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Commercial Airplanes 767 Service Bulletin ALERT Number: 767-53A0264 Original Issue: May 12, 2015 Revision 1: April 25, 2016 ATA System: 5315 5335 5365 SUBJECT: FUSELAGE - Skins - Section 41, 43, and 46 Skin Lap Splice Inspection Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2015 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Unpublished Work.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 12, 2015 767-53A0264Revision 1: April 25, 2016 1 of 127
3.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 12, 2015 767-53A0264Revision 1: April 25, 2016 2 of 127 BOEING SERVICE BULLETIN 767-53A0264
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Table of Contents
Revision Transmittal Sheet7
S u m m a r y9
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 0 B. Concurrent Requirements ...................................... 2 1 C. Reason ................................................ 2 1 D. Description .............................................. 2 1 E. Compliance .............................................. 2 2 F . A p p r o v a l ............................................... 3 1 G. Manpower .............................................. 3 2 H. Weight and Balance Changes .................................... 3 6 I. Electrical Load Data ......................................... 3 6 J . R e f e r e n c e s .............................................. 3 6
1. Existing Data: ......................................... 3 6
2. Data Supplied with this Service Bulletin: ........................... 3 7
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 7 K. Publications Affected ........................................ 3 8 L. Interchangeability and Intermixability of Parts ........................... 3 8 M. Software Accomplishment Summary ................................ 3 8
2. MATERIAL INFORMATION ........................................ 3 9 A. Material - Price and Availability ................................... 3 9 B. Industry Support Information .................................... 3 9 C. Parts Necessary for Each Airplane ................................. 3 9 1 . K i t s / P a r t s ............................................ 3 9
2. Parts and Materials Supplied by the Operator ........................ 3 9
3. Parts Modified and Reidentified ................................ 3 9
4. Parts Removed and Not Replaced .............................. 3 9 D. Parts Necessary to Change Spares ................................. 3 9 E. Special Tooling - Price and Availability ............................... 3 9 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 1 A. GENERAL INFORMATION ..................................... 4 1 B. WORK INSTRUCTIONS ....................................... 4 2 FIGURE 1: FUSELAGE SECTION 41 SKIN LAP SPLICE S-8L AND S-8R, STA 368 TO STA 434 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1] . . . 50 FIGURE 2: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA 368 TO STA 434 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1 ] ................................................ 5 2 F I G U R E 3 : T H I S F I G U R E I S D E L E T E D.................................. 5 4 F I G U R E 4 : T H I S F I G U R E I S D E L E T E D.................................. 5 5 FIGURE 5: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 1; Group 2] ........................................... 5 6 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 6: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 1; Group 2] ........................................... 5 8 FIGURE 7: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 2; Group 3] ........................................... 6 0 FIGURE 8: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 2; Group 3] ........................................... 6 2 FIGURE 9: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 4] . . . 64 FIGURE 10: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 4] . . . 66 FIGURE 11: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 5] . . . 68 FIGURE 12: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 5] . . . 70 FIGURE 13: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 6] . . . 72 FIGURE 14: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 6] . . . 74 FIGURE 15: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 7] . . . 76 FIGURE 16: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 7] . . . 78 FIGURE 17: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 8] . . . 80 FIGURE 18: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 8] . . . 82 FIGURE 19: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 10] . . . 84 FIGURE 20: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 10] . . . 86 FIGURE 21: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 11-12] . 88 FIGURE 22: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 11-12] . 90 FIGURE 23: FUSELAGE SECTION 43 SKIN LAP SPLICE S-8R, STA 434 TO 654+22 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 11-15] ....... 9 2 FIGURE 24: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA 368 TO STA 434 INTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION . . 94 FIGURE 25: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA 368 TO STA 434 LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION ................... 9 6 FIGURE 26: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 13] . . 98 FIGURE 27: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 13] . . 100 FIGURE 28: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 14] . . 102 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 29: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 14] . . 104 FIGURE 30: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 15] . . 106 FIGURE 31: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 15] . . 108 APPENDIX A: LOGIC DIAGRAM FOR TABLE 1: FUSELAGE SECTION 41 SKIN LAP SPLICE S-8L AND S-8R, STA 368 TO STA 434 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1] ............................... 1 1 0 APPENDIX B: LOGIC DIAGRAM FOR TABLE 2: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA 368 TO STA 434 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1] ............................... 1 1 2 APPENDIX C: LOGIC DIAGRAM FOR TABLE 3: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1-8, 10-15] .............................. 1 1 4 APPENDIX D: LOGIC DIAGRAM FOR TABLE 4: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1-8, 10-15] .............................. 1 1 6 APPENDIX E: LOGIC DIAGRAM FOR TABLE 5: FUSELAGE SECTION 43 SKIN LAP SPLICE S-8R, STA 434 TO 654+22 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 11] ........................................... 1 1 8 APPENDIX F: LOGIC DIAGRAM FOR TABLE 6: FUSELAGE SECTION 43 SKIN LAP SPLICE S-8R, STA 434 TO 654+22 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 12] ........................................... 1 2 0 APPENDIX G: LOGIC DIAGRAM FOR TABLE 7: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA 368 TO STA 434 INTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION .................................... 1 2 2 APPENDIX H: LOGIC DIAGRAM FOR TABLE 8: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA 368 TO STA 434 LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION ................................................. 1 2 4 APPENDIX I: LOGIC DIAGRAM FOR TABLE 9: FUSELAGE SECTION 43 SKIN LAP SPLICE S-8R, STA 434 TO 654+22 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 13-15] ......................................... 1 2 6 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 12, 2015 767-53A0264Revision 1: April 25, 2016 5 of 127 BOEING SERVICE BULLETIN 767-53A0264
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Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 12, 2015 767-53A0264Revision 1: April 25, 2016 6 of 127 BOEING SERVICE BULLETIN 767-53A0264
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Commercial Airplanes 767 Service Bulletin ALERT Revision Transmittal SheetNumber: 767-53A0264Original Issue: May 12, 2015 Revision 1: April 25, 2016 ATA System: 5315 5335 5365 SUBJECT: FUSELAGE - Skins - Section 41, 43, and 46 Skin Lap Splice Inspection This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2014-14-04 is related to this service bulletin.
The effective date of AD 2014-14-04 is September 5, 2014.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
Effects of this Revision on airplanes on which Original Issue was previously done:
None.
REASON FOR REVISION This Revision is sent to update the effectivity of this service bulletin, add work instructions and figures for three new airplane groups with a large main deck cargo door, clarify repeat inspection requirements and update logic diagrams.
These sections were changed:
1. Summary., Concurrent Requirements: Added Referance to Paragraph 1.B, Concurrent requirements
2. Paragraph 1.A., Effectivity:
– Airplanes VA311-VA313, VA509-VA510, VA512-513, VA807-VA809, VB101-VB104, VB106-VB109, VB115-VB116, VB120 and VB441-VB444 have been moved from Group 2 to Group 3.
– Airplanes VS901-VS912, VS921-VS928, VS931-VS933, VS951-VS954, VS961-VS969, VS971-VS975, VS981-VS984, VT001-VT013, VT021 and VT031-VT033 have been moved from Group 8 to Group 7.
– Airplanes VN055, VN081-VN086, VN153 and VN168 have been moved from Group 12 to Group
7.
– Airplane VN921 has been moved from Group 12 to new Group 13.
– Airplanes VL806 and VL807 have been moved from Group 4 to new Group 13.
– Airplane VN791 has been moved from Group 4 to new Group 14.
– Airplane VN792 has been moved from Group 6 to new Group 14.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 12, 2015 767-53A0264Revision 1: April 25, 2016 7 of 127
– Airplanes VS721 and VS186 have been moved from Group 7 to new Group 15.
3. Paragraph 1.B., Concurrent Requirements: Added service bulletin 767-53A0260 as a concurrent requirement.
4. Paragraph 1.D., Description: Added new airplane Groups to the affected maintenance zone table.
5. Paragraph 1.E., Compliance: Clarified repeat inspection requirements in Tables 1 thru 8 and added Table 9 for new airplane Groups, and added reference to new APPENDIX I.
6. Paragraph 1.G., Manpower: Revised Manpower table for Group 1, Configuration 1, added new manpower Tables For Group 1, Configuration 2, and Groups 13,14 and 15.
7. Paragraph 3.A., Accomplishment Instructions: Updated General Information, Note 13.
8. Paragraph 3.B., Work Instructions: Clarified work instructions for repeat inspections for areas that have not been repaired and added inspection instructions for the new airplane Groups, added Reference to Paragraph 1.E., Compliance.
9. Figures 2 and 24: Removed step table footnote.
10. Figures 3 and 4 were deleted.
11. Figure 23 illustration was revised.
12. Figures 26, 27, 28, 29, 30 and 31: Added to give inspection instructions for new airplane Groups.
13. Appendix A, B, C, D, E, F, G and H: Logic Diagrams updated.
14. Appendix I: Added for new airplane Groups.
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 12, 2015Original Issue:
April 25, 2016Revision 1:
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 12, 2015 767-53A0264Revision 1: April 25, 2016 8 of 127 BOEING SERVICE BULLETIN 767-53A0264
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Commercial Airplanes 767 Service Bulletin ALERT SummaryNumber: 767-53A0264Original Issue: May 12, 2015 Revision 1: April 25, 2016 ATA System: 5315 5335 5365 SUBJECT: FUSELAGE - Skins - Section 41, 43, and 46 Skin Lap Splice Inspection
THIS BULLETIN 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 SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER.
CONCURRENT REQUIREMENTS Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND Widespread Fatigue Damage (WFD) analysis of the 767, as required by 14 CFR 26.21(b), has resulted in the conclusion that the existing 767 MPD Section 9 Airworthiness Limitation Instructions inspection program is not sufficient to preclude the occurrence of WFD in the fuselage skin lap splice as the airplane ages. The fuselage skin lap splice has multiple similar adjacent details which have the potential for Multi-Site Damage (MSD) and the potential for WFD. 14 CFR 26.21 requires evaluation of such designs for the potential for WFD and implementation of the appropriate service actions to ensure that WFD is precluded before the Limit of Validity (LOV). Boeing has not received any reports of cracks in the fuselage skin lap splices. Accomplishment of the inspection described in this service bulletin will enable detection and repair of cracks at the fuselage skin lap splice. If Widespread Fatigue cracking is not found and repaired, cracks can rapidly link up, which could result in rapid decompression and loss of structural integrity of the airplane.
The fuselage skin lap splices have been determined to be structure that are susceptible to Widespread Fatigue Damage (WFD).
Boeing Service Bulletin 767-53A0260 is related to this service bulletin.
Boeing Service Related Problem (SRP) 767-SRP-53-0464 and 767-SRP-53-0458 are related to this service bulletin.
Boeing 767 MPD Section 9, SSI 53-10-I07A/B, 53-30-I04A/C, 53-60-I05A/C are 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.
Original Issue: May 12, 2015 767-53A0264Revision 1: April 25, 2016 9 of 127
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 Do an external High Frequency Eddy Current (HFEC), Low Frequency Eddy Current (LFEC) and internal HFEC inspections of the fuselage skin at applicable skin lap splices for any crack. If any crack is found, do the repair in accordance with this service bulletin. If no crack is found, do repetitive inspections at the repeat interval in accordance with this service bulletin.
EFFECTIVITY 767-200, -300 and -400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2014-14-04 is related to this service bulletin.
The effective date of AD 2014-14-04 is September 5, 2014.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
This service bulletin affects SSI 53-10-I07A/B, 53-30-I04A/C, 53-60-I05A/C of 767 MPD Section 9, which is mandated by AD 2014-14-04. All other MPD inspections outside of the affected area are not affected and must continue.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspections or repairs given in this service bulletin.
MANPOWER Refer to Paragraph 1.G., Manpower.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 12, 2015 767-53A0264Revision 1: April 25, 2016 10 of 127 BOEING SERVICE BULLETIN 767-53A0264
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BOEING SERVICE BULLETIN 767-53A0264
ALERT ALERT
MATERIAL INFORMATION None.
DO AN EXTERNAL HIGH FREQUENCY EDDY CURRENT (HFEC), LOW FREQUENCY EDDY CURRENT (LFEC)
AND INTERNAL HFEC INSPECTIONS OF THE FUSELAGE
SKIN AT APPLICABLE SKIN LAP SPLICES FOR ANY CRACK
IF ANY CRACK IS FOUND, DO THE REPAIR IN ACCORDANCE WITH THIS SERVICE BULLETIN. IF NO CRACK IS FOUND, DC
REPETITIVE INSPECTIONS AT THE REPEAT INTERVAL IN ACCORDANCE WITH THIS SERVICE BULLETIN 2384039 Original Issue: May 12, 2015 Revision 1: April 25, 2016 Export Controlled ECCN: 9E991 - BOEING 767-53A0264 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 127
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 12, 2015 767-53A0264Revision 1: April 25, 2016 12 of 127 BOEING SERVICE BULLETIN 767-53A0264