# Boeing Special Attention Service Bulletin 737-53-1315: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2017-0129; AD 2017-06-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Special Attention Service Bulletin 737-53-1315](https://openairdocs.org/service-documents/boeing/sb-737-53-1315.md) - Title as filed: SB 737-53-1315_Rev1 - Pages: 102 - PDF: https://openairdocs.org/files/sha256/fb/fb/fbfb2885ffa358bcd1984b13106f25b9717a5e523176ea47d82b4b93856fd4be - Page: https://openairdocs.org/service-documents/boeing/sb-737-53-1315/file/fbfb2885ffa3 ## 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 SPECIAL ATTENTION Number: 737-53-1315 Original Issue: July 29, 2011 Revision 1: June 30, 2015 ATA System: 5360 SUBJECT: FUSELAGE - Skin - Station 727 to 1016 - Aft Skin Inspection, Repair and Replacement 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 © 2011 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 Unpublished Work.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: July 29, 2011 737-53-1315Revision 1: June 30, 2015 1 of 102 4.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 2 of 102 BOEING SERVICE BULLETIN 737-53-1315 BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 S u m m a r y ...................................................... 9 1. PLANNING INFORMATION ........................................ 1 3 A . E f f e c t i v i t y ............................................... 1 3 1. Airplanes ............................................ 1 3 2 . S p a r e s A f f e c t e d ........................................ 1 5 B. Concurrent Requirements ...................................... 1 5 C. Reason ................................................ 1 5 D. Description .............................................. 1 6 E. Compliance .............................................. 1 7 F . A p p r o v a l ............................................... 2 3 G. Manpower .............................................. 2 4 H. Weight and Balance Changes .................................... 2 6 I. Electrical Load Data ......................................... 2 6 J . R e f e r e n c e s .............................................. 2 6 1. Existing Data: ......................................... 2 6 2. Data Supplied with this Service Bulletin: ........................... 2 7 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 8 K. Publications Affected ........................................ 2 8 L. Interchangeability and Intermixability of Parts ........................... 2 9 M. Software Accomplishment Summary ................................ 2 9 2. MATERIAL INFORMATION ........................................ 3 1 A. Material - Price and Availability ................................... 3 1 B. Industry Support Information .................................... 3 2 C. Parts Necessary for Each Airplane ................................. 3 2 1 . K i t s / P a r t s ............................................ 3 2 2. Parts and Materials Supplied by the Operator ........................ 3 4 3. Parts Modified and Reidentified ................................ 3 5 4. Parts Removed and Not Replaced .............................. 3 5 D. Parts Necessary to Change Spares ................................. 3 5 E. Special Tooling - Price and Availability ............................... 3 5 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 5 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 7 A. GENERAL INFORMATION ..................................... 3 7 B. WORK INSTRUCTIONS ....................................... 3 8 FIGURE 1: INSPECTION ZONES - LEFT SIDE [Group 1-4] ....................... 5 0 FIGURE 2: INSPECTION ZONES - RIGHT SIDE [Group 1-4] ...................... 5 3 FIGURE 3: INSPECTION ZONES - LEFT SIDE [Group 5-6] ....................... 5 6 FIGURE 4: INSPECTION ZONES - RIGHT SIDE [Group 5-6] ...................... 5 8 FIGURE 5: EXTERNAL OR INTERNAL INSPECTION .......................... 6 0 FIGURE 6: INTERNAL INSPECTION ................................... 6 3 FIGURE 7: TIME LIMITED REPAIR .................................... 6 6 FIGURE 8: OPTION 1 PERMANENT REPAIR INSTALLATION FOR TIME LIMITED REPAIRS INSTALLED IN ACCORDANCE WITH ORIGINAL ISSUE OF THIS SERVICE BULLETIN ........ 7 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 3 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 4 FIGURE 9: OPTION 2 PERMANENT REPAIR INSTALLATION FOR TIME LIMITED REPAIRS INSTALLED IN ACCORDANCE WITH ORIGINAL ISSUE OF THIS SERVICE BULLETIN ........ 7 6 FIGURE 10: OPTION 1 PERMANENT REPAIR INSTALLATION FOR AIRPLANES WITH A TIME LIMITED REPAIR INSTALLED IN ACCORDANCE WITH REVISION 1 OF THIS SERVICE BULLETIN .................................................. 8 3 FIGURE 11: OPTION 2 PERMANENT REPAIR INSTALLATION FOR AIRPLANES WITH A TIME LIMITED REPAIR INSTALLED IN ACCORDANCE WITH REVISION 1 OF THIS SERVICE BULLETIN .................................................. 8 9 FIGURE 12: POST REPAIR EXTERNAL LFEC INSPECTION OF OPTION 1 PERMANENT REPAIR . 95 FIGURE 13: POST REPAIR EXTERNAL LFEC INSPECTION OF OPTION 2 PERMANENT REPAIR . 97 APPENDIX A: SKIN PANEL INSTALLATION DRAWINGS .......................... 9 9 APPENDIX B: PART DEMAND INTENT ................................... 1 0 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 4 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 5 Commercial Airplanes 737 Service Bulletin SPECIAL ATTENTION Revision Transmittal SheetNumber: 737-53-1315Original Issue: July 29, 2011 Revision 1: June 30, 2015 ATA System: 5360 SUBJECT: FUSELAGE - Skin - Station 727 to 1016 - Aft Skin Inspection, Repair and Replacement This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-16-07 is related to this service bulletin. The effective date of AD 2012-16-07 is September 18, 2012. 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: ActionConditionGroup Replace the skin panels in accor- dance with Revision 1 of this service bulletin. All Airplanes.Group 1-6 Do the inspections in accordance with Revision 1 of this service bul- letin. Airplanes that have accomplished at least one inspection in accor- dance with the Original Issue of this service bulletin. Continue post repair inspections and make the time limited repair perma- nent in accordance with Revision 1 of this service bulletin. Do post re- pair inspections of the permanent repair in accordance with Revision 1 of this service bulletin. (a) Airplanes that have accomplished the time limited repair in accordance with the Original Issue of this service bulletin. No more work is necessary until the mandatory skin panel replacement in accordance with Revision 1 of this service bulletin. Airplanes that have accomplished the permanent repair or made the time limited repair permanent in ac- cordance with the Original Issue of this service bulletin. (a) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 5 of 102 ### Page 6 ActionConditionGroup (a) The definition of "permanent repair" has changed from the Original Issue to Revision 1 of this service bulletin. The term "permanent repair" in SB 737-53-1315, Original Issue, refers to the 737-500 SRM 53- 00-01, Figure 201, Repair 31, however in SB 737-53-1315, Revision 1, "permanent repair" refers to modifying the time limited repair in accordance with PART 5: PERMANENT REPAIR INSTALLATION. REASON FOR REVISION This revision is sent to provide new and additional inspection requirements, add requirement to replace skin panels, change compliance time requirements, change time limited repair and permanent repair requirements, and change airplane grouping. The inspection areas have changed from three zones to two zones. In the Original Issue, Zones 1, 2, and 3 consisted of inspection areas of the skin where the bonded doublers are fully chem-milled to the bond line. The new zones include all previously inspected areas from the Original Issue of this service bulletin and additional areas where cracks could be found. Due to the change in zone definition, inspection criteria have been changed to enable early detection of cracks. In order to mitigate Widespread Fatigue Damage (WFD) concerns, compliance and inspection requirements have changed as shown in the following two tables. Original Issue Compliance Summary Threshold / Repeat IntervalsInspection Zone 22,000 / 4,500 flight cycles (external or internal inspections)Zone 1 (a) 22,000 / 4,500 flight cycles (external or internal inspections)Zone 2 (b) 22,000 / 3,700 flight cycles (external inspections)Zone 3 (c) (a) Zone 1: Areas under the fairing which may or may not have had a history of cracks. (b) Zone 2: Areas outside of the fairing that have similar loading and structural configuration as Zone 1 and Zone 3, but no history of cracks. (c) Zone 3: Areas outside of the fairing with a history of cracks. Revision 1 Compliance Summary Threshold / Repeat IntervalsInspection Zone 22,000 / 3,700 flight cycles (external or internal inspections)Zone 1 (a) 34,000 / 7,500 flight cycles (external inspections)Zone 2 (b) (a) Zone 1: Skin and bonded doubler with the bonded doubler chem-milled to the bond line in the pocket. (b) Zone 2: Skin and bonded doubler with a chem-milled pocket thickness of 0.050 inch and with the bonded doubler partially chem-milled. Airplane grouping has been changed as follows: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 6 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 7 Airplane Grouping Changes Revision 1 GroupOriginal Issue Group 11 2 3 4 52 6 These sections were changed: 1. In Summary - Background, updated information and added planning data table. 2. In Summary - Action, updated information. 3. In Summary - Compliance, added AD statement(s). 4. In Summary - Effectivity, added line number range. 5. In Summary, revised the illustration. 6. In Paragraph 1.C., Reason, updated information. 7. In Paragraph 1.D., Description, updated information. 8. In Paragraph 1.E., Compliance, updated compliance table information and added AD statement(s). 9. In Paragraph 1.F., Approval, added AMOC statement. 10. In Paragraph 1.G., Manpower, included new tables for skin inspections, repairs and skin panel replacement. 11. In Paragraph 1.H., Weight and Balance Changes, added new tables. 12. In Paragraph 1.J., References, updated list of references, added list of drawings supplied with this service bulletin and added drawings used in the preparation of this service bulletin. 13. Added Paragraph 1.M., Software Accomplishment Summary. 14. In Paragraph 2.A., Material - Price and Availability, updated information. 15. In Paragraph 2.C., Parts Necessary for Each Airplane, updated information and added new replacement skin panel assembly parts. 16. In Paragraph 3.B., Work Instructions, updated instructions for inspections, repairs and skin panel replacement. 17. Figure 1 thru Figure 4, changed to show new and additional inspection requirements, revised applicability. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 7 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 8 18. Figure 5 and Figure 6, updated information and inspection methods. 19. Figure 7, revised the figure. 20. Added Figure 8 thru Figure 13. 21. Added Appendix A: Skin Panel Installation Drawings. 22. Added Appendix B: Part Demand Intent. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes. Pages with no vertical lines have no changes. REVISION HISTORY July 29, 2011Original Issue: June 30, 2015Revision 1: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 8 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 9 Commercial Airplanes 737 Service Bulletin SPECIAL ATTENTION SummaryNumber: 737-53-1315Original Issue: July 29, 2011 Revision 1: June 30, 2015 ATA System: 5360 SUBJECT: FUSELAGE - Skin - Station 727 to 1016 - Aft Skin Inspection, Repair and Replacement BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. CONCURRENT REQUIREMENTS None. BACKGROUND More than three hundred incidents of skin chem-mill cracks on twenty six airplanes have been reported from Body Station (STA) 727 to 1016 and Stringer S-14 to S-25 (left and right side) between 29,808 and 53,454 flight cycles. Most of the skin cracks were found aft of the wing at STA 747 and below the window belt on the left side. Several of the reported cracks occurred in multiple adjacent bays. Since the release of the original version of this service bulletin, Boeing have completed a WFD assessment and chem-mill step cracks have been discovered while accomplishing general visual or detailed inspections in accordance with the Original Issue of this service bulletin. On the existing skin panel assembly, the doubler is chem-milled to the skin to create pockets of various depths. At these skin panel locations on the airplane, the loads could cause a condition where skin cracks could form along the longitudinal edges of the doubler. The many small cracks or Multiple Site Damage (MSD) in adjoining and identically stressed features can link together over many pressure cycles yielding a visible crack. These cracks can merge together into a larger crack and compromise structural integrity of the airframe. Continued operation with undetected skin cracks could adversely affect the structural integrity of the airplane. This service bulletin gives instructions for inspection, repair and information on replacement of skin panels where cracks can occur between Stringer S-14 and Stringer S-25 and from STA 727 to STA 1016 on the left and right side of the airplane. The inspection in accordance with this bulletin will allow early detection of cracks in the skin panels. The repair of skin cracks in accordance with this service bulletin will restore structural integrity of the skin panel. Replacement of the skin panels in accordance with this service bulletin is terminating action to the repeat inspections given in this service bulletin at the locations where the skin panels were replaced using production skin panels on airplanes with more than 53,000 total flight cycles. Section 46 Lower Lobe skin panels have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). Boeing Service Related Problems (SRP) 737-SRP-53-0416 and 737-SRP-53-0324 are related to this service bulletin. Boeing Fleet Team Digest (FTD) 737 FTD 53-14003 is related to this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 9 of 102 ### Page 10 This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesYesWeight 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 Air- plane Flight Manual) Paragraph 2.C.1., Kits/PartsYesKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION Do an external or internal inspection in Zone 1 and a detailed inspection in Zone 2 for any crack from STA 727 to STA 1016 and Stringer S-14 to Stringer S-25 on the left and right side of the airplane. If any crack is found, do either the time limited repair or the SRM repair in accordance with this service bulletin. If time limited repair is being accomplished, do the post time limited repair inspections until the time limited repair is made permanent in accordance with this service bulletin at times specified in Paragraph 1.E., Compliance. If the SRM repair is being accomplished, do the internal inspections in accordance with this service bulletin before accomplishing the SRM repair. Post repair inspections of the SRM repair must be accomplished in accordance with the SRM. If no crack is found, repeat the inspections in accordance with this service bulletin. If a time limited repair was accomplished in accordance with the Original Issue of this service bulletin, it must be made permanent in accordance with Revision 1 of this service bulletin at times specified in Paragraph 1.E., Compliance. Replace the skin panels at the locations given below in accordance with this service bulletin. Group 1-4: – STA 727 to STA 908, S-14L to S-20L – STA 727 to STA 908, S-20L to S-25L – STA 908 to STA 1016, S-14L to S-20L – STA 908 to STA 1016, S-20L to S-25L – STA 727 to STA 908, S-14R to S-20R – STA 727 to STA 908, S-20R to S-25R – STA 908 to STA 1016, S-20R to S-25R Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 10 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 11 Group 5-6: – STA 908 to STA 1016, S-20R to S-25R – STA 908 to STA 1016, S-14L to S-20L – STA 908 to STA 1016, S-20L to S-25L NOTE: The effectivity is divided into 6 groups because of different skin panel assembly configurations. The areas that require inspection are those where the bonded doubler has pockets fully chem-milled to the bond line or pockets partially chem-milled to a combined skin and doubler thickness of 0.050 inch. EFFECTIVITY 737-500 airplanes, line numbers 1718-2494 and 2498-2553. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-16-07 is related to this service bulletin. The effective date of AD 2012-16-07 is September 18, 2012. The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection and repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits/Parts. Operators are encouraged to complete the survey provided in APPENDIX B of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 11 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 12 (OCR) BOEING SERVICE BULLETIN 737-53-1315 STA INSPECTION, 1016 REPAIR AND SKIN PANEL REPLACEMENT FRAME & STRINGER & STRINGER INSPECT SKIN FOR CRACKS REPAIR IF ANY CRACK IS FOUND. OUTBOARD VIEW OF SKIN (TYPICAL) 2367911 RIGHT SIDE SHOWN, LEFT SIDE SIMILAR Original Issue: July 29, 2011 Revision 1: June 30, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. 737-53-1315 12 of 102 ### Page 13 Commercial Airplanes 737 Service Bulletin SPECIAL ATTENTION Number: 737-53-1315 Original Issue: July 29, 2011 Revision 1: June 30, 2015 ATA System: 5360 SUBJECT: FUSELAGE - Skin - Station 727 to 1016 - Aft Skin Inspection, Repair and Replacement BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. 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. DESCRIPTIONCONFIGURATIONGROUP 737-500 Airplanes within and including basic numbers P7001-P7090 but excluding variable numbers PU001-PU015. -1 737-500 Airplanes within and including basic numbers P7091-P7234 but excluding variable numbers PU016-PU025. -2 737-500 Airplanes within and including variable numbers PU001-PU015. -3 737-500 Airplanes within and including variable numbers PU016-PU025. -4 737-500 Airplanes within and including basic numbers P7235-P7245.-5 737-500 Airplanes within and including basic numbers P7246-P7246.-6 Airplane Models: 737-500 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 13 of 102 ### Page 14 GroupVariable Number 1PT001 - PT004 2PT005 - PT011 1PT021 - PT024 2PT025 - PT027 5PT028 1PT041 - PT043 2PT044 - PT059 5PT060 - PT063 6PT064 1PT101 - PT105 1PT121 - PT125 1PT146 - PT147 2PT148 1PT161 - PT165 2PT166 - PT170 1PT181 - PT184 2PT185 - PT187 1PT211 - PT219 2PT220 1PT295 2PT301 - PT303 5PT304 - PT306 1PT331 - PT351 2PT352 - PT360 1PT381 - PT391 2PT392 - PT399 2PT401 - PT435 5PT436 - PT438 2PT501 - PT512 1PT561 2PT562 - PT565 2PT581 - PT584 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 14 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 15 GroupVariable Number 2PT611 - PT621 2PT641 - PT642 2PT651 - PT655 2PT671 - PT672 2PT701 - PT703 3PU001 - PU015 4PU016 - PU025 2. Spares Affected None. B. Concurrent Requirements None. C. Reason More than three hundred incidents of skin chem-mill cracks on twenty six airplanes have been reported from Body Station (STA) 727 to 1016 and Stringer S-14 to S-25 (left and right side) between 29,808 and 53,454 flight cycles. Most of the skin cracks were found aft of the wing at STA 747 and below the window belt on the left side. Several of the reported cracks occurred in multiple adjacent bays. Since the release of the original version of this service bulletin, Boeing have completed a WFD assessment and chem-mill step cracks have been discovered while accomplishing general visual or detailed inspections in accordance with the Original Issue of this service bulletin. On the existing skin panel assembly, the doubler is chem-milled to the skin to create pockets of various depths. At these skin panel locations on the airplane, the loads could cause a condition where skin cracks could form along the longitudinal edges of the doubler. The many small cracks or Multiple Site Damage (MSD) in adjoining and identically stressed features can link together over many pressure cycles yielding a visible crack. These cracks can merge together into a larger crack and compromise structural integrity of the airframe. Continued operation with undetected skin cracks could adversely affect the structural integrity of the airplane. This service bulletin gives instructions for inspection, repair and information on replacement of skin panels where cracks can occur between Stringer S-14 and Stringer S-25 and from STA 727 to STA 1016 on the left and right side of the airplane. The inspection in accordance with this bulletin will allow early detection of cracks in the skin panels. The repair of skin cracks in accordance with this service bulletin will restore structural integrity of the skin panel. Replacement of the skin panels in accordance with this service bulletin is terminating action to the repeat inspections given in this service bulletin at the locations where the skin panels were replaced using production skin panels on airplanes with more than 53,000 total flight cycles. Section 46 Lower Lobe skin panels have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). Boeing Service Related Problems (SRP) 737-SRP-53-0416 and 737-SRP-53-0324 are related to this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 15 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 16 Boeing Fleet Team Digest (FTD) 737 FTD 53-14003 is related to this service bulletin. Revision 1 is sent to provide new and additional inspection requirements, add requirement to replace skin panels, change compliance time requirements, change time limited repair and permanent repair requirements, and change airplane grouping. D. Description Do an external or internal eddy current inspection in Zone 1 and a detailed inspection in Zone 2 for any crack from STA 727 to STA 1016 and Stringer S-14 to Stringer S-25 on the left and right side of the airplane. If any crack is found, do either the time limited repair or the SRM repair in accordance with this service bulletin. If time limited repair is being accomplished, do the post time limited repair inspections until the time limited repair is made permanent in accordance with this service bulletin at times specified in Paragraph 1.E., Compliance. If the SRM repair is being accomplished, do the internal inspections in accordance with this service bulletin before accomplishing the SRM repair. Post repair inspections of the SRM repair must be accomplished in accordance with the SRM. If no crack is found, repeat the inspections in accordance with this service bulletin. If a time limited repair was accomplished in accordance with the Original Issue of this service bulletin, it must be made permanent in accordance with Revision 1 of this service bulletin at times specified in Paragraph 1.E., Compliance. Replace the skin panels at the locations given below in accordance with this service bulletin. Group 1-4: – STA 727 to STA 908, S-14L to S-20L – STA 727 to STA 908, S-20L to S-25L – STA 908 to STA 1016, S-14L to S-20L – STA 908 to STA 1016, S-20L to S-25L – STA 727 to STA 908, S-14R to S-20R – STA 727 to STA 908, S-20R to S-25R – STA 908 to STA 1016, S-20R to S-25R Group 5-6: – STA 908 to STA 1016, S-20R to S-25R – STA 908 to STA 1016, S-14L to S-20L – STA 908 to STA 1016, S-20L to S-25L NOTE: The effectivity is divided into 6 groups because of different skin panel assembly configurations. The areas that require inspection are those where the bonded doubler has pockets fully chem-milled to the bond line or pockets partially chem-milled to a combined skin and doubler thickness of 0.050 inch. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 16 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 17 Effects of this Revision on airplanes on which Original Issue was previously done: ActionConditionGroup Replace the skin panels in accor- dance with Revision 1 of this service bulletin. All Airplanes.Group 1-6 Do the inspections in accordance with Revision 1 of this service bul- letin. Airplanes that have accomplished at least one inspection in accor- dance with the Original Issue of this service bulletin. Continue post repair inspections and make the time limited repair perma- nent in accordance with Revision 1 of this service bulletin. Do post re- pair inspections of the permanent repair in accordance with Revision 1 of this service bulletin. (a) Airplanes that have accomplished the time limited repair in accordance with the Original Issue of this service bulletin. No more work is necessary until the mandatory skin panel replacement in accordance with Revision 1 of this service bulletin. Airplanes that have accomplished the permanent repair or made the time limited repair permanent in ac- cordance with the Original Issue of this service bulletin. (a) (a) The definition of "permanent repair" has changed from the Original Issue to Revision 1 of this service bulletin. The term "permanent repair" in SB 737-53-1315, Original Issue, refers to the 737-500 SRM 53- 00-01, Figure 201, Repair 31, however in SB 737-53-1315, Revision 1, "permanent repair" refers to modifying the time limited repair in accordance with PART 5: PERMANENT REPAIR INSTALLATION The work in this service bulletin is done in the maintenance zone(s) given below. Affected Maintenance Zones ZoneModel 108, 218, 220737-500 E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-16-07 is related to this service bulletin. The effective date of AD 2012-16-07 is September 18, 2012. 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. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions. NOTE: The Damage Tolerance Inspections specified in Table 2 and Table 3 below may be used in support of compliance with 14 Code of Federal Regulations, Section 121.1109 or 129.109. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 17 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 18 TABLE 1: SKIN INSPECTION REQUIREMENTS Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the effective date of AD 2012-16-07. Before 22,000 total flight cy- cles. Zone 1: Do an internal or external inspection for any crack in accordance with PART 1: INSPECTION. (a) (c) (d) (e) (f) Airplanes that have not had any inspections done in accordance with the Origi- nal Issue of this service bulletin as of the issue date of Revision 1 of this service bulletin. -Within 4,500 flight cycles af- ter the Revision 1 date of this service bulletin. Before 34,000 total flight cy- cles. Zone 2: Do a detailed inspection for any crack in accor- dance with PART 1: IN- SPECTION. (b) (c) (d) (e) (f) -Within 3,700 flight cycles after the last inspection accomplished in accordance with the Original Issue of this service bulletin. Zone 1: Do an internal or external inspection for any crack in accordance with PART 1: INSPECTION. (a) (c) (d) (e) (f) Airplanes that have had at least one inspection done in accordance with the Original Issue of this ser- vice bulletin as of the issue date of Revision 1 of this service bulletin. -Within 4,500 flight cycles af- ter the Revision 1 date of this service bulletin. Before 34,000 total flight cy- cles. Zone 2: Do a detailed inspection for any crack in accor- dance with PART 1: IN- SPECTION. (b) (c) (d) (e) (f) OPTION 1: Time Limited Repair.Any crack found at a loca- tion inspected in accor- dance with PART 1. -Before further flight.Repair all cracks with thetime limited repair in ac- cordance with PART 3: REPAIR. (g) OPTION 2: SRM Repair. -Before further flight.Repair all cracks with the SRM repair in accor- dance with PART 3: RE- PAIR. (g) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 18 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 19 TABLE 1: SKIN INSPECTION REQUIREMENTS Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 3,700 flight cycles. (g) -Zone 1: Repeat the internal or ex- ternal inspection for any crack in accordance with PART 1: INSPECTION. (a) (c) (d) (e) (f) No crack found at a loca- tion inspected in accor- dance with PART 1. 7,500 flight cycles. (g) -Zone 2: Repeat the detailed in- spection for any crack in accordance with PART 1: INSPECTION. (b) (c) (d) (e) (f) (a) Zone 1: Skin and bonded doubler with the bonded doubler chem-milled to the bond line in the pocket. (b) Zone 2: Skin and bonded doubler with a chem-milled pocket thickness of 0.050 inch and with the bonded doubler partially chem-milled. (c) It is not required to inspect the chem-mill steps under existing external repair doublers provided either: 1. The installed repair was approved by the FAA or a Boeing company authorized representative who was authorized by the FAA to make such findings, and the installed repair extends a mini- mum of three rows of fasteners on each side of the chem-mill line, or 2. The external repair doubler satisfies the following: – The installed repair was approved by the FAA or a Boeing company authorized represen- tative who was authorized by the FAA to make such findings, and – The repair extends a minimum of 2 rows of 3/16 inch diameter fasteners on each side of the chem-mill step in the circumferential direction with 5-6D fastener spacing, and – The repair is similar to 737-500 SRM 53-00-01, Figure 201, Repair 31, with regard to fas- tener type, size, layout and pitch, repair part thickness and material, and repair installation. (d) Internal inspections can only be accomplished if it is not possible to do the external inspections of the chem-mill steps for cracks due to interference with external repair doublers or existing structure. The wing-to-body fairing must be removed to accomplish external inspections. Internal inspections in accor- dance with 737 NDT Manual Part 4, 53-30-05 and 737 NDT Manual Part 6, 53-30-22 with the pencil probe specified in the procedure can be done as an alternative to external inspections. It is optional to accomplish 737 NDT Manual Part 4, 53-30-06 instead of 737 NDT Manual Part 4, 53-30-05 and 737 NDT Manual Part 6, 53-30-22. – If repair fasteners prevent 737 NDT Manual Part 4, 53-30-05 or 737 NDT Manual Part 4, 53-30-06 from being accomplished across the full length of the chem-mill step, do one of the above inspections between the fasteners, where the probe will fit, and also do 737 NDT Manual Part 6, 53-30-22 using the pencil probe specified in the procedure along the full length of the chem-mill step. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 19 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 20 TABLE 1: SKIN INSPECTION REQUIREMENTS Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (e) If the operator has record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles, contact Boeing to get work instructions and do the work. If the operator does not have record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles, inspections are required on that skin panel at the compliance time specified in this table. (f) Inspections are not required on production skin panels that have been replaced with production skin panels after 53,000 total flight cycles. (g) Accomplishment of PART 3: REPAIR is terminating action for repeat inspection requirements at the re- paired locations only. TABLE 2: POST REPAIR INSPECTION AND MODIFICATION OF TIME LIMITED REPAIR INSTALLED IN ACCORDANCE WITH THE ORIGINAL ISSUE OR REVISION 1 OF THIS SERVICE BULLETIN Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,000 flight cycles after the installation of the time limited re- pair. (a) Do an external general visual inspection for any loose or missing fastener common to the repaired area in accordance with PART 4: POST REPAIR INSPECTION OF TIME LIMITED REPAIR. Airplanes with a time limit- ed repair installed in accor- dance with the Original Is- sue or Revision 1 of this service bulletin as of the issue date of Revision 1 of this service bulletin. -Within 4,500 flight cycles after the installation of the time limited re- pair. (a) Zone 1: Do a detailed in- spection of the bonded doubler for disbond and a HFEC inspection for any crack in the bonded doubler in accordance with PART 4: POST RE- PAIR INSPECTION OF TIME LIMITED REPAIR. (b) -Within 4,500 flight cycles after the installation of the time limited re- pair. (a) Zone 2: Do a HFEC in- spection for any crack in the bonded doubler in accordance with PART 4: POST REPAIR INSPEC- TION OF TIME LIMITED REPAIR. (c) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 20 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 21 TABLE 2: POST REPAIR INSPECTION AND MODIFICATION OF TIME LIMITED REPAIR INSTALLED IN ACCORDANCE WITH THE ORIGINAL ISSUE OR REVISION 1 OF THIS SERVICE BULLETIN Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Replace all loose or missing fasteners in ac- cordance with PART 4: POST REPAIR INSPEC- TION OF TIME LIMITED REPAIR. Any loose or missing fasten- er found. 3,000 flight cycles. (a) -Repeat the general visual inspection for any loose or missing fastener com- mon to the repair area in accordance with PART 4: POST REPAIR INSPEC- TION OF TIME LIMITED REPAIR. 3,000 flight cycles. (a) -Repeat the general visual inspection for any loose or missing fastener com- mon to the repaired area in accordance with PART 4: POST REPAIR IN- SPECTION OF TIME LIMITED REPAIR. No loose or missing fasten- er found. -Before further flight.Contact The Boeing Company for work instruc- tions and do the work. Any crack or disbond found. -Within 6,000 flight cycles after the installation of the time limited re- pair. Make the time limited re- pair permanent in accor- dance with PART 5: PERMANENT REPAIR INSTALLATION. (a) No crack or disbond found. (a) Accomplishment of PART 5: PERMANENT REPAIR INSTALLATION in accordance with this Service Bulletin is terminating action for the repeat inspections given in this table. (b) Zone 1: Skin and bonded doubler with the bonded doubler chem-milled to the bond line in the pocket. (c) Zone 2: Skin and bonded doubler with a chem-milled pocket thickness of 0.050 inches and the bonded doubler partially chem-milled. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 21 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 22 TABLE 3: POST REPAIR INSPECTION OF PERMANENT REPAIRS INSTALLED IN ACCORDANCE WITH PART 5: PERMANENT REPAIR INSTALLATION OF REVISION 1 OF THIS SERVICE BULLETIN. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 5,000 flight cycles after ac- complishment of PART 5: PERMA- NENT REPAIR INSTALLATION, OPTION 1. Do PART 6: POST RE- PAIR INSPECTION OF PERMANENT REPAIR. Airplanes with a permanent repair installed in accor- dance with PART 5: PER- MANENT REPAIR INSTAL- LATION, OPTION 1. -Within 60,000 flight cycles after accomplishment of PART 5: PERMANENT REPAIR INSTALLA- TION, OPTION 2. Do PART 6: POST RE- PAIR INSPECTION OF PERMANENT REPAIR. Airplanes with a permanent repair installed in accor- dance with PART 5: PER- MANENT REPAIR INSTAL- LATION, OPTION 2. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. Any crack found. 5,000 flight cycles.-Repeat PART 6: POST REPAIR INSPECTION OF PERMANENT RE- PAIR. No crack found. TABLE 4: SKIN PANEL REPLACEMENT Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,000 flight cycles af- ter the Revision 1 date of this service bulletin. Before 60,000 total flight cycles but not before 53,000 total flight cycles. Replace the skin panels in accordance with PART 2: SKIN PANEL RE- PLACEMENT. (a) (b) (c) All Airplanes. (a) If the operator has record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles, contact Boeing to get work instructions and do the work. If the operator does not have record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles, skin panel replacement is required at that location at the compliance time specified in this table. (b) Skin panel replacement is not required on the production skin panels that were replaced with production skin panels after 53,000 total flight cycles. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 22 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 23 TABLE 4: SKIN PANEL REPLACEMENT Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (c) Replace the following skin panels: Group 1-4: - STA 727 to STA 908, S-14R to S-20R - STA 727 to STA 908, S-20R to S-25R - STA 908 to STA 1016, S-20R to S-25R - STA 727 to STA 908, S-14L to S-20L - STA 727 to STA 908, S-20L to S-25L - STA 908 to STA 1016, S-14L to S-20L - STA 908 to STA 1016, S-20L to S-25L Group 5-6: - STA 908 to STA 1016, S-20R to S-25R - STA 908 to STA 1016, S-14L to S-20L - STA 908 to STA 1016, S-20L to S-25L 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. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves accomplishment of the inspections, repairs, skin panel replacement, and compliance times defined in Revision 1 of this service bulletin as an Alternative Method of Compliance (AMOC) to the requirements of paragraphs (g) and (h) of Airworthiness Directive AD 2012-16-07. All provisions of AD 2012-16-07 that are not specifically referenced in the above statement remain fully applicable and must be complied with accordingly. Where SB 737-53-1315, Revision 1, specifies to contact Boeing for appropriate action: Prior to further flight, repair using a method approved in accordance with paragraph (j) of AD 2012-16-07. 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 23 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 24 G. Manpower The table below shows an estimate of the task hours necessary to do this inspection and repair for each 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. Group 1-4: EXTERNAL INSPECTION Elapsed HoursTask HoursNumber of PersonsTask 3.006.002Open Access 3.7014.804FIGURE 5 - General Visual Inspection 3.0012.004FIGURE 5 - Detailed Inspection 70.50282.004FIGURE 5 - Subsur- face Inspection 3.006.002Close Access 83.20320.80TOTAL FOR EACH AIRPLANE Group 5-6: EXTERNAL INSPECTION Elapsed HoursTask HoursNumber of PersonsTask 3.006.002Open Access 1.807.204FIGURE 5 - General Visual Inspection 3.0012.004FIGURE 5 - Detailed Inspection 19.7078.804FIGURE 5 - Subsur- face Inspection 3.006.002Close Access 30.50110.00TOTAL FOR EACH AIRPLANE Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 24 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 25 Group 1-4: INTERNAL INSPECTION Elapsed HoursTask HoursNumber of PersonsTask 61.55492.408Open Access 25.60102.404FIGURE 6 - Detailed Inspection 106.95427.804FIGURE 6 - HFEC Inspection 61.55492.408Close Access 255.651515.00TOTAL FOR EACH AIRPLANE Group 5-6: INTERNAL INSPECTION Elapsed HoursTask HoursNumber of PersonsTask 29.75238.008Open Access 7.1028.404FIGURE 6 - Detailed Inspection 51.75207.004FIGURE 6 - HFEC Inspection 29.75238.008Close Access 118.35711.40TOTAL FOR EACH AIRPLANE TIME LIMITED REPAIR Elapsed HoursTask HoursNumber of PersonsTask 2.004.002Open Access 7.75 (a)15.50 (a)2FIGURE 7 2.004.002Close Access 11.7523.50TOTAL FOR EACH AIRPLANE (a) The time given is for one repair location PERMANENT REPAIR Elapsed HoursTask HoursNumber of PersonsTask 2.004.002Open Access 2.004.002OPTION 1 (a) 15.5031.002OPTION 2 (a) 2.004.002Close Access Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 25 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 26 PERMANENT REPAIR Elapsed HoursTask HoursNumber of PersonsTask (b)(b)TOTAL FOR EACH AIRPLANE (a) Time to make parts not included in Estimate. (b) Total time will be dependent upon the number and type of repair installed. POST REPAIR INSPECTION OF PERMANENT REPAIR Elapsed HoursTask HoursNumber of PersonsTask 3.003.001FIGURE 12 3.703.702FIGURE 13 (a)(a)TOTAL FOR EACH AIRPLANE (a) Total time required dependent upon the number and size of repairs requiring inspection. H. Weight and Balance Changes All airplanes: Change in Moment (Pound-Inches)Change in Weight (Pounds) --Skin Replacement +/- 0.00+/- 0.00Left Side +/- 0.00+/- 0.00Right Side +/- 0.00+/- 0.00Total Change in Moment (Pound- Inches per doubler) Change in Weight (Pounds per doubler) --Time Limited Repair +2,750 per doubler+3.5Between Station 727 and 787 +3,170 per doubler+3.5Between Station 787 and 907 +3,580 per doubler+3.5Between Station 907 and 1016 I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Boeing Service Bulletin 737-53-1315, 737-53A1177 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 26 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 27 b. Boeing Service Letter 737-SL-51-042 c. Boeing Service Related Problem (SRP) 737-SRP-53-0324, 737-SRP-53-0416 d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2012-16-07 e. Service Bulletin Index D6-19567 f. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-41-05, 20-43-03, 20-44-04, 20-50-01, 20-50-19 g. 737 Fleet Team Digest (FTD) 53-14003 h. 737 Non-Destructive Testing (NDT) Manual Part 4, 53-30-05, Part 4, 53-30-06, Part 6, 51-00-00 Procedure 16, Part 6, 51-00-00 Procedure 23, Part 6, 51-00-00 Procedure 4, Part 6, 53-30-00 Procedure 3, Part 6, 53-30-00 Procedure 4, Part 6, 53-30-00 Procedure 5, Part 6, 53-30-19, Part 6, 53-30-22, Part 6, 53-30-23, Part 6, 53-30-25, Part 6, 53-30-39 i. 737-300/400/500 Aircraft Maintenance Manual (AMM) 25-21-39, 25-21-46, 25-22-00, 25-27-15, 25-52-73, 25-52-91 j. 737-500 Structural Repair Manual (SRM) 51-40-02, 51-40-03, 51-40-08, 51-50-02, 53-00-01 2. Data Supplied with this Service Bulletin: a. Drawings: ADCNDCN/REVSheetTitleDrawing No --31SKIN PANEL INSTL-S-14L TO S-25L STA 727 TO STA 908 65-45774 --32 --33 --34 -CKPL --PSDLSKIN PANEL INSTL-S-14L TO S-25L, STATION 727 TO STATION 908 65-45774#DL -A35SKIN PANEL INSTALLATION-S-14R TO S-25R, STA 727 TO STA 908 65-45775 -A36 -A37 -B38 -CYPL --PSDLSKIN PANEL INSTL-S-14R TO S-25R, STA 727 TO STA 908 65-45775#DL Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 27 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 28 ADCNDCN/REVSheetTitleDrawing No -B15SKIN PANEL INSTL-AFT GALLEY DOOR, STA 908-STA 1016 S-4R - S-25R 65-45778 -B20 -DYPL --PSDLSKIN PANEL INSTL-AFT GALLEY DOOR, STA 908-STA 1016 S-4R - S-25R 65-45778#DL -C20SKIN PANEL INSTL-S-4L TO S-25L, STA 908 TO STA 1016 65-52988 -B21 -DPPL --PSDLSKIN PANEL INSTL-S-4L TO S-25L, STA 908 TO STA 1016 65-52988#DL -A4SKIN INSTL - AFT GALLEY DOOR, STA 908 TO STA 1016, S-4L TO S-25L 65C27755 --5 -CPL --PSDLSKIN INSTL - AFT GALLEY DOOR, STA 908 TO STA 1016, S-4L TO S-25L 65C27755#DL --4SKIN INSTL - AFT GALLEY DOOR, STA 908 TO STA 1016, S-4R TO S-25R 65C27756 --5 -DPL --PSDLSKIN INSTL - AFT GALLEY DOOR, STA 908 TO STA 1016, S-4R TO S-25R 65C27756#DL 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number Skin Panel Instl - S-14L to S-25L, STA 727 to STA 90865-45774 Skin Panel Installation, S-14R to S-25R, STA 727 to STA 90865-45775 Skin Panel Instl - Aft Galley Door, STA 908 - STA 1016, S-4R to S-25R65-45778 Skin Panel Instl - S-4L to S-25L, STA 908 to STA 101665-52988 Skin Instl - Aft Entry Door, STA 908 TO STA 1016, S-4L TO S-25L65C27755 Skin Instl - Aft Galley Door, STA 908 TO STA 1016, S-4R TO S-25R65C27756 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 28 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 29 None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected are contained in 737-500 SRM 53-00-01, Figure 201, Repair 31, for the SRM repair. The time limited repair is considered a category "C" repair that must be modified within the compliance time given in Paragraph 1.E., Compliance. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance, for the time limited repair, after it has been made permanent. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 29 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 30 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 30 of 102 BOEING SERVICE BULLETIN 737-53-1315 BLANK PAGE ### Page 31 2. MATERIAL INFORMATION A. Material - Price and Availability 1. Group 1-4: For skin panels in the following locations: – STA 727 to STA 908, S-14L to S-20L – STA 727 to STA 908, S-20L to S-25L – STA 908 to STA 1016, S-14L to S-20L – STA 908 to STA 1016, S-20L to S-25L – STA 727 to STA 908, S-14R to S-20R – STA 727 to STA 908, S-20R to S-25R – STA 908 to STA 1016, S-20R to S-25R a. Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane for the skin panel locations shown above. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. Contact Boeing for ROLT and pricing information. NOTE: Due to the nature of the skin panel replacement, extensive coordination is required. Operators are encouraged to share scheduling requirements with Boeing and to contact Boeing for replacement part information as soon as possible. Contact Boeing for ROLT and pricing information for the parts shown in Paragraph 2.A., Material - Price and Availability. 2. Group 5-6: For skin panels in the following locations: – STA 908 to STA 1016, S-20R to S-25R – STA 908 to STA 1016, S-14L to S-20L – STA 908 to STA 1016, S-20L to S-25L a. Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane for the skin panel locations shown above. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. Contact Boeing for ROLT and pricing information. NOTE: Due to the nature of the skin panel replacement, extensive coordination is required. Operators are encouraged to share scheduling requirements with Boeing and to contact Boeing for replacement part information as soon as possible. Contact Boeing for ROLT and pricing information for the parts shown in Paragraph 2.A., Material - Price and Availability. 3. The parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 31 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 32 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA Operators are encouraged to complete the survey provided in APPENDIX B of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Parts. B. Industry Support Information Boeing warranty remedies are not available for the inspection and repair procedures given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts a. To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability. Group 1: NotesQuantityStation LocationStringer LocationNamePart Number (a)1STA 727 to STA 908S-14R to S-20RSkin Assembly65C32365-40 (a)1STA 727 to STA 908S-20R to S-25RSkin Assembly65C32365-39 (a)1STA 908 to STA 1016S-20R to S-25RSkin Panel As- sembly 65-45778Y85 (a)1STA 727 to STA 908S-14L to S-20LSkin Assembly65C32364-36 (a)1STA 727 to STA 908S-20L to S-25LSkin Assembly65C32364-37 (a)1STA 908 to STA 1016S-14L to S-20LPanel Assembly65-52988Y73 (a)1STA 908 to STA 1016S-20L to S-25LPanel Assembly65-52988Y125 (a) Parts have a long lead time and extensive coordination with Boeing will be necessary. Group 2: NotesQuantityStation LocationStringer LocationNamePart Number (a)1STA 727 to STA 908S-14R to S-20RSkin Assembly65C32365-38 (a)1STA 727 to STA 908S-20R to S-25RSkin Assembly65C32365-39 (a)1STA 908 to STA 1016S-20R to S-25RSkin Panel As- sembly 65-45778Y85 (a)1STA 727 to STA 908S-14L to S-20LSkin Assembly65C32364-36 (a)1STA 727 to STA 908S-20L to S-25LSkin Assembly65C32364-37 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 32 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 33 Group 2: NotesQuantityStation LocationStringer LocationNamePart Number (a)1STA 908 to STA 1016S-14L to S-20LPanel Assembly65-52988Y73 (a)1STA 908 to STA 1016S-20L to S-25LPanel Assembly65-52988Y125 (a) Parts have a long lead time and extensive coordination with Boeing will be necessary. Group 3: NotesQuantityStation LocationStringer LocationNamePart Number (a)1STA 727 to STA 908S-14R to S-20RSkin Assembly65C32365-40 (a)1STA 727 to STA 908S-20R to S-25RSkin Assembly65C32365-39 (a)1STA 908 to STA 1016S-20R to S-25RSkin Panel As- sembly 65-45778Y85 (a)1STA 727 to STA 908S-14L to S-20LSkin Assembly65C32364-36 (a)1STA 727 to STA 908S-20L to S-25LSkin Assembly65C32364-37 (a)1STA 908 to STA 1016S-14L to S-20LPanel Assembly65-52988Y73 (a)1STA 908 to STA 1016S-20L to S-25LPanel Assembly65-52988Y74 (a) Parts have a long lead time and extensive coordination with Boeing will be necessary. Group 4: NotesQuantityStation LocationStringer LocationNamePart Number (a)1STA 727 to STA 908S-14R to S-20RSkin Assembly65C32365-38 (a)1STA 727 to STA 908S-20R to S-25RSkin Assembly65C32365-39 (a)1STA 908 to STA 1016S-20R to S-25RSkin Panel As- sembly 65-45778Y85 (a)1STA 727 to STA 908S-14L to S-20LSkin Assembly65C32364-36 (a)1STA 727 to STA 908S-20L to S-25LSkin Assembly65C32364-37 (a)1STA 908 to STA 1016S-14L to S-20LPanel Assembly65-52988Y73 (a)1STA 908 to STA 1016S-20L to S-25LPanel Assembly65-52988Y74 (a) Parts have a long lead time and extensive coordination with Boeing will be necessary. Group 5: NotesQuantityStation LocationStringer LocationNamePart Number (a)1STA 908 to STA 1016S-20R to S-25RSkin Panel As- sembly 65-45778Y85 (a)1STA 908 to STA 1016S-14L to S-20LPanel Assembly65-52988Y73 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 33 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 34 Group 5: NotesQuantityStation LocationStringer LocationNamePart Number (a)1STA 908 to STA 1016S-20L to S-25LPanel Assembly65-52988Y125 (a) Parts have a long lead time and extensive coordination with Boeing will be necessary. Group 6: NotesQuantityStation LocationStringer LocationNamePart Number (a)1STA 908 to STA 1016S-20R to S-25RSkin Panel As- sembly 65-45778Y85 (a)1STA 908 to STA 1016S-14L to S-20LPanel Assembly65-52988-120 (a)1STA 908 to STA 1016S-20L to S-25LPanel Assembly65-52988Y125 (a) Parts have a long lead time and extensive coordination with Boeing will be necessary. 2. Parts and Materials Supplied by the Operator The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available. Parts for PART 3: TIME LIMITED REPAIR NotesNameQTYPart Number / Specification (a)Repair doubler1 (40 inches x 30 inches) AMS QQ-A-250/5, 2024-T3 clad sheet (b)Blind Fasteneras necessaryBACR15FR5E( )R (b)Blind Fasteneras necessaryBACR15FR6E( )R (c)Primeras necessaryBMS 10-11, TYPE I (c) (d)Sealantas necessaryBMS 5-95 CLASS B-1/2, B-2 Refer to SOPM 20-43- 03. Chemical Film Treatmentas necessaryALODINE or IRIDITE Refer to SOPM 20-44- 04 Primeras necessaryBMS 10-79 TYPE III (a) Use to make a repair doubler in accordance with FIGURE 7. (b) Fastener substitution is permitted in accordance with 737 SRM Chapter 51. (c) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (d) Refer to SOPM 20-50-19. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 34 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 35 Parts for PART 5: PERMANENT REPAIR INSTALLATION NotesNameQTYPart Number / Specification -Repair doubler, tear strap dou- bler and tapered filler 1 (40 inches x 30 inches) AMS QQ-A-250/5, 2024-T3 clad sheet (a) (d)Rivetas necessaryBACR15BB6D( )C or BACR15ET7AD( )C or BACR15BB6AD( )C (b) Refer to SOPM 20- 41-02 Primeras necessaryBMS 10-11, TYPE I (b) (c)Sealantas necessaryBMS 5-95, CLASS B-1/2, B-2 (b) Refer to SOPM 20- 41-05 Corrosion Inhibiting Compoundas necessaryBMS 3-23, TYPE II Refer to SOPM 20-43- 03. Chemical Film Treatmentas necessaryALODINE or IRIDITE Refer to SOPM 20-44- 04 Primeras necessaryBMS 10-79 TYPE III (a) Fastener substitution is permitted in accordance with 737 SRM Chapter 51. (b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (c) Refer to SOPM 20-50-19. (d) Quantity of fasteners necessary is different between FIGURE 8, FIGURE 9, FIGURE 10 and FIGURE 11. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 35 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 36 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 36 of 102 BOEING SERVICE BULLETIN 737-53-1315 BLANK PAGE ### Page 37 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque Values: — Values for structural fasteners are given in 737 Structural Repair Manual, Chapter 51. 4. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin. 6. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 7. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 37 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 38 8. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 9. Boeing Service Letter 737-SL-51-042, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 10. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 11. Some Boeing parts are supplied in a temporary configuration. Those parts are identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-' (dash) part number. Boeing Drawing 005W0900 contains more data. 12. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 13. Refer to APPENDIX A for production skin panel installation drawing identification. The skin panels identified in Paragraph 2.C.1., Kits/Parts, are approved skin panel replacements. B. WORK INSTRUCTIONS 1. PART 1: INSPECTION NOTE: If the operator has record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles, contact Boeing to get work instructions and do the work. If the operator does not have record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles, inspections are required on that skin panel at the compliance time specified in Table 1 in Paragraph 1.E., Compliance of this service bulletin. NOTE: Inspections are not required on production skin panels that have been replaced with production skin panels after 53,000 total flight cycles. a. Determine inspection zones in accordance with: – Group 1-4: FIGURE 1 and FIGURE 2. – Group 5-6: FIGURE 3 and FIGURE 4. b. Do the actions that follow: (1) In Zone 1, do an internal or external inspection for any crack in accordance with FIGURE 5. In Zone 2, do a detailed inspection for any crack in accordance with FIGURE 5. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 38 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 39 NOTE: It is not required to inspect the chem-mill steps under existing external repair doublers provided either: 1. The installed repair was approved by the FAA or by a Boeing company authorized representative who was authorized by the FAA to make such findings, and the installed repair extends a minimum of three rows of fasteners on each side of the chem-mill line, or 2. The external repair doubler satisfies the following: – The installed repair was approved by the FAA or by a Boeing company authorized representative who was authorized by the FAA to make such findings, and – The repair extends a minimum of 2 rows of 3/16 inch diameter fasteners on each side of the chem-mill step in the circumferential direction with 5-6D fastener spacing, and – The repair is similar to 737-500 SRM 53-00-01, Figure 201, Repair 31, with regard to fastener type, size, layout, and pitch, repair part thickness and material, and repair installation. NOTE: Internal inspections can only be accomplished if it is not possible to do the external inspections of the chem-mill steps for cracks due to interference with external repair doublers or existing structure. The wing-to-body fairing must be removed to accomplish external inspections. Internal inspections in accordance with 737 NDT Manual Part 4, 53-30-05 and 737 NDT Manual Part 6, 53-30-22 with the pencil probe specified in the procedure can be done as an alternative to external inspections. It is optional to accomplish 737 NDT Manual Part 4, 53-30-06 instead of 737 NDT Manual Part 4, 53-30-05 and 737 NDT Manual Part 6, 53-30-22. If repair fasteners prevent 737 NDT Manual Part 4, 53-30-05 or 737 NDT Manual Part 4, 53-30-06 from being accomplished across the full length of the chem-mill step, do one of the above inspections between the fasteners, where the probe will fit, and also do 737 NDT Manual Part 6, 53-30-22 using the pencil probe specified in the procedure along the full length of the chem-mill step. (2) If any crack is found, do one of the options in PART 3: REPAIR (3) If no crack is found then repeat PART 1: INSPECTION at the repeat interval in accordance with Paragraph 1.E., Compliance. NOTE: Inspections are not required on production skin panels that have been replaced with production skin panels after 53,000 total flight cycles. (4) Replace the skin panels in accordance with PART 2: SKIN PANEL REPLACEMENT at the time given in Paragraph 1.E., Compliance. NOTE: Due to the nature of the skin panel replacement, extensive coordination is required. Operators are encouraged to share scheduling requirements with Boeing and to contact Boeing for replacement part information as soon as possible. Contact Boeing for ROLT and pricing information for the parts shown in Paragraph 2.A., Material - Price and Availability. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 39 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 40 2. PART 2: SKIN PANEL REPLACEMENT NOTE: If the operator has record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles, contact Boeing to get work instructions and do the work. If the operator does not have record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles, skin panel replacement is required at that location at the compliance time specified in Table 4 in Paragraph 1.E., Compliance of this service bulletin. NOTE: Skin panel replacement is not required on production skin panels that were replaced with production skin panels after 53,000 total flight cycles. NOTE: Do not replace more than one skin panel at a time. a. Group 1-4: Do the actions that follow for skin panels at the locations given below: – STA 727 to STA 908, S-14L to S-20L – STA 727 to STA 908, S-20L to S-25L – STA 908 to STA 1016, S-14L to S-20L – STA 908 to STA 1016, S-20L to S-25L – STA 727 to STA 908, S-14R to S-20R – STA 727 to STA 908, S-20R to S-25R – STA 908 to STA 1016, S-20R to S-25R NOTE: Due to the nature of the skin panel replacement, extensive coordination is required. Operators are encouraged to share scheduling requirements with Boeing and to contact Boeing for replacement part information as soon as possible. Contact Boeing for ROLT and pricing information for the parts shown in Paragraph 2.A., Material - Price and Availability. (1) Support the airplane in jig position in accordance with 737-500 SRM 51-50-02. (2) Remove fasteners in accordance with 737-500 SRM 51-40-02. (3) Replace the skin panels in accordance with the production skin panel installation drawing. See APPENDIX A for installation drawing identification. Do not replace more than one skin panel at a time. (4) If replacing a skin panel that is common to an existing lap joint modification accomplished in accordance with Service Bulletin (SB) 737-53A1177, reinstall the lap joint modification in accordance with SB 737-53A1177. (5) Install fasteners in accordance with the installation drawings identified in APPENDIX A. (a) Do not oversize any fastener hole more than 1/32 inch diameter larger than the production diameter. (b) Maintain 1.7D edge margin with existing fastener hole locations. (c) Fastener substitution is allowed in accordance with 737-500 SRM 51-40-03. (6) Put the airplane back to a serviceable condition. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 40 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 41 b. Group 5-6: Do the actions that follow for skin panels at the locations given below: – STA 908 to STA 1016, S-14L to S-20L – STA 908 to STA 1016, S-20L to S-25L – STA 908 to STA 1016, S-20R to S-25R NOTE: Due to the nature of the skin panel replacement, extensive coordination is required. Operators are encouraged to share scheduling requirements with Boeing and to contact Boeing for replacement part information as soon as possible. Contact Boeing for ROLT and pricing information for the parts shown in Paragraph 2.A., Material - Price and Availability. (1) Support the airplane in jig position in accordance with 737-500 SRM 51-50-02. (2) Remove fasteners in accordance with 737-500 SRM 51-40-02. (3) Replace the skin panels in accordance with the production skin panel installation drawing. See APPENDIX A for installation drawing identification. Do not replace more than one skin panel at a time. (4) Install fasteners in accordance with the installation drawings identified in APPENDIX A. (a) Do not oversize any fastener hole more than 1/32 inch diameter larger than the production diameter. (b) Maintain 1.7D edge margin with existing fastener hole locations. (c) Fastener substitution is allowed in accordance with 737-500 SRM 51-40-03. (5) Put the airplane back to a serviceable condition. 3. PART 3: REPAIR a. OPTION 1: Time Limited Repair CAUTION: USE CAUTION WHEN LOCATING BLIND FASTENERS RELATIVE TO HIDDEN INTERNAL STRUCTURE. DRILLING INTO HIDDEN INTERNAL STRUCTURE OR EQUIPMENT, MAY RESULT IN DOWNTIME FOR EXPENSIVE REPAIR. (1) For typical cracks in the skin at the chem-mill step, except at the fuselage cut-outs, lap splice, and the butt joints, do the repair in accordance with FIGURE 7. (2) If the time limited repair is done in accordance with this service bulletin, do the post repair inspection of the time limited repair in accordance with PART 4: POST REPAIR INSPECTION OF TIME LIMITED REPAIR at the times specified in Paragraph 1.E., Compliance. (3) This repair can only be used to repair one chem-mill crack, if an additional chem-mill crack or an existing repair is within 40 inches, repair the crack in accordance with PART 3: REPAIR, OPTION 2: SRM Repair. (4) Put the airplane back to a serviceable condition. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 41 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 42 b. OPTION 2: SRM Repair (1) Get access to the internal surface of the skin: (a) Remove the passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. (b) Remove the passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. (c) Remove the passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. (d) Remove the passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. (e) Remove the aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. (2) In Zone 1, do a detailed inspection of the bonded doubler for any disbond and an HFEC inspection for any crack in the bonded doubler in accordance with FIGURE 6. In Zone 2, do a HFEC inspection for any crack in the bonded doubler in accordance with FIGURE 6. NOTE: The HFEC inspections are not required along the horizontal edge of the bonded doubler if the stringer does not make it possible to place the eddy current probe at the proper location for inspection. (3) If a shear-tie does not make it possible to place the eddy current probe at the proper location for this inspection, remove the two end fasteners from the shear-tie in the area of the inspection and do an open hole HFEC inspection in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 16. If no crack is found and a repair doubler will be installed common to the inspected hole, install a repair fastener in accordance with the repair instructions. If no crack is found and a repair doubler will not be installed common to the hole, install the same size and type as the production fastener. If the hole was changed from production, contact The Boeing Company for work instructions and do the work. (4) If any disbond is found, contact The Boeing Company for work instructions and do the work. (5) If no disbond is found, repair all cracks found in accordance with 737-500 SRM 53-00-01, Figure 201, Repair 31 (6) Install the furnishings that were removed for access: (a) Install the aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 42 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 43 (b) Install the passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. (c) Install the passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. (d) Install the passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. (e) Install the passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. (7) Put the airplane back to a serviceable condition. 4. PART 4: POST REPAIR INSPECTION OF TIME LIMITED REPAIR NOTE: Making the time limited repair permanent in accordance with PART 5: PERMANENT REPAIR INSTALLATION is terminating action for the inspection requirement in Table 2 in Paragraph 1.E., Compliance of this service bulletin. a. Do an external general visual inspection for any loose or missing fastener common to the repaired area at times given in Paragraph 1.E., Compliance. (1) If any loose or missing fastener is found, replace all loose or missing fasteners with the same size and type as the fastener installed in accordance with FIGURE 7 and repeat PART 4: POST REPAIR INSPECTION OF TIME LIMITED REPAIR at the repeat interval in accordance with Paragraph 1.E., Compliance. NOTE: When replacing fasteners, make sure that the fastener holes are round, clean, and not damaged. Make sure that the hole diameters are in accordance with FIGURE 7. (2) If no loose or missing fastener is found, repeat PART 4: POST REPAIR INSPECTION OF TIME LIMITED REPAIR at the repeat interval in accordance with Paragraph 1.E., Compliance. b. Do an internal inspection of the bonded doubler for any crack or disbond common to the repaired area at the times given in Paragraph 1.E., Compliance as follows: (1) Get access to the internal surface of the skin: (a) Remove the passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. (b) Remove the passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. (c) Remove the passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. (d) Remove the passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 43 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 44 (e) Remove the aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. (2) In Zone 1, do a detailed inspection of the bonded doubler for any disbond and a HFEC inspection for any crack in the bonded doubler in accordance with FIGURE 6. In Zone 2, do a HFEC inspection for any crack in the bonded doubler in accordance with FIGURE 6. (a) If any crack or disbond is found, contact The Boeing Company to get work instructions and do the work. (b) If no crack or disbond is found, do PART 5: PERMANENT REPAIR INSTALLATION at the time given in Paragraph 1.E., Compliance. (3) Install the furnishings that were removed for access: (a) Install the aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. (b) Install the passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. (c) Install the passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. (d) Install the passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. (e) Install the passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. (4) Put the airplane back to a serviceable condition. 5. PART 5: PERMANENT REPAIR INSTALLATION NOTE: Making the time limited repair permanent in accordance with PART 5: PERMANENT REPAIR INSTALLATION is terminating action for the inspection requirement in Table 2 in Paragraph 1.E., Compliance of this service bulletin. a. For airplanes with a time limited repair installed in accordance with the Original Issue of this service bulletin, the time limited repair must be modified to a permanent repair within the times given in Paragraph 1.E., Compliance using one of the following two options: OPTION 1: Make the time limited repair permanent by replacing the blind fasteners and installing internal tear strap doublers as follows: (1) Access the area as follows: – Remove and keep the passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 44 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 45 – Remove and keep the passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. – Remove and keep the passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. – Remove and keep the passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. – Remove and keep the aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. (2) Remove all blind fasteners common to the existing time limited repair. (3) Do an open hole HFEC inspection of the fastener holes for any crack common to the repaired area in accordance with FIGURE 8. (4) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (5) If no crack is found, continue to do the time limited repair modification in accordance with FIGURE 8. (6) Close access as follows: – Install kept aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. – Install kept passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. – Install kept passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. – Install kept passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. – Install kept passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. (7) Put the airplane back to a serviceable condition. (8) Do post repair inspections of the permanent repair in accordance with PART 6: POST REPAIR INSPECTION OF PERMANENT REPAIR at times specified in Paragraph 1.E., Compliance. OPTION 2: Make the time limited repair permanent by removing the existing external repair doubler and installing internal tear strap doublers and a larger external repair doubler as follows: (1) Access the area as follows: – Remove and keep the passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. – Remove and keep the passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. – Remove and keep the passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 45 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 46 – Remove and keep the passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. – Remove and keep the aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. (2) Remove all blind fasteners common to the existing time limited repair doubler. (3) Remove the existing time limited repair doubler. (4) Do the following inspections in accordance with FIGURE 9: – Do an open hole HFEC inspection of the fastener holes for any crack common to the repaired area. – Do a HFEC inspection of the cut edges (cut-out) for any crack. (5) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (6) If no crack is found, do an insurance cut on the cut edges in accordance with FIGURE 9. (7) Continue to do the time limited repair modification in accordance with FIGURE 9. (8) Close access as follows: – Install kept aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. – Install kept passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. – Install kept passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. – Install kept passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. – Install kept passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. (9) Put the airplane back to a serviceable condition. (10) Do post repair inspections of the permanent repair in accordance with PART 6: POST REPAIR INSPECTION OF PERMANENT REPAIR at times specified in Paragraph 1.E., Compliance. b. For airplanes with a time limited repair installed in accordance with Revision 1 of this service bulletin, the time limited repair must be modified to a permanent repair within the times given in Paragraph 1.E., Compliance using one of the following two options: OPTION 1: Make the time limited repair permanent by replacing the blind fasteners and installing internal tear strap doublers as follows: (1) Access the area as follows: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 46 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 47 – Remove and keep the passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. – Remove and keep the passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. – Remove and keep the passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. – Remove and keep the passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. – Remove and keep the aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. (2) Remove all blind fasteners common to the existing time limited repair doubler. (3) Do an open hole HFEC inspection of the fastener holes for any crack common to the repaired area in accordance with FIGURE 10. (4) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (5) If no crack is found, continue to do the time limited repair modification in accordance with FIGURE 10. (6) Close access as follows: – Install kept aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. – Install kept passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. – Install kept passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. – Install kept passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. – Install kept passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. (7) Put the airplane back to a serviceable condition. (8) Do post repair inspections of the permanent repair in accordance with PART 6: POST REPAIR INSPECTION OF PERMANENT REPAIR at times specified in Paragraph 1.E., Compliance. OPTION 2: Make the time limited repair permanent by removing the existing external repair doubler and installing internal tear strap doublers and a larger external repair doubler as follows: (1) Access the area as follows: – Remove and keep the passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. – Remove and keep the passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 47 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 48 – Remove and keep the passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. – Remove and keep the passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. – Remove and keep the aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. (2) Remove all blind fasteners common to the existing time limited repair doubler. (3) Remove the existing time limited repair doubler. (4) Do an open hole HFEC inspection of the fastener holes for cracks common to the repaired area in accordance with FIGURE 11. (5) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (6) If no crack is found, continue to do the time limited repair modification in accordance with FIGURE 11. (7) Close access as follows: – Install kept aft cargo compartment sidewall panels and insulation blankets. Refer to 737-300/400/500 AMM 25-52-73 and 737-300/400/500 AMM 25-52-91 as accepted procedures. – Install kept passenger cabin sidewall insulation blankets. Refer to 737-300/400/500 AMM 25-21-39 as an accepted procedure. – Install kept passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an accepted procedure. – Install kept passenger carpets. Refer to 737-300/400/500 AMM 25-27-15 as an accepted procedure. – Install kept passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted procedure. (8) Put the airplane back to a serviceable condition. (9) Do post repair inspections of the permanent repair in accordance with PART 6: POST REPAIR INSPECTION OF PERMANENT REPAIR at times specified in Paragraph 1.E., Compliance. 6. PART 6: POST REPAIR INSPECTION OF PERMANENT REPAIR NOTE: The following instructions do not apply to repairs installed in accordance with 737-500 SRM 53-00-01, Figure 201, Repair 31. a. Do an external inspection as follows: (1) If a permanent repair was installed in accordance with PART 5: PERMANENT REPAIR INSTALLATION, OPTION 1, do an LFEC inspection of the skin at the critical fastener row of the repair doubler for any crack in accordance with FIGURE 12 at the times given in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 48 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 49 (a) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (b) If no crack is found, repeat PART 6: POST REPAIR INSPECTION OF PERMANENT REPAIR at the repeat interval in accordance with Paragraph 1.E., Compliance. (2) If a permanent repair was installed in accordance with PART 5: PERMANENT REPAIR INSTALLATION, OPTION 2, do an LFEC inspection of the skin at the critical fastener row of the repair doubler for any crack in accordance with FIGURE 13 at the times given in Paragraph 1.E., Compliance. (a) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (b) If no crack is found, repeat PART 6: POST REPAIR INSPECTION OF PERMANENT REPAIR at the repeat interval in accordance with Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2011 737-53-1315Revision 1: June 30, 2015 49 of 102 BOEING SERVICE BULLETIN 737-53-1315 ### Page 50 (OCR) BOEING SERVICE BULLETIN 737-53-1315 This Figure applies only to: Group 1-4. STA 1016 STA 727 STA 727 * S-10L * S-14L S-20L STA * BLO S-25L 907 S-25R STA 1016 2048353 FIGURE 1: INSPECTION ZONES - LEFT SIDE (SHEET 1 OF 3) Original Issue: July 29, 2011 Revision 1 June 30, 2015 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 737-53-1315 50 of 102 ### Page 51 (OCR) BOEING SERVICE BULLETIN 737-53-1315 STA STA 727 727A S-14L S-15L S-16L S-17L - UPPER S-18L SKIN S-19L ZONE LAP JOINT → S-20L ZONE 1 S-21L S-22L S-23L - LOWER S-24L SKIN S-25L FAIRING PERIMETER STA STA STA STA STA STA STA 787 807 827 847 867 887 907 S-14L S-15L ZONE S-16L S-17L • UPPER S-18L SKIN S-19L LAP JOINT → S-20L ZONE 1 S-21L S-22L S-23L - LOWER S-24L SKIN FWD S-25L RSSS) ZONE 1: SKIN/BONDED DOUBLER WITH THE BONDED DOUBLER CHEM-MILLED TO THE BOND LINE IN THE POCKET DON ZONE 2; SKIN/BONDED DOUBLER WITH A CHEM-MILLED POCKET THICKNESS OF 0.050 INCHES (BONDED DOUBLER PARTIALLY CHEM-MILLED) SKIN/BONDED DOUBLER WITH NO CHEM-MILLED POCKETS OR SKIN/BONDED DOUBLER 2048375 WITH A CHEM-MILLED POCKET THICKNESS GREATER THAN 0.050 INCHES (BONDED DOUBLER PARTIALLY CHEM-MILLED) FIGURE 1: INSPECTION ZONES - LEFT SIDE (SHEET 2 OF 3) Original Issue: July 29, 2011 Revision 1 June 30, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53-1315 Work - See page 1 for details. 51 of 102 ### Page 52 (OCR) BOEING SERVICE BULLETIN 737-53-1315 STA 1016 STA STA STA STA STA STA 907 927 947 967 987 1006 S-14L ZONE 1 S-15L S-16L DOOR S-17L CUTOUT UPPER S-18L SKIN S-19L LAP JOINT-→ S-20L S-21L S-22L ZONE S-23L - LOWER S-24L SKIN S-25L DOOR CUTOUT C B23 ZONE 1: SKIN/BONDED DOUBLER WITH THE BONDED DOUBLER CHEM-MILLED TO THE BOND LINE IN THE POCKET SKIN/BONDED DOUBLER WITH NO CHEM-MILLED POCKETS OR SKIN/BONDED DOUBLER WITH A CHEM-MILLED POCKET THICKNESS GREATER THAN 0.050 INCHES (BONDED DOUBLER PARTIALLY CHEM-MILLED) 2048384 FIGURE 1: INSPECTION ZONES - LEFT SIDE (SHEET 3 OF 3) Original Issue: July 29, 2011 Revision 1 June 30, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53-1315 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 102 ### Page 53 (OCR) BOEING SERVICE BULLETIN 737-53-1315 This Figure applies only to: Group 1-4. STA 1016 STA S-10R 727 S-14R S-20R • STA S-25R - 787 STA S-25L 907 1016 STA 2048404 FIGURE 2: INSPECTION ZONES - RIGHT SIDE (SHEET 1 OF 3) Original Issue: July 29, 2011 Revision 1 June 30, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. 737-53-1315 53 of 102 ### Page 54 (OCR) BOEING SERVICE BULLETIN 737-53-1315 S87 167 147 127C STA STA STA 727B 727A 727 S-14R S-15R - S-16R ZONE 2 S-17R UPPER SKIN S-18R S-19R S-20R - LAP JOINT S-21R ZONE S-22R LOWER S-23R SKIN S-24R S-25R FAIRING PERIMETER FWD STA STA STA STA STA STA STA 907 887 867 847 827 807 787 S-14R S-15R S-16R S-17R UPPER SKIN S-18R ZONE S-19R S-20R → LAP JOINT S-21R DOOR S-22R CUTOUT LOWER • S-23R SKIN S-24R S-25R FWD B02 ZONE 1: SKIN/BONDED DOUBLER WITH THE BONDED DOUBLER CHEM-MILLED TO THE BOND LINE IN THE POCKET I ZONE 2; SKIN/BONDED DOUBLER WITH A CHEM-MILLED POCKET THICKNESS OF 0.050 INCHES (BONDED DOUBLER PARTIALLY CHEM-MILLED) | SKIN/BONDED DOUBLER WITH NO CHEM-MILLED POCKETS OR SKIN/BONDED DOUBLER 2048630 WITH A CHEM-MILLED POCKET THICKNESS GREATER THAN 0.050 INCHES (BONDED DOUBLER PARTIALLY CHEM-MILLED) FIGURE 2: INSPECTION ZONES - RIGHT SIDE (SHEET 2 OF 3) Original Issue: July 29, 2011 Revision 1 June 30, 2015 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 737-53-1315 Work - See page 1 for details. 54 of 102 ### Page 55 (OCR) BOEING SERVICE BULLETIN 737-53-1315 STA 1016 STA STA STA STA STA STA 1006 987 967 947 927 907 S-14R S-15R DOOR S-16R CUTOUT S-17R - UPPER S-18R SKIN S-19R LAP JOINT - S-20R S-21R ZONE S-22R S-23R DOOR ZONE • LOWER S-24R CUTOUT SKIN S-25R FWD 12% ZONE 1: SKIN/BONDED DOUBLER WITH THE BONDED DOUBLER CHEM-MILLED TO THE BOND LINE IN THE POCKET WITH A CHEM-MILLED POCKET THICKNESS GREATER THAN 0.050 INCHES (BONDED SKIN/BONDED DOUBLER WITH NO CHEM-MILLED POCKETS OR SKIN/BONDED DOUBLER 2048385 DOUBLER PARTIALLY CHEM-MILLED) FIGURE 2: INSPECTION ZONES - RIGHT SIDE (SHEET 3 OF 3) Original Issue: July 29, 2011 Revision 1 June 30, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53-1315 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 102 ### Page 56 (OCR) BOEING SERVICE BULLETIN 737-53-1315 This Figure applies only to: Group 5-6. STA 1016 STA 727 STA 727 * S-10L * S-14L S-20L STA * BLO S-25L 907 S-25R STA 1016 2048631 FIGURE 3: INSPECTION ZONES - LEFT SIDE (SHEET 1 OF 2) Original Issue: July 29, 2011 Revision 1 June 30, 2015 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 737-53-1315 56 of 102 ### Page 57 (OCR) BOEING SERVICE BULLETIN 737-53-1315 STA STA STA STA STA STA STA 1016 907 927 947 967 987 1006 S-14L 2222 ZONE 1 S-15L S-16L DOOR CUTOUT S-17L - UPPER S-18L SKIN S-19L LAP JOINT → S-20L S-21L ZONE 1 S-22L S-23L - LOWER S-24L SKIN DOOR S-25L CUTOUT WD STA STA STA STA STA STA 787 807 827 867 887 907 S-14L S-15L S-16L S-17L UPPER S-18L SKIN ZONE 2 S-19L LAP JOINT → S-20L S-21L S-22L S-23L LOWER S-24L SKIN S-25L FWD B882 ZONE 1: SKIN/BONDED DOUBLER WITH THE BONDED DOUBLER CHEM-MILLED TO THE BOND LINE IN THE POCKET \ ZONE 2: SKIN/BONDED DOUBLER WITH A CHEM-MILLED POCKET THICKNESS OF 0.050 INCHES (BONDED DOUBLER PARTIALLY CHEM-MILLED) SKIN/BONDED DOUBLER WITH NO CHEM-MILLED POCKETS OR SKIN/BONDED DOUBLER WITH A CHEM-MILLED POCKET THICKNESS GREATER THAN 0.050 INCHES (BONDED DOUBLER PARTIALLY CHEM-MILLED) FIGURE 3: INSPECTION ZONES - LEFT SIDE (SHEET 2 OF 2) Original Issue: July 29, 2011 Revision 1 June 30, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53-1315 Work - See page 1 for details. 57 of 102 ### Page 58 (OCR) BOEING SERVICE BULLETIN 737-53-1315 This Figure applies only to: Group 5-6. STA 1016 SILA STA S-10R 727 S-14R S-20R- STA S-25R 787 STA S-25L 907 1016 STA 2048633 FIGURE 4: INSPECTION ZONES - RIGHT SIDE (SHEET 1 OF 2) Original Issue: July 29, 2011 Revision 1 June 30, 2015 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright @ Unpublished 737-53-1315 Work - See page 1 for details. 58 of 102 ### Page 59 (OCR) BOEING SERVICE BULLETIN 737-53-1315 STA STA STA STA STA STA STA 1016 1006 987 967 947 927 907 S-14R S-15R DOOR S-16R CUTOUT S-17R • UPPER S-18R SKIN S-19R LAP JOINT → S-20R S-21R ZONE S-22R ZONE S-23R DOOR LOWER S-24R CUTOUT SKIN S-25R STA 907 S-14R S-15R S-16R S-17R - UPPER S-18R SKIN ONE 2 S-19R LAP JOINT → S-20R S-21R S-22R S-23R CUTOUT DOOR • LOWER S-24R SKIN S-25R FWD B888 ZONE 1: SKIN/BONDED DOUBLER WITH THE BONDED DOUBLER CHEM-MILLED TO THE BOND LINE IN THE POCKET J ZONE 2: SKIN/BONDED DOUBLER WITH A CHEM-MILLED POCKET THICKNESS OF 0.050 INCHES (BONDED DOUBLER PARTIALLY CHEM-MILLED) SKIN/BONDED DOUBLER WITH NO CHEM-MILLED POCKETS OR SKIN/BONDED DOUBLER WITH A CHEM-MILLED POCKET THICKNESS GREATER THAN 0.050 INCHES (BONDED DOUBLER PARTIALLY CHEM-MILLED) FIGURE 4: INSPECTION ZONES - RIGHT SIDE (SHEET 2 OF 2) Original Issue: July 29, 2011 Revision 1 June 30, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. 737-53-1315 59 of 102 ### Page 60 (OCR) BOEING SERVICE BULLETIN 737-53-1315 AND B STA S-14l S-TOI 727 STA S-20L LEFT SIDE SHOWN, RIGHT SIDE SIMILAR 787 STA T BLO S-25L 907 STA S-25R 1016 2405162 FIGURE 5: EXTERNAL OR INTERNAL INSPECTION (SHEET 1 OF 3) Original Issue: July 29, 2011 Revision 1 June 30, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53-1315 Work - See page 1 for details. 60 of 102 The text continues at https://openairdocs.org/service-documents/boeing/sb-737-53-1315/file/fbfb2885ffa3.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). 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