# Boeing Alert Service Bulletin 767-53A0264: Revision 1

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- Document: [Boeing Alert Service Bulletin 767-53A0264](https://openairdocs.org/service-documents/boeing/767-53a0264.md)
- Title as filed: BOEING SB-767-53A0264-01-
- Pages: 127
- PDF: https://openairdocs.org/files/sha256/1f/bf/1fbf32f37d28fe3aade53be66adaf13c8249e4410a2028a05bc4251b1cdf05a2
- Page: https://openairdocs.org/service-documents/boeing/767-53a0264/file/1fbf32f37d28

## Text

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### Page 1

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Unpublished Work.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

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Original Issue: May 12, 2015
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ALERTALERT
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Table of Contents
Revision Transmittal Sheet ............................................ 7
S u m m a r y  ...................................................... 9
1. PLANNING INFORMATION ........................................ 1 3
A . E f f e c t i v i t y  ............................................... 1 3
1. Airplanes ............................................ 1 3
2 . S p a r e s  A f f e c t e d  ........................................ 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
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ALERTALERT

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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
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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
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ALERTALERT
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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.
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– 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:
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ALERTALERT

### Page 9

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
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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 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
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.
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### Page 11 (OCR)

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
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PROPRIETARY - Copyright © Unpublished
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Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT
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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
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.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is applicable to 767-200, -300 and -400ER Airplanes in 15 Groups. The
Variable Numbers and Group Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
767-200 airplanes, line numbers 1 thru 42.-1
767-200 airplanes, line numbers 1 thru 42, with forward large cargo
door.
1
767-200 airplanes, line numbers 1 thru 42, with forward small cargo
door.
2
767-200 airplanes, line numbers 43 and on, with forward large cargo
door.
-2
767-200 airplanes, line numbers 43 and on, with forward small cargo
door.
-3
767-300 airplanes with forward entry doors, Type I emergency exit
door and forward large cargo door.
-4
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### Page 14

DESCRIPTIONCONFIGURATIONGROUP
767-300 airplanes with forward entry door, Type I emergency exit
door, and forward small cargo door.
-5
767-300 airplanes with forward entry doors and forward large cargo
door.
-6
767-300 airplanes with forward large cargo door, excluding Group 4
and Group 6.
-7
767-300 airplanes with forward small cargo door, excluding Group
5.
-8
767-400ER airplanes.-9
767-200 Special Freighter (SF) airplane, line number 109, with forward
small cargo door.
-10
767-300 Boeing Converted Freighter (BCF) airplanes, line number
269 with forward large cargo door.
-11
767-300 Boeing Converted Freighter (BCF) airplanes, line numbers
285, 379, 432, 463, 556 and 645 with forward large cargo door.
-12
767-300 Boeing Converted Freighter (BCF) airplanes, line numbers
484, 635 and 650, with forward entry doors, Type I emergency exit
door, and forward large cargo door.
-13
767-300 Boeing Converted Freighter (BCF) airplanes, line numbers
434 and 438 with forward entry doors and forward large cargo door.
-14
767-300 Boeing Converted Freighter (BCF) airplanes, line numbers
710 and 877 with forward large cargo door.
-15
Airplane Models:
767-200, 767-300, 767-400ER
GroupVariable Number
1VA006
1VA008 - VA012
3VA016
3VA018 - VA020
1VA301
1VA303 - VA308
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GroupVariable Number
3VA309 - VA315
1VA501 - VA502
3VA508 - VA510
10VA511
3VA512 - VA523
3VA525
3VA527 - VA530
1VA702 - VA703
2VA704
2VA706 - VA719
1VA803 - VA804
3VA807 - VA809
1VB001
2VB002
1VB053
3VB055
3VB101 - VB112
3VB114 - VB122
3VB125
1VB201
3VB282
3VB302
3VB327 - VB330
3VB371 - VB373
3VB441 - VB444
2VE002
2VE021
2VE023
2VE041
2VE063 - VE064
2VE066 - VE069
2VE084 - VE085
2VE102 - VE103
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GroupVariable Number
2VE116 - VE118
2VE121 - VE124
2VE141 - VE149
2VE151 - VE152
2VE171 - VE172
2VF001 - VF002
2VF042
2VF051
2VF061 - VF062
2VF071 - VF072
2VF091 - VF093
2VF162
2VF171
2VF180
3VF181 - VF184
2VF251
8VK005 - VK016
7VK021 - VK022
8VK031 - VK045
8VK051 - VK056
8VK094 - VK113
5VK131 - VK133
7VK142 - VK148
6VK164
7VK171
7VK181
7VK186
6VL001 - VL003
6VL005 - VL006
6VL011
7VL701 - VL703
6VL751 - VL755
13VL806 - VL807
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GroupVariable Number
4VL871 - VL873
4VL891 - VL900
4VL911 - VL914
7VL931 - VL932
7VL941
7VN001 - VN041
7VN051 - VN064
7VN081 - VN099
4VN111 - VN114
4VN117 - VN127
4VN130 - VN137
7VN151 - VN153
7VN155 - VN158
7VN163 - VN168
6VN174
11VN191
12VN192 - VN197
7VN198
6VN211
7VN224 - VN225
6VN231 - VN233
6VN242 - VN243
7VN251 - VN252
7VN254 - VN276
7VN291 - VN292
6VN301 - VN314
4VN371 - VN372
4VN376
4VN381 - VN388
4VN421
7VN422 - VN427
7VN436
4VN472
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GroupVariable Number
7VN491 - VN513
4VN531 - VN532
4VN536 - VN537
4VN541 - VN542
4VN546 - VN547
4VN551
4VN556 - VN557
4VN561 - VN562
4VN631 - VN633
6VN634 - VN636
4VN637 - VN638
7VN651 - VN658
7VN671
7VN676
8VN681 - VN691
7VN731 - VN732
7VN751 - VN753
14VN791 - VN792
7VN811 - VN813
13VN921
4VN922
7VN931 - VN936
4VN951 - VN953
7VN966 - VN972
9VQ001 - VQ021
9VQ071 - VQ086
9VQ111
2VR051 - VR060
2VR081
2VR084
8VR401
7VR421 - VR423
7VR426
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GroupVariable Number
8VR441
7VR461
8VR471 - VR472
4VS051 - VS056
6VS061
7VS066 - VS070
7VS073 - VS078
7VS091 - VS104
7VS111 - VS113
7VS131 - VS133
4VS136 - VS137
7VS176 - VS177
15VS186
7VS187
7VS196 - VS203
7VS206 - VS208
4VS211
4VS216 - VS217
7VS231
4VS246 - VS248
4VS261 - VS263
7VS266 - VS274
7VS291 - VS293
7VS301 - VS303
4VS306 - VS311
4VS316
4VS321 - VS324
4VS331 - VS333
4VS336 - VS337
7VS366 - VS367
7VS381 - VS382
7VS391 - VS392
7VS401
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GroupVariable Number
4VS426 - VS428
7VS466 - VS472
7VS486
6VS496 - VS497
6VS506 - VS507
7VS526
7VS546 - VS549
7VS701 - VS720
15VS721
7VS722 - VS736
7VS751 - VS759
7VS821 - VS825
7VS841 - VS844
7VS861
4VS881 - VS883
4VS891
7VS896
7VS901 - VS912
4VS916
7VS921 - VS928
7VS931 - VS933
4VS941
7VS951 - VS954
7VS961 - VS969
7VS971 - VS975
4VS976 - VS977
7VS981 - VS984
7VT001 - VT013
7VT021
7VT031 - VT033
2. Spares Affected
None.
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B. Concurrent Requirements
The service bulletin listed below must be done before or at the same time as this service bulletin:
DescriptionService BulletinCompany
S-2R Skin Lap Splice, STA 368 TO STA 434 - Inspection767-53A0260Boeing
C. Reason
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.
Revision 1 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.
D. Description
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.
Revision 1- Effects of this Revision on airplanes on which Original Issue was previously done:
None.
The work in this service bulletin is done in the maintenance zone(s) given below.
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### Page 22

Group 1-3, 10:
Affected Maintenance Zones
ZoneModel
121, 122, 123, 124, 125, 126, 151, 152, 153,
154, 155, 156, 161, 162, 163, 164, 221, 222,
223, 224, 231, 232, 233, 234, 251, 252, 253, 254
767-200
Group 4-8, 11-15:
Affected Maintenance Zones
ZoneModel
121, 122, 123, 124, 125, 126, 151, 152, 153,
154, 155, 156, 161, 162, 163, 164, 221, 222,
223, 224, 231, 232, 233, 234, 251, 252, 253, 254
767-300
Group 9:
Affected Maintenance Zones
ZoneModel
121, 122, 123, 124, 125, 126, 151, 152, 153,
154, 155, 156, 161, 162, 163, 164, 221, 222,
223, 224, 231, 232, 233, 234, 251, 252, 253, 254
767-400ER
E. 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.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX
A, APPENDIX B, APPENDIX C, APPENDIX D, APPENDIX E, APPENDIX F, APPENDIX G, APPENDIX
H and APPENDIX I.
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Group 1:
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
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the last
HFEC inspection in
accordance with
MPD SSI 53-10-
I07A, or, within
3,000 flight cycles
after the Original
Issue date of this
service bulletin,
whichever occurs
later.
Before 50,000
total flight cy-
cles.
Do PART 1: FUSELAGE SEC-
TION 41 SKIN LAP SPLICE S-8L
AND S-8R, STA 368 TO STA 434
EXTERNAL SURFACE HIGH
FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
(a)
All Airplanes
-Before further flight.CONDITION 1 (ACTION 1): Do
PART 8: REPAIR.
CONDITION 1:
ANY CRACK
FOUND 6,000 flight cycles.-CONDITION 1 (ACTION 2): Re-
peat PART 1: FUSELAGE SEC-
TION 41 SKIN LAP SPLICE S-8L
AND S-8R, STA 368 TO STA 434
EXTERNAL SURFACE HIGH
FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
(a)
6,000 flight cycles.-Repeat PART 1: FUSELAGE
SECTION 41 SKIN LAP SPLICE
S-8L AND S-8R, STA 368 TO
STA 434 EXTERNAL SURFACE
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) INSPECTION for
any crack.
CONDITION 2:
NO CRACK
FOUND
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs,
approved by the Boeing ODA via FAA form 8100-9, or repairs installed in accordance with 767-200 SRM
53-00-01 cover the affected inspection areas. Damage Tolerance Inspection instructions specified in ap-
proval for existing repairs must continue. Inspection outside of the repaired region must continue as in-
structed in accordance with this service bulletin.
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### Page 24

Group 1:
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
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 12,000 flight
cycles after the last
HFEC inspection in
accordance with
MPD SSI 53-10-
I07A, or, within
3,000 flight cycles
after the Original
Issue date of this
service bulletin,
whichever occurs
later.
Before 50,000
total flight cy-
cles.
Do PART 2: FUSELAGE SEC-
TION 41 SKIN LAP SPLICE S-17L
AND S-17R, STA 368 TO STA
434 EXTERNAL SURFACE HIGH
FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
(a)
All Airplanes
-Before further flight.CONDITION 3 (ACTION 1): Do
PART 8: REPAIR.
CONDITION 3:
ANY CRACK
FOUND 12,000 flight cy-
cles.
-CONDITION 3 (ACTION 2): Re-
peat PART 2: FUSELAGE SEC-
TION 41 SKIN LAP SPLICE S-17L
AND S-17R, STA 368 TO STA
434 EXTERNAL SURFACE HIGH
FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
(a)
12,000 flight cy-
cles.
-Repeat PART 2: FUSELAGE
SECTION 41 SKIN LAP SPLICE
S-17L AND S-17R, STA 368 TO
STA 434 EXTERNAL SURFACE
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) INSPECTION for
any crack.
CONDITION 4:
NO CRACK
FOUND
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs,
approved by the Boeing ODA via FAA form 8100-9, or repairs installed in accordance with 767-200 SRM
53-00-01 cover the affected inspection areas. Damage Tolerance Inspection instructions specified in ap-
proval for existing repairs must continue. Inspection outside of the repaired region must continue as in-
structed in accordance with this service bulletin.
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### Page 25

Group 1-8, 10-15:
Table 3: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the last
HFEC inspection in
accordance with
MPD SSI 53-30-
I04C and MPD 53-
60-I05C, or, within
3,000 flight cycles
after the Original
Issue date of this
service bulletin,
whichever occurs
later.
Before 60,000
total flight cy-
cles.
Do PART 3: FUSELAGE SEC-
TION 43 AND SECTION 46 SKIN
LAP SPLICE BELOW S-20 EX-
TERNAL SURFACE HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
(a)
All Airplanes
-Before further flight.CONDITION 5 (ACTION 1): Do
PART 8: REPAIR.
CONDITION 5:
ANY CRACK
FOUND 6,000 flight cycles.-CONDITION 5 (ACTION 2): Re-
peat PART 3: FUSELAGE SEC-
TION 43 AND SECTION 46 SKIN
LAP SPLICE BELOW S-20 EX-
TERNAL SURFACE HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
(a)
6,000 flight cycles.-Repeat PART 3: FUSELAGE
SECTION 43 AND SECTION 46
SKIN LAP SPLICE BELOW S-20
EXTERNAL SURFACE HIGH
FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
CONDITION 6:
NO CRACK
FOUND
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs,
approved by the Boeing ODA via FAA form 8100-9, or repairs installed in accordance with 767-200 SRM
53-00-01, 767-200SF SRM 53-00-01, 767-300 SRM 53-00-01, or 767-300BCF SRM 53-00-01 cover the
affected inspection areas. Damage Tolerance Inspection instructions specified in approval for existing
repairs must continue. Inspection outside of the repaired region must continue as instructed in accordance
with this service bulletin.
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### Page 26

Group 1-8, 10-15:
Table 4: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 9,000 flight
cycles after the last
HFEC inspection in
accordance with
MPD SSI 53-30-
I04A and MPD 53-
60-I05A, or, within
3,000 flight cycles
after the Original
Issue date of this
service bulletin,
whichever occurs
later.
Before 60,000
total flight cy-
cles.
Do PART 4: FUSELAGE SEC-
TION 43 AND SECTION 46 SKIN
LAP SPLICE ABOVE S-20 EX-
TERNAL SURFACE HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
(a)
All Airplanes
-Before further flight.CONDITION 7 (ACTION 1): Do
PART 8: REPAIR.
CONDITION 7:
ANY CRACK
FOUND 9,000 flight cycles.-CONDITION 7 (ACTION 2): Re-
peat PART 4: FUSELAGE SEC-
TION 43 AND SECTION 46 SKIN
LAP SPLICE ABOVE S-20 EX-
TERNAL SURFACE HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
(a)
9,000 flight cycles.-Repeat PART 4: FUSELAGE
SECTION 43 AND SECTION 46
SKIN LAP SPLICE ABOVE S-20
EXTERNAL SURFACE HIGH
FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
CONDITION 8:
NO CRACK
FOUND
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs,
approved by the Boeing ODA via FAA form 8100-9, or repairs installed in accordance with 767-200 SRM
53-00-01, 767-200SF SRM 53-00-01, 767-300 SRM 53-00-01, or 767-300BCF SRM 53-00-01 over the
affected inspection areas. Damage Tolerance Inspection instructions specified in approval for existing
repairs must continue. Inspection outside of the repaired region must continue as instructed in accordance
with this service bulletin.
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### Page 27

Group 11:
Table 5: FUSELAGE SECTION 43 SKIN LAP SPLICE S-8R, STA 434 TO 654+22 EXTERNAL SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 3,000 flight
cycles after the
Original Issue date
of this service bul-
letin.
Within 30,000 flight
cycles after BCF
modification.
Do PART 5: FUSELAGE
SECTION 43 SKIN LAP
SPLICE S-8R, STA 434 TO
654+22 EXTERNAL SUR-
FACE HIGH FREQUENCY
EDDY CURRENT (HFEC) IN-
SPECTION for any crack.
All Airplanes
(a)
-Before further flight.CONDITION 9 (ACTION 1):
Do PART 8: REPAIR.
CONDITION 9:
ANY CRACK
FOUND 9,000 flight cycles.-CONDITION 9 (ACTION 2):
Repeat PART 5: FUSELAGE
SECTION 43 SKIN LAP
SPLICE S-8R, STA 434 TO
654+22 EXTERNAL SUR-
FACE HIGH FREQUENCY
EDDY CURRENT (HFEC) IN-
SPECTION for any crack.
(a)
9,000 flight cycles.-Repeat PART 5: FUSELAGE
SECTION 43 SKIN LAP
SPLICE S-8R, STA 434 TO
654+22 EXTERNAL SUR-
FACE HIGH FREQUENCY
EDDY CURRENT (HFEC) IN-
SPECTION for any crack.
CONDITION 10:
NO CRACK
FOUND
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs,
approved by the Boeing ODA via FAA form 8100-9, or repairs installed in accordance with 767-300BCF
SRM 53-00-01 cover the affected inspection areas. Damage Tolerance Inspection instructions specified
in approval for existing repairs must continue. Inspection outside of the repaired region must continue as
instructed in accordance with this service bulletin.
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### Page 28

Group 12:
Table 6: FUSELAGE SECTION 43 SKIN LAP SPLICE S-8R, STA 434 TO 654+22 EXTERNAL SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 3,000 flight
cycles after the
Original Issue date
of this service bul-
letin.
Within 20,000 flight
cycles after BCF
modification.
Do PART 5: FUSELAGE
SECTION 43 SKIN LAP
SPLICE S-8R, STA 434 TO
654+22 EXTERNAL SUR-
FACE HIGH FREQUENCY
EDDY CURRENT (HFEC) IN-
SPECTION for any crack.
All Airplanes
(a)
-Before further flight.CONDITION 9 (ACTION 1):
Do PART 8: REPAIR.
CONDITION 9:
ANY CRACK
FOUND 9,000 flight cycles.-CONDITION 9 (ACTION 2):
Repeat PART 5: FUSELAGE
SECTION 43 SKIN LAP
SPLICE S-8R, STA 434 TO
654+22 EXTERNAL SUR-
FACE HIGH FREQUENCY
EDDY CURRENT (HFEC) IN-
SPECTION for any crack.
(a)
9,000 flight cycles.-Repeat PART 5: FUSELAGE
SECTION 43 SKIN LAP
SPLICE S-8R, STA 434 TO
654+22 EXTERNAL SUR-
FACE HIGH FREQUENCY
EDDY CURRENT (HFEC) IN-
SPECTION for any crack.
CONDITION 10:
NO CRACK
FOUND
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs,
approved by the Boeing ODA via FAA form 8100-9, or repairs installed in accordance with 767-300BCF
SRM 53-00-01 cover the affected inspection areas. Damage Tolerance Inspection instructions specified
in approval for existing repairs must continue. Inspection outside of the repaired region must continue as
instructed in accordance with this service bulletin.
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### Page 29

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
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 12,000 flight
cycles after the last
HFEC inspection in
accordance with
MPD SSI 53-10-
I07B, or, within
3,000 flight cycles
after the Original Is-
sue date of this ser-
vice bulletin,
whichever occurs
later.
Before 50,000 total
flight cycles.
Do PART 6: FUSELAGE
SECTION 41 SKIN LAP
SPLICE S-17L AND S-17R,
STA 368 TO STA 434 INTER-
NAL SURFACE HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
(a)
All Airplanes
-Before further flight.CONDITION 11 (ACTION 1):
Do PART 8: REPAIR.
CONDITION 11:
ANY CRACK
FOUND 12,000 flight cy-
cles.
-CONDITION 11 (ACTION 2):
Repeat PART 6: FUSELAGE
SECTION 41 SKIN LAP
SPLICE S-17L AND S-17R,
STA 368 TO STA 434 INTER-
NAL SURFACE HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
(a)
12,000 flight cy-
cles.
-Repeat PART 6: FUSELAGE
SECTION 41 SKIN LAP
SPLICE S-17L AND S-17R,
STA 368 TO STA 434 INTER-
NAL SURFACE HIGH FRE-
QUENCY EDDY CURRENT
(HFEC) INSPECTION for any
crack.
CONDITION 12:
NO CRACK
FOUND
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs,
approved by the Boeing ODA via FAA form 8100-9, or repairs installed in accordance with 767-200 SRM
53-00-01, 767-200SF SRM 53-00-01, 767-300 SRM 53-00-01, 767-300BCF SRM 53-00-01, or 767-400ER
SRM 53-00-01 cover the affected inspection areas. Damage Tolerance Inspection instructions specified
in approval for existing repairs must continue. Inspection outside of the repaired region must continue as
instructed in accordance with this service bulletin.
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Table 8: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA 368 TO STA 434 EXTERNAL
LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 3,000 flight
cycles after the last
LFEC inspection in
accordance with
MPD SSI 53-10-
I07B, or, within
3,000 flight cycles
after the Original Is-
sue date of this ser-
vice bulletin,
whichever occurs
later.
Before 50,000 total
flight cycles.
Do PART 7: FUSELAGE
SECTION 41 SKIN LAP
SPLICE S-17L AND S-17R,
STA 368 TO STA 434 EXTER-
NAL LOW FREQUENCY ED-
DY CURRENT (LFEC) IN-
SPECTION for any crack.
(a)
All Airplanes
-Before further flight.CONDITION 13 (ACTION 1):
Do PART 8: REPAIR.
CONDITION 13:
ANY CRACK
FOUND 3,000 flight cycles.-CONDITION 13 (ACTION 2):
Repeat PART 7: FUSELAGE
SECTION 41 SKIN LAP
SPLICE S-17L AND S-17R,
STA 368 TO STA 434 EXTER-
NAL LOW FREQUENCY ED-
DY CURRENT (LFEC) IN-
SPECTION for any crack.
(a)
3,000 flight cycles.-Repeat PART 7: FUSELAGE
SECTION 41 SKIN LAP
SPLICE S-17L AND S-17R,
STA 368 TO STA 434 EXTER-
NAL LOW FREQUENCY ED-
DY CURRENT (LFEC) IN-
SPECTION for any crack.
CONDITION 14:
NO CRACK
FOUND
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs,
approved by the Boeing ODA via FAA form 8100-9, or repairs installed in accordance with 767-200 SRM
53-00-01, 767-200SF SRM 53-00-01, 767-300 SRM 53-00-01, 767-300BCF SRM 53-00-01, or 767-400ER
SRM 53-00-01 cover the affected inspection areas. Damage Tolerance Inspection instructions specified
in approval for existing repairs must continue. Inspection outside of the repaired region must continue as
instructed in accordance with this service bulletin.
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Group 13-15:
Table 9: FUSELAGE SECTION 43 SKIN LAP SPLICE S-8R, STA 434 TO 654+22 EXTERNAL SURFACE
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
Repeat Interval
(Not To Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 3,000 flight
cycles after the
Original Issue date
of this service bul-
letin.
Within 40,000 flight
cycles after BCF
modification.
Do PART 5: FUSELAGE
SECTION 43 SKIN LAP
SPLICE S-8R, STA 434 TO
654+22 EXTERNAL SUR-
FACE HIGH FREQUENCY
EDDY CURRENT (HFEC) IN-
SPECTION for any crack.
All Airplanes
(a)
-Before further flight.CONDITION 9 (ACTION 1):
Do PART 8: REPAIR.
CONDITION 9:
ANY CRACK
FOUND 9,000 flight cycles.-CONDITION 9 (ACTION 2):
Repeat PART 5: FUSELAGE
SECTION 43 SKIN LAP
SPLICE S-8R, STA 434 TO
654+22 EXTERNAL SUR-
FACE HIGH FREQUENCY
EDDY CURRENT (HFEC) IN-
SPECTION for any crack.
(a)
9,000 flight cycles.-Repeat PART 5: FUSELAGE
SECTION 43 SKIN LAP
SPLICE S-8R, STA 434 TO
654+22 EXTERNAL SUR-
FACE HIGH FREQUENCY
EDDY CURRENT (HFEC) IN-
SPECTION for any crack.
CONDITION 10:
NO CRACK
FOUND
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs,
approved by the Boeing ODA via FAA form 8100-9, or repairs installed in accordance with 767-300BCF
SRM 53-00-01 cover the affected inspection areas. Damage Tolerance Inspection instructions specified
in approval for existing repairs must continue. Inspection outside of the repaired region must continue as
instructed in accordance with this service bulletin.
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.
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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 Seattle Aircraft Certification Office approves the accomplishment
of the inspections defined in this service bulletin along with the corresponding compliance times specified
in Paragraph 1.E., Compliance, of this service bulletin, as an alternative method of compliance (AMOC)
to the inspections defined in D622T001-DTR Structural Significant Items (SSI) 53-10-I07A/B,
53-30-I04A/C, 53-60-I05A/C and Section 9 of the Maintenance Planning Document D622T001-9,
required by paragraphs (i) and (k) of AD 2014-14-04. This AMOC only applies to the areas inspected
in accordance with this service bulletin. All provisions of AD 2014-14-04 that are not specifically
referenced in this paragraph remain fully applicable and must be complied with accordingly.
G. Manpower
The table below shows an estimate of the task hours necessary to do the inspections for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools
Group 1, Configuration 1:
Elapsed HoursTask HoursNumber of PersonsTask
2.55.02FIGURE 1
2.55.02FIGURE 2
13.2553.04FIGURE 5
22.2589.04FIGURE 6
2.55.02FIGURE 24
4.59.02FIGURE 25
47.5166.0TOTAL FOR EACH AIRPLANE
Group 1, Configuration 2:
Elapsed HoursTask HoursNumber of PersonsTask
2.55.02FIGURE 1
2.55.02FIGURE 2
14.2557.04FIGURE 7
22.2589.04FIGURE 8
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Group 1, Configuration 2:
Elapsed HoursTask HoursNumber of PersonsTask
2.55.02FIGURE 24
4.59.02FIGURE 25
48.5170.0TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
13.2553.04FIGURE 5
22.2589.04FIGURE 6
2.55.02FIGURE 24
4.59.02FIGURE 25
42.5156.0TOTAL FOR EACH AIRPLANE
Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
14.2557.04FIGURE 7
22.2589.04FIGURE 8
2.55.02FIGURE 24
4.59.02FIGURE 25
43.5160.0TOTAL FOR EACH AIRPLANE
Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
16.566.04FIGURE 9
18.072.04FIGURE 10
2.55.02FIGURE 24
4.59.02FIGURE 25
41.5152.0TOTAL FOR EACH AIRPLANE
Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
17.570.04FIGURE 11
18.072.04FIGURE 12
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Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
2.55.02FIGURE 24
4.59.02FIGURE 25
42.5156.0TOTAL FOR EACH AIRPLANE
Group 6:
Elapsed HoursTask HoursNumber of PersonsTask
16.566.04FIGURE 13
18.072.04FIGURE 14
2.55.02FIGURE 24
4.59.02FIGURE 25
41.5152.0TOTAL FOR EACH AIRPLANE
Group 7:
Elapsed HoursTask HoursNumber of PersonsTask
17.7571.04FIGURE 15
18.072.04FIGURE 16
2.55.02FIGURE 24
4.59.02FIGURE 25
42.75157.0TOTAL FOR EACH AIRPLANE
Group 8:
Elapsed HoursTask HoursNumber of PersonsTask
20.582.04FIGURE 17
18.072.04FIGURE 18
2.55.02FIGURE 24
4.59.02FIGURE 25
45.5168.0TOTAL FOR EACH AIRPLANE
Group 9:
Elapsed HoursTask HoursNumber of PersonsTask
2.55.02FIGURE 24
4.59.02FIGURE 25
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Group 9:
Elapsed HoursTask HoursNumber of PersonsTask
7.014.0TOTAL FOR EACH AIRPLANE
Group 10:
Elapsed HoursTask HoursNumber of PersonsTask
26.553.02FIGURE 19
41.082.02FIGURE 20
2.55.02FIGURE 24
4.59.02FIGURE 25
74.5149.0TOTAL FOR EACH AIRPLANE
Group 11-12:
Elapsed HoursTask HoursNumber of PersonsTask
35.571.02FIGURE 21
32.565.02FIGURE 22
4.08.02FIGURE 23
2.55.02FIGURE 24
4.59.02FIGURE 25
79.0158.0TOTAL FOR EACH PLANE
Group 13:
Elapsed HoursTask HoursNumber of PersonsTask
4.08.02FIGURE 23
2.55.02FIGURE 24
2.55.02FIGURE 25
14.558.04FIGURE 26
10.7543.04FIGURE 27
34.25119.0TOTAL FOR EACH PLANE
Group 14:
Elapsed HoursTask HoursNumber of PersonsTask
4.08.02FIGURE 23
2.55.02FIGURE 24
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Group 14:
Elapsed HoursTask HoursNumber of PersonsTask
2.55.02FIGURE 25
14.2557.04FIGURE 28
10.7543.04FIGURE 29
34.0118.0TOTAL FOR EACH PLANE
Group 15:
Elapsed HoursTask HoursNumber of PersonsTask
4.08.02FIGURE 23
2.55.02FIGURE 24
2.55.02FIGURE 25
15.8563.404FIGURE 30
10.7543.04FIGURE 31
35.60124.40TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 767-53A0260
b. Boeing Service Related Problem (SRP) 767-SRP-53-0458, 767-SRP-53-0464
c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2014-14-04
d. Service Bulletin Index D624T001
e. 767 Aircraft Maintenance Manual (AMM) 25-21-01, 25-21-05, 25-25-01, 25-59-01, 25-59-05
f. 767 Maintenance Planning Data (MPD) Section 9
g. 767 Non-Destructive Testing (NDT) Manual Part 6, 53-10-18, Part 6, 53-10-19, Part 6, 53-10-20
h. 767-200 Structural Repair Manual (SRM) 53-00-01
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i. 767-200SF Structural Repair Manual (SRM) 53-00-01
j. 767-300 Structural Repair Manual (SRM) 53-00-01
k. 767-300BCF Structural Repair Manual (SRM) 53-00-01
l. 767-400ER Structural Repair Manual (SRM) 53-00-01
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
SKIN PANEL ASSY - STA 246 TO STA 434, S-17 TO S-26141T3330
SKIN PANEL ASSY- STA 246 TO STA 434, STGR 8 TO STGR 17141T3320
SKIN PANEL ASSY - STA 434 TO STA 785.9 S-8R TO S-17R143T3410
SKIN PANEL ASSY- STA 434 TO STA 785.9, S-36L TO S-36R143T3220
SKIN PANEL ASSY - STA 434 TO STA 785.9, S-26 TO S-36L143T3210
SKIN PANEL ASSY - STA 434 TO STA 785.9, S-17L TO S-26L143T3320
SKIN PANEL ASSY - STA 434 TO STA 785.9, S-8L TO S-17L143T3310
SKIN PANEL ASSY- STA 434 TO STA 785.9 S-8L TO S-2R143T3110
SKIN PANEL ASSY - STA 434 TO STA 785.9, S-2R TO S-8R143T3120
SKIN PANEL ASSY - STA 434 TO STA 785.9, S-17R TO S-26R143T3510
SKIN PANEL ASSY - STA 434 TO STA 785.9, S-26R TO S-36R143T3520
SKIN PANEL ASSY - STA 654 TO 785.9, S-26R TO S-36R143T3561
SKIN PANEL ASSY - STA 654 TO 785.9, S-17R TO S-26R143T3461
SKIN PANEL ASSY - STA 654 TO STA 785.9, S-8R TO S-17R143T3451
SKIN PANEL ASSY - STA 654 TO STA 785.9 S-2R TO S-8R143T3161
SKIN PANEL ASSY - STA 654 TO 785.9, S-8L TO S-17L143T3351
SKIN PANEL ASSY - STA 654 TO STA 785.9, S-17L TO S-26L143T3361
SKIN PANEL ASSY - STA 654 TO STA 785.9, S-26L TO S-36L143T3251
SKIN PANEL ASSY - STA 654 TO STA 785.9, S-36L TO S-36R143T3261
SKIN PANEL ASSY - STA 1065 TO STA 1307, S-26R TO S-36R146T3510
SKIN PANEL ASSY - STA 1065 TO STA 1307, S-17R TO S-26R146T3520
SKIN PANEL ASSY - STA 1065 TO STA 1395, S-8 TO S-17146T3310
SKIN PANEL ASSY - STA 1065 TO STA 1395, S-2R TO S-8L146T3110
SKIN PANEL ASSY - STA 1065 TO STA 1395, S-2R TO S-8R146T3120
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TitleDrawing Number
SKIN PANEL ASSY - STA 1065 TO STA 1307, S-17L TO S-26L146T3320
SKIN PANEL ASSY - STA 1065 TO STA 1307, S-26L TO S-36L146T3210
SKIN PANEL ASSY - STA 1307 TO STA 1582, S-17L TO S-26L146T3340
SKIN PANEL ASSY - STA 1307 TO STA 1582, S-26L TO S-36L146T3230
SKIN PANEL ASSY - STA 1395 TO STA 1582, S-8 TO S-17146T3330
SKIN PANEL ASSY - STA 1395 TO STA 1582, S-8L TO S-2R146T3130
SKIN PANEL ASSY - STA 1395 TO STA 1582, S2R TO S-8R146T3140
SKIN PANEL ASSY - STA 1395 TO STA 1582, S-8R TO S-17R146T3430
SKIN PANEL ASSY - STA 1395 TO STA 1582, S-17R TO S-26R146T3440
SKIN PANEL ASSY - STA 1307 TO STA 1582, S-26R TO S-36R146T3530
SKIN PANEL ASSY - STA 1065 TO STA 1219, S-26R TO S-36R146T3551
SKIN PANEL ASSY - STA 1065 TO STA 1219, S-17R TO S-26R146T3561
SKIN PANEL ASSY - STA 1065 TO STA 1219, S-8R TO S-17R146T3451
SKIN PANEL ASSY - STA 1065 TO STA 1219, S-2R TO S-8R146T3161
SKIN PANEL ASSY - STA 1065 TO STA 1219, S-8L TO S-17L146T3351
SKIN PANEL ASSY - STA 1065 TO STA 1219, S-17L TO S-26L146T3361
SKIN PANEL ASSY - STA 1065 TO STA 1219, S-26L TO S-36L146T3251
SKIN PANEL ASSY - STA 1307 TO STA 1582, S-36L TO S-36R146T3240
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. None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS 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.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspections or repairs 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.
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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 767 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 767
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 767
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. 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.
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.
7. Refer to Appendices A, B, C, D, E, F, G, H and I for logic diagram(s). 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.
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8. 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.
9. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
10. 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.
11. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
12. The CONDITIONS, ACTIONS and OPTIONS shown apply to each fuselage skin lap
slice independently.
13. 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. 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.
B. WORK INSTRUCTIONS
1. Group 1:
RC - Do PART 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
for any crack.
a. CONDITION 1: ANY CRACK FOUND
(1) CONDITION 1 (ACTION 1): Do PART 8: REPAIR.
(2) CONDITION 1 (ACTION 2): Repeat PART 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 for any crack at the time specified in Paragraph
1.E., Compliance.
b. CONDITION 2: NO CRACK FOUND
(1) Repeat PART 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 for any crack at the time specified in Paragraph 1.E., Compliance.
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### Page 43

2. Group 1:
RC - Do PART 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
for any crack.
a. CONDITION 3: ANY CRACK FOUND
(1) CONDITION 3 (ACTION 1): Do PART 8: REPAIR.
(2) CONDITION 3 (ACTION 2): Repeat PART 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 for any crack at the time specified in Paragraph
1.E., Compliance.
b. CONDITION 4: NO CRACK FOUND
(1) Repeat PART 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 for any crack at the time specified in Paragraph 1.E., Compliance.
3. Group 1-8, 10-15:
RC - Do PART 3: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20
EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION for any
crack.
a. CONDITION 5: ANY CRACK FOUND
(1) CONDITION 5 (ACTION 1): Do PART 8: REPAIR.
(2) CONDITION 5 (ACTION 2): Repeat PART 3: FUSELAGE SECTION 43 AND SECTION
46 SKIN LAP SPLICE BELOW S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION for any crack at the time specified in Paragraph 1.E.,
Compliance.
b. CONDITION 6: NO CRACK FOUND
(1) Repeat PART 3: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW
S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
for any crack at the time specified in Paragraph 1.E., Compliance.
4. Group 1-8, 10-15:
RC - Do PART 4: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20
EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION for any
crack.
a. CONDITION 7: ANY CRACK FOUND
(1) CONDITION 7 (ACTION 1): Do PART 8: REPAIR.
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### Page 44

(2) CONDITION 7 (ACTION 2): Repeat PART 4: FUSELAGE SECTION 43 AND SECTION
46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION for any crack at the time specified in Paragraph 1.E.,
Compliance.
b. CONDITION 8: NO CRACK FOUND
(1) Repeat PART 4: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE
S-20 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
for any crack at the time specified in Paragraph 1.E., Compliance.
5. Group 10-15:
RC - Do PART 5: FUSELAGE SECTION 43 SKIN LAP SPLICE S-8R, STA 434 TO 654+22
EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION for any
crack.
a. CONDITION 9: ANY CRACK FOUND
(1) CONDITION 9 (ACTION 1): Do PART 8: REPAIR.
(2) CONDITION 9 (ACTION 2): Repeat PART 5: FUSELAGE SECTION 43 SKIN LAP SPLICE
S-8R, STA 434 TO 654+22 EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for any crack at the time specified in Paragraph 1.E., Compliance.
b. CONDITION 10: NO CRACK FOUND
(1) Repeat PART 5: FUSELAGE SECTION 43 SKIN LAP SPLICE S-8R, STA 434 TO 654+22
EXTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
for any crack at the time specified in Paragraph 1.E., Compliance.
6. RC - Do PART 6: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA 368 TO
STA 434 INTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
for any crack.
a. CONDITION 11: ANY CRACK FOUND
(1) CONDITION 11 (ACTION 1): Do PART 8: REPAIR.
(2) CONDITION 11 (ACTION 2): Repeat PART 6: FUSELAGE SECTION 41 SKIN LAP
SPLICE S-17L AND S-17R, STA 368 TO STA 434 INTERNAL SURFACE HIGH
FREQUENCY EDDY CURRENT (HFEC) INSPECTION for any crack at the time specified
in Paragraph 1.E., Compliance.
b. CONDITION 12: NO CRACK FOUND
(1) Repeat PART 6: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA
368 TO STA 434 INTERNAL SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTION for any crack at the time specified in Paragraph 1.E., Compliance.
7. RC - Do PART 7: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA 368 TO
STA 434 EXTERNAL LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack.
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### Page 45

a. CONDITION 13: ANY CRACK FOUND
(1) CONDITION 13 (ACTION 1): Do PART 8: REPAIR.
(2) CONDITION 13 (ACTION 2): Repeat PART 7: FUSELAGE SECTION 41 SKIN LAP
SPLICE S-17L AND S-17R, STA 368 TO STA 434 EXTERNAL LOW FREQUENCY
EDDY CURRENT (LFEC) INSPECTION for any crack at the time specified in Paragraph
1.E., Compliance.
b. CONDITION 14: NO CRACK FOUND
(1) Repeat PART 7: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA
368 TO STA 434 External Low Frequency Eddy Current (LFEC) INSPECTION for any
crack at the time specified in Paragraph 1.E., Compliance.
8. Put the airplane back to a serviceable condition.
Group 1:
PART 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
1. RC - Do a HFEC inspection of the outer skin lap splice upper row of fasteners for any crack in
accordance with the Figure for the applicable Group shown in the table that follows:
FIGUREGROUP
FIGURE 1GROUP 1
NOTE: It is not necessary to do inspections in accordance with this service bulletin in areas where
existing repairs, approved by the Boeing ODA via FAA form 8100-9, or repairs installed
in accordance with 767-200 SRM 53-00-01 cover the affected inspection areas. Damage
Tolerance Inspection instructions specified in approval for existing repairs must continue.
Inspection outside of the repaired region must continue as instructed in accordance with
this service bulletin.
Group 1:
PART 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
1. RC - Do a HFEC inspection of the outer skin lap splice upper row of fasteners for any crack in
accordance with the Figure for the applicable Group shown in the table that follows:
FIGUREGROUP
FIGURE 2GROUP 1
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### Page 46

NOTE: It is not necessary to do inspections in accordance with this service bulletin in areas where
existing repairs, approved by the Boeing ODA via FAA form 8100-9, or repairs installed
in accordance with 767-200 SRM 53-00-01 cover the affected inspection areas. Damage
Tolerance Inspection instructions specified in approval for existing repairs must continue.
Inspection outside of the repaired region must continue as instructed in accordance with
this service bulletin.
Group 1-8, 10-15:
PART 3: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL
SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
1. RC - Do a HFEC inspection of the outer skin lap splice upper row of fasteners for any crack in
accordance with the Figure for the applicable Group shown in the table that follows:
FIGUREGROUP
FIGURE 5GROUP 1, CONFIGURATION 1
FIGURE 7GROUP 1, CONFIGURATION 2
FIGURE 5GROUP 2
FIGURE 7GROUP 3
FIGURE 9GROUP 4
FIGURE 11GROUP 5
FIGURE 13GROUP 6
FIGURE 15GROUP 7
FIGURE 17GROUP 8
FIGURE 19GROUP 10
FIGURE 21GROUPS 11 and 12
FIGURE 26GROUP 13
FIGURE 28GROUP 14
FIGURE 30GROUP 15
NOTE: It is not necessary to do inspections in accordance with this service bulletin in areas where
existing repairs, approved by the Boeing ODA via FAA form 8100-9, or repairs installed
in accordance with 767-200 SRM 53-00-01, 767-200SF SRM 53-00-01, 767-300 SRM
53-00-01, or 767-300BCF SRM 53-00-01 cover the affected inspection areas. Damage
Tolerance Inspection instructions specified in approval for existing repairs must continue.
Inspection outside of the repaired region must continue as instructed in accordance with
this service bulletin.
Group 1-8, 10-15:
PART 4: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL
SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
1. RC - Do a HFEC inspection of the outer skin lap splice upper row of fasteners for any crack in
accordance with the Figure for the applicable Group shown in the table that follows:
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### Page 47

FIGUREGROUP
FIGURE 6GROUP 1, CONFIGURATION 1
FIGURE 8GROUP 1, CONFIGURATION 2
FIGURE 6GROUP 2
FIGURE 8GROUP 3
FIGURE 10GROUP 4
FIGURE 12GROUP 5
FIGURE 14GROUP 6
FIGURE 16GROUP 7
FIGURE 18GROUP 8
FIGURE 20GROUP 10
FIGURE 22GROUPS 11 and 12
FIGURE 27GROUP 13
FIGURE 29GROUP 14
FIGURE 31GROUP 15
NOTE: It is not necessary to do inspections in accordance with this service bulletin in areas where
existing repairs, approved by the Boeing ODA via FAA form 8100-9, or repairs installed
in accordance with 767-200 SRM 53-00-01, 767-200SF SRM 53-00-01, 767-300 SRM
53-00-01, or 767-300BCF SRM 53-00-01 cover the affected inspection areas. Damage
Tolerance Inspection instructions specified in approval for existing repairs must continue.
Inspection outside of the repaired region must continue as instructed in accordance with
this service bulletin.
Group 11-15:
PART 5: FUSELAGE SECTION 43 SKIN LAP SPLICE S-8R, STA 434 TO 654+22 EXTERNAL
SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
1. RC - Do a HFEC inspection of the outer skin lap splice upper row of fasteners for any crack in
accordance with the Figure for the applicable Group shown in the table that follows:
FIGUREGROUP
FIGURE 23GROUPS 11, 12, 13, 14 and 15
NOTE: It is not necessary to do inspections in accordance with this service bulletin in areas where
existing repairs, approved by the Boeing ODA via FAA form 8100-9, or repairs installed
in accordance with 767-300BCF SRM 53-00-01 cover the affected inspection areas.
Damage Tolerance Inspection instructions specified in approval for existing repairs must
continue. Inspection outside of the repaired region must continue as instructed in
accordance with this service bulletin.
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### Page 48

PART 6: 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. Remove and keep the following equipment/furnishings to get access to the fuselage skin lap splices
internal surfaces. Refer to the Aircraft Maintenance Manual (AMM) for the applicable Group shown
in the table that follows as accepted procedures:
AMMEQUIPMENT / FURNISH-
ING
GROUP
767 AMM 25-25-01Passenger SeatsGROUPS 1, 2, 3, 4, 5,
6, 7, 8 and 9 767 AMM 25-21-01Panels
767 AMM 25-21-05Insulation
767 AMM 25-59-01Cargo Lining PanelsGROUPS 10, 11, 12,
13, 14 and 15 767 AMM 25-59-05Insulation
2. RC - Do a HFEC inspection of the inner skin lap splice lower row of fasteners for any crack in
accordance with the Figure for the applicable Group shown in the table that follows:
FIGUREGROUP
FIGURE 24ALL GROUPS
NOTE: It is not necessary to do inspections in accordance with this service bulletin in areas where
existing repairs, approved by the Boeing ODA via FAA form 8100-9, or repairs installed
in accordance with 767-200 SRM 53-00-01, 767-200SF SRM 53-00-01, 767-300 SRM
53-00-01, 767-300BCF SRM 53-00-01, or 767-400ER SRM 53-00-01 cover the affected
inspection areas. Damage Tolerance Inspection instructions specified in approval for
existing repairs must continue. Inspection outside of the repaired region must continue
as instructed in accordance with this service bulletin.
3. Install kept equipment/furnishings that were removed for access to the fuselage skin lap splices
internal surfaces. Refer to the Aircraft Maintenance Manual (AMM) for the applicable Group shown
in the table that follows as accepted procedures:
AMMEQUIPMENT / FURNISH-
ING
GROUP
767 AMM 25-25-01Passenger SeatsGROUPS 1, 2, 3, 4, 5,
6, 7, 8 and 9 767 AMM 25-21-01Panels
767 AMM 25-21-05Insulation
767 AMM 25-59-01Cargo Lining PanelsGROUPS 10, 11, 12,
13, 14 and 15 767 AMM 25-59-05Insulation
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### Page 49

PART 7: FUSELAGE SECTION 41 SKIN LAP SPLICE S-17L AND S-17R, STA 368 TO STA 434
EXTERNAL LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION
1. RC - Do a LFEC inspection of the inner skin lap splice lower row of fasteners for any crack in
accordance with the Figure for the applicable Group shown in the table that follows:
FIGUREGROUP
FIGURE 25ALL GROUPS
NOTE: It is not necessary to do inspections in accordance with this service bulletin in areas where
existing repairs, approved by the Boeing ODA via FAA form 8100-9, or repairs installed
in accordance with 767-200 SRM 53-00-01, 767-200SF SRM 53-00-01, 767-300 SRM
53-00-01, 767-300BCF SRM 53-00-01, or 767-400ER SRM 53-00-01 cover the affected
inspection areas. Damage Tolerance Inspection instructions specified in approval for
existing repairs must continue. Inspection outside of the repaired region must continue
as instructed in accordance with this service bulletin.
PART 8: REPAIR
1. RC - Repair fuselage skin lap splice cracks in accordance with the Structural Repair Manual (SRM)
for the applicable Group shown in the table that follows:
SRMGROUP
767-200 SRM 53-00-01GROUPS 1, 2 and 3
767-300 SRM 53-00-01GROUPS 4, 5, 6, 7 and 8
767-400ER SRM 53-00-01GROUP 9
767-200SF SRM 53-00-01GROUP 10
767-300BCF SRM 53-00-01GROUPS 11, 12, 13, 14 and 15
NOTE: It is not necessary to do inspections in accordance with this service bulletin in areas where
existing repairs, approved by the Boeing ODA via FAA form 8100-9, or repairs installed
in accordance with 767-200 SRM 53-00-01, 767-200SF SRM 53-00-01, 767-300 SRM
53-00-01, 767-300BCF SRM 53-00-01, or 767-400ER SRM 53-00-01 cover the affected
inspection areas. Damage Tolerance Inspection instructions specified in approval for
existing repairs must continue. Inspection outside of the repaired region must continue
as instructed in accordance with this service bulletin.
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ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN 767-53A0264
ALERT  ALERT
This Figure applies only to: Group 1.
STA
434
STA  STA
246  368
000
- S-8R
BL O-
- S-8L
1000
INSPECTION AREA  SECTION 41
A-A
LAP SPLICE
OUTER SKIN
FRAME
STRINGER
INNER SKIN
INSPECTION AREA  2381617
TYPICAL SKIN LAP SPLICE
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
(SHEET 1 OF 2)
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### Page 51

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataLocationNameTaskStep
(a)S-8L, STA 368 TO STA 434Outer SkinInspect1
S-8R, STA 368 TO STA 434
(a) Do a surface HFEC inspection of the outer skin lap splice upper row of fasteners for any crack in accordance
with 767 NDT Manual Part 6, 53-10-18.
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
(SHEET 2 OF 2)
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ALERTALERT

### Page 52 (OCR)

BOEING SERVICE BULLETIN 767-53A0264
ALERT  ALERT
This Figure applies only to: Group 1.
STA  STA STA
246  368  434
100 OT S-17R
BLO
000
- S-17L
- INSPECTION AREA
SECTION 41
A-A
LAP SPLICE
OUTER SKIN
FRAME
STRINGER
INNER SKIN
I INSPECTION AREA  TYPICAL SKIN LAP SPLICE  2383171
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
(SHEET 1 OF 2)
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### Page 53

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataLocationNameTaskStep
(a)S-17L, STA 368 TO STA 434Outer SkinInspect1
S-17R, STA 368 TO STA 434
(a) Do a surface HFEC inspection of the outer skin lap splice upper row of fasteners for any crack in accordance
with 767 NDT Manual Part 6, 53-10-18.
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
(SHEET 2 OF 2)
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ALERTALERT

### Page 54

FIGURE 3: THIS FIGURE IS DELETED
(SHEET 1 OF 1)
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### Page 55

FIGURE 4: THIS FIGURE IS DELETED
(SHEET 1 OF 1)
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ALERTALERT

### Page 56 (OCR)

BOEING SERVICE BULLETIN 767-53A0264
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 1; Group 2.
- INSPECTION AREA
STA  B  STA  STA  STA  STA  STA
434  654  786.1  1065  1395  1582
S-36R
S-26R
000000000000  000000000000000000
000000000000  000000000000000000
• S-26L
S-36L
STA  STA STA  STA
1109  1241 1307  1480
SECTION 43  A-A  SECTION 46  B-B
OUTER SKIN  - LAP SPLICE
FRAME
STRINGER
INNER SKIN  2383175
INSPECTION AREA  TYPICAL SKIN LAP SPLICE
FIGURE 5: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL
SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 1 OF 2)
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### Page 57

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataLocationNameTaskStep
(a)S-26L, STA 434 TO STA 786.1Outer SkinInspect1
S-26R, STA 654 TO STA 786.1
S-36L, STA 434 TO STA 786.1
S-36R, STA 654 TO STA 786.1
(a)S-26L, STA 1109 TO STA 1395Outer SkinInspect2
S-26L, STA 1480 TO STA 1582
S-26R, STA 1395 TO STA 1582
S-36L, STA 1241 TO STA 1307
(a) Do a surface HFEC inspection of the outer skin lap splice upper row of fasteners for any crack along
Stringers S-26R, S-26L, S-36R and S-36L in accordance with 767 NDT Manual Part 6, 53-10-18.
FIGURE 5: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL
SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 2 OF 2)
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ALERTALERT

### Page 58 (OCR)

BOEING SERVICE BULLETIN 767-53A0264
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 1; Group 2.
• INSPECTION AREA
STA  STA  STA  STA
434  786.1  1065  1582
000000000000  -S-17R  000000000000000000
-S-8R  - S-8R
-S-2R  - S-2R
-S-8L  - S-8L
000000000000  00 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0
-S-17L
STA  STA  STA
698  1109  1285
SECTION 43  SECTION 46
A-A  B-B
- LAP SPLICE
OUTER SKIN
FRAME
STRINGER
INNER SKIN  2383282
INSPECTION AREA  TYPICAL SKIN LAP SPLICE
FIGURE 6: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL
SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 1 OF 2)
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### Page 59

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataLocationNameTaskStep
(a)S-2R, STA 434 TO STA 786.1Outer SkinInspect1
S-8L, STA 434 TO STA 786.1
S-8R, STA 434 TO STA 786.1
S-17L, STA 434 TO STA 698
S-17R, STA 434 TO STA 698
(a)S-2R, STA 1285 TO STA 1582Outer SkinInspect2
S-8L, STA 1109 TO STA 1582
S-8R, STA 1109 TO STA 1582
(a) Do a surface HFEC inspection of the outer skin lap splice upper row of fasteners for any crack along
Stringers S-2R, S-8R, S-8L, S-17R, S-17L in accordance with 767 NDT Manual Part 6, 53-10-18.
FIGURE 6: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE ABOVE S-20 EXTERNAL
SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 2 OF 2)
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ALERTALERT

### Page 60 (OCR)

BOEING SERVICE BULLETIN 767-53A0264
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 2; Group 3.
— INSPECTION AREA
STA STA  STA  STA  STA  STA  STA
434  500  632  786.1  1065  1395  1582
S-36R -
S-26R -
000000000000  000000000000000000
000000000000 0  000000000000000000
S-26L -
S-36L -
STA  STA  TA SI  STA
654  1153  1241 13  1480
SECTION 43  SECTION 46
A-A  B-B
OUTER SKIN
~ LAP SPLICE
FRAME
STRINGER  INNER SKIN
INSPECTION AREA  TYPICAL SKIN LAP SPLICE  2383292
FIGURE 7: FUSELAGE SECTION 43 AND SECTION 46 SKIN LAP SPLICE BELOW S-20 EXTERNAL
SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
(SHEET 1 OF 2)
Original Issue: May 12, 2015
Revision 1 April 25, 2016  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0264
Work - See page 1 for details.  60 of 127

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