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.

ECCN: 9E991

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Unpublished Work.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.

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BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT

BLANK PAGE
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

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ALERT ALERT
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

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BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
Commercial 

Airplanes 767

Service Bulletin

ALERT

Summary 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.

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.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

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Planning Data Affected Reference

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected No Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required No Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

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.

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ALERT ALERT
MANPOWER

Elapsed

Hours

Total Task

Hours

Airplanes

Group 1, Configuration 1 Airplanes 45.20 12.60

Group 1, Configuration 2 Airplanes 46.70 13.35

Group 2, Configuration 1 Passenger Airplanes 45.20 12.60

Group 2, Configuration 1 Converted Freighters 17.20 8.60

Group 2, Configuration 2 Passenger Airplanes 46.70 13.35

Group 2, Configuration 2 Converted Freighters 18.70 9.35

Group 3 Passenger Airplanes 45.20 12.60

Group 3 Freighters and Converted Freighters 17.20 8.60

Group 4 Passenger Airplanes 46.70 13.35

Group 4 Freighters and Converted Freighters 18.70 9.35

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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ALERT ALERT
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.

GROUP CONFIGURATION DESCRIPTION

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 -

2 - Airplanes from line number 176 to 423.

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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GROUP CONFIGURATION DESCRIPTION

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

Variable Number Group

VA001 - VA020 1

VA301 - VA315 1

VA501 - VA526 1

VA527 - VA530 2

VA701 - VA712 1

VA713 - VA719 2

VA801 - VA810 1

VB001 - VB002 1

VB051 - VB055 1

VB101 - VB125 1

VB201 - VB202 1

VB251 - VB253 1

VB281 - VB284 1

VB301 - VB302 1

VB321 - VB324 1

VB325 - VB332 2

VB371 - VB373 1

VB401 1

VB441 - VB444 3

VE001 - VE002 1

VE003 2

VE021 - VE023 1

VE041 - VE043 1

VE061 - VE068 1

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Variable Number Group

VE069 2

VE083 - VE084 1

VE085 - VE086 2

VE101 - VE103 1

VE104 2

VE116 - VE117 1

VE118 2

VE121 - VE123 1

VE124 - VE126 2

VE141 - VE142 1

VE143 - VE151 2

VE152 3

VE171 - VE172 2

VF001 - VF002 2

VF041 - VF042 2

VF051 2

VF061 - VF062 2

VF071 - VF072 2

VF091 - VF093 2

VF101 - VF102 2

VF161 2

VF162 3

VF171 - VF172 3

VF180 - VF184 3

VF251 3

VK001 - VK004 1

VK005 - VK011 2

VK012 - VK016 3

VK021 - VK022 2

VK031 - VK037 1

VK038 - VK053 2

VK054 - VK056 3

VK081 - VK099 2

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ALERT ALERT
Variable Number Group

VK100 - VK113 3

VK131 - VK133 2

VK141 - VK142 2

VK143 - VK148 3

VK161 - VK164 3

VK171 3

VK181 3

VK186 3

VL001 1

VL002 - VL006 2

VL011 1

VL701 - VL703 3

VL751 - VL755 3

VL806 - VL807 3

VL871 - VL873 3

VL891 - VL900 3

VL911 - VL914 3

VL931 - VL932 3

VL941 3

VN001 - VN019 2

VN020 - VN041 3

VN051 - VN062 2

VN063 - VN064 3

VN081 - VN092 2

VN093 - VN099 3

VN111 - VN124 2

VN125 - VN127 3

VN130 - VN132 2

VN133 - VN137 3

VN151 - VN158 2

VN163 - VN168 2

VN171 - VN173 2

VN174 3

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ALERT ALERT
Variable Number Group

VN191 - VN193 2

VN194 - VN198 3

VN211 - VN212 2

VN221 - VN224 2

VN225 3

VN231 - VN234 2

VN241 2

VN242 - VN243 3

VN251 - VN259 2

VN260 - VN276 3

VN291 2

VN292 - VN293 3

VN301 - VN306 2

VN307 - VN314 3

VN371 - VN372 2

VN376 2

VN381 2

VN382 - VN388 3

VN421 - VN427 3

VN436 3

VN471 - VN472 2

VN491 - VN496 2

VN497 - VN513 3

VN531 - VN532 2

VN536 - VN537 2

VN541 - VN542 2

VN546 - VN547 3

VN551 2

VN556 - VN557 3

VN561 - VN562 3

VN631 - VN633 2

VN634 - VN638 3

VN651 - VN652 2

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Variable Number Group

VN653 - VN658 3

VN671 - VN672 2

VN676 3

VN681 - VN683 2

VN684 - VN691 3

VN731 2

VN732 3

VN751 - VN753 2

VN791 - VN792 3

VN811 - VN813 3

VN921 - VN922 3

VN931 - VN936 3

VN951 - VN953 3

VN966 - VN972 3

VQ001 - VQ021 3

VQ071 - VQ086 3

VQ111 4

VR051 - VR060 3

VR081 3

VR084 3

VR086 3

VR087 - VR089 4

VR106 - VR109 4

VR201 - VR211 3

VR251 3

VR256 - VR260 3

VR266 - VR292 4

VR401 3

VR421 - VR423 3

VR426 3

VR441 3

VR461 3

VR471 - VR472 3

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ALERT ALERT
Variable Number Group

VS051 - VS056 3

VS061 3

VS066 - VS070 3

VS073 - VS078 3

VS091 - VS104 3

VS111 - VS113 3

VS131 - VS133 3

VS136 - VS137 3

VS176 - VS177 3

VS186 - VS187 3

VS196 - VS203 3

VS206 - VS208 3

VS211 3

VS216 - VS217 3

VS231 3

VS246 - VS248 3

VS261 - VS263 3

VS266 - VS274 3

VS291 - VS293 3

VS301 - VS303 3

VS306 - VS311 3

VS316 3

VS321 - VS324 3

VS331 - VS333 3

VS336 - VS337 3

VS366 - VS367 3

VS381 - VS382 3

VS391 - VS392 3

VS401 3

VS426 - VS428 3

VS466 - VS472 3

VS486 3

VS496 - VS497 3

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Variable Number Group

VS506 - VS507 3

VS526 3

VS546 - VS549 3

VS701 - VS710 3

VS711 - VS720 4

VS721 - VS731 3

VS732 - VS736 4

VS751 - VS759 3

VS821 - VS825 3

VS841 - VS844 3

VS861 3

VS881 - VS882 3

VS883 4

VS891 3

VS896 4

VS901 - VS912 4

VS916 4

VS921 - VS928 4

VS931 - VS933 4

VS941 4

VS951 - VS954 4

VS961 - VS969 4

VS971 - VS977 4

VS981 - VS984 4

VT001 - VT013 4

VT021 4

VT031 - VT033 4

VT501 3

VT511 - VT513 4

VT521 - VT523 4

VT531 - VT533 4

VT541 - VT546 4

VT551 - VT552 4

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Variable Number Group

VT556 - VT585 4

VV001 3

VW701 - VW721 3

VW851 3

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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ALERT ALERT
Group 1-2:

Affected Maintenance Zones

Model Zone

767-200, 767-300 165, 166, 251, 252, 253, 254, 311, 312

Group 3-4:

Affected Maintenance Zones

Model Zone

767-200, 767-300, 767-300F, 165, 166, 251, 252, 253, 254, 311, 312

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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ALERT ALERT
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)

Condition Action

Within 3,000 -

flight cycles after the original

issue date of

this service bulletin.

Before 50,000

total flight cycles.

Do PART 2: FASTENER

REMOVAL AND OPEN

HOLE HFEC INSPECTION of the aft pressure

bulkhead web for any

crack.

All airplanes.

(a)

Contact The Boeing Before further flight. -

Company for repair instructions and do the repair.

CONDITION 1: ANY

CRACK FOUND IN THE

AFT PRESSURE BULKHEAD WEB.

12,000 flight cycles.Repeat PART 2: FASTEN- - -

ER REMOVAL AND

OPEN HOLE HFEC INSPECTION of the aft

pressure bulkhead web

for any crack.

CONDITION 2: NO

CRACK FOUND IN THE

AFT PRESSURE BULKHEAD 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)

Condition Action

Within 3,000 -

flight cycles after the original

issue date of

this service bulletin.

Within 37,500

flight cycles after replacement

of the aft pressure bulkhead.

Do PART 2: FASTENER

REMOVAL AND OPEN

HOLE HFEC INSPECTION of the aft pressure

bulkhead web for any

crack.

All airplanes.

(a)

Contact The Boeing Before further flight. -

Company for repair instructions and do the repair.

CONDITION 1: ANY

CRACK FOUND IN THE

AFT PRESSURE BULKHEAD WEB.

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ALERT ALERT
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)

Condition Action

12,000 flight cycles.Repeat PART 2: FASTEN- - -

ER REMOVAL AND

OPEN HOLE HFEC INSPECTION of the aft

pressure bulkhead web

for any crack.

CONDITION 2: NO

CRACK FOUND IN THE

AFT PRESSURE BULKHEAD 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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ALERT ALERT
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

Task Number of Persons Task Hours Elapsed Hours

Open Access 4 20.00 5.00

FIGURE 1 2 4.70 2.35

FIGURE 3 2 0.50 0.25

Close Access 4 20.00 5.00

TOTAL FOR EACH AIRPLANE 45.20 12.60

Group 2, Configuration 1; Group 3:

Freighters and Converted Freighters Only

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.00 3.00

FIGURE 1 2 4.70 2.35

FIGURE 3 2 0.50 0.25

Close Access 2 6.00 3.00

TOTAL FOR EACH AIRPLANE 17.20 8.60

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ALERT ALERT
Group 1; Group 2, Configuration 2; Group 4:

Passenger Airplanes Only

Task Number of Persons Task Hours Elapsed Hours

Open Access 4 20.00 5.00

FIGURE 2 2 6.00 3.00

FIGURE 4 2 0.70 0.35

Close Access 4 20.00 5.00

TOTAL FOR EACH AIRPLANE 46.70 13.35

Group 1; Group 2, Configuration 2; Group 4:

Freighters and Converted Freighters Only

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.00 3.00

FIGURE 2 2 6.00 3.00

FIGURE 4 2 0.70 0.35

Close Access 2 6.00 3.00

TOTAL FOR EACH AIRPLANE 18.70 9.35

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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ALERT ALERT
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:

Drawing Number Title

148T2620 Splice Plate - Press Bulkhead STA 1582

148T2610 Bulkhead End Item Pressure Dome, Station 1582.0

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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ALERT ALERT
M. Software Accomplishment Summary

Not affected.

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ALERT ALERT
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:

Part Number / QTY Name Notes

Specification

BACR15FT6D8C 18 Rivet -

Group 1; Group 2, Configuration 2; Group 4:

Part Number / QTY Name Notes

Specification

BACR15FT6D8C 24 Rivet -

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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ALERT ALERT
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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BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
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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ALERT ALERT
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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ALERT ALERT
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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BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
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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ALERT ALERT
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.

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BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
This Figure applies only to: Group 2, Configuration 1; Group 3.

FIGURE 1: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -

FASTENER REMOVAL AND WEB INSPECTION

(SHEET 1 OF 2)

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ALERT ALERT
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.

Step Task Name Identification Qty More Data

Six fasteners on aft

row of each of three

splice plates. (a) (b)

1 Remove Fastener - 18

Do a HFEC inspection of open holes

for any crack in accordance with 767

NDT Manual Part 6,

51-00-04 or 767

NDT Manual Part 6,

51-00-11. (b)

Aft Pressure Bulkhead - 3

Web

2 Inspect

(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)

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BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
This Figure applies only to: Group 1; Group 2, Configuration 2; Group 4.

FIGURE 2: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -

FASTENER REMOVAL AND WEB INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
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.

Step Task Name Identification Qty More Data

Six fasteners on aft

row of each of four

splice plates. (a) (b)

1 Remove Fastener - 24

Do a HFEC inspection of open holes

for any crack in accordance with 767

NDT Manual Part 6,

51-00-04 or 767

NDT Manual Part 6,

51-00-11. (b)

Aft Pressure Bulkhead - 4

Web

2 Inspect

(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)

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Original Issue: April 20, 2015

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BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
This Figure applies only to: Group 2, Configuration 1; Group 3.

FIGURE 3: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER

INSTALLATION

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: April 20, 2015

767-53A0266

36 of 41

BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
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.

Step Task Name Identification Qty More Data

Six rivets on aft row

of each of three

splice plates. (a) (b)

1 Install (New) Rivet BACR15FT6D8C 18

(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

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Work - See page 1 for details.

Original Issue: April 20, 2015

767-53A0266

37 of 41

BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
This Figure applies only to: Group 1; Group 2, Configuration 2; Group 4.

FIGURE 4: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER

INSTALLATION

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 20, 2015

767-53A0266

38 of 41

BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
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.

Step Task Name Identification Qty More Data

Six rivets on aft row

of each of four splice

plates. (a) (b)

1 Install (New) Rivet BACR15FT6D8C 24

(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)

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BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT
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.

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.

APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: AFT PRESSURE

BULKHEAD WEB INSPECTIONS AT PRESSURE CHORD JOINT.

(SHEET 1 OF 1)

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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.

APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 2: 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

ALERT ALERT