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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Unpublished Work.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
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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
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BLANK PAGE
Table of Contents
Revision Transmittal Sheet5
S u m m a r y7
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
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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
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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
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
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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
ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph
1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedYesPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator 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
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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
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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
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
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