# Boeing Alert Service Bulletin 767-53A0266: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2015-4210; AD 2016-13-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 767-53A0266](https://openairdocs.org/service-documents/boeing/767-53a0266.md)
- Title as filed: U.S. DOT/FAA - SB 767-53A0266  R0
- Pages: 41
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## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-53A0266
Original Issue: April 20, 2015
ATA System: 5380
SUBJECT: FUSELAGE - Aft Pressure Bulkhead - STA 1582 Aft Pressure Bulkhead Web Inspection
Under Pressure Chord Splice Plate
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Unpublished Work.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: April 20, 2015
767-53A0266
1 of 41
5.0

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PROPRIETARY - Copyright © Unpublished
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Original Issue: April 20, 2015
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ALERTALERT
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### Page 3

Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 23
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 25
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 26
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
FIGURE 1: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -
FASTENER REMOVAL AND WEB INSPECTION  [Group 2, Configuration 1; Group 3] . . 32
FIGURE 2: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -
FASTENER REMOVAL AND WEB INSPECTION [Group 1; Group 2, Configuration 2; Group 4]
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
FIGURE 3: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER
INSTALLATION [Group 2, Configuration 1; Group 3] . . . . . . . . . . . . . . . . . . . . . 36
FIGURE 4: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER
INSTALLATION [Group 1; Group 2, Configuration 2; Group 4] . . . . . . . . . . . . . . . 38
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: AFT PRESSURE
BULKHEAD WEB INSPECTIONS AT PRESSURE CHORD JOINT. [Group 2, Configuration 1;
Group 3-4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 4

APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 2: AFT PRESSURE
BULKHEAD WEB INSPECTIONS AT PRESSURE CHORD JOINT. [Group 1; Group 2,
Configuration 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
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Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-53A0266Original Issue: April 20, 2015
ATA System: 5380
SUBJECT: FUSELAGE - Aft Pressure Bulkhead - STA 1582 Aft Pressure Bulkhead Web Inspection
Under Pressure Chord Splice Plate
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
None.
BACKGROUND
Accomplishment of the inspection described in this service bulletin will enable detection and repair of cracks if
they should occur, in the areas under splice plates at the Station (STA) 1582 aft pressure bulkhead web to
pressure chord joint. If a crack is present in the aft pressure bulkhead web and not found and repaired, crack
growth can result in possible rapid decompression and loss of structural integrity.
The aft pressure bulkhead web is attached to the pressure chords with a double row of fasteners and the pressure
chord segments are spliced using pressure chord splice plates. At these splice plate locations, the aft pressure
bulkhead web is hidden and cannot be inspected in accordance with existing 767 MPD Section 9 or Service
Bulletin (SB) 767-53A0087 and do not provide sufficient crack detection probability of the aft pressure bulkhead
web under splice plates.
Boeing Service Related Problem (SRP) 767-SRP-53-0470 is related to this service bulletin.
Boeing SB 767-53A0087 and 767-53A0139 are related to this service bulletin.
Boeing 767 MPD SSI 53-80-I01A is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
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ReferenceAffectedPlanning Data
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
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Get access to the forward and aft sides of the aft pressure bulkhead at STA 1582. Locate the splice plates that
splice pressure chords on the circumference of the forward side of the aft pressure bulkhead. Remove the aft
row of fasteners from each splice plate and do an open hole High Frequency Eddy Current (HFEC) inspection
for any crack in the aft pressure bulkhead web. If any crack is found, contact The Boeing Company for repair
instructions and do the repair. If no crack is found, install new fasteners, close access to the area and repeat
the inspection at the time specified in Paragraph 1.E., Compliance.
EFFECTIVITY
All 767-200/-300/-300F/-400ER airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
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.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-05-16 is related to this service bulletin.
The effective date of AD 2004-05-16 is April 13, 2004.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-09-08 is related to this service bulletin.
The effective date of AD 2012-09-08 is June 18, 2012.
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.
This service bulletin is related to 767 MPD SSI 53-80-I01A, 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 inspection and/or repair procedures given in this service
bulletin.
Export Controlled ECCN: 9E991 - BOEING
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### Page 7

MANPOWER
Elapsed
Hours
Total Task
Hours
Airplanes
12.6045.20Group 1, Configuration 1 Airplanes
13.3546.70Group 1, Configuration 2 Airplanes
12.6045.20Group 2, Configuration 1 Passenger Airplanes
8.6017.20Group 2, Configuration 1 Converted Freighters
13.3546.70Group 2, Configuration 2 Passenger Airplanes
9.3518.70Group 2, Configuration 2 Converted Freighters
12.6045.20Group 3 Passenger Airplanes
8.6017.20Group 3 Freighters and Converted Freighters
13.3546.70Group 4 Passenger Airplanes
9.3518.70Group 4 Freighters and Converted Freighters
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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### Page 8 (OCR)

BOEING SERVICE BULLETIN 767-53A0266
ALERT  ALERT
REMOVE ROW OF SIX AFT FASTENERS AND DO A HIGH
FREQUENCY EDDY CURRENT INSPECTION FOR ANY CRACK.
IF ANY CRACK IS FOUND, CONTACT THE BOEING COMPANY
FOR REPAIR INSTRUCTIONS AND DO THE REPAIR. IF NO
CRACK IS FOUND, DO REPEAT INSPECTIONS.
BULKHEAD WEB
TYPICAL RADIAL
STIFFENER
SPLICE PLATE
STA
1582
SKIN  INBD
TYPICAL INSPECTION AREA
NOTE:
SOME AFFECTED AIRPLANE CONFIGURATIONS HAVE SHORT
STIFFENERS AT THE AFT PRESSURE BULKHEAD TO PRESSURE
CHORD JOINT. SHORT STIFFENERS ARE NOT SHOWN FOR
CLARITY.
Original Issue: April 20, 2015
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0266
Work - See page 1 for details.  8 of 41

### Page 9

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-53A0266
Original Issue: April 20, 2015
ATA System: 5380
SUBJECT: FUSELAGE - Aft Pressure Bulkhead - STA 1582 Aft Pressure Bulkhead Web Inspection
Under Pressure Chord Splice Plate
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 all 767 Airplanes, in 4 Groups. The Variable Numbers and
Group Information for the applicable airplanes are given below.
Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
NOTE: The Variable Number table below includes all affected airplanes up to Line Number 1097.
Affected airplanes after Line Number 1097 will be added to the service bulletin's
MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet
Profile Page.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes from line number 1 to 175 with aft pressure bulkhead
replaced in accordance with SB 767-53A0139, with four pressure
chord splice plates.
-1
Airplanes from line number 176 to 423.-2
Airplanes with original production bulkhead installed with three
pressure chord splice plates.
1
Airplanes with aft pressure bulkhead replaced in accordance with a
Boeing Organization Design Authorization (ODA) approval via FAA
Form 8100-9, with four pressure chord splice plates.
2
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### Page 10

DESCRIPTIONCONFIGURATIONGROUP
Airplanes from line number 424 to 926 installed with three pressure
chord splice plates.
-3
Airplanes from line number 927 and on installed with four pressure
chord splice plates.
-4
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
1VA001 - VA020
1VA301 - VA315
1VA501 - VA526
2VA527 - VA530
1VA701 - VA712
2VA713 - VA719
1VA801 - VA810
1VB001 - VB002
1VB051 - VB055
1VB101 - VB125
1VB201 - VB202
1VB251 - VB253
1VB281 - VB284
1VB301 - VB302
1VB321 - VB324
2VB325 - VB332
1VB371 - VB373
1VB401
3VB441 - VB444
1VE001 - VE002
2VE003
1VE021 - VE023
1VE041 - VE043
1VE061 - VE068
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GroupVariable Number
2VE069
1VE083 - VE084
2VE085 - VE086
1VE101 - VE103
2VE104
1VE116 - VE117
2VE118
1VE121 - VE123
2VE124 - VE126
1VE141 - VE142
2VE143 - VE151
3VE152
2VE171 - VE172
2VF001 - VF002
2VF041 - VF042
2VF051
2VF061 - VF062
2VF071 - VF072
2VF091 - VF093
2VF101 - VF102
2VF161
3VF162
3VF171 - VF172
3VF180 - VF184
3VF251
1VK001 - VK004
2VK005 - VK011
3VK012 - VK016
2VK021 - VK022
1VK031 - VK037
2VK038 - VK053
3VK054 - VK056
2VK081 - VK099
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GroupVariable Number
3VK100 - VK113
2VK131 - VK133
2VK141 - VK142
3VK143 - VK148
3VK161 - VK164
3VK171
3VK181
3VK186
1VL001
2VL002 - VL006
1VL011
3VL701 - VL703
3VL751 - VL755
3VL806 - VL807
3VL871 - VL873
3VL891 - VL900
3VL911 - VL914
3VL931 - VL932
3VL941
2VN001 - VN019
3VN020 - VN041
2VN051 - VN062
3VN063 - VN064
2VN081 - VN092
3VN093 - VN099
2VN111 - VN124
3VN125 - VN127
2VN130 - VN132
3VN133 - VN137
2VN151 - VN158
2VN163 - VN168
2VN171 - VN173
3VN174
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GroupVariable Number
2VN191 - VN193
3VN194 - VN198
2VN211 - VN212
2VN221 - VN224
3VN225
2VN231 - VN234
2VN241
3VN242 - VN243
2VN251 - VN259
3VN260 - VN276
2VN291
3VN292 - VN293
2VN301 - VN306
3VN307 - VN314
2VN371 - VN372
2VN376
2VN381
3VN382 - VN388
3VN421 - VN427
3VN436
2VN471 - VN472
2VN491 - VN496
3VN497 - VN513
2VN531 - VN532
2VN536 - VN537
2VN541 - VN542
3VN546 - VN547
2VN551
3VN556 - VN557
3VN561 - VN562
2VN631 - VN633
3VN634 - VN638
2VN651 - VN652
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GroupVariable Number
3VN653 - VN658
2VN671 - VN672
3VN676
2VN681 - VN683
3VN684 - VN691
2VN731
3VN732
2VN751 - VN753
3VN791 - VN792
3VN811 - VN813
3VN921 - VN922
3VN931 - VN936
3VN951 - VN953
3VN966 - VN972
3VQ001 - VQ021
3VQ071 - VQ086
4VQ111
3VR051 - VR060
3VR081
3VR084
3VR086
4VR087 - VR089
4VR106 - VR109
3VR201 - VR211
3VR251
3VR256 - VR260
4VR266 - VR292
3VR401
3VR421 - VR423
3VR426
3VR441
3VR461
3VR471 - VR472
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GroupVariable Number
3VS051 - VS056
3VS061
3VS066 - VS070
3VS073 - VS078
3VS091 - VS104
3VS111 - VS113
3VS131 - VS133
3VS136 - VS137
3VS176 - VS177
3VS186 - VS187
3VS196 - VS203
3VS206 - VS208
3VS211
3VS216 - VS217
3VS231
3VS246 - VS248
3VS261 - VS263
3VS266 - VS274
3VS291 - VS293
3VS301 - VS303
3VS306 - VS311
3VS316
3VS321 - VS324
3VS331 - VS333
3VS336 - VS337
3VS366 - VS367
3VS381 - VS382
3VS391 - VS392
3VS401
3VS426 - VS428
3VS466 - VS472
3VS486
3VS496 - VS497
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GroupVariable Number
3VS506 - VS507
3VS526
3VS546 - VS549
3VS701 - VS710
4VS711 - VS720
3VS721 - VS731
4VS732 - VS736
3VS751 - VS759
3VS821 - VS825
3VS841 - VS844
3VS861
3VS881 - VS882
4VS883
3VS891
4VS896
4VS901 - VS912
4VS916
4VS921 - VS928
4VS931 - VS933
4VS941
4VS951 - VS954
4VS961 - VS969
4VS971 - VS977
4VS981 - VS984
4VT001 - VT013
4VT021
4VT031 - VT033
3VT501
4VT511 - VT513
4VT521 - VT523
4VT531 - VT533
4VT541 - VT546
4VT551 - VT552
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GroupVariable Number
4VT556 - VT585
3VV001
3VW701 - VW721
3VW851
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of the inspection described in this service bulletin will enable detection and repair of
cracks if they should occur, in the areas under splice plates at the STA 1582 aft pressure bulkhead
web to pressure chord joint. If a crack is present in the aft pressure bulkhead web and not found and
repaired, crack growth can result in possible rapid decompression and loss of structural integrity.
The aft pressure bulkhead web is attached to the pressure chords with a double row of fasteners and
the pressure chord segments are spliced using pressure chord splice plates. At these splice plate
locations, the aft pressure bulkhead web is hidden and cannot be inspected in accordance with existing
767 MPD Section 9 or SB 767-53A0087 and do not provide sufficient crack detection probability of the
aft pressure bulkhead web under splice plates.
Boeing Service Related Problem 767-SRP-53-0470 is related to this service bulletin.
Boeing Service Bulletins 767-53A0087 and 767-53A0139 are related to this service bulletin.
Boeing 767 MPD SSI 53-80-I01A is related to this service bulletin.
D. Description
Get access to the forward and aft sides of the aft pressure bulkhead at STA 1582. Locate the splice
plates that splice pressure chords on the circumference of the forward side of the aft pressure bulkhead.
Remove the aft row of fasteners from each splice plate and do an open hole HFEC inspection for any
crack in the aft pressure bulkhead web. If any crack is found, contact The Boeing Company for repair
instructions and do the repair. If no crack is found, install new fasteners, close access to the area and
repeat the inspection at the time specified in Paragraph 1.E., Compliance.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1-2:
Affected Maintenance Zones
ZoneModel
165, 166, 251, 252, 253, 254, 311, 312767-200, 767-300
Group 3-4:
Affected Maintenance Zones
ZoneModel
165, 166, 251, 252, 253, 254, 311, 312767-200, 767-300, 767-300F,
767-400ER
E. Compliance
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.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-05-16 is related to this service
bulletin. The effective date of AD 2004-05-16 is April 13, 2004.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-09-08 is related to this service
bulletin. The effective date of AD 2012-09-08 is June 18, 2012.
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.
This service bulletin is related to 767 MPD SSI 53-80-I01A of 767 MPD 622T001-9, which is mandated
by AD 2014-14-04. All other MPD inspections outside of the affected area are not affected and must
continue.
Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX
A and APPENDIX B.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
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Group 2, Configuration 1; Group 3-4:
Table 1: Open Hole High Frequency Eddy Current (HFEC) Inspection at STA 1582 Aft Pressure Bulkhead
Web Under the Pressure Splice Plates
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the original
issue date of
this service bul-
letin.
Before 50,000
total flight cy-
cles.
Do PART 2: FASTENER
REMOVAL AND OPEN
HOLE HFEC INSPEC-
TION of the aft pressure
bulkhead web for any
crack.
All airplanes.
(a)
-Before further flight.Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 1: ANY
CRACK FOUND IN THE
AFT PRESSURE BULK-
HEAD WEB.
12,000 flight cy-
cles.
--Repeat PART 2: FASTEN-
ER REMOVAL AND
OPEN HOLE HFEC IN-
SPECTION of the aft
pressure bulkhead web
for any crack.
CONDITION 2: NO
CRACK FOUND IN THE
AFT PRESSURE BULK-
HEAD WEB.
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs
approved by Boeing ODA via FAA 8100-9 form cover the affected inspection areas. Damage tolerance
inspection instructions specified in approval for existing repairs must continue. Inspection outside of the
repaired area must continue in accordance with this service bulletin.
Group 1; Group 2, Configuration 2:
Table 2: Open Hole High Frequency Eddy Current (HFEC) Inspection at STA 1582 Aft Pressure Bulkhead
Web Under the Pressure Splice Plates
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the original
issue date of
this service bul-
letin.
Within 37,500
flight cycles af-
ter replacement
of the aft pres-
sure bulkhead.
Do PART 2: FASTENER
REMOVAL AND OPEN
HOLE HFEC INSPEC-
TION of the aft pressure
bulkhead web for any
crack.
All airplanes.
(a)
-Before further flight.Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 1: ANY
CRACK FOUND IN THE
AFT PRESSURE BULK-
HEAD WEB.
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Group 1; Group 2, Configuration 2:
Table 2: Open Hole High Frequency Eddy Current (HFEC) Inspection at STA 1582 Aft Pressure Bulkhead
Web Under the Pressure Splice Plates
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
12,000 flight cy-
cles.
--Repeat PART 2: FASTEN-
ER REMOVAL AND
OPEN HOLE HFEC IN-
SPECTION of the aft
pressure bulkhead web
for any crack.
CONDITION 2: NO
CRACK FOUND IN THE
AFT PRESSURE BULK-
HEAD WEB.
(a)
(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs
approved by Boeing ODA via FAA 8100-9 form cover the affected inspection areas. Damage tolerance
inspection instructions specified in approval for existing repairs must continue. Inspection outside of the
repaired area must continue 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.
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.
The Manager of the FAA Seattle Aircraft Certification Office (SACO) approves the accomplishment of
inspections defined in this Service Bulletin (SB) along with the corresponding compliance times specified
in Paragraph 1.E., Compliance of this SB, Original Issue, as an Alternative Method Of Compliance
(AMOC) to the inspections defined in D622T001-DTR Structural Significant Item (SSI) 53-80-I01A and
Section 9 of the Maintenance Planning Document (MPD) D622T001-9, required by paragraphs (i) and
(k) of Airworthiness Directive (AD) 2014-14-04. This AMOC only applies to the areas inspected in
accordance with this SB. All other inspections outside of this SB inspection region are not affected and
must continue. All provisions of AD 2014-14-04 that are not specifically referenced in this paragraph
remain fully applicable and must be complied with accordingly.
In Addition, the Manager of the FAA SACO approves the accomplishment of inspections defined in
this SB along with the corresponding compliance times specified in Paragraph 1.E., Compliance of this
SB, Original Issue, as an AMOC to the inspections defined in SB 767-53A0087 required by paragraphs
(a) and (b) of AD 2004-05-16. This AMOC only applies to the areas inspected in accordance with this
SB. All other inspections outside of this SB inspection region are not affected and must continue. All
provisions of AD 2004-05-16 that are not specifically referenced in this paragraph remain fully applicable
and must be complied with accordingly.
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In addition, the Manager of the FAA SACO approves the accomplishment of inspections, after
Replacement of an Aft Pressure Bulkhead, defined in this SB along with the corresponding compliance
times specified in Paragraph 1.E., Compliance of this SB, Original Issue, as an AMOC to the inspections
defined in SB 767-53A0139 required by paragraph (h) of AD 2012-09-08. This AMOC only applies to
the areas inspected in accordance with this service bulletin. All other inspections outside of this service
bulletin inspection region are not affected and must continue. All provisions of AD 2012-09-08 that are
not specifically referenced in this paragraph remain fully applicable and must be complied with
accordingly.
G. Manpower
The tables below show estimates of the task hours necessary to do the inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimates do not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools.
Group 2, Configuration 1; Group 3:
Passenger Airplanes Only
Elapsed HoursTask HoursNumber of PersonsTask
5.0020.004Open Access
2.354.702FIGURE 1
0.250.502FIGURE 3
5.0020.004Close Access
12.6045.20TOTAL FOR EACH AIRPLANE
Group 2, Configuration 1; Group 3:
Freighters and Converted Freighters Only
Elapsed HoursTask HoursNumber of PersonsTask
3.006.002Open Access
2.354.702FIGURE 1
0.250.502FIGURE 3
3.006.002Close Access
8.6017.20TOTAL FOR EACH AIRPLANE
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Group 1; Group 2, Configuration 2; Group 4:
Passenger Airplanes Only
Elapsed HoursTask HoursNumber of PersonsTask
5.0020.004Open Access
3.006.002FIGURE 2
0.350.702FIGURE 4
5.0020.004Close Access
13.3546.70TOTAL FOR EACH AIRPLANE
Group 1; Group 2, Configuration 2; Group 4:
Freighters and Converted Freighters Only
Elapsed HoursTask HoursNumber of PersonsTask
3.006.002Open Access
3.006.002FIGURE 2
0.350.702FIGURE 4
3.006.002Close Access
9.3518.70TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 767-53A0087, 767-53A0139
b. Boeing Service Letter 767-SL-51-036
c. Boeing Service Related Problem (SRP) 767-SRP-53-0470
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2004-05-16, 2012-09-08,
2014-14-04
e. Service Bulletin Index D624T001
f. Standard Overhaul Practices Manual (SOPM) 20-50-01
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g. 767 Aircraft Maintenance Manual (AMM) 25-31-04, 25-52-01, 25-52-03, 25-55-01, 25-59-01,
25-59-05, 27-41-00, 38-11-01, 38-32-11
h. 767 Maintenance Planning Data (MPD) 622T001-9, Section 9, SSI 53-80-I01A
i. 767 Non-Destructive Testing (NDT) Manual Part 6, 51-00-04, Part 6, 51-00-11
j. 767-200 Structural Repair Manual (SRM) 51-40-02, 51-40-03, 51-40-05
k. 767-200SF Structural Repair Manual (SRM) 51-40-02, 51-40-03, 51-40-05
l. 767-300 Structural Repair Manual (SRM) 51-40-02, 51-40-03, 51-40-05
m. 767-300BCF Structural Repair Manual (SRM) 51-40-02, 51-40-03, 51-40-05
n. 767-300F Structural Repair Manual (SRM) 51-40-02, 51-40-03, 51-40-05
o. 767-400 Structural Repair Manual (SRM) 51-40-02, 51-40-03, 51-40-05
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Splice Plate - Press Bulkhead STA 1582148T2620
Bulkhead End Item Pressure Dome, Station 1582.0148T2610
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
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.
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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 inspection and/or repair procedures given in this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
Group 2, Configuration 1; Group 3:
NotesNameQTYPart Number /
Specification
-Rivet18BACR15FT6D8C
Group 1; Group 2, Configuration 2; Group 4:
NotesNameQTYPart Number /
Specification
-Rivet24BACR15FT6D8C
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.
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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
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
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).
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
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. Boeing Service Letter 767-SL-51-036, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
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8. Refer to Appendices A and B for logic diagrams. Logic diagrams are provided as an
aid only. Information contained in Paragraph 1.E., Compliance is the primary source
for compliance times. Information in Paragraph 3.B., Work Instructions is the primary
source for tasks required for compliance.
9. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
10. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
11. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
12. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
13. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
14. Some steps in the Work Instructions are identified as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
identified as RC must be done to comply with the AD. Alternative procedures for
steps not identified with RC can be used if the RC steps can still be done as specified,
and the airplane can be put back in a serviceable condition. An Alternative Method
of Compliance (AMOC) is not necessary for deviations to steps that are not identified
as RC.
B. WORK INSTRUCTIONS
1. Do PART 1: OPEN ACCESS.
2. RC - Do PART 2: FASTENER REMOVAL AND OPEN HOLE HFEC INSPECTION.
a. CONDITION 1: ANY CRACK FOUND IN THE AFT PRESSURE BULKHEAD WEB.
(1) RC - Contact The Boeing Company for repair instructions and do the repair.
b. CONDITION 2: NO CRACK FOUND IN THE AFT PRESSURE BULKHEAD WEB.
(1) RC - Repeat PART 2: FASTENER REMOVAL AND OPEN HOLE HFEC INSPECTION.
3. Do PART 3: FASTENER INSTALLATION.
4. Do PART 4: CLOSE ACCESS.
5. Put the airplane back to a serviceable condition.
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PART 1: OPEN ACCESS
1. For passenger airplanes only:
a. Remove and keep the aft galley. Refer to 767 AMM 25-31-04 as an accepted procedure.
2. For freighter airplanes (including Boeing Converted Freighters) only:
a. Remove and keep the cargo lining panels from the aft pressure bulkhead in the main deck
cargo compartment. Refer to 767 AMM 25-59-01 as an accepted procedure.
3. Remove and keep insulation from around splice plates that splice pressure chords on the aft
pressure bulkhead in the main deck cargo compartment. Refer to 767 AMM 25-59-05 as an
accepted procedure.
4. Remove and keep the end wall in the bulk cargo compartment. Refer to 767 AMM 25-52-01 as an
accepted procedure.
5. For passenger airplanes only:
a. Remove and keep the right side potable water tank. If installed, remove and keep the left side
potable water tank. Refer to 767 AMM 38-11-01 as an accepted procedure.
b. If necessary for access, remove and keep the waste tank. On some affected airplanes, the
waste tanks are installed forward of the affected area. On these airplanes, waste tank removal
is not necessary for access to the aft pressure bulkhead. Refer to 767 AMM 38-32-11 as an
accepted procedure.
6. Remove and keep insulation from around splice plates that splice pressure chords on the aft
pressure bulkhead in the bulk cargo compartment. Refer to 767 AMM 25-52-03 as an accepted
procedure.
WARNING: MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF THE HORIZONTAL
STABILIZER AND ELEVATOR SURFACES BEFORE MOVING THE STABILIZER.
INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT COULD OCCUR.
7. Position the horizontal stabilizer to neutral and deactivate controls. Refer to 767 AMM 27-41-00
as an accepted procedure.
WARNING: DO NOT STAND ON ACCESS DOOR 312AR. THE WEIGHT OF PERSONNEL COULD
CAUSE THE SPRING LOADED LATCH TO RELEASE, AND PERSONNEL MAY BE
INJURED BY FALLING THROUGH THE OPENING.
8. Open access door 312AR for access to the aft side of the aft pressure bulkhead. Use a suitable
platform or cover over the access door while working inside the tail section.
PART 2: FASTENER REMOVAL AND OPEN HOLE HFEC INSPECTION
CAUTION: TO PREVENT ANY MOVEMENT OF THE PRESSURE DOME, PERFORM PART 2 ON
ONE SPLICE PLATE AT A TIME.
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IF DRILLING OF FASTENERS IS REQUIRED, HOLD STEEL SHEETS TO THOSE
FASTENERS ON THE AFT SIDE OF THE AFT PRESSURE BULKHEAD.
1. Group 2, Configuration 1; Group 3:
Remove the aft row of fasteners from splice plates that splice pressure chords and do open hole
HFEC inspections for any crack in the aft pressure bulkhead web in accordance with FIGURE 1.
2. Group 1; Group 2, Configuration 2; Group 4:
Remove the aft row of fasteners from splice plates that splice pressure chords and do open hole
HFEC inspections for any crack in the aft pressure bulkhead web in accordance with FIGURE 2.
PART 3: FASTENER INSTALLATION
1. Group 2, Configuration 1; Group 3:
Install the aft row of fasteners on splice plates that splice pressure chords in accordance with
FIGURE 3.
2. Group 1; Group 2, Configuration 2; Group 4:
Install the aft row of fasteners on splice plates that splice pressure chords in accordance with
FIGURE 4.
PART 4: CLOSE ACCESS
WARNING: DO NOT STAND ON ACCESS DOOR 312AR. THE WEIGHT OF PERSONNEL COULD
CAUSE THE SPRING LOADED LATCH TO RELEASE, AND PERSONNEL MAY BE
INJURED BY FALLING THROUGH THE OPENING.
1. Remove any platforms or covers that were used to cover access door 312AR and close the access
door.
WARNING: MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF THE HORIZONTAL
STABILIZER AND ELEVATOR SURFACES BEFORE MOVING THE STABILIZER.
INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT COULD OCCUR.
2. Reactivate controls for the horizontal stabilizer. Refer to 767 AMM 27-41-00 as an accepted
procedure.
3. Install insulation to splice plates that splice pressure chords on the aft pressure bulkhead in the
bulk cargo compartment. Refer to 767 AMM 25-52-03 as an accepted procedure.
4. For passenger airplanes only:
a. If removed, install the waste tank. Refer to 767 AMM 38-32-11 as an accepted procedure.
b. Install the right side potable water tank. If removed, install the left side potable water tank.
Refer to 767 AMM 38-11-01 as an accepted procedure.
5. Install the end wall in the bulk cargo compartment. Refer to 767 AMM 25-55-01 as an accepted
procedure.
6. Install insulation to splice plates that splice pressure chords on the aft pressure bulkhead in the
main deck compartment. Refer to 767 AMM 25-59-05 as an accepted procedure.
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### Page 31

7. For passenger airplanes only:
a. Install the aft galley. Refer to 767 AMM 25-31-04 as an accepted procedure.
8. For freighter airplanes (including Boeing Converted Freighters) only:
a. Install the cargo lining panels to the aft pressure bulkhead in the main deck cargo compartment.
Refer to 767 AMM 25-59-01 as an accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 20, 2015
767-53A0266
31 of 41
BOEING SERVICE BULLETIN 767-53A0266
ALERTALERT

### Page 32 (OCR)

BOEING SERVICE BULLETIN 767-53A0266
ALERT  ALERT
This Figure applies only to: Group 2, Configuration 1; Group 3.
BULKHEAD WEB
6 LOCATIONS
STA
1582
S-12R
SKIN
INBD
SPLICE PLATE
(TYPICAL)
S-39L TO S-39R
SOME AFFECTED AIRPLANE CONFIGURATIONS HAVE
SHORT STIFFENERS AT THE AFT PRESSURE  BULKHEAD TO PRESSURE CHORD JOINT.  2385797
SHORT STIFFENERS ARE NOT SHOWN FOR CLARITY.
FIGURE 1: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -
FASTENER REMOVAL AND WEB INSPECTION
(SHEET 1 OF 2)
Original Issue: April 20, 2015
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0266
Work - See page 1 for details.  32 of 41

### Page 33

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationNameTaskStep
Six fasteners on aft
row of each of three
splice plates. (a) (b)
18-FastenerRemove1
Do a HFEC inspec-
tion of open holes
for any crack in ac-
cordance with 767
NDT Manual Part 6,
51-00-04 or 767
NDT Manual Part 6,
51-00-11. (b)
3-Aft Pressure Bulkhead
Web
Inspect2
(a) Refer to 767-200 SRM 51-40-02, 767-200SF SRM 51-40-02, 767-300 SRM 51-40-02, 767-300F SRM
51-40-02, 767-300BCF SRM 51-40-02 or 767-400 SRM 51-40-02 as an accepted procedure.
(b) 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 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 in accordance with this service bulletin.
FIGURE 1: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -
FASTENER REMOVAL AND WEB INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 20, 2015
767-53A0266
33 of 41
BOEING SERVICE BULLETIN 767-53A0266
ALERTALERT

### Page 34 (OCR)

BOEING SERVICE BULLETIN 767-53A0266
ALERT  ALERT
This Figure applies only to: Group 1; Group 2, Configuration 2; Group 4.
BULKHEAD WEB
1)2
6 LOCATIONS
INBD  STA
1582
S-11L
TO
S-12L
S-11R
SKIN  TO
S-12R
SPLICE PLATE
(TYPICAL)
S-23R
NOTE:
SOME AFFECTED AIRPLANE CONFIGURATIONS HAVE
SHORT STIFFENERS AT THE AFT PRESSURE  2385802
BULKHEAD TO PRESSURE CHORD JOINT.
SHORT STIFFENERS ARE NOT SHOWN FOR CLARITY.  S-24L
FIGURE 2: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -
FASTENER REMOVAL AND WEB INSPECTION
(SHEET 1 OF 2)
Original Issue: April 20, 2015
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0266
Work - See page 1 for details.  34 of 41

### Page 35

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationNameTaskStep
Six fasteners on aft
row of each of four
splice plates. (a) (b)
24-FastenerRemove1
Do a HFEC inspec-
tion of open holes
for any crack in ac-
cordance with 767
NDT Manual Part 6,
51-00-04 or 767
NDT Manual Part 6,
51-00-11. (b)
4-Aft Pressure Bulkhead
Web
Inspect2
(a) Refer to 767-200 SRM 51-40-02, 767-200SF SRM 51-40-02, 767-300 SRM 51-40-02, 767-300F SRM
51-40-02, 767-300BCF SRM 51-40-02 or 767-400 SRM 51-40-02 as an accepted procedure.
(b) 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 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 in accordance with this service bulletin.
FIGURE 2: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -
FASTENER REMOVAL AND WEB INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 20, 2015
767-53A0266
35 of 41
BOEING SERVICE BULLETIN 767-53A0266
ALERTALERT

### Page 36 (OCR)

BOEING SERVICE BULLETIN 767-53A0266
ALERT  ALERT
This Figure applies only to: Group 2, Configuration 1; Group 3.
BULKHEAD WEB
STA
1582
6 LOCATIONS
00
INBD
SKIN
S-11R
SPLICE PLATE  TO
(TYPICAL)  S-12R
S-11L
TO
S-12L
NOTE:
SOME AFFECTED AIRPLANE CONFIGURATIONS HAVE
SHORT STIFFENERS AT THE AFT PRESSURE  BULKHEAD TO PRESSURE CHORD JOINT.  2385803
SHORT STIFFENERS ARE NOT SHOWN FOR CLARITY.  S-39L TO S-39R
FIGURE 3: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER
INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 20, 2015
Export Controlled ECCN: 9E991 - BOEING  767-53A0266
PROPRIETARY - Copyright © Unpublished  Work - See page 1 for details.  36 of 41

### Page 37

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationNameTaskStep
Six rivets on aft row
of each of three
splice plates. (a) (b)
18BACR15FT6D8CRivetInstall (New)1
(a) Refer to 767-200 SRM 51-40-02, 767-200SF SRM 51-40-02, 767-300 SRM 51-40-02, 767-300F SRM
51-40-02, 767-300BCF SRM 51-40-02 or 767-400 SRM 51-40-02 as an accepted procedure. Refer to
767-200 SRM 51-40-05, 767-200SF SRM 51-40-05, 767-300 SRM 51-40-05, 767-300F SRM 51-40-05,
767-300BCF SRM 51-40-05 or 767-400 SRM 51-40-05 for hole quality specifications.
(b) Alternative fastener installation in accordance with 767-200 SRM 51-40-03, 767-200SF SRM 51-40-03,
767-300 SRM 51-40-03, 767-300F SRM 51-40-03, 767-300BCF SRM 51-40-03 or 767-400 SRM 51-40-
03 is allowed. Also, installation of BACB30VT6K*X and BACC30BL6 in a transition fit hole is acceptable.
FIGURE 3: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER
INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 20, 2015
767-53A0266
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BOEING SERVICE BULLETIN 767-53A0266
ALERTALERT

### Page 38 (OCR)

BOEING SERVICE BULLETIN 767-53A0266
ALERT  ALERT
This Figure applies only to: Group 1; Group 2, Configuration 2; Group 4.
BULKHEAD WEB
1) 6 LOCATIONS  STA
1582
B
S-11L
TO
S-12L
SKIN
INBD
SPLICE PLATE
(TYPICAL)
S-11R
_ TO
S-12R
FWD
NOTE:
SOME AFFECTED AIRPLANE CONFIGURATIONS HAVE
SHORT STIFFENERS AT THE AFT PRESSURE
BULKHEAD TO PRESSURE CHORD JOINT.  S-24L
SHORT STIFFENERS ARE NOT SHOWN FOR CLARITY.
FIGURE 4: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER
INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 20, 2015
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  38 of 41

### Page 39

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationNameTaskStep
Six rivets on aft row
of each of four splice
plates. (a) (b)
24BACR15FT6D8CRivetInstall (New)1
(a) Refer to 767-200 SRM 51-40-02, 767-200SF SRM 51-40-02, 767-300 SRM 51-40-02, 767-300F SRM
51-40-02, 767-300BCF SRM 51-40-02 or 767-400 SRM 51-40-02 as an accepted procedure. Refer to
767-200 SRM 51-40-05, 767-200SF SRM 51-40-05, 767-300 SRM 51-40-05, 767-300F SRM 51-40-05,
767-300BCF SRM 51-40-05 or 767-400 SRM 51-40-05 for hole quality specifications.
(b) Alternative fastener installation in accordance with 767-200 SRM 51-40-03, 767-200SF SRM 51-40-03,
767-300 SRM 51-40-03, 767-300F SRM 51-40-03, 767-300BCF SRM 51-40-03 or 767-400 SRM 51-40-
03 is allowed. Also, installation of BACB30VT6K*X and BACC30BL6 in a transition fit hole is acceptable.
FIGURE 4: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER
INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 20, 2015
767-53A0266
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BOEING SERVICE BULLETIN 767-53A0266
ALERTALERT

### Page 40

This Appendix applies only to: Group 2, Configuration 1; Group 3-4.
Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
FASTENER REMOVAL AND OPEN HOLE HFEC INSPECTION.PART 2
ANY CRACK FOUND IN THE AFT PRESSURE BULKHEAD WEB.CONDITION 1
NO CRACK FOUND IN THE AFT PRESSURE BULKHEAD WEB.CONDITION 2
APPENDIX A:  LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: AFT PRESSURE
BULKHEAD WEB INSPECTIONS AT PRESSURE CHORD JOINT.
(SHEET 1 OF 1)
Export Controlled ECCN: 9E991 - BOEING
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Original Issue: April 20, 2015
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BOEING SERVICE BULLETIN 767-53A0266
ALERTALERT

### Page 41 (OCR)

BOEING SERVICE BULLETIN 767-53A0266
ALERT  ALERT
This Appendix applies only to: Group 1; Group 2, Configuration 2.
Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
Title  Description
PART 2  FASTENER REMOVAL AND OPEN HOLE HFEC INSPECTION.
CONDITION 1  ANY CRACK FOUND IN THE AFT PRESSURE BULKHEAD WEB.
CONDITION 2  NO CRACK FOUND IN THE AFT PRESSURE BULKHEAD WEB.
WHICHEVER OCCURS LATER
WITHIN 37,500 FLIGHT  WITHIN 3,000 FLIGHT
CYCLES AFTER  CYCLES AFTER THE
REPLACEMENT OF THE  ORIGINAL ISSUE DATE OF
AFT PRESSURE BULKHEAD  THIS SERVICE BULLETIN
DO PART 2
CONDITION 1  CONDITION 2
NOT TO EXCEED 12,000
BEFORE FURTHER FLIGHT  FLIGHT CYCLES
CONTACT THE BOEING
COMPANY FOR REPAIR  REPEAT PART 2
INSTRUCTIONS AND DO THE
REPAIR
2406028
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 2: AFT PRESSURE
BULKHEAD WEB INSPECTIONS AT PRESSURE CHORD JOINT.
(SHEET 1 OF 1)
Original Issue: April 20, 2015
Export Controlled ECCN: 9E991 - BOEING  767-53A0266
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  41 of 41

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