# Boeing Alert Service Bulletin 767-27A0224: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2005-22523; AD 2013-05-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 767-27A0224](https://openairdocs.org/service-documents/boeing/767-27a0224.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin - SB-767-27A0224-01
- Pages: 78
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## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
Number: 767-27A0224
Original Issue: June 23, 2011
Revision 1: December 16, 2011
ATA System: 2731
SUBJECT: FLIGHT CONTROLS - Elevator Control System - Pressure Seal Change, Aft Bulkhead
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). 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 © 2011 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 9
1. PLANNING INFORMATION ........................................ 1 3
A. Effectivity ............................................... 1 3
1. Airplanes ............................................ 1 3
2. Spares Affected ........................................ 1 9
B. Concurrent Requirements ...................................... 2 0
C. Reason ................................................ 2 0
D. Description .............................................. 2 1
E. Compliance .............................................. 2 2
F. Approval ............................................... 2 3
G. Manpower .............................................. 2 3
H. Weight and Balance Changes .................................... 2 6
I. Electrical Load Data ......................................... 2 7
J. References .............................................. 2 7
1. Existing Data .......................................... 2 7
2. Data supplied with this Service Bulletin ............................ 2 8
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 8
K. Publications Affected ........................................ 2 8
L. Interchangeability and Intermixability of Parts ........................... 2 8
2. MATERIAL INFORMATION ........................................ 2 9
A. Material - Price and Availability ................................... 2 9
B. Industry Support Information .................................... 2 9
C. Parts Necessary For Each Airplane ................................. 2 9
1. Kits/Parts ............................................ 2 9
2. Parts and Materials Supplied by the Operator ........................ 3 1
3. Parts Modified and Reidentified ................................ 3 1
4. Parts Removed and Not Replaced .............................. 3 1
D. Parts Necessary to Change Spares ................................. 3 1
E. Special Tooling - Price and Availability ............................... 3 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 3
A. GENERAL INFORMATION ..................................... 3 3
B. WORK INSTRUCTIONS ....................................... 3 4
FIGURE 1: AFT PRESSURE BULKHEAD - REMOVE THE PRESSURE SEAL ASSEMBLIES [Group 1-3]
.................................................. 3 6
FIGURE 2: AFT PRESSURE BULKHEAD - REMOVE THE FLANGED TUBES [Group 1, Configuration 3;
Group 2, Configuration 2; Group 4, Configuration 3] ..................... 3 9
FIGURE 3: AFT PRESSURE BULKHEAD - REMOVE THE FLANGED TUBES [Group 1, Configuration 4;
Group 2, Configuration 3; Group 3; Group 4, Configuration 4] ................ 4 2
FIGURE 4: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES AND
INSTALL CLAMPS [Group 1, Configuration 2-4; Group 2-3] ................. 4 4
FIGURE 5: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES [Group 1,
Configuration 1] ......................................... 5 1
FIGURE 6: AFT PRESSURE BULKHEAD - INSTALL NEW PRESSURE SEAL ASSEMBLIES [Group 1-3]
.................................................. 5 5
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FIGURE 7: AFT PRESSURE BULKHEAD - REMOVE THE PRESSURE SEAL ASSEMBLIES [Group 4]
.................................................. 5 9
FIGURE 8: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES AND
INSTALL CLAMPS [Group 4, Configuration 2-4] ....................... 6 3
FIGURE 9: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES [Group 4,
Configuration 1] ......................................... 7 0
FIGURE 10: AFT PRESSURE BULKHEAD - INSTALL NEW PRESSURE SEAL ASSEMBLIES [Group 4]
.................................................. 7 4
APPENDIX A: ELEVATOR CONTROL CABLES - OPERATIONAL TEST ................. 7 8
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Commercial 
Airplanes
767
Service Bulletin
Revision Transmittal SheetNumber: 767-27A0224Original Issue: June 23, 2011
Revision 1: December 16, 2011
ATA System: 2731
SUBJECT: FLIGHT CONTROLS - Elevator Control System - Pressure Seal Change, Aft Bulkhead
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on the airplane(s) changed in accordance with the original issue of this service
bulletin.
REASON FOR REVISION
This revision is sent to include a configuration that was not shown in the original issue, and to provide an
operational test that is more applicable to the change.
These sections were changed:
1. Paragraph 1.A., Effectivity: Added Group 4 for airplanes line number 225-226, 228-469, and removed these
airplanes from Group 1.
2. Summary, Background: Terminating action for Boeing service bulletin 767-25A0322 and 767-25A0323,
Revision 1 is described. The validation information is added.
3. Summary, Action: Group applicability of two steps are updated.
4. Summary, Manpower: The manpower estimates are updated.
5. Paragraph 1.C., Reason: Terminating action for Boeing service bulletin 767-25A0322 and 767-25A0323,
Revision 1 is described. The validation information is added.
6. Paragraph 1.D., Description: Group applicability of two steps and the affected maintenance zones are
updated.
7. Paragraph 1.E., Compliance: Group applicability of each compliance table is updated. A footnote is added
to Table 1. The footnote in Tables 2 and 3 are each updated to specify the revision level of the service
bulletins.
8. Paragraph 1.G., Manpower: Group applicability of each table is updated, and Group 4 tables are added.
The estimate for Appendix A replaces the estimate for Test. The totals for each airplane are updated.
9. Paragraph 1.H., Weight and Balance Changes: Group applicability of each table is updated.
10. Paragraph 1.J.1, Existing Data: Aircraft Maintenance Manual references are added.
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11. Paragraph 1.K.1, Publications: 767 Illustrated Parts Catalog reference 53-80 is removed.
12. Paragraph 2.A, Material - Price and Availability: Group applicability of each table is updated.
13. Paragraph 2.C.1., Kits/Parts: The applicability of each top kit is updated.
14. Paragraph 2.C.4., Parts Removed and Not Replaced: Group applicability of each table is updated.
15. Paragraph 3.A., General Information: Note 1 is deleted, and all steps are renumbered.
16. Paragraph 3.B., Work Instructions: Group applicability of the steps is updated. Steps are added for Group
4 airplanes. The Control Columns Travel Limits Test is replaced by an operational test.
17. Figures 1 and 6: All references to the part name, COVER in the step table are replaced with the part name,
SEAL COVER to maintain consistency with the illustration.
18. Figures 2 and 3: Group applicability is updated.
19. Figure 4: The view showing steps 8 and 9 now shows the flanged tubes without the seal, seal cover, and
seal plates installed. Steps 9 is moved to the upper clamp installation, and step 8 is moved to the lower
clamp installation.
20. Figures 4 and 5: A new view is added.
21. Figure 6: A new view is added to show the position of the pressure seal assembly. A new substep is added
to steps 1 and 4.
22. Figures 7-10 are added for Group 4 airplanes.
23. Appendix A is added for an operational test.
The data given in Information Notice 767-27A0224 IN 01 is included in this revision.
As a part of a service bulletin validation program, this change was completed on airplane VN028 by Service
Bulletin 767-27A0224Original Issue before the release of Revision 1 of this service bulletin. The change completed
on airplane VN028 by Service Bulletin 767-27A0224 Original Issue is equivalent to the release of Revision 1 of
this service bulletin. Airplane VN028 has the configuration of a Group 4, Configuration 2 airplane.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
June 23, 2011Original Issue:
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December 16, 2011Revision 1:
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Commercial 
Airplanes
767
Service Bulletin
SummaryNumber: 767-27A0224Original Issue: June 23, 2011
Revision 1: December 16, 2011
ATA System: 2731
SUBJECT: FLIGHT CONTROLS - Elevator Control System - Pressure Seal Change, Aft Bulkhead
CONCURRENT REQUIREMENTS
None.
BACKGROUND
The change given in this service bulletin will help to prevent elevator control restrictions due to frozen moisture
on the left elevator control cables at the aft pressure bulkhead seals. Elevator control restrictions reduce the
pilot's ability to control the airplane pitch. This can reduce the ability of the flight crew to maintain safe flight
during the approach to landing.
Service bulletins 767-27A0192 and 767-27A0193, original issue, were released to add drain holes to the flanged
tubes to make sure that moisture leaks from the main deck can not collect and freeze on the left elevator control
cables at the aft pressure bulkhead seals. A subsequent revision to 767-27A0192 removed airplanes from the
effectivity. Further investigation and testing at Boeing indicated that the elevator control restrictions could be
prevented with installation of longer flanged tubes through the existing tubes at the aft pressure bulkhead seals.
This change was implemented on production airplanes line number 972-974. Service bulletin 767-27A0219,
original issue, was released to implement a similar solution for airplanes before line number 972, and was
validated on one airplane. Subsequent to the validation, Boeing released 767-27A0219, revision 1. Revision 1
incorporated several improvements from the validation, including a longer flanged tube for the E1B elevator
control cable. Subsequently, operators reported unsuccessful attempts to incorporate service bulletin 767-27A0219
(original issue and revision 1) due to control cable misalignment conditions that are acceptable for the existing
configuration, but not for the 767-27A0219 configuration. Boeing recommended that operators stop work on
incorporation of service bulletin 767-27A0219, revision 1.
During the time after the release of service bulletins 767-27A0192 and 767-27A0193, Boeing received several
reports of elevator control restriction events that occurred among airplanes that had incorporated either issue
of service bulletin 767-27A0192, or service bulletin 767-27A0193, original issue.
Airplanes after line number 974 were manufactured with one-piece flanged tubes, and are not affected by this
service bulletin.
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This service bulletin replaces the two existing pressure seal assemblies for the left elevator control cables at
the aft pressure bulkhead. Each new pressure seal assembly extends forward along its control cable to keep
moisture away from its control cable. This service bulletin also closes the existing drain holes for airplanes that
have drain holes in the seal block tubes. For airplanes that incorporated 767-27A0219, original issue or revision
1, the flanged tubes are removed. After incorporation of this service bulletin, the repetitive inspection of the drain
holes as specified in service bulletins 767-27-0204 and 767-27-0205 are terminated for the affected airplanes.
For airplanes that have not incorporated service bulletins 767-27A0192 , 767-27A0193 , or 767-27A0219 , this
service bulletin terminates the A2 galley leak repetitive inspection as specified in revision 1 of service bulletin
767-25A0322 and 767-25A0323 .
This service bulletin replaces service bulletins 767-27A0192, revision 1; 767-27A0193, original issue; and
767-27A0219, revision 1.
Boeing Service Related Problem (SRP) 767-SRP-27-0208 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 767 FTD 27-05002 is related to this service bulletin.
As a part of a service bulletin validation program, this change was completed on airplane VN028 by Service
Bulletin 767-27A0224 Original Issue before the release of Revision 1 of this service bulletin. The change
completed on airplane VN028 by Service Bulletin 767-27A0224 Original Issue is equivalent to the release of
Revision 1 of this service bulletin. Airplane VN028 has the configuration of a Group 4, Configuration 2 airplane.
ACTION (PRR B12901-99RS)
1. Open access to the aft pressure bulkhead.
2. On the aft pressure bulkhead, remove two pressure seal assemblies.
3. Group 1, Configuration 3-4; Group 2, Configuration 2-3; Group 3; Group 4, Configuration 3-4:
Remove the two flanged tubes from the tubes in the seal block.
4. Clean the two seal block tubes.
5. Group 1, Configuration 2-4; Group 2-3; Group 4, Configuration 2-4:
Install a clamp to close the drain hole in each of the seal block tubes.
6. Install two new pressure seal assemblies.
7. Do the functional test.
8. Close access to the aft pressure bulkhead.
EFFECTIVITY
767-200, 767-300, 767-300F, and 767-400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of
affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an 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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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
Elapsed HoursTotal Task HoursAirplanes
5.555.55Group 1, Configuration 2; Group 2, Configuration
1; Group 4, Configuration 2
6.556.55Group 1, Configuration 3-4; Group 2, Configura-
tion 2-3; Group 3; Group 4, Configuration 3-4
5.155.15Group 1, Configuration 1; Group 4, Configuration
1
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BOEING SERVICE BULLETIN 767-27A0224
MATERIAL INFORMATION
STA
1582  INSTALL NEW PRESSURE
SEAL ASSEMBLY IN THE
1605  STA  EXISTING FLANGED TUBES.  CLOSE A DRAIN HOLE
THROUGH THE BOTTOM
STA
OF EACH TUBE.
1629
ELEVATOR
CONTROL
CABLE E1A
PRESSURE
BULKHEAD
ELEVATOR
CONTROL
CABLE E1B
STRINGER 20
STRINGER 22
2038188
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Commercial 
Airplanes
767
Service Bulletin
Number: 767-27A0224
Original Issue: June 23, 2011
Revision 1: December 16, 2011
ATA System: 2731
SUBJECT: FLIGHT CONTROLS - Elevator Control System - Pressure Seal Change, Aft Bulkhead
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplane(s) shown below. Refer to PRR B12901-99RS for data about
this change.
Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes line number 470-717, and 719-905, except 767-200 AWACS-1
Airplanes that have not incorporated service bulletin 767-27A0192,
767-27A0193, or 767-27A0219
1
Airplanes that have incorporated service bulletin 767-27A0192 or
767-27A0193, but have not incorporated service bulletin 767-27A0219
2
Airplanes that have incorporated the original issue of service bulletin
767-27A0219
3
Airplanes that have incorporated revision 1 of service bulletin
767-27A0219
4
Airplanes line number 906-971-2
Airplanes that have not incorporated service bulletin 767-27A02191
Airplanes that have incorporated the original issue of service bulletin
767-27A0219
2
Airplanes that have incorporated revision 1 of service bulletin
767-27A0219
3
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DESCRIPTIONCONFIGURATIONGROUP
Airplanes line number 972-974-3
Airplanes line number 225-226, 228-469-4
Airplanes that have not incorporated service bulletin 767-27A0192
or 767-27A0219
1
Airplanes that have incorporated service bulletin 767-27A0192 but
have not incorporated service bulletin 767-27A0219
2
Airplanes that have incorporated the original issue of service bulletin
767-27A0219
3
Airplanes that have incorporated revision 1 of service bulletin
767-27A0219
4
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
4VA713 - VA719
4VB327 - VB332
1VB441 - VB444
4VE086
4VE104
4VE118
4VE147 - VE151
1VE152
4VE171 - VE172
4VF041 - VF042
4VF051
4VF061 - VF062
4VF071 - VF072
4VF091 - VF093
4VF101 - VF102
4VF161
1VF162
1VF171 - VF172
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GroupVariable Number
1VF180
1VF251
4VK008 - VK011
1VK012 - VK016
4VK046 - VK054
1VK055 - VK056
4VK090 - VK102
1VK103 - VK113
4VK131 - VK133
4VK141 - VK142
1VK143 - VK148
4VK161
1VK162 - VK164
1VK171
1VK181
1VK186
4VL002 - VL006
1VL701 - VL703
1VL751 - VL755
1VL806 - VL807
1VL871 - VL873
1VL891 - VL900
1VL911 - VL914
1VL931 - VL932
1VL941
4VN006
4VN008 - VN028
1VN029 - VN041
4VN055 - VN064
4VN081 - VN093
1VN094 - VN099
4VN111 - VN124
1VN125 - VN127
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GroupVariable Number
4VN130 - VN132
1VN133 - VN137
4VN151 - VN158
4VN163 - VN168
4VN171 - VN173
1VN174
4VN191 - VN195
1VN196 - VN198
4VN211 - VN212
4VN221 - VN224
1VN225
4VN231 - VN234
4VN241 - VN243
4VN251 - VN262
1VN263 - VN276
4VN291
1VN292 - VN293
4VN301 - VN308
1VN309 - VN314
4VN371 - VN372
4VN376
4VN381 - VN383
1VN384 - VN388
1VN421 - VN427
1VN436
4VN471 - VN472
4VN491 - VN505
1VN506 - VN513
4VN531 - VN532
4VN536 - VN537
4VN541 - VN542
1VN546 - VN547
4VN551
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GroupVariable Number
4VN556 - VN557
1VN561 - VN562
4VN631 - VN633
1VN634 - VN638
4VN651 - VN652
1VN653 - VN658
4VN671 - VN672
1VN676
4VN681 - VN685
1VN686 - VN691
4VN731
1VN732
4VN751 - VN753
4VN791 - VN792
4VN811 - VN813
1VN921 - VN922
1VN931 - VN936
1VN951 - VN953
1VN966 - VN972
1VQ001 - VQ021
1VQ071 - VQ086
2VQ111
1VR051 - VR060
1VR081
1VR084
2VR086 - VR089
2VR106 - VR109
1VR201 - VR211
1VR251
1VR256 - VR260
1VR401
1VR421 - VR423
1VR426
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GroupVariable Number
1VR441
1VR461
1VR471 - VR472
1VS051 - VS056
1VS061
1VS066 - VS070
1VS073 - VS078
1VS091 - VS104
1VS111 - VS113
1VS131 - VS133
1VS136 - VS137
1VS176 - VS177
1VS186 - VS187
1VS196 - VS203
1VS206 - VS208
1VS211
1VS216 - VS217
1VS231
1VS246 - VS248
1VS261 - VS263
1VS266 - VS274
1VS291 - VS293
1VS301 - VS303
1VS306 - VS311
1VS316
1VS321 - VS324
1VS331 - VS333
1VS336 - VS337
1VS366 - VS367
1VS381 - VS382
1VS391 - VS392
1VS401
1VS426 - VS428
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GroupVariable Number
1VS466 - VS472
1VS486
1VS496 - VS497
1VS506 - VS507
1VS526
1VS546 - VS549
1VS701 - VS704
2VS705 - VS719
3VS720
1VS721 - VS728
2VS729 - VS735
1VS751 - VS753
2VS754 - VS759
1VS821 - VS824
2VS825
1VS841 - VS844
1VS861
2VS881 - VS883
2VS891
2VS896
2VS901 - VS912
2VS916
3VS921 - VS922
1VT501
2VT511 - VT513
2VT521 - VT523
2VT531 - VT533
2VV001
1VW701 - VW721
1VW851
2. Spares Affected
None.
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B. Concurrent Requirements
None.
C. Reason
The change given in this service bulletin will help to prevent elevator control restrictions due to frozen
moisture on the left elevator control cables at the aft pressure bulkhead seals. Elevator control restrictions
reduce the pilot's ability to control the airplane pitch. This can reduce the ability of the flight crew to
maintain safe flight during the approach to landing.
Service bulletins 767-27A0192 and 767-27A0193, original issue, were released to add drain holes to
the flanged tubes to make sure that moisture leaks from the main deck can not collect and freeze on
the left elevator control cables at the aft pressure bulkhead seals. A subsequent revision to 767-27A0192
removed airplanes from the effectivity. Further investigation and testing at Boeing indicated that the
elevator control restrictions could be prevented with installation of longer flanged tubes through the
existing tubes at the aft pressure bulkhead seals. This change was implemented on production airplanes
line number 972-974. Service bulletin 767-27A0219, original issue, was released to implement a similar
solution for airplanes before line number 972, and was validated on one airplane. Subsequent to the
validation, Boeing released 767-27A0219, revision 1. Revision 1 incorporated several improvements
from the validation, including a longer flanged tube for the E1B elevator control cable. Subsequently,
operators reported unsuccessful attempts to incorporate service bulletin 767-27A0219 (original issue
and revision 1) due to control cable misalignment conditions that are acceptable for the existing
configuration, but not for the 767-27A0219 configuration. Boeing recommended that operators stop
work on incorporation of service bulletin 767-27A0219, revision 1.
During the time after the release of service bulletins 767-27A0192 and 767-27A0193, Boeing received
several reports of elevator control restriction events that occurred among airplanes that had incorporated
either issue of service bulletin 767-27A0192, or service bulletin 767-27A0193, original issue.
Airplanes after line number 974 were manufactured with one-piece flanged tubes, and are not affected
by this service bulletin.
This service bulletin replaces the two existing pressure seal assemblies for the left elevator control
cables at the aft pressure bulkhead. Each new pressure seal assembly extends forward along its control
cable to keep moisture away from its control cable. This service bulletin also closes the existing drain
holes for airplanes that have drain holes in the seal block tubes. For airplanes that incorporated
767-27A0219, original issue or revision 1, the flanged tubes are removed. After incorporation of this
service bulletin, the repetitive inspection of the drain holes as specified in service bulletins 767-27-0204
and 767-27-0205 are terminated for the affected airplanes. For airplanes that have not incorporated
service bulletins 767-27A0192 , 767-27A0193 , or 767-27A0219 , incorporation of this service bulletin
is the terminating action for the A2 galley leak repetitive inspection as specified in revision 1 of service
bulletin 767-25A0322 and 767-25A0323 .
This service bulletin replaces service bulletins 767-27A0192, revision 1; 767-27A0193, original issue;
and 767-27A0219, revision 1.
Boeing Service Related Problem (SRP) 767-SRP-27-0208 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 767 FTD 27-05002 is related to this service bulletin.
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As a part of a service bulletin validation program, this change was completed on airplane VN028 by
Service Bulletin 767-27A0224 Original Issue before the release of Revision 1 of this service bulletin.
The change completed on airplane VN028 by Service Bulletin 767-27A0224 Original Issue is equivalent
to the release of Revision 1 of this service bulletin. Airplane VN028 has the configuration of a Group
4, Configuration 2 airplane.
Revision 1 is sent to include a configuration that was not shown in the original issue, and to provide
an operational test that is more applicable to the change.
D. Description
1. Open access to the aft pressure bulkhead.
2. On the aft pressure bulkhead, remove two pressure seal assemblies.
3. Group 1, Configuration 3-4; Group 2, Configuration 2-3; Group 3; Group 4, Configuration
3-4:
Remove the two flanged tubes from the tubes in the seal block.
4. Clean the two seal block tubes.
5. Group 1, Configuration 2-4; Group 2-3; Group 4, Configuration 2-4:
Install a clamp to close the drain hole in each of the seal block tubes.
6. Install two new pressure seal assemblies.
7. Do the functional test.
8. Close access to the aft pressure bulkhead.
Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of
this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1-2:
Affected Maintenance Zones
ZoneModel
311767-200, 767-300, 767-300F,
767-400ER
Group 3:
Affected Maintenance Zones
ZoneModel
311767-300
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Group 4:
Affected Maintenance Zones
ZoneModel
311767-200, 767-300
E. 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.
Group 1, 4, Configuration 1:
Table 1: On the aft pressure bulkhead, replace two pressure seal assemblies with new pressure
seal assemblies.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 24 months
after the original is-
sue date of this
service bulletin
Do the change in accor-
dance with the Accom-
plishment Instructions (a)
All Airplanes
(a) The accomplishment of this service bulletin is the terminating action for the A2 galley leak
repetitive inspection as specified in revision 1 of service bulletins 767-25A0322 and 767-
25A0323.
Group 1, Configuration 2; Group 2, Configuration 1; Group 4, Configuration 2:
Table 2: On the aft pressure bulkhead, replace two pressure seal assemblies with new pressure
seal assemblies, and close the two drain holes.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 24 months
after the original is-
sue date of this
service bulletin
Do the change in accor-
dance with the Accom-
plishment Instructions (a)
All Airplanes
(a) The accomplishment of this service bulletin is the terminating action for the repetitive in-
spection and cleaning of the flanged tubes as specified in the original issue of service
bulletins 767-27-0204 and 767-27-0205.
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Group 1, Configuration 3-4; Group 2, Configuration 2-3; Group 3; Group 4, Configuration 3-4:
Table 3: On the aft pressure bulkhead, remove two flanged tubes, replace two pressure seal as-
semblies with new pressure seal assemblies, and close the two drain holes.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-No compliance
time is given. Boe-
ing recommends
this service bulletin
be done at the op-
erator's discretion.
Do the change in accor-
dance with the Accom-
plishment Instructions (a)
All Airplanes
(a) The accomplishment of this service bulletin is the terminating action for the repetitive in-
spection and cleaning of the flanged tubes as specified in revision 1 and revision 2 of
service bulletins 767-27-0204 and 767-27-0205.
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.
G. Manpower
The applicable 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.
Group 1, Configuration 2; Group 2, Configuration 1:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.750.751Figure 1
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Group 1, Configuration 2; Group 2, Configuration 1:
Elapsed HoursTask HoursNumber of PersonsTask
0.300.301Clean Seal Block
Tubes
1.501.501Figure 4
1.001.001Figure 6
1.001.001Appendix A
0.500.501Close Access
5.555.55TOTAL FOR EACH AIRPLANE
Group 1, Configuration 3; Group 2, Configuration 2:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.750.751Figure 1
1.001.001Figure 2
0.300.301Clean Seal Block
Tubes
1.501.501Figure 4
1.001.001Figure 6
1.001.001Appendix A
0.500.501Close Access
6.556.55TOTAL FOR EACH AIRPLANE
Group 1, Configuration 4; Group 2, Configuration 3; Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.750.751Figure 1
1.001.001Figure 3
0.300.301Clean Seal Block
Tubes
1.501.501Figure 4
1.001.001Figure 6
1.001.001Appendix A
0.500.501Close Access
6.556.55TOTAL FOR EACH AIRPLANE
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Group 1, Configuration 1:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.750.751Figure 1
0.300.301Clean Seal Block
Tubes
1.101.101Figure 5
1.001.001Figure 6
1.001.001Appendix A
0.500.501Close Access
5.155.15TOTAL FOR EACH AIRPLANE
Group 4, Configuration 2:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.750.751Figure 7
0.300.301Clean Seal Block
Tubes
1.501.501Figure 8
1.001.001Figure 10
1.001.001Appendix A
0.500.501Close Access
5.555.55TOTAL FOR EACH AIRPLANE
Group 4, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.750.751Figure 7
1.001.001Figure 2
0.300.301Clean Seal Block
Tubes
1.501.501Figure 8
1.001.001Figure 10
1.001.001Appendix A
0.500.501Close Access
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Group 4, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
6.556.55TOTAL FOR EACH AIRPLANE
Group 4, Configuration 4:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.750.751Figure 7
1.001.001Figure 3
0.300.301Clean Seal Block
Tubes
1.501.501Figure 8
1.001.001Figure 10
1.001.001Appendix A
0.500.501Close Access
6.556.55TOTAL FOR EACH AIRPLANE
Group 4, Configuration 1:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.750.751Figure 7
0.300.301Clean Seal Block
Tubes
1.101.101Figure 9
1.001.001Figure 10
1.001.001Appendix A
0.500.501Close Access
5.155.15TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Group 1, Configuration 2; Group 2, Configuration 1; Group 4, Configuration 2:
None.
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Group 1, Configuration 3; Group 2, Configuration 2; Group 4, Configuration 3:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
-137.5-0.1767-200
-148.9-0.1767-300, 767-300F
-159.5-0.1767-400ER
Group 1, Configuration 4; Group 2, Configuration 3; Group 3; Group 4, Configuration
4:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
-168.6-0.1767-200
-182.7-0.1767-300, 767-300F
-195.6-0.1767-400ER
Group 1, 4, Configuration 1:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+174.4+0.11767-200
+188.8+0.11767-300, 767-300F
+202.3+0.11767-400ER
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Engineering Change Memo PRR B12901-99RS
b. Boeing Service Bulletin 767-25A0322 , 767-25A0323 , 767-27-0204, 767-27-0205,
767-27A0192, 767-27A0193, 767-27A0219, 767-27A0224
c. Boeing Service Letter 767-SL-51-036
d. Boeing Service Related Problem (SRP) 767-SRP-27-0208
e. Standard Overhaul Practices Manual (SOPM) 20-50-12
f. 767 Aircraft Maintenance Manual (AMM) 06-42-00, 24-22-00, 29-11-00
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g. 767 Fleet Team Digest (FTD) 27-05002
h. 767-400 Aircraft Maintenance Manual (AMM) 06-42-00, 24-22-00, 29-11-00
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
Pressure Seal Instl - Pressure Dome STA 1582.0255T4821
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
20-10767 Aircraft Maintenance Manual
27-21767 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 does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits 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 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
Group 1, Configuration 2-4; Group 2-3; Group 4, Configuration 2-4:
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)
QTYDateNameKit Number
$261.00281101-Mar-2011TOP KIT - Seal Tube
Installation, Elevator
Control Cable
015T1855-1
4902-May-2011
Group 1, 4, Configuration 1:
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
$252.00281TOP KIT - Seal Tube Installation, Elevator
Control Cable
015T1855-2
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.
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NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane. Select the kit that is applicable to the
airplane by group/configuration as specified in Paragraph 2.A., Material - Price and
Availability.
Kit 015T1855
NotesExisting Part
Number
NameQTYNew Part Number
-2-1
Group 1, Configuration
2-4; Group 2-3; Group
4, Configuration 2-4
TOP KIT - Seal
Tube Installation,
Elevator Control
Cable
.-015T1855-1
Group 1, Configuration
1; Group 4, Configura-
tion 1
TOP KIT - SEAL
TUBE INSTALLA-
TION, ELEVATOR
CONTROL CABLE
-.015T1855-2
(a) (c)66-20184-1HALF TUBE - 1/8
DIA CABLE PRES-
SURE SEAL
22255T4858-3
(a) (c)66-20184-1HALF TUBE - 1/8
DIA CABLE PRES-
SURE SEAL
22255T4858-4
(b) (f)CLAMP, LOOP.2AN735-16
(b) (d) (f)NUT.3BACN10YR3CD
(b) (e) (f)BOLT.2BACS12HN3-10
(BACS12HN3-9
optional)
(b) (d) (f)WASHER.10NAS1149C0332R
(b) (d) (f)WASHER.3NAS1149C0363R
(a) Discard the existing part. Keep the existing part if there are other uses for it.
(b) This part is not used for Production
(c) You cannot use the existing part to replace the new or changed part
(d) There are more parts than are necessary
(e) If the fastener grip length shown is not available at Boeing, fasteners supplied in kits may be
one grip length longer than specified.
(f) If the part number listed is not available or has been superseded, a substitute part may be
supplied in kits. Boeing Document D-590 and Boeing Drawing 012W6100 is used to determine
the part numbers used as substitutes.
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2. Parts and Materials Supplied by the Operator
NotesExisting Part NumberNameQTYPart Number /
Specification
(a)-SEALANT-BMS 5-95
(a)-ADHESIVEBMS 5-45, CLASS
B (BMS 5-92,
TYPE 5 optional)
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier
data.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
Group 1, Configuration 1-2; Group 2, 4, Configuration 1; Group 4, Configuration 2:
None.
Group 1, Configuration 3; Group 2, Configuration 2; Group 4, Configuration 3:
NotesQTYNameExisting Part
Number
1TUBE, FLANGED148T2747-7
1TUBE, FLANGED148T2747-8
Group 1, Configuration 4; Group 2, Configuration 3; Group 3; Group 4, Configuration 4:
NotesQTYNameExisting Part
Number
2TUBE, FLANGED148T2747-7
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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BLANK PAGE

### Page 33

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. The work instructions are divided into work packages. Task Hours and Elapsed Hours
for each package are given in Paragraph 1.G., Manpower. You can do each work
package independently.
4. 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 are in Structural Repair Manual (SRM)
Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
5. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51. Alternate fasteners are listed in SRM Chapter 51 and Boeing
Drawing 012W6100.
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.
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.
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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.
The removed part can be discarded if a new or serviceable part is installed.
12. 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.
B. WORK INSTRUCTIONS
1. Open door 312AR to get access to the aft pressure bulkhead. Refer to 767 AMM 06-42-00 or
767-400 AMM 06-42-00 as an accepted procedure.
2. Group 1-3:
On the aft pressure bulkhead, remove two pressure seal assemblies in accordance with FIGURE
1.
NOTE: It is acceptable if the control cable touches the seal block tube when the seal assembly
is removed.
3. Group 4:
On the aft pressure bulkhead, remove two pressure seal assemblies in accordance with FIGURE
7.
NOTE: It is acceptable if the control cable touches the seal block tube when the seal assembly
is removed.
4. Group 1, Configuration 3; Group 2, Configuration 2; Group 4, Configuration 3:
Remove the two flanged tubes from the tubes in the seal block in accordance with FIGURE 2.
5. Group 1, Configuration 4; Group 2, Configuration 3; Group 3; Group 4, Configuration 4:
Remove the two flanged tubes from the tubes in the seal block in accordance with FIGURE 3
6. Clean the two seal block tubes. Use a brush that will not cause damage to plastic surfaces or
control cables. As an alternative, you can use a lint free cloth.
7. Group 1, Configuration 2-4; Group 2-3:
Assemble a new pressure seal assembly and install a new clamp over the drain hole for each of
the two seal block tubes in accordance with FIGURE 4.
8. Group 4, Configuration 2-4:
Assemble a new pressure seal assembly and install a new clamp over the drain hole for each of
the two seal block tubes in accordance with FIGURE 8.
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9. Group 1, Configuration 1:
Assemble a new pressure seal assembly for each of the two seal block tubes in accordance with
FIGURE 5.
10. Group 4, Configuration 1:
Assemble a new pressure seal assembly for each of the two seal block tubes in accordance with
FIGURE 9.
11. Group 1-3:
After the adhesive on the pressure seal assembly has cured, install the new pressure seal assembly
in accordance with FIGURE 6.
12. Group 4:
After the adhesive on the pressure seal assembly has cured, install the new pressure seal assembly
in accordance with FIGURE 10.
13. Do the Elevator Control Cables Operational Test to make sure that the elevator control cables
move smoothly through the new pressure seal assemblies. Refer to APPENDIX A as an accepted
procedure.
14. Close access to the aft pressure bulkhead.
15. Put the airplane back to its usual condition.
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BOEING SERVICE BULLETIN 767-27A0224

### Page 36 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
This Figure applies only to: Group 1-3.
STA
1582
PRESSURE
BULKHEAD
2038193
FIGURE 1: AFT PRESSURE BULKHEAD - REMOVE THE PRESSURE SEAL ASSEMBLIES
(SHEET 1 OF 3)
Original Issue: June 23, 2011
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
STA
1605
STA
1629
ELEVATOR
CONTROL
CABLE E1AÙ
PRESSURE
ELEVATOR  BULKHEAD
CONTROL
CABLE E1B
• FWD
STRINGER 20 -
STRINGER 22
DUCT LEAK
DETECTOR
LOOPS
CABLES
FWD
2038215
FIGURE 1: AFT PRESSURE BULKHEAD - REMOVE THE PRESSURE SEAL ASSEMBLIES
(SHEET 2 OF 3)
Original Issue: June 23, 2011
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### Page 38

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 this figure.
More DataQtyIdentificationNameTaskStep
4-NUTRemove / Keep1
8-WASHERRemove / Keep
4-BOLTRemove / Keep
This part stays on its
elevator control ca-
ble.
2-SEAL COVERRemove / Keep
This part stays on its
elevator control ca-
ble.
2-SEAL PLATERemove / Keep
466-20184-1BALL-HALFRemove
FIGURE 1: AFT PRESSURE BULKHEAD - REMOVE THE PRESSURE SEAL ASSEMBLIES
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 767-27A0224

### Page 39 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
This Figure applies only to: Group 1, Configuration 3; Group 2, Configuration 2; Group 4, Configuration
3.
STA
1582
STA
1605
STA
1629
ELEVATOR
CONTROL
CABLE E1A
PRESSURE
BULKHEAD
ELEVATOR
CONTROL
CABLE E1B
STRINGER 20 -
STRINGER 22
2038484
FIGURE 2: AFT PRESSURE BULKHEAD - REMOVE THE FLANGED TUBES
(SHEET 1 OF 3)
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### Page 40

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 this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Pull this part out of
the bulkhead seal
block.
1148T2747-7TUBE, FLANGEDPull1
CAUTION: PROTECT THE ELEVATOR CONTROL CABLE FROM THE CUTTER. A DAMAGED CONTROL
CABLE MUST BE REPLACED.
Make a lengthwise
cut through the tube
wall. The tube mate-
rial is plastic.
1148T2747-7TUBE, FLANGEDCut2
1148T2747-7TUBE, FLANGEDRemove3
Pull this part out of
the bulkhead seal
block.
1148T2747-8TUBE, FLANGEDPull4
FIGURE 2: AFT PRESSURE BULKHEAD - REMOVE THE FLANGED TUBES
(SHEET 2 OF 3)
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BOEING SERVICE BULLETIN 767-27A0224

### Page 41

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
CAUTION: PROTECT THE ELEVATOR CONTROL CABLE FROM THE CUTTER. A DAMAGED CONTROL
CABLE MUST BE REPLACED.
Make a lengthwise
cut through the tube
wall. The tube mate-
rial is plastic.
1148T2747-8TUBE, FLANGEDCut5
1148T2747-8TUBE, FLANGEDRemove6
FIGURE 2: AFT PRESSURE BULKHEAD - REMOVE THE FLANGED TUBES
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 767-27A0224

### Page 42 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
This Figure applies only to: Group 1, Configuration 4; Group 2, Configuration 3; Group 3; Group 4,
Configuration 4.
STA
1582
STA
1605
STA
1629
ELEVATOR
CONTROL
CABLE E1A
PRESSURE
BULKHEAD
ELEVATOR
CONTROL
CABLE E1B
STRINGER 20 •
STRINGER 22
2038561
FIGURE 3: AFT PRESSURE BULKHEAD - REMOVE THE FLANGED TUBES
(SHEET 1 OF 2)
Original Issue: June 23, 2011
Revision 1 December 16, 2011  767-27A0224
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### Page 43

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 this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Pull this part out of
the bulkhead seal
block.
2148T2747-7TUBE, FLANGEDPull1
CAUTION: PROTECT THE ELEVATOR CONTROL CABLE FROM THE CUTTER. A DAMAGED CONTROL
CABLE MUST BE REPLACED.
Make a lengthwise
cut through the tube
wall. The tube mate-
rial is plastic.
2148T2747-7TUBE, FLANGEDCut2
2148T2747-7TUBE, FLANGEDRemove3
FIGURE 3: AFT PRESSURE BULKHEAD - REMOVE THE FLANGED TUBES
(SHEET 2 OF 2)
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BOEING SERVICE BULLETIN 767-27A0224

### Page 44 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
This Figure applies only to: Group 1, Configuration 2-4; Group 2-3.
STA
1582
STA
1605
STA
1629
AND D
ELEVATOR
CONTROL
CABLE E1A
PRESSURE
BULKHEAD
ELEVATOR
CONTROL
CABLE E1B
STRINGER 20
STRINGER 22 •
2038635
FIGURE 4: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES AND INSTALL
CLAMPS
(SHEET 1 OF 7)
Original Issue: June 23, 2011
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### Page 45 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
B 2 LOCATIONS  SEAL PLATE
SEAL
COVER
2038781
FIGURE 4: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES AND INSTALL
CLAMPS
(SHEET 2 OF 7)
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### Page 46

FIGURE 4: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES AND INSTALL
CLAMPS
(SHEET 3 OF 7)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
EQ
WASHER
WASHER
BOLT
• BOLT
DRAIN
HOLE
INBD  CLAMP
C-C  2039026
FIGURE 4: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES ANDINSTALL
CLAMPS
(SHEET 4 OF 7)
Original Issue: June 23, 2011
Revision 1 December 16, 2011  767-27 A0224
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### Page 48

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 this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Use an abrasive to
make scratches on
the two faces of the
slot area shown. 80-
grit is recommend-
ed. (a)
2255T4858-3HALF TUBE - 1/8 DIA
CABLE PRESSURE
SEAL
Prepare1
Use an abrasive to
make scratches on
the area shown. 80-
grit is recommend-
ed. (a)
2255T4858-4HALF TUBE - 1/8 DIA
CABLE PRESSURE
SEAL
Prepare2
Put this half on its
control cable. Make
sure that the Seal
Plate is forward of
this half tube. Make
sure that the Seal
Cover is aft of this
half tube.
2255T4858-3HALF TUBE - 1/8 DIA
CABLE PRESSURE
SEAL
Install (New)3
Put this half into its
mating half. Leave a
clearance of 0.11 +/-
0.01 inch as shown
in the illustration.
2255T4858-4HALF TUBE - 1/8 DIA
CABLE PRESSURE
SEAL
Install (New)
Apply adhesive to fill
the open slots as
shown in the illustra-
tion. (b)
-BMS 5-45, CLASS B
(BMS 5-92, TYPE 5
optional)
ADHESIVEApply4
Push the half into its
mating half to align
the spherical sur-
faces. Adhesive will
come out of the
seam.
-255T4858-4HALF TUBE - 1/8 DIA
CABLE PRESSURE
SEAL
Align5
Fill the groove along
each pressure seal
assembly. (b)
-BMS 5-45, CLASS B
(BMS 5-92, TYPE 5
optional)
ADHESIVEApply6
FIGURE 4: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES AND INSTALL
CLAMPS
(SHEET 5 OF 7)
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BOEING SERVICE BULLETIN 767-27A0224

### Page 49

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove unwanted
adhesive from the
outer surfaces of
each pressure seal
assembly.
--PRESSURE SEAL AS-
SEMBLY
Clean7
Apply a thin layer to
the mating surface
of the clamp.
-BMS 5-95SEALANTApply8
Make sure that the
band of the clamp
covers the drain
hole.
1AN735-16CLAMP, LOOPInstall (New)
Use Qty 0 to 3
washers to adjust
the clamp for the
best fit to the tube.
3NAS1149C0332RWASHERInstall (New)
1BACS12HN3-10
(BACS12HN3-9 option-
al)
BOLTInstall (New)
1NAS1149C0363RWASHERInstall (New)
1BACN10YR3CDNUTInstall (New)
Apply a thin layer to
the mating surface
of the clamp.
-BMS 5-95SEALANTApply9
Make sure that the
band of the clamp
covers the drain
hole.
1AN735-16CLAMP, LOOPInstall (New)
Use Qty 0 to 3
washers to adjust
the clamp for the
best fit to the tube.
3NAS1149C0332RWASHERInstall (New)
1BACS12HN3-10
(BACS12HN3-9 option-
al)
BOLTInstall (New)
1NAS1149C0363RWASHERInstall (New)
1BACN10YR3CDNUTInstall (New)
(a) This step makes a better adhesive bond.
FIGURE 4: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES AND INSTALL
CLAMPS
(SHEET 6 OF 7)
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BOEING SERVICE BULLETIN 767-27A0224

### Page 50

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(b) Refer to SOPM 20-50-12 as an accepted procedure for adhesive mixing and surface cleaning. The appli-
cable instructions in SOPM 20-50-12 are for Type 44 (BMS 5-45, Class B), or Type 117 (BMS 5-92, Type
5) adhesive as applied to acetal thermoplastic surfaces.
The parts shown in the table below are provided as extra parts for this figure.
MORE DATAQTYIDENTIFICATIONNAME
1BACN10YR3CDNUT
4NAS1149C0332RWASHER
1NAS1149C0363RWASHER
FIGURE 4: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES AND INSTALL
CLAMPS
(SHEET 7 OF 7)
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Original Issue: June 23, 2011
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50 of 78
BOEING SERVICE BULLETIN 767-27A0224

### Page 51 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
This Figure applies only to: Group 1, Configuration 1.
STA
1582
STA
1605
STA
1629
ELEVATOR
CONTROL
CABLE E1A
‚ PRESSURE
BULKHEAD
ELEVATOR
CONTROL
CABLE E1B
STRINGER 20 -
STRINGER 22
FIGURE 5: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES
(SHEET 1 OF 4)
Original Issue: June 23, 2011
Revision 1 December 16, 2011  767-27A0224
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### Page 52 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
B 2 LOCATIONS  SEAL PLATE
SEAL
COVER
SEAL PLATE
2 LOCATIONS
2038803
FIGURE 5: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES
(SHEET 2 OF 4)
Original Issue: June 23, 2011
Revision 1 December 16, 2011  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  52 of 78

### Page 53

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 this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Use an abrasive to
make scratches on
the two faces of the
slot area shown. 80-
grit is recommend-
ed. (a)
2255T4858-3HALF TUBE - 1/8 DIA
CABLE PRESSURE
SEAL
Prepare1
Use an abrasive to
make scratches on
the area as shown.
80-grit is recom-
mended. (a)
2255T4858-4HALF TUBE - 1/8 DIA
CABLE PRESSURE
SEAL
Prepare2
Put this half on its
control cable. Make
sure that the Seal
Plate is forward of
this half tube. Make
sure that the Seal
Cover is aft of this
half tube.
2255T4858-3HALF TUBE - 1/8 DIA
CABLE PRESSURE
SEAL
Install (New)3
Put this half into its
mating half. Leave a
clearance of 0.11 +/-
0.01 inch as shown
in the illustration.
2255T4858-4HALF TUBE - 1/8 DIA
CABLE PRESSURE
SEAL
Install (New)
FIGURE 5: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES
(SHEET 3 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 23, 2011
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53 of 78
BOEING SERVICE BULLETIN 767-27A0224

### Page 54

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Apply adhesive to fill
the open slots as
shown in the illustra-
tion. (b)
-BMS 5-45, CLASS B
(BMS 5-92, TYPE 5
optional)
ADHESIVEApply4
Push the half into its
mating half to align
the spherical sur-
faces. Adhesive will
come out of the
seam.
-255T4858-4HALF TUBE - 1/8 DIA
CABLE PRESSURE
SEAL
Align5
Fill the groove along
each pressure seal
assembly. (b)
-BMS 5-45, CLASS B
(BMS 5-92, TYPE 5
optional)
ADHESIVEApply6
Remove unwanted
adhesive from the
outer surfaces of
each pressure seal
assembly.
--PRESSURE SEAL AS-
SEMBLY
Clean7
(a) This step makes a better adhesive bond.
(b) Refer to SOPM 20-50-12 as an accepted procedure for adhesive mixing and surface cleaning. The appli-
cable instructions in SOPM 20-50-12 are for Type 44 (BMS 5-45, Class B), or Type 117 (BMS 5-92, Type
5) adhesive as applied to acetal thermoplastic surfaces.
FIGURE 5: AFT PRESSURE BULKHEAD - ASSEMBLE NEW PRESSURE SEAL ASSEMBLIES
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 23, 2011
767-27A0224Revision 1 December 16, 2011
54 of 78
BOEING SERVICE BULLETIN 767-27A0224

### Page 55 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
This Figure applies only to: Group 1-3.
STA
1582
STA
1605
STA
1629
ELEVATOR
CONTROL
CABLE E1A
‚ PRESSURE
BULKHEAD
ELEVATOR
CONTROL
CABLE E1B
STRINGER 20 -
STRINGER 22
2044918
FIGURE 6: AFT PRESSURE BULKHEAD - INSTALL NEW PRESSURE SEAL ASSEMBLIES
(SHEET 1 OF 4)
Original Issue: June 23, 2011
Revision 1 December 16, 2011  767-27A0224
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### Page 56 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
SEAM  135°
45°
SEAL GROOVE
A-A
NUT
WASHER
FLANGED
TUBE
PRESSURE
SEAL
ASSEMBLY
SEAM
SEAL
COVER
WASHER  NUT
WASHER
BOLT
SEA
PLATI
CONTROL
GABLE
TEND
2 LOCATIONS
BOLT  WASHER  2044936
FIGURE 6: AFT PRESSURE BULKHEAD - INSTALL NEW PRESSURE SEAL ASSEMBLIES
(SHEET 2 OF 4)
Original Issue: June 23, 2011
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### 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 this figure.
More DataQtyIdentificationNameTaskStep
1-SEAL PLATEInstall (Kept)1
Make sure that the
groove with adhe-
sive points down.
Make sure that the
seam of the ball is in
a horizontal position
as specified in the il-
lustration.
1-PRESSURE SEAL AS-
SEMBLY
Align
1-PRESSURE SEAL AS-
SEMBLY
Insert
1-SEAL COVERInstall (Kept)
4-WASHERInstall (Kept)
2-BOLTInstall (Kept)
Do not tighten the
nut. Leave it loose
on the bolt.
2-NUTInstall (Kept)
Adjust the washers
to give the minimum
cable deflection.
4-WASHERAdjust2
2-BOLTTighten3
FIGURE 6: AFT PRESSURE BULKHEAD - INSTALL NEW PRESSURE SEAL ASSEMBLIES
(SHEET 3 OF 4)
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57 of 78
BOEING SERVICE BULLETIN 767-27A0224

### Page 58

More DataQtyIdentificationNameTaskStep
1-SEAL PLATEInstall (Kept)4
Make sure that the
groove with adhe-
sive points down.
Make sure that the
seam of the ball is in
a horizontal position
as specified in the il-
lustration.
1-PRESSURE SEAL AS-
SEMBLY
Align
1-PRESSURE SEAL AS-
SEMBLY
Insert
1-SEAL COVERInstall (Kept)
4-WASHERInstall (Kept)
2-BOLTInstall (Kept)
Do not tighten the
nut. Leave it loose
on the bolt.
2-NUTInstall (Kept)
Adjust the washers
to give the minimum
cable deflection.
4-WASHERAdjust5
2-BOLTTighten6
FIGURE 6: AFT PRESSURE BULKHEAD - INSTALL NEW PRESSURE SEAL ASSEMBLIES
(SHEET 4 OF 4)
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Original Issue: June 23, 2011
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58 of 78
BOEING SERVICE BULLETIN 767-27A0224

### Page 59 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
This Figure applies only to: Group 4.
STA
1582
PRESSURE
BULKHEAD
2115185
FIGURE 7: AFT PRESSURE BULKHEAD - REMOVE THE PRESSURE SEAL ASSEMBLIES
(SHEET 1 OF 4)
Original Issue: June 23, 2011
Revision 1 December 16, 2011  BOEING PROPRIETARY -  767-27A0224
Copyright © Unpublished Work - See page 1 for details.  59 of 78

### Page 60 (OCR)

BOEING SERVICE BULLETIN 767-27A0224
STA
1605
STA
1629
ELEVATOR
CONTROL
CABLE E1A
PRESSURE
ELEVATOR  BULKHEAD
CONTROL
CABLE E1B
STRINGER 20 •
STRINGER 22 •
DUCT LEAK
DETECTOR
LOOPS
LA
CABLES
FWD
2115188
FIGURE 7: AFT PRESSURE BULKHEAD - REMOVE THE PRESSURE SEAL ASSEMBLIES
(SHEET 2 OF 4)
Original Issue: June 23, 2011
Revision 1 December 16, 2011  767-27A0224
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