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Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1364 Original Issue: May 24, 2017 ATA System: 5311 SUBJECT: FUSELAGE- Frames and Bulkheads - Body Stations 685, 695, and 706 - Stub Beam Web 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Unpublished Work.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 737-53A1364 1 of 114
4.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Table of Contents
S u m m a r y5
1. PLANNING INFORMATION ........................................ 1 3 A . E f f e c t i v i t y ............................................... 1 3
1. Airplanes ............................................ 1 3 2 . S p a r e s A f f e c t e d ........................................ 2 5 B. Concurrent Requirements ...................................... 2 5 C. Reason ................................................ 2 5 D. Description .............................................. 2 6 E. Compliance .............................................. 3 0 F . A p p r o v a l ............................................... 3 8 G. Manpower .............................................. 3 9 H. Weight and Balance Changes .................................... 4 0 I. Electrical Load Data ......................................... 4 0 J . R e f e r e n c e s .............................................. 4 0
1. Existing Data: ......................................... 4 0
2. Data Supplied with this Service Bulletin: ........................... 4 1
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 1 K. Publications Affected ........................................ 4 1 L. Interchangeability and Intermixability of Parts ........................... 4 2 M. Software Accomplishment Summary ................................ 4 2
2. MATERIAL INFORMATION ........................................ 4 3 A. Material - Price and Availability ................................... 4 3 B. Industry Support Information .................................... 4 3 C. Parts Necessary for Each Airplane ................................. 4 3 1 . K i t s / P a r t s ............................................ 4 3
2. Parts and Materials Supplied by the Operator ........................ 4 3
3. Parts Modified and Reidentified ................................ 4 3
4. Parts Removed and Not Replaced .............................. 4 3 D. Parts Necessary to Change Spares ................................. 4 3 E. Special Tooling - Price and Availability ............................... 4 3 F. Special Tooling Necessary to do this Service Bulletin ....................... 4 3
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 5 A. GENERAL INFORMATION ..................................... 4 5 B. WORK INSTRUCTIONS ....................................... 4 7 FIGURE 1: STUB BEAM WEBS AT STA 685 AND STA 706 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 2] ............... 5 6 FIGURE 2: STUB BEAM WEBS AT STA 685 AND STA 706 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 2] ............... 5 9 FIGURE 3: STUB BEAM WEBS AT STA 685 AND STA 706 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 3] ............... 6 2 FIGURE 4: STUB BEAM WEBS AT STA 685 AND STA 706 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 3] ............... 6 4 FIGURE 5: STUB BEAM WEBS AT STA 685 AND STA 706 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 4, 6] .............. 6 6 FIGURE 6: STUB BEAM WEBS AT STA 685 AND STA 706 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 4, 6] .............. 6 9 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 7: STUB BEAM WEBS AT STA 685 AND STA 706 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 5] ............... 7 2 FIGURE 8: STUB BEAM WEBS AT STA 685 AND STA 706 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 5] ............... 7 5 FIGURE 9: STUB BEAM WEBS AT STA 685 AND STA 706 - GENERAL VISUAL INSPECTION FOR ANY EXISTING REPAIR [Group 2-6] ................................ 7 8 FIGURE 10: STUB BEAM WEBS AT STA 685 AND STA 706 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE CRITICAL FASTENER ROW [Group 2-6] . . . 81 FIGURE 11: STUB BEAM WEBS AT STA 685 AND STA 706 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE CRITICAL FASTENER ROW [Group 2-6] . . . 84 FIGURE 12: STUB BEAM WEB AT STA 695 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 2] .......................... 8 7 FIGURE 13: STUB BEAM WEB AT STA 695 - RIGHT SIDE - DETAILED INSPECTION [Group 2] . . . 89 FIGURE 14: STUB BEAM WEB AT STA 695 - LEFT SIDE - DETAILED INSPECTION [Group 3] .... 9 1 FIGURE 15: STUB BEAM WEB AT STA 695 - RIGHT SIDE - DETAILED INSPECTION [Group 3] . . . 93 FIGURE 16: STUB BEAM WEB AT STA 695 - LEFT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 4, 6] ......................... 9 5 FIGURE 17: STUB BEAM WEB AT STA 695 - RIGHT SIDE - HIGH FREQUENCY EDDY CURRENT (HFEC) AND DETAILED INSPECTIONS [Group 4, 6] ......................... 9 7 FIGURE 18: STUB BEAM WEB AT STA 695 - LEFT SIDE - DETAILED INSPECTION [Group 5] .... 9 9 FIGURE 19: STUB BEAM WEB AT STA 695 - RIGHT SIDE - DETAILED INSPECTION [Group 5] . . 101 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 BEAM WEBS [Group 2-3] .................... 1 0 3 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 BEAM WEBS IN REPAIRED AREAS [Group 2-3] ............................. 1 0 5 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 BEAM WEBS [Group 4-6] ............................... 1 0 8 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 BEAM WEBS IN REPAIRED AREAS [Group 4-6] ............................. 1 1 0 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 2-6] ............................. 1 1 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-53A1364Original Issue: May 24, 2017 ATA System: 5311 SUBJECT: FUSELAGE- Frames and Bulkheads - Body Stations 685, 695, and 706 - Stub Beam Web 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 beam webs below the passenger floor at Body Stations (STA) 685, STA 695, and STA 706, left and right sides. Stub beam webs at STA 685, STA 695, and STA 706 have been identified as susceptible to cracking, if not corrected, cracks in three adjacent stub beam webs 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.
Cracks found in the STA 685, STA 695, and STA 706 stub beams are a result of fatigue caused by cyclical loading from pressurization, wing and landing loads. The cracks can lead to the loss of structural integrity of the airframe during flight, collapse of the main landing gear, and/or 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 21,673 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 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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ReferenceAffectedPlanning Data 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 AffectedNoPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator 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 beam webs at the lower inboard notch at Left Buttock Line (LBL) 45 and Right Buttock Line (RBL) 45 and at the penetration holes between LBL 45 and LBL 60, and RBL 45 and RBL 60. Do a HFEC surface inspection for any crack in the STA 695 stub beam web at the penetration holes between LBL 45 and LBL 60. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beam webs 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 beam webs, contact The Boeing Company for the repair instructions and do the repair, and repeat the inspection at all unrepaired stub beam webs at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the inspection at all unrepaired stub beam webs 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 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 of the critical fastener row in stub beam web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack. If an 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 unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by Boeing, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair, at unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If no existing repair is found, repeat the general visual inspection for Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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any existing repair at the repeat interval specified in Paragraph 1.E., Compliance. If any crack is found during HFEC inspections of the critical row fasteners, contact The Boeing Company for repair instructions and do the repair, repeat the HFEC inspections of the critical row fasteners 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 unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat HFEC surface inspection of the critical fastener row in stub beam 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.
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 60, and Right Buttock Line (RBL) 45 and RBL 60. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beam webs 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 beam webs contact The Boeing Company for repair instructions and do the repair, and repeat the inspection at all unrepaired stub beam webs at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat the inspection at all unrepaired stub beam webs 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 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 of the critical fastener row in stub beam web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack. If an 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 unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by Boeing, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair, at unrepaired locations, 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. If any crack is found during HFEC inspections of the critical row fasteners, contact The Boeing Company for repair instructions and do the repair, repeat the HFEC inspections of the critical row fasteners 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 unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat HFEC surface inspection of the critical fastener row in stub beam 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.
Group 4, 6:
Do a High Frequency Eddy Current (HFEC) surface inspection for any crack in the STA 685 and STA 706 stub beam webs at the lower inboard notch at Left Buttock Line (LBL) 45 and Right Buttock Line (RBL) 45 and at the penetration holes between LBL 45 and LBL 60, and RBL 45 and RBL 60. Do a HFEC surface inspection for any crack in the STA 695 stub beam web at the penetration holes between LBL 45 and LBL 60, and RBL 45 and RBL 60. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beam webs at all fastener locations, tooling holes and penetration holes on the left side and right side. If no crack is found, repeat the inspection at areas with approved existing repairs 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 737-300 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 does not exceed the trim out allowance specified in the SRM, repair the stub beam web in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21, and repeat Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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the inspection for any crack, at the repeat interval specified in Paragraph 1.E., Compliance. If the crack in the stub beam 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 unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If any crack is found outside the stub beam webs outside the lower inboard notch, contact The Boeing Company for repair instructions and do the repair.
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 of the critical fastener row in stub beam web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack. If an 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 unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by Boeing, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair, at unrepaired locations, 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. If any crack is found during HFEC inspections of the critical row fasteners, contact The Boeing Company for repair instructions and do the repair, repeat the HFEC inspections of the critical row fasteners 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 unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat HFEC surface inspection of the critical fastener row in stub beam 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.
Group 5:
Do a High Frequency Eddy Current (HFEC) surface inspection for any crack in the STA 685 and STA 706 stub beam webs at the lower inboard notch at Left Buttock Line (LBL) 45 and Right Buttock Line (RBL) 45 and at the penetration holes between LBL 45 and LBL 60, and RBL 45 and RBL 60. Do a detailed inspection for any crack in the STA 685, STA 695, and STA 706 stub beam webs at all fastener locations, tooling holes and penetration holes on the left side and right side. If no crack is found, repeat the inspection at areas with approved existing repairs 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 737-300 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 does not exceed the trim out allowance specified in the SRM, repair the stub beam web in accordance with 737-300 SRM 53-00-07, Repair 21 or 737-500 SRM 53-00-07, Repair 21, and repeat the inspection for any crack, at the repeat interval specified in Paragraph 1.E., Compliance. If the crack in the stub beam 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 unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If any crack is found outside the stub beam webs outside the lower inboard notch, contact The Boeing Company for repair instructions and do the repair.
Group 5:
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 of the critical fastener row in stub beam web common to the structural filler in the STA 685 and STA 706 stub beam webs for any crack. If an 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 unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If any existing repair is found not approved by Boeing, contact The Boeing Company for repair instructions and do the repair, and repeat the general visual inspection for any existing repair, at unrepaired locations, at the repeat interval Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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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. If any crack is found during HFEC inspections of the critical row fasteners, contact The Boeing Company for repair instructions and do the repair, repeat the HFEC inspections of the critical row fasteners 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 unrepaired locations, at the repeat interval specified in Paragraph 1.E., Compliance. If no crack is found, repeat HFEC surface inspection of the critical fastener row in stub beam 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.
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 related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
Refer to Paragraph 1.E., Compliance
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this service bulletin.
MANPOWER Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION None.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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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
LEFT SIDE SHOWN, RIGHT SIDE SIMILAR FLOOR BEAM Original Issue: May 24, 2017 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1364 Work - See page 1 for details. 10 of 114
BOEING SERVICE BULLETIN 737-53A1364
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DO A HIGH FREQUENCY
- FRAME FUSELAGE 57.48 LBL CRACK EDDY CURRENT (HFEC) INSPECTION FOR ANY 45.57 LBL WL
208.10
STUB BEAM WEB
INBD TYPICAL CRACK STA 685 SHOWN 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 45.57 WL
208.10 +++++
TYPICAL STUB BEAM
CRACK NBD WEB STA 695 (VIEW LOOKING FWD) 2534753 Original Issue: May 24, 2017 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 737-53A1364 Work - See page 1 for details. 11 of 114
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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