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Commercial Airplanes 747 Service Bulletin ALERT Number: 747-57A2360 Original Issue: January 20, 2017 Revision 1: February 09, 2022 ATA System: 5715 SUBJECT: WINGS - Landing Gear Support Beam - Fuse Pin - Inspection and Replacement EXPORT CONTROLLED - This technology or software is subject to the U.S. Export Administration Regulations (EAR), (15 C.F.R. Parts 730-774). No authorization from the U.S. Department of Commerce is required for export, re-export, in-country transfer, or access EXCEPT to country group E:1 or E:2 countries/persons per Supp.1 to Part 740 of the EAR.
9E991ECCN:
Copyright © 2017 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
Original Issue: January 20, 2017 747-57A2360Revision 1: February 09, 2022 1 of 206
5.0
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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Table of Contents
Revision Transmittal Sheet5
S u m m a r y9
1. PLANNING INFORMATION ........................................ 1 5 A . E f f e c t i v i t y ............................................... 1 5
1. Airplanes ............................................ 1 5 2 . S p a r e s A f f e c t e d ........................................ 1 9 B. Concurrent Requirements ...................................... 1 9 C. Reason ................................................ 1 9 D. Description .............................................. 2 0 E. Compliance .............................................. 2 3 F . A p p r o v a l ............................................... 7 8 G. Manpower .............................................. 7 9 H. Weight and Balance Changes .................................... 8 1 I. Electrical Load Data ......................................... 8 1 J . R e f e r e n c e s .............................................. 8 1
1. Existing Data: ......................................... 8 1
2. Data Supplied with this Service Bulletin: ........................... 8 1
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 8 2 K. Publications Affected ........................................ 8 2 L. Interchangeability and Intermixability of Parts ........................... 8 2 M. Software Accomplishment Summary ................................ 8 2
2. MATERIAL INFORMATION ........................................ 8 3 A. Material - Price and Availability ................................... 8 3 B. Industry Support Information .................................... 8 3 C. Parts Necessary for Each Airplane ................................. 8 3 1 . K i t s / P a r t s ............................................ 8 3
2. Parts and Materials Supplied by the Operator ........................ 8 3
3. Parts Modified and Reidentified ................................ 8 5
4. Parts Removed and Not Replaced .............................. 8 5 D. Parts Necessary to Change Spares ................................. 8 5 E. Special Tooling - Price and Availability ............................... 8 5 F. Special Tooling Necessary to do this Service Bulletin ....................... 8 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 8 7 A. GENERAL INFORMATION ..................................... 8 7 B. WORK INSTRUCTIONS ....................................... 8 9 FIGURE 1: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN ................. 9 6 FIGURE 2: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL .................................................. 9 8 FIGURE 3: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL ................................................. 1 0 2 FIGURE 4: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF FUSE PIN . 106 F I G U R E 5 : D E L E T E D........................................... 1 0 8 FIGURE 6: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - INSTALLATION ................................................. 1 0 9 FIGURE 7: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - INSTALLATION ........................................ 1 1 3 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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FIGURE 8: ULTRASONIC (UT) INSPECTION OF FUSE PIN ...................... 1 1 7 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 1 [Group 8] ..... 1 1 9 APPENDIX B: JACKING PROCEDURE FOR FUSE PIN REMOVAL [Group 1-8] ............. 1 2 8 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 2 [Group 3] ..... 1 2 9 APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 3 [Group 3] ..... 1 4 3 APPENDIX E: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 4 [Group 9] ..... 1 5 4 APPENDIX F: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 5 [Group 8] ..... 1 5 9 APPENDIX G: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 6 [Group 9] ..... 1 6 8 APPENDIX H: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 7 [Group 1-2, 5, 7] . 177 APPENDIX I: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 8 [Group 1-2, 5, 7] . 183 APPENDIX J: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 9 [Group 4, 6] .... 1 8 4 APPENDIX K: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 10 [Group 4, 6] . . . 195 APPENDIX L: JACKING PROCEDURE FOR FUSE PIN REMOVAL [Group 9] .............. 2 0 6 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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Commercial Airplanes 747 Service Bulletin ALERT Revision Transmittal SheetNumber: 747-57A2360Original Issue: January 20, 2017 Revision 1: February 09, 2022 ATA System: 5715 SUBJECT: WINGS - Landing Gear Support Beam - Fuse Pin - Inspection and Replacement This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-18-05 is related to this service bulletin.
The effective date of AD 2017-18-05 is October 5, 2017.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
Effects of this Revision on airplanes on which Original Issue was previously done:
Airplanes in groups 1-8 with CRES fuse pin installed requires ultrasonic testing (UT) inspection when performing surface HFEC inspection of fuse pin and airplanes with Alloy Steel fuse pin installed requires replacement with new Alloy Steel fuse pin.
Airplanes with line numbers 1308-1308 1313-1313 1315-1315 1317-1318 1320-1321 1326-1326 1328-1331 1338-1338 1340-1341 1344-1344 1347-1347 1350-1350 1361-1361 1365-1365 1368-1368 1375-1377 1380-1383 1386-1387 1389-1389 1391-1392 1395-1395 1398-1400 1402-1402 1404-1404 1409-1409 1413-1417 1419-1419 were moved from Group 3 to Group 8 of this service bulletin effectivity.
Airplanes with line numbers 1420-1574 were added to Group 9 of this service bulletin effectivity.
REASON FOR REVISION This revision is sent to add 747-8/-8F airplanes, with 115U8227-1 fuse pins installed in production, to the effectivity of this service bulletin and revise the service bulletin effectivity for 747-400/-400F airplanes. 747-8/-8F airplanes have a similar fuse pin in the same location as on the 747-400. Analysis shows these fuse pins to be susceptible to fatigue cracks on the inner and outer surfaces.
The data given in Information Notice 747-57A2360 IN 01 is included in this revision.
These sections were changed:
1. Summary, Background, added new 747-8 information and Boeing Service Related Problem (SRP).
2. Summary, Action, added ultrasonic testing (UT) inspection.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017 747-57A2360Revision 1: February 09, 2022 5 of 206
3. Summary, Effectivity, statement updated.
4. Summary, Compliance, added information and Federal Aviation Authority (FAA) Airworthiness Directive (AD) reference.
5. Paragraph 1.A.1., Airplanes, added airplanes, new group and new configurations.
6. Paragraph 1.C., Reason, added Revision 1 information and Boeing Service Related Problem (SRP).
7. Paragraph 1.D., Description, added ultrasonic testing (UT) inspection.
8. Paragraph 1.E., Compliance, added FAA AD reference and logic diagram information.
9. Paragraph 1.E., Compliance Tables 1-10, revised compliance for groups 1-8, added new compliance for new airplanes, and UT inspection added.
10. Paragraph 1.F., Approval, added FAA AD Alternative Method of Compliance statement.
11. Paragraph 1.G., Manpower, changed for new work.
12. Paragraph 1.J., References, added references.
13. Paragraph 2.C.2., Parts and Materials Supplied by the Operator, updated and added additional tables for new airplanes.
14. Paragraph 3.A., General Information, revised information.
15. Paragraph 3.B., Work Instructions, changed work instructions to include new UT inspection, added information and applicability.
16. Figure 1: Changed illustration inspection area.
17. Figure 2: Added AMM procedure.
18. Figure 3: Added AMM procedure.
19. Figure 4: Changed HFEC inspection requirements.
20. Figure 5: Deleted.
21. Figure 6: Added AMM procedure.
22. Figure 7: Added AMM procedure.
23. Figure 8: Added new UT inspection.
24. Appendix A: Added applicability and revised logic diagram.
25. Appendix B: Added applicability.
26. Appendix C-G: Added new logic diagram.
27. Appendix G: Added applicability and jacking information.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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The data given in Information Notice 747-57A2360 IN 01 is included in this revision.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY January 20, 2017Original Issue:
February 09, 2022Revision 1:
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Commercial Airplanes 747 Service Bulletin ALERT SummaryNumber: 747-57A2360Original Issue: January 20, 2017 Revision 1: February 09, 2022 ATA System: 5715 SUBJECT: WINGS - Landing Gear Support Beam - Fuse Pin - Inspection and Replacement
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER.
CONCURRENT REQUIREMENTS None.
BACKGROUND Accomplishment of this service bulletin will make sure there is no crack in the fuse pin of the wing landing gear beam end fitting. An undetected crack in a fuse pin can cause the fuse pin to break. A broken fuse pin will not support the wing landing gear beam, causing damage to the surrounding structure, including flight control cables and hydraulic systems. Damage to the hydraulic systems and control cables could result in loss of controllability of the airplane.
One operator reported to Boeing that during a walk-around after a flight, the operator found damage to the lower trailing edge panels of the left wing of a 747-400 airplane. Further inspection revealed that the left wing landing gear beam end fitting fuse pin had broken into two pieces. The airplane had 17,879 flight cycles and 102,793 flight hours at the time of the failure. Boeing has done an analysis and determined that the fuse pin broke as a result of fatigue. This is the only report Boeing has received of a broken fuse pin in this location in the entire 747 fleet. 747-8/-8F airplanes have a similar fuse pin in the same location as on the 747-400. Analysis shows these fuse pins to be susceptible to fatigue cracks on the inner surface of the fuse pins, as well as the outer surface originating at the lubrication hole. Due to potential cracks originating at the lubrication hole, ultrasonic inspection (UT) is required in addition to the surface HFEC inspection of fuse pin.
This service bulletin gives instructions to inspect and replace cracked fuse pins of the wing landing gear support beam end fittings. Repeat inspections or replacements are necessary to make sure that there is no crack in the fuse pin.
Boeing Service Related Problem (SRP) 747-8-57-0329 is related to this service bulletin.
Boeing Service Related Problem (SRP) 747-57-0290 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 57-15008 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 57-18002 is related to this service bulletin.
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017 747-57A2360Revision 1: February 09, 2022 9 of 206
This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph
1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedYesPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION (PRR 86901-2RS) Do one of the following options and repeat OPTION 1, OPTION 2, OPTION 3, or OPTION 4 thereafter:
Group 1-6, 8-9:
OPTION 1: NEW CRES FUSE PIN INSTALLATION
1. Get access and remove the fuse pin.
NOTE: Jacking of the airplane is necessary to remove and replace the fuse pin.
2. Install new CRES fuse pin.
3. Close access.
Group 1-7:
OPTION 2: NEW STEEL ALLOY FUSE PIN INSTALLATION
1. Get access and remove the fuse pin.
NOTE: Jacking of the airplane is necessary to remove and replace the fuse pin.
2. Install new steel alloy fuse pin.
3. Close access.
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Group 1-6, 8-9:
OPTION 3: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN
1. Get access and remove the fuse pin.
NOTE: Jacking of the airplane is necessary to remove and do a MPI of the fuse pin.
2. Do a MPI of the fuse pin for any crack.
a. If no crack is found, install a new or serviceable CRES fuse pin.
b. If any crack is found, install a new or serviceable CRES fuse pin.
3. Close access.
Group 1-6, 8-9:
OPTION 4: SURFACE HIGH-FREQUENCY EDDY CURRENT (HFEC) AND ULTRASONIC TESTING (UT)
INSPECTION OF FUSE PIN
1. Get access to the fuse pin.
NOTE: Jacking of the airplane is not necessary to do a surface HFEC and UT inspection of the fuse pin as removal is not necessary.
2. Do a surface HFEC and UT inspection of the fuse pin for any crack.
a. If no crack is found, install kept grease plug.
b. If any crack is found, remove and install a new or serviceable CRES fuse pin.
NOTE: Jacking of the airplane is necessary to remove and replace the fuse pin.
3. Close access.
Group 1-6, 8-9:
OPTION 5: SERVICEABLE CRES FUSE PIN INSTALLATION
1. Get access and remove the fuse pin.
NOTE: Jacking of the airplane is necessary to remove and replace the fuse pin.
2. Install serviceable CRES fuse pin.
3. Close access.
EFFECTIVITY All 747-100/-100B/-100B SUD/-200B/-200C/-200F/-300/-400/-400D/-400F/747SP/747SR/-8/-8F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
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COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-18-05 is related to this service bulletin.
The effective date of AD 2017-18-05 is October 5, 2017.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection and repair procedures given in this service bulletin.
MANPOWER OPTION 1: NEW CRES FUSE PIN INSTALLATION Elapsed HoursTotal Task HoursAirplanes
10.3045.50All airplanes OPTION 2: NEW STEEL ALLOY FUSE PIN INSTALLATION Elapsed HoursTotal Task HoursAirplanes
10.3045.50All airplanes OPTION 3: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN Elapsed HoursTotal Task HoursAirplanes
12.3047.50All airplanes OPTION 4: SURFACE HIGH-FREQUENCY EDDY CURRENT (HFEC) AND ULTRA-
SONIC TESTING (UT) INSPECTION OF FUSE PIN Elapsed HoursTotal Task HoursAirplanes
10.1010.10All airplanes OPTION 5: SERVICEABLE CRES FUSE PIN INSTALLATION Elapsed HoursTotal Task HoursAirplanes
10.3045.50All airplanes Refer to Paragraph 1.G., Manpower.
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