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Commercial Airplanes 737 Service Bulletin ALERT Number: 737-57A1318 Original Issue: May 15, 2013 Revision 1: July 22, 2016 ATA System: 5715 SUBJECT: WINGS - Landing Gear Support Beam - Rear Spar and Landing Gear Support Fitting Inspection Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2013 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Unpublished Work.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: May 15, 2013 737-57A1318Revision 1: July 22, 2016 1 of 192
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Original Issue: May 15, 2013 737-57A1318Revision 1: July 22, 2016 2 of 192 BOEING SERVICE BULLETIN 737-57A1318
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Table of Contents
Revision Transmittal Sheet7
S u m m a r y ..................................................... 1 1
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 ........................................ 3 1 B. Concurrent Requirements ...................................... 3 1 C. Reason ................................................ 3 1 D. Description .............................................. 3 2 E. Compliance .............................................. 3 4 F . A p p r o v a l ............................................... 5 6 G. Manpower .............................................. 5 6 H. Weight and Balance Changes .................................... 6 1 I. Electrical Load Data ......................................... 6 1 J . R e f e r e n c e s .............................................. 6 1
1. Existing Data: ......................................... 6 1
2. Data Supplied with this Service Bulletin: ........................... 6 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 6 2 K. Publications Affected ........................................ 6 2 L. Interchangeability and Intermixability of Parts ........................... 6 3 M. Software Accomplishment Summary ................................ 6 3
2. MATERIAL INFORMATION ........................................ 6 5 A. Material - Price and Availability ................................... 6 5 B. Industry Support Information .................................... 6 5 C. Parts Necessary for Each Airplane ................................. 6 5 1 . K i t s / P a r t s ............................................ 6 5
2. Parts and Materials Supplied by the Operator ........................ 6 5
3. Parts Modified and Reidentified ................................ 7 0
4. Parts Removed and Not Replaced .............................. 7 0 D. Parts Necessary to Change Spares ................................. 7 1 E. Special Tooling - Price and Availability ............................... 7 1 F. Special Tooling Necessary to do this Service Bulletin ....................... 7 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 7 3 A. GENERAL INFORMATION ..................................... 7 3 B. WORK INSTRUCTIONS ....................................... 7 4 FIGURE 1: LEFT WING - LANDING GEAR SUPPORT BEAM - 12 FASTENER HOLE INSPECTION [Group 2, Configuration 1, 3; Group 3, Configuration 1, 3; Group 4, Configuration 1, 3; Group 5, Configuration 1, 3; Group 6, Configuration 1, 3-4; Group 7] ................. 8 3 FIGURE 2: RIGHT WING - LANDING GEAR SUPPORT BEAM - 12 FASTENER HOLE INSPECTION [Group 2, Configuration 1, 3; Group 3, Configuration 1, 3; Group 4, Configuration 1, 3; Group 5, Configuration 1, 3; Group 6, Configuration 1, 3-4; Group 7] ................. 8 4 FIGURE 3: LEFT WING - LANDING GEAR SUPPORT BEAM - 12 FASTENER HOLE INSPECTION [Group 2-6, Configuration 2] ...................................... 8 5 FIGURE 4: RIGHT WING - LANDING GEAR SUPPORT BEAM - 12 FASTENER HOLE INSPECTION [Group 2-6, Configuration 2] ...................................... 8 6 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 15, 2013 737-57A1318Revision 1: July 22, 2016 3 of 192 BOEING SERVICE BULLETIN 737-57A1318
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FIGURE 5: LEFT WING - LANDING GEAR SUPPORT BEAM - 8 FASTENER HOLE INSPECTION [Group 2-6, Configuration 3; Group 7, Configuration 1] ........................ 8 7 FIGURE 6: RIGHT WING - LANDING GEAR SUPPORT BEAM - 8 FASTENER HOLE INSPECTION [Group 2-6, Configuration 3; Group 7, Configuration 1] ........................ 8 9 FIGURE 7: LEFT WING - LANDING GEAR SUPPORT BEAM - 8 FASTENER HOLE INSPECTION [Group 2-6, Configuration 2] ...................................... 9 1 FIGURE 8: RIGHT WING - LANDING GEAR SUPPORT BEAM - 8 FASTENER HOLE INSPECTION [Group 2-6, Configuration 2] ...................................... 9 3 FIGURE 9: LEFT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING - INSPECTION OF THE 4 UPPER ROW FASTENER HOLES INSPECTED IN SB 737-57-1216 [Group 2-6, Configuration 1] ......................................... 9 5 FIGURE 10: RIGHT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING - INSPECTION OF THE 4 UPPER ROW FASTENER HOLES INSPECTED IN SB 737-57-1216 [Group 2-6, Configuration 1] ......................................... 9 7 FIGURE 11: LEFT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING - INSPECTION OF THE 4 UPPER ROW FASTENER HOLES NOT INSPECTED IN SB 737-57-1216 [Group 2-6, Configuration 1] ...................................... 9 9 FIGURE 12: RIGHT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING - INSPECTION OF THE 4 UPPER ROW FASTENER HOLES NOT INSPECTED IN SB 737-57-1216 [Group 2-6, Configuration 1] ..................................... 1 0 1 FIGURE 13: LEFT WING - LANDING GEAR SUPPORT BEAM - SURFACE INSPECTION [Group 2, Configuration 1, 3; Group 3, Configuration 1, 3; Group 4, Configuration 1, 3; Group 5, Configuration 1, 3; Group 6, Configuration 1, 3-4; Group 7] ................ 1 0 3 FIGURE 14: RIGHT WING - LANDING GEAR SUPPORT BEAM - SURFACE INSPECTION [Group 2, Configuration 1, 3; Group 3, Configuration 1, 3; Group 4, Configuration 1, 3; Group 5, Configuration 1, 3; Group 6, Configuration 1, 3-4; Group 7] ................ 1 0 5 FIGURE 15: LEFT WING - LANDING GEAR SUPPORT BEAM - SURFACE INSPECTION [Group 2-6, Configuration 2] ........................................ 1 0 7 FIGURE 16: RIGHT WING - LANDING GEAR SUPPORT BEAM - SURFACE INSPECTION [Group 2-6, Configuration 2] ........................................ 1 0 9 FIGURE 17: LEFT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 2, Configuration 1, 3] ........................ 1 1 1 FIGURE 18: RIGHT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 2, Configuration 1, 3] ........................ 1 1 4 FIGURE 19: LEFT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 2, Configuration 2] ......................... 1 1 7 FIGURE 20: RIGHT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 2, Configuration 2] ......................... 1 2 0 FIGURE 21: LEFT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 3, Configuration 1, 3; Group 4, Configuration 1, 3; Group 5, Configuration 1 , 3 ] .............................................. 1 2 3 FIGURE 22: RIGHT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 3, Configuration 1, 3; Group 4, Configuration 1, 3; Group 5, Configuration 1 , 3 ] .............................................. 1 2 6 FIGURE 23: LEFT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 3-5, Configuration 2] ........................ 1 2 9 FIGURE 24: RIGHT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 3-5, Configuration 2] ........................ 1 3 2 FIGURE 25: LEFT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 6, Configuration 1, 3] ........................ 1 3 5 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 26: RIGHT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 6, Configuration 1, 3] ........................ 1 3 8 FIGURE 27: LEFT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 6, Configuration 2] ......................... 1 4 1 FIGURE 28: RIGHT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 6, Configuration 2] ......................... 1 4 3 FIGURE 29: LEFT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 7, Configuration 1] ......................... 1 4 5 FIGURE 30: RIGHT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 7, Configuration 1] ......................... 1 4 8 FIGURE 31: LEFT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 6, Configuration 4; Group 7, Configuration 2] ........... 1 5 1 FIGURE 32: RIGHT WING - LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING FASTENER INSTALLATION [Group 6, Configuration 4; Group 7, Configuration 2] ........... 1 5 3 APPENDIX A: LOGIC DIAGRAMS FOR COMPLIANCE TASKS AND COMPLIANCE TIMES [Group 2-3, Configuration 1] ........................................ 1 5 5 APPENDIX B: LOGIC DIAGRAMS FOR COMPLIANCE TASKS AND COMPLIANCE TIMES [Group 2-3, Configuration 2] ........................................ 1 5 9 APPENDIX C: LOGIC DIAGRAMS FOR COMPLIANCE TASKS AND COMPLIANCE TIMES [Group 2-3, Configuration 3] ........................................ 1 6 3 APPENDIX D: LANDING GEAR SUPPORT BEAM - AFT SUPPORT FITTING - IDENTIFICATION OF FASTENER HOLE LOCATIONS ............................... 1 6 7 APPENDIX E: ACCESS INSTRUCTIONS FOR REPAIR .......................... 1 6 9 APPENDIX F: LOGIC DIAGRAMS FOR COMPLIANCE TASKS AND COMPLIANCE TIMES [Group 4-6, Configuration 1] ........................................ 1 7 8 APPENDIX G: LOGIC DIAGRAMS FOR COMPLIANCE TASKS AND COMPLIANCE TIMES [Group 4-6, Configuration 2; Group 7, Configuration 1] .......................... 1 8 2 APPENDIX H: LOGIC DIAGRAMS FOR COMPLIANCE TASKS AND COMPLIANCE TIMES [Group 4-6, Configuration 3] ........................................ 1 8 6 APPENDIX I: LOGIC DIAGRAMS FOR COMPLIANCE TASKS AND COMPLIANCE TIMES [Group 6, Configuration 4; Group 7, Configuration 2] .......................... 1 9 0 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 15, 2013 737-57A1318Revision 1: July 22, 2016 5 of 192 BOEING SERVICE BULLETIN 737-57A1318
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Original Issue: May 15, 2013 737-57A1318Revision 1: July 22, 2016 6 of 192 BOEING SERVICE BULLETIN 737-57A1318
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Commercial Airplanes 737 Service Bulletin ALERT Revision Transmittal SheetNumber: 737-57A1318Original Issue: May 15, 2013 Revision 1: July 22, 2016 ATA System: 5715 SUBJECT: WINGS - Landing Gear Support Beam - Rear Spar and Landing Gear Support Fitting Inspection This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2014-03-06 is related to this service bulletin.
The effective date of AD 2014-03-06 is April 09, 2014.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2014-12-13 is related to this service bulletin.
The effective date of AD 2014-12-13 is July 25, 2014.
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:
– A new inspection has been added and the compliance threshold and repeat inspection intervals have been shortened. The new inspection is in the same area as the existing inspection and is done at the same time as the existing inspection.
– The repeat HFEC surface inspections in OPTION 3 are no longer terminated once the OPTION 3 12 hole HFEC open hole inspection is done.
REASON FOR REVISION This revision is sent to provide updated compliance information, and to add Alert status to the bulletin, as cracks discovered during inspections showed that the original inspection schedule was insufficient. This revision is also sent to incorporate Information Notices 737-57-1318 IN 01, IN 02, and IN 03, which address an error in Figures 25 and 26 for Group 7 airplanes and to add access information to the bulletin for doing the SRM repair. This revision also adds the inspection of the forward support fitting to the open-hole inspection after the discovery of cracking in the forward support fitting during inspections called out in the original issue.
These sections were changed:
1. In Paragraph 1.A.1, Effectivity, created new configurations for Group 6 and 7 airplanes that have previously done the repairs called out in this service bulletin.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 15, 2013 737-57A1318Revision 1: July 22, 2016 7 of 192
2. In Paragraph 1.C, Background, added more information based on inspection results from the Original Issue of the service bulletin.
3. In Paragraph 1.D, Description, changed options for previous configurations due to release of SRM repair and added options for new configurations.
4. In Paragraph 1.E, Compliance, changed existing compliance tables and added new compliance tables to reflect changes in compliance times between Groups 2-3 and Groups 4-6, to add additional work required in case of crack detection and to show new configurations.
5. In Paragraph 1.F, Approval, added two paragraphs for AD Alternate Method of Compliance.
6. In Paragraph 1.G, Manpower, changed manpower tables to reflect new and changed configurations.
7. In Paragraph 2.C, Parts Necessary for Each Airplane: changed parts tables to show differences between groups and added a new parts table for Group 7, Configuration 1 airplanes.
8. In Paragraph 3.B.Part 3, Work Instructions, steps 1, 2, and 3: changed instructions to reflect release of SRM repairs and additional inspections of airplanes with cracks.
9. Added Paragraph 3.B.Part 3, Work Instructions, Step 4, to cover repairs of Group 6 Configuration 4 and Group 7 Configuration 2.
10. In Paragraph 3.B.Part 4, Work Instructions, Step 1: changed instructions to show new figures for fastener installation.
11. Changed Figures 1-12 to add inspection of the forward support fitting.
12. Changed Figures 17, 18, 21, 22, 25 and 26 to add a note to make sure there is adequate clearance around Fastener 5.
13. Added Figures 29 and 30 to give correct fasteners for Group 7 Configuration 1.
14. Added Figures 31 and 32.
15. In Appendix A, Band C: changed logic diagrams to reflect updated compliance times.
16. Added Appendix E to provide access instructions for inspections and repairs.
17. Added Appendix F, G, H, and I to provide logic diagrams to reflect updated compliance times.
18. Throughout the SB: updated the term "cracking" to "any crack", changed "inspection" to "HFEC inspection", and called out the structure being inspected.
The data given in Information Notices 737-57-1318 IN 01, IN 02, and IN 03 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.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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REVISION HISTORY May 15, 2013Original Issue:
July 22, 2016Revision 1:
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Original Issue: May 15, 2013 737-57A1318Revision 1: July 22, 2016 9 of 192 BOEING SERVICE BULLETIN 737-57A1318
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Original Issue: May 15, 2013 737-57A1318Revision 1: July 22, 2016 10 of 192 BOEING SERVICE BULLETIN 737-57A1318
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Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-57A1318Original Issue: May 15, 2013 Revision 1: July 22, 2016 ATA System: 5715 SUBJECT: WINGS - Landing Gear Support Beam - Rear Spar and Landing Gear Support Fitting Inspection
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 This service bulletin gives instructions to do High Frequency Eddy Current (HFEC) inspections for any crack in the aft and forward support fittings for the Main Landing Gear (MLG) beam, and the rear spar upper chord and rear spar web. If the work in this Service Bulletin (SB) is not done, a crack can grow undetected and result in the inability of the structure to carry limit load or result in a fuel leak that can jeopardize continued safe flight and landing.
Boeing has received five reports of cracks found during inspections or replacement of the MLG beam aft support fitting as given in SB 737-57-1216. Cracks were found in either the aft support fitting, the rear spar upper chord or the rear spar web. One report was of a vertical crack found in the rear spar web along with cracks in the aft support fitting and rear spar upper chord. During another separate inspection, cracks were reported in two holes in the rear spar upper chord and rear spar web. A third report was of a crack in the rear spar upper chord that extended downward to the edge of the vertical flange and upward to the horizontal flange. The affected airplanes had accumulated between 42,988 and 66,572 total flight hours and between 29,015 and 60,238 total flight cycles. Analysis shows that the aft support fitting, rear spar web and rear spar upper chord cracks are caused by operating load fatigue.
Since the Original Issue of this SB, an operator discovered a 2.375 inch long crack in the inspar upper skin at Wing Buttock Line (WBL) 157 just forward of the rear spar on the right wing and adjacent to the area inspected in this SB. Two additional smaller cracks were found in the skin at two holes common to the rear spar in the same area. Subsequent inspections revealed that the rear spar upper chord was almost completely severed and the left rear spar upper chord was completely severed. Rear spar web cracks were also noted on both wings. The affected airplane had accumulated 51,548 total flight cycles. After the initial report of the inspar upper Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 15, 2013 737-57A1318Revision 1: July 22, 2016 11 of 192
skin crack, additional reports of inspar upper skin cracking were reported in the same area. Inspar upper skin cracking at this location is the subject of SB 737-57A1326 and SB 737-57A1328. Although skin cracking is addressed outside of this service bulletin, analysis shows that rear spar upper chord cracking can negatively influence the inspar upper skin cracking condition. In addition to influencing skin cracking, rear spar upper chord cracking can also influence cracking at other mating structure.
Since the Original Issue of this SB, multiple operators have also reported cracking in the MLG beam forward support fitting, found while doing repairs to address cracked chords, and this fitting has been added to the bulletin inspections.
Accomplishment of the work in this SB will make sure that any crack in the fastener holes in the area of the upper spar chord adjacent to the MLG beam aft support fitting at Rear Spar Station (RSS) 224.14 is found and repaired before reaching a critical length.
Boeing Service Related Problem (SRP) 737-SRP-57-0295 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 737 FTD 57-15001 is related to this service bulletin.
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., ComplianceYesAD Related Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedNoPublications 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 Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION For Group 1 airplanes, contact Boeing to get instructions for the inspection and/or repair for this service bulletin, and do the work instructed by Boeing.
For Group 2-5, Group 6, Configuration 1-3, and for Group 7, Configuration 1, do one of the following inspection options:
– Do a High Frequency Eddy Current (HFEC) open hole inspection for any crack in the forward support fitting, the aft support fitting, the rear spar upper chord, and the rear spar web at 12 fastener holes in the upper chord.
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