# Boeing Alert Service Bulletin 767-53A0267: Revision 1

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- Title as filed: SB-767-53A0267-01--BOEING
- Pages: 206
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### Page 1

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-53A0267
Original Issue: August 13, 2015
Revision 1: August 04, 2016
ATA System: 5380
SUBJECT: FUSELAGE - Aft Pressure Bulkhead - Replacement of Station 1582 Aft Pressure
Bulkhead
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Unpublished Work.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.
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2.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
S u m m a r y  ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A . E f f e c t i v i t y  ............................................... 1 1
1. Airplanes ............................................ 1 1
2 . S p a r e s  A f f e c t e d  ........................................ 1 3
B. Concurrent Requirements ...................................... 1 3
C. Reason ................................................ 1 4
D. Description .............................................. 1 4
E. Compliance .............................................. 1 5
F . A p p r o v a l  ............................................... 1 5
G. Manpower .............................................. 1 6
H. Weight and Balance Changes .................................... 1 8
I. Electrical Load Data ......................................... 1 8
J . R e f e r e n c e s  .............................................. 1 8
1. Existing Data: ......................................... 1 8
2. Data Supplied with this Service Bulletin: ........................... 1 8
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 1
K. Publications Affected ........................................ 2 2
L. Interchangeability and Intermixability of Parts ........................... 2 2
M. Software Accomplishment Summary ................................ 2 2
2. MATERIAL INFORMATION ........................................ 2 3
A. Material - Price and Availability ................................... 2 3
B. Industry Support Information .................................... 2 3
C. Parts Necessary for Each Airplane ................................. 2 3
1 . K i t s / P a r t s  ............................................ 2 3
2. Parts and Materials Supplied by the Operator ........................ 3 4
3. Parts Modified and Reidentified ................................ 3 5
4. Parts Removed and Not Replaced .............................. 3 5
D. Parts Necessary to Change Spares ................................. 3 5
E. Special Tooling - Price and Availability ............................... 3 5
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 9
A. GENERAL INFORMATION ..................................... 3 9
B. WORK INSTRUCTIONS ....................................... 4 0
FIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION ................ 5 5
FIGURE 2: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION ................ 6 0
FIGURE 3: REMOVAL OF AUXILIARY PITOT SYSTEM TUBES AND SEALS ............. 6 2
FIGURE 4: REMOVAL OF PRESSURE SEALS .............................. 6 6
FIGURE 5: APU FUEL LINE BULKHEAD FITTING REMOVAL ..................... 6 9
FIGURE 6: APU FUEL LINE BULKHEAD FITTING INSTALLATION ................... 7 2
FIGURE 7: AFT SECTION 48 (TAIL CONE) FASTENER REMOVAL .................. 7 5
FIGURE 8: STA 1809.5 CENTER BULKHEAD REMOVAL ........................ 7 8
FIGURE 9: FORWARD SECTION 48 PARTS REMOVAL ........................ 8 5
F I G U R E  1 0 : A F T  P R E S S U R E  B U L K H E A D  P R E S S U R E  R I N G  F A S T E N E R  R E M O V A L ......... 8 7
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FIGURE 11: AFT PRESSURE BULKHEAD ATTACHMENT TO THE PRESSURE RING AT STA 1582 . 89
FIGURE 12: FORWARD SECTION 48 INSTALLATION .......................... 9 1
FIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION ................. 1 1 0
FIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION ................ 1 2 2
FIGURE 15: AFT SECTION 48 (TAIL CONE) INSTALLATION ...................... 1 3 4
FIGURE 16: PRESSURE SEAL INSTALLATION ............................. 1 3 9
FIGURE 17: INSTALLATION OF AUXILIARY PITOT SYSTEM TUBES AND PRESSURE SEALS . . 142
FIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS ......... 1 4 6
FIGURE 19: REMOVE STA 1809.5 BULKHEAD STABILIZATION TOOLS ............... 1 5 6
FIGURE 20: STA 1582 FLOOR BEAM DETACHMENT .......................... 1 5 8
FIGURE 21: STA 1582 FLOOR BEAM SUPPORT ............................ 1 6 2
FIGURE 22: STA 1582 FLOOR BEAM ATTACHMENT .......................... 1 6 5
FIGURE 23: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN REMOVAL ........... 1 7 0
FIGURE 24: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION ......... 1 7 3
FIGURE 25: RIGHT SIDE HORIZONTAL STABILIZER FAIRING SKIN REMOVAL ........... 1 7 7
FIGURE 26: RIGHT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION ........ 1 8 0
FIGURE 27: PREPARATION OF THE VERTICAL FIN .......................... 1 8 3
FIGURE 28: INSTALLATION OF THE VERTICAL FIN .......................... 1 9 0
APPENDIX A: APU WIRING TEST PROCEDURE ............................. 1 9 9
APPENDIX B: ALIGNMENT PINS ...................................... 2 0 4
APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: REPLACEMENT OF THE
STA 1582 AFT PRESSURE BULKHEAD .......................... 2 0 5
APPENDIX D: PART DEMAND INTENT ................................... 2 0 6
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Commercial 
Airplanes
767
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 767-53A0267Original Issue: August 13, 2015
Revision 1: August 04, 2016
ATA System: 5380
SUBJECT: FUSELAGE - Aft Pressure Bulkhead - Replacement of Station 1582 Aft Pressure
Bulkhead
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
None.
REASON FOR REVISION
Revision 1 is sent to replace kit number 015T1812-2 with 015T1907-1, and add five airplanes to the effectivity
that were inadvertently omitted at initial release.
These sections were changed:
1. 1.A. Effectivity, added airplane Variable Numbers VN018, VN092, VN191, VN371, and VN537.
2. 1.K.1 Publications Affected - Publications, included additional publications that are affected by this
service bulletin.
3. 2.A. Material - Price and Availability, updated kit number and Re-Order Lead Time (ROLT) information.
4. 2.C.1 Kits/Parts, replaced kit 015T1812-2 with kit number 015T1907-1.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
August 13, 2015Original Issue:
August 04, 2016Revision 1:
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Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-53A0267Original Issue: August 13, 2015
Revision 1: August 04, 2016
ATA System: 5380
SUBJECT: FUSELAGE - Aft Pressure Bulkhead - Replacement of Station 1582 Aft Pressure
Bulkhead
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
This service bulletin gives instruction for the replacement of the Station (STA) 1582 aft pressure bulkhead due
to Widespread Fatigue Damage (WFD). The WFD analysis of the 767, as required by 14 CFR 26.21(b), has
resulted in the conclusion that the existing MPD Section 9, Airworthiness Limitation Item (ALI) inspection program
is not sufficient to preclude the occurrence of WFD in the aft pressure bulkhead before the Limit of Validity (LOV)
as the airplane ages. If widespread fatigue cracking at aft pressure bulkhead radial web lap splices is not found
and repaired, the cracks can rapidly link up and become large, and can result in possible rapid decompression
and loss of structural integrity.
Boeing has not received any reports of cracks in the aft pressure bulkhead web on line number 176 through
423.
The Aft Pressure Bulkhead has been determined to be structure that is susceptible to Widespread Fatigue
Damage (WFD).
Federal Aviation Administration (FAA) AD 2012-09-08 was released to mandate replacement of the initial
configuration aft pressure bulkhead which was installed on line number 1 through 175 per service bulletin
767-53A0139. Design changes were made to improve the durability of the bulkhead in production at line number
176, and again at line number 424. However, the configuration of aft pressure bulkheads installed on line number
176 through 423, have the same web gage of 0.032 inch as the initial configuration aft pressure bulkhead and
does not provide adequate strength to preclude WFD before the Limit of Validity (LOV).
Boeing Service Related Problem (SRP) 767-SRP-53-0469 is related to this service bulletin.
Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will end the inspections
at aft pressure bulkhead web for indications of "oil cans" and previous "oil can" repairs currently required by
Boeing Service Bulletin 767-53A0105 and AD 2004-14-19.
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Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will end the repeat
inspections at aft pressure bulkhead web lap splices currently required by Boeing Service Bulletin 767-53A0147
and AD 2009-06-19.
Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will also end the repeat
inspections of web at pressure chord joint currently required by Boeing Service Bulletin 767-53A0087 and AD
2004-05-16.
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 ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications 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/PartsYesKits/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
YesSpecial Tooling Required
ACTION
Remove equipment for access to the forward and aft sides of the STA 1582 aft pressure bulkhead. Remove the
vertical fin, the tail cone (with the APU installed), the left and right STA 1809.5 center bulkhead, and the horizontal
stabilizer. Disconnect and remove the forward portion of Section 48 (with the aft pressure bulkhead attached)
from Section 46 at STA 1582. Remove the aft pressure bulkhead from Section 48 and install a new aft pressure
bulkhead in accordance with this service bulletin. Attach the modified forward part of Section 48 to Section 46
at STA 1582. Reinstall the horizontal stabilizer and reassemble the STA 1809.5 bulkhead. Reinstall the tail cone
and the vertical fin. Install the equipment that was removed for access to the aft pressure bulkhead. Test disturbed
systems in accordance with this service bulletin.
EFFECTIVITY
767-200 and 767-300 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
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Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-14-19 is related to this service bulletin.
The effective date of AD 2004-14-19 is August 20, 2004.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-06-19 is related to this service bulletin.
The effective date of AD 2009-06-19 is April 28, 2009.
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.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX D of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
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Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-53A0267
Original Issue: August 13, 2015
Revision 1: August 04, 2016
ATA System: 5380
SUBJECT: FUSELAGE - Aft Pressure Bulkhead - Replacement of Station 1582 Aft Pressure
Bulkhead
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
Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is applicable to 767-200 and -300 Airplanes, line numbers 176 - 423 in 3
Groups. The Variable Numbers and Group Information for the applicable airplanes are given below.
DESCRIPTIONCONFIGURATIONGROUP
Airplane Line numbers 176-401 with Non-Dual bottle fire extinguisher-1
Airplane Line numbers 186-416 with APC Dual Bottle fire extinguisher-2
Airplane Line numbers 202-423 which have dedicated Static pressure
inputs
-3
Airplane Models:
767-200, 767-300
GroupVariable Number
1VA527 - VA530
1VA713 - VA719
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GroupVariable Number
1VB325
2VB326
1VB327 - VB332
1VE003
1VE069
1VE085 - VE086
1VE104
1VE118
1VE124 - VE126
1VE143 - VE151
1VE171 - VE172
3VF001 - VF002
3VF041 - VF042
3VF051
3VF061 - VF062
3VF071 - VF072
3VF091 - VF093
3VF101 - VF102
2VF161
2VK005 - VK011
2VK021 - VK022
2VK038 - VK053
1VK081 - VK099
1VK131 - VK133
1VK141 - VK142
2VL002 - VL006
3VN001 - VN019
3VN051 - VN062
3VN081 - VN092
3VN111 - VN124
3VN130 - VN132
3VN151 - VN158
3VN163 - VN168
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GroupVariable Number
3VN171 - VN173
3VN191 - VN193
2VN211 - VN212
2VN221 - VN224
3VN231 - VN234
2VN241
2VN251 - VN259
3VN291
2VN301 - VN306
3VN371 - VN372
3VN376
3VN381
3VN471 - VN472
3VN491 - VN496
3VN531 - VN532
3VN536 - VN537
3VN541 - VN542
3VN551
3VN631 - VN633
3VN651 - VN652
2VN671 - VN672
3VN681 - VN683
2VN731
3VN751 - VN753
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
This service bulletin gives instruction for the replacement of the Station (STA) 1582 aft pressure bulkhead
due to Widespread Fatigue Damage (WFD). The WFD analysis of the 767, as required by 14 CFR
26.21(b), has resulted in the conclusion that the existing MPD Section 9, Airworthiness Limitation Item
(ALI) inspection program is not sufficient to preclude the occurrence of WFD in the aft pressure bulkhead
before the Limit of Validity (LOV) as the airplane ages. If widespread fatigue cracking at aft pressure
bulkhead radial web lap splices is not found and repaired, the cracks can rapidly link up and become
large, and can result in possible rapid decompression and loss of structural integrity.
Boeing has not received any reports of cracks in the aft pressure bulkhead web on line number 176
through 423.
The Aft Pressure Bulkhead has been determined to be structure that is susceptible to Widespread
Fatigue Damage (WFD).
Federal Aviation Administration (FAA) AD 2012-09-08 was released to mandate replacement of the
initial configuration aft pressure bulkhead which was installed on line number 1 through 175. Design
changes were made to improve the durability of the bulkhead in production at line number 176, and
again at line number 424. However, the configuration of aft pressure bulkheads installed on line number
176 through 423, have the same web gage of 0.032 inch as the initial configuration aft pressure bulkhead
and does not provide adequate strength to preclude WFD before the Limit of Validity (LOV).
Boeing Service Related Problem (SRP) 767-SRP-53-0469 is related to this service bulletin.
Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will end the
inspections at aft pressure bulkhead web for indications of "oil cans" and previous "oil can" repairs
currently required by Boeing Service Bulletin 767-53A0105 and AD 2004-14-19.
Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will end the
repeat inspections at aft pressure bulkhead web lap splices currently required by Boeing Service Bulletin
767-53A0147 and AD 2009-06-19.
Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will also end
the repeat inspections of web at pressure chord joint currently required by Boeing Service Bulletin
767-53A0087 and AD 2004-05-16.
D. Description
Remove equipment for access to the forward and aft sides of the STA 1582 aft pressure bulkhead.
Remove the vertical fin, the tail cone (with the APU installed), the left and right STA 1809.5 center
bulkhead, and the horizontal stabilizer. Disconnect and remove the forward portion of Section 48 (with
the aft pressure bulkhead attached) from Section 46 at STA 1582. Remove the aft pressure bulkhead
from Section 48 and install a new aft pressure bulkhead in accordance with this service bulletin. Attach
the modified forward part of Section 48 to Section 46 at STA 1582. Reinstall the horizontal stabilizer
and reassemble the STA 1809.5 bulkhead. Reinstall the tail cone and the vertical fin. Install the
equipment that was removed for access to the aft pressure bulkhead. Test disturbed systems in
accordance with this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Affected Maintenance Zones
ZoneModel
165, 166, 251, 252, 253, 254, 311, 312, 313,
314, 315, 316, 321, 322, 323, 324, 325, 326,
331, 332, 333, 334, 335, 336, 337, 338, 341,
342, 343, 344, 345, 346, 347, 348
767-200, 767-300
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 2004-14-19 is related to this service
bulletin. The effective date of AD 2004-14-19 is August 20, 2004.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-06-19 is related to this service
bulletin. The effective date of AD 2009-06-19 is April 28, 2009.
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.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Table 1: Replacement of the STA 1582 Aft Pressure Bulkhead
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 36
months after the
original issue
date of this ser-
vice bulletin.
Before 60,000
total flight cycles
but no earlier
than 37,500 to-
tal flight cycles.
Do PART 2: AFT PRES-
SURE BULKHEAD RE-
PLACEMENT
All Airplanes
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.
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The Manager of the FAA Seattle Aircraft Certification Office approves the modification defined in this
service bulletin as an alternative method of compliance to the requirements of paragraph (b), (c) and
(d) of AD 2004-14-19. All provisions of AD 2004-14-19 that are not specifically referenced in the above
statement remain fully applicable and must be complied with.
In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the modification
defined in this service bulletin as an alternative method of compliance to the requirements of paragraph
(f) of AD 2009-06-19. All provisions of AD 2009-06-19 that are not specifically referenced in the above
statement remain fully applicable and must be complied with.
In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the modification
defined in this service bulletin as an alternative method of compliance to the requirements of paragraph
(a) and (b) of AD 2004-05-16. All provisions of AD 2004-05-16 that are not specifically referenced in
the above statement remain fully applicable and must be complied with.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools
AFT PRESSURE BULKHEAD REPLACEMENT
Elapsed HoursTask HoursNumber of PersonsTask
3.006.002Prepare the new
bulkhead (Paragraph
3.B., Part 1)
38.00228.006Get Access (Para-
graph 3.B., Part 2,
through Step 21)
36.00216.006Remove the vertical
fin (Paragraph 3.B.,
Part 2, Step 22)
33.50201.006Remove the horizon-
tal stabilizer (Para-
graph 3.B., Part 2,
Step 35)
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AFT PRESSURE BULKHEAD REPLACEMENT
Elapsed HoursTask HoursNumber of PersonsTask
15.0090.006Remove the forward
part of Section 48
(Paragraph 3.B., Part
2, Step 32 through
Step 34)
3.2513.004Remove the aft pres-
sure bulkhead from
the forward part of
Section 48 (Para-
graph 3.B., Part 2,
Step 35)
3.2513.004Install the new aft
pressure bulkhead in
the forward part of
Section 48 (Para-
graph 3.B., Part 2,
Step 36)
15.0090.006Install the forward
part of Section 48
(Paragraph 3.B., Part
2, Step
20.50123.006Install the horizontal
stabilizer (Paragraph
3.B., Part 2, Steps 39
through 44)
13.5081.006Install the tail cone
(Paragraph 3.B., Part
2, Steps 45 through
49)
36.00216.006Install the vertical fin
(Paragraph 3.B., Part
2, Step 50
39.50237.006Restore Access
(Paragraph 3.B., Part
2, Step 51 through
Step 69)
9.0027.003Test disturbed sys-
tems (Paragraph
3.B., Part 3)
265.501541.00TOTAL FOR EACH AIRPLANE
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H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+98084.0+62.0767-200
+106268.0+62.0767-300
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 767-25A0300, 767-53A0078, 767-53A0085, 767-53A0087,
767-53A0105, 767-53A0131, 767-53A0139, 767-53A0147
b. Boeing Service Letter 767-SL-00-014, 767-SL-51-008-B, 767-SL-51-036
c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2003-10-11, 2003-13-03,
2004-05-16, 2004-14-19, 2005-11-02, 2009-06-19, 2011-14-02, 2012-09-08
d. Service Bulletin Index D624T001
e. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-30-03, 20-41-01, 20-41-02,
20-50-01, 20-50-19
f. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19
g. 767 Aircraft Maintenance Manual (AMM) 05-51-24, 07-11-03, 12-15-01, 12-15-02, 20-10-03,
20-10-04, 20-10-09, 22-10-00, 22-21-00, 23-11-00, 23-41-00, 24-22-00, 25-21-01, 25-21-05,
25-22-01, 25-22-02, 25-22-10, 25-25-01, 25-25-04, 25-27-02, 25-31-04, 25-41-04, 25-52-03,
25-55-01, 27-21-00, 27-21-11, 27-21-13, 27-23-00, 27-28-00, 27-31-00, 27-31-01, 27-31-02,
27-32-00, 27-41-00, 27-41-10, 27-48-00, 27-58-01, 28-25-05, 29-11-00, 31-31-00, 31-51-04,
32-00-20, 33-31-00, 33-45-00, 34-11-01, 36-11-01, 38-11-01, 38-32-11, 38-32-51, 51-24-09,
53-01-01, 53-66-02, 55-10-01, 55-10-02, 55-17-51, 55-36-02
h. 767 Aircraft Recovery Document (ARD)
i. 767-200 Structural Repair Manual (SRM) 51-20-01, 51-50-02
j. 767-300 Structural Repair Manual (SRM) 51-20-01, 51-50-02
2. Data Supplied with this Service Bulletin:
a. Drawings:
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ADCNDCN/REVSheetTitleDrawing No
-J1Section 48/72 Integration100T3480
-CPSDL
--1Shim Details - Section 48/72100T3481
-C1Corrosion Inhibiting Compound Installation
- Fuselage
140T6000
-A1Mechanical Equipment Forward 48 Section
Stand
2ME148T0200PBR
-A2
-A1Mechanical Equipment Aft 48 Section Stand2ME148T0600PBR
-A2
--1Mechanical Equipment Strongback, Pres-
sure Bulkhead Transportation and Installa-
tion
2ME148T2610PBR
-A2
-A3
-A4
-A5
--1Miscellaneous Tool Torque Multiplier and
Adapter, Vertical Fin
2MIT100T3480PBR
-A2
-A3
--4
--5
--6
-A1Overhead Mechanical Equipment Vertical
Fin Assembly Sling
2OHME100T3480PBR
--1Mechanical Equip Sling and Strongback
Fwd 48 Section Pressure Bulkhead
3ME140T0140PBR
--2
--3
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ADCNDCN/REVSheetTitleDrawing No
--1Aft Pressure Bulkhead Parts Removal624T0020
-A10
--11
-A12
-A13
-A14
-A15
-A16
-A17
--2
--3
--4
--5
-A6
-A7
-B8
-A9
-B1Mechanical Equipment Vertical Fin Lift Fit-
tings
ME100T3480PBR
--1Mechanical Equipment Forward 48 Section
Handling Fitting
ME148T0200PBR
-A1Mechanical Equipment Aft 48 Section Han-
dling Fitting
ME148T0600PBR
--1Mechanical Equipment Strongback Pressure
Bulkhead Removal
ME148T2610PBR
-A2
-A3
-A5
-A1Mechanical Equipment Vert Fin Stand Floor
Mounted
ME170T0100PBR
-A2
-A1Mechanical Equipment Floor Mounted Stand
Horizontal Stabilizer
ME180T0000PBR
--1Mechanical Equipment Lift Fittings Front
and Rear Spar Horizontal Stabilizer
ME182T0000PBR
--1Misc Tool Alignment Pins Vertical Fin Body
Join
MIT100T3480PBR
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ADCNDCN/REVSheetTitleDrawing No
--1Overhead Mech Equip Pressure Dome Sling
Fwd 48 Section
OHME148T2610PBR
--2
--1Overhead Mech Equip Horizontal Stabilizer
Complete
OHME180T0100PBR
--2
--1Portable Mechanical Equipment Forward
48 Section Internal Scaffolding
PME148T0010PBR
--2
--3
--4
--5
--6
--1Protective Equipment Pressure Bulkhead
Cover
PRE148T2610PBR
--1Shipping Mech Equip Ground Transporta-
tion Aft Pressure Bulkhead
SME148T2610PBR
--2
--3
--4
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Section 48/72 Integration100T3480
Monocoque Integration - Section 46/48140T0140
Floor System Integration Section 46 - 48140T0540
Seal Application Section 48 Integration140T4800
Stanchion Installation - Sect 46146T5500
Support Instl - Galley Tie Down Fittings, Sect 46146T5604
Fastener Instl Bulkhead Splice STA 1809.5148T0006
Fastener Instl148T0007
Fastener Instl - STA 1809.5 Splice, Sect 48148T0008
Frame Instl - Pivot Bulkhead148T1150
Bulkhead End Item - Center, Horiz Stab Pivot, STA
1809.5
148T2740
Seal Instl - Pitot/Static Tubing Pressure Dome233T9112
Pressure Seal Instl - Pressure Dome STA 1582.0255T4821
Retainer Instl - Pressure Seal, Hydraulic Tubing272T4831
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TitleDrawing Number
Tubing Instl - APU Fuel Feed, Body Sections 45, 46
and 48
346T0003
Corrosion Inhibiting Compound Installation - Fuselage140T6000
Shim Details - Section 48/72100T3481
NOTE: These drawings were used to prepare this service bulletin. These drawings are not
necessary to make the specified changes, and are not supplied with this service bulletin.
These drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
28-25, 29-11, 34-11, 53-80767 Illustrated Parts Catalog
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits/parts are subject to the terms and conditions of the Boeing standard purchase order
acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NameKit Number
$86,435.00550Top Kit - STA 1582 Aft Pressure Bulkhead
Replacement
015T1907-1
$578,050.00450Aft Pressure Bulkhead691T0103-1
Operators are encouraged to complete the survey provided in APPENDIX D of this service bulletin to
help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit, one aft bulkhead assembly and the items shown in Paragraph 2.C.2., Parts
and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is
divided into Figure kits for each installation figure shown in the table below.
Kit 691T0103
QuantityPart Number
1691T0103-1
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Figure Kit
1413121161Top Kit
111111015T1907-1
Figure Kit
262422171615Top Kit
111111015T1907-1
Figure Kit
28Top Kit
1015T1907-1
ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
1413121161
Qty
(a)WASHER..2...140T0140-5
(b)CLIP..1...140T0142U1
(140T0142-1 option-
al)
(b)CLIP..1...140T0142U2
(140T0142-2 option-
al)
-FITTING ASSY..2...140T0169-7
-COVER PLATE.....1140T0345-1
-SEAL BLOCK AS-
SY
.....1140T0345-3
-FILLER22....148T0012-2
-FILLER22....148T0012-3
-SHIM11....148T0012-4
-SHIM11....148T0012-5
-FILLER11....148T0012-11
-SHIM2.....148T0012-18
-SHIM.2....148T0012-19
-SPLICE-STRAP22....148T0015-1
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ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
1413121161
Qty
-SEAL BLOCK AS-
SY
.....1148T2629-2
-BRACKET ASSY-..1...272T4825-9
-SEAL....1.40345  (678782
optional)
-FITTING ASSY..2...412T3106-406
-fitting assy..1...412T3106-408
(a)BOLT, PROTRUD-
ING HD
88....BACB30MY10K10X
(a)BOLT TITANIUM
O/S
1010....BACB30MY10K3X
(a)BOLT, PROTRUD-
ING HD
55....BACB30MY10K5X
(a)BOLT, PROTRUD-
ING HD
11....BACB30MY10K6X
(a)BOLT, PROTRUD-
ING HD
1111....BACB30MY10K7X
(a)BOLT, PROTRUD-
ING HD
1414....BACB30MY10K8X
(a)BOLT, PROTRUD-
ING HD
44....BACB30MY12K10X
(a)BOLT, PROTRUD-
ING HD
22....BACB30MY12K6X
(a)BOLT, PROTRUD-
ING HD
44....BACB30MY12K7X
(a)BOLT, PROTRUD-
ING HD
44....BACB30MY12K8X
(a)BOLT, PROTRUD-
ING HD
77....BACB30MY8K10X
(a)BOLT, PROTRUD-
ING HD
33....BACB30MY8K11X
(a)BOLT, PROTRUD-
ING HD
44....BACB30MY8K12X
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ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
1413121161
Qty
(a)BOLT, PROTRUD-
ING HD
3535....BACB30MY8K5X
(a)BOLT, PROTRUD-
ING HD
11....BACB30MY8K6X
(a)BOLT, PROTRUD-
ING HD
6565....BACB30MY8K7X
(a)BOLT, PROTRUD-
ING HD
33....BACB30MY8K8X
(a)BOLT, PROTRUD-
ING HD
11....BACB30MY8K9X
(a)BOLT, HEX HEAD.....16BACB30NM4K14
(a)BOLT, 100 DEG
HEX DR
44....BACB30NW8K13X
(a)BOLT, 100 DEG
HEX DR
22....BACB30NW8K5X
(a)BOLT, 100 DEG
HEX DR
22....BACB30NW8K7X
(a)BOLT, 100 DEG
HEX DR
44....BACB30NW8K8X
(a)BOLT, PROTRUD-
ING HD
44....BACB30NX10K11X
(a)BOLT, PROTRUD-
ING HD
44....BACB30NX10K12X
(a)BOLT, PROTRUD-
ING HD
22....BACB30NX10K8X
(a)BOLT, PROTRUD-
ING HD
22....BACB30NX10K9X
(a)BOLT, PROTRUD-
ING HD
44....BACB30NX12K12X
(a)BOLT, PROTRUD-
ING HD
..2...BACB30NX6K10X
(a)BOLT, PROTRUD-
ING HD
..20...BACB30NX6K4X
(a)BOLT, PROTRUD-
ING HD
..2...BACB30NX6K5X
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ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
1413121161
Qty
(a)BOLT, 12 PT
HEAD
..26...BACB30US5K16
(a)BOLT, 12 PT
HEAD
..58...BACB30US5K17
(a)BOLT, 12 PT
HEAD
..40...BACB30US5K18
(a)BOLT, 12 PT
HEAD
..24...BACB30US5K19
(a)BOLT, 12 PT
HEAD
..10...BACB30US5K21
(a)BOLT, 12 PT
HEAD
..6...BACB30US5K25
(a)BOLT, 12 PT
HEAD
..4...BACB30US6K31
(a)BOLT, 12 PT
HEAD
..40...BACB30US6K33
(a)BOLT, 12 PT
HEAD
..32...BACB30US6K34
(a)BOLT, 12 PT
HEAD
..8...BACB30US6K35
(a)BOLT, 12 PT
HEAD
..8...BACB30US6K36
(a)BOLT, 12 PT
HEAD
..20...BACB30US7K35
(a)BOLT, 12 PT
HEAD
..12...BACB30US7K39
(a)BOLT, 12 PT
HEAD
..16...BACB30US7K40
(a)BOLT, 12 PT
HEAD
..16...BACB30US8K42
(a)COLLAR1414....BACC30BH10
(a)COLLAR44....BACC30BH12
(a)COLLAR..24...BACC30BH6
(a)COLLAR4949....BACC30M10
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ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
1413121161
Qty
(a)COLLAR1414....BACC30M12
(a)COLLAR145145....BACC30M8
(a)NUT..156...BACN10HR5CD
(a)SELF-LOCKING
NUT
..92...BACN10HR6CD
(a)NUT..44...BACN10HR7CD
(a)NUT..16...BACN10HR8CD
(a)NUT, SELF-LOCK.....15BACN11AG3
(a)RIVET, UNIVER-
SAL HD
.....50BACR15BB5A7C
(a)RIVET, UNIVER-
SAL HD
.....5BACR15BB6A8C
(a)RIVET.....8BACR15FT6KE7C
(a)RIVET55....BACR15FV7KE7
(a)RIVET11....BACR15FV7KE8
(a)BOLT.....15BACS12HN3-7
-SHIM, LAMINAT-
ED
..2...BACS40R011B012F
-SHIM,LAMINATED22....BACS40R011B027F
-SHIM, LAMINAT-
ED
22....BACS40R012B027F
-SHIM, LAMINAT-
ED
11....BACS40R016B098F
-SHIM, LAMINAT-
ED
11....BACS40R027C030F
(a)CSK WASHER..156...BACW10BP5CD
(a)WASHER-PLAIN..154...BACW10BP5DP
(a)WASHER, PLAIN..92...BACW10BP6CD
(a)WASHER..92...BACW10BP6DP
(a)WASHER..44...BACW10BP7CD
(a)WASHER..44...BACW10BP7DP
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ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
1413121161
Qty
(a)WASHER..16...BACW10BP8CD
(a)WASHER..16...BACW10BP8DP
(a)WASHER....8.NAS1149D0316J
(a)WASHER.....30NAS1149D0332J
(a)WASHER, FLAT.....5NAS1149D0363J
(a)RIVET, BLIND...31..NAS1399D6A10
(NAS1399D6AB10
optional)
-SPACERS FOR
RIVETS
.....1NAS42DD3-44FC
-SPACERS FOR
RIVETS
.....1NAS42DD3-48FC
-SPACERS FOR
RIVETS
.....1NAS42DD3-64FC
(a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer
than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,
substitute fasteners may be supplied in kits.
(b) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify
these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts
are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this
service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service
Letter 767-SL-00-014 for more information.
ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
262422171615
Qty
(a)washer.....2148T2746-1
-filler.....2148T2746-2
-TUBE ASSY...1..233T9110-566
-TUBE ASSEMBLY...1..233T9110-665
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ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
262422171615
Qty
-PLATER RETAIN-
ER
...2..233T9113-4
-SEAL....3.270T0004-1101
-SEAL....1.270T0004-1102
-RETAINER-....1.272T4830-1
-RETAINER ASSY-....1.272T4830-2
-SEAL-...1..69B41314-6
(a)BOLT...24..BACB30LM3-3
(a)BOLT, 12 PT
HEAD
.....10BACB30LT5-12
(a)BOLT, 12 PT
HEAD
.....8BACB30LT7-12
(a)BOLT, PROTRUD-
ING HD
..12...BACB30MY8K4X
(a)BOLT, 100 DEG
HEX DR
66....BACB30NW8K8X
(a)HEX DRIVE BOLT.....44BACB30NX10K10
(a)BOLT.....54BACB30NX10K7
(a)BOLT.....8BACB30NX14K16
(a)BOLT, PROTRUD-
ING HD
..3...BACB30NX6K4X
(a)BOLT.....8BACB30NX6K5
(a)BOLT, PROTRUD-
ING HD
..5...BACB30NX6K6X
(a)HI LOK.....8BACB30NX8K5
(a)BOLT, PROTRUD-
ING HD
..22...BACB30NX8K5X
(a)BOLT, PROTRUD-
ING HD
..6...BACB30NX8K6X
(a)BOLT, HEX DRIVE.....76BACB30NX8K7
(a)BOLT, PROTRUD-
ING HD
..14...BACB30NX8K7X
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### Page 31

ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
262422171615
Qty
(a)BOLT, 12 PT
HEAD
.....4BACB30US12K37
(a)BOLT, 12 PT
HEAD
.....4BACB30US12K40
(a)BOLT, 12 PT
HEAD
.....22BACB30US7K24
(a)BOLT, 12 PT
HEAD
.....2BACB30US7K26
(a)BOLT, 12 PT
HEAD
.....4BACB30US7K27
(a)BOLT, 12 PT
HEAD
.....32BACB30US7K28
(a)BOLT, 12 PT
HEAD
.....2BACB30US8K30
(a)BOLT, 12 PT
HEAD
.....4BACB30US8K31
(a)BOLT, 100 DEG
HEAD
1010....BACB30VF3K5
(a)BOLT33....BACB30VF3K7
-CLAMP, LOOP...10..BACC10DK6
(a)COLLAR.....107BACC30BH10
(a)COLLAR,
PRELOAD
.....8BACC30BH14
(a)COLLAR.....8BACC30BH6
(a)COLLAR..42..84BACC30BH8
(a)COLLAR..8...BACC30M6
(a)COLLAR6612...BACC30M8
(a)SELF-LOCKING
NUT
.....8BACN10HR12CD
(a)NUT.....60BACN10HR7CD
(a)NUT.....4BACN10HR8CD
(a)NUT....18.BACN10JC3CD
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### Page 32

ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
262422171615
Qty
(a)SELF-LOCKING
NUT
.....10BACN10JC5CD
(a)SELF-LOCKING
NUT
.....8BACN10JC7CD
(a)RIVET, UNIVER-
SAL HD
22....BACR15FT5KE9C
(a)RIVET55....BACR15FV6KE7
(a)RIVET11....BACR15FV6KE8
(a)BOLT....24.BACS12HN3-9
-SHIM, LAMINAT-
ED
..2...BACS40R040C095F
(a)WASHER, PLAIN.....8BACW10BP12CD
(a)WASHER, PLAIN.....8BACW10BP12DP
(a)CSK WASHER.....10BACW10BP5CD
(a)WASHER-PLAIN.....12BACW10BP5DP
(a)WASHER.....68BACW10BP7CD
(a)WASHER.....68BACW10BP7DP
(a)WASHER.....4BACW10BP8DP
(a)WASHER....24.NAS1149D0316J
(a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer
than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,
substitute fasteners may be supplied in kits.
ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
28
Qty
(a)BOLT, PROTRUD-
ING HD
6BACB30NX10K10X
(a)BOLT, PROTRUD-
ING HD
6BACB30NX10K12X
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### Page 33

ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
28
Qty
(a)BOLT, PROTRUD-
ING HD
2BACB30NX10K13X
(a)BOLT, PROTRUD-
ING HD
2BACB30NX10K15X
(a)BOLT, PROTRUD-
ING HD
4BACB30NX12K11X
(a)BOLT, PROTRUD-
ING HD
10BACB30NX12K14X
(a)BOLT TIANIUM
O/S
58BACB30NX12K15X
(a)BOLT, HEX DRIVE14BACB30NX12K9X
(a)BOLT, PROTRUD-
ING HD
4BACB30NX16K11X
(a)BOLT, PROTRUD-
ING HD
8BACB30NX6K19X
(a)BOLT, PROTRUD-
ING HD
4BACB30NX6K6X
(a)BOLT, PROTRUD-
ING HD
4BACB30NX8K16X
(a)BOLT, PROTRUD-
ING HD
28BACB30NX8K5X
(a)BOLT, PROTRUD-
ING HD
6BACB30NX8K9X
(a)BOLT, 12 PT
HEAD
4BACB30US16K47
(a)BOLT, 12 PT
HEAD
4BACB30US16K48
(a)BOLT, 12 PT
HEAD
2BACB30US16K50
(a)BOLT, 12 PT
HEAD
2BACB30US16K51
(a)BOLT, 12 PT
HEAD
4BACB30US18K52
(a)COLLAR16BACC30BH10
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### Page 34

ALL
KIT 015T1907-1
Notes
Existing Part
NumberName
Figure
New Part Number
28
Qty
(a)COLLAR86BACC30BH12
(a)COLLAR12BACC30BH6
(a)COLLAR38BACC30BH8
(a)COLLAR4BACC30X16
(a)BARREL NUT12BACN11B16CS
(a)BARREL NUT4BACN11B18CS
(a)WASHER, PLAIN12BACW10BP16CD
(a)WASHER, PLAIN4BACW10BP18CD
(a)WASHER16NAS1149E1632P
(a) If grip length shown is not available at Boeing, fasteners supplied in kits may
be one grip length longer than indicated. Also, if any fasteners part numbers
listed are not available or have been superseded, substitute fasteners may be
supplied in kits.
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.
NotesNameQtyPart Number/Specifica-
tion
-Plate1A
-Plate1B
-Bolt8BACB30NM4K4
-Bolt120BACB30NX6K5
-Bolt18BACB30NX6K8
-Collar138BACC30BH6SW
-Bolt8BACB30LM3-3
-Epoxy Adhesive2 OzBMS 5-25
-Sealant2 OzBMS 5-95
-Sealant2 OzBMS 5-125 Type II
-Sealant2 OzBMS 5-142
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### Page 35

NotesNameQtyPart Number/Specifica-
tion
-Sealant2 OzBMS 3-27
-Sealant2 OzBMS 3-38
-Primer2 OzBMS 10-11
-Angle6C
-Angle2D
-Angle2E
-Plate2F
-Angle2G
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
Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service
Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of
the service bulletin by e-mail to ServiceBulletinRentalLoanTools@boeing.com. The tool(s) are subject
to the terms and conditions of the Boeing standard purchase order acknowledgement. Prices are in
United States dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (425) 965-8237
Rental Data:
Daily Price as of
the Original Issue
date of this ser-
vice bulletin (US
Dollars)
NameTool Kit Number
$550.00Forward 48 Section Internal
Scaffolding
PME148T0010PBR
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### Page 36

Rental Data:
Daily Price as of
the Original Issue
date of this ser-
vice bulletin (US
Dollars)
NameTool Kit Number
$224.00Pressure Bulkhead CoverPRE148T2610PBR
$200.00Vertical Fin Alignment PinsMIT100T3480PBR
$260.00Vertical Fin Floor StandME170T0100PBR
$420.00Pressure Dome SlingOHME148T2610PBR
$260.00Vertical Fin Lift Sling2OHME100T3480PBR
$380.00Vertical Fin Lift FittingsME100T3480PBR
$200.00Horizontal Stabilizer Lift FittingsME182T0000PBR
$380.00Horizontal Stabilizer Lift SlingOHME180T0100PBR
$260.00Forward 48 Section Sling and
Strongback
3ME140T0140PBR
$550.00Vertical Fin Torque Multiplier
and Adapter
2MIT100T3480PBR
$400.00Aft 48 Section Lift Sling and At-
tach Fittings
ME148T0600PBR
(a)Pressure Bulkhead Removal
Strongback
ME148T2610PBR
$240.00Horizontal Stabilizer Floor StandME180T0000PBR
$380.00Aft 48 Section Stand2ME148T0600PBR
$420.00Forward 48 Section Attach Fit-
tings
ME148T0200PBR
$440.00Forward 48 Section Stand2ME148T0200PBR
$400.00Pressure Bulkhead Transporta-
tion Removal Strongback
2ME148T2610PBR
$460.00Pressure Bulkhead Ground
Transportation Fixture
2SME148T2610PBR
A $150.00 handling is added to all tool rentals
(a) Rental price data for this tool was not available at the time this service
bulletin was issued.
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### Page 37

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPON-
DER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFOR-
MATION
Purchase Data:
Unit Price as of
the Original Issue
date of this Ser-
vice Bulletin (US
Dollars)
NameTool Kit Number
$192,263.00Forward 48 Section internal
Scaffolding
PME148T0010PBR
$24,471.00Pressure Bulkhead CoverPRE148T2610PBR
$12,818.00Vertical Fin Alignments PinsMIT100T3480PBR
$27,104.00Vertical Fin Floor StandME170T0100PBR
$82,322.00Pressure Dome SlingOHME148T2610PBR
$28,371.00Vertical Fin Lift Sling2OHME100T3480PBR
$60,331.00Vertical Fin Lift SlingME100T3480PBR
$12,819.00Horizontal Stabilizer Lift FittingsME182T0000PBR
$64,089.00Horizontal Stabilizer Lift SlingOHME180T0100PBR
$28,680.00Forward 48 Section Sling and
Strongback
3ME140T0140PBR
$192,263.00Vertical Fin Torque Multiplier
and Adapter
2MIT100T3480PBR
$74,129.00Aft 48 Section Lift Sling and At-
tach Fittings
ME148T0600PBR
$62,077.00Aft 48 Section Stand2ME148T0600PBR
$81,929.00Forward 48 Section Attach fit-
tings
ME148T0200PBR
$94,649.00Forward 48 Section Stand2ME148T0200PBR
$21,600.00Horizontal Stabilizer Floor StandME180T0000PBR
$72,810.00Pressure Bulkhead Transporta-
tion
2ME148T2610PBR
(a)Pressure Dome Removal
Strongback
ME148T2610PBR
$105,508.00Pressure Bulkhead Ground
Transportation Fixture
2SME148T2610PBR
(a) Purchase price data for this tool was not available at the time this service bulletin was
issued.
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### Page 38

F. Special Tooling Necessary to do this Service Bulletin
To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.
Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be
necessary. Examine operator tool supply to make sure all necessary tools are available.
NameTool Kit Number
Forward 48 Section Internal
Scaffolding
PME148T0010PBR
Pressure Bulkhead CoverPRE148T2610PBR
Vertical Fin Alignment PinsMIT100T3480PBR
Vertical Fin Floor StandME170T0100PBR
Pressure Dome SlingOHME148T2610PBR
Pressure Dome Removal
Strongback
ME148T2610PBR
Vertical Fin Lift Sling2OHME100T3480PBR
Vertical Fin Lift FittingsME100T3480PBR
Horizontal Stabilizer Lift FittingsME182T0000PBR
Horizontal Stabilizer Lift SlingOHME180T0100PBR
Forward 48 Section Sling and
Strongback
3ME140T0140PBR
Vertical Fin Torque Multiplier and
Adapter
2MIT100T3480PBR
Aft 48 Section Lift Sling and At-
tach Fittings
ME148T0600PBR
Horizontal Stabilizer Floor StandME180T0000PBR
Aft 48 Section Stand2ME148T0600PBR
Forward 48 Section Attach Fit-
tings
ME148T0200PBR
Forward 48 Section Stand2ME148T0200PBR
Pressure Bulkhead Transporta-
tion
2ME148T2610PBR
Pressure Bulkhead Ground
Transportation Fixture
2SME148T2610PBR
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### Page 39

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 767 Structural Repair Manual,
Chapter 51.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
6. 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.
7. 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.
8. 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.
9. Refer to Appendix C 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.
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### Page 40

10. 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.
11. 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.
12. 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.
13. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
14. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
16. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
17. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. An Alternative Method of
Compliance (AMOC) is required for any deviations to RC steps, including sub-steps
and identified figures. Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection program without
obtaining approval of an AMOC. This is provided that the RC steps, including
sub-steps and identified figures, can still be done as specified, and the airplane can
be put back in an airworthy condition.
B. WORK INSTRUCTIONS
1. Do PART 1: BULKHEAD PREPARATION
2. Do PART 2: AFT PRESSURE BULKHEAD REPLACEMENT
3. Do PART 3: SYSTEM TESTS
4. Put the airplane back to a serviceable condition
PART 1: BULKHEAD PREPARATION
1. Prepare the new aft pressure bulkhead assembly in accordance with FIGURE 1.
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### Page 41

2. Group 2:
Do additional preparation of the new aft pressure bulkhead assembly in accordance with FIGURE
2.
PART 2: AFT PRESSURE BULKHEAD REPLACEMENT
1. Supply airplane electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure.
2. Pressurize the center hydraulic system. Refer to 767 AMM 29-11-00 as an accepted procedure.
3. Use the STAB TRIM levers or switches to move the horizontal stabilizer to the neutral position (2
units of trim on the position indicator).
4. Remove the pressure from the center, right, and left hydraulic systems. Refer to 767 AMM 29-11-00
as an accepted procedure.
5. Set the C, R, and L STAB TRIM switches on the P10 Panel to the CUTOUT position and attach
DO-NOT-OPERATE tags.
6. On the P61 right side panel, put these switches in the OFF position and attach DO-NOT-OPERATE
tags:
S2 RIGHT TAIL HD SHUT OFF VALVE SWITCH
S4 CENTER TAIL HD SHUT OFF VALVE SWITCH
S6 LEFT TAIL HD SHUT OFF VALVE SWITCH
7. Open the following circuit breakers and attach DO-NOT-CLOSE tags:
a. On the P11 Overhead Circuit Breaker Panel:
(1) For the APU Fuel System:
11B36, APU START
11D34, FUEL DC PUMP PWR
11D35, FUEL DC PUMP CONT
11M25, FUEL PUMPS L FWD R AFT
(2) For the horizontal stabilizer ballscrew and pivot pins:
11A36, ALT STAB TRIM (if installed)
11C12, STAB TRIM SHUTOFF L
11C13, STAB TRIM SHUTOFF CENTER
11H17, FLT CONT SHUTOFF TAIL LEFT
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### Page 42

11H18, FLT CONT SHUTOFF TAIL CENTER
11H27, FLT CONT SHUTOFF TAIL RIGHT
11D29, ENG HYD PUMP L SUPPLY
11D30, ENG HYD. PUMP R SUPPLY
11L25, HYD ELEC PUMP L
11L16, HYD ELEC PUMP R
11L15, ELEC HYD PUMP C
111L18, HYD SYS C PRESS
11D31, AIR HYD PUMP
b. On the P6 Main Power Distribution Panel:
6E3, APU FUEL VALVES
8. Remove airplane electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure.
9. Support and jack the airplane indoors as follows:
a. Install nose and main landing gear down locks. Refer to 767 AMM 32-00-20 as an accepted
procedure.
b. Deflate the nose gear and pump oil into the nose gear. Simultaneously deflate both main
gears and pump oil into the main gears. When the oil flow is free of nitrogen bubbles close
the valves. Pump additional oil into both the nose and main landing gear oleos to achieve one
inch of chrome showing. Refer to 767 AMM 12-15-01 and 767 AMM 12-15-02 as accepted
procedures.
c. Partially support the airplane with nose and main landing gear/axial jacks at all five axle
jackpoints. Refer to 767 AMM 07-11-03 as an accepted procedure. Apply a 10,000 - 12,000
pound load at each axial jack location. Install wheel chocks and chains at each main landing
gear.
NOTE: Parking brake can remain set.
d. Mechanically lock all five axle jacks.
10. Disassemble and remove (or shift forward) equipment from the aft part of the passenger
compartment for access to the Aft Pressure Bulkhead joint at STA 1582. This includes:
a. Passenger seats. Refer to 767 AMM 25-25-01 as an accepted procedure.
b. Partitions. Refer to 767 AMM 25-25-04 as an accepted procedure.
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### Page 43

c. Aft Galley Complex A1, A4, or A1-A3. Refer to 767 AMM 25-31-04 as an accepted procedure.
d. Lavatories. Refer to 767 AMM 25-41-04 as an accepted procedure.
e. Sidewall Panels. Refer to 767 AMM 25-21-01 as an accepted procedure.
f. Ceiling panels. Refer to 767 AMM 25-22-01, 767 AMM 25-22-02, and/or 767 AMM 25-22-10
as accepted procedures.
g. Sidewall and Ceiling Insulation. Refer to 767 AMM 25-21-05 as an accepted procedure.
h. Doorway/Galley Floor Covering. Refer to 767 AMM 25-27-02 as an accepted procedure.
i. Floor Panels. Refer to 767 AMM 53-01-01 as an accepted procedure.
11. Disassemble and remove (or shift forward) equipment from the aft end of the bulk cargo
compartment for access to the Aft Pressure Bulkhead joint at STA 1582. This includes:
a. Bulk Cargo Compartment Aft Lining. Refer to 767 AMM 25-55-01 as an accepted procedure.
b. Bulk Cargo Compartment Sidewall Lining, for access to the pitot-static tubes on the left side
from the aft pressure bulkhead to the bulk cargo door aft frame at STA 1461. Refer to 767
AMM 25-55-01 as an accepted procedure.
c. Potable Water Tanks. Refer to 767 AMM 38-11-01 as an accepted procedure.
d. Vacuum Lavatory Waste Tanks. Refer to 767 AMM 38-32-11 as an accepted procedure.
e. Sidewall Insulation, which includes insulation blankets and capstrips from the sidewall, ceiling,
and aft pressure bulkhead. Refer to 767 AMM 25-52-03 as an accepted procedure.
NOTE: Boeing Service Bulletin 767-25A0300, "Equipment/Furnishings - Insulation - Aft
Bulkhead to Floor Insulation Blankets Modification", which is mandated by FAA AD
2003-13-03, requires replacement of aft pressure bulkhead insulation blankets.
12. Disconnect the elevator (E1A/E1B/E2A/E2B), stabilizer trim (ST1A/ST1B/ ST2A/ST2B) and rudder
(RA/RB) control cables. Refer to 767 AMM 20-10-03 as an accepted procedure.
a. Install cable clamps.
b. Disconnect the cables at any turnbuckle aft of the aft pressure bulkhead.
c. Remove and salvage any air seals where the cable penetrates the aft pressure bulkhead.
d. Move and coil the cable ends forward and aft of the aft pressure bulkhead.
13. Remove and salvage the control cable air seals and fasteners for the elevator (E1A/E1B/E2A/E2B),
stabilizer trim (ST1A/ST1B/ ST2A/ST2B) and rudder (RA/RB) control cables. Refer to 767 AMM
20-10-04 as an accepted procedure. The salvaged air seals will be installed on the new aft pressure
bulkhead assembly when the control cables are reinstalled.
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14. Disconnect and remove auxiliary pitot tubes and seals in accordance with FIGURE 3.
15. Disconnect and remove auxiliary static system tubes (if installed) and hydraulic lines as follows.
a. Group 3:
Disconnect the auxiliary static system (AS1 and AS2) tubes at the junctions between STA
1605.5 and STA 1629, between stringers S-31L and S-32L. Cap the open ends of all tubes.
Refer to 767 AMM 20-10-09 as an accepted procedure.
b. Disconnect and cap the hydraulic lines at or near STA 1809.
c. Disconnect and cap the hydraulic lines forward of the aft pressure bulkhead.
d. Remove and discard the pressure seals at the aft pressure bulkhead in accordance with
FIGURE 4.
e. Remove hydraulic lines between the aft pressure bulkhead and STA 1809.
f. Group 3:
Move the auxiliary static system (AS1 and AS2) tubes forward of STA 1582.
16. Disconnect the electrical connectors from the altitude pressure switches. Refer to 767 AMM
38-32-51 as an accepted procedure.
17. Disconnect electrical systems, including:
a. Lights
b. APU Power
c. High Frequency Communications
d. Stall Warning Systems
e. Interphone
f. Autopilot
g. Yaw Damper
h. Rudder Trim Actuator
i. Rudder Ratio Changer
j. Rudder and Elevator Shutoff Valves
k. Rudder Position Indicator
l. Stabilizer Trim Control System
m. Flap/Stabilizer Position Module
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n. Flight Recorder Systems
o. APU Fire Detection System
18. Disassemble and remove and keep all seal components where wires penetrate the aft pressure
bulkhead. Move all loose wires forward or aft, as necessary.
19. Disconnect and remove the APU Air Supply Duct. Refer to 767 AMM 36-11-01 as an accepted
procedure.
20. Disconnect the APU fuel line at the aft pressure bulkhead as follows:
a. In the aft end of the bulk cargo compartment, disconnect the shroud and APU fuel line at the
aft pressure bulkhead fitting. Salvage all bolts, nuts, and washers. Refer to the task "Remove
the APU Fuel Line and Shroud Between the Center Compartment of the Auxiliary Fuel Tank
and the Pressure Bulkhead for the Aft Cargo Compartment" in 767 AMM 28-25-05 as an
accepted procedure.
b. Remove the APU fuel line between the aft pressure bulkhead the APU firewall. Refer to the
task "Remove the APU Fuel Line and Shroud Between the Pressure Bulkhead for the Aft
Cargo Compartment and the APU Firewall Bulkhead" in 767 AMM 28-25-05 as an accepted
procedure.
c. Remove and keep the APU fuel line bulkhead fitting in accordance with FIGURE 5.
d. Install the APU fuel line bulkhead fitting on the new aft pressure bulkhead in accordance with
FIGURE 6.
21. Remove the Dorsal Fin. Refer to 767 AMM 53-66-02 as an accepted procedure.
CAUTION: SLOWLY LIFT AND REMOVE LARGE STRUCTURAL COMPONENTS TO PREVENT
DAMAGE TO THE AIRPLANE OR TO PERSONS.
22. Remove the Vertical Fin. A vertical fin removal procedure is shown in 767 ARD 2-60-2. (This
procedure has similarities that can be used as a guideline):
a. Install internal scaffolding PME148T0010PBR inside Section 48.
b. Attach vertical fin lift fittings ME100T3480PBR to the vertical fin.
c. Attach vertical fin lift sling 2OHME100T3480PBR to the vertical fin and apply 1,000 pounds
upward prelift tension to the sling.
d. Disconnect the fin-to-body link at the leading edge of the fin. Remove the 16 tension bolts
and 156 lock bolts that attach the vertical fin to the aft body. Use torque tool 2MIT100T3480PBR
as necessary when removing the tension bolts. Record the locations and quantity of all shims
removed at the time of the fin removal. Store the service ready shims for reuse. Lift the vertical
fin off the body. A vertical fin removal procedure is shown in 767 ARD 2-60-2 for airplane
recovery purposes.
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e. Without a rotating fixture, the vertical fin must be stored in an upright position. Use fin stand
ME170T0100PBR or create a tool to act as a base to support the vertical fin by attaching to
the four corner tension bolt locations. The vertical fin should be stored indoors.
NOTE: All H-11 hardware should have been replaced at fin to body joint per Boeing Service
Bulletin 767-53A0085 and FAA AD 2003-10-11 by July 1, 2006.
CAUTION: THE TRAP LOCKING DEVICES MUST BE REMOVED FROM THE HORIZONTAL
STABILIZER PIVOTS ON BOTH THE LEFT AND RIGHT SIDES TO DO THE PIN
ROTATION CHECK
23. Support the horizontal stabilizer with 767 SRM Horizontal Stabilizer supplementary supports in
accordance with 767-200 SRM 51-50-02 and 767-300 SRM 51-50-02 Detail IV on the left and right
sides. The four jacks should be loaded until the horizontal stabilizer pivot fittings begin to move
vertically relative to the airplane Section 48 structure (767 AMM 55-17-51) and check that the outer
pin can be rotated freely.
NOTE: The sum of all four jacks loads should not exceed 5,000 pounds. The center of gravity
of the Horizontal Stabilizer is aft of the pivot fitting pins. The jacks at the rear spar will
support greater percentage of load than jacks at the front spar. The corresponding left
side and right side jacks should be uniformly loaded.
24. Remove the horizontal stabilizer-to-body seals. Refer to 767 AMM 55-10-01 as an accepted
procedure.
25. Remove the horizontal stabilizer-to-body blade seals. Refer to 767 AMM 55-10-02 as an accepted
procedure.
26. Remove horizontal stabilizer fairing skin panels in accordance with FIGURE 23 and FIGURE 25.
CAUTION: INSUFFICIENT OR EXCESSIVE LIFT FORCE CAN RESULT IN STRUCTURAL DAMAGE
AND A SAFETY HAZARD.
27. Do one of the options that follow:
a. Option 1: REMOVAL OF ALL ELEVATORS
(1) Remove all the elevators installed on the horizontal stabilizer. Refer to 767 AMM 27-31-01
and 767 AMM 27-31-02 as an accepted procedure.
NOTE: If the elevators are not removed, it will require installation of forward lower tool
fittings on the tail cone after it is removed and prior to storing the structure on
the stand.
(2) Remove the rudder-to-body seal. Refer to 767 AMM 55-36-02 as an accepted procedure.
(3) Install lift fittings ME148T0600PBR-1/-2/-3/-4/-5 and sling ME148T0600PBR-12.
(4) Break the fay seal between the tail cone and STA 1809.5
(5) Support the tail cone between STA 1809 and STA 1952 with lift fittings and sling
ME148T0600PBR.
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NOTE: The APU will remain in place.
(6) Remove the fasteners that attach the tail cone to the STA 1809 bulkhead in accordance
with FIGURE 7.
(7) Slowly lift the tail cone aft and up to clear the upper STA 1809.5 bulkhead structure and
airplane.
NOTE: Make sure not to damage the STA 1809.5 bulkhead structure, HSTAB or airplane.
(8) Locate and store the tail cone on stand 2ME148T0600PBR.
b. Option 2: NON REMOVAL OF ELEVATORS
(1) Remove the rudder-to-body seal. Refer to 767 AMM 55-36-02 as an accepted procedure.
(2) Install lift fittings ME148T0600PBR-1/-2/-5 and sling ME148T0600PBR-12.
NOTE: Do not install lift fittings ME148T0600PBR-3/-4 at this time.
(3) Install protective foam pads between the tail cone and HSTAB/inboard elevators.
(4) Break the fay seal between the tail cone and STA 1809.5.
(5) Support the tail cone between STA 1809 and STA 1952 with lift fittings and sling
ME148T0600PBR. The APU will remain in place. Remove the fasteners that attach the
tail cone to the STA 1809 bulkhead in accordance with FIGURE 7.
(6) Prepare the tail cone between and lift fittings ME148T0600PBR-3/-4 for installation.
NOTE: Do not install the lift fittings at this time. The lift fittings will be installed after the
tail cone is removed from the airplane and before storing on stand.
(7) Slowly lift the tail cone vertically up to clear the lower section of STA 1809.5 bulkhead
structure, HSTAB and elevators and slowly move aft to clear the upper section of STA
1809.5 bulkhead structure HSTAB and elevators.
NOTE: Make sure not to damage the STA 1809.5 bulkhead structure, HSTAB, elevators
or airplane.
(8) Install lift fittings ME148T0600PBR-3/-4.
(9) Locate and store the tail cone on stand 2ME148T0600PBR.
28. Attach horizontal stabilizer lift fittings ME182T0000PBR and lift sling OHME180T0100PBR to the
horizontal stabilizer and make the sling cable assembly tight.
29. Disconnect the stabilizer trim ballscrew from the horizontal stabilizer center section. Refer to 767
AMM 27-41-10 as an accepted procedure.
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### Page 48

30. Do not remove the horizontal stabilizer pivot pins. Make sure the horizontal stabilizer sling cable
assembly is still tight. With the horizontal stabilizer vertically balanced as described in Step 23 and
Step 28, complete the disassembly of the STA 1809.5 bulkhead in accordance with FIGURE 8 to
allow the horizontal stabilizer to be removed. The left and right STA 1809.5 center bulkhead
assemblies will remain attached to the horizontal stabilizer at the pivot pins. Make sure there is
no load on the hinge pins as the center of gravity is subject to change.
NOTE: Secure the jackscrew in order to prevent it swinging whilst carrying out access, inspection,
repair or replacement.
CAUTION: THE LEFT AND RIGHT STA 1809.5 BULKHEAD OUTER CHORDS WILL NO LONGER
BE CONNECTED TO THE SURROUNDING STRUCTURE AFTER COMPLETION OF
THE FASTENER REMOVALS GIVEN IN FIGURES 7 AND 8. TO PREVENT DAMAGE
TO THE OUTER CHORDS, USE CARE TO REMOVE THE OUTER CHORDS WHILE
THE HORIZONTAL STABILIZER (WITH THE STA 1809.5 CENTER BULKHEAD
ASSEMBLIES ATTACHED) IS REMOVED.
31. Use the horizontal stabilizer lift sling to vertically lift the horizontal stabilizer a small amount to
unload the 767 SRM Horizontal Stabilizer supplementary supports, then remove the supplementary
supports. Remove the left and right STA 1809.5 bulkhead outer chords, which are trapped between
the STA 1809.5 center bulkhead assemblies and the forward part of section 48 that remains. Move
the horizontal stabilizer aft until it is clear of the STA 1809.5 bulkhead. Set the horizontal stabilizer
down on a storage fixture similar to ME180T0000PBR.
32. Make and install temporary STA 1809.5 bulkhead stabilizing tools in accordance with FIGURE 18.
CAUTION: INSUFFICIENT OR EXCESSIVE LIFT FORCE CAN RESULT IN STRUCTURAL DAMAGE
AND A SAFETY HAZARD.
LEAVING THE PME148T0010PBR INTERNAL SCAFFOLDING INSIDE THE FORWARD
PART OF SECTION 48 DURING THE OVERHEAD REMOVAL PROCESS RESULTS
IN A FORWARD SHIFT IN THE CENTER OF GRAVITY OF THE FORWARD PART OF
SECTION 48 THAT MAY CAUSE SEPARATION DIFFICULTIES.
33. RC - Support the forward part of Section 48 (STA 1582 to STA 1809) with lift fittings and sling
3ME140T0140PBR and handling fittings ME148T0200PBR. Remove fasteners, clips, and fittings
in accordance with FIGURE 9. Detach the STA 1582 floor beam in accordance with FIGURE 20.
Remove the forward part of Section 48 (the aft pressure bulkhead will remain attached to the
forward part of Section 48 at this time). Remove and store the forward part of Section 48 (which
includes the aft pressure bulkhead) on stand 2ME148T0200PBR.
WARNING: UNTIL THE STA 1582 FLOOR BEAM TEMPORARY SUPPORTS ARE INSTALLED, DO
NOT PLACE EXCESSIVE WEIGHT ON THE MAIN DECK FLOOR STRUCTURE AFT
OF STA 1562. THE MAIN DECK FLOOR AFT OF STA 1562 IS NOT SUPPORTED. DO
THIS TO PREVENT INJURY TO PERSONNEL AND DAMAGE TO THE FLOOR
STRUCTURE.
WARNING: INSTALL APPROPRIATE SAFETY BARRICADES OR SIMILAR TO BLOCK THE END
OF THE MAIN DECK FLOOR AFT OF STA 1582. DO THIS TO PREVENT INJURY TO
PERSONNEL.
34. Install temporary supports for the STA 1582 floor beam in accordance with FIGURE 22. Prior to
installation of the supports, make sure that the floor grid is level, and not deflected down or up.
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35. RC - Attach removal strongback ME148T2610PBR and lifting fixture OHME148T2610PBR to the
existing aft pressure bulkhead in the forward part of Section 48. Remove the rivets that attach the
aft pressure bulkhead to the Section 48 pressure ring in accordance with FIGURE 10. Remove
the old aft pressure bulkhead from the forward part of Section 48.
NOTE: Some rivets will need to be removed just prior to installation of the strongback due to the
rivet location being hidden under the strongback attach location.
36. RC - Attach lifting fixture OHME148T2610PBR to installation strongback 2ME148T2610PBR (this
strongback is shipped already attached to the new aft pressure bulkhead) and lift the new bulkhead
into position in the forward part of Section 48. Install fasteners to attach the new aft pressure
bulkhead to the Section 48 (STA 1582) pressure ring in accordance with FIGURE 11. Remove
the aft pressure bulkhead lifting fixture.
37. Install protective equipment PRE148T2610PBR on the new dome.
WARNING: WITH THE STA 1582 FLOOR BEAM TEMPORARY SUPPORTS REMOVED, DO NOT
PLACE EXCESSIVE WEIGHT ON THE MAIN DECK FLOOR STRUCTURE AFT OF
STA 1562. THE MAIN DECK FLOOR AFT OF STA 1562 IS NOT SUPPORTED. DO
THIS TO PREVENT INJURY TO PERSONNEL AND DAMAGE TO THE FLOOR
STRUCTURE.
CAUTION: JUST PRIOR TO FINAL POSITIONING OF THE FORWARD PART OF SECTION 48,
REMOVE THE STA 1582 FLOOR BEAM TEMPORARY SUPPORTS. DO THIS TO
PREVENT DAMAGE TO THE NEW AFT PRESSURE BULKHEAD FROM THE FLOOR
BEAM SUPPORT FASTENERS.
38. RC - Lift the forward part of Section 48 (STA 1582 to STA 1809, including the new aft pressure
bulkhead) into position from the storage stand with lift fittings and sling 3ME140T0140PBR and
handling fittings ME148T0200PBR. Install fasteners in accordance with FIGURE 12 to attach the
new aft pressure bulkhead and the forward part of Section 48 to Section 46 at STA 1582. Attach
the STA 1582 floorbeam in accordance with FIGURE 22. Remove the sling, handling fittings, and
lift fittings.
39. Remove the temporary STA 1809.5 bulkhead stabilizing tools in accordance with FIGURE 20.
40. RC - Lift the horizontal stabilizer (with the left and right STA 1809.5 center bulkheads attached at
the hinge pins) from the storage fixture and move it near its final position using the lift sling and
lift fittings. Before moving the horizontal stabilizer into its final position, position the previously
removed left and right STA 1809.5 bulkhead outer chords between the forward part of Section 48
and the STA 1809.5 center bulkhead assemblies. The final position is set by alignment of the left
and right center bulkhead fastener patterns.
41. Support the horizontal stabilizer with 767 SRM Horizontal Stabilizer supplementary supports in
accordance with 767-200 SRM 51-50-02 and 767-300 SRM 51-50-02 Detail IV on the left and right
sides. The four jacks should be loaded until the supports have taken the load off the horizontal
stabilizer lift sling. Do not yet remove the horizontal stabilizer lift sling or lift fittings.
NOTE: The sum of all four jacks loads should not exceed 5,000 pounds. The center of gravity
of the Horizontal Stabilizer is aft of the pivot fitting pins. The jacks at the rear spar will
support greater percentage of load than jacks at the front spar. The corresponding left
side and right side jacks should be uniformly loaded.
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42. RC - Attach the left and right STA 1809.5 center bulkheads in accordance with FIGURE 13 and
FIGURE 14. Use care to prevent excessive loading of the stabilizer hinge joints.
43. Connect the stabilizer trim ballscrew to the horizontal stabilizer center section. Refer to 767 AMM
27-41-10 as an accepted procedure.
44. Remove the horizontal stabilizer lift sling and lift fittings. Reinstall the production fasteners at the
lift fitting attach points.
45. Lift the tail cone into position with the sling and lift fittings. Install the fasteners in accordance with
FIGURE 15, to attach the tail cone to the STA 1809 bulkhead. Remove the sling and lift fittings.
NOTE: Accomplishment of Part 3 Step 41 (horizontal stabilizer support), Step 42 (align and attach
STA 1809.5 center bulkheads), Step 43 (stabilizer trim ballscrew attachment), Step 44
(removal of lift sling and fittings), and Step 45 (attach tail cone) should return the horizontal
stabilizer to the position initially given in Step 23.
46. The horizontal stabilizer is now supported by suitable means, with trap lock devices removed.
Check that the right and left horizontal stabilizer pivot pins can be rotated freely with an applied
torque of 400 in-lb or less. If necessary, remove and reinstall both the left and right pivot pins.
Refer to 767 AMM 55-17-51 as an accepted procedure.
47. Install horizontal stabilizer fairing skin panels in accordance with FIGURE 24 and FIGURE 26.
48. Install the horizontal stabilizer-to-body seals. Refer to 767 AMM 55-10-01 as an accepted procedure.
49. Install the horizontal stabilizer-to-body blade seals. Refer to 767 AMM 55-10-02 as an accepted
procedure.
50. Prepare the Vertical Fin in accordance with FIGURE 27.
51. Install the Vertical Fin in accordance with FIGURE 28.
52. Inspect the fin-to-body joints. If there is no sealant, apply sealant in accordance with Boeing Drawing
140T4800. Do not plug drain holes.
53. Finish the fastener heads, damaged paint, bare areas and all fillet seals in the interior of the fin in
accordance with SOPM 20-41-02.
54. Apply corrosion inhibiting compound in the interior of the fin with BMS 3-23 in accordance with
Boeing Drawing 140T6000. Refer to 767-200 SRM 51-20-01 and 767-300 SRM 51-20-01 for
additional help.
55. Connect the fin-to-body link at the leading edge of the fin.
56. Remove the internal scaffolding PME148T0010PBR from inside Section 48.
57. Remove the vertical fin lift fittings and sling.
58. Finish all bare aluminum with chemical film treatment and two coats of BMS 10-11, Type I primer.
Apply corrosion inhibiting compound to both the forward and aft sides of the aft pressure bulkhead.
Refer to 767 AMM 51-24-09 as an accepted procedure.
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59. Install the Dorsal Fin. Refer to 767 AMM 53-66-02 as an accepted procedure.
60. Install the APU fuel line between the aft pressure bulkhead the APU firewall. Refer to the task
"Install the APU Fuel Line and Shroud Between the Pressure Bulkhead for the Aft Cargo
Compartment and the APU Firewall Bulkhead" in 767 AMM 28-25-05 as an accepted procedure.
61. In the aft end of the bulk cargo compartment, attach the APU fuel line and shroud to the aft pressure
bulkhead fitting. Refer to the task "Install the APU Fuel Line and Shroud Between the Center
Compartment of the Auxiliary Fuel Tank and the Pressure Bulkhead for the Aft Cargo Compartment"
in 767 AMM 28-25-05 as an accepted procedure.
62. Install the APU Air Supply Duct. Refer to 767 AMM 36-11-01 as an accepted procedure.
63. Connect electrical systems, including:
a. Lights
b. APU Power
c. High Frequency Communications
d. Stall Warning Systems
e. Interphone
f. Autopilot
g. Yaw Damper
h. Rudder Trim Actuator
i. Rudder Ratio Changer
j. Rudder and Elevator Shutoff Valves
k. Rudder Position Indicator
l. Stabilizer Trim Control System
m. Flap/Stabilizer Position Module
n. Flight Recorder Systems
o. APU Fire Detection System
64. Install salvaged pressure seals where wires penetrate the aft pressure bulkhead.
65. Connect the electrical connectors for the altitude pressure switches. Refer to 767 AMM 38-32-51
as an accepted procedure.
66. Install the hydraulic lines that were removed earlier that pass through the aft pressure bulkhead.
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67. Group 3:
Install the auxiliary static system tubes that were removed earlier that pass through the aft pressure
bulkhead.
68. Install pressure seals at the aft pressure bulkhead in accordance with FIGURE 16.
69. Install auxiliary pitot tubes and seals in accordance with FIGURE 17.
70. Reconnect the stabilizer trim (ST1A/ST1B/ ST2A/ST2B), elevator (E1A/E1B/E2A/E2B), and rudder
(RA/RB) control cables. Refer to 767 AMM 20-10-03 as an accepted procedure.
a. Connect the cable ends (coiled forward and aft of the aft pressure bulkhead) through the aft
pressure bulkhead at the appropriate turnbuckle.
b. Install new or salvaged air seals and fasteners where cables penetrate the aft pressure
bulkhead. Refer to 767 AMM 20-10-04 as an accepted procedure.
c. Remove cable clamps.
71. Adjust the Stabilizer Trim System. Refer to 767 AMM 27-41-00 as an accepted procedure.
72. Adjust the Elevator System. Refer to 767 AMM 27-31-00 as an accepted procedure.
73. Adjust the Rudder System. Refer to 767 AMM 27-21-00 as an accepted procedure.
74. Install equipment in the aft end of the bulk cargo compartment that was removed for access. This
includes:
a. Potable Water Tanks. Refer to 767 AMM 38-11-01 as an accepted procedure.
b. Vacuum Lavatory Waste Tanks. Refer to 767 AMM 38-32-11 as an accepted procedure.
c. Sidewall Insulation. Refer to 767 AMM 25-52-03 as an accepted procedure.
d. Bulk Cargo Compartment Aft Lining. Refer to 767 AMM 25-55-01 as an accepted procedure.
e. Bulk Cargo Compartment Sidewall Lining, for access to the pitot-static tubes on the left side
from the aft pressure bulkhead to the bulk cargo door aft frame at STA 1461. Refer to 767
AMM 25-55-01 as an accepted procedure.
75. Install equipment in the aft part of the passenger compartment that was removed for access. This
includes:
a. Floor Panels. Refer to 767 AMM 53-01-01 as an accepted procedure.
b. Doorway/Galley Floor Covering. Refer to 767 AMM 25-27-02 as an accepted procedure.
c. Sidewall and Ceiling Insulation. Refer to 767 AMM 25-21-05 as an accepted procedure.
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d. Ceiling panels. Refer to 767 AMM 25-22-01, 767 AMM 25-22-02, and/or 767 AMM 25-22-10
as accepted procedures.
e. Sidewall Panels. Refer to 767 AMM 25-21-01 as an accepted procedure.
f. Aft Galley Complex A1, A4, or A1-A3. Refer to 767 AMM 25-31-04 as an accepted procedure.
g. Lavatories. Refer to 767 AMM 25-41-04 as an accepted procedure.
h. Partitions. Refer to 767 AMM 25-25-04 as an accepted procedure.
i. Passenger seats. Refer to 767 AMM 25-25-01 as an accepted procedure.
76. Dejack the airplane. Service the nose and main landing gears and put them in serviceable condition.
PART 3: SYSTEM TESTS
1. Bleed the hydraulic system. Refer to 767 AMM 29-11-00 as an accepted procedure. Do a leak
check of the hydraulic lines that were removed and reinstalled. Refer to 767 AMM 20-10-09 as an
accepted procedure.
2. Do a leak test of the new pitot-static tubes. Refer to 767 AMM 34-11-01 as an accepted procedure.
3. Do a test of the Autopilot. Refer to the task "AFDS Operational Test" in 767 AMM 22-10-00 as an
accepted procedure.
4. Do a test of the Yaw Damper System. Refer to the task "Operational Test - Yaw Damper System"
in 767 AMM 22-21-00 an accepted procedure.
5. Test the left and right High Frequency Communications Systems. Refer to the task "Operational
Test - HF Communication System" in 767 AMM 23-11-00 as an accepted procedure.
6. Do a test of the Interphone system. Refer to the task "Operational Test - Service Interphone
System" in 767 AMM 23-41-00 as an accepted procedure.
7. Do a test of the Stick Nudger. Refer to steps 2.A., 2.B., 2.C., 2.D., 2.G., and 2.H. in the task
"Operational Test - Stall Warning System" in 767 AMM 27-32-00 as an accepted procedure.
8. Test the Horizontal Stabilizer Trim Control System. Refer to the task "Operational Test" in 767
AMM 27-41-00 as an accepted procedure.
9. Test the Stabilizer Trim System. Refer to the "Manual-Mechanical Stabilizer Trim Control Operational
Test", the "Lever Force Test" and the "Horizontal Stabilizer Trim Control System Operational Test"
in 767 AMM 27-41-00 as an accepted procedure.
10. Test the Elevator System. Refer to the task "System Test - Elevator Controls" in 767 AMM 27-31-00
as an accepted procedure. It is acceptable to not perform the "Elevator Position Indication Test",
the "Elevator Power Control Actuators Test", the "Elevator Feel System Test", the "Stick Nudger
Test", and the "Elevator Autopilot Servo Rods Test" tasks within the Systems Test.
11. Do an operational test of the Elevator Control System. Refer to the task "Operational Test - Elevator
Control System" in 767 AMM 27-31-00 as an accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
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### Page 54

12. Test the Rudder System. Refer to the task "System Test - Rudder and Rudder Trim Control" in
767 AMM 27-21-00. It is acceptable to not perform the "Test Rudder Pedal Adjustment Mechanism
Travel", the "Test Captain's Rudder Pedal Travel", the "Test First Officer's Pedal Travel", the "Test
Single Hydraulic System and PCA", the "Test Rudder Ratio-Changer System", the "Test Rudder
Ration Flight Deck Annunciation", the "Test the Left RRCM", the "Test the Right RRCM", and the
"Rudder Trim Authority and Rate Test" tasks within the System Test.
13. Test the Rudder Trim Actuator. Refer to the task "Rudder Trim Actuator - Test" in 767 AMM
27-21-11 as an accepted procedure.
14. Test the Rudder Ratio Changer. Refer to the task "Rudder Ratio Changer Mechanism - Test" in
767 AMM 27-21-13 as an accepted procedure.
15. Test the Rudder and Elevator Shutoff Valves. Refer to the task "Rudder and Elevator Shutoff
Valves - System Test" in 767 AMM 27-23-00 as an accepted procedure.
16. Test the Rudder Position Indicator. Refer to the task "Rudder Position Indication - Operational
Test" in 767 AMM 27-28-00 as an accepted procedure.
17. Test the Position Indicating System. Refer to the task "Operational Test - Position Indicating
System" in 767 AMM 27-48-00 as an accepted procedure.
18. Test the Flap/Stabilizer Position Module. Refer to the task "Test for the FSPM" in 767 AMM 27-58-01
as an accepted procedure.
19. Test the Takeoff Configuration Warning Card Module. Refer to steps 4.A., 4.B., 4.C., 4.I., and
4.J.in the task "Warning Electronics Unit (WEU) Card Module Test" in 767 AMM 31-51-04 as an
accepted procedure.
20. Test the Flight Data Recorder. Refer to the task "Flight Data Recorder Operational Test" in 767
AMM 31-31-00 as an accepted procedure.
21. Test the service lights. Refer to the task "Service Lights - Operational Test" in 767 AMM 33-31-00
as an accepted procedure.
22. Test the logo lights. Refer to the task "Logo Lights - Operational Test" in 767 AMM 33-45-00 as
an accepted procedure.
23. Test the altitude pressure switches. Refer to 767 AMM 38-32-51 as an accepted procedure.
24. Test the APU wiring in accordance with APPENDIX A.
25. Do a cabin pressure leakage test. Refer to 767 AMM 05-51-24 as an accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 13, 2015
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### Page 55 (OCR)

BOEING SERVICE BULLETIN 767-53A0267
ALERT  ALERT
STA
1582
VIEW IN THE FORWARD DIRECTION  2392499
FIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION
(SHEET 1 OF 5)
Original Issue: August 13, 2015
Revision 1 August 04, 2016  PROPRIETARY - Copyright @ Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0267
Work - See page 1 for details.  55 of 206

### Page 56 (OCR)

BOEING SERVICE BULLETIN 767-53A0267
ALERT  ALERT
D  2 3 21 LOCATIONS
3.78
33 SEAL BLOCK
2.42
6 18 LOCATIONS
2.47
SEAL BLOCK + 5
PRESSURE
BULKHEAD
ASSEMBLY
FWD
2392497
FIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION
(SHEET 2 OF 5)
Original Issue: August 13, 2015
Revision 1 August 04, 2016  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-53A0267
Work - See page 1 for details.  56 of 206

### Page 57

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 new aft pressure bulkhead.
More DataQtyIdentificationNameTaskStep
-4-FastenerRemove1
1.19 - 1.21 inch di-
ameter, normal to
the bulkhead sur-
face. 125 microinch
or better surface fin-
ish.
4-HoleDrill / Ream
Break sharp edges
and apply chemical
film treatment and
two coats of BMS10-
11, Type I primer to
the bare edges of
the holes.
--FinishApply
--148T2629-2SEAL BLOCK ASSYLocate2
-21-Rivet HoleDrill / Ream
FIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION
(SHEET 3 OF 5)
Export Controlled ECCN: 9E991 - BOEING
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### Page 58

More DataQtyIdentificationNameTaskStep
Apply a pressure
faying surface seal
to the entire mating
surface of the seal
block assembly.
-BMS 5-95SealantApply3
-1148T2629-2SEAL BLOCK ASSYInstall (New)
-21BACR15BB5A7CRIVET, UNIVERSAL
HD
Install (New)
-4-FastenerRemove4
--140T0345-3SEAL BLOCK ASSYLocate
-22-Rivet HoleDrill / Ream
Apply a pressure
faying surface seal
to the entire mating
surface of the seal
block assembly.
-BMS 5-95SealantApply5
-1140T0345-3SEAL BLOCK ASSYInstall (New)
-18BACR15BB5A7CRIVET, UNIVERSAL
HD
Install (New)6
-4BACR15BB5A7CRIVET, UNIVERSAL
HD
Install (New)7
Optional, if oversize
rivets are necessary.
4BACR15BB6A8CRIVET, UNIVERSAL
HD
Install (New)
Apply a pressure
faying surface seal
to the entire mating
surface of the cover-
plate and pressure
pan.
-BMS 5-95SealantApply8
-1140T0345-1COVER PLATEInstall (New)
-14BACS12HN3-7BOLTInstall (New)9
Under screw head.14NAS1149D0332JWASHERInstall (New)
Under nut.14NAS1149D0332JWASHERInstall (New)
-14BACN11AG3NUT, SELF-LOCKInstall (New)
Fillet seal all screw
heads, nuts, and
washers.
-BMS 5-95SealantApply10
The parts shown in the table below are provided as extra parts for this figure.
FIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION
(SHEET 4 OF 5)
Export Controlled ECCN: 9E991 - BOEING
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### Page 59

More DataQtyIdentificationName
16BACB30NM4K14BOLT, HEX HEAD
1BACN11AG3NUT, SELF-LOCK
7BACR15BB5A7CRIVET, UNIVERSAL
HD
1BACR15BB6A8CRIVET, UNIVERSAL
HD
8BACR15FT6KE7CRIVET
1BACS12HN3-7BOLT
2NAS1149D0332JWASHER
5NAS1149D0363JWASHER, FLAT
1NAS42DD3-44FCSPACERS FOR RIV-
ETS
1NAS42DD3-48FCSPACERS FOR RIV-
ETS
1NAS42DD3-64FCSPACERS FOR RIV-
ETS
FIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 13, 2015
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59 of 206
BOEING SERVICE BULLETIN 767-53A0267
ALERTALERT

### Page 60 (OCR)

BOEING SERVICE BULLETIN 767-53A0267
ALERT  ALERT
STA
1582
VIEW IN THE FORWARD DIRECTION  2392500
FIGURE 2: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION
(SHEET 1 OF 2)
Original Issue: August 13, 2015
Revision 1 August 04, 2016  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-53A0267
Work - See page 1 for details.  60 of 206

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