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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 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BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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 Boeing livery 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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Original Issue: June 23, 2011 767-27A0224Revision 1: December 16, 2011 1 of 78
2.0
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 23, 2011 767-27A0224Revision 1: December 16, 2011 2 of 78 BOEING SERVICE BULLETIN 767-27A0224
BLANK PAGE
Table of Contents
Revision Transmittal Sheet5
Summary9
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, Configuration 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 Original Issue: June 23, 2011 Revision 1: December 16, 2011 Copyright © Unpublished Work - See page 1 for details. BOEING PROPRIETARY - 767-27A0224 12 of 78