamber sensitivity to the compressor air velocity profile. 2. Description ___________ A. Components The combustion case encloses the combustion chamber and high pressure turbine (HPT) components. The combustion chamber, compressor rear stationary (CDP) seal, HPT nozzle assembly, and HPT shroud/stage 1 LPT nozzle assembly are mounted in and structurally supported by the combustion case. The case mounts and positions the 20 fuel nozzles, 2 igniters, and fuel manifold. The fuel manifold system is composed of a fuel supply manifold (Y tube), 2 fuel manifolds halves, 3-piece drain manifold, and overboard drain tube. B. Ports There are 6 borescope ports ; 4 for inspection of the combustion chamber and HPT nozzles and 2 for inspection of the HPT blades and shrouds and the stage 1 LPT blades. The case has 4 ports for extraction of compressor discharge air for customer use, 4 ports for introduction of stage 5 compressor air for low pressure cooling and 3 ports for HPT shroud cooling air (one for source air and 2 for introduction of air to the shrouds). There is also one port for the following : start bleed dump, P3 sensor, T3 sensor, and CCCP air. There are 2 ports for the spark igniters and 2 ports for turbine clearance control thermocouples.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Combustion Case Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B COMBUSTION CASE ASSEMBLY - INSPECTION/CHECK ___________________________________________ TASK 72-41-00-290-001 Borescope Inspection of the Combustion Chamber Liners, Dome Areas,HPT Nozzle Vanes and Shrouds (as far as visible through two opposite ports) 1. __________________ Reason for the Job Refer to the MPD TASK: 724000-C1 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-42-00-290-041 72-51-00-290-004 72-53-00-290-004
Borescope Inspection of the Combustion Chamber Liners and Dome Area Borescope Inspection of High-Pressure Turbine Nozzle Assembly Borescope/Inspection of the High-Pressure Turbine Shroud
3. __________ Job Set-up Subtask 72-41-00-869-051 A. Not Applicable 4. Procedure _________ Subtask 72-41-00-290-051 A. Do a borescope inspection: (1) Borescope inspect combustion chamber liners and dome areas (Ref. TASK 72-42-00-290-041). NOTE : Combustion chamber port access is required through as many ____ ports as necessary to assure 100% combustor inspection coverage. (2) Borescope inspect high pressure turbine nozzle vanes (Ref. TASK 7251-00-290-004) .
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/08
C F M 56-5B (3) Borescope inspect high pressure turbine shrouds (Ref. TASK 72-53-00290-004).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B TASK 72-41-00-200-002 Inspection/Check of the Combustion Case Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-41-00-300-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-41-00-991-300
Fluorescent-Penetrant Inspection-Portable-Water Washable Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Repairs of the Combustion Case Assembly Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-41-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-41-00-010-054 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-41-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-41-00-010-056 D. Open the thrust reverser cowl doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-41-00-991-300) Subtask 72-41-00-230-052 A. Do a fluorecent penetrant inspection. (1) Do a fluorescent penetrant inspection of actual or suspected cracks in the combustion case assembly (Ref. TASK 70-51-00-230-002). Subtask 72-41-00-210-051 B. Do a visual inspection. (1) Do the visual inspection that follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Combustion casing body for : - Cracks
Not serviceable
- Nicks, scores and scratches
Any number 0.03 in. (0.76 mm) deep after removal of high metal
- Dents
Any number 0.10 in. (2.54 mm) deep after removal of high metal
- Buckling or distortion because of overtemperature
Not serviceable
- Hot spots (discoloration)
Any number, if metal not crazed. No cracks are permitted.
2. Combustion casing forward flanges for :
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
Combustion Case Assembly Figure 601/TASK 72-41-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Bolt hole cracks One crack per hole, 2 that extend cracks per frame radially outward - Bolt hole cracks that extend radially inward
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
3. Combustion case midflange for : - Broken bolts
One broken bolt with a minimum of 5 bolts that are not broken on both sides of the broken bolt. No more than 2 broken bolts in any group of 20.
See limit extensions (Ref. TASK 72-00-00-200025)
4. Combustion casing aft flange for : - Bolt hole cracks that extend radially outward
One crack per hole, 2 cracks per frame
- Bolt hole cracks that extend radially inward
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
5. Fuel nozzle pads for : - Thread damage
Minimum of 4 undamaged threads must be present after chasing threads
- Nicks, scores, pits and deposits
Any number on sealing surface 0.03 in. (0.76 mm) deep not extending across more than 50 percent of sealing surface after removal of high metal
Remove high metal and deposits (Ref. TASK 72-4100-300-002)
6. Igniter and borescope bosses for :
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Thread damage Minimum of 3 undamaged threads must be present after chasing threads 7. HPT shroud cooling and CDP bleed pads for : - Nicks, scores, pits and scratches
Any number, any length 0.03 in. (0.76 mm) in depth provided discrepancy does not extend over 75 percent of sealing surface
Remove high metal (Ref. TASK 72-41-00-300002).
- Cracks extending from bolt holes
One crack per hole no longer than 0.06 in. (1.52 mm)
See limit extensions (Ref. TASK 72-00-00-200025)
5. Close-up ________ Subtask 72-41-00-410-054 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-41-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B Subtask 72-41-00-410-056 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B COMBUSTION CASE ASSEMBLY - REPAIRS __________________________________ TASK 72-41-00-300-002 Repairs of the Combustion Case Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No
specific specific specific specific
abrasive stone fine file warning notice access platform 1 m (3 ft. 3 in.)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2189
Material No.
CP2191
* durite G422 (Ref. 70-30-00) * durite G421 (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Fluorescent-Penetrant Inspection-Portable-Water Washable Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-41-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-41-00-010-055 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B (2) Put the access platform in position. Subtask 72-41-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-41-00-010-057 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-41-00-350-051 A. Blend the part CAUTION : DO NOT PERMIT THE REMOVED MATERIAL, TOOLS, OR CONSUMABLES TO _______ FALL INTO THE COMBUSTION CASE. ENGINE DAMAGE CAN OCCUR. (1) Blend the part with a fine file, durite G422 (Material No. CP2189) or durite G421 (Material No. CP2191) or abrasive stone. Remove as small an amount of the parent metal as possible. Subtask 72-41-00-230-053 B. Do a fluorescent penetrant inspection of all the blend areas. No cracks are permitted. (Ref. TASK 70-51-00-230-002) 5. Close-up ________ Subtask 72-41-00-410-055 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B Subtask 72-41-00-440-053 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-41-00-410-057 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B COMBUSTION CHAMBER ASSEMBLY - DESCRIPTION AND OPERATION _______________________________________________________ 1. _______ General (Ref. Fig. 001, 002) The combustion case contains the combustion chamber, which is a short, annular structure. The combustion chamber consists of outer and inner cowls, 20 primary swirl nozzles, dome, and outer and inner liners. The liners and cowls are bolted to the dome. The function of the combustion chamber is to supply a uniform combustion pattern for low thermal stress. The staged burning valve, controlled by FADEC, adapts the function of the combustion chamber to the engine requirements by the use of either 10 or 20 open fuel nozzles. 2. ___________ Description (Ref. Fig. 001, 002) A. Dome The dome consists of both cast and machined components. Twenty primary swirl nozzles and 20 secondary swirl nozzles with venturies and sleeves are used to provide mixing of air and fuel. The entire surface of the dome is cooled by a film of cooling air. B. Cowl The inner and outer cowls are designed to provide uniform and stable airflow profiles to the combustion chamber. C. Liners The outer and inner liners are of an integral design with panel overhangs which contain closely spaced cooling holes that provide film cooling. Dilution holes are employed in the liners to provide additional mixing and cooling air which lowers the gas temperature at the turbine inlet. The outer liner contains 2 ferrules for the spark igniters.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Combustion Chamber Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Combustion Chamber Section Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B COMBUSTION CHAMBER ASSEMBLY - INSPECTION/CHECK ______________________________________________ TASK 72-42-00-290-041 Borescope Inspection of the Combustion Chamber Liners and Dome Area 1. __________________ Reason for the Job This TASK is applicable for NON/P, /P and /3 engines equiped with a Single Annular Combustor chamber. NOTE : Inspection of the combustion chamber is limited to the areas that can ____ be seen with a rigid borescope, at the 1, 3, 6 and 10 oclock borescope ports, and at the 2 spark igniter ports. The borescope ports at the 1, 3, 6, and 10 oclock positions are located immediately in front of the fuel manifold. These ports and the 2 spark igniter ports permit the borescope inspection of the combustion chamber and the HPT nozzle. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
856A1320 856A1322 856A1323
protective caps warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET 1 MONITOR, RESOLUTION BORESCOPE
EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.8 mm dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-42-00-290-006 73-11-40-790-002 74-21-30-000-002 74-21-30-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 NTM 720000 72-42-00-991-301 72-42-00-991-302 72-42-00-991-303 72-42-00-991-305 72-42-00-991-306
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Borescope Inspection of the Outer Side of the Combustion Chamber Outer Liners Leak Check of the Fuel Nozzles Removal of the Spark Igniter Installation of the Spark Igniter Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. Fig. Fig. Fig. Fig.
601 602 603 604 605
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-42-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-42-00-010-058 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-42-00-040-053 C. Make the thrust reverser unserviceable for maintenance (Ref. TASK 78-3000-481-041) Subtask 72-42-00-010-059 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-42-00-991-301, 602/TASK 72-42-00-991-302, 603/TASK 72-42-00-991-303, 604/TASK 72-42-00-991-305, 605/TASK 72-42-00-991-306) Subtask 72-42-00-010-060 A. Remove parts before borescope inspection. (1) Remove the borescope plugs from the approximate 3 and 10 oclock positions on the combustion case. Subtask 72-42-00-290-054 B. Do a borescope inspection. (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure the borescope and the lightsource are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Connect the fiber light cable to the BORESCOPE-KIT (856A1320P04/P05) and to the port on BORESCOPE-LIGHT SOURCE SET (856A1322P03/P04/P07). (3) Put the rigid borescope, (856A1320P04/P05), into the ports and turn on the light source of borescope-lightsource set (856A1322P03 or P04). (4) Turn the rigid borescope a full 360 degrees to inspect the dome of the combustion chamber, fuel nozzles, the inner and outer liners, and the aft sections. Adjust the borescope equipment to obtain maximum clarity of view. (5) Inspect the following : ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. All surfaces for : A. Discoloration
Any amount
B. Carbon Accumulation
Any amount
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Missing, chipped Any amount or spalled areas of thermal barrier coating 2. Dome Assembly (Spectacle Plate, Deflector amd Sleeve) for : A. Distortion of deflector or sleeve
Any amount
B. Radial crack in spectacle plate
Any number up to 2 in. (50.8 mm) length and not connected to each other
See limit extension (Ref. TASK 72-00-00-200025)
C. Circumferential crack in spectacle plate
Any number up to 3 in. (76.2 mm) length separated by 6 in. (152.4 mm)
See limit extension (Ref. TASK 72-00-00-200025)
D. Connected cracks in spectacle plate
Not more than (1) radial crack 2 in. (50.8 mm) long with (1) circumferential crack 3 in. (76.2 mm) long separated by 6 in. (152.4 mm).
See limit extension (Ref. TASK 72-00-00-200025)
E. Missing material from spectacle plate
Max. 0.06 in. (1.52 mm) x 0.06 in. (1.52 mm) at intersection of connected crack
See limit extension (Ref. TASK 72-00-00-200025)
F. Radial crack in deflector or sleeve
Any number up to 0.5 in. (12.7 mm) length
See limit extension (Ref. TASK 72-00-00-200025)
G. Circumferential cracks in deflector or sleeve
Any number up to 0.75 in. (19.05 mm)
See limit extension (Ref. TASK 72-00-00-200025)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
Combustion Chamber (Inner and Outer Liner Inspection) Figure 601/TASK 72-42-00-991-301- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Combustion Chamber (Inner and Outer Liner Inspection) Figure 601/TASK 72-42-00-991-301- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B
Combustion Chamber (Sectional View) Figure 602/TASK 72-42-00-991-302- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B
Combustion Chamber (Sectional View) Figure 602/TASK 72-42-00-991-302- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B
Cracks and Missing Material in Dome Area Figure 603/TASK 72-42-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-42-00 CES
Page 611 May 01/08
C F M 56-5B
Outer Liner (Inner) Figure 604/TASK 72-42-00-991-305- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B
Outer Liner (Inner) Figure 604/TASK 72-42-00-991-305- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B
Inner Liner (Inner) Figure 605/TASK 72-42-00-991-306- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B
Inner Liner (Inner) Figure 605/TASK 72-42-00-991-306- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------H. Connected cracks Connection of any radial See limit extension in deflector or and circumferential (Ref. TASK 72-00-00-200sleeve cracks within limits of 025) paragraphs F. and G. above. Limit is exceeded when third crack connects J. Missing material from overhangs on deflector or sleeve
Any amount up to 0.2 in. (5.08 mm) maximum depth.
See limit extension (Ref. TASK 72-00-00-200025)
K. Burn through holes
3 per dome 1 in. (25.4 mm) x 1 in. (25.4 mm) maximum
See limit extension (Ref. TASK 72-00-00-200025)
L. Fuel nozzles for dislodged wear sleeves
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
3. Inner and outer liners for : A. Outer liner axial cracks
Any number across 1 Panel or less and up to 4 cracks across more than 1 panel but not longer than 3 panels
If a crack extends across more than 3 panels, borescope the outer side of the outer liner in the crack locations (Ref. TASK 72-42-00-290-006). See limit extension (Ref. TASK 72-00-00-200025).
NOTE : When applying limits, the dome band is interpreted as a panel. ____ B. Inner liner axial cracks
Any number across 1 panel or less and up to 4 cracks across more than 1 panel but not longer than 2 panels
If up to 1 crack is across 4 Panels, and no material is missing more than 3 times the diameter of a dilution hole and does not connect to a circumferential crack longer than 0.5 in. (12.7
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------mm), then reinspect in 750 cycles. See limit extensions (Ref. TASK 7200-00-200-025). C. Circumferential cracks
There is no limit to the number with these conditions: The cracks are no longer than 2 dilution lands. There are no more than 2 adjacent cracks in a dilution land. The cracks are separated by a minimum of 3 dilution lands that do not have cracks.
See limit extensions (Ref. TASK 72-00-00-200025)
NOTE : A dilution land is the area of the panel between the dilution ____ holes. Connection of any axial and circumferential cracks up to max limits of paragraphs A. B. and C. above. Limit is exceeded when third crack connects
See limit extension (Ref. TASK 72-00-00-200025)
E. Burn through or missing material
Per liner, 8 areas with these conditions : 3 or more adjacent holes are not aligned axially. 6 areas are not more than 2 times the size of a dilution hole. No more than 2 areas are not more than 3 times the size of a dilution hole. No more than 1 area is not more than 4 times the size of a dilution hole. The area can be 3
See limits extension (Ref. TASK 72-00-00-200025)
R R R R
D. Connected cracks
EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Feb 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------times the size of a dilution hole, if the dilution hole was contained in the damaged area, and is considered a hole that is 2 times the size of a dilution hole. F. Missing overhangs
Per liner : 14 areas each 2 times the size of a dilution hole providing maximum axial alignment of distress is 3 adjacent panels.
See limits extensions (Ref. TASK 72-00-00-200025).
G. Distortion
Any amount within 0.5 in. (12.7 mm) of original contour
See limit extension (Ref. TASK 72-00-00-200025)
(6) When the inspection is complete, turn off the light source and remove the borescope. (7) If any defects are found then remove additional borescope plugs and the spark igniters to inspect all of the combustion chamber. If no defects are found, install parts removed for borescope inspection. Subtask 72-42-00-010-064 C. Remove parts before additional borescope inspection. (1) Remove the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug. NOTE : If you remove the drain tube from the fuel nozzle adjacent to ____ the 6 oclock borescope plug, you will be required to perform a leak check after this inspection. Use the 6 oclock borescope port only if necessary. (2) Remove the borescope plugs from the approximate 1 and 6 oclock positions.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
C F M 56-5B (3) Remove both spark igniters (Ref. TASK 74-21-30-000-002). (4) Install protective caps on the leads and the spark igniters. Subtask 72-42-00-290-056 D. Do a borescope inspection of the entire combustion chamber. (1) Repeat paragraph 4.B.(1) thru 4.B.(5) for each borescope and spark igniter location. Subtask 72-42-00-410-059 E. Install parts removed for borescope inspection. (1) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (2) Install the borescope plugs. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE _______ COMBUSTOR BORESCOPE PLUGS DO NOT HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF BORESCOPE PLUGS WITH STEMS FROM OTHER LOCATIONS WILL RESULT IN THE STEM FEATURE BEING BURNED AWAY BY COMBUSTION GASES. (a) Install the borescope plugs and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (3) Safety the plugs with lockwire 0.8 mm dia. (Material No. CP8001) (4) If necessary, install the fuel drain tube to the fuel nozzle adjacent to the six oclock borescope plug. TORQUE the coupling nuts on the fuel drain tube to between 120 and 135 lbf.in (1.35 and 1.52 m.daN) and safety with lockwire 0.8 mm dia. (Material No. CP8001) (5) If necessary, remove the protective caps and install the spark igniters (Ref. TASK 74-21-30-400-002) Subtask 72-42-00-290-062 F. If necessary, do the borescope inspection of the outer side of the outer liner to confirm the extent of outer liner axial cracks (Ref. TASK 72-4200-290-006).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 619 Nov 01/08
C F M 56-5B Subtask 72-42-00-790-051 G. Do a fuel nozzle leak check. (1) If you removed the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug, do a fuel nozzle leak check (Ref. TASK 73-1140-790-002). 5. Close-up ________ Subtask 72-42-00-410-057 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-42-00-440-055 B. Make the thrust reverser serviceable after maintenance (Ref. TASK 78-3000-081-041) Subtask 72-42-00-410-058 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/08
C F M 56-5B TASK 72-42-00-290-006 Borescope Inspection of the Outer Side of the Combustion Chamber Outer Liners 1. __________________ Reason for the Job To confirm the extent of the outer liner axial cracks, as necessary. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1321 856A1322 856A1323
warning notice access platform 1 m (3 ft. 3 in.) 1 FIBERSCOPE SET 1 BORESCOPE-LIGHT SOURCE SET 1 MONITOR, RESOLUTION BORESCOPE
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 73-11-40-000-002 73-11-40-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 NTM 720000 72-42-00-991-304
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Removal of the Fuel Nozzle Installation of the Fuel Nozzle Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 606
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 621 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-42-00-941-057 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-42-00-010-072 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform Subtask 72-42-00-040-057 C. Make the thrust reverser unserviceable for maintenance (Ref. TASK 78-3000-481-041) Subtask 72-42-00-010-075 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 606/TASK 72-42-00-991-304) Subtask 72-42-00-010-073 A. Remove parts before borescope inspection. (1) Select fuel nozzles to remove that will allow access to the outer liner area to be inspected. (2) Remove the fuel nozzles (Ref. TASK 73-11-40-000-002) Subtask 72-42-00-290-061 B. Do a borescope inspection. (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure borescope and the ligth source are serviceable. See the Non Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Connect the fiber ligth cable to the FIBERSCOPE SET (856A1321P01 or 856A1321P03 or 856A1321P06) and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P03, P04, or P07). (3) Put the fiberscope of the FIBERSCOPE SET (856A1321P01 or 856A1321P03 or 856A1321P06) into the fuel nozzle ports and turn on the light source of BORESCOPE-LIGHT SOURCE SET (856A1322P03, or P04). (4) Adjust the borescope equipment to obtain maximum clarity of view. (5) Inspect the following: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Outer side of outer liners for: A. Outer liner axial crack locations
Any number if cracks do not extend through more than one of ribs 4, 5, and 6 if rib 1 is not cracked through.
Reinspect the combustor in 750 cycles. See limit extensions (Ref. TASK 7200-00-200-025).
NOTE : When applying limits, the dome band is interpreted as a panel. ____
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 623 Nov 01/08
C F M 56-5B
Outer Liner (Outer) Figure 606/TASK 72-42-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 624 Nov 01/08
C F M 56-5B (6) When the inspection is complete, turn off the light source and remove the fiberscope. Subtask 72-42-00-410-069 C. Install the fuel nozzles (Ref. TASK 73-11-40-400-002). 5. Close-up ________ Subtask 72-42-00-410-070 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-42-00-440-053 B. Make the thrust reverser serviceable after maintenance (Ref. TASK 78-3000-081-041). Subtask 72-42-00-410-072 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 625 Nov 01/08
C F M 56-5B TASK 72-42-00-290-005 Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET 1 MONITOR, RESOLUTION BORESCOPE
856A1320 856A1322 856A1323
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.8 mm dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 626 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-51-00-290-004 72-51-00-290-004 73-11-40-790-002 74-21-30-000-002 74-21-30-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 NTM 720000 72-42-00-991-301 72-42-00-991-307 72-42-00-991-308
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Borescope Inspection of High-Pressure Turbine Nozzle Assembly Borescope Inspection of High-Pressure Turbine Nozzle Assembly Leak Check of the Fuel Nozzles Removal of the Spark Igniter Installation of the Spark Igniter Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 607 Fig. 608
3. __________ Job Set-up Subtask 72-42-00-941-054 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Nov 01/08
C F M 56-5B Subtask 72-42-00-010-061 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-42-00-040-054 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041) Subtask 72-42-00-010-062 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-42-00-991-301) Subtask 72-42-00-010-063 A. Remove parts before borescope inspection. (1) Remove the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug. NOTE : If you remove the drain tube from the fuel nozzle adjacent to ____ the 6 oclock borescope plug, you will be required to perform a leak check after this inspection. Use the 6 oclock borescope port only if necessary. (2) Remove the borescope plugs from the approximate 1, 3, 6 and 10 oclock positions. (3) Remove both spark igniters (Ref. TASK 74-21-30-000-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 628 Nov 01/08
C F M 56-5B Subtask 72-42-00-290-055 B. Do a borescope inspection. (Ref. Fig. 607/TASK 72-42-00-991-307, 608/TASK 72-42-00-991-308) NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure ____ borescope and the lightsource are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (1) Connect the fiber light cable to the BORESCOPE-KIT (856A1320 P04 ot P05) and to the port on BORESCOPE-LIGHT SOURCE SET (856A1322 P03 or P04 or P07). (2) Put the rigid borescope, (856A1320 P04 or P05), into the left side ignitor position and turn on the light source of borescope-lightsource set. (3) Turn the borescope until you can see the deflector plate, sleeve, primary swirler, and the fuel nozzle tip that is located clockwise from the ignitor. (4) Inspect the position of the fuel nozzle tip to the bore of the primary swirler for the conditions as follows: (a) the tip of the fuel nozzle must be within the bore of the primary swirler. (b) if the fuel nozzle is out of position with the dome, refer to paragraph B.(10). (5) Do the fuel nozzle tip inspection for the fuel nozzle that is counterclockwise from the igniter. (6) Turn the borescope until you can see the second deflector and the second sleeve that is clockwise from the igniter. (7) Inspect the gap between the deflector and the spectacle plate on the inner liner side. The nominal dimension of the gap is 0.08 in. (2.03 mm). Inspect for the following: (a) the gap must be 0.3 in. (7.6 mm) max at the edge of the deflector (b) if the gap is over the max, refer to pargraph B.(10). (8) Do the deflector gap inspection for the second deflector counterclockwise from the igniter.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 629 Nov 01/08
C F M 56-5B
Combustion Chamber Inspection Figure 607/TASK 72-42-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 630 Nov 01/08
C F M 56-5B
Combustion Chamber Inspection Figure 608/TASK 72-42-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 631 Nov 01/08
C F M 56-5B (9) Do the inspection B.(1) thru B.(8) to the right side igniter and the borescope ports. (10) If any of the results of the inspections are out of limits, remove the fuel nozzle adjacent to the area. Insert the borescope and rotate to view the affected fuel nozzle and primary swirler. (11) Inspect the position of the fuel nozzle tip to the bore of the primary swirler. If the fuel nozzle is out of position with the primary swirler, remove the engine. There are no allowable service extensions that apply. (12) Do a one time borescope inspection between 200-400 hours after the birdstrike occurred (Ref. TASK 72-51-00-290-004) for NON/P hardware and (Ref. TASK 72-51-00-290-004) for /P hardware , but only look for leading edge missing material/burn through. (a) If no leading edge distress is seen, go back to the usual borescope inspection interval. (b) If missing material/burn through is seen on the HPT nozzle leading edge wall, contact CFMI. (13) When the inspection is complete, turn off the light source and remove the borescope. Subtask 72-42-00-410-060 C. Install parts removed for borescope inspection. (1) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (2) Install the borescope plugs. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE _______ COMBUSTOR BORESCOPE PLUGS DO NOT HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF BORESCOPE PLUGS WITH STEMS FROM OTHER LOCATIONS WILL RESULT IN THE STEM FEATURE BEING BURNED AWAY BY COMBUSTION GASES. (a) Install the borescope plugs and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (3) Safety the plug with lockwire 0.8 mm dia. (Material No. CP8001).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 632 Nov 01/08
C F M 56-5B (4) If necessary, install the fuel drain tube to the fuel nozzle adjacent to the six oclock borescope plug. TORQUE the coupling nuts on the fuel drain tube to between 120 and 135 lbf.in (1.35 and 1.52 m.daN) and safety with lockwire 0.8 mm dia. (Material No. CP8001) (5) Install the spark igniters (Ref. TASK 74-21-30-400-002). Subtask 72-42-00-790-052 D. Do a fuel nozzle leak check. (1) If you removed the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug, do a fuel nozzle leak check (Ref. TASK 73-1140-790-002). 5. Close-up ________ Subtask 72-42-00-410-061 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-42-00-440-054 B. Make the thrust reverser serviceable. (Ref. TASK 78-30-00-081-041) Subtask 72-42-00-410-062 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 633 Nov 01/08
C F M 56-5B TASK 72-42-00-290-007 Borescope Inspection of the Inner Cowl Bolts of the Combustion Chamber 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1321 856A1322 856A1323
warning notice access platform 1 m (3 ft. 3 in.) 1 FIBERSCOPE SET 1 BORESCOPE-LIGHT SOURCE SET 1 MONITOR, RESOLUTION BORESCOPE
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 73-11-40-000-002 73-11-40-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 NTM 720000
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Fuel Nozzle Installation of the Fuel Nozzle Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 634 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-42-00-941-059 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-42-00-010-080 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform Subtask 72-42-00-040-059 C. Make the thrust reverser unserviceable for maintenance (Ref. TASK 78-3000-481-041) Subtask 72-42-00-010-081 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 635 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-42-00-010-082 A. Remove parts before borescope inspection. (1) Select fuel nozzles to remove that will allow access to the outer liner area to be inspected. (2) Remove the fuel nozzles (Ref. TASK 73-11-40-000-002) Subtask 72-42-00-290-066 B. Do a borescope inspection. (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure borescope and the light source are serviceable. See the Non Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Connect the fiber light cable to the FIBERSCOPE SET (856A1321P01 or 856A1321P03 or 856A1321P06) and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P03, P04, or P07). (3) Put the fiberscope of the FIBERSCOPE SET (856A1321P01 or 856A1321P03 or 856A1321P06) into the fuel nozzle ports and turn on the light source of BORESCOPE-LIGHT SOURCE SET (856A1322P03, or P04). (4) Adjust the borescope equipment to obtain maximum clarity of view. (5) Inspect the following: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Inner side of inner cowl for: A. Missing bolts
Not serviceable
See limit extensions
B. Loose bolts
Not serviceable
See limit extensions
C. Cracked bolt tack welds
Not serviceable
See limit extensions
(6) When the inspection is complete, turn off the light source and remove the fiberscope.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 636 Nov 01/08
C F M 56-5B Subtask 72-42-00-410-078 C. Install the fuel nozzles (Ref. TASK 73-11-40-400-002). 5. Close-up ________ Subtask 72-42-00-410-076 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-42-00-440-059 B. Make the thrust reverser serviceable after maintenance (Ref. TASK 78-3000-081-041). Subtask 72-42-00-410-077 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 637 Nov 01/08
C F M 56-5B TURBINE SECTION - DESCRIPTION AND OPERATION ___________________________________________ 1. _______ General The modules of the turbine are the high pressure turbine and the low pressure turbine. A. High pressure turbine module (Ref. Fig. 001) The HPT module consists of 1-stage nozzle and rotor. The nozzles are supported by the HPT case, the rotor is attached to the high pressure compressor rotor. B. Low pressure turbine module (Ref. Fig. 002) The LPT module consists of 4-stage turbine, rotor, nozzles, stator case and rear frame. The rotor is connected to the fan. Surrounding the stator case is a clearance control manifold system.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-50-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
High Pressure Turbine Section Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-50-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Low Pressure Turbine Rotor/Stator Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-50-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B TURBINE SECTION - REMOVAL/INSTALLATION ______________________________________ TASK 72-50-00-920-001 Discard Life Limited Parts of HPT and LPT 1. __________________ Reason for the Job R
Refer to the MPD TASK: 725000-C2 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-00-00-400-042 ESM 051103 ESM 051104 ESM 720052 ESM 720054
Removal of the Power Plant Installation of the Power Plant
3. __________ Job Set-up Subtask 72-50-00-010-051 A. Remove the engine (Ref. TASK 71-00-00-000-042). 4. Procedure _________ Subtask 72-50-00-020-051 A. Remove and discard life limited parts of the high pressure turbine (Ref. ESM 720052) and the low pressure turbine and (Ref. ESM 720054). NOTE : (Ref. ESM 051103) and (Ref. ESM 051104) for time limits. ____ 5. Close-up ________ Subtask 72-50-00-410-051 A. Install the engine (Ref. TASK 71-00-00-400-042).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-50-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B HPT NOZZLE ASSEMBLY - DESCRIPTION AND OPERATION _______________________________________________ 1. _______ General (Ref. Fig. 001, 002) The high pressure turbine (HPT) nozzle is a single-stage air cooled assembly that mounts in the combustion case and directs the gas flow from the combustion chamber onto the blades of the HPT rotor at the optimum angle. The major parts of the nozzle are 21 nozzle segments and inner support. The aft support and seal assembly, while not integral components of the HPT nozzle module are included since they attach to the HPT stator parts. 2. Description ___________ A. Nozzle Segments The HPT nozzle segments are assemblies of 2 vane/platform castings that are brazed together. Each vane is a cast shell divided into forward and aft compartments by an inner rib. The vanes and platforms are cooled by compressor discharge air entering the vane compartments through inserts in the inner and outer ends of vanes and exiting through the vane leading and trailing edges. The vanes and platforms are made of high strength nickel base alloy with protective coating on vane airfoils and on platform flowpath surfaces. B. Inner Support The nozzle inner support is a one-piece nickel base alloy ring. The major portion of the nozzle axial load is carried by the inner support through the bolted flanges of the support and nozzle inner platforms. The nozzle inner platform and the inner support form a seal ring which controls the amount of cooling air leakage that passes between the seal and the HPT blades. C. Aft Outer Support and Seal The aft outer support is a one-piece nickel base alloy ring that provides support for the 4-step honeycomb seal that mates with the HPT rotor inducer seal to help maintain the proper amount of cooling air flow and rotor thrust.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
High Pressure Turbine Nozzle Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Stage 1 HPT Nozzle Cooling Airflow Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B HPT NOZZLE ASSEMBLY - INSPECTION/CHECK ______________________________________ TASK 72-51-00-290-004 Borescope Inspection of High-Pressure Turbine Nozzle Assembly 1. __________________ Reason for the Job This TASK is applicable for NON/P engines. NOTE : Inspection of the high pressure turbine (HPT) nozzle assembly is ____ limited to the areas that can be seen with a rigid borescope at the 1, 3, 6, and 10 oclock borescope ports, and at the 2 spark igniter ports. The borescope ports at the 1, 3, 6, and 10 oclock position are located immediately in front of the fuel manifold. Special inspection of the HPT nozzle convex side can be accomplished, if required using with a flexible borescope. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific 856A1310 856A1320 856A1321 856A1322 856A1323 856A1351
1 1 1 1 1 1
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) KIT, BORESCOPE GUIDE - HP TURBINE BORESCOPE-KIT FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE GUIDE TUBE,BORESCOPE-HPT SHROUD
EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8mm) dia (Ref. 70-30-00) * lockwire 0.032 in. (0.8mm) dia (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 73-11-40-790-002 74-21-30-000-002 74-21-30-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-51-00-991-300 72-51-00-991-301
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Leak Check of the Fuel Nozzles Removal of the Spark Igniter Installation of the Spark Igniter Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602
3. __________ Job Set-up Subtask 72-51-00-941-051 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-51-00-010-053 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-51-00-040-051 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-51-00-010-054 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 601/TASK 72-51-00-991-300, 602/TASK 72-51-00-991-301) Subtask 72-51-00-010-056 A. Remove parts before borescope inspection. (1) Remove the borescope plugs from the approximate 3 and 10 oclock positions on the combustion case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B
Inspection of the High-Pressure Turbine-Nozzle Assembly Figure 601/TASK 72-51-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
HPT Nozzle Assembly Inspection, Convex Side Figure 602/TASK 72-51-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B Subtask 72-51-00-290-052 B. Do a Borescope Inspection (1) Connect the fiber light cable to the BORESCOPE-KIT (856A1320 P04 or P05), and to the porton BORESCOPE-LIGHT SOURCE SET (856A1322 P02 or P03 or P04 or P07 or P08). NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make ____ sure the borescope or the fiberscope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NDTM 720000). (2) Put the rigid borescope, of the BORESCOPE-KIT (856A1320/P04 or P05), into the ports and turn on the light source BORESCOPE-LIGHT SOURCE SET (856A1322/PO3 or PO4). (3) Rotate and adjust the borescope to view the HPT nozzle area. (4) If inspection of the nozzle convex side is necessary, use a FIBERSCOPE SET (856A1321 P01 or P03) and KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01), or GUIDE TUBE,BORESCOPE-HPT SHROUD (856A1351P01). NOTE : If KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01) is used to ____ view the convex side, an 8 ft. (2.43 m) fiberscope must be used. (5) Inspect the following: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Leading edge of vane airfoil for: A. Cracks that interconnect nose holes.
Any number, 0.3 in. (7.62 mm) long; no missing material.
See limit extension (Ref. TASK 72-00-00-200025).
B. Burns or spalling.
Any amount, burns through airfoil limited to 0.3 in. (7.62 mm) X 0.5 in. (12.7 mm) per vane, maximum of 4 vanes per 90-degree arc.
See limit extensions (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Baffle. NOTE : The airfoils baffle is visible inside the airfoil when missing ____ material occurs. It is sheet metal with cooling holes. (1) Cracks.
Any number.
(2) Missing material.
Any area equivalent to a rectangle defined by 4 adjacent holes.
See limit extension (Ref. TASK 72-00-00-200025).
A. Radial cracks extending out of gill holes.
Any number; no missing material.
See limit extension (Ref. TASK 72-00-00-200025).
B. Other cracks (not in gill hole rows).
Any number; no missing material.
See limit extension (Ref. TASK 72-00-00-200025).
C. Burns and cracks.
Any number; no missing material or burn through.
See limit extension (Ref. TASK 72-00-00-200025).
2. Concave surface of vane airfoil for:
3. Convex surface of vane airfoil for: A. Radial cracks.
Any number.
B. Axial cracks.
Any number.
C. Burns and bulges.
Any number.
See limit extension (Ref. TASK 72-00-00-200025).
D. Missing panel
Not serviceable.
See limit extension (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------E. Missing Thermal Any amount. Barrier Coating (TBC) 4. Trailing edge of vane airfoil for: A. Axial cracks starting from slots adjacent to trailing edge
Any number.
B. Burns and cracks.
Any number.
C. Buckling or bowing
Any amount.
D. Missing material (loss of metal).
Total area removed from trailing edge not to be more than 0.5 in. (12.7 mm) in axial direction.
See limit extension (Ref. TASK 72-00-00-200025).
5. All areas of airfoil for: A. Craze cracking.
Any amount.
NOTE : Craze cracking looks like many surface cracks that have no visual ____ width or depth. B. Nicks, scores, scratches and dents.
Any number.
C. Metal splatter.
Any amount.
D. Missing codep coating.
Any amount.
6. Inner and outer platform for: A. Cracks in parent metal.
Any number.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Missing metal or No through holes, but See limit extensions burning of parent any amount of missing (Ref. TASK 72-00-00-200metal. material from cracking 025). or burning is permitted. C. Nicks, scores, scratches and dents or platform surface.
Any amount.
D. Bulging and bowing.
Any amount.
E. Cracks in platform braze joint.
Any amount, no separation of braze joint allowed unless caused by burning.
(6) When the inspection is complete, turn off the light source and remove the borescope and the guide tube. (7) If any defects are found then remove additional borescope plugs and the spark igniters to inspect all of the HPT nozzle assembly. Subtask 72-51-00-010-055 C. Remove parts before borescope inspection. (1) Remove the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug. NOTE : If you remove the drain tube from the fuel nozzle adjacent to ____ the 6 oclock borescope plug, you will be required to perform a leak check after this inspection. Use the 6 oclock borescope port only if necessary. (2) Remove the borescope plugs from the approximate 1 and 6 oclock positions. (3) Remove both spark igniters (Ref. TASK 74-21-30-000-002)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B Subtask 72-51-00-290-053 D. Do a borescope inspection. (1) Repeat paragraph 4.B.(1) thru (6) for each borescope and spark igniter location. Subtask 72-51-00-410-054 E. Install parts removed for borescope inspection. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE COMBUSTOR _______ BORESCOPE PLUGS DO NOT HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF BORESCOPE PLUGS WITH STEMS FROM OTHER LOCATIONS WILL RESULT IN THE STEM FEATURE BEING BURNED AWAY BY COMBUSTION GASES. (1) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (2) Install the borescope plugs and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (3) Wirelock the plugs with lockwire 0.032 in. (0.8mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8mm) dia (Material No. CP8002). (4) If necessary, install the fuel drain tube to the fuel nozzle adjacent to the 6 oclock borescope plug. TORQUE the coupling nuts on the fuel drain tube to between 120 and 135 lbf.in (1.35 and 1.52 m.daN) and safety with lockwire 0.032 in. (0.8mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8mm) dia (Material No. CP8002) (5) Install the spark igniters (Ref. TASK 74-21-30-400-002). Subtask 72-51-00-790-050 F. Do a fuel nozzle leak check. (1) If you removed the drain tube from the fuel nozzle adjacent to the oclock borescope plug, do a fuel nozzle leak check (Ref. TASK 73-1140-790-002)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-51-00-410-052 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-51-00-440-051 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-51-00-410-053 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B TASK 72-51-00-290-004- 01 Borescope Inspection of High-Pressure Turbine Nozzle Assembly 1. __________________ Reason for the Job This TASK is applicable for /P and /3 engines. NOTE : Inspection of the high pressure turbine (HPT) nozzle assembly is ____ limited to the areas that can be seen with a rigid borescope at the 1, 3, 6, and 10 oclock borescope ports, and at the 2 spark igniter ports. The borescope ports at the 1, 3, 6, and 10 oclock position are located immediately in front of the fuel manifold. Special inspection of the HPT nozzle convex side can be accomplished, if required, with a flexible borescope. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific 856A1310 856A1320 856A1321 856A1322 856A1323 856A1351
1 1 1 1 1 1
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) KIT, BORESCOPE GUIDE - HP TURBINE BORESCOPE-KIT FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE GUIDE TUBE,BORESCOPE-HPT SHROUD
EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8mm) dia (Ref. 70-30-00) * lockwire 0.032 in. (0.8mm) dia (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 73-11-40-790-002 74-21-30-000-002 74-21-30-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-51-00-991-301
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Leak Check of the Fuel Nozzles Removal of the Spark Igniter Installation of the Spark Igniter Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 602
3. __________ Job Set-up Subtask 72-51-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-51-00-010-057 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-51-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-51-00-010-058 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 602/TASK 72-51-00-991-301) Subtask 72-51-00-010-059 A. Remove parts before borescope inspection. (1) Remove the borescope plugs from the approximate 3 and 10 oclock positions on the combustion case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B Subtask 72-51-00-290-054 B. Do a Borescope Inspection (1) Connect the fiber light cable to the BORESCOPE-KIT (856A1320 P04 or P05), and to the port on BORESCOPE-LIGHT SOURCE SET (856A1322 P02 or P03 or P04 or P07 or P08). NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make ____ sure the borescope or the fiberscope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NDTM 720000). (2) Put the rigid borescope, of the BORESCOPE-KIT (856A1320/P04 or P05), into the ports and turn on the light source BORESCOPE-LIGHT SOURCE SET (856A1322/PO3 or PO4). (3) Rotate and adjust the borescope to view the HPT nozzle area. (4) If inspection of the nozzle convex side is necessary, use a FIBERSCOPE SET (856A1321 P01 or P03) and KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01), or GUIDE TUBE,BORESCOPE-HPT SHROUD (856A1351P01). NOTE : If KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01) is used to ____ view the convex side, an 8 ft. (2.43 m) fiberscope must be used. (5) Inspect the following: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Leading edge of vane airfoil for: A. Cracks.
Any number, 0.3 in. (7.62 mm) long; no missing material.
See limit extension (Ref. TASK 72-00-00-200025).
B. Other cracks (not interconnecting nose holes).
Any number, 0.5 in. (12.7 mm) long; no missing material.
See limit extension (Ref. TASK 72-00-00-200025).
C. Baffle.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------NOTE : The airfoils baffle is visible inside the airfoil when missing ____ material occurs. It is sheet metal with cooling holes. (1) Cracks.
Any number.
(2) Missing material.
Any area equivalent to a rectangle defined by 4 adjacent holes.
See limit extension (Ref. TASK 72-00-00-200025).
D. Burns or missing material.
Any amount, burns through airfoil limited to 0.3 in. (7.62 mm) X 0.5 in. (12.7 mm) per vane, maximum of 4 vanes per 90 degree arc.
See limit extensions (Ref. TASK 72-00-00-200025).
E. Missing thermal barrier coating (TBC).
Any amount.
2. Concave surface of vane airfoil for: A. Cracks.
Any number.
See limit extension (Ref. TASK 72-00-00-200025).
B. Burns or missing material.
Any number; no missing material or burn through.
See limit extension (Ref. TASK 72-00-00-200025).
C. Missing thermal barrier coating (TBC).
Any amount.
3. Convex surface of vane airfoil for: A. Radial cracks.
Any number; no missing material
See limit extension (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Axial cracks. Any number; no missing See limit extension material (Ref. TASK 72-00-00-200025). C. Burns and bulges.
Any number; no missing material
D. Missing Thermal Barrier Coating (TBC)
Any amount.
See limit extension (Ref. TASK 72-00-00-200025).
4. Trailing edge of vane airfoil for: A. Axial cracks starting from slots adjacent to trailing edge
Any number.
B. Burns and cracks.
Any number.
C. Buckling or bowing
Any amount.
D. Missing material (loss of metal).
Total area removed from trailing edge not to be more than 0.5 in. (12.7 mm) in axial direction.
See limit extension (Ref. TASK 72-00-00-200025).
5. All areas of airfoil for: A. Craze cracking.
Any amount.
NOTE : Craze cracking looks like many surface cracks that have no visual ____ width or depth. B. Nicks, scores, scratches and dents.
Any number.
C. Metal splatter.
Any amount.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------6. Inner and outer platform for: A. Cracks in parent metal.
Any number.
B. Missing metal or burning of parent metal.
No through holes, but any amount of missing material from cracking or burning is permitted.
C. Nicks, scores, scratches and dents on platform surface.
Any amount.
D. Bulging and bowing.
Any amount.
E. Cracks in platform braze joint.
Any amount, no separation of braze joint allowed unless caused by burning.
See limit extensions (Ref. TASK 72-00-00-200025).
(6) When the inspection is complete, turn off the light source and remove the borescope and the guide tube. (7) If any defects are found then remove additional borescope plugs and the spark igniters to inspect all of the HPT nozzle assembly. Subtask 72-51-00-010-060 C. Remove parts before borescope inspection. (1) Remove the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug. NOTE : If you remove the drain tube from the fuel nozzle adjacent to ____ the 6 oclock borescope plug, you will be required to perform a leak check after this inspection. Use the 6 oclock borescope port only if necessary.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
C F M 56-5B (2) Remove the borescope plugs from the approximate 1 and 6 oclock positions. (3) Remove both spark igniters (Ref. TASK 74-21-30-000-002) Subtask 72-51-00-290-055 D. Do a borescope inspection. (1) Repeat paragraph 4.B.(1) thru (6) for each borescope and spark igniter location. Subtask 72-51-00-410-055 E. Install parts removed for borescope inspection. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE COMBUSTOR _______ BORESCOPE PLUGS DO NOT HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF BORESCOPE PLUGS WITH STEMS FROM OTHER LOCATIONS WILL RESULT IN THE STEM FEATURE BEING BURNED AWAY BY COMBUSTION GASES. (1) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (2) Install the borescope plugs and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (3) Wirelock the plugs with lockwire 0.032 in. (0.8mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8mm) dia (Material No. CP8002). (4) If necessary, install the fuel drain tube to the fuel nozzle adjacent to the 6 oclock borescope plug. TORQUE the coupling nuts on the fuel drain tube to between 120 and 135 lbf.in (1.35 and 1.52 m.daN) and safety with lockwire 0.032 in. (0.8mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8mm) dia (Material No. CP8002) (5) Install the spark igniters (Ref. TASK 74-21-30-400-002). Subtask 72-51-00-790-051 F. Do a fuel nozzle leak check. (1) If you removed the drain tube from the fuel nozzle adjacent to the oclock borescope plug, do a fuel nozzle leak check (Ref. TASK 73-1140-790-002)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 619 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-51-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-51-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-51-00-410-057 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/08
C F M 56-5B HPT ROTOR ASSEMBLY - DESCRIPTION AND OPERATION ______________________________________________ 1. _______ General (Ref. Fig. 001) The high pressure turbine (HPT) rotor is a single-stage, air-cooled, high-efficiency turbine. Structurally the rotor consists of the front shaft, the forward air seal, the disk, and the rear shaft. 2. Description ___________ A. Front Shaft The front shaft forms the structural connection between the compressor rotor and the HPT rotor, and supports the aft end of the compressor rotor. B. Disk The HPT disk is a forged and machined part that retains the turbine blades in axial dovetail slots. The inner part of the disk is cooled by booster discharge air. The outer part of the disk is cooled by compressor discharge air. C. Rear Shaft The rear shaft is bolted to the aft side of the disk at a rabbeted flange and forms the aft support for the HPT rotor. The shaft is supported by the No. 4 roller bearing which rides on the low pressure shaft. Repairable abrasive-coated seals are machined as an integral part of the rear shaft. D. Front Outer Seal The front outer seal is bolted between the disk and the front shaft of the rotor. It forms a cavity between itself and the disk to direct compressor discharge air against the disk web and out through the turbine blades. The seal is a labyrinth inclined tooth form that reduces leakage past the seals. The seal teeth are abrasive coated and repairable. E. Blades (Ref. Fig. 002) The 80 HPT blades are made of a high temperature nickel alloy that has a high strength to weight ratio and are made in a single-crystal. Each blade has its own shank and dovetail. Compressor discharge air flows through the blades to decrease the temperature of the metal. The air flows through the root entrance holes, through eight internal cavities and out the holes in the leading edge, airfoil, tip, and trailing edges. The blades have a Thermal Barrier Coating (TBC) on the airfoil and platform to decrease the temperature of the metal. The TBC is a white ceramic that has a thickness of 0.006 in. (0.15 mm).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
High Pressure Turbine Rotor Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
HP Turbine Blade Cooling Airflow Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B HPT ROTOR ASSEMBLY - INSPECTION/CHECK _____________________________________ TASK 72-52-00-290-001 R
Borescope Inspection of HPT Blades (from the front and the rear) 1. __________________ Reason for the Job Refer to the MPD TASK: 725000-C1 This TASK is applicable for NON /P engines. Inspection of the high pressure turbine (HPT) blades from the rear is limited to the areas that can be seen with a rigid borescope, at the 5:30 and 8:30 oclock borescope ports (S16 and S17). The borescope ports at the 5:30 and 8:30 oclock positions are located immediately in front of the combustion case aft flange. Inspection of the HPT blades from the front can be accomplished, if required, with a flexible borescope through the spark igniter ports (S10 and S11) of the combustion case. NOTE : There are 80 HPT blades installed in the rotor. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No
specific specific specific specific specific
856A1320 856A1322 856A1323 856A1488
1 1 1 1
warning notice 0.75 in. square drive socket 2ft. long breaker bar access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) BORESCOPE-KIT BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE MOTOR, DRIVE - CORE ENGINE ROTATION
EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2619
Material No.
CP2656
Material No.
CP8001
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * lockwire 0.032in.(0.8mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-42-00-290-007 72-42-00-290-041 72-52-00-290-004 72-63-00-000-002 72-63-00-400-002
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Borescope Inspection of the Inner Cowl Bolts of the Combustion Chamber Borescope Inspection of the Combustion Chamber Liners and Dome Area Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-000-002 80-11-10-400-002 NTM 720000 72-52-00-991-304 72-52-00-991-300 72-52-00-991-301 72-52-00-991-302
Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. Fig. Fig. Fig.
601 602 603 604
3. __________ Job Set-up Subtask 72-52-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B Subtask 72-52-00-010-056 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform. Subtask 72-52-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-52-00-010-057 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 601/TASK 72-52-00-991-304, 602/TASK 72-52-00-991-300, 603/TASK 72-52-00-991-301, 604/TASK 72-52-00-991-302) Subtask 72-52-00-869-051 A. Prepare for inspection: (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure that the borescope or fiberscope and light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Install the tools to turn the core engine. NOTE : The core engine may be turned using a breaker bar (see step ____ (a)) or with a drive motor (see step (b)).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
Core Rotation Drive Motor Installation Figure 601/TASK 72-52-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
Inspection of the HPT Blade Figure 602/TASK 72-52-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Rub Wear Notches on the Blade Tip and Cracks (Only Applicable NON /P Engines) Figure 603/TASK 72-52-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B
High-Pressure Turbine Blade Inspection Areas (Only Applicable NON /P Engines) Figure 604/TASK 72-52-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B (a) To turn the core manually with a breaker bar, do the steps that follow: 1 _
Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter (Ref. TASK 72-63-00-000-002).
2 _
Install a 0.75 in. square drive socket with a 2ft. long breaker bar into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward). NOTE : To turn the core engine CW, the handcranking drive must ____ be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 _
Remove the starter (Ref. TASK 80-11-10-000-002).
2 _
Install the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488 P01 or P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad shaft and engage the splines. NOTE : The tool must be installed in the horizontal position ____ with the air hoses to the rear.
3 _
Turn the tool until the captive bolts align with the gearbox bolt holes.
4 _
Tighten the two captive bolts by hand.
5 _
Install the clamp to secure the drive motor.
6 _
Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 _
Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(3) Remove one of the borescope plugs (S16 or S17) found immediately in front of the aft flange of the combustion case at the 5:30 and 8:30 oclock positions.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B (4) Connect the fiber light cable to the BORESCOPE-KIT (856A1320 P04 or P05), and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07). (5) Put the rigid borescope of the BORESCOPE-KIT (856A1320 P04 or P05) into the borescope port and turn on the light source of BORESCOPELIGHT SOURCE SET (856A1322 P03 or P04). Subtask 72-52-00-290-053 B. Do a borescope inspection : (1) Look at the trailing edge, tip concave and convex side of the HPT blades as follows: NOTE : There are 80 HPT blades installed in the rotor. ____ (a) Adjust the borescope equipment to obtain maximum clarity of view. (b) Turn the HPT rotor CW (aft looking forward). Stop the rotor at each blade to make sure all of the defects can be seen. NOTE : To turn the HPT rotor CW, the rotation pad drive must be ____ turned counterclockwise (CCW). (c) Inspect the HPT blades (from the rear) and use the limits that follow: NOTE : It is not easy to visually tell when cooling holes are ____ plugged. Cooling holes which are apparently plugged are permitted if any cracking, erosion or burning is within serviceable limits. NOTE : Crack indications which are not completely identified may ____ be sprayed with stoddard solvent (Material No. CP2011) or acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or an equivalent substitute to remove light engine deposits. NOTE : If a HPT blade has impact damage, you must do a 360 degree ____ combustor borescope inspection to look for combustor distress (Ref. TASK 72-42-00-290-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B NOTE : For the purposes of estimating the size of any distress, ____ the radial spacing of the trailing edge slots is approximately 0.1 in. (2.54 mm). ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Trailing edge for: NOTE : Casting core ____ lines are permitted. A. Cracks in area C and root fillet. Make sure that discoloration, scratches or marks are not seen as cracks.
If cracks are less than 0.10 in. (2.54 mm) long, reinspect in 400 cycles. If the cracks are more than 0.10 in. (2.54 mm) but less than 0.20 in. (5.08 mm), reinspect in 200 cycles. Cracks longer than 0.20 in. (5.08 mm) are not allowed.
B. Cracks in area B.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Cracks in area A.
One permitted, 0.10in. (2,54 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
D. Missing material. Burning, or holes in tip and area A.
Any amount down to the first slot below the tip shelf.
See limit extensions (Ref. TASK 72-00-00-200025).
E. Plugged air passages in area C.
Not serviceable.
F. Plugged air passages in area B.
One permitted.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Plugged air One permitted. passages in area A. H. Nicks and dents, area A.
Any amount, if there are no cracks or torn metal.
J. Nicks and dents, areas B, C, and root fillet.
3 permitted, 0.057 in. (1.45 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
K. Bent material at the tip, areas B or C.
Any amount.
L. Missing thermal barrier coating.
Any amount.
2. Blade tip for: NOTE : There can be 2 or 4 notched blades in the HPT rotor that are used to ____ show blade tip wear. The blade tip wears as it rubs against the shroud. The number of notches that can be seen is an indication of tip wear. It is possible that all tip notches can be gone because of wear. Missing notches have no effect on the serviceable condition of the blade. A. Radial cracks on convex side.
Any number permitted 0.15 in. (3.81 mm) long.
See limits extension (Ref. TASK 72-00-00-200025).
B. Radial cracks on concave side.
Any number up to 0.7 in. (17.78 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Bent, curled or missing material.
Any amount within 0.15 in. (3.81 mm) of tip.
D. Missing thermal barrier coating.
Any amount.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------3. Convex and concave surfaces for: A. Nicks or dents, area A.
Any number, 0.25 in. (6.35 mm) long.
B. Nicks or dents, area B.
Any number, 0.1 in. (2.54 mm) long.
C. Nicks or dents, area C.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
D. Cracks in other areas.
Not serviceable.
E. Missing thermal barrier coating.
Any amount.
See limit extensions (Ref. TASK 72-00-00-200025).
4. Blade airfoil for: A. Distortions or evidence of burning or melting.
Not serviceable.
B. Missing codep coating.
Any amount.
C. Evidence of foreign object impact damage.
None allowed.
See limit extensions (Ref. TASK 72-00-00-200025).
Inspect combustion chamber inner cowl bolts (Ref. TASK 72-42-00-290007).
(2) When the inspection is complete, turn off the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07) and remove the BORESCOPE-KIT (856A1320 P04 or P05).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B (3) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (4) Install the borescope plug. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE TWO LPT _______ STAGE 1 NOZZLE BORESCOPE PLUGS HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF THESE PLUGS IN THE COMBUSTION CASE WILL RESULT IN THE STEM BEING BURNED AWAY BY COMBUSTION GASSES. (a) Install the borescope plug(s) and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (5) Safety the plugs with lockwire 0.032in.(0.8mm) dia. (Material No. CP8001). (6) If no defects were found remove the tools used to rotate the core as follows: NOTE : If the breaker bar is installed see steps (a) and (b). If the ____ drive motor is installed see steps (c) and (d). (a) Remove the 0.75 in. (19.05 mm) square drive socket and 2 ft. (0.60 m) breaker bar from the core rotation drive pad. (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002). (c) Remove the drive motor from the starter pad of the AGB. (d) Install the starter (Ref. TASK 80-11-10-400-002). (7) If defects were found do a borescope inspection of the HPT blades from the front (Ref. TASK 72-52-00-290-004).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-52-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors without making thrust reverser serviceable (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-52-00-440-053 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-52-00-410-057 C. Close Access (1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the warning notice(s). (3) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B TASK 72-52-00-290-001- 01 R
Borescope Inspection of HPT Blades (from the front and the rear) 1. __________________ Reason for the Job Refer to the MPD TASK: 725000-C1 This TASK is applicable for /P and /3 engines. Inspection of the high pressure turbine (HPT) blades from the rear is limited to the areas that can be seen with a rigid borescope, at the 5:30 and 8:30 oclock borescope ports (S16 and S17). The borescope ports at the 5:30 and 8:30 oclock positions are located immediately in front of the combustion case aft flange. Inspection of the HPT blades from the front can be accomplished, if required, with a flexible borescope through the spark igniter ports (S10 and S11) of the combustion case.
R
NOTE : There are 80 HPT blades installed in the rotor. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No
specific specific specific specific specific
856A1320 856A1322 856A1323 856A1488
1 1 1 1
warning notice 0.75 in. square drive socket 2ft. long breaker bar access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) BORESCOPE-KIT BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE MOTOR, DRIVE - CORE ENGINE ROTATION
EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2619
Material No.
CP2656
Material No.
CP8001
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * lockwire 0.032in.(0.8mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-42-00-290-007 72-42-00-290-041 72-52-00-290-004 72-63-00-000-002 72-63-00-400-002
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Borescope Inspection of the Inner Cowl Bolts of the Combustion Chamber Borescope Inspection of the Combustion Chamber Liners and Dome Area Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-000-002 80-11-10-400-002 NTM 720000 72-52-00-991-304 72-52-00-991-300 72-52-00-991-305 72-52-00-991-306 72-52-00-991-308
Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. Fig. Fig. Fig. Fig.
601 602 605 606 607
3. __________ Job Set-up Subtask 72-52-00-941-055 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
C F M 56-5B Subtask 72-52-00-010-060 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform. Subtask 72-52-00-040-055 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-52-00-010-061 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 601/TASK 72-52-00-991-304, 602/TASK 72-52-00-991-300, 605/TASK 72-52-00-991-305, 606/TASK 72-52-00-991-306, 607/TASK 72-52-00-991-308) Subtask 72-52-00-869-052 A. Prepare for inspection: (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure that the borescope or fiberscope and light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Install the tools to turn the core engine. NOTE : The core engine may be turned using a breaker bar (see step ____ (a)) or with a drive motor (see step (b)).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 619 Nov 01/08
C F M 56-5B
HP Blade Cracks (Applicable /P and /3 Engines) Figure 605/TASK 72-52-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/08
C F M 56-5B
High-Pressure Turbine Blade Inspection Areas (Only Applicable /P and /3 Engines) Figure 606/TASK 72-52-00-991-306 R EFF : 001-049, 051-099, 101-149, 151-199, Page 621 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-52-00
C F M 56-5B
HPT Blade Inspection (Only Applicable /P and /3 Engines) Figure 607/TASK 72-52-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/08
C F M 56-5B (a) To turn the core manually with a breaker bar, do the steps that follow: 1 _
Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter (Ref. TASK 72-63-00-000-002).
2 _
Install a 0.75 in. square drive socket with a 2ft. long breaker bar into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward). NOTE : To turn the core engine CW, the handcranking drive must ____ be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 _
Remove the starter (Ref. TASK 80-11-10-000-002).
2 _
Install the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488 P01 or P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad shaft and engage the splines. NOTE : The tool must be installed in the horizontal position ____ with the air hoses to the rear.
3 _
Turn the tool until the captive bolts align with the gearbox bolt holes.
4 _
Tighten the two captive bolts by hand.
5 _
Install the clamp to secure the drive motor.
6 _
Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 _
Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(3) Remove one of the borescope plugs (S16 or S17) found immediately in front of the aft flange of the combustion case at the 5:30 and 8:30 oclock positions.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 623 Nov 01/08
C F M 56-5B (4) Connect the fiber light cable to the BORESCOPE-KIT (856A1320 P04 or P05), and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07). (5) Put the rigid borescope of the BORESCOPE-KIT (856A1320 P04 or P05) into the borescope port and turn on the light source of BORESCOPELIGHT SOURCE SET (856A1322 P03 or P04). Subtask 72-52-00-290-055 B. Do a borescope inspection: (1) Look at the trailing edge, tip concave and convex side of the HPT blades as follows: (a) Adjust the borescope equipment to obtain maximum clarity of view. (b) Turn the HPT rotor CW (aft looking forward). Stop the rotor at each blade to make sure all of the defects can be seen. NOTE : To turn the HPT rotor CW, the rotation pad drive must be ____ turned counterclockwise (CCW). (c) Inspect the HPT blades (from the rear) and use the limits that follow: NOTE : It is not easy to visually tell when cooling holes are ____ plugged. Cooling holes which are apparently plugged are permitted if any cracking, erosion or burning is within serviceable limits. NOTE : Crack indications which are not completely identified may ____ be sprayed with stoddard solvent (Material No. CP2011) or acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or an equivalent substitute to remove light engine deposits. NOTE : If a HPT blade has impact damage, you must do a 360-degree ____ combustor borescope inspection to look for combustor distress (Ref. TASK 72-42-00-290-041) and inner cowl bolts (Ref. TASK 72-42-00-290-007).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 624 Nov 01/08
C F M 56-5B NOTE : For the purposes of estimating the size of any distress, ____ the radial spacing of the trailing edge slots is approximately 0.1 in. (2.54 mm). ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Trailing edge for: NOTE : Casting core ____ lines are permitted. A. Cracks in area B and C including root filet. Make sure that discoloration, scratches or marks are not seen as cracks.
For a crack up to 0.12 in. (3.0 mm) in length, the maximum reinspection interval is 400 cycles. For a crack more than 0.12 in. (3.0 mm) and up to 0.20 in. (5.1 mm) in length, the maximum reinspection interval is 200 cycles.
See limit extensions (Ref. TASK 72-00-00-200025).
B. Cracks in area A.
One permitted, 0.10in. (2.54 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Missing material. Burning, or holes in tip and area A.
No limit, as long as the missing material is not more than 0.50 in. x 0.50 in. (12.7 mm x 12.7 mm).
See limit extensions (Ref. TASK 72-00-00-200025).
D. Missing thermal barrier coating.
Any amount.
E. Plugged air passages in area C.
Not serviceable.
F. Plugged air passages in area B.
One permitted.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 625 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Plugged air One permitted. passages in area A. Any amount, if there are no cracks or torn metal.
J. Nicks and dents, areas B, C, and root fillet.
No limit, as long as the nicks and dents are not more than 0.01 in. (0.25 mm) long.
K. Bent material at the tip, areas B or C.
Any amount.
R R R R
H. Nicks and dents, area A.
2. Blade tip for: NOTE : There can be 2 or 4 notched blades in the HPT rotor that are used to ____ show blade tip wear. The blade tip wears as it rubs against the shroud. The number of notches that can be seen is an indication of tip wear. It is possible that all tip notches can be gone because of wear. Missing notches have no effect on the serviceable condition of the blade. A. Radial cracks on convex side not within 0.5 in. (12.7 mm) of trailing edge.
Any number up to 0.15 in. (3.81 mm) long.
See limits extension (Ref. TASK 72-00-00-200025).
B. Radial cracks on concave side not within 0.5 in. (12.7 mm) of trailing edge.
Any number up to 0.7 in. (17.78 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Bent, curled or missing material.
Any amount above tip shelf.
See limit extensions (Ref. TASK 72-00-00-200025).
D. Radial cracks (convex or
Any amount.
EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 626 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------concave) within 0.50 in. (12.7 mm) of trailing edge. E. Missing thermal barrier coating.
Any amount.
3. Convex and concave surfaces for: A. Nicks or dents, area A.
Any number, 0.25 in. (6.35 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
B. Nicks or dents, area B.
Any number, 0.1 in. (2.54 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Nicks or dents, area C.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
See limit extensions (Ref. TASK 72-00-00-200025).
D. Cracks in other areas.
Not serviceable.
E. Missing thermal barrier coating.
Any amount.
4. Blade airfoil for: A. Distortions or evidence of burning or melting.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
(2) When the inspection is complete, turn off the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07) and remove the BORESCOPE-KIT (856A1320 P04 or P05).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Nov 01/08
C F M 56-5B (3) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (4) Install the borescope plug. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE TWO LPT _______ STAGE 1 NOZZLE BORESCOPE PLUGS HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF THESE PLUGS IN THE COMBUSTION CASE WILL RESULT IN THE STEM BEING BURNED AWAY BY COMBUSTION GASSES. (a) Install the borescope plug(s) and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (5) Safety the plugs with lockwire 0.032in.(0.8mm) dia. (Material No. CP8001). (6) If no defects were found remove the tools used to rotate the core as follows: NOTE : If the breaker bar is installed see steps (a) and (b). If the ____ drive motor is installed see steps (c) and (d). (a) Remove the 0.75 in. (19.05 mm) square drive socket and 2 ft. (0.60 m) breaker bar from the core rotation drive pad. (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002). (c) Remove the drive motor from the starter pad of the AGB. (d) Install the starter (Ref. TASK 80-11-10-400-002). (7) If defects were found do a borescope inspection of the HPT blades from the front (Ref. TASK 72-52-00-290-004).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 628 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-52-00-410-060 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors without making thrust reverser serviceable (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-52-00-440-055 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-52-00-410-061 C. Close Access (1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the warning notice(s). (3) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 629 Nov 01/08
C F M 56-5B TASK 72-52-00-290-004 Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) 1. __________________ Reason for the Job This TASK is applicable for NON /P engines. Inspection of the high pressure turbine (HPT) blades from the front is limited to the areas that can be seen with a flexible borescope installed at the spark igniter ports (S10 and S11). NOTE : There are 80 HPT blades installed in the rotor. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific No specific 856A1310 856A1321 856A1322 856A1323 856A1488
1 1 1 1 1
access platform protective caps warning notice 0.75 in. square drive socket 2ft. long breaker bar KIT, BORESCOPE GUIDE - HP TURBINE FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE MOTOR, DRIVE - CORE ENGINE ROTATION
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-42-00-290-005 72-63-00-000-002 72-63-00-400-002 74-21-30-000-002 74-21-30-400-002
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Removal of the Spark Igniter Installation of the Spark Igniter
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 630 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-000-002 80-11-10-400-002 NTM 720000 72-52-00-991-304 72-52-00-991-300 72-52-00-991-301 72-52-00-991-302 72-52-00-991-303
Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. Fig. Fig. Fig. Fig.
601 602 603 604 608
3. __________ Job Set-up Subtask 72-52-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 631 Nov 01/08
C F M 56-5B Subtask 72-52-00-010-054 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-52-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-52-00-010-055 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 601/TASK 72-52-00-991-304, 602/TASK 72-52-00-991-300, 603/TASK 72-52-00-991-301, 604/TASK 72-52-00-991-302, 608/TASK 72-52-00-991-303) Subtask 72-52-00-290-052 A. Prepare for inspection: (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure the borescope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Install the tools to turn the core engine. NOTE : The core engine may be turned using a breaker bar (see step ____ (a)) or with a drive motor (see step (b)).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 632 Nov 01/08
C F M 56-5B
High-Pressure Turbine Blade (Only Applicable NON /P Engines) Figure 608/TASK 72-52-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 633 Nov 01/08
C F M 56-5B (a) To turn the core manually with a breaker bar, do the steps that follow: 1 _
Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter (Ref. TASK 72-63-00-000-002).
2 _
Install a 0.75 in. square drive socket with a 2ft. long breaker bar into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward). NOTE : To turn the core engine CW, the handcranking drive must ____ be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 _
Remove the starter (Ref. TASK 80-11-10-000-002).
2 _
Install the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488 P01 or P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad drive shaft and engage the splines. NOTE : The tool must be installed in the horizontal position ____ with the air hoses to the rear.
3 _
Turn the tool until the captive bolts align with the gearbox bolt holes.
4 _
Tighten the two captive bolts by hand.
5 _
Install the clamp to secure the drive motor.
6 _
Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 _
Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(3) Remove either one of the spark igniters (Ref. TASK 74-21-30-000-002). (4) Install the protective caps on the lead and the spark igniter. (5) Put the KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01) over the straightening rod.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 634 Nov 01/08
C F M 56-5B (6) Push the plastic guide tube and straightening rod into the combustion chamber through the spark igniter port (S10 or S11) as far as it will go. (7) Turn the pointed tab on the plastic guide tube to the rear of the engine and remove the straightening rod from the plastic guide tube. (8) Installation of the borescope: CAUTION : FOLLOW THE INSTRUCTIONS CAREFULLY FOR INSERTING OR REMOVING _______ THE FLEXIBLE BORESCOPE. DOING THE PROCEDURE INCORRECTLY WILL DAMAGE THE TIP CONTROL FUNCTION. (a) Connect the fiber light cable to the FIBERSCOPE SET (856A1321 P01 or P03) to the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07). (b) Align the borescope lens with one of the plastic tabs on the guide tube and install it into the tube. Make sure that the borescope tip is not moved up or down when putting it into the plastic guide tube. (c) Push the borescope through the plastic guide tube until the tip comes out of the end of the tube. (d) Push the tip of the borescope between the nozzle vanes by using the tip deflection control. (e) Turn on the light source of the BORESCOPE-LIGHT SOURCE SET (856A1322 P03 or P04). (f) Adjust the borescope equipment to get maximum clarity of view. (9) Turn the HPT rotor CW (aft looking forward). Stop the rotor at each blade to make sure all of the defects can be seen. NOTE : To turn the HPT rotor CW, the rotation pad drive must be ____ turned CCW. (10) Inspect the HPT blades (from the front) and use the limits that follow: NOTE : It is not easy to visually tell when cooling holes are ____ plugged. Cooling holes which are apparently plugged are permitted if any cracking, erosion or burning is within serviceable limits.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 635 Nov 01/08
C F M 56-5B NOTE : Crack indications which are not completely identified may be ____ sprayed with solvent (CP2011) or an equivalent substitute to remove light engine deposits. NOTE : When a HPT blade has impact damage, you must do a 360 degree ____ combustor borescope inspection to look for combustor distress (Ref. TASK 72-42-00-290-005). NOTE : For purposes of estimating the size of any distress, the ____ radial spacing of the trailing edge slots is approximately 0.1 in. (2.55 mm). ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Leading edge for: A. Axial and radial cracks in area A.
Any number 0.05 in. (1.27 mm) long if they do not connect more than 2 holes.
B. Axial and radial cracks in areas B and C, including root radius not intersecting nose or gill holes.
Not serviceable.
C. Nicks and dents in area A.
Any amount.
D. Nicks and dents in area B.
Any amount.
E. Nicks and dents in area C, including root radius.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
F. Axial nose or gill hole cracks, areas B and C.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
See limit extensions (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 636 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Radial nose or None allowed in area C, See limit extensions gill hole cracks, one permitted, 0.03 in. (Ref. TASK 72-00-00-200areas B and C. (0.76 mm) long in area 025). B. H. Dirt or environmental build-up.
Any amount.
J. Missing material in areas A and B.
Any amount provided cavity 2 not exposed (max 2 blades per engine). Repeat the inspection within 100 hours.
K. Missing material in area C.
Not serviceable.
L. Missing thermal barrier coating.
Any amount.
See limit extensions (Ref. TASK 72-00-00-200025).
2. Blade tip for: NOTE : There are 4 notched blades (90 degrees apart) in the HPT rotor to ____ show the amount of blade tip rubbing. If the notches can or cannot be seen, the condition is serviceable. A. Radial cracks on concave side.
Any number permitted 0.7 in. (17.78 mm) max radial length.
B. Bent, curled or missing material.
Any amount within 0.2 in. (5.08 mm) of tip.
C. Missing thermal barrier coating.
Any amount.
See limit extensions (Ref. TASK 72-00-00-200025).
3. Concave and convex surfaces for: A. Nicks or dents, area A.
Any number 0.25 in. (6.35 mm) long.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 637 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Nicks or dents, Any number, 0.1 in. area B. (2.54 mm) long. C. Nicks or dents, area C.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
D. Cracks, other areas.
Not serviceable.
E. Missing thermal barrier coating.
Any amount.
4. Blade airfoil for: A. Distortions or evidence of burning or melting.
Not serviceable.
B. Missing codep coating.
Any amount.
C. Missing thermal barrier coating.
Any amount.
(11) When the inspection is completed, turn off the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07) and remove the FIBERSCOPE SET (856A1321 P01 or P03) and guide tube. (12) Install the spark igniter (Ref. TASK 74-21-30-400-002). (13) Tools used to rotate the core as follows: (14) Remove the tools used to rotate the core as follows: NOTE : If the breaker bar is installed see steps (a) and (b). If the ____ drive motor is installed see steps (c) and (d). (a) Remove the 0.75 in. (19.05 mm) square drive socket and 2 ft. (0.6 mm) breaker bar from the core rotation drive pad.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 638 Nov 01/08
C F M 56-5B (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002). (c) Remove the drive motor from the starter pad of the AGB. (d) Install the starter (Ref. TASK 80-11-10-400-002). 5. Close-up ________ Subtask 72-52-00-410-054 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-52-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-52-00-410-055 C. Close Access (1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 639 Nov 01/08
C F M 56-5B TASK 72-52-00-290-004- 01 Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) 1. __________________ Reason for the Job This TASK is applicable for /P engines. Inspection of the high pressure turbine (HPT) blades from the front is limited to the areas that can be seen with a flexible borescope installed at the spark igniter ports (S10 and S11). NOTE : There are 80 HPT blades installed in the rotor. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific No specific 856A1310 856A1321 856A1322 856A1323 856A1488
1 1 1 1 1
access platform protective caps warning notice 0.75 in. square drive socket 2ft. long breaker bar KIT, BORESCOPE GUIDE - HP TURBINE FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE MOTOR, DRIVE - CORE ENGINE ROTATION
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-42-00-290-005 72-63-00-000-002 72-63-00-400-002 74-21-30-000-002 74-21-30-400-002
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Removal of the Spark Igniter Installation of the Spark Igniter
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Page 640 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-000-002 80-11-10-400-002 NTM 720000 72-52-00-991-304 72-52-00-991-300 72-52-00-991-305 72-52-00-991-306 72-52-00-991-307
Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. Fig. Fig. Fig. Fig.
601 602 605 606 609
3. __________ Job Set-up Subtask 72-52-00-941-054 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 641 Nov 01/08
C F M 56-5B Subtask 72-52-00-010-058 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-52-00-040-054 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-52-00-010-059 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 601/TASK 72-52-00-991-304, 602/TASK 72-52-00-991-300, 605/TASK 72-52-00-991-305, 606/TASK 72-52-00-991-306, 609/TASK 72-52-00-991-307) Subtask 72-52-00-290-054 A. Prepare for inspection: (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure the borescope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Install the tools to turn the core engine. NOTE : The core engine may be turned using a breaker bar (see step ____ (a)) or with a drive motor (see step (b)).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 642 Nov 01/08
C F M 56-5B
High-Pressure Turbine Blade (Only Applicable /P and /3 Engines) Figure 609/TASK 72-52-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 643 Nov 01/08
C F M 56-5B (a) To turn the core manually with a breaker bar, do the steps that follow: 1 _
Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter (Ref. TASK 72-63-00-000-002).
2 _
Install a 0.75 in. square drive socket with a 2ft. long breaker bar into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward). NOTE : To turn the core engine CW, the handcranking drive must ____ be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 _
Remove the starter (Ref. TASK 80-11-10-000-002).
2 _
Install the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488 P01 or P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad drive shaft and engage the splines. NOTE : The tool must be installed in the horizontal position ____ with the air hoses to the rear.
3 _
Turn the tool until the captive bolts align with the gearbox bolt holes.
4 _
Tighten the two captive bolts by hand.
5 _
Install the clamp to secure the drive motor.
6 _
Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 _
Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(3) Remove either one of the spark igniters (Ref. TASK 74-21-30-000-002). (4) Install the protective caps on the lead and the spark igniter. (5) Put the KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01) over the straightening rod.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 644 Nov 01/08
C F M 56-5B (6) Push the plastic guide tube and straightening rod into the combustion chamber through the spark igniter port (S10 or S11) as far as it will go. (7) Turn the pointed tab on the plastic guide tube to the rear of the engine and remove the straightening rod from the plastic guide tube. (8) Installation of the borescope: CAUTION : FOLLOW THE INSTRUCTIONS CAREFULLY FOR INSERTING OR REMOVING _______ THE FLEXIBLE BORESCOPE. DOING THE PROCEDURE INCORRECTLY WILL DAMAGE THE TIP CONTROL FUNCTION. (a) Connect the fiber light cable to the FIBERSCOPE SET (856A1321 P01 or P03) to the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07). (b) Align the borescope lens with one of the plastic tabs on the guide tube and install it into the tube. Make sure that the borescope tip is not moved up or down when putting it into the plastic guide tube. (c) Push the borescope through the plastic guide tube until the tip comes out of the end of the tube. (d) Push the tip of the borescope between the nozzle vanes by using the tip deflection control. (e) Turn on the light source of the BORESCOPE-LIGHT SOURCE SET (856A1322 P03 or P04). (f) Adjust the borescope equipment to get maximum clarity of view. (9) Turn the HPT rotor CW (aft looking forward). Stop the rotor at each blade to make sure all of the defects can be seen. NOTE : To turn the HPT rotor CW, the rotation pad drive must be ____ turned CCW. (10) Inspect the HPT blades (from the front) and use the limits that follow: NOTE : It is not easy to visually tell when cooling holes are ____ plugged. Cooling holes which are apparently plugged are permitted if any cracking, erosion or burning is within serviceable limits.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 645 Nov 01/08
C F M 56-5B NOTE : Crack indications which are not completely identified may be ____ sprayed with solvent (CP2011) or an equivalent substitute to remove light engine deposits. NOTE : When a HPT blade has impact damage, you must do a 360 degree ____ combustor borescope inspection to look for combustor distress (Ref. TASK 72-42-00-290-005). NOTE : For purposes of estimating the size of any distress, the ____ radial spacing of the trailing edge slots is approximately 0.1 in. (2.55 mm) . ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Leading edge for: A. Axial and radial cracks in area A.
Any number 0.05 in. (1.27 mm) long if they do not connect more than 2 holes.
B. Axial and radial cracks in areas B and C, including root radius not intersecting nose or gill holes.
Not serviceable.
C. Nicks and dents in area A.
Any amount.
D. Nicks and dents in area B.
Any amount.
E. Nicks and dents in area C, including root radius.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
F. Axial nose or gill hole cracks, areas B and C.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
See limit extensions (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 646 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Radial nose or None allowed in area C, See limit extensions gill hole cracks, one permitted, 0.03 in. (Ref. TASK 72-00-00-200areas B and C. (0.76 mm) long in area 025). B. H. Dirt or environmental build-up.
Any amount.
J. Missing material in areas A and B.
Any amount provided cavity 2 not exposed (max 2 blades per engine). Repeat the inspection within 100 hours.
K. Missing material in area C.
Not serviceable.
L. Missing thermal barrier coating.
Any amount.
See limit extensions (Ref. TASK 72-00-00-200025).
2. Blade tip for: NOTE : There are 2 notched blades in the HPT rotor to show the amount of ____ blade tip rubbing. If the notches can or cannot be seen, the condition is serviceable. A. Radial cracks on convex side not within 0.50 in. (12.7 mm) of trailing edge.
Any number up to 0.15 in. (3.8 mm) max radial length.
See limit extensions (Ref. TASK 72-00-00-200025).
B. Radial cracks on concave side not within 0.50 in. (12.7 mm) of trailing edge.
Any number up to 0.7 in. (17.8 mm) max length.
See limit extensions (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 647 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Radial cracks Any amount. (convex or concave) within 0.50 in. (12.7 mm) of trailing edge. D. Bent, curled or missing material.
Any amount above tip shelf.
E. Missing thermal barrier coating.
Any amount.
See limit extensions (Ref. TASK 72-00-00-200025).
3. Concave and convex surfaces for: A. Nicks or dents, area A.
Any number 0.25 in. (6.35 mm) long.
B. Nicks or dents, area B.
Any number, 0.1 in. (2.54 mm) long.
C. Nicks or dents, area C.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
D. Cracks,other areas.
Not serviceable.
E. Missing thermal barrier coating.
Any amount.
4. Blade airfoil for: A. Distortions or evidence of burning or melting.
Not serviceable.
B. Missing thermal barrier coating.
Any amount.
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Page 648 Nov 01/08
C F M 56-5B (11) When the inspection is completed, turn off the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07) and remove the FIBERSCOPE SET (856A1321 P01 or P03) and guide tube. (12) Install the spark igniter (Ref. TASK 74-21-30-400-002). (13) Tools used to rotate the core as follows: (14) Remove the tools used to rotate the core as follows: NOTE : If the breaker bar is installed see steps (a) and (b). If the ____ drive motor is installed see steps (c) and (d). (a) Remove the 0.75 in. (19.05 mm) square drive socket and 2 ft. (0.6 mm) breaker bar from the core rotation drive pad. (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002). (c) Remove the drive motor from the starter pad of the AGB. (d) Install the starter (Ref. TASK 80-11-10-400-002). 5. Close-up ________ Subtask 72-52-00-410-058 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-52-00-440-054 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 649 Nov 01/08
C F M 56-5B Subtask 72-52-00-410-059 C. Close Access (1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 650 Nov 01/08
C F M 56-5B HPT SHROUD AND STAGE 1 LPT NOZZLE ASSEMBLY - DESCRIPTION AND OPERATION ______________________________________________________________________ 1. _______ General (Ref. Fig. 001) A. HPT shroud and stage 1 LPT nozzle assembly (1) The high pressure turbine (HPT) shroud and stage 1 low pressure turbine (LPT) nozzle assembly is located inside the aft end of the combustion case. It forms the interface between the core section and the LPT module of the engine. The forward flange of the assembly is rabbeted and bolted to the inner surfaces of the combustion case. The aft flange is bolted between the combustion case aft flange and the LPT stator forward flange. (2) The shroud/nozzle support has a thermal response matched to the rotor to provide good tip clearance control and structural stability. An air cavity between the shroud/nozzle support and the combustion case directs mixed 5th and 9th stage compressor bleed air onto the support and the outer, or backside, of the shrouds. This cooling air maintains closer clearances between the shrouds and the rotor blades. (3) The stage 1 LPT nozzles direct the core engine exhaust gas onto the stage one LPT blades. An air cavity between the stage one nozzle support and the combustion case directs 5th stage compressor bleed air through the nozzle vanes for cooling. After passing through the vanes, the air pressurizes and cools the cavity between the aft side of the HPT rotor and the forward side of the LPT rotor. 2. Description ___________ A. HPT shroud and stage 1 LPT nozzle assembly The HPT shroud and stage 1 LPT nozzle assembly consists of the shroud/nozzle support and HPT shrouds, and the stage 1 nozzles, inner air seal, and stationary air seal. (1) The shroud/nozzle support forms the outer shell of the assembly and provides an air space or manifold area between the outer shell and the combustion case. High pressure compressor (HPC) bleed air is introduced into the manifold area to provide cooling for the HPT shrouds and the LPT nozzles. (2) The HPT shrouds have a smooth abrasive rub surface that is tolerant to localized blade tip rubs and has good resistance to erosion from hot exhaust gases. The shrouds are held in place on the support by retainers and are individually replaceable.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
HPT Shroud and Stage 1 LPT Nozzle Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B (3) The assembly has 28 LPT nozzle segments, each having 3 vanes. The nozzle segments are installed in the shroud/nozzle support and are held in place on the nozzle inner air seal by the stationary air seal which is bolted on the aft face of the inner air seal. The assembly is bolted between the LPT case forward flange and the combustion case aft flange. Borescope ports at 5.30 and 8.30 oclock positions (ALF) are provided in the support to allow inspection of the nozzle area.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B HPT SHROUD AND STAGE 1 LPT NOZZLE ASSEMBLY - INSPECTION/CHECK _____________________________________________________________ TASK 72-53-00-290-003 Borescope/Inspection of the Stage 1 Low-Pressure Turbine Nozzle Assembly 1. __________________ Reason for the Job Inspection of the low pressure turbine (LPT) nozzle is limited to the areas that can be seen with a rigid borescope. Insert the borescope through the borescope ports located on stage 1 LPT nozzle support. If no defects are found then the borescope inspection is complete. If defects are found then look at the high-pressure turbine (HPT) shrouds. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET 1 MONITOR, RESOLUTION BORESCOPE
856A1320 856A1322 856A1323
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
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Page 601 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-53-00-290-004 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-53-00-991-300 72-53-00-991-301
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Borescope/Inspection of the High-Pressure Turbine Shroud Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602
3. __________ Job Set-up Subtask 72-53-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B Subtask 72-53-00-010-055 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-53-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-53-00-010-058 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-53-00-991-300, 602/TASK 72-53-00-991-301) Subtask 72-53-00-020-051 A. Remove the borescope plugs found immediately in front of the aft flange of the combustion case. Subtask 72-53-00-290-052 B. Do a borescope inspection. (1) Connect the fiber light cable to the BORESCOPE-KIT (856A1320P04/P05) and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make ____ sure the borescope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NDTM 720000).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B
Stage 1 LPT Nozzle and HPT Shroud Inspection Figure 601/TASK 72-53-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
Stage 1 LPT Nozzle Segment Figure 602/TASK 72-53-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B (2) Put the rigid borescope of the BORESCOPE-KIT (856A1320P04/P05), and to the port into turn on the light source of BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). (3) Inspect the stage 1 LPT nozzle and use the limits that follow : ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Stage 1 LPT nozzle for: A. Cracks in leading edge.
Any number, that are not more than 0.6 in. (15.24 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
B. Cracks in trailing edge.
Any number, that are not more than 0.8 in. (20.32 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Cracks on concave/convex side of airfoil between inner and outer platform.
Any number, that are not more than 1 in. (25.4 mm) long. If there is a separation of 0.25 in. between adjacent crack.
See limit extensions (Ref. TASK 72-00-00-200025).
D. Crack in radius in between airfoil L.E./T.E. and outer platform.
One on each airfoil, not more than 1.2 in. (30 mm) long with a minimum of 0.4 in. (10 mm) from any adjacent crack.
See limit extensions (Ref. TASK 72-00-00-200025).
E. Burns, erosion and corrosion
Any amount, if there is no missing material (no perforation of the airfoil cavity).
See limit extensions (Ref. TASK 72-00-00-200025).
F. Nicks, scores, scratches, dents or deposits on concave/convex surface or trailing edge
Any amount, not through, provided there are no cracks out of distressed area.
See limit extensions (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Nicks, dents, Any amount, if cracks See limit extensions tears in leading criteria are in the (Ref. TASK 72-00-00-200edge. limits. 025). H. Cracks in outer platform forward lip.
Two on each nozzle segment 0.59 in. (15 mm) apart minimum, if they run axially and do not grow longer circumferentially.
J. Cracks in inner or outer platform.
For NON /P engines. Any number no longer than 0.59 in. (15 mm). For /P engines. Three cracks per segment not to exceed 0.59 in. (15 mm) long and Metal does not go into the gaspath.
K. Craze cracking
Any amount
See limit extensions (Ref. TASK 72-00-00-200025).
NOTE : Craze cracking is defined as numerous superficial surface ____ cracks which have no visual width or depth. (4) If defects are found, look at the HPT shrouds (Ref. TASK 72-53-00290-004). Subtask 72-53-00-080-052 C. When the inspection is complete, turn off the light source BORESCOPELIGHT SOURCE SET (856A1322P02/ P03/P04/P07/P08), and remove the rigid borescope, BORESCOPE-KIT (856A1320P04/P05). Subtask 72-53-00-420-051 D. Install parts removed for borescope inspection. (1) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B (2) Install the borescope plugs and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (3) Wirelock the plugs with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). 5. Close-up ________ Subtask 72-53-00-410-055 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-53-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-53-00-410-058 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B TASK 72-53-00-290-004 Borescope/Inspection of the High-Pressure Turbine Shroud 1. __________________ Reason for the Job Inspection of the high pressure turbine (HPT) shrouds is limited to the areas that can be seen with a flexible borescope, at the spark igniter ports. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 856A1321 856A1322 856A1323 856A1351
1 1 1 1
protective caps warning notice access platform 1 m (3 ft. 3 in.) FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE GUIDE TUBE,BORESCOPE-HPT SHROUD
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 74-21-30-000-002 74-21-30-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-53-00-991-300 72-53-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Removal of the Spark Igniter Installation of the Spark Igniter Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 603
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-53-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-53-00-010-056 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-53-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-53-00-010-059 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-53-00-991-300) Subtask 72-53-00-010-057 A. Remove the spark igniters (Ref. TASK 74-21-30-000-002). (1) Install the protective caps on the leads and the spark igniters. Subtask 72-53-00-290-053 B. Do a borescope inspection: CAUTION : FOLLOW THE INSTRUCTIONS CAREFULLY FOR INSERTING OR REMOVING THE _______ FLEXIBLE BORESCOPE. DOING THE PROCEDURE INCORRECTLY WILL DAMAGE THE TIP CONTROL FUNCTION. R R
(1) Put the GUIDE TUBE,BORESCOPE-HPT SHROUD (856A1351G01), over the straightening rod. (2) Push the plastic guide tube and straightening rod into the combustion chamber as far as it will go. (3) Turn the pointed tab on the plastic guide tube to the rear of the engine and remove the straightening rod from the plastic guide tube. (4) Connect the FIBERSCOPE SET (856A1321P01/P03/P06), and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make ____ sure borescope and the light source are serviceable. See the Non Destructive Test Manual for this procedure (Ref. NDTM 720000). (5) Align the borescope lens with one of the plastic tabs on the guide tube and install it into the tube. Make sure that the borescope tip is not moved up or down when putting it into the plastic guide tube. (6) Push the borescope through the plastic guide tube until the tip comes out of the end of the tube. (7) Push the tip of the borescope between the nozzle vanes by using the tip deflection control. (8) Turn on the light source of BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08).
EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Feb 01/09
C F M 56-5B (9) Adjust the borescope equipment to obtain maximum clarity of view. (10) Inspect the HPT Shrouds: (Ref. Fig. 603/TASK 72-53-00-991-302) ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. HPT shrouds for: A. Cracks
Surface cracks permitted any number and any lenght axially across width in Surface A and B
See limit extensions (Ref. TASK 72-00-00-200025).
Any number of circumferential cracks that are not connected and are no more than 1 in. (25.3999 mm) long in Surface B
See limit extensions (Ref. TASK 72-00-00-200025).
Circumferential cracks that are connected to axial cracks cannot be over 0.25 in. (6.3499 mm) long and not less than 0.25 in. (6.3499 mm) from the shroud edge Surface A
See limit extensions (Ref. TASK 72-00-00-200025).
B. Burning/erosion
Any amount of material which is not there. (This include holes through the backstrip). Remaining material is not permitted to be in the flowpath.
C. Split-Line Aft Corners
Any amount of circumferential missing or distorted surface material less than 0.200 in. (5.08 mm) and axial missing or distorted
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-53-00 CES
Page 613 Nov 01/09
C F M 56-5B
HPT Shroud Thermal Densified Coating Limits Figure 603/TASK 72-53-00-991-302- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B
HPT Shroud Thermal Densified Coating Limits Figure 603/TASK 72-53-00-991-302- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------surface material less than 0.400 in. (10.16 mm) measured from the edge of the shroud. D. Rubs/wear
Any amount
E. Distortion
Any amount, if shroud is not in the flowpath.
F. Burn through on rub land
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025).
Subtask 72-53-00-080-053 C. When the inspection is completed, turn off the light source, BORESCOPELIGHT SOURCE SET (856A1322 P02/P03/P04/P07/P08) and remove the FIBERSCOPE SET (856A1321P01/P03/P06) and GUIDE TUBE,BORESCOPE-HPT SHROUD (856A1351G01). Subtask 72-53-00-410-056 D. Install the spark igniters (Ref. TASK 74-21-30-400-002). 5. Close-up ________ Subtask 72-53-00-410-057 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-53-00-440-053 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, R CES
Page 616 Nov 01/09
C F M 56-5B Subtask 72-53-00-410-059 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Nov 01/09
C F M 56-5B LPT ROTOR/STATOR ASSEMBLY - DESCRIPTION AND OPERATION _____________________________________________________ 1. _______ General (Ref. Fig. 001) A. The low pressure turbine (LPT) module is a 4-stage axial-flow turbine. It is mounted between the core engine and the turbine frame. The module consists of the following major assemblies : (1) Stages 2-4 LPT nozzle assemblies (LPT stator assembly). (2) LPT rotor assembly. 2. Description ___________ A. LPT Stator Assembly (Ref. Fig. 001, 002) The LPT assembly consists of the LPT case assembly, stages 2-4 LPT nozzle assemblies and the air cooling tubes and manifolds assembly. The nozzle assemblies consist of cast vane segments, and are installed inside the LPT case. (1) The LPT case is made of nickel alloy. The case front flange is bolted to the stage 1 nozzle support ; the rear flange of the LPT case is bolted to the outer front flange of the turbine frame. The LPT shroud support is mounted radially in line with the front flange of LPT case and the stage 1 outer stationary air seal. Six thermal insulation blankets are attached to the inner surface of LPT case. Each blanket is divided into segments and is designed to accommodate either the nozzle segment vane outer platforms or the outer air seal segments. The outer air seal segments are radially in line with stages 2, 3 and 4 of the LPT rotor. At its periphery, and in the vertical plane of the stage 2 nozzle assembly, the LPT case has instrumentation ports at nine specific locations. Nine EGT (T495) thermocouples are installed in these instrumentation ports. Each of the thermocouple probes is engaged through one specific nozzle segment of the stage 2 nozzle assembly. The LPT case has three other ports located lengthwise, at the 5 oclock position, aft looking forward. The three ports provide for the borescope inspection of the LPT internal ports. (2) The stage 2 LPT nozzle assembly consists of 18 nickel alloy segments with aluminization. Each nozzle segment has 7 vane airfoils. The segment inner platforms are retained by the inner stationary air seals, which are the fixed part of the inner interstage rotating air seals. One of the nozzle segments has a port for borescope inspection at the 5 oclock position (aft looking forward) and a hole to house one probe of exhaust gas temperature (EGT) harness. Eight other
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Low Pressure Turbine Rotor/Stator Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Low Pressure Turbine Rotor/Stator Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B nozzle segments also have one hole to accommodate one probe of the EGT harness. (3) The stage 3 LPT nozzle assembly consists of 20 nickel alloy segments of 6 vane airfoils each and is similar in design to the stage 2 nozzle assembly. One of the vane segments has a port for borescope inspection at the 5 oclock position (aft looking FWD). (4) The stage 4 LPT nozzle assembly consists of 22 nickel alloy segments of 6 vanes each and is similar in design to the stage 2 nozzle assembly. One of the nozzle segments has a port for borescope inspection at the 5 oclock position (aft looking FWD). (5) The LPT cooling system consists of 2 air cooling manifolds made of steel alloy and 2 tube halves made of steel alloy. Each manifold and tube half assembly is made up of 6 tubes provided with orifices which direct the air toward the LPT case. B. LPT Rotor Assembly (Ref. Fig. 003) (1) LPT disks are made of nickel alloy. The disk front flanges accommodate the blade retainer which provides axial retention of each blade stage assembly. They also retain the rotating air seals which control air passage between LPT nozzle assembly and rotor. The outer rim of disks has machined recesses accommodating the blade dovetails. (2) The stage 1 blade assembly consists of 162 tip-shrouded, nickel alloy blades with aluminization, equipped with antiwear shields. The front of the blade dovetails has a retaining lug which houses a blade retainer. Blade retainer is held axially by the rotating air seal. (3) The rotating air seals are made of nickel alloy. They are sandwich-mounted between stages 1, 2, 3 and 4 disks. They control air passage between the stator and the rotor. (4) Stages 2-4 of the LPT rotor are similar except for the following differences. Stages 2-3 LPT disks have 150 blades, equipped with antiwear shields, stage 4 LPT disk has 134 blades. The turbine rotor support is sandwich-mounted between the stage 3 rotating air seal and the stage 3 disk. (5) The turbine rotor support, made of nickel alloy, provides connection between the assembly of disks and the LPT shaft. It divides the LPT rotor inner enclosure into 2 separate cavities.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
Low Pressure Turbine Rotor Assembly Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B LPT ROTOR/STATOR ASSEMBLY - INSPECTION/CHECK ____________________________________________ TASK 72-54-00-290-005 Inspection of the Stage 1-3 Blades 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET
856A1320 856A1322
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-300 72-54-00-991-301 72-54-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603
3. __________ Job Set-up Subtask 72-54-00-941-056 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-066 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-056 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-075 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-54-00-991-300, 602/TASK 72-54-00-991-301, 603/TASK 72-54-00-991-302) Subtask 72-54-00-010-067 A. Removal of Borescope Plugs (1) Let the temperature of parts decrease to ambient temperature. PRE SB CFMI 72-0376 (2) Cut and remove the lockwires. Then, remove the borescope plugs S16, S17, S18, S19 and S20. NOTE : The borescope plugs S16 and S17 are in the same plane and ____ located, respectively, at 5:30 and 8:30 (ALF) immediately in front of the combustion case aft flange. The borescope plugs S18, S19 and S20 are located approximately at 5:00 oclock (ALF) on the LPT case and, from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT, respectively. END OF PRE SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B
Location of the Borescope Ports and Possible Borescope Access Via One Instrumentation Boss Figure 601/TASK 72-54-00-991-300- 14 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, Page 604 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-54-00
C F M 56-5B
Location of the Borescope Ports and Possible Borescope Access Via One Instrumentation Boss Figure 601/TASK 72-54-00-991-300- 24 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, Page 605 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-54-00
C F M 56-5B
Location of the Borescope Ports and Possible Borescope Access Via One Instrumentation Boss Figure 601/TASK 72-54-00-991-300- 34 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, Page 606 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-54-00
C F M 56-5B
Location of the Borescope Ports and Possible Borescope Access Via One Instrumentation Boss Figure 601/TASK 72-54-00-991-300- 44 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, Page 607 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-54-00
C F M 56-5B
Low Pressure Turbine Borescope Inspection Figure 602/TASK 72-54-00-991-301- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B
Low Pressure Turbine Borescope Inspection Figure 602/TASK 72-54-00-991-301- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B
Low Pressure Turbine Borescope Inspection Figure 602/TASK 72-54-00-991-301- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
72-54-00 CES
Page 611 Feb 01/98
C F M 56-5B
R R
Low Pressure Turbine Blades and Nozzle Damage Description Figure 603/TASK 72-54-00-991-302- 14 (SHEET 1)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B
R R
Low Pressure Turbine Blades and Nozzle Damage Description Figure 603/TASK 72-54-00-991-302- 24 (SHEET 2)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B
R R
Low Pressure Turbine Blades and Nozzle Damage Description Figure 603/TASK 72-54-00-991-302- 34 (SHEET 3)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B
R R
Low Pressure Turbine Blades and Nozzle Damage Description Figure 603/TASK 72-54-00-991-302- 44 (SHEET 4)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B POST SB CFMI 72-0376 (3) Cut and remove the lockwires. Then, remove the borescope plugs S16, S17. NOTE : The borescope plugs S16 and S17 are in the same plane and ____ located, respectively, at 5:30 and 8:30 (ALF) immediately in front of the combustion case aft flange. (4) Remove the self locking borescope cap assemblies S18, S19 and S20. NOTE : The borescope cap assemblies S18, S19 and S20 are located ____ approximately at 5:00 oclock (ALF) on the LPT case and, from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT, respectively. END OF SB CFMI 72-0376 Subtask 72-54-00-480-054 B. Install the BORESCOPE-KIT (856A1320P04/P05) as follows: (1) Connect the power supply. CAUTION : BEFORE YOU CONNECT THE POWER SUPPLY TO THE POWER SOURCE BE _______ SURE THE ON-OFF SWITCH IS IN THE OFF POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM. MAKE SURE THAT PROJECTOR AND POWER SUPPLY ARE CORRECTLY GROUNDED. (a) Connect the power supply to a grounded, power source. (2) Connect light source cable to rigid borescope and to port on BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08) . (3) Turn light source on; insert borescope and position it as desired for inspection. Subtask 72-54-00-290-054 C. The stage 1-3 LPT rotor blades are long span blades. To fully examine the airfoil surface, it is recommended to do as follows: (1) Turn the fan rotor slowly and smoothly to examine the blades. (2) Change the probe engagement depth so as to see the blade airfoils as they move in front of the probe.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/08
C F M 56-5B (3) While you adjust the probe engagement depth, turn the probe about its axis (azimuth) to get a maximum view, for a given turn speed of the rotor. NOTE : The blade span increases from the 2nd to the 3rd LPT stage. As ____ the full engagement of the probe is necessary, you may have to make more than one turn of the LPT rotor to see all the blade airfoils. (4) When you look at the leading edges of the blades, turn the rotor so that their concave side (pressure face) comes toward the borescope. (5) To look at the trailing edges, turn the rotor in the opposite direction so that the convex side (suction face) of the blades comes toward the borescope. (6) Do the inspection of the stage 1-3 blades for the damage which follow: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Cracks
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
2. Nicks on concave or convex sides. Does not include areas E.
Not more than 0.01 in. (0.25 mm) deep for stage 1 and 0.02 in. (0.5 mm) deep for stage 2-3.
See limit extensions (Ref. TASK 72-00-00-200025)
3. Dents on concave or convex sides. Does not include areas E.
Not more than 0.01 in. (0.25 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
4. Nicks and/or dents on leading or trailing edges. Does not include areas E.
Not more than 0.02 in. (0.5 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
5. Nicks and/or dents in areas E.
Not more than 0.01 in. (0.25 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
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Page 617 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------6. Rubbing on leading Not more than 0.01 in. See limit extensions edge platform , (0.25 mm) deep (Ref. TASK 72-00-00-200leading edge root 025) radius in area E. 7. Distortion of leading edges caused by overtemperature.
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025) See limit extensions (Ref. TASK 72-00-00-200025)
R
8. Pretwist clearances 0.1 in. (2.54 mm) max of such that adjacent total gap for stage 1. interlocks do not Not serviceable for touch each other. stage 2-3. For CFM56-5B non/P engines
R R R R
9. Stage 1, 2 and 3 Not more than 0.0150 in. blades tip shroud out (0.38 mm). of flush. For CFM56-5B/P engines
See limit extensions (Ref. TASK 72-00-00-200025)
R R R R
10. Stage 1 blades tip shroud out of flush.
Not more than 0.0433 in. (1.10 mm), and not more than 0.0315 in. (0.80 mm) on the hard faces.
See limit extensions (Ref. TASK 72-00-00-200025)
R R R R
11. Stage 2 blades tip shroud out of flush.
Not more than 0.0472 in. (1.20 mm), and not more than 0.0354 in. (0.90 mm) on the hard faces.
See limit extensions (Ref. TASK 72-00-00-200025)
R R R R
12. Stage 3 blades tip shroud out of flush.
Not more than 0.0433 in. (1.10 mm), and not more than 0.0354 in. (0.90 mm) on the hard faces.
See limit extensions (Ref. TASK 72-00-00-200025)
R R R
13. Stage 1 blades root platform out of flush.
Not more than 0.0198 in. (0.50 mm).
See limit extensions (Ref. TASK 72-00-00-200025)
R R R R
14. Stage 2 and 3 blades Not more than 0.0236 in. root platform out of (0.60 mm). flush. For ALL CFM56-5B engines
See limit extensions (Ref. TASK 72-00-00-200025)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
R R R R R R R R R R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------15. Shingled or Not serviceable If you find the blade tip unlatched tip shrouds shingled or shrouds. unlatched on different borescope inspections, it may be the sign of a wear of the hard-facing on the blade tip interlock surfaces. See limit extensions (Ref. TASK 72-00-00-200025)
R R
16. Deposit material, peeling off on airfoil.
Any amount provided there is no evidence of bowing and/or melting.
R
17. Rubbing/scratches on forward face of root platform
Any amount
R
18. Blades seal teeth wear.
1/2 of tooth height worn if only one stage is affected. 1/3 of tooth height worn if 2 stages are affected. 1/4 of tooth height worn if 3 stages are affected.
R
19. Corrosion / Pitting
For CFM56-5B/P engines: Any amount
Subtask 72-54-00-080-054 D. Removal of Borescope (1) When inspection is complete, turn lamp switch off, leave main light source blower on for a while to cool lamp and housing. (2) Remove the borescope.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 619 Nov 01/08
C F M 56-5B Subtask 72-54-00-410-066 E. Install the Borescope Plugs PRE SB CFMI 72-0376 (1) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads of the borescope plugs S16, S17, S18, S19, S20 and install on the combustion case (S16, S17) and on the LPT case (S18, S19, S20). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (2) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads of the borescope plugs S16, S17 and on the combustion case (S16, S17). (3) Apply graphite grease (Material No. CP2101) to the threads of the self locking borescope cap assemblies S18, S19, S20 and install on the LPT case (S18, S19, S20). END OF SB CFMI 72-0376 PRE SB CFMI 72-0376 (4) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (5) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (6) TORQUE self locking borescope caps assembly to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). NOTE : To achieve the correct installation of the self locking ____ borescope cap assembly, the slot of its ring must be positioned on the borescope boss lug at the final tightening. END OF SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-54-00-410-067 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-056 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-076 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 621 Nov 01/08
C F M 56-5B TASK 72-54-00-290-006 Inspection of the Stage 4 Blades 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET
856A1320 856A1322
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-54-00-210-004 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-300 72-54-00-991-301 72-54-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Optional Visual Inspection of the Stage 4 Blades from the Rear of the Engine Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603
3. __________ Job Set-up Subtask 72-54-00-941-057 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 623 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-068 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-057 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-076 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-54-00-991-300, 602/TASK 72-54-00-991-301, 603/TASK 72-54-00-991-302) Subtask 72-54-00-010-069 A. Remove the Plugs which Follow (1) Let the temperature of parts decrease to ambient temperature. PRE SB CFMI 72-0376 (2) Cut and remove the lockwire from the borescope plug S20. Remove the plug. NOTE : The plug S20 is the aftmost borescope plug located at 5:00 ____ oclock on the LPT case (ALF). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 624 Nov 01/08
C F M 56-5B (3) Remove the self locking borescope cap assembly S20. NOTE : The plug S20 is the aftmost borescope cap assembly located at ____ 5:00 oclock on the LPT case (ALF). END OF SB CFMI 72-0376 (4) Locate the instrumentation boss located at the 8:30 oclock position (ALF) on the turbine frame. (a) Remove the 2 bolts and nuts which attach a blanking plug to this turbine frame boss. (b) Remove the blanking plug and its gasket. NOTE : This gives you a borescope access to look at the trailing ____ edge and tip shroud of the stage 4 LPT blades. Subtask 72-54-00-480-055 B. Install the BORESCOPE-KIT (856A1320P04/P05) as follows: (1) Connect the power supply. CAUTION : BEFORE YOU CONNECT THE POWER SUPPLY TO THE POWER SOURCE BE _______ SURE THE ON-OFF SWITCH IS IN THE OFF POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM. MAKE SURE THAT PROJECTOR AND POWER SUPPLY ARE CORRECTLY GROUNDED. (a) Connect the power supply to a grounded 110 VAC 60Hz power source. (2) Connect light source cable to rigid borescope and to port on BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). (3) Turn light source on; insert borescope and position it as desired for inspection. Subtask 72-54-00-290-055 C. The stage 4 LPT rotor blades are long span blades. To fully examine their airfoil surface, it is recommended to do these steps. (1) Turn the fan rotor slowly and smoothly to examine the blades. (2) Change the probe engagement depth to see the airfoils as the blades move in front of the probe.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 625 Nov 01/08
C F M 56-5B (3) While you change the probe engagement depth, turn the probe (azimuth). This will let you have a maximum view for given turn speed of the rotor. NOTE : The stage 4 blades have the longest span of the blade stages. ____ So, as the full engagement of the probe is necessary, you may have to make 2, 3 or more turns of the LPT rotor to see all the blade areas. (4) When you look at the leading edges of the blades, turn the rotor so that the concave side (or pressure face) of the blades comes toward the borescope. (5) When you look at the trailing edges, turn the rotor in the opposite direction so that the convex side (suction face) comes toward the borescope. (6) Do the inspection of the stage 4 blades for the damage which follow: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Cracks
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
2. Nicks on concave or convex sides. Does not include area E.
Not more than 0.02 in. (0.5 mm) deep.
See limit extension (Ref. TASK 72-00-00-200025)
3. Dents on concave or convex sides. Does not include area E.
Not more than 0.01 in. (0.25 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
4. Nicks and/or dents on leading or trailing edges. Does not include area E.
Not more than 0.02 in. (0.5 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
5. Nicks and/or dents in area E.
Not more than 0.01 in. (0.25 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
R
For CFM56-5B non/P engines
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 626 Nov 01/08
R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------6. Tip shroud out of Not more than 0.0150 in. See limit extensions flush. (0.38 mm). (Ref. TASK 72-00-00-200025). For CFM56-5B/P engines
R R
7. Tip shroud out of flush.
Not more than 0.0354 in. (0.90 mm).
See limit extensions (Ref. TASK 72-00-00-200025)
R R
8. Root platform out of flush.
Not more than 0.039 in. (1.0 mm).
See limit extensions (Ref. TASK 72-00-00-200025)
R R
R R R R R R R R R R R R
For ALL CFM56-5B engines 9. Shingled or unlatched tip shrouds.
Not serviceable
If you find the blade tip shrouds shingled or unlatched on different borescope inspections, it may be the sign of a wear of the hard-facing on the blade tip interlock surfaces. The 4th stage blades may be unshingled or relatched by hand (Ref. TASK 72-5400-210-004) See limit extensions (Ref. TASK 72-00-00-200025) See NOTE below.
R
10. Hard-facing wear.
Any quantity that do not cause a mismatch of the blade tip shroud aft face of more than 0.12 in. (3.05 mm).
See limit extensions (Ref. TASK 72-00-00-200025). See NOTE below.
R
11. Blade airfoil pretwist that cause gaps such as interlocks do not touch each other.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025). See NOTE below.
R R R R
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------NOTE : If the aircraft maintenance schedule permits, it is recommended to ____ do a visual inspection when you find these defects. Blades that are shingled or unlatched may be put back in their correct interlock positions, in following the special procedure (Ref. TASK 72-54-00210-004). R
12. Distortion of leading edge caused by overtemperature.
Not serviceable
R
13. Deposit material peeling off airfoil.
Any amount, provided there is no evidence of bowing and/or melting.
Subtask 72-54-00-080-055 D. Removal of Borescope (1) When inspection is completed, turn lamp switch off, leave main light source blower on for a while to cool lamp and housing. (2) Remove the borescope. Subtask 72-54-00-410-068 E. Install the Borescope Plug S20 on the LPT Case PRE SB CFMI 72-0376 (1) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619), to the threads of the plug. END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (2) Apply graphite grease (Material No. CP2101) to the threads of the self locking borescope cap assembly. END OF SB CFMI 72-0376 PRE SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 628 Nov 01/08
C F M 56-5B (3) Install the plug on the LPT case. TORQUE to between 55 and 60 lbf.in (0.62 and 0.67 m.daN). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (4) Install the self locking borescope cap assemby on the LPT case. TORQUE to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). NOTE : To achieve the correct installation of the self locking ____ borescope cap assembly, the slot of its ring must be positioned on the borescope boss lug at the final tightening. END OF SB CFMI 72-0376 PRE SB CFMI 72-0376 (5) Safety the plug with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in (0.8 mm) dia. (Material No. CP8002). END OF PRE SB CFMI 72-0376 Subtask 72-54-00-410-089 F. Install the blanking plug on the turbine frame instrumention boss at 8:30 oclock (ALF) as follows: (1) Lubricate the threads of the 2 plug attachment bolts with graphite grease (Material No. CP2101). (2) Install the gasket on the blanking plug and engage the plug in the turbine frame boss. (3) Install the 2 bolts and the 2 nuts (self-locking) to attach the plug to the boss. (4) TORQUE the 2 nuts to between 95 and 110 lbf.in (1.07 and 1.24 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 629 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-54-00-410-069 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-057 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-077 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 630 Nov 01/08
C F M 56-5B TASK 72-54-00-290-007 Inspection of the Stage 2-4 Nozzle Segments 1. __________________ Reason for the Job This Task is only available for CFM56-5BX not/P engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 FIBERSCOPE SET 1 BORESCOPE-LIGHT SOURCE SET
856A1320 856A1321 856A1322
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 631 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-300 72-54-00-991-301 72-54-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603
3. __________ Job Set-up Subtask 72-54-00-941-058 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 632 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-070 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-058 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-077 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-54-00-991-300, 602/TASK 72-54-00-991-301, 603/TASK 72-54-00-991-302) Subtask 72-54-00-010-071 A. Remove Borescope Plugs (1) Let the temperature of the parts decrease to ambient temperature. PRE SB CFMI 72-0376 (2) Cut and remove the lockwires and remove the LPT borescope plugs S18, S19, S20. NOTE : The borescope plugs S18, S19, S20 are located approximately at ____ 5:00 oclock (ALF) on the LPT case, and from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT respectively. END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 633 Nov 01/08
C F M 56-5B (3) Remove the self locking borescope cap assemblies S18, S19, S20. NOTE : The borescope cap assemblies S18, S19, S20 are located ____ approximately at 5:00 oclock (ALF) on the LPT case, and from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT respectively. END OF SB CFMI 72-0376 Subtask 72-54-00-480-056 R R
B. Installation of the BORESCOPE-KIT (856A1320P04/P05) or FIBERSCOPE SET (856A1321P03/P05/P06) as follows: (1) Connect the power supply. CAUTION : BEFORE YOU CONNECT THE POWER SUPPLY TO THE POWER SOURCE BE _______ SURE THE ON-OFF SWITCH IS IN THE OFF POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM. MAKE SURE THAT PROJECTOR AND POWER SUPPLY ARE CORRECTLY GROUNDED. (a) Connect the power supply. (2) Connect light source cable to rigid borescope and to port on BORESCOPE-LIGHT SOURCE SET (856A1322/P02/P03/P04/P07/P08). (3) Turn light source on; insert borescope and position it as desired for inspection.
R R
(a) If you use flexible borescope, make sure that it is correctly adjusted. Subtask 72-54-00-290-056
R
C. Inspection of the stage 2-4 nozzle segment for the following:
R R
NOTE : You can use a rigid borescope or a flexible borescope to do this ____ inspection.
R R
NOTE : If you use the rigid borescope, the following limits are given for ____ nozzle segments you can see near the borescope holes.
R R
NOTE : LPT stage 2 and 4 nozzles have six airfoils for each segment. LPT ____ stage 3 nozzles have seven airfoils for each segment.
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 634 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------R R R R R
1. Cracks in trailing and leading edges.
See limit extensions (Ref. TASK 72-00-00-200025).
One crack maximum for each nozzle segment that is 0.5 in. (12.7 mm) (1/3 of the chord width) to 1.0 in. (25.4 mm) in length (2/3 of the chord width).
See limit extensions (Ref. TASK 72-00-00-200025).
R R R R R R R
Any quantity (leading or trailing edge) if cracks are less than 0.5 in. (12.7 mm) in length (1/3 of the chord width).
R
2. Nicks and/or dents on leading and/or trailing edges.
Any quantity, provided cracks criteria are met.
See limit extensions (Ref. TASK 72-00-00-200025).
R
3. Nicks and/or dents on concave and/or convex sides.
Any quantity, provided cracks criteria are met.
See limit extensions (Ref. TASK 72-00-00-200025).
R R
4. Burned areas, hot spots, discoloration.
Any quantity, if there is no missing material and you see no bowing and/or melting.
See limit extensions (Ref. TASK 72-00-00-200025).
R
5. Material particles peeling off on airfoil.
Any quantity, if you see no bowing and/or melting.
Subtask 72-54-00-080-056 D. Removal of Borescope (1) When inspection is complete, turn lamp switch off, leave main light source blower on for a while to cool lamp and housing. (2) Remove the borescope.
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 635 Nov 01/09
C F M 56-5B Subtask 72-54-00-410-070 E. Install Borescope Plugs PRE SB CFMI 72-0376 (1) Apply graphite grease (Material No. CP2101) to the threads of the borescope plugs S18, S19, S20 and install on the LPT case. END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (2) Apply graphite grease (Material No. CP2101) to the threads of the borescope cap assemblies S18, S19, S20 and install on the LPT case. END OF SB CFMI 72-0376 PRE SB CFMI 72-0376 (3) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (4) TORQUE self locking borescope cap assemblies to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). NOTE : To achieve the correct installation of the self locking ____ borescope cap assembly, the slot of its ring must be positioned on the borescope boss lug at the final tightening. END OF SB CFMI 72-0376
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, R CES
Page 636 Nov 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-54-00-410-071 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-058 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-078 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, R CES
Page 637 Nov 01/09
C F M 56-5B TASK 72-54-00-290-007- 01 Inspection of the Stage 2-4 Nozzle Segments 1. __________________ Reason for the Job R
This Task is only available for CFM56-5BX /P engines and /3 engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 FIBERSCOPE SET 1 BORESCOPE-LIGHT SOURCE SET
856A1320 856A1321 856A1322
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 638 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-300 72-54-00-991-305 72-54-00-991-306
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 604 Fig. 605
3. __________ Job Set-up Subtask 72-54-00-941-067 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 639 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-093 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-066 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-094 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-54-00-991-300, 604/TASK 72-54-00-991-305, 605/TASK 72-54-00-991-306) Subtask 72-54-00-010-095 A. Remove Borescope Plugs (1) Let the temperature of the parts decrease to ambient temperature. PRE SB CFMI 72-0376 (2) Cut and remove the lockwires and remove the LPT borescope plugs S18, S19, S20. NOTE : The borescope plugs S18, S19, S20 are located approximately at ____ 5:00 oclock (ALF) on the LPT case, and from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT respectively. END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 640 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-54-00 CES
Page 641 Aug 01/09
C F M 56-5B
Illustration of the Low Pressure Turbine Figure 604/TASK 72-54-00-991-305- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 642 Nov 01/08
C F M 56-5B
Illustration of the Low Pressure Turbine Figure 604/TASK 72-54-00-991-305- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 643 Nov 01/08
C F M 56-5B
Illustration of the Low Pressure Turbine Figure 604/TASK 72-54-00-991-305- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 644 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-54-00 CES
Page 645 Nov 01/08
C F M 56-5B
Illustration of the Low Pressure Turbine Blades and Nozzle Damage Figure 605/TASK 72-54-00-991-306- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 646 Nov 01/08
C F M 56-5B
Illustration of the Low Pressure Turbine Blades and Nozzle Damage Figure 605/TASK 72-54-00-991-306- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 647 Nov 01/08
C F M 56-5B
Illustration of the Low Pressure Turbine Blades and Nozzle Damage Figure 605/TASK 72-54-00-991-306- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 648 Nov 01/08
C F M 56-5B (3) Remove the self locking borescope cap assemblies S18, S19, S20. NOTE : The borescope cap assemblies S18, S19, S20 are located ____ approximately at 5:00 oclock (ALF) on the LPT case, and from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT respectively. END OF SB CFMI 72-0376 Subtask 72-54-00-480-058 R R
B. Installation of the BORESCOPE-KIT (856A1320P04/P05) or FIBERSCOPE SET (856A1321P03/P05/P06) as follows: (1) Connect the power supply. CAUTION : BEFORE YOU CONNECT THE POWER SUPPLY TO THE POWER SOURCE BE _______ SURE THE ON-OFF SWITCH IS IN THE OFF POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM. MAKE SURE THAT PROJECTOR AND POWER SUPPLY ARE CORRECTLY GROUNDED. (a) Connect the power supply. (2) Connect light source cable to rigid borescope and to port on BORESCOPE-LIGHT SOURCE SET (856A1322/P02/P03/P04/P07/P08). (3) Turn light source on; insert borescope and position it as desired for inspection.
R R
(a) If you use flexible borescope, make sure that it is correctly adjusted. Subtask 72-54-00-290-058
R
C. Inspection of the stage 2-4 nozzle segment for the following:
R R
NOTE : You can use a rigid borescope or a flexible borescope to do this ____ inspection.
R R
NOTE : If you use the rigid borescope, the following limits are given for ____ nozzle segments you can see near the borescope holes.
R R
NOTE : LPT stage 2 and 4 nozzles have six airfoils for each segment. LPT ____ stage 3 nozzles have seven airfoils for each segment.
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 649 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------R R R R R R
1. Cracks in trailing and leading edges.
See limit extensions (Ref. TASK 72-00-00-200025).
One crack maximum for each nozzle segment that is 0.5 in. (12.7 mm) (1/3 of the chord width) to 1.0 in. (25.4 mm) in length (2/3 of the chord width).
See limit extensions (Ref. TASK 72-00-00-200025).
R R R R R R R
Any quantity (leading or trailing edge) if cracks are less than 0.5 in. (12.7 mm) in length (1/3 of the chord width).
R
2. Nicks and/or dents on leading and/or trailing edges.
Any quantity, provided cracks criteria are met.
See limit extensions (Ref. TASK 72-00-00-200025).
R
3. Nicks and/or dents on concave and/or convex sides.
Any quantity, provided cracks criteria are met.
See limit extensions (Ref. TASK 72-00-00-200025).
R R
4. Burned areas, hot spots, discoloration.
Any quantity, if there is no missing material and you see no bowing and/or melting.
See limit extensions (Ref. TASK 72-00-00-200025).
R
5. Material particles peeling off on airfoil.
Any quantity, if you see no bowing and/or melting.
Subtask 72-54-00-080-058 D. Removal of Borescope (1) When inspection is complete, turn lamp switch off, leave main light source blower on for a while to cool lamp and housing. (2) Remove the borescope.
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 650 Nov 01/09
C F M 56-5B Subtask 72-54-00-410-095 E. Install Borescope Plugs PRE SB CFMI 72-0376 (1) Apply graphite grease (Material No. CP2101) to the threads of the borescope plugs S18, S19, S20 and install on the LPT case. END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (2) Apply graphite grease (Material No. CP2101) to the threads of the borescope cap assemblies S18, S19, S20 and install on the LPT case. END OF SB CFMI 72-0376 PRE SB CFMI 72-0376 (3) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (4) TORQUE self locking borescope cap assemblies to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). NOTE : To achieve the correct installation of the self locking ____ borescope cap assembly, the slot of its ring must be positioned on the borescope boss lug at the final tightening. END OF SB CFMI 72-0376
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, R CES
Page 651 Nov 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-54-00-410-096 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-066 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-097 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, R CES
Page 652 Nov 01/09
C F M 56-5B TASK 72-54-00-290-008 Inspection of the Stage 1-4 Stationary Air Seals 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET
856A1320 856A1322
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 653 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-300 72-54-00-991-301 72-54-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603
3. __________ Job Set-up Subtask 72-54-00-941-059 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 654 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-072 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Allow parts, to return to ambient temperature. Subtask 72-54-00-040-059 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-078 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-54-00-991-300, 602/TASK 72-54-00-991-301, 603/TASK 72-54-00-991-302) Subtask 72-54-00-010-084 A. Removal of the Borescope Plugs (1) Let the temperature of parts decrease to ambient temperature. PRE SB CFMI 72-0376 (2) Cut and remove the lockwires. Then, remove the borescope plugs S16, S17, S18, S19 and S20. NOTE : The borescope plugs S16 and S17 are in the same plane and ____ located respectively, at 5:30 and 8:30 (ALF) immediately in front of combustion case aft flange. The borescope plugs S18, S19 and S20 are located at 5:00 oclock (ALF) on the LPT case. From front to rear they relate approximately to the 2nd, 3rd and 4th LPT stages.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 655 Nov 01/08
C F M 56-5B END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (3) Cut and remove the lockwires. Then, remove the borescope plugs S16, S17. NOTE : The borescope plugs S16 and S17 are in the same plane and ____ located respectively, at 5:30 and 8:30 (ALF) immediately in front of the combustion case aft flange. (4) Remove the self locking borescope cap assemblies S18, S19 and S20. NOTE : The borescope cap assemblies S18, S19 and S20 are located at ____ 5:00 oclock (ALF) on the LPT case. From front to rear they relate approximately to the 2nd, 3rd and 4th LPT stages. END OF SB CFMI 72-0376 Subtask 72-54-00-480-057 B. Install the BORESCOPE-KIT (856A1320P04/P05) as follows: (1) Connect the power supply. CAUTION : BEFORE YOU CONNECT THE POWER SUPPLY TO THE POWER SOURCE BE _______ SURE THE ON-OFF SWITCH IS IN THE OFF POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM. MAKE SURE THAT PROJECTOR AND POWER SUPPLY ARE CORRECTLY GROUNDED. (a) Connect power supply to a grounded 110 VAC 60 Hz power source. (2) Connect light source cable to rigid borescope and to port on BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). (3) Turn light source on; insert borescope and position it as desired for inspection.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 656 Nov 01/08
C F M 56-5B Subtask 72-54-00-290-057 C. Inspect the Stage 1-4 Outer Stationary Air Seals for the Following NOTE : The limits given below are for the stationary air seal areas you ____ can see near the borescope holes. ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Stage 1-3 stationary air seals. A. Rub marks or chicken marks from seal teeth.
Not deeper than 0.08 in. (2.03 mm)
2. Stage 4 stationary air seals. NOTE : This inspection is only to be done when stage 4 blades are shingled ____ or unlatched. A. Worn, jagged or crushed honeycomb material.
Not more than 0.08 in. (2.03 mm)
See limit extensions (Ref. TASK 72-00-00-200025).
3. Stage 1/4 stationary air seals. A. Distortion
Any quantity if shroud does not come out.
Subtask 72-54-00-080-057 D. Removal of Borescope (1) When inspection is complete, turn lamp switch off, leave main light source blower on for a while to cool and housing. (2) Remove the borescope.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 657 Nov 01/08
C F M 56-5B Subtask 72-54-00-410-072 E. Install the Borescope Plugs PRE SB CFMI 72-0376 (1) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619), to the threads of the borescope plugs S16, S17, S18, S19, S20 and install on the combustion case (S16, S17) and on the LPT case (S18, S19, S20). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (2) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619), to the threads of the borescope plugs S16, S17 and install on the combustion case (S16, S17). (3) Apply graphite grease (Material No. CP2101) to the threads of the self locking borescope cap assemblies S18, S19, S20 and install on the LPT case (S18, S19, S20). END OF SB CFMI 72-0376 PRE SB CFMI 72-0376 (4) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002) END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (5) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (6) TORQUE the self locking borescope cap assemblies to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). NOTE : To achieve the correct installation of the self locking ____ borescope cap assembly, the slot of its ring must be positioned on the borescope boss lug at the final tightening.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 658 Nov 01/08
C F M 56-5B END OF SB CFMI 72-0376 5. Close-up ________ Subtask 72-54-00-410-073 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-059 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-079 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 659 Nov 01/08
C F M 56-5B TASK 72-54-00-210-004 Optional Visual Inspection of the Stage 4 Blades from the Rear of the Engine 1. __________________ Reason for the Job To do a direct, hands-on, visual inspection of the stage 4 LPT blades. During the borescope inspection of this blade stage (Ref. TASK 72-54-00-290-00600), on some rare occasions, you may see blades with their tip shroud shingled or unlatched, or with radial mismatches/out-of-flush defects or with gaps at their interlocks. This inspection is not mandatory since the Limit Extensions (Ref. TASK 72-00-00-200-02500) referred to in the borescope inspection of the stage 4 blades give the specific time/cycles of operation with these defects. However, it makes sense to prevent a further deterioration of the turbine stage, before the expiration of the permitted limit extensions. Therefore, a visual inspection is recommended as soon as possible after the finding of these defects, if the aircraft maintenance schedule permits. The benefits of this visual inspection are that you can: - put back some blades that are shingled/unlatched in the correct interlock positions - make a more accurate measurement of the mismatch (at the blade tip shrouds) than the estimate you can make from the borescope inspection - better see gaps, or areas of the blade interlocks that do not touch each other (the gaps are the result of the deterioration of the blade pretwist (angle) characteristic) - make an evaluation of the correct blade pretwist characteristic through a simple manual method. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 660 Nov 01/08
C F M 56-5B B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-303
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 606
3. __________ Job Set-up Subtask 72-54-00-941-063 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 661 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-085 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-063 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-086 D. Get Access (1) Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (2) Let the temperature of parts decrease to ambient temperature. 4. Procedure _________ (Ref. Fig. 606/TASK 72-54-00-991-303) Subtask 72-54-00-010-087 A. Removal for Access to the Inspection Area (1) Remove the core nozzle assembly (Ref. TASK 78-11-11-000-041). (2) Remove the centerbody (Ref. TASK 78-11-12-000-041). NOTE : The removal of these nacelle hot exhaust components is ____ necessary in order to get an unrestricted access to the turbine last stage, through the rear of the engine. Besides, this inspection necessitates some checks and corrective actions you can do only by hand.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 662 Nov 01/08
C F M 56-5B Subtask 72-54-00-210-055 B. Inspection of Defects Found during the Borescope Inspection (1) Shingling/Unlatching CAUTION : DO NOT HIT THE BLADES WITH A DRIFT AND A HAMMER TO PUT THEM _______ BACK IN THEIR CORRECT INTERBLOCKS. FURTHER DAMAGE TO THE BLADES COULD RESULT. IF NECESSARY, USE ONLY SHAPED TOOLS MADE OF HARDWOOD OR HARD PLASTICS MATERIAL AS PRYING OR PUSHING TOOLS. (a) Past experience has shown that it is possible to put back shingled/unlatched blades in their correct interlocking position. To do this, apply hand force as show in sheet 2. (Ref. Fig. 606/TASK 72-54-00-991-303) (b) If you can not remove the shingling/unlatching of two blades (or more) do no try further. Let expire the applicable limit extensions. Beyond these, it is up to the airline management to take the necessary hardware actions. (2) Hard-facing wear on the blade interlock surfaces. NOTE : A worn hard-facing may be at the origin of the shingling and ____ unlatching defects. This condition results in radial and axial mismatches at the blade tip shrouds which are no longer in the same alignment (radial out-of-flush, for example). (a) You can measure the interlock wear by the quantity of the aft mismatch of the blade tip shroud. (b) Use the honeycomb cells in the outer stationary air seal as a scale to measure the quantity of mismatch. One honeycomb cell is 0.06 in. (1.52 mm) in the largest dimension. If you are not sure, use modeling clay to get an imprint. Then, measure and record the value of the mismatch. The mismatch at the aft edge of the blade tip shroud must not be more than 0.12 in. (3.05 mm). (3) Blade pretwist check. CAUTION : DO NOT USE PLIERS IN ORDER TO CLOSE THE GAPS AND GET BACK _______ THEIR PRETWIST ANGLE. IT IS IMPOSSIBLE TO CORRECT THIS CONDITION.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 663 Nov 01/08
C F M 56-5B
R
Visual Inspection of the Stage 4 Blades Figure 606/TASK 72-54-00-991-303- 13 (SHEET 1)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 664 Aug 01/09
C F M 56-5B
R
Visual Inspection of the Stage 4 Blades Figure 606/TASK 72-54-00-991-303- 23 (SHEET 2)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 665 Aug 01/09
C F M 56-5B
R
Visual Inspection of the Stage 4 Blades Figure 606/TASK 72-54-00-991-303- 33 (SHEET 3)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 666 Aug 01/09
C F M 56-5B (a) An incorrect pretwist is shown by gaps and some mismatch at the blade tip shrouds (sheet 3). (Ref. Fig. 606/TASK 72-54-00-991-303) Result: the adjacent interlock surfaces do not touch each other as they should. This condition is not serviceable. - if you see that kind of defects, let expire the applicable limit extensions. Beyond these, let the airline management take the necessary hardware actions - if not, you may want to take the opportunity of full access to the stage 4 blades and do the manual check shown in sheet 1. (Ref. Fig. 606/TASK 72-54-00-991-303) Do the check on at least 2 blades in each quadrant to make a good evaluation of the pretwist characteristic. Subtask 72-54-00-410-086 C. Install the Exhaust Components Removed for Access to the Inspection Area (1) Install the centerbody (Ref. TASK 78-11-12-400-041). (2) Install the core nozzle assembly (Ref. TASK 78-11-11-400-041). 5. Close-up ________ Subtask 72-54-00-410-087 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-063 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-088 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s). EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, R CES
Page 667 Aug 01/09
C F M 56-5B
INTENTIONALLY BLANK
R 72-54-00 CES
Page 668 Aug 01/09
C F M 56-5B TASK 72-54-00-210-005 Inspection of the Turbine Case 1. __________________ Reason for the Job This TASK is applicable for NON /P engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-54-00-300-004 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Replacement of the Broken Studs of EGT (T49.5) Sensor Bracket Assy Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-54-00-941-060 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 669 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-54-00-010-073 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Let the temperature of parts decrease to ambient temperature. Subtask 72-54-00-040-060 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-079 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 670 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-54-00-210-052 A. Inspect the Turbine Case for the Following ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Aft flange. A. Cracks that connect bolt holes.
Not serviceable
B. Cracks that extend from bolt holes to outer edge of flange.
5 cracks with a minimum 5 hole separation between cracks.
C. Cracks that extend from bolt holes toward casing skin.
Not serviceable.
D. Cracks in other areas of flange.
5 cracks per flange 0.25 in. (6.35 mm) long with a minimum 5 in. (127 mm) separation between any other cracks.
E. Nicks, scores and scratches.
Any number 1 in. (25.4 mm) long 0.01 in. (0.25 mm) deep after removal of high metal with 1 in. (25.4 mm) minimum separation.
F. Cracks in flange/case skin radius.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
2. Casing skin for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 671 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Cracks in parent Any number 0.04 in. (1 See limit extensions metal mm) long and 2 in. (50.8 (Ref. TASK 72-00-00-200mm) minimum apart. 025). B. Nicks and scratches.
Any number 0.01 in. (0.25 mm) deep after removal of high metal.
C. Dents
Any number, smooth contour, 0.02 in. (0.5 mm) deep.
3. All threaded ports and bosses for: A. Damaged threads.
One full thread cumulative or continuous may be removed after chasing threads.
B. Cracks in weld of ports and bosses.
One per port in boss 0.04 in. (1 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
4. Ring sector support for: A. Cracks
Any number if attachment parts are secured.
5. Angle brackets for: A. Broken bracket.
Not serviceable.
B. Cracks in all other areas.
Any amount providing cooling air tubes and attaching fasteners are secured.
6. Cooling air tube supports for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 672 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Cracks at Any amount providing mountaing flanges. support is secured. B. Cracks in all other areas:
7. The EGT (T49.5) sensors probe brackets for:
Any amount providing cooling air tubes and attaching fasteners are secured. One full thread cumulative or continuous can be removed after
See the over serviceable limit extensions related to the LPT case (Ref. TASK
A. Damaged Threads
chasing threads.
72-00-00-200-025).
B. Broken Stud
Not permitted.
Replace the stud by a bolt (Ref. TASK 72-54-00-300004) if access of bracket permit this. If not, replace the engine.See the over serviceable limit extensions related to the LPT case (Ref. TASK 72-0000-200-025).
5. Close-up ________ Subtask 72-54-00-410-074 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-060 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 673 Nov 01/08
C F M 56-5B Subtask 72-54-00-410-080 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 674 Nov 01/08
C F M 56-5B TASK 72-54-00-210-005- 01 Inspection of the Turbine Case 1. __________________ Reason for the Job This TASK is applicable for /P engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-54-00-300-004 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Replacement of the Broken Studs of EGT (T49.5) Sensor Bracket Assy Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-54-00-941-064 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 675 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-54-00-010-088 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Let the temperature of parts decrease to ambient temperature. Subtask 72-54-00-040-064 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-089 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 676 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-54-00-210-056 A. Inspect the Turbine Case for the Following ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Aft flange. A. Cracks that connect bolt holes.
Not serviceable
B. Cracks that extend from bolt holes to outer edge of flange.
5 cracks with a minimum 5 hole separation between cracks.
C. Cracks that extend from bolt holes toward casing skin.
Not serviceable.
D. Cracks in other areas of flange.
5 cracks per flange 0.25 in. (6.35 mm) long with a minimum 5 in. (127 mm) separation between any other cracks.
E. Nicks, scores and scratches.
Any number 1 in. (25.4 mm) long 0.01 in. (0.25 mm) deep after removal of high metal with 1 in. (25.4 mm) minimum separation.
F. Cracks in flange/case skin radius.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
2. Casing skin for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 677 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Cracks in parent Any number 0.04 in. (1 See limit extensions metal mm) long and 2 in. (50.8 (Ref. TASK 72-00-00-200mm) minimum apart. 025). B. Nicks and scratches.
Any number 0.01 in. (0.25 mm) deep after removal of high metal.
C. Dents
Any number, smooth contour, 0.02 in. (0.5 mm) deep.
3. All threaded ports and bosses for: A. Damaged threads.
One full thread cumulative or continuous may be removed after chasing threads.
B. Cracks in weld of ports and bosses.
One per port in boss 0.04 in. (1 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
4. Ring sector support for: A. Cracks
Any number if attachment parts are secured.
5. Angle brackets for: A. Broken bracket.
Not serviceable.
B. Cracks in all other areas.
Any amount providing cooling air tubes and attaching fasteners are secured.
6. Cooling air tube supports for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 678 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Cracks at Any amount providing mountaing flanges. support is secured. B. Cracks in all other areas:
Any amount providing cooling air tubes and attaching fasteners are secured.
C. Breakage of the forward mounting lug
One per half distribution manifold.
7. Cooling air tubes A. Dents
8. The EGT (T49.5) sensors probe brackets for:
All dents are permitted if they have a smooth contour and are not more than 30 percent of the tube outer diameter. One full thread cumulative or continuous can be removed after
See the over serviceable limit extensions related to the LPT case (Ref. TASK
A. Damaged threads
chasing threads.
72-00-00-200-025).
B. Broken stud
Not permitted.
Replace the stud by a bolt (Ref. TASK 72-54-00-300004) if access of bracket permit this. If not, replace the engine. See the over serviceable limit extensions related to the LPT case (Ref. TASK 72-0000-200-025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 679 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-54-00-410-091 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-064 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-092 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 680 Nov 01/08
C F M 56-5B TASK 72-54-00-210-003 General Visual Inspection of Piping of LPT Case Air Cooling 1. __________________ Reason for the Job Refer to the MPD TASK: 752000-C3 This task is applicable for non /P engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-54-00-941-061 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 681 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-54-00-010-074 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-061 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-080 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-54-00-210-053 A. Inspect cooling air tubes and manifolds as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Cooling air manifold for: A. Cracks in mounting lug.
One crack on each lug, if not longer than 0.2 in. (5 mm)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 682 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Cracks in sheet Any number, if not Refer to limit extensions metal longer than 0.5 in. (Ref. TASK 72-00-00-200(12.7 mm) , 1 in. (25.4 025). mm) apart, and 3 in. (76.2 mm) cumulative lenght. C. Dents
Any number if smooth contour and not deeper than 0.03 in. (0.76 mm).
2. Cooling air tubes for: A. Cracks in tubes
Any numbers if not longer than 2 in. (50.8 mm) and separated by at least one support member.
B. Dents
Any number, if no more than 30 percent of tube outer diameter.
C. Cracks in tube clamps
Any number if tubes are correctly attached.
5. Close-up ________ Subtask 72-54-00-410-075 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust-reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 683 Nov 01/08
C F M 56-5B Subtask 72-54-00-440-061 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-081 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 684 Nov 01/08
C F M 56-5B TASK 72-54-00-210-003- 01 General Visual Inspection of Piping of LPT Case Air Cooling 1. __________________ Reason for the Job Refer to the MPD TASK: 752000-C3 This task is applicable for /P and /3 engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 SPM 704111 72-54-00-991-304
Fluorescent-Penetrant Inspection-Portable-Water Washable Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 607
3. __________ Job Set-up Subtask 72-54-00-941-065 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 685 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-54-00-010-090 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-065 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-091 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 686 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-54-00-210-057 A. Inspect cooling air tubes and manifolds as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Cooling air manifold for: (Ref. Fig. 607/TASK 72-54-00-991-304) A. Cracks in the forward mounting lug
One crack on each side is permitted
B. Broken forward mounting lug
One breakage on one side of a lug is permitted One breakage on each side of a forward lug is permitted according the two adjacent support tube : are not broken or crack is not longer than 0.59 in. (15 mm) on the mounting lugs.
C. Dents
A continue in-service limit of 10 hours or 10 cycles is permitted if one adjacent support tube is broken. If one or two adjacent tubes have a crack that is more than 0.59 in. (15 mm), check the part for crack evolution after 10 hours or 10 cycles -If no crack evolution: Check after 50 hours or 50 cycles following the first check, then check every 100 hours or 100 cycles -If crack evolution : A continue in-service limit of 30 hours or 30 cycles is permitted
Any number if smooth contour and not deeper than 0.03 in. (0.76 mm).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 687 Nov 01/08
C F M 56-5B
Visual Inspection of the Mounting Lugs (Only Applicable /P Engines) Figure 607/TASK 72-54-00-991-304- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 688 Nov 01/08
C F M 56-5B
Visual Inspection of the Mounting Lugs (Only Applicable /P Engines) Figure 607/TASK 72-54-00-991-304- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 689 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------D. Nick, scratch and Maximum finish depth Make the defect smooth by chafing (wear) on after you make the hand blending per (Ref. tube external defect smooth is 0.008 SPM 704111) if necessary surface. in. (0.20 mm). to remove sharp edges. Do a local fluorescent penetrant inspection (Ref. TASK 70-51-00-230002). No crack is permitted. 2. Cooling air tubes for: A. Cracks in tubes
Any numbers if not longer than 2 in. (50.8 mm) and separated by at least one support member.
B. Dents
Any number, if no more than 30 percent of tube outer diameter.
C. Cracks in tube clamps
Any number if tubes are correctly attached.
5. Close-up ________ Subtask 72-54-00-410-093 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust-reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 690 Nov 01/08
C F M 56-5B Subtask 72-54-00-440-065 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-094 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 691 Nov 01/08
C F M 56-5B LPT ROTOR/STATOR ASSEMBLY - REPAIRS ___________________________________ TASK 72-54-00-300-004 Replacement of the Broken Studs of EGT (T49.5) Sensor Bracket Assy 1. __________________ Reason for the Job NOTE : The replacement of broken studs depends on accessibility. ____ NOTE : Make sure that free access is available for drilling and tapping ____ process. NOTE : You must discard the repaired bracket assy at the first LPT ____ rotor/stator disassembly. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 77-21-10-000-008 77-21-10-000-009 77-21-10-000-026 77-21-10-000-027 77-21-10-000-028 77-21-10-000-029 77-21-10-400-008 77-21-10-400-009 77-21-10-400-026 77-21-10-400-027
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Upper Extension Lead Removal of the Lower Extension Lead Removal of the Upper Right Thermocouple Lead Assembly Removal of the Lower Left Thermocouple Lead Assembly Removal of the Upper Left Thermocouple Lead Assembly Removal of the Lower Right Thermocouple Lead Assembly Installation of the Upper Extension Lead Installation of the Lower Extension Lead Installation of the Upper Right Thermocouple Lead Assembly Installation of the Lower Left Thermocouple Lead Assembly
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------77-21-10-400-028 77-21-10-400-029 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 SPM 704450 SPM 704450320006 SPM 704460320007 72-54-00-991-310 72-54-00-991-311 72-54-00-991-312 72-54-00-991-313
Installation of the Upper Left Thermocouple Lead Assembly Installation of the Lower Right Thermocouple Lead Assembly Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
Fig. Fig. Fig. Fig.
801 802 803 804
3. __________ Job Set-up Subtask 72-54-00-941-069 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-099 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-068 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-100 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-010-101 E. Get Access (1) Remove the T49.5 Thermocouple and Extension Lead Assembly (Ref. TASK 77-21-10-000-008), (Ref. TASK 77-21-10-000-009), (Ref. TASK 77-21-10000-026), (Ref. TASK 77-21-10-000-027), (Ref. TASK 77-21-10-000-028), (Ref. TASK 77-21-10-000-029), to get access to the studs of the bracket. 4. Procedure _________ (Ref. Fig. 801/TASK 72-54-00-991-310, 802/TASK 72-54-00-991-311, 803/TASK 72-54-00-991-312, 804/TASK 72-54-00-991-313) Subtask 72-54-00-320-052 A. Preparation for broken stud drilling WARNING : DO NOT BREATHE THE PARTICLES FROM GRINDING OR LET THE PARTICLES _______ TOUCH YOU. THE PARTICLES CAN CAUSE DAMAGE, INJURY OR IRRITATION TO YOU. USE PERSONAL PROTECTION EQUIPMENT. USE LOCAL MECHANICAL EXHAUST VENTILATION OR AN APPROVED RESPIRATOR.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B
Replacement of the Defective Studs on LPT Case Figure 801/TASK 72-54-00-991-310 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B
Dimensional Measurements for Working on Studs and Black Plate Figure 802/TASK 72-54-00-991-311 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/08
C F M 56-5B
Locally Manufactured Tool for Replacement of the Defective Studs on LPT Case Figure 803/TASK 72-54-00-991-312 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/08
C F M 56-5B
Lockwire of Bolt after Replacement of the Defective Studs on LPT Case Figure 804/TASK 72-54-00-991-313 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B WARNING : USE EYE PROTECTION WHEN YOU USE COMPRESSED AIR TO CLEAN, COOL _______ OR DRY PARTS OR TOOLS. PARTICLES CAN CAUSE AN INJURY TO YOUR EYES. DO NOT USE MORE THAN 30 PSIG (200 KPA). DO NOT POINT COMPRESSED AIR AT YOURSELF OR OTHER PERSONS. NOTE : It is easier to use a square access to remove the nuts, with ____ bulkheads removed. (1) Calculate the length of the remaining broken tack welded stud (shank) with the remaining serviceable tack welded stud. (2) Install a locally manufactured tool on the remaining serviceable tack welded stud as follows: (a) Engage correctly the center pin of tooling in the bore which is the EGT (T49.5) sensor probe location. (b) Tighten the tooling to the LPT case with the original nut on the remaining serviceable tack welded stud. (c) Make sure the tooling is correctly installed against the LPT case. (3) Install the correct drill guide sleeve (sleeve is identified as clearance guide) for a 0.25 in. (6.3499 mm) drill. (4) Install and attach it with the use of a retaining screw between the drill guide sleeve and the locally manufactured tool. (5) Do a check from the top of the drill guide sleeve to the EGT sensor probe location of the LPT case. Subtask 72-54-00-917-054 B. Drilling of the broken stud shank (1) Calculate the necessary drill depth (with the dimensions given before and the dimensions shown in the figure) to remove the broken stud shank. (2) Make a selection to get the correct drilling stop ring for a 0.25 in. (6.3499 mm) drill. (3) Attach the stop ring to the 0.25 in. (6.3499 mm) diameter drill and set it to the depth as calculated in the paragraph above. (4) Put the drill into the tooling sleeve.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Nov 01/08
C F M 56-5B (5) Drill to a depth permitted by the stop ring to remove the remaining broken stud shank (Ref. SPM 704450320006). Subtask 72-54-00-917-055 C. Preparation for tack welded stud head drilling (1) Remove the drill guide sleeve (clearance guide). (2) Replace it with the other drill guide sleeve (identified as tapping drill guide) for a 0.2110 in. (5.3593 mm) drill. (3) Calculate the drill depth (with the dimensions given before and the dimensions shown in the figure) to drill through the tack welded stud head and the back plate. Subtask 72-54-00-917-056 D. Drilling of the tack welded stud head (1) Install a correct stop ring (stop ring is identified with a drill size of 0.211 in. (5.3593 mm) 0.2110 inch (5,36 mm)) to drill a 0.211 in. (5.3593 mm) diameter and set it to the depth specified as calculated in the Drilling of the broken stud shank paragraph B. (2) Put the drill into the tooling sleeve. CAUTION : OBEY THE INSTRUCTIONS BELOW TO PREVENT DAMAGE TO ADJACENT _______ PARTS AND TO REMOVE AND DISASSEMBLE THE ENGINE. (3) Drill through the stud head and the back plate but do not drill the insulation blanket and the other parts below (Ref. SPM 704450). (4) Remove the drill guide sleeve (identified as tapping drill guide). (5) Replace it with the other drill guide sleeve (identified as clearance guide). (6) Remove with a vacuum device all unwanted material. Subtask 72-54-00-917-057 E. Tapping of the tack welded stud head of the back plate. (1) Calculate the specified tap depth (with the dimensions given before and the dimensions shown in the figure) to tap through the tack welded stud head and the back plate only.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B (2) Set the 0.25 in. (6.3499 mm) stop ring to the specified depth with the tap given in tooling. (3) Put the tap into the tooling sleeve. CAUTION : OBEY THE INSTRUCTIONS BELOW TO PREVENT DAMAGE TO ADJACENT _______ PARTS AND TO REMOVE AND DISASSEMBLE THE ENGINE. (4) Tap the head of the tack welded stud and the back plate (Ref. SPM 704460320007) but do not push the parts below. (5) Remove with a vacuum all unwanted material and clean the adjacent areas. (6) Loosen the nut and remove the tooling. Subtask 72-54-00-320-053 F. Installation of the EGT (T49.5) sensor probe and check (1) Install the T49.5 Thermocouple and Extension Lead Assembly (Ref. TASK 77-21-10-400008), (Ref. TASK 77-21-10-400-009), (Ref. TASK 77-21-10-400-026), (Ref. TASK 77-21-10-400-027), (Ref. TASK 77-21-10-400-028), (Ref. TASK 77-21-10-400-029). 5. Close-up ________ Subtask 72-54-00-410-100 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-068 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
C F M 56-5B Subtask 72-54-00-410-101 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B LPT SHAFT - DESCRIPTION AND OPERATION _____________________________________ 1. _______ General (Ref. Fig. 001) A. Low pressure turbine shaft (1) The low pressure turbine (LPT) shaft module connects the fan shaft with the LPT rotor. It is composed of the LPT shaft, center vent tube and center vent tube rear extension duct. The aft end of the LPT shaft is supported by the No. 5 bearing ; its forward end is coupled with the fan shaft. The LPT shaft has 2 functions : coupling the fan/booster rotor with the LPT rotor and providing for high pressure turbine rear support through the No. 4 bearing. In addition, the LPT shaft houses the center vent tube of the forward and aft engine sumps. (2) The LPT shaft module consists of the following major parts : (a) LPT shaft. (b) No. 4 roller bearing. (c) No. 5 roller bearing. 2. ___________ Description (Ref. Fig. 002, 003) A. Low pressure Turbine Shaft (1) The LPT shaft is made of steel alloy. It is located concentrically in the high pressure rotor system. Its forward end is provided with outer splines for coupling with the fan shaft. It is axially retained by a shoulder and a coupling nut. At the aft end of the shaft, the No. 4 and 5 bearings are located axially on both sides of an integral hub. On the rear face, the hub supports 2 rotating air/oil seals which control the air circulation through the LPT rotor and the sump pressurizing air. On the front face, the hub supports the turbine rotor support. (2) The center vent tube is made of composite material. It is installed inside the LPT shaft. Its forward end is inserted in the LPT shaft plug and its aft end is supported by the LPT shaft hub. It is maintained coaxial in the LPT shaft through 2 inner locating diameters: one at the front end of the LPT shaft; the other at the rear end of the shaft.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Low Pressure Turbine Shaft Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Low Pressure Turbine Shaft Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
No. 4 and No. 5 Bearing Lubrication Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B (3) The center vent tube rear extension duct is installed at the aft end of the center vent tube. Its relative angular position is maintained by locating pins, and axial retention is provided by an inner nut threaded into the center vent tube. A centrifugal air/oil separator is retained by a nut against a central shoulder on the duct. Its relative angular position is maintained by slots at its front end. B. No. 4 Bearing The no. 4 bearing, which takes the high pressure turbine (HPT) rotor radial loads, is a roller bearing installed between the HPT rear shaft and the LPT shaft. The bearing outer race is housed in the HPT rear shaft bore, and its inner race is bolted to the front face of the LPT shaft integral hub. The inner race has a shoulder which would act as an emergency bearing in case of roller failure. The inner race front end is provided with a sump air seal. C. No. 5 Bearing The No. 5 Bearing supports the LPT rotor aft end inside the turbine frame and takes the radial loads. The bearing outer race is mounted in the turbine frame and its inner race is mounted at the rear of the LPT shaft integral hub. Axial retention is provided by a retainer nut. Retainer nut relative position is maintained by rivet.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B LPT SHAFT - MAINTENANCE PRACTICES _________________________________ TASK 72-55-00-960-002 Replacement of LPT Shaft Plug O-rings 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A2632 856A2668 856A2946 856A3793
1 1 1 1
scriber warning notice PULLER KIT-PULLER ADAPTERS RING-PROTECTIVE FAN DISK FIXTURE,PUSHER PULLER-CVT
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP2442
* acetone (Ref. 70-30-00) * engine oil (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 201 Nov 01/08
C F M 56-5B C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------20 20 40 40 40 40 50 50 50 50 70 70 80 90 90 90 90 100 100 100 100
retaining ring retaining ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring retaining ring retaining ring damper seals O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring
72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00
01A-050 01B-050 01A-030 01A-030A 01B-030 01B-030A 01A-020 01A-020A 01B-020 01B-020A 01A-050 01B-050 01B-060 01A-030 01A-030A 01B-030 01B-030A 01A-020 01A-020A 01B-020 01B-020A
D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-400-005 72-21-00-400-006 72-55-00-991-301 72-55-00-991-302
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Fig. 201 Fig. 202
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 202 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-55-00-941-051 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-55-00-010-051 B. Preparation for the replacement of LPT shaft plug O-rings (1) Remove the spinner front cone.(Ref. TASK 72-21-00-000-005) (2) Remove the spinner rear cone.(Ref. TASK 72-21-00-000-006) 4. Procedure _________ Subtask 72-55-00-960-051 A. Replacement of LPT shaft plug O-rings PRE CFM SB72-0436 (1) Replacement of LPT shaft plug O-rings NOTE : You must do this procedure for engine without center vent tube ____ forward removable (CFM SB72-0436) (Ref. Fig. 201/TASK 72-55-00-991-301) (a) Remove the retaining ring from forward end of LPT shaft, using a scriber.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 203 Nov 01/08
C F M 56-5B
Low Pressure Turbine Shaft Assembly (PRE CFM SB72-0436) Figure 201/TASK 72-55-00-991-301- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 204 Nov 01/08
C F M 56-5B
Low Pressure Turbine Shaft Assembly (PRE CFM SB72-0436) Figure 201/TASK 72-55-00-991-301- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 205 Nov 01/08
C F M 56-5B (b) Remove LPT shaft plug (10) using the KIT-PULLER ADAPTERS (856A2668G02) or PULLER (856A2632G01). (c) Remove and discard O-rings located in forward/aft grooves. (d) Remove the KIT-PULLER ADAPTERS (856A2668G02) or the PULLER (856A2632G01) from the LPT shaft plug (10). Install the LPT shaft plug (10) in the storage box. CAUTION : ACETONE IS EXPLOSIVE, AN IRRITANT, AN ALLERGEN, AND HAS _______ POISONOUS DETERIORATION. USE PERSONAL PROTECTION EQUIPMENT. USE VAPOR/FUME CONTROL OR A RESPIRATOR. (e) Clean the oil stains on the plug grooves with acetone (Material No. CP1039). (f) Clean the oil stains on the inner diameter of LPT forward shaft with bent brush soaked with acetone (Material No. CP1039). CAUTION : MAKE SURE THAT YOU CORRECTLY INSTALL A NEW O-RING IN _______ THE SEAL GROOVE AT THE FORWARD END OF THE LPT SHAFT PLUG. IF THE O-RING IS NOT CORRECTLY INSTALLED, DAMAGE TO THE ENGINE CAN OCCUR. (g) Lightly coat new O-ring (40) and new O-ring (50) with engine oil (Material No. CP2442) and install into the seal grooves of LPT shaft. (h) Install LPT shaft plug assembly into forward end of LPT shaft and onto center vent tube. NOTE : Insert lug of LPT shaft in aligned slots of LPT coupling ____ nut and LPT shaft. (i) Install retaining ring (20) onto LPT shaft. 1 _
Do a visual inspection to make sure of the correct installation of retaining ring (20) END OF PRE CFM SB72-0436 POST CFM SB72-0436
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 206 Nov 01/08
C F M 56-5B (2) Replacement of the O-rings and Damper Seals on the center vent tube forward removable (Ref. Fig. 202/TASK 72-55-00-991-302) WARNING : USE HEAT INSULATED GLOVES WHEN YOU TOUCH CHILLED OR HOTS _______ PARTS TO PREVENT INJURY WARNING : ENGINE OIL IS TOXIC. USE PERSONAL PROTECTION EQUIPMENT. USE _______ IN A WELL-VENTILATED AREA. (a) Install the RING-PROTECTIVE FAN DISK (856A2946G01) as follows: 1 _
Install the lower sector of the RING-PROTECTIVE FAN DISK (856A2946G01) in position in the fan disk hole.
2 _
Attach the lower sector of the RING-PROTECTIVE FAN DISK (856A2946G01) with the knurled screws.
3 _
Install the upper sector of the RING-PROTECTIVE FAN DISK (856A2946G01) in position in the fan disk hole.
4 _
Attach the upper sector of the RING-PROTECTIVE FAN DISK (856A2946G01) with the knurled screws.
(b) Remove the retaining ring from the front of the LPT shaft. (c) Screw the tube of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) in the center vent tube (60). (d) Install the support of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) on the fan disk flange with four screws. (e) Engage the plate of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) in the slot of the screw and attach it with the knurled nut. (f) Manually turn clockwise the screw of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) to disengage the center vent tube (60) from the LPT Shaft. NOTE : You can use a wrench if the counter torque is important. ____ (g) Remove the support of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) from the fan disk flange.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 207 Nov 01/08
C F M 56-5B
Center Vent Tube Forward Removable (POST CFM SB72-0436) Figure 202/TASK 72-55-00-991-302- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 208 Nov 01/08
C F M 56-5B
Center Vent Tube Forward Removable (POST CFM SB72-0436) Figure 202/TASK 72-55-00-991-302- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 209 Nov 01/08
C F M 56-5B
Center Vent Tube Forward Removable (POST CFM SB72-0436) Figure 202/TASK 72-55-00-991-302- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 210 Nov 01/08
C F M 56-5B (h) Remove the center vent tube (60) equipped with the tube of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) from the LPT Shaft. (i) Remove the tube of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) from the center vent tube. (j) Remove and discard O-rings located in forward/aft grooves ofthe center vent tube. (k) Remove and discard the damper seals located in the other grooves of the center vent tube. (l) Clean the oil stains with acetone (Material No. CP1039) on the center vent tube (60), in the O-rings (90) and (100) and damper seals (80) grooves and in the inner diameter of the fan disk with a lint-free cloth. (m) Clean the oil stains on the inner diameter of LPT forward shaft with bent brush soaked with acetone acetone (Material No. CP1039). (n) Install the center vent tube (60) in the storage box. CAUTION : MAKE SURE THAT YOU CORRECTLY INSTALL THREE NEW DAMPER _______ SEALS IN THE THREE SEAL GROOVES OF THE CENTER VENT TUBE. YOU MUST HAVE THE PLATE FACE OF THE DAMPER SEALS POINTED TO OUTER OF THE CENTER VENT TUBE. IF THE DAMPER SEALS ARE NOT CORRECTLY INSTALLED, DAMAGE TO THE ENGINE CAN OCCUR. (o) Lightly coat three new damper seals (80) with engine oil (Material No. CP2442) and install them into their seal grooves of the center vent tube (60). CAUTION : MAKE SURE THAT YOU CORRECTLY INSTALL TWO NEW O-RINGS IN _______ THE SEAL GROOVE AT THE FORWARD END OF THE CENTER VENT TUBE. IF THE O-RINGS ARE NOT CORRECTLY INSTALLED, DAMAGE TO THE ENGINE CAN OCCUR. (p) Lightly coat new O-ring (90) and new O-ring (100) with engine oil (Material No. CP2442) and install into the seal grooves of the center vent tube (60).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 211 Nov 01/08
C F M 56-5B (q) Prepare the center vent tube (60) for installation as follows: 1 _
Screw the tube of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) in the center vent tube (60). CAUTION : TAKE CARE NOT TO DAMAGE THE LPT SHAFT INTERNAL _______ SUPPORTS AND PAINT DURING THE INSTALLATION OF THE CENTER VENT TUBE.
2 _
Align and install the center vent tube (60) into the LPT Shaft.
3 _
Align the lug of the center vent tube (60) with the aligned slots of the LPT Shaft and the LPT coupling.
(r) Install the FIXTURE,PUSHER PULLER-CVT (856A3793G02) as follows: 1 _
Install the support of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) on the fan disk flange with four screws.
2 _
Engage the plate of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) in the slot of the screw and attach it with the knurled nut.
(s) Complete the installation of the center vent tube (60) as follows: CAUTION : TAKE CARE TO STOP TURN COUNTER-CLOCKWISE THE SCREW OF _______ FIXTURE OF PUSHER/PULLER BEFORE THE LUG OF THE CENTER VENT TUBE TOUCHES THE SLOT OF THE LPT SHAFT. 1 _
Manually turn counter-clockwise the screw of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) to engage the center vent tube (60) into the slot of the LPT Shaft. NOTE : You can use a wrench if the counter torque is ____ important.
2 _
Remove the support of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) from the fan disk flange.
3 _
Remove the tube of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) from the center vent tube (60).
(t) Install the retaining ring (70) onto the LPT shaft.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 212 Nov 01/08
C F M 56-5B (u) Remove the RING-PROTECTIVE FAN DISK (856A2946G01) as follows: 1 _
Unscrew the knurled screws of the RING-PROTECTIVE FAN DISK (856A2946G01) which attach the upper sector.
2 _
Remove the upper sector of the RING-PROTECTIVE FAN DISK (856A2946G01) from the fan disk hole.
3 _
Unscrew the knurled screws of the RING-PROTECTIVE FAN DISK (856A2946G01) which attach the lower sector.
4 _
Remove the lower sector of the RING-PROTECTIVE FAN DISK (856A2946G01) from the fan disk hole.
(v) Do a visual inspection to make sure of the correct installation of retaining ring (70). END OF POST CFM SB72-0436 5. Close-up ________ Subtask 72-55-00-410-051 A. Install the Spinner Rear and Front Cone. (1) Install the spinner rear cone.(Ref. TASK 72-21-00-400-006) (2) Install the spinner front cone.(Ref. TASK 72-21-00-400-005)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 213 Nov 01/08
C F M 56-5B LPT SHAFT - INSPECTION/CHECK ____________________________ TASK 72-55-00-200-002 Inspection/Check of the Low Pressure Turbine Shaft Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-56-00-000-002 72-56-00-400-002 78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-55-00-991-901
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Oil Inlet Cover Assembly Installation of the Oil Inlet Cover Assembly Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601
EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Feb 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-55-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice in position to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice in position to tell persons not to energize the FADEC 1(2). Subtask 72-55-00-010-054 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): - FOR 1000EM1 437AL, 438AR - FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-55-00-040-051 C. Deactivation of the Thrust Reverser WARNING : YOU MUST DEACTIVATE THE THRUST REVERSER HYDRAULIC CONTROL UNIT _______ BEFORE YOU WORK ON OR AROUND THE THRUST REVERSER. IF YOU DO NOT DO THIS THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE INJURY AND DAMAGE. (1) Make the thrust reverser unserviceable for maintenance (Ref. TASK 7830-00-481-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Feb 01/09
C F M 56-5B Subtask 72-55-00-010-055 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): - FOR 1000EM1 451AL, 452AR - FOR 1000EM2 461AL, 462AR. Subtask 72-55-00-860-051 E. Aircraft Maintenance Configuration (1) Make sure that the core nozzle is removed (Ref. TASK 78-11-11-000041). (2) Make sure that the centerbody is removed (Ref. TASK 78-11-12-000041). (3) Make sure that the oil inlet cover assembly is removed (Ref. TASK 7256-00-000-002). 4. Procedure _________ (Ref. Fig. 601/TASK 72-55-00-991-901) Subtask 72-55-00-210-051 A. Visual Inspection of the Turbine Frame Assembly ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Air/oil separator (all areas, if exposed) for: A. Corrosion or pitting
Any amount
EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Feb 01/09
C F M 56-5B
Inspection of Air/Oil Separator Exposed Areas Figure 601/TASK 72-55-00-991-901 EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Feb 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-55-00-410-054 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the oil inlet cover assembly (Ref. TASK 72-56-00-400-002). (3) Install the centerbody (Ref. TASK 78-11-12-400-041). (4) Install the core nozzle (Ref. TASK 78-11-11-400-041). (5) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): - FOR 1000EM1 451AL, 452AR - FOR 1000EM2 461AL, 462AR. Subtask 72-55-00-440-051 B. Activation of the Thrust Reverser (1) Make the thrust reverser serviceable after maintenance (Ref. TASK 7830-00-081-041). Subtask 72-55-00-410-055 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): - FOR 1000EM1 437AL, 438AR - FOR 1000EM2 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Feb 01/09
C F M 56-5B TURBINE FRAME ASSEMBLY - DESCRIPTION AND OPERATION __________________________________________________ 1. General _______ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 001) **ON A/C 051-051, (Ref. Fig. 001A) R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 001B)
R R
**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, The turbine frame module is the major structure assembly at the rear of the engine. It supports the low pressure turbine (LPT) rotor rear section and provides for engine rear mounting on the airframe. The turbine frame consists of the following major parts : - Turbine frame. - No. 5 bearing support. 2. Description ___________ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, Post SB CFMI 72-0176 NOTE : This description is for Turbine Frame with Radial Struts only ____ A. Turbine Frame with Radial Struts (Ref. Fig. 002) The turbine frame assembly is made of nickel alloy and consists of a hub and a polygonal outer casing connected with radial struts. The external skin of the outer casing is lined with heat-insulation blankets. (Ref. Fig. 001)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Exploded View of Turbine Frame Assembly Figure 001 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 2 May 01/05
C F M 56-5B
R R
Exploded View of Turbine Frame Assembly Figure 001A
R EFF : 051-051, 72-56-00 CES
Page 3 May 01/05
C F M 56-5B
Exploded View of Turbine Frame Assembly Figure 001B R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
Turbine Frame Struts Section and Numbering Figure 002 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 5 May 01/05
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C F M 56-5B (1) There are 16 struts, airfoil-shaped and radial to the hub. The struts provide internal passage for the following items : (Ref. Fig. 003) (a) Aft sump oil scavenge tube (No. 7 strut) (b) Oil supply tube for the No. 4 and No. 5 bearings (No. 10 strut). (2) The aft sump overboard seal drain tube is routed between struts No. 8 and No. 9. (3) The front flange of the outer casing is bolted to the LPT case. The outer casing rear flange supports the primary exhaust nozzle. At its periphery, there are 3 clevis mounts for engine/airframe adaptation, and 2 brackets for handling and installation on engine storage stand. (Ref. Fig. 003)
R
(4) The hub inner front flange supports (from rear to front) the air heat cover and the No.5 bearing support. The air heat cover has three attachment circles: - the inner one attaches (from rear to front) the inner flange of the air heat cover and the flange of the No.5 bearing support, to the hub inner front flange. The No.5 bearing support contains the adjusting sleeve in its central bore. - the mid one provides support and attachment for the oil collector located forward of the air heat cover. - the outer one attaches both the outer flange of the air heat cover, and the seal cover, to studs located on the forward face of the hub. The air heat cover acts altogether as a support for the oil collector and (rearwards) as a seal and a heat shield. (5) The hub inner rear flange has the following attachment items: - a bolt circle on its inner diameter - a stud circle on its outer diameter The bolt circle provides attachment for the sheet metal flange assembly. The flange assembly provides the support, attachment and centering for the flame arrestor. The stud circle provides attachment for the engine exhaust plug (centerbody) with nuts. Post SB CFMI 72-0176
EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 6 Nov 01/07
C F M 56-5B
R R
Turbine Frame Struts Section and Numbering Figure 002A
R EFF : 051-051, 72-56-00 CES
Page 7 May 01/05
C F M 56-5B
Turbine Frame Struts Section and Numbering Figure 002B R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 8 Nov 01/08
C F M 56-5B
Turbine Frame Section Figure 003 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 9 May 01/05
R
C F M 56-5B B. No. 5 Bearing Support for Turbine Frame with Radial Struts (Ref. Fig. 004) The No. 5 bearing support is made of steel alloy. Its outer flange is bolted, with the aft oil sump assembly, to the turbine frame. The inner flange of No. 5 bearing support accommodates the No. 5 bearing outer race and an adjusting sleeve. The rear face of the support carries the oil inlet cover which supports the oil supply tube for the No. 4 and 5 bearings, and provides for pressurization of the dual air/oil seal installed at the rear end of the center vent tube rear extension duct. The oil inlet cover supports the rear extension duct. The No. 5 bearing support has machined passages for : - Pressurizing air to the oil inlet cover. - Sump bleed air to the center vent tube. - Oil to the scavenge tube. - Oil supply to the No.5 bearing squeeze film vibration damping system. **ON A/C 051-051, Pre SB CFMI 72-0368 Pre SB CFMI 72-0176 NOTE : This descripton is for Turbine Frame with Tangential Non ____ Symetrical Section Struts only.
R
A. Turbine Frame with Tangential Non Symetrical Section Struts (Ref. Fig. 002A) The turbine frame assembly is made of nickel alloy and consists of a hub and a polygonal outer casing connected with tangential struts. (Ref. Fig. 001A)
R
(1) There are 16 struts, airfoil-shaped and tangential to the hub. The struts provide internal passage for the following items : (Ref. Fig. 003A)
R
(a) Aft sump oil scavenge tube (No. 7 strut) (b) Oil supply tube for the No. 4 and No. 5 bearings (No. 10 strut). (2) The aft sump overboard seal drain tube is routed between struts No. 7 and No. 8.
EFF : 001-049, 051-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 10 Nov 01/07
C F M 56-5B
R R
Turbine Frame Section Figure 003A
R EFF : 051-051, 72-56-00 CES
Page 11 May 01/05
C F M 56-5B
Turbine Frame Section Figure 003B R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 12 Nov 01/08
C F M 56-5B
Oil Pressurizing Seals-Location Figure 004 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 13 May 01/05
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C F M 56-5B (3) The front flange of the outer casing is bolted to the LPT case. The outer casing rear flange supports the primary exhaust nozzle. At its periphery, there are 3 clevis mounts for engine/airframe adaptation, and 2 brackets for handling and installation on engine storage stand. (Ref. Fig. 003A) (4) On its front side, the hub of turbine frame has 3 attachment flanges that are, from the center and outward: - the hub inner front flange. This flange supports the No.5 bearing support. - the hub mid front flange. This flange supports the oil collector (or aft oil sump assembly). - the hub outer front flange. This flange supports the seal cover. The seal cover also provides forward retention of the inner flow path tiles. (5) On its rear side, the turbine frame has the following attachment items that are, from the center and outwards: - a flange located on the hub of turbine frame. This flange provides the support and attachment for the sheet metal flange assembly. This sheet metal flange assembly itself supports and centers the flame arrestor and also provides a rear support and centering for the oil inlet cover. - a circle of studs (quantity: 16). There is a stud projecting rearward at the root section of each tangential strut. The studs provide support and attachment for the engine exhaust plug (centerbody) with nuts. (6) The inner wall of the turbine frame gaspath is lined with stainless steel protective tiles. These tiles are located between the tangential struts. They have two stiffeners on their inner side to better withstand vibrations. Pre SB CFMI 72-0176 Pre SB CFMI 72-0368 B. No. 5 Bearing Support for Turbine Frame with Tangential Non Symetrical Section Struts (Ref. Fig. 004A) The No. 5 bearing support is made of steel alloy. Its attachment flange is bolted to the hub inner front flange of the turbine frame. The inner front bore of the No. 5 bearing support accommodates the No. 5 bearing outer race and an adjusting sleeve. The rear face of the support carries the oil inlet cover which supports the oil supply tube for the No. 4 and 5 bearings, and provides for pressurization of the dual air/oil seal installed at the rear end of the center vent tube rear extension duct.
R
EFF : 051-051, 72-56-00 CES
Page 14 Nov 01/07
C F M 56-5B
R R
Oil Pressurizing Seals-Location Figure 004A
EFF : 051-051, 72-56-00 CES
Page 15 May 01/05
C F M 56-5B The oil inlet cover supports the rear extension duct. The No. 5 bearing support has machined passages for : - Pressurizing air to the oil inlet cover. - Sump bleed air to the center vent tube. - Oil to the scavenge tube. - Oil supply to the No.5 bearing squeeze film vibration damping system. R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Post SB CFMI 72-0368 NOTE : This descripton is for Turbine Frame with Tangential Symetrical ____ Section Struts only. A. Turbine Frame with Tangential Symetrical Section Struts (Ref. Fig. 002B) The turbine frame assembly is made of nickel alloy and consists of a hub and a polygonal outer casing connected with tangential struts of a symetrical section. (Ref. Fig. 001B) (1) There are 16 struts, airfoil-shaped and tangential to the hub. The struts provide internal passage for the following items : (Ref. Fig. 003B) (a) Aft sump oil scavenge tube (No. 7 strut) (b) Oil supply tube for the No. 4 and No. 5 bearings (No. 10 strut). (2) The aft sump overboard seal drain tube is routed between struts No. 7 and No. 8. (3) The front flange of the outer casing is bolted to the LPT case. The outer casing rear flange supports the primary exhaust nozzle. At its periphery, there are 3 clevis mounts for engine/airframe adaptation, and 2 brackets for handling and installation on engine storage stand. (Ref. Fig. 003B) (4) On its front side, the hub of that are, from the center and - the hub inner front flange. support. - the hub outer front flange. (aft oil sump assembly).
turbine frame has 2 attachment flanges outward: This flange supports the No.5 bearing This flange supports the oil collector
R EFF : 051-051, 106-149, 155-199, 208-249, 72-56-00 251-299, 301-399, 401-499, CES
Page 16 Nov 01/08
C F M 56-5B (5) On its rear side, the turbine frame has the following attachment items that are, from the center and outwards: - a flange located on the hub of turbine frame. This flange provides the support and attachment for the sheet metal flange assembly on its mid circle. This sheet metal flange assembly itself supports and centers the flame arrestor and also provides a rear support and centering for the oil inlet cover on its inner circle, and also supports and centers the flow path fairing on its outer circle. - a circle of studs (quantity: 16). There is a stud projecting rearward at the root section of each tangential strut. The studs provide support and attachment for the engine exhaust plug (centerbody) with nuts. (6) The inner wall of the turbine frame gaspath is covered with the flow path fairing. The flow path fairing is a one part bolted to the plate lock, and to the flange assembly. This plate lock is mounted between the TRF, and the exhaust plug on the aft side. B. No. 5 Bearing Support for Turbine Frame with Tangential Symetrical Section Struts (Ref. Fig. 004B) The No. 5 bearing support is made of steel alloy. Its outer flange is attached, with the oil collector (aft oil sump assembly), to the turbine frame with bolts. The inner front bore of the No. 5 bearing support accomodates the No. bearing outer race and an adjusting sleeve. The rear face of the support carries the oil inlet cover which supports the oil supply tube for the No. 4 and 5 bearings, and provides for pressurization of the dual air/oil seal installed at the rear end of the center vent tube rear extension duct. The oil inlet cover supports the rear extension duct. The No. 5 bearing support has machined passages for : - Pressurizing air to the oil inlet cover. - Sump bleed air to the center vent tube. - Oil to the scavenge tube. - Oil to the No.5 bearing squeeze film vibration damping system.
R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 17 Nov 01/08
C F M 56-5B
Oil Pressurizing Seals-Location Figure 004B R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 18 Nov 01/08
C F M 56-5B TURBINE FRAME ASSEMBLY - REMOVAL/INSTALLATION _____________________________________________ TASK 72-56-00-000-001 Removal of the Flame Arrestor and Flange Assembly 1. __________________ Reason for the Job To allow the inspection/check and the cleaning of the rear sump oil supply tube in the LPT frame. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-11-11-000-041 78-11-12-000-041
Removal of the Core Nozzle Assembly Removal of the Centerbody
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-300
Fig. 401
**ON A/C 051-051, 72-56-00-991-300-B R
Fig. 401A
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-300-A
Fig. 401B
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
R R
C F M 56-5B **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 3. __________ Job Set-up Subtask 72-56-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-055 B. Get Access (1) Remove the core nozzle (Ref. TASK 78-11-11-000-041). (2) Remove the centerbody (Ref. TASK 78-11-12-000-041). 4. Procedure _________ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 401/TASK 72-56-00-991-300) **ON A/C 051-051, (Ref. Fig. 401A/TASK 72-56-00-991-300-B)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Nov 01/08
C F M 56-5B
Flame Arrestor and Flange Assembly Figure 401/TASK 72-56-00-991-300 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 403 May 01/05
C F M 56-5B
R R
Flame Arrestor and Flange Assembly Figure 401A/TASK 72-56-00-991-300-B
R EFF : 051-051, 72-56-00 CES
Page 404 May 01/05
R
C F M 56-5B **ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 401B/TASK 72-56-00-991-300-A) **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207, Subtask 72-56-00-020-050 A. Removal of the Flame Arrestor PRE SB CFMI 72-045 (1) Remove the six bolts (20) which attach the flame arrestor (30) to the oil inlet cover through the flange assembly (90). POST SB CFMI 72-045 (2) Remove the six bolts (20) which attach the flame arrestor (10) or (30) to the oil inlet cover through the flange assembly (90). END OF SB CFMI 72-045 Subtask 72-56-00-020-051 B. Removal of the Flange Assembly NOTE : This procedure is for both of Turbine Frame with Tangential Non ____ Symetrical Section Struts or with Radial Struts only. (1) Remove the three bolts (40) and washers (50) which attach the sleeve (60) to the flange assembly (90). (2) Remove the sleeve (60). (3) Remove the thirty two bolts (70) which attach the flange assembly (90) to the LPT frame. (4) Remove the flange assembly (90) from the LPT frame. (5) Remove and discard the gasket seal (80).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 405 Nov 01/08
C F M 56-5B
Flame Arrestor and Flange Assembly Figure 401B/TASK 72-56-00-991-300-A R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 406 Nov 01/08
R
C F M 56-5B **ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-020-050-A A. Removal of the Flame Arrestor (1) Remove the six bolts (20) which attach the flame arrestor (30) to the oil inlet cover through the flange assembly (160). Subtask 72-56-00-020-051-A B. Removal of the Flange Assembly NOTE : This procedure is for Turbine Frame with Tangential Symetrical ____ Section Struts only. (1) Remove the sixteen bolts (150) which attach the flow path fairing to the outer circle of the flange assembly (160) through the plate lock (170). (2) Remove the twenty four bolts (70) which attach the mid circle of the flange assembly (160) to the LPT frame hub rear flange. (3) Remove the flange assembly (160) from the LPT frame. (4) Remove and discard the gasket seal (80).
R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 407 Nov 01/08
C F M 56-5B **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, TASK 72-56-00-400-001 Installation of the Flame Arrestor and Flange Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------80 80
gasket seal gasket seal
72-56-00 02A-010 72-56-00 02B-010
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 408 Nov 01/09
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041
Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-300
Fig. 401
**ON A/C 051-051, 72-56-00-991-300-B R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-300-A
R R
Fig. 401A
Fig. 401B
**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 3. __________ Job Set-up Subtask 72-56-00-860-050 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the core nozzle is removed (Ref. TASK 78-11-11-000041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 409 Nov 01/08
C F M 56-5B (4) Make sure that the centerbody is removed (Ref. TASK 78-11-12-000041). 4. Procedure _________ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 401/TASK 72-56-00-991-300) **ON A/C 051-051, (Ref. Fig. 401A/TASK 72-56-00-991-300-B) R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 401B/TASK 72-56-00-991-300-A) **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207, Subtask 72-56-00-420-050 A. Installation of the Flange Assembly NOTE : This procedure is for Turbine Frame with Tangential Non ____ Symmetrical Section Struts or with Radial Struts only. (1) Install a new gasket seal (80) on the rear flange of the oil inlet cover. (2) Install the flange assembly (90) in position on the LPT frame. (3) Lubricate the threads of bolts (70) with graphite grease (Material No. CP2101). CAUTION : MAKE SURE THAT THE GASKET SEAL IS IN THE CORRECT POSITION _______ ON THE REAR FLANGE OF THE OIL INLET COVER. (4) Attach the flange assembly (90) with thirty two bolts (70). (5) TORQUE the bolts (70) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 410 Nov 01/08
C F M 56-5B (6) Lubricate the threads of bolts (40) with graphite grease (Material No. CP2101). (7) Install the sleeve (60) in position on the flange assembly. (8) Attach the sleeve (60) with three bolts (40) and washers (50). (9) TORQUE the bolts (40) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). Subtask 72-56-00-420-051 B. Installation of the Flame Arrestor (1) Lubricate the threads of bolts (20) with graphite grease (Material No. CP2101). PRE SB CFMI 72-045 (2) Install the flame arrestor (30) in position on the flange assembly (90). POST SB CFMI 72-045 (3) Install the flame arrestor (10) or (30) in position on the flange assembly (90). END OF SB CFMI 72-045 (4) Attach the flame arrestor with six bolts (20). (5) TORQUE the bolts (20) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-420-050-A A. Installation of the Flange Assembly NOTE : This procedure is for Turbine Frame with Tangential Symmetrical ____ Section Structs only. (1) Install a new gasket seal (80) on the rear flange of the oil inlet cover.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 411 Nov 01/08
C F M 56-5B (2) Install the flange assembly (160) in position on the LPT frame with flow path fairing and plate lock (170) installed. (3) Lubricate the threads of bolts (70) with graphite grease (Material No. CP2101). CAUTION : MAKE SURE THAT THE GASKET SEAL IS IN THE CORRECT POSITION _______ ON THE REAR FLANGE OF THE OIL INLET COVER. NOTE : Make sure that the flange assembly is correctly positioned ____ with the aft sump overboard seal drain tube in its position. (4) Attach the flange assembly (160) with twenty four bolts (70) to the hub inner rear flange of LPT frame. (5) TORQUE the bolts (70) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). (6) Lubricate the threads of bolts (150) with graphite grease (Material No. CP2101). (7) Attach the flange assembly (160) with sixteen bolts (150) to the flow path fairing installed on LPT frame through the plate lock (170). (8) TORQUE the bolts (150) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). Subtask 72-56-00-420-051-A B. Installation of the Flame Arrestor (1) Lubricate the threads of bolts (20) with graphite grease (Material No. CP2101). (2) Install the flame arrestor (30) in position on the flange assembly (160). (3) Attach the flame arrestor with six bolts (20). (4) TORQUE the bolts (20) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN).
R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 412 Nov 01/08
R R
C F M 56-5B **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 5. Close-up ________ Subtask 72-56-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the centerbody (Ref. TASK 78-11-12-400-041). (3) Install the core nozzle (Ref. TASK 78-11-11-400-041). (4) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 413 Nov 01/08
C F M 56-5B TASK 72-56-00-000-002 Removal of the Oil Inlet Cover Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific 856A3419
warning notice 1 ADAPTER, PULLER - OIL INLET COVER
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-56-00-000-001
Removal of the Flame Arrestor and Flange Assembly
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-301
Fig. 402
**ON A/C 051-051, 72-56-00-991-301-B R
Fig. 402A
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-301-A
Fig. 402B
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-302
Fig. 403
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 414 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 051-051, 72-56-00-991-302-B R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-302-A
R R
Fig. 403A
Fig. 403B
**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 3. __________ Job Set-up Subtask 72-56-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-056 B. Remove the flame arrestor and the flange assembly (Ref. TASK 72-56-00000-001).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 415 Nov 01/08
C F M 56-5B 4. Procedure _________ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 402/TASK 72-56-00-991-301) **ON A/C 051-051, (Ref. Fig. 402A/TASK 72-56-00-991-301-B) R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 402B/TASK 72-56-00-991-301-A) **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 403/TASK 72-56-00-991-302) **ON A/C 051-051, (Ref. Fig. 403A/TASK 72-56-00-991-302-B)
R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 403B/TASK 72-56-00-991-302-A) **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, Subtask 72-56-00-020-052 A. Removal of the Rear Sump Oil Supply Tubes NOTE : For Turbine Frame with Radial Struts only. ____ (1) Cut and remove all the lockwires which safety the tube coupling nuts. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 416 Nov 01/08
C F M 56-5B
Oil Inlet Cover Figure 402/TASK 72-56-00-991-301 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 417 May 01/05
C F M 56-5B
R R
Oil Inlet Cover Figure 402A/TASK 72-56-00-991-301-B
R EFF : 051-051, 72-56-00 CES
Page 418 May 01/05
C F M 56-5B
Oil Inlet Cover Figure 402B/TASK 72-56-00-991-301-A R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 419 Nov 01/08
C F M 56-5B
Aft Sump Oil Supply Tubes Figure 403/TASK 72-56-00-991-302 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 420 May 01/05
C F M 56-5B
R R
Aft Sump Oil Supply Tubes Figure 403A/TASK 72-56-00-991-302-B
R EFF : 051-051, 72-56-00 CES
Page 421 May 01/05
C F M 56-5B
Aft Sump Oil Supply Tubes Figure 403B/TASK 72-56-00-991-302-A R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 422 Nov 01/08
C F M 56-5B (2) Loosen the coupling nuts of the oil supply tube (40) from the nipple (50), on the oil inlet cover (80) and from the oil supply tube (140), in the LPT frame strut. (3) Loosen both coupling nuts of the damping oil tube (70) from the nipple (90) on the No. 5 bearing support and from the oil supply tube (40). (4) Cut and remove the lockwire which safeties the sleeve locking nut (110). (5) Loosen the sleeve locking nut (110) to free the oil supply tube (140) in the LPT frame strut. (6) Cut and remove the lockwire which safeties the bolts (130). (7) Remove the bolts (130) and disengage the end fitting (120) from the LPT frame. (8) Remove the damping oil tube (70) and the oil supply tube (40). (9) Install bolts (130) again to attach the end fitting (120) to the LPT frame. Tighten bolts (130) by hand. **ON A/C 051-051, Subtask 72-56-00-020-052-B A. Removal of the Rear Sump Oil Supply Tubes NOTE : This procedure is for Turbine Frame with Tangential Non Symetrical ____ Section Struts only. (1) Cut and remove all the lockwires which safety the tube coupling nuts. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (2) Loosen the coupling nuts of the oil supply tube (40) from the nipple (50), on the oil inlet cover (80) and from the oil supply tube (100), in the LPT frame strut.
EFF : 001-049, 051-099, 101-105, 151-154, 72-56-00 201-207, R CES
Page 423 Nov 01/08
C F M 56-5B (3) Loosen both coupling nuts of the damping oil tube (70) from the nipple (90) on the No. 5 bearing support and from the oil supply tube (40). (4) Remove the damping oil tube (70) and the oil supply tube (40). R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-020-052-A A. Removal of the Rear Sump Oil Supply Tubes NOTE : This procedure is for Turbine Frame with Tangential Symetrical ____ Section Struts only. (1) Cut and remove all the lockwires which safety the tube coupling nuts. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (2) Loosen the coupling nuts of the oil supply tube (170) from the nipple (180), on the oil inlet cover (160) and from the oil supply tube (220), in the LPT frame strut. (3) Loosen both coupling nuts of the damping oil tube (200) from the nipple (210) on the No. 5 bearing support and from the oil supply tube (170). (4) Remove the damping oil tube (200) and the oil supply tube (170). **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207, Subtask 72-56-00-020-053 B. Removal of the Oil Inlet Cover NOTE : For Turbine Frame with Tangential Non Symetrical Section Struts or ____ with Radial Struts only. (1) Remove the bolts (30) which attach the oil inlet cover (80) to the No. 5 bearing support.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 424 Nov 01/08
C F M 56-5B (2) Install the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), on the rear flange of the oil inlet cover (80). (3) Remove the oil inlet cover (80). (4) Remove and discard the O-ring (20). (5) Remove and discard the gasket seal (10). (6) Remove the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), from the oil inlet cover (80). (7) Cut and remove the lockwire which safeties the nipple (50) to the oil inlet cover (80). (8) Remove the nipple (50) from the oil inlet cover (80). (9) Remove and discard the O-ring (60). R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-020-053-A B. Removal of the Oil Inlet Cover NOTE : For Turbine Frame with Tangential Symetrical Section Structs only. ____ (1) Remove the bolts (30) which attach the oil inlet cover (160) to the No. 5 bearing support. (2) Install the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), on the rear flange of the oil inlet cover (160). (3) Remove the oil inlet cover (160). (4) Remove and discard the O-ring (20). (5) Remove and discard the gasket seal (230). (6) Remove the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), from the oil inlet cover (160). (7) Cut and remove the lockwire which safeties the nipple (180) to the oil inlet cover (160). (8) Remove the nipple (180) from the oil inlet cover (160).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 425 Nov 01/08
C F M 56-5B (9) Remove and discard the O-ring (190). R R
**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, Subtask 72-56-00-210-055 C. Inspection of the oil inlet cover (1) Check for rubs marks from seal teeth in the abradable coating of the oil inlet cover. (a) If marks are found with an average less than 0.010 in. (0.2539 mm) (0.2539 mm) deep over entire circumference, the oil inlet cover is serviceable. (b) If marks are found with an average more than 0.010 in. (0.2539 mm) deep over entire circumference, the oil inlet cover must be sent to shop for repair.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 426 Nov 01/08
C F M 56-5B TASK 72-56-00-400-002 Installation of the Oil Inlet Cover Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R
No specific No specific No specific
soft nose pliers warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) 1 TOOL SET SEAL FITTING AGB-TGB 1 ADAPTER, PULLER - OIL INLET COVER
No specific 856A2794 856A3419
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2442
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00) USA AMS 5687 lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00) USA AMS 5689 lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 427 Feb 01/10
C F M 56-5B C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------10 10 20 20 20 20 60 60 60 60 60 60 190 190 190 190 190 190 230 230
Gasket Gasket O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring Gasket Gasket
seal seal
72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00
seal seal
02A-140 02B-140 02A-130 02A-130A 02B-130 02B-130A 02A-080 02A-080A 02A-080B 02B-080 02B-080A 02B-080B 02A-080 02A-080A 02A-080B 02B-080 02B-080A 02B-080B 02A-140 02B-140
D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-56-00-000-001 72-56-00-400-001
Removal of the Flame Arrestor and Flange Assembly Installation of the Flame Arrestor and Flange Assembly
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-301
Fig. 402
**ON A/C 051-051, 72-56-00-991-301-B
Fig. 402A
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 428 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-301-A
Fig. 402B
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-302
Fig. 403
**ON A/C 051-051, 72-56-00-991-302-B R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-302-A
R R
Fig. 403A
Fig. 403B
**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 3. __________ Job Set-up Subtask 72-56-00-860-051 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the flame arrestor and the flange assembly are removed (Ref. TASK 72-56-00-000-001).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 429 Nov 01/08
C F M 56-5B 4. Procedure _________ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 402/TASK 72-56-00-991-301) **ON A/C 051-051, (Ref. Fig. 402A/TASK 72-56-00-991-301-B) R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 402B/TASK 72-56-00-991-301-A) **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 403/TASK 72-56-00-991-302) **ON A/C 051-051, (Ref. Fig. 403A/TASK 72-56-00-991-302-B)
R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 403B/TASK 72-56-00-991-302-A) **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207, Subtask 72-56-00-420-052 A. Installation of the Oil Inlet Cover (80) NOTE : For Turbine Frame with Tangential Non Symetrical Section Struts or ____ with Radial Struts only. (1) Lubricate a new O-ring (60) with engine oil (Material No. CP2442). (2) Install the O-ring (60) on the nipple (50), with the TOOL SET SEAL FITTING AGB-TGB (856A2794G01).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 430 Nov 01/08
C F M 56-5B (3) Install the nipple (50) on the oil inlet cover (80) at 7:00 oclock position, aft looking forward. Tighten by hand to seat. (4) TORQUE the nipple (50) to between 180 and 195 lbf.in (2.03 and 2.20 m.daN). (5) Safety the nipple (50) to the oil inlet cover (80) with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). (6) Lubricate a new O-ring (20) with engine oil (Material No. CP2442). (7) Install the O-ring (20) in the front groove on the oil inlet cover (80). (8) Position a new Gasket seal (10) on the oil inlet cover (80). (9) Lubricate the threads of the bolts (20) with graphite grease (Material No. CP2101). (10) Install the oil inlet cover COVER (856A3419G02), in the inlet cover flange with the bottom of the No. 5 bearing
(80) with the ADAPTER, PULLER - OIL INLET LPT frame. Match the position of the oil oil scavenge tube which comes out at the support.
(11) Attach the oil inlet cover (80) to the No. 5 bearing support with bolts (30). (12) TORQUE the bolts (30) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). (13) Safety bolts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-420-052-A A. Installation of the Oil Inlet Cover (80) NOTE : For Turbine Frame with Tangential Symetrical Section Struts only. ____ (1) Lubricate a new O-ring (190) with engine oil (Material No. CP2442). (2) Install the O-ring (190) on the nipple (180), with the TOOL SET SEAL FITTING AGB-TGB (856A2794G01).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 431 Nov 01/08
C F M 56-5B (3) Install the nipple (180) on the oil inlet cover (160) at 7:00 oclock position, aft looking forward. Tighten by hand to seat. (4) TORQUE the nipple (180) to between 180 and 195 lbf.in (2.03 and 2.20 m.daN). (5) Safety the nipple (180) to the oil inlet cover (160) with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). (6) Lubricate a new O-ring (20) with engine oil (Material No. CP2442). (7) Install the O-ring (20) in the front groove on the oil inlet cover (160). (8) Position a new Gasket seal (230) on the oil inlet cover (160). (9) Lubricate the threads of the bolts (30) with graphite grease (Material No. CP2101). (10) Install the oil inlet cover (160) with the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), in the LPT frame. Match the position of the oil inlet cover flange with the oil scavenge tube which comes out at the bottom of the No. 5 bearing support. (11) Attach the oil inlet cover (160) to the No. 5 bearing support with bolts (30). (12) TORQUE the bolts (30) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). (13) Safety bolts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, Subtask 72-56-00-420-053 B. Installation of the Oil Supply Tubes CAUTION : MAKE SURE THAT THE SLEEVE LOCKING NUT OF THE OIL SUPPLY TUBE IN _______ THE LPT FRAME HUB IS LOOSENED. NOTE : For Turbine Frame with Radial Struts only. ____
R EFF : 001-049, 052-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 432 Nov 01/08
C F M 56-5B (1) Make sure that the sleeve locking nut (110) is loosened and remove the two bolts (130) which attach the end fitting (120) to the LPT frame. R R R
(2) Put the oil supply tube (40) and the damping oil tube (70) in position.
R
(3) Connect the oil supply tube (40) to the nipple (50) and to the oil supply tube (140). Tighten the coupling nuts by hand.
R R R
(4) Connect the damping oil tube (70) to the nipple (90) of the No. 5 bearing support and to the oil supply tube (40). Tighten the coupling nuts by hand. (5) Lubricate the threads of the bolts (130) with graphite grease (Material No. CP2101). (6) Attach the end fitting (120) to the LPT frame with bolts (130). (7) Tighten the sleeve locking nut (110) by hand.
R R R R
CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (8) Make sure the oil tubes are installed without strain.
R R
(9) TORQUE both coupling nuts of the oil tube (40) to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
R
(10) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R
(11) TORQUE the sleeve locking nut (110) to between 50 and 55 lbf.in (0.56 and 0.62 m.daN).
R
(12) Safety the sleeve locking nut (110) with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R
(13) TORQUE the two bolts (130) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN).
EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 433 Feb 01/10
R
C F M 56-5B (14) Safety bolts (130) with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R
(15) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R R R
(a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of the damping oil tube (70) connected to nipple of the No. 5 bearing support to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(16) Make sure that the damping oil tube (70) is installed without strain as follows:
R R
(a) Loosen the union nut of the damping oil tube connected on the oil tube (40).
R R
(b) Make sure that the damping oil tube is installed without strain, and in line with the nipple of the oil tube (40).
R R
(c) If necessary, bend the damping oil tube in bent sections. Do not bend the tube near end fittings.
R R
(17) Reconnect the coupling nut of the damping oil tube (70) to the oil tube (40). Tighten the coupling nut with hand.
R
(18) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R R
(a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of damping oil tube (70) to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(19) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 434 Feb 01/10
C F M 56-5B **ON A/C 051-051, Subtask 72-56-00-420-053-B B. Installation of the Oil Supply Tubes NOTE : This procedure is for Turbine Frame with Tangential Non Symetrical ____ Section Struts only. NOTE : Make sure that Oil Supply Tube in the LPT frame is correctly ____ positioned. (1) Put the oil supply tube (40) and the damping oil tube (70) in position. R R
(2) Connect the oil supply tube (40) to the nipple (50) and to the oil supply tube (100). Tighten the coupling nuts by hand.
R R R
(3) Connect the damping oil tube (70) to the nipple (90) of the No. 5 bearing support and to the oil supply tube (40). Tighten the coupling nuts by hand.
R R R R
CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (4) Make sure the oil tubes are installed without strain.
R R
(5) TORQUE both coupling nuts of the oil tube (40) to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
R
(6) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R
(7) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R EFF : 051-051, 72-56-00 CES
Page 435 Feb 01/10
R R R
C F M 56-5B (a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of the damping oil tube (70) connected to nipple of the No. 5 bearing support to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(8) Make sure that the damping oil tube (70) is installed without strain as follows:
R R
(a) Loosen the union nut of the damping oil tube connected on the oil tube (40).
R R
(b) Make sure that the damping oil tube is installed without strain, and in line with the nipple of the oil tube (40).
R R
(c) If necessary, bend the damping oil tube in bent sections. Do not bend the tube near end fittings.
R R
(9) Reconnect the coupling nut of the damping oil tube (70) to the oil tube (40). Tighten the coupling nut with hand.
R
(10) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R R
(a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of damping oil tube (70) to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(11) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). **ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-420-053-A B. Installation of the Oil Supply Tubes NOTE : This procedure is for Turbine Frame with Tangential Symetrical ____ Section Struts only. NOTE : Make sure that Oil Supply Tube in the LPT frame is correctly ____ positioned.
R EFF : 051-051, 106-149, 155-199, 208-249, 72-56-00 251-299, 301-399, 401-499, CES
Page 436 Feb 01/10
C F M 56-5B (1) Put the oil supply tube (170) and the damping oil tube (200) in position. R R
(2) Connect the oil supply tube (170) to the nipple (180) and to the oil supply tube (220). Tighten the coupling nuts by hand.
R R R
(3) Connect the damping oil tube (200) to the nipple (210) of the No. 5 bearing support and to the oil supply tube (170). Tighten the coupling nuts by hand.
R R R R
CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (4) Make sure the oil tubes are installed without strain.
R R
(5) TORQUE both coupling nuts of the oil tube (170) to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
R
(6) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R
(7) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R R R
(a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of the damping oil tube (200) connected to nipple of the No. 5 bearing support to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(8) Make sure that the damping oil tube (200) is installed without strain as follows:
R R
(a) Loosen the union nut of the damping oil tube connected on the oil tube (170).
R R
(b) Make sure that the damping oil tube is installed without strain, and in line with the nipple of the oil tube (170).
EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 437 Feb 01/10
R R
C F M 56-5B (c) If necessary, bend the damping oil tube in bent sections. Do not bend the tube near end fittings.
R R
(9) Reconnect the coupling nut of the damping oil tube (200) to the oil tube (170). Tighten the coupling nut with hand.
R
(10) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R R
(a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of damping oil tube (200) to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(11) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 5. Close-up ________ Subtask 72-56-00-410-057 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the flange assembly and the flame arrestor (Ref. TASK 72-5600-400-001). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 438 Feb 01/10
C F M 56-5B TURBINE FRAME ASSEMBLY - INSPECTION/CHECK _________________________________________ TASK 72-56-00-210-002 Inspection/Check of the Turbine Frame Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-56-00-000-001 72-56-00-300-003 72-56-00-300-006 72-56-00-400-001 R R R R
78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-56-00-991-305
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Removal of the Flame Arrestor and Flange Assembly Replacement of Defective Studs Replacement of the Oil Supply Tube Assembly Installation of the Flame Arrestor and Flange Assembly Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/08
C F M 56-5B 3. __________ Job Set-up R
Subtask 72-56-00-860-054
R
A. Aircraft Maintenance Configuration
R R
(1) Make sure that the core nozzle is removed (Ref. TASK 78-11-11-000041).
R R
(2) Make sure that the centerbody is removed (Ref. TASK 78-11-12-000041). Subtask 72-56-00-941-051
R
B. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-053
R
C. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-56-00-040-051
R
D. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B Subtask 72-56-00-010-054 R
E. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-56-00-991-305) Subtask 72-56-00-210-051 A. Visual inspection of the Turbine Frame Assembly: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Forward and aft outer flanges for : - Cracks connecting bolt holes
Not serviceable
- Cracks extending from bolt holes to outer edge of flange.
One crack 0.20 in. (5.1 mm) max. per hole with a minimum 5-hole separation between cracks.
- Cracks extending from bolt holes toward casing skin.
Five cracks 0.20 in. (5.1 mm) max. per flange with a minimum 10-hole separation between cracks. Axial cracks only.
- Cracks in other areas of flange.
Five cracks per flange 0.20 in. (5.1 mm) long with a minimum 5 in. (127 mm) separation between any other cracks.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B
Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 15 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 25 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 35 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 45 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B
Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 55 (SHEET 5) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Nicks, scores and Five per flange 1 in. scratches. (25.4 mm) long, 0.01 in. (0.25 mm) dup, after removal of high metal with 1 in. (25.4 mm) minimum separation. 2. Engine mounting lug areas, airframe attach points only for : - Cracks out of bolt holes
Not serviceable
- Cracks in welds or in other areas of engine mounting lug area.
Not serviceable
- Nicks, scores and scratches.
Any number 1 in. (25.4 mm) long, 0.02 in. (0.5 mm) deep after removal of high metal with 1 in. (25.4 mm) minimum separation.
3. All other areas of outer casing skin for : - Cracks
Not serviceable.
- Nicks, scores and scratches.
Any number 1 in. (25.4mm) long, 0.03 in. (0.76 mm) deep after removal of high metal and 1 in. (25.4 mm) minimum apart.
4. Oil supply and scavenge tubes for :
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Cracks Not serviceable. Replace the oil supply tube (Ref. TASK 72-56-00300-006). - Nicks, scratches
Any number 0.01 in. (0.25 mm) deep after removal of high metal.
Replace the oil supply tube (Ref. TASK 72-56-00300-006).
- Dents
Two per tube, smooth contour 0.05 in. (1.27 mm) deep.
Replace the oil supply tube (Ref. TASK 72-56-00300-006).
- Oil marks
Any amount
5. Struts for: - Cracks
Not serviceable.
- Nicks, scores and scratches.
Any number, any length 0.02 in. (0.51 mm) deep after removal of high metal.
- Dents
Any number, smooth contour 0.02 in. (0.51 mm) deep.
- Broken stud or damaged threads
Three (3) maximum: - If not adjacent to each other: 500hrs/500cyc - If two (2) non-serviceable studs are adjacent, but the third one is separated from them by two (2) serviceable studs: 500hrs/500cyc
Replace stud (Ref. TASK 72-56-00-300-003) within 500 hours/500 cycles.
6. No. 7 and No. 10 struts (oil supply and scavenge tubes) bulkheads for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Cracks in the Two cracks, any lenght bulkhead wall on each bulkhead - Cracks from the bulkhead, extending in the hub skin
Not serviceable
7. Sump flooding boss area for: - Cracks in the hub
Two cracks, no longer than 1 in. (25.4 mm) and 1 in. (25.4 mm) apart, minimum
Flame arrestor for: - cracks in all areas including the retaining metal strip
Any number
- Missing retaining strips
Serviceable, if one strip remains
- Honeycomb grid plug for obturation
Any area up to 50 percent of obturation
- Honeycomb missing
Not serviceable
Replace the flame arrestor within the next 10 cycles (Ref. TASK 72-56-00-000001) (Ref. TASK 72-56-00400-001)
8. Thermal insulation blankets - missing or protuding blanket in the flowpath
Not serviceable
Install a new blanket. See overserviceable limit extension (Ref. TASK 7200-00-200-025)
9. Guide bushing for the oil supply tube for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- worn area No more than 0.06 in. (1.52 mm) - flush with the LPT bore
Not serviceable
600 cycles or 750 hours max serviceable extension is allowed with less than 0.06 in. (1.52 mm). 25 cycles or 50 hours max serviceable extension is allowed with more than 0.06 in. (1.52 mm).
5. Close-up ________ Subtask 72-56-00-410-053 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. R
(2) Install the centerbody (Ref. TASK 78-11-12-400-041).
R
(3) Install the core nozzle (Ref. TASK 78-11-11-400-041).
R
(4) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-56-00-440-051 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B Subtask 72-56-00-410-054 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B TURBINE FRAME ASSEMBLY - CLEANING/PAINTING __________________________________________ TASK 72-56-00-100-001 Cleaning of the Oil Inlet Cover 1. __________________ Reason for the Job Use this procedure to clean the oil inlet cover. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-56-00-000-002 72-56-00-400-002 SPM 702111 SPM 702112 SPM 702131 72-56-00-991-303
Removal of the Oil Inlet Cover Assembly Installation of the Oil Inlet Cover Assembly
Fig. 701
3. __________ Job Set-up Subtask 72-56-00-941-054 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 701 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-057 B. Remove the oil inlet cover (Ref. TASK 72-56-00-000-002). 4. Procedure _________ (Ref. Fig. 701/TASK 72-56-00-991-303) Subtask 72-56-00-110-050 A. Degreasing of the Oil Inlet Cover (1) Solvent degreasing (alternative procedure available) - refer to CFMI SPM (Ref. SPM 702111), Solvent Degreasing of all materials, except Titanium Alloys. (2) Vapor degreasing (alternative procedure) - refer to CFMI SPM (Ref. SPM 702112), Vapor Degreasing. NOTE : Use one of these procedures to remove oil and grease from the ____ oil inlet cover. Subtask 72-56-00-130-050 B. Cleaning of the Oil Inlet Cover - refer to CFMI SPM (Ref. SPM 702131), Descalling ferrous alloys. Subtask 72-56-00-210-052 C. Inspection of the Oil Nozzle (1) Make sure that the oil nozzle is clean and clear of unwanted material.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 702 Nov 01/08
C F M 56-5B
Cleaning of the Oil Inlet Cover Figure 701/TASK 72-56-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 703 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-56-00-410-058 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the oil inlet cover (Ref. TASK 72-56-00-400-002). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 704 Nov 01/08
C F M 56-5B TASK 72-56-00-100-002 Cleaning of the Aft Sump Oil Supply Tube 1. __________________ Reason for the Job Use this procedure to clean the aft sump oil supply tube where it goes through the No. 10 turbine frame strut, when you suspect signs of cocking in this oil supply tube, after an air flow check of the aft sump oil supply circuit. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-56-00-000-002 72-56-00-400-002 SPM 702117 R R
Removal of the Oil Inlet Cover Assembly Installation of the Oil Inlet Cover Assembly
**ON A/C 001-049, 052-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 72-56-00-991-304
Fig. 702
**ON A/C 051-051, 72-56-00-991-304-A
Fig. 702A
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 705 Nov 01/08
R R
C F M 56-5B **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 3. __________ Job Set-up Subtask 72-56-00-941-055 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-058 B. Remove the oil inlet cover (Ref. TASK 72-56-00-000-002). 4. Procedure _________
R R
**ON A/C 001-049, 052-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, (Ref. Fig. 702/TASK 72-56-00-991-304) **ON A/C 051-051, (Ref. Fig. 702A/TASK 72-56-00-991-304-A)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 706 Nov 01/08
C F M 56-5B
Cleaning of the Aft Sump Oil Supply Tube Figure 702/TASK 72-56-00-991-304 R EFF : 001-049, 052-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 707 Nov 01/08
C F M 56-5B
Cleaning of the Aft Sump Oil Supply Tube Figure 702A/TASK 72-56-00-991-304-A R EFF : 051-051, 72-56-00 CES
Page 708 Aug 01/07
R R
C F M 56-5B **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, Subtask 72-56-00-110-051 A. Degreasing and Cleaning of the Aft Sump Oil Supply Tube (1) Connect steel tubing and an approved pump to the oil supply tube ends. (2) Do the cleaning of internal lube oil tube (Ref. SPM 702117). 5. Close-up ________ Subtask 72-56-00-410-059 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the oil inlet cover (Ref. TASK 72-56-00-400-002). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 709 Nov 01/08
C F M 56-5B TASK 72-56-00-100-005 Cleaning of the Aft Sump Oil Scavenge Tube 1. __________________ Reason for the Job Use this procedure to clean the aft sump oil scavenge tube where it goes through the No. 7 turbine frame strut, when you suspect signs of coking in this oil scavenge tube, after an air flow check of the aft sump oil scavenge circuit. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 0.70 to 10.00 m.daN (5.00 to 75.00 lbf.ft) Torque Wrench : range 2.00 to 20.00 m.daN (15.00 to 150.00 lbf.ft) 1 WRENCH-COUNTERTORQUE NO 5 BEARING NIPPLE LINE
No specific R
856A3492
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1041
Material No.
CP1065
Material No.
CP2104
Material No.
CP2442
Material No.
CP2554
Material No.
CP8001
Material No.
CP8006
* alcohol-isopropyl (Ref. 70-30-00) * kerosene (Ref. 70-30-00) * lubricant-molybdenum disulfide, solid-molykote G (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * lubricant oil WD-40 (Ref. 70-30-00) * safetywire (Ref. 70-30-00) * safety cable (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 710 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-56-00-000-002 72-56-00-400-002 SPM 702117 72-56-00-991-306 72-56-00-991-307
Removal of the Oil Inlet Cover Assembly Installation of the Oil Inlet Cover Assembly Fig. 703 Fig. 704
3. __________ Job Set-up Subtask 72-56-00-941-063 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-069 B. Remove the oil inlet cover (Ref. TASK 72-56-00-000-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 711 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 703/TASK 72-56-00-991-306, 704/TASK 72-56-00-991-307) Subtask 72-56-00-020-065 A. Disconnect the oil scavenge tube CAUTION : USE TWO WRENCHES TO LOOSEN THE TUBE COUPLING NUTS. USE ONE _______ WRENCH TO HOLD THE NIPPLE FITTING. USE THE OTHER WRENCH TO LOOSEN THE COUPLING NUT. IF THE NIPPLE FITTING TURNS, DAMAGE CAN OCCUR. (1) Disconnect the aft sump oil scavenge tube from the oil scavenge tube, at the No. 7 TRF strut. CAUTION : USE THE COUNTER WRENCH TO LOOSEN THE TUBE COUPLING NUTS. _______ OTHER WRENCHES CAN CAUSE DAMAGE TO THE HARDWARE. (2) Disconnect the oil scavenge tube from the nipple of the No. 5 bearing support. (Ref. Fig. 703/TASK 72-56-00-991-306) (a) Cut and remove the safetywire between the nipple, at the 6 oclock position of the No. 5 bearing support nipple, and the coupling nut of the oil scavenge tube. R R
(b) Install the WRENCH-COUNTERTORQUE NO 5 BEARING NIPPLE LINE (856A3492) (G03) or (G04) on the TRF flange: 1 _
Loosen the four counter wrench bolts.
2 _
Install the counter wrench on the No. 5 bearing support nipple.
3 _
Tighten the two support bolts on the turbine rear frame.
4 _
Do a clockwise rotation on the counter wrench to take up and tighten the four counter wrench bolts.
(c) Disconnect the oil scavenge tube from the nipple of the No. 5 bearing support with the oil scavenge tube nut wrench. (d) Remove the counter wrench from the TRF flange.
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 712 Nov 01/09
C F M 56-5B (e) Disengage the guide bushing of the oil scavenge tube from the 5 oclock boss of the TRF outer case to get access to the oil scavenge tube upper end. Subtask 72-56-00-290-050 B. Do a visual inspection of the oil scavenge tube with a flexible borescope tool of 2.5 mm (0.0984 in.) to 4 mm (0.1574 in.) dia. and a light source. (1) Make sure that it is free of any particles/contamination. If you find any signs of oil coking, remove the oil scavenge tube to do a chemical cleaning. Subtask 72-56-00-110-054 C. If the borescope check of the oil scavenge tube shows coking contamination, degrease and clean the tube as follows: (1) Attach the steel tubing and the pump to the removed oil scavenge tube. NOTE : You must use steel tubing and an acceptable pump to do this ____ procedure. (2) Clean the internal oil tubes (Ref. SPM 702117). (3) Do a visual inspection of the cleaned oil scavenge tube with a flexible borescope tool of 2.5 mm (0.0984 in.) to 4 mm (0.1574 in.) dia. and a light source after cleaning to make sure that it is free of any particles/contamination before re-installation. (a) No oil coked particles/contamination is permitted. (b) Repeat the cleaning task until the tube is free of particles/contamination. (4) Disconnect the cleaned tube from the steel tubing and the pump.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 713 Nov 01/08
C F M 56-5B
Oil Scavenge Tube Nut Figure 703/TASK 72-56-00-991-306- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 714 Nov 01/08
C F M 56-5B
Oil Scavenge Tube Nut Figure 703/TASK 72-56-00-991-306- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 715 Nov 01/08
C F M 56-5B
Oil Scavenge Line Cleaning Figure 704/TASK 72-56-00-991-307- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 716 Nov 01/08
C F M 56-5B
Oil Scavenge Line Cleaning Figure 704/TASK 72-56-00-991-307- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 717 Nov 01/08
C F M 56-5B Subtask 72-56-00-110-055 D. Degrease and mechanically clean the oil scavenge tube (not removable) as follows: NOTE : This is a mechanical cleaning because the tube is non-removable. ____ (1) Put protection on the No. 5 bearing to prevent any contamination by the material. NOTE : Be careful to put protection equipment on the No. 5 bearing ____ before you start a mechanical cleaning of the oil scavenge line. (2) Put protection on all the cavities and tube ends to prevent any contamination by the material. (3) Put a cap for the oil scavenge tube on the outer case side. (4) Put a sufficient quantity of lubricant oil WD-40 (Material No. CP2554) to fill the tube and keep it for a sufficient time to affect the coking in the concerned area. (5) Put a container under the tube to collect the penetrant corrosion inhibitor. (6) Remove the cap from the tube and collect the penetrant corrosion inhibitor. (7) Turn the tube in its position to get access to the ends of the tube. (8) Introduce a cylinder-brush tool through the tube ends and move the tool to the coked area. WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE YOUR _______ CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. (9) Put a small quantity of kerosene (Material No. CP1065) with a filler tool in the tube. (10) Do an alternative movement of rotation on the tool to break the coking contamination.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 718 Nov 01/08
C F M 56-5B (11) Extract the tool and use lint-free cloths to collect the coked particle. WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE YOUR _______ CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. (12) Clean the cylinder-brush tool with kerosene (Material No. CP1065). CAUTION : DO NOT INTRODUCE ANY PARTICULES/CONTAMINATION TO THE _______ INTERNAL SIDE OF BEARING SUPPORT TO PREVENT BEARING CONTAMINATION. IF NOT, YOU CAN CAUSE DAMAGE TO ENGINE. (a) Repeat the cleaning until tube is free of particles/contamination. WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE _______ YOUR CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY _______ SHOULD BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING. NOTE : No oil coked particles/contamination is permitted. ____ (13) Do a flushing of the tube with kerosene (Material No. CP1065) or alcohol-isopropyl (Material No. CP1041). (14) Dry the tube with a clean compressed air source or nitrogen source. (15) Do a visual inspection of the cleaned tube with a flexible borescope tool of 2.5 mm (0.0984 in.) to 4 mm (0.1574 in.) dia. and a light source after cleaning to make sure that it is free of any particles/contamination before you use it again. (16) Do a mechanical cleaning of the nipple of the No. 5 bearing support at the 6 oclock position to remove any signs of oil coking. (17) Dry and clean the nipple with a compressed air source or nitrogen source.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 719 Nov 01/08
C F M 56-5B (18) Do a visual inspection of the cleaned tube with a flexible borescope tool of 2.5 mm (0.0984 in.) to 4 mm (0.1574 in.) dia. and a light source after cleaning to make sure that it is free of any particles/contamination before the installation of the oil scavenge tube. (a) Repeat the cleaning until the nipple is free of particles/contamination. NOTE : No oil coked particles/contamination is permitted. ____ Subtask 72-56-00-420-063 E. Reconnection of the oil scavenge line (1) Reconnect the oil scavenge line as follows: (a) Remove the protection from the No. 5 bearing cavity and oil scavenge tube ends. (b) Apply a thin layer of lubricant-molybdenum disulfide, solidmolykote G (Material No. CP2104) with a spray gun on the guide bushing of the oil scavenge tube. (c) Engage the guide bushing of the oil scavenge tube into the boss of the TRF at the 5 oclock position. (d) Connect the coupling nut of oil scavenge tube to the 6 oclock nipple on the No. 5 bearing support. Tighten the coupling nut by hand. CAUTION : ALWAYS INSTALL THE COUNTER WRENCH ON THE NIPPLE OF THE _______ NUMBER-5 BEARING SUPPORT. THEN LOOSEN OR TIGHTEN THE COUPLING NUT OF THE OIL SCAVENGE TUBE. THIS WILL HELP TO PREVENT DAMAGE TO THE NIPPLE. R
(2) Install the WRENCH-COUNTERTORQUE NO 5 BEARING NIPPLE LINE (856A3492) (G03) or (G04) on the TRF flange. (a) Loosen the four counter wrench bolts. (b) Install the counter wrench on the No. 5 bearing support nipple. (c) Tighten the two support bolts on the turbine rear frame. (d) Do a clockwise rotation on the counter wrench to take up and tighten the four counter wrench bolts.
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 720 Nov 01/09
C F M 56-5B (3) Tighten the coupling nut of the oil scavenge tube to between 5 and 6 m.daN (36.87 and 44.24 lbf.ft) with the oil scavenge tube nut wrench. (a) Attach with safetywire (Material No. CP8001) or safety cable (Material No. CP8006). (4) Remove the counter wrench from the TRF flange. (5) Reconnect the rear sump oil scavenge tube to the oil scavenge tube. (Ref. Fig. 704/TASK 72-56-00-991-307) WARNING : DO NOT LET THE ENGINE OIL STAY ON YOUR SKIN FOR A LONG _______ TIME. FLUSH OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND INTO YOUR BODY. (a) Apply a layer of engine oil (Material No. CP2442) on the threads of the rear sump oil scavenge tube. CAUTION : USE TWO WRENCHES TO TIGHTEN THE TUBE COUPLING NUTS. USE _______ ONE WRENCH TO HOLD THE NIPPLE FITTING. USE THE OTHER WRENCH TO TIGHTEN THE COUPLING NUT. IF THE NIPPLE FITTING TURNS, DAMAGE CAN OCCUR. (b) Tighten the coupling nuts to between 10.2 and 12.4 m.daN (75.22 and 91.44 lbf.ft). (c) Safety the coupling nut to the nipple with safetywire (Material No. CP8001) or safety cable (Material No. CP8006). 5. Close-up ________ Subtask 72-56-00-410-071 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the oil inlet cover (Ref. TASK 72-56-00-400-002). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 721 Nov 01/08
C F M 56-5B TURBINE FRAME ASSEMBLY - REPAIRS ________________________________ TASK 72-56-00-300-003 Replacement of Defective Studs 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R R R
No specific
Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN)
No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 72-56-00-991-310
Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Fig. 801
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-56-00-010-065 A. Get Access (1) Remove the core nozzle (Ref. TASK 78-11-11-000-041). (2) Remove the center body (Ref. TASK 78-11-12-000-041). 4. Procedure _________ (Ref. Fig. 801/TASK 72-56-00-991-310) Subtask 72-56-00-869-054 A. Preparation for Replacement (1) Clear away the stud to repair by removing the attachment bolts on the rear flange of the two adjacent thermal insulation blankets and lifting them. After SB 72-247 (2) Clear away the stud to repair by removing the attachment bolts and washers on the rear flange of the two adjacent thermal insulation blankets and lifting them. END of SB 72-247 Subtask 72-56-00-350-052 B. Replace defective studs (1) Remove the tack weld which safeties the defective stud to the frame. To do this, use a small, narrow grinding wheel. NOTE : Be careful not to cut into the metal of the frame when you do ____ the grinding. (2) Loosen and remove the stud. Discard it. (3) Complete the removal of the remaining tack weld material. To do this, use a small, manual grind tool. (4) Blow the areas adjacent to the hole for the stud with shop air.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B
Replacement of the Defective Studs on the Turbine Frame Figure 801/TASK 72-56-00-991-310 R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B (5) Apply a thin layer of graphite grease (Material No. CP2101) on the stud threads which go in the hole of the frame. (6) Tighten the new stud by hand on the turbine frame. Then use a torque wrench to complete the installation. TORQUE the stud to between 243.8 and 269.5 lbf.in (2.75 and 3.04 m.daN). (7) Loose the stud and TORQUE it a second time to between 243.8 and 269.5 lbf.in (2.75 and 3.04 m.daN). NOTE : You must do the tack welding of the new stud in shop, at the ____ next maintenance opportunity. (8) Apply a thin layer of graphite grease (Material No. CP2101) on the bolts which secure the thermal insulation blankets. PRE CFM SB 72-247 (9) Re-install the two adjacent thermal insulation blankets with attachment bolts on the rear flange. END of PRE CFM SB 72-247 POST CFM SB 72-247 (10) Re-install the two adjacent thermal insulation blankets with washers and attachment bolts on the rear flange. END of CFM SB 72-247 (11) TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN). 5. Close-up ________ Subtask 72-56-00-410-065 A. Close Access (1) Install the center body (Ref. TASK 78-11-12-400-041). (2) Install the core nozzle (Ref. TASK 78-11-11-400-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B TASK 72-56-00-300-004 Replacement of Defective or Missing Thermal Insulation Blankets (On Radial Struts TRF Only) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific
Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 72-56-00-991-320
Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Fig. 802
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-56-00-010-066 A. Get Access (1) Remove the core nozzle (Ref. TASK 78-11-11-000-041). (2) Remove the center body (Ref. TASK 78-11-12-000-041). 4. Procedure _________ (Ref. Fig. 802/TASK 72-56-00-991-320) Subtask 72-56-00-350-053 A. Replacement of defective or missing thermal insulation blankets (1) Replacement of items (30), (40) (and (50) for POST CFM SB 72-554) PRE CFM SB 72-247 (a) Remove the attachments bolts (10) from the rear flange of the thermal insulation blanket. END OF PRE CFM SB 72-247 POST CFM SB 72-247 (b) Remove the attachment bolts (10) and washers (20) from the rear flange of the thermal insulation blanket. END OF POST CFM SB 72-247 (c) Remove the blanket by lifting the rear flange, then pull and twist it. NOTE : Be careful to not damage the seal cover when you disengage ____ the thermal insulation blanket. (d) Install the new thermal insulation blanket items (30),(40) (and 50 for POST CFM SB 72-554). NOTE : Be careful to not damage the seal cover when you engage ____ the front edge of the thermal insulation blanket.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/08
C F M 56-5B (e) Apply a thin layer of graphite grease (Material No. CP2101) on the bolts. PRE CFM SB 72-247 (f) Install the two bolts (10) securing the blanket. END OF PRE CFM SB 72-247 POST CFM SB 72-247 (g) Install the two washers (20) and two bolts (10) securing the blanket. END OF POST CFM SB 72-247 (h) TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN). (2) Removal of item (50) (for PRE CFM SB 72-554) PRE CFM SB 72-247 (a) Remove the attachments bolts (10) from the rear flange of the thermal insulation blanket. END OF PRE CFM SB 72-247 POST CFM SB 72-247 (b) Remove the attachment bolts (10) and washers (20) from the rear flange of the thermal insulation blanket. END OF POST CFM SB 72-247 (c) Stretch the old thermal insulation blankets CAUTION : THE REMOVAL OF THE OLD THERMAL INSULATION BLANKETS _______ BETWEEN STRUTS 2-3, 7-8, 10-11 AND 15-16 MUST BE PERFORMED CAREFULLY DUE TO THEIR SPECIFIC SHAPE. TAKE CARE TO PREVENT DAMAGE TO ADJACENT PARTS WHEN YOU PUT THE BLANKETS OUT OF SHAPE TO PERMIT THEIR REMOVAL. 1 _
Stretch the old thermal insulation blankets out of shape as necessary to permit their disengagement from the heat shield and their removal from the LPT frame.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B
Replacement of the Thermal Insulation Blankets Figure 802/TASK 72-56-00-991-320- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Nov 01/08
C F M 56-5B
Replacement of the Thermal Insulation Blankets Figure 802/TASK 72-56-00-991-320- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B (d) Install the new thermal insulation blanket item (50). NOTE : Be careful to not damage the seal cover when you engage ____ the front edge of the thermal insulation blanket. (e) Apply a thin layer of graphite grease (Material No. CP2101) on the bolts. PRE CFM SB 72-247 (f) Install the two bolts (10) securing the blanket. END OF PRE CFM SB 72-247 POST CFM SB 72-247 (g) Install the two washers (20) and two bolts (10) securing the blanket. END OF POST CFM SB 72-247 (h) TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN). 5. Close-up ________ Subtask 72-56-00-410-066 A. Close Access (1) Install the center body (Ref. TASK 78-11-12-400-041). (2) Install the core nozzle (Ref. TASK 78-11-11-400-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
C F M 56-5B TASK 72-56-00-300-006 Replacement of the Oil Supply Tube Assembly 1. __________________ Reason for the Job This procedure is done to replace the oil supply tube assembly. This procedure is applicable only for engines Post SB CFM 72-0403 or Post SB CFM 72-0499. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice Torque Wrench : range 0.00 to 1.20 (0.00 to Torque Wrench : range 0.20 to 3.60 (2.00 to 1 FIXTURE INSTALLATION AND REMOVAL
No specific 856A2677
m.daN 9.00 lbf.ft) m.daN 26.00 lbf.ft)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2104
Material No.
CP2442
Material No.
CP8001
Material No.
CP8002
Material No. 19-003
* molykote G rapid plus (solid lubricant) (Ref. 70-30-00) * engine oil (Ref. 70-30-00) (Ref. 70-30-00) USA AMS 5687 Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Ref. 70-30-00) USA AMS 5689 Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Ref. 70-30-00) USA AMS 3819 LINT-FREE COTTON CLOTH (Ref. 20-31-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------70 70 80 80 90 90
oil supply tube oil supply tube coupling nut coupling nut retaining ring retaining ring
72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00
02A-190 02B-190 02A-180 02B-180 02A-170 02B-170
D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 72-56-00-000-001 72-56-00-400-001 78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 72-56-00-991-311
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Removal of the Flame Arrestor and Flange Assembly Installation of the Flame Arrestor and Flange Assembly Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Fig. 803
3. __________ Job Set-up Subtask 72-56-00-941-062 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1 (2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1 (2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1 (2). Subtask 72-56-00-010-068 B. Get Access (1) Remove the core nozzle assembly (Ref. TASK 78-11-11-000-041). (2) Remove the centerbody (Ref. TASK 78-11-12-000-041). (3) Remove the flame arrestor and the flange assembly (Ref. TASK 72-5600-000-001). NOTE : Discard the gasket seal installed between the flame arrestor ____ and the flange assembly. 4. Procedure _________ Subtask 72-56-00-300-051 A. Replacement of the Oil Supply Tube Assembly (Ref. Fig. 803/TASK 72-56-00-991-311) (1) Disconnect the oil supply tube assembly (10) from the rear sump oil supply tube (60) as follows: WARNING : ENGINE OIL IS TOXIC. USE PERSONAL PROTECTION EQUIPMENT. USE _______ IN A WELL-VENTILATED AREA. (a) Put a container under the engine, before you disconnect the coupling nut (20) of the oil supply tube assembly (10), to collect the drained oil. CAUTION : USE TWO WRENCHES TO LOOSEN OR TIGHTEN THE TUBE COUPLING _______ NUTS. ONE WRENCH TO HOLD THE UNION AND ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE HARDWARE. (b) Loosen the coupling nut (20), which attaches the rear sump oil-supply tube (60) to the oil supply tube assembly (10). (c) Loosen the bolt and nut that attach the rear sump oil-supply tube (60) through the shield and clamp from the turbine rear-frame outer case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/08
C F M 56-5B
Removal/Installation of the Oil Supply Tube Assembly Figure 803/TASK 72-56-00-991-311 R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Nov 01/08
C F M 56-5B (d) Disconnect the coupling nut (20) of the oil supply tube assembly (10) from the rear sump oil tube (60) at the turbine rear-frame outer case. (2) Remove the oil supply tube assembly as follows: (a) Cut and remove the safetywires from the coupling nuts. CAUTION : USE TWO WRENCHES TO LOOSEN OR TIGHTEN THE TUBE COUPLING _______ NUTS. ONE WRENCH TO HOLD THE UNION AND ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE HARDWARE. (b) Loosen the coupling nut between the damping oil tube (110) and the oil tube (50). (c) Loosen the coupling nut (80) between the oil supply tube assembly (10) and the oil tube (50). (d) Loosen the coupling nut between the oil tube (50) and the nipple (120) on the oil inlet cover (100). (e) Disconnect and remove the oil tube (50). (f) Pull and remove the retaining ring (90), which attaches the coupling nut (80) on the oil supply tube (70). Use the tool set FIXTURE INSTALLATION AND REMOVAL to remove the retaining ring. (g) Remove the coupling nut (80) from the oil supply tube assembly (10). (h) Pull the oil supply tube (70) down through the No. 10 strut at 7 oclock position to fully disengage its guide bushing from the boss. (i) Remove the oil supply tube (70) from the turbine rear-frame outer case. (3) Clean the turbine rear-frame inner hub area; use a lint-free cotton cloth MISCELLANEOUS (Material No. 19-003). NOTE : Make sure that you clean the turbine rear-frame inner hub area ____ before installation of the oil supply tube.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B (4) Installation of the oil supply tube assembly (10) as follows: (a) Apply a thin layer of molykote G rapid plus (solid lubricant) (Material No. CP2104) with a spray gun on the guide bushing of the oil supply tube (70). (b) Insert the oil supply tube (70) into the No. 10 strut of the turbine rear frame at the 7 oclock position. (c) Engage the guide bushing of the oil supply tube (70) into the boss. (d) Put the coupling nut (80) in position on the oil supply tube (70). Make sure you align the groove on the tube and the coupling nut. CAUTION : BE CAREFUL TO HOLD THE COUPLING NUT IN PLACE WITH A _______ LOCK WRENCH WHEN YOU ENGAGE THE RETAINING RING WITH COMBINATION PLIERS. (e) Insert the retaining ring (90) in the coupling nut (80). NOTE : Use the tool set FIXTURE INSTALLATION AND REMOVAL to ____ install the retaining ring. NOTE : Make sure that the retaining ring is fully inserted into ____ the coupling nut when its outer diameter base is in contact with the nut. NOTE : Make sure that the coupling nut rotates freely after the ____ installation of the retaining ring. (5) Install the oil tube (50) on the damping oil tube (110) as follows: WARNING : ENGINE OIL IS TOXIC. USE PERSONAL PROTECTION EQUIPMENT. USE _______ IN A WELL-VENTILATED AREA. CAUTION : USE TWO WRENCHES TO LOOSEN OR TIGHTEN THE TUBE COUPLING _______ NUTS. ONE WRENCH TO HOLD THE UNION AND ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE HARDWARE. (a) Apply a thin layer of engine oil (Ref. 70-30-00) (Material No. CP2442) on the nipple (120) of the oil inlet cover (100) and on the threads of the oil tube (50).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B (b) Put the oil tube (50) with its ends positioned on the nipple (120) of the oil inlet cover (100) and oil supply tube assembly (10). (c) Connect the oil tube (50) to the nipple (120) and to the oil supply tube assembly (10). Tighten the coupling nuts by hand. WARNING : ENGINE OIL IS TOXIC. USE PERSONAL PROTECTION EQUIPMENT. _______ USE IN A WELL-VENTILATED AREA. (d) Apply a thin layer of engine oil (Ref. 70-30-00) (Material No. CP2442) on the threads of the oil tube (50). (e) Put a damping oil tube (110) in position. (f) Connect the damping oil tube (110) to the oil tube (50). Tighten the coupling nut by hand. NOTE : Make sure that the oil tubes are installed without strain. ____ (g) TORQUE the coupling nut of the damping oil tube (110) to between 1.05 and 1.15 m.daN (92.92 and 101.76 lbf.in). (h) Safety the coupling nut with Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Material No. CP8001) or Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Material No. CP8002). (i) TORQUE the coupling nuts of the oil tube (50) to between 3.05 and 3.35 m.daN (22.49 and 24.70 lbf.ft). (j) Safety the coupling nut with Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Material No. CP8001) or Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Material No. CP8002). (6) Connect the oil supply tube assembly (10) to the rear sump oil-supply tube (60) as follows: (a) Install the rear sump oil-supply tube (60) to the oil supply tube assembly (10) with the coupling nut (20). Tighten the coupling nut by hand. NOTE : Make sure that the rear sump oil supply tube (60) is ____ unstrained. (b) TORQUE the coupling nut (20) to between 3.05 and 3.35 m.daN (22.49 and 24.70 lbf.ft).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
C F M 56-5B (c) TORQUE the nut with the bolt that attaches the rear sump oil-supply tube (60) to the turbine rear-frame outer case through the shield and clamp to between 0.50 and 0.55 m.daN (44.24 and 48.67 lbf.in). NOTE : The nut is installed on the turbine frame side. ____ 5. Close-up ________ Subtask 72-56-00-410-069 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the flange assembly and the flame arrestor (Ref. TASK 72-5600-400-001). (3) Install the centerbody (Ref. TASK 78-11-12-400-041). (4) Install the core nozzle assembly (Ref. TASK 78-11-11-400-041). (5) Do a check of the oil level (Ref. TASK 12-13-79-610-002). Subtask 72-56-00-410-070 B. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B ACCESSORY DRIVE SECTION - DESCRIPTION AND OPERATION ___________________________________________________ 1. _______ General (Ref. Fig. 001) Power for both engine and aircraft accessories is extracted thru a system of gearboxes and shafts. The inlet gearbox, which is located in the fan frame hub, takes power from the HP compressor front shaft and transmits this power to the transfer gearbox, installed under the fan frame through the radial drive shaft. A horizontal drive shaft then transmits the power to accessory gearbox. The accessory gearbox drives the following equipment : - The Integrated Drive Generator (IDG) (electrical power generation) at 0.5947 N2. - Hydraulic pump (hydraulic power generation) at 0.256 N2. - The Hydromechanical Unit (HMU) and the fuel pump at 0.423 N2. - The lubrication unit at 0.423 N2. - The ECU control alternator
R EFF : 001-049, 051-099, 101-149, 151-199, 72-60-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Accessory Drive System Figure 001 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-60-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Accessory Drive System Figure 001 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-60-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B INLET GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION __________________________________________________ 1. _______ General (Ref. Fig. 001) The inlet gearbox (IGB) assembly is located in the fan frame sump and is bolted to the forward side of the fan frame aft flange. The gearbox contains a horizontal bevel gear, a radial bevel gear, a core engine thrust (No. 3 ball) bearing, and a core engine roller bearing. The gearbox assembly serves as the mechanical coupling between the HPC rotor and the TGB. 2. Description ___________ A. Horizontal Bevel Gear The horizontal bevel gear, which has 47 teeth, is splined to the compressor rotor front shaft and secured to it by the No. 3 ball bearing locking nut. The horizontal bevel gear mates to the radial bevel gear to provide rotational torque to the transfer gearbox (TGB) assembly. B. Radial Bevel Gear The radial bevel gear, which has 35 teeth, is mounted on 2 roller bearings and one ball bearing (there are no duplex bearings). The gear is internally splined to accept the radial drive shaft which is removable from the exterior of the engine to allow individual replacement of the IGB and TGB. C. Thrust Bearing (No. 3 Ball) The No. 3 ball bearing is installed during IGB assembly between the gearbox housing and the horizontal bevel gear. It provides axial positioning of the forward end of the high pressure compressor (HPC) rotor. D. Roller Bearing (No. 3 Roller) The No. 3 roller bearing is installed during IGB assembly between the gearbox housing and the horizontal bevel gear. It positions the core engine rotor radially.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-61-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Inlet Gearbox Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-61-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B TRANSFER GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION _____________________________________________________ 1. _______ General (Ref. Fig. 001) The transfer gearbox (TGB) provides power transmission between the inlet gearbox (IGB) and the accessory gearbox (AGB). It consists of the following major assemblies: - Radial drive shaft assembly. - TGB assembly. 2. ___________ Description (Ref. Fig. 002, 003) A. Radial Drive Shaft Assembly The radial drive shaft (RDS) assembly is installed inside the fan frame No. 7 strut at the 6 oclock position. It consists of the radial drive shaft and the shaft midlength bearing. (1) The radial drive shaft is made of steel alloy. It is hollow and measures approximately 29.52 in. (0.75 m). Both ends are externally splined and connect the IGB bevel gear and the TGB input bevel gear. A foolproof slot is machined on the shaft to avoid inversion of RDS during installation. (2) The shaft midlength bearing provides proper centering of radial drive shaft in its housing. Its inner race is mounted half-way up on the RDS and the outer race is part of the radial drive shaft housing. B. TGB Assembly The TGB assembly is installed under the fan frame at the 6 oclock position. It consists of the housing and a set of 2 bevel gears. (1) The TGB housing is made of two aluminum alloy castings bolted together. It is secured to the fan frame through a single clevis/link rod mounting arrangement located at the upper part of the TGB housing front end. The upper part of the TGB housing contains an adapter which corresponds to an adapter mounted on the fan frame. The TGB housing accommodates 3 oil nozzles for lubrication of the bevel gears and the bearings. The casting of the TGB housing is double-walled, to provide better oil scavenge. (2) The upper part of the TGB houses the input bevel gear, its bearing housing, ball bearing, and roller bearing. The bore of the bevel gear is splined at its upper end and connects with the radial drive shaft. An oil distributor installed inside the bevel gear and secured by a Spirolock system, ensures oil distribution and axial retention of the radial drive shaft.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Transfer Gearbox Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Transfer Gearbox Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
Transfer Gearbox Assembly Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B (3) The horizontal part of the TGB houses the horizontal bevel gear, its bearing housing, ball bearing and roller bearing. The bore of this bevel gear is splined at its forward end and connects with the horizontal drive shaft. An oil distributor installed inside the bevel gear and secured by a Spirolock system, ensures oil distribution to the bearing. The horizontal drive shaft housing is made of aluminum alloy, and the bearing housing is a cast part. It protects the horizontal drive shaft and the bevel gear assembly, and ensures connection with the AGB. It is bolted to both TGB and AGB housings. The suspension clevis is a cast part and is integral with the horizontal drive shaft housing.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B TRANSFER GEARBOX ASSEMBLY - REMOVAL/INSTALLATION ________________________________________________ TASK 72-62-00-000-002 Removal of the Transfer Gearbox Module 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific No specific No specific No specific 856A2537 856A2719 856A2727 856A2805
1 1 1 1
blanking plug blanking plugs and covers container hydraulic hoist platform slide hammer assy CG240 soft nose pliers warning notice PROTECTOR-MOUNTING PIN FIXTURE,SUPPORT-TGB R/I PULLER RADIAL DRIVE SHAFT TURNBUCKLE-TGB R/I
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-63-00-400-002 72-63-00-860-001 78-30-00-481-041 78-36-00-010-040 80-11-10-000-002 72-62-00-991-300 72-62-00-991-301 72-62-00-991-302
Opening of the Fan Cowl Doors Installation of the Handcranking Drive Cover Disengagement/Engagement of the Horizontal Drive Shaft Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Removal of the Pneumatic Starter Fig. 401 Fig. 402 Fig. 403
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-62-00-991-303 72-62-00-991-304 72-62-00-991-305 72-62-00-991-306 72-62-00-991-307 72-62-00-991-308
Fig. Fig. Fig. Fig. Fig. Fig.
404 405 406 407 408 409
3. __________ Job Set-up Subtask 72-62-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-62-00-010-056 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-62-00-040-054 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Nov 01/08
C F M 56-5B Subtask 72-62-00-010-058 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 401/TASK 72-62-00-991-300, 402/TASK 72-62-00-991-301, 403/TASK 72-62-00-991-302, 404/TASK 72-62-00-991-303, 405/TASK 72-62-00-991-304, 406/TASK 72-62-00-991-305, 407/TASK 72-62-00-991-306, 408/TASK 72-62-00-991307, 409/TASK 72-62-00-991-308) Subtask 72-62-00-020-053 A. Remove TGB external parts as follows: (1) Install a suitable container under the TGB to catch residual fluid draining from tubes and control. (2) Drain the TGB as follows: (a) Cut and remove the lockwire which safeties the drain plug (20) to the TGB. (b) Remove the drain plug (20) and let the oil drain. (c) Install the drain plug (20). Tighten by hand. (3) Loosen and remove the 4 bolts (110) securing the TGB scavenge tube (170) to the TGB housing (120) LH side. (4) Remove and retain gasket (90) located between TGB housing (120) and TGB scavenge tube flange. (5) Loosen and remove the 4 bolts (230) which secure the oil tank vent tube (220) assy to the TGB housing (120). (6) Remove and retain gasket (240) located between the oil tank vent tube (220) flange and the TGB housing (120).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 403 Nov 01/08
C F M 56-5B
Drain Plug Removal Figure 401/TASK 72-62-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 404 Nov 01/08
C F M 56-5B
Disconnection of Tubes on LH Side of TGB Figure 402/TASK 72-62-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 405 Nov 01/08
C F M 56-5B
Disconnection of Brackets on RH and Lower Side of TGB Figure 403/TASK 72-62-00-991-302- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 406 Nov 01/08
C F M 56-5B
Disconnection of Brackets on RH and Lower Side of TGB Figure 403/TASK 72-62-00-991-302- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 407 Nov 01/08
C F M 56-5B
Installation of the TGB Turnbuckle Figure 404/TASK 72-62-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 408 Nov 01/08
C F M 56-5B
Removal of the TGB Figure 405/TASK 72-62-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 409 Nov 01/08
C F M 56-5B
Removal of the Mounting Pin Figure 406/TASK 72-62-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 410 Nov 01/08
C F M 56-5B
Extraction of Mounting Pin Figure 407/TASK 72-62-00-991-306 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 411 Nov 01/08
C F M 56-5B
Extraction of Radial Drive Shaft Figure 408/TASK 72-62-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 412 Nov 01/08
C F M 56-5B
Installation of Blanking Items on TGB Housing Ports Figure 409/TASK 72-62-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 413 Nov 01/08
C F M 56-5B (7) Loosen union nut. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Loosen union nut (100) which attaches the securing TGB oil supply tube (180) to TGB housing (120). (8) Remove the two bolts (290) securing RH rear bracket (270) and the bleed bias bracket (280) to the right side of the TGB housing (120). (9) Remove the two bolts (360) securing bracket (60) on the rear face of the TGB housing (120). (10) Remove the two bolts (40 and 50) securing upper LH bracket (30) to the LH and rear side of TGB housing . (11) Remove the bolt (70) securing lower LH bracket (80) on the left side of the TGB housing (120). (12) Remove the bolt (300) securing forward bracket (260) on the right side of the TGB housing (120). Subtask 72-62-00-480-052 B. Installation of support equipment. (1) Install TURNBUCKLE-TGB R/I (856A2805G01) as follows: NOTE : To prevent AGB rotation during the TGB removal it is necessary ____ to install the TGB turnbuckle. (a) Remove the pneumatic starter (Ref. TASK 80-11-10-000-002). (b) Remove bolts and nuts from holes No. 46 and 47 on flange F to free brackets at this place. (c) Install the TGB turnbuckle yoke on the flange F of the fan inlet case. Attach the yoke at holes No. 47 and 48, with the 2 lockpins supplied. (d) Adjust the height of tool, using the coupling screw to obtain the exact position of the baseplate on the AGB rear flange.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 414 Nov 01/08
C F M 56-5B (e) Attach the TGB turnbuckle to the AGB housing with screws and washers supplied. (f) Handtighten the coupling screw in order to lock the AGB relative to the fan frame. (2) Install FIXTURE,SUPPORT-TGB R/I (856A2719G02) as follows: (a) Install TGB removal/installation support on an hydraulic hoist platform. (b) Position hydraulic hoist platform under TGB module. (c) Remove the 2 bolts (350), nuts (330) and washers (340) securing TGB housing to the horizontal drive shaft housing at the 4:30 and 7:30 oclock positions. (d) Actuate hydraulic hoist platform and adjust rear yoke of TGB support with TGB rear mount until the lockpin can be inserted. (e) Adjust the 2 front plates of tool and engage the 2 lockpins in the 4:30 and 7:30 oclock position holes of the TGB forward flange. (f) Remove the bolts. CAUTION : DO NOT REMOVE THE 3 BOLTS, NUTS AND WASHERS INSTALLED _______ IN THE HOLES FITTED WITH FLANGED BUSHINGS. 1 _
Remove the 7 bolts (190) nuts (210) and 4 washers (200) securing TGB housing and the LH support bracket to the horizontal drive shaft housing.
Subtask 72-62-00-020-052 C. Removal of the TGB from the Fan Frame. (1) Install PROTECTOR-MOUNTING PIN (856A2537G01) on the external threads of the mounting pin (400). (2) Install impact puller into the tapped head of mounting pin (400). (3) Remove mounting pin (400). Remove the impact puller from the mounting pin. (4) Separate TGB from fan frame by slowly lowering TGB and fixture assy using a hydraulic hoist platform.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 415 Nov 01/08
C F M 56-5B (5) Keep gasket (410) located between AGB and TGB. (6) Remove and discard the O-ring (420) on the horizontal drive shaft. (7) Remove the O-ring (430) on the oil distributor in the bevel gear. NOTE : Make sure that O-ring (430) is serviceable and O-ring outer ____ diameter is correct. If it is not serviceable, remove and discard it with soft nose pliers. (8) Remove and discard the seal ring (295). (Ref. Fig. 403/TASK 72-62-00-991-302) (9) Two different cases may appear after lowering the TGB: (a) If the radial drive shaft (440) comes with the TGB, remove the shaft from TGB and perform step (12). (b) If the radial drive shaft (440) remains into the fan frame proceed as follows: 1 _
Install PULLER RADIAL DRIVE SHAFT (856A2727G01) to the radial drive shaft.
2 _
Attach slide hammer assy CG240 to the puller.
3 _
Extract radial drive shaft from fan frame.
(10) Remove and discard the O-ring (450) located in groove at lower side of shaft. (11) Store the radial drive shaft into its storage tube assy. Subtask 72-62-00-420-056 D. Installation of blanking plugs and covers and handcranking assy. (1) Installation of blanking plugs and covers on the TGB. (a) Install cover (510) onto forward face of TGB housing. (b) Install cover (470) onto upper face of TGB housing. (c) Install plug (500) onto port of TGB vent tube of TGB housing. (d) Install plug (490) onto scavenge tube port of TGB housing.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 416 Nov 01/08
C F M 56-5B (e) Install cap (480) onto TGB oil supply tube nipple. (f) Install cover onto AGB horizontal drive shaft housing aft end. (g) Install blanking plug on open ports of all tubes. (2) Installation of the Handcranking assy: NOTE : You can ignore this step if the TGB is immediately replaced. ____ (a) Engage the horizontal drive shaft (Ref. TASK 72-63-00-860-001). (b) Install the handcranking drive cover (Ref. TASK 72-63-00-400002). NOTE : Do not replace the O-rings of the handcranking drive ____ cover. New O-rings will be installed after reinstallation of the TGB. Subtask 72-62-00-080-052 E. Removal of the TGB from the Tool. (1) Hold the TGB and remove the rear lockpin of the FIXTURE,SUPPORT-TGB R/I (856A2719G02). (2) Disengage the TGB from the support and place in a storage container.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 417 Nov 01/08
C F M 56-5B TASK 72-62-00-400-002 Installation of the Transfer Gearbox Module 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
No specific
hydraulic hoist platform soft nose pliers warning notice Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) PROTECTOR-MOUNTING PIN FIXTURE,SUPPORT-TGB R/I PULLER RADIAL DRIVE SHAFT TURNBUCKLE-TGB R/I
No specific 856A2537 856A2719 856A2727 856A2805
1 1 1 1
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2442
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 418 Feb 01/10
C F M 56-5B C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------10 10 370 420 420 430 430 450
O-ring O-ring cotter pin O-ring O-ring O-ring O-ring O-ring
72-62-00 72-62-00 72-00-00 72-63-00 72-63-00 72-62-00 72-62-00 72-62-00
05 05 07 04 04 05 05 05
-040 -040A -070 -010 -010A -030 -030A -020
D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 71-00-00-710-006 71-00-00-710-025 71-13-00-010-040 71-13-00-410-040 72-63-00-000-002 72-63-00-400-002 72-63-00-860-001 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 79-00-00-210-003 80-11-10-400-002 72-62-00-991-300 72-62-00-991-301 72-62-00-991-302 72-62-00-991-303 72-62-00-991-304 72-62-00-991-305 72-62-00-991-306
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Minimum Idle Check Accel Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Disengagement/Engagement of the Horizontal Drive Shaft Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Visual Inspection of the Oil System Installation of the Pneumatic Starter Fig. 401 Fig. 402 Fig. 403 Fig. 404 Fig. 405 Fig. 406 Fig. 407
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 419 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-62-00-991-307 72-62-00-991-308
Fig. 408 Fig. 409
3. __________ Job Set-up Subtask 72-62-00-860-051 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). Subtask 72-62-00-010-059 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-62-00-040-055 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 420 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 401/TASK 72-62-00-991-300, 402/TASK 72-62-00-991-301, 403/TASK 72-62-00-991-302, 404/TASK 72-62-00-991-303, 405/TASK 72-62-00-991-304, 406/TASK 72-62-00-991-305, 407/TASK 72-62-00-991-306, 408/TASK 72-62-00-991307, 409/TASK 72-62-00-991-308) NOTE : In the procedure which follows, the AGB is supposed to be installed ____ on the engine and held in position by the TURNBUCKLE-TGB REMOVAL/INSTALLATION (856A2805G01). Subtask 72-62-00-480-053 A. Preparation for Installation: (1) Install the TGB on the FIXTURE,SUPPORT-TGB R/I (856A2719G02) as follows: (a) Adjust the 2 front plates of the tool to engage the 2 lockpins in the forward flange holes at 4:30 and 7:30 oclock positions. Tighten the 2 knurled knobs. (b) Attach the support, with the lockpin, to the rear mount flange of the TGB. (2) Install the radial drive shaft (440) in the fan frame and IGB as follows: (a) Remove the radial drive shaft (440) from storage tube assy (460). (b) Installation of new O-ring. CAUTION : NEVER INSTALL O-RINGS ALREADY USED. _______ 1 _
Lightly coat a new O-ring (450) with engine oil (Material No. CP2442) and install it in the groove of the shaft (440).
(c) Lightly coat the shaft splines (both ends) with engine oil (Material No. CP2442). (d) Install PULLER RADIAL DRIVE SHAFT (856A2727G01) in the lower end of the shaft. (e) Slide shaft in the fan frame into strut and IGB, engaging splines of shaft in splines of IGB. (f) Ensure shaft remains in place. Remove puller.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 421 Nov 01/08
C F M 56-5B (3) Inspect gaskets (90), (240) and (410) before installation to make sure that they are serviceable. If necessary, replace gaskets. Subtask 72-62-00-420-055 B. Installation of the TGB on fan frame: (1) If necessary, remove the handcranking cover (Ref. TASK 72-63-00-000002) and disengage the horizontal drive shaft (Ref. TASK 72-63-00860-001). (2) Remove covers, plugs and cap from the TGB housing. (3) Remove cover from AGB horizontal drive shaft housing. (4) Lightly coat the horizontal drive shaft splines and the gasket (410) to be installed between AGB and TGB, with engine oil (Material No. CP2442). (5) Lubricate a new seal ring (295) with engine oil (Material No. CP2442) and install into the seal groove on the TGB adapter. (Ref. Fig. 403/TASK 72-62-00-991-302) (6) Lubricate a new O-ring (420) with engine oil (Material No. CP2442). Install the O-ring (420) on the horizontal drive shaft. (7) Install the O-ring (430) in the groove on the oil distributor in the bevel gear: (Ref. Fig. 406/TASK 72-62-00-991-305) NOTE : If necessary, lubricate the new O-ring (430) with engine oil ____ (Material No. CP2442). (a) Engage the O-ring (430) by the hole of the oil distributor in the bevel gear with soft nose pliers. (b) Put the O-ring (430) in the groove of the oil distributor in the bevel gear with soft nose pliers. NOTE : Make sure that O-ring (430) is correctly installed in the ____ groove of the oil distributor in the bevel gear. (8) Raise and position TGB at desired level under fan frame using hydraulic hoist platform and taking care not to interfere with adjacent accessories or tubes. Adjust jack details of fixture to complete positioning.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 422 Nov 01/08
C F M 56-5B (9) Insert the gasket (410) and hold it in place between TGB and AGB mating flanges. (10) Lightly coat threads of 3 bolts (160) with graphite grease (Material No. CP2101) and install at 2:30, 6:30, and 10:30 oclock positions (flanged bushings positions) with washers (140) and nuts (130) to secure AGB and TGB handtight. (11) Install TGB mounting pin (400) as follows: (a) Lightly coat threads of pin with graphite grease (Material No. CP2101) and install PROTECTOR-MOUNTING PIN (856A2537G01) on to threaded end of pin. (b) Position TGB mount link, located on fan frame, in TGB clevis mount, align holes and engage pin (400). (c) Remove protector, install washer (390) and nut (380). (d) TORQUE to between 710 and 800 lbf.in (8.02 and 9.04 m.daN). (e) Safety nut with a new cotter pin (370). (12) Loosen the 2 lock pins of FIXTURE,SUPPORT-TGB R/I (856A2719G02) from the 4:30 and 7:30 oclock position holes in the TGB forward flange. Loosen handknobs to lower the 2 front plates of the tool. (13) Lightly coat threads of 2 bolts (350) with graphite grease (Material No. CP2101) and install at 4:30 and 7:30 oclock positions with washers (340) and nuts (330) handtight. (14) Install TGB brackets as follows: (a) Loosen bolts (160), nuts (130) and washers (140) from 2:30 and 6:30 locations. (b) Lightly coat threads of a bolt (190) with graphite grease (Material No. CP2101). Secure lower bracket (150) at the bottom and to the front face of TGB/AGB interface with bolts (160) and (190), washers (140) and (200) and nuts (130) and (210). Tighten by hand. (c) Lightly coat threads of 2 bolts (190) with graphite grease (Material No. CP2101). Secure the support bracket at the left side and onto the rear face of TGB/AGB interface with bolts (190), washers (200) and nuts (210).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 423 Nov 01/08
C F M 56-5B (d) Lightly coat threads of bolt (300) with graphite grease (Material No. CP2101). Secure forward bracket (260) on the TGB RH upper corner. TORQUE to between 100 and 110 lbf.in (1.13 and 1.24 m.daN) (e) Lightly coat threads of 2 bolts (190) with graphite grease (Material No. CP2101). Attach brackets (250) and (260) on the RH side of the TGB/AGB interface with bolts (190) and (160), washers (200) and nuts (130) and (210). (15) Install the 3 remaining bolts (190), washers (200) and nuts (210). (16) TORQUE all bolts of TGB/AGB interface to between 250 and 280 lbf.in (2.82 and 3.16 m.daN) Subtask 72-62-00-080-053 C. Removal of support equipment. (1) Removal of the FIXTURE,SUPPORT-TGB R/I (856A2719G02) (a) Remove the pin which attaches the fixture to the TGB rear mount. (b) Lower the fixture with the hydraulic hoist platform, and remove it. (2) Removal of the TURNBUCKLE-TGB R/I (856A2805G01) (a) Loosen the coupling screw. (b) Remove the screws and washers which attach the baseplate of the tool to the rear face of the AGB. (c) Remove the pins which attach the turnbuckle yoke to the flange F of the fan case and remove the turnbuckle. (d) Reinstall bolts and nuts removed from the flange F, bolt heads forward. TORQUE nuts to between 98 and 110 lbf.in (1.10 and 1.24 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 424 Nov 01/08
C F M 56-5B Subtask 72-62-00-420-057 D. Installation of the transfer gearbox module. (1) Installation of the handcranking drive assembly: (a) Push the handcranking drive shaft and install the handcranking drive (Ref. TASK 72-63-00-860-001). (b) Install the handcranking drive cover (Ref. TASK 72-63-00-400002). (2) Installation of TGB external parts (a) Installation of brackets 1 _
Lightly coat the 2 bolts (360) with graphite grease (Material No. CP2101) and secure bracket (60) on the rear face of TGB housing (120). TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN).
2 _
Lightly coat 2 bolts (290) with graphite grease (Material No. CP2101). Position the bleed bias bracket (280) on the RH rear bracket (270). Attach the brackets to the TGB housing (120) with bolts (290). TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN).
3 _
Lightly coat a bolt (70) with graphite grease (Material No. CP2101) and secure lower bracket (80) handtight on the LH side of TGB housing.
4 _
Lightly coat 2 bolts (40) and (50) with graphite grease (Material No. CP2101). Secure upper bracket (30) on the rear face of TGB housing. Secure brackets together on the LH side of TGB housing.
5 _
TORQUE the 3 bolts (40), (50) and (70) to between 100 and 110 lbf.in (1.13 and 1.24 m.daN).
(b) Installation of tubes on TGB housing (120). CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING _______ NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 425 Nov 01/08
C F M 56-5B 1 _
2 _
3 _
4 _
Connect TGB oil supply tube (180) as follows: a _
Lightly coat threads of nipple with engine oil (Material No. CP2442).
b _
Connect oil supply tube to nipple with union nut (100). Make sure tube is unstrained. TORQUE nut to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
Connect oil tank vent tube (220) assy as follows: a _
Lightly coat gasket (240) with engine oil (Material No. CP2442).
b _
Lightly coat threads of the 4 bolts (230) with graphite grease (Material No. CP2101).
c _
Install gasket (240) and attach the oil vent tube (220) flange on TGB housing using the 4 bolts (230). TORQUE to between 45 and 50 lbf.in (0.50 and 0.56 m.daN).
Connect the TGB scavenge tube (170) as follows: a _
Lightly coat gasket (90) with engine oil (Material No. CP2442).
b _
Lightly coat threads of the 4 bolts (110) with graphite grease (Material No. CP2101).
c _
Install gasket (90) and secure the scavenge tube (170) flange on TGB housing (120) using the 4 bolts (110) TORQUE to between 45 and 50 lbf.in (0.50 and 0.56 m.daN).
Check for oil scavenge plug lockwire. Proceed as follows if lockwire is not present. a _
Loosen scavenge plug from TGB housing.
b _
Remove O-ring (10) and discard.
c _
Lightly coat new O-ring (10) and threads of scavenge plug (20) with engine oil (Material No. CP2442). Install new Oring (10) on scavenge plug (20).
d _
Tighten scavenge plug (20) on TGB housing. TORQUE to between 180 and 200 lbf.in (2.03 and 2.26 m.daN). Safety
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 426 Nov 01/08
C F M 56-5B with a lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) and lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). (3) Installation of the Pneumatic Starter: (a) Reinstall the pneumatic starter (Ref. TASK 80-11-10-400-002). Subtask 72-62-00-410-057 E. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-62-00-440-053 F. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-62-00-710-051 G. Engine Checks. (1) Do an idle check (Ref. TASK 71-00-00-710-006) and do a check of the TGB and tubes for leaks (Ref. TASK 79-00-00-210-003). (2) Do a check of the oil level (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-13-79-610-002). (3) Do an acceleration/deceleration check (Ref. TASK 71-00-00-710-025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 427 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-62-00-410-058 A. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 428 Nov 01/08
C F M 56-5B TRANSFER GEARBOX ASSEMBLY - INSPECTION/CHECK ____________________________________________ TASK 72-62-00-210-002 Inspection/check of the Transfer Gearbox Assembly 1. __________________ Reason for the Job To make sure that the transfer gearbox (TGB) is serviceable. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 79-00-00-210-003
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Visual Inspection of the Oil System
3. __________ Job Set-up Subtask 72-62-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-62-00-010-055 B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-62-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-62-00-010-057 D. Open the thrust reverser cowl doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-62-00-210-052 A. Inspect the TGB ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Housing for : A. Cracks
Not serviceable
B. Nicks, dents and scratches
Any number, 0.035 in. (0.9 mm) deep after removal of high metal
C. Leaks (Ref. TASK 79-00-00-210-003)
No leakage allowed
Tighten fitting to the appropriate torque value and/or replace packing
2. TGB mounts for : A. Cracks
Not serviceable
B. Bushing loose
Not serviceable
C. Broken or missing lockwire
Not serviceable
Replace lockwire
5. Close-up ________ Subtask 72-62-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B Subtask 72-62-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-62-00-410-059 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B ACCESSORY GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION ______________________________________________________ 1. _______ General (Ref. Fig. 001) The accessory gearbox (AGB) assembly is mounted under the fan case at 6 oclock. It consists of a gear train that reduces and increases the rotational speed to meet the specific drive requirements of each accessory. Some of the accessories are installed on the AGB through quick attach/detach (QAD) rings. The AGB consists of the following major assemblies : - Horizontal drive shaft. - AGB housing. - Gear train. 2. ___________ Description (Ref. Fig. 001, 002, 003, 004, 005, 006) A. Horizontal Drive Shaft Assembly The horizontal drive shaft assembly provides power transmission between TGB and AGB. It includes the AGB-TGB coupling tube housing and the horizontal drive shaft. (1) The horizontal drive shaft is made of steel alloy. It is splined at both ends and drives the AGB gears through the handcranking driving gear. (2) The horizontal drive shaft is retained in the AGB handcranking driving gear by a castellated nut in the gearshaft. B. AGB Housing (1) The AGB housing is an aluminum alloy casting. It is mounted under the fan case by 2 clevis mounts with shouldered bushings. (2) The AGB housing front face has mounting pads for the following accessories and equipment. (a) Lubrication unit. (Ref. Fig. 002) (b) Hydraulic pump. (Ref. Fig. 002) (c) Handcranking drive. (Ref. Fig. 004)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Accessory Gearbox Module Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Accessory Gearbox Module-Section Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
Accessory Gearbox Module-Section at N2 Speed Sensor Location Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
Accessory Gearbox Module-Section at Control Alternator and Handcranking Drive Locations Figure 004 R EFF : 001-049, 051-099, 101-149, 151-199, Page 5 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-63-00
C F M 56-5B
AGB Module - Detail of the Optional Seal Configurations Figure 005 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 6 Nov 01/08
C F M 56-5B
AGB Module - Detail of Starter Drive Pad Magnetic Seal Configuration Figure 006 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 7 Nov 01/08
C F M 56-5B (d) Integrated drive generator (IDG). (Ref. Fig. 002) (e) Control alternator (FADEC power supply). (Ref. Fig. 004) (3) The AGB housing rear face connects with the horizontal drive shaft housing and has mounting pads for the following equipment : (a) Fuel pump/HMU package. (Ref. Fig. 002) (b) Starter. (Ref. Fig. 002) (c) N2 speed sensor (Ref. Fig. 003) The N2 speed sensor is installed on AGB ; the air gap adjustment is obtained by laminated shims bolted on the AGB housing. Electrical are used by ECU and N2 cockpit indicator. C. Gear Train (Ref. Fig. 002) (1) The gear train is contained within the AGB housing and drives the accessories. (2) Each gearshaft and its bearings and bearing support is a plug-in type assembly. (3) Sealing past four of the AGB drive pads (IDG, hydraulic pump, starter and fuel pump) is provided by two (optional) configurations of carbon-contact seals. There are: - Magnetic-type carbon seal,or - Sealol-type carbon seal. (a) Magnetic-type seal. (Ref. Fig. 005) This seal consists of: a non-magnetic seal housing which houses a magnetized mating ring with a polished face and a retaining ring. a rotating seal, which has a carbon seal held in a rotating ring. This seal configuration (Ref. Fig. 005) (detail K) can be used only for sealing past the drive pads which follow: - Hydraulic pump
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 8 Nov 01/08
C F M 56-5B - Fuel pump On the starter and IDG drive pads only, a different configuration of magnetic-type seal is used (Ref. Fig. 006) (detail B). This seal differs in that a thrust ring, which also acts as a thermal exchanger, is added between the mating ring and the retaining ring. (b) Sealol-type seal. (Ref. Fig. 005) (detail L) The Sealol seal is made of a carbon packing and a rotating mating ring with a polished face. The rotating mating ring has 4 lugs that engage in 4 corresponding slots in the gearshaft on bearing. A housing containing a spring-loaded carbon seal ensures constant contact between the polished face of the rotating mating ring and the carbon seal element. This seal configuration can be used for sealing past the drive pads wich follow: IDG Hydraulic pump Starter Fuel pump
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 9 Nov 01/08
C F M 56-5B ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES __________________________________________________ TASK 72-63-00-860-001 Disengagement/Engagement of the Horizontal Drive Shaft 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific
slide hammer warning notice Torque Wrench : range 180.00 to 1800.00 lbf.in (2.00 to 20.00 m.daN) 1 PULLER 1 TOOL SET,R/I-DRIVE SHAFTS
856A2632 856A2718
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
* engine oil (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------40
O-ring
72-63-00 04 -060
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 201 Feb 01/10
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-63-00-000-002 72-63-00-400-002 72-63-00-991-301 72-63-00-991-302 72-63-00-991-303 72-63-00-991-304
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Fig. 201 Fig. 202 Fig. 203 Fig. 204
3. __________ Job Set-up Subtask 72-63-00-941-059 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-066 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the handcranking drive cover (Ref. TASK 72-63-00-000-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 202 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 201/TASK 72-63-00-991-301, 202/TASK 72-63-00-991-302, 203/TASK 72-63-00-991-303, 204/TASK 72-63-00-991-304) Subtask 72-63-00-010-067 A. Removal of the Handcranking Drive Nut (1) Install the wrench, part of the TOOL SET,R/I-DRIVE SHAFTS (856A2718G02) as follows: (a) Set the wrench guide on the AGB housing and attach it with the 2 bolts supplied. (b) Turn the wrench axle to engage the forward square end of the axle into the handcranking drive (10). (2) Loosen the nut (20). Use the axle as a countertorque device. (3) Remove the tool and the nut (20) from the AGB housing. Subtask 72-63-00-010-068 B. Removal of the Handcranking Drive (1) Install and tighten the PULLER (856A2632G01) into the tapped hole of the handcranking drive (10). (2) Install and tighten a slide hammer into the puller. (3) Operate the slide hammer and remove the handcranking drive (10). (4) Remove the slide hammer from the puller. (5) Remove the PULLER (856A2632G01) from the handcranking drive (10). (6) Remove O-ring (40) from the handcranking drive (10). Discard the O-ring (40).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 203 Nov 01/08
C F M 56-5B
Removal of the Nut and of the Handcranking Drive Figure 201/TASK 72-63-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 204 Nov 01/08
C F M 56-5B
Removal of the Handcranking Drive Nut Figure 202/TASK 72-63-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 205 Nov 01/08
C F M 56-5B
Removal of the Handcranking Drive Figure 203/TASK 72-63-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 206 Nov 01/08
C F M 56-5B
Rearward Movement of the Horizontal Drive Shaft Figure 204/TASK 72-63-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 207 Nov 01/08
C F M 56-5B Subtask 72-63-00-869-054 C. Disengagement of the Horizontal Drive Shaft (1) Use the puller part of the TOOL SET,R/I-DRIVE SHAFTS (856A2718G02) as follows: (a) Put the guide pins of the puller into the internal splines of the gearshaft. (b) Tighten the tool screw by hand into the shaft. (2) Install and tighten a slide hammer into the puller. (3) Pull the horizontal drive shaft until the splines disengage from the horizontal bevel gear. (4) Remove the slide hammer and the puller from the shaft. Subtask 72-63-00-869-055 D. Engagement of the Horizontal Drive Shaft (1) Put the horizontal drive shaft back to its initial position as follows: (a) Install and tighten the puller part of the TOOL SET,R/I-DRIVE SHAFTS (856A2718G02) into the horizontal drive shaft. (b) Push the puller and turn it to engage the guide pins into the internal gearshaft splines. (c) Push the horizontal drive shaft fully rearward, until the splines engage the horizontal bevel gear (when the TGB is installed). (d) Remove the puller from the horizontal drive shaft. Subtask 72-63-00-410-062 E. Installation of the Handcranking Drive (1) Lubricate a new O-ring (40) with engine oil (Material No. CP2442) and install into the groove of the handcranking drive (10). (2) Lubricate the handcranking drive splines with engine oil (Material No. CP2442) and check for cleanliness of mating faces.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 208 Nov 01/08
C F M 56-5B (3) Install the PULLER (856A2632G01) into the handcranking drive. (4) Push the puller to install the handcranking drive in the drive AGB. Turn the puller to engage the handcranking drive into the internal gearshaft splines. Push again until the handcranking drive shaft touches the horizontal drive shaft. (5) Remove the puller from the handcranking drive. Subtask 72-63-00-410-063 F. Installation of the Handcranking Drive Nut (1) Make sure that the retaining ring (30) is installed into the groove of the nut (20). (2) Lubricate external threads of the nut (20) with engine oil (Material No. CP2442). (3) Engage the nut (20) on the wrench part of the TOOL SET,R/I-DRIVE SHAFTS (856A2718G02). (4) Safety the wrench guide on the AGB housing with the 2 bolts supplied. (5) Turn the wrench axle to engage its forward square end into the handcranking drive (10). (6) Use the wrench axle as countertorque to install the nut. TORQUE the nut (20) to between 882 and 1148 lbf.in (9.96 and 12.97 m.daN). (7) Remove the tool from the AGB. 5. Close-up ________ Subtask 72-63-00-410-064 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the handcranking drive cover (Ref. TASK 72-63-00-400-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 209 Nov 01/08
C F M 56-5B (3) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (4) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 210 Nov 01/08
C F M 56-5B ACCESSORY GEARBOX ASSEMBLY - REMOVAL/INSTALLATION _________________________________________________ TASK 72-63-00-000-002 Removal of the Handcranking Drive Cover 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 856A2632
slide hammer soft-jawed pliers warning notice 1 PULLER
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-63-00-991-300 72-63-00-991-320
Opening of the Fan Cowl Doors Fig. 401 Fig. 402
3. __________ Job Set-up Subtask 72-63-00-941-056 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-063 B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 401/TASK 72-63-00-991-300, 402/TASK 72-63-00-991-320) Subtask 72-63-00-020-057 A. Removal of the Handcranking Drive Cover NOTE : The new handcranking cover (SB CFM 72-156) must stay attached to ____ the AGB during operation. (1) Disconnect the electrical cable connectors, Channel B (70) of HJ10 harness and Channel A (50) of HJ9 harness, from the control alternator (60). Use soft-jawed pliers, if necessary. (2) Install protective caps on the electrical cables, Channel B (70) and Channel A (50), and on the control alternator electrical connectors. (3) Cut and remove the lockwire. Remove the two bolts (10) and washers (20) which attach the cover (40) to the AGB forward face. (4) Install the PULLER (856A2632G01) in the tapped hole of the cover (40). Tighten with your hand. PRE SB CFM 72-156 (5) Remove the cover (40). Use a slide hammer, if neccessary. END PRE SB CFM 72-156 POST SB CFM 72-156
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Nov 01/08
C F M 56-5B (6) Remove the cover (40) and let it hang by the lanyard cable. Use a slide hammer, if necessary. END OF SB CFM 72-156 (7) Remove the PULLER from the cover. Remove and discard the two O-rings (30).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 403 Nov 01/08
C F M 56-5B
Handcranking Drive Cover Figure 401/TASK 72-63-00-991-300- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 404 Nov 01/08
C F M 56-5B
Handcranking Drive Cover Figure 401/TASK 72-63-00-991-300- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 405 Nov 01/08
C F M 56-5B
Handcranking Drive Cover Figure 402/TASK 72-63-00-991-320- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 406 Nov 01/08
C F M 56-5B
Handcranking Drive Cover Figure 402/TASK 72-63-00-991-320- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 407 Nov 01/08
C F M 56-5B TASK 72-63-00-400-002 Installation of the Handcranking Drive Cover 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2442
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------30 30 30 30
O-rings O-rings O-rings O-rings
72-63-00 72-63-00 72-63-00 72-63-00
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
01B-050 01B-050A 01C-050 01C-050A
Page 408 Nov 01/09
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-22-00-911-002 71-00-00-710-006 71-13-00-010-040 71-13-00-410-040 73-29-00-710-040 79-00-00-210-003 72-63-00-991-300 72-63-00-991-320
Locking Procedures Minimum Idle Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Operational Test of the FADEC on the Ground (with Engine Motoring) Visual Inspection of the Oil System Fig. 401 Fig. 402
3. __________ Job Set-up Subtask 72-63-00-860-054 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-073 B. Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 409 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 401/TASK 72-63-00-991-300, 402/TASK 72-63-00-991-320) Subtask 72-63-00-420-058 A. Installation of the Handcranking Drive Cover CAUTION : DO NOT INSTALL THE COVER ON THE AGB WITHOUT THE NEW O-RINGS. IF _______ THE COVER IS INSTALLED WITHOUT THE NEW O-RINGS, THE ENGINE CAN LEAK OIL. THIS CAN CAUSE ENGINE FAILURE. (1) Lubricate two new O-rings (30) with engine oil (Material No. CP2442) and install them in the grooves of the cover (40). (2) Lubricate threads of bolts (10) with graphite grease (Material No. CP2101). PRE SB CFM 72-156 (3) Install the cover (40) and attach it with the two bolts (10) and washers (20). END PRE SB CFM 72-156 POST SB CFM 72-156 (4) Install the cover (40) which is attached by the lanyard cable to the accessory gearbox and attach it with the two bolts (10) and washers (20). END OF SB CFM 72-156 (5) TORQUE the bolts (10) to between 97 and 106 lbf.in (1.09 and 1.19 m.daN). Safety with a lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) and lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002) (Ref. TASK 70-22-00-911-002). (6) Remove protective caps from the electrical cables, Channel B (70) and Channel A (50), and from the control alternator electrical connectors. (7) Connect the electrical cable connectors, Channel A (50) of HJ9 harness and Channel B (70) of HJ10 harness, on the control alternator (60). Tighten the connectors with your hand plus one-eighth of a turn. Use soft-jawed pliers if necessary.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 410 Nov 01/08
C F M 56-5B Subtask 72-63-00-710-057 B. Test CAUTION : DO NOT OPERATE THE ENGINE WITHOUT A CORRECTLY INSTALLED COVER _______ ON THE N2 HANDCRANKING DRIVE PAD. IF THE COVER IS NOT INSTALLED CORRECTLY, THE ENGINE CAN HAVE OIL LEAKAGE. THIS CAN CAUSE ENGINE FAILURE. (1) Do an operational test of FADEC on the ground with engine motoring (Ref. TASK 73-29-00-710-040). (2) Do a minimum idle check (Ref. TASK 71-00-00-710-006) and do a check for leaks during the visual inspection of the oil system (Ref. TASK 79-00-00-210-003). 5. Close-up ________ Subtask 72-63-00-410-059 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 411 Nov 01/08
C F M 56-5B TASK 72-63-00-000-003 Removal of the Accessory Gearbox Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific No specific No specific No specific No specific 856A2537 856A2719 856A2727 856A2754 856A3519
1 1 1 1 1
blanking plugs and caps container hydraulic hoist platform pipette slide hammer soft nose pliers warning notice access platform 1 m (3 ft. 3 in.) PROTECTOR-MOUNTING PIN FIXTURE,SUPPORT-TGB R/I PULLER RADIAL DRIVE SHAFT FIXTURE,SUPPORT-AGB SLING-AGB
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
Material No.
CP2859
* engine oil (Ref. 70-30-00) * corrosion protective additive (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 412 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-003 24-21-51-000-040 26-12-15-000-042 29-11-51-000-041 71-13-00-010-040 71-71-43-000-041 71-73-49-000-003 71-73-49-000-004 71-73-49-000-007 71-73-49-000-008 71-73-49-000-026 71-73-49-000-027 71-73-49-000-028 71-73-49-000-029 71-73-49-000-049 72-63-00-860-001 73-11-10-000-003 73-21-30-000-001 77-11-20-000-002 78-30-00-481-041 78-36-00-010-040 79-21-10-000-004 80-11-10-000-002 72-63-00-991-309 72-63-00-991-310 72-63-00-991-311 72-63-00-991-312 72-63-00-991-313 72-63-00-991-314
Oil Tank Draining Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Removal of the Fan Fire Detectors (4000WD1,4000WD2) Removal of the Green Engine Pump (1030GK) Opening of the Fan Cowl Doors Removal of the Drain Manifold Module Removal of the Starter Pad Oil Drain Tube Removal of the IDG Oil Drain Tube Removal of the Fan Case Drain Tubes Removal of the Fuel Pump Drain Tubes Removal of the Heat Exchanger Drain Tube Removal of the Hydro Mechanical Unit (HMU) Drain Tube Removal of the Hydraulic Pump Drain Tube Removal of the Forward Oil Sump Drain Tube Removal of the Reservoir to Manifold Hydraulic Oil Drain Tube Disengagement/Engagement of the Horizontal Drive Shaft Removal of the Fuel Pump and Filter Assembly Removal of the Control Alternator Removal of the N2 Speed Sensor (4001EV). Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Removal of the Lubrication Unit Removal of the Pneumatic Starter Fig. 403 Fig. 404 Fig. 405 Fig. 406 Fig. 407 Fig. 408
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 413 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-63-00-941-061 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-071 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-63-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-63-00-010-074 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 414 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 403/TASK 72-63-00-991-309, 404/TASK 72-63-00-991-310, 405/TASK 72-63-00-991-311, 406/TASK 72-63-00-991-312, 407/TASK 72-63-00-991-313, 408/TASK 72-63-00-991-314) Subtask 72-63-00-941-062 A. Put a container under the Accessory Gearbox to collect the remaining fluid from the tubes and control. Subtask 72-63-00-010-070 B. Preparation for the Removal of the AGB CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (1) Remove the fan fire detector (Ref. TASK 26-12-15-000-042). (2) Remove the drain manifold module (Ref. TASK 71-71-43-000-041). (3) Remove the drain tubes under the AGB/TGB as follows: (a) FRV drain tubes (Ref. TASK 71-73-49-000-007). (b) Oil reservoir drain tube (Ref. TASK 71-73-49-000-049). (c) HMU drain tube (Ref. TASK 71-73-49-000-027). (d) Heat exchanger drain tube (Ref. TASK 71-73-49-000-026). (e) Fuel pump drain tube (Ref. TASK 71-73-49-000-008). (f) Hydraulic pump drain tube (Ref. TASK 71-73-49-000-028). (g) IDG pad drain tube (Ref. TASK 71-73-49-000-004). (h) Starter pad drain tube (Ref. TASK 71-73-49-000-003). (i) Forward sump drain tube (Ref. TASK 71-73-49-000-029). (4) Remove the hydraulic pump (Ref. TASK 29-11-51-000-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 415 Nov 01/08
C F M 56-5B
Accessory Gearbox Assembly Figure 403/TASK 72-63-00-991-309 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 416 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-63-00 CES
Page 417 Feb 01/07
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 18 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 418 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 28 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 419 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 38 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 420 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 48 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 421 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 58 (SHEET 5) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 422 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 68 (SHEET 6) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 423 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 78 (SHEET 7) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 424 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 88 (SHEET 8) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 425 Nov 01/08
C F M 56-5B
Accessory Drive Support Fixture Figure 405/TASK 72-63-00-991-311- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 426 Nov 01/08
C F M 56-5B
Accessory Drive Support Fixture Figure 405/TASK 72-63-00-991-311- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 427 Nov 01/08
C F M 56-5B
Accessory Drive Figure 406/TASK 72-63-00-991-312 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 428 Nov 01/08
C F M 56-5B
TGB Blanking Kit Figure 407/TASK 72-63-00-991-313 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 429 Nov 01/08
C F M 56-5B
AGB Blanking Kit Figure 408/TASK 72-63-00-991-314- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 430 Nov 01/08
C F M 56-5B
AGB Blanking Kit Figure 408/TASK 72-63-00-991-314- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 431 Nov 01/08
C F M 56-5B (5) Remove the integrated drive generator (IDG) (Ref. TASK 24-21-51-000040). (6) Remove the N2 speed sensor (Ref. TASK 77-11-20-000-002). (7) Remove the pneumatic starter (Ref. TASK 80-11-10-000-002). (8) Remove the lubrication unit (Ref. TASK 79-21-10-000-004). (9) Remove the fuel pump (Ref. TASK 73-11-10-000-003). (10) Remove the ECU alternator (Ref. TASK 73-21-30-000-001). (11) Drain the accessory drive section (Ref. TASK 12-13-79-610-003). (12) Install the blanking plugs and caps on the free ends of tubes and on the connectors to prevent contamination. Subtask 72-63-00-020-069 C. Removal of the Fan Case Water Drain Tubes CAUTION : MAKE SURE THAT THE TUBE NUTS ARE NOT MISSING DURING THE REMOVAL _______ OF FAN CASE WATER DRAIN TUBES. NOTE : The AGB scavenge tube has been removed to ease the removal of the ____ ECU alternator. (1) Remove the parts which attach the fan case water drain tubes (220) and (530) as follows: (a) Remove the nut (400) and the bolt (465) from the bracket (475) on the AGB left-hand side. (b) Remove the outer spring clip (425), the inner spring clip (440) and the plastic bushing (435) from the CLP fuel tube (430). (c) Remove the outer spring clip (405), the inner spring clip (420) and the plastic bushing (410) from the oil heater tube (415). (d) Remove the outer spring clip (460), the inner spring clip (450) and the plastic bushing (470) from the IDG exchanger fuel outlet tube (455). (e) Remove the bolt (445) and the bracket (475) from the AGB left-hand side.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 432 Nov 01/08
C F M 56-5B (f) Remove the nut (165) and the bolt (125) from the bracket (130). (g) Remove the outer spring clip (135), the inner spring clip (145) and the plastic bushing (140) from the TGB oil scavenge tube (110). (h) Remove the outer spring clip (160), the inner spring clip (150) and the plastic bushing (155) from the rear sump oil return tube (105). (i) Remove the bolts (120), (170) and (175) which attach the forward sump oil return tube (100), the TGB oil scavenge tube (110) and the rear sump oil return tube (105) from the AGB front face. (j) Remove and keep the gaskets (115), (180) and (185). (k) Remove the nut (70) and the bolt (65) from the bracket (90) on the AGB front face. (l) Remove the outer spring clip (75), the inner spring clip (85) and the plastic bushing (80) from the rear sump oil supply tube (60). (m) Remove the nut (15) and the bolt (40) from the bracket (45) on the AGB front face. (n) Remove the outer spring clip (35), the inner spring clip (20) and the plastic bushing (25) from the AGB/TGB oil supply tube (30). (o) Remove the nut (95) and the bolt (55) from the bracket (90) on the AGB front face. (p) Remove the outer spring clip (50), the inner spring clip (5) and the plastic bushing (10) from the AGB/TGB oil supply tube (30). (q) Remove the nut (215) and the bolt (190). (r) Remove the outer spring clip (210), the inner spring clip (200), the plastic bushing (205) and the bracket (195) from the forward fan case water drain tube (220). (s) Remove the forward fan case water drain tube (220) from the engine. (t) Remove the nut (560) and the bolt (540).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 433 Nov 01/08
C F M 56-5B (u) Remove the outer spring clip (555), the inner spring clip (545), the plastic bushing (550) and the bracket (535) from the aft fan case water drain tube (530). (v) Remove the aft fan case water drain tube (530) from the engine. (2) Disconnect the water drain tubes (220) and (530) from the fan case nipples and remove them from the engine. Subtask 72-63-00-020-065 D. Removal of the AGB External Parts (1) Disengage the IDG electrical cables from the clamp on the AGB. (2) Remove the parts which attach the AGB external parts as follows: (a) Remove the bolts (360) and (365) to remove the FWD sump oil scavenge hose (355) from the AGB rear face. (b) Remove and keep the gaskets (350) and (370). (c) Remove the bolts (390) which attach the TGB oil scavenge hose (385) to the AGB rear face. (d) Remove and keep the gasket (395). (e) Remove the bolt (685) and the washer (690) to disconnect the bonding strip (695) from the AGB. (3) Disconnect and remove the tubes (30) and (60) from the AGB. (4) Disconnect the TGB oil supply tube (230) from the AGB. (5) Removal of the Rear Sump Oil Tubes (a) Cut and remove the lockwire. (b) Disconnect the rear sump oil scavenge tube (270) and the rear sump oil supply tube (305) from the tube bundle. (c) Remove the parts which attach the rear sump oil tubes as follows: 1 _
Remove the nut (335) and the bolt (225) from the bracket (345) on the AGB rear face.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 434 Nov 01/08
C F M 56-5B 2 _
Remove the outer spring clip (320), the inner spring clip (330) and the plastic bushing (325) from the rear sump oil supply tube (305).
3 _
Remove the nut (290) and the bolt (315) from the bracket (260) on the left-hand side of the TGB/horizontal drive shaft housing junction.
4 _
Remove the outer spring clip (310), the inner spring clip (295) and the plastic bushing (300) from the rear sump oil supply tube (305).
5 _
Remove the rear sump oil supply tube (305).
6 _
Remove the nut (235) and the bolt (285) from the bracket (260) on the left-hand side of the TGB/horizontal drive shaft housing junction.
7 _
Remove the outer spring clip (240), the inner spring clip (250) and the plastic bushing (245) from the TGB oil supply tube (230).
8 _
Remove the outer spring clip (275), the inner spring clip (265) and the plastic bushing (255) from the rear sump oil scavenge tube (270).
9 _
Remove the bolts (280) which attach the rear sump oil scavenge tube (270) to the AGB rear face.
10 __
Remove the rear sump oil scavenge tube (270) from the AGB rear face.
11 __
Remove and keep the gasket (340).
(6) Removal of the TGB External Parts (a) Disconnect the TGB oil supply tubes (230) from the TGB left-hand side and remove the tubes (230). (b) Remove the parts which attach the TGB external parts as follows: 1 _
Remove the bolt (610) which attaches the clamp (565) to the bracket (345) on the horizontal drive shaft housing, left-hand side.
2 _
Remove the clamp (565) which attaches the HJ8 harness to the bracket (345).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 435 Nov 01/08
C F M 56-5B 3 _
Remove the bolt (605) which attaches the clamp (600) to the bracket (535) on the AGB/TGB interface, left hand side.
4 _
Remove the clamp (600) which attaches the HJ8 harness to the bracket (535).
5 _
Remove the bolt (590) which attaches the clamp (595) to the bracket (345) on the horizontal drive shaft housing, left-hand side.
6 _
Remove the clamp (595) which attaches the HJ7 harness to the bracket (345).
7 _
Remove the bolt (585) which attaches the clamp (580) to the bracket (260) on the AGB/TGB interface, left-hand side.
8 _
Remove the clamp (580) which attaches the HJ7 harness to the bracket (260).
9 _
Remove the bolts (665) which attach the bracket (660) and (670) to the TGB right-hand side with electrical harness. Remove the brackets (660) and (670).
10 __
Remove the bolts (655) and the washers (650) which attach the bracket (645) to the TGB right hand side.
11 __
Remove the nuts (635) and the bolts (640) which attach the bracket (645) to the bracket (505) on the TGB right-hand side. The bracket (645) is attached to the electrical harnesses.
12 __
Remove the bolts (625) which attach the bracket (630) to the TGB left-hand side.
13 __
Remove the bolts (380) and the TGB oil scavenge hose (385) from the TGB left-hand side.
14 __
Remove and keep the gasket (375).
15 __
Remove the nuts (575), the bolts (570) and the brackets (260), (535) from the bracket (520) on the AGB/TGB interface, left-hand side.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 436 Nov 01/08
C F M 56-5B (7) Removal of the Accessory Drive (a) Install the FIXTURE,SUPPORT-AGB (856A2754G01) and the FIXTURE,SUPPORT-TGB R/I (856A2719G02) as follows: 1 _
Remove the two nuts (510), washers (515) and bolts (480) which attach the TGB housing to the horizontal drive shaft housing at the 4:30 and 7:30 oclock positions.
2 _
Install the FIXTURE, FIXTURE,SUPPORT-TGB R/I (856A2719G02) on the FIXTURE,SUPPORT-AGB (856A2754G01).
3 _
Install the tool assembly on a hydraulic hoist platform and position under the accessory gearbox assembly.
4 _
Use lockpins to secure the fork and the tenon. Use adjusting screws to adjust the height to the lateral supports.
5 _
Engage the locating pin into the rear mount of the AGB. Use the knurled nut to attach the clamp. Adjust the height of the support with the adjusting screw.
6 _
Adjust the height of the FIXTURE,SUPPORT-TGB R/I (856A2719G02) with the adjusting screws.
7 _
Engage the lockpins of the front plates into the TGB holes. Use the knurled knobs to adjust the front plates, if necessary.
8 _
Attach the rear yoke to the TGB rear mount with the lockpin.
(b) Remove and discard the cotter pins (700), (725) and (740). (c) Remove the nuts (705), (720) and (745) and the washers (710), (730) and (750). (d) Install the PROTECTOR-MOUNTING PIN (856A2537G01) on the mounting pins (680), (715) and (735). (e) Remove the three mounting pins (680), (715) and (735) with an impact puller. (f) Slowly and carefully lower the hydraulic hoist platform and separate the accessory drive assembly from the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 437 Nov 01/08
C F M 56-5B (g) Two different cases can appear when you remove the accessory drive assembly from the engine: 1 _
If the radial drive shaft (675) comes with the TGB, remove the radial drive shaft (675) from the TGB.
2 _
If the radial drive shaft (675) remains in the fan frame:
3 _
Install a PULLER RADIAL DRIVE SHAFT (856A2727G01) in the radial drive shaft.
4 _
Remove the radial drive shaft (675) from the fan frame with a slide hammer.
5 _
Remove the tools from the radial drive shaft.
(h) Remove the O-ring (755) from the radial drive shaft. Discard the O-ring (755). (i) Store the radial drive shaft in its storage tube (765). (8) Removal of the TGB from the AGB (a) Disengage the horizontal drive shaft (Ref. TASK 72-63-00-860001). (b) Remove the nuts (510), the washers (515) and the bolts (480) from the TGB/AGB interface. (c) Remove the brackets (485), (505), (520) and (525). (d) Remove the TGB from the AGB and from the FIXTURE,SUPPORT-TGB R/I (856A2719G02). Keep the gasket (500). (e) Remove the O-ring (495) from the oil distributor in the bevel gear. (Ref. Fig. 404/TASK 72-63-00-991-310) NOTE : Make sure that O-ring (495) is serviceable and O-ring ____ outer diameter is correct. If it is not serviceable, remove and discard it with soft nose pliers. (f) Install the TGB blanking kit (760) as follows: 1 _
Install a cap on the upper face of the TGB housing.
2 _
Install a cap on the TGB oil supply nipple.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 438 Nov 01/08
C F M 56-5B 3 _
Install a plug in the TGB scavenge port.
4 _
Install a plug in the TGB vent port.
5 _
Install a cover on the forward face of the TGB housing.
(g) Place the TGB in a storage container. (9) Removal of the AGB from the Tools (a) Engage the horizontal drive shaft (Ref. TASK 72-63-00-860-001). (b) Remove the O-ring (490) from the horizontal drive shaft. Discard the O-ring (490). (10) When you remove all equipment from the AGB, apply storage oil on all bearings as follows: Mix 5 percent of corrosion protective additive (Material No. CP2859) with engine oil (Material No. CP2442) and lightly coat all bearings with a pipette. (a) Install the AGB blanking kit (775) as follows: 1 _
Install a cap on the lubrication unit pad.
2 _
Install a cap on the hydraulic pump pad.
3 _
Install a cap on the alternator pad.
4 _
Install a cap on the IDG pad.
5 _
Install a cap on the fuel pump pad.
6 _
Install a cap on the starter pad.
7 _
Install a cover on the radial drive shaft housing.
8 _
Put blanking plugs and caps on all nipples and orifices.
(b) Install the SLING-AGB (856A3519G01/G02) as follows: 1 _
Attach the two sectors at each end of the AGB with the two lockpins supplied.
2 _
Attach the SLING-AGB (856A3519GO1/G02) to a hoist.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 439 Nov 01/08
C F M 56-5B (c) Remove the lockpins and loosen the clamp which attach the FIXTURE,SUPPORT-AGB (856A2754G01) to the AGB. (d) Remove the AGB from the FIXTURE,SUPPORT-AGB (856A2754G01). Place the AGB in a storage container. (e) Remove the SLING-AGB (856A3519G01/G02) from the AGB.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 440 Nov 01/08
C F M 56-5B TASK 72-63-00-400-003 Installation of the Accessory Gearbox Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R R R
No No No No No
specific specific specific specific specific
No specific
hydraulic hoist platform soft nose pliers warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) Torque Wrench : range 180.00 to 1800.00 lbf.in (2.00 to 20.00 m.daN) PROTECTOR-MOUNTING PIN FIXTURE,SUPPORT-TGB R/I PULLER RADIAL DRIVE SHAFT FIXTURE,SUPPORT-AGB SLING-AGB
No specific 856A2537 856A2719 856A2727 856A2754 856A3519
1 1 1 1 1
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1008
Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
* trichloroethylene (Ref. 70-30-00) * acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 441 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2338
Material No.
CP2442
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
Material No.
CP8001
Material No.
CP8002
graphite grease (Ref. 70-30-00) * brisal-ox (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------490 490 495 495 700 725 740 755
O-ring O-ring O-ring O-ring cotter pin cotter pin cotter pin O-ring
72-63-00 72-63-00 72-62-00 72-62-00 72-00-00 72-00-00 72-00-00 72-62-00
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
04 04 05 05 07 07 07 05
-010 -010A -030 -030A -150 -110 -070 -020
Page 442 Nov 01/08
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 24-21-51-400-040 26-12-15-400-042 29-11-51-400-041 70-22-00-911-002 71-00-00-710-006 71-00-00-710-025 71-13-00-010-040 71-13-00-410-040 71-71-43-400-041 71-73-49-400-003 71-73-49-400-004 71-73-49-400-007 71-73-49-400-008 71-73-49-400-026 71-73-49-400-027 71-73-49-400-028 71-73-49-400-029 71-73-49-400-049 72-63-00-400-002 72-63-00-860-001 73-11-10-400-003 73-21-30-400-001 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 79-00-00-210-003 79-21-10-400-004 80-11-10-400-002 72-63-00-991-309 72-63-00-991-310
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Fan Fire Detectors (4000WD1,4000WD2) Installation of the Green Engine Pump (1030GK) Locking Procedures Minimum Idle Check Accel Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Installation of the Drain Manifold Module Installation of the Starter Pad Oil Drain Tube Installation of the IDG Oil Drain Tube Installation of the Fan Case Drain Tubes Installation of the Fuel Pump Drain Tubes Installation of the Heat Exchanger Drain Tube Installation of the Hydro Mechanical Unit (HMU) Drain Tube Installation of the Hydraulic Pump Drain Tube Installation of the Forward Oil Sump Drain Tube Installation of the Reservoir to Manifold Hydraulic Oil Drain Tube Installation of the Handcranking Drive Cover Disengagement/Engagement of the Horizontal Drive Shaft Installation of the Fuel Pump and Filter Assembly Installation of the Control Alternator Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Visual Inspection of the Oil System Installation of the Lubrication Unit Installation of the Pneumatic Starter Fig. 403 Fig. 404
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C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-63-00-991-311 72-63-00-991-312 72-63-00-991-313 72-63-00-991-314
Fig. Fig. Fig. Fig.
405 406 407 408
3. __________ Job Set-up Subtask 72-63-00-860-055 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-63-00-010-075 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
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C F M 56-5B Subtask 72-63-00-040-052 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041). 4. Procedure _________ (Ref. Fig. 403/TASK 72-63-00-991-309, 404/TASK 72-63-00-991-310, 405/TASK 72-63-00-991-311, 406/TASK 72-63-00-991-312, 407/TASK 72-63-00-991-313, 408/TASK 72-63-00-991-314) Subtask 72-63-00-210-053 A. Check all gaskets retained during removal for condition and serviceability (1) If gaskets are not reusable, replace them. Subtask 72-63-00-410-066 B. Preparation for the Installation of the Accessory Gearbox CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (1) Before their installation, make sure that the gaskets are serviceable, lubricate the gaskets and nipples with engine oil (Material No. CP2442) and lubricate the threads of bolts with graphite grease (Material No. CP2101), unless specified. (2) Remove blanking plugs and caps from the free ends of items before installation. (3) Install the FIXTURE,SUPPORT-TGB R/I (856A2719G02) or the FIXTURE,SUPPORT-AGB (856A2754G01). (4) Install the tool assembly on a hydraulic hoist platform. (5) Install the SLING-AGB (856A3519G01/G02) on the AGB as follows: (a) Position the two sectors at each end of the AGB and safety with the two lockpins supplied. (b) Attach the sling to a hoist.
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C F M 56-5B (6) Remove the AGB from its container and install it on the FIXTURE,SUPPORT-AGB (856A2754G01) as follows: (a) Use lockpins to safety the fork and tenon to the AGB. (b) Engage the locating pin into the rear mount of the AGB. Use the knurled knob to attach the clamp. (7) Remove the SLING-AGB (856A3519G01/G02) from the AGB. (8) Remove the AGB blanking kit (760) as follows: (a) Remove the cap from the lubrication unit pad. (b) Remove the cap from the hydraulic pump pad. (c) Remove the cap from the alternator pad. (d) Remove the cap from the IDG pad. (e) Remove the cap from the fuel pump pad. (f) Remove the cover from the radial drive shaft housing. (g) Remove the cap from the starter pad. (h) Remove the blanking plugs from the nipples and orifices. (9) Lubricate a new O-ring (490) with engine oil (Material No. CP2442) and install it in the groove of the horizontal drive shaft. (10) Lubricate the splines of the horizontal drive shaft with engine oil (Material No. CP2442). (11) Disengage the horizontal drive shaft (Ref. TASK 72-63-00-860-001). (12) Remove the TGB from its container. (13) Remove the TGB blanking kit (745) as follows: (a) Remove the cap from the TGB oil supply nipple. (b) Remove the plug from the TGB scavenge port. (c) Remove the plug from the TGB vent port. (d) Remove the cover from the FWD face of the TGB housing.
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C F M 56-5B (14) Install the O-ring (495) in the groove of the oil distributor in the bevel gear: (Ref. Fig. 404/TASK 72-63-00-991-310) NOTE : If necessary, lubricate the new O-ring (495) with engine oil ____ (Material No. CP2442). (a) Engage the O-ring (495) througt the hole of the oil distributor in the bevel gear with soft nose pliers. (b) Put the O-ring (495) in the groove of the oil distributor in the bevel gear with soft nose pliers. NOTE : Make sure that O-ring (495) is correctly installed in the ____ groove of the oil distributor in the bevel gear. (15) Install the TGB on the FIXTURE,SUPPORT-TGB R/I (856A2719G02) as follows: (a) Engage the lockpins of the front plates in the TGB holes, at the 7:30 and 4:30 locations. (b) Secure the rear yoke to the TGB rear mount with the lockpin. (c) Set the position of the TGB in relation to the AGB. (16) Install the gasket (500) between the AGB and the TGB. (17) Move the TGB forward in contact with the AGB. (18) Attach the TGB to the AGB as follows: (a) Install three bolts (480), washers (515) and nuts (510) at the flanged bushing locations (2:30, 6:30 and 10:30 oclock positions). (b) TORQUE the nuts (510) to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (c) Install two bolts (480), washers (515) and nuts (510) in the holes at the 11:30 and 0:30 oclock positions. (d) TORQUE the nuts (510) to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (e) Remove the nut (510), washer (515) and bolt (480) at the 6:30 oclock position.
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C F M 56-5B (f) Install the bracket (525) on the front face of the AGB/TGB interface, at holes at the 5:30 and 6:30 oclock positions, with two bolts (480), washers (515) and nuts (510). (g) TORQUE the nuts to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (h) Remove the nuts (510), washer (515) and bolt (480) at the 2:30 oclock position. (i) Install the bracket (485) on the front face of the AGB/TGB interface, at holes at the 3:30 and 2:30 oclock positions, with two bolts (480). (j) Install the bracket (505) on the rear face of the AGB/TGB interface, at holes at the 2:30 and 1:30 oclock positions, with a bolt (480). (k) Secure the three bolts (480) at the 1:30, 2:30 and 3:30 oclock positions with three washers (515) and nuts (510). (l) TORQUE the nuts to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (m) Install the bracket (520) on the rear face of the AGB/TGB interface, at holes at the 8:30 and 9:30 oclock positions, with two bolts (480), washers (515) and nuts (510). (n) TORQUE the nuts to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (o) Disengage the lockpins of the front plates from the holes at the 4:30 and 7:30 oclock positions. (p) Install the two bolts (480), washers (515) and nuts (510) which remain. (q) TORQUE the nuts to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (r) Engage the horizontal drive shaft (Ref. TASK 72-63-00-860-001). (19) Remove the radial drive shaft from the radial drive shaft storage tube (750). (20) Lubricate a new O-ring (755) with engine oil (Material No. CP2442) and install it in the radial drive shaft groove.
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C F M 56-5B (21) Lubricate the splines at each end of the radial drive shaft with engine oil (Material No. CP2442). (22) Install the radial drive shaft in the fan frame strut at the six oclock position with the PULLER RADIAL DRIVE SHAFT (856A2727G01). Subtask 72-63-00-420-064 C. Installation of the Accessory Gearbox Assembly CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (1) Before their installation, make sure that the gaskets are serviceable, lubricate the gaskets and nipples with engine oil (Material No. CP2442) and lubricate the threads of bolts with graphite grease (Material No. CP2101), unless specified. (2) Remove blanking plugs and caps from the free ends of items before installation. (3) Install the PROTECTOR-MOUNTING PIN (856A2537G01) on the mounting pins (665), (700), (720). NOTE : Do not lubricate the mounting pins. ____ (4) Put the accessory gearbox assembly in position under the engine. (5) Install the accessory gearbox assembly on the engine as follows: CAUTION : TAKE CARE NOT TO DAMAGE THE HARNESSES AND TUBES LEFT IN _______ PLACE ON THE ENGINE. (a) Lift the hoist platform while you engage the radial drive shaft in the TGB. (b) Secure the accessory gearbox on the engine with the mounting pins (665), (700), (720). (c) Remove the PROTECTOR-MOUNTING PIN (856A2537G01) from the mounting pins (665), (700), (720). (d) Install the washers (695), (715), (735) and nuts (690), (705), (730).
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C F M 56-5B (e) TORQUE the nuts (690), (705) to between 840 and 930 lbf.in (9.49 and 10.50 m.daN). (f) TORQUE the nut (730) to between 420 and 470 lbf.in (4.74 and 5.31 m.daN). (g) Safety with new cotter pin (700), cotter pin (725) and cotter pin (740). (6) Remove the FIXTURE,SUPPORT-AGB (856A2754G01) and FIXTURE,SUPPORT-TGB R/I (856A2719G02) assembly as follows: (a) Remove the lockpins which attach the fork and tenon to the AGB. (b) Remove the lockpin which attaches the rear yoke to the TGB rear mount. (c) Remove the clamp from the AGB rear mount. (d) Lower the hoist platform, and remove from the engine. (7) Installation of the TGB External Parts (a) Install the parts which attach the TGB external parts as follows: 1 _
Install the brackets (260), (535) to the bracket (520) on the AGB/TGB interface, left-hand side, with the bolts (570) and the nuts (575).
2 _
Install the gasket (375) between the mating faces correctly.
3 _
Install the TGB oil scavenge hose (385) on the TGB, at the right-hand side, with the bolts (380).
4 _
Install the bracket (630) on the TGB left-hand side with the bolts (625).
5 _
Install the bracket (645) on the bracket (505) on the TGB right-hand side with the bolts (640) and the nuts (635).
6 _
Install the bracket (645) on the TGB right-hand side with the bolts (655) and the washers (650). The bracket (645) is attached to the electrical harnesses.
7 _
Install the brackets (660) and (670) on the TGB right-hand side with the bolts (665).
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C F M 56-5B 8 _
Install the clamp (580) on the HJ7 harness and attach to the bracket (260) on the AGB/TGB interface, left-hand side, with the bolt (585).
9 _
Install the clamp (595) on the HJ7 harness and attach to the bracket (345) on the horizontal drive shaft housing, left-hand side, with the bolt (590).
10 __
Install the clamp (600) on the HJ8 harness and attach to the bracket (535) on the AGB/TGB interface, left-hand side, with the bolt (605).
11 __
Install the clamp (565) on the HJ8 harness and attach to the bracket (345) on the horizontal drive shaft housing, left-hand side, with the bolt (610).
(b) TORQUE the nuts (635) and bolts (380), (585), (590), (605), (610) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (c) TORQUE the nuts (575) and bolts (625), (655), (665) to between 98 and 110 lbf.in (1.10 and 1.24 m.daN). (d) Connect the TGB oil supply tubes (230) to the TGB left-hand side and to the AGB rear face. Tighten the connecting nuts with your hand. (8) Installation of the Rear Sump Oil Tubes (a) Connect the rear sump oil scavenge tube (270) to the tube bundle with your hand. (b) Connect the rear sump oil supply tube (305) to the AGB and to the tube bundle with your hand. (c) Install the parts which attach the rear sump oil tubes as follows: 1 _
Correctly install the gasket (340) between the mating faces.
2 _
Install the bolts (280) to attach the rear sump oil scavenge tube (270) on the AGB rear face.
3 _
Install the TGB oil supply tube (230) and the rear sump oil scavenge tube (270) on the left-hand side of the TGB horizontal drive shaft housing junction.
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C F M 56-5B 4 _
Install the plastic bushing (245), the inner spring clip (250) and the outer spring clip (240) on the TGB oil supply tube (230).
5 _
Install the plastic bushing (255), the inner spring clip (265) and the outer spring clip (275) on the rear sump oil scavenge tube (270).
6 _
Attach the spring clips (240), (250) and (265), (275) to the bracket (260) with the bolt (285) and the nut (235) on the left-hand side of TGB/horizontal drive shaft housing junction.
7 _
Install the rear sump oil supply tube (305) on the AGB rear face.
8 _
Install the plastic bushing (300), the inner spring clip (295) and the outer spring clip (310) on the rear sump oil supply tube (305).
9 _
Attach the spring clips (295) and (310) to the bracket (260) with the bolt (315) and the nut (290) on the TGB/horizontal drive shaft housing junction.
10 __
Install the plastic bushing (325), the inner spring clip (330) and the outer spring clip (320) on the rear sump oil supply tube (305) on the AGB rear face.
11 __
Attach the spring clips (330) and (320) to the bracket (345) with the bolt (225) and the nut (335) on the AGB rear face.
(d) Torque the nut (235) to between 98 and 110 lbf.in (1.10 and 1.24 m.daN). (e) TORQUE the nuts (290), (335) and bolts (280) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (f) TORQUE the rear sump oil supply tube (305) connecting nuts to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (g) TORQUE the rear sump oil scavenge tube (270) connecting nut to between 900 and 1100 lbf.in (10.17 and 12.43 m.daN). Safety with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002) (Ref. TASK 70-22-00911-002). (h) TORQUE the TGB oil supply tube (230) connecting nuts to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
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C F M 56-5B (9) Installation of the AGB External Parts WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL _______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. (a) Carefully clean the mating faces of the AGB, bolt (685), washer (690) and bonding strip (695) with trichloroethylene (Material No. CP1008) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041). (b) Apply a thin layer of brisal-ox (Material No. CP2338) to the mating faces of the AGB, bolt (685), washer (690), and bonding strip (695). (c) Install the parts which attach the AGB external parts as follows: 1 _
Attach the bonding strip (695) to the AGB on the starter pad with the bolt (685) and the washer (690).
2 _
Correctly install the gasket (395) between the mating faces.
3 _
Install the TGB oil scavenge hose (385) on the AGB rear face with the bolts (390).
4 _
Correctly install the gaskets (350) and (370) between the mating faces.
5 _
Install the FWD sump oil scavenge hose (355) on the AGB rear face with the bolts (360) and on the TGB right-hand side with the bolts (365).
6 _
Install the plastic bushing (10), the inner spring clip (5) and the outer spring clip (50) on the AGB/TGB oil supply tube (30).
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C F M 56-5B 7 _
Attach the spring clips (5) and (50) to the bracket (90) with the bolt (55) and the nut (95) on the AGB front face.
8 _
Install the plastic bushing (25), the inner spring clip (20) and the outer spring clip (35) on the AGB/TGB oil supply tube (30).
9 _
Attach the spring clips (20) and (35) to the bracket (45) with the bolt (40) and the nut (15) on the AGB front face.
10 __
Install the plastic bushing (80), the inner spring clip (85) and the outer spring clip (75) on the rear sump oil supply tube (60).
11 __
Attach the spring clips (75) and (85) to the bracket (90) with the bolt (65) and the nut (70) on the AGB front face.
12 __
Correctly install the gaskets (115), (180) and (185) between the mating faces.
13 __
Install the FWD sump oil return tube (100), the rear sump oil return tube (105) and the TGB oil scavenge tube (110) on the AGB front face with the bolts (120), (175) and (170).
14 __
Install the plastic bushing (140), the inner spring clip (145) and the outer spring clip (135) on the TGB oil scavenge tube (110).
15 __
Install the plastic bushing (155), the inner spring clip (150) and the outer spring clip (160) on the rear sump oil return tube (105).
16 __
Attach the spring clips (145), (135) and (150), (160) to the bracket (130) with the bolt (125) and the nut (165) on the AGB front face.
17 __
Attach the bracket (475) to the AGB left-hand side with the bolts (445).
18 __
Install the plastic bushing (470), the inner spring clip (450) and the outer spring clip (460) on the IDG exchanger fuel outlet tube (455).
19 __
Install the plastic bushing (410), the inner spring clip (420) and the outer spring clip (405) on the oil heater tube (415).
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C F M 56-5B 20 __ 21 __
Install the plastic bushing (435), the inner spring clip (440) and the outer spring clip (425) on the CLP fuel tube (430). Attach the spring clips (450), (460) and (425), (440) and (405), (420) to the bracket (475) with the bolt (465) and the nut (400) on the AGB left-hand side.
(d) TORQUE the nut (70) and bolts (390), (360), (365), (120), (170), (175) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (e) TORQUE the nuts (15), (95), (165), (400) and bolts (445), (685) to between 98 and 110 lbf.in (1.10 and 1.24 m.daN). (f) TORQUE the rear sump oil supply tube (60) connecting nut to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (g) TORQUE the AGB/TGB oil supply tube (30) connecting nut to between 450 and 550 lbf.in (5.08 and 6.21 m.daN). (h) Engage the IDG electrical cables in the clamp on the AGB. (10) Installation of the Fan Case Water Drain Tubes (a) Install the parts which attach the water drain tubes as follows: 1 _
Install the plastic bushing (550), the inner spring clip (545) and the outer spring clip (555) on the AFT fan case water drain tube (530).
2 _
Attach the spring clips (545) and (555) to the bracket (535) with the bolt (540) and the nut (560).
3 _
Install the plastic bushing (205), the inner spring clip (200) and the outer spring clip (210) on the FWD fan case water drain tube (220).
4 _
Attach the spring clips (200) and (210) to the bracket (195) with the bolt (190) and the nut (215). NOTE : The bracket (195) will be attached to the AGB scavenge ____ tube after the installation of the ECU alternator.
5 _
Install the forward fan case water drain tube (220) on the engine.
(b) Connect the water drain tubes to the nipples on the fan frame.
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C F M 56-5B (c) TORQUE the aft fan case water drain tube (530) connecting nut to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (d) TORQUE the nut (560) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). Subtask 72-63-00-410-067 D. Final Steps of the AGB Installation CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (1) Before their installation, make sure that the gaskets are serviceable, lubricate the gaskets and nipples with engine oil (Material No. CP2442) and lubricate the threads of bolts with graphite grease (Material No. CP2101), unless specified. (2) Remove blanking plugs and caps from the free ends of items before installation. (3) Install the ECU alternator (Ref. TASK 73-21-30-400-001). (4) Connect the forward fan case water drain tube (220) to the nipple on the fan frame. (5) TORQUE the forward fan case water drain tube (220) connecting nut to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (6) TORQUE the nut (215) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (7) Install the fuel pump (Ref. TASK 73-11-10-400-003). (8) Install the lubrication unit (Ref. TASK 79-21-10-400-004). (9) Install the pneumatic starter (Ref. TASK 80-11-10-400-002). (10) Install the integrated drive generator (IDG) (Ref. TASK 24-21-51-400040). (11) Install the hydraulic pump (Ref. TASK 29-11-51-400-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 456 Nov 01/08
C F M 56-5B (12) Install the drain tubes which follow under the AGB: - FRV drain tube (Ref. TASK 71-73-49-400-007) - oil reservoir drain tube (Ref. TASK 71-73-49-400-049) - HMU drain tube (Ref. TASK 71-73-49-400-027) - heat exchanger drain tube (Ref. TASK 71-73-49-400-026) - fuel pump drain tube (Ref. TASK 71-73-49-400-008) - hydraulic pump drain tube (Ref. TASK 71-73-49-400-028) - IDG pad drain tube (Ref. TASK 71-73-49-400-004) - starter pad drain tube (Ref. TASK 71-73-49-400-003) - forward sump drain tube (Ref. TASK 71-73-49-400-029). (13) Install the drain manifold module (Ref. TASK 71-71-43-400-041). (14) Install the fan fire detector (Ref. TASK 26-12-15-400-042). Subtask 72-63-00-410-068 E. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the warning notice(s). Subtask 72-63-00-440-051 F. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041) Subtask 72-63-00-710-056 G. Test after the Installation (1) Do the test given in the installation of the handcranking drive cover (Ref. TASK 72-63-00-400-002). (2) Do a minimum idle check (Ref. TASK 71-00-00-710-006) and do a check for leaks during the visual inspection of the oil system (Ref. TASK 79-00-00-210-003). (3) Do a check of the oil level (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-13-79-610-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 457 Nov 01/08
C F M 56-5B (4) Do an accel check (Ref. TASK 71-00-00-710-025). 5. Close-up ________ Subtask 72-63-00-410-069 A. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 458 Nov 01/08
C F M 56-5B ACCESSORY GEARBOX ASSEMBLY - INSPECTION/CHECK _____________________________________________ TASK 72-63-00-210-002 Inspection/Check of the Accessory Gearbox Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP8001
Material No.
CP8002
* lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-63-00-300-002 72-63-00-300-003
Opening of the Closing of the Replacement of Replacement of
Fan Cowl Doors Fan Cowl Doors a Sealol Seal (Typical) a Magnetic Seal (Typical)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-63-00-941-057 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-064 B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ Subtask 72-63-00-210-052 A. Inspection of the AGB external areas. ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Housing for : A. Cracks
Not serviceable
B. Nicks, dents and scratches
Any number, 0.035 in. (0.9 mm) deep after removal of high metal.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------2. Starter pad fuel pump No leakage permitted Replace the carbon seal pad, hydraulic pump (Ref. TASK 72-63-00-300pad and IDG pad for 002) or (Ref. TASK 72-63leaks. 00-300-003) 3. Tube fittings for leaks
No leakage permitted
Tighten the fittings and/or replace the tube seals
4. AGB mounts for : A. Cracks
Not serviceable
B. Loose bushing
Not serviceable
5. Broken or missing lockwire
Not serviceable
Replace the lockwire lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002).
6. Key-lock studs for: A. Missing
Not serviceable
5. Close-up ________ Subtask 72-63-00-410-060 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B ACCESSORY GEARBOX ASSEMBLY - REPAIRS ____________________________________ TASK 72-63-00-300-002 Replacement of a Sealol Seal (Typical) 1. __________________ Reason for the Job To replace a leaky sealol seal assembly by an other sealol seal assembly at: - the IDG drive pad - the hydraulic pump drive pad - the fuel pump drive pad - the starter drive pad NOTE : You can find two types of carbon seal installed on these Accessory ____ Gearbox (AGB) drive pads: a sealol seal assembly or a magnetic seal assembly. You can replace a sealol seal assembly either, by a new sealol seal assembly or, as an alternate, by a new magnetic seal assembly. If you replace a sealol seal by a magnetic seal, remove the sealol seal as specified in this procedure. If, as a replacement, you install a magnetic seal on the hydraulic pump and/or the fuel pump drive pad, make sure you install the correct type of magnetic seal (the one without the thrust ring added). Then, refer to the related installation paragraph. If, as a replacement, you install a magnetic seal on the Integrated Drive Generator (IDG) and/or starter drive pad, make sure you install the correct type of magnetic seal (the one equipped with a thrust ring). Then, refer to the related installation paragraph. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
856A1130 856A3576
slide hammer storage box warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 TOOL SET - JACK SCREW 2 SEALOL AND MAGNETIC SEALS-R/I
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2442
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-L-5544 graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------10
O-ring
72-63-00 02 -040
10 10
O-ring O-ring
72-63-00 03 -030 72-63-00 03 -030A
10
O-ring
72-63-00 05A-140
10 10 15 15
O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00
15 15
O-ring O-ring
72-63-00 06A-080 72-63-00 06A-080A
R R R 06A-080 06A-080A 03 -030 03 -030A
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------30 30 30 30
O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00
02 02 02 02
-050 -050A -050B -050C
30 30
O-ring O-ring
72-63-00 03 -040 72-63-00 03 -040A
30 30 30 30 30 30 30 30
O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00
R R
R
05A-150 05A-150A 05A-150B 05A-150C 06 -060 06 -060A 06A-060 06A-060A
D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-21-51-000-040 24-21-51-400-040 29-11-51-000-041 29-11-51-400-041 71-00-00-790-002 71-00-00-790-006 71-13-00-010-040 71-13-00-410-040 73-11-10-000-003 73-11-10-400-003 80-11-10-000-002 80-11-10-400-002 72-63-00-991-305 72-63-00-991-306
Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) Removal of the Green Engine Pump (1030GK) Installation of the Green Engine Pump (1030GK) Fuel or Hydraulic or Oil Leakage Limits Leak Check after the Replacement of a Sealol Seal or a Magnetic Seal on the AGB Drive Pads of the IDG, Hydraulic Pump, Starter and Fuel Pump Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Fuel Pump and Filter Assembly Installation of the Fuel Pump and Filter Assembly Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. 801 Fig. 802
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Feb 01/10
C F M 56-5B 3. __________ Job Set-up Subtask 72-63-00-941-058 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-065 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 801/TASK 72-63-00-991-305, 802/TASK 72-63-00-991-306) Subtask 72-63-00-020-058 A. Preparation for the Removal of the Sealol Seal Assembly (1) Depending on the drive pad on which you have to replace the sealol seal assembly, remove one of these units: - fuel pump (Ref. TASK 73-11-10-000-003) - hydraulic pump (Ref. TASK 29-11-51-000-041) - IDG (Ref. TASK 24-21-51-000-040) - starter (Ref. TASK 80-11-10-000-002)
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 804 Feb 01/10
C F M 56-5B
Sealol Seal Assembly (Typical) Figure 801/TASK 72-63-00-991-305 EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 805 Feb 01/10
C F M 56-5B
Removal/Istallation of a Sealol Seal Rotating Mating Ring (Typical) Figure 802/TASK 72-63-00-991-306 EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 806 Feb 01/10
C F M 56-5B Subtask 72-63-00-020-059 B. Removal of the Sealol Seal Housing Assembly (1) Remove the 3 nuts (60) and washers (50) which attach the sealol seal housing assembly (40) to the drive pad. (2) Remove the sealol seal housing assembly (40) with the jackscrews P12 from the TOOL SET - JACK SCREW (856A1130G09). Remove and discard O-ring (30). (3) Put the removed parts (60), (50) and (40) in the storage box. Subtask 72-63-00-020-060 C. Removal of the Rotating Mating Ring Assembly (1) Depending on the drive pad from which you remove the rotating mating ring assembly, get the applicable tool diameter configuration from the tool set, SEALOL AND MAGNETIC SEALS-R/I (856A3576G01). - for the fuel pump and hydraulic pump drive pads, use the smaller diameter tool with the items P09, P10 and P11 - for the starter and IDG drive pads, use the larger diameter tool with the items P02, P03 and P06. (2) Loosen the tool items: - P06 and P05 (larger diameter tool) or - P11 and P05 (smaller diameter tool). (3) Engage the tool on the gearshaft until the nylon/viton-end of item: - P02 (larger diameter tool) or - P09 (smaller diameter tool) Comes against the polished face of the rotating mating ring. (4) Tighten the item P05 by hand until you feel the jaws of the collet are tightly engaged under the mating ring. Manually give the tool one or two pulls to make sure it is correctly installed. If so, it must not come out. (5) Install the slide hammer on top of the tool. Operate the slide hammer and remove the rotating mating ring assembly from the gearshaft. PRE SB CFM 72-105
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 807 Feb 01/10
C F M 56-5B (6) Remove the O-ring (10) from the inner diameter groove of the rotating mating ring (20). Discard the O-ring (10). POST SB CFM 72-105 (7) Remove the bal seal (15) from the inner diameter groove of the rotating mating ring (20) for the IDG pad and starter pad. Discard the bal seal (150). Remove the O-ring (10) from the inner diameter groove of the rotating mating ring (20) for the fuel pump pad and hydraulic pump pad. Discard the O-ring (10). END OF SB CFM 72-105 (8) Loosen the items: - P06 and P05 (larger diameter tool) or - P11 and P05 (smaller diameter tool) And remove the rotating mating ring (20) from tool (856A3576G01). Put the mating ring (20) in the storage box. Subtask 72-63-00-020-061 D. Disposal of the Removed Sealol Seal Components (1) Tag the removed parts (40) and (20) to indicate they come from the same matched assembly. (2) Put the removed parts in a storage box and send them to the repair shop. Subtask 72-63-00-420-059 E. Preparation for the Installation of the Sealol Seal Assembly (1) Get a new sealol seal assembly corresponding to the diameter of the drive pad on which you do the replacement. (2) Clean the gearshaft area CAUTION : DO NOT USE THIS SOLVENT NEAR FLAMES OR HEAT, BECAUSE THIS _______ SOLVENT IS FLAMMABLE. DO NOT BREATHE THE GASES RELEASED FROM SOLVENT, DO NOT LET IT TOUCH YOUR SKIN OR CLOTHING AND MAKE SURE YOU HAVE A GOOD FLOW OF AIR, BECAUSE THIS SOLVENT IS DANGEROUS TO YOUR SKIN, EYES AND LUNGS.
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 808 Feb 01/10
C F M 56-5B (a) Clean the gearshaft area to come in contact with the new rotating mating ring (20) with acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656). (3) Lubricate the same gearshaft area with engine oil (Material No. CP2442). Subtask 72-63-00-420-060 F. Installation of the Rotating Mating Ring Assembly CAUTION : USE CLEAN COTTON GLOVES WHEN YOU HANDLE THE COMPONENTS OF A _______ SEALOL SEAL ASSEMBLY TO PREVENT CONTAMINATION. AT INSTALLATION, MAKE SURE THAT THE FACE OF THE ROTATING MATING RING WHICH TOUCHES THE CARBON RING IS THE POLISHED SURFACE. CAUTION : THERE ARE TWO CONFIGURATIONS OF SEALOL SEAL (SB CFM 72-105). _______ THE O-RING OR BAL SEAL ARE MATCHED TO THEIR ROTATING RING. THEY ARE NOT INTERCHANGEABLE. PRE SB CFM 72-105 (1) Remove the new rotating mating ring (20) from its packaging. Apply a thin layer of engine oil (Material No. CP2442) to the following new O-rings: - O-ring (10) for the fuel pump pad, - O-ring (10) for the starter pad, - O-ring (10) for the IDG pad, - O-ring (10) for the hydraulic pump pad. Install the O-ring (10) in the inner diameter groove of rotating ring (20). POST SB CFM 72-105 (2) Installation of the new O-ring and new bal seal. CAUTION : BE CAREFUL WHEN YOU INSTALL THE BAL SEAL (15) IN THE GROOVE _______ OF SEALOL SEAL ROTATING RING (20) BECAUSE THE BAL SEAL IS EASILY DAMAGED. CAUTION : MAKE SURE THAT THE OPENING OF THE BAL SEAL (15) IS TOWARDS _______ THE TABS OF SEALOL SEAL ROTATING RING (20). OTHERWISE IMPORTANT OIL LEAKAGE CAN OCCUR.
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 809 Feb 01/10
C F M 56-5B (a) Remove the new rotating mating ring (20) from its packaging. Apply a thin layer of engine oil (Material No. CP2442) to the following new O-rings and new bal seal: - O-ring (10) for the fuel pump pad, - O-ring (15) for the starter pad, - O-ring (15) for the IDG pad, - O-ring (10) for the hydraulic pump pad. Install the O-ring (10) in the inner diameter groove of rotating ring (20) for the fuel pump pad and hydraulic pump pad. Install the bal seal (15) in the inner diameter groove of rotating ring (20) the IDG pad and starter pad. END OF SB CFM 72-105 (3) Depending on the diameter of the new rotating mating ring assembly you install, get the applicable tool diameter configuration from the SEALOL AND MAGNETIC SEALS-R/I (856A3576G01). (4) Put the new mating ring (20) on the applicable tool, (856A3576G01), as follows: - loosen the items P06 and P05 (larger diameter tool) or P11 and P05 (smaller diameter tool) - put the new mating ring (20) on the tool, its polished face in contact with the nylon/viton end of item P02 (larger diameter tool) or P09 (smaller diameter tool) - tighten the item P05 by hand until the rotating mating ring (20) is held tightly in the collet of item P02 or P09. (5) Engage the tool and mating ring assembly on the gearshaft. Turn the tool with the handle until you feel the slots of the rotating mating ring (20) engage the lugs of the gearshaft bearing. (6) Turn the tool clockwise then counterclockwise to make sure that the lugs of the rotating mating ring are correctly engaged in the slots of the bearing (inner race). (7) Loosen the items P06 and P05 (or P11 and P05) and remove the tool. (8) Lubricate the polished face of the rotating mating ring (20) with engine oil (Material No. CP2442).
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 810 Feb 01/10
C F M 56-5B Subtask 72-63-00-420-061 G. Installation of the Sealol Seal Housing Assembly CAUTION : AT INSTALLATION, MAKE SURE THAT PARTICLES, EVEN OF EXTREMELY _______ SMALL SIZE, ARE NOT LEFT BETWEEN THE POLISHED FACE OF THE ROTATING MATING RING AND THE CARBON RING FACE OF THE SEALOL SEAL HOUSING ASSEMBLY. OTHERWISE, LEAKS WILL OCCUR. CAUTION : USE CLEAN COTTON GLOVES TO HANDLE THE SEALOL SEAL HOUSING _______ ASSEMBLY. CAUTION : THE INSTALLATION OF THE SEALOL SEAL HOUSING (40) MUST BE DONE _______ BY HAND AND WITHOUT SHOCKS TO PREVENT DAMAGE TO THE CARBON RING. (1) Lubricate a new O-ring (30) for the IDG drive pad or O-ring (30) for the hydraulic pump drive pad or O-ring (30) for the fuel pump drive pad or O-ring (30) for the starter drive pad with engine oil (Material No. CP2442) and install in the outer diameter groove of sealol seal housing assembly (40).
R
(2) Manually engage the housing assembly (40) in the bore of the pad until the O-ring (30) is fully against the entrance of the bore. (3) Apply a thin layer of graphite grease (Material No. CP2101) to the 3 studs of the pad. (4) Install the 3 washers (50) on the 3 studs. Engage the 3 nuts (60) on the studs and tighten continuously the nuts, each in small increments, until the flange of the housing assembly comes in contact with its mating face on the pad. (5) TORQUE the nuts (60) to between 55 and 60 lbf.in (0.62 and 0.67 m.daN). (6) Depending on the drive pad on which you have replaced the sealol seal assembly, install one of these units: - fuel pump (Ref. TASK 73-11-10-400-003) - hydraulic pump (Ref. TASK 29-11-51-400-041) - IDG (Ref. TASK 24-21-51-400-040) - starter (Ref. TASK 80-11-10-400-002)
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Aug 01/09
C F M 56-5B Subtask 72-63-00-410-061 H. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-63-00-710-054 J. Do a leak check of the replacement seal (Ref. TASK 71-00-00-790-006). If there are leaks (Ref. TASK 71-00-00-790-002). 5. Close-up ________ Subtask 72-63-00-942-050 A. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B TASK 72-63-00-300-003 Replacement of a Magnetic Seal (Typical) 1. __________________ Reason for the Job To replace a leaky magnetic seal by another magnetic seal at: - the Integrated Drive Generator (IDG) drive pad - the hydraulic pump drive pad - the fuel pump drive pad - the starter drive pad. NOTE : You can find two types of carbon seal installed on ____ Gearbox (AGB) drive pads: a magnetic seal assembly assembly. You can replace a magnetic seal assembly magnetic seal assembly (the one without the thrust an alternative, by a new sealol seal assembly.
these Accessory or a sealol seal either, by a new ring added) or, as
If you replace a magnetic seal by a sealol seal, remove the magnetic seal as specified in this procedure. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
slide hammer storage box warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 TOOL SET - JACK SCREW 1 SEALOL AND MAGNETIC SEALS-R/I
856A1130 856A3576
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2442
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) *
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
engine oil (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------70 70 70 70
O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00
02 02 03 03
-060 -060A -060 -060A
70 70 70 70 90 90 90 90
O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00
05A-170 05A-170A 06A-110 06A-110A 02 -070 02 -070A 03 -070 03 -070A
90 90 90 90
O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00
05A-160 05A-160A 06 -120 06 -120A
R R
R R R R R
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Feb 01/10
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-21-51-000-040 24-21-51-400-040 29-11-51-000-041 29-11-51-400-041 71-00-00-790-002 71-00-00-790-006 71-13-00-010-040 71-13-00-410-040 73-11-10-000-003 73-11-10-400-003 80-11-10-000-002 80-11-10-400-002 72-63-00-991-307 72-63-00-991-308
Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) Removal of the Green Engine Pump (1030GK) Installation of the Green Engine Pump (1030GK) Fuel or Hydraulic or Oil Leakage Limits Leak Check after the Replacement of a Sealol Seal or a Magnetic Seal on the AGB Drive Pads of the IDG, Hydraulic Pump, Starter and Fuel Pump Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Fuel Pump and Filter Assembly Installation of the Fuel Pump and Filter Assembly Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. 803 Fig. 804
3. __________ Job Set-up Subtask 72-63-00-941-060 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B Subtask 72-63-00-010-069 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 803/TASK 72-63-00-991-307, 804/TASK 72-63-00-991-308) Subtask 72-63-00-020-062 A. Preparation for the Removal of a Magnetic Seal (1) Depending on the drive pad on which you have to replace the magnetic seal assembly, remove one of these units: - Hydraulic pump (Ref. TASK 29-11-51-000-041) - Fuel pump (Ref. TASK 73-11-10-000-003) - IDG (Ref. TASK 24-21-51-000-040) - Starter (Ref. TASK 80-11-10-000-002) Subtask 72-63-00-020-063 B. Removal of the Magnetic Seal Housing Assembly (1) Remove the 3 nuts (110) and washers (100) which attach the magnetic seal housing assembly (120) to the pad. (2) Remove the magnetic seal housing assembly with jackscrews P2 from the TOOL SET - JACK SCREW (856A1130G06). (3) Remove and discard O-ring (90). Subtask 72-63-00-020-064 C. Removal of the Carbon Ring Assembly (1) Prepare the tool set SEALOL AND MAGNETIC SEALS-R/I (856A3576G01) with handle P12, sleeve P13, and collet P15. (2) Engage tool assembly in the AGB drive pad, until the jaws of the collet are behind the carbon ring assembly (80). (3) Tighten the sleeve by hand until the collet is tight against the carbon ring assembly (80).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B
Magnetic Seal Assembly (Typical) Figure 803/TASK 72-63-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
C F M 56-5B
Removal of a Magnetic Seal Carbon Ring Assembly (Typical) Figure 804/TASK 72-63-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B (4) Attach the slide hammer to the handle and remove the carbon ring assembly (80) from the gearshaft. (5) Loosen the sleeve and remove the carbon ring assembly (80), from the tool. (6) Remove and discard the O-ring (70). (7) Put the removed parts in a storage box and send them to the repair shop. Subtask 72-63-00-420-062 D. Installation of the Magnetic Seal Assembly (type without the thrust ring) CAUTION : DO NOT USE THIS SOLVENT NEAR _______ SOLVENT IS FLAMMABLE. DO NOT SOLVENT, DO NOT LET IT TOUCH SURE YOU HAVE A GOOD FLOW OF DANGEROUS TO YOUR SKIN, EYES
FLAMES OR HEAT, BECAUSE THIS BREATHE THE GASES RELEASED FROM YOUR SKIN OR CLOTHING AND MAKE AIR, BECAUSE THIS SOLVENT IS AND LUNGS.
(1) With acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or magchem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) remove the coked oil which possibly remains on the gearshaft area related to the rotary part of the magnetic seal, to prevent possible damage to the O-ring (70) at installation. (2) Get a new magnetic seal assembly. CAUTION : USE GLOVES WHEN YOU HANDLE THE MAGNETIC SEAL COMPONENTS TO _______ PREVENT CONTAMINATION. MAKE SURE THAT THE FACE OF THE MAGNETIC SEAL WHICH TOUCHES THE CARBON RING IS THE POLISHED SURFACE. (a) Remove the magnetic seal assembly from its packaging. (3) Lubricate a new O-ring (70) for the IDG drive pad or O-ring (70) for the hydraulic fuel pump drive pad or O-ring (70) for the fuel pump drive pad or O-ring (70) for the starter drive pad with engine oil (Material No. CP2442). Install the O-ring (70) in the inner groove of the carbon ring assembly (80).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 819 Nov 01/08
C F M 56-5B (4) Lubricate a new O-ring (90) for the IDG drive pad or O-ring (90) for the hydraulic pump drive pad or O-ring (90) for the fuel pump drive pad or O-ring (90) for the starter drive pad with engine oil (Material No. CP2442). Install the O-ring (90) in the outer groove of the magnetic seal housing assembly (120). (5) Lubricate the carbon ring mating face and the gearshaft with engine oil (Material No. CP2442). CAUTION : MAKE SURE THAT PARTICLES; EVEN OF EXTREMELY SMALL SIZE, ARE _______ NOT LEFT BETWEEN THE POLISHED FACE OF THE MAGNETIC RING AND THE CARBON FACE OF THE ROTATING RING ASSEMBLY DURING INSTALLATION. OTHERWISE LEAK CAN OCCUR. CAUTION : DO NOT HIT THE CARBON MATING FACE OR SLIDE IT ON THE _______ MAGNETIC MATING RING WHEN YOU INSTALL THE CARBON RING ASSEMBLY. (a) Very carefully, install the carbon ring assembly (80) against the polished face of the magnetic ring. CAUTION : DO NOT HIT THE MAGNETIC SEAL HOUSING DURING THE _______ INSTALLATION TO PREVENT DAMAGE TO THE MAGNETIC SEAL COMPONENTS. 1 _
Align the carbon ring assembly with the housing bore.
(b) Engage the magnetic seal assembly on the gearshaft until the O-ring (90) of the housing is fully against the AGB pad. (6) Lubricate the threads of the 3 studs with graphite grease (Material No. CP2101). (7) Install washers (100) and nuts (110) and continuously install the magnetic seal assembly until the housing flange is fully against the AGB pad. (8) TORQUE the nuts (110) to between 55 and 60 lbf.in (0.62 and 0.67 m.daN). (9) Depending on the drive pad on which you have replaced the magnetic seal assembly, install one of these units: - IDG (Ref. TASK 24-21-51-400-040) - hydraulic pump (Ref. TASK 29-11-51-400-041) - fuel pump (Ref. TASK 73-11-10-400-003) - Starter (Ref. TASK 80-11-10-400-002)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 820 Nov 01/08
C F M 56-5B Subtask 72-63-00-410-065 E. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-63-00-710-055 F. Do a leak check of the replacement seal (Ref. TASK 71-00-00-790-006). If there are leaks (Ref. TASK 71-00-00-790-002). 5. Close-up ________ Subtask 72-63-00-942-051 A. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 821 Nov 01/08
C F M 56-5B TASK 72-63-00-300-004 Replacement of a Magnetic Seal (IDG and Starter Drive Pads). 1. __________________ Reason for the Job To replace a leaky magnetic seal by another magnetic seal at: - the Integrated Drive Generator (IDG) drive pad, - the starter drive pad. NOTE : You can find two types of carbon seal installed on these Accessory ____ Gearbox (AGB) drive pads: a magnetic seal assembly or a sealol seal assembly. You can replace a magnetic seal assembly either, by a new magnetic seal assembly (the one equipped with a thrust ring) or, as an alternate, by a new sealol seal assembly. If you replace a magnetic seal by a sealol seal, remove the magnetic seal as specified in this procedure and go to (Ref. TASK 72-63-00-300-00200) for the installation of the sealol seal. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
856A1130 856A3576
slide hammer storage box warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 TOOL SET - JACK SCREW 1 SEALOL AND MAGNETIC SEALS-R/I
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 822 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2442
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN -------------------------------------------------------------------------------
R R R
130 130 130 130 150 150 150 150
O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
03 -060 03 -060A 06A-110 06A-110A 03 -070 03 -070A 06 -120 06 -120A
Page 823 Feb 01/10
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-21-51-000-040 24-21-51-400-040 71-00-00-790-002 71-00-00-790-006 71-13-00-010-040 71-13-00-410-040 80-11-10-000-002 80-11-10-400-002 72-63-00-991-315 72-63-00-991-316
Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) Fuel or Hydraulic or Oil Leakage Limits Leak Check after the Replacement of a Sealol Seal or a Magnetic Seal on the AGB Drive Pads of the IDG, Hydraulic Pump, Starter and Fuel Pump Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. 805 Fig. 806
3. __________ Job Set-up Subtask 72-63-00-941-063 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 824 Nov 01/08
C F M 56-5B Subtask 72-63-00-010-072 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 805/TASK 72-63-00-991-315, 806/TASK 72-63-00-991-316) Subtask 72-63-00-020-066 A. Preparation for the Removal of a Magnetic Seal (1) Depending on the drive pad on which you have to replace the magnetic seal assembly, remove one of these units: - IDG (Ref. TASK 24-21-51-000-040) - starter (Ref. TASK 80-11-10-000-002) Subtask 72-63-00-020-067 B. Removal of the Magnetic Seal Housing Assembly (1) Remove the 3 nuts (170) and washers (160) which attach the magnetic seal housing assembly (180) to the pad. (2) Remove the magnetic seal housing assembly (180) with jackscrews P2 from the TOOL SET - JACK SCREW (856A1130G06). (3) Remove and discard O-ring (150). Subtask 72-63-00-020-068 C. Removal of the Carbon Ring Assembly (1) Prepare the tool set SEALOL AND MAGNETIC SEALS-R/I (856A3576G01), with handle P12, sleeve P13, and collet P14. (2) Engage the tool assembly (856A3576G01), in the AGB drive pad, until the jaws of the collet are behind the carbon ring assembly (140). (3) Tighten the sleeve by hand until the collet is tight against the carbon ring assembly (140).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 825 Nov 01/08
C F M 56-5B
Magnetic Seal Assembly (Typical for the IDG and Starter Drive Pads) Figure 805/TASK 72-63-00-991-315 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 826 Nov 01/08
C F M 56-5B
Removal of the Carbon Ring Assembly (Typical, at IDG Drive Pad) Figure 806/TASK 72-63-00-991-316 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 827 Nov 01/08
C F M 56-5B (4) Attach the slide hammer to the handle and remove the carbon ring assembly (140) from the gearshaft. (5) Loosen the sleeve and remove the carbon ring assembly (140) from the tool. (6) Remove and discard the O-ring (130). (7) Put the removed parts in a storage box and send them to the repair shop. Subtask 72-63-00-420-063 D. Installation of the Magnetic Seal Assembly (type equipped with the thrust ring) CAUTION : DO NOT USE THIS SOLVENT NEAR _______ SOLVENT IS FLAMMABLE. DO NOT SOLVENT, DO NOT LET IT TOUCH SURE YOU HAVE A GOOD FLOW OF DANGEROUS TO YOUR SKIN, EYES
FLAMES OR HEAT, BECAUSE THIS BREATHE THE GASES RELEASED FROM YOUR SKIN OR CLOTHING AND MAKE AIR, BECAUSE THIS SOLVENT IS AND LUNGS.
(1) With acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or magchem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) remove the coked oil which possibly remains on the gearshaft area related to the rotary part of the magnetic seal, to prevent possible damage to the O-ring (130) at installation. (2) Get a new magnetic seal assembly. CAUTION : USE GLOVES WHEN YOU HANDLE THE MAGNETIC SEAL COMPONENTS TO _______ PREVENT CONTAMINATION. MAKE SURE THAT THE FACE OF THE MAGNETIC SEAL WHICH TOUCHES THE CARBON RING IS THE POLISHED SURFACE. (a) Remove the magnetic seal assembly from its packaging. (3) For the starter drive pad: - lubricate a new O-ring (130) with engine oil Install the O-ring (130) in the inner groove assembly (140). - lubricate a new O-ring (150) with engine oil Install the O-ring (150) in the outer groove housing assembly (180).
R
(Material No. CP2442). of the carbon ring (Material No. CP2442). of the magnetic seal
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 828 Feb 01/09
R
C F M 56-5B (4) For the IDG drive pad: - lubricate a new O-ring (130) with engine oil Install the O-ring (130) in the inner groove assembly (140) - lubricate a new O-ring (150) with engine oil Install the O-ring (150) in the outer groove housing assembly (180).
(Material No. CP2442). of the carbon ring (Material No. CP2442). of the magnetic seal
(5) Lubricate the carbon ring mating face and the gearshaft with engine oil (Material No. CP2442). CAUTION : MAKE SURE THAT PARTICLES; EVEN OF EXTREMELY SMALL SIZE, ARE _______ NOT LEFT BETWEEN THE POLISHED FACE OF THE MAGNETIC RING AND THE CARBON FACE OF THE ROTATING RING ASSEMBLY DURING INSTALLATION. OTHERWISE LEAK CAN OCCUR. CAUTION : DO NOT HIT THE CARBON MATING FACE OR SLIDE IT ON THE _______ MAGNETIC MATING RING WHEN YOU INSTALL THE CARBON RING ASSEMBLY. (a) Very carefully, install the carbon ring assembly (140) against the polished face of the magnetic ring. CAUTION : DO NOT HIT THE MAGNETIC SEAL HOUSING DURING THE _______ INSTALLATION TO PREVENT DAMAGE TO THE MAGNETIC SEAL COMPONENTS. 1 _
Align the carbon ring assembly with the housing bore.
(6) Engage the magnetic seal assembly on the gearshaft until the O-ring (150) of the housing is fully against the AGB pad. (7) Lubricate the threads of the 3 studs with graphite grease (Material No. CP2101). (8) Install washers (160) and nuts (170) and continuously install the magnetic seal assembly until the housing flange is fully against the AGB pad. (9) TORQUE the nuts (170) to between 55 and 60 lbf.in (0.62 and 0.67 m.daN). (10) Depending on the drive pad on which you have replaced the magnetic seal assembly, install one of these units: - IDG (Ref. TASK 24-21-51-400-040) - starter (Ref. TASK 80-11-10-400-002)
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 829 Feb 01/09
C F M 56-5B Subtask 72-63-00-410-070 E. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-63-00-710-058 F. Do a leak check of the replacement seal (Ref. TASK 71-00-00-790-006). If there are leaks (Ref. TASK 71-00-00-790-002). 5. Close-up ________ Subtask 72-63-00-942-052 A. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 830 Nov 01/08
L.E.P. 1- 9 REVISED TO REFLECT THIS REVISION INDICATING NEW,REVISED, AND/OR DELETED PAGES T. OF C. REVISED TO REFLECT THIS REVISION 5 72-00-00 LAYOUT IMPROVED OR EFFECTIVITY UPDATED 224 72-00-00 311, 322
TOOL DESIGNATION(S) DATA UPDATED
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-00-00 610, 665676, 685A612
CORRECTION/ADDITION/AMPLIFICATION UPDATE CRITERIA
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-00-00 701
WARNING/NOTE/REASON FOR THE JOB AMENDED
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-21-00 402- 403, 406
CORRECTION/ADDITION/AMPLIFICATION ADDED POST CFM SB 72-0193 CONFIGURATION AND ALTERNATIV
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-21-00 601
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
72-23-00 444
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
72-23-00 610, 613, 616
CORRECTION/ADDITION/AMPLIFICATION ADDED MAX SERVICEABLE LIMITS FOR WEAR ON B1 FLANGE RADIUS
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-31-00 601- 602, 620- 631
CORRECTION/ADDITION/AMPLIFICATION SERVICEABLE LIMIT A. SHOULD READ, A. CRACKS ONE LOCK WITH A CRACK IS PERMITTED
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 72-HIGHLIGHTS Page REVISION NO. 48
CES
1 of 2 Feb 01/10
C F M 56-5B -------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES -------------------------------------------------------------------------------------WITH REMARKS SEE LIMIT EXTENSIONS 72-00-00-200-005 AND B. LOOSENESS NOT SERVICEABLE WITH REMARKS SEE LIMIT EXTENSIONS 72-00-00-200-005 72-31-00 801, 808
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
72-56-00 427, 433438
EFFECTIVITY UPDATED CORRECTION/ADDITION/AMPLIFICATION ADDED DAMPING OIL TUBE INSTALLATION BEST PRACTICES
72-62-00 418
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
72-63-00 201
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
72-63-00 802- 810, 814, 823
LAYOUT IMPROVED OR EFFECTIVITY UPDATED
001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499,
72-HIGHLIGHTS Page REVISION NO. 48 CES
2 of 2 Feb 01/10
C F M 56-5B CHAPTER 72 __________ ENGINE LIST OF EFFECTIVE PAGES _______________________ N, R or D indicates pages which are New, Revised or Deleted respectively Remove and insert the affected pages and complete the Record of Revisions and the Record of Temporary Revisions as necessary CH/SE/SU
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611 612 613 614 615 616 617 618 619 620 621 622 623 624 625 626 627 628 629 630 631 632 633 634 635 636 637 638 639 640 641 642 643 644 645 646 647 648 649 650 651 652 653 654 655 656 657 658 659 660 661
DATE Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09
CH/SE/SU 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00
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DATE Nov01/09 Nov01/09 Nov01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10
CH/SE/SU 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-00-00 72-21-00 72-21-00
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DATE Feb01/10 Nov01/08 Nov01/08 Nov01/08 Aug01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Nov01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Nov01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09
1 Nov01/08 2 Nov01/08
72-L.E.P. Page 2 Feb 01/10 CES
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DATE Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Feb01/10 Nov01/09 Feb01/09 Feb01/10 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 May01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/98 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 May01/09 May01/09 Nov01/08 Nov01/08 Nov01/08
CH/SE/SU 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00
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448 449 450 451 452 453 454 455 456 601 602 603 604 605 606 607 608 609 610 611 612 613 614 615 616 617 618 619 620 621 622 623 624 625 626 627 628 629 630 631 632 633 634 635 636 637 638 639 640 641 642
DATE Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 May01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/02 Nov01/08 Nov01/08 Nov01/08 Nov01/08 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09
CH/SE/SU 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-21-00 72-22-00 72-22-00
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DATE May01/09 Aug01/09 May01/09 May01/09 May01/09 Nov01/08 Nov01/08 Aug01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 May01/09 May01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08
1 Nov01/08 2 Nov01/08
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72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00
1 2 3 4 5 6 7 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 417 418 419 420 421 422 423 424 425 426 427 428 429 430 431 432 433 434 435 436 437
Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Feb01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08
CH/SE/SU 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00
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438 439 440 441 442 443 444 445 446 447 448 449 450 451 452 453 454 455 456 457 458 459 460 461 462 463 464 465 466 467 468 469 470 471 472 473 474 475 476 477 478 479 601 602 603 604 605 606 607 608 609
DATE Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09 Nov01/09 Feb01/09 Feb01/09 Feb01/09 Nov01/09 Feb01/09 Feb01/09 Feb01/09 Nov01/09 Feb01/09 Feb01/09 Feb01/09 Feb01/09 Nov01/09 Aug01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08
CH/SE/SU 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00
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DATE Feb01/10 Nov01/08 May01/09 Feb01/10 May01/09 Aug01/09 Feb01/10 May01/09 May01/09 May01/09 Nov01/09 Nov01/09 Nov01/09 May01/09 May01/09 May01/09 May01/09 Nov01/09 May01/09 May01/09 May01/09 May01/09 May01/09 May01/09 Nov01/09 May01/09 May01/09 May01/09 May01/09 May01/09 Feb01/09 Feb01/09 Feb01/09 May01/09 May01/09 Aug01/09 May01/09 May01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Feb01/09 Feb01/09
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DATE Feb01/09 Feb01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09 Nov01/08 Nov01/08 Feb01/09 Feb01/09 Feb01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09 Feb01/09 Nov01/08 Feb01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09
CH/SE/SU
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1 2 401 402
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1 2 3 601 602 603 604 605 606 607 608 609 610 611 612 613 614 615 616 617 618 619 620 621 622 623 624 625 626 627 628 629 630 631 801 802 803 804 805 806 807 808 809 810 811 812
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1 Nov01/08 2 Nov01/08
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627 628 629 630 631 632 633 634 635 636 637
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608 609 610 611 612 613 614 615 616 617 618 619 620 621 622 623 624 625 626 627 628 629 630 631 632 633 634 635 636 637 638 639 640 641 642 643 644 645 646 647 648 649 650
Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08
72-53-00 72-53-00 72-53-00 72-53-00 72-53-00 72-53-00 72-53-00
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72-53-00 72-53-00 72-53-00 72-53-00 72-53-00 72-53-00 72-53-00 72-53-00 72-53-00 72-53-00 72-53-00 72-53-00 72-53-00
605 606 607 608 609 610 611 612 613 614 615 616 617
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CH/SE/SU 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00
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PAGE 633 634 635 636 637 638 639 640 641 642 643 644 645 646 647 648 649 650 651 652 653 654 655 656 657 658 659 660 661 662 663 664 665 666 667 668 669 670 671 672 673 674 675 676 677 678 679 680 681 682 683
DATE Nov01/08 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/08 Nov01/08 Aug01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Aug01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08
CH/SE/SU
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DATE
72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00 72-54-00
684 685 686 687 688 689 690 691 801 802 803 804 805 806 807 808 809 810 811
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72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00
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72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00
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C F M 56-5B CH/SE/SU C PAGE 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00
R
R R R R N N
8 9 10 11 12 13 14 15 16 17 18 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 417 418 419 420 421 422 423 424 425 426 427 428 429 430 431 432 433 434 435 436 437 438 601 602
DATE Nov01/08 May01/05 Nov01/07 May01/05 Nov01/08 May01/05 Nov01/07 May01/05 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 May01/05 May01/05 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 May01/05 May01/05 Nov01/08 May01/05 May01/05 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Nov01/08 Nov01/08
CH/SE/SU 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00
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DATE Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Aug01/07 Nov01/08 Nov01/09 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08
CH/SE/SU
C
PAGE
DATE
72-60-00 72-60-00 72-60-00
1 Nov01/08 2 Nov01/08 3 Nov01/08
72-61-00 72-61-00
1 Nov01/08 2 Nov01/08
72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-62-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00
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1 2 3 4 5 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 417 418 419 420 421 422 423 424 425 426 427 428 601 602 603 604
Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08
1 2 3 4 5 6
Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08
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C F M 56-5B CH/SE/SU C PAGE 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00
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7 8 9 201 202 203 204 205 206 207 208 209 210 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 417 418 419 420 421 422 423 424 425 426 427 428 429 430 431 432 433 434 435 436 437 438
DATE Nov01/08 Nov01/08 Nov01/08 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/07 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08
CH/SE/SU 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00
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R R R R R R R R R
R
R
439 440 441 442 443 444 445 446 447 448 449 450 451 452 453 454 455 456 457 458 601 602 603 801 802 803 804 805 806 807 808 809 810 811 812 813 814 815 816 817 818 819 820 821 822 823 824 825 826 827 828
DATE Nov01/08 Nov01/08 Nov01/09 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Feb01/10 Aug01/09 Nov01/08 Nov01/09 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Nov01/09 Feb01/10 Nov01/08 Nov01/08 Nov01/08 Nov01/08 Feb01/09
CH/SE/SU 72-63-00 72-63-00
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PAGE
DATE
829 Feb01/09 830 Nov01/08
72-L.E.P. Page 9 Feb 01/10 CES
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT ENGINE - GENERAL ________________ DESCRIPTION AND OPERATION
________ CH/SE/SU 72-00-00
C _
PAGE ___________ ____ EFFECTIVITY 1
General
1
Engine Modules
1
Fan/Booster Rotor
1
Fan/Booster Stator
1
Fan Frame
6
Compressor Rotor
6
Compressor Stator
6
Combustor
6
High Pressure Turbine
6
Low Pressure Turbine
6
Turbine Frame
7
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 Page 1 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Accessories and Accessory Drives
Bearings and Seals
Bearings
Oil Distribution
Seals Arrangement
Bearing Functions
Engine Boroscope Inspection Port Provisions, Location and Identification On the Inner Wall (Fairing) of the Fan Bypass Duct On the High Pressure Compressor (HPC) Front and Rear Casings On the Combustion Case
On the Low Pressure Turbine Case
C _
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 11 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 11 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 11 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 11 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 15 001-049, 051-099 101-149, 151-199 201-249, 251-299 72-CONTENTS
R CES
Page 2 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
_________________ ENGINE - GENERAL MAINTENANCE PRACTICES
CH/SE/SU ________
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499
72-00-00 201
Engine Tubes, Hoses, and Fittings
201
Air Flow Check of the Forward Sump Oil Supply Circuit
214
Air Flow Check of the AGB/TGB Oil Supply Circuit
219
Air Flow Check of the Aft Sump Oil Supply Circuit
224
_________________ ENGINE - GENERAL SERVICING
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299
72-00-00 301
Recommendations for Engine Preservation
301
Preservation for a Period of up to 30 Days
304
Preservation for a Period of up to 90 Days
308
Preservation for a Period of 30 to 365 Days.
311
72-CONTENTS R CES
Page 3 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Preservation Renewal Requirements.
Procedure for Exceeded Long Term Preservation Period. Depreservation
_________________ ENGINE - GENERAL INSPECTION/CHECK
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 326 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 328 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 329 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-00-00 601
Inspection/Check of Foreign Object Damage (FOD) (Bird Strike Included)
601
Procedure After Engine Fire or Use of Fire-Extinguishing Agents
613
Procedure after Halogen Products Contamination
618
Procedure after Volcanic Ash, Dust, or Sand Ingestion
622
Inspection/Check After the Engine has Exceeded the Operational Limits
628
Off-Schedule Vane Replacement
647
Over-Serviceable-Limit Extensions
650
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 Page 4 Nov 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Over-Serviceable-Limit Extensions
Inspection/Check of the PS3 Line
Visual Inspection of the Fan Section after Engine Operation in Severe Icing Condition Monitor the Engine EGT for Possible Engine Performance Deterioration
_________________ ENGINE - GENERAL CLEANING/PAINTING
C _
PAGE EFFECTIVITY ____ ___________ 201-249, 251-299 301-399, 401-499 677 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 699 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 A608 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 A610 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-00-00 701
Engine Dry-out and Re lubrication
701
Engine Washing Requirements
714
Hand Cleaning of the Fan Gas Path and Fan Blades
718
Washing of the Engine Gas Path with Pure Water
722
Washing of the Engine Gas Path with Cleaning Agent
733
External Cleaning
744
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 Page 5 Feb 01/10
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
FAN AND BOOSTER ASSEMBLY DESCRIPTION AND OPERATION
72-21-00
General
Fan and booster assembly
Description
C _
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 1
1
1
1
Spinner Front Cone
1
Spinner Rear Cone
1
Fan Disk
1
Fan Blades
5
Booster Rotor
5
Booster Vane Assemblies
5
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 Page 6 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______ FAN AND BOOSTER ASSEMBLY REMOVAL/INSTALLATION
CH/SE/SU ________
C _
PAGE ___________ ____ EFFECTIVITY
72-21-00 401
Removal of the Spinner Front Cone
401
Installation of the Spinner Front Cone
404
Removal of the Spinner Rear Cone
407
Installation of the Spinner Rear Cone
409
Removal of the Fan Rotor Blades
414
Installation of the Fan Rotor Blades
420
Replacement of Fan Rotor Blades in Pairs
426
Replacement of Individual Fan Blades
442
Discard Fan Disc and Booster Spool
447
Discard Fan Shaft
448
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 Page 7 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Removal of the Stage 1 Booster Vane Assembly
CH/SE/SU ________
Installation of the Stage 1 Booster Vane Assembly
FAN AND BOOSTER ASSEMBLY INSPECTION/CHECK
C _
____ EFFECTIVITY PAGE ___________ 449 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 453 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-21-00 601
Inspection/Check of the Spinner Cone
601
Borescope Inspection of the Booster Rotor Blades, Stages 2, 3, 4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5 Inspect Fan Rotor Blades Installed on the Fan Disk
606
Inspect Fan Rotor Blades Removed from the Fan Disk.
633
Inspection/Check of the Stage 1 Booster Vane, Fan Disk, Fan Blades Spacers and Booster Spool.
644
Detailed Inspection and Relubrication of Fan Blade Dovetails, Midspan Shrouds, Retainers, Spacers, Dampers and Fan Disk Dovetail Slots
655
FAN AND BOOSTER ASSEMBLY REPAIRS
617
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-21-00 801
001-049, 051-099 101-149, 151-199 201-249, 251-299
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
Page 8 May 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Replacement of the Crimped Self-Locking Nuts on the Spinner Rear Cone Correction of the Static Imbalance
Blending of Fan Rotor Blades
Blending of the Stage 1 Booster Vane Assembly Angular Distribution for a Replacement of 3 to 18 Pairs of fan Rotor Blades Manual Method NO.1 AND NO.2 BEARING SUPPORT ASSEMBLY DESCRIPTION AND OPERATION
General
No. 1 and no. 2 bearing support module Description
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 801 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 804 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 810 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 825 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 829 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-22-00 1
1
1
1
No. 1 Bearing Support
1
No. 1 Ball Bearing
7
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 Page 9 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________ No. 2 Bearing Support
No. 2 Roller Bearing
Oil Manifold Assembly
External Piping
Fan Shaft
Forward Stationary Air/Oil Seal
FAN FRAME ASSEMBLY DESCRIPTION AND OPERATION
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 8 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 8 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 8 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-23-00 1
General
1
Fonctions
1
Fan Frame.
1
Fan Inlet Case.
1
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 Page 10 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Description
Fan Frame Assembly
Fan Inlet Case Assembly
FAN FRAME ASSEMBLY REMOVAL/INSTALLATION
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 6 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 6 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 7 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-23-00 401
Removal of the Fan Outlet Guide Vane (OGV) Doublets
401
Installation of the Fan Outlet Guide Vane (OGV) Doublets
405
Removal of the Forward Acoustical Panels of the Fan
409
Installation of the Forward Acoustical Panels of the Fan
412
Removal of the Mid Acoustical Panels
415
Installation of the Mid Acoustical Panels
418
Removal of the Aft Acoustical Panels
422
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149,
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 Page 11 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______ Installation of the Aft Acoustical Panels Removal of the Fan Duct Panels
Installation of the Fan Duct Panels Removal of the Splitter Fairing
Installation of the Splitter Fairing Removal of the PS13 Line
Installation of the PS13 Line
Removal of the PS12 Line
Installation of the PS12 Line
Installation of Acoustical Panels Attachment Screw/Nut Locking Installation of Acoustical Panels Attachment Screw Locking
CH/SE/SU ________
C _
PAGE EFFECTIVITY ____ ___________ 201-249, 251-299 301-399, 401-499 426 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 432 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 436 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 440 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 444 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 448 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 453 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 457 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 467 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 471 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 475 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 72-CONTENTS
R CES
Page 12 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______ FAN FRAME ASSEMBLY INSPECTION/CHECK
CH/SE/SU ________
C _
PAGE ___________ ____ EFFECTIVITY
72-23-00 601
Visual Inspection of the Fan Frame Assembly
601
Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material
616
Inspection/Check of the PS13 Line
627
Inspection/Check of the PS12 line
634
Inspection of Forward Acoustical Panels
643
Inspection of Mid Acoustical Panels
650
Inspection of Aft Acoustical Panels
655
Visual Inspection of the Junction Box
660
FAN FRAME ASSEMBLY REPAIRS
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499
72-23-00 801
72-CONTENTS R CES
Page 13 Aug 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Local Reconditioning of the Abradable Material- Defects less than 0.12 in. (3 mm) deep and 0.50 in.2 (3.2 cm2) Removal of Rust from the Fan Frame Casing
CH/SE/SU ________
Repair of Fan Duct Panel
Repair of the Abradable (material) Shroud with Circular Patches Repair of Forward, Mid and Aft Acoustical Panels when Unbounded Cup Replacement of the Riveted Self Locking Nuts for the Attachment of the Forward Acoustical Panels Replacement of Lateral Bracket Plate on the Junction Box
_____________________ HP COMPRESSOR SECTION DESCRIPTION AND OPERATION
Discard Life Limited HP Compressor
____ EFFECTIVITY PAGE ___________ 801 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 806 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 811 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 815 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 825 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 831 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 840 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-30-00 1
General
______________________ HP COMPRESSOR SECTION REMOVAL/INSTALLATION
C _
1
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049,
051-099 151-199 251-299 401-499 051-099
72-30-00 401
401
72-CONTENTS R CES
Page 14 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT rotating parts
CH/SE/SU ________
HPC ROTOR ASSEMBLY DESCRIPTION AND OPERATION
72-31-00
C _
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 1
General
1
Description
1
Front Shaft
1
Disk and Spools
1
Blades
1
Rear Seal
1
HPC ROTOR ASSEMBLY INSPECTION/CHECK
Inspection of the High Pressure Compressor Rotor Assembly
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-31-00 601
601
72-CONTENTS R CES
Page 15 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT HPC ROTOR ASSEMBLY REPAIRS
________ CH/SE/SU 72-31-00
C _
PAGE ___________ ____ EFFECTIVITY 801
Repair of Broken Borescope Plug
801
Blend Repair of the High Pressure Compressor (HPC) Rotor Blades Stages 1-9
808
HPC FRONT STATOR ASSEMBLY DESCRIPTION AND OPERATION
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499
72-32-00 1
General
1
Description
1
Front Stator Casing
1
Vanes
1
Variable Vane Actuation
1
HPC FRONT STATOR ASSEMBLY INSPECTION/CHECK
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-32-00 601
72-CONTENTS R CES
Page 16 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Inspection/Check of the HPC Front Stator Assembly
HPC FRONT STATOR ASSEMBLY REPAIRS
CH/SE/SU ________
C _
____ EFFECTIVITY PAGE ___________ 601 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-32-00 801
Removal of the Inlet Guide Vane (IGV) and Stage 3 Vane Lever Arms or Bushings
801
Installation of the Inlet Guide Vane (IGV) and Stage 3 Vane Lever Arms or Bushings
806
Removal of the Actuation Ring Connecting Links
810
Installation of the Actuation Ring Connecting Links
814
Replacement of the Actuation Ring Flanged Bushing (Stages 1 and 2)
819
HPC REAR STATOR ASSEMBLY DESCRIPTION AND OPERATION
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099
72-33-00 1
General
1
Description
1
Casing
1
72-CONTENTS R CES
Page 17 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Vanes
__________________ COMBUSTION SECTION DESCRIPTION AND OPERATION
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-40-00 1
General
COMBUSTION CASE ASSEMBLY DESCRIPTION AND OPERATION
C _
1
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499
72-41-00 1
General
1
Description
1
Components
1
Ports
1
COMBUSTION CASE ASSEMBLY INSPECTION/CHECK
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-41-00 601
72-CONTENTS R CES
Page 18 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Borescope Inspection of the Combustion Chamber Liners, Dome Areas, HPT Nozzle Vanes and Shrouds (as far as visible through two opposite ports) Inspection/Check of the Combustion Case Assembly
COMBUSTION CASE ASSEMBLY REPAIRS
CH/SE/SU ________
____ EFFECTIVITY PAGE ___________ 601 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 603
001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499
801
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-41-00
Repairs of the Combustion Case Assembly
COMBUSTION CHAMBER ASSEMBLY DESCRIPTION AND OPERATION
C _
801
72-42-00 1
General
1
Description
1
Dome
1
Cowl
1
Liners
1
72-CONTENTS R CES
Page 19 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
COMBUSTION CHAMBER ASSEMBLY INSPECTION/CHECK
C _
PAGE ___________ ____ EFFECTIVITY
72-42-00 601
Borescope Inspection of the Combustion Chamber Liners and Dome Area
601
Borescope Inspection of the Outer Side of the Combustion Chamber Outer Liners
621
Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD
626
Borescope Inspection of the Inner Cowl Bolts of the Combustion Chamber
634
_______________ TURBINE SECTION DESCRIPTION AND OPERATION
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-50-00 1
General
1
High pressure turbine module
1
Low pressure turbine module
1
________________ TURBINE SECTION REMOVAL/INSTALLATION
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-50-00 401
001-049, 051-099 101-149, 151-199
72-CONTENTS R CES
Page 20 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Discard Life Limited Parts of HPT and LPT
HPT NOZZLE ASSEMBLY DESCRIPTION AND OPERATION
C _
PAGE EFFECTIVITY ____ ___________ 201-249, 251-299 301-399, 401-499 401 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-51-00 1
General
1
Description
1
Nozzle Segments
1
Inner Support
1
Aft Outer Support and Seal
1
HPT NOZZLE ASSEMBLY INSPECTION/CHECK
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299
72-51-00 601
Borescope Inspection of High-Pressure Turbine Nozzle Assembly
601
Borescope Inspection of High-Pressure Turbine Nozzle Assembly
612
72-CONTENTS R CES
Page 21 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
HPT ROTOR ASSEMBLY DESCRIPTION AND OPERATION
72-52-00
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 1
General
1
Description
1
Front Shaft
1
Disk
1
Rear Shaft
1
Front Outer Seal
1
Blades
1
HPT ROTOR ASSEMBLY INSPECTION/CHECK
Borescope Inspection of HPT Blades (from the front and the rear)
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-52-00 601
601
72-CONTENTS R CES
Page 22 Nov 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Borescope Inspection of HPT Blades (from the front and the rear)
CH/SE/SU ________
Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) HPT SHROUD AND STAGE 1 LPT NOZZLE ASSEMBLY DESCRIPTION AND OPERATION
1
1
HPT shroud and stage 1 LPT nozzle assembly
1
Description
1
HPT shroud and stage 1 LPT nozzle assembly
Borescope/Inspection of the Stage 1 Low-Pressure Turbine Nozzle Assembly
____ EFFECTIVITY PAGE ___________ 616 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 630 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 640 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-53-00
General
HPT SHROUD AND STAGE 1 LPT NOZZLE ASSEMBLY INSPECTION/CHECK
C _
1
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
051-099 151-199 251-299 401-499 051-099 151-199 251-299
72-53-00 601
601
72-CONTENTS R CES
Page 23 Nov 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Borescope/Inspection of the High-Pressure Turbine Shroud
LPT ROTOR/STATOR ASSEMBLY DESCRIPTION AND OPERATION
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499 609 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-54-00 1
General
1
The low pressure turbine (LPT) module is a 4-stage axial-flow turbine.
1
Description
1
LPT Stator Assembly
1
LPT Rotor Assembly
4
LPT ROTOR/STATOR ASSEMBLY INSPECTION/CHECK
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-54-00 601
Inspection of the Stage 1-3 Blades
601
Inspection of the Stage 4 Blades
622
72-CONTENTS R CES
Page 24 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Inspection of the Stage 2-4 Nozzle Segments
CH/SE/SU ________
Inspection of the Stage 2-4 Nozzle Segments Inspection of the Stage 1-4 Stationary Air Seals Optional Visual Inspection of the Stage 4 Blades from the Rear of the Engine Inspection of the Turbine Case
Inspection of the Turbine Case
General Visual Inspection of Piping of LPT Case Air Cooling General Visual Inspection of Piping of LPT Case Air Cooling
LPT ROTOR/STATOR ASSEMBLY REPAIRS
____ EFFECTIVITY PAGE ___________ 631 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 638 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 653 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 660 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 669 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 675 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 681 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 685 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-54-00 801
Replacement of the Broken Studs of EGT (T49.5) Sensor Bracket Assy
LPT SHAFT DESCRIPTION AND OPERATION
C _
801
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-55-00 1
001-049, 051-099
72-CONTENTS R CES
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
Page 25 Nov 01/08
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
General
Low pressure turbine shaft
Description
Low pressure Turbine Shaft
No. 4 Bearing
No. 5 Bearing
LPT SHAFT MAINTENANCE PRACTICES
Inspection/Check of the Low
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 5 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 5 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-55-00 201
Replacement of LPT Shaft Plug O-rings
LPT SHAFT INSPECTION/CHECK
C _
201
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049,
051-099 151-199 251-299 401-499 051-099
72-55-00 601
601
72-CONTENTS R CES
Page 26 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Pressure Turbine Shaft Assembly
CH/SE/SU ________
TURBINE FRAME ASSEMBLY DESCRIPTION AND OPERATION
72-56-00
C _
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 1
Turbine Frame with Radial Struts
1
No. 5 Bearing Support for Turbine Frame with Radial Struts
10
Turbine Frame with Tangential Non Symetrical Section Struts No. 5 Bearing Support for Turbine Frame with Tangential Non Symetrical Section Struts Turbine Frame with Tangential Symetrical Section Struts
10
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-105, 201-207, 001-049, 101-105, 201-207, 051-051,
14
051-051,
16
No. 5 Bearing Support for Turbine Frame with Tangential Symetrical Section Struts
17
106-149, 208-249, 301-399, 106-149, 208-249, 301-399,
155-199 251-299 401-499 155-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099
General
1
Description
1
TURBINE FRAME ASSEMBLY REMOVAL/INSTALLATION
CES
052-099 151-154
72-56-00 401
Removal of the Flame Arrestor and Flange Assembly
401
Installation of the Flame Arrestor
408
72-CONTENTS R
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 052-099 151-154
Page 27 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT and Flange Assembly
CH/SE/SU ________
Removal of the Oil Inlet Cover Assembly Installation of the Oil Inlet Cover Assembly
TURBINE FRAME ASSEMBLY INSPECTION/CHECK
PAGE EFFECTIVITY ____ ___________ 101-149, 151-199 201-249, 251-299 301-399, 401-499 414 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 427 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-56-00 601
Inspection/Check of the Turbine Frame Assembly
TURBINE FRAME ASSEMBLY CLEANING/PAINTING
C _
601
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-56-00 701
Cleaning of the Oil Inlet Cover
701
Cleaning of the Aft Sump Oil Supply Tube
705
Cleaning of the Aft Sump Oil Scavenge Tube
710
TURBINE FRAME ASSEMBLY REPAIRS
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-56-00 801
001-049, 051-099 101-149, 151-199
72-CONTENTS R CES
Page 28 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
Replacement of Defective Studs
Replacement of Defective or Missing Thermal Insulation Blankets (On Radial Struts TRF Only) Replacement of the Oil Supply Tube Assembly
_______________________ ACCESSORY DRIVE SECTION DESCRIPTION AND OPERATION
PAGE EFFECTIVITY ____ ___________ 201-249, 251-299 301-399, 401-499 801 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 805 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 811 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-60-00 1
General
INLET GEARBOX ASSEMBLY DESCRIPTION AND OPERATION
C _
1
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-61-00 1
General
1
Description
1
Horizontal Bevel Gear
1
Radial Bevel Gear
1
72-CONTENTS R CES
Page 29 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________ Thrust Bearing (No. 3 Ball)
Roller Bearing (No. 3 Roller)
TRANSFER GEARBOX ASSEMBLY DESCRIPTION AND OPERATION
C _
____ EFFECTIVITY PAGE ___________ 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 1 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-62-00 1
General
1
Description
1
Radial Drive Shaft Assembly
1
TGB Assembly
1
TRANSFER GEARBOX ASSEMBLY REMOVAL/INSTALLATION
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-62-00 401
Removal of the Transfer Gearbox Module
401
Installation of the Transfer Gearbox Module
418
72-CONTENTS R CES
Page 30 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
CH/SE/SU ________
TRANSFER GEARBOX ASSEMBLY INSPECTION/CHECK
PAGE ___________ ____ EFFECTIVITY
72-62-00 601
Inspection/check of the Transfer Gearbox Assembly
ACCESSORY GEARBOX ASSEMBLY DESCRIPTION AND OPERATION
C _
601
1
1
Description
1
Horizontal Drive Shaft Assembly
1
AGB Housing
1
Gear Train
8
Disengagement/Engagement of the Horizontal Drive Shaft
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249,
051-099 151-199 251-299 401-499 051-099 151-199 251-299
72-63-00
General
ACCESSORY GEARBOX ASSEMBLY MAINTENANCE PRACTICES
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
72-63-00 201
201
72-CONTENTS R CES
Page 31 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ SUBJECT _______
ACCESSORY GEARBOX ASSEMBLY REMOVAL/INSTALLATION
CH/SE/SU ________
C _
PAGE EFFECTIVITY ____ ___________ 301-399, 401-499
72-63-00 401
Removal of the Handcranking Drive Cover
401
Installation of the Handcranking Drive Cover
408
Removal of the Accessory Gearbox Assembly
412
Installation of the Accessory Gearbox Assembly
441
ACCESSORY GEARBOX ASSEMBLY INSPECTION/CHECK
Replacement of a Sealol Seal (Typical)
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
051-099 151-199 251-299 401-499 051-099 151-199 251-299 401-499
72-63-00 601
Inspection/Check of the Accessory Gearbox Assembly
ACCESSORY GEARBOX ASSEMBLY REPAIRS
001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399, 001-049, 101-149, 201-249, 301-399,
601
72-63-00 801
801
72-CONTENTS R CES
Page 32 Feb 01/09
C F M 56-5B CHAPTER 72 __________ ENGINE TABLE OF CONTENTS _________________ _______ SUBJECT Replacement of a Magnetic Seal (Typical) Replacement of a Magnetic Seal (IDG and Starter Drive Pads).
CH/SE/SU ________
C _
____ EFFECTIVITY PAGE ___________ 813 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499 822 001-049, 051-099 101-149, 151-199 201-249, 251-299 301-399, 401-499
72-CONTENTS CES
Page 33 Feb 01/09
C F M 56-5B ENGINE - GENERAL - DESCRIPTION AND OPERATION ____________________________________________ 1. _______ General (Ref. Fig. 001, 002, 003, 004) The engine is a dual-rotor, variable stator, high bypass ratio turbo fan power plant. The 9 stage high pressure compressor is driven by 1 stage high pressure turbine, and the integrated front fan and booster is driven by 4 stage low pressure turbine. An annular combustor converts fuel and compressor discharge air into energy to provide engine thrust part through primary exhaust and to drive the turbines. The accessory drive system extracts energy from the high pressure rotor to drive the engine accessories and the engine mounted aircraft accessories. Reverse thrust for braking the aircraft after landing is supplied by an integrated system which acts on the fan discharge airflow (Ref. 78-00-00). 2. Engine ______________ Modules The principal modules of the engine are fan and booster, high pressure compressor, combustor chamber, high pressure turbine, low pressure turbine and accessory drive gearbox. Detailed descriptions of the components of each section are given in corresponding sections of this document. The description of each engine module is as follows: A. Fan/Booster Rotor The fan rotor consists of one full diameter booster for the secondary flow single stage fan and a smaller 4 Stage booster for the core engine flow. The fan and the booster are mounted on a common internal concentric shaft driven by the fan pressure turbine. Two bearings support the fan assembly in the frame. B. Fan/Booster Stator Fixed stator vanes are provided for both, the fan and booster rotor. The fan casing, in which the stator is mounted has provision for blade containment forward of and in the plan of the fan rotor. The casing is supported by the fan frame and supports the accessory drive gearbox.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Engine LH Side Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Engine RH Side Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
Engine Schematic Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
Major External Dimensions Figure 004 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B C. Fan Frame The fan frame is one of the major structural and aerodynamic components of the engine. Aerodynamically the fan frame forms the inner and outer flow passage of the fan airstream as well as the core airstream. Structurally, it carries inlet cowl loads, supports the fan casing, the two fan bearings and the core engine forward bearing; it contains the forward engine mount, it houses the accessory drive power take off gearbox and radial drive shaft; it contains the variable bypass valves between the booster and high pressure compressor; it supports the transfer and accessory gearboxes; and provides the mounting surfaces for fan-stream acoustic panels. The fan frame also serves as the forward support for the compressor. D. Compressor Rotor The compressor is a nine stage axial flow assembly. The rotor consists of the stage 1 and 2 discs which form a spool, a separately attached stage 3 disc and a spool containing stage 4 - 9 discs. Stage 1, 2 and 3 have axial dovetail slots and stage 4 - 9 blades are retained in circumferential slots. All blades are individually replaceable without spool disassembly. E. Compressor Stator All 9 stages of the compressor stator are shrouded. The Inlet Guide Vanes (IGV) and the first 3 stages of the compressor are variable. The casing is composed of two semi cylindrical halves, permitting a quick access to the core engine compressor. F. Combustor A step diffuser is incorporated upstream of the combustor for reduction of the combustor sensitivity to the compressor velocity profile. The combustor can be replaced without disturbing the fuel nozzles. The combustor casing provides structural support for the combustor, the compressor Outlet Guide Vanes (OGV) the High Pressure (HP) stator and shrouds, and the seals for Compressor Discharge Pressure (CDP). G. High Pressure Turbine The High Pressure Turbine (HPT) is an air cooled single stage high energy turbine. Rotor blades are individually replaceable without the need for rotor disassembly or rebalancing. H. Low Pressure Turbine The Low Pressure Turbine (LPT) consists of 4 and half stages of blades and vanes. The first stage nozzle vane is cooled and provides cooling air for the high pressure and low pressure turbine discs. The LPT drives the fan rotor through the inner concentric shaft and is aerodynamically coupled to the high pressure system. The LPT casing is a 360 degrees design to provide structural continuity.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 6 Nov 01/08
C F M 56-5B J. Turbine Frame The turbine frame is located aft the LPT. It contains the aft LPT bearing, and supports the primary exhaust system. It contains the engine rear mount fitting. K. Accessories and Accessory Drives Engine and aircraft accessories are mounted on the accessory gearbox which is located on the outside of the lower part of the casing and driven through a radial shaft at 6 oclock position. Power for the engine and aircraft accessories is extracted from the HPC rotor shaft through an inlet gearbox and the radial drive shaft. Quick Attach/Detach (QAD) accessory mounting flanges are provided for the engine accessories. 3. Bearings __________________ and Seals (Ref. Fig. 005, 006, 007) A. Bearings The engine rotors are supported by bearings installed in the sump cavities provided by the two frames. The forward sump is in the fan frame and is the location of bearings No. 1, No. 2 (fan/booster shaft) and No. 3 (HP shaft forward part). The aft sump is in the turbine rear frame where are bearings No. 4 (HP shaft aft part) and No. 5 (LP shaft aft part). B. Oil Distribution The bearings must be lubricated and oil is distributed to these components by nozzles. However, the oil must be retained within the engine, so seals of various types are provided to confine the oil and direct its recirculation. C. Seals Arrangement The arrangement of oil and air seals, the provisions for oil supply, oil scavenge, seal pressurization, sump vent subsystems produce a system known as a dry sump. Engine sumps are vented to ambient pressure through the center-vent tube which is contained in the LP shaft. D. Bearing Functions Bearings provide reduced rolling friction, support the rotors axially and radially within the engine structure, and position the rotors relative to the stators. The bearing must control the forces of gravity weight aerodynamic loads of pumping and turbine driving and gyroscopic loads due to aircraft maneuvers.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 7 Nov 01/08
C F M 56-5B
Forward Sump Figure 005 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 8 Nov 01/08
C F M 56-5B
Aft Sump Figure 006 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 9 Nov 01/08
C F M 56-5B
Sump Venting System Figure 007 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 10 Nov 01/08
C F M 56-5B 4. ________________________________________________________________________ Engine Boroscope Inspection Port Provisions, Location and Identification (Ref. Fig. 008, 009, 010) There is a total of 22 borescope port provisions along the engine. The most important number of them is found on the engine right side, mostly between the 4 and 5 oclock positions, aft looking forward. Their location and identification are as follows: A. On the Inner Wall (Fairing) of the Fan Bypass Duct (Ref. Fig. 008) There are two (8 mm dia) borescope port provisions. From front to rear, the first port, identified S03, is just below the 3 oclock position, between two OGVs. The second port, identified S05, is near the 4 oclock position, just in front of the Variable Bleed Valves (VBVs) plane. Refer to ATA 72-21-00 for the internal parts and areas you can fully or partially see through these two borescope port provisions. B. On the High Pressure Compressor (HPC) Front and Rear Casings (Ref. Fig. 009, 010) There are nine (8 and 10 mm dia) borescope port provisions, located between the 4 and 5 oclock positions, aft looking forward. From the HPC inlet plane IGV to the last stage (ninth) of the HPC, they are identified as follows: - S1, S2, S3, S4, S5, S6, S7, S8 and S9. Refer to ATA 72-31-00 for the internal parts and airfoil areas you can see through these 9 borescope port provisions. C. On the Combustion Case (Ref. Fig. 008, 009, 010) There are six borescope port provisions around the combustion case: - S12, S13, S14, S15, located in the same plane, at the 1, 3, 6 and 10 oclock positions respectively, and immediately in front of the fuel manifold, - S16 and S17, located in the same plane, at approximately the 5:30 and 8:30 oclock positions respectively, and immediately in front of the combustion case aft flange. The two ports which install the two spark igniters on the combustion case can also be used as borescope port provisions. These ports are identified as S10 and S11. They are in the same plane, at the 4 and 8 oclock positions respectively. The S10, S11, S12, S13, S14 and S15 ports permit the borescope inspection of the HPT rotor blades (S10 and S11), the combustion chamber and the HPT nozzle. The S16 and S17 ports permit the borescope inspection of the HPT shrouds, the stage 1 LPT nozzle segments and leading edge of stage 1 LPT rotor blades.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 11 Nov 01/08
C F M 56-5B
Engine Borescope Port Provisions - Location and Identification on Left Side Figure 008 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 12 Nov 01/08
C F M 56-5B
Engine Borescope Port Provisions - Location and Identification on Right Side Figure 009 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 13 Nov 01/08
C F M 56-5B
Borescope Port Provisions - Location and Engine Station Figure 010 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 14 Nov 01/08
C F M 56-5B Refer to ATA 72-41-00, 72-42-00, 72-51-00, 72-52-00 and 72-53-00 for the internal parts and the areas you can, fully or partially, see through the six normal borescope port provisions of the combustion case and the two spark igniter ports. NOTE : The use of the spark igniter ports as borescope provisions (S10 ____ and S11) necessitates the removal of the spark igniters (Refer to ATA 74-21-30). D. On the Low Pressure Turbine Case (Ref. Fig. 009, 010) There are three borescope port provisions on the LPT case. Location at the 5 oclock position approximately. From front to rear, they are identified S18, S19 and S20. Refer to ATA 72-54-00 for the internal parts and areas you can, fully or partially, see through these borescope port provisions. NOTE : The borescope ports S16 and S17 must be used to inspect: ____ - the LPT nozzle, stage 1 (Refer to ATA 72-53-00), - the leading edge and tip shroud of LPT rotor blades, stage 1 (Ref. to ATA 72-54-00).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 15 Nov 01/08
C F M 56-5B ENGINE - GENERAL - MAINTENANCE PRACTICES ________________________________________ TASK 72-00-00-917-002 Engine Tubes, Hoses, and Fittings 1. __________________ Reason for the Job This section gives the general inspection and removal/installation instructions for engine tubes, hoses, and fittings. NOTE : Assemblies covered by this task do not contain parts that have a ____ regular replacement or inspection schedule. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific
container protective caps protective closures
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
Material No.
CP5070
Material No.
CP8001
Material No.
CP8002
* engine oil (Ref. 70-30-00) * vaseline (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 201 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-21-00-918-002 71-00-00-710-006 73-11-30-200-002 72-00-00-991-314 72-00-00-991-315 72-00-00-991-316
Seals (Preformed Packings and O-rings) and Gaskets Minimum Idle Check Inspection/Check of the Fuel Manifold Assembly Fig. 201 Fig. 202 Fig. 203
3. __________ Job Set-up Subtask 72-00-00-869-076 A. Not Applicable 4. Procedure _________ (Ref. Fig. 201/TASK 72-00-00-991-314, 202/TASK 72-00-00-991-315, 203/TASK 72-00-00-991-316) Subtask 72-00-00-210-073 A. If a tube, hose, or fitting on the engine has apparent damage, do the inspection that follows: NOTE : The limits in this table are general and they do not replace the ____ limits on components given in this manual. NOTE : The inspection of the fuel manifold is given in (Ref. TASK 73-11____ 30-200-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 202 Nov 01/08
C F M 56-5B
Tube and Hose Seating Surfaces Figure 201/TASK 72-00-00-991-314 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 203 Nov 01/08
C F M 56-5B
Swivel Flanged Connectors Figure 202/TASK 72-00-00-991-315 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 204 Nov 01/08
C F M 56-5B
Hose Assembly Inspection Areas Figure 203/TASK 72-00-00-991-316 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 205 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Tubing for: A. Splits, cracks or kinks
Not serviceable
Replace tube.
B. Dents or flat areas
Any amount when the contour is not more than 20 percent of original tube OD
Replace tube.
C. Nicks or scores on drain lines, drain shrouds, and scavenge lines, does not include aft sump oil scavenge line
Max. depth not more than 0.010 in. (0.25 mm) after blending
Blend the nicks or scores.
D. Nicks or scores on all other fuel, air and oil lines and aft sump oil scavenge line
Max. depth not more than 0.005 in. (0.13 mm) after blending
Blend the nicks or scores.
A. Scratches in circumference areas A and C
Any amount to 0.005 in. (0.13 mm) after removal of high metal
Remove high metal.
B. Scratches in circumference area B
Any amount not detectable using a 0.040 in. (1.02 mm) radius ball scribe
Remove high metal.
C. Axial scratches areas A and C
Any amount to 0.005 in. (0.13 mm) after removal of high metal
Remove high metal.
2. Seating surfaces of the fitting for: (Ref. Fig. 201/TASK 72-00-00-991-314)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 206 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------D. Axial scratches Not serviceable Replace tube. area B E. Nicks and pits area C
Any amount not more than 0.03 in. (0.8 mm) deep after blending
Blend depressions.
F. Nicks and pits areas A and B
Not serviceable
Replace tube.
G. Score marks in circumference of silver plated seating (mating) surfaces
Any amount when score mark does not go through parent metal
Replace tube.
H. Deformation in circumference (spreading) of tube/ferrule
Any amount when nut is free to turn
Replace tube.
J. Deformation in circumference (spreading) of flare nut
Any amount when nut is free to turn
Replace tube.
K. Axial deformation (dishing) of spherical seat fitting surface
Any amount if depth is constant and less than 0.005 (0.13 mm) to the initial surface
Replace tube.
A. Damaged corners
Any amount when the correct torque can be applied
Replace tube or hose.
B. Damaged thread
Total of one full thread or one continuous thread may be missing after chasing threads
Chase threads.
3. Tube and hose fitting nuts for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 207 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Lockwire hole torn Serviceable if one hole Replace tube or hose. out is still there 4. Swivel flange fittings for: (Ref. Fig. 202/TASK 72-00-00-991-315) A. Nicks or scratches on seating surface (surface B)
Not serviceable
Replace tube.
B. Nicks or scratches on mating surfaces (surfaces A and C)
Any nick or scratch not more than 0.020 in. (0.51 mm) deep after removal of high metal
Remove high metal.
C. Cracks
Not serviceable
Replace tube.
D. Seating surface (surface B) out-of-flat
0.006 in. (0.15 mm) out-of-flat
Replace tube.
E. Cracks that extend out from bolt holes
Permitted when not more than 2 bolt holes are cracked
Replace tube.
F. Weld joint cracks
Not serviceable
Replace tube.
Not serviceable
Replace tube or hose.
3 broken wires per plait and no more than 6 broken wires per assembly or per lineal foot (0.3 m) of hose
Replace hose.
5. Tube and hose assembly for: A. Leakage 6. Hose assemblies for: (Ref. Fig. 203/TASK 72-00-00-991-316) A. Broken hose braid
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 208 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Crimps Not serviceable Replace hose. C. Internal obstructions
Not serviceable
Remove obstruction or replace hose.
D. Cuts in fire sleeve areas A and B
Up to 3 cuts that do not cross per hose section if the length is not more than 0.20 in. (5.1 mm)
Replace hose.
NOTE : Area A is defined as follows L = 2.5 times the hose outer diameter ____ at both ends of the hose. Area B is the length between the two Areas A E. Tears in fire sleeve material area A
Not serviceable
Replace hose.
F. Tears in fire sleeve material area B
1 per hose section if the depth is not more than 0.010 in. (0.25 mm) and total area is not more than 0.40 in.2 (10.2 mm2)
Replace hose.
7. Tube mechanical joints (ferrules) for: A. Wear on end face
Any amount when O-ring retention flange is not deformed.
B. Nicks, dents and scratches on end face
Any amount when O-ring retention flange is not deformed after removal of high metal.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 209 Nov 01/08
C F M 56-5B Subtask 72-00-00-917-052 B. If necessary, replace the damaged tube as follows: WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE YOUR _______ CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. (1) Disassemble the connection. NOTE : Tubes can have oil or fuel in them as they are removed. Drain ____ the fluid into a container. (2) Install protective closures and protective caps on drilled passages, fuel lines, oil lines, air lines and open engine ports when parts are removed. (3) Use protection on the machined surfaces to prevent damage. (4) Remove and discard O-ring, if necessary. (5) Remove and do an inspection of the gaskets or seals, if necessary (Ref. TASK 70-21-00-918-002). (6) Do an inspection of the mating and threaded surfaces for cleanliness, contamination, scratches, dents, or other surface defects. (7) Do an inspection of the tube for satisfactory general condition and make sure that no damage has occurred. (8) Remove the closures and caps used for protection immediately before installation. (9) Lubricate new O-rings with vaseline (Material No. CP5070). (10) Apply a thin layer of engine oil (Material No. CP2442) to the gaskets and seals. (11) Install new O-rings, or serviceable gaskets, or seals, as necessary. (12) Install the tube but do not use force. A small elastic distortion is permitted to engage the connections.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 210 Nov 01/08
C F M 56-5B (13) Tightening method: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Tighten all end fittings and clamps with your hands. After a system is installed, torque the clamps first, then torque the end fittings. (14) Do not chafe tubes when you install the clamps. Attach the tube loosely with a clamp and position the tube to get the best clearance, then tighten the clamps. (15) Use the correct size clamps for the tube you install (16) Make sure there is clearance between the tube and each adjacent part. Correct minimum clearances are given in the table that follows: R R R R R R R R R R R R R R R R R R
------------------------------------------------------------------------------| | MINIMUM | | | AFFECTED EQUIPMENT | CLEARANCE | REMARKS | ------------------------------------------------------------------------------| STRUCTURE: | 0.25 in. | Not less than 0.06 in. | | Frames, bolts, | (6.4 mm) | (1.5 mm) clearance in | | rivets, webs, etc. | | 1 in. (25.4 mm) or | | | | less of clamping | | | | points | ------------------------------------------------------------------------------| MECHANISM: | 0.5 in. | Keep the clearance | | Actuators, linkages, etc. | (12.7 mm) | during the full | | | | travel of the | | | | mechanism | ------------------------------------------------------------------------------| GROUPED TUBING: | 0.19 in. | Clamp lines that | | Parallel runs, | (4.8 mm) | go across each other | | intersections, | | to get minimum | | etc. | | clearance of 0.12 in. | | | | (3.0 mm) | ------------------------------------------------------------------------------(17) Coupling nuts must turn freely by hand. (18) The mating surfaces of the flanges of the tube must be installed at 90 degrees to each other.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 211 Nov 01/08
C F M 56-5B (19) Make sure that fasteners are installed correctly when tightened to the specified value. (20) Safety the connection with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). Subtask 72-00-00-917-053 C. If necessary, replace the damaged hose as follows: WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE YOUR _______ CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. (1) Disassemble the connection. NOTE : Hoses can have oil or fuel in them as they are removed. Drain ____ the fluid into a container. (2) Install protective closures and protective caps on drilled passages, fuel lines, oil lines, air lines and open engine ports when parts are removed. (3) Remove and discard O-rings, if necessary. (4) Remove and do an inspection of the gaskets or seals, if necessary (Ref. TASK 70-21-00-918-002). (5) Do an inspection of the mating and threaded surfaces for cleanliness, contamination, scratches, dents or other surface defects. (6) Do an inspection of the hose for satisfactory general condition and make sure that no damage has occurred. (7) Remove the protective closures and caps immediately before installation. (8) Lubricate new O-rings with vaseline (Material No. CP5070). (9) Apply a thin layer of engine oil (Material No. CP2442) to the gaskets and seals. (10) Install new O-rings, or serviceable gaskets, or seals, as necessary. (11) Do not bend or try to make the preformed hoses straight.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 212 Nov 01/08
C F M 56-5B (12) Tightening method: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Tighten all the end fittings and clamps with your hand. After a system is installed, torque the clamps first, then torque the end fittings. (13) Do not chafe hoses when you install the clamps. Attach the tube loosely with a clamp and position the hose to get the best clearance, then tighten the clamps. (14) Use the correct size clamps for the hose you install. A clamp that is too large will cause chafing. A clamp that is too small will cause a restriction. (15) Make sure there is clearance between the hose and each adjacent part. (16) Coupling nuts must turn freely by hand. (17) The mating surfaces of the flanges of the hose must be installed at 90 degrees to each other. (18) Make sure that fasteners are installed correctly when tightened to the specified value. (19) Safety the connection with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). Subtask 72-00-00-710-051 D. If fuel or oil lines were disconnected, do a minimum idle leak check and check for leaks (Ref. TASK 71-00-00-710-006).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 213 Nov 01/08
C F M 56-5B TASK 72-00-00-820-004 Air Flow Check of the Forward Sump Oil Supply Circuit 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
container of 0.5 USgal (2 l.) test rig warning notice Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) 1 ADAPTER, TEST RIG - AIR FLOW CHECK
856A3267
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP8001
Material No.
CP8002
* lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 214 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 71-00-00-000-042 71-00-00-400-042 71-00-00-710-006 71-00-00-820-002 71-13-00-010-040 71-13-00-410-040 72-00-00-991-317
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Removal of the Power Plant Installation of the Power Plant Minimum Idle Check Oil Circuit Air Flow Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Fig. 204
3. __________ Job Set-up Subtask 72-00-00-941-106 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-148 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 215 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 204/TASK 72-00-00-991-317) Subtask 72-00-00-280-070 A. Forward Sump Air Flow Check WARNING : USE PROTECTIVE GLOVES AND BE CAREFUL WITH OIL SPLASHES WHEN YOU _______ DISCONNECT OIL TUBES. HOT OIL CAN CAUSE DEEP BURNS. (1) Put a container of 0.5 USgal (2 l.) under the junction of the oil supply tube (10) and oil supply hose (20). (2) Cut and remove the lockwire which safeties the union nut of the oil supply hose (20) to the oil supply tube (10). (3) Disconnect the oil supply hose. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Disconnect the oil supply hose (20) from the oil supply tube (10). (4) Connect the test rig equipped with ADAPTER, TEST RIG - AIR FLOW CHECK (856A3267G02), to the oil supply tube (10). (5) TORQUE the union nut to between 225 and 275 lbf.in (2.54 and 3.10 m.daN). (6) Do the check of the forward sump oil supply circuit (Ref. TASK 71-0000-820-002). (7) If the measured flow rate is not within the limits, replace the power plant (Ref. TASK 71-00-00-000-042) and (Ref. TASK 71-00-00-400-042). (8) Disconnect the test rig from the oil supply tube (10). (9) Connect the oil supply hose (20) to the oil supply tube (10). (10) TORQUE the union nut to between 450 and 550 lbf.in (5.08 and 6.21 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 216 Nov 01/08
C F M 56-5B
Air Flow Check of the Forward Sump Oil Supply Circuit Figure 204/TASK 72-00-00-991-317 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 217 Nov 01/08
C F M 56-5B (11) Safety the union nut with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). Subtask 72-00-00-710-059 B. Do an idle check (Ref. TASK 71-00-00-710-006) and check for leaks. Subtask 72-00-00-610-053 C. Do a check of the oil level (Ref. TASK 12-13-79-610-002). 5. Close-up ________ Subtask 72-00-00-410-147 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 218 Nov 01/08
C F M 56-5B TASK 72-00-00-820-005 Air Flow Check of the AGB/TGB Oil Supply Circuit 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R R R
No No No No
specific specific specific specific
container of 0.5 USgal (2 l.) test rig warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) 1 ADAPTER, TEST RIG - AIR FLOW CHECK
No specific 856A3267
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
* graphite grease (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 219 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 71-00-00-710-006 71-00-00-820-002 71-13-00-010-040 71-13-00-410-040 72-63-00-000-003 72-63-00-400-003 72-00-00-991-318
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Minimum Idle Check Oil Circuit Air Flow Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Accessory Gearbox Assembly Installation of the Accessory Gearbox Assembly Fig. 205
3. __________ Job Set-up Subtask 72-00-00-941-107 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-149 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 220 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 205/TASK 72-00-00-991-318) Subtask 72-00-00-280-071 A. AGB/TGB Air Flow Check WARNING : USE PROTECTIVE GLOVES AND BE CAREFUL WITH OIL SPLASHES WHEN YOU _______ DISCONNECT OIL TUBES. HOT OIL CAN CAUSE DEEP BURNS. (1) Remove bolt (50), outer spring clip (20), inner spring clip (40), and plastic bushings (30), which attach the AGB/TGB oil supply tube (10) to the AGB bracket. (2) Put a container of 0.5 USgal (2 l.) under the junctions of the oil supply tube (10) to the AGB and to the lubrication unit. (3) Disconnect the oil supply tube. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Disconnect the oil supply tube (10) from the nipples of the AGB and lubrication unit. (4) Connect the test rig, equipped with ADAPTER, TEST RIG - AIR FLOW CHECK (856A3267G02), to the AGB nipple. (5) TORQUE the union nut to between 225 and 275 lbf.in (2.54 and 3.10 m.daN). (6) Do the check of the the AGB/TGB oil supply circuit (Ref. TASK 71-0000-820-002). (7) If the measured flow rate is not within the limits, replace the accessory gearbox module (Ref. TASK 72-63-00-000-003) and (Ref. TASK 72-63-00-400-003). (8) Disconnect the test rig from the AGB nipple. (9) Connect the AGB/TGB oil supply tube (10) to the AGB and lubrication unit nipples. Tighten by hand.
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Page 221 Nov 01/08
C F M 56-5B
Air Flow Check of the AGB/TGB Oil Supply Circuit Figure 205/TASK 72-00-00-991-318 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 222 Nov 01/08
C F M 56-5B (10) Lubricate the threads of bolt (50) with graphite grease (Material No. CP2101). (11) Attach the AGB/TGB oil supply tube (10) to AGB bracket with plastic bushings (30), inner spring clip (40), outer spring clip (20) and bolt (50). (12) Make sure that the EGB/TGB oil supply tube (10) is not strained. (13) TORQUE the bolt (50) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (14) TORQUE the union nuts to between 450 and 550 lbf.in (5.08 and 6.21 m.daN). Subtask 72-00-00-710-060 B. Do an idle check (Ref. TASK 71-00-00-710-006) and check for leaks. Subtask 72-00-00-610-054 C. Do a check of the oil level (Ref. TASK 12-13-79-610-002). 5. Close-up ________ Subtask 72-00-00-410-148 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
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Page 223 Nov 01/08
C F M 56-5B TASK 72-00-00-820-006 Air Flow Check of the Aft Sump Oil Supply Circuit 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No
specific specific specific specific specific
access platform container of 0.5 USgal (2 l.) test rig warning notice Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) 1 ADAPTER, TEST RIG - AIR FLOW CHECK
No specific 856A3267
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
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Page 224 Feb 01/10
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 71-00-00-710-006 71-00-00-820-002 71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-00-00-991-319
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Minimum Idle Check Oil Circuit Air Flow Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 206
3. __________ Job Set-up Subtask 72-00-00-941-108 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
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Page 225 Nov 01/08
C F M 56-5B Subtask 72-00-00-010-150 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-00-00-040-082 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-151 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 206/TASK 72-00-00-991-319) Subtask 72-00-00-820-051 A. Aft Sump Air Flow Check WARNING : USE PROTECTIVE GLOVES AND BE CAREFUL WITH OIL SPLASHES WHEN YOU _______ DISCONNECT OIL TUBES. HOT OIL CAN CAUSE DEEP BURNS. (1) Put a container of 0.5 USgal (2 l.) under the junctions of the oil supply tube (20). (2) Remove nuts (60) and (180), bolts (70) and (160) which attach clamps (80) and (170) to the oil supply tube (20). (3) Remove clamps (80), (170) and shields (90) and (190).
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Page 226 Nov 01/08
C F M 56-5B (4) Remove the aft sump oil supply tube as follows: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Remove the bolt (130) which attaches the clamps (120) and (140) to the bracket (150) on flange T. (b) Remove the nut (50) and the bolt (30) which attaches the clamps (40) and (110) to the bracket (100) on flange S. (c) Disconnect the oil supply tube (20) from the oil supply tube (10) and from the aft sump oil supply tube (30). (d) Remove oil supply tube (20). (5) Install a fitting reducer 0.750-16 and 0.5625-18 THD (19 and 14.3 mm) to the end of the aft sump oil supply tube (30). (6) Connect the test rig equipped with ADAPTER, TEST RIG - AIR FLOW CHECK (856A3267G02), to the fitting reducer. (7) TORQUE the union nuts to between to between 225 and 275 lbf.in (2.54 and 3.10 m.daN). (8) Do the check of the aft sump oil supply circuit (Ref. TASK 71-00-00820-002). (9) If the measured flow rate is not within the limits, do the cleaning of the oil inlet cover, and do the cleaning of the aft sump oil supply tube. (10) Disconnect the test rig from the fitting reducer. (11) Remove the fitting reducer from the aft sump oil supply tube (30). (12) Install the aft sump oil supply tube (20) as follows: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Connect the oil supply tube (20) to the oil supply tube (10) and to the aft sump oil supply tube (30).
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C F M 56-5B
Air Flow Check of the Aft Sump Oil Supply Circuit Figure 206/TASK 72-00-00-991-319- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 228 Nov 01/08
C F M 56-5B
Air Flow Check of the Aft Sump Oil Supply Circuit Figure 206/TASK 72-00-00-991-319- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 229 Nov 01/08
C F M 56-5B
Air Flow Check of the Aft Sump Oil Supply Circuit Figure 206/TASK 72-00-00-991-319- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 230 Nov 01/08
C F M 56-5B (b) Tighten the coupling nuts by hand. (c) Install clamps (120) and (170) on the oil supply tube (20). (d) Lubricate threads of bolt (30) and (130) with graphite grease (Material No. CP2101). (e) Attach clamps (120) and (140) to the bracket (150) on flange T, with bolt (130). (f) Attach clamps (40) and (110) to the bracket (100) on flange S, with bolt (30) and nut (50). (g) Make sure that the oil tube (20) is not strained. (h) TORQUE the bolt (30) and (130) to to between 45 and 50 lbf.in (0.50 and 0.56 m.daN). (i) TORQUE the coupling nuts of tubes (20) and (30) to to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (j) Lubricate threads of bolt (70) and (160) with graphite grease (Material No. CP2101). (k) Install shields (90) and (190) on couplings of the oil tube (20), with clamps (80) and (170), bolts (70) and (160), and nuts (60) and (180). NOTE : The nut (180) must be installed on the turbine frame side. ____ (l) TORQUE the nuts (60) and (180) to to between 45 and 50 lbf.in (0.50 and 0.56 m.daN). 5. Close-up ________ Subtask 72-00-00-410-149 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
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Page 231 Nov 01/08
C F M 56-5B Subtask 72-00-00-710-061 B. Do an idle check (Ref. TASK 71-00-00-710-006) and check for leaks. Subtask 72-00-00-610-055 C. Do a check of the oil level (Ref. TASK 12-13-79-610-002). Subtask 72-00-00-440-082 D. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-150 E. Close-up (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s). (3) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 232 Nov 01/08
C F M 56-5B ENGINE - GENERAL - SERVICING ____________________________ TASK 72-00-00-600-026 Recommendations for Engine Preservation 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-600-006 72-00-00-600-007 72-00-00-600-008 72-00-00-600-009 72-00-00-600-025 72-00-00-600-027 75-31-20-820-001
Preservation for a Period of up to 30 Days Preservation for a Period of 30 to 365 Days. Preservation Renewal Requirements. Procedure for Exceeded Long Term Preservation Period. Preservation for a Period of up to 90 Days Depreservation Set the Variable Bleed Valve Assembly to the Closed position
3. __________ Job Set-up Subtask 72-00-00-869-073 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-620-062 A. Engine preservation (1) The procedures that follow are recommended as the necessary minimum, to protect the CFM56 engine against corrosion, liquid and debris which go into the engine, and atmospheric conditions during periods of storage, and inactivity ; or which follow an engine-out ferry, or landing which follows an In Flight Shut Down (IFSD). These procedures are also recommended for installed engines on an inoperative aircraft or an engine not to be operated for more than thirty days.
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Page 301 Nov 01/08
C F M 56-5B (2) Preservation Tasks The recommended procedure for preservation of the engine changes depending upon the duration of inactivity, the type of preservation used, and if the engine is operable or non-operable. NOTE : Engines that can be started are considered operable. Engines ____ that for any reason cannot be started are considered non-operable. Preservation renewal procedures are also covered in this instruction. (3) Select the preservation procedure and use the schedule that follows: (a) Up to 30 days (Ref. TASK 72-00-00-600-006). (b) Up to 90 days (Ref. TASK 72-00-00-600-025). (c) 30 to 365 days (Ref. TASK 72-00-00-600-007). (d) Preservation renewal requirements (Ref. TASK 72-00-00-600-008). (e) Procedure for exceeded long term preservation (Ref. TASK 72-0000-600-009). (f) Depreservation (Ref. TASK 72-00-00-600-027). NOTE : There is no restriction on the number of times you can do ____ the preservation procedure again, as long as it is accomplished each year. (4) Preservation Program The preservation procedures in this section are recommended as a guide to determine what precautions must be applied to give the engine sufficient protection from the elements during periods of storage and inactivity. Engine preservation is a flexible program that should be implemented in such a manner as to conform with particular weather and storage conditions. You must pay more attention to the preservation program for inactive engines exposed to high humidity and/or large temperature changes, especially if they are near a salt water area. These definitely require more attention to preservation needs than those inactive engines stored in drier climates or less severe weather conditions. The preservation program for spare and/or stored engines must be scheduled before you implement the preservation renewal requirements and monitored regularly to make sure that the necessary action is implemented before expiration of the preservation period. Depending upon weather conditions and the condition of the engine protection equipment covers, the effectiveness of the preservation protection
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C F M 56-5B must be analysed and modified in order to keep the engine in serviceable condition. NOTE : You cannot preserve and place engines in storage and then ____ forget them. A correct plan (as given for an engine in revenue service) must be scheduled and then implemented. When you use desiccants they must be changed on a regular basis, based on the environmental conditions, to maintain the desiccant with a good protection life. It is recommended that the variable bleed valves (VBV) must be closed when the engine is to be preserved and stored or when you do maintenance in this area. This prevents the possibility of foreign objects going into the core engine inlet through the VBVs. For closure of the VBV doors, refer to (Ref. TASK 75-31-20-820-001).
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Page 303 Nov 01/08
C F M 56-5B TASK 72-00-00-600-006 Preservation for a Period of up to 30 Days 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A2930
forklift start cart 1 COVER-FITTED BARE QECD ENGINE SHIPPING
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2098
Material No.
CP2160
USA MIL-D-3464 desiccant bags (Ref. 70-30-00) USA MIL-LP-378 vapor barrier film (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-003 71-00-00-710-028 72-00-00-100-007 75-31-20-820-001 78-31-00-710-042 80-11-00-040-045
Engine Automatic Start Engine Shutdown Engine Dry-out and Re lubrication Set the Variable Bleed Valve Assembly to the Closed position Operational Test of the Thrust Reverser System Manually Operate the Starter Valve
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Page 304 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-00-00-869-070 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-620-057 A. Preservation for a Period of up to 30 days. CAUTION : IF ENGINE WAS FERRIED OR SUBJECTED TO AN IN FLIGHT SHUTDOWN _______ (IFSD), ENGINE MUST BE DRIED OUT AND RELUBRICATED WITHIN 24 HOURS PER DRY OUT PROCEDURE OF THIS SECTION. CAUTION : UNDER NO CIRCUMSTANCES SHALL PRESERVATIVE OIL OR EQUIVALENT BE _______ SPRAYED INTO THE ENGINE INLET, CORE COMPRESSOR OR TURBINE, OR ENGINE EXHAUST. DIRT PARTICLES DEPOSITED ON THE WETTED BLADES AND VANES MAY ADVERSELY AFFECT ENGINE PERFORMANCE DURING SUBSEQUENT OPERATION. (1) Operable Engine Preservation. (a) On-wing installed engines. 1 _
Start the engines (Ref. TASK 71-00-00-710-003) and let them become stable at ground idle for 15 to 20 minutes, followed by a thrust reverser cycle (Ref. TASK 78-31-00-710-042) then stop the engines (Ref. TASK 71-00-00-710-028). NOTE : You can ignore this step if it was done during the last ____ engine operation (flight cycle). Under these conditions, consider the engine is preserved for 30 days from time of last operation.
2 _
Cover entrance to fan cowling and exit openings.
(b) Engines installed on stand. CAUTION : OPERATION SHOULD BE CARRIED OUT IN A CONFINED SPACE _______ WITH SUFFICIENT VENTILATION AND ON A FLAT HORIZONTAL SURFACE. CAUTION : MAXIMUM TOWING SPEED IS 3MPH (5KM/H). _______
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Page 305 Nov 01/08
C F M 56-5B 1 _
Tow stand base (dolly) to an area with sufficient ventilation and a flat surface.
2 _
Carefully raise stand base with a forklift.
3 _
Remove the pins, raise and stow the four caster wheels of stand base.
4 _
Lower stand base to level surface, remove the forklift.
5 _
Attach the forward and aft caster wheels with pins.
6 _
Remove COVER-FITTED BARE QECD ENGINE SHIPPING (856A2930G01) or (856A2930G02) from the engine.
7 _
Do the engine motoring procedure at max motoring speed for 4 minutes and shut down. NOTE : When you do the engine motoring procedure on stand, you ____ can connect a start cart hose to the starter shutoff valve with a locally manufactured adapter (Ref. TASK 80-11-00-040-045).
8 _
Make sure that VBV doors are closed (Ref. TASK 75-31-20-820001).
9 _
Cover VBV grills with vapor barrier film (Material No. CP2160).
10 __
Cap or cover all strut, piping, accessory openings and electrical connections.
11 __
Seal front and back openings/exposed areas with vapor barrier film (Material No. CP2160). It is recommended that desiccant bags (Material No. CP2098) be placed on either side of the engine, but not in contact with the engine hardware.
12 __
Cover full engine with COVER-FITTED BARE QECD ENGINE SHIPPING (856A2930G01) and attach tightly in place.
13 __
Raise stand base with a forklift.
14 __
Deploy, lower and pin caster wheels of stand base.
15 __
Lower stand base, remove forklift.
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Page 306 Nov 01/08
C F M 56-5B 16 __
Tow stand base CAUTION : MAXIMUM TOWING SPEED IS 3MPH (5KM/H). _______ a _
Tow stand base (dolly) with engine to storage area.
(2) Preservation - Non-operable Engines (a) Dry out and relubricate engine (Ref. TASK 72-00-00-100-007) if engine was ferried or subjected to an IFSD. (b) If engine is non-operable, consider the engine is preserved for 30 days from time of last operation. (3) Make sure that VBV doors are closed (Ref. TASK 75-31-20-820-001). (4) Cover VBV grills with vapor barrier film (Material No. CP2160). (5) Cap or cover all strut, piping and accessory openings and electrical connections. (6) Seal front and back openings/exposed areas with vapor barrier film (Material No. CP2160). It is recommended that desiccant bags (Material No. CP2098) be placed on either side of the engine, but not in contact with the engine hardware. (7) Cover full engine with COVER-FITTED BARE QECD ENGINE SHIPPING (856A2782G01/G02), and attach tightly in place if in a trailer or stand. If on wing, cover entrance of fan cowling and exit opening of tailpipe.
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Page 307 Nov 01/08
C F M 56-5B TASK 72-00-00-600-025 Preservation for a Period of up to 90 Days 1. __________________ Reason for the Job You must do the preservation procedure at the end of engine operation or not earlier than one day before an engine return to shop, when the engine must not operate for a period up to 90 days. This procedure is only applicable to on-wing installed engines. 2. ______________________ Job Set-up Information A. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
Material No.
CP5067
Material No.
CP5075
* engine oil (Ref. 70-30-00) * lubrication system corrosion preventive oil (Ref. 70-30-00) * corrosion preventive additive (Ref. 70-30-00)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 71-00-00-710-003 71-00-00-710-028 78-31-00-710-042
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Engine Automatic Start Engine Shutdown Operational Test of the Thrust Reverser System
3. __________ Job Set-up Subtask 72-00-00-869-067 A. Not Applicable
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Page 308 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-00-00-620-058 A. Preservation for a Period of up to 90 days. CAUTION : IF ENGINE WAS FERRIED OR SUBJECTED TO AN IN FLIGHT SHUTDOWN _______ (IFSD), ENGINE MUST BE DRIED OUT AND RELUBRICATED WITHIN 24 HOURS PER DRY OUT PROCEDURE OF THIS SECTION. CAUTION : UNDER NO CIRCUMSTANCES SHALL PRESERVATIVE OIL OR EQUIVALENT BE _______ SPRAYED INTO THE ENGINE INLET, CORE COMPRESSOR OR TURBINE, OR ENGINE EXHAUST. DIRT PARTICLES DEPOSITED ON THE WETTED BLADES AND VANES MAY ADVERSELY AFFECT ENGINE PERFORMANCE DURING SUBSEQUENT OPERATION. Subtask 72-00-00-620-068 B. Operable Engine Preservation - Period of Up to 90 days. (1) Do the servicing of the oil tank with an approved mixture of engine oil (Material No. CP2442) and at least 5 percent of lubrication system corrosion preventive oil (Material No. CP5067) or, as an alternative, 7 percent corrosion preventive additive (Material No. CP5075) by volume (Ref. TASK 12-13-79-610-002). NOTE : In both cases, a minimum of 19 l (5 USgal) of oil mixture is ____ necessary for preservation motoring. (2) Start the engine (Ref. TASK 71-00-00-710-003) and let it become stable at ground idle for 15-20 minutes, followed by a thrust reverser cycle (Ref. TASK 78-31-00-710-042) then stop the engine (Ref. TASK 71-00-00-710-028). (3) Cover the entrance to fan inlet cowl and exit openings. NOTE : For a period of up to 90 days, the preservation of the fuel ____ system is not necessary.
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Page 309 Nov 01/08
C F M 56-5B Subtask 72-00-00-620-069 C. Alternative Procedure. Operable Engine Preservation one Day before the Preservation Plan-Period of Up to 90 days. (1) Do the servicing of the oil tank with an approved mixture of engine oil (Material No. CP2442) and at least 5 percent of lubrication system corrosion preventive oil (Material No. CP5067) by volume (Ref. TASK 12-13-79-610-002). NOTE : In this case a minimum of 19l (5 US gal) of oil mixture is ____ necessary for preservation motoring. NOTE : It is not permitted to use corrosion preventive additive ____ (Material No. CP5075) for this procedure. NOTE : In this case, it is not necessary to do the ground idle run. ____ (2) Cover the entrance to fan inlet cowl and exit openings. NOTE : For a period of up to 90 days, the preservation of the fuel ____ system is not necessary.
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C F M 56-5B TASK 72-00-00-600-007 Preservation for a Period of 30 to 365 Days. 1. __________________ Reason for the Job The preservation procedures are applied at the end of engine operation, before the engine goes back to the shop, and when the engine does not operate for a period of 30 to 365 days. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No No No No No R
specific specific specific specific specific specific specific specific
caps circuit breaker(s) safety clip(s) container 26.5 USgal (100 l) container 4 US gal (16 l) oil pressurizing cart plugs soft nose pliers Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 FADEC-ENGINE PRESERVATION FALSE METERING VALVE SIGNAL 1 COVER-FITTED BARE QECD ENGINE SHIPPING
856A1480 856A2930
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2098
Material No.
CP2160
Material No.
CP2442
Material No.
CP5066
Material No.
CP5067
USA MIL-D-3464 desiccant bags (Ref. 70-30-00) USA MIL-LP-378 vapor barrier film (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * fuel system corrosion preventive oil (Ref. 70-30-00) * lubrication system corrosion preventive oil (Ref. 70-30-00)
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Page 311 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP5075
* corrosion preventive additive (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-003 12-13-79-610-004 70-21-00-918-002 71-00-00-710-001 71-00-00-710-002 73-11-10-000-003 75-31-20-820-001 72-00-00-991-310 72-00-00-991-311 72-00-00-991-312
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Oil Tank Draining Draining of the Accessory Drive Section Seals (Preformed Packings and O-rings) and Gaskets Dry Motoring Check Wet Motoring Check Removal of the Fuel Pump and Filter Assembly Set the Variable Bleed Valve Assembly to the Closed position Fig. 301 Fig. 302 Fig. 303
3. __________ Job Set-up Subtask 72-00-00-865-054 A. Open, safety and tag this(these) circuit breaker(s): ------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION ------------------------------------------------------------------------------FOR 1000EM1 49VU FUEL/LP VALVE/MOT1/ENG1 1QG A08 121VU FUEL/LP VALVE/MOT2/ENG1 3QG M25 FOR 1000EM2 49VU FUEL/LP VALVE/MOT1/ENG2 2QG A09 121VU FUEL/LP VALVE/MOT2/ENG2 4QG M26
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C F M 56-5B 4. Procedure _________ (Ref. Fig. 301/TASK 72-00-00-991-310, 302/TASK 72-00-00-991-311, 303/TASK 72-00-00-991-312) Subtask 72-00-00-620-059 A. Preservation for a Period of 30 to 365 Days. CAUTION : IF ENGINE WAS FERRIED OR SUBJECTED TO AN IN FLIGHT SHUTDOWN _______ (IFSD), ENGINE MUST BE DRIED OUT AND RELUBRICATED WITHIN 24 HOURS PER DRY OUT PROCEDURE OF THIS SECTION. CAUTION : UNDER NO CIRCUMSTANCES SHALL PRESERVATIVE OIL OR EQUIVALENT BE _______ SPRAYED INTO THE ENGINE INLET, CORE COMPRESSOR OR TURBINE, OR ENGINE EXHAUST. DIRT PARTICLES DEPOSITED ON THE WETTED BLADES AND VANES MAY ADVERSELY AFFECT ENGINE PERFORMANCE DURING SUBSEQUENT OPERATION. (1) Operable Engine Preservation. CAUTION : DO NOT USE SILICONE BASE OILS IN THE FUEL SYSTEM. DAMAGE TO _______ THE ENGINE CAN BE CAUSED. (a) Drain the oil tank (Ref. TASK 12-13-79-610-003). (b) Do the servicing of the oil tank with a mixture of approved engine oil (Material No. CP2442) and 7 percent (by volume) corrosion preventive additive (Material No. CP5075) or with a mixture of approved engine oil (Material No. CP2442) and 5 percent (by volume) lubrication system corrosion preventive oil (Material No. CP5067) (Ref. TASK 12-13-79-610-002). A minimum of 19 l (5 USgal) of oil is necessary to do the motoring procedure of the engine during preservation. (c) When you do the engine motoring procedure without the accessories installed, make sure that the items that follow are installed. 1 _
Pad covers and gaskets on pads where accessories are normally installed.
2 _
Caps on the pad cavity drains to prevent the loss of engine oil.
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C F M 56-5B
Fuel Pump Inlet, PCR Port and LPTCC Fuel Supply Hose Location Figure 301/TASK 72-00-00-991-310 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
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C F M 56-5B
Fuel Draining Figure 302/TASK 72-00-00-991-311 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
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C F M 56-5B
Location of Fuel Pump Discharge Pressure Ports and Lubrication Unit Filters Drain Figure 303/TASK 72-00-00-991-312- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, Page 316 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-00-00
C F M 56-5B
Location of Fuel Pump Discharge Pressure Ports and Lubrication Unit Filters Drain Figure 303/TASK 72-00-00-991-312- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, Page 317 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-00-00
C F M 56-5B (d) Disconnect the fuel pump inlet tube. 1 _
Put a container 4 US gal (16 l) under the fuel pump inlet tube.
2 _
Remove the 4 bolts and the 4 washers which attach the fuel inlet tube to the fuel manifold duct. Let the fuel drain into the container.
3 _
Keep the gasket.
(e) Install a temporary line to the fuel pump inlet tube. Use the line to supply oil fuel system corrosion preventive oil (Material No. CP5066) at 50 psi (3.5 bar) maximum pressure. - The line is to be locally manufactured. For details: (Ref. Fig. 303/TASK 72-00-00-991-312) (f) Disconnect: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING _______ NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. 1 _
Disconnect the line from the PCR port on the HMU.
(g) Install a temporary hose drain line 118 in. (3 m) long from the HMU PCR port and put the hose to drain in a container 26.5 USgal (100 l) capacity. Attach the hose to prevent spillage. - The drain line is to be locally manufactured with a coupling tube welding P/N J382P06 (0.5625-18 diameter UNJF-3A Threads/material AMS 5645). (h) Do a dry motoring check for 30 seconds (Ref. TASK 71-00-00-710001). 1 _
Stop the engine motoring. Let the engine coast down.
(i) Remove the temporary drain line from the PCR port on the HMU.
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C F M 56-5B (j) Tighten coupling nut: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING _______ NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. 1 _
Install the PCR line to the PCR port. Torque coupling nut to between 180 and 200 lbf.in (2.03 and 2.26 m.daN).
(k) Do a wet motoring check for 5 seconds (Ref. TASK 71-00-00-710002) or until you see sprayed preservation fluid come out of the engine exhaust nozzle. Move the ENG MASTER control switch to OFF and motor for 2 minutes. NOTE : A minimum of 20 quarts (19 liters) of fuel system ____ corrosion preventive oil (Material No. CP5066) is necessary for preservation motoring. (l) Stop the engine motoring. Let the engine coast down. (m) Turn the fan rotor: WARNING : DO NOT TURN THE FAN ROTOR BY HAND UNLESS YOU ARE _______ WEARING HEAVY PROTECTIVE GLOVES. MAKE SURE YOU DO NOT SLIP WHEN YOU TURN THE FAN ROTOR. INJURY TO PERSONS CAN BE CAUSED. 1 _
Pull the fan rotor through a minimum of 2 complete turns if it did not turn during motoring.
(n) Remove the temporary oil supply line from the fuel pump inlet tube. (o) Make sure that the gasket is clean and serviceable (Ref. TASK 7021-00-918-002). (p) Install the 4 washers and the 4 bolts which attach the fuel inlet tube to the fuel manifold duct. (q) TORQUE the bolts to between 65 and 85 lbf.in (0.73 and 0.96 m.daN). (r) Make sure that VBV doors are closed (Ref. TASK 75-31-20-820-001).
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Page 319 Nov 01/08
C F M 56-5B (s) Install vapor barrier film (Material No. CP2160) on all open areas. (t) Install caps or plugs on all open engine areas, such as struts, pipes and accessory pads. (u) Put desiccant bags (Material No. CP2098) on either side of the engine. Do not allow the desiccant to touch the engine surfaces. NOTE : Replace the desiccant at regular times based on ____ atmospheric and weather conditions. Put the desiccant in the engine so that it will give sufficient protection. Install it so that you will have to move a minimum quantity of engine protective covers. (v) Put COVER-FITTED BARE QECD ENGINE SHIPPING (856A2930G01/GO2) over all of the engine. Make sure it is tight. (w) Put a tag on the engine to show the engine is preserved. (2) Non-operable Engine Preservation. (a) Drain the fuel system as follows. Collect the fuel in a satisfactory container. 1 _
Disconnect the filter upstream (inlet) pressure sensing tube from the fuel filter housing (this is the lower sensing tube connected to the fuel filter differential pressure switch at its other end). Let the fuel drain from the disconnected port.
2 _
Disconnect the fuel supply line. Install a cap on the fuel pump inlet tube.
3 _
Remove the fuel filter drain plug. Let the fuel drain from the filter.
4 _
Remove the fuel pump drain plug. Let the fuel drain from the pump.
5 _
Remove the fuel filter element. Discard the element (Ref. TASK 73-11-10-000-003).
(b) Preserve the engine as follows: CAUTION : DO NOT USE SILICONE BASE OILS IN THE FUEL SYSTEM. _______ DAMAGE TO THE ENGINE CAN BE CAUSED.
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C F M 56-5B 1 _
Remove the PBP port plug from the fuel pump. Connect an oil pressurizing cart that contains fuel system corrosion preventive oil (Material No. CP5066) to the boost discharge pressure (PBP) port on the fuel pump. TORQUE the connector to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
2 _
Pump filtered (10 micron) oil into the fuel pump until it flows out of the fuel filter inlet pressure port and filter housing. Continue to pump the oil into the fuel pump until the oil that flows out does not have fuel mixed with it.
3 _
Connect the tube to the fuel filter inlet pressure port. TORQUE the coupling nut to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
4 _
Install a new fuel filter element. Install the bowl cover and drain plug. TORQUE the drain plug to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
5 _
Remove the fuel pump discharge (PHP) port plug.
6 _
Pump filtered (10 micron) oil into the PBP port until it flows out of the PHP port. Continue to pump the oil into the PBP port until the oil that flows out does not have fuel mixed with it.
7 _
Disconnect the cart from the PBP port.
8 _
Install the PBP port plug. TORQUE the plug to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
9 _
Connect the cart to the fuel pump discharge (PHP) port. TORQUE the connector to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
10 __
Disconnect: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE _______ COUPLING NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. a _
11 __
Disconnect the line (hose) from the HMU PCR port.
Install a temporary line to the PCR port and let it drain into the container.
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C F M 56-5B 12 __
R R
R R
Disconnect the HJ8 electrical harness from the receptacle connector identified CHANNEL B on the HMU. Use soft nose pliers, if necessary.
13 __
Connect the FADEC-ENGINE PRESERVATION FALSE METERING VALVE SIGNAL (856A1480G01) to the HMU receptacle identified CHANNEL B in order to open the Fuel Metering Valve (FMV) in the HMU and allow the preservation oil to flow to the fuel nozzles.
14 __
Pump filtered (10 micron) oil through the PHP port until it flows out of the PCR temporary line. Continue to pump oil through the PHP port until the oil that flows out does not have fuel mixed with it.
15 __
Remove TOOL FADEC-ENGINE PRESERVATION FALSE METERING VALVE SIGNAL (856A1480G01) from the HMU receptacle connector, CHANNEL B.
16 __
Remove the temporary drain line from the PCR port of the HMU.
17 __
Tighten coupling nut: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE _______ COUPLING NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. a _
Re-connect the PCR line to the HMU PCR port. TORQUE coupling nut to between 180 and 200 lbf.in (2.03 and 2.26 m.daN).
18 __
Re-connect the HJ8 electrical harness to the HMU receptacle connector identified CHANNEL B.
19 __
Disconnect: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE _______ COUPLING NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. a _
Disconnect the LPTCC fuel supply hose from the HMU.
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C F M 56-5B 20 __
Install a temporary line to the LPTCC port of the HMU and let it drain into the container. Pump filtered (10 micron) oil through the PHP port until it flows out of the LPTCC temporary line. Continue to pump oil through the PHP port until the oil that flows out does not have fuel mixed with it.
21 __
Disconnect the cart from the PHP port.
22 __
Re-install the PHP port plug on the fuel pump. TORQUE plug to between 45 and 55 lbf.in (0.50 and 0.62 m.daN).
23 __
Tighten coupling nut: CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE _______ COUPLING NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. a _
24 __
Remove the temporary line. Re-connect the LPTCC fuel supply hose to the HMU. TORQUE the coupling nut to between 180 and 200 lbf.in (2.03 and 2.26 m.daN).
Install caps on all fuel system ports. Make sure that all lines are connected and do not leak.
(c) Close the VBV doors (Ref. TASK 75-31-20-820-001). (d) Install vapor barrier film (Material No. CP2160) over the VBV bleed grills. (e) Drain the engine oil from the areas that follow: 1 _
Oil tank (Ref. TASK 12-13-79-610-003).
2 _
Accessory gearbox (AGB) (Ref. TASK 12-13-79-610-004).
3 _
Transfer gearbox (TGB) (Ref. TASK 12-13-79-610-004)
4 _
Supply filter on lubrication unit.
5 _
The oil supply lines between the lubrication unit and the sumps and gearboxes.
6 _
The scavenge oil lines between the sumps and gearboxes and the lubrication unit.
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C F M 56-5B 7 _
Drain the oil from the oil supply or scavenge lines that have caps installed and that do not connect back to the lubrication unit. Install the caps after the oil has been drained.
(f) Preserve the lubrication system as follows: 1 _
R R R R R
Pump a mixture of approved engine oil (Material No. CP2442) and 7 percent (by volume) corrosion preventive additive (Material No. CP5075) or a mixture of approved engine oil (Material No. CP2442) and 5 percent (by volume) lubrication system corrosion preventive oil (Material No. CP5067) into the areas that follow. Use a cart or hand pump equipped with a volume measuring device and pump the oil at a maximum pressure of 50 psi (3.5 bar). Turn the fan and core rotors by hand while you pump the oil in. Continue to turn the rotors for 1 minute after all of the oil is added.
----------------------------------------------------------------------------| LOCATION | OIL QUANTITY | ----------------------------------------------------------------------------| Oil supply to the AGB | 6 qt (6 liters) | ----------------------------------------------------------------------------| Oil supply to the TGB | 1 qt (1 liter) | ----------------------------------------------------------------------------| Oil supply to the forward sump | 2 qt (2 liters) | ----------------------------------------------------------------------------| Oil supply to the aft sump | 1 qt (1 liter) | ----------------------------------------------------------------------------| Oil tank | 18 qt (17 liters) | ----------------------------------------------------------------------------| Lube and scavenge pumps | Wet parts | | (Oil supply and scavenge discharge) | |
R ----------------------------------------------------------------------------2 _
Install caps on all of the lube system ports, pipes, drains, vents, etc.
(g) Install vapor barrier film (Material No. CP2160) on all of the open engine sections. (h) Install a tag on each section of the engine to show that the lubrication and fuel system is preserved.
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C F M 56-5B (i) Put COVER-FITTED BARE QECD ENGINE SHIPPING (856A2782G01/G02) over the engine. Make sure that it is tight to keep unwanted material out of the engine. 5. Close-up ________ Subtask 72-00-00-865-055 A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 1000EM1 1QG, 3QG FOR 1000EM2 2QG, 4QG
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C F M 56-5B TASK 72-00-00-600-008 Preservation Renewal Requirements. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-100-007 72-00-00-600-006 72-00-00-600-007 72-00-00-600-025
Engine Dry-out and Preservation for a Preservation for a Preservation for a
Re lubrication Period of up to 30 Days Period of 30 to 365 Days. Period of up to 90 Days
3. __________ Job Set-up Subtask 72-00-00-869-069 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-620-060 A. Preservation renewal requirements (1) Period up to 30 Days- Operable Engine (a) Two (2) renewals are allowed (Ref. TASK 72-00-00-600-006). (2) Period up to 30 Days - Non-operable engine NOTE : No renewal is allowed, the engine components should be ____ preserved (Ref. TASK 72-00-00-600-025) (Split engine or Engine Modules).
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C F M 56-5B (3) Period up to 90 Days - Operable Engine NOTE : Before represervation, it is recommended to prelubricate ____ engine sumps by hand-pumping oil through disconnected oil supply lines at lube unit and prelubricate lube unit by hand-pumping oil (Ref. TASK 72-00-00-100-007). (a) One (1) renewal is allowed (Ref. TASK 72-00-00-600-025). (4) Period 30 to 365 days - Operable Engine (a) Repeat the full procedure. Refer to the original 30 to 365 days preservation procedure (Ref. TASK 72-00-00-600-007). 1 _
Make sure that the engine is safely attached and protective cover is correctly in place.
(5) Period 30 to 365 days. Non-operable Engine (a) No renewal is allowed, engine must be serviced and operable.
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C F M 56-5B TASK 72-00-00-600-009 Procedure for Exceeded Long Term Preservation Period. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information Not Applicable 3. __________ Job Set-up Subtask 72-00-00-869-071 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-620-061 A. If the engine preservation period is expired, refer to your CFMI Representative for instruction. NOTE : An engineering analysis must be used to analyse the situation ____ applicable to each special case. Some parameters are to be analysed such as total time after the preservation time limit, engine storage location and condition, humidity level, temperature variation, dessicant replacement interval, etc...
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C F M 56-5B TASK 72-00-00-600-027 Depreservation 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 12-13-79-610-003 12-13-79-610-004 71-00-00-710-001 71-00-00-710-002
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Oil Tank Draining Draining of the Accessory Drive Section Dry Motoring Check Wet Motoring Check
3. __________ Job Set-up Subtask 72-00-00-869-072 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-630-051 A. Depreservation (1) Remove all moisture barrier material, seals, caps, covers, etc., as applicable, from the engine. (2) Connect fuel supply to the engine, and reconnect oil supply and scavenge lines if applicable. (3) Drain oil tank (Ref. TASK 12-13-79-610-003). NOTE : For an operable engine which is preserved for a period of up ____ to 90 days, this step is not necessary.
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C F M 56-5B (4) Drain accessory drive assembly (Ref. TASK 12-13-79-610-004). NOTE : For an operable engine which is preserved for a period of up ____ to 90 days, this step is not necessary. (5) Fill the oil tank (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-1379-610-002). NOTE : For an operable engine which is preserved for a period of up ____ to 90 days, do a check for oil tank level and fill the tank, if necessary (Ref. TASK 12-13-79-610-002). (6) Do a wet motoring of the engine (Ref. TASK 71-00-00-710-002). (7) Do one or more dry motoring operations to remove the remaining fuel (Ref. TASK 71-00-00-710-001).
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C F M 56-5B ENGINE - GENERAL - INSPECTION/CHECK ___________________________________ TASK 72-00-00-200-006 Inspection/Check of Foreign Object Damage (FOD) (Bird Strike Included) WARNING : THERE IS A POSSIBLE HEALTH RISK TO PERSONNEL WHO DO MAINTENANCE TASKS _______ AFTER A BIRD STRIKE. THE SAFETY MEASURES THAT FOLLOW ARE RECOMMENDED: - USE DISPOSABLE GLOVES. - USE A DISPOSABLE COVERALL IF THERE IS A RISK OF BODY CONTACT WITH THE BIRD REMAINS. - DO NOT USE PRESSURIZED AIR OR WATER TO CLEAN THE PARTS WHICH WERE IN CONTACT WITH THE BIRD. - REMOVE THE BIRD REMAINS AND PUT THEM IN A PLASTIC BAG. - DO NOT TOUCH YOUR FACE, EYES, NOSE, ETC. WITH YOUR GLOVES. - REMOVE THE GLOVES AND THE DISPOSABLE COVERALL AND PUT THEM IN THE SAME PLASTIC BAG AS THE REMAINS. SEAL THE BAG. - DISCARD THE BAG AS YOU DO FOR USUAL GARBAGE. - CAREFULLY WASH YOUR HANDS WITH SOAP AND WATER. NOTE : In any case, operators and maintenance personnel should comply with the ____ recommendations of the local medical authorities. The requirements of the relevant medical authority take precedence over any CFM guidelines in these matters and their advice must always be sought. 1. __________________ Reason for the Job You must do a visual inspection and, when applicable, a borescope inspection when unwanted materials (foreign objects) have gone into the engine. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
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C F M 56-5B B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-008 71-13-00-010-040 71-13-00-410-040 72-21-00-210-005 72-21-00-210-009 72-21-00-290-003 72-23-00-210-004 72-31-00-290-002 72-42-00-290-005 72-54-00-290-006 73-21-40-210-002 78-30-00-081-041 78-30-00-481-041
R
78-36-00-010-040 78-36-00-410-040 72-00-00-991-313
Power Assurance Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Inspection/Check of the Spinner Cone Inspect Fan Rotor Blades Installed on the Fan Disk Borescope Inspection of the Booster Rotor Blades, Stages 2,3,4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5 Visual Inspection of the Fan Frame Assembly Inspection of the High Pressure Compressor Rotor Assembly Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD Inspection of the Stage 4 Blades Visual Inspection of the T12 Temperature Sensor Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601
3. __________ Job Set-up Subtask 72-00-00-941-067 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
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Page 602 Feb 01/09
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-074 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-059 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-079 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-00-00-210-062 A. Visual Inspection NOTE : Visual inspection must be done without part removal. ____ (1) Possible damage to the spinner front and rear cones (Ref. TASK 72-2100-210-005). (2) General condition of the fan rotor blades (Ref. TASK 72-21-00-210009). (3) Wear of abradable material in fan inlet case (Ref. TASK 72-23-00-210004). (4) Condition of acoustical panels that may have been damaged as a result of interference with blade tip (Ref. TASK 72-23-00-210-004). (5) Condition of splitter fairing and booster inlet guide vanes (IGV) (Ref. TASK 72-23-00-210-004) and (Ref. TASK 72-21-00-210-005).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B (6) Condition of fan outlet guide vanes (OGV) and seals of fan OGV inner shroud (Ref. TASK 72-23-00-210-004). (7) Damage to T12 sensor probe (Ref. TASK 73-21-40-210-002). (8) Condition of exhaust and stage 4 LP turbine blades (Ref. TASK 72-5400-290-006). Subtask 72-00-00-280-057 B. Gaspath Inspection (1) FOD associated with normal engine parameters. NOTE : The borescope inspection may be delayed 25 hours or 10 cycles ____ (whichever comes first) provided FOD did not result in missing material to the fan blades. Service extension is only permitted on one engine in the event of a dual engine FOD. (a) Do the step that follows if one or more of these conditions apply: - FOD event has resulted in fan blade missing material/fan blade damage beyond serviceable limits. - FOD event struck fan blades radially inward of mid span shroud. - Evidence of debris has entered the booster inlet, ie: damage or debris on spinner front and rear cones, stage 1 booster vane or splitter fairing. 1 _
Do a borescope inspection of the HPC stages 1, 3 and 8 (Ref. TASK 72-31-00-290-002).
2 _
If damage is found inspect the other stages (Ref. TASK 72-3100-290-002).
3 _
Do a borescope of the combustion chamber dome assembly after a bird strike/ingestion event (Ref. TASK 72-42-00-290-005).
4 _
If the engine is PRE CFM SB 72-0418, do a borescope inspection of the stage 5 booster blades (Ref. TASK 72-21-00-290-003). Examine carefully the concave and convex sides of stage 5 booster blades in area E. (Ref. Fig. 601/TASK 72-00-00-991-313) Examine carefully blades around blade locks area.
R R R R R R R
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Feb 01/09
C F M 56-5B
INTENTIONALLY BLANK
R 72-00-00 CES
Page 605 Nov 01/09
C F M 56-5B
PS3 Line Figure 601/TASK 72-00-00-991-313- 14 (SHEET 1)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Feb 01/09
C F M 56-5B
PS3 Line Figure 601/TASK 72-00-00-991-313- 24 (SHEET 2)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Feb 01/09
C F M 56-5B
PS3 Line Figure 601/TASK 72-00-00-991-313- 34 (SHEET 3)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Feb 01/09
C F M 56-5B
PS3 Line Figure 601/TASK 72-00-00-991-313- 44 (SHEET 4)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Feb 01/09
C F M 56-5B (2) FOD associated with abnormal engine parameters. (a) If FOD event was associated with surge, stall or flameout, do the steps which follow: 1 _
Do a borescope inspection of the booster (Ref. TASK 72-21-00290-003). - If the engine is PRE CFM SB 72-0418, do a borescope inspection of the stage 5 examine carefully the concave and convex sides of stage 5 booster blades in area E (Ref. Fig. 601/TASK 72-00-00-991-313) and blades around blade locks area.
2 _
Do a borescope inspection of the HPC stages 1, 3 and 8 (Ref. TASK 72-31-00-290-002).
3 _
If damage is found inspect the other stages (Ref. TASK 72-3100-290-002).
4 _
Do a borescope inspection of the combustion chamber dome area (Ref. TASK 72-42-00-290-005).
5 _
Do a Maximum Power Assurance check (Ref. TASK 71-00-00-710008).
R Subtask 72-00-00-210-063 C. Birdstrike Inspection NOTE : Before this inspection, perform steps 4.A Visual Inspection and ____ 4.B Gaspath Inspection. (1) Examine the external portions of the nacelle inlet at the point of impact and look for: (a) Cracks. (b) Signs of distortion. (c) Loose or missing fasteners.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Feb 01/10
C F M 56-5B (2) Examine the inlet cowl structure for secondary damage and look for: (a) Cracks. (b) Signs of distortion. (c) Delamination. (d) Loose or missing fasteners. (3) Examine all open ports in the inlet and look for: (a) Blockage. (4) If the FOD went through the inlet cowl structure, look for: (a) Damage to internal structure. (b) Damage to internal equipment. (5) If there is an indication of engine imbalance, examine the following nacelle components for signs of damage: (a) Inlet cowl. (b) Exhaust nozzle. (c) Fan cowl hinges and surrounding structure. (d) Fan cowl latches and surrounding structure. (e) Centerbody attachment rings and fasteners. 5. Close-up ________ Subtask 72-00-00-410-073 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 611 Nov 01/09
C F M 56-5B Subtask 72-00-00-440-059 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-078 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 612 Nov 01/09
C F M 56-5B TASK 72-00-00-200-007 Procedure After Engine Fire or Use of Fire-Extinguishing Agents WARNING : A LARGE NUMBER OF O-RINGS, GASKETS AND OTHER TYPES OF SEALS ARE MADE _______ OF VITON MATERIAL. VITON MATERIAL DECOMPOSES WHEN THE TEMPERATURE IS MORE THAN 750 DEG.F (400 DEG.C). ONE OF THE BY-PRODUCTS OF THIS DECOMPOSITION IS HYDROFLUORIC ACID. THIS ACID CAN CAUSE BAD BURNS. THUS, USE ACID-RESISTANT GLOVES IF YOU MUST REPLACE A VITON SEAL DURING MAINTENANCE AFTER A FIRE. 1. __________________ Reason for the Job You must do this procedure when fire-extinguishing agents have been used. NOTE : After any fire damage, the removal of the engine from the aircraft ____ for inspection is necessary. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
vacuum cleaner warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2155
USA MIL-C-25779D ardrox 6025 (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 613 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------29-00-00-280-006 71-00-00-000-042 71-00-00-710-001 71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 ESM 720000
Check of the Green or Yellow Hydraulic System after Operation in a Possible Cavitation Condition of the Engine Pump Removal of the Power Plant Dry Motoring Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-00-00-941-068 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 614 Nov 01/09
C F M 56-5B Subtask 72-00-00-010-075 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-060 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-080 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-00-00-280-072 A. If the crew closed the fire shut-off valve during operation of the fire extinguishers, do the check of the hydraulic system after Operation of the engine pumps in possible starvation or cavitation condition: (Ref. TASK 29-00-00-280-006). Check of the Green or Yellow Hydraulic System after Operation in a Possible Cavitation Condition of the Engine Pump. Subtask 72-00-00-280-058 B. Fire Extinguishing Agents Applied Externally NOTE : Do as soon as possible to avoid soak of contamination on engine ____ hardware. (1) If the engine has been exposed to fire extinguishing agents on external surfaces, perform the following where appropriate: (a) Carbon dioxide (CO2) contamination: 1 _
Cold sections: parts not exposed to heat require no maintenance action.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 615 Nov 01/09
C F M 56-5B 2 _
Hot sections: engine parts which were at elevated temperatures when exposed to CO2 must be removed and checked.
(b) Chemical foam contamination: CAUTION : DO NOT ALLOW FOAM TO ENTER ANY ENGINE CAVITIES AS FOAM _______ RESIDUES MAY CAUSE CORROSION DAMAGE. 1 _
Wash exposed areas using clean, running water.
2 _
Scrub to remove all foam agents.
(c) Dry chemical powders contamination: CAUTION : DO NOT USE WATER. DRY AGENT COMBINES WITH WATER TO FORM _______ AN EVEN MORE CORROSIVE COMPOUND. DO NOT ALLOW AGENT TO ENTER ANY ENGINE CAVITIES. RESIDUES WILL CAUSE CORROSION DAMAGE. 1 _
Remove all powder residues from engine by utilizing vacuum cleaner and compressed air at 30-40 psi (205-275 kPa) as required.
2 _
If powder has turned to glaze due to elevated temperatures, scrub with ardrox 6025 (Material No. CP2155).
Subtask 72-00-00-280-059 C. Fire Extinguishing Agents Applied Internally (1) If the engine has been exposed to fire extinguishing agents on internal surfaces, perform the following where appropriate: (a) Carbon dioxide (CO2) contamination: Remove parts exposed to CO2 for inspection. (b) Chemical foam contamination. NOTE : Do as soon as possible to avoid soak of contamination on ____ engine hardware. 1 _
Flush with clean water and motor engine (if practicable) to remove foam residues.
2 _
Remove engine for disassembly, inspection and cleaning.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 616 Nov 01/09
C F M 56-5B (c) Dry chemical powder contamination: 1 _
Remove all accessible loose powder using vacuum cleaner and compressed air at 30-40 psi (205-275 kPa).
2 _
If powder has turned to glaze due to elevated temperatures, rinse with ardrox 6025 (Material No. CP2155).
3 _
Dry-motor to clear and dry engine (Ref. TASK 71-00-00-710001).
4 _
Remove engine for disassembly and cleaning (Ref. TASK 71-0000-000-042) and (Ref. ESM 720000).
5. Close-up ________ Subtask 72-00-00-410-074 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-060 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-079 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 617 Nov 01/09
C F M 56-5B TASK 72-00-00-200-042 Procedure after Halogen Products Contamination 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
* engine oil (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 12-13-79-610-003 12-13-79-610-004 71-00-00-710-003 71-00-00-710-028 71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Oil Tank Draining Draining of the Accessory Drive Section Engine Automatic Start Engine Shutdown Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 618 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-36-00-410-040
Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-00-00-941-132 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-172 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-090 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-173 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 619 Nov 01/09
C F M 56-5B 4. Procedure _________ Subtask 72-00-00-280-076 A. Halogen Products Contamination CAUTION : THE ENGINE CONTAINS NUMEROUS TITANIUM PARTS, THEREFORE HALOGEN _______ SUBSTANCES MUST NOT BE USED. (1) In flight: Use of nacelle extinguishing equipment (fire confirmed or not). No maintenance action. (2) On ground: (a) Use of nacelle extinguishing equipment only: open nacelle doors immediately to disperse halogen vapors. No further maintenance action is required. (b) If halogen fluids have been sprayed in the engine (in undetermined quantity), do the following steps. 1 _
If the engine can be restarted within 30 minutes. - Perform a ground run at Idle for 10 minutes (Ref. TASK 7100-00-710-003). - Drain oil tank (Ref. TASK 12-13-79-610-003). - Drain accessory gearbox (AGB) (Ref. TASK 12-13-79-610-004). - Reservice oil tank with new engine oil (Material No. CP2442) (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-13-79-610002).
2 _
If reignition and ground run cannot be performed before 30 minutes, perform as soon as possible, and within one hour, the following: - Start and motor the engine for 5 minutes (Ref. TASK 71-0000-710-003). - Stop motoring for 5 to 10 minutes (Ref. TASK 71-00-00-710028). - Re-start and motor engine for 5 minutes (Ref. TASK 71-00-00710-003). - Drain oil tank (Ref. TASK 12-13-79-610-003). - Drain accessory gearbox (AGB) (Ref. TASK 12-13-79-610-004). - Reservice oil tank with new engine oil (Material No. CP2442) (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-13-79-610002). - Perform a ground run at idle for 10 minutes within 3 hours (Ref. TASK 71-00-00-710-003).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 620 Nov 01/09
C F M 56-5B 3 _
If motoring the engine is impossible within 3 hours, remove and return engine to shop for disassembly, cleaning and inspection.
5. Close-up ________ Subtask 72-00-00-410-175 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-090 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-176 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 621 Nov 01/09
C F M 56-5B TASK 72-00-00-200-043 Procedure after Volcanic Ash, Dust, or Sand Ingestion 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 12-13-79-610-003 12-13-79-610-004 12-13-79-610-005 71-00-00-710-001 71-13-00-010-040 71-13-00-410-040 72-31-00-290-002 72-42-00-290-005 72-51-00-290-004 R R R R
72-52-00-290-001 72-52-00-290-001 72-52-00-290-004 72-52-00-290-004
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Oil Tank Draining Draining of the Accessory Drive Section Flushing of Oil System Dry Motoring Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Inspection of the High Pressure Compressor Rotor Assembly Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD Borescope Inspection of High-Pressure Turbine Nozzle Assembly Borescope Inspection of HPT Blades (from the front and the rear) Borescope Inspection of HPT Blades (from the front and the rear) Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------73-21-40-210-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 79-21-10-920-002 TSM 77 PB 101
Visual Inspection of the T12 Temperature Sensor Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Remove and Discard Supply Filter
3. __________ Job Set-up Subtask 72-00-00-941-133 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-174 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-091 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 623 Nov 01/09
C F M 56-5B Subtask 72-00-00-010-175 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-00-00-280-077 A. Volcanic Ash, Dust, or Sand Inspection (1) The following requirements are subsequent to incidents of engines flown or operated in volcanic ash, dust, or sand. (a) Visually check engine inlet and exhaust areas for evidence of damage or excessive erosion. (b) Borescope inspect High Pressure Compressor and High Pressure Turbine for evidence of the following (Ref. TASK 72-31-00-290002), (Ref. TASK 72-42-00-290-005), (Ref. TASK 72-51-00-290-004), (Ref. TASK 72-52-00-290-001) or (Ref. TASK 72-52-00-290-001), (Ref. TASK 72-52-00-290-004) or (Ref. TASK 72-52-00-290-004): NOTE : Inspect all stages of the HPC. The aft stages of the HPC ____ will be most effected by erosion. NOTE : Inspect the HPT nozzle vanes and the HPT blades for ____ erosion and accumulation of solidified material. Sufficient amounts of material accumulation on the HPT nozzle vanes can cause a reduced engine stall margin. 1 _
Excessive erosion.
2 _
Foreign object damage (FOD).
3 _
Build-up of ash, dust, or sand deposits that have solidified on the HPT nozzle vanes and HPT blades. a _
If material has solidified on the HPT vanes or blades, contact CFM.
(c) Oil system. 1 _
Replace scavenge oil filter (Ref. TASK 79-21-10-920-002).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 624 Nov 01/09
C F M 56-5B 2 _
Drain oil (Ref. TASK 12-13-79-610-003) and (Ref. TASK 12-1379-610-004).
3 _
Replace oil (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-1379-610-002).
(d) Monitor engine operation to determine if a shift in performance parameters has occurred. If parameters are abnormal, (Ref. TSM 77 PB 101). (e) Check for proper cooling of ignition leads. (f) Check condition of T12 temperature sensor (Ref. TASK 73-21-40210-002). (g) Flush accessory and transfer gearboxes (Ref. TASK 12-13-79-610005). (h) Check for fouling of LPT case air cooling Scoop and precooler Scoop on Thrust Reverser (T/R). (2) The following requirements are subsequent to incidents of engines NOT flown or operated in volcanic ash, dust, or sand, but have been exposed to volcanic ash, dust, or sand on the ground. NOTE : Do not water wash an engine that has been exposed to volcanic ____ ash, dust, or sand. Particles may accumulate in the HPT nozzle vanes and HPT blade cooling paths. Material may accumulate in the HPC rotor spools and cause rotor imbalance. (a) Inspect the engine inlet and exhaust for accumulation of ash, dust, or sand particles. 1 _
Vacuum any particles from accessible areas of the inlet and exhaust.
2 _
Dry motor the engine for two minutes (Ref. TASK 71-00-00-710001).
3 _
Borescope the HPC and HPT at 6o clock positions to inpect for ash, dust, or sand (Ref. TASK 72-31-00-290-002), (Ref. TASK 72-42-00-290-005), (Ref. TASK 72-51-00-290-004), (Ref. TASK 72-52-00-290-001) or (Ref. TASK 72-52-00-290-001), (Ref. TASK 72-52-00-290-004) or (Ref. TASK 72-52-00-290-004).
4 _
If loose material is still present in the engine flow path, dry motor the engine for two more minutes.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 625 Nov 01/09
C F M 56-5B 5 _
Repeat the borescope inspection and dry motoring until all material has been removed.
(b) Oil System. 1 _
Replace scavenge oil filter (Ref. TASK 79-21-10-920-002).
2 _
Drain oil (Ref. TASK 12-13-79-610-003) and (Ref. TASK 12-1379-610-004).
3 _
Replace oil (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-1379-610-002).
(c) Monitor engine operation to determine if a shift in performance parameters has occured. If parameters are abnormal, (Ref.TSM 77 PB 101). (3) Do a one time repeat borescope inspection at an A-check or 400-800 cycles to ensure HPT nozzle vane and HPT blade integrity. 5. Close-up ________ Subtask 72-00-00-410-177 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-091 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 626 Nov 01/09
C F M 56-5B Subtask 72-00-00-410-178 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 627 Nov 01/09
C F M 56-5B TASK 72-00-00-200-008 Inspection/Check After the Engine has Exceeded the Operational Limits 1. __________________ Reason for the Job If an exceedance occurs, the DMC memorizes in its memory the maximum value reached during the last flight leg for N1, N2 and EGT. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 12-13-79-610-003 12-13-79-610-004 71-00-00-710-001 71-00-00-710-008 71-13-00-010-040 71-13-00-410-040 72-00-00-100-008 72-21-00-210-005 72-21-00-290-003 72-23-00-210-003 72-23-00-210-004 72-31-00-290-002 R R
72-52-00-290-001
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Oil Tank Draining Draining of the Accessory Drive Section Dry Motoring Check Power Assurance Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Engine Washing Requirements Inspection/Check of the Spinner Cone Borescope Inspection of the Booster Rotor Blades, Stages 2,3,4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5 Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material Visual Inspection of the Fan Frame Assembly Inspection of the High Pressure Compressor Rotor Assembly Borescope Inspection of HPT Blades (from the front and the rear)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 628 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-52-00-290-004 72-54-00-290-005 72-56-00-210-002 77-00-00-710-042 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 TSM 73-00-00-810-865 TSM 73-00-00-810-866 TSM 77-00-00-810-849 TSM 77-00-00-810-850 TSM 79-00-00-810-805 TSM 79-00-00-810-818 TSM 79-00-00-810-836 TSM 79-00-00-810-837 72-00-00-991-305 72-00-00-991-306 72-00-00-991-307 72-00-00-991-323 72-00-00-991-324
Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) Inspection of the Stage 1-3 Blades Inspection/Check of the Turbine Frame Assembly Reset of the N1, N2 and EGT Max Pointers Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Engine 1 or 2 Stall/Surge Stall of the engine 1 or 2 / Audible stall / Engine surge EGT Overlimit on Engine 1 or 2 N1 Overlimit on Engine 1 or 2 Abnormal Oil Temperature on Engine 1 or on Engine 2 Incorrect Oil Quantity Level on Engine 1 Low Oil Pressure Indication on Engine 1 Low Oil Pressure Indication on Engine 2 Fig. 602 Fig. 603 Fig. 604 Fig. 605 Fig. 606
3. __________ Job Set-up Subtask 72-00-00-941-069 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 629 Nov 01/09
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-076 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-061 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-081 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 602/TASK 72-00-00-991-305, 603/TASK 72-00-00-991-306, 604/TASK 72-00-00-991-307) Subtask 72-00-00-290-052 A. Checks to be Done after a Hot Start NOTE : Starting exhaust gas temperature (EGT) (T495) limits are given. ____ (1) Area A: EGT (T495) is more than 725 deg.C but less than or equal to 750 deg.C for a period of less than 30 seconds. (a) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight (Ref. TSM TASK 7700-00-810-849). (b) A maximum service extension of 5 flight cycles is permitted before you must correct the problem.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 630 Nov 01/09
C F M 56-5B
Operational EGT (T495) Limits for Ground Starting and Sub-Idle Operation Figure 602/TASK 72-00-00-991-305 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 631 Nov 01/09
C F M 56-5B
Operational EGT (T495) Limits Above Idle Figure 603/TASK 72-00-00-991-306 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 632 Nov 01/09
C F M 56-5B
Oil Pressure Versus Core Speed (N2) Figure 604/TASK 72-00-00-991-307 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 633 Nov 01/09
C F M 56-5B (2) Area B: EGT (T495) is more than 750 deg.C but less than or equal to 800 deg.C for less than 10 seconds. (a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope ports S16 and S17) (Ref. TASK 72-54-00-290-005) and (Ref. TASK 72-52-00-290-004). (b) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight (Ref. TSM TASK 7700-00-810-849). (c) A maximum service extension of one start is permitted and, if that start is satisfactory, 1 cycle is permitted before you must correct the problem. (3) Area C: Stop the start and do these checks before you try to start the engine again. CAUTION : HPT BLADES THAT HAVE HAD ENGINE EGT MORE THAN 990 DEG.C _______ (1814 DEG.F) CANNOT BE REPAIRED. THE ENGINE MUST BE REMOVED AND RETURNED TO SHOP FACILITY TO EXAMINE FOR DAMAGE. (a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope ports S16 and S17). (Ref. TASK 72-52-00-290004) and (Ref. TASK 72-54-00-290-005) (b) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight (Ref. TSM TASK 7700-00-810-849). (4) If EGT is more than 950 deg.C reset the EGT max pointer after you correct the problem (Ref. TASK 77-00-00-710-042). Subtask 72-00-00-290-053 B. Checks to be Done if an Overtemperature Condition Occurs at all Engine Ratings other than Starting (Ref. Fig. 603/TASK 72-00-00-991-306) NOTE : There can be many causes for an EGT overtemperature condition, ____ such as: - engine warm up before take off is not sufficient - full rated takeoff in hot day condition - dirty compressor airfoils, engine deterioration (low remaining EGT margin), engine bleed selected during take off after throttle push
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 634 Nov 01/09
C F M 56-5B - FOD, engine system malfunction (for example: VBV actuation), or engine hardware malfunction (for example: airfoil failure, hot air leak, etc.). NOTE : Some positive EGT margin can result by doing an engine gas path ____ water wash (Ref. TASK 72-00-00-100-008). This makes engine performance better but is temporary. It is not a long term repair for high EGT or engine deterioration. Read the DMU Exceedance Report, the DMC Max Value Report and/or the ECU data by the Menu Mode Specific Data Report (if available) to find the maximum EGT value that was recorded during the event, as well as the amount of time of the overtemperature condition. If none of these reports are available, get the data from the AIDS or DFDR. (1) Follow these instructions for the applicable power range where the engine overtemperature occurred: (a) Takeoff (Ref. Fig. 605/TASK 72-00-00-991-323) NOTE : Consider EGT indicated max value and physical max time ____ value, as printed out from PWR SETTING MAX VALUES report. 1 _
Find if there was an Area A, B or C takeoff exceedance.
(b) Climb, Cruise or Max Continuous (Ref. Fig. 606/TASK 72-00-00-991-324) NOTE : Consider EGT indicated max value and physical max time ____ value, as printed out from PWR SETTING MAX VALUES report. NOTE : If the flight crew has logged an EGT indication above the ____ 915 degrees C climb, cruise, or max continuous power limit, maintenance personnel should be concerned with the total time the engine was at 915 degrees C or above regardless of the time that has elapsed since takeoff power was reduced to climb, cruise or max continuous power.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 635 Nov 01/09
C F M 56-5B
Operational EGT (T495) Limits at Take Off Figure 605/TASK 72-00-00-991-323 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 636 Nov 01/09
C F M 56-5B
Operational EGT (T495) Limits at Climb, Cruise or MAX Continuous Figure 606/TASK 72-00-00-991-324 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 637 Nov 01/09
C F M 56-5B (2) Area A: (Unusual Operation) (a) If the EGT overtemperature condition is identified to be caused by not having sufficient engine warm-up before take off: 1 _
No troubleshooting is necessary. NOTE : Warm-up time is not sufficient if engine is as follows: ____ - shut down for more than 4 hours - operated at idle or above for less than 15 minutes
(b) If the EGT overtemperature condition is identified to be caused by engine deterioration (low remaining EGT margin), or engine bleed selected during take off after throttle push: 1 _
No troubleshooting is necessary.
(c) If the cause of the EGT overtemperature condition cannot be identified by the above, or you think it could have been caused by FOD or engine hardware failure: 1 _
Do troubleshooting for EGT OVERLIMIT . (Ref. TSM TASK 77-0000-810-849)
2 _
Troubleshooting can be deferred for five overtemperature conditions in Area A but can not go over 25 cycles after the first overtemperature condition. NOTE : There are known engine malfunctions that can lead to an ____ EGT overtemperature condition and thus a Class 1 ECAM warning message. These malfunctions require troubleshooting prior to engine operation. (Example: VBV ACT, HMU , CHECK HOT AIR LEAKS, NAC TEMP SENSOR, etc.).
(d) You can have a maximum of 20 overtemperature conditions in Area A, before engine removal is required and sent to a shop for a full performance overhaul workscope.
R R R R R R R R
NOTE : EGT exceedences above the EGT red line limit will make ____ maintenance troubleshooting actions necessary. The EGT exceedance may be caused by a system related problem or a performance deterioration. In case of performance deterioration related exceedance, engine must be sent to shop for performance overhaul.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 638 Nov 01/09
C F M 56-5B (3) Area B: (Unusual Operation) (a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope port S17) (Ref. TASK 72-52-00-290-001) and (Ref. TASK 72-54-00-290-005). (b) Do troubleshooting for EGT OVERLIMIT (Ref. TSM TASK 77-00-00810-849). 1 _
Troubleshooting can be deferred for 10 cycles unless the fault repeats.
(c) You can have a maximum of 20 overtemperature conditions in Areas A and B together or 10 overtemperature conditions in Area B alone, before engine removal is required and sent to a shop for a full performance overhaul workscope.
R R R R R R R R
NOTE : EGT exceedences above the EGT red line limit will make ____ maintenance troubleshooting actions necessary. The EGT exceedance may be caused by a system related problem or a performance deterioration. In case of performance deterioration related exceedance, engine must be sent to shop for performance overhaul. (4) Area C: (Unserviceable) (a) Remove and return engine to a shop facility to examine damage. (b) One non-revenue flight for fly-back is permitted before the engine must be removed, if there is no damage above the serviceable limits: 1 _
Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope port S17) (Ref. TASK 72-52-00-290-001) and (Ref. TASK 72-54-00-290-005).
2 _
Do a troubleshooting for EGT OVERLIMIT (Ref. TSM TASK 77-0000-810-849).
(5) If the maximum EGT is more than 950 deg.C, the EGT maximum pointer must be set again after the corrective action is done (Ref. TASK 7700-00-710-042).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 639 Nov 01/09
C F M 56-5B Subtask 72-00-00-280-062 C. Checks to be Performed when Abnormal Rotation Speeds are Reached (1) Overspeed (a) The speed limits are as follows: 1 _
Fan speed (N1): 104 percent
2 _
Core speed (N2): 105 percent
(b) Fan (N1) overspeed inspections: 1 _
If fan is operated at speeds from 104 percent to 105.8 percent, the engine must be inspected as follows: - Review available data to understand reason for the overspeed. - Correct the cause. Troubleshoot. (Ref. TSM TASK 77-00-00810-850) - Visually inspect the engine inlet, the fan blades, the exhaust nozzle, and the stage 4 LPT blades. - Check the fan rotor for freedom of rotation and shingling of blades (Ref. TASK 72-21-00-210-005). - Inspect abradable material in fan inlet case for rubbing (Ref. TASK 72-23-00-210-003). - Borescope inspect the stage 5 of booster rotor blades (borescope port S05 at 3:30 oclock location and at the rear end of booster) (Ref. TASK 72-21-00-290-003). - Borescope inspect stage 1 LPT blades (borescope ports S16 and S17) (Ref. TASK 72-54-00-290-005).
2 _
If fan speed exceeds 105.8 percent, remove engine and return to shop for overspeed inspection.
3 _
If fan speed has exceeded 104 percent the N1 max pointer must be reset after corrective action has been performed (Ref. TASK 77-00-00-710-042).
(c) Core engine (N2) overspeed inspections: 1 _
If core engine rotor is operated at speeds from 105 percent to 105.8 percent the engine must be inspected as follows: - Inspect exhaust nozzles for particles. - Borescope inspect stages 1, 3, and 8 HPC blades (borescope ports S2, S4 and S9) (Ref. TASK 72-31-00-290-002).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 640 Nov 01/09
C F M 56-5B - Borescope inspect HPT blades (borescope ports S16 and S17) (Ref. TASK 72-52-00-290-004). 2 _
If core engine rotation speed exceeds 105.8 percent, shutdown, remove engine and return to shop for overspeed inspections.
3 _
If core engine rotation speed has exceeded 105 percent the N2 max pointer must be reset after corrective action has been performed (Ref. TASK 77-00-00-710-042).
Subtask 72-00-00-210-064 D. Checks Required after Lubrication System Operation Limits are Exceeded (1) Oil pressure (a) The Figure gives the relation between oil pressure and N2 speed. (b) Critical zone A, with oil pressure lower than 13 psi (0,90 bar). 1 _
If engine operation with no oil or very low pressure has exceeded any one of the following, remove engine and return to shop. - Take-off power for 10 seconds. - Cruise power for 10 seconds. - Idle (flight or ground) for 30 seconds.
2 _
If engine not exceeding time limits per step 1_ has been operated with no oil pressure or very low pressure, remove all oil filters, screens, magnetic plug and chip detectors, and check for presence of metal/debris. If no suspect metal debris is observed, troubleshoot (Ref. TSM TASK 79-00-00-810-836) or (Ref. TSM TASK 79-00-00-810-837).
(c) Zones B and/or D: Troubleshoot (Ref. TSM TASK 79-00-00-810-836) or (Ref. TSM TASK 79-00-00-810-837). (2) Supply Oil Temperature (a) Maximum oil temperature for continuous engine operation is 140 deg.C (284 deg.F). (b) Engine operation with oil between 140 deg.C (284 deg.F) and 155 deg.C (311 deg.F) is allowed for 15 minutes.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 641 Nov 01/09
C F M 56-5B (c) Above 155 deg.C (311 deg.F) the oil system must be drained (Ref. TASK 12-13-79-610-003) and (Ref. TASK 12-13-79-610-004) and serviced (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-13-79-610002). Troubleshoot (Ref. TSM TASK 79-00-00-810-805). (d) After abnormally high oil temperature, check that the supply filter, common scavenge filter and chip detectors of lube unit are free of metal particles. If metal particles are present, remove and disassemble the engine for inspection. (3) Oil Consumption (a) Normal oil consumption is not expected to exceed 0.57 l.hr (approximately 0.6 quart.hr) (0.15 USgal.hr). (b) As soon as one of the following cases occur, Troubleshooting (Ref. TSM TASK 79-00-00-810-818) or (Ref. TSM TASK 79-00-00-810818) must be performed: - Oil consumption exceeds 0.85 l.hr (approximately 0.9 quart.hr) (0.22 USgal.hr). - Oil consumption substantially exceeds that of the other operating engines. - Oil consumption indicates a gradual increasing trend. - Oil consumption indicates sudden step increase. (c) The maximum serviceable oil consumption rate is limited to 1.5 l.hr (approximately 1.5 quart.hr) (0.40 USgal.hr). Consumption monitoring. - Troubleshooting (Ref. TSM TASK 79-00-00-810-818) or (Ref. TSM TASK 79-00-00-810-818) must be performed as soon as the oil consumption rate overshoots the limit. - If the result of the troubleshooting is not conclusive and no action can be taken to reduce the oil consumption rate, the engine has to be replaced. Subtask 72-00-00-210-104 E. IFSD time limitation (1) Dry-out the engine if you can not restart within 24 hours and after each ferry flight.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 642 Nov 01/09
C F M 56-5B Subtask 72-00-00-210-065 F. Checks Required after Rough Landing Limits are Exceeded (1) General (a) The following procedure is to be used following a rough landing. (2) Visual Inspection/Checks. Inspect the following: (a) Wear of abradable material in fan inlet case at the 6 and 12 oclock positions (Ref. TASK 72-23-00-210-003). (b) Engine mounting pads forward and aft (Ref. TASK 72-23-00-210-004) and (Ref. TASK 72-56-00-210-002). (c) Accessory and hardware attachments for metal fractures or excessive distortion. (d) Piping connections for leaks. (e) Lines, tubing for possible interferences. (f) Turbine frame aft flange (Ref. TASK 72-56-00-210-002). (3) Borescope Inspection/Checks. Inspect the following: (a) Stages 1, 3, and 8 HPC blades (borescope ports S2, S4, and S9). (Ref. TASK 72-31-00-290-002). Subtask 72-00-00-210-066 G. Inspection after Stall (1) General (a) If a stall or suspected stall has occurred, the following inspection and troubleshooting must be done (Ref. TSM TASK 73-0000-810-865) or (Ref. TSM TASK 73-00-00-810-866). (2) Visual Inspection/Checks. Inspect the following: (a) Fan rotor and abradable material (Ref. TASK 72-21-00-210-005) and (Ref. TASK 72-23-00-210-003).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 643 Nov 01/09
C F M 56-5B (3) Borescope Inspection/Checks. Inspect the following: (a) For engine stalls in the start region, or for off-idle stalls which result in engine rollback into sub-idle N2 range: 1 _
If the start region EGT limit of 725 deg.C was exceeded, borescope inspect HPT blades and stage 1 LPT blades (borescope ports S16 and S17) (Ref. TASK 72-52-00-290-004) and (Ref. TASK 72-54-00-290-005). (Ref. Fig. 602/TASK 72-00-00-991-305)
2 _
If the cause of the stall is not known, borescope inspect stages 1, 3 and 8 HPC blades (borescope ports S2, S4 and S9) (Ref. TASK 72-31-00-290-002).
(b) For engine stalls at or above idle which do not result in engine rollback into sub-idle N2: 1 _
Borescope inspect HPT blades and stage 1 LPT blades (borescope ports S16 and S17) (Ref. TASK 72-52-00-290-004) and (Ref. TASK 72-54-00-290-005). (Ref. Fig. 603/TASK 72-00-00-991-306)
2 _
If the cause of the stall is not known, borescope inspect stage 5 of booster rotor blades (borescope port S05 at 3:30 oclock location and at the rear end of booster) (Ref. TASK 72-21-00-290-003) and stages 1, 3 and 8 HPC blades (borescope ports S2, S4 and S9) (Ref. TASK 72-31-00-290-002).
Subtask 72-00-00-210-067 H. Excessive Vertical Loading Greater than the Specified Limits (1) General (a) Engine suspected of experiencing excessive g loading during transportation must be given the following inspection. The inspection consists of visual and manual checks followed by a functional check. (2) Check engine for obvious damage as follows: (a) Visually inspect for buckling, deformation or cracking in engine skin and flange areas around transportation mounts.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 644 Nov 01/09
C F M 56-5B (b) To turn fan rotor by hand: WARNING : USE CARE TO AVOID PERSONAL INJURY WHEN YOU MANUALLY _______ TURN THE FAN ROTOR. ASSURE SAFE FOOTING.USE HEAVY PROTECTIVE GLOVES 1 _
Turn fan rotor by hand ; check for bearing roughness, unusual noises and binding. Clear indications of this type of damage require engine disassembly. NOTE : Light rubbing of seals and shrouds is normal. ____
(c) If seal or shroud interference is found and appears minimal, the engine can be considered serviceable after completing a successful dry motoring check (Ref. TASK 71-00-00-710-001) and power assurance check (Ref. TASK 71-00-00-710-008). (d) After functional test run, check scavenge screens and master magnetic chip detector for the presence of metal particles caused by bearing damage. Return engine to shop for inspection if unusual deposits are found. 5. Close-up ________ Subtask 72-00-00-410-075 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-061 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 645 Nov 01/09
C F M 56-5B Subtask 72-00-00-410-080 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 646 Nov 01/09
C F M 56-5B TASK 72-00-00-200-009 Off-Schedule Vane Replacement 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-00-00-941-070 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 647 Nov 01/09
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-077 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-040-062 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-082 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-00-00-210-070 A. Vane scheduling errors can occur if the lever arms which control the compressor stator vanes are damaged or disassembled. (1) When the vane scheduling errors are greater than 4 degrees, you must replace all HPC blades on one stage forward of and 2 stages aft of the stage which has off-schedule vanes.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 648 Nov 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-00-00-410-076 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-062 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-081 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 649 Nov 01/09
C F M 56-5B TASK 72-00-00-200-025 Over-Serviceable-Limit Extensions 1. __________________ Reason for the Job This TASK is applicable to NON /P engines. It can occur that specific defects do not agree with the Maximum Serviceable Limits, and that the maintenance facilities, at a given location, are not sufficient to do the necessary corrective actions. In these circumstances, limit extensions will permit to send the engine where correction is possible, or to schedule the necessary maintenance in the extension period. NOTE : The limit extensions are one-time extensions only. Applicable ____ hardware action is necessary at the completion of the extended serviceable period. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-210-006 72-21-00-210-009 72-23-00-210-003 79-00-00-210-003 72-00-00-991-308 72-00-00-991-309 72-00-00-991-321
Inspect Fan Rotor Blades Removed from the Fan Disk. Inspect Fan Rotor Blades Installed on the Fan Disk Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material Visual Inspection of the Oil System Fig. 607 Fig. 608 Fig. 609
3. __________ Job Set-up Subtask 72-00-00-941-071 A. Not applicable
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 650 Nov 01/09
C F M 56-5B 4. Procedure _________ (Ref. Fig. 607/TASK 72-00-00-991-308, 608/TASK 72-00-00-991-309, 609/TASK 72-00-00-991-321) Subtask 72-00-00-210-071 A. Over-serviceable-limit Extensions ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------1. Fan and booster A. Spinner front cone (1) Damaged surface protection greater than 50 percent of total surface
50 cycles
(2) Corrosion marks (white mushroom pattern) before part removal
A continuation in service of 100 cycles maximum is permitted
B. Spinner rear cone (1) Oil wetting at inner of spinner cone or fan disk or forward fan shaft
50 cycles
(2) Seal ring tear: any number if cumulated length is more than 0.4 in. (10 mm)
50 cycles
C. Fan blade (1) Fully missing molydag on inner faces of the platforms
250 cycles
(2) Flaking of Cu.Ni.In coating on blade dovetail pressure faces (contact areas), up to 10 percent if there is no indication of wear on base material
Examine blades for serviceability. (Ref. TASK 72-2100-210-006) 1200 cycles after relubrication. Repeat extension is permitted
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 651 Nov 01/09
C F M 56-5B
Booster Rotor and Stator Damage Extended Figure 607/TASK 72-00-00-991-308 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 652 Nov 01/09
C F M 56-5B
INTENTIONALLY BLANK
R 72-00-00 CES
Page 653 Nov 01/09
C F M 56-5B
Extended Vanes Damage Limits Figure 608/TASK 72-00-00-991-309- 12 (SHEET 1) EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 654 Nov 01/09
C F M 56-5B
Extended Vanes Damage Limits Figure 608/TASK 72-00-00-991-309- 22 (SHEET 2) EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 655 Nov 01/09
C F M 56-5B
Inspection/Check of the Fan Outlet Guide Vanes (OGV) Figure 609/TASK 72-00-00-991-321- 13 (SHEET 1) EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 656 Nov 01/09
C F M 56-5B
Inspection/Check of the Fan Outlet Guide Vanes (OGV) Figure 609/TASK 72-00-00-991-321- 23 (SHEET 2) EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 657 Nov 01/09
C F M 56-5B
Inspection/Check of the Fan Outlet Guide Vanes (OGV) Figure 609/TASK 72-00-00-991-321- 33 (SHEET 3) EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 658 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Flaking of Cu.Ni.In coating on blade dovetail 400 cycles after pressure faces (contact areas), more than 10 relubrication. percent and less than 50 percent if there is Repeat extension is no indication of wear on base material not permitted (4) Shingling at mid span shrouds
Turn the shingled blades to the 12 oclock position and unshingle with hand force or by using a piece of wood. Examine blades for serviceability (Ref. TASK 72-2100-210-009). Remove and send the shingled blades to a shop for a dimensional and an F.P.I. inspection in less than 50 cycles.
(5) Nicks, dents, scratches and sheared edges on midspan shroud surfaces up to 0.035 in. (0.89 mm) deep if defects are not in the midspan shroud to airfoil fillet radius
50 cycles
(6) Missing or damaged hard coating on midspan shroud pressure faces more than 20 percent but less than 40 percent of coated area
50 cycles
D. Fan disk (1) Wear greater than 50 percent of area on disk dovetail pressure faces
100 cycles
E. Booster rotor blade for: (1) Piece missing:
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 659 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------any number in area G, at leading edge and 50 cycles/75 hours trailing edge tip corners, 0.8 in. (20 mm) radial and 0.5 in. (12.5 mm) axial (2) Cracks and tears in area G, 0.8 in. (20 mm) from tip: any number, less than 0.8 in. (20 mm) radial and less than 0.492 in. (12.5 mm) axial
50 cycles/75 hours
(3) Wear or local distortion of T/E and L/E tips if less than 15 blades, 0.984 in. (25 mm) radial and 0.59 in. (15 mm) axial
100 cycles/150 hours
(4) Nicks, dents, scratches for area E: any number, less than 0.059 in. (1.5 mm) in diameter, protrusion acceptable, not thru
50 cycles/75 hours
(5) Nicks, dents, scratches for airfoil out of area E, not L/E and T/E: any number, less than 0.236 in. (6 mm) in diameter, protrusion acceptable
50 cycles/75 hours
(6) Nicks, dents, scratches out of area E on L/E and T/E: maximum axial length less than 0.059 in. (1.49 mm)
50 cycles/75 hours
(7) Distorted L/E and T/E, out of area E, maximum circumference equals 0.275 in. (6.98 mm) radial length equals 0.708 in. (17.98 mm)
50 cycles/75 hours
F. Booster vanes (stage 1 only) for: (1) Piece missing: maximum 20 blades more than 0.256 in. (6.5 mm) axial, 0.728 in. (18.49 mm) radial, no cracks starting from damage area allowed in areasA and B
50 cycles/75 hours
(2) Cracks and tears in than 0.256 in. (6.5 (1.98 mm) axial. In more than 0.128 in. 0.039 in. (0.99 mm)
10 cycles/15 hours
area C, any number, more mm) radial and 0.078 in. areas A and B, any number (3.25 mm) radial and axial
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 660 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Distortion of T/E and L/E: any number, if the 50 cycles/75 hours length L is not more than 1 in. (25.4 mm) and the maximum dimension X along the chord width is not more than 0.492 in. (12.5 mm). (4) Nicks, dents, scratches for areas A and B: any number, less than 0.157 in. (3.99 mm) in diameter, protrusion permitted
10 cycles/15 hours
(5) Nicks, dents, scratches for area C: any number, less than 0.295 in. (7.49 mm) in diameter, protrusion permitted
50 cycles/75 hours
(6) Nicks, dents, scratches L/E and T/E maximum axial length less than 0.118 in. (2.99 mm) in diameter
20 cycles/30 hours
(7) Cracked inner shroud: Maximum of 4 cracks extending from the L/E to the T/E of the inner shroud (passing through a recess) are permitted if there is a minimum separation of 3 non-cracked vane recesses between 2 cracked recesses.
3000 hours/C check
A sound check (see note below) done on the vanes at, and adjacent to the cracked inner shroud area, must demonstrate no difference in tonality.
This extension may be used again indefinitely in intervals of 3000 hours as long as there is no further deterioration of these conditions.
NOTE : Sound Tonality Check Recommendation ____ A sound tonality check must be done to detect if the abradable material inside the inner shroud is still in contact with the root of the vane. Use a smooth-ended cylindrical tool made of steel with diameter of approximately 0.5 in. (12.6999 mm). (For example, a ratchet wrench extension bar). Tools made of aluminium, plastic or wood do not permit the detection of significant variation in the sound tone from one vane to the next. Removal of 2 or 3 fan blades gives a better accessibility to do the check.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 661 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------Be careful to not use a tool or excessive force during the check. This would damage the vanes. Do the check on an area including 3 or 4 vanes on each side of the vane where the cracked inner shroud is located. Place the tool on the leading edge mid-span of the counterclockwise most vane. Lightly stroke the vane and subsequent vanes in the clockwise direction using a constant speed. Note any variations in the sound tone from one vane to the next. If there is a difference between the vane where the recess is cracked and the other vanes, the stage 1 vane assembly is unserviceable. (8) Vane leading and trailing edges - Nicks, dents and scratches on LE/TE in areas B and C with a maximum axial length less than 0.117 in. (2.97 mm) - Nicks, dents and scratches on LE/TE in area A with a maximum axial length of 0.117 in. (2.97 mm)
10 cycles/50 hours
2 cycles/10 hours
2. Fan frame A. Fan frame (1) Cracks, any number if max length of 0.16 in. (4.06 mm) and min. separation of 1 in. (25.4 mm)
10 cycles or 25 hours
(2) Nicks and dents, any number
10 cycles or 25 hours
B. Fan inlet case (1) Cracks: any number, if max length of 0.16 in. (4.06 mm) and min. separation of 1 in. (25.4 mm)
10 cycles or 25 hours
(2) Nicks and scratches: any number
10 cycles or 25 hours
(3) Crater in abradable liner (length<5x width) and damage other than crack rub and
50 cycles or 125 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 662 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------circumferential defect: if the damage is within the maximum serviceable limit (Ref. TASK 72-23-00-210-003), but the fan case parent metal is exposed and is confirmed via visual inspection to be undamaged. (4) Grooves in abradable liner (oriented within 0 deg. to 80 deg. from engine axis and length>5x width: if the damage is within the maximum serviceable limit, (Ref. TASK 72-2300-210-003) but the fan case parent metal is exposed and is confirmed via visual inspection to be undamaged
50 cycles or 125 hours.
(5) Circumferential defect in abradable liner (360 deg. or oriented within 80 deg. to 90 deg. from engine axis): For one or a cumulated defect less than 2 in. (50.8 mm) if the fan case parent metal remains not damaged under visual inspection.
50 cycles or 125 hours.
C. Outlet Guide Vanes (OGV) for: (Ref. Fig. 609/TASK 72-00-00-991-321) (1) Broken vane: not serviceable, if vane is replaced
10 cycles extension
(2) Missing vane: One doublet missing
10 cycles extension
(3) Cracks Outer platform: cracks from or along the airfoil are defined (Ref. Fig. 609/TASK 72-00-00-991-321)
50 cycles extension
(4) Metal leading edge missing: up to 0.78 in. (20 mm) in height and 0.39 in. (10 mm)
100 cycles extension
(5) Nicks and/or dents, on leading edge (metallic leading edge), if damage between 0.12 in. (3 mm) and 0.19 in. (5 mm) deep
A maximum service extension of 100 cycles
(6) Erosion of composite material, any amount
50 cycles or 125 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 663 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------D. OGV inner shroud (1) Cracks, cut or torn seal at mating with OGV, any amount
25 cycles or 50 hours
E. Fan duct panels (1) One fan duct panel missing is permitted, if you make sure that the VBV area is free of unwanted object before the first aircraft release of the day.
10 cycles
(2) Missing lowers on panel
50 cycles with 3 missing lowers maximum
F. Splitter fairing (1) Cracks: any amount
10 cycles or 25 hours
G. Mid acoustical panels
20 cycles
(1) Disbonded damper more than 20 percent of the total surface 3. Compressor rotor A. Compressor rotor blades NOTE : The depth of a defect such as a nick is measured along the axis of ____ the damage unless otherwise noted. (1) Stages 1-4 radial cracks within 0.30 in. (7.6 mm) of the leading and trailing edges more than 0.25 in. (6.4 mm) but less than 0.40 in. (10.2 mm) in length.
10 cycles or 25 hours
(2) Stages 1-4 chord-wise cracks more than 0.20 in. (5.1 mm) but less than 0.30 in. (7.6 mm) in length.
10 cycles or 25 hours
(3) Stages 1-4 nicks, missing material and erosion on the leading and trailing edges
10 cycles or 25 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 664 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------found in Dim. B more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm). (4) Stages 1-4 dents on the leading and trailing edges found in Dim. B more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm) in depth, or less than 0.06 in. (1.5 mm) deflection from the original contour.
10 cycles or 25 hours
(5) Stages 1 nicks, dents and tears on the leading and trailing edge in Dim. A more than 0.25 in. (6.4 mm) but less than 0.30 in. (7.6 mm) in depth.
10 cycles or 25 hours
(6) Stages 1-4 missing material and erosion at the leading and trailing edge tip corners more than 0.30 in. (7.6 mm) but less than 0.40 in. (10.1 mm).
10 cycles or 25 hours
R R R R
(7) Stage 2, more than 4 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
R R R R
(8) Stage 3, more than 5 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
R R R R
(9) Stage 4, more than 6 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
R
(10) Stages 1-4 nicks, dents and missing material on the leading and trailing edges of the lower 25% of the airfoil (but not the root radius) more than 0.03 in. (0.76 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R
(11) Nicks, dents, wear and scratches of the trailing edge root radius of stage 2 and stage 3 of more than 0.03 in. (0.8 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R R
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 665 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(12) Stages 5-9 radial cracks that are no more 10 cycles or 25 than 0.20 in. (5.1 mm) from the leading or hours trailing edge and more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm) in length.
R
(13) Stages 5-9 chord-wise cracks that are no more than 0.20 in. (5.1 mm) from the tip and are more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm) in length.
10 cycles or 25 hours
R
(14) Stages 5-9 nicks, tears, missing material and erosion on the leading and trailing edges found in Dim. B that are more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R
(15) Stages 5-9 dents on the leading and trailing edges found in Dim. B that are more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm) in depth or less than 0.06 in. (1.5 mm) deflection from the original contour.
10 cycles or 25 hours
R
(16) Stages 5-9 nicks, dents and tears on the leading and trailing edges found in Dim. A that are more than 0.15 in. (3.8 mm) but than less 0.20 in. (5.1 mm).
10 cycles or 25 hours
R
(17) Stages 5-9 missing material and erosion at the leading and trailing edge tip corners if the damage is more than 0.20 in. (5.1 mm) but less than 0.30 in. (7.6 mm).
10 cycles or 25 hours
R
(18) Stages 5-9 curl on the end of the airfoil when the blade chord is more than 50% but less than 75% of the chord maximum radial length, 0.3 in. (7.6 mm), when it does not engage the stationary parts during operation.
10 cycles or 25 hours
R
(19) Stages 5-9 nicks, dents and missing material edges found in the lower 25% of the airfoil (but not the root radius) more than 0.03 in. (0.76 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 666 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(20) Stages 2-3 trailing edge root radius nicks, 10 cycles or 25 dents and scratches more than 0.03 in. (7.6 hours mm) but less than 0.08 in. (2.0mm) in depth. 4. Compressor front stator A. Casing cracks 0.17 in. (4.32 mm) max length in skin
10 cycles or 25 hours
B. Casing nicks, pits, scores or scratches, any amount, any depth
10 cycles or 25 hours
C. Broken actuation ring connector, one side only, if connector is replaced
5 cycles
D. Vane actuation ring cracks, distortion, bends, twists or distress, provided ring has not separated
5 cycles
E. Loose vane assemblies with metal-to-metal contact on up to 50 percent of vanes
10 cycles or 25 hours
5. Combustion case A. Forward and aft flange radial cracks inward from bolt holes
10 cycles
B. Midflange radial cracks
10 cycles
C. Maximum of 10 broken midflange bolts with no more than 4 broken bolts in any group of 20
25 cycles
D. High pressure turbine (HPT) shroud cooling and compressor discharge pressure (CDP) pad cracks more than 0.06 in. (1.52 mm) from bolt holes
10 cycles
6. Combustion chamber A. Dome assembly (1) Radial crack in spectacle plate
25 hours
Any number up to 2.5 inches (63.5 mm) in length and not connected to each other
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 667 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(2) Circumferential crack in spectacle plate 25 hours Any number up to 3.6 inches (91 mm) in length separated by 4.8 inches (125 mm) (3) Connected cracks in spectacle plate
25 hours
Not more than (1) radial crack 2.5 in. (50.8 mm) long with (1) circumferential crack 3.6 in. (91 mm) long, separated by 4.8 in. (125 mm) (4) Missing material from spectacle plate
25 hours
The damage is more then the given limits (5) Radial crack in deflector or sleeve
25 cycles
Any number up to 0.6 in. (16 mm) in length (6) Circumferential cracks in deflector or sleeve
25 cycles
Any number up to 0.9 in. (23 mm) in length (7) Connected cracks in deflector or sleeve
25 cycles
Connection of any radial and circumferential cracks within limits of (5) and (6) above. Limit is exceeded when third crack connects (8) Missing material from overhangs on deflector or sleeve
50 cycles
Any amount up to 0.240 in. (6.10 mm) maximum depth (9) Burn through holes
25 cycles
3 per dome 1.2 in. (30mm) x 1.2 in. (30 mm) maximum B. Inner and outer liners (1) Outer liner axial cracks
100 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 668 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------Up to 5 cracks across more than one panel, and a crack can go across up to 5 panels in sequence (2) Outer liner axial cracks (from outer side borescope)
25 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 5 panels. At least one of the cooling ribs (3, 4, 5, or 6) does not have cracks that extend through to the outer side. Rib 1 is not cracked through. (3) Inner liner axial cracks
100 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 4 panels in sequence (4) Circumferential cracks
25 cycles
Any number up to 3 dilution lands in length separated by 3 non-cracked dilution lands (5) Connected cracks
100 cycles
Connection of any axial and circumferential cracks up to max limits of paragraphs (1), (2), (3), and (4) (6) Burn through or missing material
100 cycles
There are not more than 8 areas that are not more than 2 times the diameter of a dilution hole. There are not more than 2 areas that are not more than 3 times the diameter of a dilution hole. There are not more than one area that is not more than 4 times the size of a dilution hole. There are not more than 3 areas in adjacent panels that are aligned axially if they have a separation of a minimum of 3 dilution lands that are not damaged.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 669 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(7) Missing overhangs 25 cycles Per liner: 17 areas each twice the size of a dilution hole, providing max axial alignment of distress is 3 adjacent panels (8) Distortion
25 cycles
Any amount within 0.7 in. (17.8 mm) of original contour C. Combustor inner cowl bolts (1) Missing bolt: Maximum of 3 bolts are missing with 4 bolts intact between 2 missing bolts. All other bolts are tight with tack welds intact
50 cycles for next check, then repeat BSI every 400 cycles
(2) Bolt tack weld cracked but bolt is not loose: If a maximum of 5 tack welds are cracked, no more than two consecutive, with 4 tack welds intact between two cracked tack welds
25 cycles for first check, 50 cycles for second check, repeat BSI check every 100 cycles
(3) Bolt tack weld is cracked and bolt is loose: If one or more bolts are loose
5 cycles
7. Fuel Nozzles A. Fuel nozzles with dislodged wear sleeves or wear sleeves with 4 interrupted weld designs
5 cycles
8. HPT nozzle A. Leading edge missing material, from cracking or burn-through, up to 0.5 in. (12.7 mm) X 0.5 in. (12.7 mm) per vane. Maximum of 4 vanes per 90 degree arc
25 cycles
B. Concave surfaces of airfoil missing material, from cracking or burn-through, up to 0.75 in. (19.04 mm) diameter per vane
25 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 670 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------C. Convex side missing panel 25 cycles provided HPT blades are within limits D. Inner and outer platforms missing material, from cracking or burn-through, up to 0.5 in. (12.7 mm) diameter per segment
25 cycles
E. Trailing edge missing material up to 0.75 in. (19 mm)in axial direction
25 cycles
F. Baffle missing material, any amount.
10 cycles
9. HPT rotor blade A. Trailing edge cracks in Area A less than 0.2 in. (5.08 mm) long
10 cycles
B. Trailing edge cracks and convex airfoil cracks within 0.5 in. (12.7 mm) of trailing edge (10 blades maximum) in Area B less than 0.3 in. (7.62 mm) long
25 cycles
C. Radial tip cracks less than 0.35 in. (8.89 mm) long
10 cycles
D. Leading edge cracks in Area A less than 0.1 in. (2.54 mm) long
10 cycles
E. Axial nose or gill hole cracks in Area B less than 0.05 in. (1.27 mm) long
10 cycles
F. Radial nose or gill hole cracks in Area B less than 0.06 in. (1.52 mm) long
10 cycles
G. Radial nose or gill hole cracks in Area C less than 0.03 in. (0.76 mm) long
10 cycles
H. Leading edge missing material in areas A and B. Any amount provided cavity 2 is not exposed (any number of blades)
25 cycles
J. Airfoil distortion or evidence of burning or melting (10 blades maximum)
25 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 671 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------10. HPT shroud and stage 1 low pressure turbine (LPT) nozzle A. HPT shrouds (1) Circumferential cracks that connect and are more than 1 in. (25.3999 mm) long.
25 cycles
(2) Circumferential cracks more than 0.25 in. (6.3499 mm) long that connect to axial cracks in Area B.
25 cycles
(3) Burn through of shroud rub land
25 cycles
B. Stage 1 LPT nozzle (1) Cracks in all areas up to 1.4 in. (35 mm) long provided not more than 2 adjacent airfoils per segment
10 cycles
(2) One crack permitted on each airfoil, from leading edge to trailing edge, if there is no missing material.
100 cycles
(3) Burns, erosion, corrosion and missing metal up to 1 in.2 (645.16 mm2) per airfoil and no cracks extending from distressed area
5 cycles
11. LPT Rotor A. LPT blades (all stages) (1) Blade pretwist - Total gap, for stage 1, up to 0.1 in. (2.54 mm)
5 cycles
- Stages 2-4 gaps such that adjacent interlocks do not contact each other
5 cycles
(2) 0.08 in. (2.03 mm) max. deflection over a length 10 times longer max, only for stage 1 LPT blades distorted leading edges, due to overtemperature
15 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 672 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Stages 1, 2, 3 blades - Area E: Any amount of impact damage/rubbing provided there is no missing material or cracks
5 cycles or 10 hours
- Other areas: Any amount of impact damage such as bending, nicks and/or dents is allowed provided there is no missing material or cracks exceeding 50 percent of chord width
5 cycles or 10 hours
(4) Stage 4 blades - Any amount of tip shroud interlock wear allowed
25 cycles or 50 hours
- Blades tip shroud protrusion not to exceed 0.04 in. (1.01 mm)
10 cycles or 25 hours
- Area E: Any amount of impact damage such as nicks and/or dents is allowed provided there is no missing material or cracks
5 cycles or 10 hours
- Other areas: Any amount of impact damage. One complete airfoil and any number of tip shrouds with associated airfoil tips may be missing provided engine vibration is not excessive
5 cycles or 10 hours
- Blades tip shrouds shingled or unlatched provided rotor turns freely and engine vibration is not excessive
5 cycles or 10 hours in shingled condition.
B. Nozzle segments 2 to 4 (1) Three cracks maximum for each nozzle segment if cracks are more than 0.5 in. (12.7 mm) (1/3 of the chord width) and less than 1.0 in. (25.4 mm) (2/3 of the chord width) if the
200 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 673 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------adjacent nozzle segments have no more than two cracks more than 0.5 in. (12.7 mm) (1/3 of the chord width) and less than 1.0 in. (25.4 mm) (2/3 of the chord width). (2) One crack maximum for each nozzle segment that is more than 1.0 in. (25.4 mm) (2/3 of the chord width) including open airfoil.
200 cycles
(3) One full chord crack on two airfoils for each segment if the adjacent nozzle segments have no more than one airfoil with a full chord crack.
25 cycles
(4) Nicks, dents, tears, missing pieces up to 2 in.2 (1290.32 mm2) on nonadjacent vanes provided there are no cracks extending from distressed areas
10 cycles
(5) Burned areas with missing material or melted
25 cycles
C. Stage 4 shroud abradable material (1) Worn, jagged or crushed sealing surface exceeding 50 percent of the honeycomb height provided sectors of the shroud abradable material are not missing
10 cycles
12. LPT Casing A. Forward and aft flanges (1) One crack connecting 2 bolt holes without penetrating pressure vessel outer skin
10 cycles
(2) One crack into skin 0.4 in. (10.16 mm) long maximum
10 cycles
B. External surface of the casing (1) One crack 0.4 in. (10.16 mm) long maximum C. Cooling air tube and manifold assemblies
10 cycles 10 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 674 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(1) One separated circumferential tube (2) 3 in. (76.2 mm) cumulative cooling air manifold crack (3) One separated cooling air tube support D. Thread ports and bosses (1) One crack 0.5 in. (12.7 mm) maximum providing there is no leakage
10 cycles
13. Turbine frame A. Forward and aft flanges
10 cycles
(1) One circumferential crack connecting two bolt holes (2) One crack into skin 0.5 in. (12.7 mm) maximum B. Engine mounting lug areas airframe attach points only
10 cycles
(1) One crack out of one mount lug bolt hole 0.25 in. (6.35 mm) maximum (2) Skin crack 0.25 in. (6.35 mm) maximum. C. Threaded parts and bosses
10 cycles
(1) One crack 0.5 in. (12.7 mm) long providing there is no fluid or air leakage D. Stud on the aft face of the inner hub. (1) Missing/broken/loose stud(s): - One (1) or two (2) studs:
500hrs/500cyc
- Three (3) studs: *If not adjacent to each other:
500hrs/500cyc
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 675 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------*If two (2) non-serviceable studs are 500hrs/500cyc adjacent, but the third one is separated from them by two (2) serviceable studs: *If not:
Replace studs
- Four (4) studs or more:
Replace studs
E. Thermal insulation blankets
100 cycles
(1) Missing or protruding blankets F. Other areas
10 cycles
(1) One crack 0.25 in. (6.35 mm) maximum 14. Accessory gearbox A. Two opposite keylock studs missing provided there is no leakage at flange
3 cycles or 30 hours
B. Oil leakage from AGB/Starter carbon seal (Ref. TASK 79-00-00-210-003)
10 cycles provided seal drain line is disconnected and drain cavity is capped
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 676 Feb 01/10
C F M 56-5B TASK 72-00-00-200-025- 01 Over-Serviceable-Limit Extensions 1. __________________ Reason for the Job This TASK is applicable to /P engines and /3 engines. It can occur that specific defects do not agree with the Maximum Serviceable Limits, and that the maintenance facilities, at a given location, are not sufficient to do the necessary corrective actions. In these circumstances, limit extensions will permit to send the engine where correction is possible, or to schedule the necessary maintenance in the extension period. NOTE : The limit extensions are one-time extensions only. Applicable ____ hardware action is necessary at the completion of the extended serviceable period. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-210-006 72-21-00-210-009 72-23-00-210-003 79-00-00-210-003 72-00-00-991-308 72-00-00-991-309 72-00-00-991-321 72-00-00-991-320
Inspect Fan Rotor Blades Removed from the Fan Disk. Inspect Fan Rotor Blades Installed on the Fan Disk Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material Visual Inspection of the Oil System Fig. 607 Fig. 608 Fig. 609 Fig. 610
3. __________ Job Set-up Subtask 72-00-00-941-105 A. Not applicable
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 677 Nov 01/09
C F M 56-5B 4. Procedure _________ (Ref. Fig. 607/TASK 72-00-00-991-308, 608/TASK 72-00-00-991-309, 609/TASK 72-00-00-991-321, 610/TASK 72-00-00-991-320) Subtask 72-00-00-210-101 A. Over-serviceable-limit Extensions ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------1. Fan and booster A. Spinner front cone (1) Damaged surface protection greater than 50 percent of total surface
50 cycles
(2) Corrosion marks (white mushroom pattern) before part removal
A continuation in service of 100 cycles maximum is permitted
B. Spinner rear cone (1) Oil wetting at inner of spinner cone or fan disk or forward fan shaft
50 cycles
(2) Seal ring tear: any number if cumulated length is more than 0.4 in. (10 mm)
50 cycles
C. Fan blade (1) Fully missing molydag on inner faces of the platforms
250 cycles
(2) Flaking of Cu.Ni.In coating on blade dovetail pressure faces (contact areas), up to 10 percent if there is no indication of wear on base material
Examine blades for serviceability. (Ref. TASK 72-2100-210-006) 1200 cycles after relubrication. Repeat extension is permitted
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 678 Nov 01/09
C F M 56-5B
HPT Blade Inspection (Only Applicable /P Engines) Figure 610/TASK 72-00-00-991-320 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 679 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Flaking of Cu.Ni.In coating on blade dovetail 400 cycles after pressure faces (contact areas), more than 10 relubrication. percent and less than 50 percent if there is Repeat extension is no indication of wear on base material not permitted (4) Shingling at mid span shrouds
Turn the shingled blades to the 12 oclock position and unshingle with hand force or by using a piece of wood. Examine blades for serviceability (Ref. TASK 72-2100-210-009) Remove and send the shingled blades to a shop for a dimensional and an F.P.I. inspection in less than 50 cycles
(5) Nicks, dents, scratches and sheared edges on midspan shroud surfaces up to 0.035 in. (0.89 mm) deep if defects are not in the midspan shroud to airfoil fillet radius
50 cycles
(6) Missing or damaged hard coating on midspan shroud pressure faces more than 20 percent but less than 40 percent of coated area
50 cycles
D. Fan disk (1) Wear greater than 50 percent of area on disk dovetail pressure faces
100 cycles
E. Booster rotor blade for: (1) Piece missing:
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 680 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------any number in area G, at leading edge and 50 cycles/75 hours trailing edge tip corners, 0.8 in. (20 mm) radial and 0.5 in. (12.5 mm) axial (2) Cracks and tears in area G, 0.8 in. (20 mm) from tip : any number less than 0.8 in. (20 mm) radial and less than 0.492 in. (12.5 mm) axial
50 cycles/75 hours
(3) Wear or local distortion of T/E and L/E tips if less than 15 blades 0.984 in. (25 mm) radial and 0.59 in. (15 mm) axial
100 cycles/150 hours
(4) Nicks, dents, scratches for area E: any number, less than 0.059 in. (1.5 mm) in diameter, protrusion acceptable, not thru
50 cycles/75 hours
(5) Nicks, dents, scratches for airfoil out of area E, not L/E and T/E: any number, less than 0.236 in. (6 mm) in diameter, protrusion acceptable
50 cycles/75 hours
(6) Nicks, dents, scratches out of area E on L/E and T/E: maximum axial length less than 0.059 in. (1.49 mm)
50 cycles/75 hours
(7) Distorted L/E and T/E, out of area E maximum circumference equals 0.275 in. (6.98 mm) radial length equals 0.708 in. (17.98 mm)
50 cycles/75 hours
F. Booster vanes (stage 1 only) for: (1) Piece missing: maximum 20 blades more than 0.256 in. (6.5 mm) axial, 0.728 in. (18.49 mm) radial, no cracks starting from damage area allowed in areas A and B
50 cycles/75 hours
(2) Cracks and tears in than 0.256 in. (6.5 (1.98 mm) axial. In more than 0.128 in. 0.039 in. (0.99 mm)
10 cycles/15 hours
area C, any number, more mm) radial and 0.078 in. areas A and B, any number (3.25 mm) radial and axial
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 681 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Distortion of T/E and L/E: any number, if the 50 cycles/75 hours length L is no more than 1 in. (25.4mm) and the maximum dimension X along the chord width is not more than 0.492 in. (12.5mm) (4) Nicks, dents, scratches for areas A and B ; any number, less than 0.157 in. (3.99 mm) in diameter, protrusion permitted
10 cycles/15 hours
(5) Nicks, dents, scratches for area C: any number, less than 0.295 in. (7.49 mm) in diameter, protrusion permitted
50 cycles/75 hours
(6) Nicks, dents, scratches L/E and T/E maximum axial length less than 0.118 in. (2.99 mm) in diameter
20 cycles/30 hours
(7) Cracked inner shroud: Maximum of 4 cracks extending from the L/E to the T/E of the inner shroud (passing through a recess) are permitted if there is a minimum separation of 3 non-cracked vane recesses between 2 cracked recesses.
3000 hours/C check
A sound check (see note below) done on the vanes at, and adjacent to the cracked inner shroud area, must demonstrate no difference in tonality.
This extension may be used again indefinitely in intervals of 3000 hours as long as there is no further deterioration of these conditions.
NOTE : Sound Tonality Check Recommendation: ____ A sound tonality check must be done to detect if the abradable material inside the inner shroud is still in contact with the root of the vane. Use a smooth-ended cylindrical tool made of steel with diameter of approximately 0.5 in. (12.6999 mm). (For example, a ratchet wrench extension bar). Tools made of aluminium, plastic or wood do not permit the detection of significant variation in the sound tone from one vane to the next. Removal of 2 or 3 fan blades gives a better accessibility to do the check.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 682 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------Be careful to not use a tool or excessive force during the check. This would damage the vanes. Do the check on an area including 3 or 4 vanes on each side of the vane where the cracked inner shroud is located. Place the tool on the leading edge mid-span of the couterclockwise most vane. Lightly stroke the vane and subsequent vanes in the clockwise direction using a constant speed. Note any variations in the sound tone from one vane to the next. If there is a difference between the vane where the recess is cracked and the other vanes, the stage 1 vane assembly is unserviceable. (8) Vane leading and trailing edges - Nicks, dents and scratches on LE/TE in areas B and C with a maximum axial length less than 0.117 in. (2.97 mm) - Nicks, dents and scratches on LE/TE in area A with a maximum axial length of 0.117 in. (2.97 mm)
10 cycles/50 hours
2 cycles/10 hours
2. Fan frame A. Fan frame (1) Cracks, any number if max length of 0.16 in. (4.06 mm) and min. separation of 1 in. (25.4 mm)
10 cycles or 25 hours
(2) Nicks and dents, any number
10 cycles or 25 hours
B. Fan inlet case (1) Cracks: any number, if max length of 0.16 in. (4.06 mm) and min. separation of 1 in. (25.4 mm)
10 cycles or 25 hours
(2) Nicks and scratches: any number
10 cycles or 25 hours
(3) Crater in abradable liner (length<5x width) and damage other than crack rub and
50 cycles or 125 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 683 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------circumferential defect : If the damage is within the maximum serviceable limit, (Ref. TASK 72-23-00-210-003), but the fan case parent metal is exposed and is confirmed via visual inspection to be undamaged. (4) Grooves in abradable liner (oriented within 0 deg. to 80 deg. from engine axis and length>5x width : If the damage is within the maximum serviceable limit, (Ref. TASK 72-2300-210-003) but the fan case parent metal is exposed and is confirmed via visual inspection to be undamaged
50 cycles or 125 hours
(5) Circumferential defect in abradable liner (360 deg. or oriented within 80 deg. to 90 deg. from engine axis) : for one or a cumulated defect less than 2 in. (50.8 mm) if the fan case parent metal remains not damaged under visual inspection.
50 cycles or 125 hours.
C. Outlet Guide Vanes (OGV) for: (Ref. Fig. 609/TASK 72-00-00-991-321) (1) Broken vane: Not serviceable, if vane is replaced
10 cycles extension
(2) Missing vane: One doublet missing
10 cycles extension
(3) Crack Outer platform: cracks from or along the airfoil are defined (Ref. Fig. 609/TASK 72-00-00-991-321)
50 cycles extension
(4) Metal leading edge missing: up to 0.78 in. (20 mm) in height and 0.39 in. (10 mm)
100 cycles extension
(5) Nicks and/or dents, on leading edge (metallic leading edge), if damage between 0.12 in. (3 mm) and 0.19 in. (5 mm) deep
A maximum service extension of 100 cycles
(6) Erosion of composite material, any amount
50 cycles or 125 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 684 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------D. OGV inner shroud (1) Cracks, cut or torn seal at mating with OGV, any amount
25 cycles or 50 hours
E. Fan duct panels (1) One fan duct panel missing is permitted, if you make sure that the VBV area is free of unwanted object before the first aircraft release of the day.
10 cycles
(2) Missing lowers on panel
50 cycles with 3 missing lowers maximum
F. Splitter fairing (1) Cracks: any amount
10 cycles or 25 hours
G. Mid acoustical panels
20 cycles
(1) Disbonded damper more than 20 percent of the total surface 3. Compressor rotor A. Compressor rotor blades NOTE : The depth of a defect such as a nick is measured along the axis of ____ the damage unless otherwise noted. (1) Stages 1-4 radial cracks within 0.30 in. (7.6 mm) of the leading and trailing edges more than 0.25 in. (6.4 mm) but less than 0.40 in. (10.2 mm) in length.
10 cycles or 25 hours
(2) Stages 1-4 chord-wise cracks more than 0.20 in. (5.1 mm) but less than 0.30 in. (7.6 mm) in length.
10 cycles or 25 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 685 Feb 01/10
R R R
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(3) Stages 1-4 nicks, missing material and 10 cycles or 25 erosion on the leading and trailing edges hours found in Dim. B more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm), if the HPC blade is NOT a Tech Insertion stage 4 blade (PN P394XXX).
R R R R R R
(4) Stages 1-4 nicks, missing material and erosion on the leading and trailing edges found in Dim. B more than 0.03 in. (1.0 mm) in depth but less than 0.08 in. (2.0 mm) in depth, if the HPC blade is a Tech insertion stage 4 blade (PN P394XXX).
10 cycles or 25 hours
R
(5) Stages 1-4 dents on the leading and trailing edges found in Dim. B more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm) in depth, or less than 0.06 in. (1.5 mm) deflection from the original contour.
10 cycles or 25 hours
R
(6) Stages 1-4 nicks, dents and tears on the leading and trailing edge in Dim. A more than 0.25 in. (6.4 mm) but less than 0.30 in. (7.6 mm) in depth.
10 cycles or 25 hours
R R
(7) Stages 1 missing material and erosion at the leading and trailing edge tip corners more than 0.30 in. (7.6 mm) but less than 0.40 in. (10.1 mm).
10 cycles or 25 hours
R R R R
(8) Stage 2, more than 4 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
R R R R
(9) Stage 3, more than 5 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
R R R R
(10) Stage 4, more than 6 blades missing material and erosion at the leading and trailing edge tip corners more than 0.030 in (7.6mm) in depth but less than 0.40 (10.2mm) in depth.
10 cycles or 25 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 686 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(11) Stages 1-4 nicks, dents and missing material 10 cycles or 25 on the leading and trailing edges of the hours lower 25% of the airfoil (but not the root radius) more than 0.03 in. (0.76 mm) but less than 0.08 in. (2.0 mm).
R
(12) Nicks, dents, wear and scratches of the trailing edge root radius of stage 2 and stage 3 of more than 0.03 in. (0.8 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R
(13) Stages 5-9 radial cracks that are no more than 0.20 in. (5.1 mm) from the leading or trailing edge and more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm) in length.
10 cycles or 25 hours
R
(14) Stages 5-9 chord-wise cracks that are no more than 0.20 in. (5.1 mm) from the tip and are more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm) in length.
10 cycles or 25 hours
R
(15) Stages 5-9 nicks, tears, missing material and erosion on the leading and trailing edges found in Dim. B that are more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R
(16) Stages 5-9 dents on the leading and trailing edges found in Dim. B that are more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm) in depth or less than 0.06 in. (1.5 mm) deflection from the original contour.
10 cycles or 25 hours
R
(17) Stages 5-9 nicks, dents and tears on the leading and trailing edges found in Dim. A that are more than 0.15 in. (3.8 mm) but less 0.20 in. (5.1 mm).
10 cycles or 25 hours
R
(18) Stages 5-9 missing material and erosion at the leading and trailing edge tip corners if the damage is more than 0.20 in. (5.1 mm) but less than 0.30 in.
10 cycles or 25 hours
Stages 5-9 curl on the end of the airfoil when the blade chord is more than 50%
10 cycles or 25 hours
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 687 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(19) but less than 75% of the chord maximum radial length, 0.3 in. (7.6 mm), when it does not engage the stationary parts during operation.
R
(20) Stages 5-9 nicks, dents and missing material edges found in the lower 25% of the airfoil (but not the root radius) more than 0.03 in. (0.76 mm) but less than 0.08 in. (2.0 mm).
10 cycles or 25 hours
R
(21) Stages 2-3 trailing edge root radius nicks, dents and scratches more than 0.03 in. (7.6 mm) but less than 0.08 in. (2.0 mm) in depth.
10 cycles or 25 hours
R
(22) Stages 4-9 blade locks with two cracks.
10 cycles or 25 hours
R
(23) Stages 4-9 blade locks that are loose.
25 cycles or 100 hours
4. Compressor front stator A. Casing cracks 0.17 in. (4.32 mm) max length in skin
10 cycles or 25 hours
B. Casing nicks, pits, scores or scratches, any amount, any depth
10 cycles or 25 hours
C. Broken actuation ring connector, one side only, if connector is replaced
5 cycles
D. Vane actuation ring cracks, distortion, bends, twists or distress, provided ring has not separated
5 cycles
E. Loose vane assemblies with metal-to-metal contact on up to 50 percent of vanes
10 cycles or 25 hours
5. Combustion case A. Forward and aft flange radial cracks inward from bolt holes
10 cycles
B. Midflange radial cracks
10 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 688 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------C. Maximum of 10 broken midflange bolts with no more 25 cycles than 4 broken bolts in any group of 20 D. High pressure turbine (HPT) shroud cooling and compressor discharge pressure (CDP) pad cracks more than 0.06 in. (1.52 mm) from bolt holes
10 cycles
6. Combustion chamber A. Dome assembly (1) Radial crack in spectacle plate
25 hours
Any number up to 2.5 inches (63.5 mm) in length and not connected to each other. (2) Circumferential crack in spectacle plate
25 hours
Any number up to 3.6 inches (91 mm) in length separated by 4.8 inches (125 mm) (3) Connected cracks in spectacle plate
25 hours
Not more than (1) radial crack 2.5 in. (50.8 mm) long with (1) circumferential crack 3.6 in. (91 mm) long, separated by 4.8 in. (125 mm) (4) Missing material from spectacle plate
25 hours
The damage is more then the given limits (5) Radial crack in deflector or sleeve
25 cycles
Any number up to 0.6 in. (16 mm) in length (6) Circumferential cracks in deflector or sleeve
25 cycles
Any number up to 0.9 in. (23 mm) in length (7) Connected cracks in deflector or sleeve
25 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 689 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------Connection of any radial and circumferential cracks within limits of (5) and (6) above. Limit is exceeded when third crack connects (8) Missing material from overhangs on deflector or sleeve
50 cycles
Any amount up to 0.240 in. (6.10 mm) maximum depth (9) Burn through holes
25 cycles
3 per dome 1.2 in. (30mm) x 1.2 in. (30 mm) maximum. B. Inner and outer liners (1) Outer liner axial cracks
100 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 5 panels in sequence (2) Outer liner axial cracks (from outer side borescope)
25 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 5 panels. At least one of the cooling ribs (3, 4, 5, or 6) does not have cracks that extend through to the outer side. Rib 1 is not cracked through. (3) Inner liner axial cracks
100 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 4 panels in sequence (4) Circumferential cracks
25 cycles
Any number up to 3 dilution lands in length separated by 3 non-cracked dilution lands (5) Connected cracks
100 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 690 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------Connection of any axial and circumferential cracks up to max limits of paragraphs (1), (2), (3), and (4) (6) Burn through or missing material
100 cycles
There are not more than 8 areas that are not more than 2 times the diameter of a dilution hole. There are not more than 2 areas that are not more than 3 times the diameter of a dilution hole. There are not more than one area that is not more than 4 times the size of a dilution hole. There are not more than 3 areas in adjacent panels that are aligned axially if they have a separation of a minimum of 3 dilution lands that are not damaged. (7) Missing overhangs
25 cycles
Per liner: 17 areas each twice the size of a dilution hole, providing max axial alignment of distress is 3 adjacent panels (8) Distortion
25 cycles
Any amount within 0.7 in. (17.8 mm) of original contour C. Combustor inner cowl bolts (1) Missing bolt: Maximum of 3 bolts are missing with 4 bolts intact between 2 missing bolts. All other bolts are tight with tack welds intact
50 cycles for next check, then repeat BSI every 400 cycles
(2) Bolt tack weld cracked but bolt is not loose: If a maximum of 5 tack welds are cracked, no more than two consecutive, with 4 tack welds intact between two cracked tack welds
25 cycles for first check, 50 cycles for second check, repeat BSI check 100 cycles
(3) Bolt tack weld is cracked and bolt is loose: If one or more bolts are loose
5 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 691 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------7. HPT nozzle A. Leading edge missing material, from cracking or burn-through, up to 0.5 in. (12.7 mm) X 0.5 in. (12.7 mm) per vane. Maximum of 4 vanes per 90 degree arc
25 cycles
B. Concave surfaces of airfoil missing material, from cracking or burn-through, up to 0.75 in. (19.0 mm) diameter per vane
25 cycles
C. Convex surfaces of airfoil missing material from cracking or burn-through, up to 0.75 in. (19.0 mm) diameter per vane
25 cycles
D. Inner and outer platforms missing material, from cracking or burn-through, up to 0.5 in. (12.7 mm) diameter per segment
25 cycles
E. Trailing edge missing material up to 0.75 in. (19 mm)in axial direction
25 cycles if HPT blades are within limits
F. Baffle missing material, any amount.
10 cycles
8. HPT rotor blade (Ref. Fig. 610/TASK 72-00-00-991-320) A. Trailing edge cracks in Area A less than 0.2 in. (5.08 mm) long
40 cycles
B. Convex airfoil cracks within 0.5 in. (12.7 mm) of trailing edge (10 blades maximum) in Area B less than 0.3 in. (7.62 mm) long
25 cycles
C. Trailing edge cracks in Areas B and C less than 0.30 in. (7.62 mm) long
40 cycles
D. Radial tip cracks on the convex side not within 0.5 in. (12.7 mm) of the trailing edge, less than 0.35 in. (8.9 mm) long
50 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 692 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------E. Radial tip cracks on the concave side not within 50 cycles 0.5 in. (12.7 mm) of the trailing edge, less than 1.0 in. (25.4 mm) long F. Leading edge cracks in Area A less than 0.1 in. (2.54 mm) long
10 cycles
G. Axial nose or gill hole cracks in Areas B and C less than 0.05 in. (1.27 mm) long
10 cycles
H. Radial nose or gill hole cracks in Area B less than 0.06 in. (1.52 mm) long
10 cycles
J. Radial nose or gill hole cracks in Area C less than 0.03 in. (0.76 mm) long
10 cycles
K. Missing material at trailing edge tip and Area A up to 0.5 in. x 0.75 in. (12.7 mm x 19 mm)
50 cycles
L. Leading edge missing material in areas A and B. Any amount provided cavity 2 is not exposed (any number of blades)
25 cycles
M. Airfoil distortion or evidence of burning or melting (10 blades maximum)
25 cycles
N. Airfoil tip bent, curled, or missing material if the missing material below the tip shelf is less than 0.05 in. (1.27 mm) in diameter
10 cycles
P. Airfoil convex and concave surface nicks or dents in Areas A, B and C if no cracks or missing material
25 cycles
9. HPT shroud and stage 1 low pressure turbine (LPT) nozzle A. HPT shrouds (1) Circumferential cracks that connect and are more than 1 in. (25.3999 mm) long.
25 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 693 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(2) Circumferential cracks more than 0.25 in. 25 cycles (6.3499 mm) long that connect to axial cracks in Area B. (3) Burn through of shroud rub land
25 cycles
B. Stage 1 LPT nozzle (1) Cracks in all areas up to 1.4 in. (35 mm) long provided not found on 2 adjacent airfoil segments
10 cycles
(2) One crack permitted on each airfoil, from leading edge to trailing edge, if there is no missing material.
100 cycles
(3) Burns, erosion, corrosion and missing metal up to 1 in.2 (645.16 mm2) per airfoil and no cracks extending from distressed area
5 cycles
(4) Cracks in outer and inner platforms up to 1.0 in. (25 mm) provided not found on 2 adjacent airfoil segments
100 cycles
10. LPT Rotor A. LPT blades (all stages) (1) Blade pretwist - Total gap, for stage 1, up to 0.1 in. (2.54 mm)
5 cycles
- Stage 2-4 gaps such that adjacent interlocks do not contact each other
5 cycles
(2) 0.08 in. (2.03 mm) max. deflection over a length 10 times longer max, only for stage 1 LPT blades distorted leading edges, due to overtemperature
15 cycles
(3) Stage 1, 2, 3 blades
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 694 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------- Area E: 5 cycles or 10 Any amount of impact damage/rubbing hours provided there is no missing material or cracks - Other areas: Any amount of impact damage such as bending, nicks and/or dents is allowed provided there is no missing material or cracks exceeding 50 percent of chord width
5 cycles or 10 hours
(4) Stage 4 blades - Any amount of tip shroud interlock wear allowed
25 cycles or 50 hours
- Blade tip shroud protrusion not to exceed 0.04 in. (1.01 mm)
10 cycles or 25 hours
- Area E: Any amount of impact damage such as nicks and/or dents is allowed provided there is no missing material or cracks
5 cycles or 10 hours
- Other areas: Any amount of impact damage. One complete airfoil and any number of tip shrouds with associated airfoil tips may be missing provided engine vibration is not excessive
5 cycles or 10 hours
- Blade tip shrouds shingled or unlatched provided rotor turns freely and engine vibration is not excessive
5 cycles or 10 hours in shingled condition.
B. Nozzle segments 2 to 4 (1) Three cracks maximum for each nozzle segment if cracks are more than 0.5 in. (12.7 mm) (1/3 of the chord width) and less than 1.0 in. (25.4 mm) (2/3 of the chord width) if the adjacent nozzle segments have no more than two cracks more than 0.5 in. (12.7 mm) (1/3
200 cycles
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 695 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------of the chord width) and less than 1.0 in. (25.4 mm) (2/3 of the chord width). (2) One crack maximum for each nozzle segment that is more than 1.0 in. (25.4 mm) (2/3 of the chord width) including open airfoil.
200 cycles
(3) One full chord crack on two airfoils for each segment if the adjacent nozzle segments have no more than one airfoil with a full chord crack.
25 cycles
(4) Nicks, dents, tears, missing pieces up to 2 in.2 (1290.32 mm2) on nonadjacent vanes provided there are no cracks extending from distressed areas
10 cycles
(5) Burned areas with missing material or melted
25 cycles
C. Stage 4 shroud abradable material (1) Worn, jagged or crushed sealing surface exceeding 50 percent of the honeycomb height provided sectors of the shroud abradable material are not missing
10 cycles
11. LPT Casing A. Forward and aft flanges (1) One crack connecting 2 bolt holes without penetrating pressure vessel outer skin
10 cycles
(2) One crack into skin 0.4 in. (10.16 mm) long maximum
10 cycles
B. External surface of the casing (1) One crack 0.4 in. (10.16 mm) long maximum C. Cooling air tube and manifold assemblies
10 cycles 10 cycles
(1) One separated circumferential tube
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 696 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------(2) 3 in. (76.2 mm) cumulative cooling air manifold crack (3) One separated cooling air tube support D. Thread ports and bosses (1) One crack 0.5 in. (12.7 mm) maximum providing there is no leakage
10 cycles
12. Turbine frame A. Forward and aft flanges
10 cycles
(1) One circumferential crack connecting two bolt holes (2) One crack into skin 0.5 in. (12.7 mm) maximum B. Engine mounting lug areas airframe attach points only
10 cycles
(1) One crack out of one mount lug bolt hole 0.25 in. (6.35 mm) maximum (2) Skin crack 0.25 in. (6.35 mm) maximum. C. Threaded parts and bosses
10 cycles
(1) One crack 0.5 in. (12.7 mm) long providing there is no fluid or air leakage D. Stud on the aft face of the inner hub. (1) Missing/broken/loose stud(s): - One (1) or two (2) studs:
500hrs/500cyc
- Three (3) studs: *If not adjacent to each other:
500hrs/500cyc
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 697 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------CONDITION MAX EXTENSION ------------------------------------------------------------------------------*If two (2) non-serviceable studs are 500hrs/500cyc adjacent, but the third one is separated from them by two (2) serviceable studs: *If not:
Replace studs
- Four (4) studs or more:
Replace studs
E. Thermal insulation blankets
100 cycles
(1) Missing or protruding blankets F. Other areas
10 cycles
(1) One crack 0.25 in. (6.35 mm) maximum 13. Accessory gearbox A. Two opposite keylock studs missing provided there is no leakage at flange
3 cycles or 30 hours
B. Oil leakage from AGB/Starter carbon seal (Ref. TASK 79-00-00-210-003)
10 cycles provided seal drain line is disconnected and drain cavity is capped
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 698 Feb 01/10
C F M 56-5B TASK 72-00-00-200-026 Inspection/Check of the PS3 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific
plastic wire warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN)
No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddart solvent (Ref. 70-30-00) * graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 699 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP8001
Material No.
CP8002
* lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------36-11-49-000-044 36-11-49-400-044 71-13-00-010-040 71-13-00-410-040 72-00-00-991-313
Removal of the High Pressure Tee Duct Installation of the High Pressure Tee Duct Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Fig. 601
3. __________ Job Set-up Subtask 72-00-00-941-072 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A600 Feb 01/10
C F M 56-5B Subtask 72-00-00-010-086 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-00-00-991-313) CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO HOLD _______ THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. Subtask 72-00-00-210-068 A. Visual Inspection of the PS3 Line (1) Inspect the PS3 line as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. The tubes for: - cracks
Not serviceable
Replace the tube
- dents
4 per lineal foot, spaced at least 1 in. (25,4 mm) apart, provided depht of each dent does not exceed 20 percent of tube outer diameter for straight section or 10 percent of tube outer diameter for bend section
- flat areas
Lenght shall not be greater than 3 times the tube outer diameter, and contour change shall not exceed 20 percent of
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A601 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------tube outer diameter for straight section or 10 percent of tube outer diameter for bend section - nicks, scratches
0.005 in. (0,13 mm) max. depht
The hose for: - broken hose braid
3 broken wires per plait, and no more than 6 broken wires per assembly, or per lineal 12 in. (305 mm) of hose
- chafing on hose
Not serviceable
Replace the hose
- crimps
Not serviceable
Replace the hose
- cuts, tears, chafing on fire sleeves
Any number, provided maximum depth does not exceed one-half of sleeve thickness
Subtask 72-00-00-280-063 B. Dry out and Cleaning of the PS3 Line (1) Cut and remove the lockwire. (2) Disconnect the PS3 hose (20) from the ECU. (3) Disconnect the PS3 tube from the core engine as follows: (a) If necessary, get access to the PS3 restrictor: Remove the High Pressure Tee Duct (Ref. TASK 36-11-49-000-044). (b) Remove the nut (160), the bolt (190) and the clamp (180) which attach the PS3 tube (170) to the bracket (150), on flange P, at the 8 oclock position (Detail F).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A602 Feb 01/10
C F M 56-5B (c) Cut and remove the lockwires. (d) Disconnect the PS3 tube (170) from the restrictor (200). (e) Remove the restrictor from the engine. (4) Cut and remove the lockwires. (5) Disconnect the PS3 hose (20) from the ECU and from the PS3 tube (10). (6) Check the hose for blockage blocked hose is not serviceable: Replace the hose (20). (7) Blow clean dry air into the PS3 tube (10) end to remove any dirt or water accumulation in the PS3 line. Subtask 72-00-00-020-052 C. Removal of the PS3 Line Connections NOTE : Do the steps which follows only if you suspect leakage. ____ (1) Cut and remove the lockwire which safeties the PS3 tube (10) to the tube bundle. (2) Disconnect the PS3 tube (10) from the tube bundle. (3) Remove the parts which attach the PS3 tube (10) to the engine as follows: ---------------------------------------------------------------------------| REMOVE | FROM | NOTE | ---------------------------------------------------------------------------|Nut (70) | Bracket (40) and P25 | At the 6:30 oclock | |Bolt (30) | tube on flange G | position (Detail C) | |Outer spring clip (60) | | | |Inner spring clip (50) | | | |Plastic bushing (80) | | | ---------------------------------------------------------------------------|Nut (130) | Bracket (120) and P25 | At the 5 oclock | |Bolt (90) | on flange G | position (Detail C) | |Outer spring clip (100) | | | |Inner spring clip (110) | | | |Plastic bushing (140) | | | ---------------------------------------------------------------------------(4) Remove the PS3 tube (10) from the engine.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A603 Feb 01/10
C F M 56-5B Subtask 72-00-00-210-069 D. Inspection of the PS3 Line Connection (1) Inspect the connecting parts as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fitting nuts for: - damaged corners
Any amount, provided proper torque can be obtained
- damaged threads
Any amount, provided effective threads are not reduced by more than one after chasing
- safetywire hole deformation and wear
Serviceable, provided metal around hole is not cracked or torn
Chase the threads
2. Fittings and restrictor (200) seating surfaces for: - circumferential scratches
Any amount not detectable with a 0.04 in. (1 mm) radius ball scribe
- axial scratches
Not serviceable
Replace the tube or the part
- nicks, pits
Not serviceable
Replace the tube or the part
(2) If necessary, clean the parts with: stoddart solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A604 Feb 01/10
C F M 56-5B (3) If necessary, remove the dirt from the ECU nipple with a plastic wire. Take care to not introduce dirt into the ECU. (4) Check the tube bundle weep hole for clogging or dirt accumulation. (5) If necessary, clean the tube bundle weep hole with stoddart solvent (Material No. CP2011) or acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) and a plastic wire. Subtask 72-00-00-420-056 E. Installation of the PS3 Line CAUTION : DURING INSTALLATION, MAKE SURE THAT THE PS3 LINE DOES NOT TOUCH _______ THE LOWER STARTER DUCT OR OTHER PARTS IN THIS AREA. IF IT DOES, CHAFING OF THE PS3 HOSE CAN OCCUR. (1) Install the reducer (200) on the core engine. (2) TORQUE the reducer to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (3) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (4) Connect the PS3 tube (170) to the reducer on core engine. (5) TORQUE the connecting nut to between 135 and 150 lbf.in (1.52 and 1.69 m.daN). (6) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (7) Lubricate the threads of the bolt (190) with graphite grease (Material No. CP2101). (8) Install the clamp (180), the bolt (190) and the nut (160) which secure the PS3 tube (170) to the bracket (150) on flange M, at the 8 Oclock position (Detail F). (9) TORQUE the nut (160) to between 55 and 70 lbf.in (0.62 and 0.79 m.daN).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A605 Feb 01/10
C F M 56-5B (10) If necessary, install the High Pressure Tee Duct (Ref. TASK 36-11-49400-044). (11) Lubricate the threads of the tube bundle tube. (12) Connect the PS3 tube (10) to the tube bundle tube nipple by hand. (13) Install the parts which secure the PS3 tube (10) to the engine as follows: ----------------------------------------------------------------------------| INSTALL | ON | NOTE | ----------------------------------------------------------------------------| Nut (70) | Bracket (40) and P25 | At the 6:30 Oclock | | Bolt (30) | tube on flange G | position (Detail C) | | Outer spring clip (60) | | | | Inner spring clip (50) | | | | Plastic bushing (80) | | | ----------------------------------------------------------------------------| Nut (130) | Bracket (120) and P25 | At the 5 Oclock | | Bolt (90) | tube on flange G | position (Detail C) | | Outer spring clip (100)| | | | Inner spring clip (110)| | | | Plastic bushing (140) | | | ----------------------------------------------------------------------------(14) TORQUE the PS3 tube (10) connecting nut to the tube bundle to between 135 and 150 lbf.in (1.52 and 1.69 m.daN). (15) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (16) TORQUE the nuts (70), (130) to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). (17) Lubricate the ECU and PS3 tube (10) nipples with engine fuel. (18) Connect the PS3 hose (20) to the ECU and to the PS3 tube (10). (19) TORQUE the PS3 hose connecting nuts to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (20) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). NOTE : The PS3 and the PS12 connecting nuts are safetied together. ____
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A606 Feb 01/10
C F M 56-5B 5. Close-up ________ Subtask 72-00-00-410-086 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A607 Feb 01/10
C F M 56-5B TASK 72-00-00-200-028 Visual Inspection of the Fan Section after Engine Operation in Severe Icing Condition 1. __________________ Reason for the Job You must do a visual inspection of the fan section area (primarily, the front end of the fan section) after the engines have operated in bad icing conditions. NOTE : This inspection can be done with the fan cowl and thrust reverser ____ cowl doors closed. If necessary, use an electric torch (flashlight) to look rearwards through the fan rotor blades. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
electric torch (flashlight) rubber mat, or equivalent floor protection
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-210-005 72-21-00-210-009 72-23-00-210-004
Inspection/Check of the Spinner Cone Inspect Fan Rotor Blades Installed on the Fan Disk Visual Inspection of the Fan Frame Assembly
3. __________ Job Set-up Subtask 72-00-00-941-073 A. Put a rubber mat, or equivalent floor protection, in the powerplant inlet cowl before you go into it to do this inspection. If necessary, use an electric torch (flashlight) for a better lighting aft of the fan rotor blades.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A608 Feb 01/10
C F M 56-5B 4. Procedure _________ Subtask 72-00-00-210-072 A. Visual Inspection (1) Look for possible damage to the spinner front and rear cones exposed areas (Ref. TASK 72-21-00-210-005). (2) Examine the general condition of the fan rotor blades (Ref. TASK 7221-00-210-009). (3) Look for possible damage to the fan forward acoustical panels (Ref. TASK 72-23-00-210-004). (4) Through the fan rotor blades, look for possible damage to: NOTE : If necessary, (dim lighting conditions) use an electric torch ____ (flashlight). (a) The leading edge of fan outlet guide vanes (OGVs), (b) Splitter fairing, (c) Fan mid acoustical panels (located between the fan rotor blades and the OGV assembly), (Ref. TASK 72-23-00-210-004). 5. Close-up ________ Subtask 72-00-00-869-074 A. Put the aircraft back to its initial configuration. (1) Remove the rubber mat, or equivalent floor protection from the powerplant inlet cowl. (2) Make sure the inlet cowl area is clean and clear of tool(s) and other items.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page A609 Feb 01/10
C F M 56-5B TASK 72-00-00-280-002 Monitor the Engine EGT for Possible Engine Performance Deterioration 1. __________________ Reason for the Job PRE SB CFM56-5B 72-182 This TASK is applicable for /P engines. POST SB CFM56-5B 72-182 After SB CFM56-5b 72-182 is done with the 2D stage 9 blades, this TASK is no longer needed. 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-41-00-861-002 24-41-00-862-002 TSM
77-00-00-810-849
Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EGT Overlimit on Engine 1 or 2
3. __________ Job Set-up Subtask 72-00-00-861-054 A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 72-00-00-869-085 B. Get the engine takeoff EGT data, with the use of the MCDU or DAR/QAR data.
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Page A610 Feb 01/10
C F M 56-5B 4. Procedure _________ Subtask 72-00-00-280-065 A. Do this procedure to get engine EGT trend information. (1) Takeoff EGT data must be recorded and evaluated as follows: (a) Once each month during usual conditions. (b) Once each week if the calculated EGT margin (see EGT Calculation Procedure paragraph) becomes 20 deg.C (36.00 deg.F), or less. (c) Once each day if the calculated EGT margin (see EGT Calculation Procedure paragraph) becomes 10 deg.C (18.00 deg.F), or less. (d) The next flight immediately after an unusual condition that can cause engine deterioration such as: 1 _
a bird strike,
2 _
other unwanted materials that have gone into the engine,
3 _
engine vibration advisory warning.
(2) After an unusual condition, if the data shows an EGT margin more than the 20 deg.C level, examine the data once each month. After an unusual condition, if the data shows an EGT margin between the 10 deg.C and 20 deg.C levels, examine the data once each week. Subtask 72-00-00-970-050 B. EGT Calculation Procedure (1) Do the procedure that follows to calculate the EGT margin. (a) Use the CFMI trend monitoring programs (GEM or ADEPT) and process the recorded takeoff data. (b) Calculate 5B/P EGTMARGIN as follows: EGTMARGIN=EGTMAR+EGTADJ where: EGTMAR=EGT margin output from GEM or ADEPT and EGTADJ=adjustment shown in Table as compared to engine rating
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Page A611 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------| Engine Model Rating | ------------------------------------------------------------------------------| | 5B1/P | 5B2/P | 5B3/P | 5B4/P | 5B5/P | 5B6/P | | | or | or | or | or | or | or | | | 5B1/2P | 5B2/2P | 5B3/2P | 5B4/2P | 5B5/2P | 5B6/2P | ------------------------------------------------------------------------------| EGTADJ⁰C | -34 | -20 | -3 | -23 | -66 | -48 | ------------------------------------------------------------------------------(2) If the EGTMARGIN calculated becomes negative, do the correction procedures that follow: (a) Troubleshoot the engine (Ref. TSM TASK 77-00-00-810-849). (b) If no errors are found or a cause that can be corrected is not found, the engine must be removed after not more than five flights. (c) If EGT or data systems errors are found, they must be corrected and the EGT must continue to be monitored. 5. Close-up ________ Subtask 72-00-00-862-054 A. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).
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Page A612 Feb 01/10
C F M 56-5B ENGINE - GENERAL - CLEANING/PAINTING ____________________________________ TASK 72-00-00-100-007 Engine Dry-out and Re lubrication 1. __________________ Reason for the Job It is recommended to do this procedure as soon as possible after landing in the event of: - An In-Flight Shutdown (IFSD). - An engine was ferried. You can ignore this procedure if the engine is to be operated in the limit of 24 hours after landing. In this case, run the engine for a minimum of 15 to 20 minutes at ground idle power.
R R R R R
2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 856A2320 856A2659 856A2718 856A2796 856A3810
1 1 1 1 1
hot air hose hot air source warning notice TOOL SET,DRYING AND RELUBRICATION-ENGINE SUMPS FILTER ADAPTER TOOL SET,R/I-DRIVE SHAFTS SAFETY PROTECTOR _ HANDCRANKING PAD ADAPTER, AIR - DRY OUT ENGINE SUMPS
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
Material No.
CP5067
Material No.
CP5075
* engine oil (Ref. 70-30-00) * lube system corrosion preventive oil (Ref. 70-30-00) * corrosion preventive additive (Ref. 70-30-00)
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Page 701 Feb 01/10
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-63-00-000-002 72-63-00-400-002 78-36-00-410-040 79-00-00-281-003 72-00-00-991-300 72-00-00-991-301 72-00-00-991-302 72-00-00-991-303
Opening of the Fan Cowl Doors Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Closing of the Thrust Reverser Doors Check of FWD, AFT Sump, AGB, and TGB scavenge screens Fig. 701 Fig. 702 Fig. 703 Fig. 704
3. __________ Job Set-up Subtask 72-00-00-941-063 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-071 B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
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Page 702 Nov 01/08
C F M 56-5B Subtask 72-00-00-160-052 C. Material Requirements: (1) Hot air source characteristics: (a) Output: 120-130 lb/min (54-59 kg/min) (b) Temperature: 300-325 deg. F (150-163 deg. C) (c) Supply pressure: 30-44 psi (207-303 kPa) (2) Air filter characteristics: (a) Filtration : 25 microns absolute (b) Temperature: 300-325 deg. F (150-163 deg. C) (c) Min. flow capacity: 2 lb/sec (0.9 kg/sec) (d) Differential pressure: 10 psi (69 kPa) (e) Working pressure: 70 psi (5 bar) (f) Proof pressure: 105 psi (7 bar) (3) Air circulation: (a) The hot air flows through the exhaust nozzle, aft and forward sumps, TGB and AGB assemblies, engine flow path, and open scavenge circuits of the lubrication unit. Subtask 72-00-00-020-051 D. Preparation before the job (1) Remove the scavenge screen plugs. (2) If the core engine can turn, remove the handcranking drive cover (Ref. TASK 72-63-00-000-002). (3) Fill the oil container of the TOOL SET,DRYING AND RELUBRICATIONENGINE SUMPS (856A2320G02) as follows: (a) When you use the lube system corrosion preventive oil (Material No. CP5067), put 0.8 l (0.21 USgal) of oil in the container.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 703 Nov 01/08
C F M 56-5B (b) When you use corrosion preventive additive (Material No. CP5075), mix a solution of 0.4 l (0.11 USgal) of product with an equal quantity of engine oil (Material No. CP2442) in the container. 4. Procedure _________ (Ref. Fig. 701/TASK 72-00-00-991-300, 702/TASK 72-00-00-991-301, 703/TASK 72-00-00-991-302, 704/TASK 72-00-00-991-303) Subtask 72-00-00-480-051 A. Installation of the Dry Out and Relubrication Tools WARNING : WEAR HEAVY PROTECTIVE GLOVES TO HANDLE THE HOT AIR HOSES, _______ FILTER AND SOURCE WHEN THEY ARE HOT. (1) Install the TOOL SET,DRYING AND RELUBRICATION-ENGINE SUMPS (856A2320G02) as follows: (a) Install the sleeves (10) in the lubrication unit. (b) Tighten the sleeves, and make the sleeves openings face together, as shown in (Ref. Fig. 701/TASK 72-00-00-991-300) (c) Lubricate the o-rings of the tool body and of the knurled knobs (20) with engine oil (Material No. CP2442). (d) Install the tool body and attach it to the sleeves (10) with the knurled knobs (20). (e) Tighten the knurled knobs. (2) Install the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01) as follows: (a) Install the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01) in position on the exhaust nozzle end. (b) Attach the jaws (70) to the exhaust nozzle end with bolts (90) and nuts (80). (c) Tighten the nuts (80). (d) Tighten the nuts (60).
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Page 704 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-00-00 CES
Page 705 Aug 01/09
C F M 56-5B
Engine Sumps Relubrication Tool Setup Figure 701/TASK 72-00-00-991-300- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 706 Nov 01/08
C F M 56-5B
Engine Sumps Relubrication Tool Setup Figure 701/TASK 72-00-00-991-300- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 707 Nov 01/08
C F M 56-5B
Dry Out Air Adapter Attachment to Rear End of Exhaust Plug Figure 702/TASK 72-00-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 708 Nov 01/08
C F M 56-5B
Engine Dry-out Figure 703/TASK 72-00-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 709 Nov 01/08
C F M 56-5B
Engine Relubrication Figure 704/TASK 72-00-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 710 Nov 01/08
C F M 56-5B (3) If the core engine can turn, install the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01) as follows: (a) Put the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01) in position on the AGB. (b) Tighten the bolts. (c) Lubricate the seal of the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01) with engine oil (Material No. CP2442). (d) Engage the wrench, part of TOOL SET,R/I-DRIVE SHAFTS (856A2718G02/P04) in the handcranking drive, throught the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01). (4) Connect the hot air source and the FILTER ADAPTER (856A2659G01) to the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01). Subtask 72-00-00-160-053 B. Dry-out of the engine WARNING : STAY CLEAR OF THE LUBRICATION UNIT BY 20 FEET BECAUSE HOT AIR _______ WILL BE BLOWN FROM THE TOOL SET-RELUBE ENG. SUMPS. (1) Turn on the hot air source. (2) Increase the air temperature slowly and continuously 150 deg.C (302 deg.F) to 163 deg.C (325 deg.F) . (3) Blowing: WARNING : WEAR HEAVY PROTECTIVE GLOVES TO AVOID INJURY WHEN MANUALLY _______ TURNING THE FAN ROTOR. (a) Blow hot air into the engine for 20 minutes. (4) During this period, turn the fan rotor 3-4 times by hand, and if possible, turn the core engine 3-4 times with the wrench, part of TOOL SET,R/I-DRIVE SHAFTS (856A2718G02/P18). (5) Turn on the hot air source off. (6) Disconnect the hot air hose from the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01) and connect it to the TOOL SET,DRYING AND RELUBRICATION-ENGINE SUMPS (856A2320G02).
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Page 711 Aug 01/09
C F M 56-5B Subtask 72-00-00-640-051 C. Relubrication of the engine WARNING : STAY CLEAR FROM THE EXHAUST NOZZLE NOT TO BREATHE OIL MIST. _______ (1) Turn on the hot air source. (2) Increase the air temperature slowly and continuously 150 deg.C (320 deg.F) 163 deg.C (325 deg.F) . (3) Open the oil supply valve (30). (4) Turn the fan rotor and the core engine: WARNING : WEAR HEAVY PROTECTIVE GLOVES TO AVOID INJURY WHEN MANUALLY _______ TURNING THE FAN ROTOR. (a) Turn the fan rotor and the core engine (if possible) approximately once every minute, until the oil container is empty (5-6 minutes). (5) Turn the hot air source off. (6) Disconnect the hot air hose from the TOOL SET,DRYING AND RELUBRICATION-ENGINE SUMPS (856A2320G02). (7) Let the engine temperature decrease to the ambiant temperature. Subtask 72-00-00-080-051 D. Removal of the tools (1) Remove the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01) as follows. (a) Loosen the nuts (60). (b) Loosen the nuts (80). (c) Disengage the ADAPTER, AIR - DRY OUT ENGINE SUMPS (856A3810G01) from the exhaust nozzle end. (2) Remove the TOOL SET,DRYING AND RELUBRICATION-ENGINE SUMPS (856A2320G02) from the lubrication unit as follows: (a) Make sure that the oil supply valve is closed.
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Page 712 Aug 01/09
C F M 56-5B (b) Disconnect the oil supply and air pressure supply lines from the oil container. (c) Loosen the knurled knobs (20). (d) Remove the tool body from the sleeves (10). (e) Remove the sleeves (10) from the lubrication unit. (3) If installed, remove the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01) as follows: (a) Disengage the wrench, part of TOOL SET,R/I-DRIVE SHAFTS (856A2718G02/P04) from the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01). (b) Remove the SAFETY PROTECTOR _ HANDCRANKING PAD (856A2796G01) from the AGB. 5. Close-up ________ Subtask 72-00-00-420-054 A. Procedure after the job (1) If necessary, install the handcranking drive cover (Ref. TASK 72-6300-400-002). (2) Make sure that the scavenge screens are clean and serviceable (Ref. TASK 79-00-00-281-003). (3) Install the scavenge screen plugs. Subtask 72-00-00-410-071 B. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the warning notice(s).
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Page 713 Aug 01/09
C F M 56-5B TASK 72-00-00-100-008 Engine Washing Requirements CAUTION : DO NOT USE METHANOL OR ENGINE TITANIUM PARTS COULD BE DAMAGED. _______ CAUTION : DO NOT WASH AN ENGINE WHICH HAS BEEN EXPOSED TO DRY CHEMICAL FIRE _______ EXTINGUISHING AGENTS. CAUTION : DO NOT WASH AN ENGINE UNLESS THE EGT IS BELOW 150 DEG.F (66 DEG.C). _______ CAUTION : DO NOT WASH AN ENGINE AT TEMPERATURE BELOW 14 DEG.F (-10 DEG.C). _______ 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
Material No.
CP5060
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * gas path cleaner (Ref. 70-30-00)
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Page 714 Aug 01/09
C F M 56-5B B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-100-026 72-00-00-100-028
Washing of the Engine Gas Path with Pure Water Washing of the Engine Gas Path with Cleaning Agent
3. __________ Job Set-up Subtask 72-00-00-869-075 A. Not Applicable 4. Procedure _________ Subtask 72-00-00-110-061 A. Engine Washing Requirements (1) General (a) You can wash the engine either with pure water only (Ref. TASK 72-00-00-100-026), or with a solution of gas path cleaner (Material No. CP5060) (Ref. TASK 72-00-00-100-028). 1 _
For EGT margin recovery, it is recommended to perform the engine gas path water wash with pure water only (without cleaning agent) (Ref. TASK 72-00-00-100-026). Pure water (without detergent) is effective in most situations depending on the engine operating environment and the gas path cleaning program implemented by the operator.
2 _
An engine gas path water wash using detergent (Ref. TASK 7200-00-100-028) provides the most effective method for cleaning the engine compressors. However, the use of detergent requires the strict application of the engine rinsing and bleed system cycling per AMM procedures to thus prevent fumes in the cabin when the aircraft resumes revenue service operation. Consideration should be given to accomplishing gas path cleaning with detergent if any of the following conditions are met: - organic debris or oil deposits are observed on compressor airfoil. - the engine has less than 10 deg. C EGT margin left.
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Page 715 Aug 01/09
C F M 56-5B (b) In both cases, you can use isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) as anti-freeze agent, if necessary. (2) Water (a) Water properties 1 _
Do not use water with more than 100 parts per million total solids.
2 _
Do not use water with more than 25 parts per million sodium plus potassium (Na+K), and with a pH of 6.8-8.0 (potable water usually meets these requirements).
3 _
Hot water 150 deg.F (66 deg.C) to 200 deg.F (93 deg.C) is more effective for cleaning or rinsing.
(b) Water flow CAUTION : DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) _______ PER MINUTE. IF NOT, THEN ENGINE DAMAGE CAN OCCUR. 1 _
Apply a water flow between 5 USgal (19 l) and 6 USgal (23 l) per minute.
(c) Water temperature 1 _
For best results, increase the temperature of the water to 150 deg.F (66 deg.C) to 200 deg.F (93 deg.C).
2 _
Hot water 150 deg.F (66 deg.C) to 200 deg.F (93 deg.C) will wash and rinse the gas path with more efficiency than cold water.
(3) Cleaning solution (if required) WARNING : USE RUBBER GLOVES AND EYE PROTECTION WHEN HANDLING LIQUID _______ DETERGENT. LIQUID DETERGENT AND ANTI-FREEZE SOLVENT HAVE LOW FLASHPOINTS. KEEP AWAY FROM HEAT AND OPEN FLAME. PROVIDE ADEQUATE VENTILATION. STAND AT LEAST 3 FEET (1M) AWAY FROM COWLING INLET WHEN SPRAYING LIQUIDS INTO ENGINE TO AVOID PERSONAL INJURY.
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Page 716 Aug 01/09
C F M 56-5B (a) Mix 20 to 25 percent of gas path cleaner (Material No. CP5060) with 75 to 80 percent water. (4) Anti-freeze mixtures WARNING : USE RUBBER GLOVES AND EYE PROTECTION WHEN HANDLING LIQUID _______ DETERGENT. LIQUID DETERGENT AND ANTI-FREEZE SOLVENT HAVE LOW FLASHPOINTS. KEEP AWAY FROM HEAT AND OPEN FLAME. PROVIDE ADEQUATE VENTILATION. STAND AT LEAST 3 FEET (1M) AWAY FROM COWLING INLET WHEN SPRAYING LIQUIDS INTO ENGINE TO AVOID PERSONAL INJURY. CAUTION : USE ONLY ISOPROPYL ALCOHOL AS AN ANTI-FREEZE MIXTURE. _______ METHANOL CAN CAUSE CORROSION OF THE TITANIUM PARTS OF THE ENGINE. (a) Use anti-freeze mixtures at temperatures below 40 deg.F (5 deg.C). (b) Prepare mixtures as follows: 1 _
For temperatures of 40 deg.F (5 deg.C) to 23 deg.F (-5 deg.C), mix 25 percent of isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) to 75 percent of water.
2 _
For temperatures of 23 deg.F (-5 deg.C) to 14 deg.F (-10 deg.C), mix 35 percent of isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) to 65 percent of water.
(c) Do not use anti-freeze mixtures at temperatures below 14 deg.F (-10 deg.C).
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Page 717 Aug 01/09
C F M 56-5B TASK 72-00-00-100-025 Hand Cleaning of the Fan Gas Path and Fan Blades 1. __________________ Reason for the Job This cleaning procedure gives instructions to remove the contamination from the fan blades, the Outlet Guide Vanes (OGV) and the acoustical panels of an engine, by hand washing. NOTE : It is recommended that you clean the fan blades and the gas path at ____ the same time. NOTE : This task can contribute to fuel savings. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R R
Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2240
Material No.
CP2279
Material No.
CP2470
Material No.
CP2559
Material No.
CP2560
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * scotch brite type A CFS (Ref. 70-30-00) * scotch brite type S CFS (Ref. 70-30-00) * TURCO 5948 DPM (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00)
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Page 718 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
Material No.
CP5060
* mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * gas path cleaner (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-100-008
Engine Washing Requirements
3. __________ Job Set-up Subtask 72-00-00-941-064 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 719 Aug 01/09
C F M 56-5B 4. Procedure _________ Subtask 72-00-00-110-062 A. Hand Cleaning of the Fan Gas Path CAUTION : DO NOT USE METHANOL OR ENGINE TITANIUM PARTS COULD BE DAMAGED. _______ (1) Mix 20 percent of gas path cleaner (Material No. CP5060) with 80 percent of water. (2) Spraying CAUTION : DO NOT SPRAY CLEANING SOLUTION DIRECTLY INTO BOOSTER (LPC) _______ INLET. IF THE CLEANING SOLUTION IS PUT INTO THE BOOSTER INLET, THE ENGINE MUST BE OPERATED TO DRY OUT THE SOLUTION, OR ENGINE DAMAGE CAN OCCUR. (a) Use anti-freeze mixture, if necessary (Ref. TASK 72-00-00-100008). (b) Spray the blades, the Outlet Guide Vanes (OGV), the acoustical panels and the fan inlet and outlet with the wash solution. Do not spray the fan wash solution into the Low Pressure Compressor (LPC) inlet. NOTE : Apply the solution to the two sides of the blade at the 6 ____ oclock position. This will decrease the amount of solution that touches the blade dovetails. The solution will remove the lubricant. If you wipe the blades, do it in the down direction, away from the rotor. (3) Rub the sprayed areas with a cloth. (4) Rinse the blades with water. Subtask 72-00-00-110-063 B. Fan Blades Cleaning (1) If the blades stay dirty, do the procedure which follows: CAUTION : DO NOT USE THIS SOLVENT NEAR FLAMES OR HEAT, BECAUSE THIS _______ SOLVENT IS FLAMMABLE. DO NOT BREATHE THE GASES RELEASED FROM SOLVENT, DO NOT LET IT TOUCH YOUR SKIN OR CLOTHING AND MAKE SURE YOU HAVE A GOOD FLOW OF AIR, BECAUSE THIS SOLVENT IS DANGEROUS TO YOUR SKIN, EYES AND LUNGS.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 720 Aug 01/09
R R R R
C F M 56-5B (a) Remove light deposits with soft cloth and acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041) or TURCO 5948 DPM (Material No. CP2470). (b) Remove heavy stubborn deposits with scotch brite type A CFS (Material No. CP2240) or scotch brite type S CFS (Material No. CP2279) and acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041) or TURCO 5948 DPM (Material No. CP2470).
R R R R
(c) Rinse thoroughly with water. 5. Close-up ________ Subtask 72-00-00-869-064 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-00-00-942-052 B. Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 721 Aug 01/09
C F M 56-5B TASK 72-00-00-100-026 Washing of the Engine Gas Path with Pure Water CAUTION : IF CLEANING AGENT IS USED, PROPER AIRCRAFT MAINTENANCE CONFIGURATION, _______ ENGINE RINSING AND POST ENGINE WASH TEST MUST BE COMPLETED TO PREVENT THE POSSIBILITY OF FUMES IN THE CABIN WHEN AIRCRAFT RESUMES REVENUE FLIGHT OPERATION. 1. __________________ Reason for the Job For Exhaust Gas Temperature (EGT) margin recovery, it is recommended to perform the engine gas path water wash with pure water only. NOTE : This task can contribute to fuel savings. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN)
No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP5067
Material No.
CP5075
Material No.
CP8001
Material No.
CP8002
* lube system corrosion preventive oil (Ref. 70-30-00) * corrosion preventive additive (Ref. 70-30-00) * lockwire (Ref. 70-30-00) * lockwire (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 722 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 21-00-00-615-003 21-00-00-615-004 24-41-00-861-002 24-41-00-862-002 71-00-00-710-001 71-00-00-710-003 71-00-00-710-028 71-13-00-010-040 71-13-00-410-040 72-00-00-100-008 72-00-00-991-325 72-00-00-991-304
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Decontamination of the Environmental Control System (ECS) when the Temperature is below 24 deg.C (Engine/s) Decontamination of the Environmental Control System (ECS) when the Temperature is above 24 deg.C (Engine/s) Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Dry Motoring Check Engine Automatic Start Engine Shutdown Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Engine Washing Requirements Fig. 705 Fig. 706
3. __________ Job Set-up Subtask 72-00-00-941-065 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ENG/FADEC GND PWR/1(2) pushbutton switch is OFF (the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 723 Aug 01/09
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-072 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ Subtask 72-00-00-110-057 A. Preparation of the Engine for Washing (1) For engine washing requirements (Ref. TASK 72-00-00-100-008). NOTE : The disconnection of P25 line is only available for engines ____ equipped with PMUX option. (2) Disconnect PS3 line and P25 line (if installed) from the Electronic Control Unit (ECU). (3) Plug the open tubes and ports of the ECU with standard protective covers. (4) Disconnect the rigid anti-ice servo pressure line (25) from the nacelle anti-ice valve (NAI). (Ref. Fig. 705/TASK 72-00-00-991-325) NOTE : Let the rigid anti-ice servo pressure line free (not plugged) ____ during the washing of the engine. (5) Install a standard protective cover on the anti-ice servo pressure line port of the NAI valve. (6) Prepare an anti-freeze mixture, if necessary, as defined in engine washing requirements (Ref. TASK 72-00-00-100-008). CAUTION : CORROSION PREVENTIVE ADDITIVE SHOULD BE USED. HOWEVER, IF _______ NONE OF THE CORROSION PREVENTIVE PRODUCTS SPECIFIED (REFER TO CHAPTER B. CONSUMABLE MATERIALS) IS AVAILABLE, THE ENGINE MUST RESUME REVENUE SERVICE OPERATION WITHIN 24 HOURS FOLLOWING THE POST ENGINE WASH TEST.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 724 Aug 01/09
C F M 56-5B
Rigid Anti-Ice Muscle Line Figure 705/TASK 72-00-00-991-325 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 725 Aug 01/09
C F M 56-5B (7) Service the oil tank with one quart (one liter) of lube system corrosion preventive oil (Material No. CP5067) or corrosion preventive additive (Material No. CP5075) (Ref. TASK 12-13-79-610002). NOTE : The oil tank must be topped off up to the window mark. ____ Subtask 72-00-00-861-051 B. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 72-00-00-860-051 C. Aircraft Maintenance Configuration (1) On the ANTI ICE section of panel 25VU, make sure that the ANTI ICE/ENG 1(2) pushbutton switch is OFF (the ON legend of the ANTI ICE/ENG 1(2) pushbutton switch is off). (2) On the AIR COND panel 30VU, make sure that ENG 1(2) BLEED pushbutton switch is OFF (the OFF legend of the ENG1(2) BLEED is on). (3) On the AIR COND panel 30VU, make sure that PACK 1 and PACK 2 pushbutton switches are OFF (the OFF legend of the PACK 1 and the PACK 2 pushbutton switches are on). Subtask 72-00-00-110-058 D. Engine Washing CAUTION : DO NOT WASH AN ENGINE WHICH HAS BEEN EXPOSED TO DRY CHEMICAL _______ FIRE EXTINGUISHING AGENTS. CAUTION : DO NOT WASH AN ENGINE UNLESS THE EGT IS BELOW 150 DEG.F (66 _______ DEG.C). CAUTION : DO NOT WASH AN ENGINE AT TEMPERATURE BELOW 14 DEG.F (-10 _______ DEG.C). CAUTION : THE FUEL PUMP AND HYDRO-MECHANICAL UNIT (HMU) ARE FUEL _______ LUBRICATED. DO NOT MOTOR, START, OR OPERATE ENGINE UNLESS A POSITIVE FUEL INLET PRESSURE IS INDICATED ON THE LOWER ECAM (FUEL SYSTEM PAGE). DAMAGE TO COMPONENTS MAY RESULT. CAUTION : DO NOT EXCEED STARTER DUTY CYCLE. STARTER DAMAGE MAY RESULT. _______
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 726 Aug 01/09
C F M 56-5B CAUTION : MAKE SURE THE N1 ROTOR TURNS FREELY THROUGHOUT WASHING TO _______ PREVENT OIL SYSTEM CONTAMINATION. CAUTION : DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) PER _______ MINUTE. IF NOT, THEN ENGINE DAMAGE CAN OCCUR. CAUTION : DRY MOTOR CYCLE DURATIONS MUST NOT EXCEED 2 MINUTES (REFER TO _______ AMM TASK 71-00-00-710-001). (1) Dry motor the engine for two minutes (Ref. TASK 71-00-00-710-001). (2) After 10 seconds of motoring with a positive fan rotation, inject the water at 1 oclock position (aft view) on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LP compressor inlet if a specific rig is used). (3) Stop the water injection before the end of the engine motoring. (4) Let the engine soak for 5 minutes. (5) Repeat steps (1) to (4). (6) Let the engine soak for 5 minutes. (7) Dry motor the engine again (Ref. TASK 71-00-00-710-001). NOTE : Water can potentially drain out of the disconnected rigid ____ anti-ice servo pressure line. If water drains out, continue to dry motor the engine until there is no more water draining out of the line. Subtask 72-00-00-420-055 E. Installation of PS3 Line and P25 Line (1) Remove the plugs from the PS3 and P25 lines and from the ECU. CAUTION : DO NOT BLOW COMPRESSED AIR OR NITROGEN INTO THE ECU AS _______ DAMAGE TO THE ECU CAN OCCUR. (2) Blow PS3 and P25 lines clear of water using compressed air or nitrogen. CAUTION : DURING INSTALLATION, MAKE SURE THAT THE PS3 LINE DOES NOT _______ TOUCH THE LOWER STARTER DUCT OR OTHER PARTS IN THIS AREA. IF IT DOES, CHAFING OF THE PS3 HOSE CAN OCCUR.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 727 Aug 01/09
C F M 56-5B (3) Connect PS3 line to ECU, TORQUE to between 270 and 300 lbf.in (3.05 and 3.39 m.daN) and safety with lockwire (Material No. CP8001) or lockwire (Material No. CP8002). (4) Connect P25 line to ECU, TORQUE to between 180 and 200 lbf.in (2.03 and 2.26 m.daN) and safety with lockwire (Material No. CP8001) or lockwire (Material No. CP8002). (5) Remove the standard protective cover from the nacelle anti-ice line port of the NAI valve. (6) Connect the rigid anti-ice servo pressure line (25) to nacelle anti-ice valve (4000 DN). TORQUE the forward hose nut to between 135 and 150 lbf.in (1.52 and 1.69 m.daN) . Subtask 72-00-00-410-085 F. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the following engine fan cowl doors (Ref. TASK 71-13-00-410040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-620-063 G. Post Engine Wash Test (Ref. Fig. 706/TASK 72-00-00-991-304) (1) On the AIR COND panel 30VU, make sure that: - The crossbleed valve selector switch is in the OPEN position. (2) Start the engine within 2 hours (or 30 minutes in icing condition) of the last wash cycle to purge the lube/sump system of any water ingestion (Ref. TASK 71-00-00-710-003). NOTE : APU bleed valve must be closed (the ON legend of the APU bleed ____ pushbutton switch is OFF) after engine start, to avoid the supply of air to the wing anti-ice systems from the APU.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 728 Aug 01/09
C F M 56-5B
Engine Cleaning (Washing with Pure Water) Figure 706/TASK 72-00-00-991-304 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 729 Aug 01/09
C F M 56-5B NOTE : This engine run is done to ensure that the bleed system is ____ free from contaminant. Smoke/Smell in the cabin and Starter Air Valve (SAV) contamination can result if contaminant enters the bleed system. NOTE : Corrosion preventive products (refer to chapter B. Consumable ____ Materials) must be used if not done already. If none of the corrosion preventive products specified above are available, the engine must resume Revenue Service operation within 24 hours following this Post Wash Test. (a) Let the engine run at idle for 5 minutes. (b) After 5 minutes from engine start, do the following: 1 _
Press the ENG 1(2) BLEED pushbutton switch to operate the engine bleed system.
2 _
Make sure that the OFF legend of the ENG1 (2) BLEED pushbutton switch goes off when the engine bleed system operates.
3 _
Press the ANTI ICE/WING pushbutton switch to operate the wing anti-ice system. NOTE : The aim is to purge water potentially trapped in High ____ Pressure (HP) bleed ducts and HP engine bleed chambers.
4 _
Make sure that the ON legend of the ANTI ICE/WING pushbutton switch goes on when the wing anti-ice system operates. NOTE : The Wing Anti-Ice (WAI) valves will automatically close ____ 30 seconds after the Wing Anti-Ice system is selected ON. This is to prevent wing slats overheat. However, the ON legend remains illuminated until the switch is deselected.
5 _
Make sure that Pressure Regulating Valve (PRV) and High Pressure Valve (HPV) are open on ECAM BLEED page with engine running at this speed while WAI valve is open.
6 _
Once WAI valve is closed, let the engine run at idle for 5 minutes. NOTE : Do not actuate WAI systems before the 5-minute period ____ at idle is over in order to avoid WAI systems overheat.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 730 Aug 01/09
C F M 56-5B 7 _
Increase and stabilize engine thrust to at least 60 percent Fan (N1).
8 _
Press twice the ANTI ICE/WING pushbutton switch to operate the Wing Anti-Ice system once more. NOTE : The aim is to purge water potentially trapped in IP ____ bleed ducts and IP engine bleed chambers. NOTE : If the Wing Anti-Ice ON legend is still on, pressing ____ twice the WAI pushbutton switch enables a second WAI cycle of 30 seconds to be started. NOTE : Do not perform more than two attempts with a minimum of ____ 5 minutes between the two attempts, in order to avoid WAI systems overheat.
9 _
Make sure that the ON legend of the ANTI ICE/WING pushbutton switch comes on when the wing anti-ice system operates.
10 __
Make sure that PRV is open and HPV is closed on ECAM BLEED page with engine running at this speed while the WAI valve is open.
(c) Once the WAI valve is closed, pull the throttle to stabilize the engine thrust at idle for 5 minutes. (d) After 15 minutes from engine start, do the following: 1 _
Press the ANTI ICE/WING pushbutton switch and make sure that the ON legend of the ANTI ICE/WING pushbutton switch goes off.
2 _
Turn the crossbleed valve selector switch to the AUTO position.
3 _
Press the PACK 1 (2) pushbutton switch to operate the air conditioning pack.
4 _
Make sure that the OFF legend of the PACK 1 (2) pushbutton switch goes off.
5 _
Check for evidence of anti-freeze mixture odor/smoke in the cabin. - If evidence is found, continue to operate the engine at idle until no odor/smoke remains in the cabin.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 731 Aug 01/09
C F M 56-5B - After 10 minutes engine running, if continuous odor/smoke remains in the cabin, shut down the engine (Ref. TASK 71-0000-710-028) and decontaminate the Environmental Control System (ECS). Note that APU Bleed valve must be open before engine shutdown - When Ambient Air Temperature is below 75.2 Deg F (24 Deg C) (Ref. TASK 21-00-00-615-003) - When Ambient Air Temperature is above 75.2 Deg F (24 Deg C) (Ref. TASK 21-00-00-615-004) - If no evidence is found, shut down the engine (Ref. TASK 7100-00-710-028). 5. Close-up ________ Subtask 72-00-00-869-065 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-00-00-862-051 B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002). Subtask 72-00-00-942-053 C. Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 732 Aug 01/09
C F M 56-5B TASK 72-00-00-100-028 Washing of the Engine Gas Path with Cleaning Agent 1. __________________ Reason for the Job Engine washing with cleaning agent is preferred when organic debris or oil deposits are present or remaining EGT margin is less than 5 deg. C. NOTE : When cleaning agent is used, proper Aircraft Maintenance ____ Configuration, engine rinsing and post engine wash test must be completed to prevent the possibility of fumes in the cabin when Aircraft resumes revenue flight operation. NOTE : The engine bleed system must be operative prior to proceeding with ____ engine washing with cleaning agent. Check that there is no failure message on the engine bleed system. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN)
No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP5067
Material No.
CP5075
Material No.
CP8001
Material No.
CP8002
* lube system corrosion preventive oil (Ref. 70-30-00) * corrosion preventive additive (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) DIA (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) DIA (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 733 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 21-00-00-615-003 21-00-00-615-004 24-41-00-861-002 24-41-00-862-002 71-00-00-710-001 71-00-00-710-001 71-00-00-710-003 71-00-00-710-028 71-13-00-010-040 71-13-00-410-040 72-00-00-100-008 72-00-00-991-325 72-00-00-991-322
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Decontamination of the Environmental Control System (ECS) when the Temperature is below 24 deg.C (Engine/s) Decontamination of the Environmental Control System (ECS) when the Temperature is above 24 deg.C (Engine/s) Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power Dry Motoring Check Dry Motoring Check Engine Automatic Start Engine Shutdown Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Engine Washing Requirements Fig. 705 Fig. 707
3. __________ Job Set-up Subtask 72-00-00-941-101 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 734 Aug 01/09
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-138 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ Subtask 72-00-00-110-079 A. Preparation of the Engine for Washing CAUTION : CORROSION PREVENTIVE ADDITIVE SHOULD BE USED. HOWEVER, IF NONE _______ OF THE CORROSION PREVENTIVE PRODUCTS SPECIFIED (REFER TO CHAPTER B. CONSUMABLE MATERIALS) IS AVAILABLE, THE ENGINE MUST RESUME REVENUE SERVICE OPERATION WITHIN 24 HOURS FOLLOWING THE POST ENGINE WASH TEST. (1) For engine washing requirements (Ref. TASK 72-00-00-100-008). NOTE : The disconnection of the P25 line is only available for ____ engines equipped with the PMUX option. (2) Disconnect PS3 line and P25 line (if installed) from the Electronic Control Unit (ECU). (3) Plug the open tubes and ports of the ECU with standard protective covers. (4) Disconnect the rigid anti-ice servo pressure line (25) from the nacelle anti-ice valve (NAI). (Ref. Fig. 705/TASK 72-00-00-991-325) NOTE : Let the rigid anti-ice servo pressure line free (not plugged) ____ during the washing of the engine. (5) Install a standard protective cover on the anti-ice servo pressure line port of the NAI valve. (6) Prepare an anti-freeze mixture, if necessary, as defined in engine washing requirements (Ref. TASK 72-00-00-100-008).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 735 Aug 01/09
C F M 56-5B (7) Service the oil tank with one quart (one liter) of lube system corrosion preventive oil (Material No. CP5067) or corrosion preventive additive (Material No. CP5075) (Ref. TASK 12-13-79-610002). NOTE : The oil tank must be topped off up to the window mark. ____ Subtask 72-00-00-410-137 B. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-861-053 C. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 72-00-00-860-052 D. Aircraft Maintenance Configuration (1) On the overhead control and indicating panel 25VU, make sure that the ON legend of the ANTI-ICE/ENG 1(2) pushbutton switch is off. (2) On the AIR COND panel 30VU, make sure that the OFF legend of the ENG 1(2) BLEED pushbutton switch is on. (3) On the AIR COND panel 30VU, make sure that the OFF legends of the PACK 1 and the PACK 2 pushbutton switches are on. Subtask 72-00-00-110-081 E. Engine Washing CAUTION : DO NOT WASH AN ENGINE WHICH HAS BEEN EXPOSED TO DRY CHEMICAL _______ FIRE EXTINGUISHING AGENTS. CAUTION : DO NOT WASH AN ENGINE UNLESS THE EGT IS BELOW 150 DEG.F (66 _______ DEG.C).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 736 Aug 01/09
C F M 56-5B CAUTION : DO NOT WASH AN ENGINE AT TEMPERATURE BELOW 14 DEG.F (-10 _______ DEG.C). CAUTION : THE FUEL PUMP AND HYDRO-MECHANICAL UNIT (HMU) ARE FUEL _______ LUBRICATED. DO NOT MOTOR, START, OR OPERATE ENGINE UNLESS A POSITIVE FUEL INLET PRESSURE IS INDICATED ON THE LOWER ECAM (FUEL SYSTEM PAGE). DAMAGE TO COMPONENTS MAY RESULT. CAUTION : DO NOT EXCEED STARTER DUTY CYCLE. STARTER DAMAGE MAY RESULT. _______ CAUTION : MAKE SURE THE N1 ROTOR TURNS FREELY THROUGHOUT WASHING TO _______ PREVENT OIL SYSTEM CONTAMINATION. CAUTION : DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) PER _______ MINUTE. IF NOT, THEN ENGINE DAMAGE CAN OCCUR. (1) Dry motor the engine for two minutes (Ref. TASK 71-00-00-710-001). (2) After 30 seconds in motoring, inject the cleaning solution at 1 oclock position on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LP compressor inlet if a specific rig is used). (3) Stop the cleaning solution injection before the end of the engine motoring. (4) After two minutes in motoring, release the ENG/MAN START/1 (2) pushbutton switch. (5) Let the engine soak for 5 minutes. (6) Repeat steps (1) to (5) if extreme organic debris or oil deposits were present or if remaining EGT margin prior to the water wash was less than 10 deg. C. Subtask 72-00-00-110-082 F. Engine Rinsing CAUTION : DO NOT RINSE THE ENGINE EXPOSED TO DRY CHEMICAL EXTINGUISHING _______ AGENT. DO NOT RINSE THE ENGINE UNLESS THE EGT IS BELOW 150 DEG.F (66 DEG.C.). DO NOT RINSE THE ENGINE AT TEMPERATURE BELOW 14 DEG. F (-10 DEG.C.).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 737 Aug 01/09
C F M 56-5B CAUTION : THE FUEL PUMP AND HYDRO-MECHANICAL UNIT (HMU) ARE FUEL _______ LUBRICATED. DO NOT MOTOR, START, OR OPERATE ENGINE UNLESS A POSITIVE FUEL INLET PRESSURE IS INDICATED ON THE LOWER ECAM (FUEL SYSTEM PAGE). DAMAGE TO COMPONENTS MAY RESULT. CAUTION : DO NOT EXCEED STARTER DUTY CYCLE. STARTER DAMAGE MAY RESULT. _______ CAUTION : MAKE SURE THAT THE N1 ROTOR TURNS FREELY THROUGHOUT RINSING TO _______ PREVENT OIL SYSTEM CONTAMINATION. CAUTION : DO NOT APPLY WATER AT MORE THAN 6 US GAL (23 LITERS) PER _______ MINUTE. IF NOT, THEN ENGINE DAMAGE CAN OCCUR. (1) Dry motor the engine for two minutes (Ref. TASK 71-00-00-710-001). (2) After 10 seconds in motoring with positive fan rotation, inject the water at 1 oclock position on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LP compressor inlet if a specific rig is used). (3) Stop the water injection before the end of the engine motoring. (4) Let the engine soak for 5 minutes. (5) Dry motor the engine again for two minutes (Ref. TASK 71-00-00-710001). (6) After 10 seconds in motoring with positive fan rotation, inject the water, at 1 oclock position on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LP compressor inlet if a specific rig is used). (7) Stop the water injection before the end of the engine motoring. (8) Let the engine soak for 5 minutes. (9) Dry motor the engine again for two minutes (Ref. TASK 71-00-00-710001). (10) After 10 seconds in motoring with positive fan rotation, inject the water, at 1 oclock position on the Low Pressure Compressor (LPC) inlet through the fan blades (or at the LP compressor inlet if a specific rig is used). (11) Stop the water injection before the end of the engine motoring.
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 738 Aug 01/09
C F M 56-5B (12) If water still drains out of the disconnected rigid anti-ice muscle line, dry motor the engine again until no water drains out (Ref. TASK 71-00-00-710-001). Subtask 72-00-00-010-139 G. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-420-064 H. Installation of PS3 Line and P25 Line CAUTION : DO NOT BLOW COMPRESSED AIR OR NITROGEN INTO THE ECU AS DAMAGE _______ TO THE ECU CAN OCCUR. CAUTION : DURING INSTALLATION, MAKE SURE THAT THE PS3 LINE DOES NOT TOUCH _______ THE LOWER STARTER DUCT OR OTHER PARTS IN THIS AREA. IF IT DOES, CHAFING OF THE PS3 HOSE CAN OCCUR. (1) Remove the plugs from the PS3 and P25 lines and from the ECU. (2) Blow PS3 and P25 lines clear of water with compressed air or nitrogen. (3) Connect PS3 line to ECU, TORQUE to between 270 and 300 lbf.in (3.05 and 3.39 m.daN) and safety with lockwire 0.032 in. (0.8 mm) DIA (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) DIA (Material No. CP8002). (4) Connect P25 line to ECU, TORQUE to between 180 and 200 lbf.in (2.03 and 2.26 m.daN) and safety with lockwire 0.032 in. (0.8 mm) DIA (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) DIA (Material No. CP8002). (5) Remove the standard protective cover from the nacelle anti-ice port of the NAI valve. (6) Connect the rigid anti-ice servo pressure line (25) to nacelle anti-ice valve, torque the forward hose nut to between 135 and 150 lbf.in (1.52 and 1.69 m.daN).
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Page 739 Aug 01/09
C F M 56-5B Subtask 72-00-00-410-138 J. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-00-00-620-065 K. Post Engine Wash Test (Ref. Fig. 707/TASK 72-00-00-991-322) (1) On the AIR COND panel 30VU, make sure that: - The OFF legend of the PACK 1 and the PACK 2 pushbutton switches are on prior to start the procedure. - The cross bleed valve rotary selector is on OPEN position. (2) Start the engine within 2 hours (or 30 minutes if icing condition) of the last wash cycle to purge the lube/sump system of any water ingestion (Ref. TASK 71-00-00-710-003). NOTE : APU Bleed Valve must be closed (the ON legend of APU ____ pushbutton switch is off) after engine start, to avoid the supply of the air to the Wing-Anti-ice Systems from APU. NOTE : This engine run is done to ensure that the bleed system is ____ free from contaminant. Smoke/smell in cabin can result if contaminant enters in the bleed system. NOTE : Corrosion preventive products should be used. If none of the ____ corrosion preventive products specified above is available, the aircraft must resume Revenue Service operation within 24 hours following this Post Wash Test. (a) Let the engine run at idle for 5 minutes. (b) After 5 minutes from engine start, do the following: 1 _
Press the ANTI-ICE/ENG 1(2) pushbutton switch to operate the engine anti-ice system.
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Page 740 Aug 01/09
C F M 56-5B
Engine Cleaning (Washing with Cleaning Agent) Figure 707/TASK 72-00-00-991-322 EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, R CES
Page 741 Aug 01/09
C F M 56-5B 2 _
Make sure that the ON legend of the ANTI-ICE/ENG 1(2) pushbutton switch comes on when the engine anti-ice system operates. CAUTION : AFTER 30 MINUTES FROM ENGINES START, ANTI-ICE/ENG _______ 1(2) PUSHBUTTON SWITCH SHOULD BE PRESSED OFF TO DEACTIVATE THE ENGINE ANTI-ICE SYSTEM. IF NOT, DAMAGE TO THE ENGINE COULD OCCUR.
3 _
Press the ENG 1(2) BLEED pushbutton switch to operate the engine bleed system.
4 _
Make sure that the OFF legend of the ENG 1(2) BLEED pushbutton switch goes off when the engine bleed anti-ice system operates.
5 _
Press the ANTI-ICE/WING pushbutton switch to operate the wing anti-ice system.
6 _
Make sure that the ON legend of the ANTI-ICE/WING pushbutton switch comes on when the wing anti-ice system operates.
7 _
Increase and stabilize engine thrust to at least 60 percent Fan (N1) Speed until HPV is closed while PRV is open on ECAM BLEED page.
8 _
Make sure that HPV is closed and PRV opened on ECAM BLEED page with engine running at this speed.
(c) Let the engine run this stabilized Fan (N1) Speed for 10 minutes. (d) Pull throttle to stabilize engine thrust at idle for 5 minutes. (e) After 20 minutes from engine start, do the following: 1 _
Press the ANTI-ICE/ENG and ANTI-ICE/WING pushbutton switches to turn off both anti ice systems.
2 _
Make sure that the ON legend of the ANTI-ICE/ENG and ANTI-ICE/WING pushbutton switches goes off.
3 _
Turn the cross bleed valve rotary selector to AUTO position.
4 _
Press the PACK 1 (2) pushbutton switch to operate the air conditioning pack.
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Page 742 Aug 01/09
C F M 56-5B 5 _
Make sure that the ON legend of the pushbutton switch comes on.
6 _
Check for evidence of cleaning agent or anti-freeze mixture odor/smoke in the cabin. - if evidence is found, continue to operate the engine at idle until no odor/smoke remains in the cabin. - after 10 minutes engine running, if continuous odor/smoke remains in the cabin, shut down the engine (Ref. TASK 71-0000-710-028) and decontaminate the Environmental Control System (ECS). . When Ambient Air Temperature is below 24 deg. C (Ref. TASK 21-00-00-615-003). . When Ambient Air Temperature is above 24 deg. C (Ref. TASK 21-00-00-615-004). - if no evidence is found, shut down the engine (Ref. TASK 7100-00-710-028).
5. Close-up ________ Subtask 72-00-00-869-084 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-00-00-942-059 B. Remove the warning notice(s). Subtask 72-00-00-862-053 C. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862002).
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Page 743 Aug 01/09
C F M 56-5B TASK 72-00-00-100-027 External Cleaning 1. __________________ Reason for the Job NOTE : This task can contribute to fuel savings. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No
specific specific specific specific
clean cloth soaked rag soft bristle brush warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2010
Material No.
CP2011
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * white spirit (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
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Page 744 Aug 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 SPM 732113160001
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-00-00-941-066 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-084 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
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Page 745 Aug 01/09
C F M 56-5B Subtask 72-00-00-040-064 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-00-00-010-085 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-00-00-110-059 A. Engine external cleaning (1) Hydrocarbon method WARNING : HYDROCARBONS ARE FLAMMABLE AND TOXIC. _______ AVOID PROLONGED CONTACT WITH THE SKIN, AND OBSERVE PRECAUTIONS AGAINST FIRE. CAUTION : SOME PLASTICS AND RUBBER-BASE MATERIALS ARE ATTACKED BY _______ HYDROCARBON SOLVENTS. - stoddard solvent (Material No. CP2011) or acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or magchem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or white spirit (Material No. CP2010) is recommended. Light accumulations of grease, oil, gum, and dirt may be removed with hydrocarbon solvent. This method is not effective in removing baked-on oil deposits. (a) Apply solvent by spraying or using soaked rag. NOTE : A soft bristle brush may be used to remove stubborn ____ accumulations. (b) Wipe thoroughly to remove accumulation and dry with a clean cloth or rinse with water.
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Page 746 Aug 01/09
C F M 56-5B (2) Steam cleaning method (a) Steam cleaning is a superficial cleaning process that is useful when it is not desireable to remove paint and surface coatings. NOTE : Do not use steam cleaning compounds. ____ (3) Cap all tube ends, manifold openings and air extraction ports to prevent entry of any contaminants or foreign objects. (a) Handling of the plugs: WARNING : FIRING TIPS OF IGNITER PLUGS WITH SPECIAL HANDLING _______ MARKINGS CONTAIN BERYLLIUM OXIDE. INHALATION OR INGESTION OF, OR CONTACT WITH BERYLLIUM OXYDE DUST IS HARMFUL TO YOUR HEALTH ; DO NOT GRIND, CLEAN OR MACHINE. HOLD PLUG BY INPUT CONNECTOR ONLY. TO AVOID PERSONAL INJURY, DO NOT HANDLE FIRING TIP. IF FITING TIP OF PLUG IS CONTACTED, AVOID TOUCHING OTHER AREAS OF YOUR BODY, AND WASH HANDS WITH SOAP AND WARM WATER. USED PLUGS SHOULD BE PLACED IN A PLASTIC ZIP LOC BAG FOR STORAGE OF SERVICEABLE PARTS AND/OR ACCUMULATION FOR DISPOSAL. SCRAP PLUGS MUST BE PLACED IN A SEALED CONTAINER AND BURIED IN THE EARTH PER RECOMMENDATIONS OF THE NATIONAL INSTITUTE FOR OCCUPATIONAL SAFETY AND HEALTH. LOCAL GOVERNMENT REQUIREMENTS OR LOCAL STANDARDS (IF THEY ARE MORE RESTRICTIVE) WILL BE THE ONLY AUTHORIZATION FOR DEVIATION FROM THESE REQUIREMENTS. (4) Steam clean the accessible exterior surfaces of the engine in accordance with (Ref. SPM 732113160001). To prevent damage to exposed plastic parts, avoid dwelling of steam on such parts to minimize excessive build-up of heat. (5) Remove covers installed above.
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Page 747 Aug 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-00-00-410-083 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-00-00-440-064 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-00-00-410-084 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-00-00 201-249, 251-299, 301-399, 401-499, CES
Page 748 Aug 01/09
C F M 56-5B FAN AND BOOSTER ASSEMBLY - DESCRIPTION AND OPERATION ____________________________________________________ 1. _______ General (Ref. Fig. 001) A. Fan and booster assembly (1) The fan and booster assembly consists of a single-stage fan rotor and a 4-stage axial booster, cantilever-mounted at the rear of the fan disk. (2) The fan and booster assembly consists of the following sections: (a) The fan section. It consists of: - spinner rear and front cones. - fan disk. - fan blades. (b) The booster section. It consists of: - booster rotor which is a spool with 4 stages of blades - booster stator which contains 5 stages of vane assemblies. 2. ___________ Description (Ref. Fig. 002, 003) A. Spinner Front Cone The spinner front cone is made of composite material. Its design precludes the need for an engine nose anti-icing system. The front cone is bolted to the rear cone. B. Spinner Rear Cone The spinner rear cone is made of aluminum alloy. Its rear flange is bolted to the fan disk and is part of the fan blades retention system. The outer rim of rear flange is provided with tapped holes for trim balance bolts. The front flange provides for attachment of the spinner front cone. C. Fan Disk The fan disk is a titanium alloy forging. Its inner rear flange provides attachement for the fan shaft and its outer rear flange is bolted to the booster rotor. The outer front flange provides attachment for the spinner rear cone. The disk outer rim has 36 recesses designed for fan blade retention.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Fan and Booster Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Fan and Booster Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
Booster Rotor and Stator Assembly Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B D. Fan Blades There are 36 titanium alloy, mid-span shrouded fan blades approximately 23 in. (0.58 m) long. Each of the blades has a dovetail base that engages in disk rim recess. Blades are individually retained by a spacer that limits radial movement. A retainer lug, machined at the rear end of each blade root, engages the forward flange of the booster spool and limits the forward and rearward axial movements. E. Booster Rotor (Ref. Fig. 003) The booster rotor consists of the booster spool and 4 stages of blades. (1) The booster spool is forged and machined from titanium and is cantilever-mounted on the rear of the fan disk. The inner front flange, bolted to the fan disk, acts as a stop for the fan blade spacers and blades. The 4-stage spool has circumferential slots that retain the stages 2, 3, 4 and 5 rotor blades, locking lugs and balance weights. Stage 2 has 64 blades, stage 3 and 4 have 70 blades and stage 5 has 68 blades. Rotating air seal serrations are machined between each stage on the outer diameter of spool. A forward rotating air seal, integral with the front web of the booster spool, provides (partial) sealing between the fan rotor stage and the inner shroud of booster stator stage 1 and (partial) pressurization of the engine forward sump. (2) The booster blades are approximately 3.5 to 4.2 in. (89 to 107 mm) long and serve primarily to supercharge the compressor. Blades are held in the dovetail slots by locking lugs. F. Booster Vane Assemblies (1) The stacked vane assemblies are cantilever-mounted on the fan frame front face. The entire assembly is composed of 5 stages of similar design. Each vane assembly consists of : (a) An outer shroud which, depending on its assembly location, is fitted with one or 2 mounting flanges at its ends. The outer shroud inner face of stages 1, 3, 4 and 5 vanes assemblies is lined with an abradable material facing, respectively, the 1, 2, 3 and 4 rotor blades. (b) An inner shroud, whose inner face is lined with abradable material facing the seal serrations machined on the booster spool.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B (c) Individual vanes of the stage 1 and stage 5 vane assemblies are welded to the outer shroud. Individual vanes of the stages 2, 3 and 4 vane assemblies are bolted to the outer shroud. (d) Stator vanes are retained on the inner shroud by the abradable material. Stage one vane assembly has 100 vanes, stage 2 vane assembly has 122 vanes, stage 3 vane assembly has 122 vanes stage 4 vane assembly has 116 vanes and stage 5 vane has 96 vanes. (2) The outer shroud rear flange of stage 5 vane assembly is bolted to the front face of the fan frame. The inner shroud rear flange is rabbeted to form an interference fit with a corresponding flange on the fan frame. (3) The outer shroud of booster stage 3 and of stage 5 vane assemblies has an orifice at the 3:30 oclock position to permit the borescope inspection of the booster mid and rear stages rotor blades (full view) and of the related vane assemblies (partial view only). These borescope orifices are designed SO3 and SO5, respectively in the chapter which follows.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 6 Nov 01/08
C F M 56-5B FAN AND BOOSTER ASSEMBLY - REMOVAL/INSTALLATION _______________________________________________ TASK 72-21-00-000-005 Removal of the Spinner Front Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1130
warning notice access platform 1 m (3 ft. 3 in.) 1 TOOL SET - JACK SCREW
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-991-300
Fig. 401
3. __________ Job Set-up Subtask 72-21-00-941-067 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put the access platform in position. 4. Procedure _________ (Ref. Fig. 401/TASK 72-21-00-991-300) Subtask 72-21-00-020-063 A. Removal of the Spinner Front Cone: CAUTION : BE CAREFUL NOT TO LOOSE THE WASHERS WHEN YOU REMOVE THE _______ ATTACHMENT BOLTS. NORMALLY, THEY ARE STUCK ON THE FRONT CONE. PRE CFM SB 72-0193 (1) Remove the bolts (40) which attach the spinner front cone (50) to the spinner rear cone (20). END OF PRE CFM SB 72-0193 POST CFM SB 72-0193 R R R
(2) Alternative Procedure Available. Remove the bolts (40) and the washers (35) which attach the spinner front cone P/N 338-00-204-0 (50) to the spinner rear cone (20).
R R
(3) Alternative Procedure. Remove the bolts (40) which attach the spinner front cone P/N 338-085-204-0 (50) to the spinner rear cone (20). END OF POST CFM SB 72-0193
R
(4) Move the Spinner Front Cone: CAUTION : BE CAREFUL NOT TO LET THE SPINNER FRONT CONE FALL DOWN WHEN _______ YOU DETACH IT FROM THE REAR CONE. (a) Move the spinner front cone (50) apart from the spinner rear cone (20) with the 3 jackscrews (P08) from the tool set TOOL SET JACK SCREW, (856A1130G02/G06)
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Page 402 Feb 01/10
C F M 56-5B
R
Spinner Front and Rear Cones Figure 401/TASK 72-21-00-991-300
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Page 403 Feb 01/10
C F M 56-5B TASK 72-21-00-400-005 Installation of the Spinner Front Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
heat gun warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 PIN,GUIDE-SPINNER REAR CONE
856A3409
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
* engine oil (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-991-300
Fig. 401
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Page 404 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-860-054 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. 4. Procedure _________ (Ref. Fig. 401/TASK 72-21-00-991-300) Subtask 72-21-00-480-057 A. Install the guide pins as follows: (1) Apply a thin layer of engine oil (Material No. CP2442) to the 3 PIN,GUIDE-SPINNER REAR CONE (856A3409G01). (2) Install the guide pins on the flange of the spinner rear cone. Install one of the pins in the offset hole. Subtask 72-21-00-420-066 B. Prepare and Install the Spinner Cone: R R
WARNING : USE HEAT INSULATED GLOVES WHEN YOU TOUCH CHILLED OR HOTS PARTS _______ TO PREVENT INJURY (1) Increase the temperature of the front flange of the spinner rear cone to approximately 80 deg.C (176 deg.F) with a heat gun. (2) Install the Spinner Front Cone. CAUTION : DURING INSTALLATION, MAKE SURE THERE IS A WASHER, BONDED OR _______ NOT, UNDER EACH BOLT HEAD. (a) Install the spinner front cone (50) on the spinner rear cone (20). Carefully align the offset holes. Subtask 72-21-00-080-053 C. Remove the guide pins.
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Page 405 Feb 01/09
C F M 56-5B Subtask 72-21-00-420-073 D. Attach the Spinner Front Cone. (1) Apply a thin layer of engine oil (Material No. CP2442) to the threads of the 6 bolts (40). PRE CFM SB 72-0193 (2) Attach the spinner front cone (50) to the spinner rear cone (20) with the bolts (40). END OF PRE CFM SB 72-0193 POST CFM SB 72-0193 R R R
(3) Alternative Procedure Available. Attach the spinner front cone P/N 338-001-204-0 (50) to the spinner rear cone (20) with the bolts (40) and the washers (35).
R R
(4) Alternative Procedure. Attach the spinner front cone P/N 338-085-204-0 (50) to the spinner rear cone (20) with the bolts (40). END OF POST CFM SB 72-0193
R
(5) Tighten the bolts (40) by hand, and let the mating parts return to the ambient temperature.
R
(6) TORQUE the bolts (40) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). 5. Close-up ________ Subtask 72-21-00-869-062 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-061 B. Close Access (1) Remove the warning notice(s). (2) Remove the access platform(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 406 Feb 01/10
C F M 56-5B TASK 72-21-00-000-006 Removal of the Spinner Rear Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1130
warning notice access platform 1 m (3 ft. 3 in.) 1 TOOL SET - JACK SCREW
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-991-300
Removal of the Spinner Front Cone Fig. 401
3. __________ Job Set-up Subtask 72-21-00-941-068 A. Safety Precautions (1) Put the access platform in position. (2) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (3) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 407 Nov 01/08
C F M 56-5B (4) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). 4. Procedure _________ (Ref. Fig. 401/TASK 72-21-00-991-300) Subtask 72-21-00-020-064 A. Remove the Spinner Rear Cone: CAUTION : BE CAREFUL NOT TO LET THE SPINNER FRONT CONE FALL DOWN WHEN YOU _______ DETACH IT FROM THE REAR CONE. (1) Remove spinner front cone (Ref. TASK 72-21-00-000-005) (2) Remove the bolts (30) and the washers (10) which attach the spinner rear cone (20) to the fan disk. (3) Remove the spinner rear cone from the fan disk with the 6 jackscrews from the TOOL SET - JACK SCREW (856A1130G02/G06).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 408 Nov 01/08
C F M 56-5B TASK 72-21-00-400-006 Installation of the Spinner Rear Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No
specific specific specific specific specific
feeler gage set heat gun warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 PIN,GUIDE-SPINNER REAR CONE
856A3409
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2442
* graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-006 72-21-00-400-005 72-21-00-991-300 72-21-00-991-301
Removal of the Spinner Rear Cone Installation of the Spinner Front Cone Fig. 401 Fig. 402
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 409 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-860-055 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position. (2) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (3) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). 4. Procedure _________ (Ref. Fig. 401/TASK 72-21-00-991-300, 402/TASK 72-21-00-991-301) Subtask 72-21-00-480-058 A. Install guide pins as follows: (1) Apply a thin layer of engine oil (Material No. CP2442) to the 3 PIN,GUIDE-SPINNER REAR CONE (856A3409G01). (2) Install the 3 guide pins, equally spaced, on the forward flange of the fan disk. Install one of the pins in the offset hole of the flange. Subtask 72-21-00-420-067 B. Install the spinner rear cone as follows: (1) Apply a thin layer of graphite grease (Material No. CP2101) to the threads of the bolts (30). (2) Safety precautions WARNING : USE HEAT INSULATED GLOVES WHEN YOU TOUCH CHILLED OR HOTS _______ PARTS TO PREVENT INJURY (a) Increase the temperature of the aft flange of spinner rear cone (20) to 60 deg.C (140.00 deg.F) with a heat gun.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 410 Nov 01/08
C F M 56-5B
Post Installation checks of the Spinner Rear Cone Figure 402/TASK 72-21-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 411 Nov 01/08
C F M 56-5B (3) Install the spinner rear cone. CAUTION : TAKE CARE NOT TO LET THE SPINNER REAR CONE FALL WHEN YOU _______ INSTALL IT ON THE FAN DISK. DAMAGE TO THE CONE COULD RESULT. (a) Install the spinner rear cone on the fan disk forward flange as follows: 1 _
Align the offset holes NOTE : The offset hole in the spinner rear cone is identified ____ by a spherical indentation on its rear flange.
2 _
Install three equally-spaced bolts (30) and washers (10) and tighten them until the rear cone comes fully against the forward flange of fan disk. While you do this, make sure that the lip of the rear cone seal engages correctly under the front edge of the fan blade platforms.
(4) Let the assembly return to ambient temperature. Then remove the 3 guide pins PIN,GUIDE-SPINNER REAR CONE (856A3409G01). (5) Install the remaining bolts (30) and washers (10). (6) TORQUE all the bolts (30) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). Subtask 72-21-00-220-056 C. Do a check of the spinner rear cone to fan disk for correct installation as follows: (Ref. Fig. 402/TASK 72-21-00-991-301) (1) Make a check of the Gap F34 over 360 degrees with a feeler gage set. NOTE : The gap F34 is the blueprint clearance, or gap, between the ____ aft edge of the spinner rear cone and the front edge of the fan blade platforms after installation. (a) The gap F34 must measure between: (0.020 in. (0.5 mm) to 0.051 in. (1.3 mm) (b) If this gap F34 is out of limits at any location of the circumference, remove the rear cone (Ref. TASK 72-21-00-000-006) find the cause (see the NOTE) and correct it.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 412 Nov 01/08
C F M 56-5B NOTE : The cause might be a mis-installed blade on the fan disk, ____ a FOD damaged blade in the platform area, or a out-of-shape aft flange of the spinner rear cone, for example. (2) Make a check of the seating of the spinner rear cone on the fan disk flange at location A. (a) Do this check at 6 locations at least, and radially to the flange scallops. (b) The seating is correct if you cannot engage a feeler gage of 0.001 in. (0.02 mm) maximum thickness between two flange scallops at the specified 6 locations marked A. (c) If you can engage the 0.001 in. (0.02 mm) feeler gage at two or three consecutive locations, the seating is incorrect in the related sector. Before to do anything else, make sure the bolts in this sector are correctly torqued. If after this check the seating remains incorrect, remove the spinner rear cone (Ref. TASK 72-21-00-000-006), find the cause and correct it. Subtask 72-21-00-410-060 D. Install spinner front cone (Ref. TASK 72-21-00-400-005) 5. Close-up ________ Subtask 72-21-00-869-063 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-062 B. Close Access (1) Remove the warning notice(s). (2) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 413 Nov 01/08
C F M 56-5B TASK 72-21-00-000-007 Removal of the Fan Rotor Blades CAUTION : ALL FAN ROTOR BLADES SHALL BE MATCHMARKED OR NUMBERED FOR ASSEMBLY IN _______ ORIGINAL ALIGNMENT AND POSITION USING ONLY APPROVED MARKING MATERIAL. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 856A2631
rubber mat or foam material flooring warning notice access platform 1 m (3 ft. 3 in.) 1 STAND,STORAGE-FAN BLADES
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP5061
* temporary marking (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-991-302
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Fig. 403
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 414 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-941-069 A. Safety Precautions (1) Put the access platform in position. (2) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (3) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (4) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-21-00-010-058 B. Preparation for Removal of the Fan Blades: (1) Install a rubber mat or foam material flooring in the inlet cowl before you go into it. (2) Remove spinner front cone. (Ref. TASK 72-21-00-000-005) (3) Remove spinner rear cone. (Ref. TASK 72-21-00-000-006) NOTE : Removal will be easier if fan blade to be removed is placed at ____ the 12 oclock position.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 415 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 403/TASK 72-21-00-991-302) Subtask 72-21-00-020-065 A. Removal of the fan blades: CAUTION : USE ONLY APPROVED MARKING MATERIAL TO PREVENT DAMAGE TO THE _______ BLADES. (1) Temporarily mark each blade (80) from 1 to 36 on their convex side. Use a temporary marking (Material No. CP5061). Blade No. 1 will be the blade immediately above the offset hole in the fan disk bolt flange. Numbering is counter-clockwise (CCW), forward locking aft. (2) Removal of the first and second fan blades circled 1 and 2. NOTE : The removal of blades (80) is counterclockwise (CCW) after the ____ first blade removed. NOTE : Put the first blade to be removed at the 12 oclock position ____ to ease the removal. (a) Remove spacer (70) from the fan blade circled 2 located immediately at left of the first blade circled 1 you want to remove. Carefully lower blade circled 2 in its dovetail recess (this unlocks it from its engagement on the booster spool), and move it at a slope (inclined) to the left. Do not try to remove it now. (b) Remove spacer (70) from the first blade circled 1 to be removed. (c) Lower blade circled 1 in its dovetail recess (this unlocks it), and carrefully pul it forward while you move its left midspan shroud above the right midspan shroud of the (sloped) blade circled 2 at left. Remove blade circled 1. (d) Remove blade. (3) Removal of the 3rd to the 36th blades: (a) The removal of the following blades is easier, done CCW, and as follows for each blade: 1 _
Remove spacer (70)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 416 Nov 01/08
C F M 56-5B 2 _
Remove blade (80).
(4) Put spacer (70) and fan blades from 1 through 36 in their related compartements on STAND,STORAGE-FAN BLADES (865A2631G01)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 417 Nov 01/08
C F M 56-5B
Removal of Fan Blades Figure 403/TASK 72-21-00-991-302- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 418 Nov 01/08
C F M 56-5B
Removal of Fan Blades Figure 403/TASK 72-21-00-991-302- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 419 Nov 01/08
C F M 56-5B TASK 72-21-00-400-007 Installation of the Fan Rotor Blades CAUTION : ALL FAN ROTOR BLADES SHALL BE MATCHMARKED OR NUMBERED FOR ASSEMBLY IN _______ ORIGINAL ALIGNMENT AND POSITION USING ONLY APPROVED MARKING MATERIAL. CAUTION : DO NOT DISSOCIATE FAN BLADE PAIRS MATCHED DURING ORIGINAL ASSEMBLY. _______ BLADES FROM A SAME PAIR MUST ALWAYS BE LOCATED 180 DEGREES APART. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A2631
warning notice access platform 1 m (3 ft. 3 in.) 1 STAND,STORAGE-FAN BLADES
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2104
Material No.
CP5062
* molykote g rapid (Ref. 70-30-00) * MoS2 dry film lubricant (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-400-005 72-21-00-400-006 72-21-00-991-303 72-21-00-991-304
Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Fig. 404 Fig. 405
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 420 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-860-056 A. Aircraft Maintenance Configuration (1) Make sure that the access platform is in position. (2) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (3) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). 4. Procedure _________ (Ref. Fig. 404/TASK 72-21-00-991-303, 405/TASK 72-21-00-991-304) Subtask 72-21-00-420-068 A. Preparation and Installation of the Fan Rotor Blades: (1) Preparation for Installation of Fan Rotor Blades. CAUTION : THE FAN BLADES ARE KEPT IN NUMERICAL ORDER ON THE STORAGE _______ STAND AND MUST BE INSTALLED ACCORDINGLY ON THE FAN DISK. BLADE N⁰1 IS INSTALLED IN FRONT OF THE OFFSET BOLT OF THE FAN DISK. NUMBERS ARE GIVEN COUNTERCLOCKWISE, FORWARD LOOKING AFT. NOTE : Installation will be easier if the fan disk blade recess into ____ which the blade is to be installed is placed at the 6 Oclock position. (a) Get the fan blades (80) from STAND,STORAGE-FAN BLADES (856A2631G01). NOTE : Put the fan disk dovetail slot, where you want to install ____ blade No. 1 at the 6 Oclock position. This will help installation of the blades on the fan disk.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 421 Nov 01/08
C F M 56-5B
Installation of the First Fan Blade at 6 Oclock Figure 404/TASK 72-21-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 422 Nov 01/08
C F M 56-5B
Installation of the 2 Last Fan Blades at 12 Oclock Figure 405/TASK 72-21-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 423 Nov 01/08
C F M 56-5B (b) Apply lubricant MoS2 dry film lubricant (Material No. CP5062) or molykote g rapid (Material No. CP2104) to the disk slots, the spacers, the blade roots (dovetails), the blade platforms and lateral surfaces of these platforms, and the midspan shroud mating surfaces, before you install the blades. NOTE : You must apply a large quantity of lubricant to all the ____ dovetail and slot pressure faces. Brush application is prefered. If you use spray application , a minimum of 4 to 6 passes is necessary to supply all the pressure faces with sufficient lubrication. Let the lubricant become dry to a dull opaque finish before you install the blades in the disk slots. (2) Installation of the Fan Rotor Blades. (a) Position the fan blade No. 1 correctly (leading edge forward) and engage (dovetail lug first) in the fan disk slot No. 1 immediately below the offset hole in the fan disk bolt flange. (b) Push the blade in full position. (c) Pull down the fan blade to engage the lug into the booster spool recess. (d) Install the spacer (70) between the fan blade No. 1 and the disk. Push the spacer fully in position against the front frange of the booster spool. (e) Continue COUNTERCLOCKWISE, forward locking aft and use the same procedure as for fan blade No. 1 to install blades No. 2 through No. 34 in their related slots. NOTE : The midspan shroud section of each blade will engage and ____ mate with the related midspan shroud sections of adjacent blades. (f) Install the 2 last fan blades 35 and 36 at the 12 Oclock position, as follows: 1 _
Fully engage blade 36, in its dovetail recess. Let its dovetail root touch the bottom of the recess. Do not install its spacer.
2 _
Carefully engage blade 35, in its dovetail recess and install its spacer (70).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 424 Nov 01/08
C F M 56-5B 3 _
Install the spacer (70) of blade 36.
(g) Make sure that all the blades and spacers are correctly installed. (h) Install the spinner rear cone. (Ref. TASK 72-21-00-400-006) (i) Install the spinner front cone. (Ref. TASK 72-21-00-400-005) (j) Remove the rubber pad or foam material flooring from the inlet cowl. 5. Close-up ________ Subtask 72-21-00-869-064 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-063 B. Close Access (1) Remove the warning notice(s). (2) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 425 Nov 01/08
C F M 56-5B TASK 72-21-00-300-028 Replacement of Fan Rotor Blades in Pairs 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 CFMI SOFTWARE FOR BLADE MAPPING
856A3770
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
Material No.
CP5061
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * temporary marking (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 426 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-009 71-00-00-750-001 72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-300-009 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-21-00-991-327 72-21-00-991-341 72-21-00-991-342 72-21-00-991-343 72-21-00-991-344 72-21-00-991-345 72-21-00-991-346
Vibration Check Fan Trim Balance - 1 sensor 3 speed Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Correction of the Static Imbalance Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Fig. 406 Fig. 407 Fig. 408 Fig. 409 Fig. 410 Fig. 411 Fig. 412
3. __________ Job Set-up Subtask 72-21-00-941-085 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 427 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 406/TASK 72-21-00-991-327, 407/TASK 72-21-00-991-341, 408/TASK 72-21-00-991-342, 409/TASK 72-21-00-991-343, 410/TASK 72-21-00-991-344) Subtask 72-21-00-869-079 A. Remove the fan blades before record moment weight. CAUTION : DO NOT MIX PAIR OF BLADES PRE CFM SB 72-0057 AND POST CFM SB _______ 72-0057 ON THE SAME FAN DISK. NOTE : The spare blades are grouped in pairs so that the difference ____ between the moment weights is not more than 80 in.g (200 cm.g). If the result of the fan blade plotting is not correct, you must do the checks and corrections given below before and after blade installation to make sure the engine imbalance is not more than the limits. This will also optimize the engine operation. Four conditions can exist, refer to the logic diagram. (Ref. Fig. 406/TASK 72-21-00-991-327)
R R R R R
NOTE : In all replacement cases: 1,2,3.....N pairs of fan blades and for ____ individual fan blade replacement, a vibration survey can be performed (Ref. TASK 71-00-00-710-009). Results from the vibration survey will determine if a trim balance is necessary. In this last case, do a trim balance operation (Ref. TASK 71-00-00-750-001) if the aircraft is at the main base or as soon as the aircraft returns to the base. (1) Put a rubber mat in the air intake cowl. (2) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (3) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (4) Record location of each blade to be replaced and of each blade opposite. (5) Remove fan blades (Ref. TASK 72-21-00-000-007)
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 428 May 01/09
C F M 56-5B
R
Diagram for Fan Blade Change Figure 406/TASK 72-21-00-991-327
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 429 Nov 01/08
C F M 56-5B
Fan Blade Replacement Figure 407/TASK 72-21-00-991-341 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 430 Nov 01/08
C F M 56-5B
Replacement of Several Pairs of Fan Blades Figure 408/TASK 72-21-00-991-342 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 431 Nov 01/08
C F M 56-5B
Fan Blades, Balance Screw Location Chart and Vectorial Diagram Figure 409/TASK 72-21-00-991-343 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 432 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
72-21-00 CES
Page 433 Nov 01/98
C F M 56-5B
Various Balance Screw Arrangements for Given Moment Weights Figure 410/TASK 72-21-00-991-344- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 434 Nov 01/08
C F M 56-5B
Various Balance Screw Arrangements for Given Moment Weights Figure 410/TASK 72-21-00-991-344- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 435 Nov 01/08
C F M 56-5B (6) Write moment weight on base of blades that you remove using temporary marking (Material No. CP5061). (Ref. Fig. 407/TASK 72-21-00-991-341) NOTE : Grease deposits can mask the moment weight indication. If ____ necessary, clean blade base with isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656). Subtask 72-21-00-420-081 B. Record moment weight on base of spare blades. CAUTION : FOR EACH PAIR OF FAN BLADES, INSTALL THE HEAVIER SPARE BLADE AT _______ THE POSITION OF THE HEAVIER BLADE TO BE REMOVED. (1) Write the moment weight on base of the spare blades with temporary marking (Material No. CP5061). (2) Install spare blades (Ref. TASK 72-21-00-400-007). Subtask 72-21-00-820-053 C. Determine the balance screws to be installed. (1) Determine the resultant vector length and direction, then select balance screws to provide a correction returning the fan to its initial balance condition as follows. NOTE : It is advisable to limit the number of balance screws on the ____ spinner due the complexity and the risk of confusion when performing further corrections, and to install only one set of balance screws. This requires the construction of a vector diagram for determining the sum of the corrections. An example is given in (Ref. TASK 72-21-00-300-009). (a) Assume the following blades with the moment weights indicated are to be removed: No. 01: 164832 cm.g (64894 in.g) No. 36: 163245 cm.g (64270 in.g) No. 03: 162510 cm.g (63980 in.g) No. 35: 164185 cm.g (64640 in.g)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 436 Nov 01/08
C F M 56-5B (b) Assume the moment weights of the opposite blades are as follows: No. 19: 164647 cm.g (64823 in.g) No. 18: 163405 cm.g (64333 in.g) No. 21: 162650 cm.g (64035 in.g) No. 17: 164160 cm.g (64630 in.g) (c) Calculate differences between moment weights D1: (No. 01/19) = 164832 - 164647 = 185 cm.g D2: (No. 18/36) = 163405 - 163245 = 160 cm.g D3: (No. 21/03) = 162650 - 162510 = 140 cm.g D4: (No. 35/17) = 164185 - 164160 = 025 cm.g (d) Calculate blades as D1: (No. D2: (No. D3: (No. D4: (No.
moment below: 01/19) 18/36) 21/03) 35/17)
as below: (73 in.g) (63 in.g) (55 in.g) (10 in.g)
weight differences corresponding to spare fan = = = =
162905 161205 164570 163825
-
162730 161185 164545 163630
= = = =
175 020 025 195
cm.g cm.g cm.g cm.g
(69 (08 (10 (77
in.g) in.g) in.g) in.g)
(e) Calculate differences between removed blades and spare blades as below: D1 - D1 = 185 - 175 = 010 cm.g (04 in.g) = F1 D2 - D2 = 160 - 020 = 140 cm.g (55 in.g) = F2 D3 - D3 = 140 - 025 = 115 cm.g (45 in.g) = F3 D4 - D4 = 195 - 025 = 170 cm.g (67 in.g) = F4 (f) Determine the direction of corrections as follows: NOTE : When D is greater than D the balance weight should be ____ added close to the heavier blade. When D is lighter than D the balance weight should be added close to the lighter blade. 1 _
For blades No. 1 and 19, D1 is greater than D1 and the balance weight should therefore be added close to the heavier blade: No. 1.
2 _
For blades No. 18 and 36, D2 is greater than D2 and the balance weight should therefore be added close to the heavier blade: No. 18.
3 _
For blades No. 21 and 3, D3 is greater than D3 and the balance weight should therefore be added close to the heavier blade: No. 21.
4 _
For blades No. 35 and 17, D4 is less than D4 and the balance weight should ore be added close to the lighter blade: No. 17.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 437 Nov 01/08
C F M 56-5B (g) Construct vectorial diagram as follows: (Ref. Fig. 408/TASK 72-21-00-991-342, 409/TASK 72-21-00-991-343) 1 _
On a polar diagram draw vectors corresponding to moment weight difference calculated in (e) and orientated as in (f). (Ref. Fig. 409/TASK 72-21-00-991-343)
2 _
Draw the resultant Fr representing the correction required from F1, F2, F3 and F4. NOTE : In this example, Fr is approximately 405 cm.g (159 ____ in.g) and orientated close to the balance screw No. 18. NOTE : When resultant imbalance direction is between 2 holes, ____ the screw given in fifth column of referenced figures must be placed in the nearest hole.
(h) Select balance screws as follows: (Ref. Fig. 410/TASK 72-21-00-991-344) 1 _
Find in the tables the values of the resultant Fr calculated in paragraph (g). This indicates which balance screw must be installed. The screw in the fifth column of the table must be installed at location calculated in paragraph (g). NOTE : In this example, for a resultant Fr of 405 cm.g (159 ____ in.g), one centered screw P01 installed in hole No. 18 and two lateral screw P02 installed in holes No. 17 and No. 19 provide a correction returning the fan to its initial balance condition. NOTE : Balance screws are identified by a number corresponding ____ to their moment weight (P01-P02-P03-P04-P05-P06-P07) engraved on screw head. As it may be difficult to read the numbers due to erosion and pollution, the relationship between the screw reference and screw length is shown in. (Ref. Fig. 411/TASK 72-21-00-991-345)
(2) Install balance screws. TORQUE the screws to between 65 and 75 lbf.in (0.73 and 0.84 m.daN). (3) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (4) Install the spinner front cone (Ref. TASK 72-21-00-400-005).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 438 Nov 01/08
C F M 56-5B
Balance Screws Figure 411/TASK 72-21-00-991-345 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 439 Nov 01/08
C F M 56-5B (5) Remove the rubber mat from the air intake cowl. (6) Do a vibration check (Ref. TASK 71-00-00-710-009) if resultant is greater than 400 cm.g (157.5 in.g). (Ref. Fig. 412/TASK 72-21-00-991-346) (a) If the vibration level is out of the limits, do a trim balance (Ref. TASK 71-00-00-750-001) with CFMI SOFTWARE FOR BLADE MAPPING. 5. Close-up ________ Subtask 72-21-00-869-080 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-078 B. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 440 Nov 01/08
C F M 56-5B
Diagram for Fan Blade Change in Individual Figure 412/TASK 72-21-00-991-346 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 441 Nov 01/08
C F M 56-5B TASK 72-21-00-300-029 Replacement of Individual Fan Blades 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 CFMI SOFTWARE FOR BLADE MAPPING
856A3770
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
* graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-009 71-00-00-750-001 72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-21-00-991-341 72-21-00-991-344
Vibration Check Fan Trim Balance - 1 sensor 3 speed Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Fig. 407 Fig. 410
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 442 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-991-345 72-21-00-991-346
Fig. 411 Fig. 412
3. __________ Job Set-up Subtask 72-21-00-941-086 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put an access platform in position. 4. Procedure _________ (Ref. Fig. 407/TASK 72-21-00-991-341, 410/TASK 72-21-00-991-344, 411/TASK 72-21-00-991-345, 412/TASK 72-21-00-991-346) Subtask 72-21-00-020-076 A. Record moment weight of blades. CAUTION : DO NOT MIX PAIR OF BLADES PRE CFM SB 72-0057 AND POST CFM SB _______ 72-0057 ON THE SAME FAN DISK. NOTE : If pairs of fan blades are not available as spare, you can replace ____ one blade individually. If the result of the fan blade plotting is not correct, you must do the inspections and corrections given below before and after the fan blade installation to make sure the engine imbalance is not more than the limits. This will also
R R R
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 443 May 01/09
C F M 56-5B optimize the engine operation. Two conditions can exist, refer to the logic dynamic. (Ref. Fig. 412/TASK 72-21-00-991-346) NOTE : In all cases of individual blade replacement, remove its opposite ____ to record the moment weight of the opposite blade. (1) Put a rubber mat in the air intake cowl. (2) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (3) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (4) Record moment weight of removed blade. (5) Remove fan blade (Ref. TASK 72-21-00-000-007) (6) Record moment weight of blade to be installed. Subtask 72-21-00-420-082 B. Install fan blade (Ref. TASK 72-21-00-400-007) Subtask 72-21-00-750-055 C. Calculate difference between moment weights of both blades. (1) If difference between moment weights D is greater than 200 cm.g (80 in.g), correct the imbalance as in the example which follows: NOTE : If you change only one fan blade and if the moment weight with ____ the opposite blade is less than 200 cm.g (80 in.g), no correction is necessary. NOTE : If you change more than one fan blade, a vectoriel diagram ____ must be done in order to identify the resultant imbalance. Apply the procedure as shown in the following example. (2) Assume a blade with moment weight of 162750 cm.g (64075 in.g) is to be replaced in any position. (3) A spare blade is provided with moment weight of 163296 cm.g (64290 in.g). (4) Calculate the difference between the moment weights as below: 163296 - 162750 = 546 cm.g (215 in.g).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 444 May 01/09
C F M 56-5B (5) Select balance screws as follows: (a) To determine the solutions closest to above difference of 546 cm.g (215 in.g). One centered screw P05 and 2 lateral screws P01 = 541 cm.g (213 in.g). This solution permits a satisfactory correction for returning the fan close to its initial balance condition. (Ref. Fig. 410/TASK 72-21-00-991-344) (6) Locate balance screws as follows: (a) As the new blade is heavier than the removed blade, install balance screws close to the opposite blade. NOTE : If the new blade is lighter than the removed blade, ____ install balance screw close to the removed blade. (7) Install balance screws lightly coated with graphite grease (Material No. CP2101). TORQUE screws to between 65 and 75 lbf.in (0.73 and 0.84 m.daN). NOTE : Balance screws are identified by a number corresponding to ____ their moment weight (P01-P02-P03-P04-P05-P06-P07) engraved on screw head. As it may be difficult to read the numbers due to erosion and pollution, the relationship between the screw reference and screw length is shown in. (Ref. Fig. 411/TASK 72-21-00-991-345) (8) Install the spinner rear cone (Ref. TASK 72-21-00-400-005). (9) Install the spinner front cone (Ref. TASK 72-21-00-400-006). (10) Remove the rubber mat from the inlet cowl. (11) Do a vibration-check (Ref. TASK 71-00-00-710-009) if resultant is greater than 400 cm.g (157.5 in.g). (Ref. Fig. 412/TASK 72-21-00-991-346) (a) If the vibration level is out of the limits, do a trim balance (Ref. TASK 71-00-00-750-001) with CFMI SOFTWARE FOR BLADE MAPPING .
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 445 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-21-00-869-081 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-079 B. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 446 Nov 01/08
C F M 56-5B TASK 72-21-00-920-001 Discard Fan Disc and Booster Spool 1. __________________ Reason for the Job Refer to the MPD TASK: 722100-C1 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-00-00-400-042 ESM 722100
Removal of the Power Plant Installation of the Power Plant
3. __________ Job Set-up Subtask 72-21-00-010-062 A. Remove the engine (Ref. TASK 71-00-00-000-042). 4. Procedure _________ Subtask 72-21-00-020-077 A. Remove and discard fan disk and booster spool (Ref. ESM 722100). Subtask 72-21-00-420-083 B. Install new fan disc and booster spool (Ref. ESM 722100). 5. Close-up ________ Subtask 72-21-00-410-064 A. Install the engine (Ref. TASK 71-00-00-400-042).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 447 Nov 01/08
C F M 56-5B TASK 72-21-00-920-002 Discard Fan Shaft 1. __________________ Reason for the Job Refer to the MPD TASK: 722100-C2 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-00-00-400-042 ESM 722200
Removal of the Power Plant Installation of the Power Plant
3. __________ Job Set-up Subtask 72-21-00-010-063 A. Remove the engine (Ref. TASK 71-00-00-000-042). 4. Procedure _________ Subtask 72-21-00-020-078 A. Remove and discard fan shaft (Ref. ESM 722200). Subtask 72-21-00-420-084 B. Install fan shaft (Ref. ESM 722200). 5. Close-up ________ Subtask 72-21-00-410-065 A. Install the engine (Ref. TASK 71-00-00-400-042).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 448 Nov 01/08
C F M 56-5B TASK 72-21-00-000-008 Removal of the Stage 1 Booster Vane Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific 856A1130
warning notice 1 TOOL SET - JACK SCREW
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-23-00-000-028 72-21-00-991-305 72-21-00-991-306
Removal of Removal of Removal of Removal of Fig. 413 Fig. 414
the the the the
Spinner Front Cone Spinner Rear Cone Fan Rotor Blades Splitter Fairing
3. __________ Job Set-up Subtask 72-21-00-941-070 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 449 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). 4. Procedure _________ (Ref. Fig. 413/TASK 72-21-00-991-305, 414/TASK 72-21-00-991-306) Subtask 72-21-00-020-071 A. Preparation for Removal of the Stage 1 Booster Vane Assembly: (1) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (2) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (3) Remove all the fan blades (Ref. TASK 72-21-00-000-007). (4) Remove the splitter fairing (Ref. TASK 72-23-00-000-028). Subtask 72-21-00-020-066 B. Removal of the Stage 1 Booster Vane Assembly: (1) Remove the 24 bolts that secure the stage 1 vane assembly to the stage 2 vane (2) Move apart stage 1 vane assembly from the stage 2 vane assembly, using jackscrews, P13, from the TOOL SET - JACK SCREW (856A1130G02/G06), on the equally spaced threaded holes located on the rear flange of the stage 1 vane assembly.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 450 Nov 01/08
C F M 56-5B
Stage 1 Booster Vane Assembly Figure 413/TASK 72-21-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 451 Nov 01/08
C F M 56-5B
Installation of Stage 1 Booster Vane Assembly Figure 414/TASK 72-21-00-991-306 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 452 Nov 01/08
C F M 56-5B TASK 72-21-00-400-008 Installation of the Stage 1 Booster Vane Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
heat gun warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 GUIDE PINS - BOOSTER VANE ASSY
856A2916
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 453 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-23-00-400-028 72-21-00-991-305 72-21-00-991-306
Installation Installation Installation Installation Fig. 413 Fig. 414
of of of of
the the the the
Spinner Front Cone Spinner Rear Cone Fan Rotor Blades Splitter Fairing
3. __________ Job Set-up Subtask 72-21-00-860-057 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). 4. Procedure _________ (Ref. Fig. 413/TASK 72-21-00-991-305, 414/TASK 72-21-00-991-306) Subtask 72-21-00-480-059 A. Install the 3 guide pins, GUIDE PINS - BOOSTER VANE ASSY (856A2916G01), equally spaced on vane assembly, stage 2. Subtask 72-21-00-110-053 B. Clean the Making Faces: WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY SHOULD _______ BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 454 Nov 01/08
C F M 56-5B (1) Thoroughly clean the mating faces of the stage 1 and stage 2 vanes assemblies with acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041). Subtask 72-21-00-420-069 C. Preparation and Installation of the Stage 1 Vane Assembly: (1) Increase the temperature of the forward flange of stage 2 vane assembly to between 75 deg.C (167.00 deg.F) and 85 deg.C (185.00 deg.F) with a heat gun. (2) Install the stage 1 vane assembly WARNING : WEAR THERMAL INSULATED GLOVES WHEN HANDLING HEATED OR _______ CHILLED PARTS TO PREVENT INJURY TO HANDS. (a) Align the offset holes and use the 3 guide pins, to install the stage 1 vane assembly on the booster assembly. Subtask 72-21-00-080-054 D. Remove the guide pins, GUIDE PINS - BOOSTER VANE ASSY (856A2916G01), apply a thin layer of graphite grease (Material No. CP2101) on the threads of bolts and seat the stage 1 vane assembly with 24 bolts. Subtask 72-21-00-220-053 E. Do a check of the seating of the stage 1 vane assembly on the stage 2 vane assembly with 0.001 in. (0.02 mm) feeler gage. Subtask 72-21-00-420-074 F. Install the Fan Components: (1) Let the parts return to ambient temperature and TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN) (2) Install the splitter fairing (Ref. TASK 72-23-00-400-028). (3) Install all the fan blades (Ref. TASK 72-21-00-400-007). (4) Install the spinner rear cone (Ref. TASK 72-21-00-400-006).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 455 Nov 01/08
C F M 56-5B (5) Install the spinner front cone (Ref. TASK 72-21-00-400-005). 5. Close-up ________ Subtask 72-21-00-869-065 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-064 B. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 456 Nov 01/08
C F M 56-5B FAN AND BOOSTER ASSEMBLY - INSPECTION/CHECK ___________________________________________ TASK 72-21-00-210-005 Inspection/Check of the Spinner Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2216
* Loctite 496 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-200-025 72-00-00-200-025 72-21-00-000-005 72-21-00-000-006 72-21-00-300-001 72-21-00-400-005 72-21-00-400-006 72-55-00-960-002
Over-Serviceable-Limit Extensions Over-Serviceable-Limit Extensions Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Replacement of the Crimped Self-Locking Nuts on the Spinner Rear Cone Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Replacement of LPT Shaft Plug O-rings
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Feb 01/10
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-941-078 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-21-00-020-072 B. Remove the Spinner Cone. (1) Remove the spinner front cone (Ref. TASK 72-21-00-000-005) (2) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006) 4. Procedure _________ Subtask 72-21-00-210-055 A. Inspection of the spinner cone ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Spinner front cone for: A. Cracks
Not serviceable.
Install a new or serviceable spinner front cone (Ref. TASK 72-21-00400-005).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Nicks, dents and No limited quantity scratches C. Damaged or missing surface protection for aluminium spinner front cone.
No limit if not greater than 50 percent of total surface
If more than 50 percent of total surface, install a new or serviceable spinner front cone (Ref. TASK 7221-00-400-005)
D. Loose or missing bonded washer.
Not serviceable.
Reinstall washer using Loctite 496 (Material No. CP2216) and hold it in pressure
E. Tip erosion.
No limit if radius is not greater than 0.28 in. (7.1 mm) after blending.
Do blending procedure to maximum serviceable limits or install a new serviceable spinner front cone (Ref. TASK 72-21-00400-005).
F. Missing anti-erosion paint.
Any amount is permitted.
G. Corrosion marks (white mushroom pattern) before part removal.
These corrosion marks are not serviceable.
Refer to over serviceable (Ref. TASK 72-00-00-200025).
A. Cracks
Not serviceable
Install a new or serviceable spinner rear cone (Ref. TASK 72-21-00400-006).
B. Dents
No limited quantity
C. Damaged surface protection.
No limit if not greater than 10 percent of total surface
2. Spinner rear cone for:
If more than 10 percent of total surface, install a new or serviceable spinner
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------rear cone (Ref. TASK 7221-00-400-006). D. Missing self-locking nuts
Not serviceable
Replace nuts (Ref. TASK 72-21-00-300-001) or install a new or serviceable spinner rear cone (Ref. TASK 72-21-00400-006).
E. Self-locking nuts with loss of self-locking quality
Not serviceable if running torque is less than to 4 lbf.in (0.04 m.daN)
Replace nuts (Ref. TASK 72-21-00-300-001) or install a new or serviceable spinner rear cone (Ref. TASK 72-21-00400-006).
F. Self-locking nuts with axial looseness
Not more than 0.008 in. (0.2 mm)
Crimp again (no crack permitted) or replace nuts (Ref. TASK 72-21-00-300001)
G. Self-locking nuts with lateral looseness
Not more than 0.008 in. (0.2 mm)
Replace nuts (Ref. TASK 72-21-00-300-001) or install a new or serviceable spinner rear cone (Ref. TASK 72-21-00400-006).
H. Oil wetting at inner of spinner cone or fan disk or forward fan shaft
None permitted
Refer to limit extensions (Ref. TASK 72-00-00-200025) or (Ref. TASK 72-0000-200-025). Replace O-rings on the LPT shaft plug (Ref. TASK 72-55-00960-002).
J. Seal ring tears
Maximum cumulated length 0.4 in. (10 mm)
Refer to limit extensions (Ref. TASK 72-00-00-200025) or (Ref. TASK 72-0000-200-025). Install a new or serviceable spinner
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------rear cone (Ref. TASK 7221-00-400-006). NOTE : Whenever serviceable limits for the following are exceeded, refer ____ to the over-serviceable limit extension if necessary (Ref. TASK 72-00-00-200-025) or (Ref. TASK 72-00-00-200-025) . 5. Close-up ________ Subtask 72-21-00-420-076 A. Install the Spinner Cone. (1) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (2) Install the spinner front cone (Ref. TASK 72-21-00-400-005). Subtask 72-21-00-869-073 B. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-072 C. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B TASK 72-21-00-290-003 Borescope Inspection of the Booster Rotor Blades, Stages 2,3,4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1320 856A1322
warning notice access platform 1 m (3 ft. 3 in.) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-21-00-991-307 72-21-00-991-308 72-21-00-991-309 72-21-00-991-310 72-21-00-991-313
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603 Fig. 604 Fig. 605
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-941-079 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-21-00-010-059 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-21-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-21-00-010-060 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-21-00-991-307, 602/TASK 72-21-00-991-308, 603/TASK 72-21-00-991-309, 604/TASK 72-21-00-991-310, 605/TASK 72-21-00-991-313) Subtask 72-21-00-290-053 A. Borescope Inspection Methods (1) Inspection of booster rotor blades through the borescope ports SO3 and SO5 and booster inlet. (a) There are 2 borescope ports (SO3 and SO5) located (approximately) at the 3.30 oclock position at the periphery of the booster section and almost radially in line with the stages 3 and 4 of the booster stator. Through these ports, you can see the leading and trailing edges of the booster stage 3, 4 and 5 rotor blades. Through the booster inlet, you can get a borescope view of the booster rotor blades, stage 2. (b) To do the inspection of the booster stages 2, 3, 4 and 5 rotor blades: 1 _
Use BORESCOPE-KIT (856A1320P04/P05) (field of view 60 deg., angle of vision 90 deg.) with a long right angle extension.
2 _
Use BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08) NOTE : It is necessary to index and turn the fan rotor. You ____ can turn the fan and booster rotor assembly by hand from the engine inlet.
Subtask 72-21-00-480-060 B. Installation of the borescope. CAUTION : MAKE SURE THAT THE INPUT VOLTAGE OF THE BORESCOPE LIGHT SOURCE _______ SET CORRESPONDS TO THAT OF THE POWER SUPPLY. CAUTION : MAKE SURE THAT : _______ THE ON-OFF SWITCH IS IN THE OFF POSITION. THE LIGHT INTENSITY CONTROL IS SET TO THE MINIMUM BEFORE YOU CONNECT THE BOROSCOPE LIGHT-SOURCE SET TO THE POWER SUPPLY. MAKE SURE THAT THE LIGHT SOURCE AND THE POWER SUPPLY ARE CORRECTLY GROUNDED.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B
Booster Borescope Ports Figure 601/TASK 72-21-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B
Borescope Inspection of the Stage 2 Booster Blades Figure 602/TASK 72-21-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B
Borescope Inspection of the Stage 3 and 4 Booster Blades Figure 603/TASK 72-21-00-991-309 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B
R
Borescope Inspection of the Stage 5 Booster Blades Figure 604/TASK 72-21-00-991-310
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/09
C F M 56-5B
Booster Rotor Blades Damage Inspection (All stages) Figure 605/TASK 72-21-00-991-313 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B (1) Connect the BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08) to a grounded power supply. (a) Connect the fiber light cable to the BORESCOPE-KIT (856A1320P04/P05) and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). (b) Turn the light source on. Engage the borescope and the long right-angle extension, and set it as necessary for inspection. Subtask 72-21-00-290-054 C. Borescope Inspection of the booster blades. WARNING : USE CARE TO AVOID PERSONAL INJURY WHEN YOU MANUALLY TURN THE _______ FAN ROTOR. ASSURE SAFE FOOTING.USE HEAVY PROTECTIVE GLOVES NOTE : Any amount of erosion/flaking of abradable lining material on the ____ outer shroud is permitted on booster vane stages 3,4 & 5. (1) Do an borescope inspection of the booster blades while you turn the fan rotor clockwise (aft looking forward) to complete the procedure. ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Booster rotor blades (all stages) for: A. Missing piece on tip corner
Axial or radial depth 0.25 in. (6.35 mm) max.
B. Cracks
Not serviceable
C. Wear or local deformation (blade tip corner on leading and/or trailing edges
Axial depth 0.5 in. (12.7 mm) and 0.8 in. (20.32 mm) radial max.
D. Nicks, dents on concave and/or convex sides located in area E
No limited quantity if not deeper than 0.01 in. (0.25 mm)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------E. Nicks, dents on No limited quantity if concave and/or not deeper than 0.04 in. convex sides not (1.02 mm) located in area E F. Nicks, dents, on leading and/or mex trailing edges
Axial depth 0.02 in. (0.5 mm) max.
NOTE : If any damage is found, do a borescope inspection of all booster ____ downstream stages and compressor. G. Distorted leading and/or trailing edges not located in area E
Circumferential displacement 0.2 in. (5 mm) maximum NOTE : Whenever ____ serviceable limits for the following are exceeded, refer to the over-serviceable limit extension if necessary (Ref. TASK 72-0000-200-025).
(2) When the inspection is completed, turn the switch off. Leave the main light source blower on for a while to cool the lamp and the housing.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-21-00-410-061 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-21-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-21-00-410-062 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/08
C F M 56-5B TASK 72-21-00-210-009 Inspect Fan Rotor Blades Installed on the Fan Disk 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice 1 ACCESS PLATFORM 1M(3 FT)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 72-00-00-200-025 72-21-00-000-007 72-21-00-300-028 72-21-00-300-029 72-21-00-320-003 72-21-00-400-007 72-23-00-210-003 72-21-00-991-314 72-21-00-991-315
Fluorescent-Penetrant Inspection-Portable-Water Washable Over-Serviceable-Limit Extensions Removal of the Fan Rotor Blades Replacement of Fan Rotor Blades in Pairs Replacement of Individual Fan Blades Blending of Fan Rotor Blades Installation of the Fan Rotor Blades Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material Fig. 606 Fig. 607
3. __________ Job Set-up Subtask 72-21-00-941-087 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (c) Put the ACCESS PLATFORM 1M(3 FT) in position. 4. Procedure _________ (Ref. Fig. 606/TASK 72-21-00-991-314, 607/TASK 72-21-00-991-315) Subtask 72-21-00-210-059 A. Inspection of the fan blades (in situ, installed on the fan disk) NOTE : If pairs of fan blades are not available as spare for replacement ____ (Ref. TASK 72-21-00-300-028), you can replace one blade individually (Ref. TASK 72-21-00-300-029), when the difference between the moment weight of the blade removed and its opposite is not more than 800 cm.g (315 in.g). However, you must do the inspections and corrections given in the replacement procedure with the conditions of the referenced procedure, thus, to make sure the engine vibration is not more than the limits. This also optimizes the operation of the engine. ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fan rotor blades for:
Not serviceable.
Replace pair of matched
A. Cracks or Tears.
blades (Ref. TASK 72-21-
(1) Operational cracks. (2) FOD caused cracks or tears.
00-300-028). Not serviceable
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-21-00 CES
Page 619 May 01/09
C F M 56-5B
Fan Rotor Blades - Blend Limits Figure 606/TASK 72-21-00-991-314- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/08
C F M 56-5B
Fan Rotor Blades - Blend Limits Figure 606/TASK 72-21-00-991-314- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 621 Nov 01/08
C F M 56-5B
Fan Rotor Blades - Blend Limits Figure 606/TASK 72-21-00-991-314- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-21-00 CES
Page 623 Nov 01/02
C F M 56-5B
Fan Rotor Blades - Local Distortions Figure 607/TASK 72-21-00-991-315- 14 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 624 Nov 01/08
C F M 56-5B
Fan Rotor Blades - Local Distortions Figure 607/TASK 72-21-00-991-315- 24 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 625 Nov 01/08
C F M 56-5B
Fan Rotor Blades - Local Distortions Figure 607/TASK 72-21-00-991-315- 34 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 626 Nov 01/08
C F M 56-5B
Fan Rotor Blades - Local Distortions Figure 607/TASK 72-21-00-991-315- 44 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------(Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity. B. Nicks, dents and scratches on contour surfaces of root area, and full airfoil out of midspan shroud
No limited quantity, if not deeper than 0.003 in.(0.08 mm) after removal of high metal.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007) or blend the defects if damage is within the blending limit of figure (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
C. Nicks, dents and scratches on leading edge of root area, Area A.
No limited quantity, if not deeper than 0.006 in.(0.15 mm)
Do blending procedure (Ref. TASK 72-21-00-320003)
D. Nicks, dents and scratches on trailing edge, Area D
No limited quantity, if not deeper than 0.006 in. (0.15 mm).
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007) or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
critical area.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 628 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------E. Nicks, dents and No limited quantity, if Replace blade (Ref. TASK scratches on not deeper than 0.03 in. 72-21-00-000-007) and leading edge in (0.76 mm), with 0.40 in. (Ref. TASK 72-21-00-400Area B. (10.16 mm) max length 007) or blend the defectts for scratches after (Ref. TASK 72-21-00-320removal of high metal. 003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity. F. Localized distortion on leading and trailing edges of root area, Area A.
Not serviceable.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007).
G. Leading and trailing edges distortion in Areas B and D (out of root area trailing edge).
Two areas may be distorted up to 0.34 in. (8.64 mm) out of contour provided there are no sharp corners and the minimum length L is six times the depth of the distortion.
Do a spot fluorescent-penetrant inspection (Ref. TASK 7051-00-230-002).
H. Blade tip (Area C) for:
Tip curl must not extend more than dimension
Replace pair of blades if not in the limits
(1) Leading edge tip curl
X1=0.5 in. (13 mm) across the blade tip and not more than dimension X=0.5 in. (13 mm), along the leading edge. Maximum deflection from original contour is dimension Y=0.25 in. (6.35 mm).
(Ref. TASK 72-21-00-300028) No continued in-service extension is permitted.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 629 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A maximum of 6 blades can have tip curl up to dimension X1=1.3 in. (33 mm) across the blade tip and dimension X=2 in. (51 mm) along the leading edge with maximum deflection from original contour dimension Y=0.6 in. (15 mm). Not more than 3 blades to these increased limits can be adjacent. In all cases, deflection tip angle must not be more than 60 degrees from original airfoil. (2) Trailing edge tip curl.
Tip curl must not extend more than dimension Z1=0.5 in. (13 mm) across the blade tip and not more than dimension Z=0.5 in. (13 mm) along the trailing edge, with maximum deflection from original contour dimension Y1=0.25 in. (6.35 mm). A maximum of 5 blades can have tip curl up to dimension Z1=1 in. (25.4 mm) across the blade tip and up to dimension Z=1 in.(25.4mm) along the trailing edge with maximum deflection from original contour dimension Y1=0.3 in. (7.62 mm).
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028). No continued in-service extention is permitted.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 630 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------No more than 3 blades to these increased limits can be adjacent. (3) Nicks and dents.
No limited quantity if not deeper than 0.04 in. (1.02 mm) and not longer than 0.25 in. (6.35 mm).
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007) or blend the defects (Ref. TASK 72-21-00-320003) if damage is within limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
J. Nicks, dents and scratches on surface of blade platform (excluding fillet and recess area).
For scratches: no limited quantity, if not deeper than 0.02 in. (0.5 mm) and not longer than 0.40 in. (10.16 mm). For nicks and dents, no limit on diameter after removal of high metal.
Do blending procedure (Ref. TASK 72-21-00-320003).
K. Pits
No limited quantity if not deeper than 0.005 in. (0.13 mm). No limits as regards diameter or spacing.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
L. Wear due to shingling on midspan shroud.
Any amount up to 0.005 in. (0.13 mm) deep.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
M. High metal caused by shingling on midspan shroud.
Any amount after smoothing of high metal.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 631 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------N. Shingled midspan Not serviceable. Refer to over serviceable shrouds. limit extensions (Ref. TASK 72-00-00-200025). P. Fan blade(s) tip seizure in fan case abradable shroud
Not serviceable.
Release the blade(s) with hand force to move the seized blade(s) tip forward and circumferentially. Then, do an inspection of the blade(s) as told in this procedure and abradable shroud (Ref. TASK 72-23-00-210003) for serviceability. Make sure that there is free rotation of N1 rotor system.
Subtask 72-21-00-010-064 B. If necessary, remove the fan blades for full inspection (Ref. TASK 72-2100-000-007) 5. Close-up ________ Subtask 72-21-00-410-066 A. Close access. (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the warning notice(s). (3) Remove the access platform(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 632 May 01/09
C F M 56-5B TASK 72-21-00-210-006 Inspect Fan Rotor Blades Removed from the Fan Disk. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A5817
warning notice 1 ACCESS PLATFORM 1M(3 FT) 1 TOOL,CHECK-FAN BLADE SHANK
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 72-00-00-200-025 72-21-00-000-007 72-21-00-210-004 72-21-00-300-028 72-21-00-300-029 72-21-00-320-003 72-21-00-400-007 72-21-00-991-314 72-21-00-991-315
Fluorescent-Penetrant Inspection-Portable-Water Washable Over-Serviceable-Limit Extensions Removal of the Fan Rotor Blades Detailed Inspection and Relubrication of Fan Blade Dovetails, Midspan Shrouds, Retainers, Spacers, Dampers and Fan Disk Dovetail Slots Replacement of Fan Rotor Blades in Pairs Replacement of Individual Fan Blades Blending of Fan Rotor Blades Installation of the Fan Rotor Blades Fig. 606 Fig. 607
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 633 May 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-941-080 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (c) Put an ACCESS PLATFORM 1M(3 FT) in position. 4. Procedure _________ (Ref. Fig. 606/TASK 72-21-00-991-314, 607/TASK 72-21-00-991-315) Subtask 72-21-00-210-056 A. Full inspection of the fan blades (removed from fan disk) (Ref. Fig. 606/TASK 72-21-00-991-314, 607/TASK 72-21-00-991-315) CAUTION : DO NOT CLEAN TITANIUM PARTS WITH COMPOUNDS WHICH CONTAIN _______ HALOGEN. HALOGEN DECREASES THE STRENGTH OF TITANIUM. NOTE : The removal of the fan blades is necessary to do a full inspection ____ of those blades (Ref. TASK 72-21-00-000-007). NOTE : If pairs of fan blades are not available as spare for replacement ____ (Ref. TASK 72-21-00-300-028), you can replace one blade individually (Ref. TASK 72-21-00-300-029), when the difference between the moment weight of the blade removed and its opposite is not more than 800 cm.g (315 in.g). However, you must do the inspections and corrections given in the replacement procedure with the conditions of the referenced procedure, thus, to make sure the engine vibration is not more than the limits. This also optimizes the operation of the engine.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 634 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fan rotor blades for: A. Cracks or tears. (1) Operational cracks.
Not serviceable.
Replace pair of matched blades (Ref. TASK 72-2100-300-028).
(2) FOD caused cracks or tears.
Not serviceable.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
B. Nicks, dents and scratches on contour surfaces of root area, and full airfoil out of midspan shroud critical area.
No limited quantity if no deeper than 0.003 in. (0.08 mm) after removal of high metal.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
C. Nicks, dents and scratches on leading edge of root area, Area A.
No limited quantity if not deeper than 0.006 in. (0.15 mm).
Do blending procedure (Ref. TASK 72-21-00-320003).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 635 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------D. Nicks, dents and No limited quantity if Replace blade (Ref. TASK scratches on not deeper than 0.006 72-21-00-000-007) and trailing edge, in. (0.15 mm). (Ref. TASK 72-21-00-400Area D. 007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity. E. Nicks, dents and scratches on leading edge in Area B.
No limited quantity if not deeper than 0.03 in. (0.76 mm), with 0.40 in. (10.16 mm) max length for scratches after removal of high metal.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
F. Localized distortion on leading and trailing edges of root area, Area A.
Not serviceable.
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007).
G. Leading and trailing edges distortion in Areas B and D (out of root area trailing edge).
Two areas may be distorted up to 0.34 in. (8.64 mm) out of contour provided there are no sharp corners and the minimum length L is six
Do a spot fluorescent penetrant inspection (Ref. TASK 70-51-00-230002).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 636 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------times the depth of the distortion. H. Blade tip (Area C) for: (1) Leading edge tip curl.
(2) Trailing edge tip curl.
Tip curl must not extend more than dimension X1 = 0.5 in. (13 mm) across the blade tip and not more than dimension X = 0.5 in. (13 mm) along the leading edge, with maximum deflection from original contour dimension X1 = 0.25 in. (6.35 mm).
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028). No continued in-service extension is permitted.
A maximum of 6 blades can have tip curl up to dimension X1 = 1.3 in. (33 mm) across the blade tip and dimension X = 2 in. (51 mm) along the leading edge with maximum deflection from original contour dimension Y = 0.6 in. (15 mm). No more than 3 blades to these increased limits can be adjacent. In all cases, deflection tip angle must not be more than 60 degrees from original airfoil.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028). No continue in-service extension is permitted.
Tip curl must not extend more than dimension Z1 = 0.5 in. (13 mm) across the blade tip and not more than dimension Z = 0.5 in. (13 mm) along
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028). No continued in-service extension is permitted.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 637 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------the trailing edge, with maximum deflection from original contour dimension Y1= 0.25 in. (6.35 mm). A maximum of 5 blades can have tip curl up to dimension Z1 = 1 in. (25.4 mm) across the blade tip and up to dimension Z = 1 in. (25.4 mm) along the trailing edge with maximum deflection from original contour dimension Y1= 0.3 in. (7.62 mm). No more than 3 blades to these increased limits can be adjacent.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028). No continued in-service extension is permitted.
(3) Nicks and dents.
No limited quantity if not deeper than 0.03 in. (0.76 mm) and no longer than 0.25 in. (6.35 mm).
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
J. Nicks, dents and scratches on surface of blade platform (excluding fillet and recess area).
For scratches: no limited quantity,if not deeper than 0.02 in. (0.5 mm) and, not longer than 0.40 in. (10.16 mm).
Do blending procedure (Ref. TASK 72-21-00-320003).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 638 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------For nicks and dents, no limit on diameter after removal of high metal. K. Missing Molydag coating on dovetail pressure faces.
Missing Molydag coating is permitted on 100 percent of the surface if parent material is not damaged.
(1) Worn or missing Cu.Ni.In coating in the non-contact area (Area 1).
Any amount if parent material is not damaged.
(2) Worn or missing Cu.Ni.In coating in the contact area (Area 2) of the dovetail pressure face.
Flaking of Cu.Ni.In up to 10 percent is permitted if coating adherence is correct in adjacent areas and if there is no evidence of wear on base material.
See over serviceable limit extension (Ref. TASK 7200-00-200-025) and examine blades for serviceability. Make sure that MoS2 dry film lubricant is applied to disk slots, the blade roots (dovetails), the blade platforms and lateral surfaces of those platforms, and the midspan shroud mating surfaces before blade installation (Ref. TASK 72-21-00-210004).
Flaking of Cu.Ni.In over 10 percent and less than 50 percent is permitted if coating adherence is correct in adjacent areas and if there is no evidence of wear on base material.
See over serviceable limit extension (Ref. TASK 7200-00-200-025) and examine blades for serviceability. Make sure that MoS2 dry film lubricant is applied to disk slots, the blade roots (dovetails), the blade platforms and lateral surfaces of those
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 639 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------platforms, and the midspan shroud mating surfaces before blade installation (Ref. TASK 72-21-00-210004) . L. Missing coating on inner faces of platform.
Any amount.
M. Fretting on dovetail pressure faces.
Not serviceable.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
N. Nicks, dents and scratches in dovetail fillet radius.
Not serviceable.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
P. Pits.
No limited quantity if not deeper than 0.005 in. (0.13 mm). No limits as regards diameter or spacing.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
Q. Nicks, dents and scratches on midspan shroud.
No limited quantity if not deeper than 0.010 in. (0.25 mm). No limited length for scratches, and 0.5 in. (12.7 mm) diameter for dents. None permitted in midspan shroud critical
Replace blade (Ref. TASK 72-21-00-000-007) and (Ref. TASK 72-21-00-400007), or blend the defects (Ref. TASK 72-21-00-320003) if damage is within the blending limit of figure. (Ref. Fig. 606/TASK 72-2100-991-314) You must repair blended fan blades following ESM 72-21-01 Rep 01 at first shop visit opportunity.
area.
R. Missing hard coating from
Flaking of hard coating is permitted if coating
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 640 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------midspan shroud not adherence is correct in exceeding 10 adjacent areas. percent of the midspan shroud mating face. Missing hard coating from midspan shroud exceeding 10 percent but less than 20 percent of the midspan shroud mating face.
Flaking of hard coating is permitted if coating adherence is correct in adjacent areas.
Monitor every 1500 cycles. Remove and examine blades for serviceability (Ref. TASK 72-21-00-000007). Make sure that MoS2 dry film lubricant is applied to disk slots, the blade roots (dovetails), the blade platforms and lateral surfaces of those platforms, and the midspan shroud mating surfaces before blade installation (Ref. TASK 72-21-00-400007).
Missing hard coat from midspan shroud exceeding 20 percent of the midspan shroud mating face.
Not serviceable.
See over serviceable limit extensions (Ref. TASK 7200-00-200-025).
S. Wear due to shingling on midspan shroud.
Any amount up to 0.005 in. (0.13 mm) deep.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
T. High metal caused by shingling on midspan shroud.
Any amount after smoothing of high metal.
U. Fretting on:
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 641 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------WARNING : YOU MUST _______ CLEAN THE FAN BLADE SHANKS WITH ISOPROPY ALCOHOL (MATERIA No. CP1041) BEFORE YOU DO THE INSPECTI NOTE : It is ____ necessary to do the wear depth measurement on all fan blade shanks with the tool TOOL,CHECKFAN BLADE SHANK. (1) Aft side of shank.
No limit if not deeper than 0.003 in. (0.08 mm).
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
(2) Lateral sides of shank
No limit if not deeper than 0.012 in. (0.30 mm) (concave side) and 0.008 in. (0.20 mm) (convex side) on the area referenced by X for length and Y for width.
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 642 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------(3) Forward face No limit if not deeper Replace pair of blades if of dovetail. than 0.003 in. (0.08 not in the limits mm). (Ref. TASK 72-21-00-300028). (4) Slide edges of platform.
No limit if not deeper than 0.013 in. (0.33 mm).
Replace pair of blades if not in the limits (Ref. TASK 72-21-00-300028).
V. Shingled midspan shrouds.
Not serviceable.
See over serviceable limit extensions (Ref. TASK 7200-00-200-025).
W. Fan blade(s) tip seizure in fan case abradable shroud.
Not serviceable.
Release the blade(s) with hand force to move the seized blade(s) tip forward and circumferentially. Then, do an inspection of the blade(s) and abradable shroud for serviceability. Make sure that there is free N1 rotation.
5. Close-up ________ Subtask 72-21-00-942-075 A. Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the warning notice(s). (3) Remove the access platform(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 643 May 01/09
C F M 56-5B TASK 72-21-00-210-007 Inspection/Check of the Stage 1 Booster Vane, Fan Disk, Fan Blades Spacers and Booster Spool. 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R
72-00-00-200-025 72-21-00-000-007 72-21-00-000-008 72-21-00-320-004 72-21-00-400-007 72-21-00-400-008 72-21-00-991-317 72-21-00-991-318 72-21-00-991-319 72-21-00-991-336
Over-Serviceable-Limit Extensions Removal of the Fan Rotor Blades Removal of the Stage 1 Booster Vane Assembly Blending of the Stage 1 Booster Vane Assembly Installation of the Fan Rotor Blades Installation of the Stage 1 Booster Vane Assembly Fig. 608 Fig. 609 Fig. 610 Fig. 611
3. __________ Job Set-up Subtask 72-21-00-941-081 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 644 Aug 01/09
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-21-00-020-073 B. Remove the fan blades (Ref. TASK 72-21-00-000-007). 4. Procedure _________ (Ref. Fig. 608/TASK 72-21-00-991-317, 609/TASK 72-21-00-991-318, 610/TASK 72-21-00-991-319) Subtask 72-21-00-210-057 A. Do this visual inspection: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Stage 1 booster vanes for: (Ref. Fig. 610/TASK 72-21-00-991-319) A. Piece missing:
Maximum number 20 blades up to 0.25 in. (6.5 mm) axial, 0.73 in. (18.5 mm) radial on all airfoil surfaces, except top/bottom 0.4 in. (10 mm).
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
B. Broken vane:
Not serviceable
Replace stage 1 booster vane (Ref. TASK 72-21-00000-008) and (Ref. TASK 72-21-00-400-008)
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 645 May 01/09
C F M 56-5B
Inspection of Fan Disk Figure 608/TASK 72-21-00-991-317 EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, R CES
Page 646 May 01/09
C F M 56-5B
Fan Blades Spacer Figure 609/TASK 72-21-00-991-318 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 647 May 01/09
C F M 56-5B
Stage 1 Booster Vane Damage Limits Figure 610/TASK 72-21-00-991-319- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 648 Nov 01/08
C F M 56-5B
Stage 1 Booster Vane Damage Limits Figure 610/TASK 72-21-00-991-319- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 649 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Disengagement from Not serviceable Replace stage 1 booster inner shroud: vane (Ref. TASK 72-21-00000-008) and (Ref. TASK 72-21-00-400-008) In area C, any number, less than 0.25 in. (6.5 mm) radial less than 0.08 in. (2 mm) axial.
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
E. Distortion of trailing edge and leading edge:
Any number, if the length L is not more than 0.709 in. (18 mm) and the maximum dimension X along the chord width is not more than 0.256 in. (6.5 mm)
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
F. Nicks, dents, scratches for areas A and B:
Any number, less than 0.09 in. (2.29 mm) in diameter protrusion.
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
G. Nicks, dents, scratches for area C:
Any number, less than 0.197 in. (5 mm) in diameter protrusion acceptable, not through
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
H. Nicks, dents, scratches on leading edge and trailing edge
Maximum axial length less than 0.08 in. (2 mm) in diameter protrusion acceptable, not thru.
For L/E, repair the stage 1 booster vane (Ref. TASK 72-21-00-320-004) Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
J. Deposits and erosion:
Any amount.
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025)
K. Cracked inner shroud
Not serviceable.
Refer to maximum serviceable limits (Ref. TASK 72-00-00-200025).
R R R R R R
D. Cracks and tears:
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 650 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------L. Erosion of Any amount. abradable lining on outer shroud M. Flaking of abradable lining on outer shroud
Any number, maximum surface affected less than 52.70 sq.in (340 cm2) for CFM56-5B/P & CFM56-5B/2P engines. Any number, maximum surface affected less than 15.50 sq.in (100 cm2) for CFM56-5B engine.
2. Fan disk for: (Ref. Fig. 608/TASK 72-21-00-991-317) A. Cracks
Not serviceable.
B. Wear on dovetail slot pressure faces.
No limit, if less than 50 percent of area is damaged. If the maximum affected surface, even only on one side of one slot, is greater than or equal to 50%, any amount if less than 0.152 mm (0.0059 in.) deep.
C. Nicks and scratches.
No limited quantity, if not deeper than 0.01 in. (0.25 mm) after removal of high metal. None permitted within 0.5 in. (12.7 mm) of dovetail slots disk bore and aft surface of web.
See limit extensions (Ref. TASK 72-00-00-200025)
3. Fan blade spacer for: (Ref. Fig. 609/TASK 72-21-00-991-318)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 651 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Cracks Not serviceable. Replace blade spacer B. Fretting
No limit, if the damage is not more than 0.005 in. (0.125 mm) deep.
Replace blade spacer
C. Corrosion, pitting
No limit for the damage less than 0.0098 in. (0.25 mm) deep, if the surface protection is not damaged.
Replace blade spacer
D. Damaged Surface protection
No limit for the damage less than 20 percent of total surface if parent material is found without corrosion pitting in the damaged area.
Replace blade spacer
E. Scratches
No limit for the damage 0.005 in. (0,125 mm) deep maximum after the removal of high metal.
Replace blade spacer
4. Booster spool for: (Ref. Fig. 611/TASK 72-21-00-991-336) A. Wear on front flange
No limit if not deeper than 0.001 in. (0.0254 mm) for wear due to contact with the rear surface of the fan blade shank.
B. Dents, nicks and scratches on front surface of seal tooth
Any amount if less than 0.003 in. (0.08 mm) deep.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 652 Nov 01/08
C F M 56-5B
Booster Spool Figure 611/TASK 72-21-00-991-336 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 653 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Plugs on surface A A maximum of 8 plug See limit extensions missing is permitted. (Ref. TASK 72-00-00-200025) 5. Close-up ________ Subtask 72-21-00-420-077 A. Install the fan blades (Ref. TASK 72-21-00-400-007). Subtask 72-21-00-869-075 B. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-073 C. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 654 Nov 01/08
C F M 56-5B TASK 72-21-00-210-004 Detailed Inspection and Relubrication of Fan Blade Dovetails, Midspan Shrouds, Retainers, Spacers, Dampers and Fan Disk Dovetail Slots 1. __________________ Reason for the Job Refer to the MPD TASK: 722000-C2 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
soft bristle brush warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2104
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
Material No.
CP5062
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * molykote G rapid (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * MoS2 dry film lubricant (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 655 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-007 72-21-00-210-006 72-21-00-210-007 R
72-21-00-400-007 72-23-00-280-006 72-21-00-991-335
Removal of the Fan Rotor Blades Inspect Fan Rotor Blades Removed from the Fan Disk. Inspection/Check of the Stage 1 Booster Vane, Fan Disk, Fan Blades Spacers and Booster Spool. Installation of the Fan Rotor Blades Inspection of Mid Acoustical Panels Fig. 612
3. __________ Job Set-up Subtask 72-21-00-941-089 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-21-00-020-079 B. Remove the fan blades (Ref. TASK 72-21-00-000-007). Subtask 72-21-00-110-056 C. CLean the fan blade dovetails. WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY SHOULD _______ BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING.
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 656 May 01/09
C F M 56-5B (1) Clean the fan blade dovetails and midspan shrouds, the fan blade spacers and the fan disk dovetail slots with isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656). Use a soft bristle brush if necessary, to remove dirt build-ups. 4. Procedure _________ (Ref. Fig. 612/TASK 72-21-00-991-335) Subtask 72-21-00-210-061 A. Do an inspection/check of the items which follow: (1) Fan blade airfoils, midspan shrouds and dovetails (Ref. TASK 72-2100-210-006). (2) Fan blade spacers and fan dovetails slots (Ref. TASK 72-21-00-210007). R
Subtask 72-21-00-210-062
R R
B. Do a tap test inspection for the mid acoustical panel delamination (Ref. TASK 72-23-00-280-006) 5. Close-up ________ Subtask 72-21-00-640-052 A. Apply MoS2 dry film lubricant (Material No. CP5062) or molykote G rapid (Material No. CP2104): - the fan disk dovetail slots, - the blade spacers, - the blade dovetails, - the blade midspan shrouds, before the re-installion of the blades. Lubricant should be applied liberally to all dovetail and slot pressure faces. Brush application is preferred. Allow the lubricant to dry to a dull opaque finish before installation of blades in disk slots. Subtask 72-21-00-420-085 B. Install fan blades (Ref. TASK 72-21-00-400-007).
EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 657 May 01/09
C F M 56-5B
Fan Blade, Blade Spacer and Disk Areas to Be Inspected after Cleaning for Removal of Lubricant from Pressure Faces Figure 612/TASK 72-21-00-991-335 R EFF : 001-049, 051-099, 101-149, 151-199, Page 658 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-21-00
C F M 56-5B Subtask 72-21-00-942-080 C. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 659 Nov 01/08
C F M 56-5B FAN AND BOOSTER ASSEMBLY - REPAIRS __________________________________ TASK 72-21-00-300-001 Replacement of the Crimped Self-Locking Nuts on the Spinner Rear Cone 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-400-005 72-21-00-400-006 SPM 704251350018
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Installation of the Spinner Front Cone Installation of the Spinner Rear Cone
3. __________ Job Set-up Subtask 72-21-00-941-071 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put an access platform in position. 4. Procedure _________ Subtask 72-21-00-020-067 A. Removal of the defective cimpred Nut(s). (1) Remove the spinner front cone (Ref. TASK 72-21-00-000-005) (2) If necessary, remove the spinner rear cone (Ref. TASK 72-21-00-000006) (3) Remove the defective crimped self-locking nut(s) from the spinner rear cone. (Ref. SPM 704251350018) Subtask 72-21-00-420-070 B. Crimping of the New Self-Locking Nuts. CAUTION : BE CAREFUL NOT TO CAUSE DAMAGE TO THE SURFACE PROTECTION AROUND _______ THE NUTS DURING NUT INSTALLATION. (1) Crimp the new self-locking nut(s). (Ref. SPM 704251350018) NOTE : No radial or end play is permitted in the installation of the ____ crimped self-locking nuts type B. (2) Install the spinner front cone. (Ref. TASK 72-21-00-400-005) (3) Install the spinner rear cone. (Ref. TASK 72-21-00-400-006)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-21-00-942-065 A. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B TASK 72-21-00-300-009 Correction of the Static Imbalance 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-009 71-00-00-750-001 72-21-00-991-324 72-21-00-991-328
Vibration Check Fan Trim Balance - 1 sensor 3 speed Fig. 801 Fig. 802
3. __________ Job Set-up Subtask 72-21-00-941-074 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). 1(2). (4) Put an access platform in position. 4. Procedure _________ (Ref. Fig. 801/TASK 72-21-00-991-324, 802/TASK 72-21-00-991-328) Subtask 72-21-00-750-053 A. Example of static imbalance correction on a spinner still equipped with balance screws other than P07. (Ref. Fig. 802/TASK 72-21-00-991-328) (1) Assume a balance weight Fc = 480 cm.g (189 in.g) orientated toward balance screw No. 24, is to be installed on the spinner which is still equipped with balance screws P02 in screw positions No. 18 and 19, and P05 in screw position No. 22. (2) Both screws P02 have a total moment weight F1 of 327 cm.g (129 in.g) acting along an axis between both screws. (3) Screw P05, installed in position No. 22, has a moment weight F2 of 375 cm.g (148 in.g) acting along an axis going through the screw location. (4) Vectorial sum corresponding to the 3 balance screws has a resultant F3 of approximately 656 cm.g (258 in.g). (5) Fc and F3 have a vectorial sum Ft of 1072 cm.g (422 in.g) acting along an axis close to balance screw No. 22. (6) Shows that 1 centered screw P04 and 2 lateral screws P05 provide a total moment weight of 1048 cm.g (413 in.g). (Ref. Fig. 801/TASK 72-21-00-991-324) (7) One balance screw P04 must be installed in position 22 and 2 lateral screws P04 must be installed in position 21 and 23, instead of screws previously installed. NOTE : As vectorial sum Ft defined in paragraph A(5) is greater than ____ 400 cm.g (157 in.g), static correction must be followed by a trim balance operation (Ref. TASK 71-00-00-750-001).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/08
C F M 56-5B
Various Balance Screw Arrangements For Given Moment Weights Figure 801/TASK 72-21-00-991-324- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/08
C F M 56-5B
Various Balance Screw Arrangements For Given Moment Weights Figure 801/TASK 72-21-00-991-324- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B
Static Imbalance Correction Figure 802/TASK 72-21-00-991-328 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Nov 01/08
C F M 56-5B NOTE : you can do a vibration check (Ref. TASK 71-00-00-710-009) when ____ you replace the fan blade(s) or when you install the same fan blade set again. The results of the the survey will show if it is necessary to do a fan trim balance or if the installation is correct (Ref. TASK 71-00-00-750-001). 5. Close-up ________ Subtask 72-21-00-869-069 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-068 B. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B TASK 72-21-00-320-003 Blending of Fan Rotor Blades 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific 856A2682G01 856A2949
magnifying glass power 10x to 20x soft file warning notice Light source - white 1 EDDY CURRENT INSTRUMENT 1 TEMPLATE, CHECKING - FAN BLADE LEADING EDGE
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2189
Material No.
CP2191
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * durite G422 (Ref. 70-30-00) * durite G421 (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2656
* mag-chem skysol (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 70-52-00-250-002 72-21-00-000-007 SPM 704111 SPM 704112 72-21-00-991-329 72-21-00-991-333 72-21-00-991-334
Fluorescent-Penetrant Inspection-Portable-Water Washable Eddy Current Inspection of the Fan Blade Leading Edge Removal of the Fan Rotor Blades Fig. 803 Fig. 804 Fig. 805
3. __________ Job Set-up Subtask 72-21-00-941-075 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 803/TASK 72-21-00-991-329, 804/TASK 72-21-00-991-333, 805/TASK 72-21-00-991-334) Subtask 72-21-00-020-069 A. Remove the damaged fan blades, if necessary (Ref. TASK 72-21-00-000-007). Subtask 72-21-00-220-054 B. Examine the fan blades. (1) Leading edge and trailing edge in the critical root area. (a) Find the critical root area. 1 _
The root area longitudinal dimension is 2.32 in. (60 mm).
(2) Mid span shroud area. (a) Find the critical area for the mid span shroud. 1 _
The critical areas are at 1.57 in. (40 mm) from the leading edge and at 1.18 in. (30 mm) on each side of the mid span shroud.
2 _
The critical areas are at 0.63 in. (16 mm) from the bottom of the mid span shroud and at 0.39 in. (10 mm) from the mid span shroud trailing edge.
(3) Leading edge and trailing edge repair in non critical areas. (a) The leading edge dimensions. 1 _
Taper the blend repair for area A and area B as follows: a _
In area A the blend repair is not more than 0.08 in. (2 mm).
b _
In area B the blend repair is not more than 0.339 in. (8.6 mm).
c _
When the distance (Dim. O) between two blend repairs is less than or equal to five times the depth of the smallest of these blends, tangentially blend out the bottom of the two blends.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B
Blend Repair of the Fan Rotor Blade Airfoil Figure 803/TASK 72-21-00-991-329 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/08
C F M 56-5B
Fan Blade Blending Repair limits Figure 804/TASK 72-21-00-991-333- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Nov 01/08
C F M 56-5B
Fan Blade Blending Repair limits Figure 804/TASK 72-21-00-991-333- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B
Fan Blade Blending Repair limits Figure 804/TASK 72-21-00-991-333- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B
Typical Examples of Unacceptable Leading Edges Contours Figure 805/TASK 72-21-00-991-334 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
C F M 56-5B d _
The total length of blend repairs permitted on the leading edge is equal to 2.76 in. (70 mm) per blade.
(b) The leading edge (area A and B) blend repairs are permitted with these limits. 1 _
Make sure that after you do the blending repair, the edge thickness is not less than the initial thickness.
2 _
The longitudinal direction of the repair for area A must be equal to or more than ten times the depth (Dim. P) of the damage.
3 _
The longitudinal direction of the repair for area B must be equal to or more than eight times the depth (Dim. P) of the damage.
4 _
The minimum radius R4 is equal to or more than fifteen times of depth (Dim. P) for area A.
5 _
The minimum radius R4 is equal to or more than ten times of depth (Dim. P) for area B.
6 _
The radius R3 for the blend repair on either side of the initial damage is a minimum radius blend of 0.2 in. (5 mm) and a maximum radius blend of 0.31 in. (8 mm).
7 _
If the distance (Dim. O1) between the blend repair and the blade tip is not more than two times the depth (Dim. P) of the repair, do the step: a _
Blend the bottom area of the repair tangentially from the depth of the area to the blade tip and blend the tip to the blending tip radius R1 with a minimum radius blend of 0.02 in. (0.5 mm) and a maximum radius blend of 0.67 in. (17 mm) at R1 minimum possible value.
(c) The trailing edge dimensions. 1 _
Taper the blend repair as follows: a _
The blend repair is not more than 0.059 in. (1.5 mm).
b _
When the distance (Dim. O) between two blend repairs is less than or equal to five times the depth of the smaller repair area, blend the two repairs together to a depth of a line which tangentially connects the bottom areas.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B c _
The total length of blend repairs permitted on the trailing edge is equal to 1.77 in. (45 mm) per blade.
(d) Trailing edge blend repairs are permitted with these limits. 1 _
Make sure that after you do the blending repair, the edge thickness is not less than the initial thickness.
2 _
The longitudinal direction of the repair must be equal to or more than ten times the depth (Dim. P) of the damage.
3 _
The minimum radius R4 is equal to or more than fifteen times the depth (Dim. P).
4 _
The radius R3 for the blend repair on either side of the initial damage is a minimum radius blend of 0.2 in. (5 mm) and a maximum radius blend of 0.31 in. (8 mm).
5 _
If the distance (Dim. O1) between the blend repair and the blade tip is not more than two times the depth (Dim. P) of the repair, do this step: a _
Blend the bottom area of the repair tangentially from the depth of the area to the blade tip and blend the tip to the blending tip radius R2 with a minimum radius blend of 0.02 in. (0.5 mm) and a maximum radius blend of 0.43 in. (11 mm) at R2 minimum possible value.
(4) Leading edge and trailing edge repair in critical areas. (a) The leading edge and trailing edge dimensions. 1 _
Taper the blend repair as follows: a _
The blend repair for the leading edge is not more than 0.04 in. (1 mm).
b _
The blend repair for the trailing edge is not more than 0.059 in. (1.5 mm).
(b) The leading edge and trailing edge blend repairs are permitted with these limits. 1 _
Taper the blend repair as follows: a _
The longitudinal direction of the repair must be equal to or more than twenty times the depth (Dim. P) of the damage.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 819 Nov 01/08
C F M 56-5B b _
The minimum radius R4 is equal to or more than thirty times the depth (Dim P).
(5) Blade tip repair (area C). (a) The blend repair does not extend more than 0.04 in. (1 mm). (b) The chordal direction of the repair must be equal to or more than eight times the depth (Dim. P) of the damage. (c) The minimum radius R4 is equal to or more than ten times the depth (Dim. P) of the damage. (d) The radius R3 for the blend repair on either side of the initial damage is a minimum radius blend of 0.2 in. (5 mm) and a maximum radius blend of 0.31 in. (8 mm). (e) The radius R1 blend repair between the leading edge and the tip is not less than 0.02 in. (0.5 mm) and not more than 0.67 in. (17 mm). (f) The radius R2 blend repair between the trailing edge and the tip is not less than 0.02 in. (0.5 mm) and not more than 0.43 in. (11 mm). (g) When the distance (Dim. O) between two blend repairs is less than or equal to five times the depth (Dim. P) of the repair, blend the two repairs together to a line which tangentially connects the bottom areas. (h) If the distance (Dim. O1) between the blend tip repair and the blade leading edge is less than two times the depth (Dim. P) of the repair, do this step: 1 _
Blend the bottom of the repair tangentially across to the blade leading edge and blend the tip to the blending tip radius R1 minimum possible value.
(i) If the distance (Dim. O1) between the blend tip repair and the blade trailing edge is less than two times the depth (Dim. P) of the repair, do this step: 1 _
Blend the bottom of the repair tangentially across to the blade trailing edge and blend the tip to the blending tip radius R2 minimum possible value.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 820 Nov 01/08
C F M 56-5B (j) The total chordal length of the blend repairs permitted on the blade tip is equal to 0.8 in. (20 mm) per blade. (6) Fan blade airfoil blend repairs. (a) The convex or concave blend repair. 1 _
Repairs are permitted on the surface with this limit: a _
2 _
Do not repair inside the blade critical areas.
If the distance (Dim. U) is not less than 0.079 in. (2 mm), do this step: a _
The convex or concave blend repair depth becomes not more than 0.024 in. (0.6 mm).
3 _
The concave or convex blend repair minimum radius R5 is not less than five times the depth (Dim. K).
4 _
The concave or convex blend repair area length is the sum of dimensions (Dim. S) and (Dim. T). a _
The total length of (Dim. S) and (Dim. T) for a blend repair is not more than 0.425 in. (10.8 mm).
b _
The chordal length (Dim. S) for a blade is six times the repair length (Dim. K).
c _
The maximun longitudinal length (Dim. T) is two times the length (Dim. S).
d _
The distance (Dim. O2) between two blend repairs must be more than the blend repair length (Dim. S) + (Dim. T) of the largest blend.
e _
The total length (Dim. S) + (Dim. T) of all blend repairs on the convex side must not be more than 1.3 in. (33 mm).
f _
The total length (Dim. S) + (Dim. T) of all blend repairs on the concave side must not be more than 1.3 in. (33 mm).
(7) Mid span shroud blend repair. (a) The distance (Dim. D) between two blend repairs must be more than five times the two defects largest blend.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 821 Nov 01/08
C F M 56-5B (b) The distance (Dim. V) for a blend repair is not more than 0.02 in. (0.5 mm). (c) The longitudinal direction (Dim. W) for a blend repair must be equal to or more than eight times the depth (Dim. V). (d) The minimum radius R6 is equal to or more than ten times the depth (Dim. V). (e) The radius R3 for the blend repair on either side of the damage is a minimum radius blend of 0.2 in. (5 mm) and a maximum radius blend of 0.31 in. (8 mm). (f) The minimum distance (Dim. M) is equal to or more than six times the depth (Dim. V). (g) The maximum distance (Dim. N) is two times the length (Dim. M). (h) The total length of (Dim. M) and (Dim. N) for a blend repair is not more than 0.35 in. (9 mm). (i) The distance (Dim. X) between two blend repairs, located either on the same or opposite sides, must be more than 0.177 in. (4.5 mm). (j) The total length (Dim. W) of all blend repairs must not be more than 0.16 in. (4 mm). Subtask 72-21-00-320-052 C. Do the blending operation as follows: CAUTION : EXCESSIVE HEAT CREATED DURING BLENDING CAN WEAKEN BLADE. TO _______ AVOID EXCESSIVE HEAT WHEN POWER GRINDING OR BLENDING TOOLS ARE USED, CHECK FOR HEAT BUILDING BY TOUCHING OCCASIONALLY WITH BARE HAND. IF BLADE BECOMES TOO HOT TO TOUCH, ALLOW MATERIAL TO COOL BEFORE CONTINUING REPAIR. NOTE : If five or more fan blades have been subject to this blending ____ repair, perform trim balance operation. It is recommended that location of repaired blades be recorded to perform trim balance operation.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 822 Nov 01/08
C F M 56-5B (1) Remove the surface damage from the blade airfoil per (Ref. SPM 704111) using a soft file or strips of durite G422 (Material No. CP2189) or durite G421 (Material No. CP2191) grade 150 or 180, used dry. The blended areas must make a smooth transition into the surrounding areas. NOTE : To prevent axial scratches, always do the blending in a ____ longitudinal direction, parallel with the length of the blade. (2) Complete the blending with strips of durite G422 (Material No. CP2189) grade 400 or 800, used dry. The surface finish (roughness) on blended areas must be as close as pratical to the original finish. (3) If a large or deep blend is required, a low speed power tool equipped with an appropriate titanium grinding tool may be used to shorten the time required to remove the metal per (Ref. SPM 704112) but you must complete with hand blending as told above. NOTE : Reworked contour must conform to original contour. ____ (Ref. Fig. 805/TASK 72-21-00-991-334) Subtask 72-21-00-110-054 D. Clean the blade: CAUTION : TITANIUM PARTS REQUIRE THE USE OF NON-HALOGENATED SOLVENTS. _______ (1) Clean blade using isopropyl alcohol (Material No. CP1041) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) . Subtask 72-21-00-230-052 E. Do an Inspection of Blended Area: (1) Do a fluorescent inspection (Ref. TASK 70-51-00-230-002) or an eddy current inspection with EDDY CURRENT INSTRUMENT (856A2682G01) (Ref. TASK 70-52-00-250-002) of blended area for cracks. No crack is permitted. NOTE : If you did the blending operation on the leading edge in area ____ B, you can delay the fluorescent-penetrant inspection by 10 flight cycles or 25 flight hours.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 823 Nov 01/08
C F M 56-5B In this case, you must do a visual inspection with a magnifying glass power 10x to 20x under Light source - white, to make sure sure that the damage is fully removed. (a) If necessary, repeat blending and inspection until no crack is detected. Refer paragraph A. to paragraph E. (1). (2) If you have a template, TEMPLATE, CHECKING - FAN BLADE LEADING EDGE (856A2949G01), use it after the blending of the leading edge as follows: (a) Put it on the leading edge of the blade on concave side so that the tabs touch the leading edge and the midspan shroud fillet radius with airfoil. 5. Close-up ________ Subtask 72-21-00-869-070 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-069 B. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 824 Nov 01/08
C F M 56-5B TASK 72-21-00-320-004 Blending of the Stage 1 Booster Vane Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific
soft file warning notice access platform 0.5 m (1 ft. 8 in.)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2189
Material No.
CP2191
* durite G422 (Ref. 70-30-00) * durite G421 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 72-21-00-000-007 72-21-00-400-007 72-21-00-991-330
Fluorescent-Penetrant Inspection-Portable-Water Washable Removal of the Fan Rotor Blades Installation of the Fan Rotor Blades Fig. 806
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 825 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-21-00-941-076 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). 1(2). (4) Put an access platform in position. 4. Procedure _________ (Ref. Fig. 806/TASK 72-21-00-991-330) Subtask 72-21-00-020-074 A. Remove the Fan rotor blades (Ref. TASK 72-21-00-000-007). Subtask 72-21-00-220-055 B. Check for dimensions and location of defects on edge and compare with repair limits. (Ref. Fig. 806/TASK 72-21-00-991-330) Subtask 72-21-00-320-053 C. Perform blending of defects using a soft file or strips of durite G422 (Material No. CP2189) or durite G421 (Material No. CP2191), used dry. (1) Remove a minimum of 0.01 in. (0.25 mm) of base metal in addition to depth of defect.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 826 Nov 01/08
C F M 56-5B
Blending of a Stage 1 Vane Assembly Leading Edge Figure 806/TASK 72-21-00-991-330 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 827 Nov 01/08
C F M 56-5B Subtask 72-21-00-230-053 D. Fluorescent penetrant inspect reworked area (Ref. TASK 70-51-00-230-002). No crack is allowed. 5. Close-up ________ Subtask 72-21-00-420-078 A. Install the fan rotor blades (Ref. TASK 72-21-00-400-007). Subtask 72-21-00-869-071 B. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-070 C. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 828 Nov 01/08
C F M 56-5B TASK 72-21-00-300-025 Angular Distribution for a Replacement of 3 to 18 Pairs of fan Rotor Blades Manual Method 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-991-331
Fig. 807
3. __________ Job Set-up Subtask 72-21-00-941-077 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 829 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put an access platform in position. 4. Procedure _________ (Ref. Fig. 807/TASK 72-21-00-991-331) Subtask 72-21-00-350-051 A. Manual Distribution Method. (1) Put the blades in decreasing order of moment weights. The moment weight of each blade is marked under the blade root. (2) Temporarily give numbers to the blades from 1 to 36, blade No. 1 is the haviest, blade No. 36 is the lightest. (3) Make the angular distribution of blades as shown in table of referenced figure. (Ref. Fig. 807/TASK 72-21-00-991-331) (4) Calculate the resulting (static) moment of the imbalance of the blades. (5) Decrease the calculated resultant to the lowest possible amount. To do this, change the location of the blades as necessary. NOTE : The moment weight difference between 2 blades 180-degree apart ____ must be kept within 200 g.cm. The resultant moment of imbalance must be less than 80 g.cm. 5. Close-up ________ Subtask 72-21-00-869-072 A. Make sure that the work area is clean and clear of tool(s) and other items. Subtask 72-21-00-942-071 B. Close Access (1) Remove the access platform(s). (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 830 Nov 01/08
C F M 56-5B
Angular Distribution and Installation of Blades on Fan Disk Figure 807/TASK 72-21-00-991-331 R EFF : 001-049, 051-099, 101-149, 151-199, 72-21-00 201-249, 251-299, 301-399, 401-499, CES
Page 831 Nov 01/08
C F M 56-5B NO.1 AND NO.2 BEARING SUPPORT ASSEMBLY - DESCRIPTION AND OPERATION __________________________________________________________________ 1. _______ General (Ref. Fig. 001) A. No. 1 and no. 2 bearing support module (1) The No. 1 and No. 2 bearing support module is bolted to the fan frame front face and supports both the fan and booster rotor assemblies. (2) The bearing support consists of the following major parts : (a) No. 1 bearing support. (b) No. 1 ball bearing. (c) No. 2 bearing support. (d) No. 2 roller bearing. (e) Oil manifold assembly. (f) External piping. (g) Fan shaft. (h) Forward stationary air/oil seal. 2. ___________ Description (Ref. Fig. 002, 003, 004, 005) A. No. 1 Bearing Support (Ref. Fig. 002, 003) The No. 1 bearing support is a titanium weldment. The rear outer flange of the support is bolted to the fan frame. The front flange of the support carries the No. 1 ball bearing housing. The rear inner flange carries the No. 2 bearing support. The outer casing is provided with a flange onto which is attached the No. 1 bearing stationary air/oil seal. The bottom rear of the casing has an orifice providing for oil draining through the fan frame hub. The forward casing has holes for oil and air venting into the No. 1 bearing air/oil seal and from there, to the front engine sump via a vent tube.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
No.1 and No.2 Bearing Support Module Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
No.1 and No.2 Bearing Support and Oil Manifold Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
No.1 Bearing Support Assembly Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
No.2 Bearing Support Assembly Figure 004 R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B
No.1 and No.2 Bearing Support External Piping Figure 005 R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 6 Nov 01/08
C F M 56-5B B. No. 1 Ball Bearing (Ref. Fig. 002, 003) The No. 1 ball bearing is a thrust bearing which carries the axial loads generated by the low pressure rotor system. Its one-piece outer race is located in the bearing housing. Its inner race has 2 halves attached by a nut to the No. 1 bearing sleeve which is installed on the fan shaft. The bearing sleeve is provided with an oil baffle upstream of No. 1 bearing. The bearing sleeve has provisions for locking the No. 1 bearing, locating the oil baffle forward of the No. 1 bearing, and integral with the sleeve, the No. 1 bearing rotating air/oil seal. C. No. 2 Bearing Support (Ref. Fig. 002, 004) The No. 2 bearing support is a steel alloy assembly. Its front flange is bolted to the No. 1 bearing support. Its rear flange accommodates the No. 2 roller bearing outer race. Holes are provided in this support for internal pressure equalization purposes in the forward oil sump. It also has an integral sleeve, at the 4 oclock position, providing for N1 speed sensor installation. There are holes at the 9 oclock position for oil supply to the oil manifold assembly and for installing the No. 2 bearing oil nozzle. D. No. 2 Roller Bearing (Ref. Fig. 002, 004) The No. 2 roller bearing takes the radial loads from the fan and booster rotor. Its inner race is mounted on the fan shaft and the outer race is bolted to the No. 2 bearing support. The N1 speed sensor ring, mounted on the fan shaft, will take up the radial loads in case of No. 2 bearing failure and, in addition, acts as a pulse generating rotor for the N1 speed sensor. The rear rotating air/oil seal is mounted at the rear of the fan shaft and provides for sealing of the engine forward sump. E. Oil Manifold Assembly (Ref. Fig. 001, 002) The oil manifold is installed inside of the No. 1 bearing support. It has one tube assembly which supplies oil to the dual oil nozzle at the No. 1 bearing and another tube assembly which supplies oil to the single oil nozzle at the No. 2 bearing. The manifold is connected to the oil supply line of fan frame through an oil coupling connection located at the 9 oclock position of the bearing support.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 7 Nov 01/08
C F M 56-5B F. External Piping (Ref. Fig. 002, 005) The external piping consists of 5 tubes mounted externally relative to the No. 1 bearing support. These tubes connect the forward stationary air/oil seal rear face to the fan frame front face. There are 3 air pressurization tubes for the No. 1 bearing dual stationary air/oil seal at the 3:30, 8:30, and 11:30 oclock positions. There is one oil scavenge tube at 6 oclock position from the forward oil sump and one oil drain tube at 5 oclock position, in case of failure of the dual stationary air/oil seal. G. Fan Shaft (Ref. Fig. 002) The fan shaft is a steel alloy forging. It is supported by the No. 1 and No. 2 bearings. Its front flange provides for attachment with the fan disk. Mechanical coupling with the low pressure turbine (LPT) shaft is provided by inner drive splines and an inner shoulder for axial retention. The shaft is fitted with a rotating air/oil separator, mounted between the No. 1 and No. 2 bearings, which removes oil particles from the forward sump air vented overboard. H. Forward Stationary Air/Oil Seal (Ref. Fig. 003) The stationary air/oil seal is a composite material assembly. It limits the engine forward sump at its front end, and is used to duct pressurization air to labyrinths provided on the No. 1 bearing sleeve. Space located between the seal inner and outer skin is divided into independent compartments for pressurization, drainage and oil scavenge.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-22-00 201-249, 251-299, 301-399, 401-499, CES
Page 8 Nov 01/08
C F M 56-5B FAN FRAME ASSEMBLY - DESCRIPTION AND OPERATION ______________________________________________ 1. _______ General (Ref. Fig. 001, 002, 003) The fan frame module provides front handling mounts and is the main forward support for mounting the engine to the aircraft. Its purpose is to support the fan, booster and high pressure compressor (HPC) rotors, and to provide ducting for primary and secondary airflows. The fan frame module consists of the following major assemblies: - Fan frame assembly. - Fan Inlet Case assembly. 2. _________ Fonctions The Fan Frame and Fan Inlet Case perform the following primary functions: A. Fan Frame. (1) An inlet airflow path to the core engine. (2) A support for loads of the fan stator, fan rotor and fan reverser. (3) Containment of accessory drive power take off gears (inlet gearbox) and radial drive shaft arrangement. (4) A variable bypass bleed valve system. (5) Housing for the oil pressure, scavenge, drain lines and venting/pressurisation/sealing system associated with the bearings and gears located in the engine forward sump. B. Fan Inlet Case. (1) Provides for attachment of the engine inlet cowl and the support and transmission of attachment loads from this point to the fan frame. (2) Provides fan blade containment. (3) Provides attachment points for acoustical panels, and fan OGV. (4) Provides an abradable lining for fan blade tips.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Fan Frame Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Fan Frame Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
Fan Frame Assembly Figure 003 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
Fan Frame Assembly Figure 003 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B 3. Description ___________ (Ref. Fig. 002, 003) A. Fan Frame Assembly The fan frame assembly is a fabricated structural weldment made of concentric rings connected by radial struts. It consists of the basic fan frame structure and the fan inlet case assembly. (1) The basic fan frame structure is made of steel alloy. It consists of a hub, mid box structure and outer casing interconnected through 4 thick and 8 thin radial struts. (a) Structural strength for the fan frame is obtained from the 12 struts. The struts are hollow and provide passage for the following equipment : 1 _
No. 1 bearing vibration sensor cable (No. 4 strut).
2 _
N1 speed sensor and drain cavity (No. 6 strut).
3 _
Transfer gearbox (TGB) radial drive shaft and scavenge tube (No. 7 strut).
4 _
Forward sump oil supply tube (No. 10 strut).
(b) The hub front face supports the No. 1 and No. 2 bearing support. The rear face supports, from front to rear, the IGB and No. 3 bearing module and the rear stationary air/oil seal together with its pressurization air supply ring. The hub outer surface, which is also the inner wall of the primary airflow annulus, has orifices for bleed air requirements. (c) The mid box structure is located radially between the primary and secondary airflows. It houses the 11 variable bleed valve (VBV) ballscrew actuators and the VBV master ballscrew actuator , and air scoops for the LPT active clearance control system (LPTACC). The front flange of the structure supports the rear outer flanges of the stage 5 booster vane assembly, and the fan OGV inner shroud. The structure rear flange supports the HPC forward case, the VBV hydraulic fuel gear motor and provides for engine mounting. (d) The outercasing makes up the outer wall of the secondary airflow. Located on the outer surface of the casing are the 2 ground handling mounts and the TGB mounting pad. The fan inlet case mounts to the outer casing front flange, and the fan discharge duct mounts to the outer casing rear face.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 6 Nov 01/08
C F M 56-5B (e) An adapter ring, with a V-groove, is bolted to the outer casing rear flange to adapt the outer cowl of the engine (fan) thrust reverser (Ref. 78-30-00). 4. Fan _______________________ Inlet Case Assembly (Ref. Fig. 001, 002) The fan inlet case assembly is composed of the 2 parts which follows: - The upstream fan case - The downstream fan case The upstream fan case is a structural weldment made of alloy steel. The outer rear flange is bolted to the downstream fan case outer front flange. The downstream fan case is made of aluminium. The outer rear flange is bolted to the outer front flange of the fan frame. The outer surface of the fan inlet case assembly has flanges and ribs to provide additional strength to the case during engine operation. It also has 2 hoisting points for engine ground handling purposes (2 and 10 oclock positions), 2 accessory gearbox (AGB) mounts and various other mounting provisions for engine equipment. The inner surface houses an abradable shroud located radially in line with the fan rotor blades, 6 fan forward acoustical panels, 6 fan mid acoustical panels, the fan OGV assembly and 12 aft acoustical panels. The engine air inlet cowl is attached to the front flange of the fan inlet case. The fan outlet guide vanes (OGV) are made of composite material. The fan OGV inner shroud rear flange is bolted to the fan frame. Its forward outer surface contains 35 apertures to allow passage of the vane inner platforms and two borescope inspection ports. The fan splitter fairing is attached to the forward end of the fan OGV inner shroud. The fan OGV assembly has 35 twin vanes (or vane doublets). The vane inner platform are axially retained by the inner face of the fan (OGV) inner shroud. The vane outer platforms are bolted to the fan inlet case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 7 Nov 01/08
C F M 56-5B FAN FRAME ASSEMBLY - REMOVAL/INSTALLATION _________________________________________ TASK 72-23-00-000-008 Removal of the Fan Outlet Guide Vane (OGV) Doublets 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-23-00-000-026 78-30-00-481-041 78-36-00-010-040 72-23-00-991-300
Opening of the Fan Cowl Doors Removal of the Aft Acoustical Panels Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Fig. 401
3. __________ Job Set-up Subtask 72-23-00-941-071 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-083 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-23-00-040-061 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-094 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 401/TASK 72-23-00-991-300) Subtask 72-23-00-020-059 A. Removal of the Fan Outlet Guide Vane (OGV) Doublets (Rearward) (1) Remove the aft acoustical panels (Ref. TASK 72-23-00-000-026) (2) Remove the sealant which covers the three bolts (20) and (30) in the outer platform recesses. If necessary only. (3) Remove the three bolts (20) and (30) which attach the OGV doublet (10) platform.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Nov 01/08
C F M 56-5B
Removal and Installation of the Fan Outlet Guide Vane Doublets Figure 401/TASK 72-23-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 403 Nov 01/08
C F M 56-5B (4) Lower the OGV doublet (10) inner platform down into the OGV inner shroud. (5) Move the OGV doublet (10) outer platform rearward at the necessary angle to disengage the inner platform from its recess. (6) Remove the OGV doublet (10). (7) Remove the sealant which remains on the acoustical panels.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 404 Nov 01/08
C F M 56-5B TASK 72-23-00-400-008 Installation of the Fan Outlet Guide Vane (OGV) Doublets 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2242
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * RTV 732 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-400-026 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Installation of the Aft Acoustical Panels Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 405 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------SPM 706612 72-23-00-991-300
Fig. 401
3. __________ Job Set-up Subtask 72-23-00-860-058 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-23-00-010-093 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-040-065 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 406 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 401/TASK 72-23-00-991-300) Subtask 72-23-00-420-059 A. Installation of the Fan Outlet Guide Vane (OGV) Doublets (Rearward) (1) Engage the OGV inner platform into the OGV inner shroud recess. (2) Push the OGV outer platform forward between the adjacent OGV doublets and up against the inner diameter of the fan case. (3) Apply a thin layer of graphite grease (Material No. CP2101) to the threads of the three bolts (20) and (30), and attach the OGV doublet with the 3 bolts. NOTE : You must install the longer bolt (20) to the aft end of the ____ OGV outer platform. (4) TORQUE the bolts to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). (5) Apply RTV 732 (Material No. CP2242) all around the OGV(s) outer(s) platform(s) recesses. (6) Fill the sealant per (Ref. SPM 706612) to smooth the fan duct outer wall. (7) Install the aft acoustical panels (Ref. TASK 72-23-00-400-026). 5. Close-up ________ Subtask 72-23-00-410-077 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 407 Nov 01/08
C F M 56-5B Subtask 72-23-00-440-058 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-087 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 408 Nov 01/08
C F M 56-5B TASK 72-23-00-000-009 Removal of the Forward Acoustical Panels of the Fan 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-991-301
Fig. 402
3. __________ Job Set-up Subtask 72-23-00-941-072 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 409 Nov 01/08
C F M 56-5B (4) Put a warning notice to tell persons not to start the engine 1(2). (5) Put an access platform in position at the front of the engine. 4. Procedure _________ (Ref. Fig. 402/TASK 72-23-00-991-301) Subtask 72-23-00-020-060 A. Remove the fan forward acoustical panels (70) as follows: CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO UNTORQUE AND LOOSEN ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. (1) Remove the screws (80) which attach the forward panel (70) located in fan case. NOTE : If one screw is found untorqued, it must be discarded and ____ replaced for re-installation. (2) Disengage and remove the panel (70) from the case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 410 Nov 01/08
C F M 56-5B
Fan Forward Acoustical Panel Figure 402/TASK 72-23-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 411 Nov 01/08
C F M 56-5B TASK 72-23-00-400-009 Installation of the Forward Acoustical Panels of the Fan 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-280-005 72-23-00-300-045 72-23-00-400-043 72-23-00-400-044
Inspection of Forward Acoustical Panels Replacement of the Riveted Self Locking Nuts for the Attachment of the Forward Acoustical Panels Installation of Acoustical Panels Attachment Screw/Nut Locking Installation of Acoustical Panels Attachment Screw Locking
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 412 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-860-061 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. 4. Procedure _________ Subtask 72-23-00-420-060 A. Install the fan forward acoustical panels as follows: CAUTION : MAKE SURE THAT THE PS12 INSTRUMENTATION NIPPLE WHICH COMES OUT _______ OF THE FAN INLET CASE IS CORRECTLY ENGAGED IN THE PANEL. CAUTION : COATING SCREWS IS MANDATORY. _______ (1) Apply a layer of graphite grease (Material No. CP2101) to the threads of all the screws that attach the acoustical panels and to the contact faces below the screw heads. (2) Do a visual inspection of the forward acoustical panel cup (Ref. TASK 72-23-00-280-005) (3) If panel cup is found pierced (Ref. TASK 72-23-00-400-044). (4) Install the panel assy on the forward case, and attach it with 6 screws (80). CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO TORQUE ALL ACOUSTICAL _______ PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 413 Nov 01/08
C F M 56-5B (5) Measure the self locking nut torque of each nut when you start to tighten the screw. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO TORQUE ALL ACOUSTICAL _______ PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : Whenever possible, start the torque with the screws in the ____ center of the acoustical panels. NOTE : Make sure that the screws are not damaged, replace them if ____ necessary. (a) If the self locking nut torque is less than 4.5 lbf.in (0.05 m.daN), (Ref. TASK 72-23-00-400-043). (b) If the self locking nut torque is more than 4.5 lbf.in (0.05 m.daN), but less than 31 lbf.in (0.35 m.daN), TORQUE the screws to between 84 and 93 lbf.in (0.94 and 1.05 m.daN). R R R
(c) If the self locking nut torque is more than 31 lbf.in (0.35 m.daN) replace the self locking nut (Ref. TASK 72-23-00-300-045). 5. Close-up ________ Subtask 72-23-00-410-090 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 414 Feb 01/09
C F M 56-5B TASK 72-23-00-000-025 Removal of the Mid Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-23-00-991-302
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Fig. 403
3. __________ Job Set-up Subtask 72-23-00-941-073 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 415 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-084 B. Get Access (1) Put an access platform in position at the front of the engine. (2) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (3) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (4) Temporarily mark each fan blade from 1 to 36. (5) Remove 3 consecutive fan blades (Ref. TASK 72-21-00-000-007). To compensate for imbalance caused by the removal of 3 blades, it is recommended to remove 3 blades 180 degrees opposed to those previously removed. 4. Procedure _________ (Ref. Fig. 403/TASK 72-23-00-991-302) Subtask 72-23-00-020-061 A. Remove the Mid Acoustical Panels as follows: CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO UNTORQUE AND LOOSEN ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. (1) Remove the short screws (100) and the long screws (101) which attach the mid acoustical panels (110). NOTE : If one screw is found untorqued, it must be discarded and ____ replaced for re-installation. (2) Disengage panels from case and remove.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 416 Nov 01/08
C F M 56-5B
Mid Acoustical Panel Figure 403/TASK 72-23-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 417 Nov 01/08
C F M 56-5B TASK 72-23-00-400-025 Installation of the Mid Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-23-00-280-006 72-23-00-400-043 72-23-00-400-044 ESM 722302300008 72-23-00-991-302
Removal of the Power Plant Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Inspection of Mid Acoustical Panels Installation of Acoustical Panels Attachment Screw/Nut Locking Installation of Acoustical Panels Attachment Screw Locking Fig. 403
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 418 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-860-062 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. 4. Procedure _________ (Ref. Fig. 403/TASK 72-23-00-991-302) Subtask 72-23-00-420-061 A. Install the Mid Acoustical Panels as follows: CAUTION : COATING SCREWS IS MANDATORY. _______ (1) Coat with graphite grease (Material No. CP2101) screw threads and contact faces under screw heads. (2) Do a visual inspection of the mid acoustical panel cup (Ref. TASK 7223-00-280-006). (3) If panel cup is found pierced (Ref. TASK 72-23-00-400-044). (4) Install the panel assy on the forward case, and attach it with 3 short screws (100) and 3 long screws (101). CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : The longest screws have to be re-installed at the aft end of ____ panel.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 419 Nov 01/08
C F M 56-5B (5) Measure the self locking nut torque of each nut when you start to tighten the screw. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO TORQUE ALL ACOUSTICAL _______ PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : Whenever possible, start to torque with the screws in the ____ center of the acoustical panels. NOTE : Make sure that the screws are not damaged, replace them if ____ necessary. (a) If the self locking nut torque is less than 4.5 lbf.in (0.05 m.daN), (Ref. TASK 72-23-00-400-043). (b) If the self locking nut torque is within 4.5 lbf.in (0.05 m.daN) and 31 lbf.in (0.35 m.daN), torque the screws to between 84 and 93 lbf.in (0.94 and 1.05 m.daN) (c) If the self locking nut torque is more than 31 lbf.in (0.35 m.daN) but less than 49 lbf.in (0.55 m.daN), torque the screws at the running torque value and add 44 lbf.in (0.5 m.daN). (d) If the self locking torque is more than 49 lbf.in (0.55 m.daN), remove the engine (Ref. TASK 71-00-00-000-042) and do the engine shop repair procedure to replace the self locking nut (Ref. ESM 722302300008). 5. Close-up ________ Subtask 72-23-00-410-078 A. Close Access (1) Install the fan rotor blades at the locations recorded at the removal (Ref. TASK 72-21-00-400-007). (2) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (3) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (4) Make sure that the work area is clean and clear of tool(s) and other items. (5) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 420 Nov 01/08
C F M 56-5B (6) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 421 Nov 01/08
C F M 56-5B TASK 72-23-00-000-026 Removal of the Aft Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 78-30-00-481-041 78-36-00-010-040 72-23-00-991-303
Opening of the Fan Cowl Doors Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Fig. 404
3. __________ Job Set-up Subtask 72-23-00-941-074 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 422 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-085 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-23-00-040-062 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-095 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 404/TASK 72-23-00-991-303) Subtask 72-23-00-020-062 A. Remove the Aft Acoustical Panels as follows (typical, any panel): CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO UNTORQUE AND LOOSEN ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 423 Nov 01/08
C F M 56-5B
Aft Acoustical Panel (Configuration 1 and Configuration 2) Figure 404/TASK 72-23-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 424 Nov 01/08
C F M 56-5B (1) Remove the screws (130) that attach the aft acoustical panel (140). NOTE : If one screw is found untorqued, it must be discarded and ____ replaced for re-installation. PRE SB 72-071 (Configuration One) (2) Disengage panel (140) from case and T/R adapter ring. Remove the panel (140) which comes with its two lateral bonded seals. POST SB 72-071 (Conguration Two) (3) Disengage panel (140) from case and T/R adapter ring. Remove the panel (140). This panel will come without its U-shaped seal (145). Let the seal (145) squeezed between the two struts and adjacent aft acoustical panels that frame the panel you remove. Remove the seal (145) and thus, the two adjacent panels, only if this seal is badly damaged.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 425 Nov 01/08
C F M 56-5B TASK 72-23-00-400-026 Installation of the Aft Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-13-00-010-040 71-13-00-410-040 72-23-00-210-004 72-23-00-280-007 72-23-00-400-043 72-23-00-400-044 78-30-00-081-041
Removal of the Power Plant Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Visual Inspection of the Fan Frame Assembly Inspection of Aft Acoustical Panels Installation of Acoustical Panels Attachment Screw/Nut Locking Installation of Acoustical Panels Attachment Screw Locking Make the Thrust Reverser Serviceable after Maintenance
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 426 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 ESM 722302300008 72-23-00-991-303
Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 404
3. __________ Job Set-up Subtask 72-23-00-860-059 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-23-00-010-099 B. Get Access (1) Make sure that the fan cowl doors are open (Ref. TASK 71-13-00-010040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Make sure that the thrust reverser doors are open (Ref. TASK 78-3600-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 427 Nov 01/08
C F M 56-5B Subtask 72-23-00-040-068 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041). 4. Procedure _________ (Ref. Fig. 404/TASK 72-23-00-991-303) Subtask 72-23-00-420-062 A. Install the Aft Acoustical Panels as follows (typical, any panel): CAUTION : COATING SCREWS IS MANDATORY. _______ NOTE : The 12 aft acoustical panels are attached both to the fan inlet ____ case and to the T/R adapter ring, at their aft end. (1) Apply a layer of graphite grease (Material No. CP2101) to the threads of all the screws that attach the acoustical panels and to contact faces below the screw heads. PRE SB 72-071 (2) Visually inspect the aft acoustical panel cup (Ref. TASK 72-23-00280-007). (3) If panel cup is found pierced (Ref. TASK 72-23-00-400-044). (4) Install the panel assy on the forward case, an attach it with seven screws (130). (5) Before the installation, do a visual inspection of the panel (140) (Ref. TASK 72-23-00-210-004). Make sure that the two lateral bonded seals are in position. Although it is not at this time mandatory to obey the inspection criterion related to these bonded seals, we recommended they are in position, in good condition and fully bonded to the panel. (6) Put the panel (140), with its two bonded seals, on the fan case and the T/R adapter ring. Attach it loosely with the seven screws (130). CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 428 Nov 01/08
C F M 56-5B NOTE : You must install the 3 longest screws (130) at the aft of the ____ panel. (7) Measure the self locking nut torque of each nut when you start to tighten the screw. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : Whenever possible, start to torque with the screws in the ____ center ot the acoustical panels. NOTE : Make sure that the screws are not damaged, replace them if ____ necessary. (a) If the self locking nut torque is less than 4.5 lbf.in (0.05 m.daN) (Ref. TASK 72-23-00-400-043). (b) If the self locking nut torque is within 4.5 lbf.in (0.05 m.daN) and 31 lbf (0.35 m.daN), TORQUE the screws to between 66 and 75 lbf.in (0.74 and 0.84 m.daN). (c) If the self locking nut torque is more than 31 lbf.in (0.35 m.daN) but less than 49 lbf.in (0.55 m.daN), TORQUE the screws at the running torque value and add 44 lbf.in (0.5 m.daN). (d) If the self locking torque is more than 49 lbf.in (0.55 m.daN), remove the engine (Ref. TASK 71-00-00-000-042) and do the engine shop repair procedure to replace the self locking nut (Ref. ESM 722302300008). END OF SB 72-071 POST SB 72-071 (8) Before the installation, do a visual inspection of the panel (140) (Ref. TASK 72-23-00-210-004). Make sure that the two U-shaped seals (145) that are in stand-by on the two (non-removed and adjacent) fan aft acoustical panels are in good condition. If not, remove the panel(s) which hold the damaged seal(s) and install a new seal. See note below. NOTE : Refer to the PPIPC (72-23-00) when it is necessary to replace ____ a seal (145). Because of the different strut sizes and clock positions, the seals (145) do not all have the same pre-formed shapes and can thus have different part numbers.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 429 Nov 01/08
C F M 56-5B (9) Put the panel (140) in its approximate position on the fan case and the T/R adapter ring. Engage one seal (145) first, against one of the panel edges, then engage the other seal (145) against the opposite panel edge. Make sure that the seals (145) are correctly compressed between the panel and the adjacent struts around the panel. NOTE : It is not easy to get access to some (panel) clock locations. ____ External aid will possibly be necessary to install the seal (145) correctly between the panel and the related struss. (10) Push and hold the panel (140) against the fan case and attach it loosely with the seven srews (130). CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : You must install the 3 longest screws (130) at the aft of the ____ panel. (11) Measure the self locking nut torque of each nut when you start to tighten the screw. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. NOTE : When possible, start the torque with the screws in the center ____ of the acoustical panels. NOTE : Make sure that the screws are not damaged, replace them if ____ necessary. (a) If the self locking nut torque is less than 4.5 lbf.in (0.05 m.daN) (Ref. TASK 72-23-00-400-043). (b) If the self locking nut torque is within 4.5 lbf.in (0.05 m.daN) and 31 lbf (0.35 m.daN), TORQUE the screws to between 66 and 75 lbf.in (0.74 and 0.84 m.daN) (c) If the self locking nut torque is more than 31 lbf.in (0.35 m.daN) but less than 49 lbf.in (0.55 m.daN), TORQUE the screws at the running torque value and add 44 lbf.in (0.5 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 430 Nov 01/08
C F M 56-5B (d) If the self locking torque is more than 49 lbf.in (0.55 m.daN), remove the engine (Ref. TASK 71-00-00-000-042) and do the engine shop repair procedure to replace the self locking nut (Ref. ESM 722302300008). END OF SB 72-071 5. Close-up ________ Subtask 72-23-00-410-079 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-059 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-088 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 431 Nov 01/08
C F M 56-5B TASK 72-23-00-000-027 Removal of the Fan Duct Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 78-30-00-481-041 78-36-00-010-040 72-23-00-991-305
Opening of the Fan Cowl Doors Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Fig. 405
3. __________ Job Set-up Subtask 72-23-00-941-075 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 432 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-086 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-23-00-040-063 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-096 D. Open the thrust reverser cowl doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 405/TASK 72-23-00-991-305) Subtask 72-23-00-020-063 A. Removal of the fan duct panels. CAUTION : DURING REMOVAL OF FAN DUCT PANELS, DO NOT FULLY REMOVE CAPTIVE _______ SCREWS FROM PANEL. THESE SCREWS ARE HELD IN PLACE BY A RETAINING BUSHING ON THE BACK SIDE OF THE PANELS WHICH MAY FALL INTO THE VBV CAVITY IF SCREWS ARE FULLY REMOVED. AFTER REMOVAL OF EACH PANEL, IT MUST BE VERIFIED THAT BUSHINGS ARE STILL WITH PANEL AND NOT IN VBV CAVITY.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 433 Nov 01/08
C F M 56-5B
Fan Duct Panel Figure 405/TASK 72-23-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 434 Nov 01/08
C F M 56-5B (1) Loosen the captive screws (150), and remove the panel (160). (2) Unscrew and remove the retaining bushings (170) from the screws (150). (3) Remove the washers (180) from the screws (150).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 435 Nov 01/08
C F M 56-5B TASK 72-23-00-400-027 Installation of the Fan Duct Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 436 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-23-00-991-305
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 405
3. __________ Job Set-up Subtask 72-23-00-860-060 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-23-00-010-100 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 437 Nov 01/08
C F M 56-5B (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-040-069 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041). 4. Procedure _________ (Ref. Fig. 405/TASK 72-23-00-991-305) Subtask 72-23-00-420-063 A. Installation of the fan duct panels. (1) Clean the fan frame cavity and the fan duct panels with acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or magchem skysol (Material No. CP2656) at the RTV contact area between the fan frame /fan duct panel. (2) Install the captive screw (150) the washers (180) and the retaining bushings (170) on the fan duct panel (160). (3) Apply a thin layer of graphite grease (Material No. CP2101) to the threads of the screws (150), and install the new panel (160). (4) Install the panel on the bleed valve cavity and attach it with captive screws. (5) TORQUE screws to between 85 and 95 lbf.in (0.96 and 1.07 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 438 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-080 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser door: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-060 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-089 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 439 Nov 01/08
C F M 56-5B TASK 72-23-00-000-028 Removal of the Splitter Fairing 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific 856A2663
rubber mat slide hammer warning notice access platform 1 m (3 ft. 3 in.) 1 ADAPTER, PULLER - SPLITTER FAIRING
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-23-00-991-306 72-23-00-991-307
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Fig. 406 Fig. 407
3. __________ Job Set-up Subtask 72-23-00-941-076 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 440 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put an access platform in position. Subtask 72-23-00-010-087 B. Removal of the Spinner Cone, the Spinner Rear Cone and the Fan Blades. (1) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (2) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (3) Remove the fan blades (Ref. TASK 72-21-00-000-007). 4. Procedure _________ (Ref. Fig. 406/TASK 72-23-00-991-306, 407/TASK 72-23-00-991-307) Subtask 72-23-00-020-064 A. Removal of the Splitter Fairing. CAUTION : INSTALL A RUBBER MAT IN THE FAN INLET CASE TO PREVENT DAMAGE TO _______ THE ACOUSTICAL PANELS. (1) Install a rubber mat in the fan inlet case. (2) Remove the countersunk head screws (20) which attach the splitter fairing (10) to the inner shroud of the fan outlet guide vane (OGV) assembly. (3) Pull out the splitter fairing (10) with a slide hammer (856A2663G01) attached to the ADAPTER, PULLER - SPLITTER FAIRING. (Ref. Fig. 407/TASK 72-23-00-991-307) alternatively positioned in each splitter fairing extraction slot. Remove the splitter fairing (10). (4) Remove the rubber mat from the fan inlet case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 441 Nov 01/08
C F M 56-5B
Splitter Fairing Figure 406/TASK 72-23-00-991-306 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 442 Nov 01/08
C F M 56-5B
Removal of the Splitter Fairing Figure 407/TASK 72-23-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 443 Nov 01/08
C F M 56-5B TASK 72-23-00-400-028 Installation of the Splitter Fairing 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No
specific specific specific specific specific
heat gun rubber mat warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 444 Feb 01/10
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-23-00-991-306
Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Fig. 406
3. __________ Job Set-up Subtask 72-23-00-860-063 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. 4. Procedure _________ (Ref. Fig. 406/TASK 72-23-00-991-306) Subtask 72-23-00-420-064 A. Installation of the splitter fairing CAUTION : INSTALL A RUBBER MAT IN THE FAN INLET CASE TO PREVENT DAMAGE TO _______ THE ACOUSTICAL PANELS. (1) Install a rubber mat in the fan inlet case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 445 Nov 01/08
C F M 56-5B (2) Clean the mating surfaces: WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL _______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. (a) Fully clean the mating surfaces of the splitter fairing front flange with acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99R (Material No. CP2584) or mag-chem skysol (Material No. CP2656). (3) Put the splitter fairing (10) on the inner shroud of the fan outlet guide vane (OGV) assembly and on the outer shroud of the stage 1 vane assembly. (4) Heat the front flange of the splitter fairing with a heat gun to approximately 140 deg.F (60 deg.C) until it can be fully engaged in the OGV inner shroud rabbet diameter. (5) Lubricate the threads of the countersunk head screws (20) with graphite grease (Material No. CP2101). (6) Install screws (20). TORQUE to between 40 and 45 lbf.in (0.45 and 0.50 m.daN). (7) Remove the rubber mat from the fan inlet case. 5. Close-up ________ Subtask 72-23-00-410-081 A. Close Access (1) Installation of the Fan Blades, the Spinner Rear Cone and the Spinner Front Cone. (2) Install the fan rotor blades (Ref. TASK 72-21-00-400-007). (3) Install the spinner rear cone (Ref. TASK 72-21-00-400-006).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 446 Nov 01/08
C F M 56-5B (4) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (5) Make sure that the work area is clean and clear of tool(s) and other items. (6) Remove the access platform(s). (7) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 447 Nov 01/08
C F M 56-5B TASK 72-23-00-000-029 Removal of the PS13 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1.5 m (4 ft. 11 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-23-00-991-315
Opening of the Fan Cowl Doors Fig. 408
3. __________ Job Set-up Subtask 72-23-00-941-086 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 448 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-103 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. 4. Procedure _________ (Ref. Fig. 408/TASK 72-23-00-991-315) Subtask 72-23-00-020-065 A. Removal of the PS13 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Cut and remove the lockwire. (2) Disconnect the PS13 line from the PS13 boss on the fan frame. (3) Cut and remove the lockwire. (4) Disconnect the PS13 line from the ECU.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 449 Nov 01/08
C F M 56-5B
Removal/Installation of the PS13 Line Figure 408/TASK 72-23-00-991-315- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 450 Nov 01/08
C F M 56-5B
Removal/Installation of the PS13 Line Figure 408/TASK 72-23-00-991-315- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 451 Nov 01/08
C F M 56-5B (5) Remove the parts which attach the PS13 line to the fan frame as follows: R R R R R R R R R R R R R R R R R R R R R R R R R
------------------------------------------------------------------------------| REMOVE | FROM | NOTE | ------------------------------------------------------------------------------| Nut (10) | Bracket (20) on flange F | At the 4:45 oclock | | Bolt (40) | | position (Detail B) | ------------------------------------------------------------------------------| Nut (80) | Bracket (60) on flange F | At the 4:30 oclock | | Bolt (50) | | position (Detail C) | | Clamp (70) | | | ------------------------------------------------------------------------------| Nut (120) | Bracket (110) on flange F | At the 4 oclock | | Bolt (90) | | position (Detail D) | | Clamp (100) | | | ------------------------------------------------------------------------------| Nut (140) | Bracket (150) on flange F | At the 3:45 oclock | | Bolt (130) | | position (Detail E) | | Clamp (160) | | | ------------------------------------------------------------------------------| Nuts (200) | Brackets (180) on flange G | At the 3 oclock, | | Bolts (170) | | 2 oclock and 1:30 oclock | | Clamps (190) | | positions (3 locations) | | | | (Detail F) | ------------------------------------------------------------------------------| Nut (240) | Bracket (220) on flange G | At the 2:30 oclock | | Bolt (210) | | position (Detail G) | | Clamp (230) | | | -------------------------------------------------------------------------------
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 452 Nov 01/08
C F M 56-5B TASK 72-23-00-400-029 Installation of the PS13 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1.5 m (4 ft. 11 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-991-315
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Fig. 408
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 453 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-860-064 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-23-00-010-105 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 408/TASK 72-23-00-991-315) Subtask 72-23-00-420-065 A. Installation of the PS13 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Lubricate the ECU and the fan frame boss nipples with engine fuel. (2) Connect the PS13 line to the ECU and to the fan frame boss by hand. (3) Lubricate the threads of the bolts (40), (50), (90), (130), (170), (210) with graphite grease (Material No. CP2101).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 454 Nov 01/08
C F M 56-5B (4) Install the parts which attach the PS13 line as follows: R R R R R R R R R R R R R R R R R R R R R R R R R
------------------------------------------------------------------------------| INSTALL | ON | NOTE | ------------------------------------------------------------------------------| Nut (10) | Bracket (20) on flange F | At the 4:45 oclock | | Bolt (40) | | position (Detail B) | ------------------------------------------------------------------------------| Nut (80) | Bracket (60) on flange F | At the 4:30 oclock | | Bolt (50) | | position (Detail C) | | Clamp (70) | | | ------------------------------------------------------------------------------| Nut (120) | Bracket (110) on flange F | At the 4 oclock | | Bolt (90) | | position (Detail D) | | Clamp (100) | | | ------------------------------------------------------------------------------| Nut (140) | Bracket (150) on flange F | At the 3:45 oclock | | Bolt (130) | | position (Detail E) | | Clamp (160) | | | ------------------------------------------------------------------------------| Nuts (200) | Brackets (180) on flange G | At the 3 oclock, | | Bolts (170) | | 2 oclock and 1:30 oclock | | Clamps (190) | | positions (3 locations) | | | | (Detail F) | ------------------------------------------------------------------------------| Nut (240) | Bracket (220) on flange G | At the 2:30 oclock | | Bolt (210) | | position (Detail G) | | Clamp (230) | | | ------------------------------------------------------------------------------(5) TORQUE the PS13 connection to the ECU to between 180 and 200 lbf.in (2.03 and 2.26 m.daN). (6) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (7) TORQUE the PS13 connection to the fan frame boss to between 135 and 150 lbf.in (1.52 and 1.69 m.daN). (8) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 455 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-095 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s). (4) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 456 Nov 01/08
C F M 56-5B TASK 72-23-00-000-040 Removal of the PS12 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1.5 m (4 ft. 11 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-23-00-991-316
Opening of the Fan Cowl Doors Fig. 409
3. __________ Job Set-up Subtask 72-23-00-941-083 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 457 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-106 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. 4. Procedure _________ (Ref. Fig. 409/TASK 72-23-00-991-316) Subtask 72-23-00-020-066 A. Removal of the PS12 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Cut and remove the lockwire. (2) Disconnect the PS12 line from the ECU. (3) Cut and remove the lockwires. (4) Disconnect the PS12 line from the 3 fan frame bosses.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 458 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-23-00 CES
Page 459 Feb 01/09
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 16 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 460 Nov 01/08
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 26 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 461 Nov 01/08
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 36 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 462 Nov 01/08
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 46 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 463 Nov 01/08
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 56 (SHEET 5) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 464 Nov 01/08
C F M 56-5B
Removal/Installation of the PS12 Line Figure 409/TASK 72-23-00-991-316- 66 (SHEET 6) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 465 Nov 01/08
C F M 56-5B (5) Remove the parts which attach the PS12 Line as follows: ------------------------------------------------------------------------------| REMOVE | FROM | NOTE | ------------------------------------------------------------------------------| Nut (30) | Bracket (40) on flange G | At the 5 oclock | | Bolt (10) | | position (Detail C) | ------------------------------------------------------------------------------| Nut (70) | Bracket (80) on flange E | At the 4:45 oclock | | Bolt (50) | | position (Detail D) | | Clamp (60) | | | ------------------------------------------------------------------------------| Nut (110) | Bracket (120) on flange C | At the 4:30 oclock | | Bolt (90) | | position (Detail E) | | Clamp (100) | | | ------------------------------------------------------------------------------| Nut (150) | Bracket (140) on flange C | At the 4 oclock | | Bolt (130) | | position (Detail F) | ------------------------------------------------------------------------------| Nuts (180) | Brackets (170) on flange C | From the 3:30 oclock | | Bolts (190) | | to the 1:45 Oclock | | Clamps (160) | | positions (Detail G) | | | | (5 locations) | ------------------------------------------------------------------------------| Nut (230) | Bracket (220) on flange C | From the 1 oclock | | Bolt (200) | | to the 8:15 oclock | | Clamp (210) | | positions (Detail H) | | | | (12 locations) | ------------------------------------------------------------------------------| Nut (260) | Bracket (250) on flange C | At the 11:45 oclock | | Bolt (240) | | position (Detail J) | ------------------------------------------------------------------------------| Nut (290) | Bracket (280) on flange C | At the 8 oclock | | Bolt (270) | | position (Detail K) | ------------------------------------------------------------------------------(6) remove the PS12 line (20) from the Engine.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 466 Feb 01/09
C F M 56-5B TASK 72-23-00-400-040 Installation of the PS12 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1.5 m (4 ft. 11 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-991-316
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Fig. 409
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 467 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-860-065 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-23-00-010-104 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 409/TASK 72-23-00-991-316) Subtask 72-23-00-420-066 A. Installation of the PS12 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Install the PS12 line (20) in position on the engine. (2) Lubricate the threads of the fan frame bosses and ECU nipples with engine fuel. (3) Connect the PS12 line to the 3 fan frame bosses and to the ECU. (4) Tighten the connecting nuts by hand.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 468 Feb 01/09
C F M 56-5B (5) Lubricate the threads of the bolts with graphite grease (Material No. CP2101). (6) Install the parts which attach the PS12 line as follows: ------------------------------------------------------------------------------| INSTALL | ON | NOTE | ------------------------------------------------------------------------------| Bolt (10) | Bracket (40) on flange G | At the 5 oclock | | Nut (30) | | position (Detail C) | ------------------------------------------------------------------------------| Clamp (60) | Bracket (80) on flange E | At the 4:45 oclock | | Bolt (50) | | position (Detail D) | | Nut (70) | | | ------------------------------------------------------------------------------| Clamp (100) | Bracket (120) on flange C | At the 4:30 oclock | | Bolt (90) | | position (Detail D) | | Nut (110) | | | ------------------------------------------------------------------------------| Bolt (130) | Bracket (140) on flange C | At the 4 oclock | | Nut (150) | | position (Detail F) | ------------------------------------------------------------------------------| Clamps (160) | Brackets (170) on flange C | From the 3:30 oclock | | Bolts (190) | | to the 1:45 oclock | | Nuts (180) | | positions (Detail G) | | | | (5 locations) | ------------------------------------------------------------------------------| Clamps (210) | Bracket (220) on flange C | From the 1 oclock | | Bolts (200) | | to the 8:15 oclock | | Nuts (230) | | positions (Detail H) | | | | (12 locations) | ------------------------------------------------------------------------------| Bolt (240) | Bracket (250) on flange C | At the 11:45 oclock | | Nut (260) | | position (Detail J) | ------------------------------------------------------------------------------| Bolt (270) | Bracket (280) on flange C | At the 8 oclock | | Nut (290) | | position (Detail K) | ------------------------------------------------------------------------------(7) Distribute the slack all along the line. (8) TORQUE the nuts (30), (70), (110), (150), (180), (230), (260), (290) to to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (9) TORQUE the fan frame bosses and ECU connections to to between 135 and 150 lbf.in (1.52 and 1.69 m.daN).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 469 Feb 01/09
C F M 56-5B (10) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). NOTE : The PS3 and the PS12 connecting nuts are safetied together. ____ 5. Close-up ________ Subtask 72-23-00-410-096 A. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s). Remove the access platform(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 470 Feb 01/09
C F M 56-5B TASK 72-23-00-400-043 Installation of Acoustical Panels Attachment Screw/Nut Locking 1. __________________ Reason for the Job This procedure gives task to lock acoustical panel screws when the corresponding self locking nut torque is smaller than the AMM limits. This procedure applies to any acoustical panel screws: fwd, mid and aft. Any screws and corresponding riveted self locking nuts locked per this procedure will have to be changed at first shop visit opportunity. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2242
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-A-46106A RTV (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 471 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2656
* mag-chem skysol (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-23-00-941-093 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 472 Feb 01/09
C F M 56-5B Subtask 72-23-00-010-116 B. Get Access (1) Open the fan cowls: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-23-00-040-071 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-117 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-23-00-420-069 A. Locking of Acoustical Panels. (1) Remove the screws if the torque of the related self locking nut is less than the AMM limits. (2) Clean the screws and the nuts with acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or magchem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041). (3) Apply RTV (Material No. CP2242) or equivalent on screw threads and below the screw heads. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH AND TORQUE _______ ALL ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 473 Feb 01/09
C F M 56-5B (4) Re-install the acoustical panels and screws. (a) TORQUE the screws of the forward and mid panels to between 84 and 93 lbf.in (0.94 and 1.05 m.daN) (b) TORQUE the screws of the aft panels to between 66 and 75 lbf.in (0.74 and 0.84 m.daN). 5. Close-up ________ Subtask 72-23-00-410-107 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-065 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041) Subtask 72-23-00-410-108 C. Close Access (1) Close the fan cowls: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 474 Feb 01/09
C F M 56-5B TASK 72-23-00-400-044 Installation of Acoustical Panels Attachment Screw Locking 1. __________________ Reason for the Job This procedure tells you how to lock acoustical panel screws when the panel cup examined has a hole caused by the screw head. This procedure applies to all acoustical panel screws: fwd, mid and aft. It is necessary to replace panels with damaged cups re-installed by this procedure at the subsequent shop visit. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2242
Material No.
CP2266
Material No.
CP2431
USA MIL-T-5544 graphite grease (Ref. 70-30-00) USA MIL-A-4610A RTV 732 (Ref. 70-30-00) * RTV 102 (Ref. 70-30-00) * RTV 730 (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 475 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-13-00-010-040 71-13-00-410-040 72-23-00-300-045 72-23-00-400-043 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 ESM 722302300008 SPM 702111
Removal of the Power Plant Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Replacement of the Riveted Self Locking Nuts for the Attachment of the Forward Acoustical Panels Installation of Acoustical Panels Attachment Screw/Nut Locking Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-23-00-941-094 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 476 Feb 01/09
C F M 56-5B Subtask 72-23-00-010-118 B. Get Access (1) Open the fan cowls: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-23-00-040-072 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-119 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-23-00-420-070 A. Locking of Acoustical Panels CAUTION : COATING SCREWS IS MANDATORY. _______ (1) If panel cup(s) found pierced, do the procedure that follows: WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL _______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. (a) Remove the bolt. (b) Clean all damaged cups (Ref. SPM 702111).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 477 Feb 01/09
C F M 56-5B (c) Fill all damaged cups with RTV 732 (Material No. CP2242) or RTV 102 (Material No. CP2266) or RTV 730 (Material No. CP2431) NOTE : You must install the screw, with only a light layer of ____ graphite grease (Material No. CP2101), a short time after you apply the RTV (before polymerisation). (2) Apply a layer of graphite grease (Material No. CP2101) to the threads of all the screws that attach the acoustical panels. (3) Re-install the acoustical panels and screws. CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL _______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS. (4) Measure the self locking nut torque of each nut when you start to tighten the screw. NOTE : Make sure that the screws are not damaged, replace them if ____ necessary. (a) If the self locking nut torque is less than 4.5 lbf.in (0.05 m.daN), (Ref. TASK 72-23-00-400-043). (b) If the self locking nut torque is more than 4.5 lbf.in (0.05 m.daN), but less than 31 lbf.in (0.35 m.daN), TORQUE the screws of fwd and mid panels to between 84 and 93 lbf.in (0.94 and 1.05 m.daN) and TORQUE screws of the aft panels to between 66 and 75 lbf.in (0.74 and 0.84 m.daN). (c) If the self locking nut torque is more than 31 lbf.in (0.35 m.daN), but less than 49 lbf.in (0.55 m.daN), TORQUE screws at the running torque value and add 44 lbf.in (0.5 m.daN). (d) If the self locking nut torque is more than 49 lbf.in (0.55 m.daN): - replace the self locking nut of the fwd panels (Ref. TASK 7223-00-300-045). - remove the engine (Ref. TASK 71-00-00-000-042) and do the engine shop repair procedure (Ref. ESM 722302300008) to replace the self locking of the mid and aft panels.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 478 Feb 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-109 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-066 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041) Subtask 72-23-00-410-110 C. Close Access (1) Close the fan cowls: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 479 Feb 01/09
C F M 56-5B FAN FRAME ASSEMBLY - INSPECTION/CHECK _____________________________________ TASK 72-23-00-210-004 Visual Inspection of the Fan Frame Assembly CAUTION : TITANIUM PARTS REQUIRE THE USE OF NON-HALOGENATED SOLVENTS. _______ 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-21-00-320-003 72-23-00-000-027 72-23-00-000-028 72-23-00-280-005 72-23-00-280-006 72-23-00-280-007 72-23-00-300-042 72-23-00-350-002 72-23-00-400-027 72-23-00-400-028 78-30-00-081-041 78-30-00-481-041
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Blending of Fan Rotor Blades Removal of the Fan Duct Panels Removal of the Splitter Fairing Inspection of Forward Acoustical Panels Inspection of Mid Acoustical Panels Inspection of Aft Acoustical Panels Repair of Fan Duct Panel Removal of Rust from the Fan Frame Casing Installation of the Fan Duct Panels Installation of the Splitter Fairing Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-36-00-010-040 78-36-00-410-040 72-23-00-991-308 72-23-00-991-309 72-23-00-991-328 72-23-00-991-326
Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603 Fig. 604
3. __________ Job Set-up Subtask 72-23-00-941-077 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-088 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-23-00-040-066 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 602 Aug 01/09
C F M 56-5B Subtask 72-23-00-010-101 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-23-00-991-308, 602/TASK 72-23-00-991-309) Subtask 72-23-00-210-057 A. Visual inspection of the fan Frame Assembly ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fan frame casing for: (Ref. Fig. 601/TASK 72-23-00-991-308) A. Cracks
No limits in quantity if 0.08 in. (2,03 mm) max. length and a minimum of 1 in. (25,40 mm) apart.
B. Dents or nicks on struts
No limits in quantity if, 0.08 in. (2.03 mm) max. depth
C. Corrosion (discoloration)
No limits in quantity
D. Scaling or pitting
Not serviceable
At the first opportunity remove rust (Ref. TASK 7223-00-350-002)
2. Inlet case on B1 and B3 upstream bracket location for: (Ref. Fig. 601/TASK 72-23-00-991-308)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check Figure 601/TASK 72-23-00-991-308- 15 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check Figure 601/TASK 72-23-00-991-308- 25 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check Figure 601/TASK 72-23-00-991-308- 35 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check Figure 601/TASK 72-23-00-991-308- 45 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check Figure 601/TASK 72-23-00-991-308- 55 (SHEET 5) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B
Fan Duct Panels Figure 602/TASK 72-23-00-991-309 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Wear of flanges Two expanded adjacent Remove the inlet case. holes oversized holes are permitted if: - Each expanded hole is not more than 0.315 in. (8 mm) width and not more than 0.6 in. (15 mm) long. - 5 holes minimum in good condition are on both sides of expanded holes. B. Wear, fretting, chafing of flange holes.
If 0.008 in. (0,20 mm) max. depth or If 0.02 in. (0,5 mm) max. depth and 0.155 sq.in. (100 sq.mm) max. surface.
10 cycles serviceable extension is allowed.
C. Wear, fretting, chafing on the top of flange holes.
If 0.02 in. (0,5 mm) max. width and 0.8 in. (20 mm) max. length.
10 cycles serviceable extension is allowed.
D. Washer impression around flange holes
If 0.032 in. (0,81 mm) max. depth and 0.60 in. (15,25 mm) max. diameter.
10 cycles serviceable extension is allowed. Do blending (Ref. TASK 72-2100-320-003) until high metal is removed.
3. Fan inlet case on B1 upstream bracket location (Ref. Fig. 603/TASK 72-23-00-991-328) R R
A. Wear on B1 flange radius. (Ref. Fig. 604/TASK 72-23-00991-326)
R R
For damage that measures (X) from the B1 flange,
a maximum depth of wear (A) is permitted
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Feb 01/10
C F M 56-5B
Fan Inlet Case on B1 upstream bracket location Figure 603/TASK 72-23-00-991-328 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B
R R
Wear on B1 Flange Radius Figure 604/TASK 72-23-00-991-326
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------4. Inlet case on B4 upstream fan case: A. Expanded holes
Two expanded adjacent holes are permitted if: - Each expanded hole is not more than 0.315 in. (8 mm) width and not more than 0.39 in. (10 mm) long. - 5 holes minimum in good condition are on both sides of expanded holes.
B. Wear, fretting, chafing around flange holes.
If 0.031 in. (0.8 mm) max. depth and 0.155 sq.in. (100 sq.mm) max. surface.
10 cycles serviceable extension is permitted.
5. Inlet case on B4 downstream fan case: A. Expanded holes
Two expanded adjacent holes are permitted if: - Each expanded hole is not more than 0.315 in. (8 mm) width and not more than 0.39 in. (10 mm) long. - 5 holes minimum in good condition are on both sides of expanded holes.
B. Wear, fretting, chafing around flange holes.
If 0.024 in. (0.6 mm) max. depth and 0.155 sq.in. (100 sq.mm) max. surface.
10 cycles serviceable extension is permitted.
6. Fan FWD acoustical panel (Ref. TASK 7223-00-280-005)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 613 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------7. Fan MID acoustical panel (Ref. TASK 7223-00-280-006)
R
8. Fan aft acoustical panels (Ref. TASK 7223-00-280-007)
R
9. Splitter fairing for
R
A. Cracks
Not serviceable
B. Damaged protective coating
No limits in quantity
C. Erosion
No limits in quantity
Replace the fairing (Ref. TASK 72-23-00-000028) and (Ref. TASK 72-2300-400-028)
10. Fan duct panels for: (Ref. Fig. 602/TASK 72-23-00-991-309) A. Missing louver
1 missing louver permitted per panel if no more than 4 panels have this damage
Replace panel (Ref. TASK 72-23-00-000-027) and (Ref. TASK 72-23-00-400027).
B. Nicks, dents or scratches
No limits
C. Loose bolts
Not serviceable
Make sure that washers are installed and torque bolts to between 85 and 95 lbf.in (0.96 and 1.07 m.daN)
D. Cracks in screw hole area
One for each screw hole max length 0.25 in. (6,35 mm)
Replace panel (Ref. TASK 72-23-00-000-027) and (Ref. TASK 72-23-00-400027)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------E. Cracks in flanged Not serviceable Repair panel (Ref. TASK edges 72-23-00-300-042) 2 cracks permitted on the same panel
Repair panel (Ref. TASK 72-23-00-300-042)
G. Fan duct panel missing
Not serviceable
Install fan duct panel(s) (Ref. TASK 72-23-00-400027)
R R
F. Cracks on louver and area adjacent to louver
R R R
Refer to over serviceable limit extension (Ref. TASK 72-00-00-200-025) 5. Close-up ________ Subtask 72-23-00-410-082 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-061 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-093 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Aug 01/09
C F M 56-5B TASK 72-23-00-210-003 Detailed Inspection of Engine Inlet, Fan Blades, Fan Outlet and Abradable Material 1. __________________ Reason for the Job R
Refer to the MPD TASK: 722000-C1 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-21-00-210-009 72-23-00-000-008 72-23-00-300-040 72-23-00-300-043 72-23-00-400-008 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-23-00-991-308 72-23-00-991-310
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Inspect Fan Rotor Blades Installed on the Fan Disk Removal of the Fan Outlet Guide Vane (OGV) Doublets Local Reconditioning of the Abradable MaterialDefects less than 0.12 in. (3 mm) deep and 0.50 in.2 (3.2 cm2) Repair of the Abradable (material) Shroud with Circular Patches Installation of the Fan Outlet Guide Vane (OGV) Doublets Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 605
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Feb 01/10
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-080 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-090 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-23-00-040-067 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-102 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 617 May 01/09
C F M 56-5B 4. Procedure _________ R
(Ref. Fig. 601/TASK 72-23-00-991-308, 605/TASK 72-23-00-991-310) Subtask 72-23-00-210-058 A. Detailed Visual Inspection of the Engine Inlet, Fan Blades, Fan Outlet and Abradable Material ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Inlet case for: (Ref. Fig. 601/TASK 72-23-00-991-308) A. Cracks
Not permitted.
B. Cracks or crazing in the rubber of AGB mount
Any amount.
C. Nicks
On area A, if 0.012 in. (0,30 mm) max. depth and 0.046 sq.in. (30 sq.mm) max. surface. On area B, if 0.008 in. (0,20 mm) max. depth and 0.046 sq.in. (30 sq.mm) max. surface. On area C, if 0.012 in. (0,30 mm) max. depth and 0.077 sq.in. (50 sq.mm) max. surface
50 cycles serviceable extension is allowed.
D. Scratches
0.008 in. (0,20 mm) max. depth and 1.968 in. (50 mm) max. length
50 cycles serviceable extension is allowed.
E. Dents
On area A, if 0.002 in. (0,5 mm) max. depth and 0.124 sq.in. (80 sq.mm) max. surface. On area B, if 0.008 in. (0,20 mm) max. depth and
50 cycles serviceable extension is allowed.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------0.124 sq.in. (80 sq.mm) max. surface. On area C, if 0.02 in. (0,5 mm) max. depth and 0.155 sq.in. (100 sq.mm) max. surface. F. Wear
On area A and B, if 0.004 in. (0,10 mm) max. depth and 0.465 sq.in. (300 sq.mm) max. surface. On area C, if 0.004 in. (0,10 mm) max. depth and 0.62 sq.in. (400 sq.mm) max. surface.
50 cycles serviceable extension is allowed.
2. Fan rotor blades: (Ref. TASK 72-21-00210-009) 3. Abradable for: (Ref. Fig. 601/TASK 72-23-00-991-308) A. Cracks
Any amount
B. Rubs
Any amount
C. Crater (length<5x width) and damage other than crack rub and circumferential defect
Cumulated damage more than 160 in.2 (1032,25 cm2) with no one area larger than 30 in.2 (193,54 cm2) and : a) The maximum axial width (parallel to engine axis) is less than 2.5 in. (63.5 mm) b) The minimum distance between the areas is equal to the maximum dimension of the nearest damaged area.
For defect above those limits : local reconditioning : (Ref. TASK 72-23-00-300040) circular patch : (Ref. TASK 72-23-00-300043) refer to limits : (Ref. TASK 72-00-00-200025)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 619 May 01/09
C F M 56-5B
R
Inspection/Check of the Fan-Outlet Guide Vanes (OGV) Figure 605/TASK 72-23-00-991-310- 13 (SHEET 1)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/09
C F M 56-5B
R
Inspection/Check of the Fan-Outlet Guide Vanes (OGV) Figure 605/TASK 72-23-00-991-310- 23 (SHEET 2)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 621 Nov 01/09
C F M 56-5B
R
Inspection/Check of the Fan-Outlet Guide Vanes (OGV) Figure 605/TASK 72-23-00-991-310- 33 (SHEET 3)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------c) The fan case parent metal does not show through.
R
D. Grooves (orientated within 0 deg. and 80 deg. from engine axis and length>5x width)
All damage is permitted if : a) The maximum width of one groove is not more than 0.32 in. (8.12 mm). b) A maximum of total width of 1.25 in. (31.75 mm) of groove is with a minimum separation of 0.1 in. (2.54 mm). c) The fan case parent metal does not show through.
For defect above those limits : local reconditioning : (Ref. TASK 72-23-00-300040) refer to limits : (Ref. TASK 72-00-00-200025)
E. Circumferential defect (360 deg. or orientated within 80 deg. to 90 deg. from engine axis
All damage is permitted if : a) The maximum axial width (parallel to engine axis) of one or cumulated defect is less than 1.5 in. (38.1 mm) b) Fan case parent metal does not show through.
For defect above those limits : local reconditioning : (Ref. TASK 72-23-00-300040) refer to limits : (Ref. TASK 72-00-00-200025)
A. Broken vane
Not serviceable
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
B. Missing vane
One doublet missing
10 cycles extension allowed with one doublet missing. Complete set inspection required when new doublet fitted.
4. Outlet Guide Vanes (OGV) for: (Ref. Fig. 605/TASK 72-23-00-991-310)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 623 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008). C. Cracks airfoil
Not serviceable
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
outer platform
Cracks from or along the airfoil are defined on fig.604
50 cycles extension allowed if cracks are found out of tolerance. Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
D. Delamination
Not serviceable
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
E. Eroded surface (glass film)
50 percent of airfoil
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
F. Unbonding of metal leading edge
Up to 0.31 sqare in. (200 square mm) serviceable if no parent composite material.
Replace the vane doublet (Ref. AMM TASK 72-23-00-000-008) and (Ref. AMM TASK 72-23-00-400-008).
Over 0.31 square in. (200 square mm).
Remove the unbonding area. Refer to paragraph G.Metal leading edge missing
Up to 0.78 in. (20 mm) height and 0.39 in. (10 mm) wide.
100 cycles extension allowed if missing material is over criteria.
G. Metal leading edge missing
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 624 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------Speed tape (CP2516) usage is recommended when missing metal on leading edge to preserve repair possibility, avoiding any damage on composite material. H. Outer and inner platform debonding
Not serviceable
Replace the vane doublet (Ref. AMM TASK 72-23-00-000-008) and (Ref. AMM TASK 72-23-00-400-008).
J. Nick and/or dents, on leading edge (metallic leading edge)
Any amount of damage less than 0.12 in. (3 mm) deep and metal not torn : serviceable. If damage less than 0.12 in. (3mm) deep and metal torn, refer to paragraph G..
A maximum service extension of 100 cycles is allowed if damage is between 0.12 in. (3mm) and 0.19 in. (5mm) deep.
K. Nick and/or dents, on trailing edge
No limited number if less than 0.01 in. (0.25 mm) depth
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
L. Nick and/or dent on concave or convex side
No limited number if less than 0.02 in. (0.51 mm) depth
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
M. Nick and/or dent on inner or outer platform
No limited number if less than 0.02 in. (0.51 mm) depth
Replace the vane doublet (Ref. TASK 72-23-00-000008) and (Ref. TASK 72-2300-400-008).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 625 May 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-084 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-063 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-094 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 626 May 01/09
C F M 56-5B TASK 72-23-00-280-001 Inspection/Check of the PS13 Line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
plastic wire warning notice access platform 1.5 m (4 ft. 11 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2010
Material No.
CP8001
Material No.
CP8002
* white spirit (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-000-029 72-23-00-400-029 72-23-00-991-320
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the PS13 Line Installation of the PS13 Line Fig. 606
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-084 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-107 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. 4. Procedure _________ R
(Ref. Fig. 606/TASK 72-23-00-991-320) Subtask 72-23-00-210-062 A. Visual Inspection of the PS13 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 628 May 01/09
C F M 56-5B (1) Inspect the PS13 line as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Inspect the hose for: - broken hose braid
3 broken wires per plait, and no more than 6 broken wires per assembly, or per lineal 12 in. (305 mm) of hose.
- crimps
Not serviceable
Replace the PS13 line (Ref. TASK 72-23-00-000029) and (Ref. TASK 72-2300-400-029).
Subtask 72-23-00-210-060 B. Visual Inspection of the PS13 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Inspect the PS13 hose connections as follows: (a) Cut and remove the lockwires. (b) Disconnect the PS13 hose from the ECU and from the fan frame boss.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 629 May 01/09
C F M 56-5B
PS13 Line Figure 606/TASK 72-23-00-991-320- 12 (SHEET 1)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 630 May 01/09
C F M 56-5B
PS13 Line Figure 606/TASK 72-23-00-991-320- 22 (SHEET 2)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 631 May 01/09
C F M 56-5B (c) Inspect the connections as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fitting nuts for: - damaged corners
Any amount, provided proper torque can be obtained.
- damaged threads
Any amount, provided effective threads are not reduced by more than one after chasing.
- safetywire hole deformation and wear.
Serviceable, provided metal around hole is not cracked or torn.
Chase the threads.
2. Fittings seating surfaces for: - circumferential scratches
Any amount not detectable with a 0.04 in. (1 mm) radius ball scribe.
- axial scratches
Not serviceable
Replace the hose or the part.
- nicks, pits
Not serviceable
Replace the hose or the part.
(2) Clean the weep hole with white spirit (Material No. CP2010) and a plastic wire. (3) Blow clean dry air into the PS13 connection to ECU to remove any dirt or water accumulation. Blocked hose is not serviceable. If necessary, replace the hose (Ref. TASK 72-23-00-000-029) and (Ref. TASK 72-2300-400-029). (4) Check the ECU nipple for dirt. If necessary, remove the dirt with a plastic wire. Take care to not introduce dirt inside the ECU.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 632 May 01/09
C F M 56-5B (5) Check the fan frame boss for dirt. If necessary, remove the dirt with stoddart solvent and a plastic wire. Blow clean dry air into the fan frame boss nipple. (6) Lubricate the ECU and the fan frame boss nipples with engine fuel. (7) Connect the PS13 line to the ECU and to the fan frame boss. (8) TORQUE the ECU connection to between 180 and 200 lbf.in (2.03 and 2.26 m.daN). (9) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (10) TORQUE the fan frame boss connection to between 135 and 150 lbf.in (1.52 and 1.69 m.daN). (11) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). 5. Close-up ________ Subtask 72-23-00-410-097 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s). (4) Remove the access platform(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 633 May 01/09
C F M 56-5B TASK 72-23-00-280-002 Inspection/Check of the PS12 line 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
plastic wire warning notice access platform 1.5 m (4 ft. 11 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2010
Material No.
CP8001
Material No.
CP8002
* white spirit (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-000-040 72-23-00-400-040 72-23-00-991-321
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the PS12 Line Installation of the PS12 Line Fig. 607
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 634 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-085 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-108 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. 4. Procedure _________ R
(Ref. Fig. 607/TASK 72-23-00-991-321) Subtask 72-23-00-210-063 A. Visual Inspection of the PS12 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 635 May 01/09
C F M 56-5B
PS12 Line Figure 607/TASK 72-23-00-991-321- 14 (SHEET 1)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 636 May 01/09
C F M 56-5B
PS12 Line Figure 607/TASK 72-23-00-991-321- 24 (SHEET 2)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 637 May 01/09
C F M 56-5B
PS12 Line Figure 607/TASK 72-23-00-991-321- 34 (SHEET 3)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 638 May 01/09
C F M 56-5B
PS12 Line Figure 607/TASK 72-23-00-991-321- 44 (SHEET 4)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 639 May 01/09
C F M 56-5B (1) Inspect the PS12 line as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Inspect the hose for: - broken hose braid
3 broken wires per plait, and no more than 6 broken wires per assembly, or per lineal 12 in. (305 mm) of hose.
- crimps
Not serviceable
Replace the PS12 line (Ref. TASK 72-23-00-000040) and (Ref. TASK 72-2300-400-040).
Subtask 72-23-00-210-061 B. Visual Inspection of the PS12 Line CAUTION : USE 2 WRENCHES TO REMOVE/INSTALL THE TUBE UNION NUT: ONE TO _______ HOLD THE FITTING, THE OTHER TO LOOSE/TORQUE THE NUT. OTHERWISE, DAMAGE TO THE HARDWARE CAN OCCUR. (1) Inspect the PS12 hose connections as follows: (a) Cut and remove the lockwires. (b) Disconnect the PS12 hose from the ECU and from the fan frame bosses.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 640 Feb 01/09
C F M 56-5B (c) Inspect the connections as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Fitting nuts for: - damaged corners
Any amount, provided proper torque can be obtained.
- damaged threads
Any amount, provided effective threads are not reduced by more than one after chasing.
- safetywire hole deformation and wear.
Serviceable, provided metal around hole is not cracked or torn.
Chase the threads.
2. Fittings seating surfaces for: - circumferential scratches
Any amount not detectable with a 0.04 in. (1 mm) radius ball scribe.
- axial scratches
Not serviceable
Replace the hose or the part.
- nicks, pits
Not serviceable
Replace the hose or the part.
(2) Clean the weep holes with white spirit (Material No. CP2010) and plastic wire. (3) Blow clean dry air into the PS12 connection to ECU to remove any dirt or water accumulation. Blocked hose is not serviceable. If necessary, replace the hose (Ref. TASK 72-23-00-000-040) and (Ref. TASK 72-2300-400-040). (4) Check the ECU nipple for dirt. If necessary, remove the dirt with plastic wire. Take care to not introduce dirt inside the ECU.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 641 Feb 01/09
C F M 56-5B (5) Check the fan frame bosses for dirt. If necessary, remove the dirt with stoddart solvent and a plastic wire. Blow clean dry air into the fan frame bosses nipples. (6) Lubricate the ECU and the fan frame bosses nipples with engine fuel. (7) Connect the PS12 line to the ECU and to the fan frame bosses. (8) TORQUE the PS12 connections to between 135 and 150 lbf.in (1.52 and 1.69 m.daN). (9) Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). 5. Close-up ________ Subtask 72-23-00-410-098 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the access platform(s). (4) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 642 Feb 01/09
C F M 56-5B TASK 72-23-00-280-005 Inspection of Forward Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-000-009 72-23-00-300-044 72-23-00-400-009 72-23-00-400-044 R
72-23-00-991-311
Removal of the Forward Acoustical Panels of the Fan Repair of Forward, Mid and Aft Acoustical Panels when Unbounded Cup Installation of the Forward Acoustical Panels of the Fan Installation of Acoustical Panels Attachment Screw Locking Fig. 608
3. __________ Job Set-up Subtask 72-23-00-941-090 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 643 May 01/09
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put a warning notice to tell persons not to start the engine 1(2). (5) Put an access platform in position at the front of the engine. 4. Procedure _________ R
(Ref. Fig. 608/TASK 72-23-00-991-311) Subtask 72-23-00-350-058 A. Inspection of FWD Acoustical Panels ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. FWD acoustical panels A. Dents, marks, indentations caused by screw head.
No limits
B. Pierced cups caused by screw head.
Not serviceable
Install the panel (Ref. TASK 72-23-00-400044)
C. Unbonded cups.
Not serviceable
Repair the panel (Ref. TASK 72-23-00-300044) and re-install the panel immediately (Ref. TASK 72-23-00-400009).
D. Missing cups.
Not serviceable
Replace the panel (Ref. TASK 72-23-00-000009) and (Ref. TASK 72-2300-400-009).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 644 May 01/09
C F M 56-5B
INTENTIONALLY BLANK
R 72-23-00 CES
Page 645 Aug 01/09
C F M 56-5B
Fan Acoustical Panels Figure 608/TASK 72-23-00-991-311- 12 (SHEET 1)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 646 May 01/09
C F M 56-5B
Fan Acoustical Panels Figure 608/TASK 72-23-00-991-311- 22 (SHEET 2)
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 647 May 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------E. Missing insert No limits thread F. Missing panel
Not serviceable
G. Loose bolts
Not serviceable
H. Local collapse of panel inner surface
No limits
J. Subsurface linear impressions or wrinkles
No limits
Serviceable criteria applied on new parts
K. Voids
Five per panel, 2 in. (50.8 mm) apart, 0.12 in. (3 mm) Dia max, 0.012 in. (0.3 mm) max depth
Serviceable criteria applied on new parts
(1) Missing
No limits
Remove the loose material with a sharp blade.
(2) Defects (dents, nicks, tears, flaking) that let show the inner skin
No limits
Remove the loose material with a sharp blade.
No limits with a total surface area less than 4 square in. (2580 sq mm)
Remove the loose material with a sharp blade.
Tighten bolts
L. Defects in the protective coating (initial Tedlar film, or paint) such as:
M. Inner skin defects, such as: (1) Superficial defects (dents, nicks,
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 648 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------tears, impacts per panel marks) not through the skin (2) Defects (tears, cracks, punctures) through the skin
Not serviceable
Replace panel(s) (Ref. TASK 72-23-00-000009) and (Ref. TASK 72-2300-400-009).
5. Close-up ________ Subtask 72-23-00-410-103 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 649 Aug 01/09
C F M 56-5B TASK 72-23-00-280-006 Inspection of Mid Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-00-00-200-025 72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-23-00-000-025 72-23-00-300-044 72-23-00-400-025 72-23-00-400-044 72-23-00-991-311
Over-Serviceable-Limit Extensions Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Removal of the Mid Acoustical Panels Repair of Forward, Mid and Aft Acoustical Panels when Unbounded Cup Installation of the Mid Acoustical Panels Installation of Acoustical Panels Attachment Screw Locking Fig. 608
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 650 Aug 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-091 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-113 B. Get Access (1) Put an access platform in position at the front of the engine. (2) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (3) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (4) Put temporary mark on each fan blade from 1 to 36. (5) Remove 3 consecutive fan blades (Ref. TASK 72-21-00-000-007). To compensate for imbalance caused by the removal of 3 blades, it is recommended to remove 3 blades 180 degrees opposite to those removed before.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 651 Aug 01/09
C F M 56-5B 4. Procedure _________ (Ref. Fig. 608/TASK 72-23-00-991-311) Subtask 72-23-00-350-059 A. Inspection of Mid Acoustical Panels ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Leading edge delamination
Not serviceable
Replace panel (Ref. TASK 72-23-00-000-025) and (Ref. TASK 72-23-00-400025)
2. Inner skin delamination in acoustical area
20 percent of acoustical area
Above 20 percent, replace panel (Ref. TASK 72-23-00000-025) and (Ref. TASK 72-23-00-400-025)
3. Mid acoustical panel cups A. Dents, marks, indentations caused by screw head
No limits
B. Pierced cups caused by screw head
No limits
(Ref. TASK 72-23-00-400044)
C. Unbonded cups
Not serviceable
(Ref. TASK 72-23-00-300044)
D. Missing cups.
Not serviceable
(Ref. TASK 72-23-00-300044)
4. Missing panel
Not serviceable
5. Loose bolts
Not serviceable
Tighten bolts
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 652 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------6. Subsurface linear No limits Serviceable criteria impressions or applied on new parts wrinkles 7. Voids
Five per panel, 2 in. (50.8 mm) apart, 0.12 in. (3 mm) Dia max, 0.012 in. (0.3 mm) max depth
Serviceable criteria applied on new parts
A. Missing
No limits
Remove the loose material with a sharp blade
B. Defects (dents, nicks, tears, flaking) that let show the inner skin
No limits
Remove the loose material with a sharp blade
A. Superficial defects (dents, nicks, tears, impact marks) not through the skin
No limits with a total surface area less than 4 square in. (2580 sq mm) per panel
Remove the loose material with a sharp blade
B. Defects (tears, cracks, punctures) through the skin
Not serviceable
Replace panel(s) (Ref. TASK 72-23-00-000025) and (Ref. TASK 72-2300-400-025)
C. Stiffener delamination under panel leading edge
Sound not constant with adjacent area by tap test control. Do the tap test control on the first 0.83 in. (21 mm)
Replace panel(s) (Ref. TASK 72-23-00-000025) and (Ref. TASK 72-2300-400-025)
8. Defects in the protective coating (initial Tedlar film, or paint) such as:
9. Inner skin defects, such as:
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 653 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------area from the leading edge on assembled panels 10. Damper A. Cracks (if panel removed)
Any amount
B. Disbonded damper (if panel removed)
Any amount not more than 20 percent of the total bonded surface
Replace mid acoustical panel of not in the limits (Ref. TASK 72-23-00-000025) and (Ref. TASK 72-2300-400-025) Refer to the over-serviceable limit extensions (Ref. TASK 7200-00-200-025)
5. Close-up ________ Subtask 72-23-00-410-104 A. Close Access (1) Install the fan rotor blades at the locations recorded at the removal (Ref. TASK 72-21-00-400-007). (2) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (3) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (4) Make sure that the work area is clean and clear of tool(s) and other items. (5) Remove the access platform(s). (6) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 654 Aug 01/09
C F M 56-5B TASK 72-23-00-280-007 Inspection of Aft Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-000-026 72-23-00-300-044 72-23-00-400-026 72-23-00-400-044 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-23-00-991-311
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Aft Acoustical Panels Repair of Forward, Mid and Aft Acoustical Panels when Unbounded Cup Installation of the Aft Acoustical Panels Installation of Acoustical Panels Attachment Screw Locking Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 608
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 655 Aug 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-095 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-120 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-23-00-040-073 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-23-00-010-121 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 656 Aug 01/09
C F M 56-5B 4. Procedure _________ (Ref. Fig. 608/TASK 72-23-00-991-311) Subtask 72-23-00-350-060 A. Inspection of Aft Acoustical Panels ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Aft acoustical panel cups A. Dents, marks, indentations caused by screw head.
No limits
(Ref. TASK 72-23-00-400026) for re-installation.
B. Pierced cups caused by screw head.
Not serviceable
(Ref. TASK 72-23-00-400044)
C. Unbonded cups.
Not serviceable
(Ref. TASK 72-23-00-300044)
D. Missing cups.
Not serviceable
(Ref. TASK 72-23-00-300044)
No limits unless the whole seal is missing
Replace seal if missing
Not serviceable
Install the seal correctly, or install a new U-shaped seal (Ref. TASK 72-23-00-000026) or (Ref. TASK 72-2300-400-026)
PRE SB 72-071 E. Damaged or missing bonded seal(s) END OF PRE SB 72-071 POST SB 72-071 F. Mis-installed, badly damaged or missing U-shaped seal (removable)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 657 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------END OF SB 72-071 G. Missing panel
Not serviceable
H. Loose bolts
Not serviceable
Tighten bolts
J. Subsurface linear impressions or wrinkles
No limits
Serviceable criteria applied on new parts
K. Voids
Five per panels, 2 in. (50.8 mm) apart, 0.12 in. (3 mm) Dia max, 0.012 in. (0.3 mm) max depth
Serviceable criteria applied on new parts
(1) Missing
No limits
Remove the loose material with a sharp blade
(2) Defects (dents, nicks, tears, flaking) that let show the inner skin
No limits
Remove the loose material with a sharp blade
No limits with a total surface area less than 4 square in. (2580 sq mm) per panel
Remove the loose material with a sharp blade
L. Defects in the protective coating (initial Tedlar film, or paint) such as:
M. Inner skin defects, such as: (1) Superficial defects (dents, nicks, tears, impact marks) not through the skin
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 658 Aug 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------(2) Defects Not serviceable Replace panel(s) (tears, (Ref. TASK 72-23-00-000cracks, 026) and (Ref. TASK 72-23punctures) 00-400-026) through the skin 5. Close-up ________ Subtask 72-23-00-410-111 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-067 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-23-00-410-112 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 659 Feb 01/09
C F M 56-5B TASK 72-23-00-210-007 Visual Inspection of the Junction Box 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2242
USA MIL-A-46106A RTV 732 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-23-00-300-046
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Replacement of Lateral Bracket Plate on the Junction Box
3. __________ Job Set-up Subtask 72-23-00-941-097 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 660 Feb 01/09
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-123 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ Subtask 72-23-00-210-067 A. Visual Inspection of the Junction Box ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------Crack on the two lateral bracket plates.
One crack 0.78 in. (20 mm) max length.
Stop crack by drilling a 0.12 in. (3 mm) hole at each ends of the crack. Clean the part.Apply RTV 732 (Material No. CP2242) or equivalent on the inner face of the affected area
Any amount
Replace the damaged lateral bracket plate (Ref. TASK 72-23-00-300046).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 661 Feb 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-115 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 662 Feb 01/09
C F M 56-5B FAN FRAME ASSEMBLY - REPAIRS ____________________________ TASK 72-23-00-300-040 Local Reconditioning of the Abradable Material- Defects less than 0.12 in. (3 mm) deep and 0.50 in.2 (3.2 cm2) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No No No
specific specific specific specific specific specific
heat gun or a infra-red lamp protective mats spatula vacuum cleaner warning notice access platform 0.5 m (1 ft. 8 in.)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2239
Material No.
CP2297
Material No.
CP2298
Material No.
CP2559
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * abrasive cloth (Ref. 70-30-00) * base RTV 147 A (Ref. 70-30-00) * catalyst (hardener) RTV 147 B (black color) (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades
3. __________ Job Set-up Subtask 72-23-00-941-078 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B Subtask 72-23-00-010-089 B. Get Access (1) Put an access platform in position. (2) Install protective mats in the lower half of the inlet cowl. (3) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (4) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006). (5) Remove a sufficient number of fan blades to get access to repair area (Ref. TASK 72-21-00-000-007). 4. Procedure _________ Subtask 72-23-00-320-053 A. Prepare the Repair Area (1) Remove the damaged area from the abradable shroud, until only an area without damage is there. NOTE : All oil contaminated areas must be removed. ____ (2) Make the surface of the repair area rough with an abrasive cloth (Material No. CP2239) (3) Blow the dust out of the shroud or vacuum cleaner. Subtask 72-23-00-110-052 B. Degrease the Area WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY SHOULD _______ BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING. (1) Clean the area to be repaired with acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or magchem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B Subtask 72-23-00-340-051 C. Prepare the Base and Hardener for the Repair WARNING : PUT ON PROTECTIVE GLOVES WHEN YOU USE THE BASE AND HARDENER. IF _______ YOU DO NOT OBEY THIS PRECAUTION, INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR. (1) Mix, by weight, 100 parts of the base RTV 147 A (Material No. CP2297) and 10 parts of the catalyst (hardener) RTV 147 B (black color) (Material No. CP2298). (2) Stir the mixture by hand or mechanically until it becomes a homogenous compound. NOTE : The compound has a pot life of 2 hours after mixing, at ____ ambient temperature. (3) Apply the compound with a spatula. Lighthy hit the compound to remove the air bubbles (if any). Subtask 72-23-00-350-052 D. Cure the Compound with a heat gun or a infra-red lamp as follows: (1) 1 hour at 210 deg.F (98.9 deg.C). (2) 1/2 hour at 200 deg.F (93.3 deg.C). Subtask 72-23-00-320-054 E. Complete the Repair as follows: (1) Make sure the cured compound is constant in color. Make sure it does not contain air bubbles. (2) Use an abrasive cloth (Material No. CP2239) to make the repaired surface smooth with all adjacent areas of the abradable shroud. (3) Clean the repair area and the inlet cowl with a vacuum cleaner.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-083 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the fan blades (Ref. TASK 72-21-00-400-007). (3) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (4) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (5) Remove the protective mats from the inlet cowl. (6) Remove the access platform(s). (7) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/08
C F M 56-5B TASK 72-23-00-350-002 Removal of Rust from the Fan Frame Casing 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific
brush warning notice access platform 1 m (3 ft. 3 in.)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2189
Material No.
CP2208
Material No.
CP2442
* durite G422 (Ref. 70-30-00) * 3M-361 tape (Ref. 70-30-00) * engine oil (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-991-313
Fig. 801
3. __________ Job Set-up Subtask 72-23-00-941-081 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-097 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-23-00-040-064 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B Subtask 72-23-00-010-098 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 801/TASK 72-23-00-991-313) Subtask 72-23-00-140-051 A. Protect the fan duct panels with 3M-361 tape (Material No. CP2208). CAUTION : DAMAGE CAN RESULT IF ENGINE OIL IS SPREAD ON VARIABLE STATOR _______ VANE BUSHINGS OF THE COMPRESSOR FRONT STATOR. (1) Remove loose rust on hub and struts using a cloth. (2) If rust is still present, polish struts (radially) and hub using durite G422 (Material No. CP2189). (3) Coat the cleaned areas with engine oil (Material No. CP2442) using a cloth or brush. (4) Remove the masking tape from fan duct panels. 5. Close-up ________ Subtask 72-23-00-410-091 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-23-00-440-062 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Nov 01/08
C F M 56-5B
Fan Frame Casing - Rust Removal Figure 801/TASK 72-23-00-991-313 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B Subtask 72-23-00-410-092 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
C F M 56-5B TASK 72-23-00-300-042 Repair of Fan Duct Panel 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP5006
* austenite stainless steel wire - 321SS (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-000-027 72-23-00-400-027 SPM 70-32-11-23000500 SPM 70-41-11-35000900 SPM 70-45-11-31000200 72-23-00-991-314
Removal of the Fan Duct Panels Installation of the Fan Duct Panels
Fig. 802
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-082 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-092 B. Remove the fan duct panel (Ref. TASK 72-23-00-000-027). 4. Procedure _________ (Ref. Fig. 802/TASK 72-23-00-991-314) NOTE : This repair procedure provides instruction for reconditioning cracked ____ fan duct panels by weld buildup. Subtask 72-23-00-310-052 A. Stop the crack by drilling a 0.079 in. (2 mm) dia. hole at both ends. (1) Weld up the crack under argon atmosphere, and using weld wire austenite stainless steel wire - 321SS (Material No. CP5006). (Ref. SPM 70-45-11-31000200). (2) Check the welded area (Ref. SPM 70-32-11-23000500). (3) Flush the weld bead (Ref. SPM 70-41-11-35000900). (4) Perform a fluorescent inspection of the weld bead (Ref. SPM 70-32-1123000500).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B
Fan Duct Panels Figure 802/TASK 72-23-00-991-314 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-086 A. Close Access (1) Install the fan duct panel (Ref. TASK 72-23-00-400-027). (2) Make sure that the work area is clean and clear of tool(s) and other items. (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Nov 01/08
C F M 56-5B TASK 72-23-00-300-043 Repair of the Abradable (material) Shroud with Circular Patches CAUTION : THIS REPAIR MUST NOT BE DONE IN A HUMID ATMOSPHERE. THIS COULD AFFECT _______ THE QUALITY OF THE BONDING COMPOUND. THE MINIMUM AMBIENT TEMPERATURE MUST BE 60 DEG.F (15 DEG.C). 1. __________________ Reason for the Job General Defect more than 0.12 in. (3 mm) deep and 0.50 in.2 (3.2 cm2) and with fan case base metal exposed. This task refers to a procedure for the in-place of the abradable shroud by installation of circular patches 1.968 in. (50 mm) maximum diameter. NOTE : The following patch repair is estimated to take less than 3 hours in ____ the hangar when done by skilled mechanics familiarized with the procedure. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No No No No No
specific specific specific specific specific specific specific specific
clean, white cloth heat gun or infrared lamp or heatings panels paint brush protective mats scalpel vacuum cleaner warning notice access platform 0.5 m (1 ft. 8 in.)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2239
Material No.
CP2244
Material No.
CP2297
Material No.
CP2298
Material No.
CP2306
Material No.
CP2339
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) * abrasive cloth 3 M 301D grit size 80 or 120 (Ref. 70-30-00) * Primer 1200 (Ref. 70-30-00) * base RTV 147 A (Ref. 70-30-00) * catalyst (hardener) RTV 147B (black color) (Ref. 70-30-00) * heat-resistant tape 3 M No. 5490 (Ref. 70-30-00) * RTV 630 (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-400-005 72-21-00-400-006 72-21-00-400-007 72-23-00-991-317
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Installation of the Fan Rotor Blades Fig. 803
3. __________ Job Set-up Subtask 72-23-00-941-088 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-110 B. Get Access (1) Put an access platform in position. (2) Intall protective mats in the lower half of the inlet cowl. (3) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (4) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
C F M 56-5B (5) Remove a sufficient number of fan blades to get access to the repair area (Ref. TASK 72-21-00-000-007). 4. Procedure _________ (Ref. Fig. 803/TASK 72-23-00-991-317) Subtask 72-23-00-320-059 A. Repair of the Abradable Shroud with Circular Patches (1) Remove the unwanted pieces of abradable liner. (a) Punch out the abradable material to the base metal, at the location of the defect, maximum diameter 1.968 in. (50 mm). (b) Use a scalpel and abrasive cloth 3 M 301D grit size 80 or 120 (Material No. CP2239) to remove all pieces of the abradable material. (c) Blow the part clean with shop air. Subtask 72-23-00-110-054 B. Degrease Area WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY SHOULD _______ BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING. (1) Use the acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or magchem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) to remove the grease from the area to be repaired.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-23-00 CES
Page 819 Feb 01/09
C F M 56-5B
Repair of the Abradable Shroud With Circular Patches Figure 803/TASK 72-23-00-991-317- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 820 Nov 01/08
C F M 56-5B
Repair of the Abradable Shroud With Circular Patches Figure 803/TASK 72-23-00-991-317- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 821 Nov 01/08
C F M 56-5B Subtask 72-23-00-340-053 C. Apply the Abradable Liner Patch (1) Remove grease from the part with a clean, white cloth soaked in acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or magchem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656). (2) Prepare the bonding compound as follows: WARNING : PUT ON PROTECTIVE GLOVES WHEN YOU USE THE BASE AND _______ HARDENER. IF YOU DO NOT OBEY THIS PRECAUTION, INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR. NOTE : You must use the compound within 2 hours after it is mixed ____ (a) Mix 100 parts of base RTV 147 A (Material No. CP2297) with 10 parts of catalyst (hardener) RTV 147B (black color) (Material No. CP2298) or use RTV 630 (Material No. CP2339), at ambient temperature. (b) Stir the mixture manually or mechanically until it is fully mixed. (3) Apply the primer as follows: (a) Remove grease from the area to be repaired. (b) Apply the Primer 1200 (Material No. CP2244) on the degreased area of fan case with a clean, white cloth or a paint brush. (c) Allow to dry at ambient temperature for 45 minutes. NOTE : Too much primer will reduce adherence. Also do not touch ____ the primer after it is applied. (4) Prepare the abradable liner patch as follows: (a) From a (spare) new fan inlet case abradable cartridge (Ref. PIPC 72230065375), punch out a circular patch at the equivalent size of the defect. NOTE : In this repair, the maximum diameter dimension of the ____ patch is set at 1.968 inch (50 mm).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 822 Feb 01/09
C F M 56-5B (b) Lightly sand the underside and the edges of the patch with abrasive cloth 3 M 301D grit size 80 or 120 (Material No. CP2239). (c) Punch one hole with a diameter 0.118 inch (3 mm) at the center of the patch. Keep the 0.118 in. (3 mm) diameter piece of abradable. It will be used as a cap after the final application of the repair patch. NOTE : The hole of the center of the patch will do as a vent hole ____ during the application of the patch on the fan inlet case. (d) Degrease. WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY _______ SHOULD BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING. 1 _
Remove the grease with acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) .
2 _
Apply bonding compound on the case, on the underside and edges of the patch.
(e) Bond the patch. 1 _
Press strongly all around the little hole to remove unwanted compound and any air below the patch.
2 _
After the final application, plug the central hole with the cap.
3 _
Remove the mixture from the part surface with a white cloth before polymerization.
4 _
Hold the patch in place with heat-resistant tape 3 M No. 5490 (Material No. CP2306).
Subtask 72-23-00-350-055 D. Do the Polymerization as follows: (1) With an heat gun or infrared lamp or heatings panels heat the patch for 2 hours 15 minutes at 158 deg.F (70 deg.C) or 1 hour at 212 deg.F (100 deg.C) to cure the bonding compound.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 823 Feb 01/09
C F M 56-5B Subtask 72-23-00-210-065 E. Do a Last Check of the Abradable Liner (1) When you do the visual check, examine all joints and patch areas to make sure there are no defects as porosity or trapped air bubbles. (2) If you see defects, you do the repair again. Subtask 72-23-00-320-060 F. Complete the Repair as follows: (1) Hand finish the abradable liner. (a) Hand finish the reconditioned area to put it back to the contour and dimensions of the adjacent areas. (b) Sand lightly with an abrasive cloth 3 M 301D grit size 80 or 120 (Material No. CP2239). (2) Remove the abradable material dust and hand sanding residues from the repair area with a vacuum cleaner. 5. Close-up ________ Subtask 72-23-00-410-100 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the fan blades (Ref. TASK 72-21-00-400-007). (3) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (4) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (5) Remove the mats from the lower half from the inlet cowl. (6) Remove the access platform(s). (7) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 824 Feb 01/09
C F M 56-5B TASK 72-23-00-300-044 Repair of Forward, Mid and Aft Acoustical Panels when Unbounded Cup 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1040
Material No.
CP2242
Material No.
CP2266
Material No.
CP2431
* methyl-ethyl-ketone (Ref. 70-30-00) * RTV732 (Ref. 70-30-00) * RTV102 (Ref. 70-30-00) * RTV730 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-23-00-000-009 72-23-00-000-025 72-23-00-000-026 72-23-00-400-009 72-23-00-400-025 72-23-00-400-026 72-23-00-991-318
Removal of the Forward Acoustical Panels of the Fan Removal of the Mid Acoustical Panels Removal of the Aft Acoustical Panels Installation of the Forward Acoustical Panels of the Fan Installation of the Mid Acoustical Panels Installation of the Aft Acoustical Panels Fig. 804
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 825 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-098 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). (4) Put a warning notice to tell persons not to start the engine 1(2). (5) Put an access platform in position at the front of the engine. Subtask 72-23-00-010-124 B. Remove the forward or mid or aft acoustical panel (Ref. TASK 72-23-00000-009) or (Ref. TASK 72-23-00-000-025) or (Ref. TASK 72-23-00-000-026) 4. Procedure _________ (Ref. Fig. 804/TASK 72-23-00-991-318) Subtask 72-23-00-350-061 A. Repair the unbounded cup (1) Clean the repair area with methyl-ethyl-ketone (Material No. CP1040). (2) Apply RTV732 (Material No. CP2242) or RTV102 (Material No. CP2266) or RTV730 (Material No. CP2431) on the panel cup surface. (3) Install the cup on the forward or mid or aft acoustical panel. NOTE : You must install the acoustical panel in a short time after ____ you apply the RTV (before polymerisation).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 826 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-116 A. Close Access (1) Install the forward or mid or aft acoustical panel (Ref. TASK 72-2300-400-009) or (Ref. TASK 72-23-00-400-025) or (Ref. TASK 72-23-00400-026). NOTE : You must install the acoustical panel in a short time after ____ you apply the RTV (before polymerisation). (2) Make sure that the work area is clean and clear of tool(s) and other items. (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 827 Nov 01/08
C F M 56-5B
Fan Acoustical Panels Figure 804/TASK 72-23-00-991-318- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 828 Nov 01/08
C F M 56-5B
Fan Acoustical Panels Figure 804/TASK 72-23-00-991-318- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 829 Nov 01/08
C F M 56-5B
Fan Acoustical Panels Figure 804/TASK 72-23-00-991-318- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 830 Nov 01/08
C F M 56-5B TASK 72-23-00-300-045 Replacement of the Riveted Self Locking Nuts for the Attachment of the Forward Acoustical Panels 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------70 70 80 80 90 90 90 90 90
self-locking self-locking self-locking self-locking self-locking self-locking self-locking self-locking self-locking
nuts nuts nuts nuts nuts nuts nuts nuts nuts
72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00 72-23-00
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
25 25 25 25 25 25 25 25 25
-020 -020A -040 -040A -060 -060A -060B -060C -060D
Page 831 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-000-007 72-21-00-400-005 72-21-00-400-006 72-23-00-000-009 72-23-00-400-009 72-23-00-400-028 SPM 704311390003 SPM 704331390005 SPM 704450320006 72-23-00-991-319 72-23-00-991-322
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Removal of the Fan Rotor Blades Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Removal of the Forward Acoustical Panels of the Fan Installation of the Forward Acoustical Panels of the Fan Installation of the Splitter Fairing
Fig. 805 Fig. 806
3. __________ Job Set-up Subtask 72-23-00-941-099 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 832 Nov 01/08
C F M 56-5B Subtask 72-23-00-010-125 B. Get Access (1) Put an access platform in position. (2) Remove the spinner front cone (Ref. TASK 72-21-00-000-005). (3) Remove the spinner rear cone (Ref. TASK 72-21-00-000-006) (4) Remove a sufficient number of fan blades to get access to the repair area (Ref. TASK 72-21-00-000-007). (5) Remove the forward acoustical panel (Ref. TASK 72-23-00-000-009). 4. Procedure _________ (Ref. Fig. 805/TASK 72-23-00-991-319) Subtask 72-23-00-350-062 A. Replacement of the Riveted Self-Locking Nuts (Ref. Fig. 806/TASK 72-23-00-991-322) NOTE : If necessary, for the repair size rivets, drill at the same time ____ the rivet holes in the new nut you install and the rivet holes on the containment case (Ref. SPM 704311390003) or (Ref. SPM 704331390005). (1) Remove the rivet head with a 0.094 in. (2,4 mm) diameter drill (Ref. SPM 704450320006). (2) If you cannot remove the rivet head, use a 0.125 in. (3,2 mm) diameter drill related to the repair size rivet (Ref. SPM 704331390005) or (Ref. SPM 704450320006). (3) Do a check of the rivet holes (Ref. SPM 704331390005). (4) Install the new self-locking nuts self-locking nuts (70) or selflocking nuts (80) or self-locking nuts (90) on the containment case with new rivets (10) or (20) or (30) or (40) or (50) or (60) (Ref. SPM 704331390005).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 833 Nov 01/08
C F M 56-5B
Replacement of the Self Locking Nuts Figure 805/TASK 72-23-00-991-319 R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 834 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-23-00 CES
Page 835 Nov 01/08
C F M 56-5B
Dimensional Information for the Replacement of the Self Locking Nuts Figure 806/TASK 72-23-00-991-322- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 836 Nov 01/08
C F M 56-5B
Dimensional Information for the Replacement of the Self Locking Nuts Figure 806/TASK 72-23-00-991-322- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 837 Nov 01/08
C F M 56-5B
Dimensional Information for the Replacement of the Self Locking Nuts Figure 806/TASK 72-23-00-991-322- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 838 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-23-00-410-117 A. Close Access (1) Install the forward acoustical panel (Ref. TASK 72-23-00-400-009). (2) Install the fan blades (Ref. TASK 72-23-00-400-028). (3) Install the spinner rear cone (Ref. TASK 72-21-00-400-006). (4) Install the spinner front cone (Ref. TASK 72-21-00-400-005). (5) Make sure that the work area is clean and clear of tool(s) and other items. (6) Remove the access platform(s). (7) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 839 Nov 01/08
C F M 56-5B TASK 72-23-00-300-046 Replacement of Lateral Bracket Plate on the Junction Box 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific R
warning notice
B. Expendable Parts
R R R
------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN -------------------------------------------------------------------------------
R R
40 40
R
bracket plate bracket plate
72-00-00 05 -061 72-00-00 05 -062
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 SPM 70-21-12-110-003 SPM 70-32-21-230-010 SPM 70-41-11-350-009 SPM 70-43-11-390-003 SPM 70-43-32-390-006 72-23-00-991-323 72-23-00-991-324 72-23-00-991-325
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors
Fig. 807 Fig. 808 Fig. 809
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 840 Feb 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-23-00-941-106 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice in position to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-23-00-010-133 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): - FOR 1000EM1 437AL, 438AR - FOR 1000EM2 447AL, 448AR. 4. Procedure _________ (Ref. Fig. 807/TASK 72-23-00-991-323) Subtask 72-23-00-390-051 A. Removal of the Damaged Bracket Plate WARNING : METAL PARTICLES FROM DRILLING CAN CAUSE DAMAGE, INJURY OR _______ IRRITATION TO YOU. USE PERSONAL PROTECTION EQUIPMENT. (1) Drill to remove rivets from the riveted bracket plate (Ref. SPM 7043-32-390-006). (2) Do a visual inspection of the junction box. No crack is permitted.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 841 Feb 01/09
C F M 56-5B
R R
Replacement of Lateral Bracket Plate Figure 807/TASK 72-23-00-991-323
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 842 Nov 01/08
C F M 56-5B (3) Remove the riveted nuts (20) from the bracket plate you remove. WARNING : METAL PARTICLES FROM DRILLING CAN CAUSE DAMAGE, INJURY OR _______ IRRITATION TO YOU. USE PERSONAL PROTECTION EQUIPMENT. (a) Drill to remove the rivets (10) which attach the riveted nuts (20) (Ref. SPM 70-43-11-390-003). NOTE : Be careful not to damage the riveted nut. If the riveted ____ nut is damaged, install a new one. Subtask 72-23-00-420-073 B. Installation of the New Bracket Plate (1) Install the riveted nut (20) on the new bracket plate. (a) Do a visual inspection of the rivet holes in the tube bundle junction box (Ref. SPM 70-43-11-390-003). (Ref. Fig. 808/TASK 72-23-00-991-324) (b) Drill the rivet holes and the riveted nut. WARNING : METAL PARTICLES FROM DRILLING CAN CAUSE DAMAGE, INJURY _______ OR IRRITATION TO YOU. USE PERSONAL PROTECTION EQUIPMENT. 1 _
If necessary, drill again at the same time the rivet holes in the junction box and in the riveted nut you are to rivet (Ref. SPM 70-43-11-390-003). (Ref. Fig. 808/TASK 72-23-00-991-324)
(c) Put the riveted nut (20) in position and rivet it with two rivets (10) (Ref. SPM 70-43-11-390-003). NOTE : Make sure that the rivet head does not come out of its ____ recess. If necessary, grind it smooth with the surface. (2) Put the new bracket plate (40) in position on the junction box. (Ref. Fig. 808/TASK 72-23-00-991-324) and (Ref. Fig. 809/TASK 72-23-00-991-325) (3) Drill the rivet holes and the riveted nut. WARNING : METAL PARTICLES FROM DRILLING CAN CAUSE DAMAGE, INJURY OR _______ IRRITATION TO YOU. USE PERSONAL PROTECTION EQUIPMENT.
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 843 Feb 01/09
C F M 56-5B
R R
Location of the Riveted Holes Figure 808/TASK 72-23-00-991-324- 13 (SHEET 1)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 844 Nov 01/08
C F M 56-5B
R R
Location of the Riveted Holes Figure 808/TASK 72-23-00-991-324- 23 (SHEET 2)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 845 Nov 01/08
C F M 56-5B
R R
Location of the Riveted Holes Figure 808/TASK 72-23-00-991-324- 33 (SHEET 3)
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 846 Nov 01/08
C F M 56-5B
R R
Dimension Information of Position Figure 809/TASK 72-23-00-991-325
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, CES
Page 847 Nov 01/08
C F M 56-5B (a) Drill at the same time the rivet holes in the junction box and in the bracket plate (40) (Ref. SPM 70-43-32-390-006). (Ref. Fig. 808/TASK 72-23-00-991-324) (4) Do a fluorescent inspection of the holes (Ref. SPM 70-32-21-230-010). No crack is permitted. (5) Do a hand blending of the contact areas (Ref. SPM 70-41-11-350-009). (6) Remove the grease from the junction box contact area and the bracket plate (Ref. SPM 70-21-12-110-003). (7) Put the new bracket plate (40) in position and rivet it with six rivets (30) (Ref. SPM 70-43-32-390-006). 5. Close-up ________ Subtask 72-23-00-410-126 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): - FOR 1000EM1 437AL, 438AR - FOR 1000EM2 447AL, 448AR. (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-23-00 201-249, 251-299, 301-399, 401-499, R CES
Page 848 Feb 01/09
C F M 56-5B HP COMPRESSOR SECTION - DESCRIPTION AND OPERATION _________________________________________________ 1. _______ General (Ref. Fig. 001) The major components of the compressor are : compressor rotor and compressor stator. The front of the compressor stator is supported by the fan frame and the front of the compressor rotor is supported by the No.3 bearing in the fan frame. The rear of the compressor stator is attached to the combustion case and the rear of the compressor rotor is attached to the HPT rotor to form the core rotor. The rear of the core rotor is supported by the No.4 bearing. A portion of the fan discharge airflow passes thru the booster to the compressor. Compression is progressive as the primary airflow moves from stage through the axial compressor. Air passes through successive stages of compressor rotor blades and compressor stator vanes, being compressed as it passes from stage to stage. After passing through 9 stages of blades, the air has been compressed. The inlet guide vanes and the first 3 stages of the stator are variable, and change their angular position as a function of compressor inlet temperature and engine speed. The purpose of this variability is to optimize efficiency and stall margin for engine speed, compressor inlet temperature and pressure conditions.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-30-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
HP Compressor Section Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-30-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B HP COMPRESSOR SECTION - REMOVAL/INSTALLATION ____________________________________________ TASK 72-30-00-920-001 Discard Life Limited HP Compressor rotating parts 1. __________________ Reason for the Job Refer to the MPD TASK: 723000-C1 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-00-00-400-042 ESM 051102 ESM 723104 ESM 723105 ESM 723106 ESM 723107 ESM 723108
Removal of the Power Plant Installation of the Power Plant
3. __________ Job Set-up Subtask 72-30-00-010-052 A. Remove the engine (Ref. TASK 71-00-00-000-042). 4. Procedure _________ Subtask 72-30-00-020-052 A. Remove and discard life - (Ref. ESM 723104) for - (Ref. ESM 723105) for - (Ref. ESM 723106) for - (Ref. ESM 723107) for - (Ref. ESM 723108) for
limited the HPC the HPC the HPC the HPC the HPC
parts of the high pressure compressor: Stage 1-2 Spool Stage 3 Disk Stage 4-9 Spool rotor Shaft CDP Seal
NOTE : (Ref. ESM 051102) for time limits. ____
R EFF : 001-049, 051-099, 101-149, 151-199, 72-30-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-30-00-410-052 A. Install the engine (Ref. TASK 71-00-00-400-042).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-30-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Nov 01/08
C F M 56-5B HPC ROTOR ASSEMBLY - DESCRIPTION AND OPERATION ______________________________________________ 1. _______ General (Ref. Fig. 001) The compressor rotor (C/R) is a 9-stage, high-speed, unitized spool-disk structure. The rotor consists of 5 major parts : front shaft, stages 1-2 spool, stage 3 disk, stages 4-9 spool, and C/R rear (compressor discharge pressure (CDP)) rotating air seal. Spools are assembled by inertia welding. The front shaft, disk, and spools are joined at a single bolted joint to form a smooth, rigid unit. Interfering rabbeted diameters are used for proper positioning of parts and for rotor stability. 2. ___________ Description (Ref. Fig. 001, 002) A. Front Shaft The front shaft is bolted between stages 1-2 spool and stage 3 disk, and is the forward support for the rotor. The shaft is splined to and secured to the inlet gearbox (IGB) horizontal bevel gear by a coupling nut. The IGB contains the thrust bearing for the core engine. The front shaft is made of titanium alloy. B. Disk and Spools The stages 1-2 spool and stage 3 disk are made of titanium alloy forgings and retain the stages 1, 2, and 3 blades in axial slots. The stages 4-9 spool is made of a nickel alloy and retains stages 4 through 9 blades in circumferential grooves. The disk and stages 4-9 spool are internally cooled by low pressure compressor (booster) discharge air which enters the rotor through holes in the front shaft. Abrasive coated seals between the rotor blade stages improve compressor performance. C. Blades Blades in stages 1, 2 and 3 are made of a titanium alloy. Blades in stages 4 through 9 are made of a nickel alloy. The first 3 stages of blades are secured in the disk and spool axial slots by retaining rings ; blades in the stages 4-9 spool are secured in the circumferential grooves by locking lugs. All blades are replaceable without disassembling the rotor. D. Rear Seal The compressor rotor rear rotating (CDP) air seal is a one-piece nickel alloy forged part with abrasive, protective-coated sealing teeth. The seal is mounted to the aft flange of the stages 4-9 spool by a tight fitting rabbet diameter and is axially clamped by the bolts and nuts securing the forward flange of the high pressure turbine rotor to the compressor.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Compressor Rotor Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
HP Compressor Rotor Section Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B HPC ROTOR ASSEMBLY - INSPECTION/CHECK _____________________________________ TASK 72-31-00-290-002 Inspection of the High Pressure Compressor Rotor Assembly 1. __________________ Reason for the Job Inspection of a high pressure compressor rotor (HPCR) with the stator case installed is limited to those areas that can be seen with a rigid borescope. There are nine borescope ports (S1 through S9) in the compressor stator case, between the 4 and 5 oclock position, aft looking forward. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No No
specific specific specific specific specific specific
No specific No specific 856A1084 856A1320 856A1321 856A1322 856A1323 856A1488
1 1 1 1 1 1
caps on the cart hoses container warning notice 0.75 in. square drive socket 2ft. long breaker bar Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) CART-STATOR ACTUATOR BORESCOPE-KIT FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE MOTOR, DRIVE - CORE ENGINE ROTATION
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Page 601 Feb 01/10
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R
71-00-00-710-001 71-00-00-710-006 71-13-00-010-040 71-13-00-410-040 72-00-00-200-005 72-00-00-200-025 72-31-00-300-002 72-31-00-300-004 72-63-00-000-002 72-63-00-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-000-002 80-11-10-400-002 NTM 720000 72-31-00-991-300 72-31-00-991-301 72-31-00-991-302 72-31-00-991-309 72-31-00-991-306 72-31-00-991-307 72-31-00-991-308
Dry Motoring Check Minimum Idle Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Over-Serviceable-Limit Extensions Repair of Broken Borescope Plug Blend Repair of the High Pressure Compressor (HPC) Rotor Blades Stages 1-9 Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. Fig. Fig. Fig. Fig. Fig. Fig.
601 602 603 604 605 606 607
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Page 602 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-31-00-991-310 72-31-00-991-315
Fig. 608 Fig. 609
3. __________ Job Set-up Subtask 72-31-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-31-00-010-055 B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. Subtask 72-31-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-31-00-010-056 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR.
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Page 603 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-31-00-991-300, 602/TASK 72-31-00-991-301, 603/TASK 72-31-00-991-302, 604/TASK 72-31-00-991-309, 605/TASK 72-31-00-991-306, 606/TASK 72-31-00-991-307, 607/TASK 72-31-00-991-308, 608/TASK 72-31-00-991310) Subtask 72-31-00-410-055 A. Do a borescope installation: (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure that the borescope or fiberscope and light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Install the tools to turn the core engine. NOTE : The core engine may be turned using a breaker bar (see step ____ (a)) or with a drive motor (see step (b)). (a) To turn the core manually with a breaker bar, do the steps that follow: 1 _
Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter. (Ref. TASK 72-63-00-000-002)
2 _
Install a 0.75 in. square drive socket with a 2ft. long breaker bar into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward). NOTE : To turn the core engine CW, the handcranking drive must ____ be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 _
Remove the starter (Ref. TASK 80-11-10-000-002).
2 _
Install the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P0/P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad drive shaft and engage the splines. NOTE : The tool must be installed in the horizontal position ____ with the air hoses to the rear.
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Page 604 Nov 01/08
C F M 56-5B
Core Rotation Drive Motor Installation Figure 601/TASK 72-31-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
VSV System Connections at the HMU Figure 602/TASK 72-31-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Borescope Ports of the High-Pressure Compressor Figure 603/TASK 72-31-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B
Removal of IGV Borescope Plug (S1) Figure 604/TASK 72-31-00-991-309 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B
HPC Rotor Indexing to Zero Figure 605/TASK 72-31-00-991-306 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B
Locally Manufactured Alignment Rod Figure 606/TASK 72-31-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B
Locally Manufactured Deep Socket Wrench Figure 607/TASK 72-31-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B
Compressor Blades Inspection Figure 608/TASK 72-31-00-991-310- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B
Compressor Blades Inspection Figure 608/TASK 72-31-00-991-310- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B 3 _
Turn the tool until the captive bolts align with the gearbox bolt holes.
4 _
Tighten the two captive bolts by hand.
5 _
Install the clamp to secure the drive motor.
6 _
Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 _
Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(3) Actuate the VSV system to the full open position as follows: WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE YOUR _______ CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. CAUTION : USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE NIPPLE _______ WHEN YOU DISCONNECT/CONNECT FUEL LINES ON NIPPLES. NOTE : Put a container under the HMU to catch fuel released when fuel ____ lines are disconnected. NOTE : If the CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) is ____ not available, the VSV system may be actuated to the full open position on an exceptional basis by dry motoring the engine (Ref. TASK 71-00-00-710-001). (a) Disconnect the VSV rod-end and head-end flex-hoses from the hydromechanical unit (HMU). (b) Remove the caps from the CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04). (c) Attach the rod-end and head-end hoses from the cart to rod-end and head-end connectors of the rod-end and head-end hoses you disconnected from the HMU. (d) Actuate the variable stator system CAUTION : DO NOT LET THE PRESSURE BE MORE THAN 300PSI (20.68BAR) _______ OR YOU WILL CAUSE DAMAGE TO ENGINE PARTS.
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Page 614 Nov 01/08
C F M 56-5B 1 _
Pump the actuator until the VSV system is at the open position (actuator rod retracted).
(e) Disconnect the CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04). WARNING : PRESSURE OF UP TO 300 PSI. (20.68 BAR) EXISTS IN THE _______ SUPPLY LINES. RELIEVE PRESSURE TO PREVENT INJURY WHEN DISCONNECTING FITTINGS. 1 _
Follow the instructions for use of the CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) to relieve any static pressure existing in the supply hoses. Gages on the CART-STATOR ACTUATOR (856A1084G02 or 856A1084G04) should read zero and the selector valve should be in the OFF position.
2 _
Disconnect the hoses of the cart from the rod-end and head-end hoses.
3 _
Install the caps on the cart hoses.
(f) Connect the rod-end and head-end hoses to the HMU. CAUTION : USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE _______ NIPPLE WHEN YOU DISCONNECT/CONNECT FUEL LINES ON NIPPLES. 1 _
TORQUE the head-end hose to between 450 and 550 lbf.in (5.08 and 6.21 m.daN).
2 _
TORQUE the rod-end hose to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
(4) Remove the borescope plugs from the stages to be inspected as follows. Tag each borescope plug to identify the stage from which it was removed: NOTE : The borescope plugs are located along the compressor case ____ between the 4 and 5 oclock positions, aft looking forward. (a) Cut and remove the lockwire from the borescope plugs to be removed. (b) Remove the IGV borescope plug (S1), if necessary, as follows: 1 _
Remove the two screws (20) that attach the borescope access blanking plate (10) at 5 oclock, aft looking forward, on the fan frame inner flange.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B 2 _
Remove the borescope access blanking plate (10).
3 _
Remove the IGV borescope plug (S1).
4 _
Tag the plug to ensure it will be reinstalled in the correct port.
(c) Remove the stage 1 through stage 5 borescope plugs (S2 through S6), as necessary. Tag each plug to ensure it will be reinstalled in the correct port. (d) Remove the stage 6, 7 and 8 borescope plugs (S7 through S9), as necessary, as follows: CAUTION : DO NOT PUT MORE THAN 280 lbf.in. (31.64 m.daN) OF _______ TORQUE ON THE 6TH, 7TH AND 8TH STAGE BOROSCOPE PLUGS WHEN YOU REMOVE THEM, OR THE INNER PLUG SHAFT COULD BREAK. 1 _
Loosen the outer borescope plug.
2 _
Pull the outer borescope plug straight out as far as possible to engage the internal shaft spline.
3 _
Remove the borescope plug.
4 _
Tag each plug to ensure it will be reinstalled in the correct port.
5 _
If the borescope plug is broken or if the inner plug does not come out with the outer plug, remove the broken inner plug with a deep socket wrench (Ref. TASK 72-31-00-300-002).
(5) Connect the fiber light cable to the fiberscope (green or blue band) from the BORESCOPE-KIT (856A1320P04 or P05) and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P01 through P07). Turn the light source on. (6) If you use the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02) to turn the core engine, do an inspection of the compressor blades as follows. If you use the breaker bar to turn the core, go to step (7). (a) Index the core engine to zero as follows: 1 _
Put the fiberscope into the stage 3 borescope port (S4) and look aft to the stage 4 compressor blade platform.
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Page 616 Nov 01/08
C F M 56-5B 2 _
While you look in the fiberscope turn the core clockwise (CW), as seen from the front of the engine, using the MOTOR, DRIVE CORE ENGINE ROTATION (856A1488P01 or P02).
3 _
Turn the core until you see the first blade slot locking lug.
4 _
Continue to turn the core until you see the second locking lug. The second locking lug is 2 blades past the first locking lug.
5 _
Align the leading edge of the first blade past the second locking lug with the leading edge of the nearest stage 4 vane. This is the zero index point and blade number 1.
6 _
Set the pointer on the protractor to the zero degree mark. The core engine is now set to the zero index point for inspection of all stages of the compressor rotor.
(b) Do an inspection of stage 4 compressor blades while you turn the core engine using the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02). (c) Use the limits found in step 4.B. (d) Remove the fiberscope (e) Insert the fiberscope in the borescope plug of the next stage to be inspected and repeat step (b) thru (d) for the other stages to be inspected. (f) If the vane segments in stages 6, 7 and 8 have moved to partially cover the borescope port, do step (8). (7) If you use the breaker bar to turn the core engine, do an inspection of the compressor blades as follows. (a) Insert the fiberscope in the borescope port of the stage you want to inspect. (b) Do an inspection of the compressor blade you see. Use the limits found in the inspection table. (c) Rotate the core engine so that you can see the next blade. Use the breaker bar to turn the core engine clockwise (CW). NOTE : To turn the core engine CW, the handcranking drive must be ____ turned counterclockwise (CCW).
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Page 617 Nov 01/08
C F M 56-5B (d) Repeat steps (b) and (c) until you have inspected all of the blades in that stage. Count the blades as you inspect them to make sure all of the compressor blades are inspected. The number of blades in each stage is: 1 _
Stage 1 : 38 blades
2 _
Stage 2 : 53 blades
3 _
Stage 3 : 60 blades
4 _
Stage 4 : 68 blades
5 _
Stage 5 : 75 blades
6 _
Stage 6 : 82 blades
7 _
Stage 7 : 82 blades
8 _
Stage 8 : 80 blades
9 _
Stage 9 : 76 blades
(e) Repeat steps (a) thru (d) for the other stages to be inspected. (f) If the vane segments in stages 6, 7 and 8 have moved to partially cover the borescope holes (S7 through S9), do step (8). (8) To inspect the stages 6, 7, 8 and 9 blades when the vane segments have moved to partially cover the borescope holes, use the alternatives that follow: CAUTION : MAKE SURE THE FLEXIBLE BORESCOPE DOES NOT GET CAUGHT IN THE _______ BLADES WHILE YOU TURN THE CORE. (a) If the diameter of the borescope holes are larger than 0.24 in. (6.01 mm) , do the borescope inspection using the FIBERSCOPE SET (856A1321P01 through P03). (b) If the diameter of the borescope holes are less than 0.24 in. (6.01 mm) , do the following steps: 1 _
Put a tapered rod in the borescope hole. The rod must be made from 0.37 in. (9.40 mm) diameter aluminum, 18 in. (0.46 mm) long, with a 4 in. (101.60 mm) taper at one end. The tapered end must be rounded to 0.062 in. (1.57 mm) radius, accurate radius not necessary.
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Page 618 Nov 01/08
C F M 56-5B 2 _
Apply a light downward force on the end of the tapered rod to move the vane segments.
(c) If the stage 7 borescope hole (S8) is not fully open, inspect the aft part of the compressor through the stage 8 borescope hole (S9). If the stage 8 borescope hole (S9) is not fully open, try to do the inspection through the stage 6 borescope port (S7). Subtask 72-31-00-290-051 B. Inspect the blades to the limits that follow: (Ref. Fig. 608/TASK 72-31-00-991-310, 609/TASK 72-31-00-991-315) NOTE : If you find airfoil damage, we recommend that you do a borescope ____ inspection of the stage 5 booster blades and the abradable (Refer to CFM SB 72-03910). NOTE : The depth of a defect such as a nick is measured along the axis of ____ the damage unless otherwise noted. NOTE : Unless otherwise identified, all damage limits for high pressure ____ compressor blades are the same for the different blade configurations. ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Stages 1-4 compressor blades: A. Cracks in Dim. A and tip
Any number of radial cracks within 0.30 in. (7.6 mm) of the leading or trailing edge, up to 0.25 in. (6.4 mm) in length are serviceable
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
Any number of radial cracks more than 0.30 in. (7.6 mm) from the leading or trailing edge, up to 0.10 in. (2.5 mm) in length are serviceable
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Page 619 Nov 01/08
C F M 56-5B
R
Stage 1-3 VSV Shroud Rubbing Figure 609/TASK 72-31-00-991-315
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Page 620 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------Any number of chord-wise See limit extensions cracks, up to 0.30 in. (Ref. TASK 72-00-00-200(7.6 mm) from the tip, 025) or repair (Ref. TASK up to 0.2 in. (5.1 mm) 72-31-00-300-004). in length are serviceable B. Missing or chipped erosion coating
Any amount
C. Tears on the leading and trailing edge found in Dim. B
Not serviceable
See repair (Ref. TASK 7231-00-300-004).
Any number if the damage is less than 0.04 in. (1.0 mm)
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
R R R R R
D. Nicks, missing material and erosion on the leading and trailing edge found in Dim. B, il the HPC blade is not a Tech Insertion Stage 4 blade (PN P394XXX)
R R R R R R R R R R
E. Nicks, missing material and erosion on the leading and trailing edge found in Dim. B, if the HPC blade is a Tech Insertion Stage 4 blade (PN P394XXX)
Any number, if the damage is less than 0.030 in. (0.8 mm) in depth
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004)
R
F. Dents on the leading or trailing edge found in Dim. B
Any amount if the damage is less than 0.04 in. (1.0 mm) in depth or up to 0.06 in. (1.5 mm) deflection from the original contour
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
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Page 621 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Nicks, dents and Any number if less than See limit extensions tears on the 0.25 in. (6.4 mm) in (Ref. TASK 72-00-00-200leading and depth 025). trailing edge tip corners in Dim. A
R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R
H. Missing material and erosion at the leading and trailing edge tip corners in Dim. A and tip
a) Individual blades with missing material more than 0.30 x 0.30 inch (7.6 x 7.6 mm) on both leading and trailing edges are not permitted. b) Any number of blades for each stage 1 thru 4, up to 0.30 x 0.30 inch (7.6 x 7.6 mm) if the downstream damage is serviceable. c) For stage 2, a maximum of 4 blades up to 0.40 x 0.40 inch (10.2 x 10.2mm), and 46 blades up to 0.30 x 0.30 inch (7.6 x 7.6mm) for total of 50 blades with missing tip corners. d) For stage 3, a maximum of 5 blades up to 0.40 x 0.40 inch (10.2 x 10.2mm) and 51 blades up to 0.30 x 0.30 inch (7.6 x 7.6 mm) for a total of total of 56 blades with missing tip corners.
See limit extensions (Ref. TASK 72-00-00-200025).
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Page 622 Feb 01/10
R R R R R R R R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------e) For stage 4, maximum of 6 blades up to 0.40 x 0.40 inch (10.2 x 10.2mm) and 57 blades up to 0.30 x 0.30 inch (7.6 x 7.6 mm) for a total of total of 63 blades with missing tip corners
R
J. Curl on the end of the airfoil
Up to 25% of chord, maximum radial length of 0.30 in. (7.6 mm) when it does not engage the stationary parts during operation
R
K. Nicks, dents and scratches of the airfoil root radius (does not include the trailing edge root radius of stage 2 and stage 3).
Any amount, if less than 0.003 in. (0.08 mm) in depth. Scratches parallel with the platform are not serviceable.
R
L. Nicks, dents and scratches of the trailing edge root radius of stage 2 and stage 3.
Any amount, if less than 0.03 in. (0.8mm) in depth.
R
M. Tears on the leading and trailing edge found in the lower 25% of the airfoil (but not the root radius)
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025).
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 623 Feb 01/10
R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------N. Nicks, dents and Any amount if the damage See limit extensions missing material is less than 0.03 in. (Ref. TASK 72-00-00-200on the leading and (0.76 mm) in depth. 025). trailing edge of the lower 25% of the airfoil (but not the root radius) Wear or scratches on trailing edge platform of stages 2 and 3
Any amount, if less than 0.03 in. (0.8 mm) in depth.
See limit extensions (Ref. TASK 72-00-00-200025).
Up to 25% of the blades across stages 5 through 9 can have radial cracks that are within 0.20 in. (5.1 mm) from the leading or trailing edge. These cracks can be up to 0.15 in. (3.8 mm) in length.
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
2. Stages 5-9 compressor blades: A. Cracks in Dim. A and tip
Radial cracks more than 0.20 in. (5.1 mm) from the leading or trailing edge are not serviceable Up to 25% of the blades across stages 5 through 9 can have chord-wise cracks that are no more than 0.20 in. (5.1 mm) from the tip. These cracks can be up to 0.15 in. (3.8 mm) in length B. Missing or chipped erosion coating
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
Any amount
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 624 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Nicks, tears, Any number if the damage See limit extensions missing material is less than 0.04 in. (Ref. TASK 72-00-00-200and erosion on the (1.0 mm) 025) or repair (Ref. TASK leading and 72-31-00-300-004). trailing edge found in Dim. B D. Dents on the leading and trailing edge found in Dim. B
Any number if the damage is less than 0.04 in. (1.0 mm) in depth or 0.06 in. (1.5 mm) deflection from the original contour
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
E. Nicks, dents and tears on the leading and trailing edge found in Dim. A
Any number is serviceable if the damage is less than 0.15 in. (3.8 mm)
See limit extensions (Ref. TASK 72-00-00-200025) or repair (Ref. TASK 72-31-00-300-004).
F. Missing material and erosion at the leading and trailing edge tip corners
All blades, up to 0.15 x 0.15 in. (3.8 x 3.8 mm), if downstream damage is serviceable. A maximum of 25 blades across stages 5 through 9 up to 0.2 x 0.2 in. (5 x 5 mm).
See limit extensions (Ref. TASK 72-00-00-200025).
G. Curl on the end of the airfoil
Up to 50% of chord maximum radial length 0.30 in. (7.6 mm) when it does not engage the stationary parts during operation
See limit extensions (Ref. TASK 72-00-00-200025).
H. Nicks, dents and scratches on the airfoil root radius
Any amount if less than 0.003 in. (0.10 mm) in depth. Scratches parallel with the platform are not serviceable.
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, R CES
Page 625 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------J. Tears on the Not serviceable leading and trailing edge found in the lower 25% of the airfoil (but not the root radius) K. Nicks, dents and missing material on the leading and trailing edge of the lower 25% of the airfoil (but not the root radius)
Any amount if the damage is less than 0.03 in. (0.76 mm)
See limit extensions (Ref. TASK 72-00-00-200025).
3. Stages 1-9 compressor blade tips: A. Tears, nicks, dents, missing material, erosion, bending and burrs
Any number or amount is serviceable
NOTE : The blade tip is the top 0.10 in. (2.5 mm) of the blade. ____ B. Nick and dents on the airfoil center panel
Any number if the damage is not cracked on the opposite side of the airfoil
C. Erosion and scratches on the airfoil center panel
Any amount
D. Material on the blade
Any amount
4. Platform of stages 4-9 locking blades.
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, R CES
Page 626 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Clearance between Serviceable the blade platforms B. Distortion on the blades
Any amount
C. Cracks
Not serviceable
D. Shingling
Not serviceable
5. Blade locks for stages 4-9 blades: R R R
A. Cracks
One lock with a crack is permitted
See limit extensions (Ref. TASK 72-00-00-200005)
R R R R
B. Looseness
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200005)
6. Stator flow path: A. Missing rub coating
Any amount
B. Cracks which are crazed
Any amount
NOTE : The area adjacent to the borescope ports is the only rub coat you ____ can examine. 7. Stages 1 through 3 compressor stator variable vane shrouds A. Wear caused by rubbing on vanes
Any amount
8. HPC Inner Shroud Lip for:
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Wear from Any amount rotor-stator contact Subtask 72-31-00-010-057 C. Remove the borescope equipment (1) When inspection is complete, turn the lamp switch off. Keep the main light source blower on until the lamp and housing cools down. (2) Before you install the borescope plugs, put the 0.37 in. (9.40 mm) diameter tapered rod into the borescope hole. This will make sure the hole is open. (3) Install the IGV borescope plug (S1) as follows: (a) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads and pressure face of the borescope plug. (b) Put the borescope plug in the correct borescope port. Tighten the plug by hand. (c) TORQUE the plug to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (d) Wirelock the plugs with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (e) Install the borescope access blanking plate (10) using the two screws (20). (4) Install the stage 1 through 5 borescope plugs (S2 through S6) as follows: (a) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads and pressure face of the borescope plugs. (b) Install the borescope plug in the borescope port. Tighten the borescope plug by hand.
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, R CES
Page 628 Feb 01/10
C F M 56-5B (c) TORQUE the borescope plugs to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (d) Wirelock the borescope plugs. Use lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (5) Install the stage 6, 7 and 8 borescope plugs (S7, S8 and S9) as follows: CAUTION : MAKE SURE YOU FULLY SCREW THE INNER CAP IN. IF NOT FULLY _______ SCREWED IN, THE INNER CAP OF THE BORESCOPE PLUG WILL DEFLECT THE COMPRESSOR REAR CASE AS THE OUTER CAP IS TIGHTENED. THIS WILL CAUSE BINDING OF THE COMPRESSOR ROTOR. (a) Make sure the borescope port is open. Insert the 0.37 in. (9.40 mm) diameter tapered rod in the borescope port. (b) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads and pressure face of the borescope plugs. (c) Put the plug in the correct borescope port and tighten the inner plug by hand. Use the outer plug to turn the inner plug. (d) TORQUE the inner plug to between 90 and 100 lbf.in (1.01 and 1.13 m.daN). Loosen half a turn and RETORQUE to between 15 and 20 lbf.in (0.16 and 0.22 m.daN) more than the running torque. (e) Compress the plug spring and tighten the outer plug by hand. NOTE : If the inner plug is correctly installed and the threads ____ are not damaged, you can install the outer plug by hand. If the outer plug cannot be fully installed by hand, the inner plug is not correctly installed. Remove the plug and repeat steps (c), (d) and (e). (f) TORQUE the outer plug to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (g) Wirelock all 3 outer plugs together with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002).
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, R CES
Page 629 Feb 01/10
C F M 56-5B (6) Remove the tools used to rotate the core as follows: NOTE : If the breaker bar is installed, see steps (a) and (b). If the ____ drive motor is installed, see steps (c) and (d). (a) Remove the 0.75 in. square drive socket and 2ft. long breaker bar from the handcranking drive pad. (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002). (c) Remove the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02) from the starter pad of the AGB. (d) Install the starter (Ref. TASK 80-11-10-400-002). 5. Close-up ________ Subtask 72-31-00-410-057 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-31-00-710-054 B. If fuel or oil lines were disconnected, do a minimum idle leak check (Ref. TASK 71-00-00-710-006) and check for leaks. Subtask 72-31-00-440-052 C. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 630 Feb 01/10
C F M 56-5B Subtask 72-31-00-410-058 D. Close Access (1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 631 Feb 01/10
C F M 56-5B HPC ROTOR ASSEMBLY - REPAIRS ____________________________ TASK 72-31-00-300-002 Repair of Broken Borescope Plug 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No R R
specific specific specific specific
deep socket wrench warning notice T-handle 0.37 in. (9.40mm) diameter tapered Rod (locally purchased) access platform 1 m (3 ft. 3 in.) Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
No specific No specific No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
* graphite grease (Ref. 70-30-00) * Never seez-pure (Ref. 70-30-00) * Safetywire 0.032 in.(0.8 mm) dia. (Ref. 70-30-00) * Safetywire 0.032 in.(0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Feb 01/10
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-31-00-991-304 72-31-00-991-305
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 801 Fig. 802
3. __________ Job Set-up Subtask 72-31-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-31-00-010-058 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B (2) Put the access platform in position. Subtask 72-31-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-31-00-010-059 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 801/TASK 72-31-00-991-304, 802/TASK 72-31-00-991-305) Subtask 72-31-00-300-051 A. Remove the broken borescope plug as follows: (1) Remove the retaining ring, if necessary. (2) Install the locally manufactured deep socket wrench on the inner plug. (Ref. Fig. 802/TASK 72-31-00-991-305) (3) Install a T-handle on the socket wrench. (4) Remove the borescope plug. Subtask 72-31-00-420-064 B. Install a replacement borescope plug as follows: (1) Install the stage 1 through 5 borescope plugs (S1 through S5) as follows: (a) Apply graphite grease (Material No. CP2101) Never seez-pure (Material No. CP2619) to the threads and pressure face of the borescope plug. (b) Install the borescope plug in the borescope port. Tighten the borescope plug by hand.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B
Locally Manufactured Deep Socket Wrench Figure 801/TASK 72-31-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B
Broken Borescope Plug Removal Figure 802/TASK 72-31-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/08
C F M 56-5B (c) TORQUE the borescope plug to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (d) Wirelock the borescope plug. Use Safetywire 0.032 in.(0.8 mm) dia. (Material No. CP8001) or Safetywire 0.032 in.(0.8 mm) dia. (Material No. CP8002). (2) Install the stage 6, 7 and 8 borescope plugs (S6, S7 and S8) as follows: CAUTION : MAKE SURE YOU FULLY SCREW THE INNER CAP IN. IF NOT FULLY _______ SCREWED IN, THE INNER CAP OF THE BORESCOPE PLUG WILL DEFLECT THE COMPRESSOR REAR CASE AS THE OUTER CAP IS TIGHTENED. THIS WILL CAUSE BINDING OF THE COMPRESSOR ROTOR. (a) Make sure the borescope port is open. Insert 0.37 in. (9.40mm) diameter tapered Rod (locally purchased) in the borescope port. (b) Apply graphite grease (Material No. CP2101) or Never seez-pure (Material No. CP2619) to the threads and pressure face of the borescope plug. (c) Put the plug in the correct borescope port and tighten the inner plug by hand. Use the outer plug to turn the inner plug. (d) Torque the inner plug to between 75 and 85 lbf.in (0.84 and 0.96 m.daN). Loosen half a turn and RETORQUE to between 15 and 20 lbf.in (0.16 and 0.22 m.daN). (e) Compress the plug spring and tighten the outer plug by hand. NOTE : If the inner plug is correctly installed and the threads ____ are not damged, you can install the outer plug by hand. If the outer plug cannot be fully installed by hand , the inner plug is not correctly installed. Remove the plug and repeat steps (c), (d) and (e). (f) TORQUE the outer plug to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (g) Wirelock all 3 outer plugs together with Safetywire 0.032 in.(0.8 mm) dia. (Material No. CP8001) or Safetywire 0.032 in.(0.8 mm) dia. (Material No. CP8002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-31-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-31-00-440-053 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-31-00-410-059 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B TASK 72-31-00-300-004 Blend Repair of the High Pressure Compressor (HPC) Rotor Blades Stages 1-9 1. __________________ Reason for the Job This TASK is the blend repair of the HPC rotor blades with a borescope blend tool. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific R R
warning notice CCD video camera and monitor (Wolf Compatible) HPC, blade, borescope, blending tool (Wolf tool 5.08036.00) access platform 1 m (3 ft. 3 in.) Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
No specific No specific No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Feb 01/10
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-710-006 71-13-00-010-040 71-13-00-410-040 72-63-00-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-400-002 72-31-00-991-311 72-31-00-991-312 72-31-00-991-313 72-31-00-991-314
Minimum Idle Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Installation of the Handcranking Drive Cover Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Installation of the Pneumatic Starter Fig. 803 Fig. 804 Fig. 805 Fig. 806
3. __________ Job Set-up Subtask 72-31-00-941-057 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B Subtask 72-31-00-010-064 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-31-00-040-055 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-31-00-010-065 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 803/TASK 72-31-00-991-311, 804/TASK 72-31-00-991-312, 805/TASK 72-31-00-991-313, 806/TASK 72-31-00-991-314) Subtask 72-31-00-220-050 A. Blending Limits R R R R R R R R R R R R R R
------------------------------------------------------------------------------| INSPECT/CHECK | MAXIMUM | | | BLENDABLE LIMITS | ------------------------------------------------------------------------------| (1) Tears, nicks, dents, missing material | | | and erosion on the leading and trailing | | | edge of stages 1-4 compressor blade found | | | in Dim. B of the airfoil. | | ------------------------------------------------------------------------------| NOTE: Blend repair of the leading and trailing edges can not extend into | | the lower 25 percent of the airfoil length. | | NOTE: More than one blend in the same area is permitted if the total | | material removed from the initial contour is not more than the limit | | that can be repaired. |
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R
C F M 56-5B ------------------------------------------------------------------------------| INSPECT/CHECK | MAXIMUM | | | BLENDABLE LIMITS | ------------------------------------------------------------------------------------------------------------------------------------------------------------| (a) No maximum number of blended damage | Maximum depth is 0.060 in. | | areas. | (1.52 mm) after you blend. | ------------------------------------------------------------------------------| (2) Tears, nicks, dents, missing material | | | and erosion on the leading and trailing | | | edge of stages 1-4 compressor blade | | | found in Dim. A. | | ------------------------------------------------------------------------------| NOTE: More than one blend in the same area is permitted if the total | | material removed from the initial contour is not more than the limit | | that can be repaired. | ------------------------------------------------------------------------------| (a) No maximum number of blended damage | Maximum blended area is 0.30 | | areas. | x 0.30 in. (7.6 x 7.6 mm) | | | after you blend. | ------------------------------------------------------------------------------| (b) No maximum number of dents. | Maximum depth is 0.080 in. | | | (2.03 mm). | | | Maximum deflection from | | | initial contour is 0.080 in. | | | (2.03 mm). | ------------------------------------------------------------------------------| (c) No maximum number of missing tip | Maximum depth is 0.300 in. | | corners. | (7.62 mm). | | | Maximum length is 0.300 in. | | | (7.62 mm). | ------------------------------------------------------------------------------| (3) Tears, nicks, dents, missing material | | | and erosion on the leading and trailing | | | edge of stages 5-9 compressor blade | | | found in dimension Dim. B of the airfoil| | ------------------------------------------------------------------------------| (a) No maximum number of blended damage | Maximum blendable limits: | | areas. | 0.060 in. (1.52 mm) max | | | depth after you blend. | ------------------------------------------------------------------------------| (4) Tears, nicks, dents, missing material | | | and erosion on the leading and trailing | | | edge of stages 5-9 compressor blade | | | found in area Dim. A. | | ------------------------------------------------------------------------------| (a) Up to 20 percent of the blades in each| Maximum area is 0.20 x 0.20 |
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B
HPC Blade Borescope Blending Tool Figure 803/TASK 72-31-00-991-311- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B
HPC Blade Borescope Blending Tool Figure 803/TASK 72-31-00-991-311- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/08
C F M 56-5B
Blend Area Example Figure 804/TASK 72-31-00-991-312 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Nov 01/08
C F M 56-5B
Borescope Blend Tool Tip Selection/Blend Tip Installation Figure 805/TASK 72-31-00-991-313 R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B
Compressor Blades Inspection Areas Figure 806/TASK 72-31-00-991-314- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B
Compressor Blades Inspection Areas Figure 806/TASK 72-31-00-991-314- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
R R R R R R R R R
C F M 56-5B ------------------------------------------------------------------------------| INSPECT/CHECK | MAXIMUM | | | BLENDABLE LIMITS | ------------------------------------------------------------------------------| stage can have tears, nicks, erosion | in. (5.1 x 5.1 mm) after you | | and material that is not there. | blend. | ------------------------------------------------------------------------------| (b) No maximum number of dents. | Maximum depth is 0.080 in. | | | (2.03 mm). | | | Maximum deflection from | | | initial contour is 0.080 in. | | | (2.03 mm). | ------------------------------------------------------------------------------Subtask 72-31-00-320-053 B. Perform Blade Blending NOTE : Equivalent substitutes for the HPC, blade, borescope, blending ____ tool (Wolf tool 5.08036.00) and CCD video camera and monitor (Wolf Compatible) are not permitted unless approved by CFMI. (1) Measure the damaged area as follows: NOTE : Do not install or remove the tool tip from the drive shaft ____ head with the drive shaft head in the zero degree position. If you remove the tool tip with the drive shaft head in the zero degree position, the drive belt will disengage. (a) Put the drive shaft head (2) in the 90 degree position. Install the measuring grid tip (5) onto the drive shaft head (2) and tighten the lockscrew. This will prevent damage to the rotor blades or the blend tool. (b) Put the measuring grid tip (5) in the zero degree position and put the tool (4) into the borescope port. (c) Monitor the measuring grid tip (5), and position the drive shaft head (2) to the 90 degree position. (d) Put the measuring grid tip (5) near the HPC blade damage area. NOTE : Each square on the grid is 0.039 x 0.039 in. (1.00 x 1.00 ____ mm). The overall grid size is 0.197 x 0.197 in. (5.00 x 5.00 mm).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B (e) Write down the damage result such as defect size and location. (f) Compare the recorded blade damage against the permitted blend limits. NOTE : Make sure the blade damage is less than the permitted ____ blend limits. (g) If the damage is less than permitted limits, find the length of the blend necessary to keep the minimum blend radius. (h) Calculate the minimum blend radius at eight times the depth of the defect, or four times on both sides of the center of the blade defect. (i) Put the drive shaft head (2) in the zero degree position, and remove the tool from the borescope port. (j) Put the drive shaft head (2) in the 90 degree position. Loosen the lockscrew, and remove the measuring grid tip (5) from the drive shaft head. (2) Blade blending procedure NOTE : Do not blend into the lower 25 percent of the airfoil length ____ (L). NOTE : When blending rotor blades, blend in a radial direction in ____ relation to the engine centerline. Avoid removing metal from leading and trailing edges of airfoil sections in such a way that the edges become thin or sharp; blend so as to maintain approximately the original contour. NOTE : The finish on the blended area must be as close to the ____ original finish as possible. (a) Put the drive shaft head (2) in the 90 degree position, and use the applicable grind tip to blend the HPC stage damaged. NOTE : Use longer blend tool tips for the forward blades, and ____ shorter blend tool tips for the aft blades.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 819 Nov 01/08
C F M 56-5B (b) Apply the light source to the blend tool. NOTE : Do not install or remove a tool tip from the drive shaft ____ head with the drive shaft head in the zero degree position. If you remove the tool tip with the drive shaft head in the zero degree position, the drive belt will disengage. NOTE : Make sure the blend tip is pointed away from the operator ____ in the 90 degree position. Start the drive motor and make sure the tip rotates in the clockwise direction. If the direction of rotation is counter clockwise, check the drive belt for possible twisted installation. (3) Put the blend tool tip in the zero degree position. Put the blend tool tip into the compressor, through the borescope access port. (4) Put the primary blade edge grinding tip (1) in the borescope port, view the tool tip and move the tool tip from the zero degree to the 90 degree position. (5) Put the primary blade edge grinding tip (1) near the HPC blade defect. (6) Align the blend tool tip with the blade defect and check for correct movement across the total length of the area to be blended. NOTE : Do not start the drive motor (14) at this time. ____ NOTE : Make sure the blend tool tip correctly touches across the ____ total area to be blended. (7) Use the primary blade edge grinding tip (1) and mark the two sides of the blade defect. NOTE : The minimum blend radius should be eight times the depth of ____ the defect, or four times on both sides of the center of the blade defect. (8) Start the drive motor (14) and apply pressure to the grid tip (1) at the defect area. (a) After sufficient practice with the grind tip (1) on the blade leading edge surface, turn on the motor using the on/off switch (16) and use the motor speed control (6) to increase speed.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 820 Nov 01/08
C F M 56-5B NOTE : If the grind tip (1) does not turn freely, apply less ____ pressure to the blade edge surface. (9) During blending, make sure that you put a contour on the edge of the blade and remove the sharp edges. (10) Stop the drive motor (14). (11) Put the grind tip (1) in the zero degree position. (12) Remove the grind tip (1) from the borescope access port. (13) Put the grind tip (1) in the 90 degree position. (14) Loosen the lockscrew and remove the grind tip (1) from the drive shaft head (2). NOTE : Do not install or remove a tool tip from the drive shaft head ____ with the drive shaft head in the zero degree position. If you remove the tool tip with the drive shaft head in the zero degree position, the drive belt will disengage. (15) Install the polishing ball tip (4) onto the drive shaft head (2) and tighten the lockscrew. This will prevent damage to the rotor blades or the blend tool. NOTE : Do not install or remove a tool tip from the drive shaft head ____ with the drive shaft head in the zero degree position. If you remove the tool tip with the drive shaft head in the zero degree position, the drive belt will disengage. (16) Put the polishing ball tip (4) in the zero degree position and put it into the borescope access port. Next, put the drive shaft head (2) in the 90 degree position. (17) Polish the blended surface and stop the drive motor (14). (18) Put the polishing ball tip (4) in the zero degree position and remove from the borescope port. (19) Use the standard borescope probe 1 configuration (magnified 1 : 1 at 7 in. (177 mm)) and inspect the blended blades to make sure you removed all the defect.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 821 Nov 01/08
C F M 56-5B Subtask 72-31-00-290-052 C. Follow-Up Inspection after the Borescope Blending (1) A one-time inspection of the blended area(s) no sooner than 25 cycles and not later than 100 cycles is required. (a) No follow-up inspection is required if all blending was confirmed in Area A and on tip. 5. Close-up ________ Subtask 72-31-00-410-066 A. Close Access (1) Install the stage 1 thru 5 borescope plugs (S1 thru S5) as follows: (a) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads and pressure face of the borescope plugs. (b) Install the borescope plug in the borescope port. Tighten the borescope plug by hand. (c) TORQUE the borescope plugs to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (d) Wirelock the borescope plugs. Use lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (2) Install the stage 6, 7 and 8 borescope plugs (S6, S7 and S8) as follows: CAUTION : MAKE SURE YOU FULLY SCREW THE INNER CAP IN. IF NOT FULLY _______ SCREWED IN, THE INNER CAP OF THE BORESCOPE PLUG WILL DEFLECT THE COMPRESSOR REAR CASE AS THE OUTER CAP IS TIGHTENED. THIS WILL CAUSE BINDING OF THE COMPRESSOR ROTOR. (a) Make sure the borescope port is open. Insert the 0.37 in. (9.40 mm) diameter tapered rod in the borescope port. (b) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads and pressure face of the borescope plugs.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 822 Nov 01/08
C F M 56-5B (c) Put the plug in the correct borescope port and tighten the inner plug by hand. Use the outer plug to turn the inner plug. (d) TORQUE the inner plug to between 90 and 100 lbf.in (1.01 and 1.13 m.daN). Loosen half a turn and RETORQUE to between 15 and 20 lbf.in (0.16 and 0.22 m.daN) more than the running torque. (e) Compress the plug spring and tighten the outer plug by hand. NOTE : If the inner plug is correctly installed and the threads ____ are not damaged, you can install the outer plug by hand. If the outer plug cannot be fully installed by hand, the inner plug is not correctly installed. Remove the plug and repeat steps (c), (d) and (e). (f) TORQUE the outer plug to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (g) Wirelock all 3 outer plugs together with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (3) Remove the tool used to rotate the core. (a) Remove the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488P01 or P02) from the starter pad of the AGB if installed. (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002) if removed. (c) Install the starter (Ref. TASK 80-11-10-400-002) if removed. (4) Make sure that the work area is clean and clear of tool(s) and other items. (5) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-31-00-440-055 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 823 Nov 01/08
C F M 56-5B Subtask 72-31-00-710-051 C. Test CAUTION : DO NOT OPERATE THE ENGINE WITHOUT A CORRECTLY INSTALLED COVER _______ ON THE N2 HANDCRANKING DRIVE PAD. IF THE COVER IS NOT INSTALLED CORRECTLY, THE ENGINE CAN HAVE OIL LEAKAGE. THIS CAN CAUSE ENGINE FAILURE. (1) Do a minimum idle check (Ref. TASK 71-00-00-710-006) and check for leaks. Subtask 72-31-00-410-067 D. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-31-00 201-249, 251-299, 301-399, 401-499, CES
Page 824 Nov 01/08
C F M 56-5B HPC FRONT STATOR ASSEMBLY - DESCRIPTION AND OPERATION _____________________________________________________ 1. _______ General The compressor front stator consists of the front casing halves, the inlet guide vanes (IGV), and the first 5 stages of stator vanes. 2. ___________ Description (Ref. Fig. 001, 002) A. Front Stator Casing The front case halves are made from M152 steel forging. The stage 1-5 flowpath is a machined, integral part of the case, instead of liners. The lower halves of the front casing have ports for the inspection of the internal areas. The front stator forms the load carrying structure between the fan frame and the combustion case. Bleed air is taken from the pads on the front case for the use of the customer. The bleed air is also used for high pressure turbine cooling and clearance control and for low pressure turbine cooling. B. Vanes The IGV and the stages 1 through 3 vanes are variable ; the stages 4 and 5 vanes are fixed. All vanes are made of steel. The fixed vanes, in stages 4 and 5, are fabricated into segments consisting of several vanes each. All stages of vanes have honeycomb shrouds on their inner diameter. The shrouds together with the rotor seal teeth, form interstage seals to prevent flowpath recirculation. C. Variable Vane Actuation Actuation of the variable vanes is accomplished with hydraulically actuated bellcrank assemblies mounted on the front compressor stator at the 2 and 8 oclock positions. Fixed linkages connect the bellcranks to actuation rings. Lever arms attached to the variable vanes connect to the actuation rings. Fuel from the hydromechanical unit (HMU) operates the hydraulic actuators.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Compressor Front Stator Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
HP Compressor Stator Section Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B HPC FRONT STATOR ASSEMBLY - INSPECTION/CHECK ____________________________________________ TASK 72-32-00-210-002 Inspection/Check of the HPC Front Stator Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-13-00-010-040 71-13-00-410-040 72-00-00-200-009 72-00-00-200-025 72-32-00-000-004 72-32-00-400-004 72-32-00-960-002 75-32-10-000-002 75-32-10-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-32-00-991-300 72-32-00-991-304
Removal of the Power Plant Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Off-Schedule Vane Replacement Over-Serviceable-Limit Extensions Removal of the Actuation Ring Connecting Links Installation of the Actuation Ring Connecting Links Replacement of the Actuation Ring Flanged Bushing (Stages 1 and 2) Removal of the Variable Stator Vane (VSV) Actuators Installation of the Variable Stator Vane (VSV) Actuators Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-32-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-32-00-010-058 B. Get access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-32-00-040-055 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-32-00-010-059 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-32-00-991-300, 602/TASK 72-32-00-991-304) Subtask 72-32-00-210-052 A. Inspection/Check of the HPC Front Stator Assembly CAUTION : LEVER ARM DISTRESS OR MISASSEMBLY RESULTING IN VANE SCHEDULING _______ ERRORS IN EXCESS OF 4 DEGREES REQUIRES SPECIAL INSPECTION/ DISPOSITION OF COMPRESSOR ROTOR BLADES. R
(1) Inspect the following areas: (a) If vane scheduling errors occur (Ref. TASK 72-00-00-200-009). ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Casing for : - Cracks
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
- Nicks, pits, scores and scratches
Any number, any length, 0.010 in. (0.25 mm) deep after removal of high metal
See limit extensions (Ref. TASK 72-00-00-200025).
- Cracks (or broken)
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
- Distortion, bends, twists or distress
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
- Separation
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025).
2. Vane actuation rings for :
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Aug 01/09
C F M 56-5B
Compressor Front Stator Assembly-Inspection Figure 601/TASK 72-32-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-32-00 CES
Page 605 Nov 01/03
C F M 56-5B
Stator Vane ID to Rotor Contact Figure 602/TASK 72-32-00-991-304- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Stator Vane ID to Rotor Contact Figure 602/TASK 72-32-00-991-304- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Damaged or broken Bushing body is intact lever arm bushing and provides 360 degrees support to lever arm pin - Missing bushings on Stages 1 and 2
Not serviceable
- Missing or broken bushing legs
Any amount
See Repair Procedures (Ref. TASK 72-32-00-960002)
3. Actuation ring connector for : - Cracks (or broken) one side only
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
- Cracks (or broken) both sides
Not serviceable
R R R
- Bushings with broken or missing legs
Any amount
R R R
- Missing bushings
Not serviceable
Replace actuation ring (Ref. TASK 72-32-00-000004) and (Ref. TASK 72-3200-400-004)
- Broken or bent
Not serviceable
Remove engine for replacement of HPC rotor blades in one stage forward of and 2 stages aft of stage with defective lever arms
- Cracked
Not serviceable
Replace lever arm (Ref. TASK 72-32-00-000-
4. Vane lever arms, IGVs and stage 3 for :
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------004) and (Ref. TASK 72-3200-400-004) - Nicks, dents and scratches
Area A not serviceable Area B 0.010 in. (0.25 mm) after removal of high metal provided bottom of defect is not sharp pointed. Area C (not including pin) 0.002 in. (0.05 mm) deep.
5. Vane lever arms, stage 1 and 2 for : (Ref. Fig. 601/TASK 72-32-00-991-300) - Broken or bent
Not serviceable
Remove engine for replacement of HPC rotor blades in one stage forward of and 2 stages aft of stage with defective lever arms
- Cracked
Not serviceable
Remove engine for replacement of cracked lever arm
- Nicks, dents and scratches
Area A not serviceable Area B 0.010 in. (0.25 mm) after removal of high metal provided bottom of defect is not sharp pointed. Area C (not including pin) 0.002 in. ( 0.05 mm) deep.
6. Vane assembly, IGVs and stage 3 for : - Looseness
Any amount of radial and side movement provided bushing not missing. No metal to metal contact allowed. (Listen for
See limit extensions (Ref. TASK 72-00-00-200025)
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, R CES
Page 609 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------metallic sound while shaking vane stem) 7. Vane assembly, stages 1 and 2 for : - Looseness
Any amount of radial and side movement provided bushing not missing. No metal to metal contact allowed. (Listen for metallic sound while shaking vane stem)
See limit extensions (Ref. TASK 72-00-00-200025)
- Cracks
Not serviceable
Remove the engine for the replacement of the bellcrank assembly (Ref. TASK 71-00-00-000042) or Replace vane actuation assembly (Ref. TASK 75-3210-000-002) and (Ref. TASK 75-32-10-400-002)
- Nicks, pits, scores and scratches
Any number, any length 0.030 in. (0.76 mm) deep after removal of high metal
Replace vane actuation system (Ref. TASK 75-3210-000-002) and (Ref. TASK 75-32-10-400-002)
0.010 in. (0.25 mm) diametral
Remove the engine for the replacement of the bellcrank assembly (Ref. TASK 71-00-00-000042)
8. Vane actuation system (bellcrank assembly) for :
9. Spherical bearings for : - Looseness of ball in race
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, R CES
Page 610 Nov 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-32-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-32-00-440-053 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-32-00-410-057 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B HPC FRONT STATOR ASSEMBLY - REPAIRS ___________________________________ TASK 72-32-00-000-003 Removal of the Inlet Guide Vane (IGV) and Stage 3 Vane Lever Arms or Bushings 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1012 856A1051
warning notice access platform 1 m (3 ft. 3 in.) 1 LEVER,COUNTERTORQUE-CPRSR STATOR VANE ACTUATION ARM 1 PULLER,ARM-COMPRESSOR STATOR ACTUATION
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 78-30-00-481-041 78-36-00-010-040 72-32-00-991-301 72-32-00-991-302
Opening of the Fan Cowl Doors Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Fig. 801 Fig. 802
3. __________ Job Set-up Subtask 72-32-00-941-054 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-32-00-010-060 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-32-00-040-056 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-32-00-010-061 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 801/TASK 72-32-00-991-301, 802/TASK 72-32-00-991-302) Subtask 72-32-00-020-052 A. Remove the IGV and stage 3 lever arms and bushings. (1) Hold the lever arm with LEVER,COUNTERTORQUE-CPRSR STATOR VANE ACTUATION ARM (856A1012G01), while you loosen the vane stem nut. Do not let the vane turn.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B
Replacement of Lever Arm and/or Vane Bushing Figure 801/TASK 72-32-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B
IGV and Stage 3 Lever Arm Engaged Correctly and Incorrectly Figure 802/TASK 72-32-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B (2) Remove the nut and washer from the vane. (3) Remove the lever arm from the vane with PULLER,ARM-COMPRESSOR STATOR ACTUATION (856A1051G01). (4) Remove the bushing from the stator case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/08
C F M 56-5B TASK 72-32-00-400-003 Installation of the Inlet Guide Vane (IGV) and Stage 3 Vane Lever Arms or Bushings 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific 856A1012
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 LEVER,COUNTERTORQUE-CPRSR STATOR VANE ACTUATION ARM
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-32-00-991-301 72-32-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 801 Fig. 802
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-32-00-860-052 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-32-00-010-064 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-32-00-040-058 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-32-00-420-052 A. Install the IGV and stage 3 lever arms. CAUTION : CORRECTLY ALIGN THE WITNESS MARK ON THE VANE STEM WITH THE _______ LEVER ARM. BLADE DAMAGE CAN OCCUR IF THE VANE STEM IS NOT CORRECTLY ALIGNED. (1) Install the replacement bushing in the stator case. (2) Install the replacement lever arms on the vane while you engage the lever arm pin into the actuation ring. (3) Make sure the lever arm fully engages the vane stem flats. (4) Install the washer and nut on the vane stem. Hold the lever arm with LEVER,COUNTERTORQUE-CPRSR STATOR VANE ACTUATION ARM (856A1012G01), while you tighten the nut. (5) TORQUE the nut to between 55 and 70 lbf.in (0.62 and 0.79 m.daN). Do not let the vane turn. Subtask 72-32-00-210-053 B. Do a visual check. (1) The lever arm must fully engage the vane stem flats. (Ref. Fig. 801/TASK 72-32-00-991-301) (2) A minimum of 2 vane stem threads must be above the nut. (Ref. Fig. 802/TASK 72-32-00-991-302)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-32-00-410-058 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-32-00-440-054 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-32-00-410-059 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B TASK 72-32-00-000-004 Removal of the Actuation Ring Connecting Links 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 78-30-00-481-041 78-36-00-010-040 72-32-00-991-303
Opening of the Fan Cowl Doors Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Fig. 803
3. __________ Job Set-up Subtask 72-32-00-941-055 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-32-00-010-062 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-32-00-040-057 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-32-00-010-063 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 803/TASK 72-32-00-991-303) Subtask 72-32-00-020-053 A. Remove the connecting link. (1) Disconnect the tie rod from the clevis of the defective connecting link as follows: NOTE : Do not adjust the tie rod. ____ (a) Remove the nut.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B
Replacement of the Actuation Ring Connecting Links Figure 803/TASK 72-32-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B (b) Remove the D-head bolt. (2) Cut and remove lockire, remove the bolts that hold the connecting link to the actuation ring. NOTE : There is a locating pin at each end of the connecting link. ____ The straight pin stays in the actuation ring segment. The pin with the head comes out with the connecting link.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/08
C F M 56-5B TASK 72-32-00-400-004 Installation of the Actuation Ring Connecting Links 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2365
Material No.
CP8001
USA MIL-T-5544 Graphite grease (Ref. 70-30-00) USA MIL-S-22473 Grade A Loctite 290 (Ref. 70-30-00) * Lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-32-00-991-303
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 803
3. __________ Job Set-up Subtask 72-32-00-860-053 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-32-00-010-065 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-32-00-040-059 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041). 4. Procedure _________ (Ref. Fig. 803/TASK 72-32-00-991-303) Subtask 72-32-00-420-053 A. Install the connecting link. (1) If the straight pin comes out with the connecting link, apply Loctite 290 (Material No. CP2365) to the end of the straight pin that goes in the actuation ring. (2) Install the straight pin in the actuation ring. NOTE : On the right side, the pin goes in the top segment of the ____ actuation ring. On the left side, the pin goes in the lower segment of the actuation ring. (3) Install the connecting link to the actuation ring segments. Make sure the straight pin fully engages the hole in the actuation ring and the lever arms are correctly engaged in the connecting link bushings. (4) Install the headed pin in the connecting link and actuation ring segment. (5) Apply Graphite grease (Material No. CP2101) to the threads and friction surface of the bolts. (6) Install the bolts. TORQUE the bolts to between 55 and 70 lbf.in (0.62 and 0.79 m.daN). (7) Make sure that the straight pin is correctly installed in the actuation ring. Use lockwire through the inspection hole of the connecting link to feel for the pin.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B (8) Do a visual check: CAUTION : BLADE DAMAGE CAN OCCUR IF THE LEVER ARMS ARE NOT CORRECTLY _______ ENGAGED. (a) Make sure all of the lever arms are correctly engaged in the connecting link bushings. (9) Wirelock the bolts: CAUTION : MAKE SURE THE D-HEAD BOLT IS SEATED IN THE RECESS OF THE _______ CONNECTING LINK. (a) Use the Lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001). (10) Apply Graphite grease (Material No. CP2101) to the threads of the D-head bolt. (11) Install the tie rod in the connecting link with the D-head bolt and nut. The bolt head goes aft for IVG and forward for stages 1, 2, and 3. (12) Install the nut and TORQUE to between 105 and 115 lbf.in (1.18 and 1.29 m.daN). NOTE : Do not adjust the tie rod. ____ 5. Close-up ________ Subtask 72-32-00-410-060 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-32-00-440-055 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
C F M 56-5B Subtask 72-32-00-410-061 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the warning notice(s). (3) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B TASK 72-32-00-960-002 Replacement of the Actuation Ring Flanged Bushing (Stages 1 and 2) 1. __________________ Reason for the Job To replace missing actuation ring bushings. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2267
* RTV 106 (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-32-00-991-305
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 804
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 819 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-32-00-941-057 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-32-00-010-068 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-32-00-040-061 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-32-00-010-069 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 820 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 804/TASK 72-32-00-991-305) CAUTION : DO NOT REMOVE THE LEVER ARMS TO COMPLETE THIS REPAIR. _______ Subtask 72-32-00-420-055 A. Install the new actuation ring lever arm bushing (1) If necessary, clean the pieces of old bushing from the ring. NOTE : The new bushing cannot be inserted onto the lever arm with the ____ legs attached. NOTE : The actuation ring is assembled with different types of ____ bushings. Be sure to select the correct bushing from the Illustrated Parts Catalog. (2) Carefully, break the 4 legs off of the new bushing. (3) Install the new bushing from outboard side of actuation ring (Ref. Fig. 804/TASK 72-32-00-991-305) WARNING : RTV 106 IS TOXIC AND FLAMMABLE. USE PERSONAL PROTECTION _______ EQUIPMENT. USE IN A WELL-VENTILATED AREA. (4) Apply approximately 0.125 in. (3.18 mm) RTV 106 (Material No. CP2267) to the outer flange of the bushing. (5) Permit the RTV 106 to cure for not less than 24 hours before you operate the engine. 5. Close-up ________ Subtask 72-32-00-410-064 A. Close access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 821 Nov 01/08
C F M 56-5B
Replacement of the Stages 1 and 2 Actuation Ring Flanged Bushing Figure 804/TASK 72-32-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 822 Nov 01/08
C F M 56-5B Subtask 72-32-00-440-057 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-32-00-410-065 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-32-00 201-249, 251-299, 301-399, 401-499, CES
Page 823 Nov 01/08
C F M 56-5B HPC REAR STATOR ASSEMBLY - DESCRIPTION AND OPERATION ____________________________________________________ 1. _______ General (Ref. Fig. 001) The compressor rear stator consists of the rear casing halves, 3 stages of fixed vanes, and interstage honeycomb seals. The halves are attached together at the 3 and 9 oclock splitline with bolts. The rear stator assembly is found inside the front stator assembly and is cantilever mounted to the rear stator support. The outer flange of the rear stator support is installed between the front stator of the compressor and the combustion case. The rear flange has rabbets for close tolerance concentricity with the combustion case. The forward end is radially restrained by manifold supports attached to the front case to maintain concentricity. 2. Description ___________ A. Casing The rear casing halves are a matched set machined from an incoloy forging. The casings have internally machined circumferential slots that retain stages 6, 7, and 8 stator vane segments. Stage 6, 7, 8, and 9 rub lands are hard-coated. The casing contains ports for borescope inspection of internal area. B. Vanes The vanes in stages 6,7, and 8 are made into segments consisting of several vanes each. These segments are installed in circumferential slots in the casing. Each stage of vanes has shrouds with removable honeycomb seal segments attached to the inner platforms.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-33-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Compressor Rear Stator Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-33-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B COMBUSTION SECTION - DESCRIPTION AND OPERATION ______________________________________________ 1. _______ General (Ref. Fig. 001) The combustion of fuel takes place in the combustor installed in the compressor rear frame. The controlled release of energy of combustion through the turbine nozzles drive the engine rotors. (HP rotor for self sustaining operation and the LP rotor to develop airflow through the fan exhaust nozzle and to provide gases to the core engine exhaust nozzle for additional thrust).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-40-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Combustion Chamber Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-40-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B COMBUSTION CASE ASSEMBLY - DESCRIPTION AND OPERATION ____________________________________________________ 1. _______ General (Ref. Fig. 001) The combustion case is a fabricated structural weldment located between the high pressure compressor (HPC) and the low pressure turbine (LPT). It provides the structural interface, transmits the engine axial load, and provides gas flow path between the compressor and LPT. The case incorporates the compressor outlet guide vanes (OGV) and a diffuser for the reduction of combustion chamber sensitivity to the compressor air velocity profile. 2. Description ___________ A. Components The combustion case encloses the combustion chamber and high pressure turbine (HPT) components. The combustion chamber, compressor rear stationary (CDP) seal, HPT nozzle assembly, and HPT shroud/stage 1 LPT nozzle assembly are mounted in and structurally supported by the combustion case. The case mounts and positions the 20 fuel nozzles, 2 igniters, and fuel manifold. The fuel manifold system is composed of a fuel supply manifold (Y tube), 2 fuel manifolds halves, 3-piece drain manifold, and overboard drain tube. B. Ports There are 6 borescope ports ; 4 for inspection of the combustion chamber and HPT nozzles and 2 for inspection of the HPT blades and shrouds and the stage 1 LPT blades. The case has 4 ports for extraction of compressor discharge air for customer use, 4 ports for introduction of stage 5 compressor air for low pressure cooling and 3 ports for HPT shroud cooling air (one for source air and 2 for introduction of air to the shrouds). There is also one port for the following : start bleed dump, P3 sensor, T3 sensor, and CCCP air. There are 2 ports for the spark igniters and 2 ports for turbine clearance control thermocouples.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Combustion Case Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B COMBUSTION CASE ASSEMBLY - INSPECTION/CHECK ___________________________________________ TASK 72-41-00-290-001 Borescope Inspection of the Combustion Chamber Liners, Dome Areas,HPT Nozzle Vanes and Shrouds (as far as visible through two opposite ports) 1. __________________ Reason for the Job Refer to the MPD TASK: 724000-C1 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-42-00-290-041 72-51-00-290-004 72-53-00-290-004
Borescope Inspection of the Combustion Chamber Liners and Dome Area Borescope Inspection of High-Pressure Turbine Nozzle Assembly Borescope/Inspection of the High-Pressure Turbine Shroud
3. __________ Job Set-up Subtask 72-41-00-869-051 A. Not Applicable 4. Procedure _________ Subtask 72-41-00-290-051 A. Do a borescope inspection: (1) Borescope inspect combustion chamber liners and dome areas (Ref. TASK 72-42-00-290-041). NOTE : Combustion chamber port access is required through as many ____ ports as necessary to assure 100% combustor inspection coverage. (2) Borescope inspect high pressure turbine nozzle vanes (Ref. TASK 7251-00-290-004) .
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/08
C F M 56-5B (3) Borescope inspect high pressure turbine shrouds (Ref. TASK 72-53-00290-004).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B TASK 72-41-00-200-002 Inspection/Check of the Combustion Case Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 1 m (3 ft. 3 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-41-00-300-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-41-00-991-300
Fluorescent-Penetrant Inspection-Portable-Water Washable Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Repairs of the Combustion Case Assembly Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-41-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-41-00-010-054 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put an access platform in position. Subtask 72-41-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-41-00-010-056 D. Open the thrust reverser cowl doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-41-00-991-300) Subtask 72-41-00-230-052 A. Do a fluorecent penetrant inspection. (1) Do a fluorescent penetrant inspection of actual or suspected cracks in the combustion case assembly (Ref. TASK 70-51-00-230-002). Subtask 72-41-00-210-051 B. Do a visual inspection. (1) Do the visual inspection that follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Combustion casing body for : - Cracks
Not serviceable
- Nicks, scores and scratches
Any number 0.03 in. (0.76 mm) deep after removal of high metal
- Dents
Any number 0.10 in. (2.54 mm) deep after removal of high metal
- Buckling or distortion because of overtemperature
Not serviceable
- Hot spots (discoloration)
Any number, if metal not crazed. No cracks are permitted.
2. Combustion casing forward flanges for :
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
Combustion Case Assembly Figure 601/TASK 72-41-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Bolt hole cracks One crack per hole, 2 that extend cracks per frame radially outward - Bolt hole cracks that extend radially inward
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
3. Combustion case midflange for : - Broken bolts
One broken bolt with a minimum of 5 bolts that are not broken on both sides of the broken bolt. No more than 2 broken bolts in any group of 20.
See limit extensions (Ref. TASK 72-00-00-200025)
4. Combustion casing aft flange for : - Bolt hole cracks that extend radially outward
One crack per hole, 2 cracks per frame
- Bolt hole cracks that extend radially inward
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
5. Fuel nozzle pads for : - Thread damage
Minimum of 4 undamaged threads must be present after chasing threads
- Nicks, scores, pits and deposits
Any number on sealing surface 0.03 in. (0.76 mm) deep not extending across more than 50 percent of sealing surface after removal of high metal
Remove high metal and deposits (Ref. TASK 72-4100-300-002)
6. Igniter and borescope bosses for :
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Thread damage Minimum of 3 undamaged threads must be present after chasing threads 7. HPT shroud cooling and CDP bleed pads for : - Nicks, scores, pits and scratches
Any number, any length 0.03 in. (0.76 mm) in depth provided discrepancy does not extend over 75 percent of sealing surface
Remove high metal (Ref. TASK 72-41-00-300002).
- Cracks extending from bolt holes
One crack per hole no longer than 0.06 in. (1.52 mm)
See limit extensions (Ref. TASK 72-00-00-200025)
5. Close-up ________ Subtask 72-41-00-410-054 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-41-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B Subtask 72-41-00-410-056 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B COMBUSTION CASE ASSEMBLY - REPAIRS __________________________________ TASK 72-41-00-300-002 Repairs of the Combustion Case Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No No No No
specific specific specific specific
abrasive stone fine file warning notice access platform 1 m (3 ft. 3 in.)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2189
Material No.
CP2191
* durite G422 (Ref. 70-30-00) * durite G421 (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Fluorescent-Penetrant Inspection-Portable-Water Washable Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-41-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-41-00-010-055 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B (2) Put the access platform in position. Subtask 72-41-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-41-00-010-057 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-41-00-350-051 A. Blend the part CAUTION : DO NOT PERMIT THE REMOVED MATERIAL, TOOLS, OR CONSUMABLES TO _______ FALL INTO THE COMBUSTION CASE. ENGINE DAMAGE CAN OCCUR. (1) Blend the part with a fine file, durite G422 (Material No. CP2189) or durite G421 (Material No. CP2191) or abrasive stone. Remove as small an amount of the parent metal as possible. Subtask 72-41-00-230-053 B. Do a fluorescent penetrant inspection of all the blend areas. No cracks are permitted. (Ref. TASK 70-51-00-230-002) 5. Close-up ________ Subtask 72-41-00-410-055 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B Subtask 72-41-00-440-053 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-41-00-410-057 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-41-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B COMBUSTION CHAMBER ASSEMBLY - DESCRIPTION AND OPERATION _______________________________________________________ 1. _______ General (Ref. Fig. 001, 002) The combustion case contains the combustion chamber, which is a short, annular structure. The combustion chamber consists of outer and inner cowls, 20 primary swirl nozzles, dome, and outer and inner liners. The liners and cowls are bolted to the dome. The function of the combustion chamber is to supply a uniform combustion pattern for low thermal stress. The staged burning valve, controlled by FADEC, adapts the function of the combustion chamber to the engine requirements by the use of either 10 or 20 open fuel nozzles. 2. ___________ Description (Ref. Fig. 001, 002) A. Dome The dome consists of both cast and machined components. Twenty primary swirl nozzles and 20 secondary swirl nozzles with venturies and sleeves are used to provide mixing of air and fuel. The entire surface of the dome is cooled by a film of cooling air. B. Cowl The inner and outer cowls are designed to provide uniform and stable airflow profiles to the combustion chamber. C. Liners The outer and inner liners are of an integral design with panel overhangs which contain closely spaced cooling holes that provide film cooling. Dilution holes are employed in the liners to provide additional mixing and cooling air which lowers the gas temperature at the turbine inlet. The outer liner contains 2 ferrules for the spark igniters.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Combustion Chamber Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Combustion Chamber Section Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B COMBUSTION CHAMBER ASSEMBLY - INSPECTION/CHECK ______________________________________________ TASK 72-42-00-290-041 Borescope Inspection of the Combustion Chamber Liners and Dome Area 1. __________________ Reason for the Job This TASK is applicable for NON/P, /P and /3 engines equiped with a Single Annular Combustor chamber. NOTE : Inspection of the combustion chamber is limited to the areas that can ____ be seen with a rigid borescope, at the 1, 3, 6 and 10 oclock borescope ports, and at the 2 spark igniter ports. The borescope ports at the 1, 3, 6, and 10 oclock positions are located immediately in front of the fuel manifold. These ports and the 2 spark igniter ports permit the borescope inspection of the combustion chamber and the HPT nozzle. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
856A1320 856A1322 856A1323
protective caps warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET 1 MONITOR, RESOLUTION BORESCOPE
EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.8 mm dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-42-00-290-006 73-11-40-790-002 74-21-30-000-002 74-21-30-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 NTM 720000 72-42-00-991-301 72-42-00-991-302 72-42-00-991-303 72-42-00-991-305 72-42-00-991-306
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Borescope Inspection of the Outer Side of the Combustion Chamber Outer Liners Leak Check of the Fuel Nozzles Removal of the Spark Igniter Installation of the Spark Igniter Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. Fig. Fig. Fig. Fig.
601 602 603 604 605
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-42-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-42-00-010-058 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-42-00-040-053 C. Make the thrust reverser unserviceable for maintenance (Ref. TASK 78-3000-481-041) Subtask 72-42-00-010-059 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-42-00-991-301, 602/TASK 72-42-00-991-302, 603/TASK 72-42-00-991-303, 604/TASK 72-42-00-991-305, 605/TASK 72-42-00-991-306) Subtask 72-42-00-010-060 A. Remove parts before borescope inspection. (1) Remove the borescope plugs from the approximate 3 and 10 oclock positions on the combustion case. Subtask 72-42-00-290-054 B. Do a borescope inspection. (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure the borescope and the lightsource are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Connect the fiber light cable to the BORESCOPE-KIT (856A1320P04/P05) and to the port on BORESCOPE-LIGHT SOURCE SET (856A1322P03/P04/P07). (3) Put the rigid borescope, (856A1320P04/P05), into the ports and turn on the light source of borescope-lightsource set (856A1322P03 or P04). (4) Turn the rigid borescope a full 360 degrees to inspect the dome of the combustion chamber, fuel nozzles, the inner and outer liners, and the aft sections. Adjust the borescope equipment to obtain maximum clarity of view. (5) Inspect the following : ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. All surfaces for : A. Discoloration
Any amount
B. Carbon Accumulation
Any amount
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Missing, chipped Any amount or spalled areas of thermal barrier coating 2. Dome Assembly (Spectacle Plate, Deflector amd Sleeve) for : A. Distortion of deflector or sleeve
Any amount
B. Radial crack in spectacle plate
Any number up to 2 in. (50.8 mm) length and not connected to each other
See limit extension (Ref. TASK 72-00-00-200025)
C. Circumferential crack in spectacle plate
Any number up to 3 in. (76.2 mm) length separated by 6 in. (152.4 mm)
See limit extension (Ref. TASK 72-00-00-200025)
D. Connected cracks in spectacle plate
Not more than (1) radial crack 2 in. (50.8 mm) long with (1) circumferential crack 3 in. (76.2 mm) long separated by 6 in. (152.4 mm).
See limit extension (Ref. TASK 72-00-00-200025)
E. Missing material from spectacle plate
Max. 0.06 in. (1.52 mm) x 0.06 in. (1.52 mm) at intersection of connected crack
See limit extension (Ref. TASK 72-00-00-200025)
F. Radial crack in deflector or sleeve
Any number up to 0.5 in. (12.7 mm) length
See limit extension (Ref. TASK 72-00-00-200025)
G. Circumferential cracks in deflector or sleeve
Any number up to 0.75 in. (19.05 mm)
See limit extension (Ref. TASK 72-00-00-200025)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
Combustion Chamber (Inner and Outer Liner Inspection) Figure 601/TASK 72-42-00-991-301- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Combustion Chamber (Inner and Outer Liner Inspection) Figure 601/TASK 72-42-00-991-301- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B
Combustion Chamber (Sectional View) Figure 602/TASK 72-42-00-991-302- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B
Combustion Chamber (Sectional View) Figure 602/TASK 72-42-00-991-302- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B
Cracks and Missing Material in Dome Area Figure 603/TASK 72-42-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-42-00 CES
Page 611 May 01/08
C F M 56-5B
Outer Liner (Inner) Figure 604/TASK 72-42-00-991-305- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B
Outer Liner (Inner) Figure 604/TASK 72-42-00-991-305- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B
Inner Liner (Inner) Figure 605/TASK 72-42-00-991-306- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B
Inner Liner (Inner) Figure 605/TASK 72-42-00-991-306- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------H. Connected cracks Connection of any radial See limit extension in deflector or and circumferential (Ref. TASK 72-00-00-200sleeve cracks within limits of 025) paragraphs F. and G. above. Limit is exceeded when third crack connects J. Missing material from overhangs on deflector or sleeve
Any amount up to 0.2 in. (5.08 mm) maximum depth.
See limit extension (Ref. TASK 72-00-00-200025)
K. Burn through holes
3 per dome 1 in. (25.4 mm) x 1 in. (25.4 mm) maximum
See limit extension (Ref. TASK 72-00-00-200025)
L. Fuel nozzles for dislodged wear sleeves
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
3. Inner and outer liners for : A. Outer liner axial cracks
Any number across 1 Panel or less and up to 4 cracks across more than 1 panel but not longer than 3 panels
If a crack extends across more than 3 panels, borescope the outer side of the outer liner in the crack locations (Ref. TASK 72-42-00-290-006). See limit extension (Ref. TASK 72-00-00-200025).
NOTE : When applying limits, the dome band is interpreted as a panel. ____ B. Inner liner axial cracks
Any number across 1 panel or less and up to 4 cracks across more than 1 panel but not longer than 2 panels
If up to 1 crack is across 4 Panels, and no material is missing more than 3 times the diameter of a dilution hole and does not connect to a circumferential crack longer than 0.5 in. (12.7
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------mm), then reinspect in 750 cycles. See limit extensions (Ref. TASK 7200-00-200-025). C. Circumferential cracks
There is no limit to the number with these conditions: The cracks are no longer than 2 dilution lands. There are no more than 2 adjacent cracks in a dilution land. The cracks are separated by a minimum of 3 dilution lands that do not have cracks.
See limit extensions (Ref. TASK 72-00-00-200025)
NOTE : A dilution land is the area of the panel between the dilution ____ holes. Connection of any axial and circumferential cracks up to max limits of paragraphs A. B. and C. above. Limit is exceeded when third crack connects
See limit extension (Ref. TASK 72-00-00-200025)
E. Burn through or missing material
Per liner, 8 areas with these conditions : 3 or more adjacent holes are not aligned axially. 6 areas are not more than 2 times the size of a dilution hole. No more than 2 areas are not more than 3 times the size of a dilution hole. No more than 1 area is not more than 4 times the size of a dilution hole. The area can be 3
See limits extension (Ref. TASK 72-00-00-200025)
R R R R
D. Connected cracks
EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Feb 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------times the size of a dilution hole, if the dilution hole was contained in the damaged area, and is considered a hole that is 2 times the size of a dilution hole. F. Missing overhangs
Per liner : 14 areas each 2 times the size of a dilution hole providing maximum axial alignment of distress is 3 adjacent panels.
See limits extensions (Ref. TASK 72-00-00-200025).
G. Distortion
Any amount within 0.5 in. (12.7 mm) of original contour
See limit extension (Ref. TASK 72-00-00-200025)
(6) When the inspection is complete, turn off the light source and remove the borescope. (7) If any defects are found then remove additional borescope plugs and the spark igniters to inspect all of the combustion chamber. If no defects are found, install parts removed for borescope inspection. Subtask 72-42-00-010-064 C. Remove parts before additional borescope inspection. (1) Remove the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug. NOTE : If you remove the drain tube from the fuel nozzle adjacent to ____ the 6 oclock borescope plug, you will be required to perform a leak check after this inspection. Use the 6 oclock borescope port only if necessary. (2) Remove the borescope plugs from the approximate 1 and 6 oclock positions.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
C F M 56-5B (3) Remove both spark igniters (Ref. TASK 74-21-30-000-002). (4) Install protective caps on the leads and the spark igniters. Subtask 72-42-00-290-056 D. Do a borescope inspection of the entire combustion chamber. (1) Repeat paragraph 4.B.(1) thru 4.B.(5) for each borescope and spark igniter location. Subtask 72-42-00-410-059 E. Install parts removed for borescope inspection. (1) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (2) Install the borescope plugs. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE _______ COMBUSTOR BORESCOPE PLUGS DO NOT HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF BORESCOPE PLUGS WITH STEMS FROM OTHER LOCATIONS WILL RESULT IN THE STEM FEATURE BEING BURNED AWAY BY COMBUSTION GASES. (a) Install the borescope plugs and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (3) Safety the plugs with lockwire 0.8 mm dia. (Material No. CP8001) (4) If necessary, install the fuel drain tube to the fuel nozzle adjacent to the six oclock borescope plug. TORQUE the coupling nuts on the fuel drain tube to between 120 and 135 lbf.in (1.35 and 1.52 m.daN) and safety with lockwire 0.8 mm dia. (Material No. CP8001) (5) If necessary, remove the protective caps and install the spark igniters (Ref. TASK 74-21-30-400-002) Subtask 72-42-00-290-062 F. If necessary, do the borescope inspection of the outer side of the outer liner to confirm the extent of outer liner axial cracks (Ref. TASK 72-4200-290-006).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 619 Nov 01/08
C F M 56-5B Subtask 72-42-00-790-051 G. Do a fuel nozzle leak check. (1) If you removed the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug, do a fuel nozzle leak check (Ref. TASK 73-1140-790-002). 5. Close-up ________ Subtask 72-42-00-410-057 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-42-00-440-055 B. Make the thrust reverser serviceable after maintenance (Ref. TASK 78-3000-081-041) Subtask 72-42-00-410-058 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/08
C F M 56-5B TASK 72-42-00-290-006 Borescope Inspection of the Outer Side of the Combustion Chamber Outer Liners 1. __________________ Reason for the Job To confirm the extent of the outer liner axial cracks, as necessary. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1321 856A1322 856A1323
warning notice access platform 1 m (3 ft. 3 in.) 1 FIBERSCOPE SET 1 BORESCOPE-LIGHT SOURCE SET 1 MONITOR, RESOLUTION BORESCOPE
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 73-11-40-000-002 73-11-40-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 NTM 720000 72-42-00-991-304
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Removal of the Fuel Nozzle Installation of the Fuel Nozzle Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 606
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 621 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-42-00-941-057 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-42-00-010-072 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform Subtask 72-42-00-040-057 C. Make the thrust reverser unserviceable for maintenance (Ref. TASK 78-3000-481-041) Subtask 72-42-00-010-075 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 606/TASK 72-42-00-991-304) Subtask 72-42-00-010-073 A. Remove parts before borescope inspection. (1) Select fuel nozzles to remove that will allow access to the outer liner area to be inspected. (2) Remove the fuel nozzles (Ref. TASK 73-11-40-000-002) Subtask 72-42-00-290-061 B. Do a borescope inspection. (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure borescope and the ligth source are serviceable. See the Non Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Connect the fiber ligth cable to the FIBERSCOPE SET (856A1321P01 or 856A1321P03 or 856A1321P06) and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P03, P04, or P07). (3) Put the fiberscope of the FIBERSCOPE SET (856A1321P01 or 856A1321P03 or 856A1321P06) into the fuel nozzle ports and turn on the light source of BORESCOPE-LIGHT SOURCE SET (856A1322P03, or P04). (4) Adjust the borescope equipment to obtain maximum clarity of view. (5) Inspect the following: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Outer side of outer liners for: A. Outer liner axial crack locations
Any number if cracks do not extend through more than one of ribs 4, 5, and 6 if rib 1 is not cracked through.
Reinspect the combustor in 750 cycles. See limit extensions (Ref. TASK 7200-00-200-025).
NOTE : When applying limits, the dome band is interpreted as a panel. ____
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 623 Nov 01/08
C F M 56-5B
Outer Liner (Outer) Figure 606/TASK 72-42-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 624 Nov 01/08
C F M 56-5B (6) When the inspection is complete, turn off the light source and remove the fiberscope. Subtask 72-42-00-410-069 C. Install the fuel nozzles (Ref. TASK 73-11-40-400-002). 5. Close-up ________ Subtask 72-42-00-410-070 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-42-00-440-053 B. Make the thrust reverser serviceable after maintenance (Ref. TASK 78-3000-081-041). Subtask 72-42-00-410-072 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 625 Nov 01/08
C F M 56-5B TASK 72-42-00-290-005 Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET 1 MONITOR, RESOLUTION BORESCOPE
856A1320 856A1322 856A1323
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.8 mm dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 626 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-51-00-290-004 72-51-00-290-004 73-11-40-790-002 74-21-30-000-002 74-21-30-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 NTM 720000 72-42-00-991-301 72-42-00-991-307 72-42-00-991-308
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Borescope Inspection of High-Pressure Turbine Nozzle Assembly Borescope Inspection of High-Pressure Turbine Nozzle Assembly Leak Check of the Fuel Nozzles Removal of the Spark Igniter Installation of the Spark Igniter Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 607 Fig. 608
3. __________ Job Set-up Subtask 72-42-00-941-054 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Nov 01/08
C F M 56-5B Subtask 72-42-00-010-061 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-42-00-040-054 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041) Subtask 72-42-00-010-062 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-42-00-991-301) Subtask 72-42-00-010-063 A. Remove parts before borescope inspection. (1) Remove the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug. NOTE : If you remove the drain tube from the fuel nozzle adjacent to ____ the 6 oclock borescope plug, you will be required to perform a leak check after this inspection. Use the 6 oclock borescope port only if necessary. (2) Remove the borescope plugs from the approximate 1, 3, 6 and 10 oclock positions. (3) Remove both spark igniters (Ref. TASK 74-21-30-000-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 628 Nov 01/08
C F M 56-5B Subtask 72-42-00-290-055 B. Do a borescope inspection. (Ref. Fig. 607/TASK 72-42-00-991-307, 608/TASK 72-42-00-991-308) NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure ____ borescope and the lightsource are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (1) Connect the fiber light cable to the BORESCOPE-KIT (856A1320 P04 ot P05) and to the port on BORESCOPE-LIGHT SOURCE SET (856A1322 P03 or P04 or P07). (2) Put the rigid borescope, (856A1320 P04 or P05), into the left side ignitor position and turn on the light source of borescope-lightsource set. (3) Turn the borescope until you can see the deflector plate, sleeve, primary swirler, and the fuel nozzle tip that is located clockwise from the ignitor. (4) Inspect the position of the fuel nozzle tip to the bore of the primary swirler for the conditions as follows: (a) the tip of the fuel nozzle must be within the bore of the primary swirler. (b) if the fuel nozzle is out of position with the dome, refer to paragraph B.(10). (5) Do the fuel nozzle tip inspection for the fuel nozzle that is counterclockwise from the igniter. (6) Turn the borescope until you can see the second deflector and the second sleeve that is clockwise from the igniter. (7) Inspect the gap between the deflector and the spectacle plate on the inner liner side. The nominal dimension of the gap is 0.08 in. (2.03 mm). Inspect for the following: (a) the gap must be 0.3 in. (7.6 mm) max at the edge of the deflector (b) if the gap is over the max, refer to pargraph B.(10). (8) Do the deflector gap inspection for the second deflector counterclockwise from the igniter.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 629 Nov 01/08
C F M 56-5B
Combustion Chamber Inspection Figure 607/TASK 72-42-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 630 Nov 01/08
C F M 56-5B
Combustion Chamber Inspection Figure 608/TASK 72-42-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 631 Nov 01/08
C F M 56-5B (9) Do the inspection B.(1) thru B.(8) to the right side igniter and the borescope ports. (10) If any of the results of the inspections are out of limits, remove the fuel nozzle adjacent to the area. Insert the borescope and rotate to view the affected fuel nozzle and primary swirler. (11) Inspect the position of the fuel nozzle tip to the bore of the primary swirler. If the fuel nozzle is out of position with the primary swirler, remove the engine. There are no allowable service extensions that apply. (12) Do a one time borescope inspection between 200-400 hours after the birdstrike occurred (Ref. TASK 72-51-00-290-004) for NON/P hardware and (Ref. TASK 72-51-00-290-004) for /P hardware , but only look for leading edge missing material/burn through. (a) If no leading edge distress is seen, go back to the usual borescope inspection interval. (b) If missing material/burn through is seen on the HPT nozzle leading edge wall, contact CFMI. (13) When the inspection is complete, turn off the light source and remove the borescope. Subtask 72-42-00-410-060 C. Install parts removed for borescope inspection. (1) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (2) Install the borescope plugs. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE _______ COMBUSTOR BORESCOPE PLUGS DO NOT HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF BORESCOPE PLUGS WITH STEMS FROM OTHER LOCATIONS WILL RESULT IN THE STEM FEATURE BEING BURNED AWAY BY COMBUSTION GASES. (a) Install the borescope plugs and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (3) Safety the plug with lockwire 0.8 mm dia. (Material No. CP8001).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 632 Nov 01/08
C F M 56-5B (4) If necessary, install the fuel drain tube to the fuel nozzle adjacent to the six oclock borescope plug. TORQUE the coupling nuts on the fuel drain tube to between 120 and 135 lbf.in (1.35 and 1.52 m.daN) and safety with lockwire 0.8 mm dia. (Material No. CP8001) (5) Install the spark igniters (Ref. TASK 74-21-30-400-002). Subtask 72-42-00-790-052 D. Do a fuel nozzle leak check. (1) If you removed the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug, do a fuel nozzle leak check (Ref. TASK 73-1140-790-002). 5. Close-up ________ Subtask 72-42-00-410-061 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-42-00-440-054 B. Make the thrust reverser serviceable. (Ref. TASK 78-30-00-081-041) Subtask 72-42-00-410-062 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 633 Nov 01/08
C F M 56-5B TASK 72-42-00-290-007 Borescope Inspection of the Inner Cowl Bolts of the Combustion Chamber 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A1321 856A1322 856A1323
warning notice access platform 1 m (3 ft. 3 in.) 1 FIBERSCOPE SET 1 BORESCOPE-LIGHT SOURCE SET 1 MONITOR, RESOLUTION BORESCOPE
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 73-11-40-000-002 73-11-40-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 NTM 720000
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Fuel Nozzle Installation of the Fuel Nozzle Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 634 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-42-00-941-059 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-42-00-010-080 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform Subtask 72-42-00-040-059 C. Make the thrust reverser unserviceable for maintenance (Ref. TASK 78-3000-481-041) Subtask 72-42-00-010-081 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 635 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-42-00-010-082 A. Remove parts before borescope inspection. (1) Select fuel nozzles to remove that will allow access to the outer liner area to be inspected. (2) Remove the fuel nozzles (Ref. TASK 73-11-40-000-002) Subtask 72-42-00-290-066 B. Do a borescope inspection. (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure borescope and the light source are serviceable. See the Non Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Connect the fiber light cable to the FIBERSCOPE SET (856A1321P01 or 856A1321P03 or 856A1321P06) and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P03, P04, or P07). (3) Put the fiberscope of the FIBERSCOPE SET (856A1321P01 or 856A1321P03 or 856A1321P06) into the fuel nozzle ports and turn on the light source of BORESCOPE-LIGHT SOURCE SET (856A1322P03, or P04). (4) Adjust the borescope equipment to obtain maximum clarity of view. (5) Inspect the following: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Inner side of inner cowl for: A. Missing bolts
Not serviceable
See limit extensions
B. Loose bolts
Not serviceable
See limit extensions
C. Cracked bolt tack welds
Not serviceable
See limit extensions
(6) When the inspection is complete, turn off the light source and remove the fiberscope.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 636 Nov 01/08
C F M 56-5B Subtask 72-42-00-410-078 C. Install the fuel nozzles (Ref. TASK 73-11-40-400-002). 5. Close-up ________ Subtask 72-42-00-410-076 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-42-00-440-059 B. Make the thrust reverser serviceable after maintenance (Ref. TASK 78-3000-081-041). Subtask 72-42-00-410-077 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-42-00 201-249, 251-299, 301-399, 401-499, CES
Page 637 Nov 01/08
C F M 56-5B TURBINE SECTION - DESCRIPTION AND OPERATION ___________________________________________ 1. _______ General The modules of the turbine are the high pressure turbine and the low pressure turbine. A. High pressure turbine module (Ref. Fig. 001) The HPT module consists of 1-stage nozzle and rotor. The nozzles are supported by the HPT case, the rotor is attached to the high pressure compressor rotor. B. Low pressure turbine module (Ref. Fig. 002) The LPT module consists of 4-stage turbine, rotor, nozzles, stator case and rear frame. The rotor is connected to the fan. Surrounding the stator case is a clearance control manifold system.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-50-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
High Pressure Turbine Section Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-50-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Low Pressure Turbine Rotor/Stator Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-50-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B TURBINE SECTION - REMOVAL/INSTALLATION ______________________________________ TASK 72-50-00-920-001 Discard Life Limited Parts of HPT and LPT 1. __________________ Reason for the Job R
Refer to the MPD TASK: 725000-C2 2. ______________________ Job Set-up Information A. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-00-00-000-042 71-00-00-400-042 ESM 051103 ESM 051104 ESM 720052 ESM 720054
Removal of the Power Plant Installation of the Power Plant
3. __________ Job Set-up Subtask 72-50-00-010-051 A. Remove the engine (Ref. TASK 71-00-00-000-042). 4. Procedure _________ Subtask 72-50-00-020-051 A. Remove and discard life limited parts of the high pressure turbine (Ref. ESM 720052) and the low pressure turbine and (Ref. ESM 720054). NOTE : (Ref. ESM 051103) and (Ref. ESM 051104) for time limits. ____ 5. Close-up ________ Subtask 72-50-00-410-051 A. Install the engine (Ref. TASK 71-00-00-400-042).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-50-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B HPT NOZZLE ASSEMBLY - DESCRIPTION AND OPERATION _______________________________________________ 1. _______ General (Ref. Fig. 001, 002) The high pressure turbine (HPT) nozzle is a single-stage air cooled assembly that mounts in the combustion case and directs the gas flow from the combustion chamber onto the blades of the HPT rotor at the optimum angle. The major parts of the nozzle are 21 nozzle segments and inner support. The aft support and seal assembly, while not integral components of the HPT nozzle module are included since they attach to the HPT stator parts. 2. Description ___________ A. Nozzle Segments The HPT nozzle segments are assemblies of 2 vane/platform castings that are brazed together. Each vane is a cast shell divided into forward and aft compartments by an inner rib. The vanes and platforms are cooled by compressor discharge air entering the vane compartments through inserts in the inner and outer ends of vanes and exiting through the vane leading and trailing edges. The vanes and platforms are made of high strength nickel base alloy with protective coating on vane airfoils and on platform flowpath surfaces. B. Inner Support The nozzle inner support is a one-piece nickel base alloy ring. The major portion of the nozzle axial load is carried by the inner support through the bolted flanges of the support and nozzle inner platforms. The nozzle inner platform and the inner support form a seal ring which controls the amount of cooling air leakage that passes between the seal and the HPT blades. C. Aft Outer Support and Seal The aft outer support is a one-piece nickel base alloy ring that provides support for the 4-step honeycomb seal that mates with the HPT rotor inducer seal to help maintain the proper amount of cooling air flow and rotor thrust.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
High Pressure Turbine Nozzle Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Stage 1 HPT Nozzle Cooling Airflow Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B HPT NOZZLE ASSEMBLY - INSPECTION/CHECK ______________________________________ TASK 72-51-00-290-004 Borescope Inspection of High-Pressure Turbine Nozzle Assembly 1. __________________ Reason for the Job This TASK is applicable for NON/P engines. NOTE : Inspection of the high pressure turbine (HPT) nozzle assembly is ____ limited to the areas that can be seen with a rigid borescope at the 1, 3, 6, and 10 oclock borescope ports, and at the 2 spark igniter ports. The borescope ports at the 1, 3, 6, and 10 oclock position are located immediately in front of the fuel manifold. Special inspection of the HPT nozzle convex side can be accomplished, if required using with a flexible borescope. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific 856A1310 856A1320 856A1321 856A1322 856A1323 856A1351
1 1 1 1 1 1
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) KIT, BORESCOPE GUIDE - HP TURBINE BORESCOPE-KIT FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE GUIDE TUBE,BORESCOPE-HPT SHROUD
EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8mm) dia (Ref. 70-30-00) * lockwire 0.032 in. (0.8mm) dia (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 73-11-40-790-002 74-21-30-000-002 74-21-30-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-51-00-991-300 72-51-00-991-301
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Leak Check of the Fuel Nozzles Removal of the Spark Igniter Installation of the Spark Igniter Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602
3. __________ Job Set-up Subtask 72-51-00-941-051 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-51-00-010-053 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-51-00-040-051 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-51-00-010-054 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 601/TASK 72-51-00-991-300, 602/TASK 72-51-00-991-301) Subtask 72-51-00-010-056 A. Remove parts before borescope inspection. (1) Remove the borescope plugs from the approximate 3 and 10 oclock positions on the combustion case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B
Inspection of the High-Pressure Turbine-Nozzle Assembly Figure 601/TASK 72-51-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
HPT Nozzle Assembly Inspection, Convex Side Figure 602/TASK 72-51-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B Subtask 72-51-00-290-052 B. Do a Borescope Inspection (1) Connect the fiber light cable to the BORESCOPE-KIT (856A1320 P04 or P05), and to the porton BORESCOPE-LIGHT SOURCE SET (856A1322 P02 or P03 or P04 or P07 or P08). NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make ____ sure the borescope or the fiberscope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NDTM 720000). (2) Put the rigid borescope, of the BORESCOPE-KIT (856A1320/P04 or P05), into the ports and turn on the light source BORESCOPE-LIGHT SOURCE SET (856A1322/PO3 or PO4). (3) Rotate and adjust the borescope to view the HPT nozzle area. (4) If inspection of the nozzle convex side is necessary, use a FIBERSCOPE SET (856A1321 P01 or P03) and KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01), or GUIDE TUBE,BORESCOPE-HPT SHROUD (856A1351P01). NOTE : If KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01) is used to ____ view the convex side, an 8 ft. (2.43 m) fiberscope must be used. (5) Inspect the following: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Leading edge of vane airfoil for: A. Cracks that interconnect nose holes.
Any number, 0.3 in. (7.62 mm) long; no missing material.
See limit extension (Ref. TASK 72-00-00-200025).
B. Burns or spalling.
Any amount, burns through airfoil limited to 0.3 in. (7.62 mm) X 0.5 in. (12.7 mm) per vane, maximum of 4 vanes per 90-degree arc.
See limit extensions (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Baffle. NOTE : The airfoils baffle is visible inside the airfoil when missing ____ material occurs. It is sheet metal with cooling holes. (1) Cracks.
Any number.
(2) Missing material.
Any area equivalent to a rectangle defined by 4 adjacent holes.
See limit extension (Ref. TASK 72-00-00-200025).
A. Radial cracks extending out of gill holes.
Any number; no missing material.
See limit extension (Ref. TASK 72-00-00-200025).
B. Other cracks (not in gill hole rows).
Any number; no missing material.
See limit extension (Ref. TASK 72-00-00-200025).
C. Burns and cracks.
Any number; no missing material or burn through.
See limit extension (Ref. TASK 72-00-00-200025).
2. Concave surface of vane airfoil for:
3. Convex surface of vane airfoil for: A. Radial cracks.
Any number.
B. Axial cracks.
Any number.
C. Burns and bulges.
Any number.
See limit extension (Ref. TASK 72-00-00-200025).
D. Missing panel
Not serviceable.
See limit extension (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------E. Missing Thermal Any amount. Barrier Coating (TBC) 4. Trailing edge of vane airfoil for: A. Axial cracks starting from slots adjacent to trailing edge
Any number.
B. Burns and cracks.
Any number.
C. Buckling or bowing
Any amount.
D. Missing material (loss of metal).
Total area removed from trailing edge not to be more than 0.5 in. (12.7 mm) in axial direction.
See limit extension (Ref. TASK 72-00-00-200025).
5. All areas of airfoil for: A. Craze cracking.
Any amount.
NOTE : Craze cracking looks like many surface cracks that have no visual ____ width or depth. B. Nicks, scores, scratches and dents.
Any number.
C. Metal splatter.
Any amount.
D. Missing codep coating.
Any amount.
6. Inner and outer platform for: A. Cracks in parent metal.
Any number.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Missing metal or No through holes, but See limit extensions burning of parent any amount of missing (Ref. TASK 72-00-00-200metal. material from cracking 025). or burning is permitted. C. Nicks, scores, scratches and dents or platform surface.
Any amount.
D. Bulging and bowing.
Any amount.
E. Cracks in platform braze joint.
Any amount, no separation of braze joint allowed unless caused by burning.
(6) When the inspection is complete, turn off the light source and remove the borescope and the guide tube. (7) If any defects are found then remove additional borescope plugs and the spark igniters to inspect all of the HPT nozzle assembly. Subtask 72-51-00-010-055 C. Remove parts before borescope inspection. (1) Remove the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug. NOTE : If you remove the drain tube from the fuel nozzle adjacent to ____ the 6 oclock borescope plug, you will be required to perform a leak check after this inspection. Use the 6 oclock borescope port only if necessary. (2) Remove the borescope plugs from the approximate 1 and 6 oclock positions. (3) Remove both spark igniters (Ref. TASK 74-21-30-000-002)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B Subtask 72-51-00-290-053 D. Do a borescope inspection. (1) Repeat paragraph 4.B.(1) thru (6) for each borescope and spark igniter location. Subtask 72-51-00-410-054 E. Install parts removed for borescope inspection. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE COMBUSTOR _______ BORESCOPE PLUGS DO NOT HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF BORESCOPE PLUGS WITH STEMS FROM OTHER LOCATIONS WILL RESULT IN THE STEM FEATURE BEING BURNED AWAY BY COMBUSTION GASES. (1) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (2) Install the borescope plugs and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (3) Wirelock the plugs with lockwire 0.032 in. (0.8mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8mm) dia (Material No. CP8002). (4) If necessary, install the fuel drain tube to the fuel nozzle adjacent to the 6 oclock borescope plug. TORQUE the coupling nuts on the fuel drain tube to between 120 and 135 lbf.in (1.35 and 1.52 m.daN) and safety with lockwire 0.032 in. (0.8mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8mm) dia (Material No. CP8002) (5) Install the spark igniters (Ref. TASK 74-21-30-400-002). Subtask 72-51-00-790-050 F. Do a fuel nozzle leak check. (1) If you removed the drain tube from the fuel nozzle adjacent to the oclock borescope plug, do a fuel nozzle leak check (Ref. TASK 73-1140-790-002)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-51-00-410-052 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-51-00-440-051 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-51-00-410-053 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B TASK 72-51-00-290-004- 01 Borescope Inspection of High-Pressure Turbine Nozzle Assembly 1. __________________ Reason for the Job This TASK is applicable for /P and /3 engines. NOTE : Inspection of the high pressure turbine (HPT) nozzle assembly is ____ limited to the areas that can be seen with a rigid borescope at the 1, 3, 6, and 10 oclock borescope ports, and at the 2 spark igniter ports. The borescope ports at the 1, 3, 6, and 10 oclock position are located immediately in front of the fuel manifold. Special inspection of the HPT nozzle convex side can be accomplished, if required, with a flexible borescope. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific 856A1310 856A1320 856A1321 856A1322 856A1323 856A1351
1 1 1 1 1 1
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) KIT, BORESCOPE GUIDE - HP TURBINE BORESCOPE-KIT FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE GUIDE TUBE,BORESCOPE-HPT SHROUD
EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8mm) dia (Ref. 70-30-00) * lockwire 0.032 in. (0.8mm) dia (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 73-11-40-790-002 74-21-30-000-002 74-21-30-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-51-00-991-301
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Leak Check of the Fuel Nozzles Removal of the Spark Igniter Installation of the Spark Igniter Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 602
3. __________ Job Set-up Subtask 72-51-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-51-00-010-057 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-51-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-51-00-010-058 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 602/TASK 72-51-00-991-301) Subtask 72-51-00-010-059 A. Remove parts before borescope inspection. (1) Remove the borescope plugs from the approximate 3 and 10 oclock positions on the combustion case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B Subtask 72-51-00-290-054 B. Do a Borescope Inspection (1) Connect the fiber light cable to the BORESCOPE-KIT (856A1320 P04 or P05), and to the port on BORESCOPE-LIGHT SOURCE SET (856A1322 P02 or P03 or P04 or P07 or P08). NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make ____ sure the borescope or the fiberscope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NDTM 720000). (2) Put the rigid borescope, of the BORESCOPE-KIT (856A1320/P04 or P05), into the ports and turn on the light source BORESCOPE-LIGHT SOURCE SET (856A1322/PO3 or PO4). (3) Rotate and adjust the borescope to view the HPT nozzle area. (4) If inspection of the nozzle convex side is necessary, use a FIBERSCOPE SET (856A1321 P01 or P03) and KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01), or GUIDE TUBE,BORESCOPE-HPT SHROUD (856A1351P01). NOTE : If KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01) is used to ____ view the convex side, an 8 ft. (2.43 m) fiberscope must be used. (5) Inspect the following: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Leading edge of vane airfoil for: A. Cracks.
Any number, 0.3 in. (7.62 mm) long; no missing material.
See limit extension (Ref. TASK 72-00-00-200025).
B. Other cracks (not interconnecting nose holes).
Any number, 0.5 in. (12.7 mm) long; no missing material.
See limit extension (Ref. TASK 72-00-00-200025).
C. Baffle.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------NOTE : The airfoils baffle is visible inside the airfoil when missing ____ material occurs. It is sheet metal with cooling holes. (1) Cracks.
Any number.
(2) Missing material.
Any area equivalent to a rectangle defined by 4 adjacent holes.
See limit extension (Ref. TASK 72-00-00-200025).
D. Burns or missing material.
Any amount, burns through airfoil limited to 0.3 in. (7.62 mm) X 0.5 in. (12.7 mm) per vane, maximum of 4 vanes per 90 degree arc.
See limit extensions (Ref. TASK 72-00-00-200025).
E. Missing thermal barrier coating (TBC).
Any amount.
2. Concave surface of vane airfoil for: A. Cracks.
Any number.
See limit extension (Ref. TASK 72-00-00-200025).
B. Burns or missing material.
Any number; no missing material or burn through.
See limit extension (Ref. TASK 72-00-00-200025).
C. Missing thermal barrier coating (TBC).
Any amount.
3. Convex surface of vane airfoil for: A. Radial cracks.
Any number; no missing material
See limit extension (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Axial cracks. Any number; no missing See limit extension material (Ref. TASK 72-00-00-200025). C. Burns and bulges.
Any number; no missing material
D. Missing Thermal Barrier Coating (TBC)
Any amount.
See limit extension (Ref. TASK 72-00-00-200025).
4. Trailing edge of vane airfoil for: A. Axial cracks starting from slots adjacent to trailing edge
Any number.
B. Burns and cracks.
Any number.
C. Buckling or bowing
Any amount.
D. Missing material (loss of metal).
Total area removed from trailing edge not to be more than 0.5 in. (12.7 mm) in axial direction.
See limit extension (Ref. TASK 72-00-00-200025).
5. All areas of airfoil for: A. Craze cracking.
Any amount.
NOTE : Craze cracking looks like many surface cracks that have no visual ____ width or depth. B. Nicks, scores, scratches and dents.
Any number.
C. Metal splatter.
Any amount.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------6. Inner and outer platform for: A. Cracks in parent metal.
Any number.
B. Missing metal or burning of parent metal.
No through holes, but any amount of missing material from cracking or burning is permitted.
C. Nicks, scores, scratches and dents on platform surface.
Any amount.
D. Bulging and bowing.
Any amount.
E. Cracks in platform braze joint.
Any amount, no separation of braze joint allowed unless caused by burning.
See limit extensions (Ref. TASK 72-00-00-200025).
(6) When the inspection is complete, turn off the light source and remove the borescope and the guide tube. (7) If any defects are found then remove additional borescope plugs and the spark igniters to inspect all of the HPT nozzle assembly. Subtask 72-51-00-010-060 C. Remove parts before borescope inspection. (1) Remove the drain tube from the fuel nozzle adjacent to the 6 oclock borescope plug. NOTE : If you remove the drain tube from the fuel nozzle adjacent to ____ the 6 oclock borescope plug, you will be required to perform a leak check after this inspection. Use the 6 oclock borescope port only if necessary.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
C F M 56-5B (2) Remove the borescope plugs from the approximate 1 and 6 oclock positions. (3) Remove both spark igniters (Ref. TASK 74-21-30-000-002) Subtask 72-51-00-290-055 D. Do a borescope inspection. (1) Repeat paragraph 4.B.(1) thru (6) for each borescope and spark igniter location. Subtask 72-51-00-410-055 E. Install parts removed for borescope inspection. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE COMBUSTOR _______ BORESCOPE PLUGS DO NOT HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF BORESCOPE PLUGS WITH STEMS FROM OTHER LOCATIONS WILL RESULT IN THE STEM FEATURE BEING BURNED AWAY BY COMBUSTION GASES. (1) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (2) Install the borescope plugs and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (3) Wirelock the plugs with lockwire 0.032 in. (0.8mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8mm) dia (Material No. CP8002). (4) If necessary, install the fuel drain tube to the fuel nozzle adjacent to the 6 oclock borescope plug. TORQUE the coupling nuts on the fuel drain tube to between 120 and 135 lbf.in (1.35 and 1.52 m.daN) and safety with lockwire 0.032 in. (0.8mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8mm) dia (Material No. CP8002) (5) Install the spark igniters (Ref. TASK 74-21-30-400-002). Subtask 72-51-00-790-051 F. Do a fuel nozzle leak check. (1) If you removed the drain tube from the fuel nozzle adjacent to the oclock borescope plug, do a fuel nozzle leak check (Ref. TASK 73-1140-790-002)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 619 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-51-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the access platform(s). Subtask 72-51-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-51-00-410-057 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-51-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/08
C F M 56-5B HPT ROTOR ASSEMBLY - DESCRIPTION AND OPERATION ______________________________________________ 1. _______ General (Ref. Fig. 001) The high pressure turbine (HPT) rotor is a single-stage, air-cooled, high-efficiency turbine. Structurally the rotor consists of the front shaft, the forward air seal, the disk, and the rear shaft. 2. Description ___________ A. Front Shaft The front shaft forms the structural connection between the compressor rotor and the HPT rotor, and supports the aft end of the compressor rotor. B. Disk The HPT disk is a forged and machined part that retains the turbine blades in axial dovetail slots. The inner part of the disk is cooled by booster discharge air. The outer part of the disk is cooled by compressor discharge air. C. Rear Shaft The rear shaft is bolted to the aft side of the disk at a rabbeted flange and forms the aft support for the HPT rotor. The shaft is supported by the No. 4 roller bearing which rides on the low pressure shaft. Repairable abrasive-coated seals are machined as an integral part of the rear shaft. D. Front Outer Seal The front outer seal is bolted between the disk and the front shaft of the rotor. It forms a cavity between itself and the disk to direct compressor discharge air against the disk web and out through the turbine blades. The seal is a labyrinth inclined tooth form that reduces leakage past the seals. The seal teeth are abrasive coated and repairable. E. Blades (Ref. Fig. 002) The 80 HPT blades are made of a high temperature nickel alloy that has a high strength to weight ratio and are made in a single-crystal. Each blade has its own shank and dovetail. Compressor discharge air flows through the blades to decrease the temperature of the metal. The air flows through the root entrance holes, through eight internal cavities and out the holes in the leading edge, airfoil, tip, and trailing edges. The blades have a Thermal Barrier Coating (TBC) on the airfoil and platform to decrease the temperature of the metal. The TBC is a white ceramic that has a thickness of 0.006 in. (0.15 mm).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
High Pressure Turbine Rotor Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
HP Turbine Blade Cooling Airflow Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B HPT ROTOR ASSEMBLY - INSPECTION/CHECK _____________________________________ TASK 72-52-00-290-001 R
Borescope Inspection of HPT Blades (from the front and the rear) 1. __________________ Reason for the Job Refer to the MPD TASK: 725000-C1 This TASK is applicable for NON /P engines. Inspection of the high pressure turbine (HPT) blades from the rear is limited to the areas that can be seen with a rigid borescope, at the 5:30 and 8:30 oclock borescope ports (S16 and S17). The borescope ports at the 5:30 and 8:30 oclock positions are located immediately in front of the combustion case aft flange. Inspection of the HPT blades from the front can be accomplished, if required, with a flexible borescope through the spark igniter ports (S10 and S11) of the combustion case. NOTE : There are 80 HPT blades installed in the rotor. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No
specific specific specific specific specific
856A1320 856A1322 856A1323 856A1488
1 1 1 1
warning notice 0.75 in. square drive socket 2ft. long breaker bar access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) BORESCOPE-KIT BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE MOTOR, DRIVE - CORE ENGINE ROTATION
EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2619
Material No.
CP2656
Material No.
CP8001
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * lockwire 0.032in.(0.8mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-42-00-290-007 72-42-00-290-041 72-52-00-290-004 72-63-00-000-002 72-63-00-400-002
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Borescope Inspection of the Inner Cowl Bolts of the Combustion Chamber Borescope Inspection of the Combustion Chamber Liners and Dome Area Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-000-002 80-11-10-400-002 NTM 720000 72-52-00-991-304 72-52-00-991-300 72-52-00-991-301 72-52-00-991-302
Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. Fig. Fig. Fig.
601 602 603 604
3. __________ Job Set-up Subtask 72-52-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B Subtask 72-52-00-010-056 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform. Subtask 72-52-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-52-00-010-057 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 601/TASK 72-52-00-991-304, 602/TASK 72-52-00-991-300, 603/TASK 72-52-00-991-301, 604/TASK 72-52-00-991-302) Subtask 72-52-00-869-051 A. Prepare for inspection: (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure that the borescope or fiberscope and light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Install the tools to turn the core engine. NOTE : The core engine may be turned using a breaker bar (see step ____ (a)) or with a drive motor (see step (b)).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
Core Rotation Drive Motor Installation Figure 601/TASK 72-52-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
Inspection of the HPT Blade Figure 602/TASK 72-52-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Rub Wear Notches on the Blade Tip and Cracks (Only Applicable NON /P Engines) Figure 603/TASK 72-52-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B
High-Pressure Turbine Blade Inspection Areas (Only Applicable NON /P Engines) Figure 604/TASK 72-52-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B (a) To turn the core manually with a breaker bar, do the steps that follow: 1 _
Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter (Ref. TASK 72-63-00-000-002).
2 _
Install a 0.75 in. square drive socket with a 2ft. long breaker bar into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward). NOTE : To turn the core engine CW, the handcranking drive must ____ be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 _
Remove the starter (Ref. TASK 80-11-10-000-002).
2 _
Install the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488 P01 or P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad shaft and engage the splines. NOTE : The tool must be installed in the horizontal position ____ with the air hoses to the rear.
3 _
Turn the tool until the captive bolts align with the gearbox bolt holes.
4 _
Tighten the two captive bolts by hand.
5 _
Install the clamp to secure the drive motor.
6 _
Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 _
Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(3) Remove one of the borescope plugs (S16 or S17) found immediately in front of the aft flange of the combustion case at the 5:30 and 8:30 oclock positions.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B (4) Connect the fiber light cable to the BORESCOPE-KIT (856A1320 P04 or P05), and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07). (5) Put the rigid borescope of the BORESCOPE-KIT (856A1320 P04 or P05) into the borescope port and turn on the light source of BORESCOPELIGHT SOURCE SET (856A1322 P03 or P04). Subtask 72-52-00-290-053 B. Do a borescope inspection : (1) Look at the trailing edge, tip concave and convex side of the HPT blades as follows: NOTE : There are 80 HPT blades installed in the rotor. ____ (a) Adjust the borescope equipment to obtain maximum clarity of view. (b) Turn the HPT rotor CW (aft looking forward). Stop the rotor at each blade to make sure all of the defects can be seen. NOTE : To turn the HPT rotor CW, the rotation pad drive must be ____ turned counterclockwise (CCW). (c) Inspect the HPT blades (from the rear) and use the limits that follow: NOTE : It is not easy to visually tell when cooling holes are ____ plugged. Cooling holes which are apparently plugged are permitted if any cracking, erosion or burning is within serviceable limits. NOTE : Crack indications which are not completely identified may ____ be sprayed with stoddard solvent (Material No. CP2011) or acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or an equivalent substitute to remove light engine deposits. NOTE : If a HPT blade has impact damage, you must do a 360 degree ____ combustor borescope inspection to look for combustor distress (Ref. TASK 72-42-00-290-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B NOTE : For the purposes of estimating the size of any distress, ____ the radial spacing of the trailing edge slots is approximately 0.1 in. (2.54 mm). ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Trailing edge for: NOTE : Casting core ____ lines are permitted. A. Cracks in area C and root fillet. Make sure that discoloration, scratches or marks are not seen as cracks.
If cracks are less than 0.10 in. (2.54 mm) long, reinspect in 400 cycles. If the cracks are more than 0.10 in. (2.54 mm) but less than 0.20 in. (5.08 mm), reinspect in 200 cycles. Cracks longer than 0.20 in. (5.08 mm) are not allowed.
B. Cracks in area B.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Cracks in area A.
One permitted, 0.10in. (2,54 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
D. Missing material. Burning, or holes in tip and area A.
Any amount down to the first slot below the tip shelf.
See limit extensions (Ref. TASK 72-00-00-200025).
E. Plugged air passages in area C.
Not serviceable.
F. Plugged air passages in area B.
One permitted.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Plugged air One permitted. passages in area A. H. Nicks and dents, area A.
Any amount, if there are no cracks or torn metal.
J. Nicks and dents, areas B, C, and root fillet.
3 permitted, 0.057 in. (1.45 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
K. Bent material at the tip, areas B or C.
Any amount.
L. Missing thermal barrier coating.
Any amount.
2. Blade tip for: NOTE : There can be 2 or 4 notched blades in the HPT rotor that are used to ____ show blade tip wear. The blade tip wears as it rubs against the shroud. The number of notches that can be seen is an indication of tip wear. It is possible that all tip notches can be gone because of wear. Missing notches have no effect on the serviceable condition of the blade. A. Radial cracks on convex side.
Any number permitted 0.15 in. (3.81 mm) long.
See limits extension (Ref. TASK 72-00-00-200025).
B. Radial cracks on concave side.
Any number up to 0.7 in. (17.78 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Bent, curled or missing material.
Any amount within 0.15 in. (3.81 mm) of tip.
D. Missing thermal barrier coating.
Any amount.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------3. Convex and concave surfaces for: A. Nicks or dents, area A.
Any number, 0.25 in. (6.35 mm) long.
B. Nicks or dents, area B.
Any number, 0.1 in. (2.54 mm) long.
C. Nicks or dents, area C.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
D. Cracks in other areas.
Not serviceable.
E. Missing thermal barrier coating.
Any amount.
See limit extensions (Ref. TASK 72-00-00-200025).
4. Blade airfoil for: A. Distortions or evidence of burning or melting.
Not serviceable.
B. Missing codep coating.
Any amount.
C. Evidence of foreign object impact damage.
None allowed.
See limit extensions (Ref. TASK 72-00-00-200025).
Inspect combustion chamber inner cowl bolts (Ref. TASK 72-42-00-290007).
(2) When the inspection is complete, turn off the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07) and remove the BORESCOPE-KIT (856A1320 P04 or P05).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B (3) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (4) Install the borescope plug. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE TWO LPT _______ STAGE 1 NOZZLE BORESCOPE PLUGS HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF THESE PLUGS IN THE COMBUSTION CASE WILL RESULT IN THE STEM BEING BURNED AWAY BY COMBUSTION GASSES. (a) Install the borescope plug(s) and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (5) Safety the plugs with lockwire 0.032in.(0.8mm) dia. (Material No. CP8001). (6) If no defects were found remove the tools used to rotate the core as follows: NOTE : If the breaker bar is installed see steps (a) and (b). If the ____ drive motor is installed see steps (c) and (d). (a) Remove the 0.75 in. (19.05 mm) square drive socket and 2 ft. (0.60 m) breaker bar from the core rotation drive pad. (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002). (c) Remove the drive motor from the starter pad of the AGB. (d) Install the starter (Ref. TASK 80-11-10-400-002). (7) If defects were found do a borescope inspection of the HPT blades from the front (Ref. TASK 72-52-00-290-004).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-52-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors without making thrust reverser serviceable (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-52-00-440-053 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-52-00-410-057 C. Close Access (1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the warning notice(s). (3) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B TASK 72-52-00-290-001- 01 R
Borescope Inspection of HPT Blades (from the front and the rear) 1. __________________ Reason for the Job Refer to the MPD TASK: 725000-C1 This TASK is applicable for /P and /3 engines. Inspection of the high pressure turbine (HPT) blades from the rear is limited to the areas that can be seen with a rigid borescope, at the 5:30 and 8:30 oclock borescope ports (S16 and S17). The borescope ports at the 5:30 and 8:30 oclock positions are located immediately in front of the combustion case aft flange. Inspection of the HPT blades from the front can be accomplished, if required, with a flexible borescope through the spark igniter ports (S10 and S11) of the combustion case.
R
NOTE : There are 80 HPT blades installed in the rotor. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No No
specific specific specific specific specific
856A1320 856A1322 856A1323 856A1488
1 1 1 1
warning notice 0.75 in. square drive socket 2ft. long breaker bar access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) BORESCOPE-KIT BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE MOTOR, DRIVE - CORE ENGINE ROTATION
EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2619
Material No.
CP2656
Material No.
CP8001
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * lockwire 0.032in.(0.8mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-42-00-290-007 72-42-00-290-041 72-52-00-290-004 72-63-00-000-002 72-63-00-400-002
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Borescope Inspection of the Inner Cowl Bolts of the Combustion Chamber Borescope Inspection of the Combustion Chamber Liners and Dome Area Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-000-002 80-11-10-400-002 NTM 720000 72-52-00-991-304 72-52-00-991-300 72-52-00-991-305 72-52-00-991-306 72-52-00-991-308
Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. Fig. Fig. Fig. Fig.
601 602 605 606 607
3. __________ Job Set-up Subtask 72-52-00-941-055 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
C F M 56-5B Subtask 72-52-00-010-060 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform. Subtask 72-52-00-040-055 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-52-00-010-061 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 601/TASK 72-52-00-991-304, 602/TASK 72-52-00-991-300, 605/TASK 72-52-00-991-305, 606/TASK 72-52-00-991-306, 607/TASK 72-52-00-991-308) Subtask 72-52-00-869-052 A. Prepare for inspection: (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure that the borescope or fiberscope and light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Install the tools to turn the core engine. NOTE : The core engine may be turned using a breaker bar (see step ____ (a)) or with a drive motor (see step (b)).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 619 Nov 01/08
C F M 56-5B
HP Blade Cracks (Applicable /P and /3 Engines) Figure 605/TASK 72-52-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/08
C F M 56-5B
High-Pressure Turbine Blade Inspection Areas (Only Applicable /P and /3 Engines) Figure 606/TASK 72-52-00-991-306 R EFF : 001-049, 051-099, 101-149, 151-199, Page 621 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-52-00
C F M 56-5B
HPT Blade Inspection (Only Applicable /P and /3 Engines) Figure 607/TASK 72-52-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/08
C F M 56-5B (a) To turn the core manually with a breaker bar, do the steps that follow: 1 _
Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter (Ref. TASK 72-63-00-000-002).
2 _
Install a 0.75 in. square drive socket with a 2ft. long breaker bar into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward). NOTE : To turn the core engine CW, the handcranking drive must ____ be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 _
Remove the starter (Ref. TASK 80-11-10-000-002).
2 _
Install the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488 P01 or P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad shaft and engage the splines. NOTE : The tool must be installed in the horizontal position ____ with the air hoses to the rear.
3 _
Turn the tool until the captive bolts align with the gearbox bolt holes.
4 _
Tighten the two captive bolts by hand.
5 _
Install the clamp to secure the drive motor.
6 _
Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 _
Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(3) Remove one of the borescope plugs (S16 or S17) found immediately in front of the aft flange of the combustion case at the 5:30 and 8:30 oclock positions.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 623 Nov 01/08
C F M 56-5B (4) Connect the fiber light cable to the BORESCOPE-KIT (856A1320 P04 or P05), and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07). (5) Put the rigid borescope of the BORESCOPE-KIT (856A1320 P04 or P05) into the borescope port and turn on the light source of BORESCOPELIGHT SOURCE SET (856A1322 P03 or P04). Subtask 72-52-00-290-055 B. Do a borescope inspection: (1) Look at the trailing edge, tip concave and convex side of the HPT blades as follows: (a) Adjust the borescope equipment to obtain maximum clarity of view. (b) Turn the HPT rotor CW (aft looking forward). Stop the rotor at each blade to make sure all of the defects can be seen. NOTE : To turn the HPT rotor CW, the rotation pad drive must be ____ turned counterclockwise (CCW). (c) Inspect the HPT blades (from the rear) and use the limits that follow: NOTE : It is not easy to visually tell when cooling holes are ____ plugged. Cooling holes which are apparently plugged are permitted if any cracking, erosion or burning is within serviceable limits. NOTE : Crack indications which are not completely identified may ____ be sprayed with stoddard solvent (Material No. CP2011) or acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or an equivalent substitute to remove light engine deposits. NOTE : If a HPT blade has impact damage, you must do a 360-degree ____ combustor borescope inspection to look for combustor distress (Ref. TASK 72-42-00-290-041) and inner cowl bolts (Ref. TASK 72-42-00-290-007).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 624 Nov 01/08
C F M 56-5B NOTE : For the purposes of estimating the size of any distress, ____ the radial spacing of the trailing edge slots is approximately 0.1 in. (2.54 mm). ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Trailing edge for: NOTE : Casting core ____ lines are permitted. A. Cracks in area B and C including root filet. Make sure that discoloration, scratches or marks are not seen as cracks.
For a crack up to 0.12 in. (3.0 mm) in length, the maximum reinspection interval is 400 cycles. For a crack more than 0.12 in. (3.0 mm) and up to 0.20 in. (5.1 mm) in length, the maximum reinspection interval is 200 cycles.
See limit extensions (Ref. TASK 72-00-00-200025).
B. Cracks in area A.
One permitted, 0.10in. (2.54 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Missing material. Burning, or holes in tip and area A.
No limit, as long as the missing material is not more than 0.50 in. x 0.50 in. (12.7 mm x 12.7 mm).
See limit extensions (Ref. TASK 72-00-00-200025).
D. Missing thermal barrier coating.
Any amount.
E. Plugged air passages in area C.
Not serviceable.
F. Plugged air passages in area B.
One permitted.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 625 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Plugged air One permitted. passages in area A. Any amount, if there are no cracks or torn metal.
J. Nicks and dents, areas B, C, and root fillet.
No limit, as long as the nicks and dents are not more than 0.01 in. (0.25 mm) long.
K. Bent material at the tip, areas B or C.
Any amount.
R R R R
H. Nicks and dents, area A.
2. Blade tip for: NOTE : There can be 2 or 4 notched blades in the HPT rotor that are used to ____ show blade tip wear. The blade tip wears as it rubs against the shroud. The number of notches that can be seen is an indication of tip wear. It is possible that all tip notches can be gone because of wear. Missing notches have no effect on the serviceable condition of the blade. A. Radial cracks on convex side not within 0.5 in. (12.7 mm) of trailing edge.
Any number up to 0.15 in. (3.81 mm) long.
See limits extension (Ref. TASK 72-00-00-200025).
B. Radial cracks on concave side not within 0.5 in. (12.7 mm) of trailing edge.
Any number up to 0.7 in. (17.78 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Bent, curled or missing material.
Any amount above tip shelf.
See limit extensions (Ref. TASK 72-00-00-200025).
D. Radial cracks (convex or
Any amount.
EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 626 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------concave) within 0.50 in. (12.7 mm) of trailing edge. E. Missing thermal barrier coating.
Any amount.
3. Convex and concave surfaces for: A. Nicks or dents, area A.
Any number, 0.25 in. (6.35 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
B. Nicks or dents, area B.
Any number, 0.1 in. (2.54 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Nicks or dents, area C.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
See limit extensions (Ref. TASK 72-00-00-200025).
D. Cracks in other areas.
Not serviceable.
E. Missing thermal barrier coating.
Any amount.
4. Blade airfoil for: A. Distortions or evidence of burning or melting.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
(2) When the inspection is complete, turn off the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07) and remove the BORESCOPE-KIT (856A1320 P04 or P05).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Nov 01/08
C F M 56-5B (3) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces. (4) Install the borescope plug. CAUTION : BE SURE TO INSTALL THE CORRECT BORESCOPE PLUGS. THE TWO LPT _______ STAGE 1 NOZZLE BORESCOPE PLUGS HAVE A STEM FEATURE. INADVERTENT INSTALLATION OF THESE PLUGS IN THE COMBUSTION CASE WILL RESULT IN THE STEM BEING BURNED AWAY BY COMBUSTION GASSES. (a) Install the borescope plug(s) and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (5) Safety the plugs with lockwire 0.032in.(0.8mm) dia. (Material No. CP8001). (6) If no defects were found remove the tools used to rotate the core as follows: NOTE : If the breaker bar is installed see steps (a) and (b). If the ____ drive motor is installed see steps (c) and (d). (a) Remove the 0.75 in. (19.05 mm) square drive socket and 2 ft. (0.60 m) breaker bar from the core rotation drive pad. (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002). (c) Remove the drive motor from the starter pad of the AGB. (d) Install the starter (Ref. TASK 80-11-10-400-002). (7) If defects were found do a borescope inspection of the HPT blades from the front (Ref. TASK 72-52-00-290-004).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 628 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-52-00-410-060 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors without making thrust reverser serviceable (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-52-00-440-055 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-52-00-410-061 C. Close Access (1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the warning notice(s). (3) Remove the access platform(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 629 Nov 01/08
C F M 56-5B TASK 72-52-00-290-004 Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) 1. __________________ Reason for the Job This TASK is applicable for NON /P engines. Inspection of the high pressure turbine (HPT) blades from the front is limited to the areas that can be seen with a flexible borescope installed at the spark igniter ports (S10 and S11). NOTE : There are 80 HPT blades installed in the rotor. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific No specific 856A1310 856A1321 856A1322 856A1323 856A1488
1 1 1 1 1
access platform protective caps warning notice 0.75 in. square drive socket 2ft. long breaker bar KIT, BORESCOPE GUIDE - HP TURBINE FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE MOTOR, DRIVE - CORE ENGINE ROTATION
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-42-00-290-005 72-63-00-000-002 72-63-00-400-002 74-21-30-000-002 74-21-30-400-002
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Removal of the Spark Igniter Installation of the Spark Igniter
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 630 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-000-002 80-11-10-400-002 NTM 720000 72-52-00-991-304 72-52-00-991-300 72-52-00-991-301 72-52-00-991-302 72-52-00-991-303
Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. Fig. Fig. Fig. Fig.
601 602 603 604 608
3. __________ Job Set-up Subtask 72-52-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 631 Nov 01/08
C F M 56-5B Subtask 72-52-00-010-054 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-52-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-52-00-010-055 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 601/TASK 72-52-00-991-304, 602/TASK 72-52-00-991-300, 603/TASK 72-52-00-991-301, 604/TASK 72-52-00-991-302, 608/TASK 72-52-00-991-303) Subtask 72-52-00-290-052 A. Prepare for inspection: (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure the borescope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Install the tools to turn the core engine. NOTE : The core engine may be turned using a breaker bar (see step ____ (a)) or with a drive motor (see step (b)).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 632 Nov 01/08
C F M 56-5B
High-Pressure Turbine Blade (Only Applicable NON /P Engines) Figure 608/TASK 72-52-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 633 Nov 01/08
C F M 56-5B (a) To turn the core manually with a breaker bar, do the steps that follow: 1 _
Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter (Ref. TASK 72-63-00-000-002).
2 _
Install a 0.75 in. square drive socket with a 2ft. long breaker bar into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward). NOTE : To turn the core engine CW, the handcranking drive must ____ be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 _
Remove the starter (Ref. TASK 80-11-10-000-002).
2 _
Install the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488 P01 or P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad drive shaft and engage the splines. NOTE : The tool must be installed in the horizontal position ____ with the air hoses to the rear.
3 _
Turn the tool until the captive bolts align with the gearbox bolt holes.
4 _
Tighten the two captive bolts by hand.
5 _
Install the clamp to secure the drive motor.
6 _
Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 _
Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(3) Remove either one of the spark igniters (Ref. TASK 74-21-30-000-002). (4) Install the protective caps on the lead and the spark igniter. (5) Put the KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01) over the straightening rod.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 634 Nov 01/08
C F M 56-5B (6) Push the plastic guide tube and straightening rod into the combustion chamber through the spark igniter port (S10 or S11) as far as it will go. (7) Turn the pointed tab on the plastic guide tube to the rear of the engine and remove the straightening rod from the plastic guide tube. (8) Installation of the borescope: CAUTION : FOLLOW THE INSTRUCTIONS CAREFULLY FOR INSERTING OR REMOVING _______ THE FLEXIBLE BORESCOPE. DOING THE PROCEDURE INCORRECTLY WILL DAMAGE THE TIP CONTROL FUNCTION. (a) Connect the fiber light cable to the FIBERSCOPE SET (856A1321 P01 or P03) to the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07). (b) Align the borescope lens with one of the plastic tabs on the guide tube and install it into the tube. Make sure that the borescope tip is not moved up or down when putting it into the plastic guide tube. (c) Push the borescope through the plastic guide tube until the tip comes out of the end of the tube. (d) Push the tip of the borescope between the nozzle vanes by using the tip deflection control. (e) Turn on the light source of the BORESCOPE-LIGHT SOURCE SET (856A1322 P03 or P04). (f) Adjust the borescope equipment to get maximum clarity of view. (9) Turn the HPT rotor CW (aft looking forward). Stop the rotor at each blade to make sure all of the defects can be seen. NOTE : To turn the HPT rotor CW, the rotation pad drive must be ____ turned CCW. (10) Inspect the HPT blades (from the front) and use the limits that follow: NOTE : It is not easy to visually tell when cooling holes are ____ plugged. Cooling holes which are apparently plugged are permitted if any cracking, erosion or burning is within serviceable limits.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 635 Nov 01/08
C F M 56-5B NOTE : Crack indications which are not completely identified may be ____ sprayed with solvent (CP2011) or an equivalent substitute to remove light engine deposits. NOTE : When a HPT blade has impact damage, you must do a 360 degree ____ combustor borescope inspection to look for combustor distress (Ref. TASK 72-42-00-290-005). NOTE : For purposes of estimating the size of any distress, the ____ radial spacing of the trailing edge slots is approximately 0.1 in. (2.55 mm). ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Leading edge for: A. Axial and radial cracks in area A.
Any number 0.05 in. (1.27 mm) long if they do not connect more than 2 holes.
B. Axial and radial cracks in areas B and C, including root radius not intersecting nose or gill holes.
Not serviceable.
C. Nicks and dents in area A.
Any amount.
D. Nicks and dents in area B.
Any amount.
E. Nicks and dents in area C, including root radius.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
F. Axial nose or gill hole cracks, areas B and C.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
See limit extensions (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 636 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Radial nose or None allowed in area C, See limit extensions gill hole cracks, one permitted, 0.03 in. (Ref. TASK 72-00-00-200areas B and C. (0.76 mm) long in area 025). B. H. Dirt or environmental build-up.
Any amount.
J. Missing material in areas A and B.
Any amount provided cavity 2 not exposed (max 2 blades per engine). Repeat the inspection within 100 hours.
K. Missing material in area C.
Not serviceable.
L. Missing thermal barrier coating.
Any amount.
See limit extensions (Ref. TASK 72-00-00-200025).
2. Blade tip for: NOTE : There are 4 notched blades (90 degrees apart) in the HPT rotor to ____ show the amount of blade tip rubbing. If the notches can or cannot be seen, the condition is serviceable. A. Radial cracks on concave side.
Any number permitted 0.7 in. (17.78 mm) max radial length.
B. Bent, curled or missing material.
Any amount within 0.2 in. (5.08 mm) of tip.
C. Missing thermal barrier coating.
Any amount.
See limit extensions (Ref. TASK 72-00-00-200025).
3. Concave and convex surfaces for: A. Nicks or dents, area A.
Any number 0.25 in. (6.35 mm) long.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 637 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Nicks or dents, Any number, 0.1 in. area B. (2.54 mm) long. C. Nicks or dents, area C.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
D. Cracks, other areas.
Not serviceable.
E. Missing thermal barrier coating.
Any amount.
4. Blade airfoil for: A. Distortions or evidence of burning or melting.
Not serviceable.
B. Missing codep coating.
Any amount.
C. Missing thermal barrier coating.
Any amount.
(11) When the inspection is completed, turn off the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07) and remove the FIBERSCOPE SET (856A1321 P01 or P03) and guide tube. (12) Install the spark igniter (Ref. TASK 74-21-30-400-002). (13) Tools used to rotate the core as follows: (14) Remove the tools used to rotate the core as follows: NOTE : If the breaker bar is installed see steps (a) and (b). If the ____ drive motor is installed see steps (c) and (d). (a) Remove the 0.75 in. (19.05 mm) square drive socket and 2 ft. (0.6 mm) breaker bar from the core rotation drive pad.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 638 Nov 01/08
C F M 56-5B (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002). (c) Remove the drive motor from the starter pad of the AGB. (d) Install the starter (Ref. TASK 80-11-10-400-002). 5. Close-up ________ Subtask 72-52-00-410-054 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-52-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-52-00-410-055 C. Close Access (1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 639 Nov 01/08
C F M 56-5B TASK 72-52-00-290-004- 01 Borescope Inspection of the High Pressure Turbine Rotor Blade (from the front) 1. __________________ Reason for the Job This TASK is applicable for /P engines. Inspection of the high pressure turbine (HPT) blades from the front is limited to the areas that can be seen with a flexible borescope installed at the spark igniter ports (S10 and S11). NOTE : There are 80 HPT blades installed in the rotor. ____ 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific No specific 856A1310 856A1321 856A1322 856A1323 856A1488
1 1 1 1 1
access platform protective caps warning notice 0.75 in. square drive socket 2ft. long breaker bar KIT, BORESCOPE GUIDE - HP TURBINE FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE MOTOR, DRIVE - CORE ENGINE ROTATION
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-42-00-290-005 72-63-00-000-002 72-63-00-400-002 74-21-30-000-002 74-21-30-400-002
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Inspection of the Combustion Chamber and HPT Nozzle Following a Birdstrike/FOD Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Removal of the Spark Igniter Installation of the Spark Igniter
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 640 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 80-11-10-000-002 80-11-10-400-002 NTM 720000 72-52-00-991-304 72-52-00-991-300 72-52-00-991-305 72-52-00-991-306 72-52-00-991-307
Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. Fig. Fig. Fig. Fig.
601 602 605 606 609
3. __________ Job Set-up Subtask 72-52-00-941-054 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 641 Nov 01/08
C F M 56-5B Subtask 72-52-00-010-058 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-52-00-040-054 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-52-00-010-059 D. Open the thrust reverser cowl doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR. 4. Procedure _________ (Ref. Fig. 601/TASK 72-52-00-991-304, 602/TASK 72-52-00-991-300, 605/TASK 72-52-00-991-305, 606/TASK 72-52-00-991-306, 609/TASK 72-52-00-991-307) Subtask 72-52-00-290-054 A. Prepare for inspection: (1) Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make sure the borescope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NTM 720000). (2) Install the tools to turn the core engine. NOTE : The core engine may be turned using a breaker bar (see step ____ (a)) or with a drive motor (see step (b)).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 642 Nov 01/08
C F M 56-5B
High-Pressure Turbine Blade (Only Applicable /P and /3 Engines) Figure 609/TASK 72-52-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 643 Nov 01/08
C F M 56-5B (a) To turn the core manually with a breaker bar, do the steps that follow: 1 _
Remove the handcranking drive cover from the core rotation pad on the left side of the accessory gearbox (AGB), opposite the starter (Ref. TASK 72-63-00-000-002).
2 _
Install a 0.75 in. square drive socket with a 2ft. long breaker bar into the handcranking drive pad. When you do the borescope inspection, turn the core engine clockwise (CW, aft looking forward). NOTE : To turn the core engine CW, the handcranking drive must ____ be turned counterclockwise (CCW).
(b) To turn the core with a drive motor, do the steps that follow: 1 _
Remove the starter (Ref. TASK 80-11-10-000-002).
2 _
Install the MOTOR, DRIVE - CORE ENGINE ROTATION (856A1488 P01 or P02) into the accessory gearbox (AGB) starter drive pad. Align the drive shaft of the drive motor with the starter drive pad drive shaft and engage the splines. NOTE : The tool must be installed in the horizontal position ____ with the air hoses to the rear.
3 _
Turn the tool until the captive bolts align with the gearbox bolt holes.
4 _
Tighten the two captive bolts by hand.
5 _
Install the clamp to secure the drive motor.
6 _
Attach the foot or hand control air hoses to the quick disconnects on the tool.
7 _
Connect the air supply to the drive motor. The air supply must be capable of 100 psi (6.9 bar). The air supply must be lubricated and filtered at 6 SCFM (170 L/minute).
(3) Remove either one of the spark igniters (Ref. TASK 74-21-30-000-002). (4) Install the protective caps on the lead and the spark igniter. (5) Put the KIT, BORESCOPE GUIDE - HP TURBINE (856A1310G01) over the straightening rod.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 644 Nov 01/08
C F M 56-5B (6) Push the plastic guide tube and straightening rod into the combustion chamber through the spark igniter port (S10 or S11) as far as it will go. (7) Turn the pointed tab on the plastic guide tube to the rear of the engine and remove the straightening rod from the plastic guide tube. (8) Installation of the borescope: CAUTION : FOLLOW THE INSTRUCTIONS CAREFULLY FOR INSERTING OR REMOVING _______ THE FLEXIBLE BORESCOPE. DOING THE PROCEDURE INCORRECTLY WILL DAMAGE THE TIP CONTROL FUNCTION. (a) Connect the fiber light cable to the FIBERSCOPE SET (856A1321 P01 or P03) to the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07). (b) Align the borescope lens with one of the plastic tabs on the guide tube and install it into the tube. Make sure that the borescope tip is not moved up or down when putting it into the plastic guide tube. (c) Push the borescope through the plastic guide tube until the tip comes out of the end of the tube. (d) Push the tip of the borescope between the nozzle vanes by using the tip deflection control. (e) Turn on the light source of the BORESCOPE-LIGHT SOURCE SET (856A1322 P03 or P04). (f) Adjust the borescope equipment to get maximum clarity of view. (9) Turn the HPT rotor CW (aft looking forward). Stop the rotor at each blade to make sure all of the defects can be seen. NOTE : To turn the HPT rotor CW, the rotation pad drive must be ____ turned CCW. (10) Inspect the HPT blades (from the front) and use the limits that follow: NOTE : It is not easy to visually tell when cooling holes are ____ plugged. Cooling holes which are apparently plugged are permitted if any cracking, erosion or burning is within serviceable limits.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 645 Nov 01/08
C F M 56-5B NOTE : Crack indications which are not completely identified may be ____ sprayed with solvent (CP2011) or an equivalent substitute to remove light engine deposits. NOTE : When a HPT blade has impact damage, you must do a 360 degree ____ combustor borescope inspection to look for combustor distress (Ref. TASK 72-42-00-290-005). NOTE : For purposes of estimating the size of any distress, the ____ radial spacing of the trailing edge slots is approximately 0.1 in. (2.55 mm) . ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Leading edge for: A. Axial and radial cracks in area A.
Any number 0.05 in. (1.27 mm) long if they do not connect more than 2 holes.
B. Axial and radial cracks in areas B and C, including root radius not intersecting nose or gill holes.
Not serviceable.
C. Nicks and dents in area A.
Any amount.
D. Nicks and dents in area B.
Any amount.
E. Nicks and dents in area C, including root radius.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
F. Axial nose or gill hole cracks, areas B and C.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
See limit extensions (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 646 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Radial nose or None allowed in area C, See limit extensions gill hole cracks, one permitted, 0.03 in. (Ref. TASK 72-00-00-200areas B and C. (0.76 mm) long in area 025). B. H. Dirt or environmental build-up.
Any amount.
J. Missing material in areas A and B.
Any amount provided cavity 2 not exposed (max 2 blades per engine). Repeat the inspection within 100 hours.
K. Missing material in area C.
Not serviceable.
L. Missing thermal barrier coating.
Any amount.
See limit extensions (Ref. TASK 72-00-00-200025).
2. Blade tip for: NOTE : There are 2 notched blades in the HPT rotor to show the amount of ____ blade tip rubbing. If the notches can or cannot be seen, the condition is serviceable. A. Radial cracks on convex side not within 0.50 in. (12.7 mm) of trailing edge.
Any number up to 0.15 in. (3.8 mm) max radial length.
See limit extensions (Ref. TASK 72-00-00-200025).
B. Radial cracks on concave side not within 0.50 in. (12.7 mm) of trailing edge.
Any number up to 0.7 in. (17.8 mm) max length.
See limit extensions (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 647 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------C. Radial cracks Any amount. (convex or concave) within 0.50 in. (12.7 mm) of trailing edge. D. Bent, curled or missing material.
Any amount above tip shelf.
E. Missing thermal barrier coating.
Any amount.
See limit extensions (Ref. TASK 72-00-00-200025).
3. Concave and convex surfaces for: A. Nicks or dents, area A.
Any number 0.25 in. (6.35 mm) long.
B. Nicks or dents, area B.
Any number, 0.1 in. (2.54 mm) long.
C. Nicks or dents, area C.
3 permitted, 0.05 in. (1.27 mm) long. Nicks and dents must be separated by 0.125 in. (3.17 mm) minimum.
D. Cracks,other areas.
Not serviceable.
E. Missing thermal barrier coating.
Any amount.
4. Blade airfoil for: A. Distortions or evidence of burning or melting.
Not serviceable.
B. Missing thermal barrier coating.
Any amount.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 648 Nov 01/08
C F M 56-5B (11) When the inspection is completed, turn off the BORESCOPE-LIGHT SOURCE SET (856A1322 P03, P04 or P07) and remove the FIBERSCOPE SET (856A1321 P01 or P03) and guide tube. (12) Install the spark igniter (Ref. TASK 74-21-30-400-002). (13) Tools used to rotate the core as follows: (14) Remove the tools used to rotate the core as follows: NOTE : If the breaker bar is installed see steps (a) and (b). If the ____ drive motor is installed see steps (c) and (d). (a) Remove the 0.75 in. (19.05 mm) square drive socket and 2 ft. (0.6 mm) breaker bar from the core rotation drive pad. (b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400002). (c) Remove the drive motor from the starter pad of the AGB. (d) Install the starter (Ref. TASK 80-11-10-400-002). 5. Close-up ________ Subtask 72-52-00-410-058 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-52-00-440-054 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 649 Nov 01/08
C F M 56-5B Subtask 72-52-00-410-059 C. Close Access (1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-52-00 201-249, 251-299, 301-399, 401-499, CES
Page 650 Nov 01/08
C F M 56-5B HPT SHROUD AND STAGE 1 LPT NOZZLE ASSEMBLY - DESCRIPTION AND OPERATION ______________________________________________________________________ 1. _______ General (Ref. Fig. 001) A. HPT shroud and stage 1 LPT nozzle assembly (1) The high pressure turbine (HPT) shroud and stage 1 low pressure turbine (LPT) nozzle assembly is located inside the aft end of the combustion case. It forms the interface between the core section and the LPT module of the engine. The forward flange of the assembly is rabbeted and bolted to the inner surfaces of the combustion case. The aft flange is bolted between the combustion case aft flange and the LPT stator forward flange. (2) The shroud/nozzle support has a thermal response matched to the rotor to provide good tip clearance control and structural stability. An air cavity between the shroud/nozzle support and the combustion case directs mixed 5th and 9th stage compressor bleed air onto the support and the outer, or backside, of the shrouds. This cooling air maintains closer clearances between the shrouds and the rotor blades. (3) The stage 1 LPT nozzles direct the core engine exhaust gas onto the stage one LPT blades. An air cavity between the stage one nozzle support and the combustion case directs 5th stage compressor bleed air through the nozzle vanes for cooling. After passing through the vanes, the air pressurizes and cools the cavity between the aft side of the HPT rotor and the forward side of the LPT rotor. 2. Description ___________ A. HPT shroud and stage 1 LPT nozzle assembly The HPT shroud and stage 1 LPT nozzle assembly consists of the shroud/nozzle support and HPT shrouds, and the stage 1 nozzles, inner air seal, and stationary air seal. (1) The shroud/nozzle support forms the outer shell of the assembly and provides an air space or manifold area between the outer shell and the combustion case. High pressure compressor (HPC) bleed air is introduced into the manifold area to provide cooling for the HPT shrouds and the LPT nozzles. (2) The HPT shrouds have a smooth abrasive rub surface that is tolerant to localized blade tip rubs and has good resistance to erosion from hot exhaust gases. The shrouds are held in place on the support by retainers and are individually replaceable.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
HPT Shroud and Stage 1 LPT Nozzle Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B (3) The assembly has 28 LPT nozzle segments, each having 3 vanes. The nozzle segments are installed in the shroud/nozzle support and are held in place on the nozzle inner air seal by the stationary air seal which is bolted on the aft face of the inner air seal. The assembly is bolted between the LPT case forward flange and the combustion case aft flange. Borescope ports at 5.30 and 8.30 oclock positions (ALF) are provided in the support to allow inspection of the nozzle area.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B HPT SHROUD AND STAGE 1 LPT NOZZLE ASSEMBLY - INSPECTION/CHECK _____________________________________________________________ TASK 72-53-00-290-003 Borescope/Inspection of the Stage 1 Low-Pressure Turbine Nozzle Assembly 1. __________________ Reason for the Job Inspection of the low pressure turbine (LPT) nozzle is limited to the areas that can be seen with a rigid borescope. Insert the borescope through the borescope ports located on stage 1 LPT nozzle support. If no defects are found then the borescope inspection is complete. If defects are found then look at the high-pressure turbine (HPT) shrouds. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No specific No specific No specific
warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET 1 MONITOR, RESOLUTION BORESCOPE
856A1320 856A1322 856A1323
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-53-00-290-004 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-53-00-991-300 72-53-00-991-301
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Borescope/Inspection of the High-Pressure Turbine Shroud Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602
3. __________ Job Set-up Subtask 72-53-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B Subtask 72-53-00-010-055 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-53-00-040-052 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-53-00-010-058 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-53-00-991-300, 602/TASK 72-53-00-991-301) Subtask 72-53-00-020-051 A. Remove the borescope plugs found immediately in front of the aft flange of the combustion case. Subtask 72-53-00-290-052 B. Do a borescope inspection. (1) Connect the fiber light cable to the BORESCOPE-KIT (856A1320P04/P05) and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make ____ sure the borescope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure (Ref. NDTM 720000).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B
Stage 1 LPT Nozzle and HPT Shroud Inspection Figure 601/TASK 72-53-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
Stage 1 LPT Nozzle Segment Figure 602/TASK 72-53-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B (2) Put the rigid borescope of the BORESCOPE-KIT (856A1320P04/P05), and to the port into turn on the light source of BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). (3) Inspect the stage 1 LPT nozzle and use the limits that follow : ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Stage 1 LPT nozzle for: A. Cracks in leading edge.
Any number, that are not more than 0.6 in. (15.24 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
B. Cracks in trailing edge.
Any number, that are not more than 0.8 in. (20.32 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
C. Cracks on concave/convex side of airfoil between inner and outer platform.
Any number, that are not more than 1 in. (25.4 mm) long. If there is a separation of 0.25 in. between adjacent crack.
See limit extensions (Ref. TASK 72-00-00-200025).
D. Crack in radius in between airfoil L.E./T.E. and outer platform.
One on each airfoil, not more than 1.2 in. (30 mm) long with a minimum of 0.4 in. (10 mm) from any adjacent crack.
See limit extensions (Ref. TASK 72-00-00-200025).
E. Burns, erosion and corrosion
Any amount, if there is no missing material (no perforation of the airfoil cavity).
See limit extensions (Ref. TASK 72-00-00-200025).
F. Nicks, scores, scratches, dents or deposits on concave/convex surface or trailing edge
Any amount, not through, provided there are no cracks out of distressed area.
See limit extensions (Ref. TASK 72-00-00-200025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------G. Nicks, dents, Any amount, if cracks See limit extensions tears in leading criteria are in the (Ref. TASK 72-00-00-200edge. limits. 025). H. Cracks in outer platform forward lip.
Two on each nozzle segment 0.59 in. (15 mm) apart minimum, if they run axially and do not grow longer circumferentially.
J. Cracks in inner or outer platform.
For NON /P engines. Any number no longer than 0.59 in. (15 mm). For /P engines. Three cracks per segment not to exceed 0.59 in. (15 mm) long and Metal does not go into the gaspath.
K. Craze cracking
Any amount
See limit extensions (Ref. TASK 72-00-00-200025).
NOTE : Craze cracking is defined as numerous superficial surface ____ cracks which have no visual width or depth. (4) If defects are found, look at the HPT shrouds (Ref. TASK 72-53-00290-004). Subtask 72-53-00-080-052 C. When the inspection is complete, turn off the light source BORESCOPELIGHT SOURCE SET (856A1322P02/ P03/P04/P07/P08), and remove the rigid borescope, BORESCOPE-KIT (856A1320P04/P05). Subtask 72-53-00-420-051 D. Install parts removed for borescope inspection. (1) Apply a small amount of graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the borescope plug threads and pressure faces.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B (2) Install the borescope plugs and TORQUE to between 57 and 63 lbf.in (0.64 and 0.71 m.daN). (3) Wirelock the plugs with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). 5. Close-up ________ Subtask 72-53-00-410-055 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-53-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-53-00-410-058 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B TASK 72-53-00-290-004 Borescope/Inspection of the High-Pressure Turbine Shroud 1. __________________ Reason for the Job Inspection of the high pressure turbine (HPT) shrouds is limited to the areas that can be seen with a flexible borescope, at the spark igniter ports. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 856A1321 856A1322 856A1323 856A1351
1 1 1 1
protective caps warning notice access platform 1 m (3 ft. 3 in.) FIBERSCOPE SET BORESCOPE-LIGHT SOURCE SET MONITOR, RESOLUTION BORESCOPE GUIDE TUBE,BORESCOPE-HPT SHROUD
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 74-21-30-000-002 74-21-30-400-002 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-53-00-991-300 72-53-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Removal of the Spark Igniter Installation of the Spark Igniter Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 603
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-53-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-53-00-010-056 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-53-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-53-00-010-059 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 601/TASK 72-53-00-991-300) Subtask 72-53-00-010-057 A. Remove the spark igniters (Ref. TASK 74-21-30-000-002). (1) Install the protective caps on the leads and the spark igniters. Subtask 72-53-00-290-053 B. Do a borescope inspection: CAUTION : FOLLOW THE INSTRUCTIONS CAREFULLY FOR INSERTING OR REMOVING THE _______ FLEXIBLE BORESCOPE. DOING THE PROCEDURE INCORRECTLY WILL DAMAGE THE TIP CONTROL FUNCTION. R R
(1) Put the GUIDE TUBE,BORESCOPE-HPT SHROUD (856A1351G01), over the straightening rod. (2) Push the plastic guide tube and straightening rod into the combustion chamber as far as it will go. (3) Turn the pointed tab on the plastic guide tube to the rear of the engine and remove the straightening rod from the plastic guide tube. (4) Connect the FIBERSCOPE SET (856A1321P01/P03/P06), and to the port on the BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make ____ sure borescope and the light source are serviceable. See the Non Destructive Test Manual for this procedure (Ref. NDTM 720000). (5) Align the borescope lens with one of the plastic tabs on the guide tube and install it into the tube. Make sure that the borescope tip is not moved up or down when putting it into the plastic guide tube. (6) Push the borescope through the plastic guide tube until the tip comes out of the end of the tube. (7) Push the tip of the borescope between the nozzle vanes by using the tip deflection control. (8) Turn on the light source of BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08).
EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Feb 01/09
C F M 56-5B (9) Adjust the borescope equipment to obtain maximum clarity of view. (10) Inspect the HPT Shrouds: (Ref. Fig. 603/TASK 72-53-00-991-302) ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. HPT shrouds for: A. Cracks
Surface cracks permitted any number and any lenght axially across width in Surface A and B
See limit extensions (Ref. TASK 72-00-00-200025).
Any number of circumferential cracks that are not connected and are no more than 1 in. (25.3999 mm) long in Surface B
See limit extensions (Ref. TASK 72-00-00-200025).
Circumferential cracks that are connected to axial cracks cannot be over 0.25 in. (6.3499 mm) long and not less than 0.25 in. (6.3499 mm) from the shroud edge Surface A
See limit extensions (Ref. TASK 72-00-00-200025).
B. Burning/erosion
Any amount of material which is not there. (This include holes through the backstrip). Remaining material is not permitted to be in the flowpath.
C. Split-Line Aft Corners
Any amount of circumferential missing or distorted surface material less than 0.200 in. (5.08 mm) and axial missing or distorted
R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-53-00 CES
Page 613 Nov 01/09
C F M 56-5B
HPT Shroud Thermal Densified Coating Limits Figure 603/TASK 72-53-00-991-302- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B
HPT Shroud Thermal Densified Coating Limits Figure 603/TASK 72-53-00-991-302- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------surface material less than 0.400 in. (10.16 mm) measured from the edge of the shroud. D. Rubs/wear
Any amount
E. Distortion
Any amount, if shroud is not in the flowpath.
F. Burn through on rub land
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025).
Subtask 72-53-00-080-053 C. When the inspection is completed, turn off the light source, BORESCOPELIGHT SOURCE SET (856A1322 P02/P03/P04/P07/P08) and remove the FIBERSCOPE SET (856A1321P01/P03/P06) and GUIDE TUBE,BORESCOPE-HPT SHROUD (856A1351G01). Subtask 72-53-00-410-056 D. Install the spark igniters (Ref. TASK 74-21-30-400-002). 5. Close-up ________ Subtask 72-53-00-410-057 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-53-00-440-053 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, R CES
Page 616 Nov 01/09
C F M 56-5B Subtask 72-53-00-410-059 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-53-00 201-249, 251-299, 301-399, 401-499, CES
Page 617 Nov 01/09
C F M 56-5B LPT ROTOR/STATOR ASSEMBLY - DESCRIPTION AND OPERATION _____________________________________________________ 1. _______ General (Ref. Fig. 001) A. The low pressure turbine (LPT) module is a 4-stage axial-flow turbine. It is mounted between the core engine and the turbine frame. The module consists of the following major assemblies : (1) Stages 2-4 LPT nozzle assemblies (LPT stator assembly). (2) LPT rotor assembly. 2. Description ___________ A. LPT Stator Assembly (Ref. Fig. 001, 002) The LPT assembly consists of the LPT case assembly, stages 2-4 LPT nozzle assemblies and the air cooling tubes and manifolds assembly. The nozzle assemblies consist of cast vane segments, and are installed inside the LPT case. (1) The LPT case is made of nickel alloy. The case front flange is bolted to the stage 1 nozzle support ; the rear flange of the LPT case is bolted to the outer front flange of the turbine frame. The LPT shroud support is mounted radially in line with the front flange of LPT case and the stage 1 outer stationary air seal. Six thermal insulation blankets are attached to the inner surface of LPT case. Each blanket is divided into segments and is designed to accommodate either the nozzle segment vane outer platforms or the outer air seal segments. The outer air seal segments are radially in line with stages 2, 3 and 4 of the LPT rotor. At its periphery, and in the vertical plane of the stage 2 nozzle assembly, the LPT case has instrumentation ports at nine specific locations. Nine EGT (T495) thermocouples are installed in these instrumentation ports. Each of the thermocouple probes is engaged through one specific nozzle segment of the stage 2 nozzle assembly. The LPT case has three other ports located lengthwise, at the 5 oclock position, aft looking forward. The three ports provide for the borescope inspection of the LPT internal ports. (2) The stage 2 LPT nozzle assembly consists of 18 nickel alloy segments with aluminization. Each nozzle segment has 7 vane airfoils. The segment inner platforms are retained by the inner stationary air seals, which are the fixed part of the inner interstage rotating air seals. One of the nozzle segments has a port for borescope inspection at the 5 oclock position (aft looking forward) and a hole to house one probe of exhaust gas temperature (EGT) harness. Eight other
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Low Pressure Turbine Rotor/Stator Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Low Pressure Turbine Rotor/Stator Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B nozzle segments also have one hole to accommodate one probe of the EGT harness. (3) The stage 3 LPT nozzle assembly consists of 20 nickel alloy segments of 6 vane airfoils each and is similar in design to the stage 2 nozzle assembly. One of the vane segments has a port for borescope inspection at the 5 oclock position (aft looking FWD). (4) The stage 4 LPT nozzle assembly consists of 22 nickel alloy segments of 6 vanes each and is similar in design to the stage 2 nozzle assembly. One of the nozzle segments has a port for borescope inspection at the 5 oclock position (aft looking FWD). (5) The LPT cooling system consists of 2 air cooling manifolds made of steel alloy and 2 tube halves made of steel alloy. Each manifold and tube half assembly is made up of 6 tubes provided with orifices which direct the air toward the LPT case. B. LPT Rotor Assembly (Ref. Fig. 003) (1) LPT disks are made of nickel alloy. The disk front flanges accommodate the blade retainer which provides axial retention of each blade stage assembly. They also retain the rotating air seals which control air passage between LPT nozzle assembly and rotor. The outer rim of disks has machined recesses accommodating the blade dovetails. (2) The stage 1 blade assembly consists of 162 tip-shrouded, nickel alloy blades with aluminization, equipped with antiwear shields. The front of the blade dovetails has a retaining lug which houses a blade retainer. Blade retainer is held axially by the rotating air seal. (3) The rotating air seals are made of nickel alloy. They are sandwich-mounted between stages 1, 2, 3 and 4 disks. They control air passage between the stator and the rotor. (4) Stages 2-4 of the LPT rotor are similar except for the following differences. Stages 2-3 LPT disks have 150 blades, equipped with antiwear shields, stage 4 LPT disk has 134 blades. The turbine rotor support is sandwich-mounted between the stage 3 rotating air seal and the stage 3 disk. (5) The turbine rotor support, made of nickel alloy, provides connection between the assembly of disks and the LPT shaft. It divides the LPT rotor inner enclosure into 2 separate cavities.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
Low Pressure Turbine Rotor Assembly Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B LPT ROTOR/STATOR ASSEMBLY - INSPECTION/CHECK ____________________________________________ TASK 72-54-00-290-005 Inspection of the Stage 1-3 Blades 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET
856A1320 856A1322
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-300 72-54-00-991-301 72-54-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603
3. __________ Job Set-up Subtask 72-54-00-941-056 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-066 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-056 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-075 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-54-00-991-300, 602/TASK 72-54-00-991-301, 603/TASK 72-54-00-991-302) Subtask 72-54-00-010-067 A. Removal of Borescope Plugs (1) Let the temperature of parts decrease to ambient temperature. PRE SB CFMI 72-0376 (2) Cut and remove the lockwires. Then, remove the borescope plugs S16, S17, S18, S19 and S20. NOTE : The borescope plugs S16 and S17 are in the same plane and ____ located, respectively, at 5:30 and 8:30 (ALF) immediately in front of the combustion case aft flange. The borescope plugs S18, S19 and S20 are located approximately at 5:00 oclock (ALF) on the LPT case and, from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT, respectively. END OF PRE SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B
Location of the Borescope Ports and Possible Borescope Access Via One Instrumentation Boss Figure 601/TASK 72-54-00-991-300- 14 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, Page 604 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-54-00
C F M 56-5B
Location of the Borescope Ports and Possible Borescope Access Via One Instrumentation Boss Figure 601/TASK 72-54-00-991-300- 24 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, Page 605 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-54-00
C F M 56-5B
Location of the Borescope Ports and Possible Borescope Access Via One Instrumentation Boss Figure 601/TASK 72-54-00-991-300- 34 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, Page 606 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-54-00
C F M 56-5B
Location of the Borescope Ports and Possible Borescope Access Via One Instrumentation Boss Figure 601/TASK 72-54-00-991-300- 44 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, Page 607 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-54-00
C F M 56-5B
Low Pressure Turbine Borescope Inspection Figure 602/TASK 72-54-00-991-301- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B
Low Pressure Turbine Borescope Inspection Figure 602/TASK 72-54-00-991-301- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B
Low Pressure Turbine Borescope Inspection Figure 602/TASK 72-54-00-991-301- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
72-54-00 CES
Page 611 Feb 01/98
C F M 56-5B
R R
Low Pressure Turbine Blades and Nozzle Damage Description Figure 603/TASK 72-54-00-991-302- 14 (SHEET 1)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B
R R
Low Pressure Turbine Blades and Nozzle Damage Description Figure 603/TASK 72-54-00-991-302- 24 (SHEET 2)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B
R R
Low Pressure Turbine Blades and Nozzle Damage Description Figure 603/TASK 72-54-00-991-302- 34 (SHEET 3)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 614 Nov 01/08
C F M 56-5B
R R
Low Pressure Turbine Blades and Nozzle Damage Description Figure 603/TASK 72-54-00-991-302- 44 (SHEET 4)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 615 Nov 01/08
C F M 56-5B POST SB CFMI 72-0376 (3) Cut and remove the lockwires. Then, remove the borescope plugs S16, S17. NOTE : The borescope plugs S16 and S17 are in the same plane and ____ located, respectively, at 5:30 and 8:30 (ALF) immediately in front of the combustion case aft flange. (4) Remove the self locking borescope cap assemblies S18, S19 and S20. NOTE : The borescope cap assemblies S18, S19 and S20 are located ____ approximately at 5:00 oclock (ALF) on the LPT case and, from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT, respectively. END OF SB CFMI 72-0376 Subtask 72-54-00-480-054 B. Install the BORESCOPE-KIT (856A1320P04/P05) as follows: (1) Connect the power supply. CAUTION : BEFORE YOU CONNECT THE POWER SUPPLY TO THE POWER SOURCE BE _______ SURE THE ON-OFF SWITCH IS IN THE OFF POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM. MAKE SURE THAT PROJECTOR AND POWER SUPPLY ARE CORRECTLY GROUNDED. (a) Connect the power supply to a grounded, power source. (2) Connect light source cable to rigid borescope and to port on BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08) . (3) Turn light source on; insert borescope and position it as desired for inspection. Subtask 72-54-00-290-054 C. The stage 1-3 LPT rotor blades are long span blades. To fully examine the airfoil surface, it is recommended to do as follows: (1) Turn the fan rotor slowly and smoothly to examine the blades. (2) Change the probe engagement depth so as to see the blade airfoils as they move in front of the probe.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 616 Nov 01/08
C F M 56-5B (3) While you adjust the probe engagement depth, turn the probe about its axis (azimuth) to get a maximum view, for a given turn speed of the rotor. NOTE : The blade span increases from the 2nd to the 3rd LPT stage. As ____ the full engagement of the probe is necessary, you may have to make more than one turn of the LPT rotor to see all the blade airfoils. (4) When you look at the leading edges of the blades, turn the rotor so that their concave side (pressure face) comes toward the borescope. (5) To look at the trailing edges, turn the rotor in the opposite direction so that the convex side (suction face) of the blades comes toward the borescope. (6) Do the inspection of the stage 1-3 blades for the damage which follow: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Cracks
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
2. Nicks on concave or convex sides. Does not include areas E.
Not more than 0.01 in. (0.25 mm) deep for stage 1 and 0.02 in. (0.5 mm) deep for stage 2-3.
See limit extensions (Ref. TASK 72-00-00-200025)
3. Dents on concave or convex sides. Does not include areas E.
Not more than 0.01 in. (0.25 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
4. Nicks and/or dents on leading or trailing edges. Does not include areas E.
Not more than 0.02 in. (0.5 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
5. Nicks and/or dents in areas E.
Not more than 0.01 in. (0.25 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
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Page 617 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------6. Rubbing on leading Not more than 0.01 in. See limit extensions edge platform , (0.25 mm) deep (Ref. TASK 72-00-00-200leading edge root 025) radius in area E. 7. Distortion of leading edges caused by overtemperature.
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025) See limit extensions (Ref. TASK 72-00-00-200025)
R
8. Pretwist clearances 0.1 in. (2.54 mm) max of such that adjacent total gap for stage 1. interlocks do not Not serviceable for touch each other. stage 2-3. For CFM56-5B non/P engines
R R R R
9. Stage 1, 2 and 3 Not more than 0.0150 in. blades tip shroud out (0.38 mm). of flush. For CFM56-5B/P engines
See limit extensions (Ref. TASK 72-00-00-200025)
R R R R
10. Stage 1 blades tip shroud out of flush.
Not more than 0.0433 in. (1.10 mm), and not more than 0.0315 in. (0.80 mm) on the hard faces.
See limit extensions (Ref. TASK 72-00-00-200025)
R R R R
11. Stage 2 blades tip shroud out of flush.
Not more than 0.0472 in. (1.20 mm), and not more than 0.0354 in. (0.90 mm) on the hard faces.
See limit extensions (Ref. TASK 72-00-00-200025)
R R R R
12. Stage 3 blades tip shroud out of flush.
Not more than 0.0433 in. (1.10 mm), and not more than 0.0354 in. (0.90 mm) on the hard faces.
See limit extensions (Ref. TASK 72-00-00-200025)
R R R
13. Stage 1 blades root platform out of flush.
Not more than 0.0198 in. (0.50 mm).
See limit extensions (Ref. TASK 72-00-00-200025)
R R R R
14. Stage 2 and 3 blades Not more than 0.0236 in. root platform out of (0.60 mm). flush. For ALL CFM56-5B engines
See limit extensions (Ref. TASK 72-00-00-200025)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 618 Nov 01/08
R R R R R R R R R R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------15. Shingled or Not serviceable If you find the blade tip unlatched tip shrouds shingled or shrouds. unlatched on different borescope inspections, it may be the sign of a wear of the hard-facing on the blade tip interlock surfaces. See limit extensions (Ref. TASK 72-00-00-200025)
R R
16. Deposit material, peeling off on airfoil.
Any amount provided there is no evidence of bowing and/or melting.
R
17. Rubbing/scratches on forward face of root platform
Any amount
R
18. Blades seal teeth wear.
1/2 of tooth height worn if only one stage is affected. 1/3 of tooth height worn if 2 stages are affected. 1/4 of tooth height worn if 3 stages are affected.
R
19. Corrosion / Pitting
For CFM56-5B/P engines: Any amount
Subtask 72-54-00-080-054 D. Removal of Borescope (1) When inspection is complete, turn lamp switch off, leave main light source blower on for a while to cool lamp and housing. (2) Remove the borescope.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 619 Nov 01/08
C F M 56-5B Subtask 72-54-00-410-066 E. Install the Borescope Plugs PRE SB CFMI 72-0376 (1) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads of the borescope plugs S16, S17, S18, S19, S20 and install on the combustion case (S16, S17) and on the LPT case (S18, S19, S20). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (2) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619) to the threads of the borescope plugs S16, S17 and on the combustion case (S16, S17). (3) Apply graphite grease (Material No. CP2101) to the threads of the self locking borescope cap assemblies S18, S19, S20 and install on the LPT case (S18, S19, S20). END OF SB CFMI 72-0376 PRE SB CFMI 72-0376 (4) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (5) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (6) TORQUE self locking borescope caps assembly to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). NOTE : To achieve the correct installation of the self locking ____ borescope cap assembly, the slot of its ring must be positioned on the borescope boss lug at the final tightening. END OF SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 620 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-54-00-410-067 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-056 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-076 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 621 Nov 01/08
C F M 56-5B TASK 72-54-00-290-006 Inspection of the Stage 4 Blades 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET
856A1320 856A1322
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 622 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-54-00-210-004 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-300 72-54-00-991-301 72-54-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Optional Visual Inspection of the Stage 4 Blades from the Rear of the Engine Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603
3. __________ Job Set-up Subtask 72-54-00-941-057 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 623 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-068 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-057 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-076 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-54-00-991-300, 602/TASK 72-54-00-991-301, 603/TASK 72-54-00-991-302) Subtask 72-54-00-010-069 A. Remove the Plugs which Follow (1) Let the temperature of parts decrease to ambient temperature. PRE SB CFMI 72-0376 (2) Cut and remove the lockwire from the borescope plug S20. Remove the plug. NOTE : The plug S20 is the aftmost borescope plug located at 5:00 ____ oclock on the LPT case (ALF). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 624 Nov 01/08
C F M 56-5B (3) Remove the self locking borescope cap assembly S20. NOTE : The plug S20 is the aftmost borescope cap assembly located at ____ 5:00 oclock on the LPT case (ALF). END OF SB CFMI 72-0376 (4) Locate the instrumentation boss located at the 8:30 oclock position (ALF) on the turbine frame. (a) Remove the 2 bolts and nuts which attach a blanking plug to this turbine frame boss. (b) Remove the blanking plug and its gasket. NOTE : This gives you a borescope access to look at the trailing ____ edge and tip shroud of the stage 4 LPT blades. Subtask 72-54-00-480-055 B. Install the BORESCOPE-KIT (856A1320P04/P05) as follows: (1) Connect the power supply. CAUTION : BEFORE YOU CONNECT THE POWER SUPPLY TO THE POWER SOURCE BE _______ SURE THE ON-OFF SWITCH IS IN THE OFF POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM. MAKE SURE THAT PROJECTOR AND POWER SUPPLY ARE CORRECTLY GROUNDED. (a) Connect the power supply to a grounded 110 VAC 60Hz power source. (2) Connect light source cable to rigid borescope and to port on BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). (3) Turn light source on; insert borescope and position it as desired for inspection. Subtask 72-54-00-290-055 C. The stage 4 LPT rotor blades are long span blades. To fully examine their airfoil surface, it is recommended to do these steps. (1) Turn the fan rotor slowly and smoothly to examine the blades. (2) Change the probe engagement depth to see the airfoils as the blades move in front of the probe.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 625 Nov 01/08
C F M 56-5B (3) While you change the probe engagement depth, turn the probe (azimuth). This will let you have a maximum view for given turn speed of the rotor. NOTE : The stage 4 blades have the longest span of the blade stages. ____ So, as the full engagement of the probe is necessary, you may have to make 2, 3 or more turns of the LPT rotor to see all the blade areas. (4) When you look at the leading edges of the blades, turn the rotor so that the concave side (or pressure face) of the blades comes toward the borescope. (5) When you look at the trailing edges, turn the rotor in the opposite direction so that the convex side (suction face) comes toward the borescope. (6) Do the inspection of the stage 4 blades for the damage which follow: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Cracks
Not serviceable
See limit extensions (Ref. TASK 72-00-00-200025)
2. Nicks on concave or convex sides. Does not include area E.
Not more than 0.02 in. (0.5 mm) deep.
See limit extension (Ref. TASK 72-00-00-200025)
3. Dents on concave or convex sides. Does not include area E.
Not more than 0.01 in. (0.25 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
4. Nicks and/or dents on leading or trailing edges. Does not include area E.
Not more than 0.02 in. (0.5 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
5. Nicks and/or dents in area E.
Not more than 0.01 in. (0.25 mm) deep
See limit extensions (Ref. TASK 72-00-00-200025)
R
For CFM56-5B non/P engines
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 626 Nov 01/08
R
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------6. Tip shroud out of Not more than 0.0150 in. See limit extensions flush. (0.38 mm). (Ref. TASK 72-00-00-200025). For CFM56-5B/P engines
R R
7. Tip shroud out of flush.
Not more than 0.0354 in. (0.90 mm).
See limit extensions (Ref. TASK 72-00-00-200025)
R R
8. Root platform out of flush.
Not more than 0.039 in. (1.0 mm).
See limit extensions (Ref. TASK 72-00-00-200025)
R R
R R R R R R R R R R R R
For ALL CFM56-5B engines 9. Shingled or unlatched tip shrouds.
Not serviceable
If you find the blade tip shrouds shingled or unlatched on different borescope inspections, it may be the sign of a wear of the hard-facing on the blade tip interlock surfaces. The 4th stage blades may be unshingled or relatched by hand (Ref. TASK 72-5400-210-004) See limit extensions (Ref. TASK 72-00-00-200025) See NOTE below.
R
10. Hard-facing wear.
Any quantity that do not cause a mismatch of the blade tip shroud aft face of more than 0.12 in. (3.05 mm).
See limit extensions (Ref. TASK 72-00-00-200025). See NOTE below.
R
11. Blade airfoil pretwist that cause gaps such as interlocks do not touch each other.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025). See NOTE below.
R R R R
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 627 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------NOTE : If the aircraft maintenance schedule permits, it is recommended to ____ do a visual inspection when you find these defects. Blades that are shingled or unlatched may be put back in their correct interlock positions, in following the special procedure (Ref. TASK 72-54-00210-004). R
12. Distortion of leading edge caused by overtemperature.
Not serviceable
R
13. Deposit material peeling off airfoil.
Any amount, provided there is no evidence of bowing and/or melting.
Subtask 72-54-00-080-055 D. Removal of Borescope (1) When inspection is completed, turn lamp switch off, leave main light source blower on for a while to cool lamp and housing. (2) Remove the borescope. Subtask 72-54-00-410-068 E. Install the Borescope Plug S20 on the LPT Case PRE SB CFMI 72-0376 (1) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619), to the threads of the plug. END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (2) Apply graphite grease (Material No. CP2101) to the threads of the self locking borescope cap assembly. END OF SB CFMI 72-0376 PRE SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 628 Nov 01/08
C F M 56-5B (3) Install the plug on the LPT case. TORQUE to between 55 and 60 lbf.in (0.62 and 0.67 m.daN). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (4) Install the self locking borescope cap assemby on the LPT case. TORQUE to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). NOTE : To achieve the correct installation of the self locking ____ borescope cap assembly, the slot of its ring must be positioned on the borescope boss lug at the final tightening. END OF SB CFMI 72-0376 PRE SB CFMI 72-0376 (5) Safety the plug with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in (0.8 mm) dia. (Material No. CP8002). END OF PRE SB CFMI 72-0376 Subtask 72-54-00-410-089 F. Install the blanking plug on the turbine frame instrumention boss at 8:30 oclock (ALF) as follows: (1) Lubricate the threads of the 2 plug attachment bolts with graphite grease (Material No. CP2101). (2) Install the gasket on the blanking plug and engage the plug in the turbine frame boss. (3) Install the 2 bolts and the 2 nuts (self-locking) to attach the plug to the boss. (4) TORQUE the 2 nuts to between 95 and 110 lbf.in (1.07 and 1.24 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 629 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-54-00-410-069 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-057 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-077 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 630 Nov 01/08
C F M 56-5B TASK 72-54-00-290-007 Inspection of the Stage 2-4 Nozzle Segments 1. __________________ Reason for the Job This Task is only available for CFM56-5BX not/P engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 FIBERSCOPE SET 1 BORESCOPE-LIGHT SOURCE SET
856A1320 856A1321 856A1322
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 631 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-300 72-54-00-991-301 72-54-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603
3. __________ Job Set-up Subtask 72-54-00-941-058 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 632 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-070 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-058 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-077 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-54-00-991-300, 602/TASK 72-54-00-991-301, 603/TASK 72-54-00-991-302) Subtask 72-54-00-010-071 A. Remove Borescope Plugs (1) Let the temperature of the parts decrease to ambient temperature. PRE SB CFMI 72-0376 (2) Cut and remove the lockwires and remove the LPT borescope plugs S18, S19, S20. NOTE : The borescope plugs S18, S19, S20 are located approximately at ____ 5:00 oclock (ALF) on the LPT case, and from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT respectively. END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 633 Nov 01/08
C F M 56-5B (3) Remove the self locking borescope cap assemblies S18, S19, S20. NOTE : The borescope cap assemblies S18, S19, S20 are located ____ approximately at 5:00 oclock (ALF) on the LPT case, and from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT respectively. END OF SB CFMI 72-0376 Subtask 72-54-00-480-056 R R
B. Installation of the BORESCOPE-KIT (856A1320P04/P05) or FIBERSCOPE SET (856A1321P03/P05/P06) as follows: (1) Connect the power supply. CAUTION : BEFORE YOU CONNECT THE POWER SUPPLY TO THE POWER SOURCE BE _______ SURE THE ON-OFF SWITCH IS IN THE OFF POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM. MAKE SURE THAT PROJECTOR AND POWER SUPPLY ARE CORRECTLY GROUNDED. (a) Connect the power supply. (2) Connect light source cable to rigid borescope and to port on BORESCOPE-LIGHT SOURCE SET (856A1322/P02/P03/P04/P07/P08). (3) Turn light source on; insert borescope and position it as desired for inspection.
R R
(a) If you use flexible borescope, make sure that it is correctly adjusted. Subtask 72-54-00-290-056
R
C. Inspection of the stage 2-4 nozzle segment for the following:
R R
NOTE : You can use a rigid borescope or a flexible borescope to do this ____ inspection.
R R
NOTE : If you use the rigid borescope, the following limits are given for ____ nozzle segments you can see near the borescope holes.
R R
NOTE : LPT stage 2 and 4 nozzles have six airfoils for each segment. LPT ____ stage 3 nozzles have seven airfoils for each segment.
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 634 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------R R R R R
1. Cracks in trailing and leading edges.
See limit extensions (Ref. TASK 72-00-00-200025).
One crack maximum for each nozzle segment that is 0.5 in. (12.7 mm) (1/3 of the chord width) to 1.0 in. (25.4 mm) in length (2/3 of the chord width).
See limit extensions (Ref. TASK 72-00-00-200025).
R R R R R R R
Any quantity (leading or trailing edge) if cracks are less than 0.5 in. (12.7 mm) in length (1/3 of the chord width).
R
2. Nicks and/or dents on leading and/or trailing edges.
Any quantity, provided cracks criteria are met.
See limit extensions (Ref. TASK 72-00-00-200025).
R
3. Nicks and/or dents on concave and/or convex sides.
Any quantity, provided cracks criteria are met.
See limit extensions (Ref. TASK 72-00-00-200025).
R R
4. Burned areas, hot spots, discoloration.
Any quantity, if there is no missing material and you see no bowing and/or melting.
See limit extensions (Ref. TASK 72-00-00-200025).
R
5. Material particles peeling off on airfoil.
Any quantity, if you see no bowing and/or melting.
Subtask 72-54-00-080-056 D. Removal of Borescope (1) When inspection is complete, turn lamp switch off, leave main light source blower on for a while to cool lamp and housing. (2) Remove the borescope.
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 635 Nov 01/09
C F M 56-5B Subtask 72-54-00-410-070 E. Install Borescope Plugs PRE SB CFMI 72-0376 (1) Apply graphite grease (Material No. CP2101) to the threads of the borescope plugs S18, S19, S20 and install on the LPT case. END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (2) Apply graphite grease (Material No. CP2101) to the threads of the borescope cap assemblies S18, S19, S20 and install on the LPT case. END OF SB CFMI 72-0376 PRE SB CFMI 72-0376 (3) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (4) TORQUE self locking borescope cap assemblies to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). NOTE : To achieve the correct installation of the self locking ____ borescope cap assembly, the slot of its ring must be positioned on the borescope boss lug at the final tightening. END OF SB CFMI 72-0376
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, R CES
Page 636 Nov 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-54-00-410-071 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-058 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-078 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, R CES
Page 637 Nov 01/09
C F M 56-5B TASK 72-54-00-290-007- 01 Inspection of the Stage 2-4 Nozzle Segments 1. __________________ Reason for the Job R
This Task is only available for CFM56-5BX /P engines and /3 engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 FIBERSCOPE SET 1 BORESCOPE-LIGHT SOURCE SET
856A1320 856A1321 856A1322
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 638 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-300 72-54-00-991-305 72-54-00-991-306
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 604 Fig. 605
3. __________ Job Set-up Subtask 72-54-00-941-067 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 639 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-093 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-066 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-094 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-54-00-991-300, 604/TASK 72-54-00-991-305, 605/TASK 72-54-00-991-306) Subtask 72-54-00-010-095 A. Remove Borescope Plugs (1) Let the temperature of the parts decrease to ambient temperature. PRE SB CFMI 72-0376 (2) Cut and remove the lockwires and remove the LPT borescope plugs S18, S19, S20. NOTE : The borescope plugs S18, S19, S20 are located approximately at ____ 5:00 oclock (ALF) on the LPT case, and from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT respectively. END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 640 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-54-00 CES
Page 641 Aug 01/09
C F M 56-5B
Illustration of the Low Pressure Turbine Figure 604/TASK 72-54-00-991-305- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 642 Nov 01/08
C F M 56-5B
Illustration of the Low Pressure Turbine Figure 604/TASK 72-54-00-991-305- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 643 Nov 01/08
C F M 56-5B
Illustration of the Low Pressure Turbine Figure 604/TASK 72-54-00-991-305- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 644 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-54-00 CES
Page 645 Nov 01/08
C F M 56-5B
Illustration of the Low Pressure Turbine Blades and Nozzle Damage Figure 605/TASK 72-54-00-991-306- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 646 Nov 01/08
C F M 56-5B
Illustration of the Low Pressure Turbine Blades and Nozzle Damage Figure 605/TASK 72-54-00-991-306- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 647 Nov 01/08
C F M 56-5B
Illustration of the Low Pressure Turbine Blades and Nozzle Damage Figure 605/TASK 72-54-00-991-306- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 648 Nov 01/08
C F M 56-5B (3) Remove the self locking borescope cap assemblies S18, S19, S20. NOTE : The borescope cap assemblies S18, S19, S20 are located ____ approximately at 5:00 oclock (ALF) on the LPT case, and from front to rear, relate to the 2nd, 3rd and 4th stages of the LPT respectively. END OF SB CFMI 72-0376 Subtask 72-54-00-480-058 R R
B. Installation of the BORESCOPE-KIT (856A1320P04/P05) or FIBERSCOPE SET (856A1321P03/P05/P06) as follows: (1) Connect the power supply. CAUTION : BEFORE YOU CONNECT THE POWER SUPPLY TO THE POWER SOURCE BE _______ SURE THE ON-OFF SWITCH IS IN THE OFF POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM. MAKE SURE THAT PROJECTOR AND POWER SUPPLY ARE CORRECTLY GROUNDED. (a) Connect the power supply. (2) Connect light source cable to rigid borescope and to port on BORESCOPE-LIGHT SOURCE SET (856A1322/P02/P03/P04/P07/P08). (3) Turn light source on; insert borescope and position it as desired for inspection.
R R
(a) If you use flexible borescope, make sure that it is correctly adjusted. Subtask 72-54-00-290-058
R
C. Inspection of the stage 2-4 nozzle segment for the following:
R R
NOTE : You can use a rigid borescope or a flexible borescope to do this ____ inspection.
R R
NOTE : If you use the rigid borescope, the following limits are given for ____ nozzle segments you can see near the borescope holes.
R R
NOTE : LPT stage 2 and 4 nozzles have six airfoils for each segment. LPT ____ stage 3 nozzles have seven airfoils for each segment.
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 649 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------R R R R R R
1. Cracks in trailing and leading edges.
See limit extensions (Ref. TASK 72-00-00-200025).
One crack maximum for each nozzle segment that is 0.5 in. (12.7 mm) (1/3 of the chord width) to 1.0 in. (25.4 mm) in length (2/3 of the chord width).
See limit extensions (Ref. TASK 72-00-00-200025).
R R R R R R R
Any quantity (leading or trailing edge) if cracks are less than 0.5 in. (12.7 mm) in length (1/3 of the chord width).
R
2. Nicks and/or dents on leading and/or trailing edges.
Any quantity, provided cracks criteria are met.
See limit extensions (Ref. TASK 72-00-00-200025).
R
3. Nicks and/or dents on concave and/or convex sides.
Any quantity, provided cracks criteria are met.
See limit extensions (Ref. TASK 72-00-00-200025).
R R
4. Burned areas, hot spots, discoloration.
Any quantity, if there is no missing material and you see no bowing and/or melting.
See limit extensions (Ref. TASK 72-00-00-200025).
R
5. Material particles peeling off on airfoil.
Any quantity, if you see no bowing and/or melting.
Subtask 72-54-00-080-058 D. Removal of Borescope (1) When inspection is complete, turn lamp switch off, leave main light source blower on for a while to cool lamp and housing. (2) Remove the borescope.
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 650 Nov 01/09
C F M 56-5B Subtask 72-54-00-410-095 E. Install Borescope Plugs PRE SB CFMI 72-0376 (1) Apply graphite grease (Material No. CP2101) to the threads of the borescope plugs S18, S19, S20 and install on the LPT case. END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (2) Apply graphite grease (Material No. CP2101) to the threads of the borescope cap assemblies S18, S19, S20 and install on the LPT case. END OF SB CFMI 72-0376 PRE SB CFMI 72-0376 (3) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (4) TORQUE self locking borescope cap assemblies to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). NOTE : To achieve the correct installation of the self locking ____ borescope cap assembly, the slot of its ring must be positioned on the borescope boss lug at the final tightening. END OF SB CFMI 72-0376
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, R CES
Page 651 Nov 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-54-00-410-096 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-066 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-097 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, R CES
Page 652 Nov 01/09
C F M 56-5B TASK 72-54-00-290-008 Inspection of the Stage 1-4 Stationary Air Seals 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 BORESCOPE-KIT 1 BORESCOPE-LIGHT SOURCE SET
856A1320 856A1322
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2619
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * Never Seez-Pure Nickel, Special (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 653 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-300 72-54-00-991-301 72-54-00-991-302
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601 Fig. 602 Fig. 603
3. __________ Job Set-up Subtask 72-54-00-941-059 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 654 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-072 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Allow parts, to return to ambient temperature. Subtask 72-54-00-040-059 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-078 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-54-00-991-300, 602/TASK 72-54-00-991-301, 603/TASK 72-54-00-991-302) Subtask 72-54-00-010-084 A. Removal of the Borescope Plugs (1) Let the temperature of parts decrease to ambient temperature. PRE SB CFMI 72-0376 (2) Cut and remove the lockwires. Then, remove the borescope plugs S16, S17, S18, S19 and S20. NOTE : The borescope plugs S16 and S17 are in the same plane and ____ located respectively, at 5:30 and 8:30 (ALF) immediately in front of combustion case aft flange. The borescope plugs S18, S19 and S20 are located at 5:00 oclock (ALF) on the LPT case. From front to rear they relate approximately to the 2nd, 3rd and 4th LPT stages.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 655 Nov 01/08
C F M 56-5B END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (3) Cut and remove the lockwires. Then, remove the borescope plugs S16, S17. NOTE : The borescope plugs S16 and S17 are in the same plane and ____ located respectively, at 5:30 and 8:30 (ALF) immediately in front of the combustion case aft flange. (4) Remove the self locking borescope cap assemblies S18, S19 and S20. NOTE : The borescope cap assemblies S18, S19 and S20 are located at ____ 5:00 oclock (ALF) on the LPT case. From front to rear they relate approximately to the 2nd, 3rd and 4th LPT stages. END OF SB CFMI 72-0376 Subtask 72-54-00-480-057 B. Install the BORESCOPE-KIT (856A1320P04/P05) as follows: (1) Connect the power supply. CAUTION : BEFORE YOU CONNECT THE POWER SUPPLY TO THE POWER SOURCE BE _______ SURE THE ON-OFF SWITCH IS IN THE OFF POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM. MAKE SURE THAT PROJECTOR AND POWER SUPPLY ARE CORRECTLY GROUNDED. (a) Connect power supply to a grounded 110 VAC 60 Hz power source. (2) Connect light source cable to rigid borescope and to port on BORESCOPE-LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08). (3) Turn light source on; insert borescope and position it as desired for inspection.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 656 Nov 01/08
C F M 56-5B Subtask 72-54-00-290-057 C. Inspect the Stage 1-4 Outer Stationary Air Seals for the Following NOTE : The limits given below are for the stationary air seal areas you ____ can see near the borescope holes. ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Stage 1-3 stationary air seals. A. Rub marks or chicken marks from seal teeth.
Not deeper than 0.08 in. (2.03 mm)
2. Stage 4 stationary air seals. NOTE : This inspection is only to be done when stage 4 blades are shingled ____ or unlatched. A. Worn, jagged or crushed honeycomb material.
Not more than 0.08 in. (2.03 mm)
See limit extensions (Ref. TASK 72-00-00-200025).
3. Stage 1/4 stationary air seals. A. Distortion
Any quantity if shroud does not come out.
Subtask 72-54-00-080-057 D. Removal of Borescope (1) When inspection is complete, turn lamp switch off, leave main light source blower on for a while to cool and housing. (2) Remove the borescope.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 657 Nov 01/08
C F M 56-5B Subtask 72-54-00-410-072 E. Install the Borescope Plugs PRE SB CFMI 72-0376 (1) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619), to the threads of the borescope plugs S16, S17, S18, S19, S20 and install on the combustion case (S16, S17) and on the LPT case (S18, S19, S20). END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (2) Apply graphite grease (Material No. CP2101) or Never Seez-Pure Nickel, Special (Material No. CP2619), to the threads of the borescope plugs S16, S17 and install on the combustion case (S16, S17). (3) Apply graphite grease (Material No. CP2101) to the threads of the self locking borescope cap assemblies S18, S19, S20 and install on the LPT case (S18, S19, S20). END OF SB CFMI 72-0376 PRE SB CFMI 72-0376 (4) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002) END OF PRE SB CFMI 72-0376 POST SB CFMI 72-0376 (5) TORQUE plugs to between 55 and 60 lbf.in (0.62 and 0.67 m.daN) and safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002). (6) TORQUE the self locking borescope cap assemblies to between 50 and 55 lbf.in (0.56 and 0.62 m.daN). NOTE : To achieve the correct installation of the self locking ____ borescope cap assembly, the slot of its ring must be positioned on the borescope boss lug at the final tightening.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 658 Nov 01/08
C F M 56-5B END OF SB CFMI 72-0376 5. Close-up ________ Subtask 72-54-00-410-073 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-059 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-079 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 659 Nov 01/08
C F M 56-5B TASK 72-54-00-210-004 Optional Visual Inspection of the Stage 4 Blades from the Rear of the Engine 1. __________________ Reason for the Job To do a direct, hands-on, visual inspection of the stage 4 LPT blades. During the borescope inspection of this blade stage (Ref. TASK 72-54-00-290-00600), on some rare occasions, you may see blades with their tip shroud shingled or unlatched, or with radial mismatches/out-of-flush defects or with gaps at their interlocks. This inspection is not mandatory since the Limit Extensions (Ref. TASK 72-00-00-200-02500) referred to in the borescope inspection of the stage 4 blades give the specific time/cycles of operation with these defects. However, it makes sense to prevent a further deterioration of the turbine stage, before the expiration of the permitted limit extensions. Therefore, a visual inspection is recommended as soon as possible after the finding of these defects, if the aircraft maintenance schedule permits. The benefits of this visual inspection are that you can: - put back some blades that are shingled/unlatched in the correct interlock positions - make a more accurate measurement of the mismatch (at the blade tip shrouds) than the estimate you can make from the borescope inspection - better see gaps, or areas of the blade interlocks that do not touch each other (the gaps are the result of the deterioration of the blade pretwist (angle) characteristic) - make an evaluation of the correct blade pretwist characteristic through a simple manual method. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 660 Nov 01/08
C F M 56-5B B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-54-00-991-303
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 606
3. __________ Job Set-up Subtask 72-54-00-941-063 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 661 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-085 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-063 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-086 D. Get Access (1) Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (2) Let the temperature of parts decrease to ambient temperature. 4. Procedure _________ (Ref. Fig. 606/TASK 72-54-00-991-303) Subtask 72-54-00-010-087 A. Removal for Access to the Inspection Area (1) Remove the core nozzle assembly (Ref. TASK 78-11-11-000-041). (2) Remove the centerbody (Ref. TASK 78-11-12-000-041). NOTE : The removal of these nacelle hot exhaust components is ____ necessary in order to get an unrestricted access to the turbine last stage, through the rear of the engine. Besides, this inspection necessitates some checks and corrective actions you can do only by hand.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 662 Nov 01/08
C F M 56-5B Subtask 72-54-00-210-055 B. Inspection of Defects Found during the Borescope Inspection (1) Shingling/Unlatching CAUTION : DO NOT HIT THE BLADES WITH A DRIFT AND A HAMMER TO PUT THEM _______ BACK IN THEIR CORRECT INTERBLOCKS. FURTHER DAMAGE TO THE BLADES COULD RESULT. IF NECESSARY, USE ONLY SHAPED TOOLS MADE OF HARDWOOD OR HARD PLASTICS MATERIAL AS PRYING OR PUSHING TOOLS. (a) Past experience has shown that it is possible to put back shingled/unlatched blades in their correct interlocking position. To do this, apply hand force as show in sheet 2. (Ref. Fig. 606/TASK 72-54-00-991-303) (b) If you can not remove the shingling/unlatching of two blades (or more) do no try further. Let expire the applicable limit extensions. Beyond these, it is up to the airline management to take the necessary hardware actions. (2) Hard-facing wear on the blade interlock surfaces. NOTE : A worn hard-facing may be at the origin of the shingling and ____ unlatching defects. This condition results in radial and axial mismatches at the blade tip shrouds which are no longer in the same alignment (radial out-of-flush, for example). (a) You can measure the interlock wear by the quantity of the aft mismatch of the blade tip shroud. (b) Use the honeycomb cells in the outer stationary air seal as a scale to measure the quantity of mismatch. One honeycomb cell is 0.06 in. (1.52 mm) in the largest dimension. If you are not sure, use modeling clay to get an imprint. Then, measure and record the value of the mismatch. The mismatch at the aft edge of the blade tip shroud must not be more than 0.12 in. (3.05 mm). (3) Blade pretwist check. CAUTION : DO NOT USE PLIERS IN ORDER TO CLOSE THE GAPS AND GET BACK _______ THEIR PRETWIST ANGLE. IT IS IMPOSSIBLE TO CORRECT THIS CONDITION.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 663 Nov 01/08
C F M 56-5B
R
Visual Inspection of the Stage 4 Blades Figure 606/TASK 72-54-00-991-303- 13 (SHEET 1)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 664 Aug 01/09
C F M 56-5B
R
Visual Inspection of the Stage 4 Blades Figure 606/TASK 72-54-00-991-303- 23 (SHEET 2)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 665 Aug 01/09
C F M 56-5B
R
Visual Inspection of the Stage 4 Blades Figure 606/TASK 72-54-00-991-303- 33 (SHEET 3)
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 666 Aug 01/09
C F M 56-5B (a) An incorrect pretwist is shown by gaps and some mismatch at the blade tip shrouds (sheet 3). (Ref. Fig. 606/TASK 72-54-00-991-303) Result: the adjacent interlock surfaces do not touch each other as they should. This condition is not serviceable. - if you see that kind of defects, let expire the applicable limit extensions. Beyond these, let the airline management take the necessary hardware actions - if not, you may want to take the opportunity of full access to the stage 4 blades and do the manual check shown in sheet 1. (Ref. Fig. 606/TASK 72-54-00-991-303) Do the check on at least 2 blades in each quadrant to make a good evaluation of the pretwist characteristic. Subtask 72-54-00-410-086 C. Install the Exhaust Components Removed for Access to the Inspection Area (1) Install the centerbody (Ref. TASK 78-11-12-400-041). (2) Install the core nozzle assembly (Ref. TASK 78-11-11-400-041). 5. Close-up ________ Subtask 72-54-00-410-087 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-063 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-088 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s). EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, R CES
Page 667 Aug 01/09
C F M 56-5B
INTENTIONALLY BLANK
R 72-54-00 CES
Page 668 Aug 01/09
C F M 56-5B TASK 72-54-00-210-005 Inspection of the Turbine Case 1. __________________ Reason for the Job This TASK is applicable for NON /P engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-54-00-300-004 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Replacement of the Broken Studs of EGT (T49.5) Sensor Bracket Assy Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-54-00-941-060 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 669 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-54-00-010-073 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Let the temperature of parts decrease to ambient temperature. Subtask 72-54-00-040-060 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-079 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 670 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-54-00-210-052 A. Inspect the Turbine Case for the Following ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Aft flange. A. Cracks that connect bolt holes.
Not serviceable
B. Cracks that extend from bolt holes to outer edge of flange.
5 cracks with a minimum 5 hole separation between cracks.
C. Cracks that extend from bolt holes toward casing skin.
Not serviceable.
D. Cracks in other areas of flange.
5 cracks per flange 0.25 in. (6.35 mm) long with a minimum 5 in. (127 mm) separation between any other cracks.
E. Nicks, scores and scratches.
Any number 1 in. (25.4 mm) long 0.01 in. (0.25 mm) deep after removal of high metal with 1 in. (25.4 mm) minimum separation.
F. Cracks in flange/case skin radius.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
2. Casing skin for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 671 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Cracks in parent Any number 0.04 in. (1 See limit extensions metal mm) long and 2 in. (50.8 (Ref. TASK 72-00-00-200mm) minimum apart. 025). B. Nicks and scratches.
Any number 0.01 in. (0.25 mm) deep after removal of high metal.
C. Dents
Any number, smooth contour, 0.02 in. (0.5 mm) deep.
3. All threaded ports and bosses for: A. Damaged threads.
One full thread cumulative or continuous may be removed after chasing threads.
B. Cracks in weld of ports and bosses.
One per port in boss 0.04 in. (1 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
4. Ring sector support for: A. Cracks
Any number if attachment parts are secured.
5. Angle brackets for: A. Broken bracket.
Not serviceable.
B. Cracks in all other areas.
Any amount providing cooling air tubes and attaching fasteners are secured.
6. Cooling air tube supports for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 672 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Cracks at Any amount providing mountaing flanges. support is secured. B. Cracks in all other areas:
7. The EGT (T49.5) sensors probe brackets for:
Any amount providing cooling air tubes and attaching fasteners are secured. One full thread cumulative or continuous can be removed after
See the over serviceable limit extensions related to the LPT case (Ref. TASK
A. Damaged Threads
chasing threads.
72-00-00-200-025).
B. Broken Stud
Not permitted.
Replace the stud by a bolt (Ref. TASK 72-54-00-300004) if access of bracket permit this. If not, replace the engine.See the over serviceable limit extensions related to the LPT case (Ref. TASK 72-0000-200-025).
5. Close-up ________ Subtask 72-54-00-410-074 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-060 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 673 Nov 01/08
C F M 56-5B Subtask 72-54-00-410-080 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 674 Nov 01/08
C F M 56-5B TASK 72-54-00-210-005- 01 Inspection of the Turbine Case 1. __________________ Reason for the Job This TASK is applicable for /P engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-54-00-300-004 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Replacement of the Broken Studs of EGT (T49.5) Sensor Bracket Assy Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-54-00-941-064 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 675 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-54-00-010-088 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Let the temperature of parts decrease to ambient temperature. Subtask 72-54-00-040-064 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-089 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 676 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-54-00-210-056 A. Inspect the Turbine Case for the Following ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Aft flange. A. Cracks that connect bolt holes.
Not serviceable
B. Cracks that extend from bolt holes to outer edge of flange.
5 cracks with a minimum 5 hole separation between cracks.
C. Cracks that extend from bolt holes toward casing skin.
Not serviceable.
D. Cracks in other areas of flange.
5 cracks per flange 0.25 in. (6.35 mm) long with a minimum 5 in. (127 mm) separation between any other cracks.
E. Nicks, scores and scratches.
Any number 1 in. (25.4 mm) long 0.01 in. (0.25 mm) deep after removal of high metal with 1 in. (25.4 mm) minimum separation.
F. Cracks in flange/case skin radius.
Not serviceable.
See limit extensions (Ref. TASK 72-00-00-200025).
2. Casing skin for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 677 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Cracks in parent Any number 0.04 in. (1 See limit extensions metal mm) long and 2 in. (50.8 (Ref. TASK 72-00-00-200mm) minimum apart. 025). B. Nicks and scratches.
Any number 0.01 in. (0.25 mm) deep after removal of high metal.
C. Dents
Any number, smooth contour, 0.02 in. (0.5 mm) deep.
3. All threaded ports and bosses for: A. Damaged threads.
One full thread cumulative or continuous may be removed after chasing threads.
B. Cracks in weld of ports and bosses.
One per port in boss 0.04 in. (1 mm) long.
See limit extensions (Ref. TASK 72-00-00-200025).
4. Ring sector support for: A. Cracks
Any number if attachment parts are secured.
5. Angle brackets for: A. Broken bracket.
Not serviceable.
B. Cracks in all other areas.
Any amount providing cooling air tubes and attaching fasteners are secured.
6. Cooling air tube supports for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 678 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------A. Cracks at Any amount providing mountaing flanges. support is secured. B. Cracks in all other areas:
Any amount providing cooling air tubes and attaching fasteners are secured.
C. Breakage of the forward mounting lug
One per half distribution manifold.
7. Cooling air tubes A. Dents
8. The EGT (T49.5) sensors probe brackets for:
All dents are permitted if they have a smooth contour and are not more than 30 percent of the tube outer diameter. One full thread cumulative or continuous can be removed after
See the over serviceable limit extensions related to the LPT case (Ref. TASK
A. Damaged threads
chasing threads.
72-00-00-200-025).
B. Broken stud
Not permitted.
Replace the stud by a bolt (Ref. TASK 72-54-00-300004) if access of bracket permit this. If not, replace the engine. See the over serviceable limit extensions related to the LPT case (Ref. TASK 72-0000-200-025).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 679 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-54-00-410-091 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-064 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-092 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 680 Nov 01/08
C F M 56-5B TASK 72-54-00-210-003 General Visual Inspection of Piping of LPT Case Air Cooling 1. __________________ Reason for the Job Refer to the MPD TASK: 752000-C3 This task is applicable for non /P engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
3. __________ Job Set-up Subtask 72-54-00-941-061 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 681 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-54-00-010-074 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-061 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-080 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ Subtask 72-54-00-210-053 A. Inspect cooling air tubes and manifolds as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Cooling air manifold for: A. Cracks in mounting lug.
One crack on each lug, if not longer than 0.2 in. (5 mm)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 682 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------B. Cracks in sheet Any number, if not Refer to limit extensions metal longer than 0.5 in. (Ref. TASK 72-00-00-200(12.7 mm) , 1 in. (25.4 025). mm) apart, and 3 in. (76.2 mm) cumulative lenght. C. Dents
Any number if smooth contour and not deeper than 0.03 in. (0.76 mm).
2. Cooling air tubes for: A. Cracks in tubes
Any numbers if not longer than 2 in. (50.8 mm) and separated by at least one support member.
B. Dents
Any number, if no more than 30 percent of tube outer diameter.
C. Cracks in tube clamps
Any number if tubes are correctly attached.
5. Close-up ________ Subtask 72-54-00-410-075 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust-reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 683 Nov 01/08
C F M 56-5B Subtask 72-54-00-440-061 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-081 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 684 Nov 01/08
C F M 56-5B TASK 72-54-00-210-003- 01 General Visual Inspection of Piping of LPT Case Air Cooling 1. __________________ Reason for the Job Refer to the MPD TASK: 752000-C3 This task is applicable for /P and /3 engines. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-51-00-230-002 71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 SPM 704111 72-54-00-991-304
Fluorescent-Penetrant Inspection-Portable-Water Washable Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 607
3. __________ Job Set-up Subtask 72-54-00-941-065 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 685 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-54-00-010-090 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-065 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-091 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 686 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-54-00-210-057 A. Inspect cooling air tubes and manifolds as follows: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Cooling air manifold for: (Ref. Fig. 607/TASK 72-54-00-991-304) A. Cracks in the forward mounting lug
One crack on each side is permitted
B. Broken forward mounting lug
One breakage on one side of a lug is permitted One breakage on each side of a forward lug is permitted according the two adjacent support tube : are not broken or crack is not longer than 0.59 in. (15 mm) on the mounting lugs.
C. Dents
A continue in-service limit of 10 hours or 10 cycles is permitted if one adjacent support tube is broken. If one or two adjacent tubes have a crack that is more than 0.59 in. (15 mm), check the part for crack evolution after 10 hours or 10 cycles -If no crack evolution: Check after 50 hours or 50 cycles following the first check, then check every 100 hours or 100 cycles -If crack evolution : A continue in-service limit of 30 hours or 30 cycles is permitted
Any number if smooth contour and not deeper than 0.03 in. (0.76 mm).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 687 Nov 01/08
C F M 56-5B
Visual Inspection of the Mounting Lugs (Only Applicable /P Engines) Figure 607/TASK 72-54-00-991-304- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 688 Nov 01/08
C F M 56-5B
Visual Inspection of the Mounting Lugs (Only Applicable /P Engines) Figure 607/TASK 72-54-00-991-304- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 689 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------D. Nick, scratch and Maximum finish depth Make the defect smooth by chafing (wear) on after you make the hand blending per (Ref. tube external defect smooth is 0.008 SPM 704111) if necessary surface. in. (0.20 mm). to remove sharp edges. Do a local fluorescent penetrant inspection (Ref. TASK 70-51-00-230002). No crack is permitted. 2. Cooling air tubes for: A. Cracks in tubes
Any numbers if not longer than 2 in. (50.8 mm) and separated by at least one support member.
B. Dents
Any number, if no more than 30 percent of tube outer diameter.
C. Cracks in tube clamps
Any number if tubes are correctly attached.
5. Close-up ________ Subtask 72-54-00-410-093 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust-reverser cowl doors (Ref. TASK 78-36-00-410-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 690 Nov 01/08
C F M 56-5B Subtask 72-54-00-440-065 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-54-00-410-094 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 691 Nov 01/08
C F M 56-5B LPT ROTOR/STATOR ASSEMBLY - REPAIRS ___________________________________ TASK 72-54-00-300-004 Replacement of the Broken Studs of EGT (T49.5) Sensor Bracket Assy 1. __________________ Reason for the Job NOTE : The replacement of broken studs depends on accessibility. ____ NOTE : Make sure that free access is available for drilling and tapping ____ process. NOTE : You must discard the repaired bracket assy at the first LPT ____ rotor/stator disassembly. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 77-21-10-000-008 77-21-10-000-009 77-21-10-000-026 77-21-10-000-027 77-21-10-000-028 77-21-10-000-029 77-21-10-400-008 77-21-10-400-009 77-21-10-400-026 77-21-10-400-027
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Upper Extension Lead Removal of the Lower Extension Lead Removal of the Upper Right Thermocouple Lead Assembly Removal of the Lower Left Thermocouple Lead Assembly Removal of the Upper Left Thermocouple Lead Assembly Removal of the Lower Right Thermocouple Lead Assembly Installation of the Upper Extension Lead Installation of the Lower Extension Lead Installation of the Upper Right Thermocouple Lead Assembly Installation of the Lower Left Thermocouple Lead Assembly
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------77-21-10-400-028 77-21-10-400-029 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 SPM 704450 SPM 704450320006 SPM 704460320007 72-54-00-991-310 72-54-00-991-311 72-54-00-991-312 72-54-00-991-313
Installation of the Upper Left Thermocouple Lead Assembly Installation of the Lower Right Thermocouple Lead Assembly Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
Fig. Fig. Fig. Fig.
801 802 803 804
3. __________ Job Set-up Subtask 72-54-00-941-069 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B Subtask 72-54-00-010-099 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-54-00-040-068 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-54-00-010-100 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-010-101 E. Get Access (1) Remove the T49.5 Thermocouple and Extension Lead Assembly (Ref. TASK 77-21-10-000-008), (Ref. TASK 77-21-10-000-009), (Ref. TASK 77-21-10000-026), (Ref. TASK 77-21-10-000-027), (Ref. TASK 77-21-10-000-028), (Ref. TASK 77-21-10-000-029), to get access to the studs of the bracket. 4. Procedure _________ (Ref. Fig. 801/TASK 72-54-00-991-310, 802/TASK 72-54-00-991-311, 803/TASK 72-54-00-991-312, 804/TASK 72-54-00-991-313) Subtask 72-54-00-320-052 A. Preparation for broken stud drilling WARNING : DO NOT BREATHE THE PARTICLES FROM GRINDING OR LET THE PARTICLES _______ TOUCH YOU. THE PARTICLES CAN CAUSE DAMAGE, INJURY OR IRRITATION TO YOU. USE PERSONAL PROTECTION EQUIPMENT. USE LOCAL MECHANICAL EXHAUST VENTILATION OR AN APPROVED RESPIRATOR.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B
Replacement of the Defective Studs on LPT Case Figure 801/TASK 72-54-00-991-310 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B
Dimensional Measurements for Working on Studs and Black Plate Figure 802/TASK 72-54-00-991-311 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/08
C F M 56-5B
Locally Manufactured Tool for Replacement of the Defective Studs on LPT Case Figure 803/TASK 72-54-00-991-312 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/08
C F M 56-5B
Lockwire of Bolt after Replacement of the Defective Studs on LPT Case Figure 804/TASK 72-54-00-991-313 R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B WARNING : USE EYE PROTECTION WHEN YOU USE COMPRESSED AIR TO CLEAN, COOL _______ OR DRY PARTS OR TOOLS. PARTICLES CAN CAUSE AN INJURY TO YOUR EYES. DO NOT USE MORE THAN 30 PSIG (200 KPA). DO NOT POINT COMPRESSED AIR AT YOURSELF OR OTHER PERSONS. NOTE : It is easier to use a square access to remove the nuts, with ____ bulkheads removed. (1) Calculate the length of the remaining broken tack welded stud (shank) with the remaining serviceable tack welded stud. (2) Install a locally manufactured tool on the remaining serviceable tack welded stud as follows: (a) Engage correctly the center pin of tooling in the bore which is the EGT (T49.5) sensor probe location. (b) Tighten the tooling to the LPT case with the original nut on the remaining serviceable tack welded stud. (c) Make sure the tooling is correctly installed against the LPT case. (3) Install the correct drill guide sleeve (sleeve is identified as clearance guide) for a 0.25 in. (6.3499 mm) drill. (4) Install and attach it with the use of a retaining screw between the drill guide sleeve and the locally manufactured tool. (5) Do a check from the top of the drill guide sleeve to the EGT sensor probe location of the LPT case. Subtask 72-54-00-917-054 B. Drilling of the broken stud shank (1) Calculate the necessary drill depth (with the dimensions given before and the dimensions shown in the figure) to remove the broken stud shank. (2) Make a selection to get the correct drilling stop ring for a 0.25 in. (6.3499 mm) drill. (3) Attach the stop ring to the 0.25 in. (6.3499 mm) diameter drill and set it to the depth as calculated in the paragraph above. (4) Put the drill into the tooling sleeve.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Nov 01/08
C F M 56-5B (5) Drill to a depth permitted by the stop ring to remove the remaining broken stud shank (Ref. SPM 704450320006). Subtask 72-54-00-917-055 C. Preparation for tack welded stud head drilling (1) Remove the drill guide sleeve (clearance guide). (2) Replace it with the other drill guide sleeve (identified as tapping drill guide) for a 0.2110 in. (5.3593 mm) drill. (3) Calculate the drill depth (with the dimensions given before and the dimensions shown in the figure) to drill through the tack welded stud head and the back plate. Subtask 72-54-00-917-056 D. Drilling of the tack welded stud head (1) Install a correct stop ring (stop ring is identified with a drill size of 0.211 in. (5.3593 mm) 0.2110 inch (5,36 mm)) to drill a 0.211 in. (5.3593 mm) diameter and set it to the depth specified as calculated in the Drilling of the broken stud shank paragraph B. (2) Put the drill into the tooling sleeve. CAUTION : OBEY THE INSTRUCTIONS BELOW TO PREVENT DAMAGE TO ADJACENT _______ PARTS AND TO REMOVE AND DISASSEMBLE THE ENGINE. (3) Drill through the stud head and the back plate but do not drill the insulation blanket and the other parts below (Ref. SPM 704450). (4) Remove the drill guide sleeve (identified as tapping drill guide). (5) Replace it with the other drill guide sleeve (identified as clearance guide). (6) Remove with a vacuum device all unwanted material. Subtask 72-54-00-917-057 E. Tapping of the tack welded stud head of the back plate. (1) Calculate the specified tap depth (with the dimensions given before and the dimensions shown in the figure) to tap through the tack welded stud head and the back plate only.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B (2) Set the 0.25 in. (6.3499 mm) stop ring to the specified depth with the tap given in tooling. (3) Put the tap into the tooling sleeve. CAUTION : OBEY THE INSTRUCTIONS BELOW TO PREVENT DAMAGE TO ADJACENT _______ PARTS AND TO REMOVE AND DISASSEMBLE THE ENGINE. (4) Tap the head of the tack welded stud and the back plate (Ref. SPM 704460320007) but do not push the parts below. (5) Remove with a vacuum all unwanted material and clean the adjacent areas. (6) Loosen the nut and remove the tooling. Subtask 72-54-00-320-053 F. Installation of the EGT (T49.5) sensor probe and check (1) Install the T49.5 Thermocouple and Extension Lead Assembly (Ref. TASK 77-21-10-400008), (Ref. TASK 77-21-10-400-009), (Ref. TASK 77-21-10-400-026), (Ref. TASK 77-21-10-400-027), (Ref. TASK 77-21-10-400-028), (Ref. TASK 77-21-10-400-029). 5. Close-up ________ Subtask 72-54-00-410-100 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-54-00-440-068 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
C F M 56-5B Subtask 72-54-00-410-101 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-54-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B LPT SHAFT - DESCRIPTION AND OPERATION _____________________________________ 1. _______ General (Ref. Fig. 001) A. Low pressure turbine shaft (1) The low pressure turbine (LPT) shaft module connects the fan shaft with the LPT rotor. It is composed of the LPT shaft, center vent tube and center vent tube rear extension duct. The aft end of the LPT shaft is supported by the No. 5 bearing ; its forward end is coupled with the fan shaft. The LPT shaft has 2 functions : coupling the fan/booster rotor with the LPT rotor and providing for high pressure turbine rear support through the No. 4 bearing. In addition, the LPT shaft houses the center vent tube of the forward and aft engine sumps. (2) The LPT shaft module consists of the following major parts : (a) LPT shaft. (b) No. 4 roller bearing. (c) No. 5 roller bearing. 2. ___________ Description (Ref. Fig. 002, 003) A. Low pressure Turbine Shaft (1) The LPT shaft is made of steel alloy. It is located concentrically in the high pressure rotor system. Its forward end is provided with outer splines for coupling with the fan shaft. It is axially retained by a shoulder and a coupling nut. At the aft end of the shaft, the No. 4 and 5 bearings are located axially on both sides of an integral hub. On the rear face, the hub supports 2 rotating air/oil seals which control the air circulation through the LPT rotor and the sump pressurizing air. On the front face, the hub supports the turbine rotor support. (2) The center vent tube is made of composite material. It is installed inside the LPT shaft. Its forward end is inserted in the LPT shaft plug and its aft end is supported by the LPT shaft hub. It is maintained coaxial in the LPT shaft through 2 inner locating diameters: one at the front end of the LPT shaft; the other at the rear end of the shaft.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Low Pressure Turbine Shaft Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Low Pressure Turbine Shaft Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
No. 4 and No. 5 Bearing Lubrication Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B (3) The center vent tube rear extension duct is installed at the aft end of the center vent tube. Its relative angular position is maintained by locating pins, and axial retention is provided by an inner nut threaded into the center vent tube. A centrifugal air/oil separator is retained by a nut against a central shoulder on the duct. Its relative angular position is maintained by slots at its front end. B. No. 4 Bearing The no. 4 bearing, which takes the high pressure turbine (HPT) rotor radial loads, is a roller bearing installed between the HPT rear shaft and the LPT shaft. The bearing outer race is housed in the HPT rear shaft bore, and its inner race is bolted to the front face of the LPT shaft integral hub. The inner race has a shoulder which would act as an emergency bearing in case of roller failure. The inner race front end is provided with a sump air seal. C. No. 5 Bearing The No. 5 Bearing supports the LPT rotor aft end inside the turbine frame and takes the radial loads. The bearing outer race is mounted in the turbine frame and its inner race is mounted at the rear of the LPT shaft integral hub. Axial retention is provided by a retainer nut. Retainer nut relative position is maintained by rivet.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B LPT SHAFT - MAINTENANCE PRACTICES _________________________________ TASK 72-55-00-960-002 Replacement of LPT Shaft Plug O-rings 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific 856A2632 856A2668 856A2946 856A3793
1 1 1 1
scriber warning notice PULLER KIT-PULLER ADAPTERS RING-PROTECTIVE FAN DISK FIXTURE,PUSHER PULLER-CVT
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP2442
* acetone (Ref. 70-30-00) * engine oil (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 201 Nov 01/08
C F M 56-5B C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------20 20 40 40 40 40 50 50 50 50 70 70 80 90 90 90 90 100 100 100 100
retaining ring retaining ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring retaining ring retaining ring damper seals O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring
72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00 72-55-00
01A-050 01B-050 01A-030 01A-030A 01B-030 01B-030A 01A-020 01A-020A 01B-020 01B-020A 01A-050 01B-050 01B-060 01A-030 01A-030A 01B-030 01B-030A 01A-020 01A-020A 01B-020 01B-020A
D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-21-00-000-005 72-21-00-000-006 72-21-00-400-005 72-21-00-400-006 72-55-00-991-301 72-55-00-991-302
Removal of the Spinner Front Cone Removal of the Spinner Rear Cone Installation of the Spinner Front Cone Installation of the Spinner Rear Cone Fig. 201 Fig. 202
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 202 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-55-00-941-051 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-55-00-010-051 B. Preparation for the replacement of LPT shaft plug O-rings (1) Remove the spinner front cone.(Ref. TASK 72-21-00-000-005) (2) Remove the spinner rear cone.(Ref. TASK 72-21-00-000-006) 4. Procedure _________ Subtask 72-55-00-960-051 A. Replacement of LPT shaft plug O-rings PRE CFM SB72-0436 (1) Replacement of LPT shaft plug O-rings NOTE : You must do this procedure for engine without center vent tube ____ forward removable (CFM SB72-0436) (Ref. Fig. 201/TASK 72-55-00-991-301) (a) Remove the retaining ring from forward end of LPT shaft, using a scriber.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 203 Nov 01/08
C F M 56-5B
Low Pressure Turbine Shaft Assembly (PRE CFM SB72-0436) Figure 201/TASK 72-55-00-991-301- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 204 Nov 01/08
C F M 56-5B
Low Pressure Turbine Shaft Assembly (PRE CFM SB72-0436) Figure 201/TASK 72-55-00-991-301- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 205 Nov 01/08
C F M 56-5B (b) Remove LPT shaft plug (10) using the KIT-PULLER ADAPTERS (856A2668G02) or PULLER (856A2632G01). (c) Remove and discard O-rings located in forward/aft grooves. (d) Remove the KIT-PULLER ADAPTERS (856A2668G02) or the PULLER (856A2632G01) from the LPT shaft plug (10). Install the LPT shaft plug (10) in the storage box. CAUTION : ACETONE IS EXPLOSIVE, AN IRRITANT, AN ALLERGEN, AND HAS _______ POISONOUS DETERIORATION. USE PERSONAL PROTECTION EQUIPMENT. USE VAPOR/FUME CONTROL OR A RESPIRATOR. (e) Clean the oil stains on the plug grooves with acetone (Material No. CP1039). (f) Clean the oil stains on the inner diameter of LPT forward shaft with bent brush soaked with acetone (Material No. CP1039). CAUTION : MAKE SURE THAT YOU CORRECTLY INSTALL A NEW O-RING IN _______ THE SEAL GROOVE AT THE FORWARD END OF THE LPT SHAFT PLUG. IF THE O-RING IS NOT CORRECTLY INSTALLED, DAMAGE TO THE ENGINE CAN OCCUR. (g) Lightly coat new O-ring (40) and new O-ring (50) with engine oil (Material No. CP2442) and install into the seal grooves of LPT shaft. (h) Install LPT shaft plug assembly into forward end of LPT shaft and onto center vent tube. NOTE : Insert lug of LPT shaft in aligned slots of LPT coupling ____ nut and LPT shaft. (i) Install retaining ring (20) onto LPT shaft. 1 _
Do a visual inspection to make sure of the correct installation of retaining ring (20) END OF PRE CFM SB72-0436 POST CFM SB72-0436
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 206 Nov 01/08
C F M 56-5B (2) Replacement of the O-rings and Damper Seals on the center vent tube forward removable (Ref. Fig. 202/TASK 72-55-00-991-302) WARNING : USE HEAT INSULATED GLOVES WHEN YOU TOUCH CHILLED OR HOTS _______ PARTS TO PREVENT INJURY WARNING : ENGINE OIL IS TOXIC. USE PERSONAL PROTECTION EQUIPMENT. USE _______ IN A WELL-VENTILATED AREA. (a) Install the RING-PROTECTIVE FAN DISK (856A2946G01) as follows: 1 _
Install the lower sector of the RING-PROTECTIVE FAN DISK (856A2946G01) in position in the fan disk hole.
2 _
Attach the lower sector of the RING-PROTECTIVE FAN DISK (856A2946G01) with the knurled screws.
3 _
Install the upper sector of the RING-PROTECTIVE FAN DISK (856A2946G01) in position in the fan disk hole.
4 _
Attach the upper sector of the RING-PROTECTIVE FAN DISK (856A2946G01) with the knurled screws.
(b) Remove the retaining ring from the front of the LPT shaft. (c) Screw the tube of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) in the center vent tube (60). (d) Install the support of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) on the fan disk flange with four screws. (e) Engage the plate of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) in the slot of the screw and attach it with the knurled nut. (f) Manually turn clockwise the screw of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) to disengage the center vent tube (60) from the LPT Shaft. NOTE : You can use a wrench if the counter torque is important. ____ (g) Remove the support of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) from the fan disk flange.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 207 Nov 01/08
C F M 56-5B
Center Vent Tube Forward Removable (POST CFM SB72-0436) Figure 202/TASK 72-55-00-991-302- 13 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 208 Nov 01/08
C F M 56-5B
Center Vent Tube Forward Removable (POST CFM SB72-0436) Figure 202/TASK 72-55-00-991-302- 23 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 209 Nov 01/08
C F M 56-5B
Center Vent Tube Forward Removable (POST CFM SB72-0436) Figure 202/TASK 72-55-00-991-302- 33 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 210 Nov 01/08
C F M 56-5B (h) Remove the center vent tube (60) equipped with the tube of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) from the LPT Shaft. (i) Remove the tube of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) from the center vent tube. (j) Remove and discard O-rings located in forward/aft grooves ofthe center vent tube. (k) Remove and discard the damper seals located in the other grooves of the center vent tube. (l) Clean the oil stains with acetone (Material No. CP1039) on the center vent tube (60), in the O-rings (90) and (100) and damper seals (80) grooves and in the inner diameter of the fan disk with a lint-free cloth. (m) Clean the oil stains on the inner diameter of LPT forward shaft with bent brush soaked with acetone acetone (Material No. CP1039). (n) Install the center vent tube (60) in the storage box. CAUTION : MAKE SURE THAT YOU CORRECTLY INSTALL THREE NEW DAMPER _______ SEALS IN THE THREE SEAL GROOVES OF THE CENTER VENT TUBE. YOU MUST HAVE THE PLATE FACE OF THE DAMPER SEALS POINTED TO OUTER OF THE CENTER VENT TUBE. IF THE DAMPER SEALS ARE NOT CORRECTLY INSTALLED, DAMAGE TO THE ENGINE CAN OCCUR. (o) Lightly coat three new damper seals (80) with engine oil (Material No. CP2442) and install them into their seal grooves of the center vent tube (60). CAUTION : MAKE SURE THAT YOU CORRECTLY INSTALL TWO NEW O-RINGS IN _______ THE SEAL GROOVE AT THE FORWARD END OF THE CENTER VENT TUBE. IF THE O-RINGS ARE NOT CORRECTLY INSTALLED, DAMAGE TO THE ENGINE CAN OCCUR. (p) Lightly coat new O-ring (90) and new O-ring (100) with engine oil (Material No. CP2442) and install into the seal grooves of the center vent tube (60).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 211 Nov 01/08
C F M 56-5B (q) Prepare the center vent tube (60) for installation as follows: 1 _
Screw the tube of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) in the center vent tube (60). CAUTION : TAKE CARE NOT TO DAMAGE THE LPT SHAFT INTERNAL _______ SUPPORTS AND PAINT DURING THE INSTALLATION OF THE CENTER VENT TUBE.
2 _
Align and install the center vent tube (60) into the LPT Shaft.
3 _
Align the lug of the center vent tube (60) with the aligned slots of the LPT Shaft and the LPT coupling.
(r) Install the FIXTURE,PUSHER PULLER-CVT (856A3793G02) as follows: 1 _
Install the support of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) on the fan disk flange with four screws.
2 _
Engage the plate of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) in the slot of the screw and attach it with the knurled nut.
(s) Complete the installation of the center vent tube (60) as follows: CAUTION : TAKE CARE TO STOP TURN COUNTER-CLOCKWISE THE SCREW OF _______ FIXTURE OF PUSHER/PULLER BEFORE THE LUG OF THE CENTER VENT TUBE TOUCHES THE SLOT OF THE LPT SHAFT. 1 _
Manually turn counter-clockwise the screw of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) to engage the center vent tube (60) into the slot of the LPT Shaft. NOTE : You can use a wrench if the counter torque is ____ important.
2 _
Remove the support of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) from the fan disk flange.
3 _
Remove the tube of fixture of FIXTURE,PUSHER PULLER-CVT (856A3793G02) from the center vent tube (60).
(t) Install the retaining ring (70) onto the LPT shaft.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 212 Nov 01/08
C F M 56-5B (u) Remove the RING-PROTECTIVE FAN DISK (856A2946G01) as follows: 1 _
Unscrew the knurled screws of the RING-PROTECTIVE FAN DISK (856A2946G01) which attach the upper sector.
2 _
Remove the upper sector of the RING-PROTECTIVE FAN DISK (856A2946G01) from the fan disk hole.
3 _
Unscrew the knurled screws of the RING-PROTECTIVE FAN DISK (856A2946G01) which attach the lower sector.
4 _
Remove the lower sector of the RING-PROTECTIVE FAN DISK (856A2946G01) from the fan disk hole.
(v) Do a visual inspection to make sure of the correct installation of retaining ring (70). END OF POST CFM SB72-0436 5. Close-up ________ Subtask 72-55-00-410-051 A. Install the Spinner Rear and Front Cone. (1) Install the spinner rear cone.(Ref. TASK 72-21-00-400-006) (2) Install the spinner front cone.(Ref. TASK 72-21-00-400-005)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 213 Nov 01/08
C F M 56-5B LPT SHAFT - INSPECTION/CHECK ____________________________ TASK 72-55-00-200-002 Inspection/Check of the Low Pressure Turbine Shaft Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-56-00-000-002 72-56-00-400-002 78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-55-00-991-901
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Oil Inlet Cover Assembly Installation of the Oil Inlet Cover Assembly Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601
EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Feb 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-55-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice in position to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice in position to tell persons not to energize the FADEC 1(2). Subtask 72-55-00-010-054 B. Get Access (1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040): - FOR 1000EM1 437AL, 438AR - FOR 1000EM2 447AL, 448AR. (2) Put the access platform in position. Subtask 72-55-00-040-051 C. Deactivation of the Thrust Reverser WARNING : YOU MUST DEACTIVATE THE THRUST REVERSER HYDRAULIC CONTROL UNIT _______ BEFORE YOU WORK ON OR AROUND THE THRUST REVERSER. IF YOU DO NOT DO THIS THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE INJURY AND DAMAGE. (1) Make the thrust reverser unserviceable for maintenance (Ref. TASK 7830-00-481-041).
EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Feb 01/09
C F M 56-5B Subtask 72-55-00-010-055 D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040): - FOR 1000EM1 451AL, 452AR - FOR 1000EM2 461AL, 462AR. Subtask 72-55-00-860-051 E. Aircraft Maintenance Configuration (1) Make sure that the core nozzle is removed (Ref. TASK 78-11-11-000041). (2) Make sure that the centerbody is removed (Ref. TASK 78-11-12-000041). (3) Make sure that the oil inlet cover assembly is removed (Ref. TASK 7256-00-000-002). 4. Procedure _________ (Ref. Fig. 601/TASK 72-55-00-991-901) Subtask 72-55-00-210-051 A. Visual Inspection of the Turbine Frame Assembly ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Air/oil separator (all areas, if exposed) for: A. Corrosion or pitting
Any amount
EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Feb 01/09
C F M 56-5B
Inspection of Air/Oil Separator Exposed Areas Figure 601/TASK 72-55-00-991-901 EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Feb 01/09
C F M 56-5B 5. Close-up ________ Subtask 72-55-00-410-054 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the oil inlet cover assembly (Ref. TASK 72-56-00-400-002). (3) Install the centerbody (Ref. TASK 78-11-12-400-041). (4) Install the core nozzle (Ref. TASK 78-11-11-400-041). (5) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040): - FOR 1000EM1 451AL, 452AR - FOR 1000EM2 461AL, 462AR. Subtask 72-55-00-440-051 B. Activation of the Thrust Reverser (1) Make the thrust reverser serviceable after maintenance (Ref. TASK 7830-00-081-041). Subtask 72-55-00-410-055 C. Close Access (1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): - FOR 1000EM1 437AL, 438AR - FOR 1000EM2 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-55-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Feb 01/09
C F M 56-5B TURBINE FRAME ASSEMBLY - DESCRIPTION AND OPERATION __________________________________________________ 1. General _______ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 001) **ON A/C 051-051, (Ref. Fig. 001A) R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 001B)
R R
**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, The turbine frame module is the major structure assembly at the rear of the engine. It supports the low pressure turbine (LPT) rotor rear section and provides for engine rear mounting on the airframe. The turbine frame consists of the following major parts : - Turbine frame. - No. 5 bearing support. 2. Description ___________ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, Post SB CFMI 72-0176 NOTE : This description is for Turbine Frame with Radial Struts only ____ A. Turbine Frame with Radial Struts (Ref. Fig. 002) The turbine frame assembly is made of nickel alloy and consists of a hub and a polygonal outer casing connected with radial struts. The external skin of the outer casing is lined with heat-insulation blankets. (Ref. Fig. 001)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Exploded View of Turbine Frame Assembly Figure 001 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 2 May 01/05
C F M 56-5B
R R
Exploded View of Turbine Frame Assembly Figure 001A
R EFF : 051-051, 72-56-00 CES
Page 3 May 01/05
C F M 56-5B
Exploded View of Turbine Frame Assembly Figure 001B R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
Turbine Frame Struts Section and Numbering Figure 002 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 5 May 01/05
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C F M 56-5B (1) There are 16 struts, airfoil-shaped and radial to the hub. The struts provide internal passage for the following items : (Ref. Fig. 003) (a) Aft sump oil scavenge tube (No. 7 strut) (b) Oil supply tube for the No. 4 and No. 5 bearings (No. 10 strut). (2) The aft sump overboard seal drain tube is routed between struts No. 8 and No. 9. (3) The front flange of the outer casing is bolted to the LPT case. The outer casing rear flange supports the primary exhaust nozzle. At its periphery, there are 3 clevis mounts for engine/airframe adaptation, and 2 brackets for handling and installation on engine storage stand. (Ref. Fig. 003)
R
(4) The hub inner front flange supports (from rear to front) the air heat cover and the No.5 bearing support. The air heat cover has three attachment circles: - the inner one attaches (from rear to front) the inner flange of the air heat cover and the flange of the No.5 bearing support, to the hub inner front flange. The No.5 bearing support contains the adjusting sleeve in its central bore. - the mid one provides support and attachment for the oil collector located forward of the air heat cover. - the outer one attaches both the outer flange of the air heat cover, and the seal cover, to studs located on the forward face of the hub. The air heat cover acts altogether as a support for the oil collector and (rearwards) as a seal and a heat shield. (5) The hub inner rear flange has the following attachment items: - a bolt circle on its inner diameter - a stud circle on its outer diameter The bolt circle provides attachment for the sheet metal flange assembly. The flange assembly provides the support, attachment and centering for the flame arrestor. The stud circle provides attachment for the engine exhaust plug (centerbody) with nuts. Post SB CFMI 72-0176
EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 6 Nov 01/07
C F M 56-5B
R R
Turbine Frame Struts Section and Numbering Figure 002A
R EFF : 051-051, 72-56-00 CES
Page 7 May 01/05
C F M 56-5B
Turbine Frame Struts Section and Numbering Figure 002B R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 8 Nov 01/08
C F M 56-5B
Turbine Frame Section Figure 003 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 9 May 01/05
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C F M 56-5B B. No. 5 Bearing Support for Turbine Frame with Radial Struts (Ref. Fig. 004) The No. 5 bearing support is made of steel alloy. Its outer flange is bolted, with the aft oil sump assembly, to the turbine frame. The inner flange of No. 5 bearing support accommodates the No. 5 bearing outer race and an adjusting sleeve. The rear face of the support carries the oil inlet cover which supports the oil supply tube for the No. 4 and 5 bearings, and provides for pressurization of the dual air/oil seal installed at the rear end of the center vent tube rear extension duct. The oil inlet cover supports the rear extension duct. The No. 5 bearing support has machined passages for : - Pressurizing air to the oil inlet cover. - Sump bleed air to the center vent tube. - Oil to the scavenge tube. - Oil supply to the No.5 bearing squeeze film vibration damping system. **ON A/C 051-051, Pre SB CFMI 72-0368 Pre SB CFMI 72-0176 NOTE : This descripton is for Turbine Frame with Tangential Non ____ Symetrical Section Struts only.
R
A. Turbine Frame with Tangential Non Symetrical Section Struts (Ref. Fig. 002A) The turbine frame assembly is made of nickel alloy and consists of a hub and a polygonal outer casing connected with tangential struts. (Ref. Fig. 001A)
R
(1) There are 16 struts, airfoil-shaped and tangential to the hub. The struts provide internal passage for the following items : (Ref. Fig. 003A)
R
(a) Aft sump oil scavenge tube (No. 7 strut) (b) Oil supply tube for the No. 4 and No. 5 bearings (No. 10 strut). (2) The aft sump overboard seal drain tube is routed between struts No. 7 and No. 8.
EFF : 001-049, 051-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 10 Nov 01/07
C F M 56-5B
R R
Turbine Frame Section Figure 003A
R EFF : 051-051, 72-56-00 CES
Page 11 May 01/05
C F M 56-5B
Turbine Frame Section Figure 003B R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 12 Nov 01/08
C F M 56-5B
Oil Pressurizing Seals-Location Figure 004 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 13 May 01/05
R
C F M 56-5B (3) The front flange of the outer casing is bolted to the LPT case. The outer casing rear flange supports the primary exhaust nozzle. At its periphery, there are 3 clevis mounts for engine/airframe adaptation, and 2 brackets for handling and installation on engine storage stand. (Ref. Fig. 003A) (4) On its front side, the hub of turbine frame has 3 attachment flanges that are, from the center and outward: - the hub inner front flange. This flange supports the No.5 bearing support. - the hub mid front flange. This flange supports the oil collector (or aft oil sump assembly). - the hub outer front flange. This flange supports the seal cover. The seal cover also provides forward retention of the inner flow path tiles. (5) On its rear side, the turbine frame has the following attachment items that are, from the center and outwards: - a flange located on the hub of turbine frame. This flange provides the support and attachment for the sheet metal flange assembly. This sheet metal flange assembly itself supports and centers the flame arrestor and also provides a rear support and centering for the oil inlet cover. - a circle of studs (quantity: 16). There is a stud projecting rearward at the root section of each tangential strut. The studs provide support and attachment for the engine exhaust plug (centerbody) with nuts. (6) The inner wall of the turbine frame gaspath is lined with stainless steel protective tiles. These tiles are located between the tangential struts. They have two stiffeners on their inner side to better withstand vibrations. Pre SB CFMI 72-0176 Pre SB CFMI 72-0368 B. No. 5 Bearing Support for Turbine Frame with Tangential Non Symetrical Section Struts (Ref. Fig. 004A) The No. 5 bearing support is made of steel alloy. Its attachment flange is bolted to the hub inner front flange of the turbine frame. The inner front bore of the No. 5 bearing support accommodates the No. 5 bearing outer race and an adjusting sleeve. The rear face of the support carries the oil inlet cover which supports the oil supply tube for the No. 4 and 5 bearings, and provides for pressurization of the dual air/oil seal installed at the rear end of the center vent tube rear extension duct.
R
EFF : 051-051, 72-56-00 CES
Page 14 Nov 01/07
C F M 56-5B
R R
Oil Pressurizing Seals-Location Figure 004A
EFF : 051-051, 72-56-00 CES
Page 15 May 01/05
C F M 56-5B The oil inlet cover supports the rear extension duct. The No. 5 bearing support has machined passages for : - Pressurizing air to the oil inlet cover. - Sump bleed air to the center vent tube. - Oil to the scavenge tube. - Oil supply to the No.5 bearing squeeze film vibration damping system. R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Post SB CFMI 72-0368 NOTE : This descripton is for Turbine Frame with Tangential Symetrical ____ Section Struts only. A. Turbine Frame with Tangential Symetrical Section Struts (Ref. Fig. 002B) The turbine frame assembly is made of nickel alloy and consists of a hub and a polygonal outer casing connected with tangential struts of a symetrical section. (Ref. Fig. 001B) (1) There are 16 struts, airfoil-shaped and tangential to the hub. The struts provide internal passage for the following items : (Ref. Fig. 003B) (a) Aft sump oil scavenge tube (No. 7 strut) (b) Oil supply tube for the No. 4 and No. 5 bearings (No. 10 strut). (2) The aft sump overboard seal drain tube is routed between struts No. 7 and No. 8. (3) The front flange of the outer casing is bolted to the LPT case. The outer casing rear flange supports the primary exhaust nozzle. At its periphery, there are 3 clevis mounts for engine/airframe adaptation, and 2 brackets for handling and installation on engine storage stand. (Ref. Fig. 003B) (4) On its front side, the hub of that are, from the center and - the hub inner front flange. support. - the hub outer front flange. (aft oil sump assembly).
turbine frame has 2 attachment flanges outward: This flange supports the No.5 bearing This flange supports the oil collector
R EFF : 051-051, 106-149, 155-199, 208-249, 72-56-00 251-299, 301-399, 401-499, CES
Page 16 Nov 01/08
C F M 56-5B (5) On its rear side, the turbine frame has the following attachment items that are, from the center and outwards: - a flange located on the hub of turbine frame. This flange provides the support and attachment for the sheet metal flange assembly on its mid circle. This sheet metal flange assembly itself supports and centers the flame arrestor and also provides a rear support and centering for the oil inlet cover on its inner circle, and also supports and centers the flow path fairing on its outer circle. - a circle of studs (quantity: 16). There is a stud projecting rearward at the root section of each tangential strut. The studs provide support and attachment for the engine exhaust plug (centerbody) with nuts. (6) The inner wall of the turbine frame gaspath is covered with the flow path fairing. The flow path fairing is a one part bolted to the plate lock, and to the flange assembly. This plate lock is mounted between the TRF, and the exhaust plug on the aft side. B. No. 5 Bearing Support for Turbine Frame with Tangential Symetrical Section Struts (Ref. Fig. 004B) The No. 5 bearing support is made of steel alloy. Its outer flange is attached, with the oil collector (aft oil sump assembly), to the turbine frame with bolts. The inner front bore of the No. 5 bearing support accomodates the No. bearing outer race and an adjusting sleeve. The rear face of the support carries the oil inlet cover which supports the oil supply tube for the No. 4 and 5 bearings, and provides for pressurization of the dual air/oil seal installed at the rear end of the center vent tube rear extension duct. The oil inlet cover supports the rear extension duct. The No. 5 bearing support has machined passages for : - Pressurizing air to the oil inlet cover. - Sump bleed air to the center vent tube. - Oil to the scavenge tube. - Oil to the No.5 bearing squeeze film vibration damping system.
R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 17 Nov 01/08
C F M 56-5B
Oil Pressurizing Seals-Location Figure 004B R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 18 Nov 01/08
C F M 56-5B TURBINE FRAME ASSEMBLY - REMOVAL/INSTALLATION _____________________________________________ TASK 72-56-00-000-001 Removal of the Flame Arrestor and Flange Assembly 1. __________________ Reason for the Job To allow the inspection/check and the cleaning of the rear sump oil supply tube in the LPT frame. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-11-11-000-041 78-11-12-000-041
Removal of the Core Nozzle Assembly Removal of the Centerbody
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-300
Fig. 401
**ON A/C 051-051, 72-56-00-991-300-B R
Fig. 401A
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-300-A
Fig. 401B
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
R R
C F M 56-5B **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 3. __________ Job Set-up Subtask 72-56-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-055 B. Get Access (1) Remove the core nozzle (Ref. TASK 78-11-11-000-041). (2) Remove the centerbody (Ref. TASK 78-11-12-000-041). 4. Procedure _________ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 401/TASK 72-56-00-991-300) **ON A/C 051-051, (Ref. Fig. 401A/TASK 72-56-00-991-300-B)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Nov 01/08
C F M 56-5B
Flame Arrestor and Flange Assembly Figure 401/TASK 72-56-00-991-300 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 403 May 01/05
C F M 56-5B
R R
Flame Arrestor and Flange Assembly Figure 401A/TASK 72-56-00-991-300-B
R EFF : 051-051, 72-56-00 CES
Page 404 May 01/05
R
C F M 56-5B **ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 401B/TASK 72-56-00-991-300-A) **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207, Subtask 72-56-00-020-050 A. Removal of the Flame Arrestor PRE SB CFMI 72-045 (1) Remove the six bolts (20) which attach the flame arrestor (30) to the oil inlet cover through the flange assembly (90). POST SB CFMI 72-045 (2) Remove the six bolts (20) which attach the flame arrestor (10) or (30) to the oil inlet cover through the flange assembly (90). END OF SB CFMI 72-045 Subtask 72-56-00-020-051 B. Removal of the Flange Assembly NOTE : This procedure is for both of Turbine Frame with Tangential Non ____ Symetrical Section Struts or with Radial Struts only. (1) Remove the three bolts (40) and washers (50) which attach the sleeve (60) to the flange assembly (90). (2) Remove the sleeve (60). (3) Remove the thirty two bolts (70) which attach the flange assembly (90) to the LPT frame. (4) Remove the flange assembly (90) from the LPT frame. (5) Remove and discard the gasket seal (80).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 405 Nov 01/08
C F M 56-5B
Flame Arrestor and Flange Assembly Figure 401B/TASK 72-56-00-991-300-A R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 406 Nov 01/08
R
C F M 56-5B **ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-020-050-A A. Removal of the Flame Arrestor (1) Remove the six bolts (20) which attach the flame arrestor (30) to the oil inlet cover through the flange assembly (160). Subtask 72-56-00-020-051-A B. Removal of the Flange Assembly NOTE : This procedure is for Turbine Frame with Tangential Symetrical ____ Section Struts only. (1) Remove the sixteen bolts (150) which attach the flow path fairing to the outer circle of the flange assembly (160) through the plate lock (170). (2) Remove the twenty four bolts (70) which attach the mid circle of the flange assembly (160) to the LPT frame hub rear flange. (3) Remove the flange assembly (160) from the LPT frame. (4) Remove and discard the gasket seal (80).
R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 407 Nov 01/08
C F M 56-5B **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, TASK 72-56-00-400-001 Installation of the Flame Arrestor and Flange Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------80 80
gasket seal gasket seal
72-56-00 02A-010 72-56-00 02B-010
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 408 Nov 01/09
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041
Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-300
Fig. 401
**ON A/C 051-051, 72-56-00-991-300-B R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-300-A
R R
Fig. 401A
Fig. 401B
**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 3. __________ Job Set-up Subtask 72-56-00-860-050 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the core nozzle is removed (Ref. TASK 78-11-11-000041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 409 Nov 01/08
C F M 56-5B (4) Make sure that the centerbody is removed (Ref. TASK 78-11-12-000041). 4. Procedure _________ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 401/TASK 72-56-00-991-300) **ON A/C 051-051, (Ref. Fig. 401A/TASK 72-56-00-991-300-B) R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 401B/TASK 72-56-00-991-300-A) **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207, Subtask 72-56-00-420-050 A. Installation of the Flange Assembly NOTE : This procedure is for Turbine Frame with Tangential Non ____ Symmetrical Section Struts or with Radial Struts only. (1) Install a new gasket seal (80) on the rear flange of the oil inlet cover. (2) Install the flange assembly (90) in position on the LPT frame. (3) Lubricate the threads of bolts (70) with graphite grease (Material No. CP2101). CAUTION : MAKE SURE THAT THE GASKET SEAL IS IN THE CORRECT POSITION _______ ON THE REAR FLANGE OF THE OIL INLET COVER. (4) Attach the flange assembly (90) with thirty two bolts (70). (5) TORQUE the bolts (70) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 410 Nov 01/08
C F M 56-5B (6) Lubricate the threads of bolts (40) with graphite grease (Material No. CP2101). (7) Install the sleeve (60) in position on the flange assembly. (8) Attach the sleeve (60) with three bolts (40) and washers (50). (9) TORQUE the bolts (40) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). Subtask 72-56-00-420-051 B. Installation of the Flame Arrestor (1) Lubricate the threads of bolts (20) with graphite grease (Material No. CP2101). PRE SB CFMI 72-045 (2) Install the flame arrestor (30) in position on the flange assembly (90). POST SB CFMI 72-045 (3) Install the flame arrestor (10) or (30) in position on the flange assembly (90). END OF SB CFMI 72-045 (4) Attach the flame arrestor with six bolts (20). (5) TORQUE the bolts (20) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-420-050-A A. Installation of the Flange Assembly NOTE : This procedure is for Turbine Frame with Tangential Symmetrical ____ Section Structs only. (1) Install a new gasket seal (80) on the rear flange of the oil inlet cover.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 411 Nov 01/08
C F M 56-5B (2) Install the flange assembly (160) in position on the LPT frame with flow path fairing and plate lock (170) installed. (3) Lubricate the threads of bolts (70) with graphite grease (Material No. CP2101). CAUTION : MAKE SURE THAT THE GASKET SEAL IS IN THE CORRECT POSITION _______ ON THE REAR FLANGE OF THE OIL INLET COVER. NOTE : Make sure that the flange assembly is correctly positioned ____ with the aft sump overboard seal drain tube in its position. (4) Attach the flange assembly (160) with twenty four bolts (70) to the hub inner rear flange of LPT frame. (5) TORQUE the bolts (70) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). (6) Lubricate the threads of bolts (150) with graphite grease (Material No. CP2101). (7) Attach the flange assembly (160) with sixteen bolts (150) to the flow path fairing installed on LPT frame through the plate lock (170). (8) TORQUE the bolts (150) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). Subtask 72-56-00-420-051-A B. Installation of the Flame Arrestor (1) Lubricate the threads of bolts (20) with graphite grease (Material No. CP2101). (2) Install the flame arrestor (30) in position on the flange assembly (160). (3) Attach the flame arrestor with six bolts (20). (4) TORQUE the bolts (20) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN).
R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 412 Nov 01/08
R R
C F M 56-5B **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 5. Close-up ________ Subtask 72-56-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the centerbody (Ref. TASK 78-11-12-400-041). (3) Install the core nozzle (Ref. TASK 78-11-11-400-041). (4) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 413 Nov 01/08
C F M 56-5B TASK 72-56-00-000-002 Removal of the Oil Inlet Cover Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific 856A3419
warning notice 1 ADAPTER, PULLER - OIL INLET COVER
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-56-00-000-001
Removal of the Flame Arrestor and Flange Assembly
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-301
Fig. 402
**ON A/C 051-051, 72-56-00-991-301-B R
Fig. 402A
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-301-A
Fig. 402B
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-302
Fig. 403
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 414 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------**ON A/C 051-051, 72-56-00-991-302-B R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-302-A
R R
Fig. 403A
Fig. 403B
**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 3. __________ Job Set-up Subtask 72-56-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-056 B. Remove the flame arrestor and the flange assembly (Ref. TASK 72-56-00000-001).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 415 Nov 01/08
C F M 56-5B 4. Procedure _________ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 402/TASK 72-56-00-991-301) **ON A/C 051-051, (Ref. Fig. 402A/TASK 72-56-00-991-301-B) R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 402B/TASK 72-56-00-991-301-A) **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 403/TASK 72-56-00-991-302) **ON A/C 051-051, (Ref. Fig. 403A/TASK 72-56-00-991-302-B)
R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 403B/TASK 72-56-00-991-302-A) **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, Subtask 72-56-00-020-052 A. Removal of the Rear Sump Oil Supply Tubes NOTE : For Turbine Frame with Radial Struts only. ____ (1) Cut and remove all the lockwires which safety the tube coupling nuts. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 416 Nov 01/08
C F M 56-5B
Oil Inlet Cover Figure 402/TASK 72-56-00-991-301 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 417 May 01/05
C F M 56-5B
R R
Oil Inlet Cover Figure 402A/TASK 72-56-00-991-301-B
R EFF : 051-051, 72-56-00 CES
Page 418 May 01/05
C F M 56-5B
Oil Inlet Cover Figure 402B/TASK 72-56-00-991-301-A R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 419 Nov 01/08
C F M 56-5B
Aft Sump Oil Supply Tubes Figure 403/TASK 72-56-00-991-302 R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 420 May 01/05
C F M 56-5B
R R
Aft Sump Oil Supply Tubes Figure 403A/TASK 72-56-00-991-302-B
R EFF : 051-051, 72-56-00 CES
Page 421 May 01/05
C F M 56-5B
Aft Sump Oil Supply Tubes Figure 403B/TASK 72-56-00-991-302-A R EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 422 Nov 01/08
C F M 56-5B (2) Loosen the coupling nuts of the oil supply tube (40) from the nipple (50), on the oil inlet cover (80) and from the oil supply tube (140), in the LPT frame strut. (3) Loosen both coupling nuts of the damping oil tube (70) from the nipple (90) on the No. 5 bearing support and from the oil supply tube (40). (4) Cut and remove the lockwire which safeties the sleeve locking nut (110). (5) Loosen the sleeve locking nut (110) to free the oil supply tube (140) in the LPT frame strut. (6) Cut and remove the lockwire which safeties the bolts (130). (7) Remove the bolts (130) and disengage the end fitting (120) from the LPT frame. (8) Remove the damping oil tube (70) and the oil supply tube (40). (9) Install bolts (130) again to attach the end fitting (120) to the LPT frame. Tighten bolts (130) by hand. **ON A/C 051-051, Subtask 72-56-00-020-052-B A. Removal of the Rear Sump Oil Supply Tubes NOTE : This procedure is for Turbine Frame with Tangential Non Symetrical ____ Section Struts only. (1) Cut and remove all the lockwires which safety the tube coupling nuts. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (2) Loosen the coupling nuts of the oil supply tube (40) from the nipple (50), on the oil inlet cover (80) and from the oil supply tube (100), in the LPT frame strut.
EFF : 001-049, 051-099, 101-105, 151-154, 72-56-00 201-207, R CES
Page 423 Nov 01/08
C F M 56-5B (3) Loosen both coupling nuts of the damping oil tube (70) from the nipple (90) on the No. 5 bearing support and from the oil supply tube (40). (4) Remove the damping oil tube (70) and the oil supply tube (40). R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-020-052-A A. Removal of the Rear Sump Oil Supply Tubes NOTE : This procedure is for Turbine Frame with Tangential Symetrical ____ Section Struts only. (1) Cut and remove all the lockwires which safety the tube coupling nuts. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (2) Loosen the coupling nuts of the oil supply tube (170) from the nipple (180), on the oil inlet cover (160) and from the oil supply tube (220), in the LPT frame strut. (3) Loosen both coupling nuts of the damping oil tube (200) from the nipple (210) on the No. 5 bearing support and from the oil supply tube (170). (4) Remove the damping oil tube (200) and the oil supply tube (170). **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207, Subtask 72-56-00-020-053 B. Removal of the Oil Inlet Cover NOTE : For Turbine Frame with Tangential Non Symetrical Section Struts or ____ with Radial Struts only. (1) Remove the bolts (30) which attach the oil inlet cover (80) to the No. 5 bearing support.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 424 Nov 01/08
C F M 56-5B (2) Install the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), on the rear flange of the oil inlet cover (80). (3) Remove the oil inlet cover (80). (4) Remove and discard the O-ring (20). (5) Remove and discard the gasket seal (10). (6) Remove the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), from the oil inlet cover (80). (7) Cut and remove the lockwire which safeties the nipple (50) to the oil inlet cover (80). (8) Remove the nipple (50) from the oil inlet cover (80). (9) Remove and discard the O-ring (60). R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-020-053-A B. Removal of the Oil Inlet Cover NOTE : For Turbine Frame with Tangential Symetrical Section Structs only. ____ (1) Remove the bolts (30) which attach the oil inlet cover (160) to the No. 5 bearing support. (2) Install the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), on the rear flange of the oil inlet cover (160). (3) Remove the oil inlet cover (160). (4) Remove and discard the O-ring (20). (5) Remove and discard the gasket seal (230). (6) Remove the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), from the oil inlet cover (160). (7) Cut and remove the lockwire which safeties the nipple (180) to the oil inlet cover (160). (8) Remove the nipple (180) from the oil inlet cover (160).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 425 Nov 01/08
C F M 56-5B (9) Remove and discard the O-ring (190). R R
**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, Subtask 72-56-00-210-055 C. Inspection of the oil inlet cover (1) Check for rubs marks from seal teeth in the abradable coating of the oil inlet cover. (a) If marks are found with an average less than 0.010 in. (0.2539 mm) (0.2539 mm) deep over entire circumference, the oil inlet cover is serviceable. (b) If marks are found with an average more than 0.010 in. (0.2539 mm) deep over entire circumference, the oil inlet cover must be sent to shop for repair.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 426 Nov 01/08
C F M 56-5B TASK 72-56-00-400-002 Installation of the Oil Inlet Cover Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R
No specific No specific No specific
soft nose pliers warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) 1 TOOL SET SEAL FITTING AGB-TGB 1 ADAPTER, PULLER - OIL INLET COVER
No specific 856A2794 856A3419
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2442
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00) USA AMS 5687 lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00) USA AMS 5689 lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 427 Feb 01/10
C F M 56-5B C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------10 10 20 20 20 20 60 60 60 60 60 60 190 190 190 190 190 190 230 230
Gasket Gasket O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring Gasket Gasket
seal seal
72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00
seal seal
02A-140 02B-140 02A-130 02A-130A 02B-130 02B-130A 02A-080 02A-080A 02A-080B 02B-080 02B-080A 02B-080B 02A-080 02A-080A 02A-080B 02B-080 02B-080A 02B-080B 02A-140 02B-140
D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-56-00-000-001 72-56-00-400-001
Removal of the Flame Arrestor and Flange Assembly Installation of the Flame Arrestor and Flange Assembly
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-301
Fig. 402
**ON A/C 051-051, 72-56-00-991-301-B
Fig. 402A
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 428 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-301-A
Fig. 402B
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, 72-56-00-991-302
Fig. 403
**ON A/C 051-051, 72-56-00-991-302-B R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, 72-56-00-991-302-A
R R
Fig. 403A
Fig. 403B
**ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 3. __________ Job Set-up Subtask 72-56-00-860-051 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the flame arrestor and the flange assembly are removed (Ref. TASK 72-56-00-000-001).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 429 Nov 01/08
C F M 56-5B 4. Procedure _________ **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 402/TASK 72-56-00-991-301) **ON A/C 051-051, (Ref. Fig. 402A/TASK 72-56-00-991-301-B) R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 402B/TASK 72-56-00-991-301-A) **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, (Ref. Fig. 403/TASK 72-56-00-991-302) **ON A/C 051-051, (Ref. Fig. 403A/TASK 72-56-00-991-302-B)
R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, (Ref. Fig. 403B/TASK 72-56-00-991-302-A) **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207, Subtask 72-56-00-420-052 A. Installation of the Oil Inlet Cover (80) NOTE : For Turbine Frame with Tangential Non Symetrical Section Struts or ____ with Radial Struts only. (1) Lubricate a new O-ring (60) with engine oil (Material No. CP2442). (2) Install the O-ring (60) on the nipple (50), with the TOOL SET SEAL FITTING AGB-TGB (856A2794G01).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 430 Nov 01/08
C F M 56-5B (3) Install the nipple (50) on the oil inlet cover (80) at 7:00 oclock position, aft looking forward. Tighten by hand to seat. (4) TORQUE the nipple (50) to between 180 and 195 lbf.in (2.03 and 2.20 m.daN). (5) Safety the nipple (50) to the oil inlet cover (80) with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). (6) Lubricate a new O-ring (20) with engine oil (Material No. CP2442). (7) Install the O-ring (20) in the front groove on the oil inlet cover (80). (8) Position a new Gasket seal (10) on the oil inlet cover (80). (9) Lubricate the threads of the bolts (20) with graphite grease (Material No. CP2101). (10) Install the oil inlet cover COVER (856A3419G02), in the inlet cover flange with the bottom of the No. 5 bearing
(80) with the ADAPTER, PULLER - OIL INLET LPT frame. Match the position of the oil oil scavenge tube which comes out at the support.
(11) Attach the oil inlet cover (80) to the No. 5 bearing support with bolts (30). (12) TORQUE the bolts (30) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). (13) Safety bolts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). R
**ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-420-052-A A. Installation of the Oil Inlet Cover (80) NOTE : For Turbine Frame with Tangential Symetrical Section Struts only. ____ (1) Lubricate a new O-ring (190) with engine oil (Material No. CP2442). (2) Install the O-ring (190) on the nipple (180), with the TOOL SET SEAL FITTING AGB-TGB (856A2794G01).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 431 Nov 01/08
C F M 56-5B (3) Install the nipple (180) on the oil inlet cover (160) at 7:00 oclock position, aft looking forward. Tighten by hand to seat. (4) TORQUE the nipple (180) to between 180 and 195 lbf.in (2.03 and 2.20 m.daN). (5) Safety the nipple (180) to the oil inlet cover (160) with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). (6) Lubricate a new O-ring (20) with engine oil (Material No. CP2442). (7) Install the O-ring (20) in the front groove on the oil inlet cover (160). (8) Position a new Gasket seal (230) on the oil inlet cover (160). (9) Lubricate the threads of the bolts (30) with graphite grease (Material No. CP2101). (10) Install the oil inlet cover (160) with the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), in the LPT frame. Match the position of the oil inlet cover flange with the oil scavenge tube which comes out at the bottom of the No. 5 bearing support. (11) Attach the oil inlet cover (160) to the No. 5 bearing support with bolts (30). (12) TORQUE the bolts (30) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN). (13) Safety bolts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). **ON A/C 001-049, 052-099, 101-105, 151-154, 201-207, Subtask 72-56-00-420-053 B. Installation of the Oil Supply Tubes CAUTION : MAKE SURE THAT THE SLEEVE LOCKING NUT OF THE OIL SUPPLY TUBE IN _______ THE LPT FRAME HUB IS LOOSENED. NOTE : For Turbine Frame with Radial Struts only. ____
R EFF : 001-049, 052-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 432 Nov 01/08
C F M 56-5B (1) Make sure that the sleeve locking nut (110) is loosened and remove the two bolts (130) which attach the end fitting (120) to the LPT frame. R R R
(2) Put the oil supply tube (40) and the damping oil tube (70) in position.
R
(3) Connect the oil supply tube (40) to the nipple (50) and to the oil supply tube (140). Tighten the coupling nuts by hand.
R R R
(4) Connect the damping oil tube (70) to the nipple (90) of the No. 5 bearing support and to the oil supply tube (40). Tighten the coupling nuts by hand. (5) Lubricate the threads of the bolts (130) with graphite grease (Material No. CP2101). (6) Attach the end fitting (120) to the LPT frame with bolts (130). (7) Tighten the sleeve locking nut (110) by hand.
R R R R
CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (8) Make sure the oil tubes are installed without strain.
R R
(9) TORQUE both coupling nuts of the oil tube (40) to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
R
(10) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R
(11) TORQUE the sleeve locking nut (110) to between 50 and 55 lbf.in (0.56 and 0.62 m.daN).
R
(12) Safety the sleeve locking nut (110) with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R
(13) TORQUE the two bolts (130) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN).
EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 433 Feb 01/10
R
C F M 56-5B (14) Safety bolts (130) with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R
(15) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R R R
(a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of the damping oil tube (70) connected to nipple of the No. 5 bearing support to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(16) Make sure that the damping oil tube (70) is installed without strain as follows:
R R
(a) Loosen the union nut of the damping oil tube connected on the oil tube (40).
R R
(b) Make sure that the damping oil tube is installed without strain, and in line with the nipple of the oil tube (40).
R R
(c) If necessary, bend the damping oil tube in bent sections. Do not bend the tube near end fittings.
R R
(17) Reconnect the coupling nut of the damping oil tube (70) to the oil tube (40). Tighten the coupling nut with hand.
R
(18) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R R
(a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of damping oil tube (70) to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(19) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R EFF : 001-049, 052-099, 101-105, 151-154, 72-56-00 201-207, CES
Page 434 Feb 01/10
C F M 56-5B **ON A/C 051-051, Subtask 72-56-00-420-053-B B. Installation of the Oil Supply Tubes NOTE : This procedure is for Turbine Frame with Tangential Non Symetrical ____ Section Struts only. NOTE : Make sure that Oil Supply Tube in the LPT frame is correctly ____ positioned. (1) Put the oil supply tube (40) and the damping oil tube (70) in position. R R
(2) Connect the oil supply tube (40) to the nipple (50) and to the oil supply tube (100). Tighten the coupling nuts by hand.
R R R
(3) Connect the damping oil tube (70) to the nipple (90) of the No. 5 bearing support and to the oil supply tube (40). Tighten the coupling nuts by hand.
R R R R
CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (4) Make sure the oil tubes are installed without strain.
R R
(5) TORQUE both coupling nuts of the oil tube (40) to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
R
(6) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R
(7) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R EFF : 051-051, 72-56-00 CES
Page 435 Feb 01/10
R R R
C F M 56-5B (a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of the damping oil tube (70) connected to nipple of the No. 5 bearing support to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(8) Make sure that the damping oil tube (70) is installed without strain as follows:
R R
(a) Loosen the union nut of the damping oil tube connected on the oil tube (40).
R R
(b) Make sure that the damping oil tube is installed without strain, and in line with the nipple of the oil tube (40).
R R
(c) If necessary, bend the damping oil tube in bent sections. Do not bend the tube near end fittings.
R R
(9) Reconnect the coupling nut of the damping oil tube (70) to the oil tube (40). Tighten the coupling nut with hand.
R
(10) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R R
(a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of damping oil tube (70) to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(11) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). **ON A/C 106-149, 155-199, 208-249, 251-299, 301-399, 401-499, Subtask 72-56-00-420-053-A B. Installation of the Oil Supply Tubes NOTE : This procedure is for Turbine Frame with Tangential Symetrical ____ Section Struts only. NOTE : Make sure that Oil Supply Tube in the LPT frame is correctly ____ positioned.
R EFF : 051-051, 106-149, 155-199, 208-249, 72-56-00 251-299, 301-399, 401-499, CES
Page 436 Feb 01/10
C F M 56-5B (1) Put the oil supply tube (170) and the damping oil tube (200) in position. R R
(2) Connect the oil supply tube (170) to the nipple (180) and to the oil supply tube (220). Tighten the coupling nuts by hand.
R R R
(3) Connect the damping oil tube (200) to the nipple (210) of the No. 5 bearing support and to the oil supply tube (170). Tighten the coupling nuts by hand.
R R R R
CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (4) Make sure the oil tubes are installed without strain.
R R
(5) TORQUE both coupling nuts of the oil tube (170) to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
R
(6) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R
(7) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R R R
(a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of the damping oil tube (200) connected to nipple of the No. 5 bearing support to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(8) Make sure that the damping oil tube (200) is installed without strain as follows:
R R
(a) Loosen the union nut of the damping oil tube connected on the oil tube (170).
R R
(b) Make sure that the damping oil tube is installed without strain, and in line with the nipple of the oil tube (170).
EFF : 106-149, 155-199, 208-249, 251-299, 72-56-00 301-399, 401-499, CES
Page 437 Feb 01/10
R R
C F M 56-5B (c) If necessary, bend the damping oil tube in bent sections. Do not bend the tube near end fittings.
R R
(9) Reconnect the coupling nut of the damping oil tube (200) to the oil tube (170). Tighten the coupling nut with hand.
R
(10) Torque of the damping oil tube
R R R
CAUTION : HOLD THE DAMPING OIL TUBE WITH SOFT NOSE PLIERS WHEN YOU _______ TORQUE THE UNION NUT. THIS IS TO PREVENT DAMAGE TO THE TUBE.
R R
(a) Hold the damping oil tube with soft nose pliers. TORQUE the union nut of damping oil tube (200) to between 90 and 100 lbf.in (1.01 and 1.13 m.daN).
R R
(11) Safety the coupling nuts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 5. Close-up ________ Subtask 72-56-00-410-057 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the flange assembly and the flame arrestor (Ref. TASK 72-5600-400-001). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 438 Feb 01/10
C F M 56-5B TURBINE FRAME ASSEMBLY - INSPECTION/CHECK _________________________________________ TASK 72-56-00-210-002 Inspection/Check of the Turbine Frame Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice access platform 0.5 m (1 ft. 8 in.)
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-00-00-200-025 72-56-00-000-001 72-56-00-300-003 72-56-00-300-006 72-56-00-400-001 R R R R
78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 72-56-00-991-305
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Over-Serviceable-Limit Extensions Removal of the Flame Arrestor and Flange Assembly Replacement of Defective Studs Replacement of the Oil Supply Tube Assembly Installation of the Flame Arrestor and Flange Assembly Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Fig. 601
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 601 Nov 01/08
C F M 56-5B 3. __________ Job Set-up R
Subtask 72-56-00-860-054
R
A. Aircraft Maintenance Configuration
R R
(1) Make sure that the core nozzle is removed (Ref. TASK 78-11-11-000041).
R R
(2) Make sure that the centerbody is removed (Ref. TASK 78-11-12-000041). Subtask 72-56-00-941-051
R
B. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-053
R
C. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-56-00-040-051
R
D. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B Subtask 72-56-00-010-054 R
E. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 601/TASK 72-56-00-991-305) Subtask 72-56-00-210-051 A. Visual inspection of the Turbine Frame Assembly: ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Forward and aft outer flanges for : - Cracks connecting bolt holes
Not serviceable
- Cracks extending from bolt holes to outer edge of flange.
One crack 0.20 in. (5.1 mm) max. per hole with a minimum 5-hole separation between cracks.
- Cracks extending from bolt holes toward casing skin.
Five cracks 0.20 in. (5.1 mm) max. per flange with a minimum 10-hole separation between cracks. Axial cracks only.
- Cracks in other areas of flange.
Five cracks per flange 0.20 in. (5.1 mm) long with a minimum 5 in. (127 mm) separation between any other cracks.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B
Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 15 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B
Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 25 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 605 Nov 01/08
C F M 56-5B
Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 35 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 606 Nov 01/08
C F M 56-5B
Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 45 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 607 Nov 01/08
C F M 56-5B
Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 55 (SHEET 5) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 608 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Nicks, scores and Five per flange 1 in. scratches. (25.4 mm) long, 0.01 in. (0.25 mm) dup, after removal of high metal with 1 in. (25.4 mm) minimum separation. 2. Engine mounting lug areas, airframe attach points only for : - Cracks out of bolt holes
Not serviceable
- Cracks in welds or in other areas of engine mounting lug area.
Not serviceable
- Nicks, scores and scratches.
Any number 1 in. (25.4 mm) long, 0.02 in. (0.5 mm) deep after removal of high metal with 1 in. (25.4 mm) minimum separation.
3. All other areas of outer casing skin for : - Cracks
Not serviceable.
- Nicks, scores and scratches.
Any number 1 in. (25.4mm) long, 0.03 in. (0.76 mm) deep after removal of high metal and 1 in. (25.4 mm) minimum apart.
4. Oil supply and scavenge tubes for :
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 609 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Cracks Not serviceable. Replace the oil supply tube (Ref. TASK 72-56-00300-006). - Nicks, scratches
Any number 0.01 in. (0.25 mm) deep after removal of high metal.
Replace the oil supply tube (Ref. TASK 72-56-00300-006).
- Dents
Two per tube, smooth contour 0.05 in. (1.27 mm) deep.
Replace the oil supply tube (Ref. TASK 72-56-00300-006).
- Oil marks
Any amount
5. Struts for: - Cracks
Not serviceable.
- Nicks, scores and scratches.
Any number, any length 0.02 in. (0.51 mm) deep after removal of high metal.
- Dents
Any number, smooth contour 0.02 in. (0.51 mm) deep.
- Broken stud or damaged threads
Three (3) maximum: - If not adjacent to each other: 500hrs/500cyc - If two (2) non-serviceable studs are adjacent, but the third one is separated from them by two (2) serviceable studs: 500hrs/500cyc
Replace stud (Ref. TASK 72-56-00-300-003) within 500 hours/500 cycles.
6. No. 7 and No. 10 struts (oil supply and scavenge tubes) bulkheads for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 610 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- Cracks in the Two cracks, any lenght bulkhead wall on each bulkhead - Cracks from the bulkhead, extending in the hub skin
Not serviceable
7. Sump flooding boss area for: - Cracks in the hub
Two cracks, no longer than 1 in. (25.4 mm) and 1 in. (25.4 mm) apart, minimum
Flame arrestor for: - cracks in all areas including the retaining metal strip
Any number
- Missing retaining strips
Serviceable, if one strip remains
- Honeycomb grid plug for obturation
Any area up to 50 percent of obturation
- Honeycomb missing
Not serviceable
Replace the flame arrestor within the next 10 cycles (Ref. TASK 72-56-00-000001) (Ref. TASK 72-56-00400-001)
8. Thermal insulation blankets - missing or protuding blanket in the flowpath
Not serviceable
Install a new blanket. See overserviceable limit extension (Ref. TASK 7200-00-200-025)
9. Guide bushing for the oil supply tube for:
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 611 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------- worn area No more than 0.06 in. (1.52 mm) - flush with the LPT bore
Not serviceable
600 cycles or 750 hours max serviceable extension is allowed with less than 0.06 in. (1.52 mm). 25 cycles or 50 hours max serviceable extension is allowed with more than 0.06 in. (1.52 mm).
5. Close-up ________ Subtask 72-56-00-410-053 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. R
(2) Install the centerbody (Ref. TASK 78-11-12-400-041).
R
(3) Install the core nozzle (Ref. TASK 78-11-11-400-041).
R
(4) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-56-00-440-051 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 612 Nov 01/08
C F M 56-5B Subtask 72-56-00-410-054 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s). (3) Remove the warning notice(s).
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 613 Nov 01/08
C F M 56-5B TURBINE FRAME ASSEMBLY - CLEANING/PAINTING __________________________________________ TASK 72-56-00-100-001 Cleaning of the Oil Inlet Cover 1. __________________ Reason for the Job Use this procedure to clean the oil inlet cover. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-56-00-000-002 72-56-00-400-002 SPM 702111 SPM 702112 SPM 702131 72-56-00-991-303
Removal of the Oil Inlet Cover Assembly Installation of the Oil Inlet Cover Assembly
Fig. 701
3. __________ Job Set-up Subtask 72-56-00-941-054 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 701 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-057 B. Remove the oil inlet cover (Ref. TASK 72-56-00-000-002). 4. Procedure _________ (Ref. Fig. 701/TASK 72-56-00-991-303) Subtask 72-56-00-110-050 A. Degreasing of the Oil Inlet Cover (1) Solvent degreasing (alternative procedure available) - refer to CFMI SPM (Ref. SPM 702111), Solvent Degreasing of all materials, except Titanium Alloys. (2) Vapor degreasing (alternative procedure) - refer to CFMI SPM (Ref. SPM 702112), Vapor Degreasing. NOTE : Use one of these procedures to remove oil and grease from the ____ oil inlet cover. Subtask 72-56-00-130-050 B. Cleaning of the Oil Inlet Cover - refer to CFMI SPM (Ref. SPM 702131), Descalling ferrous alloys. Subtask 72-56-00-210-052 C. Inspection of the Oil Nozzle (1) Make sure that the oil nozzle is clean and clear of unwanted material.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 702 Nov 01/08
C F M 56-5B
Cleaning of the Oil Inlet Cover Figure 701/TASK 72-56-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 703 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-56-00-410-058 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the oil inlet cover (Ref. TASK 72-56-00-400-002). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 704 Nov 01/08
C F M 56-5B TASK 72-56-00-100-002 Cleaning of the Aft Sump Oil Supply Tube 1. __________________ Reason for the Job Use this procedure to clean the aft sump oil supply tube where it goes through the No. 10 turbine frame strut, when you suspect signs of cocking in this oil supply tube, after an air flow check of the aft sump oil supply circuit. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-56-00-000-002 72-56-00-400-002 SPM 702117 R R
Removal of the Oil Inlet Cover Assembly Installation of the Oil Inlet Cover Assembly
**ON A/C 001-049, 052-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 72-56-00-991-304
Fig. 702
**ON A/C 051-051, 72-56-00-991-304-A
Fig. 702A
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 705 Nov 01/08
R R
C F M 56-5B **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, 3. __________ Job Set-up Subtask 72-56-00-941-055 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-058 B. Remove the oil inlet cover (Ref. TASK 72-56-00-000-002). 4. Procedure _________
R R
**ON A/C 001-049, 052-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, (Ref. Fig. 702/TASK 72-56-00-991-304) **ON A/C 051-051, (Ref. Fig. 702A/TASK 72-56-00-991-304-A)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 706 Nov 01/08
C F M 56-5B
Cleaning of the Aft Sump Oil Supply Tube Figure 702/TASK 72-56-00-991-304 R EFF : 001-049, 052-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 707 Nov 01/08
C F M 56-5B
Cleaning of the Aft Sump Oil Supply Tube Figure 702A/TASK 72-56-00-991-304-A R EFF : 051-051, 72-56-00 CES
Page 708 Aug 01/07
R R
C F M 56-5B **ON A/C 001-049, 051-099, 101-149, 151-199, 201-249, 251-299, 301-399, 401-499, Subtask 72-56-00-110-051 A. Degreasing and Cleaning of the Aft Sump Oil Supply Tube (1) Connect steel tubing and an approved pump to the oil supply tube ends. (2) Do the cleaning of internal lube oil tube (Ref. SPM 702117). 5. Close-up ________ Subtask 72-56-00-410-059 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the oil inlet cover (Ref. TASK 72-56-00-400-002). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 709 Nov 01/08
C F M 56-5B TASK 72-56-00-100-005 Cleaning of the Aft Sump Oil Scavenge Tube 1. __________________ Reason for the Job Use this procedure to clean the aft sump oil scavenge tube where it goes through the No. 7 turbine frame strut, when you suspect signs of coking in this oil scavenge tube, after an air flow check of the aft sump oil scavenge circuit. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 0.70 to 10.00 m.daN (5.00 to 75.00 lbf.ft) Torque Wrench : range 2.00 to 20.00 m.daN (15.00 to 150.00 lbf.ft) 1 WRENCH-COUNTERTORQUE NO 5 BEARING NIPPLE LINE
No specific R
856A3492
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1041
Material No.
CP1065
Material No.
CP2104
Material No.
CP2442
Material No.
CP2554
Material No.
CP8001
Material No.
CP8006
* alcohol-isopropyl (Ref. 70-30-00) * kerosene (Ref. 70-30-00) * lubricant-molybdenum disulfide, solid-molykote G (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * lubricant oil WD-40 (Ref. 70-30-00) * safetywire (Ref. 70-30-00) * safety cable (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 710 Nov 01/09
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-56-00-000-002 72-56-00-400-002 SPM 702117 72-56-00-991-306 72-56-00-991-307
Removal of the Oil Inlet Cover Assembly Installation of the Oil Inlet Cover Assembly Fig. 703 Fig. 704
3. __________ Job Set-up Subtask 72-56-00-941-063 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-56-00-010-069 B. Remove the oil inlet cover (Ref. TASK 72-56-00-000-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 711 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 703/TASK 72-56-00-991-306, 704/TASK 72-56-00-991-307) Subtask 72-56-00-020-065 A. Disconnect the oil scavenge tube CAUTION : USE TWO WRENCHES TO LOOSEN THE TUBE COUPLING NUTS. USE ONE _______ WRENCH TO HOLD THE NIPPLE FITTING. USE THE OTHER WRENCH TO LOOSEN THE COUPLING NUT. IF THE NIPPLE FITTING TURNS, DAMAGE CAN OCCUR. (1) Disconnect the aft sump oil scavenge tube from the oil scavenge tube, at the No. 7 TRF strut. CAUTION : USE THE COUNTER WRENCH TO LOOSEN THE TUBE COUPLING NUTS. _______ OTHER WRENCHES CAN CAUSE DAMAGE TO THE HARDWARE. (2) Disconnect the oil scavenge tube from the nipple of the No. 5 bearing support. (Ref. Fig. 703/TASK 72-56-00-991-306) (a) Cut and remove the safetywire between the nipple, at the 6 oclock position of the No. 5 bearing support nipple, and the coupling nut of the oil scavenge tube. R R
(b) Install the WRENCH-COUNTERTORQUE NO 5 BEARING NIPPLE LINE (856A3492) (G03) or (G04) on the TRF flange: 1 _
Loosen the four counter wrench bolts.
2 _
Install the counter wrench on the No. 5 bearing support nipple.
3 _
Tighten the two support bolts on the turbine rear frame.
4 _
Do a clockwise rotation on the counter wrench to take up and tighten the four counter wrench bolts.
(c) Disconnect the oil scavenge tube from the nipple of the No. 5 bearing support with the oil scavenge tube nut wrench. (d) Remove the counter wrench from the TRF flange.
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 712 Nov 01/09
C F M 56-5B (e) Disengage the guide bushing of the oil scavenge tube from the 5 oclock boss of the TRF outer case to get access to the oil scavenge tube upper end. Subtask 72-56-00-290-050 B. Do a visual inspection of the oil scavenge tube with a flexible borescope tool of 2.5 mm (0.0984 in.) to 4 mm (0.1574 in.) dia. and a light source. (1) Make sure that it is free of any particles/contamination. If you find any signs of oil coking, remove the oil scavenge tube to do a chemical cleaning. Subtask 72-56-00-110-054 C. If the borescope check of the oil scavenge tube shows coking contamination, degrease and clean the tube as follows: (1) Attach the steel tubing and the pump to the removed oil scavenge tube. NOTE : You must use steel tubing and an acceptable pump to do this ____ procedure. (2) Clean the internal oil tubes (Ref. SPM 702117). (3) Do a visual inspection of the cleaned oil scavenge tube with a flexible borescope tool of 2.5 mm (0.0984 in.) to 4 mm (0.1574 in.) dia. and a light source after cleaning to make sure that it is free of any particles/contamination before re-installation. (a) No oil coked particles/contamination is permitted. (b) Repeat the cleaning task until the tube is free of particles/contamination. (4) Disconnect the cleaned tube from the steel tubing and the pump.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 713 Nov 01/08
C F M 56-5B
Oil Scavenge Tube Nut Figure 703/TASK 72-56-00-991-306- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 714 Nov 01/08
C F M 56-5B
Oil Scavenge Tube Nut Figure 703/TASK 72-56-00-991-306- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 715 Nov 01/08
C F M 56-5B
Oil Scavenge Line Cleaning Figure 704/TASK 72-56-00-991-307- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 716 Nov 01/08
C F M 56-5B
Oil Scavenge Line Cleaning Figure 704/TASK 72-56-00-991-307- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 717 Nov 01/08
C F M 56-5B Subtask 72-56-00-110-055 D. Degrease and mechanically clean the oil scavenge tube (not removable) as follows: NOTE : This is a mechanical cleaning because the tube is non-removable. ____ (1) Put protection on the No. 5 bearing to prevent any contamination by the material. NOTE : Be careful to put protection equipment on the No. 5 bearing ____ before you start a mechanical cleaning of the oil scavenge line. (2) Put protection on all the cavities and tube ends to prevent any contamination by the material. (3) Put a cap for the oil scavenge tube on the outer case side. (4) Put a sufficient quantity of lubricant oil WD-40 (Material No. CP2554) to fill the tube and keep it for a sufficient time to affect the coking in the concerned area. (5) Put a container under the tube to collect the penetrant corrosion inhibitor. (6) Remove the cap from the tube and collect the penetrant corrosion inhibitor. (7) Turn the tube in its position to get access to the ends of the tube. (8) Introduce a cylinder-brush tool through the tube ends and move the tool to the coked area. WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE YOUR _______ CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. (9) Put a small quantity of kerosene (Material No. CP1065) with a filler tool in the tube. (10) Do an alternative movement of rotation on the tool to break the coking contamination.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 718 Nov 01/08
C F M 56-5B (11) Extract the tool and use lint-free cloths to collect the coked particle. WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE YOUR _______ CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. (12) Clean the cylinder-brush tool with kerosene (Material No. CP1065). CAUTION : DO NOT INTRODUCE ANY PARTICULES/CONTAMINATION TO THE _______ INTERNAL SIDE OF BEARING SUPPORT TO PREVENT BEARING CONTAMINATION. IF NOT, YOU CAN CAUSE DAMAGE TO ENGINE. (a) Repeat the cleaning until tube is free of particles/contamination. WARNING : DO NOT LET THE FUEL TOUCH YOUR SKIN OR CLOTHES. REMOVE _______ YOUR CLOTHES IF THE FUEL TOUCHES THEM. FLUSH YOUR SKIN FULLY WITH WATER WHERE THE FUEL TOUCHED YOU. FUEL CAN BURN YOUR SKIN. WARNING : CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY _______ SHOULD BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN, OR CLOTHING. NOTE : No oil coked particles/contamination is permitted. ____ (13) Do a flushing of the tube with kerosene (Material No. CP1065) or alcohol-isopropyl (Material No. CP1041). (14) Dry the tube with a clean compressed air source or nitrogen source. (15) Do a visual inspection of the cleaned tube with a flexible borescope tool of 2.5 mm (0.0984 in.) to 4 mm (0.1574 in.) dia. and a light source after cleaning to make sure that it is free of any particles/contamination before you use it again. (16) Do a mechanical cleaning of the nipple of the No. 5 bearing support at the 6 oclock position to remove any signs of oil coking. (17) Dry and clean the nipple with a compressed air source or nitrogen source.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 719 Nov 01/08
C F M 56-5B (18) Do a visual inspection of the cleaned tube with a flexible borescope tool of 2.5 mm (0.0984 in.) to 4 mm (0.1574 in.) dia. and a light source after cleaning to make sure that it is free of any particles/contamination before the installation of the oil scavenge tube. (a) Repeat the cleaning until the nipple is free of particles/contamination. NOTE : No oil coked particles/contamination is permitted. ____ Subtask 72-56-00-420-063 E. Reconnection of the oil scavenge line (1) Reconnect the oil scavenge line as follows: (a) Remove the protection from the No. 5 bearing cavity and oil scavenge tube ends. (b) Apply a thin layer of lubricant-molybdenum disulfide, solidmolykote G (Material No. CP2104) with a spray gun on the guide bushing of the oil scavenge tube. (c) Engage the guide bushing of the oil scavenge tube into the boss of the TRF at the 5 oclock position. (d) Connect the coupling nut of oil scavenge tube to the 6 oclock nipple on the No. 5 bearing support. Tighten the coupling nut by hand. CAUTION : ALWAYS INSTALL THE COUNTER WRENCH ON THE NIPPLE OF THE _______ NUMBER-5 BEARING SUPPORT. THEN LOOSEN OR TIGHTEN THE COUPLING NUT OF THE OIL SCAVENGE TUBE. THIS WILL HELP TO PREVENT DAMAGE TO THE NIPPLE. R
(2) Install the WRENCH-COUNTERTORQUE NO 5 BEARING NIPPLE LINE (856A3492) (G03) or (G04) on the TRF flange. (a) Loosen the four counter wrench bolts. (b) Install the counter wrench on the No. 5 bearing support nipple. (c) Tighten the two support bolts on the turbine rear frame. (d) Do a clockwise rotation on the counter wrench to take up and tighten the four counter wrench bolts.
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 720 Nov 01/09
C F M 56-5B (3) Tighten the coupling nut of the oil scavenge tube to between 5 and 6 m.daN (36.87 and 44.24 lbf.ft) with the oil scavenge tube nut wrench. (a) Attach with safetywire (Material No. CP8001) or safety cable (Material No. CP8006). (4) Remove the counter wrench from the TRF flange. (5) Reconnect the rear sump oil scavenge tube to the oil scavenge tube. (Ref. Fig. 704/TASK 72-56-00-991-307) WARNING : DO NOT LET THE ENGINE OIL STAY ON YOUR SKIN FOR A LONG _______ TIME. FLUSH OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND INTO YOUR BODY. (a) Apply a layer of engine oil (Material No. CP2442) on the threads of the rear sump oil scavenge tube. CAUTION : USE TWO WRENCHES TO TIGHTEN THE TUBE COUPLING NUTS. USE _______ ONE WRENCH TO HOLD THE NIPPLE FITTING. USE THE OTHER WRENCH TO TIGHTEN THE COUPLING NUT. IF THE NIPPLE FITTING TURNS, DAMAGE CAN OCCUR. (b) Tighten the coupling nuts to between 10.2 and 12.4 m.daN (75.22 and 91.44 lbf.ft). (c) Safety the coupling nut to the nipple with safetywire (Material No. CP8001) or safety cable (Material No. CP8006). 5. Close-up ________ Subtask 72-56-00-410-071 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the oil inlet cover (Ref. TASK 72-56-00-400-002). (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 721 Nov 01/08
C F M 56-5B TURBINE FRAME ASSEMBLY - REPAIRS ________________________________ TASK 72-56-00-300-003 Replacement of Defective Studs 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R R R
No specific
Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN)
No specific B. Consumable Materials
------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 72-56-00-991-310
Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Fig. 801
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 801 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-56-00-010-065 A. Get Access (1) Remove the core nozzle (Ref. TASK 78-11-11-000-041). (2) Remove the center body (Ref. TASK 78-11-12-000-041). 4. Procedure _________ (Ref. Fig. 801/TASK 72-56-00-991-310) Subtask 72-56-00-869-054 A. Preparation for Replacement (1) Clear away the stud to repair by removing the attachment bolts on the rear flange of the two adjacent thermal insulation blankets and lifting them. After SB 72-247 (2) Clear away the stud to repair by removing the attachment bolts and washers on the rear flange of the two adjacent thermal insulation blankets and lifting them. END of SB 72-247 Subtask 72-56-00-350-052 B. Replace defective studs (1) Remove the tack weld which safeties the defective stud to the frame. To do this, use a small, narrow grinding wheel. NOTE : Be careful not to cut into the metal of the frame when you do ____ the grinding. (2) Loosen and remove the stud. Discard it. (3) Complete the removal of the remaining tack weld material. To do this, use a small, manual grind tool. (4) Blow the areas adjacent to the hole for the stud with shop air.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 802 Nov 01/08
C F M 56-5B
Replacement of the Defective Studs on the Turbine Frame Figure 801/TASK 72-56-00-991-310 R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Nov 01/08
C F M 56-5B (5) Apply a thin layer of graphite grease (Material No. CP2101) on the stud threads which go in the hole of the frame. (6) Tighten the new stud by hand on the turbine frame. Then use a torque wrench to complete the installation. TORQUE the stud to between 243.8 and 269.5 lbf.in (2.75 and 3.04 m.daN). (7) Loose the stud and TORQUE it a second time to between 243.8 and 269.5 lbf.in (2.75 and 3.04 m.daN). NOTE : You must do the tack welding of the new stud in shop, at the ____ next maintenance opportunity. (8) Apply a thin layer of graphite grease (Material No. CP2101) on the bolts which secure the thermal insulation blankets. PRE CFM SB 72-247 (9) Re-install the two adjacent thermal insulation blankets with attachment bolts on the rear flange. END of PRE CFM SB 72-247 POST CFM SB 72-247 (10) Re-install the two adjacent thermal insulation blankets with washers and attachment bolts on the rear flange. END of CFM SB 72-247 (11) TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN). 5. Close-up ________ Subtask 72-56-00-410-065 A. Close Access (1) Install the center body (Ref. TASK 78-11-12-400-041). (2) Install the core nozzle (Ref. TASK 78-11-11-400-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 804 Nov 01/08
C F M 56-5B TASK 72-56-00-300-004 Replacement of Defective or Missing Thermal Insulation Blankets (On Radial Struts TRF Only) 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific
Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 72-56-00-991-320
Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Fig. 802
EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 805 Nov 01/09
C F M 56-5B 3. __________ Job Set-up Subtask 72-56-00-010-066 A. Get Access (1) Remove the core nozzle (Ref. TASK 78-11-11-000-041). (2) Remove the center body (Ref. TASK 78-11-12-000-041). 4. Procedure _________ (Ref. Fig. 802/TASK 72-56-00-991-320) Subtask 72-56-00-350-053 A. Replacement of defective or missing thermal insulation blankets (1) Replacement of items (30), (40) (and (50) for POST CFM SB 72-554) PRE CFM SB 72-247 (a) Remove the attachments bolts (10) from the rear flange of the thermal insulation blanket. END OF PRE CFM SB 72-247 POST CFM SB 72-247 (b) Remove the attachment bolts (10) and washers (20) from the rear flange of the thermal insulation blanket. END OF POST CFM SB 72-247 (c) Remove the blanket by lifting the rear flange, then pull and twist it. NOTE : Be careful to not damage the seal cover when you disengage ____ the thermal insulation blanket. (d) Install the new thermal insulation blanket items (30),(40) (and 50 for POST CFM SB 72-554). NOTE : Be careful to not damage the seal cover when you engage ____ the front edge of the thermal insulation blanket.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 806 Nov 01/08
C F M 56-5B (e) Apply a thin layer of graphite grease (Material No. CP2101) on the bolts. PRE CFM SB 72-247 (f) Install the two bolts (10) securing the blanket. END OF PRE CFM SB 72-247 POST CFM SB 72-247 (g) Install the two washers (20) and two bolts (10) securing the blanket. END OF POST CFM SB 72-247 (h) TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN). (2) Removal of item (50) (for PRE CFM SB 72-554) PRE CFM SB 72-247 (a) Remove the attachments bolts (10) from the rear flange of the thermal insulation blanket. END OF PRE CFM SB 72-247 POST CFM SB 72-247 (b) Remove the attachment bolts (10) and washers (20) from the rear flange of the thermal insulation blanket. END OF POST CFM SB 72-247 (c) Stretch the old thermal insulation blankets CAUTION : THE REMOVAL OF THE OLD THERMAL INSULATION BLANKETS _______ BETWEEN STRUTS 2-3, 7-8, 10-11 AND 15-16 MUST BE PERFORMED CAREFULLY DUE TO THEIR SPECIFIC SHAPE. TAKE CARE TO PREVENT DAMAGE TO ADJACENT PARTS WHEN YOU PUT THE BLANKETS OUT OF SHAPE TO PERMIT THEIR REMOVAL. 1 _
Stretch the old thermal insulation blankets out of shape as necessary to permit their disengagement from the heat shield and their removal from the LPT frame.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 807 Nov 01/08
C F M 56-5B
Replacement of the Thermal Insulation Blankets Figure 802/TASK 72-56-00-991-320- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 808 Nov 01/08
C F M 56-5B
Replacement of the Thermal Insulation Blankets Figure 802/TASK 72-56-00-991-320- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 809 Nov 01/08
C F M 56-5B (d) Install the new thermal insulation blanket item (50). NOTE : Be careful to not damage the seal cover when you engage ____ the front edge of the thermal insulation blanket. (e) Apply a thin layer of graphite grease (Material No. CP2101) on the bolts. PRE CFM SB 72-247 (f) Install the two bolts (10) securing the blanket. END OF PRE CFM SB 72-247 POST CFM SB 72-247 (g) Install the two washers (20) and two bolts (10) securing the blanket. END OF POST CFM SB 72-247 (h) TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN). 5. Close-up ________ Subtask 72-56-00-410-066 A. Close Access (1) Install the center body (Ref. TASK 78-11-12-400-041). (2) Install the core nozzle (Ref. TASK 78-11-11-400-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 810 Nov 01/08
C F M 56-5B TASK 72-56-00-300-006 Replacement of the Oil Supply Tube Assembly 1. __________________ Reason for the Job This procedure is done to replace the oil supply tube assembly. This procedure is applicable only for engines Post SB CFM 72-0403 or Post SB CFM 72-0499. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific
warning notice Torque Wrench : range 0.00 to 1.20 (0.00 to Torque Wrench : range 0.20 to 3.60 (2.00 to 1 FIXTURE INSTALLATION AND REMOVAL
No specific 856A2677
m.daN 9.00 lbf.ft) m.daN 26.00 lbf.ft)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2104
Material No.
CP2442
Material No.
CP8001
Material No.
CP8002
Material No. 19-003
* molykote G rapid plus (solid lubricant) (Ref. 70-30-00) * engine oil (Ref. 70-30-00) (Ref. 70-30-00) USA AMS 5687 Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Ref. 70-30-00) USA AMS 5689 Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Ref. 70-30-00) USA AMS 3819 LINT-FREE COTTON CLOTH (Ref. 20-31-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Nov 01/08
C F M 56-5B C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------70 70 80 80 90 90
oil supply tube oil supply tube coupling nut coupling nut retaining ring retaining ring
72-56-00 72-56-00 72-56-00 72-56-00 72-56-00 72-56-00
02A-190 02B-190 02A-180 02B-180 02A-170 02B-170
D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 72-56-00-000-001 72-56-00-400-001 78-11-11-000-041 78-11-11-400-041 78-11-12-000-041 78-11-12-400-041 72-56-00-991-311
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Removal of the Flame Arrestor and Flange Assembly Installation of the Flame Arrestor and Flange Assembly Removal of the Core Nozzle Assembly Installation of the Core Nozzle Assembly Removal of the Centerbody Installation of the Centerbody Fig. 803
3. __________ Job Set-up Subtask 72-56-00-941-062 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1 (2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1 (2) pushbutton switch is off.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B (b) Put a warning notice to tell persons not to energize the FADEC 1 (2). Subtask 72-56-00-010-068 B. Get Access (1) Remove the core nozzle assembly (Ref. TASK 78-11-11-000-041). (2) Remove the centerbody (Ref. TASK 78-11-12-000-041). (3) Remove the flame arrestor and the flange assembly (Ref. TASK 72-5600-000-001). NOTE : Discard the gasket seal installed between the flame arrestor ____ and the flange assembly. 4. Procedure _________ Subtask 72-56-00-300-051 A. Replacement of the Oil Supply Tube Assembly (Ref. Fig. 803/TASK 72-56-00-991-311) (1) Disconnect the oil supply tube assembly (10) from the rear sump oil supply tube (60) as follows: WARNING : ENGINE OIL IS TOXIC. USE PERSONAL PROTECTION EQUIPMENT. USE _______ IN A WELL-VENTILATED AREA. (a) Put a container under the engine, before you disconnect the coupling nut (20) of the oil supply tube assembly (10), to collect the drained oil. CAUTION : USE TWO WRENCHES TO LOOSEN OR TIGHTEN THE TUBE COUPLING _______ NUTS. ONE WRENCH TO HOLD THE UNION AND ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE HARDWARE. (b) Loosen the coupling nut (20), which attaches the rear sump oil-supply tube (60) to the oil supply tube assembly (10). (c) Loosen the bolt and nut that attach the rear sump oil-supply tube (60) through the shield and clamp from the turbine rear-frame outer case.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/08
C F M 56-5B
Removal/Installation of the Oil Supply Tube Assembly Figure 803/TASK 72-56-00-991-311 R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Nov 01/08
C F M 56-5B (d) Disconnect the coupling nut (20) of the oil supply tube assembly (10) from the rear sump oil tube (60) at the turbine rear-frame outer case. (2) Remove the oil supply tube assembly as follows: (a) Cut and remove the safetywires from the coupling nuts. CAUTION : USE TWO WRENCHES TO LOOSEN OR TIGHTEN THE TUBE COUPLING _______ NUTS. ONE WRENCH TO HOLD THE UNION AND ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE HARDWARE. (b) Loosen the coupling nut between the damping oil tube (110) and the oil tube (50). (c) Loosen the coupling nut (80) between the oil supply tube assembly (10) and the oil tube (50). (d) Loosen the coupling nut between the oil tube (50) and the nipple (120) on the oil inlet cover (100). (e) Disconnect and remove the oil tube (50). (f) Pull and remove the retaining ring (90), which attaches the coupling nut (80) on the oil supply tube (70). Use the tool set FIXTURE INSTALLATION AND REMOVAL to remove the retaining ring. (g) Remove the coupling nut (80) from the oil supply tube assembly (10). (h) Pull the oil supply tube (70) down through the No. 10 strut at 7 oclock position to fully disengage its guide bushing from the boss. (i) Remove the oil supply tube (70) from the turbine rear-frame outer case. (3) Clean the turbine rear-frame inner hub area; use a lint-free cotton cloth MISCELLANEOUS (Material No. 19-003). NOTE : Make sure that you clean the turbine rear-frame inner hub area ____ before installation of the oil supply tube.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B (4) Installation of the oil supply tube assembly (10) as follows: (a) Apply a thin layer of molykote G rapid plus (solid lubricant) (Material No. CP2104) with a spray gun on the guide bushing of the oil supply tube (70). (b) Insert the oil supply tube (70) into the No. 10 strut of the turbine rear frame at the 7 oclock position. (c) Engage the guide bushing of the oil supply tube (70) into the boss. (d) Put the coupling nut (80) in position on the oil supply tube (70). Make sure you align the groove on the tube and the coupling nut. CAUTION : BE CAREFUL TO HOLD THE COUPLING NUT IN PLACE WITH A _______ LOCK WRENCH WHEN YOU ENGAGE THE RETAINING RING WITH COMBINATION PLIERS. (e) Insert the retaining ring (90) in the coupling nut (80). NOTE : Use the tool set FIXTURE INSTALLATION AND REMOVAL to ____ install the retaining ring. NOTE : Make sure that the retaining ring is fully inserted into ____ the coupling nut when its outer diameter base is in contact with the nut. NOTE : Make sure that the coupling nut rotates freely after the ____ installation of the retaining ring. (5) Install the oil tube (50) on the damping oil tube (110) as follows: WARNING : ENGINE OIL IS TOXIC. USE PERSONAL PROTECTION EQUIPMENT. USE _______ IN A WELL-VENTILATED AREA. CAUTION : USE TWO WRENCHES TO LOOSEN OR TIGHTEN THE TUBE COUPLING _______ NUTS. ONE WRENCH TO HOLD THE UNION AND ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE HARDWARE. (a) Apply a thin layer of engine oil (Ref. 70-30-00) (Material No. CP2442) on the nipple (120) of the oil inlet cover (100) and on the threads of the oil tube (50).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B (b) Put the oil tube (50) with its ends positioned on the nipple (120) of the oil inlet cover (100) and oil supply tube assembly (10). (c) Connect the oil tube (50) to the nipple (120) and to the oil supply tube assembly (10). Tighten the coupling nuts by hand. WARNING : ENGINE OIL IS TOXIC. USE PERSONAL PROTECTION EQUIPMENT. _______ USE IN A WELL-VENTILATED AREA. (d) Apply a thin layer of engine oil (Ref. 70-30-00) (Material No. CP2442) on the threads of the oil tube (50). (e) Put a damping oil tube (110) in position. (f) Connect the damping oil tube (110) to the oil tube (50). Tighten the coupling nut by hand. NOTE : Make sure that the oil tubes are installed without strain. ____ (g) TORQUE the coupling nut of the damping oil tube (110) to between 1.05 and 1.15 m.daN (92.92 and 101.76 lbf.in). (h) Safety the coupling nut with Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Material No. CP8001) or Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Material No. CP8002). (i) TORQUE the coupling nuts of the oil tube (50) to between 3.05 and 3.35 m.daN (22.49 and 24.70 lbf.ft). (j) Safety the coupling nut with Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Material No. CP8001) or Safetywire 0.032 in. (0.8mm) DIA (Ref.70-30-00) (Material No. CP8002). (6) Connect the oil supply tube assembly (10) to the rear sump oil-supply tube (60) as follows: (a) Install the rear sump oil-supply tube (60) to the oil supply tube assembly (10) with the coupling nut (20). Tighten the coupling nut by hand. NOTE : Make sure that the rear sump oil supply tube (60) is ____ unstrained. (b) TORQUE the coupling nut (20) to between 3.05 and 3.35 m.daN (22.49 and 24.70 lbf.ft).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
C F M 56-5B (c) TORQUE the nut with the bolt that attaches the rear sump oil-supply tube (60) to the turbine rear-frame outer case through the shield and clamp to between 0.50 and 0.55 m.daN (44.24 and 48.67 lbf.in). NOTE : The nut is installed on the turbine frame side. ____ 5. Close-up ________ Subtask 72-56-00-410-069 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the flange assembly and the flame arrestor (Ref. TASK 72-5600-400-001). (3) Install the centerbody (Ref. TASK 78-11-12-400-041). (4) Install the core nozzle assembly (Ref. TASK 78-11-11-400-041). (5) Do a check of the oil level (Ref. TASK 12-13-79-610-002). Subtask 72-56-00-410-070 B. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-56-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B ACCESSORY DRIVE SECTION - DESCRIPTION AND OPERATION ___________________________________________________ 1. _______ General (Ref. Fig. 001) Power for both engine and aircraft accessories is extracted thru a system of gearboxes and shafts. The inlet gearbox, which is located in the fan frame hub, takes power from the HP compressor front shaft and transmits this power to the transfer gearbox, installed under the fan frame through the radial drive shaft. A horizontal drive shaft then transmits the power to accessory gearbox. The accessory gearbox drives the following equipment : - The Integrated Drive Generator (IDG) (electrical power generation) at 0.5947 N2. - Hydraulic pump (hydraulic power generation) at 0.256 N2. - The Hydromechanical Unit (HMU) and the fuel pump at 0.423 N2. - The lubrication unit at 0.423 N2. - The ECU control alternator
R EFF : 001-049, 051-099, 101-149, 151-199, 72-60-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Accessory Drive System Figure 001 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-60-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Accessory Drive System Figure 001 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-60-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B INLET GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION __________________________________________________ 1. _______ General (Ref. Fig. 001) The inlet gearbox (IGB) assembly is located in the fan frame sump and is bolted to the forward side of the fan frame aft flange. The gearbox contains a horizontal bevel gear, a radial bevel gear, a core engine thrust (No. 3 ball) bearing, and a core engine roller bearing. The gearbox assembly serves as the mechanical coupling between the HPC rotor and the TGB. 2. Description ___________ A. Horizontal Bevel Gear The horizontal bevel gear, which has 47 teeth, is splined to the compressor rotor front shaft and secured to it by the No. 3 ball bearing locking nut. The horizontal bevel gear mates to the radial bevel gear to provide rotational torque to the transfer gearbox (TGB) assembly. B. Radial Bevel Gear The radial bevel gear, which has 35 teeth, is mounted on 2 roller bearings and one ball bearing (there are no duplex bearings). The gear is internally splined to accept the radial drive shaft which is removable from the exterior of the engine to allow individual replacement of the IGB and TGB. C. Thrust Bearing (No. 3 Ball) The No. 3 ball bearing is installed during IGB assembly between the gearbox housing and the horizontal bevel gear. It provides axial positioning of the forward end of the high pressure compressor (HPC) rotor. D. Roller Bearing (No. 3 Roller) The No. 3 roller bearing is installed during IGB assembly between the gearbox housing and the horizontal bevel gear. It positions the core engine rotor radially.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-61-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Inlet Gearbox Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-61-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B TRANSFER GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION _____________________________________________________ 1. _______ General (Ref. Fig. 001) The transfer gearbox (TGB) provides power transmission between the inlet gearbox (IGB) and the accessory gearbox (AGB). It consists of the following major assemblies: - Radial drive shaft assembly. - TGB assembly. 2. ___________ Description (Ref. Fig. 002, 003) A. Radial Drive Shaft Assembly The radial drive shaft (RDS) assembly is installed inside the fan frame No. 7 strut at the 6 oclock position. It consists of the radial drive shaft and the shaft midlength bearing. (1) The radial drive shaft is made of steel alloy. It is hollow and measures approximately 29.52 in. (0.75 m). Both ends are externally splined and connect the IGB bevel gear and the TGB input bevel gear. A foolproof slot is machined on the shaft to avoid inversion of RDS during installation. (2) The shaft midlength bearing provides proper centering of radial drive shaft in its housing. Its inner race is mounted half-way up on the RDS and the outer race is part of the radial drive shaft housing. B. TGB Assembly The TGB assembly is installed under the fan frame at the 6 oclock position. It consists of the housing and a set of 2 bevel gears. (1) The TGB housing is made of two aluminum alloy castings bolted together. It is secured to the fan frame through a single clevis/link rod mounting arrangement located at the upper part of the TGB housing front end. The upper part of the TGB housing contains an adapter which corresponds to an adapter mounted on the fan frame. The TGB housing accommodates 3 oil nozzles for lubrication of the bevel gears and the bearings. The casting of the TGB housing is double-walled, to provide better oil scavenge. (2) The upper part of the TGB houses the input bevel gear, its bearing housing, ball bearing, and roller bearing. The bore of the bevel gear is splined at its upper end and connects with the radial drive shaft. An oil distributor installed inside the bevel gear and secured by a Spirolock system, ensures oil distribution and axial retention of the radial drive shaft.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Transfer Gearbox Assembly Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Transfer Gearbox Assembly Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
Transfer Gearbox Assembly Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B (3) The horizontal part of the TGB houses the horizontal bevel gear, its bearing housing, ball bearing and roller bearing. The bore of this bevel gear is splined at its forward end and connects with the horizontal drive shaft. An oil distributor installed inside the bevel gear and secured by a Spirolock system, ensures oil distribution to the bearing. The horizontal drive shaft housing is made of aluminum alloy, and the bearing housing is a cast part. It protects the horizontal drive shaft and the bevel gear assembly, and ensures connection with the AGB. It is bolted to both TGB and AGB housings. The suspension clevis is a cast part and is integral with the horizontal drive shaft housing.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 5 Nov 01/08
C F M 56-5B TRANSFER GEARBOX ASSEMBLY - REMOVAL/INSTALLATION ________________________________________________ TASK 72-62-00-000-002 Removal of the Transfer Gearbox Module 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific No specific No specific No specific 856A2537 856A2719 856A2727 856A2805
1 1 1 1
blanking plug blanking plugs and covers container hydraulic hoist platform slide hammer assy CG240 soft nose pliers warning notice PROTECTOR-MOUNTING PIN FIXTURE,SUPPORT-TGB R/I PULLER RADIAL DRIVE SHAFT TURNBUCKLE-TGB R/I
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-63-00-400-002 72-63-00-860-001 78-30-00-481-041 78-36-00-010-040 80-11-10-000-002 72-62-00-991-300 72-62-00-991-301 72-62-00-991-302
Opening of the Fan Cowl Doors Installation of the Handcranking Drive Cover Disengagement/Engagement of the Horizontal Drive Shaft Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Removal of the Pneumatic Starter Fig. 401 Fig. 402 Fig. 403
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-62-00-991-303 72-62-00-991-304 72-62-00-991-305 72-62-00-991-306 72-62-00-991-307 72-62-00-991-308
Fig. Fig. Fig. Fig. Fig. Fig.
404 405 406 407 408 409
3. __________ Job Set-up Subtask 72-62-00-941-053 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-62-00-010-056 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-62-00-040-054 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Nov 01/08
C F M 56-5B Subtask 72-62-00-010-058 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR 4. Procedure _________ (Ref. Fig. 401/TASK 72-62-00-991-300, 402/TASK 72-62-00-991-301, 403/TASK 72-62-00-991-302, 404/TASK 72-62-00-991-303, 405/TASK 72-62-00-991-304, 406/TASK 72-62-00-991-305, 407/TASK 72-62-00-991-306, 408/TASK 72-62-00-991307, 409/TASK 72-62-00-991-308) Subtask 72-62-00-020-053 A. Remove TGB external parts as follows: (1) Install a suitable container under the TGB to catch residual fluid draining from tubes and control. (2) Drain the TGB as follows: (a) Cut and remove the lockwire which safeties the drain plug (20) to the TGB. (b) Remove the drain plug (20) and let the oil drain. (c) Install the drain plug (20). Tighten by hand. (3) Loosen and remove the 4 bolts (110) securing the TGB scavenge tube (170) to the TGB housing (120) LH side. (4) Remove and retain gasket (90) located between TGB housing (120) and TGB scavenge tube flange. (5) Loosen and remove the 4 bolts (230) which secure the oil tank vent tube (220) assy to the TGB housing (120). (6) Remove and retain gasket (240) located between the oil tank vent tube (220) flange and the TGB housing (120).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 403 Nov 01/08
C F M 56-5B
Drain Plug Removal Figure 401/TASK 72-62-00-991-300 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 404 Nov 01/08
C F M 56-5B
Disconnection of Tubes on LH Side of TGB Figure 402/TASK 72-62-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 405 Nov 01/08
C F M 56-5B
Disconnection of Brackets on RH and Lower Side of TGB Figure 403/TASK 72-62-00-991-302- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 406 Nov 01/08
C F M 56-5B
Disconnection of Brackets on RH and Lower Side of TGB Figure 403/TASK 72-62-00-991-302- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 407 Nov 01/08
C F M 56-5B
Installation of the TGB Turnbuckle Figure 404/TASK 72-62-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 408 Nov 01/08
C F M 56-5B
Removal of the TGB Figure 405/TASK 72-62-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 409 Nov 01/08
C F M 56-5B
Removal of the Mounting Pin Figure 406/TASK 72-62-00-991-305 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 410 Nov 01/08
C F M 56-5B
Extraction of Mounting Pin Figure 407/TASK 72-62-00-991-306 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 411 Nov 01/08
C F M 56-5B
Extraction of Radial Drive Shaft Figure 408/TASK 72-62-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 412 Nov 01/08
C F M 56-5B
Installation of Blanking Items on TGB Housing Ports Figure 409/TASK 72-62-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 413 Nov 01/08
C F M 56-5B (7) Loosen union nut. CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (a) Loosen union nut (100) which attaches the securing TGB oil supply tube (180) to TGB housing (120). (8) Remove the two bolts (290) securing RH rear bracket (270) and the bleed bias bracket (280) to the right side of the TGB housing (120). (9) Remove the two bolts (360) securing bracket (60) on the rear face of the TGB housing (120). (10) Remove the two bolts (40 and 50) securing upper LH bracket (30) to the LH and rear side of TGB housing . (11) Remove the bolt (70) securing lower LH bracket (80) on the left side of the TGB housing (120). (12) Remove the bolt (300) securing forward bracket (260) on the right side of the TGB housing (120). Subtask 72-62-00-480-052 B. Installation of support equipment. (1) Install TURNBUCKLE-TGB R/I (856A2805G01) as follows: NOTE : To prevent AGB rotation during the TGB removal it is necessary ____ to install the TGB turnbuckle. (a) Remove the pneumatic starter (Ref. TASK 80-11-10-000-002). (b) Remove bolts and nuts from holes No. 46 and 47 on flange F to free brackets at this place. (c) Install the TGB turnbuckle yoke on the flange F of the fan inlet case. Attach the yoke at holes No. 47 and 48, with the 2 lockpins supplied. (d) Adjust the height of tool, using the coupling screw to obtain the exact position of the baseplate on the AGB rear flange.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 414 Nov 01/08
C F M 56-5B (e) Attach the TGB turnbuckle to the AGB housing with screws and washers supplied. (f) Handtighten the coupling screw in order to lock the AGB relative to the fan frame. (2) Install FIXTURE,SUPPORT-TGB R/I (856A2719G02) as follows: (a) Install TGB removal/installation support on an hydraulic hoist platform. (b) Position hydraulic hoist platform under TGB module. (c) Remove the 2 bolts (350), nuts (330) and washers (340) securing TGB housing to the horizontal drive shaft housing at the 4:30 and 7:30 oclock positions. (d) Actuate hydraulic hoist platform and adjust rear yoke of TGB support with TGB rear mount until the lockpin can be inserted. (e) Adjust the 2 front plates of tool and engage the 2 lockpins in the 4:30 and 7:30 oclock position holes of the TGB forward flange. (f) Remove the bolts. CAUTION : DO NOT REMOVE THE 3 BOLTS, NUTS AND WASHERS INSTALLED _______ IN THE HOLES FITTED WITH FLANGED BUSHINGS. 1 _
Remove the 7 bolts (190) nuts (210) and 4 washers (200) securing TGB housing and the LH support bracket to the horizontal drive shaft housing.
Subtask 72-62-00-020-052 C. Removal of the TGB from the Fan Frame. (1) Install PROTECTOR-MOUNTING PIN (856A2537G01) on the external threads of the mounting pin (400). (2) Install impact puller into the tapped head of mounting pin (400). (3) Remove mounting pin (400). Remove the impact puller from the mounting pin. (4) Separate TGB from fan frame by slowly lowering TGB and fixture assy using a hydraulic hoist platform.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 415 Nov 01/08
C F M 56-5B (5) Keep gasket (410) located between AGB and TGB. (6) Remove and discard the O-ring (420) on the horizontal drive shaft. (7) Remove the O-ring (430) on the oil distributor in the bevel gear. NOTE : Make sure that O-ring (430) is serviceable and O-ring outer ____ diameter is correct. If it is not serviceable, remove and discard it with soft nose pliers. (8) Remove and discard the seal ring (295). (Ref. Fig. 403/TASK 72-62-00-991-302) (9) Two different cases may appear after lowering the TGB: (a) If the radial drive shaft (440) comes with the TGB, remove the shaft from TGB and perform step (12). (b) If the radial drive shaft (440) remains into the fan frame proceed as follows: 1 _
Install PULLER RADIAL DRIVE SHAFT (856A2727G01) to the radial drive shaft.
2 _
Attach slide hammer assy CG240 to the puller.
3 _
Extract radial drive shaft from fan frame.
(10) Remove and discard the O-ring (450) located in groove at lower side of shaft. (11) Store the radial drive shaft into its storage tube assy. Subtask 72-62-00-420-056 D. Installation of blanking plugs and covers and handcranking assy. (1) Installation of blanking plugs and covers on the TGB. (a) Install cover (510) onto forward face of TGB housing. (b) Install cover (470) onto upper face of TGB housing. (c) Install plug (500) onto port of TGB vent tube of TGB housing. (d) Install plug (490) onto scavenge tube port of TGB housing.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 416 Nov 01/08
C F M 56-5B (e) Install cap (480) onto TGB oil supply tube nipple. (f) Install cover onto AGB horizontal drive shaft housing aft end. (g) Install blanking plug on open ports of all tubes. (2) Installation of the Handcranking assy: NOTE : You can ignore this step if the TGB is immediately replaced. ____ (a) Engage the horizontal drive shaft (Ref. TASK 72-63-00-860-001). (b) Install the handcranking drive cover (Ref. TASK 72-63-00-400002). NOTE : Do not replace the O-rings of the handcranking drive ____ cover. New O-rings will be installed after reinstallation of the TGB. Subtask 72-62-00-080-052 E. Removal of the TGB from the Tool. (1) Hold the TGB and remove the rear lockpin of the FIXTURE,SUPPORT-TGB R/I (856A2719G02). (2) Disengage the TGB from the support and place in a storage container.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 417 Nov 01/08
C F M 56-5B TASK 72-62-00-400-002 Installation of the Transfer Gearbox Module 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
No specific
hydraulic hoist platform soft nose pliers warning notice Torque Wrench : range 0.00 to 50.00 lbf.in (0.00 to 0.56 m.daN) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) PROTECTOR-MOUNTING PIN FIXTURE,SUPPORT-TGB R/I PULLER RADIAL DRIVE SHAFT TURNBUCKLE-TGB R/I
No specific 856A2537 856A2719 856A2727 856A2805
1 1 1 1
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2442
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00)
EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 418 Feb 01/10
C F M 56-5B C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------10 10 370 420 420 430 430 450
O-ring O-ring cotter pin O-ring O-ring O-ring O-ring O-ring
72-62-00 72-62-00 72-00-00 72-63-00 72-63-00 72-62-00 72-62-00 72-62-00
05 05 07 04 04 05 05 05
-040 -040A -070 -010 -010A -030 -030A -020
D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 71-00-00-710-006 71-00-00-710-025 71-13-00-010-040 71-13-00-410-040 72-63-00-000-002 72-63-00-400-002 72-63-00-860-001 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 79-00-00-210-003 80-11-10-400-002 72-62-00-991-300 72-62-00-991-301 72-62-00-991-302 72-62-00-991-303 72-62-00-991-304 72-62-00-991-305 72-62-00-991-306
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Minimum Idle Check Accel Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Disengagement/Engagement of the Horizontal Drive Shaft Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Visual Inspection of the Oil System Installation of the Pneumatic Starter Fig. 401 Fig. 402 Fig. 403 Fig. 404 Fig. 405 Fig. 406 Fig. 407
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 419 Nov 01/08
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-62-00-991-307 72-62-00-991-308
Fig. 408 Fig. 409
3. __________ Job Set-up Subtask 72-62-00-860-051 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). Subtask 72-62-00-010-059 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-62-00-040-055 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 420 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 401/TASK 72-62-00-991-300, 402/TASK 72-62-00-991-301, 403/TASK 72-62-00-991-302, 404/TASK 72-62-00-991-303, 405/TASK 72-62-00-991-304, 406/TASK 72-62-00-991-305, 407/TASK 72-62-00-991-306, 408/TASK 72-62-00-991307, 409/TASK 72-62-00-991-308) NOTE : In the procedure which follows, the AGB is supposed to be installed ____ on the engine and held in position by the TURNBUCKLE-TGB REMOVAL/INSTALLATION (856A2805G01). Subtask 72-62-00-480-053 A. Preparation for Installation: (1) Install the TGB on the FIXTURE,SUPPORT-TGB R/I (856A2719G02) as follows: (a) Adjust the 2 front plates of the tool to engage the 2 lockpins in the forward flange holes at 4:30 and 7:30 oclock positions. Tighten the 2 knurled knobs. (b) Attach the support, with the lockpin, to the rear mount flange of the TGB. (2) Install the radial drive shaft (440) in the fan frame and IGB as follows: (a) Remove the radial drive shaft (440) from storage tube assy (460). (b) Installation of new O-ring. CAUTION : NEVER INSTALL O-RINGS ALREADY USED. _______ 1 _
Lightly coat a new O-ring (450) with engine oil (Material No. CP2442) and install it in the groove of the shaft (440).
(c) Lightly coat the shaft splines (both ends) with engine oil (Material No. CP2442). (d) Install PULLER RADIAL DRIVE SHAFT (856A2727G01) in the lower end of the shaft. (e) Slide shaft in the fan frame into strut and IGB, engaging splines of shaft in splines of IGB. (f) Ensure shaft remains in place. Remove puller.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 421 Nov 01/08
C F M 56-5B (3) Inspect gaskets (90), (240) and (410) before installation to make sure that they are serviceable. If necessary, replace gaskets. Subtask 72-62-00-420-055 B. Installation of the TGB on fan frame: (1) If necessary, remove the handcranking cover (Ref. TASK 72-63-00-000002) and disengage the horizontal drive shaft (Ref. TASK 72-63-00860-001). (2) Remove covers, plugs and cap from the TGB housing. (3) Remove cover from AGB horizontal drive shaft housing. (4) Lightly coat the horizontal drive shaft splines and the gasket (410) to be installed between AGB and TGB, with engine oil (Material No. CP2442). (5) Lubricate a new seal ring (295) with engine oil (Material No. CP2442) and install into the seal groove on the TGB adapter. (Ref. Fig. 403/TASK 72-62-00-991-302) (6) Lubricate a new O-ring (420) with engine oil (Material No. CP2442). Install the O-ring (420) on the horizontal drive shaft. (7) Install the O-ring (430) in the groove on the oil distributor in the bevel gear: (Ref. Fig. 406/TASK 72-62-00-991-305) NOTE : If necessary, lubricate the new O-ring (430) with engine oil ____ (Material No. CP2442). (a) Engage the O-ring (430) by the hole of the oil distributor in the bevel gear with soft nose pliers. (b) Put the O-ring (430) in the groove of the oil distributor in the bevel gear with soft nose pliers. NOTE : Make sure that O-ring (430) is correctly installed in the ____ groove of the oil distributor in the bevel gear. (8) Raise and position TGB at desired level under fan frame using hydraulic hoist platform and taking care not to interfere with adjacent accessories or tubes. Adjust jack details of fixture to complete positioning.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 422 Nov 01/08
C F M 56-5B (9) Insert the gasket (410) and hold it in place between TGB and AGB mating flanges. (10) Lightly coat threads of 3 bolts (160) with graphite grease (Material No. CP2101) and install at 2:30, 6:30, and 10:30 oclock positions (flanged bushings positions) with washers (140) and nuts (130) to secure AGB and TGB handtight. (11) Install TGB mounting pin (400) as follows: (a) Lightly coat threads of pin with graphite grease (Material No. CP2101) and install PROTECTOR-MOUNTING PIN (856A2537G01) on to threaded end of pin. (b) Position TGB mount link, located on fan frame, in TGB clevis mount, align holes and engage pin (400). (c) Remove protector, install washer (390) and nut (380). (d) TORQUE to between 710 and 800 lbf.in (8.02 and 9.04 m.daN). (e) Safety nut with a new cotter pin (370). (12) Loosen the 2 lock pins of FIXTURE,SUPPORT-TGB R/I (856A2719G02) from the 4:30 and 7:30 oclock position holes in the TGB forward flange. Loosen handknobs to lower the 2 front plates of the tool. (13) Lightly coat threads of 2 bolts (350) with graphite grease (Material No. CP2101) and install at 4:30 and 7:30 oclock positions with washers (340) and nuts (330) handtight. (14) Install TGB brackets as follows: (a) Loosen bolts (160), nuts (130) and washers (140) from 2:30 and 6:30 locations. (b) Lightly coat threads of a bolt (190) with graphite grease (Material No. CP2101). Secure lower bracket (150) at the bottom and to the front face of TGB/AGB interface with bolts (160) and (190), washers (140) and (200) and nuts (130) and (210). Tighten by hand. (c) Lightly coat threads of 2 bolts (190) with graphite grease (Material No. CP2101). Secure the support bracket at the left side and onto the rear face of TGB/AGB interface with bolts (190), washers (200) and nuts (210).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 423 Nov 01/08
C F M 56-5B (d) Lightly coat threads of bolt (300) with graphite grease (Material No. CP2101). Secure forward bracket (260) on the TGB RH upper corner. TORQUE to between 100 and 110 lbf.in (1.13 and 1.24 m.daN) (e) Lightly coat threads of 2 bolts (190) with graphite grease (Material No. CP2101). Attach brackets (250) and (260) on the RH side of the TGB/AGB interface with bolts (190) and (160), washers (200) and nuts (130) and (210). (15) Install the 3 remaining bolts (190), washers (200) and nuts (210). (16) TORQUE all bolts of TGB/AGB interface to between 250 and 280 lbf.in (2.82 and 3.16 m.daN) Subtask 72-62-00-080-053 C. Removal of support equipment. (1) Removal of the FIXTURE,SUPPORT-TGB R/I (856A2719G02) (a) Remove the pin which attaches the fixture to the TGB rear mount. (b) Lower the fixture with the hydraulic hoist platform, and remove it. (2) Removal of the TURNBUCKLE-TGB R/I (856A2805G01) (a) Loosen the coupling screw. (b) Remove the screws and washers which attach the baseplate of the tool to the rear face of the AGB. (c) Remove the pins which attach the turnbuckle yoke to the flange F of the fan case and remove the turnbuckle. (d) Reinstall bolts and nuts removed from the flange F, bolt heads forward. TORQUE nuts to between 98 and 110 lbf.in (1.10 and 1.24 m.daN).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 424 Nov 01/08
C F M 56-5B Subtask 72-62-00-420-057 D. Installation of the transfer gearbox module. (1) Installation of the handcranking drive assembly: (a) Push the handcranking drive shaft and install the handcranking drive (Ref. TASK 72-63-00-860-001). (b) Install the handcranking drive cover (Ref. TASK 72-63-00-400002). (2) Installation of TGB external parts (a) Installation of brackets 1 _
Lightly coat the 2 bolts (360) with graphite grease (Material No. CP2101) and secure bracket (60) on the rear face of TGB housing (120). TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN).
2 _
Lightly coat 2 bolts (290) with graphite grease (Material No. CP2101). Position the bleed bias bracket (280) on the RH rear bracket (270). Attach the brackets to the TGB housing (120) with bolts (290). TORQUE the bolts to between 100 and 110 lbf.in (1.13 and 1.24 m.daN).
3 _
Lightly coat a bolt (70) with graphite grease (Material No. CP2101) and secure lower bracket (80) handtight on the LH side of TGB housing.
4 _
Lightly coat 2 bolts (40) and (50) with graphite grease (Material No. CP2101). Secure upper bracket (30) on the rear face of TGB housing. Secure brackets together on the LH side of TGB housing.
5 _
TORQUE the 3 bolts (40), (50) and (70) to between 100 and 110 lbf.in (1.13 and 1.24 m.daN).
(b) Installation of tubes on TGB housing (120). CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING _______ NUTS: - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 425 Nov 01/08
C F M 56-5B 1 _
2 _
3 _
4 _
Connect TGB oil supply tube (180) as follows: a _
Lightly coat threads of nipple with engine oil (Material No. CP2442).
b _
Connect oil supply tube to nipple with union nut (100). Make sure tube is unstrained. TORQUE nut to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
Connect oil tank vent tube (220) assy as follows: a _
Lightly coat gasket (240) with engine oil (Material No. CP2442).
b _
Lightly coat threads of the 4 bolts (230) with graphite grease (Material No. CP2101).
c _
Install gasket (240) and attach the oil vent tube (220) flange on TGB housing using the 4 bolts (230). TORQUE to between 45 and 50 lbf.in (0.50 and 0.56 m.daN).
Connect the TGB scavenge tube (170) as follows: a _
Lightly coat gasket (90) with engine oil (Material No. CP2442).
b _
Lightly coat threads of the 4 bolts (110) with graphite grease (Material No. CP2101).
c _
Install gasket (90) and secure the scavenge tube (170) flange on TGB housing (120) using the 4 bolts (110) TORQUE to between 45 and 50 lbf.in (0.50 and 0.56 m.daN).
Check for oil scavenge plug lockwire. Proceed as follows if lockwire is not present. a _
Loosen scavenge plug from TGB housing.
b _
Remove O-ring (10) and discard.
c _
Lightly coat new O-ring (10) and threads of scavenge plug (20) with engine oil (Material No. CP2442). Install new Oring (10) on scavenge plug (20).
d _
Tighten scavenge plug (20) on TGB housing. TORQUE to between 180 and 200 lbf.in (2.03 and 2.26 m.daN). Safety
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 426 Nov 01/08
C F M 56-5B with a lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) and lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002). (3) Installation of the Pneumatic Starter: (a) Reinstall the pneumatic starter (Ref. TASK 80-11-10-400-002). Subtask 72-62-00-410-057 E. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR Subtask 72-62-00-440-053 F. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-62-00-710-051 G. Engine Checks. (1) Do an idle check (Ref. TASK 71-00-00-710-006) and do a check of the TGB and tubes for leaks (Ref. TASK 79-00-00-210-003). (2) Do a check of the oil level (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-13-79-610-002). (3) Do an acceleration/deceleration check (Ref. TASK 71-00-00-710-025).
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Page 427 Nov 01/08
C F M 56-5B 5. Close-up ________ Subtask 72-62-00-410-058 A. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 428 Nov 01/08
C F M 56-5B TRANSFER GEARBOX ASSEMBLY - INSPECTION/CHECK ____________________________________________ TASK 72-62-00-210-002 Inspection/check of the Transfer Gearbox Assembly 1. __________________ Reason for the Job To make sure that the transfer gearbox (TGB) is serviceable. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 79-00-00-210-003
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Visual Inspection of the Oil System
3. __________ Job Set-up Subtask 72-62-00-941-052 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine.
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Page 601 Nov 01/08
C F M 56-5B (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-62-00-010-055 B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-62-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-62-00-010-057 D. Open the thrust reverser cowl doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 602 Nov 01/08
C F M 56-5B 4. Procedure _________ Subtask 72-62-00-210-052 A. Inspect the TGB ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Housing for : A. Cracks
Not serviceable
B. Nicks, dents and scratches
Any number, 0.035 in. (0.9 mm) deep after removal of high metal
C. Leaks (Ref. TASK 79-00-00-210-003)
No leakage allowed
Tighten fitting to the appropriate torque value and/or replace packing
2. TGB mounts for : A. Cracks
Not serviceable
B. Bushing loose
Not serviceable
C. Broken or missing lockwire
Not serviceable
Replace lockwire
5. Close-up ________ Subtask 72-62-00-410-056 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 603 Nov 01/08
C F M 56-5B Subtask 72-62-00-440-052 B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-62-00-410-059 C. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-62-00 201-249, 251-299, 301-399, 401-499, CES
Page 604 Nov 01/08
C F M 56-5B ACCESSORY GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION ______________________________________________________ 1. _______ General (Ref. Fig. 001) The accessory gearbox (AGB) assembly is mounted under the fan case at 6 oclock. It consists of a gear train that reduces and increases the rotational speed to meet the specific drive requirements of each accessory. Some of the accessories are installed on the AGB through quick attach/detach (QAD) rings. The AGB consists of the following major assemblies : - Horizontal drive shaft. - AGB housing. - Gear train. 2. ___________ Description (Ref. Fig. 001, 002, 003, 004, 005, 006) A. Horizontal Drive Shaft Assembly The horizontal drive shaft assembly provides power transmission between TGB and AGB. It includes the AGB-TGB coupling tube housing and the horizontal drive shaft. (1) The horizontal drive shaft is made of steel alloy. It is splined at both ends and drives the AGB gears through the handcranking driving gear. (2) The horizontal drive shaft is retained in the AGB handcranking driving gear by a castellated nut in the gearshaft. B. AGB Housing (1) The AGB housing is an aluminum alloy casting. It is mounted under the fan case by 2 clevis mounts with shouldered bushings. (2) The AGB housing front face has mounting pads for the following accessories and equipment. (a) Lubrication unit. (Ref. Fig. 002) (b) Hydraulic pump. (Ref. Fig. 002) (c) Handcranking drive. (Ref. Fig. 004)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 1 Nov 01/08
C F M 56-5B
Accessory Gearbox Module Figure 001 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 2 Nov 01/08
C F M 56-5B
Accessory Gearbox Module-Section Figure 002 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 3 Nov 01/08
C F M 56-5B
Accessory Gearbox Module-Section at N2 Speed Sensor Location Figure 003 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 4 Nov 01/08
C F M 56-5B
Accessory Gearbox Module-Section at Control Alternator and Handcranking Drive Locations Figure 004 R EFF : 001-049, 051-099, 101-149, 151-199, Page 5 201-249, 251-299, 301-399, 401-499, Nov 01/08 CES
72-63-00
C F M 56-5B
AGB Module - Detail of the Optional Seal Configurations Figure 005 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 6 Nov 01/08
C F M 56-5B
AGB Module - Detail of Starter Drive Pad Magnetic Seal Configuration Figure 006 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 7 Nov 01/08
C F M 56-5B (d) Integrated drive generator (IDG). (Ref. Fig. 002) (e) Control alternator (FADEC power supply). (Ref. Fig. 004) (3) The AGB housing rear face connects with the horizontal drive shaft housing and has mounting pads for the following equipment : (a) Fuel pump/HMU package. (Ref. Fig. 002) (b) Starter. (Ref. Fig. 002) (c) N2 speed sensor (Ref. Fig. 003) The N2 speed sensor is installed on AGB ; the air gap adjustment is obtained by laminated shims bolted on the AGB housing. Electrical are used by ECU and N2 cockpit indicator. C. Gear Train (Ref. Fig. 002) (1) The gear train is contained within the AGB housing and drives the accessories. (2) Each gearshaft and its bearings and bearing support is a plug-in type assembly. (3) Sealing past four of the AGB drive pads (IDG, hydraulic pump, starter and fuel pump) is provided by two (optional) configurations of carbon-contact seals. There are: - Magnetic-type carbon seal,or - Sealol-type carbon seal. (a) Magnetic-type seal. (Ref. Fig. 005) This seal consists of: a non-magnetic seal housing which houses a magnetized mating ring with a polished face and a retaining ring. a rotating seal, which has a carbon seal held in a rotating ring. This seal configuration (Ref. Fig. 005) (detail K) can be used only for sealing past the drive pads which follow: - Hydraulic pump
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 8 Nov 01/08
C F M 56-5B - Fuel pump On the starter and IDG drive pads only, a different configuration of magnetic-type seal is used (Ref. Fig. 006) (detail B). This seal differs in that a thrust ring, which also acts as a thermal exchanger, is added between the mating ring and the retaining ring. (b) Sealol-type seal. (Ref. Fig. 005) (detail L) The Sealol seal is made of a carbon packing and a rotating mating ring with a polished face. The rotating mating ring has 4 lugs that engage in 4 corresponding slots in the gearshaft on bearing. A housing containing a spring-loaded carbon seal ensures constant contact between the polished face of the rotating mating ring and the carbon seal element. This seal configuration can be used for sealing past the drive pads wich follow: IDG Hydraulic pump Starter Fuel pump
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 9 Nov 01/08
C F M 56-5B ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES __________________________________________________ TASK 72-63-00-860-001 Disengagement/Engagement of the Horizontal Drive Shaft 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific
slide hammer warning notice Torque Wrench : range 180.00 to 1800.00 lbf.in (2.00 to 20.00 m.daN) 1 PULLER 1 TOOL SET,R/I-DRIVE SHAFTS
856A2632 856A2718
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
* engine oil (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------40
O-ring
72-63-00 04 -060
R
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 201 Feb 01/10
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-63-00-000-002 72-63-00-400-002 72-63-00-991-301 72-63-00-991-302 72-63-00-991-303 72-63-00-991-304
Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Handcranking Drive Cover Installation of the Handcranking Drive Cover Fig. 201 Fig. 202 Fig. 203 Fig. 204
3. __________ Job Set-up Subtask 72-63-00-941-059 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-066 B. Get Access (1) Open the fan cowls doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (2) Remove the handcranking drive cover (Ref. TASK 72-63-00-000-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 202 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 201/TASK 72-63-00-991-301, 202/TASK 72-63-00-991-302, 203/TASK 72-63-00-991-303, 204/TASK 72-63-00-991-304) Subtask 72-63-00-010-067 A. Removal of the Handcranking Drive Nut (1) Install the wrench, part of the TOOL SET,R/I-DRIVE SHAFTS (856A2718G02) as follows: (a) Set the wrench guide on the AGB housing and attach it with the 2 bolts supplied. (b) Turn the wrench axle to engage the forward square end of the axle into the handcranking drive (10). (2) Loosen the nut (20). Use the axle as a countertorque device. (3) Remove the tool and the nut (20) from the AGB housing. Subtask 72-63-00-010-068 B. Removal of the Handcranking Drive (1) Install and tighten the PULLER (856A2632G01) into the tapped hole of the handcranking drive (10). (2) Install and tighten a slide hammer into the puller. (3) Operate the slide hammer and remove the handcranking drive (10). (4) Remove the slide hammer from the puller. (5) Remove the PULLER (856A2632G01) from the handcranking drive (10). (6) Remove O-ring (40) from the handcranking drive (10). Discard the O-ring (40).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 203 Nov 01/08
C F M 56-5B
Removal of the Nut and of the Handcranking Drive Figure 201/TASK 72-63-00-991-301 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 204 Nov 01/08
C F M 56-5B
Removal of the Handcranking Drive Nut Figure 202/TASK 72-63-00-991-302 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 205 Nov 01/08
C F M 56-5B
Removal of the Handcranking Drive Figure 203/TASK 72-63-00-991-303 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 206 Nov 01/08
C F M 56-5B
Rearward Movement of the Horizontal Drive Shaft Figure 204/TASK 72-63-00-991-304 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 207 Nov 01/08
C F M 56-5B Subtask 72-63-00-869-054 C. Disengagement of the Horizontal Drive Shaft (1) Use the puller part of the TOOL SET,R/I-DRIVE SHAFTS (856A2718G02) as follows: (a) Put the guide pins of the puller into the internal splines of the gearshaft. (b) Tighten the tool screw by hand into the shaft. (2) Install and tighten a slide hammer into the puller. (3) Pull the horizontal drive shaft until the splines disengage from the horizontal bevel gear. (4) Remove the slide hammer and the puller from the shaft. Subtask 72-63-00-869-055 D. Engagement of the Horizontal Drive Shaft (1) Put the horizontal drive shaft back to its initial position as follows: (a) Install and tighten the puller part of the TOOL SET,R/I-DRIVE SHAFTS (856A2718G02) into the horizontal drive shaft. (b) Push the puller and turn it to engage the guide pins into the internal gearshaft splines. (c) Push the horizontal drive shaft fully rearward, until the splines engage the horizontal bevel gear (when the TGB is installed). (d) Remove the puller from the horizontal drive shaft. Subtask 72-63-00-410-062 E. Installation of the Handcranking Drive (1) Lubricate a new O-ring (40) with engine oil (Material No. CP2442) and install into the groove of the handcranking drive (10). (2) Lubricate the handcranking drive splines with engine oil (Material No. CP2442) and check for cleanliness of mating faces.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 208 Nov 01/08
C F M 56-5B (3) Install the PULLER (856A2632G01) into the handcranking drive. (4) Push the puller to install the handcranking drive in the drive AGB. Turn the puller to engage the handcranking drive into the internal gearshaft splines. Push again until the handcranking drive shaft touches the horizontal drive shaft. (5) Remove the puller from the handcranking drive. Subtask 72-63-00-410-063 F. Installation of the Handcranking Drive Nut (1) Make sure that the retaining ring (30) is installed into the groove of the nut (20). (2) Lubricate external threads of the nut (20) with engine oil (Material No. CP2442). (3) Engage the nut (20) on the wrench part of the TOOL SET,R/I-DRIVE SHAFTS (856A2718G02). (4) Safety the wrench guide on the AGB housing with the 2 bolts supplied. (5) Turn the wrench axle to engage its forward square end into the handcranking drive (10). (6) Use the wrench axle as countertorque to install the nut. TORQUE the nut (20) to between 882 and 1148 lbf.in (9.96 and 12.97 m.daN). (7) Remove the tool from the AGB. 5. Close-up ________ Subtask 72-63-00-410-064 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Install the handcranking drive cover (Ref. TASK 72-63-00-400-002).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 209 Nov 01/08
C F M 56-5B (3) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR. (4) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 210 Nov 01/08
C F M 56-5B ACCESSORY GEARBOX ASSEMBLY - REMOVAL/INSTALLATION _________________________________________________ TASK 72-63-00-000-002 Removal of the Handcranking Drive Cover 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific 856A2632
slide hammer soft-jawed pliers warning notice 1 PULLER
B. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 72-63-00-991-300 72-63-00-991-320
Opening of the Fan Cowl Doors Fig. 401 Fig. 402
3. __________ Job Set-up Subtask 72-63-00-941-056 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 401 Nov 01/08
C F M 56-5B (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-063 B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 401/TASK 72-63-00-991-300, 402/TASK 72-63-00-991-320) Subtask 72-63-00-020-057 A. Removal of the Handcranking Drive Cover NOTE : The new handcranking cover (SB CFM 72-156) must stay attached to ____ the AGB during operation. (1) Disconnect the electrical cable connectors, Channel B (70) of HJ10 harness and Channel A (50) of HJ9 harness, from the control alternator (60). Use soft-jawed pliers, if necessary. (2) Install protective caps on the electrical cables, Channel B (70) and Channel A (50), and on the control alternator electrical connectors. (3) Cut and remove the lockwire. Remove the two bolts (10) and washers (20) which attach the cover (40) to the AGB forward face. (4) Install the PULLER (856A2632G01) in the tapped hole of the cover (40). Tighten with your hand. PRE SB CFM 72-156 (5) Remove the cover (40). Use a slide hammer, if neccessary. END PRE SB CFM 72-156 POST SB CFM 72-156
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 402 Nov 01/08
C F M 56-5B (6) Remove the cover (40) and let it hang by the lanyard cable. Use a slide hammer, if necessary. END OF SB CFM 72-156 (7) Remove the PULLER from the cover. Remove and discard the two O-rings (30).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 403 Nov 01/08
C F M 56-5B
Handcranking Drive Cover Figure 401/TASK 72-63-00-991-300- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 404 Nov 01/08
C F M 56-5B
Handcranking Drive Cover Figure 401/TASK 72-63-00-991-300- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 405 Nov 01/08
C F M 56-5B
Handcranking Drive Cover Figure 402/TASK 72-63-00-991-320- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 406 Nov 01/08
C F M 56-5B
Handcranking Drive Cover Figure 402/TASK 72-63-00-991-320- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 407 Nov 01/08
C F M 56-5B TASK 72-63-00-400-002 Installation of the Handcranking Drive Cover 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------R R
No specific No specific
warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN)
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2101
Material No.
CP2442
Material No.
CP8001
Material No.
CP8002
USA MIL-T-5544 graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------30 30 30 30
O-rings O-rings O-rings O-rings
72-63-00 72-63-00 72-63-00 72-63-00
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
01B-050 01B-050A 01C-050 01C-050A
Page 408 Nov 01/09
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------70-22-00-911-002 71-00-00-710-006 71-13-00-010-040 71-13-00-410-040 73-29-00-710-040 79-00-00-210-003 72-63-00-991-300 72-63-00-991-320
Locking Procedures Minimum Idle Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Operational Test of the FADEC on the Ground (with Engine Motoring) Visual Inspection of the Oil System Fig. 401 Fig. 402
3. __________ Job Set-up Subtask 72-63-00-860-054 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-073 B. Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 409 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 401/TASK 72-63-00-991-300, 402/TASK 72-63-00-991-320) Subtask 72-63-00-420-058 A. Installation of the Handcranking Drive Cover CAUTION : DO NOT INSTALL THE COVER ON THE AGB WITHOUT THE NEW O-RINGS. IF _______ THE COVER IS INSTALLED WITHOUT THE NEW O-RINGS, THE ENGINE CAN LEAK OIL. THIS CAN CAUSE ENGINE FAILURE. (1) Lubricate two new O-rings (30) with engine oil (Material No. CP2442) and install them in the grooves of the cover (40). (2) Lubricate threads of bolts (10) with graphite grease (Material No. CP2101). PRE SB CFM 72-156 (3) Install the cover (40) and attach it with the two bolts (10) and washers (20). END PRE SB CFM 72-156 POST SB CFM 72-156 (4) Install the cover (40) which is attached by the lanyard cable to the accessory gearbox and attach it with the two bolts (10) and washers (20). END OF SB CFM 72-156 (5) TORQUE the bolts (10) to between 97 and 106 lbf.in (1.09 and 1.19 m.daN). Safety with a lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) and lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002) (Ref. TASK 70-22-00-911-002). (6) Remove protective caps from the electrical cables, Channel B (70) and Channel A (50), and from the control alternator electrical connectors. (7) Connect the electrical cable connectors, Channel A (50) of HJ9 harness and Channel B (70) of HJ10 harness, on the control alternator (60). Tighten the connectors with your hand plus one-eighth of a turn. Use soft-jawed pliers if necessary.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 410 Nov 01/08
C F M 56-5B Subtask 72-63-00-710-057 B. Test CAUTION : DO NOT OPERATE THE ENGINE WITHOUT A CORRECTLY INSTALLED COVER _______ ON THE N2 HANDCRANKING DRIVE PAD. IF THE COVER IS NOT INSTALLED CORRECTLY, THE ENGINE CAN HAVE OIL LEAKAGE. THIS CAN CAUSE ENGINE FAILURE. (1) Do an operational test of FADEC on the ground with engine motoring (Ref. TASK 73-29-00-710-040). (2) Do a minimum idle check (Ref. TASK 71-00-00-710-006) and do a check for leaks during the visual inspection of the oil system (Ref. TASK 79-00-00-210-003). 5. Close-up ________ Subtask 72-63-00-410-059 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 411 Nov 01/08
C F M 56-5B TASK 72-63-00-000-003 Removal of the Accessory Gearbox Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific No specific No specific No specific No specific No specific No specific No specific 856A2537 856A2719 856A2727 856A2754 856A3519
1 1 1 1 1
blanking plugs and caps container hydraulic hoist platform pipette slide hammer soft nose pliers warning notice access platform 1 m (3 ft. 3 in.) PROTECTOR-MOUNTING PIN FIXTURE,SUPPORT-TGB R/I PULLER RADIAL DRIVE SHAFT FIXTURE,SUPPORT-AGB SLING-AGB
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2442
Material No.
CP2859
* engine oil (Ref. 70-30-00) * corrosion protective additive (Ref. 70-30-00)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 412 Nov 01/08
C F M 56-5B C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-003 24-21-51-000-040 26-12-15-000-042 29-11-51-000-041 71-13-00-010-040 71-71-43-000-041 71-73-49-000-003 71-73-49-000-004 71-73-49-000-007 71-73-49-000-008 71-73-49-000-026 71-73-49-000-027 71-73-49-000-028 71-73-49-000-029 71-73-49-000-049 72-63-00-860-001 73-11-10-000-003 73-21-30-000-001 77-11-20-000-002 78-30-00-481-041 78-36-00-010-040 79-21-10-000-004 80-11-10-000-002 72-63-00-991-309 72-63-00-991-310 72-63-00-991-311 72-63-00-991-312 72-63-00-991-313 72-63-00-991-314
Oil Tank Draining Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Removal of the Fan Fire Detectors (4000WD1,4000WD2) Removal of the Green Engine Pump (1030GK) Opening of the Fan Cowl Doors Removal of the Drain Manifold Module Removal of the Starter Pad Oil Drain Tube Removal of the IDG Oil Drain Tube Removal of the Fan Case Drain Tubes Removal of the Fuel Pump Drain Tubes Removal of the Heat Exchanger Drain Tube Removal of the Hydro Mechanical Unit (HMU) Drain Tube Removal of the Hydraulic Pump Drain Tube Removal of the Forward Oil Sump Drain Tube Removal of the Reservoir to Manifold Hydraulic Oil Drain Tube Disengagement/Engagement of the Horizontal Drive Shaft Removal of the Fuel Pump and Filter Assembly Removal of the Control Alternator Removal of the N2 Speed Sensor (4001EV). Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Removal of the Lubrication Unit Removal of the Pneumatic Starter Fig. 403 Fig. 404 Fig. 405 Fig. 406 Fig. 407 Fig. 408
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 413 Nov 01/08
C F M 56-5B 3. __________ Job Set-up Subtask 72-63-00-941-061 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-071 B. Get Access (1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Put the access platform in position. Subtask 72-63-00-040-053 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-63-00-010-074 D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 414 Nov 01/08
C F M 56-5B 4. Procedure _________ (Ref. Fig. 403/TASK 72-63-00-991-309, 404/TASK 72-63-00-991-310, 405/TASK 72-63-00-991-311, 406/TASK 72-63-00-991-312, 407/TASK 72-63-00-991-313, 408/TASK 72-63-00-991-314) Subtask 72-63-00-941-062 A. Put a container under the Accessory Gearbox to collect the remaining fluid from the tubes and control. Subtask 72-63-00-010-070 B. Preparation for the Removal of the AGB CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (1) Remove the fan fire detector (Ref. TASK 26-12-15-000-042). (2) Remove the drain manifold module (Ref. TASK 71-71-43-000-041). (3) Remove the drain tubes under the AGB/TGB as follows: (a) FRV drain tubes (Ref. TASK 71-73-49-000-007). (b) Oil reservoir drain tube (Ref. TASK 71-73-49-000-049). (c) HMU drain tube (Ref. TASK 71-73-49-000-027). (d) Heat exchanger drain tube (Ref. TASK 71-73-49-000-026). (e) Fuel pump drain tube (Ref. TASK 71-73-49-000-008). (f) Hydraulic pump drain tube (Ref. TASK 71-73-49-000-028). (g) IDG pad drain tube (Ref. TASK 71-73-49-000-004). (h) Starter pad drain tube (Ref. TASK 71-73-49-000-003). (i) Forward sump drain tube (Ref. TASK 71-73-49-000-029). (4) Remove the hydraulic pump (Ref. TASK 29-11-51-000-041).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 415 Nov 01/08
C F M 56-5B
Accessory Gearbox Assembly Figure 403/TASK 72-63-00-991-309 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 416 Nov 01/08
C F M 56-5B
INTENTIONALLY BLANK
R 72-63-00 CES
Page 417 Feb 01/07
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 18 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 418 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 28 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 419 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 38 (SHEET 3) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 420 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 48 (SHEET 4) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 421 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 58 (SHEET 5) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 422 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 68 (SHEET 6) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 423 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 78 (SHEET 7) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 424 Nov 01/08
C F M 56-5B
Accessory Drive External Parts Figure 404/TASK 72-63-00-991-310- 88 (SHEET 8) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 425 Nov 01/08
C F M 56-5B
Accessory Drive Support Fixture Figure 405/TASK 72-63-00-991-311- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 426 Nov 01/08
C F M 56-5B
Accessory Drive Support Fixture Figure 405/TASK 72-63-00-991-311- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 427 Nov 01/08
C F M 56-5B
Accessory Drive Figure 406/TASK 72-63-00-991-312 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 428 Nov 01/08
C F M 56-5B
TGB Blanking Kit Figure 407/TASK 72-63-00-991-313 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 429 Nov 01/08
C F M 56-5B
AGB Blanking Kit Figure 408/TASK 72-63-00-991-314- 12 (SHEET 1) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 430 Nov 01/08
C F M 56-5B
AGB Blanking Kit Figure 408/TASK 72-63-00-991-314- 22 (SHEET 2) R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 431 Nov 01/08
C F M 56-5B (5) Remove the integrated drive generator (IDG) (Ref. TASK 24-21-51-000040). (6) Remove the N2 speed sensor (Ref. TASK 77-11-20-000-002). (7) Remove the pneumatic starter (Ref. TASK 80-11-10-000-002). (8) Remove the lubrication unit (Ref. TASK 79-21-10-000-004). (9) Remove the fuel pump (Ref. TASK 73-11-10-000-003). (10) Remove the ECU alternator (Ref. TASK 73-21-30-000-001). (11) Drain the accessory drive section (Ref. TASK 12-13-79-610-003). (12) Install the blanking plugs and caps on the free ends of tubes and on the connectors to prevent contamination. Subtask 72-63-00-020-069 C. Removal of the Fan Case Water Drain Tubes CAUTION : MAKE SURE THAT THE TUBE NUTS ARE NOT MISSING DURING THE REMOVAL _______ OF FAN CASE WATER DRAIN TUBES. NOTE : The AGB scavenge tube has been removed to ease the removal of the ____ ECU alternator. (1) Remove the parts which attach the fan case water drain tubes (220) and (530) as follows: (a) Remove the nut (400) and the bolt (465) from the bracket (475) on the AGB left-hand side. (b) Remove the outer spring clip (425), the inner spring clip (440) and the plastic bushing (435) from the CLP fuel tube (430). (c) Remove the outer spring clip (405), the inner spring clip (420) and the plastic bushing (410) from the oil heater tube (415). (d) Remove the outer spring clip (460), the inner spring clip (450) and the plastic bushing (470) from the IDG exchanger fuel outlet tube (455). (e) Remove the bolt (445) and the bracket (475) from the AGB left-hand side.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 432 Nov 01/08
C F M 56-5B (f) Remove the nut (165) and the bolt (125) from the bracket (130). (g) Remove the outer spring clip (135), the inner spring clip (145) and the plastic bushing (140) from the TGB oil scavenge tube (110). (h) Remove the outer spring clip (160), the inner spring clip (150) and the plastic bushing (155) from the rear sump oil return tube (105). (i) Remove the bolts (120), (170) and (175) which attach the forward sump oil return tube (100), the TGB oil scavenge tube (110) and the rear sump oil return tube (105) from the AGB front face. (j) Remove and keep the gaskets (115), (180) and (185). (k) Remove the nut (70) and the bolt (65) from the bracket (90) on the AGB front face. (l) Remove the outer spring clip (75), the inner spring clip (85) and the plastic bushing (80) from the rear sump oil supply tube (60). (m) Remove the nut (15) and the bolt (40) from the bracket (45) on the AGB front face. (n) Remove the outer spring clip (35), the inner spring clip (20) and the plastic bushing (25) from the AGB/TGB oil supply tube (30). (o) Remove the nut (95) and the bolt (55) from the bracket (90) on the AGB front face. (p) Remove the outer spring clip (50), the inner spring clip (5) and the plastic bushing (10) from the AGB/TGB oil supply tube (30). (q) Remove the nut (215) and the bolt (190). (r) Remove the outer spring clip (210), the inner spring clip (200), the plastic bushing (205) and the bracket (195) from the forward fan case water drain tube (220). (s) Remove the forward fan case water drain tube (220) from the engine. (t) Remove the nut (560) and the bolt (540).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
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C F M 56-5B (u) Remove the outer spring clip (555), the inner spring clip (545), the plastic bushing (550) and the bracket (535) from the aft fan case water drain tube (530). (v) Remove the aft fan case water drain tube (530) from the engine. (2) Disconnect the water drain tubes (220) and (530) from the fan case nipples and remove them from the engine. Subtask 72-63-00-020-065 D. Removal of the AGB External Parts (1) Disengage the IDG electrical cables from the clamp on the AGB. (2) Remove the parts which attach the AGB external parts as follows: (a) Remove the bolts (360) and (365) to remove the FWD sump oil scavenge hose (355) from the AGB rear face. (b) Remove and keep the gaskets (350) and (370). (c) Remove the bolts (390) which attach the TGB oil scavenge hose (385) to the AGB rear face. (d) Remove and keep the gasket (395). (e) Remove the bolt (685) and the washer (690) to disconnect the bonding strip (695) from the AGB. (3) Disconnect and remove the tubes (30) and (60) from the AGB. (4) Disconnect the TGB oil supply tube (230) from the AGB. (5) Removal of the Rear Sump Oil Tubes (a) Cut and remove the lockwire. (b) Disconnect the rear sump oil scavenge tube (270) and the rear sump oil supply tube (305) from the tube bundle. (c) Remove the parts which attach the rear sump oil tubes as follows: 1 _
Remove the nut (335) and the bolt (225) from the bracket (345) on the AGB rear face.
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C F M 56-5B 2 _
Remove the outer spring clip (320), the inner spring clip (330) and the plastic bushing (325) from the rear sump oil supply tube (305).
3 _
Remove the nut (290) and the bolt (315) from the bracket (260) on the left-hand side of the TGB/horizontal drive shaft housing junction.
4 _
Remove the outer spring clip (310), the inner spring clip (295) and the plastic bushing (300) from the rear sump oil supply tube (305).
5 _
Remove the rear sump oil supply tube (305).
6 _
Remove the nut (235) and the bolt (285) from the bracket (260) on the left-hand side of the TGB/horizontal drive shaft housing junction.
7 _
Remove the outer spring clip (240), the inner spring clip (250) and the plastic bushing (245) from the TGB oil supply tube (230).
8 _
Remove the outer spring clip (275), the inner spring clip (265) and the plastic bushing (255) from the rear sump oil scavenge tube (270).
9 _
Remove the bolts (280) which attach the rear sump oil scavenge tube (270) to the AGB rear face.
10 __
Remove the rear sump oil scavenge tube (270) from the AGB rear face.
11 __
Remove and keep the gasket (340).
(6) Removal of the TGB External Parts (a) Disconnect the TGB oil supply tubes (230) from the TGB left-hand side and remove the tubes (230). (b) Remove the parts which attach the TGB external parts as follows: 1 _
Remove the bolt (610) which attaches the clamp (565) to the bracket (345) on the horizontal drive shaft housing, left-hand side.
2 _
Remove the clamp (565) which attaches the HJ8 harness to the bracket (345).
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C F M 56-5B 3 _
Remove the bolt (605) which attaches the clamp (600) to the bracket (535) on the AGB/TGB interface, left hand side.
4 _
Remove the clamp (600) which attaches the HJ8 harness to the bracket (535).
5 _
Remove the bolt (590) which attaches the clamp (595) to the bracket (345) on the horizontal drive shaft housing, left-hand side.
6 _
Remove the clamp (595) which attaches the HJ7 harness to the bracket (345).
7 _
Remove the bolt (585) which attaches the clamp (580) to the bracket (260) on the AGB/TGB interface, left-hand side.
8 _
Remove the clamp (580) which attaches the HJ7 harness to the bracket (260).
9 _
Remove the bolts (665) which attach the bracket (660) and (670) to the TGB right-hand side with electrical harness. Remove the brackets (660) and (670).
10 __
Remove the bolts (655) and the washers (650) which attach the bracket (645) to the TGB right hand side.
11 __
Remove the nuts (635) and the bolts (640) which attach the bracket (645) to the bracket (505) on the TGB right-hand side. The bracket (645) is attached to the electrical harnesses.
12 __
Remove the bolts (625) which attach the bracket (630) to the TGB left-hand side.
13 __
Remove the bolts (380) and the TGB oil scavenge hose (385) from the TGB left-hand side.
14 __
Remove and keep the gasket (375).
15 __
Remove the nuts (575), the bolts (570) and the brackets (260), (535) from the bracket (520) on the AGB/TGB interface, left-hand side.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
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C F M 56-5B (7) Removal of the Accessory Drive (a) Install the FIXTURE,SUPPORT-AGB (856A2754G01) and the FIXTURE,SUPPORT-TGB R/I (856A2719G02) as follows: 1 _
Remove the two nuts (510), washers (515) and bolts (480) which attach the TGB housing to the horizontal drive shaft housing at the 4:30 and 7:30 oclock positions.
2 _
Install the FIXTURE, FIXTURE,SUPPORT-TGB R/I (856A2719G02) on the FIXTURE,SUPPORT-AGB (856A2754G01).
3 _
Install the tool assembly on a hydraulic hoist platform and position under the accessory gearbox assembly.
4 _
Use lockpins to secure the fork and the tenon. Use adjusting screws to adjust the height to the lateral supports.
5 _
Engage the locating pin into the rear mount of the AGB. Use the knurled nut to attach the clamp. Adjust the height of the support with the adjusting screw.
6 _
Adjust the height of the FIXTURE,SUPPORT-TGB R/I (856A2719G02) with the adjusting screws.
7 _
Engage the lockpins of the front plates into the TGB holes. Use the knurled knobs to adjust the front plates, if necessary.
8 _
Attach the rear yoke to the TGB rear mount with the lockpin.
(b) Remove and discard the cotter pins (700), (725) and (740). (c) Remove the nuts (705), (720) and (745) and the washers (710), (730) and (750). (d) Install the PROTECTOR-MOUNTING PIN (856A2537G01) on the mounting pins (680), (715) and (735). (e) Remove the three mounting pins (680), (715) and (735) with an impact puller. (f) Slowly and carefully lower the hydraulic hoist platform and separate the accessory drive assembly from the engine.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
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C F M 56-5B (g) Two different cases can appear when you remove the accessory drive assembly from the engine: 1 _
If the radial drive shaft (675) comes with the TGB, remove the radial drive shaft (675) from the TGB.
2 _
If the radial drive shaft (675) remains in the fan frame:
3 _
Install a PULLER RADIAL DRIVE SHAFT (856A2727G01) in the radial drive shaft.
4 _
Remove the radial drive shaft (675) from the fan frame with a slide hammer.
5 _
Remove the tools from the radial drive shaft.
(h) Remove the O-ring (755) from the radial drive shaft. Discard the O-ring (755). (i) Store the radial drive shaft in its storage tube (765). (8) Removal of the TGB from the AGB (a) Disengage the horizontal drive shaft (Ref. TASK 72-63-00-860001). (b) Remove the nuts (510), the washers (515) and the bolts (480) from the TGB/AGB interface. (c) Remove the brackets (485), (505), (520) and (525). (d) Remove the TGB from the AGB and from the FIXTURE,SUPPORT-TGB R/I (856A2719G02). Keep the gasket (500). (e) Remove the O-ring (495) from the oil distributor in the bevel gear. (Ref. Fig. 404/TASK 72-63-00-991-310) NOTE : Make sure that O-ring (495) is serviceable and O-ring ____ outer diameter is correct. If it is not serviceable, remove and discard it with soft nose pliers. (f) Install the TGB blanking kit (760) as follows: 1 _
Install a cap on the upper face of the TGB housing.
2 _
Install a cap on the TGB oil supply nipple.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 438 Nov 01/08
C F M 56-5B 3 _
Install a plug in the TGB scavenge port.
4 _
Install a plug in the TGB vent port.
5 _
Install a cover on the forward face of the TGB housing.
(g) Place the TGB in a storage container. (9) Removal of the AGB from the Tools (a) Engage the horizontal drive shaft (Ref. TASK 72-63-00-860-001). (b) Remove the O-ring (490) from the horizontal drive shaft. Discard the O-ring (490). (10) When you remove all equipment from the AGB, apply storage oil on all bearings as follows: Mix 5 percent of corrosion protective additive (Material No. CP2859) with engine oil (Material No. CP2442) and lightly coat all bearings with a pipette. (a) Install the AGB blanking kit (775) as follows: 1 _
Install a cap on the lubrication unit pad.
2 _
Install a cap on the hydraulic pump pad.
3 _
Install a cap on the alternator pad.
4 _
Install a cap on the IDG pad.
5 _
Install a cap on the fuel pump pad.
6 _
Install a cap on the starter pad.
7 _
Install a cover on the radial drive shaft housing.
8 _
Put blanking plugs and caps on all nipples and orifices.
(b) Install the SLING-AGB (856A3519G01/G02) as follows: 1 _
Attach the two sectors at each end of the AGB with the two lockpins supplied.
2 _
Attach the SLING-AGB (856A3519GO1/G02) to a hoist.
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C F M 56-5B (c) Remove the lockpins and loosen the clamp which attach the FIXTURE,SUPPORT-AGB (856A2754G01) to the AGB. (d) Remove the AGB from the FIXTURE,SUPPORT-AGB (856A2754G01). Place the AGB in a storage container. (e) Remove the SLING-AGB (856A3519G01/G02) from the AGB.
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
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C F M 56-5B TASK 72-63-00-400-003 Installation of the Accessory Gearbox Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R R R
No No No No No
specific specific specific specific specific
No specific
hydraulic hoist platform soft nose pliers warning notice access platform 1 m (3 ft. 3 in.) Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) Torque Wrench : range 62.00 to 900.00 lbf.in (0.70 to 10.00 m.daN) Torque Wrench : range 180.00 to 1800.00 lbf.in (2.00 to 20.00 m.daN) PROTECTOR-MOUNTING PIN FIXTURE,SUPPORT-TGB R/I PULLER RADIAL DRIVE SHAFT FIXTURE,SUPPORT-AGB SLING-AGB
No specific 856A2537 856A2719 856A2727 856A2754 856A3519
1 1 1 1 1
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1008
Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
* trichloroethylene (Ref. 70-30-00) * acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544
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C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2338
Material No.
CP2442
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
Material No.
CP8001
Material No.
CP8002
graphite grease (Ref. 70-30-00) * brisal-ox (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------490 490 495 495 700 725 740 755
O-ring O-ring O-ring O-ring cotter pin cotter pin cotter pin O-ring
72-63-00 72-63-00 72-62-00 72-62-00 72-00-00 72-00-00 72-00-00 72-62-00
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
04 04 05 05 07 07 07 05
-010 -010A -030 -030A -150 -110 -070 -020
Page 442 Nov 01/08
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------12-13-79-610-002 12-13-79-610-002 24-21-51-400-040 26-12-15-400-042 29-11-51-400-041 70-22-00-911-002 71-00-00-710-006 71-00-00-710-025 71-13-00-010-040 71-13-00-410-040 71-71-43-400-041 71-73-49-400-003 71-73-49-400-004 71-73-49-400-007 71-73-49-400-008 71-73-49-400-026 71-73-49-400-027 71-73-49-400-028 71-73-49-400-029 71-73-49-400-049 72-63-00-400-002 72-63-00-860-001 73-11-10-400-003 73-21-30-400-001 78-30-00-081-041 78-30-00-481-041 78-36-00-010-040 78-36-00-410-040 79-00-00-210-003 79-21-10-400-004 80-11-10-400-002 72-63-00-991-309 72-63-00-991-310
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Fan Fire Detectors (4000WD1,4000WD2) Installation of the Green Engine Pump (1030GK) Locking Procedures Minimum Idle Check Accel Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Installation of the Drain Manifold Module Installation of the Starter Pad Oil Drain Tube Installation of the IDG Oil Drain Tube Installation of the Fan Case Drain Tubes Installation of the Fuel Pump Drain Tubes Installation of the Heat Exchanger Drain Tube Installation of the Hydro Mechanical Unit (HMU) Drain Tube Installation of the Hydraulic Pump Drain Tube Installation of the Forward Oil Sump Drain Tube Installation of the Reservoir to Manifold Hydraulic Oil Drain Tube Installation of the Handcranking Drive Cover Disengagement/Engagement of the Horizontal Drive Shaft Installation of the Fuel Pump and Filter Assembly Installation of the Control Alternator Make the Thrust Reverser Serviceable after Maintenance Make the Thrust Reverser Unserviceable for Maintenance Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors Visual Inspection of the Oil System Installation of the Lubrication Unit Installation of the Pneumatic Starter Fig. 403 Fig. 404
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C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------72-63-00-991-311 72-63-00-991-312 72-63-00-991-313 72-63-00-991-314
Fig. Fig. Fig. Fig.
405 406 407 408
3. __________ Job Set-up Subtask 72-63-00-860-055 A. Aircraft Maintenance Configuration (1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine. (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2). (3) Make sure that the access platform is in position. Subtask 72-63-00-010-075 B. Get Access (1) Make sure that the fan cowl doors are open: (Ref. TASK 71-13-00-010040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-3600-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 444 Nov 01/08
C F M 56-5B Subtask 72-63-00-040-052 C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00481-041). 4. Procedure _________ (Ref. Fig. 403/TASK 72-63-00-991-309, 404/TASK 72-63-00-991-310, 405/TASK 72-63-00-991-311, 406/TASK 72-63-00-991-312, 407/TASK 72-63-00-991-313, 408/TASK 72-63-00-991-314) Subtask 72-63-00-210-053 A. Check all gaskets retained during removal for condition and serviceability (1) If gaskets are not reusable, replace them. Subtask 72-63-00-410-066 B. Preparation for the Installation of the Accessory Gearbox CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (1) Before their installation, make sure that the gaskets are serviceable, lubricate the gaskets and nipples with engine oil (Material No. CP2442) and lubricate the threads of bolts with graphite grease (Material No. CP2101), unless specified. (2) Remove blanking plugs and caps from the free ends of items before installation. (3) Install the FIXTURE,SUPPORT-TGB R/I (856A2719G02) or the FIXTURE,SUPPORT-AGB (856A2754G01). (4) Install the tool assembly on a hydraulic hoist platform. (5) Install the SLING-AGB (856A3519G01/G02) on the AGB as follows: (a) Position the two sectors at each end of the AGB and safety with the two lockpins supplied. (b) Attach the sling to a hoist.
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C F M 56-5B (6) Remove the AGB from its container and install it on the FIXTURE,SUPPORT-AGB (856A2754G01) as follows: (a) Use lockpins to safety the fork and tenon to the AGB. (b) Engage the locating pin into the rear mount of the AGB. Use the knurled knob to attach the clamp. (7) Remove the SLING-AGB (856A3519G01/G02) from the AGB. (8) Remove the AGB blanking kit (760) as follows: (a) Remove the cap from the lubrication unit pad. (b) Remove the cap from the hydraulic pump pad. (c) Remove the cap from the alternator pad. (d) Remove the cap from the IDG pad. (e) Remove the cap from the fuel pump pad. (f) Remove the cover from the radial drive shaft housing. (g) Remove the cap from the starter pad. (h) Remove the blanking plugs from the nipples and orifices. (9) Lubricate a new O-ring (490) with engine oil (Material No. CP2442) and install it in the groove of the horizontal drive shaft. (10) Lubricate the splines of the horizontal drive shaft with engine oil (Material No. CP2442). (11) Disengage the horizontal drive shaft (Ref. TASK 72-63-00-860-001). (12) Remove the TGB from its container. (13) Remove the TGB blanking kit (745) as follows: (a) Remove the cap from the TGB oil supply nipple. (b) Remove the plug from the TGB scavenge port. (c) Remove the plug from the TGB vent port. (d) Remove the cover from the FWD face of the TGB housing.
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C F M 56-5B (14) Install the O-ring (495) in the groove of the oil distributor in the bevel gear: (Ref. Fig. 404/TASK 72-63-00-991-310) NOTE : If necessary, lubricate the new O-ring (495) with engine oil ____ (Material No. CP2442). (a) Engage the O-ring (495) througt the hole of the oil distributor in the bevel gear with soft nose pliers. (b) Put the O-ring (495) in the groove of the oil distributor in the bevel gear with soft nose pliers. NOTE : Make sure that O-ring (495) is correctly installed in the ____ groove of the oil distributor in the bevel gear. (15) Install the TGB on the FIXTURE,SUPPORT-TGB R/I (856A2719G02) as follows: (a) Engage the lockpins of the front plates in the TGB holes, at the 7:30 and 4:30 locations. (b) Secure the rear yoke to the TGB rear mount with the lockpin. (c) Set the position of the TGB in relation to the AGB. (16) Install the gasket (500) between the AGB and the TGB. (17) Move the TGB forward in contact with the AGB. (18) Attach the TGB to the AGB as follows: (a) Install three bolts (480), washers (515) and nuts (510) at the flanged bushing locations (2:30, 6:30 and 10:30 oclock positions). (b) TORQUE the nuts (510) to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (c) Install two bolts (480), washers (515) and nuts (510) in the holes at the 11:30 and 0:30 oclock positions. (d) TORQUE the nuts (510) to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (e) Remove the nut (510), washer (515) and bolt (480) at the 6:30 oclock position.
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Page 447 Nov 01/08
C F M 56-5B (f) Install the bracket (525) on the front face of the AGB/TGB interface, at holes at the 5:30 and 6:30 oclock positions, with two bolts (480), washers (515) and nuts (510). (g) TORQUE the nuts to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (h) Remove the nuts (510), washer (515) and bolt (480) at the 2:30 oclock position. (i) Install the bracket (485) on the front face of the AGB/TGB interface, at holes at the 3:30 and 2:30 oclock positions, with two bolts (480). (j) Install the bracket (505) on the rear face of the AGB/TGB interface, at holes at the 2:30 and 1:30 oclock positions, with a bolt (480). (k) Secure the three bolts (480) at the 1:30, 2:30 and 3:30 oclock positions with three washers (515) and nuts (510). (l) TORQUE the nuts to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (m) Install the bracket (520) on the rear face of the AGB/TGB interface, at holes at the 8:30 and 9:30 oclock positions, with two bolts (480), washers (515) and nuts (510). (n) TORQUE the nuts to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (o) Disengage the lockpins of the front plates from the holes at the 4:30 and 7:30 oclock positions. (p) Install the two bolts (480), washers (515) and nuts (510) which remain. (q) TORQUE the nuts to between 240 and 290 lbf.in (2.71 and 3.27 m.daN). (r) Engage the horizontal drive shaft (Ref. TASK 72-63-00-860-001). (19) Remove the radial drive shaft from the radial drive shaft storage tube (750). (20) Lubricate a new O-ring (755) with engine oil (Material No. CP2442) and install it in the radial drive shaft groove.
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C F M 56-5B (21) Lubricate the splines at each end of the radial drive shaft with engine oil (Material No. CP2442). (22) Install the radial drive shaft in the fan frame strut at the six oclock position with the PULLER RADIAL DRIVE SHAFT (856A2727G01). Subtask 72-63-00-420-064 C. Installation of the Accessory Gearbox Assembly CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (1) Before their installation, make sure that the gaskets are serviceable, lubricate the gaskets and nipples with engine oil (Material No. CP2442) and lubricate the threads of bolts with graphite grease (Material No. CP2101), unless specified. (2) Remove blanking plugs and caps from the free ends of items before installation. (3) Install the PROTECTOR-MOUNTING PIN (856A2537G01) on the mounting pins (665), (700), (720). NOTE : Do not lubricate the mounting pins. ____ (4) Put the accessory gearbox assembly in position under the engine. (5) Install the accessory gearbox assembly on the engine as follows: CAUTION : TAKE CARE NOT TO DAMAGE THE HARNESSES AND TUBES LEFT IN _______ PLACE ON THE ENGINE. (a) Lift the hoist platform while you engage the radial drive shaft in the TGB. (b) Secure the accessory gearbox on the engine with the mounting pins (665), (700), (720). (c) Remove the PROTECTOR-MOUNTING PIN (856A2537G01) from the mounting pins (665), (700), (720). (d) Install the washers (695), (715), (735) and nuts (690), (705), (730).
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Page 449 Nov 01/08
C F M 56-5B (e) TORQUE the nuts (690), (705) to between 840 and 930 lbf.in (9.49 and 10.50 m.daN). (f) TORQUE the nut (730) to between 420 and 470 lbf.in (4.74 and 5.31 m.daN). (g) Safety with new cotter pin (700), cotter pin (725) and cotter pin (740). (6) Remove the FIXTURE,SUPPORT-AGB (856A2754G01) and FIXTURE,SUPPORT-TGB R/I (856A2719G02) assembly as follows: (a) Remove the lockpins which attach the fork and tenon to the AGB. (b) Remove the lockpin which attaches the rear yoke to the TGB rear mount. (c) Remove the clamp from the AGB rear mount. (d) Lower the hoist platform, and remove from the engine. (7) Installation of the TGB External Parts (a) Install the parts which attach the TGB external parts as follows: 1 _
Install the brackets (260), (535) to the bracket (520) on the AGB/TGB interface, left-hand side, with the bolts (570) and the nuts (575).
2 _
Install the gasket (375) between the mating faces correctly.
3 _
Install the TGB oil scavenge hose (385) on the TGB, at the right-hand side, with the bolts (380).
4 _
Install the bracket (630) on the TGB left-hand side with the bolts (625).
5 _
Install the bracket (645) on the bracket (505) on the TGB right-hand side with the bolts (640) and the nuts (635).
6 _
Install the bracket (645) on the TGB right-hand side with the bolts (655) and the washers (650). The bracket (645) is attached to the electrical harnesses.
7 _
Install the brackets (660) and (670) on the TGB right-hand side with the bolts (665).
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C F M 56-5B 8 _
Install the clamp (580) on the HJ7 harness and attach to the bracket (260) on the AGB/TGB interface, left-hand side, with the bolt (585).
9 _
Install the clamp (595) on the HJ7 harness and attach to the bracket (345) on the horizontal drive shaft housing, left-hand side, with the bolt (590).
10 __
Install the clamp (600) on the HJ8 harness and attach to the bracket (535) on the AGB/TGB interface, left-hand side, with the bolt (605).
11 __
Install the clamp (565) on the HJ8 harness and attach to the bracket (345) on the horizontal drive shaft housing, left-hand side, with the bolt (610).
(b) TORQUE the nuts (635) and bolts (380), (585), (590), (605), (610) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (c) TORQUE the nuts (575) and bolts (625), (655), (665) to between 98 and 110 lbf.in (1.10 and 1.24 m.daN). (d) Connect the TGB oil supply tubes (230) to the TGB left-hand side and to the AGB rear face. Tighten the connecting nuts with your hand. (8) Installation of the Rear Sump Oil Tubes (a) Connect the rear sump oil scavenge tube (270) to the tube bundle with your hand. (b) Connect the rear sump oil supply tube (305) to the AGB and to the tube bundle with your hand. (c) Install the parts which attach the rear sump oil tubes as follows: 1 _
Correctly install the gasket (340) between the mating faces.
2 _
Install the bolts (280) to attach the rear sump oil scavenge tube (270) on the AGB rear face.
3 _
Install the TGB oil supply tube (230) and the rear sump oil scavenge tube (270) on the left-hand side of the TGB horizontal drive shaft housing junction.
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C F M 56-5B 4 _
Install the plastic bushing (245), the inner spring clip (250) and the outer spring clip (240) on the TGB oil supply tube (230).
5 _
Install the plastic bushing (255), the inner spring clip (265) and the outer spring clip (275) on the rear sump oil scavenge tube (270).
6 _
Attach the spring clips (240), (250) and (265), (275) to the bracket (260) with the bolt (285) and the nut (235) on the left-hand side of TGB/horizontal drive shaft housing junction.
7 _
Install the rear sump oil supply tube (305) on the AGB rear face.
8 _
Install the plastic bushing (300), the inner spring clip (295) and the outer spring clip (310) on the rear sump oil supply tube (305).
9 _
Attach the spring clips (295) and (310) to the bracket (260) with the bolt (315) and the nut (290) on the TGB/horizontal drive shaft housing junction.
10 __
Install the plastic bushing (325), the inner spring clip (330) and the outer spring clip (320) on the rear sump oil supply tube (305) on the AGB rear face.
11 __
Attach the spring clips (330) and (320) to the bracket (345) with the bolt (225) and the nut (335) on the AGB rear face.
(d) Torque the nut (235) to between 98 and 110 lbf.in (1.10 and 1.24 m.daN). (e) TORQUE the nuts (290), (335) and bolts (280) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (f) TORQUE the rear sump oil supply tube (305) connecting nuts to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (g) TORQUE the rear sump oil scavenge tube (270) connecting nut to between 900 and 1100 lbf.in (10.17 and 12.43 m.daN). Safety with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002) (Ref. TASK 70-22-00911-002). (h) TORQUE the TGB oil supply tube (230) connecting nuts to between 270 and 300 lbf.in (3.05 and 3.39 m.daN).
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C F M 56-5B (9) Installation of the AGB External Parts WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL _______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. (a) Carefully clean the mating faces of the AGB, bolt (685), washer (690) and bonding strip (695) with trichloroethylene (Material No. CP1008) or acetone (Material No. CP1039) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) or isopropyl alcohol (Material No. CP1041). (b) Apply a thin layer of brisal-ox (Material No. CP2338) to the mating faces of the AGB, bolt (685), washer (690), and bonding strip (695). (c) Install the parts which attach the AGB external parts as follows: 1 _
Attach the bonding strip (695) to the AGB on the starter pad with the bolt (685) and the washer (690).
2 _
Correctly install the gasket (395) between the mating faces.
3 _
Install the TGB oil scavenge hose (385) on the AGB rear face with the bolts (390).
4 _
Correctly install the gaskets (350) and (370) between the mating faces.
5 _
Install the FWD sump oil scavenge hose (355) on the AGB rear face with the bolts (360) and on the TGB right-hand side with the bolts (365).
6 _
Install the plastic bushing (10), the inner spring clip (5) and the outer spring clip (50) on the AGB/TGB oil supply tube (30).
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Page 453 Nov 01/08
C F M 56-5B 7 _
Attach the spring clips (5) and (50) to the bracket (90) with the bolt (55) and the nut (95) on the AGB front face.
8 _
Install the plastic bushing (25), the inner spring clip (20) and the outer spring clip (35) on the AGB/TGB oil supply tube (30).
9 _
Attach the spring clips (20) and (35) to the bracket (45) with the bolt (40) and the nut (15) on the AGB front face.
10 __
Install the plastic bushing (80), the inner spring clip (85) and the outer spring clip (75) on the rear sump oil supply tube (60).
11 __
Attach the spring clips (75) and (85) to the bracket (90) with the bolt (65) and the nut (70) on the AGB front face.
12 __
Correctly install the gaskets (115), (180) and (185) between the mating faces.
13 __
Install the FWD sump oil return tube (100), the rear sump oil return tube (105) and the TGB oil scavenge tube (110) on the AGB front face with the bolts (120), (175) and (170).
14 __
Install the plastic bushing (140), the inner spring clip (145) and the outer spring clip (135) on the TGB oil scavenge tube (110).
15 __
Install the plastic bushing (155), the inner spring clip (150) and the outer spring clip (160) on the rear sump oil return tube (105).
16 __
Attach the spring clips (145), (135) and (150), (160) to the bracket (130) with the bolt (125) and the nut (165) on the AGB front face.
17 __
Attach the bracket (475) to the AGB left-hand side with the bolts (445).
18 __
Install the plastic bushing (470), the inner spring clip (450) and the outer spring clip (460) on the IDG exchanger fuel outlet tube (455).
19 __
Install the plastic bushing (410), the inner spring clip (420) and the outer spring clip (405) on the oil heater tube (415).
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Page 454 Nov 01/08
C F M 56-5B 20 __ 21 __
Install the plastic bushing (435), the inner spring clip (440) and the outer spring clip (425) on the CLP fuel tube (430). Attach the spring clips (450), (460) and (425), (440) and (405), (420) to the bracket (475) with the bolt (465) and the nut (400) on the AGB left-hand side.
(d) TORQUE the nut (70) and bolts (390), (360), (365), (120), (170), (175) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (e) TORQUE the nuts (15), (95), (165), (400) and bolts (445), (685) to between 98 and 110 lbf.in (1.10 and 1.24 m.daN). (f) TORQUE the rear sump oil supply tube (60) connecting nut to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (g) TORQUE the AGB/TGB oil supply tube (30) connecting nut to between 450 and 550 lbf.in (5.08 and 6.21 m.daN). (h) Engage the IDG electrical cables in the clamp on the AGB. (10) Installation of the Fan Case Water Drain Tubes (a) Install the parts which attach the water drain tubes as follows: 1 _
Install the plastic bushing (550), the inner spring clip (545) and the outer spring clip (555) on the AFT fan case water drain tube (530).
2 _
Attach the spring clips (545) and (555) to the bracket (535) with the bolt (540) and the nut (560).
3 _
Install the plastic bushing (205), the inner spring clip (200) and the outer spring clip (210) on the FWD fan case water drain tube (220).
4 _
Attach the spring clips (200) and (210) to the bracket (195) with the bolt (190) and the nut (215). NOTE : The bracket (195) will be attached to the AGB scavenge ____ tube after the installation of the ECU alternator.
5 _
Install the forward fan case water drain tube (220) on the engine.
(b) Connect the water drain tubes to the nipples on the fan frame.
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C F M 56-5B (c) TORQUE the aft fan case water drain tube (530) connecting nut to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (d) TORQUE the nut (560) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). Subtask 72-63-00-410-067 D. Final Steps of the AGB Installation CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS: _______ - ONE WRENCH TO HOLD THE UNION, AND - ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT. THIS PREVENTS DAMAGE TO THE PARTS. (1) Before their installation, make sure that the gaskets are serviceable, lubricate the gaskets and nipples with engine oil (Material No. CP2442) and lubricate the threads of bolts with graphite grease (Material No. CP2101), unless specified. (2) Remove blanking plugs and caps from the free ends of items before installation. (3) Install the ECU alternator (Ref. TASK 73-21-30-400-001). (4) Connect the forward fan case water drain tube (220) to the nipple on the fan frame. (5) TORQUE the forward fan case water drain tube (220) connecting nut to between 270 and 300 lbf.in (3.05 and 3.39 m.daN). (6) TORQUE the nut (215) to between 47 and 53 lbf.in (0.53 and 0.59 m.daN). (7) Install the fuel pump (Ref. TASK 73-11-10-400-003). (8) Install the lubrication unit (Ref. TASK 79-21-10-400-004). (9) Install the pneumatic starter (Ref. TASK 80-11-10-400-002). (10) Install the integrated drive generator (IDG) (Ref. TASK 24-21-51-400040). (11) Install the hydraulic pump (Ref. TASK 29-11-51-400-041).
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C F M 56-5B (12) Install the drain tubes which follow under the AGB: - FRV drain tube (Ref. TASK 71-73-49-400-007) - oil reservoir drain tube (Ref. TASK 71-73-49-400-049) - HMU drain tube (Ref. TASK 71-73-49-400-027) - heat exchanger drain tube (Ref. TASK 71-73-49-400-026) - fuel pump drain tube (Ref. TASK 71-73-49-400-008) - hydraulic pump drain tube (Ref. TASK 71-73-49-400-028) - IDG pad drain tube (Ref. TASK 71-73-49-400-004) - starter pad drain tube (Ref. TASK 71-73-49-400-003) - forward sump drain tube (Ref. TASK 71-73-49-400-029). (13) Install the drain manifold module (Ref. TASK 71-71-43-400-041). (14) Install the fan fire detector (Ref. TASK 26-12-15-400-042). Subtask 72-63-00-410-068 E. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR (3) Remove the warning notice(s). Subtask 72-63-00-440-051 F. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041) Subtask 72-63-00-710-056 G. Test after the Installation (1) Do the test given in the installation of the handcranking drive cover (Ref. TASK 72-63-00-400-002). (2) Do a minimum idle check (Ref. TASK 71-00-00-710-006) and do a check for leaks during the visual inspection of the oil system (Ref. TASK 79-00-00-210-003). (3) Do a check of the oil level (Ref. TASK 12-13-79-610-002) or (Ref. TASK 12-13-79-610-002).
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C F M 56-5B (4) Do an accel check (Ref. TASK 71-00-00-710-025). 5. Close-up ________ Subtask 72-63-00-410-069 A. Close Access (1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (2) Remove the access platform(s).
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C F M 56-5B ACCESSORY GEARBOX ASSEMBLY - INSPECTION/CHECK _____________________________________________ TASK 72-63-00-210-002 Inspection/Check of the Accessory Gearbox Assembly 1. __________________ Reason for the Job Self Explanatory 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION ------------------------------------------------------------------------------No specific
warning notice
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP8001
Material No.
CP8002
* lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00) * lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)
C. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------71-13-00-010-040 71-13-00-410-040 72-63-00-300-002 72-63-00-300-003
Opening of the Closing of the Replacement of Replacement of
Fan Cowl Doors Fan Cowl Doors a Sealol Seal (Typical) a Magnetic Seal (Typical)
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C F M 56-5B 3. __________ Job Set-up Subtask 72-63-00-941-057 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-064 B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ Subtask 72-63-00-210-052 A. Inspection of the AGB external areas. ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------1. Housing for : A. Cracks
Not serviceable
B. Nicks, dents and scratches
Any number, 0.035 in. (0.9 mm) deep after removal of high metal.
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C F M 56-5B ------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS ------------------------------------------------------------------------------2. Starter pad fuel pump No leakage permitted Replace the carbon seal pad, hydraulic pump (Ref. TASK 72-63-00-300pad and IDG pad for 002) or (Ref. TASK 72-63leaks. 00-300-003) 3. Tube fittings for leaks
No leakage permitted
Tighten the fittings and/or replace the tube seals
4. AGB mounts for : A. Cracks
Not serviceable
B. Loose bushing
Not serviceable
5. Broken or missing lockwire
Not serviceable
Replace the lockwire lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8002).
6. Key-lock studs for: A. Missing
Not serviceable
5. Close-up ________ Subtask 72-63-00-410-060 A. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR (3) Remove the warning notice(s).
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C F M 56-5B ACCESSORY GEARBOX ASSEMBLY - REPAIRS ____________________________________ TASK 72-63-00-300-002 Replacement of a Sealol Seal (Typical) 1. __________________ Reason for the Job To replace a leaky sealol seal assembly by an other sealol seal assembly at: - the IDG drive pad - the hydraulic pump drive pad - the fuel pump drive pad - the starter drive pad NOTE : You can find two types of carbon seal installed on these Accessory ____ Gearbox (AGB) drive pads: a sealol seal assembly or a magnetic seal assembly. You can replace a sealol seal assembly either, by a new sealol seal assembly or, as an alternate, by a new magnetic seal assembly. If you replace a sealol seal by a magnetic seal, remove the sealol seal as specified in this procedure. If, as a replacement, you install a magnetic seal on the hydraulic pump and/or the fuel pump drive pad, make sure you install the correct type of magnetic seal (the one without the thrust ring added). Then, refer to the related installation paragraph. If, as a replacement, you install a magnetic seal on the Integrated Drive Generator (IDG) and/or starter drive pad, make sure you install the correct type of magnetic seal (the one equipped with a thrust ring). Then, refer to the related installation paragraph. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
856A1130 856A3576
slide hammer storage box warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 TOOL SET - JACK SCREW 2 SEALOL AND MAGNETIC SEALS-R/I
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C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2442
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-L-5544 graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------10
O-ring
72-63-00 02 -040
10 10
O-ring O-ring
72-63-00 03 -030 72-63-00 03 -030A
10
O-ring
72-63-00 05A-140
10 10 15 15
O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00
15 15
O-ring O-ring
72-63-00 06A-080 72-63-00 06A-080A
R R R 06A-080 06A-080A 03 -030 03 -030A
R
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Page 802 Feb 01/10
C F M 56-5B ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------30 30 30 30
O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00
02 02 02 02
-050 -050A -050B -050C
30 30
O-ring O-ring
72-63-00 03 -040 72-63-00 03 -040A
30 30 30 30 30 30 30 30
O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00
R R
R
05A-150 05A-150A 05A-150B 05A-150C 06 -060 06 -060A 06A-060 06A-060A
D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-21-51-000-040 24-21-51-400-040 29-11-51-000-041 29-11-51-400-041 71-00-00-790-002 71-00-00-790-006 71-13-00-010-040 71-13-00-410-040 73-11-10-000-003 73-11-10-400-003 80-11-10-000-002 80-11-10-400-002 72-63-00-991-305 72-63-00-991-306
Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) Removal of the Green Engine Pump (1030GK) Installation of the Green Engine Pump (1030GK) Fuel or Hydraulic or Oil Leakage Limits Leak Check after the Replacement of a Sealol Seal or a Magnetic Seal on the AGB Drive Pads of the IDG, Hydraulic Pump, Starter and Fuel Pump Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Fuel Pump and Filter Assembly Installation of the Fuel Pump and Filter Assembly Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. 801 Fig. 802
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 803 Feb 01/10
C F M 56-5B 3. __________ Job Set-up Subtask 72-63-00-941-058 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2). Subtask 72-63-00-010-065 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 801/TASK 72-63-00-991-305, 802/TASK 72-63-00-991-306) Subtask 72-63-00-020-058 A. Preparation for the Removal of the Sealol Seal Assembly (1) Depending on the drive pad on which you have to replace the sealol seal assembly, remove one of these units: - fuel pump (Ref. TASK 73-11-10-000-003) - hydraulic pump (Ref. TASK 29-11-51-000-041) - IDG (Ref. TASK 24-21-51-000-040) - starter (Ref. TASK 80-11-10-000-002)
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 804 Feb 01/10
C F M 56-5B
Sealol Seal Assembly (Typical) Figure 801/TASK 72-63-00-991-305 EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 805 Feb 01/10
C F M 56-5B
Removal/Istallation of a Sealol Seal Rotating Mating Ring (Typical) Figure 802/TASK 72-63-00-991-306 EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 806 Feb 01/10
C F M 56-5B Subtask 72-63-00-020-059 B. Removal of the Sealol Seal Housing Assembly (1) Remove the 3 nuts (60) and washers (50) which attach the sealol seal housing assembly (40) to the drive pad. (2) Remove the sealol seal housing assembly (40) with the jackscrews P12 from the TOOL SET - JACK SCREW (856A1130G09). Remove and discard O-ring (30). (3) Put the removed parts (60), (50) and (40) in the storage box. Subtask 72-63-00-020-060 C. Removal of the Rotating Mating Ring Assembly (1) Depending on the drive pad from which you remove the rotating mating ring assembly, get the applicable tool diameter configuration from the tool set, SEALOL AND MAGNETIC SEALS-R/I (856A3576G01). - for the fuel pump and hydraulic pump drive pads, use the smaller diameter tool with the items P09, P10 and P11 - for the starter and IDG drive pads, use the larger diameter tool with the items P02, P03 and P06. (2) Loosen the tool items: - P06 and P05 (larger diameter tool) or - P11 and P05 (smaller diameter tool). (3) Engage the tool on the gearshaft until the nylon/viton-end of item: - P02 (larger diameter tool) or - P09 (smaller diameter tool) Comes against the polished face of the rotating mating ring. (4) Tighten the item P05 by hand until you feel the jaws of the collet are tightly engaged under the mating ring. Manually give the tool one or two pulls to make sure it is correctly installed. If so, it must not come out. (5) Install the slide hammer on top of the tool. Operate the slide hammer and remove the rotating mating ring assembly from the gearshaft. PRE SB CFM 72-105
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 807 Feb 01/10
C F M 56-5B (6) Remove the O-ring (10) from the inner diameter groove of the rotating mating ring (20). Discard the O-ring (10). POST SB CFM 72-105 (7) Remove the bal seal (15) from the inner diameter groove of the rotating mating ring (20) for the IDG pad and starter pad. Discard the bal seal (150). Remove the O-ring (10) from the inner diameter groove of the rotating mating ring (20) for the fuel pump pad and hydraulic pump pad. Discard the O-ring (10). END OF SB CFM 72-105 (8) Loosen the items: - P06 and P05 (larger diameter tool) or - P11 and P05 (smaller diameter tool) And remove the rotating mating ring (20) from tool (856A3576G01). Put the mating ring (20) in the storage box. Subtask 72-63-00-020-061 D. Disposal of the Removed Sealol Seal Components (1) Tag the removed parts (40) and (20) to indicate they come from the same matched assembly. (2) Put the removed parts in a storage box and send them to the repair shop. Subtask 72-63-00-420-059 E. Preparation for the Installation of the Sealol Seal Assembly (1) Get a new sealol seal assembly corresponding to the diameter of the drive pad on which you do the replacement. (2) Clean the gearshaft area CAUTION : DO NOT USE THIS SOLVENT NEAR FLAMES OR HEAT, BECAUSE THIS _______ SOLVENT IS FLAMMABLE. DO NOT BREATHE THE GASES RELEASED FROM SOLVENT, DO NOT LET IT TOUCH YOUR SKIN OR CLOTHING AND MAKE SURE YOU HAVE A GOOD FLOW OF AIR, BECAUSE THIS SOLVENT IS DANGEROUS TO YOUR SKIN, EYES AND LUNGS.
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 808 Feb 01/10
C F M 56-5B (a) Clean the gearshaft area to come in contact with the new rotating mating ring (20) with acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or mag-chem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656). (3) Lubricate the same gearshaft area with engine oil (Material No. CP2442). Subtask 72-63-00-420-060 F. Installation of the Rotating Mating Ring Assembly CAUTION : USE CLEAN COTTON GLOVES WHEN YOU HANDLE THE COMPONENTS OF A _______ SEALOL SEAL ASSEMBLY TO PREVENT CONTAMINATION. AT INSTALLATION, MAKE SURE THAT THE FACE OF THE ROTATING MATING RING WHICH TOUCHES THE CARBON RING IS THE POLISHED SURFACE. CAUTION : THERE ARE TWO CONFIGURATIONS OF SEALOL SEAL (SB CFM 72-105). _______ THE O-RING OR BAL SEAL ARE MATCHED TO THEIR ROTATING RING. THEY ARE NOT INTERCHANGEABLE. PRE SB CFM 72-105 (1) Remove the new rotating mating ring (20) from its packaging. Apply a thin layer of engine oil (Material No. CP2442) to the following new O-rings: - O-ring (10) for the fuel pump pad, - O-ring (10) for the starter pad, - O-ring (10) for the IDG pad, - O-ring (10) for the hydraulic pump pad. Install the O-ring (10) in the inner diameter groove of rotating ring (20). POST SB CFM 72-105 (2) Installation of the new O-ring and new bal seal. CAUTION : BE CAREFUL WHEN YOU INSTALL THE BAL SEAL (15) IN THE GROOVE _______ OF SEALOL SEAL ROTATING RING (20) BECAUSE THE BAL SEAL IS EASILY DAMAGED. CAUTION : MAKE SURE THAT THE OPENING OF THE BAL SEAL (15) IS TOWARDS _______ THE TABS OF SEALOL SEAL ROTATING RING (20). OTHERWISE IMPORTANT OIL LEAKAGE CAN OCCUR.
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 809 Feb 01/10
C F M 56-5B (a) Remove the new rotating mating ring (20) from its packaging. Apply a thin layer of engine oil (Material No. CP2442) to the following new O-rings and new bal seal: - O-ring (10) for the fuel pump pad, - O-ring (15) for the starter pad, - O-ring (15) for the IDG pad, - O-ring (10) for the hydraulic pump pad. Install the O-ring (10) in the inner diameter groove of rotating ring (20) for the fuel pump pad and hydraulic pump pad. Install the bal seal (15) in the inner diameter groove of rotating ring (20) the IDG pad and starter pad. END OF SB CFM 72-105 (3) Depending on the diameter of the new rotating mating ring assembly you install, get the applicable tool diameter configuration from the SEALOL AND MAGNETIC SEALS-R/I (856A3576G01). (4) Put the new mating ring (20) on the applicable tool, (856A3576G01), as follows: - loosen the items P06 and P05 (larger diameter tool) or P11 and P05 (smaller diameter tool) - put the new mating ring (20) on the tool, its polished face in contact with the nylon/viton end of item P02 (larger diameter tool) or P09 (smaller diameter tool) - tighten the item P05 by hand until the rotating mating ring (20) is held tightly in the collet of item P02 or P09. (5) Engage the tool and mating ring assembly on the gearshaft. Turn the tool with the handle until you feel the slots of the rotating mating ring (20) engage the lugs of the gearshaft bearing. (6) Turn the tool clockwise then counterclockwise to make sure that the lugs of the rotating mating ring are correctly engaged in the slots of the bearing (inner race). (7) Loosen the items P06 and P05 (or P11 and P05) and remove the tool. (8) Lubricate the polished face of the rotating mating ring (20) with engine oil (Material No. CP2442).
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, R CES
Page 810 Feb 01/10
C F M 56-5B Subtask 72-63-00-420-061 G. Installation of the Sealol Seal Housing Assembly CAUTION : AT INSTALLATION, MAKE SURE THAT PARTICLES, EVEN OF EXTREMELY _______ SMALL SIZE, ARE NOT LEFT BETWEEN THE POLISHED FACE OF THE ROTATING MATING RING AND THE CARBON RING FACE OF THE SEALOL SEAL HOUSING ASSEMBLY. OTHERWISE, LEAKS WILL OCCUR. CAUTION : USE CLEAN COTTON GLOVES TO HANDLE THE SEALOL SEAL HOUSING _______ ASSEMBLY. CAUTION : THE INSTALLATION OF THE SEALOL SEAL HOUSING (40) MUST BE DONE _______ BY HAND AND WITHOUT SHOCKS TO PREVENT DAMAGE TO THE CARBON RING. (1) Lubricate a new O-ring (30) for the IDG drive pad or O-ring (30) for the hydraulic pump drive pad or O-ring (30) for the fuel pump drive pad or O-ring (30) for the starter drive pad with engine oil (Material No. CP2442) and install in the outer diameter groove of sealol seal housing assembly (40).
R
(2) Manually engage the housing assembly (40) in the bore of the pad until the O-ring (30) is fully against the entrance of the bore. (3) Apply a thin layer of graphite grease (Material No. CP2101) to the 3 studs of the pad. (4) Install the 3 washers (50) on the 3 studs. Engage the 3 nuts (60) on the studs and tighten continuously the nuts, each in small increments, until the flange of the housing assembly comes in contact with its mating face on the pad. (5) TORQUE the nuts (60) to between 55 and 60 lbf.in (0.62 and 0.67 m.daN). (6) Depending on the drive pad on which you have replaced the sealol seal assembly, install one of these units: - fuel pump (Ref. TASK 73-11-10-400-003) - hydraulic pump (Ref. TASK 29-11-51-400-041) - IDG (Ref. TASK 24-21-51-400-040) - starter (Ref. TASK 80-11-10-400-002)
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 811 Aug 01/09
C F M 56-5B Subtask 72-63-00-410-061 H. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-63-00-710-054 J. Do a leak check of the replacement seal (Ref. TASK 71-00-00-790-006). If there are leaks (Ref. TASK 71-00-00-790-002). 5. Close-up ________ Subtask 72-63-00-942-050 A. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 812 Nov 01/08
C F M 56-5B TASK 72-63-00-300-003 Replacement of a Magnetic Seal (Typical) 1. __________________ Reason for the Job To replace a leaky magnetic seal by another magnetic seal at: - the Integrated Drive Generator (IDG) drive pad - the hydraulic pump drive pad - the fuel pump drive pad - the starter drive pad. NOTE : You can find two types of carbon seal installed on ____ Gearbox (AGB) drive pads: a magnetic seal assembly assembly. You can replace a magnetic seal assembly magnetic seal assembly (the one without the thrust an alternative, by a new sealol seal assembly.
these Accessory or a sealol seal either, by a new ring added) or, as
If you replace a magnetic seal by a sealol seal, remove the magnetic seal as specified in this procedure. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
slide hammer storage box warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 TOOL SET - JACK SCREW 1 SEALOL AND MAGNETIC SEALS-R/I
856A1130 856A3576
B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2442
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) *
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 813 Nov 01/09
C F M 56-5B ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
engine oil (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN ------------------------------------------------------------------------------70 70 70 70
O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00
02 02 03 03
-060 -060A -060 -060A
70 70 70 70 90 90 90 90
O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00
05A-170 05A-170A 06A-110 06A-110A 02 -070 02 -070A 03 -070 03 -070A
90 90 90 90
O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00
05A-160 05A-160A 06 -120 06 -120A
R R
R R R R R
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 814 Feb 01/10
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-21-51-000-040 24-21-51-400-040 29-11-51-000-041 29-11-51-400-041 71-00-00-790-002 71-00-00-790-006 71-13-00-010-040 71-13-00-410-040 73-11-10-000-003 73-11-10-400-003 80-11-10-000-002 80-11-10-400-002 72-63-00-991-307 72-63-00-991-308
Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) Removal of the Green Engine Pump (1030GK) Installation of the Green Engine Pump (1030GK) Fuel or Hydraulic or Oil Leakage Limits Leak Check after the Replacement of a Sealol Seal or a Magnetic Seal on the AGB Drive Pads of the IDG, Hydraulic Pump, Starter and Fuel Pump Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Fuel Pump and Filter Assembly Installation of the Fuel Pump and Filter Assembly Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. 803 Fig. 804
3. __________ Job Set-up Subtask 72-63-00-941-060 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 815 Nov 01/08
C F M 56-5B Subtask 72-63-00-010-069 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 803/TASK 72-63-00-991-307, 804/TASK 72-63-00-991-308) Subtask 72-63-00-020-062 A. Preparation for the Removal of a Magnetic Seal (1) Depending on the drive pad on which you have to replace the magnetic seal assembly, remove one of these units: - Hydraulic pump (Ref. TASK 29-11-51-000-041) - Fuel pump (Ref. TASK 73-11-10-000-003) - IDG (Ref. TASK 24-21-51-000-040) - Starter (Ref. TASK 80-11-10-000-002) Subtask 72-63-00-020-063 B. Removal of the Magnetic Seal Housing Assembly (1) Remove the 3 nuts (110) and washers (100) which attach the magnetic seal housing assembly (120) to the pad. (2) Remove the magnetic seal housing assembly with jackscrews P2 from the TOOL SET - JACK SCREW (856A1130G06). (3) Remove and discard O-ring (90). Subtask 72-63-00-020-064 C. Removal of the Carbon Ring Assembly (1) Prepare the tool set SEALOL AND MAGNETIC SEALS-R/I (856A3576G01) with handle P12, sleeve P13, and collet P15. (2) Engage tool assembly in the AGB drive pad, until the jaws of the collet are behind the carbon ring assembly (80). (3) Tighten the sleeve by hand until the collet is tight against the carbon ring assembly (80).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 816 Nov 01/08
C F M 56-5B
Magnetic Seal Assembly (Typical) Figure 803/TASK 72-63-00-991-307 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 817 Nov 01/08
C F M 56-5B
Removal of a Magnetic Seal Carbon Ring Assembly (Typical) Figure 804/TASK 72-63-00-991-308 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 818 Nov 01/08
C F M 56-5B (4) Attach the slide hammer to the handle and remove the carbon ring assembly (80) from the gearshaft. (5) Loosen the sleeve and remove the carbon ring assembly (80), from the tool. (6) Remove and discard the O-ring (70). (7) Put the removed parts in a storage box and send them to the repair shop. Subtask 72-63-00-420-062 D. Installation of the Magnetic Seal Assembly (type without the thrust ring) CAUTION : DO NOT USE THIS SOLVENT NEAR _______ SOLVENT IS FLAMMABLE. DO NOT SOLVENT, DO NOT LET IT TOUCH SURE YOU HAVE A GOOD FLOW OF DANGEROUS TO YOUR SKIN, EYES
FLAMES OR HEAT, BECAUSE THIS BREATHE THE GASES RELEASED FROM YOUR SKIN OR CLOTHING AND MAKE AIR, BECAUSE THIS SOLVENT IS AND LUNGS.
(1) With acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or magchem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) remove the coked oil which possibly remains on the gearshaft area related to the rotary part of the magnetic seal, to prevent possible damage to the O-ring (70) at installation. (2) Get a new magnetic seal assembly. CAUTION : USE GLOVES WHEN YOU HANDLE THE MAGNETIC SEAL COMPONENTS TO _______ PREVENT CONTAMINATION. MAKE SURE THAT THE FACE OF THE MAGNETIC SEAL WHICH TOUCHES THE CARBON RING IS THE POLISHED SURFACE. (a) Remove the magnetic seal assembly from its packaging. (3) Lubricate a new O-ring (70) for the IDG drive pad or O-ring (70) for the hydraulic fuel pump drive pad or O-ring (70) for the fuel pump drive pad or O-ring (70) for the starter drive pad with engine oil (Material No. CP2442). Install the O-ring (70) in the inner groove of the carbon ring assembly (80).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 819 Nov 01/08
C F M 56-5B (4) Lubricate a new O-ring (90) for the IDG drive pad or O-ring (90) for the hydraulic pump drive pad or O-ring (90) for the fuel pump drive pad or O-ring (90) for the starter drive pad with engine oil (Material No. CP2442). Install the O-ring (90) in the outer groove of the magnetic seal housing assembly (120). (5) Lubricate the carbon ring mating face and the gearshaft with engine oil (Material No. CP2442). CAUTION : MAKE SURE THAT PARTICLES; EVEN OF EXTREMELY SMALL SIZE, ARE _______ NOT LEFT BETWEEN THE POLISHED FACE OF THE MAGNETIC RING AND THE CARBON FACE OF THE ROTATING RING ASSEMBLY DURING INSTALLATION. OTHERWISE LEAK CAN OCCUR. CAUTION : DO NOT HIT THE CARBON MATING FACE OR SLIDE IT ON THE _______ MAGNETIC MATING RING WHEN YOU INSTALL THE CARBON RING ASSEMBLY. (a) Very carefully, install the carbon ring assembly (80) against the polished face of the magnetic ring. CAUTION : DO NOT HIT THE MAGNETIC SEAL HOUSING DURING THE _______ INSTALLATION TO PREVENT DAMAGE TO THE MAGNETIC SEAL COMPONENTS. 1 _
Align the carbon ring assembly with the housing bore.
(b) Engage the magnetic seal assembly on the gearshaft until the O-ring (90) of the housing is fully against the AGB pad. (6) Lubricate the threads of the 3 studs with graphite grease (Material No. CP2101). (7) Install washers (100) and nuts (110) and continuously install the magnetic seal assembly until the housing flange is fully against the AGB pad. (8) TORQUE the nuts (110) to between 55 and 60 lbf.in (0.62 and 0.67 m.daN). (9) Depending on the drive pad on which you have replaced the magnetic seal assembly, install one of these units: - IDG (Ref. TASK 24-21-51-400-040) - hydraulic pump (Ref. TASK 29-11-51-400-041) - fuel pump (Ref. TASK 73-11-10-400-003) - Starter (Ref. TASK 80-11-10-400-002)
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 820 Nov 01/08
C F M 56-5B Subtask 72-63-00-410-065 E. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-63-00-710-055 F. Do a leak check of the replacement seal (Ref. TASK 71-00-00-790-006). If there are leaks (Ref. TASK 71-00-00-790-002). 5. Close-up ________ Subtask 72-63-00-942-051 A. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 821 Nov 01/08
C F M 56-5B TASK 72-63-00-300-004 Replacement of a Magnetic Seal (IDG and Starter Drive Pads). 1. __________________ Reason for the Job To replace a leaky magnetic seal by another magnetic seal at: - the Integrated Drive Generator (IDG) drive pad, - the starter drive pad. NOTE : You can find two types of carbon seal installed on these Accessory ____ Gearbox (AGB) drive pads: a magnetic seal assembly or a sealol seal assembly. You can replace a magnetic seal assembly either, by a new magnetic seal assembly (the one equipped with a thrust ring) or, as an alternate, by a new sealol seal assembly. If you replace a magnetic seal by a sealol seal, remove the magnetic seal as specified in this procedure and go to (Ref. TASK 72-63-00-300-00200) for the installation of the sealol seal. 2. ______________________ Job Set-up Information A. Fixtures, Tools, Test and Support Equipment ------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
R R
No No No No
specific specific specific specific
856A1130 856A3576
slide hammer storage box warning notice Torque Wrench : range 30.00 to 220.00 lbf.in (0.34 to 2.60 m.daN) 1 TOOL SET - JACK SCREW 1 SEALOL AND MAGNETIC SEALS-R/I
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 822 Nov 01/09
C F M 56-5B B. Consumable Materials ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------Material No.
CP1039
Material No.
CP1041
Material No.
CP2011
Material No.
CP2101
Material No.
CP2442
Material No.
CP2559
Material No.
CP2560
Material No.
CP2566
Material No.
CP2584
Material No.
CP2656
* acetone (Ref. 70-30-00) * isopropyl alcohol (Ref. 70-30-00) * stoddard solvent (Ref. 70-30-00) USA MIL-T-5544 graphite grease (Ref. 70-30-00) * engine oil (Ref. 70-30-00) * ardrox 552 (Ref. 70-30-00) * turco ind 79 (Ref. 70-30-00) * mag-chem teksol (Ref. 70-30-00) * degreasol 99 R (Ref. 70-30-00) * mag-chem skysol (Ref. 70-30-00)
C. Expendable Parts ------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN -------------------------------------------------------------------------------
R R R
130 130 130 130 150 150 150 150
O-ring O-ring O-ring O-ring O-ring O-ring O-ring O-ring
72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00 72-63-00
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
03 -060 03 -060A 06A-110 06A-110A 03 -070 03 -070A 06 -120 06 -120A
Page 823 Feb 01/10
C F M 56-5B D. Referenced Information ------------------------------------------------------------------------------REFERENCE DESIGNATION ------------------------------------------------------------------------------24-21-51-000-040 24-21-51-400-040 71-00-00-790-002 71-00-00-790-006 71-13-00-010-040 71-13-00-410-040 80-11-10-000-002 80-11-10-400-002 72-63-00-991-315 72-63-00-991-316
Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) Fuel or Hydraulic or Oil Leakage Limits Leak Check after the Replacement of a Sealol Seal or a Magnetic Seal on the AGB Drive Pads of the IDG, Hydraulic Pump, Starter and Fuel Pump Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Pneumatic Starter Installation of the Pneumatic Starter Fig. 805 Fig. 806
3. __________ Job Set-up Subtask 72-63-00-941-063 A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a warning notice to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. (b) Put a warning notice to tell persons not to energize the FADEC 1(2).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 824 Nov 01/08
C F M 56-5B Subtask 72-63-00-010-072 B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 4. Procedure _________ (Ref. Fig. 805/TASK 72-63-00-991-315, 806/TASK 72-63-00-991-316) Subtask 72-63-00-020-066 A. Preparation for the Removal of a Magnetic Seal (1) Depending on the drive pad on which you have to replace the magnetic seal assembly, remove one of these units: - IDG (Ref. TASK 24-21-51-000-040) - starter (Ref. TASK 80-11-10-000-002) Subtask 72-63-00-020-067 B. Removal of the Magnetic Seal Housing Assembly (1) Remove the 3 nuts (170) and washers (160) which attach the magnetic seal housing assembly (180) to the pad. (2) Remove the magnetic seal housing assembly (180) with jackscrews P2 from the TOOL SET - JACK SCREW (856A1130G06). (3) Remove and discard O-ring (150). Subtask 72-63-00-020-068 C. Removal of the Carbon Ring Assembly (1) Prepare the tool set SEALOL AND MAGNETIC SEALS-R/I (856A3576G01), with handle P12, sleeve P13, and collet P14. (2) Engage the tool assembly (856A3576G01), in the AGB drive pad, until the jaws of the collet are behind the carbon ring assembly (140). (3) Tighten the sleeve by hand until the collet is tight against the carbon ring assembly (140).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 825 Nov 01/08
C F M 56-5B
Magnetic Seal Assembly (Typical for the IDG and Starter Drive Pads) Figure 805/TASK 72-63-00-991-315 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 826 Nov 01/08
C F M 56-5B
Removal of the Carbon Ring Assembly (Typical, at IDG Drive Pad) Figure 806/TASK 72-63-00-991-316 R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 827 Nov 01/08
C F M 56-5B (4) Attach the slide hammer to the handle and remove the carbon ring assembly (140) from the gearshaft. (5) Loosen the sleeve and remove the carbon ring assembly (140) from the tool. (6) Remove and discard the O-ring (130). (7) Put the removed parts in a storage box and send them to the repair shop. Subtask 72-63-00-420-063 D. Installation of the Magnetic Seal Assembly (type equipped with the thrust ring) CAUTION : DO NOT USE THIS SOLVENT NEAR _______ SOLVENT IS FLAMMABLE. DO NOT SOLVENT, DO NOT LET IT TOUCH SURE YOU HAVE A GOOD FLOW OF DANGEROUS TO YOUR SKIN, EYES
FLAMES OR HEAT, BECAUSE THIS BREATHE THE GASES RELEASED FROM YOUR SKIN OR CLOTHING AND MAKE AIR, BECAUSE THIS SOLVENT IS AND LUNGS.
(1) With acetone (Material No. CP1039) or isopropyl alcohol (Material No. CP1041) or stoddard solvent (Material No. CP2011) or ardrox 552 (Material No. CP2559) or turco ind 79 (Material No. CP2560) or magchem teksol (Material No. CP2566) or degreasol 99 R (Material No. CP2584) or mag-chem skysol (Material No. CP2656) remove the coked oil which possibly remains on the gearshaft area related to the rotary part of the magnetic seal, to prevent possible damage to the O-ring (130) at installation. (2) Get a new magnetic seal assembly. CAUTION : USE GLOVES WHEN YOU HANDLE THE MAGNETIC SEAL COMPONENTS TO _______ PREVENT CONTAMINATION. MAKE SURE THAT THE FACE OF THE MAGNETIC SEAL WHICH TOUCHES THE CARBON RING IS THE POLISHED SURFACE. (a) Remove the magnetic seal assembly from its packaging. (3) For the starter drive pad: - lubricate a new O-ring (130) with engine oil Install the O-ring (130) in the inner groove assembly (140). - lubricate a new O-ring (150) with engine oil Install the O-ring (150) in the outer groove housing assembly (180).
R
(Material No. CP2442). of the carbon ring (Material No. CP2442). of the magnetic seal
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 828 Feb 01/09
R
C F M 56-5B (4) For the IDG drive pad: - lubricate a new O-ring (130) with engine oil Install the O-ring (130) in the inner groove assembly (140) - lubricate a new O-ring (150) with engine oil Install the O-ring (150) in the outer groove housing assembly (180).
(Material No. CP2442). of the carbon ring (Material No. CP2442). of the magnetic seal
(5) Lubricate the carbon ring mating face and the gearshaft with engine oil (Material No. CP2442). CAUTION : MAKE SURE THAT PARTICLES; EVEN OF EXTREMELY SMALL SIZE, ARE _______ NOT LEFT BETWEEN THE POLISHED FACE OF THE MAGNETIC RING AND THE CARBON FACE OF THE ROTATING RING ASSEMBLY DURING INSTALLATION. OTHERWISE LEAK CAN OCCUR. CAUTION : DO NOT HIT THE CARBON MATING FACE OR SLIDE IT ON THE _______ MAGNETIC MATING RING WHEN YOU INSTALL THE CARBON RING ASSEMBLY. (a) Very carefully, install the carbon ring assembly (140) against the polished face of the magnetic ring. CAUTION : DO NOT HIT THE MAGNETIC SEAL HOUSING DURING THE _______ INSTALLATION TO PREVENT DAMAGE TO THE MAGNETIC SEAL COMPONENTS. 1 _
Align the carbon ring assembly with the housing bore.
(6) Engage the magnetic seal assembly on the gearshaft until the O-ring (150) of the housing is fully against the AGB pad. (7) Lubricate the threads of the 3 studs with graphite grease (Material No. CP2101). (8) Install washers (160) and nuts (170) and continuously install the magnetic seal assembly until the housing flange is fully against the AGB pad. (9) TORQUE the nuts (170) to between 55 and 60 lbf.in (0.62 and 0.67 m.daN). (10) Depending on the drive pad on which you have replaced the magnetic seal assembly, install one of these units: - IDG (Ref. TASK 24-21-51-400-040) - starter (Ref. TASK 80-11-10-400-002)
EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 829 Feb 01/09
C F M 56-5B Subtask 72-63-00-410-070 E. Close Access (1) Make sure that the work area is clean and clear of tool(s) and other items. (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR Subtask 72-63-00-710-058 F. Do a leak check of the replacement seal (Ref. TASK 71-00-00-790-006). If there are leaks (Ref. TASK 71-00-00-790-002). 5. Close-up ________ Subtask 72-63-00-942-052 A. Remove the warning notice(s).
R EFF : 001-049, 051-099, 101-149, 151-199, 72-63-00 201-249, 251-299, 301-399, 401-499, CES
Page 830 Nov 01/08
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