# Boeing Alert Service Bulletin 737-53A1364: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2019-0249; AD 2019-14-15 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 737-53A1364](https://openairdocs.org/service-documents/boeing/737-53a1364.md) - Title as filed: SB-737-53A1364-01-- - Pages: 133 - PDF: https://openairdocs.org/files/sha256/5c/a6/5ca6c55735151905afb15242ea262cb8080fe3af4b7515691a4b4bd1b6b2ddac - Page: https://openairdocs.org/service-documents/boeing/737-53a1364/file/5ca6c5573515 ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1364 Original Issue: May 24, 2017 Revision 1: October 25, 2018 ATA System: 5311 SUBJECT: FUSELAGE- Frames and Bulkheads - Body Stations 685, 695, and 706 - Stub Beam Inspection and Repair 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 © 2017 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 1 of 133 5.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 2 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 S u m m a r y ...................................................... 7 1. PLANNING INFORMATION ........................................ 1 5 A . E f f e c t i v i t y ............................................... 1 5 1. Airplanes ............................................ 1 5 2 . S p a r e s A f f e c t e d ........................................ 2 7 B. Concurrent Requirements ...................................... 2 7 C. Reason ................................................ 2 7 D. Description .............................................. 2 8 E. Compliance .............................................. 3 2 F . A p p r o v a l ............................................... 4 5 G. Manpower .............................................. 4 5 H. Weight and Balance Changes .................................... 4 7 I. Electrical Load Data ......................................... 4 7 J . R e f e r e n c e s .............................................. 4 7 1. Existing Data: ......................................... 4 7 2. Data Supplied with this Service Bulletin: ........................... 4 8 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 8 K. Publications Affected ........................................ 4 8 L. Interchangeability and Intermixability of Parts ........................... 4 8 M. Software Accomplishment Summary ................................ 4 8 2. MATERIAL INFORMATION ........................................ 4 9 A. Material - Price and Availability ................................... 4 9 B. Industry Support Information .................................... 4 9 C. Parts Necessary for Each Airplane ................................. 4 9 1 . K i t s / P a r t s ............................................ 4 9 2. Parts and Materials Supplied by the Operator ........................ 4 9 3. Parts Modified and Reidentified ................................ 4 9 4. Parts Removed and Not Replaced .............................. 4 9 D. Parts Necessary to Change Spares ................................. 4 9 E. Special Tooling - Price and Availability ............................... 4 9 F. Special Tooling Necessary to do this Service Bulletin ....................... 4 9 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 5 1 A. GENERAL INFORMATION ..................................... 5 1 B. WORK INSTRUCTIONS ....................................... 5 3 FIGURE 1: STUB BEAMS AT STA 685 AND STA 706 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 2] ..................... 6 4 FIGURE 2: STUB BEAMS AT STA 685 AND STA 706 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 2] ..................... 6 8 FIGURE 3: STUB BEAMS AT STA 685 AND STA 706 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 3] ..................... 7 2 FIGURE 4: STUB BEAMS AT STA 685 AND STA 706 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 3] ..................... 7 4 FIGURE 5: STUB BEAMS AT STA 685 AND STA 706 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 4, 6] .................... 7 6 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 3 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 4 FIGURE 6: STUB BEAMS AT STA 685 AND STA 706 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 4, 6] .................... 8 0 FIGURE 7: STUB BEAMS AT STA 685 AND STA 706 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 5] ..................... 8 4 FIGURE 8: STUB BEAMS AT STA 685 AND STA 706 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 5] ..................... 8 8 FIGURE 9: STUB BEAM WEBS AT STA 685 AND STA 706 - GENERAL VISUAL INSPECTION FOR ANY EXISTING REPAIR [Group 2-6] ................................ 9 2 FIGURE 10: STUB BEAM WEBS AT STA 685 AND STA 706 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW [Group 2-6] . . . 95 FIGURE 11: STUB BEAM WEBS AT STA 685 AND STA 706 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW [Group 2-6] . . . 98 FIGURE 12: STUB BEAM WEB AT STA 695 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 2] ......................... 1 0 1 FIGURE 13: STUB BEAM WEB AT STA 695 - RIGHT SIDE - DETAILED INSPECTION [Group 2] . . 103 FIGURE 14: STUB BEAM WEB AT STA 695 - LEFT SIDE - DETAILED INSPECTION [Group 3] . . . 105 FIGURE 15: STUB BEAM WEB AT STA 695 - RIGHT SIDE - DETAILED INSPECTION [Group 3] . . 107 FIGURE 16: STUB BEAM WEB AT STA 695 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 4, 6] ........................ 1 0 9 FIGURE 17: STUB BEAM WEB AT STA 695 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 4, 6] ........................ 1 1 1 FIGURE 18: STUB BEAM WEB AT STA 695 - LEFT SIDE - DETAILED INSPECTION [Group 5] . . . 113 FIGURE 19: STUB BEAM WEB AT STA 695 - RIGHT SIDE - DETAILED INSPECTION [Group 5] . . 115 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS FOR ANY CRACK IN THE STA 685 AND STA 706 STUB BEAMS [Group 2] ........................ 1 1 7 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 2: GENERAL VISUAL INSPECTION FOR ANY EXISTING REPAIR AND HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION FOR ANY CRACK IN THE STA 685 AND STA 706 STUB BEAMSIN REPAIRED AREAS [Group 2] ................................ 1 1 9 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION FOR ANY CRACK IN THE STA 685 AND STA 706 STUB BEAMS [Group 4-6] .................................. 1 2 2 APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 4: GENERAL VISUAL INSPECTION FOR ANY EXISTING REPAIR AND HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION FOR ANY CRACK IN THE STA 685 AND STA 706 STUB BEAMS IN REPAIRED AREAS [Group 4-6] ............................... 1 2 4 APPENDIX E: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 5: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS FOR ANY CRACK IN THE STA 695 STUB BEAM WEB [Group 2, 4-6] ............................ 1 2 7 APPENDIX F: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 6: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS FOR ANY CRACK IN THE STA 685, STA 695 AND STA 706 STUB BEAMS [Group 3] ................... 1 2 9 APPENDIX G: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 7: GENERAL VISUAL INSPECTION FOR ANY EXISTING REPAIR AND HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION FOR ANY CRACK IN THE STA 685 AND STA 706 STUB BEAMSIN REPAIRED AREAS [Group 3] ................................ 1 3 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 4 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 5 Commercial Airplanes 737 Service Bulletin ALERT Revision Transmittal SheetNumber: 737-53A1364Original Issue: May 24, 2017 Revision 1: October 25, 2018 ATA System: 5311 SUBJECT: FUSELAGE- Frames and Bulkheads - Body Stations 685, 695, and 706 - Stub Beam Inspection and Repair This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related to Service Bulletin 737-53A1364 Revision 1. The Airworthiness Directive will make the compliance tasks and times given in Service Bulletin 737-53A1364 Revision 1 mandatory. Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-25-12 is related to this service bulletin. Effects of this Revision on airplanes on which Original Issue was previously done: None. Boeing recommends affected operators revise their existing aircraft maintenance schedule to accommodate the change to compliance information. REASON FOR REVISION This revision is sent to: 1. Add an inspection of the stub beam at the inboard end of the upper chord, and the outboard end of the lower chord, at STA 685 and STA 706. 2. Revise the initial inspection compliance time for airplanes in Groups 2 through 6. 3. Revise the repeat inspection interval for airplanes in Groups 2, 4, 5, and 6. These sections were changed: 1. In Summary, Background, updated flight cycle range at the time of cracking. 2. In Summary Action, added new inspection location and removed repeat inspections at unrepaired stub beam webs. 3. Paragraph 1.C., Reason, updated flight cycle range at the time of cracking and added revision paragraph. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 5 of 133 ### Page 6 4. Paragraph 1.D., Description, added new inspection location, removed repeat inspections at unrepaired stub beam webs and added revision paragraph. 5. Paragraph 1.E., Compliance, Airworthiness Directive paragraph and footnotes in Tables 1 and 3 have been updated. Added additional action to Tables 2 and 4, new Tables 6 and 7 added and compliance times updated in all tables. 6. Paragraph 1.F., Approval, added Alternative Method of Compliance (AMOC) statement. 7. Paragraph 1.J.1., Existing Data, references have been updated. 8. Paragraph 3.A., added a new note. 9. Paragraph 3.B., Work Instructions, updated notes. 10. Figures 1, 2, 5, 6, 7 and 8, added new inspection area, updated steps and footnotes. Figures 3 & 4, added new inspection area. 11. Appendix A through Appendix E, updated logic diagrams. 12. Added new Appendix F and Appendix G logic diagram. The data given in Information Notice 737-53A1364 IN 01 is included in this revision. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes. Pages with no vertical lines have no changes. REVISION HISTORY May 24, 2017Original Issue: October 25, 2018Revision 1: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 6 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 7 Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-53A1364Original Issue: May 24, 2017 Revision 1: October 25, 2018 ATA System: 5311 SUBJECT: FUSELAGE- Frames and Bulkheads - Body Stations 685, 695, and 706 - Stub Beam Inspection and Repair THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND Accomplishment of this service bulletin will detect cracks that may have formed in the fuselage stub beams below the passenger floor at Body Stations (STA) 685, STA 695, and STA 706, left and right sides. The stub beams at STA 685, STA 695, and STA 706 have been identified as susceptible to cracking. If not corrected, cracks in the webs of the stub beams could adversely affect the structural integrity of the airplane. Boeing has received reports of cracking in the webs of the stub beams at STA 685, STA 695, and STA 706. Diagonal cracks found in the STA 685, STA 695, and STA 706 stub beam webs are a result of fatigue caused by cyclical loading from pressurization, wing and landing loads. Horizontal cracks have been found in the STA 685 stub beam at the inboard end of the upper chord and the outboard end of the lower chord, and were caused by overload of the stub beams leading to ductile separation. The cracks can lead to the loss of structural integrity of the airframe during flight, collapse of the main landing gear, and possible failure of the pressure deck if left undetected. Cracks have occurred in the stub beam webs at STA 685 on the left and right sides of airplanes, with total flight cycles ranging between 11,167 and 45,892 at the time of the crack finding. Cracks have occurred in the stub beam webs at STA 695 on the left and right sides of airplanes, with total flight cycles ranging between 49,572 and 56,712 at the time of crack finding. Cracks have also occurred in the stub beam webs at STA 706 on the left and right sides of airplanes with total flight cycles ranging between 12,017 and 64,392 at the time of crack finding. Boeing Fleet Team Digest (FTD) 737 FTD 53-15003 is related to this service bulletin. Boeing Service Related Problem (SRP) 737-SRP-53-0514 and 737-SRP-53-0577 are related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 7 of 133 ### Page 8 ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedYesPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Air- plane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator NoOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION Group 1: The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line number 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV. Group 2: Do a High Frequency Eddy Current (HFEC) surface inspection for any crack in the STA 685 and STA 706 stub beams at the upper and lower chord radii, on the left and right side of the airplane and at the penetration holes between Left Buttock Line (LBL) 45 and LBL 60, and between Right Buttock Line (RBL) 45 and RBL 60. Do a HFEC surface inspection for any crack in the STA 695 stub beam at the penetration holes between LBL 45 and LBL 64.30. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beams at all fastener locations, tooling holes and penetration holes on the left side and right side. If any crack is found in any of the STA 685, STA 695, or STA 706 stub beams, contact The Boeing Company for the repair instructions and do the repair, and repeat the inspection of the stub beams at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the inspection of the stub beams at the repeat interval specified in Paragraph 1.E., Compliance. Group 2: Do a general visual inspection for any existing repair on the STA 685 and STA 706 stub beams. If any approved existing repair is found that meets the criteria in PART 3 in Paragraph 3.B., Work Instructions, do a High Frequency Eddy Current (HFEC) surface inspection at the critical fastener row in the stub beam web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack. If any crack is found in the stub beam web during HFEC inspections at the critical fastener row, contact The Boeing Company for repair instructions, and do the repair. Repeat the HFEC inspections at the critical fastener row at locations where no crack was found at the repeat interval specified in Paragraph 1.E., Compliance. Repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 8 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 9 HFEC surface inspection at the critical fastener row in the stub web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If a Boeing Organization Designation Authorization (ODA) approved existing repair is found that does not meet the criteria in PART 3 in Paragraph 3.B., Work Instructions, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by the Boeing ODA, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no existing repair is found, repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. Group 3: Do a High Frequency Eddy Current (HFEC) surface inspection for any crack in the STA 685 and STA 706 stub beam webs at the penetration hole between Left Buttock Line (LBL) 45 and LBL 64, and between Right Buttock Line (RBL) 45 and RBL 64. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beams at all fastener locations, tooling holes and penetration holes on the left side and right side. If any crack is found in any of the STA 685, STA 695, or STA 706 stub beams contact The Boeing Company for repair instructions and do the repair, and repeat the inspection of the stub beams at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the inspection of the stub beams at the repeat interval specified in Paragraph 1.E., Compliance. Group 3: Do a general visual inspection for any existing repair on the STA 685 and STA 706 stub beams. If any approved existing repair is found that meets the criteria in PART 3 in Paragraph 3.B., Work Instructions, do a High Frequency Eddy Current (HFEC) surface inspection at the critical fastener row in the stub beam web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack. If any crack is found in the stub beam web during HFEC inspections at the critical fastener row, contact The Boeing Company for repair instructions, and do the repair. Repeat the HFEC inspections at the critical fastener row at locations where no crack was found at the repeat interval specified in Paragraph 1.E., Compliance. Repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC surface inspection at the critical fastener row in the stub web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If a Boeing Organization Designation Authorization (ODA) approved existing repair is found that does not meet the criteria in PART 3 in Paragraph 3.B., Work Instructions, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by the Boeing ODA, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no existing repair is found, repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. Group 4, 6: Do a High Frequency Eddy Current (HFEC) surface inspection for any crack in the STA 685 and STA 706 stub beams at the upper and lower chord and at the penetration holes between Left Buttock Line (LBL) 45 and the edge of the frame fitting, and between Right Buttock Line (RBL) 45 and the edge of the frame fitting. If any crack is found in any of the STA 685 or STA 706 stub beam webs at the lower inboard notch, refer to 737-300 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21 for the trim out allowance. If the crack in the stub beam web does not exceed the trim out allowance specified in the SRM, repair the stub beam in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21, and repeat the HFEC inspection for any crack, at the repeat interval specified in Paragraph 1.E., Compliance. If the crack in the stub beam web exceeds the trim out allowance of the SRM, contact The Boeing Company for repair instructions and do the Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 9 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 10 repair, and repeat the inspection for any crack, at the repeat interval specified in Paragraph 1.E., Compliance. Do a HFEC surface inspection for any crack in the STA 695 stub beam web at the penetration holes between LBL 45 and the inboard edge of the frame fitting, and between RBL 45 and the inboard edge of the frame fitting. If any crack is found at the penetration holes in the STA 695 web, contact The Boeing Company for repair instructions, do the repair and repeat the inspections at the repeat interval specified in Paragraph 1.E., Compliance. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beams at all fastener locations, tooling holes and penetration holes on the left side and right side of the airplane. If no crack is found, repeat the inspection at the repeat interval specified in Paragraph 1.E., Compliance. Group 4, 6: Do a general visual inspection for any existing repair on the STA 685 and STA 706 stub beam webs. If any approved existing repair is found that meets the criteria in PART 3 in Paragraph 3.B., Work Instructions, do a High Frequency Eddy Current (HFEC) surface inspection at the critical fastener row in the STA 685 and STA 706 stub beam webs common to the structural filler for any crack. If any crack is found in the stub beam web during the HFEC inspections at the critical fastener row, contact The Boeing Company for repair instructions and do the repair, repeat the HFEC inspections at the critical fastener row at locations where no crack was found at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC surface inspection at the critical fastener row in the STA 685 and STA 706 stub beam webs common to the structural filler for any crack at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If a Boeing ODA approved existing repair is found that does not meet the criteria in PART 3 in Paragraph 3.B., Work Instructions, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by the Boeing ODA, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no existing repair is found, repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. Group 5: Do a High Frequency Eddy Current (HFEC) surface inspection for any crack in the STA 685 and STA 706 stub beams at the upper and lower chord and at the penetration holes between LBL 45 and the edge of the frame fitting, and between RBL 45 and the edge of the frame fitting. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beams at all fastener locations, tooling holes and penetration holes on the left side and right side of the airplane, between LBL 45 and the edge of the frame fitting, and between RBL 45 and the edge of the frame fitting. If no crack is found, repeat the inspections at the repeat interval specified in Paragraph 1.E., Compliance. If any crack is found in any of the STA 685 or STA 706 stub beam webs at the lower inboard notch, refer to 737-400 SRM 53-00-07, Repair 21 for the trim out allowance. If the crack in the stub beam web does not exceed the trim out allowance specified in the SRM, repair the stub beam web in accordance with 737-400 SRM 53-00-07, Repair 21 and repeat the inspections for any crack, at the repeat interval specified in Paragraph 1.E., Compliance. If the crack in the stub beam web exceeds the trim out allowance of the SRM, contact The Boeing Company for repair instructions and do the repair, and repeat the inspections for any crack, at the repeat interval specified in Paragraph 1.E., Compliance. Group 5: Do a general visual inspection for any existing repair on the STA 685 and STA 706 stub beams. If any existing repair is found that meets the criteria in PART 3 in Paragraph 3.B., Work Instructions, do a High Frequency Eddy Current (HFEC) surface inspection at the critical fastener row in the STA 685 and STA 706 stub beam webs common to the structural filler for any crack. If any crack is found in the stub beam web during the HFEC inspections at the critical fastener row, contact The Boeing Company for repair instructions and do the repair, repeat the HFEC inspections at the critical fastener row at locations where no crack was found at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC surface Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 10 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 11 inspection at the critical fastener row in the STA 685 and STA 706 stub beam webs common to the structural filler for any crack at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If a Boeing ODA approved existing repair is found that does not meet the criteria in PART 3 in Paragraph 3.B., Work Instructions, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by the Boeing ODA, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no existing repair is found, repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. EFFECTIVITY All 737-100/200/200C/300/400/500 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related to Service Bulletin 737-53A1364 Revision 1. The Airworthiness Directive will make the compliance tasks and times given in Service Bulletin 737-53A1364 Revision 1 mandatory. Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-25-12 is related to this service bulletin. The effective date of AD 2017-25-12 is January 22, 2018. Refer to Paragraph 1.E., Compliance INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 11 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 12 (OCR) BOEING SERVICE BULLETIN 737-53A1364 ALERT ALERT STA 695 STA 706 STA 685) STA STA STA 706 695 685 STA 695 STUB BEAM STA 706 STUB BEAM STA 685 STUB BEAM LBL 45.57 LONGITUDINAL 2534757 FLOOR BEAM LEFT SIDE SHOWN, RIGHT SIDE SIMILAR Original Issue: May 24, 2017 Revision 1: October 25, 2018 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1364 Work - See page 1 for details. 12 of 133 ### Page 13 (OCR) BOEING SERVICE BULLETIN 737-53A1364 ALERT ALERT - FRAME FUSELAGE 57.48 LBL TYPICAL 45.57 LBL CRACK WL 208.10 STUB BEAM WEB DO A HIGH FREQUENCY TYPICAL CRACK INBD EDDY CURRENT (HFEC) INSPECTION FOR ANY STA 685 SHOWN CRACK STA 706 SIMILAR (VIEW LOOKING FWD) DO A DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION FOR ANY FUSELAGE CRACK FRAME LBL LBL 57.48 TYPICAL 45.57 CRACK WL 208.10 ++++ + + TYPICAL STUB BEAM CRACK INBD WEB STA 695 (VIEW LOOKING FWD) Original Issue: May 24, 2017 Revision 1: October 25, 2018 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1364 Work - See page 1 for details. 13 of 133 ### Page 14 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 14 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT BLANK PAGE ### Page 15 Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1364 Original Issue: May 24, 2017 Revision 1: October 25, 2018 ATA System: 5311 SUBJECT: FUSELAGE- Frames and Bulkheads - Body Stations 685, 695, and 706 - Stub Beam Inspection and Repair THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This bulletin is applicable to 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500 Airplane(s), line number(s) 1-3132 in 6 Group(s). Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. DESCRIPTIONCONFIGURATIONGROUP 737-100/200/200C Airplanes, Line numbers 1 to 291.-1 737-200 Airplanes, Line Numbers 292 through 1585.-2 737-200C Airplanes, Line Numbers 294 through 1113.-3 737-300 Airplanes, Line Numbers 1001 through 3130.-4 737-400 Airplanes, Line Numbers 1487 through 3132.-5 737-500 Airplanes, Line Numbers 1718 through 3116.-6 Airplane Models: 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 15 of 133 ### Page 16 GroupVariable Number 1PA001 - PA022 1PA099 1PA231 - PA232 1PC001 - PC005 1PG001 - PG075 1PG199 1PG201 - PG230 1PG251 - PG255 1PG271 - PG279 1PG301 - PG314 1PG331 - PG332 1PG351 - PG356 1PG375 1PG401 - PG403 1PG431 - PG442 1PG471 - PG475 1PG501 - PG505 1PG571 - PG583 2PG584 - PG586 1PG621 - PG630 1PG651 - PG652 1PG701 - PG705 2PH001 2PH011 - PH013 2PH021 - PH024 1PH701 - PH715 1PH731 - PH732 1PH741 - PH742 2PH743 1PJ001 - PJ002 2PJ003 - PJ009 1PJ031 - PJ032 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 16 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 17 GroupVariable Number 1PJ071 - PJ072 1PJ101 - PJ104 2PJ105 - PJ119 2PJ201 - PJ219 5PJ301 - PJ302 5PJ551 - PJ561 5PJ601 - PJ615 5PJ811 5PJ816 - PJ817 2PK026 - PK029 2PK041 - PK053 2PK061 - PK070 2PK081 - PK082 2PK091 - PK099 2PK101 - PK103 2PK111 - PK120 2PK141 - PK146 2PK201 - PK204 2PK211 - PK223 2PK231 - PK241 2PK251 - PK258 2PK271 - PK274 2PK281 - PK289 2PK291 2PK301 - PK318 2PK341 2PK351 - PK361 2PK391 2PK431 - PK433 2PK451 - PK452 2PK461 - PK469 2PK495 2PK501 - PK504 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 17 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 18 GroupVariable Number 2PK511 - PK515 2PK519 2PK521 - PK528 2PK541 - PK565 2PK581 2PK591 - PK599 2PK601 - PK617 2PK621 - PK637 2PK641 - PK642 2PK661 - PK666 2PK671 - PK681 2PK691 - PK697 2PK711 - PK716 2PK731 - PK765 2PK771 - PK779 2PK801 - PK804 2PK819 - PK827 2PK830 2PK861 - PK863 2PK871 - PK874 2PK881 - PK884 2PK901 - PK938 2PK971 - PK974 2PL001 - PL028 2PL061 2PL081 2PL101 - PL113 2PL151 2PL171 - PL172 2PL201 - PL203 2PL221 2PL401 - PL417 2PL421 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 18 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 19 GroupVariable Number 2PL441 2PL451 - PL456 2PL471 2PL491 2PL501 - PL506 2PL551 - PL562 2PL581 2PL601 - PL603 2PL611 2PL621 - PL626 2PL631 - PL632 1PL711 - PL712 1PL716 2PL717 - PL747 2PL756 2PL758 2PL761 - PL770 2PL781 - PL788 2PL793 1PL801 - PL803 2PM001 - PM006 2PM016 - PM017 2PM021 - PM023 2PM051 - PM066 2PM101 - PM119 2PM141 - PM142 2PM171 2PM181 2PM251 - PM255 2PM281 - PM283 4PM381 - PM399 4PM401 - PM417 4PM541 - PM550 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 19 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 20 GroupVariable Number 5PM551 - PM564 2PN001 - PN002 2PN021 - PN043 2PN081 - PN086 2PN101 - PN117 2PN131 - PN163 2PN401 - PN420 2PN431 - PN433 2PN451 - PN456 2PN471 - PN474 2PN481 2PN491 - PN493 2PN501 - PN502 2PN511 - PN512 2PN521 4PP001 - PP054 4PP101 - PP169 4PP181 - PP199 4PP201 - PP205 4PP221 4PP231 - PP243 4PP281 - PP286 4PP301 - PP305 4PP351 - PP353 4PP376 - PP384 4PP391 - PP393 4PP401 - PP440 4PP471 - PP475 4PP501 - PP522 4PP631 - PP634 4PP651 - PP652 4PP671 - PP699 4PP701 - PP733 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 20 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 21 GroupVariable Number 4PP771 - PP779 4PP801 - PP808 4PP821 - PP827 4PP831 - PP848 4PP851 - PP852 4PP861 - PP877 4PP891 - PP899 4PP901 - PP936 4PP946 - PP948 4PP951 - PP952 4PP961 - PP967 4PP981 - PP991 4PP993 4PQ001 - PQ016 4PQ026 - PQ041 4PQ051 - PQ092 4PQ101 - PQ199 4PQ201 - PQ202 4PQ221 - PQ237 4PQ241 - PQ243 4PQ251 - PQ267 4PQ281 - PQ299 4PQ301 - PQ307 4PQ331 - PQ332 4PQ341 - PQ348 4PQ361 - PQ373 4PQ391 - PQ395 4PQ401 - PQ418 4PQ421 4PQ431 - PQ438 4PQ447 - PQ448 4PQ451 4PQ454 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 21 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 22 GroupVariable Number 4PQ471 - PQ475 4PQ479 - PQ481 4PQ486 - PQ487 4PQ491 - PQ493 4PQ771 - PQ772 4PQ791 - PQ793 4PQ801 - PQ805 4PQ931 - PQ935 4PQ951 4PQ971 - PQ997 4PR001 - PR017 4PR021 - PR034 4PR041 - PR045 4PR061 - PR072 4PR077 - PR082 4PR091 - PR092 4PR096 4PR101 4PR121 - PR122 4PR131 - PR132 4PR141 - PR143 4PR161 - PR172 4PR181 4PS601 - PS631 4PS636 - PS638 4PS641 - PS644 4PS651 - PS657 4PS666 - PS669 4PS691 - PS692 4PS701 - PS706 4PS751 - PS799 4PS811 4PS836 - PS837 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 22 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 23 GroupVariable Number 4PS841 - PS846 4PS851 - PS852 4PS856 4PS861 - PS863 4PS866 - PS868 4PS871 - PS874 4PS896 - PS897 4PS901 - PS941 4PS956 - PS957 4PS961 - PS963 4PS971 - PS978 6PT001 - PT015 6PT021 - PT031 6PT041 - PT064 6PT101 - PT105 6PT121 - PT138 6PT146 - PT148 6PT161 - PT170 6PT181 - PT188 6PT211 - PT220 6PT295 6PT301 - PT309 6PT331 - PT360 6PT381 - PT399 6PT401 - PT438 6PT501 - PT517 6PT561 - PT565 6PT581 - PT586 6PT611 - PT621 6PT641 - PT644 6PT651 - PT656 6PT671 - PT672 6PT681 - PT685 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 23 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 24 GroupVariable Number 6PT701 - PT703 6PT716 - PT717 6PT721 - PT725 6PT801 - PT834 6PT851 - PT854 6PT871 - PT886 6PT901 - PT930 6PT971 - PT973 6PT981 - PT985 6PT996 6PU001 - PU025 6PU301 6PU311 - PU313 5PV001 - PV055 5PV201 - PV209 5PV226 - PV229 5PV231 - PV237 5PV271 - PV272 5PV281 - PV287 5PV296 5PV301 - PV302 5PV351 5PV356 - PV357 5PW001 - PW054 5PW061 - PW068 5PW072 5PW086 - PW088 5PW091 - PW094 5PW101 - PW102 5PW106 5PW111 - PW120 5PW156 - PW157 5PW161 - PW171 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 24 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 25 GroupVariable Number 5PW201 - PW252 5PW261 - PW268 5PW271 - PW276 5PW278 5PW281 - PW293 5PW296 5PW301 - PW327 5PW401 - PW408 5PW411 - PW418 5PW421 - PW424 5PW431 - PW435 5PW441 - PW450 5PW461 - PW467 5PW501 - PW504 5PW511 - PW522 5PW524 - PW550 5PW556 - PW557 5PW561 - PW564 5PW571 - PW576 5PW591 - PW596 5PW611 - PW622 5PW631 - PW637 5PW661 - PW662 5PW681 - PW683 5PW701 - PW702 5PW711 - PW717 5PW741 - PW742 5PW761 5PW771 5PW831 5PW851 - PW856 1PX071 1PX701 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 25 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 26 GroupVariable Number 1PY001 - PY008 1PY021 3PY022 1PY031 3PY036 - PY037 3PY046 - PY048 3PY051 - PY053 3PY056 - PY057 3PY101 - PY103 3PY111 - PY113 3PY131 - PY135 3PY141 - PY143 3PY151 - PY154 3PY156 - PY157 3PY161 - PY162 3PY166 3PY191 3PY201 3PY221 - PY222 3PY231 3PY241 - PY244 3PY270 - PY275 3PY281 3PY286 1PY301 - PY304 1PY321 - PY323 1PY341 - PY346 1PY361 - PY362 1PY381 3PY401 3PY409 - PY411 3PY421 - PY422 3PY441 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 26 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 27 GroupVariable Number 3PY451 3PY461 - PY463 3PY591 - PY595 3PY611 - PY612 3PY621 3PY631 3PY651 3PY671 - PY672 3PY721 3PY741 2. Spares Affected None. B. Concurrent Requirements None. C. Reason Accomplishment of this service bulletin will detect cracks that may have formed in the fuselage stub beams below the passenger floor at Body Stations (STA) 685, STA 695, and STA 706, left and right sides. The stub beams at STA 685, STA 695, and STA 706 have been identified as susceptible to cracking. If not corrected, cracks in the webs of the stub beams could adversely affect the structural integrity of the airplane. Boeing has received reports of cracking in the webs of the stub beams at STA 685, STA 695, and STA 706. Diagonal cracks found in the STA 685, STA 695, and STA 706 stub beam webs are a result of fatigue caused by cyclical loading from pressurization, wing and landing loads. Horizontal cracks have been found in the STA 685 stub beam at the inboard end of the upper chord and the outboard end of the lower chord, and were caused by overload of the stub beams leading to ductile separation. The cracks can lead to the loss of structural integrity of the airframe during flight, collapse of the main landing gear, and possible failure of the pressure deck if left undetected. Cracks have occurred in the stub beam webs at STA 685 on the left and right sides of airplanes, with total flight cycles ranging between 11,167 and 45,892 at the time of the crack finding. Cracks have occurred in the stub beam webs at STA 695 on the left and right sides of airplanes, with total flight cycles ranging between 49,572 and 56,712 at the time of crack finding. Cracks have also occurred in the stub beam webs at STA 706 on the left and right sides of airplanes with total flight cycles ranging between 12,017 and 64,392 at the time of crack finding. Boeing Fleet Team Digest (FTD) 737 FTD 53-15003 is related to this service bulletin. Boeing Service Related Problem (SRP) 737-SRP-53-0514 and 737-SRP-53-0577 are related to this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 27 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 28 Revision 1 is sent to add an inspection of the stub beam at the inboard end of the upper chord, and the outboard end of the lower chord, at STA 685 and STA 706 and revise the initial inspection compliance time for airplanes in Groups 2 through 6, and the repeat inspection compliance time for airplanes in Groups 2, 4, 5, and 6. The data given in Information Notice 737-53A1364 IN 01 is included in this revision. D. Description Group 1: The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line number 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV. Group 2: Do a High Frequency Eddy Current (HFEC) surface inspection for any crack in the STA 685 and STA 706 stub beams at the upper and lower chord radii, on the left and right side of the airplane and at the penetration holes between Left Buttock Line (LBL) 45 and LBL 60, and between Right Buttock Line (RBL) 45 and RBL 60. Do a HFEC surface inspection for any crack in the STA 695 stub beam at the penetration holes between LBL 45 and LBL 64.30. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beams at all fastener locations, tooling holes and penetration holes on the left side and right side. If any crack is found in any of the STA 685, STA 695, or STA 706 stub beams, contact The Boeing Company for the repair instructions and do the repair, and repeat the inspection of the stub beams at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the inspection of the stub beams at the repeat interval specified in Paragraph 1.E., Compliance. Group 2: Do a general visual inspection for any existing repair on the STA 685 and STA 706 stub beams. If any approved existing repair is found that meets the criteria in PART 3 in Paragraph 3.B., Work Instructions, do a High Frequency Eddy Current (HFEC) surface inspection at the critical fastener row in the stub beam web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack. If any crack is found in the stub beam web during HFEC inspections at the critical fastener row, contact The Boeing Company for repair instructions, and do the repair. Repeat the HFEC inspections at the critical fastener row at locations where no crack was found at the repeat interval specified in Paragraph 1.E., Compliance. Repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC surface inspection at the critical fastener row in the stub web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If a Boeing Organization Designation Authorization (ODA) approved existing repair is found that does not meet the criteria in PART 3 in Paragraph 3.B., Work Instructions, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by the Boeing ODA, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no existing repair is found, repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 28 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 29 Group 3: Do a High Frequency Eddy Current (HFEC) surface inspection for any crack in the STA 685 and STA 706 stub beam webs at the penetration hole between Left Buttock Line (LBL) 45 and LBL 64, and between Right Buttock Line (RBL) 45 and RBL 64. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beams at all fastener locations, tooling holes and penetration holes on the left side and right side. If any crack is found in any of the STA 685, STA 695, or STA 706 stub beams contact The Boeing Company for repair instructions and do the repair, and repeat the inspection of the stub beams at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the inspection of the stub beams at the repeat interval specified in Paragraph 1.E., Compliance. Group 3: Do a general visual inspection for any existing repair on the STA 685 and STA 706 stub beams. If any approved existing repair is found that meets the criteria in PART 3 in Paragraph 3.B., Work Instructions, do a High Frequency Eddy Current (HFEC) surface inspection at the critical fastener row in the stub beam web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack. If any crack is found in the stub beam web during HFEC inspections at the critical fastener row, contact The Boeing Company for repair instructions, and do the repair. Repeat the HFEC inspections at the critical fastener row at locations where no crack was found at the repeat interval specified in Paragraph 1.E., Compliance. Repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC surface inspection at the critical fastener row in the stub web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If a Boeing Organization Designation Authorization (ODA) approved existing repair is found that does not meet the criteria in PART 3 in Paragraph 3.B., Work Instructions, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by the Boeing ODA, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no existing repair is found, repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. Group 4, 6: Do a High Frequency Eddy Current (HFEC) surface inspection for any crack in the STA 685 and STA 706 stub beams at the upper and lower chord and at the penetration holes between Left Buttock Line (LBL) 45 and the edge of the frame fitting, and between Right Buttock Line (RBL) 45 and the edge of the frame fitting. If any crack is found in any of the STA 685 or STA 706 stub beam webs at the lower inboard notch, refer to 737-300 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21 for the trim out allowance. If the crack in the stub beam web does not exceed the trim out allowance specified in the SRM, repair the stub beam in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21, and repeat the HFEC inspection for any crack, at the repeat interval specified in Paragraph 1.E., Compliance. If the crack in the stub beam web exceeds the trim out allowance of the SRM, contact The Boeing Company for repair instructions and do the repair, and repeat the inspection for any crack, at the repeat interval specified in Paragraph 1.E., Compliance. Do a HFEC surface inspection for any crack in the STA 695 stub beam web at the penetration holes between LBL 45 and the inboard edge of the frame fitting, and between RBL 45 and the inboard edge of the frame fitting. If any crack is found at the penetration holes in the STA 695 web, contact The Boeing Company for repair instructions, do the repair and repeat the inspections at the repeat interval specified in Paragraph 1.E., Compliance. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beams at all fastener locations, tooling holes and penetration holes on the left side and right side of the airplane. If no crack is found, repeat the inspection at the repeat interval specified in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 29 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 30 Group 4, 6: Do a general visual inspection for any existing repair on the STA 685 and STA 706 stub beam webs. If any approved existing repair is found that meets the criteria in PART 3 in Paragraph 3.B., Work Instructions, do a High Frequency Eddy Current (HFEC) surface inspection at the critical fastener row in the STA 685 and STA 706 stub beam webs common to the structural filler for any crack. If any crack is found in the stub beam web during the HFEC inspections at the critical fastener row, contact The Boeing Company for repair instructions and do the repair, repeat the HFEC inspections at the critical fastener row at locations where no crack was found at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC surface inspection at the critical fastener row in the STA 685 and STA 706 stub beam webs common to the structural filler for any crack at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If a Boeing ODA approved existing repair is found that does not meet the criteria in PART 3 in Paragraph 3.B., Work Instructions, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by the Boeing ODA, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no existing repair is found, repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. Group 5: Do a High Frequency Eddy Current (HFEC) surface inspection for any crack in the STA 685 and STA 706 stub beams at the upper and lower chord and at the penetration holes between LBL 45 and the edge of the frame fitting, and between RBL 45 and the edge of the frame fitting. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beams at all fastener locations, tooling holes and penetration holes on the left side and right side of the airplane, between LBL 45 and the edge of the frame fitting, and between RBL 45 and the edge of the frame fitting. If no crack is found, repeat the inspections at the repeat interval specified in Paragraph 1.E., Compliance. If any crack is found in any of the STA 685 or STA 706 stub beam webs at the lower inboard notch, refer to 737-400 SRM 53-00-07, Repair 21 for the trim out allowance. If the crack in the stub beam web does not exceed the trim out allowance specified in the SRM, repair the stub beam web in accordance with 737-400 SRM 53-00-07, Repair 21 and repeat the inspections for any crack, at the repeat interval specified in Paragraph 1.E., Compliance. If the crack in the stub beam web exceeds the trim out allowance of the SRM, contact The Boeing Company for repair instructions and do the repair, and repeat the inspections for any crack, at the repeat interval specified in Paragraph 1.E., Compliance. Group 5: Do a general visual inspection for any existing repair on the STA 685 and STA 706 stub beams. If any existing repair is found that meets the criteria in PART 3 in Paragraph 3.B., Work Instructions, do a High Frequency Eddy Current (HFEC) surface inspection at the critical fastener row in the STA 685 and STA 706 stub beam webs common to the structural filler for any crack. If any crack is found in the stub beam web during the HFEC inspections at the critical fastener row, contact The Boeing Company for repair instructions and do the repair, repeat the HFEC inspections at the critical fastener row at locations where no crack was found at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC surface inspection at the critical fastener row in the STA 685 and STA 706 stub beam webs common to the structural filler for any crack at the repeat interval specified in Paragraph 1.E., Compliance, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If a Boeing ODA approved existing repair is found that does not meet the criteria in PART 3 in Paragraph 3.B., Work Instructions, contact The Boeing Company for repair instructions and do the repair, and repeat the Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 30 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 31 general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by the Boeing ODA, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If no existing repair is found, repeat the general visual inspection for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. Revision 1 - Effects of this Revision on airplanes on which Original Issue was previously done: None, Boeing recommends to revise the existing aircraft maintenance schedule to accommodate the change to compliance time and the repeat inspection interval. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 2-16, 2-17737-100, 737-200, 737-200C Group 2: Affected Maintenance Zones ZoneModel 2-16, 2-17737-200 Group 3: Affected Maintenance Zones ZoneModel 2-16, 2-17737-200C Group 4: Affected Maintenance Zones ZoneModel 216, 217737-300 Group 5: Affected Maintenance Zones ZoneModel 216, 217737-400 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 31 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 32 Group 6: Affected Maintenance Zones ZoneModel 216, 217737-500 E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related to Service Bulletin 737-53A1364 Revision 1. The Airworthiness Directive will make the compliance tasks and times given in Service Bulletin 737-53A1364 Revision 1 mandatory. Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-25-12 is related to this service bulletin. The effective date of AD 2017-25-12 is January 22, 2018. Accomplish the required actions, based on the applicable conditions in Tables 1 through 7, in accordance with Paragraph 3. Accomplishment Instructions. Logic diagrams showing compliance tasks and compliance times are included as aids in APPENDIX A, APPENDIX B, APPENDIX C, APPENDIX D, APPENDIX E, APPENDIX F, and APPENDIX G. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. Group 1: The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line number 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV. Group 2: Table 1: High Frequency Eddy Current (HFEC) and Detailed Inspections for Any Crack in the STA 685 and STA 706 Stub Beams Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the revision 1 issue date of this service bul- letin. Before 9,000 to- tal flight cycles. Do PART 2: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. All Airplanes. (a) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 32 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 33 Group 2: Table 1: High Frequency Eddy Current (HFEC) and Detailed Inspections for Any Crack in the STA 685 and STA 706 Stub Beams Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 1: ANY CRACK FOUND IN ANY STUB BEAM. 4,500 flight cycles.-(ACTION 2): Repeat PART 2: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. (a) 4,500 flight cycles.-Repeat PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPEC- TIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. CONDITION 2: NO CRACK FOUND IN ANY STUB BEAM. (a) (a) It is not required to do the PART 2 inspections in any area common to an existing repair. Inspections for existing repaired areas are done in accordance with Compliance Table 2. For structural details of the stub beam not covered by an existing repair, the applicable PART 2 inspections must be accomplished. Group 2: Table 2: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the revision 1 issue date of this service bul- letin. Before 9,000 to- tal flight cycles. Do PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. All Airplanes. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 33 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 34 Group 2: Table 2: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the revision 1 issue date of this service bul- letin. Within 32,000 flight cycles af- ter the repair in- stallation. Do PART 4: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) INSPEC- TION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack. CONDITION 3: ANY AP- PROVED EXISTING RE- PAIR FOUND ON THE STUB BEAM WEB THAT MEETS THE CRITERIA IN PART 3. (a) -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 3.1: ANY CRACK FOUND AT THE CRITICAL FASTENER ROW. 9,000 flight cycles.-(ACTION 2): At locations with no crack found at the critical fastener row, re- peat PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) IN- SPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack. 9,000 flight cycles.-(ACTION 3): Repeat PART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 34 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 35 Group 2: Table 2: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 9,000 flight cycles.-(ACTION 1): Repeat PART 4: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) INSPEC- TION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack. CONDITION 3.2: NO CRACK FOUND AT THE CRITICAL FASTENER ROW. 9,000 flight cycles.-(ACTION 2): Repeat PART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 4: ANY AP- PROVED EXISTING RE- PAIR FOUND ON THE STUB BEAM WEB THAT DOES NOT MEET THE CRITERIA IN PART 3. 9,000 flight cycles.-(ACTION 2): RepeatPART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. (a) -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 5: ANY EXIST- ING REPAIR FOUND NOT APPROVED BY BOEING ODA. (a) 9,000 flight cycles.-(ACTION 2): Repeat PART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. 9,000 flight cycles.-Repeat PART 3: GENER- AL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. CONDITION 6: NO EXIST- ING REPAIR FOUND. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 35 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 36 Group 2: Table 2: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (a) An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. Group 4-6: Table 3: High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beams Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the revision 1 issue date of this service bul- letin. Before 9,000 to- tal flight cycles. Do PART 2: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. All Airplanes. (a) -Before further flight.(ACTION 1): Do PART 5: STUB BEAM REPAIR. CONDITION 7: ANY CRACK FOUND IN ANY STUB BEAM THAT CAN BE REPAIRED in accor- dance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21. 4,500 flight cycles.-(ACTION 2): Repeat PART 2: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. (a)(b) -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 8: ANY CRACK FOUND IN ANY STUB BEAM THAT CAN- NOT BE REPAIRED in ac- cordance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21. 4,500 flight cycles.-(ACTION 2): Repeat PART 2: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. (a)(b) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 36 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 37 Group 4-6: Table 3: High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beams Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 4,500 flight cycles.-Repeat PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPEC- TIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. CONDITION 9: NO CRACK FOUND IN ANY STUB BEAM. (a)(b) (a) It is not required to do the PART 2 inspections in any area common to an existing repair. Inspections for existing repaired areas are done in accordance with Compliance Table 4. For structural details of the stub beam not covered by an existing repair, the applicable PART 2 inspections must be accomplished. (b) For repairs accomplished in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00- 07, Repair 21 or 737-500 SRM 53-00-07, Repair 21, refer to the SRM for inspection requirements. Group 4-6: Table 4: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the revision 1 issue date of this service bul- letin. Before 9,000 to- tal flight cycles. Do PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. All Airplanes. (a) -Within 4,500 flight cycles af- ter the revision 1 issue date of this service bul- letin. Within 32,000 flight cycles af- ter the repair in- stallation. Do PART 4: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) INSPEC- TION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack. CONDITION 10: ANY AP- PROVED EXISTING RE- PAIR FOUND ON THE STUB BEAM WEB THAT MEETS THE CRITERIA IN PART 3. (b) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 37 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 38 Group 4-6: Table 4: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 10.1: ANY CRACK FOUND AT THE CRITICAL FASTENER ROW. 9,000 flight cycles.-(ACTION 2): At locations with no crack found at the critical fastener row, re- peat PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) IN- SPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack at areas with approved exist- ing repairs. 9,000 flight cycles.-(ACTION 3): Repeat PART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. 9.000 flight cycles.-(ACTION 1): Repeat PART 4: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) INSPEC- TION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack at areas with approved existing repairs. CONDITION 10.2: NO CRACK FOUND AT THE CRITICAL FASTENER ROW. 9.000 flight cycles.-(ACTION 2): Repeat PART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 38 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 39 Group 4-6: Table 4: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 11: ANY AP- PROVED EXISTING RE- PAIR FOUND ON THE STUB BEAM WEB THAT DOES NOT MEET THE CRITERIA IN PART 3, AND WAS NOT ACCOM- PLISHED in accordance with 737-300 SRM 53-00- 07, Repair 21 or 737-400 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21. 9,000 flight cycles.-(ACTION 2): Repeat PART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. (b) -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 12: ANY EX- ISTING REPAIR FOUND NOT APPROVED BY BOEING ODA. (b) 9,000 flight cycles.-(ACTION 2): Repeat PART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. 9,000 flight cycles.-Repeat PART 3: GENER- AL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. CONDITION 13: NO EXIST- ING REPAIR FOUND. (a) For repairs accomplished in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00- 07, Repair 21 or 737-500 SRM 53-00-07, Repair 21, refer to the SRM for inspection requirements. (b) An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 39 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 40 Group 2, 4-6: Table 5: High Frequency Eddy Current (HFEC) and Detailed Inspections for Any Crack in the STA 695 Stub Beam Web Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the revision 1 issue date of this service bul- letin. Before 9,000 to- tal flight cycles. Do PART 6: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 695 STUB BEAM WEB for any crack. All Airplanes. -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 14: ANY CRACK FOUND IN ANY STUB BEAM WEB. 4,500 flight cycles.-(ACTION 2): Repeat PART 6: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 695 STUB BEAM WEB for any crack. 4,500 flight cycles.-Repeat PART 6: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPEC- TIONS OF THE STA 695 STUB BEAM WEB for any crack. CONDITION 15: NO CRACK FOUND IN ANY STUB BEAM WEB. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 40 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 41 Group 3: Table 6: High Frequency Eddy Current (HFEC) and Detailed Inspections for Any Crack in the STA 685, STA 695, and STA 706 Stub Beams Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the revision 1 issue date of this service bul- letin. Before 9,000 to- tal flight cycles. (ACTION 1): Do PART 2: HIGH FREQUENCY ED- DY CURRENT (HFEC) AND DETAILED INSPEC- TIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. All Airplanes. (a) (ACTION 2): Do PART 6: HIGH FREQUENCY ED- DY CURRENT (HFEC) AND DETAILED INSPEC- TIONS OF THE STA 695 STUB BEAM WEBS for any crack. -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 16: ANY CRACK FOUND IN ANY STUB BEAM. 9,000 flight cycles.-(ACTION 2): Repeat PART 2: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. (a) 9,000 flight cycles.-(ACTION 3): Repeat PART 6: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 695 STUB BEAM WEBS for any crack. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 41 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 42 Group 3: Table 6: High Frequency Eddy Current (HFEC) and Detailed Inspections for Any Crack in the STA 685, STA 695, and STA 706 Stub Beams Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 9,000 flight cycles.-(ACTION 1): Repeat PART 2: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. CONDITION 17: NO CRACK FOUND IN ANY STUB BEAM. (a) 9,000 flight cycles.-(ACTION 2): Repeat PART 6: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) AND DE- TAILED INSPECTIONS OF THE STA 695 STUB BEAM WEBS for any crack. (a) It is not required to do PART 2 inspections in areas where a repair covers the affected inspection zone provided all of the following conditions are met: 1. The repair is the corrective action to the crack condition identified in this service bulletin and installed after the original issue date of this service bulletin, AND 2. The installed repair was approved by the Boeing ODA via a FAA Form 8100-9. Group 3: Table 7: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the revision 1 issue date of this service bul- letin. Before 9,000 to- tal flight cycles. Do PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. All Airplanes. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 42 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 43 Group 3: Table 7: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the revision 1 issue date of this service bul- letin. Within 32,000 flight cycles af- ter the repair in- stallation. Do PART 4: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) INSPEC- TION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack. CONDITION 18: ANY AP- PROVED EXISTING RE- PAIR FOUND ON THE STUB BEAM WEB THAT MEETS THE CRITERIA IN PART 3. (a) -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 18.1: ANY CRACK FOUND AT THE CRITICAL FASTENER ROW. 9,000 flight cycles.-(ACTION 2): At locations with no crack found at the critical fastener row, re- peat PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) IN- SPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack. 9,000 flight cycles.-(ACTION 3): Repeat PART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 43 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 44 Group 3: Table 7: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 9,000 flight cycles.-(ACTION 1): Repeat PART 4: HIGH FRE- QUENCY EDDY CUR- RENT (HFEC) INSPEC- TION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack. CONDITION 18.2: NO CRACK FOUND AT THE CRITICAL FASTENER ROW. 9,000 flight cycles.-(ACTION 2): Repeat PART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 19: ANY AP- PROVED EXISTING RE- PAIR FOUND ON THE STUB BEAM WEB THAT DOES NOT MEET THE CRITERIA IN PART 3. 9,000 flight cycles.-(ACTION 2): RepeatPART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. (a) -Before further flight.(ACTION 1): Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 20: ANY EX- ISTING REPAIR FOUND NOT APPROVED BY BOEING ODA. (a) 9,000 flight cycles.-(ACTION 2): Repeat PART 3: GENERAL VISU- AL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. 9,000 flight cycles.-Repeat PART 3: GENER- AL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. CONDITION 21: NO EXIST- ING REPAIR FOUND. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 44 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 45 Group 3: Table 7: General Visual Inspection for Any Existing Repair and High Frequency Eddy Current (HFEC) Inspection for Any Crack in the STA 685 and STA 706 Stub Beam Webs In Repaired Areas Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (a) An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. In addition, the Manager of the FAA Los Angeles ACO Branch approves the inspections in this service bulletin as an alternative method of compliance to the requirements of paragraph (h) of AD 2017-25-12. All provisions of AD 2017-25-12 that are not specifically referenced in the above statement remain fully applicable and must be complied with. G. Manpower The table below shows an estimate of the task hours necessary to do this inspection 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 2: Elapsed HoursTask HoursNumber of PersonsTask 1.503.002Open Access 1.751.751FIGURE 1 1.751.751FIGURE 2 0.500.501FIGURE 9 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 45 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 46 Group 2: Elapsed HoursTask HoursNumber of PersonsTask 0.750.751FIGURE 10 0.750.751FIGURE 11 0.750.751FIGURE 12 0.750.751FIGURE 13 1.503.002Close Access 10.0013.00TOTAL FOR EACH AIRPLANE Group 3: Elapsed HoursTask HoursNumber of PersonsTask 1.503.002Open Access 1.001.001FIGURE 3 1.001.001FIGURE 4 0.500.501FIGURE 9 0.750.751FIGURE 10 0.750.751FIGURE 11 0.250.251FIGURE 14 0.250.251FIGURE 15 1.503.002Close Access 7.5010.50TOTAL FOR EACH AIRPLANE Group 4, 6: Elapsed HoursTask HoursNumber of PersonsTask 1.503.002Open Access 1.751.751FIGURE 5 1.751.751FIGURE 6 0.500.501FIGURE 9 0.750.751FIGURE 10 0.750.751FIGURE 11 0.750.751FIGURE 16 0.750.751FIGURE 17 1.503.002Close Access 10.0013.00TOTAL FOR EACH AIRPLANE Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 46 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 47 Group 5: Elapsed HoursTask HoursNumber of PersonsTask 1.503.002Open Access 1.751.751FIGURE 7 1.751.751FIGURE 8 0.500.501FIGURE 9 0.750.751FIGURE 10 0.750.751FIGURE 11 0.250.251FIGURE 18 0.250.251FIGURE 19 1.503.002Close Access 9.0012.00TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes None. I. Electrical Load Data Not applicable. J. References 1. Existing Data: a. Boeing Service Related Problem (SRP) 737-SRP-53-0514, 737-SRP-53-0577 b. Service Bulletin Index D6-19567 c. 737 Fleet Team Digest (FTD) 53-15003 d. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00 e. 737-100/200 Aircraft Maintenance Manual (AMM) 25-21-00, 25-21-21, 25-21-311, 25-21-346, 25-22-00, 25-27-100, 27-09-11, 53-21-00 f. 737-300/400/500 Aircraft Maintenance Manual (AMM) 25-21-46, 25-22-00, 25-27-15, 27-09-11, 53-21-00 g. 737-300 Structural Repair Manual (SRM) 53-00-07, Repair 21 h. 737-400 Structural Repair Manual (SRM) 53-00-07, Repair 21 i. 737-500 Structural Repair Manual (SRM) 53-00-07, Repair 21 j. Federal Aviation Administration (FAA) Airworthiness Directive (AD)2017-25-12 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 47 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 48 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number FRAME INSTL- SIDE STRUT SUPPORT, STA 68565-46543 FRAME INSTL- LOWER, STA 69565-46544 FRAME INSTL- TRUNNION BEAM SUPPORT, STA 70665-46545 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: Chapter-SectionPublication 53-00Structural Repair Manual 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 but no new DTIs are necessary. 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: May 24, 2017 737-53A1364Revision 1: October 25, 2018 48 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 49 2. MATERIAL INFORMATION A. Material - Price and Availability None. B. Industry Support Information Boeing warranty remedies are not available for the inspections procedures given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator None. 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: May 24, 2017 737-53A1364Revision 1: October 25, 2018 49 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 50 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 50 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT BLANK PAGE ### Page 51 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION 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. — Values for airframe maintenance tasks are included in Chapter 20 of 737 Aircraft Maintenance Manual (AMM). — Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM). — Values for engine maintenance tasks are included in Chapter 70 of 737 Aircraft Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step. 4. 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. 5. 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. 6. 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 51 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 52 7. 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. 8. Refer to Appendix A, B, C, D, E, F, and G for logic diagrams. Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 9. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 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. Boeing recommends only removing and replacing one stub beam at the same time. If more than one stub beam is going to be removed at the same time, contact The Boeing Company for jacking and shoring instructions. 12. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 13. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 14. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. 15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 16. Some steps in the Work Instructions are labeled as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps labeled as RC, including sub-steps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or sub-step is labeled "RC Exempt," then the RC requirement is removed from that step or sub-step. An Alternative Method of Compliance (AMOC) is required for any deviations to RC steps, including sub-steps and identified figures. Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC. This is provided that the RC steps, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 52 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 53 B. WORK INSTRUCTIONS 1. Group 1: The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line number 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV. 2. Group 2-6: Do PART 1: ACCESS. 3. Group 2: RC - Do PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. NOTE: It is not required to do the PART 2 inspections in any area common to an existing repair. Inspections for existing repaired areas are done in accordance with Compliance Table 2. For structural details of the stub beam not covered by an existing repair, the applicable PART 2 inspections must be accomplished. a. CONDITION 1: ANY CRACK FOUND IN ANY STUB BEAM. (1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) (ACTION 2): Repeat PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack at the repeat interval specified in Paragraph 1.E., Compliance. NOTE: It is not required to do the PART 2 inspections in any area common to an existing repair. Inspections for existing repaired areas are done in accordance with Compliance Table 2. For structural details of the stub beam not covered by an existing repair, the applicable PART 2 inspections must be accomplished. b. CONDITION 2: NO CRACK FOUND IN ANY STUB BEAM. (1) Repeat PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack at the repeat interval specified in Paragraph 1.E., Compliance. NOTE: It is not required to do the PART 2 inspections in any area common to an existing repair. Inspections for existing repaired areas are done in accordance with Compliance Table 2. For structural details of the stub beam not covered by an existing repair, the applicable PART 2 inspections must be accomplished. 4. Group 2: RC - Do PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. a. CONDITION 3: ANY APPROVED EXISTING REPAIR FOUND ON THE STUB BEAM WEB THAT MEETS THE CRITERIA IN PART 3. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 53 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 54 NOTE: An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. (1) Do PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack. (a) CONDITION 3.1: ANY CRACK FOUND AT THE CRITICAL FASTENER ROW. 1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) (ACTION 2): At locations with no crack found at the critical fastener row, repeat PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack at the repeat interval specified in Paragraph 1.E., Compliance. 3) (ACTION 3): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. (b) CONDITION 3.2: NO CRACK FOUND AT THE CRITICAL FASTENER ROW. 1) (ACTION 1): Repeat PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack at the repeat interval specified in Paragraph 1.E., Compliance. 2) (ACTION 2): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. b. CONDITION 4: ANY APPROVED EXISTING REPAIR FOUND ON THE STUB BEAM WEB THAT DOES NOT MEET THE CRITERIA IN PART 3. NOTE: An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. (1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) (ACTION 2): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. c. CONDITION 5: ANY EXISTING REPAIR FOUND NOT APPROVED BY BOEING ODA. NOTE: An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. (1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 54 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 55 (2) (ACTION 2): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. d. CONDITION 6: NO EXISTING REPAIR FOUND. (1) Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. 5. Group 4-6: RC - Do PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. NOTE: It is not required to do the PART 2 inspections in any area common to an existing repair. Inspections for existing repaired areas are done in accordance with Compliance Table 4. For structural details of the stub beam not covered by an existing repair, the applicable PART 2 inspections must be accomplished. a. CONDITION 7: ANY CRACK FOUND IN ANY STUB BEAM THAT CAN BE REPAIRED in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21. (1) (ACTION 1): Do PART 5: STUB BEAM REPAIR. (2) (ACTION 2): Repeat PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack at the repeat interval specified in Paragraph 1.E., Compliance. NOTE: It is not required to do the PART 2 inspections in any area common to an existing repair. Inspections for existing repaired areas are done in accordance with Compliance Table 4. For structural details of the stub beam not covered by an existing repair, the applicable PART 2 inspections must be accomplished. NOTE: For repairs accomplished in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21, refer to the SRM for inspection requirements. b. CONDITION 8: ANY CRACK FOUND IN ANY STUB BEAM THAT CANNOT BE REPAIRED in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21. (1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) (ACTION 2): Repeat PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack at the repeat interval specified in Paragraph 1.E., Compliance. NOTE: It is not required to do the PART 2 inspections in any area common to an existing repair. Inspections for existing repaired areas are done in accordance with Compliance Table 4. For structural details of the stub beam not covered by an existing repair, the applicable PART 2 inspections must be accomplished. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 55 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 56 NOTE: For repairs accomplished in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21, refer to the SRM for inspection requirements. c. CONDITION 9: NO CRACK FOUND IN ANY STUB BEAM. (1) Repeat PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack at the repeat interval specified in Paragraph 1.E., Compliance. NOTE: It is not required to do the PART 2 inspections in any area common to an existing repair. Inspections for existing repaired areas are done in accordance with Compliance Table 4. For structural details of the stub beam not covered by an existing repair, the applicable PART 2 inspections must be accomplished. NOTE: For repairs accomplished in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21, refer to the SRM for inspection requirements. 6. Group 4-6: RC - Do PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. NOTE: For repairs accomplished in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21, refer to the SRM for inspection requirements. a. CONDITION 10: ANY APPROVED EXISTING REPAIR FOUND ON THE STUB BEAM WEB THAT MEETS THE CRITERIA IN PART 3. NOTE: An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. (1) Do PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack. (a) CONDITION 10.1: ANY CRACK FOUND AT THE CRITICAL FASTENER ROW. 1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) (ACTION 2): At locations with no crack found at the critical fastener row, repeat PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack at areas with approved existing repairs at the repeat interval specified in Paragraph 1.E., Compliance. 3) (ACTION 3): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. (b) CONDITION 10.2: NO CRACK FOUND AT THE CRITICAL FASTENER ROW. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 56 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 57 1) (ACTION 1): Repeat PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack at areas with approved existing repairs at the repeat interval specified in Paragraph 1.E., Compliance. 2) (ACTION 2): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. b. CONDITION 11: ANY APPROVED EXISTING REPAIR FOUND ON THE STUB BEAM WEB THAT DOES NOT MEET THE CRITERIA IN PART 3, AND WAS NOT ACCOMPLISHED in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-400 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21. NOTE: An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. (1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) (ACTION 2): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. c. CONDITION 12: ANY EXISTING REPAIR FOUND NOT APPROVED BY BOEING ODA. NOTE: An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. (1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) (ACTION 2): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. d. CONDITION 13: NO EXISTING REPAIR FOUND. (1) Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. 7. Group 2, 4-6: RC - Do PART 6: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 695 STUB BEAM WEB for any crack. a. CONDITION 14: ANY CRACK FOUND IN ANY STUB BEAM WEB. (1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) (ACTION 2): Repeat PART 6: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 695 STUB BEAM WEB for any crack at the repeat interval specified in Paragraph 1.E., Compliance. b. CONDITION 15: NO CRACK FOUND IN ANY STUB BEAM WEB. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 57 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 58 (1) Repeat PART 6: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 695 STUB BEAM WEB for any crack at the repeat interval specified in Paragraph 1.E., Compliance. 8. Group 3: RC - (ACTION 1): Do PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack. NOTE: It is not required to do PART 2 inspections in areas where a repair covers the affected inspection zone provided all of the following conditions are met: 1. The repair is the corrective action to the crack condition identified in this service bulletin and installed after the original issue date of this service bulletin, AND 2. The installed repair was approved by the Boeing ODA via a FAA Form 8100-9. (ACTION 2): Do PART 6: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 695 STUB BEAM WEBS for any crack. a. CONDITION 16: ANY CRACK FOUND IN ANY STUB BEAM. (1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) (ACTION 2): Repeat PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack at the repeat interval specified in Paragraph 1.E., Compliance. NOTE: It is not required to do PART 2 inspections in areas where a repair covers the affected inspection zone provided all of the following conditions are met: 1. The repair is the corrective action to the crack condition identified in this service bulletin and installed after the original issue date of this service bulletin, AND 2. The installed repair was approved by the Boeing ODA via a FAA Form 8100-9. (3) (ACTION 3): Repeat PART 6: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 695 STUB BEAM WEBS for any crack at the repeat interval specified in Paragraph 1.E., Compliance. a. CONDITION 17: NO CRACK FOUND IN ANY STUB BEAM. (1) (ACTION 1): Repeat PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 685 AND STA 706 STUB BEAMS for any crack at the repeat interval specified in Paragraph 1.E., Compliance. NOTE: It is not required to do PART 2 inspections in areas where a repair covers the affected inspection zone provided all of the following conditions are met: 1. The repair is the corrective action to the crack condition identified in this service bulletin and installed after the original issue date of this service bulletin, AND Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 58 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 59 2. The installed repair was approved by the Boeing ODA via a FAA Form 8100-9. (2) (ACTION 2): Repeat PART 6: HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS OF THE STA 695 STUB BEAM WEBS for any crack at the repeat interval specified in Paragraph 1.E., Compliance. 9. Group 3: RC - Do PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair. a. CONDITION 18: ANY APPROVED EXISTING REPAIR FOUND ON THE STUB BEAM WEB THAT MEETS THE CRITERIA IN PART 3. NOTE: An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. (1) Do PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack. (a) CONDITION 18.1: ANY CRACK FOUND AT THE CRITICAL FASTENER ROW. 1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) (ACTION 2): At locations with no crack found at the critical fastener row, repeat PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack at the repeat interval specified in Paragraph 1.E., Compliance. 3) (ACTION 3): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. (b) CONDITION 18.2: NO CRACK FOUND AT THE CRITICAL FASTENER ROW. 1) (ACTION 1): Repeat PART 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT THE CRITICAL FASTENER ROW IN THE STUB BEAM WEB COMMON TO THE STRUCTURAL FILLER for any crack at the repeat interval specified in Paragraph 1.E., Compliance. 2) (ACTION 2): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. b. CONDITION 19: ANY APPROVED EXISTING REPAIR FOUND ON THE STUB BEAM WEB THAT DOES NOT MEET THE CRITERIA IN PART 3. NOTE: An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 59 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT ### Page 60 (1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) (ACTION 2): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. c. CONDITION 20: ANY EXISTING REPAIR FOUND NOT APPROVED BY BOEING ODA. NOTE: An approved repair is an installed repair that was Boeing Organization Designation Authorization (ODA) approved via an FAA Form 8100-9. (1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) (ACTION 2): Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. d. CONDITION 21: NO EXISTING REPAIR FOUND. (1) Repeat PART 3: GENERAL VISUAL INSPECTION OF THE STA 685 AND STA 706 STUB BEAM WEBS for any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. 10. Group 2-6: Do PART 7: CLOSE ACCESS. 11. Put the airplane back to a serviceable condition. Group 2-6: PART 1: ACCESS 1. Group 2-3: Use the following steps to get access: a. Remove and keep the left and the right side passenger seats to get access to the STA 685, STA 695, and STA 706 stub beams. Refer to 737-100/200 AMM 25-22-00 as an accepted procedure. b. Remove and keep the sidewall panels from the stations where passenger seats were removed. Refer to 737-100/200 AMM 25-21-00, 737-100/200 AMM 25-21-21, 737-100/200 AMM 25-21-311, or 737-100/200 AMM 25-21-346 as accepted procedures. c. Remove and keep the carpet and floor panels to get access to the STA 685, STA 695, and STA 706 stub beams. Refer to 737-100/200 AMM 25-27-100, 737-100/200 AMM 53-21-00 as accepted procedures. d. Remove and keep the flight control cables at STA 685, STA 695, and STA 706 as required. Refer to 737-100/200 AMM 27-09-11 as an accepted procedure. 2. Group 4-6: Use the following steps to get access: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 24, 2017 737-53A1364Revision 1: October 25, 2018 60 of 133 BOEING SERVICE BULLETIN 737-53A1364 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/737-53a1364/file/5ca6c5573515.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.