# Boeing Alert Service Bulletin 737-57A1318: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2016-9523; AD 2018-09-13 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 737-57A1318](https://openairdocs.org/service-documents/boeing/737-57a1318.md) - Title as filed: SB-737-57A1318-01--BOEING - Pages: 192 - PDF: https://openairdocs.org/files/sha256/58/61/58615bee4dcb14069303df9b984c40503ea48e684777f029d065e7125d290232 - Page: https://openairdocs.org/service-documents/boeing/737-57a1318/file/58615bee4dcb ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 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 Unpublished Work.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1: July 22, 2016 1 of 192 7.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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 2 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 7 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 ALERTALERT ### Page 4 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. Original Issue: May 15, 2013 737-57A1318Revision 1: July 22, 2016 4 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 5 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 ALERTALERT ### Page 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 6 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT BLANK PAGE ### Page 7 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 ### Page 8 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. Original Issue: May 15, 2013 737-57A1318Revision 1: July 22, 2016 8 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 9 REVISION HISTORY May 15, 2013Original Issue: July 22, 2016Revision 1: 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 9 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 10 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 10 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT BLANK PAGE ### Page 11 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 ### Page 12 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. 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 12 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 13 – Do a 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 8 fastener holes in the upper chord, followed by a 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 – Do a HFEC surface inspection for any crack in the rear spar upper chord and the rear spar web adjacent to the MLG beam aft support fitting, followed by a 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 For Group 6, Configuration 4 and Group 7, Configuration 2, 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. – Do a HFEC surface inspection for any crack in the rear spar upper chord and the rear spar web adjacent to the MLG beam aft support fitting, followed by a 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 If any crack is found: – For any crack in the rear spar upper chord or rear spar web: contact The Boeing Company for repair instructions and do the repair, or repair in accordance with the SRM, as applicable. – For any crack in the forward support fitting or the aft support fitting: replace the cracked fitting. – Do eddy current inspections for any crack in the inspar upper skin in accordance with SB 737-57A1328, Original Issue. EFFECTIVITY All 737-100/-200/-200C/-300/-400/-500 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE 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. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection and/or repair procedures given 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 13 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 14 (OCR) BOEING SERVICE BULLETIN 737-57A1318 ALERT ALERT MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability. MAIN LANDING GEAR SUPPORT BEAM REAR SPAR UPPER CHORD OPTIONAL: DO HFEC SURFACE INSPECTION OF THE REAR SPAR UPPER CHORD AND REAR SPAR THE REAR SPAR WEB. WEB AFT SUPPORT -ITTING DO HIGH FREQUENCY EDDY FWD CURRENT (HFEC) OPEN HOLE INSPECTION IN THE AREA OF THE UPPER SPAR CHORD ADJACENT TO THE MLG BEAM SUPPORT FITTING AT RSS 224.14. LEFT SIDE SHOWN Original Issue: May 15, 2013 Revision 1: July 22, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-57A1318 Work - See page 1 for details. 14 of 192 ### Page 15 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 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. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplane(s) shown below. NOTE: Refer to APPENDIX D for the identification of fastener hole locations. DESCRIPTIONCONFIGURATIONGROUP 737-100/200/200C airplanes, line numbers 1 - 291.-1 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 15 of 192 ### Page 16 DESCRIPTIONCONFIGURATIONGROUP 737-200 airplanes, line numbers 292, 293, 296.-2 Airplanes that have replaced the aft support fitting and inspected 4 fastener holes (locations 3, 4, 5 and 6) in accordance with SB 737-57-1216. 1 Airplanes that have not replaced the aft support fitting in accordance with SB 737-57-1216. 2 Airplanes that have replaced the aft support fitting in accordance with SB 737-57-1216 and inspected 12 fastener holes (locations 1-12) that are common to the forward fitting and the rear spar upper chord in accordance with NDT Manual Part 6, 51-00-00, Procedure 1, 11, or 16 or that have replaced the aft support fitting in accordance with SB 737-57-1216 and have not inspected any fastener holes. 3 737-200/200C airplanes, line numbers 294, 295, 297-310.-3 Airplanes that have replaced the aft support fitting and inspected 4 fastener holes (locations 3, 4, 5 and 6) in accordance with SB 737-57-1216. 1 Airplanes that have not replaced the aft support fitting in accordance with SB 737-57-1216. 2 Airplanes that have replaced the aft support fitting in accordance with SB 737-57-1216 and inspected 12 fastener holes (locations 1-12) that are common to the forward fitting and the rear spar upper chord in accordance with NDT Manual Part 6, 51-00-00, Procedure 1, 11, or 16 or that have replaced the aft support fitting in accordance with SB 737-57-1216 and have not inspected any fastener holes. 3 737-200 airplanes, line numbers 324, 325, 327, 331, 374, 375, 380, 383. -4 Airplanes that have replaced the aft support fitting and inspected 4 fastener holes (locations 3, 4, 5 and 6) in accordance with SB 737-57-1216. 1 Airplanes that have not replaced the aft support fitting in accordance with SB 737-57-1216. 2 Airplanes that have replaced the aft support fitting in accordance with SB 737-57-1216 and inspected 12 fastener holes (locations 1-12) that are common to the forward fitting and the rear spar upper chord in accordance with NDT Manual Part 6, 51-00-00, Procedure 1, 11, or 16 or that have replaced the aft support fitting in accordance with SB 737-57-1216 and have not inspected any fastener holes. 3 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 16 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 17 DESCRIPTIONCONFIGURATIONGROUP 737-200/200C airplanes, line numbers between 311 - 1585 with a unique fastener configuration. -5 Airplanes that have replaced the aft support fitting and inspected 4 fastener holes (locations 3, 4, 5 and 6) in accordance with SB 737-57-1216. 1 Airplanes that have not replaced the aft support fitting in accordance with SB 737-57-1216. 2 Airplanes that have replaced the aft support fitting in accordance with SB 737-57-1216 and inspected 12 fastener holes (locations 1-12) that are common to the forward fitting and the rear spar upper chord in accordance with NDT Manual Part 6, 51-00-00, Procedure 1, 11, or 16 or that have replaced the aft support fitting in accordance with SB 737-57-1216 and have not inspected any fastener holes. 3 737-300/400/500 airplanes, line numbers 1001 - 2364 with a unique fastener configuration. -6 Airplanes that have replaced the aft support fitting and inspected 4 fastener holes (locations 3, 4, 5 and 6) in accordance with SB 737-57-1216, and have not performed the rear spar repair in accordance with this Service Bulletin. 1 Airplanes that have not replaced the aft support fitting in accordance with SB 737-57-1216, and have not performed the rear spar repair in accordance with this Service Bulletin. 2 Airplanes that have replaced the aft support fitting in accordance with SB 737-57-1216 and inspected 12 fastener holes (locations 1-12) that are common to the forward fitting and the rear spar upper chord in accordance with NDT Manual Part 6, 51-00-00, Procedure 1, 11, or 16 or that have replaced the aft support fitting in accordance with SB 737-57-1216 and have not inspected any fastener holes, and have not performed the rear spar repair in accordance with this Service Bulletin. 3 Airplanes that have performed a rear spar upper chord repair in accordance with a Boeing ODA FAA Form 8100-9 approved repair plan that included replacement of the segment of the spar chord encompassing this service bulletin's inspection location (location 1-12, as defined in Appendix D), or airplanes that have performed the rear spar upper chord repair in accordance with 737-300 SRM 57-20-10, Repair 4, 737-400 SRM 57-20-10, Repair 4, or 737-500 SRM 57-20-10 Repair 4, or airplanes that have performed a complete rear spar upper chord replacement. 4 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 17 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 18 DESCRIPTIONCONFIGURATIONGROUP 737-300/400/500 airplanes, line numbers 2365 - 3132 which had new aft support fitting installed during production. -7 Airplanes that have not performed the rear spar repair.1 Airplanes that have performed a rear spar upper chord repair in accordance with a Boeing ODA FAA Form 8100-9 approved repair plan that included replacement of the segment of the spar chord encompassing this service bulletin's inspection location (location 1-12, as defined in Appendix D), or airplanes that have performed the rear spar upper chord repair in accordance with 737-300 SRM 57-20-10, Repair 4, 737-400 SRM 57-20-10, Repair 4, or 737-500 SRM 57-20-10 Repair 4, or airplanes that have performed a complete rear spar upper chord replacement. 2 Airplane Models: 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500 GroupVariable Number 1PA001 - PA022 1PA099 1PA231 - PA232 1PC001 - PC005 1PG001 - PG075 1PG199 1PG201 - PG230 1PG251 - PG255 1PG271 - PG279 1PG301 - PG314 1PG331 - PG332 1PG351 - PG356 1PG375 1PG401 - PG403 1PG431 - PG442 1PG471 - PG475 1PG501 - PG505 1PG571 - PG583 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 18 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 19 GroupVariable Number 2PG584 - PG586 1PG621 - PG630 1PG651 - PG652 1PG701 - PG705 4PH011 - PH013 4PH021 - PH024 1PH701 - PH715 1PH731 - PH732 1PH741 - PH742 4PH743 1PJ001 - PJ002 5PJ003 - PJ009 1PJ031 - PJ032 1PJ071 - PJ072 1PJ101 - PJ104 5PJ105 - PJ119 5PJ201 - PJ219 6PJ301 - PJ302 7PJ551 - PJ561 7PJ601 - PJ615 7PJ811 7PJ816 - PJ817 5PK026 - PK029 5PK041 - PK053 5PK061 - PK070 5PK081 - PK082 5PK091 - PK099 5PK101 - PK103 5PK111 - PK120 5PK141 - PK146 5PK201 - PK204 5PK211 - PK223 5PK231 - PK241 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 19 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 20 GroupVariable Number 5PK251 - PK258 5PK271 - PK274 5PK281 - PK289 5PK291 5PK301 - PK318 5PK341 5PK351 - PK361 5PK391 5PK431 - PK433 5PK451 - PK452 5PK461 - PK469 5PK495 5PK501 - PK504 5PK511 - PK515 5PK519 5PK521 - PK528 5PK541 - PK565 5PK581 5PK591 - PK599 5PK601 - PK617 5PK621 - PK637 5PK641 - PK642 5PK661 - PK666 5PK671 - PK681 5PK691 - PK697 5PK711 - PK716 5PK731 - PK765 5PK771 - PK779 5PK801 - PK804 5PK819 - PK827 5PK830 5PK861 - PK863 5PK871 - PK874 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 20 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 21 GroupVariable Number 5PK881 - PK884 5PK901 - PK938 5PK971 - PK974 5PL001 - PL028 5PL061 5PL081 5PL101 - PL113 5PL151 5PL171 - PL172 5PL201 - PL203 5PL221 5PL401 - PL417 5PL421 5PL441 5PL451 - PL456 5PL471 5PL491 5PL501 - PL506 5PL551 - PL562 5PL581 5PL601 - PL603 5PL611 5PL621 - PL626 5PL631 - PL632 1PL711 - PL712 1PL716 5PL717 - PL725 3PL726 - PL728 5PL729 - PL735 3PL736 - PL742 5PL743 - PL747 3PL756 5PL758 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 21 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 22 GroupVariable Number 3PL761 5PL762 - PL770 5PL781 - PL788 5PL793 1PL801 - PL803 5PM001 - PM006 5PM016 - PM017 5PM021 - PM023 5PM051 - PM066 5PM101 - PM119 5PM141 - PM142 5PM171 5PM181 5PM251 - PM255 5PM281 - PM283 6PM381 - PM399 6PM401 - PM413 7PM414 - PM417 7PM541 - PM550 6PM551 - PM556 7PM557 - PM564 5PN001 - PN002 5PN021 - PN043 5PN081 - PN086 5PN101 - PN117 5PN131 - PN163 5PN401 - PN420 5PN431 - PN433 5PN451 - PN456 5PN471 - PN474 5PN481 5PN491 - PN493 5PN501 - PN502 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 22 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 23 GroupVariable Number 5PN511 - PN512 5PN521 6PP001 - PP054 6PP101 - PP159 7PP160 6PP161 - PP169 6PP181 - PP199 6PP201 - PP205 6PP221 6PP231 - PP243 6PP281 - PP286 6PP301 - PP305 6PP351 - PP353 6PP376 - PP384 6PP391 - PP393 6PP401 - PP440 6PP471 - PP475 6PP501 - PP517 7PP518 - PP520 6PP521 - PP522 6PP631 - PP634 6PP651 - PP652 6PP671 - PP699 6PP701 - PP733 6PP771 - PP779 6PP801 - PP808 6PP821 - PP827 6PP831 - PP848 6PP851 - PP852 6PP861 - PP873 7PP874 - PP877 6PP891 - PP899 6PP901 - PP936 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 23 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 24 GroupVariable Number 6PP946 - PP948 6PP951 - PP952 6PP961 - PP967 6PP981 - PP991 6PP993 6PQ001 - PQ016 6PQ026 - PQ041 6PQ051 - PQ092 6PQ101 - PQ199 6PQ201 - PQ202 6PQ221 - PQ237 6PQ241 - PQ243 6PQ251 - PQ267 6PQ281 - PQ293 7PQ294 - PQ299 6PQ301 - PQ307 6PQ331 - PQ332 6PQ341 - PQ344 7PQ345 - PQ348 6PQ361 - PQ364 7PQ365 - PQ373 7PQ391 - PQ395 6PQ401 - PQ403 7PQ404 - PQ410 6PQ411 7PQ412 - PQ418 6PQ421 7PQ431 - PQ438 7PQ447 - PQ448 7PQ451 7PQ454 7PQ471 - PQ475 7PQ479 - PQ481 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 24 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 25 GroupVariable Number 6PQ486 7PQ487 6PQ491 - PQ492 7PQ493 7PQ771 - PQ772 7PQ791 - PQ793 7PQ801 - PQ805 7PQ931 - PQ935 7PQ951 7PQ971 - PQ997 7PR001 - PR017 7PR021 - PR034 7PR041 - PR045 7PR061 - PR072 7PR077 - PR082 7PR091 - PR092 7PR096 7PR101 7PR121 - PR122 7PR131 - PR132 7PR141 - PR143 7PR161 - PR172 7PR181 6PS601 - PS614 7PS615 - PS631 6PS636 - PS638 6PS641 - PS644 6PS651 - PS657 6PS666 - PS669 6PS691 - PS692 6PS701 - PS703 7PS704 - PS706 7PS751 - PS799 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 25 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 26 GroupVariable Number 7PS811 7PS836 - PS837 7PS841 - PS846 7PS851 - PS852 7PS856 7PS861 - PS863 7PS866 - PS868 7PS871 - PS874 7PS896 - PS897 7PS901 - PS941 7PS956 - PS957 7PS961 - PS963 7PS971 - PS978 6PT001 - PT010 7PT011 - PT015 6PT021 - PT026 7PT027 - PT031 6PT041 - PT058 7PT059 - PT064 6PT101 - PT105 6PT121 - PT125 7PT126 - PT138 6PT146 - PT148 6PT161 - PT168 7PT169 - PT170 6PT181 - PT186 7PT187 - PT188 6PT211 - PT220 6PT295 6PT301 - PT302 7PT303 - PT309 6PT331 - PT360 6PT381 - PT399 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 26 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 27 GroupVariable Number 6PT401 - PT422 7PT423 - PT438 6PT501 - PT508 7PT509 - PT517 6PT561 - PT565 6PT581 - PT583 7PT584 - PT586 6PT611 - PT621 6PT641 7PT642 - PT644 7PT651 - PT656 7PT671 - PT672 7PT681 - PT685 6PT701 - PT703 7PT716 - PT717 7PT721 - PT725 7PT801 - PT834 7PT851 - PT854 7PT871 - PT886 7PT901 - PT930 7PT971 - PT973 7PT981 - PT985 7PT996 6PU001 - PU025 7PU301 7PU311 - PU313 6PV001 - PV055 6PV201 - PV202 7PV203 - PV209 7PV226 - PV229 6PV231 - PV236 7PV237 7PV271 - PV272 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 27 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 28 GroupVariable Number 7PV281 - PV287 7PV296 7PV301 - PV302 7PV351 7PV356 - PV357 6PW001 - PW054 6PW061 - PW068 7PW072 7PW086 - PW088 6PW091 - PW094 6PW101 7PW102 7PW106 6PW111 - PW120 6PW156 - PW157 6PW161 - PW166 7PW167 - PW171 6PW201 - PW205 7PW206 - PW230 6PW231 - PW238 7PW239 - PW252 6PW261 7PW262 - PW264 6PW265 7PW266 - PW268 7PW271 - PW276 7PW278 6PW281 7PW282 - PW292 6PW293 6PW296 6PW301 - PW313 7PW314 - PW327 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 28 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 29 GroupVariable Number 7PW401 - PW408 7PW411 - PW418 7PW421 - PW424 7PW431 - PW435 7PW441 - PW450 7PW461 - PW467 6PW501 - PW504 6PW511 - PW519 7PW520 - PW522 7PW524 - PW530 6PW531 - PW542 7PW543 - PW550 7PW556 - PW557 6PW561 - PW564 6PW571 - PW576 6PW591 - PW596 6PW611 - PW620 7PW621 - PW622 6PW631 - PW633 7PW634 - PW637 6PW661 - PW662 6PW681 - PW683 6PW701 7PW702 6PW711 - PW716 7PW717 6PW741 - PW742 6PW761 7PW771 7PW831 7PW851 - PW856 1PX071 1PX701 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 29 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 30 GroupVariable Number 1PY001 - PY008 1PY021 5PY022 1PY031 3PY036 - PY037 3PY046 - PY047 5PY048 5PY051 - PY053 5PY056 - PY057 5PY101 - PY103 5PY111 - PY113 5PY131 - PY135 5PY141 - PY143 5PY151 - PY154 5PY156 - PY157 5PY161 - PY162 5PY166 5PY191 5PY201 5PY221 - PY222 5PY231 5PY241 - PY244 5PY270 - PY275 5PY281 5PY286 1PY301 - PY304 1PY321 - PY323 1PY341 - PY346 1PY361 - PY362 1PY381 5PY401 5PY409 - PY411 5PY421 - PY422 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 30 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 31 GroupVariable Number 5PY441 5PY451 5PY461 - PY463 5PY591 - PY595 5PY611 - PY612 5PY621 5PY631 5PY651 5PY671 - PY672 5PY721 5PY741 2. Spares Affected None. B. Concurrent Requirements None. C. Reason 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. 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 31 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 32 After the initial report of the inspar upper 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 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. D. Description For Group 1 airplanes, contact The Boeing Company for inspection and/or repair instructions and do the inspection and/or repair. For Group 2-5, Group 6, Configuration 1-3, and for Group 7, Configuration 1, get access to the MLG beam aft support fitting on the rear spar of the left wing and right wing and 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. – Do a 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 8 fastener holes in the upper chord, followed by a 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 – Do a HFEC surface inspection for any crack in the rear spar upper chord and the rear spar web adjacent to the MLG beam aft support fitting, followed by a 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 For Group 6, Configuration 4 and Group 7, Configuration 2, get access to the MLG beam aft support fitting on the rear spar of the left wing and right wing and do one of the following inspection options: 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 32 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 33 – 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. – Do a HFEC surface inspection for any crack in the rear spar upper chord and the rear spar web adjacent to the MLG beam aft support fitting, followed by a 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 If any crack is found: – For any crack in the rear spar upper chord or rear spar web: contact The Boeing Company for repair instructions and do the repair, or repair in accordance with the SRM, as applicable. – For any crack in the forward support fitting or the aft support fitting: replace the cracked fitting. – Do eddy current inspections for any crack in the inspar upper skin in accordance with SB 737-57A1328, Original Issue. 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. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 3-5, 4-5737-100, 737-200, 737-200C Group 2, 4: Affected Maintenance Zones ZoneModel 3-5, 4-5737-200 Group 3, 5: Affected Maintenance Zones ZoneModel 3-5, 4-5737-200, 737-200C 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 33 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 34 Group 6-7: Affected Maintenance Zones ZoneModel 305, 405737-300, 737-400, 737-500 E. Compliance 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. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions. Group 2-3, Configuration 1: Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX A. Group 2-3, Configuration 2: Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX B. Group 2-3, Configuration 3: Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX C. Group 4-6, Configuration 1: Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX F. Group 4-6, Configuration 2; Group 7, Configuration 1: Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX G. Group 4-6, Configuration 3: Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX H. Group 6, Configuration 4; Group 7, Configuration 2: Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX I. 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 34 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 35 Group 1: Table 1: High Frequency Eddy Current (HFEC) Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles after the ef- fective date of AD 2014-03-06. Before 24,000 total flight cycles. Contact The Boeing Company for inspection or repair instruc- tions and do the inspection or the repair. All airplanes. 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 35 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 36 Group 2-3, Configuration 1: Table 2: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Do one of the following inspec- tion options: All airplanes. OPTION 1: 13,000 flight cycles.(d) Within 4,500 flight cycles after the effective date of AD 2014-03-06 or within 4,500 flight cycles after the Revision 1 date of this service bul- letin, whichever occurs later. Before 13,000 total flight cycles. Do a HFEC open hole inspec- tion for any crack in the for- ward support fitting, the aft support fitting, the rear spar upper chord, and the rear spar web at the 12 fastener holes (locations 1-12) in accordance with Paragraph 3.B., Work In- structions, Part 3, Step 1.a.(1). (a) OPTION 2: -Within 4,500 flight cycles after the effective date of AD 2014-03-06 or within 4,500 flight cycles after the Revision 1 date of this service bul- letin, whichever occurs later. Within 13,000 flight cycles after the 4 fas- tener holes were pre- viously HFEC inspect- ed in accordance with SB 737-57-1216. Action 1: At the 4 upper row fastener holes (locations 3, 4, 5 and 6) that were previously HFEC inspected in accor- dance with SB 737-57-1216, do a HFEC open hole inspec- tion for any crack in the for- ward support fitting, the aft support fitting, the rear spar upper chord, and the rear spar web in accordance with Para- graph 3.B., Work Instructions, Part 3, Step 1.a.(2)(a). (a) AND 4,500 flight cy- cles. (b) Within 4,500 flight cycles after the effective date of AD 2014-03-06 or within 4,500 flight cycles after the Revision 1 date of this service bul- letin, whichever occurs later. Before 13,000 total flight cycles. Action 2: At the 4 upper row fastener holes (locations 1, 2, 7 and 8) that were not previ- ously HFEC inspected, do a HFEC open hole inspection for any crack in the forward sup- port fitting, the aft support fit- ting, the rear spar upper chord, and the rear spar web in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 1.a.(2)(b). 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 36 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 37 Group 2-3, Configuration 1: Table 2: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition (a) AND 13,000 flight cycles.(d) Within 13,000 flight cycles after the effec- tive date of AD 2014-03-06. Action 3: Do a 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 the 12 fastener holes (locations 1-12) in accor- dance with Paragraph 3.B., Work Instructions, Part 3, Step 1.a.(2)(c). (a) OPTION 3: 4,500 flight cy- cles. (c) Within 4,500 flight cycles after the effective date of AD 2014-03-06 or within 4,500 flight cycles after the Revision 1 date of this service bul- letin, whichever occurs later. Within 13,000 flight cycles after the 4 fas- tener holes were pre- viously HFEC inspect- ed in accordance with SB 737-57-1216. Action 1: Do a HFEC surface inspection for any crack in the rear spar upper chord in accor- dance with Paragraph 3.B., Work Instructions, Part 3, Step 1.a.(3)(a). AND 4,500 flight cy- cles. (c) Within 4,500 flight cycles after the effective date of AD 2014-03-06 or within 4,500 flight cycles after the Revision 1 date of this service bul- letin, whichever occurs later. Before 13,000 total flight cycles. Action 2: Do a HFEC surface inspection for any crack in the rear spar web in accordance with Paragraph 3.B., Work In- structions, Part 3, Step 1.a.(3)(b). AND 24,000 flight cycles. Within 18,000 flight cycles after the effec- tive date of AD 2014-03-06. 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 37 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 38 Group 2-3, Configuration 1: Table 2: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Action 3: Do a 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 the 12 fastener holes (locations 1-12) in accor- dance with Paragraph 3.B., Work Instructions, Part 3, Step 1.a.(3)(c). (a) -Before further flight.Do eddy current inspections for any crack in the inspar up- per skin in accordance with Paragraph 3.B., Work Instruc- tions, Part 3, Step 1.b.(1) If any crack is found. AND -Before further flight.Repair in accordance with Paragraph 3.B., Work Instruc- tions, Part 3, Step 1.b.(2). (a) Refer to APPENDIX D for the identification of fastener hole locations. (b) This repeat inspection is terminated when the inspection of the 12 fastener holes (locations 1-12) in accordance with OPTION 2, Action 3 is started. (c) This repeat inspection is NOT terminated when the inspection of the 12 fastener holes (locations 1-12) in accordance with OPTION 3, Action 3 is started. This inspection can be terminated by switching to OPTION 1, so long as the interval between OPTION 3, Action 3 and OPTION 1 does not exceed the repeat interval for OPTION 1. (d) This repeat interval applies to airplanes that have completed inspections in accordance with the Original Issue of this service bulletin. All future inspections should be calculated using this interval from the time of the previously completed inspection, as the repeat interval specified in the original issue of this service bulletin has been reduced in Revision 1. 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 38 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 39 Group 2-3, Configuration 2: Table 3: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Do one of the following inspection options:All airplanes. OPTION 1: 13,000 flight cycles.(d) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Before 13,000 total flight cy- cles. Do a 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 the 12 fastener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.a.(1). (a) OPTION 2: 4,500 flight cy- cles. (b) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Before 13,000 total flight cy- cles. Action 1: Do a 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 the 8 fasten- er holes (locations 1-8) in the upper row of fasteners in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.a.(2)(a). (a) AND 13,000 flight cycles.(d) Within 13,000 flight cycles after the effective date of AD 2014- 03-06. Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.a.(2)(b). (a) OPTION 3: 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 39 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 40 Group 2-3, Configuration 2: Table 3: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Action 1: Do a HFEC surface inspection for any crack in the rear spar upper chord and for any crack in the rear spar web in accor- dance with Paragraph 3.B., Work Instruc- tions, Part 3, Step 2.a.(3)(a). 4,500 flight cy- cles. (c) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Before 13,000 total flight cy- cles. AND 24,000 flight cycles. Within 18,000 flight cycles after the effective date of AD 2014- 03-06. Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.a.(3)(b). (a) -Before further flight.Do eddy current inspections for any crack in the inspar upper skin in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.b.(1). If any crack is found. AND -Before further flight.Repair in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.b.(2) or 2.b.(3). (a) Refer to APPENDIX D for the identification of fastener hole locations. (b) This repeat inspection is terminated when the inspection of the 12 fastener holes (locations 1-12) in accor- dance with OPTION 2, Action 2 is started. (c) This repeat inspection is NOT terminated when the inspection of the 12 fastener holes (locations 1-12) in accordance with OPTION 3, Action 2 is started. This inspection can be terminated by switching to OPTION 1, so long as the interval between OPTION 3, Action 2 and OPTION 1 does not exceed the repeat interval for OPTION 1. 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 40 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 41 Group 2-3, Configuration 2: Table 3: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition (d) This repeat interval applies to airplanes that have completed inspections in accordance with the Original Issue of this service bulletin. All future inspections should be calculated using this interval from the time of the previously completed inspection, as the repeat interval specified in the original issue of this service bulletin has been reduced in Revision 1. 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 41 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 42 Group 2-3, Configuration 3: Table 4: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Do one of the following inspection options:All airplanes. OPTION 1: 13,000 flight cycles.(d) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Within 13,000 flight cycles af- ter the fastener holes were HFEC inspect- ed in accor- dance with NDT Manual Part 6, 51-00- 00, Procedure 1, 11, or 16 or before 13,000 total flight cy- cles (whichev- er occurs later) Do a 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 the 12 fastener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(1). (a) OPTION 2: 4,500 flight cy- cles. (b) Within 4,500 flight cycles after the effective date of AD 2014- 03-06 or within 4,500 flight cy- cles after the Revision 1 date of this service bulletin, whichever occurs later. Action 1: Do a 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 the 8 fasten- er holes (locations 1-8) in the upper row of fasteners in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(2)(a). (a) AND 13,000 flight cycles.(d) Within 13,000 flight cycles after the effective date of AD 2014- 03-06. Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(2)(b). (a) OPTION 3: 4,500 flight cy- cles. (c) 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 42 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 43 Group 2-3, Configuration 3: Table 4: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Action 1: Do a HFEC surface inspection for any crack in the rear spar upper chord and for any crack in the rear spar web in accor- dance with Paragraph 3.B., Work Instruc- tions, Part 3, Step 3.a.(3)(a). Within 4,500 flight cycles after the effective date of AD 2014- 03-06 or within 4,500 flight cy- cles after the Revision 1 date of this service bulletin, whichever occurs later. AND 24,000 flight cycles. Within 18,000 flight cycles after the effective date of AD 2014- 03-06. Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(3)(b). (a) -Before further flight.Do eddy current inspections for any crack in the inspar upper skin in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.b.(1) If any crack is found. AND -Before further flight.Repair in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.b.(2) or 3.b.(3) (a) Refer to APPENDIX D for the identification of fastener hole locations. (b) This repeat inspection is terminated when the inspection of the 12 fastener holes (locations 1-12) in accor- dance with OPTION 2, Action 2 is started. (c) This repeat inspection is NOT terminated when the inspection of the 12 fastener holes (locations 1-12) in accordance with OPTION 3, Action 2 is started. This inspection can be terminated by switching to OPTION 1, so long as the interval between OPTION 3, Action 2 and OPTION 1 does not exceed the repeat interval for OPTION 1. (d) This repeat interval applies to airplanes that have completed inspections in accordance with the Original Issue of this service bulletin. All future inspections should be calculated using this interval from the time of the previously completed inspection, as the repeat interval specified in the original issue of this service bulletin has been reduced in Revision 1. 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 43 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 44 Group 4-6, Configuration 1: Table 5: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Do one of the following inspec- tion options: All airplanes. OPTION 1: 15,000 flight cycles.(d) Within 4,500 flight cycles after the effective date of AD 2014-03-06 or within 4,500 flight cycles after the Revision 1 date of this service bul- letin, whichever occurs later. Before 15,000 total flight cycles. Do a HFEC open hole inspec- tion for any crack in the for- ward support fitting, the aft support fitting, the rear spar upper chord, and the rear spar web at the 12 fastener holes (locations 1-12) in accordance with Paragraph 3.B., Work In- structions, Part 3, Step 1.a.(1). (a) OPTION 2: -Within 4,500 flight cycles after the effective date of AD 2014-03-06 or within 4,500 flight cycles after the Revision 1 date of this service bul- letin, whichever occurs later. Within 15,000 flight cycles after the 4 fas- tener holes were pre- viously HFEC inspect- ed in accordance with SB 737-57-1216. Action 1: At the 4 upper row fastener holes (locations 3, 4, 5 and 6) that were previously HFEC inspected in accor- dance with SB 737-57-1216, do a HFEC open hole inspec- tion for any crack in the for- ward support fitting, the aft support fitting, the rear spar upper chord, and the rear spar web in accordance with Para- graph 3.B., Work Instructions, Part 3, Step 1.a.(2)(a). (a) AND 4,500 flight cy- cles. (b) Within 4,500 flight cycles after the effective date of AD 2014-03-06 or within 4,500 flight cycles after the Revision 1 date of this service bul- letin, whichever occurs later. Before 15,000 total flight cycles. Action 2: At the 4 upper row fastener holes (locations 1, 2, 7 and 8) that were not previ- ously HFEC inspected, do a HFEC open hole inspection for any crack in the forward sup- port fitting, the aft support fit- ting, the rear spar upper chord, and the rear spar web in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 1.a.(2)(b). 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 44 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 45 Group 4-6, Configuration 1: Table 5: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition (a) AND 15,000 flight cycles.(d) Within 15,000 flight cycles after the effec- tive date of AD 2014-03-06. Action 3: Do a 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 the 12 fastener holes (locations 1-12) in accor- dance with Paragraph 3.B., Work Instructions, Part 3, Step 1.a.(2)(c). (a) OPTION 3: 4,500 flight cy- cles. (c) Within 4,500 flight cycles after the effective date of AD 2014-03-06 or within 4,500 flight cycles after the Revision 1 date of this service bul- letin, whichever occurs later. Within 15,000 flight cycles after the 4 fas- tener holes were pre- viously HFEC inspect- ed in accordance with SB 737-57-1216. Action 1: Do a HFEC surface inspection for any crack in the rear spar upper chord in accor- dance with Paragraph 3.B., Work Instructions, Part 3, Step 1.a.(3)(a). AND 4,500 flight cy- cles. (c) Within 4,500 flight cycles after the effective date of AD 2014-03-06 or within 4,500 flight cycles after the Revision 1 date of this service bul- letin, whichever occurs later. Before 15,000 total flight cycles. Action 2: Do a HFEC surface inspection for any crack in the rear spar web in accordance with Paragraph 3.B., Work In- structions, Part 3, Step 1.a.(3)(b). AND 24,000 flight cycles. Within 18,000 flight cycles after the effec- tive date of AD 2014-03-06. 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 45 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 46 Group 4-6, Configuration 1: Table 5: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Action 3: Do a 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 the 12 fastener holes (locations 1-12) in accor- dance with Paragraph 3.B., Work Instructions, Part 3, Step 1.a.(3)(c). (a) -Before further flight.Do eddy current inspections for any crack in the inspar up- per skin in accordance with Paragraph 3.B., Work Instruc- tions, Part 3, Step 1.b.(1). If any crack is found. AND -Before further flight.Repair in accordance with Paragraph 3.B., Work Instruc- tions, Part 3, Step 1.b.(2) or 1.b.(3). (a) Refer to APPENDIX D for the identification of fastener hole locations. (b) This repeat inspection is terminated when the inspection of the 12 fastener holes (locations 1-12) in accordance with OPTION 2, Action 3 is started. (c) This repeat inspection is NOT terminated when the inspection of the 12 fastener holes (locations 1-12) in accordance with OPTION 3, Action 3 is started. This inspection can be terminated by switching to OPTION 1, so long as the interval between OPTION 3, Action 3 and OPTION 1 does not exceed the repeat interval for OPTION 1. (d) This repeat interval applies to airplanes that have completed inspections in accordance with the Original Issue of this service bulletin. All future inspections should be calculated using this interval from the time of the previously completed inspection, as the repeat interval specified in the original issue of this service bulletin has been reduced in Revision 1. 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 46 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 47 Group 4-6, Configuration 2: Table 6: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Do one of the following inspection options:All airplanes. OPTION 1: 15,000 flight cycles.(d) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Before 15,000 total flight cy- cles. Do a 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 the 12 fastener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.a.(1). (a) OPTION 2: 4,500 flight cy- cles. (b) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Before 15,000 total flight cy- cles. Action 1: Do a 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 the 8 fasten- er holes (locations 1-8) in the upper row of fasteners in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.a.(2)(a). (a) AND 15,000 flight cycles.(d) Within 15,000 flight cycles after the effective date of AD 2014- 03-06. Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.a.(2)(b). (a) OPTION 3: 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 47 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 48 Group 4-6, Configuration 2: Table 6: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Action 1: Do a HFEC surface inspection for any crack in the rear spar upper chord and for any crack in the rear spar web in accor- dance with Paragraph 3.B., Work Instruc- tions, Part 3, Step 2.a.(3)(a). 4,500 flight cy- cles. (c) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Before 15,000 total flight cy- cles. AND 24,000 flight cycles. Within 18,000 flight cycles after the effective date of AD 2014- 03-06. Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.a.(3)(b). (a) -Before further flight.Do eddy current inspections for any crack in the inspar upper skin in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.b.(1). If any crack is found. AND -Before further flight.Repair in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 2.b.(2) or 2.b.(3). (a) Refer to APPENDIX D for the identification of fastener hole locations. (b) This repeat inspection is terminated when the inspection of the 12 fastener holes (locations 1-12) in accor- dance with OPTION 2, Action 2 is started. (c) This repeat inspection is NOT terminated when the inspection of the 12 fastener holes (locations 1-12) in accordance with OPTION 3, Action 2 is started. This inspection can be terminated by switching to OPTION 1, so long as the interval between OPTION 3, Action 2 and OPTION 1 does not exceed the repeat interval for OPTION 1. 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 48 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 49 Group 4-6, Configuration 2: Table 6: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition (d) This repeat interval applies to airplanes that have completed inspections in accordance with the Original Issue of this service bulletin. All future inspections should be calculated using this interval from the time of the previously completed inspection, as the repeat interval specified in the original issue of this service bulletin has been reduced in Revision 1. 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 49 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 50 Group 4-6, Configuration 3: Table 7: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Do one of the following inspection options:All airplanes. OPTION 1: 15,000 flight cycles.(d) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Within 15,000 flight cycles af- ter the fastener holes were HFEC inspect- ed in accor- dance with NDT Manual Part 6, 51-00- 00, Procedure 1, 11, or 16 or before 15,000 total flight cy- cles (whichev- er occurs later) Do a 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 the 12 fastener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(1). (a) OPTION 2: 4,500 flight cy- cles. (b) Within 4,500 flight cycles after the effective date of AD 2014- 03-06 or within 4,500 flight cy- cles after the Revision 1 date of this service bulletin, whichever occurs later. Action 1: Do a 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 the 8 fasten- er holes (locations 1-8) in the upper row of fasteners in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(2)(a). (a) AND 15,000 flight cycles.(d) Within 15,000 flight cycles after the effective date of AD 2014- 03-06. Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(2)(b). (a) OPTION 3: 4,500 flight cy- cles. (c) 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 50 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 51 Group 4-6, Configuration 3: Table 7: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Action 1: Do a HFEC surface inspection for any crack in the rear spar upper chord and for any crack in the rear spar web in accor- dance with Paragraph 3.B., Work Instruc- tions, Part 3, Step 3.a.(3)(a). Within 4,500 flight cycles after the effective date of AD 2014- 03-06 or within 4,500 flight cy- cles after the Revision 1 date of this service bulletin, whichever occurs later. AND 24,000 flight cycles. Within 18,000 flight cycles after the effective date of AD 2014- 03-06. Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(3)(b). (a) -Before further flight.Do eddy current inspections for any crack in the inspar upper skin in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.b.(1). If any crack is found. AND -Before further flight.Repair in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.b.(2) or 3.b.(3). (a) Refer to APPENDIX D for the identification of fastener hole locations. (b) This repeat inspection is terminated when the inspection of the 12 fastener holes (locations 1-12) in accor- dance with OPTION 2, Action 2 is started. (c) This repeat inspection is NOT terminated when the inspection of the 12 fastener holes (locations 1-12) in accordance with OPTION 3, Action 2 is started. This inspection can be terminated by switching to OPTION 1, so long as the interval between OPTION 3, Action 2 and OPTION 1 does not exceed the repeat interval for OPTION 1.. (d) This repeat interval applies to airplanes that have completed inspections in accordance with the Original Issue of this service bulletin. All future inspections should be calculated using this interval from the time of the previously completed inspection, as the repeat interval specified in the original issue of this service bulletin has been reduced in Revision 1. 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 51 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 52 Group 7, Configuration 1: Table 8: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Do one of the following inspection options:All airplanes. OPTION 1: 15,000 flight cycles.(d) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Before 15,000 total flight cy- cles. Do a 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 the 12 fastener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(1). (a) OPTION 2: 4,500 flight cy- cles. (b) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Before 15,000 total flight cy- cles. Action 1: Do a 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 the 8 fasten- er holes (locations 1-8) in the upper row of fasteners in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(2)(a). (a) AND 15,000 flight cycles.(d) Within 15,000 flight cycles after the effective date of AD 2014- 03-06 Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(2)(b). (a) OPTION 3: 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 52 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 53 Group 7, Configuration 1: Table 8: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition Action 1: Do a HFEC surface inspection for any crack in the rear spar upper chord and for any crack in the rear spar web in accor- dance with Paragraph 3.B., Work Instruc- tions, Part 3, Step 3.a.(3)(a). 4,500 flight cy- cles. (c) Within 4,500 flight cycles af- ter the effective date of AD 2014-03-06 or within 4,500 flight cycles af- ter the Revi- sion 1 date of this service bulletin, whichever oc- curs later. Before 15,000 total flight cy- cles. AND 24,000 flight cycles. Within 18,000 flight cycles after the effective date of AD 2014- 03-06. Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.a.(3)(b). (a) -Before further flight.Do eddy current inspections for any crack in the inspar upper skin in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.b.(1). If any crack is found. AND -Before further flight.Repair in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 3.b.(2) or 3.b.(3). (a) Refer to APPENDIX D for the identification of fastener hole locations. (b) This repeat inspection is terminated when the inspection of the 12 fastener holes (locations 1-12) in accor- dance with OPTION 2, Action 2 is started. (c) This repeat inspection is NOT terminated when the inspection of the 12 fastener holes (locations 1-12) in accordance with OPTION 3, Action 2 is started. This inspection can be terminated by switching to OPTION 1, so long as the interval between OPTION 3, Action 2 and OPTION 1 does not exceed the repeat interval for OPTION 1. 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 53 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 54 Group 7, Configuration 1: Table 8: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs Later) ActionCondition (d) This repeat interval applies to airplanes that have completed inspections in accordance with the Original Issue of this service bulletin. All future inspections should be calculated using this interval from the time of the previously completed inspection, as the repeat interval specified in the original issue of this service bulletin has been reduced in Revision 1. 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 54 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 55 Group 6, Configuration 4; Group 7, Configuration 2: Table 9: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time ActionCondition Do one of the following inspection options:All airplanes. OPTION 1: 15,000 flight cycles. (c) Before 15,000 flight cycles af- ter the repair. Do a 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 the 12 fastener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 4.a.(1). (a) OPTION 2: 4,500 flight cy- cles. (b) Before 15,000 flight cycles af- ter the repair. Action 1: Do a HFEC surface inspection for any crack in the rear spar upper chord and for any crack in the rear spar web in accor- dance with Paragraph 3.B., Work Instruc- tions, Part 3, Step 4.a.(2)(a). AND 24,000 flight cycles. Within 24,000 flight cycles af- ter the repair. Action 2: Do a 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 the 12 fas- tener holes (locations 1-12) in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 4.a.(2)(b). (a) -Before further flight. Do eddy current inspections for any crack in the inspar upper skin in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 4.b.(1). If any crack is found. AND -Before further flight. Repair in accordance with Paragraph 3.B., Work Instructions, Part 3, Step 4.b.(2). (a) Refer to APPENDIX D for the identification of fastener hole locations. (b) This repeat inspection is NOT terminated when the inspection of the 12 fastener holes (locations 1-12) in accordance with OPTION 2, Action 2 is started. This inspection can be terminated by switching to OPTION 1, so long as the interval between OPTION 2, Action 2 and OPTION 1 does not exceed the repeat interval for OPTION 1. 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 55 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 56 Group 6, Configuration 4; Group 7, Configuration 2: Table 9: HFEC Inspections of the Forward Support Fitting, Aft Support Fitting, Rear Spar Upper Chord and Rear Spar Web at RSS 224.14 Repeat Inter- val (Not to Ex- ceed) Compliance Time ActionCondition (c) This repeat interval applies to airplanes that have completed inspections in accordance with the Original Issue of this service bulletin. All future inspections should be calculated using this interval from the time of the previously completed inspection, as the repeat in- terval specified in the original issue of this service bulletin has been reduced in Revision 1. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (h)(1) of AD 2014-12-13. All provisions of AD 2014-12-13 that are not specifically referenced in the above statement remain fully applicable and must be complied with. In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (i) of AD 2015-21-08. All provisions of AD 2015-21-08 that are not specifically referenced in the above statement remain fully applicable and must be complied with. G. Manpower The table below shows an estimate of the task hours necessary to do this service bulletin for each side of the airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. NOTE: Refer to APPENDIX D for the identification of fastener hole locations. 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 56 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 57 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: 12 Fastener Hole Inspection (Locations 1-12) Elapsed HoursTask HoursNumber of PersonsTask 23.0039.004Open Access 2.102.101FIGURE 1 2.102.101FIGURE 2 23.0039.004Close Access 0.500.501Functional Test 50.7082.70TOTAL FOR EACH AIRPLANE Group 2-6, Configuration 2: 12 Fastener Hole Inspection (Locations 1-12) Elapsed HoursTask HoursNumber of PersonsTask 23.0039.004Open Access 2.102.101FIGURE 3 2.102.101FIGURE 4 23.0039.004Close Access 0.500.501Functional Test 50.7082.70TOTAL FOR EACH AIRPLANE Group 2-6, Configuration 3; Group 7, Configuration 1: 8 Fastener Hole Inspection (Locations 1-8) Elapsed HoursTask HoursNumber of PersonsTask 11.6018.604Open Access 1.601.601FIGURE 5 1.601.601FIGURE 6 11.6018.604Close Access 26.4040.40TOTAL FOR EACH AIRPLANE Group 2-6, Configuration 2: 8 Fastener Hole Inspection (Locations 1-8) Elapsed HoursTask HoursNumber of PersonsTask 11.6018.604Open Access 1.601.601FIGURE 7 1.601.601FIGURE 8 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 57 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 58 Group 2-6, Configuration 2: 8 Fastener Hole Inspection (Locations 1-8) Elapsed HoursTask HoursNumber of PersonsTask 11.6018.604Close Access 26.4040.40TOTAL FOR EACH AIRPLANE Group 2-6, Configuration 1: 4 Fastener Hole Inspection (Locations 1, 2, 7, 8 or 3, 4, 5, 6) Elapsed HoursTask HoursNumber of PersonsTask 11.6018.604Open Access 1.001.001FIGURE 9 1.001.001FIGURE 10 1.001.001FIGURE 11 1.001.001FIGURE 12 11.6018.604Close Access 25.2039.20TOTAL FOR EACH AIRPLANE (Inspection of Hole Locations 1, 2, 7 and 8 Only) 25.2039.20TOTAL FOR EACH AIRPLANE (Inspection of Hole Locations 3, 4, 5 and 6 Only) 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: Surface Inspection (Rear Spar Upper Chord Only) Elapsed HoursTask HoursNumber of PersonsTask 11.0018.004Open Access 1.001.001FIGURE 13 1.001.001FIGURE 14 11.0018.004Close Access 24.0038.00TOTAL FOR EACH AIRPLANE 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: Surface Inspection (Rear Spar Web Only) Elapsed HoursTask HoursNumber of PersonsTask 4.308.602Open Access 1.001.001FIGURE 13 1.001.001FIGURE 14 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 58 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 59 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: Surface Inspection (Rear Spar Web Only) Elapsed HoursTask HoursNumber of PersonsTask 4.308.602Close Access 10.6019.20TOTAL FOR EACH AIRPLANE Group 2-6, Configuration 2: Surface Inspection (Rear Spar Upper Chord Only) Elapsed HoursTask HoursNumber of PersonsTask 11.0018.004Open Access 1.001.001FIGURE 15 1.001.001FIGURE 16 11.0018.004Close Access 24.0038.00TOTAL FOR EACH AIRPLANE Group 2-6, Configuration 2: Surface Inspection (Rear Spar Web Only) Elapsed HoursTask HoursNumber of PersonsTask 4.308.602Open Access 1.001.001FIGURE 15 1.001.001FIGURE 16 4.308.602Close Access 10.6019.20TOTAL FOR EACH AIRPLANE Group 2, Configuration 1, 3: Aft Support Fitting Fastener Installation Elapsed HoursTask HoursNumber of PersonsTask 0.400.401FIGURE 17 0.400.401FIGURE 18 0.80 (a)0.80 (a)TOTAL FOR EACH AIRPLANE (a) The total time shown does not include time for repair. 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 59 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT ### Page 60 Group 2, Configuration 2: Aft Support Fitting Fastener Installation Elapsed HoursTask HoursNumber of PersonsTask 0.400.401FIGURE 19 0.400.401FIGURE 20 0.80 (a)0.80 (a)TOTAL FOR EACH AIRPLANE (a) The total time shown does not include time for repair. Group 3, Configuration 1, 3; Group 4, Configuration 1, 3; Group 5, Configuration 1, 3: Aft Support Fitting Fastener Installation Elapsed HoursTask HoursNumber of PersonsTask 0.400.401FIGURE 21 0.400.401FIGURE 22 0.80 (a)0.80 (a)TOTAL FOR EACH AIRPLANE (a) The total time shown does not include time for repair. Group 3-5, Configuration 2: Aft Support Fitting Fastener Installation Elapsed HoursTask HoursNumber of PersonsTask 0.400.401FIGURE 23 0.400.401FIGURE 24 0.80 (a)0.80 (a)TOTAL FOR EACH AIRPLANE (a) The total time shown does not include time for repair. Group 6, Configuration 1, 3: Aft Support Fitting Fastener Installation Elapsed HoursTask HoursNumber of PersonsTask 0.400.401FIGURE 25 0.400.401FIGURE 26 0.80 (a)0.80 (a)TOTAL FOR EACH AIRPLANE (a) The total time shown does not include time for repair. Group 6, Configuration 2: Aft Support Fitting Fastener Installation Elapsed HoursTask HoursNumber of PersonsTask 0.400.401FIGURE 27 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 60 of 192 BOEING SERVICE BULLETIN 737-57A1318 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/737-57a1318/file/58615bee4dcb.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.