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Commercial Airplanes 777 Service Bulletin Number: 777-55A0015 Original Issue: April 19, 2007 Revision 3: November 24, 2009 ATA System: 5527 SUBJECT: STABILIZERS - Elevator Attach Fittings - Elevator Actuator Fitting Assembly Inspection 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BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 1 of 36
6.0
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 2 of 36 BOEING SERVICE BULLETIN 777-55A0015
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Table of Contents
Revision Transmittal Sheet5
Summary7
1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 4 B. Concurrent Requirements ...................................... 1 4 C. Reason ................................................ 1 4 D. Description .............................................. 1 5 E. Compliance .............................................. 1 6 F. Approval ............................................... 1 8 G. Manpower .............................................. 1 9 H. Weight and Balance Changes .................................... 1 9 I. Electrical Load Data ......................................... 1 9 J. References .............................................. 2 0
1. Existing Data: ......................................... 2 0
2. Data supplied with this Service Bulletin: ........................... 2 0
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 0 K. Publications Affected ........................................ 2 0 L. Interchangeability and Intermixability of Parts ........................... 2 0
2. MATERIAL INFORMATION ........................................ 2 1 A. Material - Price and Availability ................................... 2 1 B. Industry Support Information .................................... 2 1 C. Parts Necessary For Each Airplane ................................. 2 1
1. Kits/Parts: ........................................... 2 1
2. Parts and Materials Supplied by the Operator: ........................ 2 1
3. Parts Modified and Reidentified: ............................... 2 2
4. Parts Removed and Not Replaced: .............................. 2 2 D. Parts Necessary to Change Spares ................................. 2 2 E. Special Tooling - Price and Availability ............................... 2 2 F. Special Tooling Necessary to do this Service Bulletin ....................... 2 2
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3 A. GENERAL INFORMATION ..................................... 2 3 B. WORK INSTRUCTIONS ....................................... 2 4 FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION .................. 2 9 FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION ................. 3 3
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 3 of 36 BOEING SERVICE BULLETIN 777-55A0015
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Commercial Airplanes 777 Service Bulletin Revision Transmittal SheetNumber: 777-55A0015Original Issue: April 19, 2007 Revision 3: November 24, 2009 ATA System: 5527 SUBJECT: STABILIZERS - Elevator Attach Fittings - Elevator Actuator Fitting Assembly Inspection This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION No more work is necessary on airplanes changed as shown in the original issue, Revision 1, or Revision 2 of this service bulletin.
No airplanes were added to the service bulletin effectivity.
Federal Aviation Administration (FAA) Airworthiness Directive 2007-26-05, Amendment 39-15307, is related to this service bulletin.
REASON FOR REVISION This revision is sent to clarify the access and restoration instructions; and clarify the words "date on this service bulletin" and provide terminating action information in the compliance tables.
These sections were changed:
1. In Table 1 of Paragraph 1.E., Compliance, the words "date on this service bulletin" was changed to "original issue date of this service bulletin."
2. In Tables 1 and 2 of Paragraph 1.E., Compliance, terminating action information for the inspection requirements as given in this service bulletin was added. Also clarified the action "Replace any cracked fitting" and condition "Replaced Fittings" by referencing Paragraph 3.B., PART 4.
3. In Paragraph 1.J., References, added 777 Aircraft Maintenance Manual (AMM) 12-12-01 and 27-31-09.
Deleted the reference 777 AMM 55-27-01. Also added Boeing Service Bulletin 777-55A0016.
4. In Paragraph 1.K., Publications Affected, damage tolerance evaluation statement was added.
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Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 5 of 36
5. In Paragraph 3.A., General Information, added a note to give an option to change the sequence of steps in Paragraph 3.B., Work Instructions.
6. In Paragraph 3.B., Work Instructions, the words "refer to" are added and deleted the words "as given in" to address PART 3 and PART 5.
7. In PART 3 and PART 5 of Paragraph 3.B., Work Instructions, procedure from 777 AMM 27-31-09 was added to clarify the access and restoration instructions to have the elevator in the "up" position instead of "down" position. Also rearranged access and restoration instructions to have the access panel removed first for access and installed last for restoration.
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 April 19, 2007Original Issue:
January 31, 2008Revision 1:
December 04, 2008Revision 2:
November 24, 2009Revision 3:
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Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 6 of 36 BOEING SERVICE BULLETIN 777-55A0015
Commercial Airplanes 777 Service Bulletin SummaryNumber: 777-55A0015Original Issue: April 19, 2007 Revision 3: November 24, 2009 ATA System: 5527 SUBJECT: STABILIZERS - Elevator Attach Fittings - Elevator Actuator Fitting Assembly Inspection
CONCURRENT REQUIREMENTS None.
BACKGROUND This service bulletin gives instructions to do surface High Frequency Eddy Current (HFEC) or dye penetrant inspections of the elevator actuator fittings at left and right Elevator Stations 169.79 and 194.79 for cracks.
Cracked actuator fittings may lack adequate residual strength to react flight loads. Cracked actuator fittings can become detached from the elevator, resulting in an unrestrained elevator. An unrestrained elevator is an unacceptable flutter condition which can result in a loss of airplane control.
One operator has told Boeing that a cracked left outboard actuator fitting was found on a 777 airplane with 17,346 flight-hours and 14,043 flight-cycles. The crack extended through the lower inboard flange of the fitting and into the vertical flange. Analysis by Boeing indicates that this crack resulted from fatigue due to higher than anticipated stress levels in the fitting flanges.
Accomplishment of the inspections shown in this service bulletin will make sure that fatigue cracks in the elevator actuator support fittings are found and cracked fittings replaced before the actuator fittings can become detached from the elevator.
Boeing Service Related Problem (SRP) 777-SRP-55-0040 is related to this service bulletin.
ACTION Get access to the elevator actuator fittings at left and right Elevator Stations 169.79 and 194.79. Do surface High Frequency Eddy Current (HFEC) or dye penetrant inspections of the actuator fittings for cracks. If cracks are found, replace the cracked fittings with new fittings of the same part number or an approved optional part number. Do the inspections again at the times given in Paragraph 1.E., Compliance.
EFFECTIVITY 777-200, 777-200LR, 777-300 and 777-300ER airplanes. Refer to Paragraph 1.A., Effectivity, for the list of affected airplanes.
COMPLIANCE See Service Bulletin Paragraph 1.E. for compliance information.
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Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 7 of 36
Federal Aviation Administration (FAA) Airworthiness Directive 2007-26-05, Amendment 39-15307 is related to this service bulletin.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are available for airplanes in warranty as of November 17, 2006. Please refer to Paragraph 2.B., Industry Support Information.
MANPOWER Elapsed HoursTotal Task HoursAirplanes
4.759.5All - Initial Inspection
4.759.5All - Repeat Inspection
MATERIAL INFORMATION None.
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Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 8 of 36 BOEING SERVICE BULLETIN 777-55A0015
BOEING SERVICE BULLETIN 777-55A0015 ELEV STA
194.79
SEE A ELEV STA
169.79
INBD & FWD
ACTUATOR
FITTINGS
ACTUATOR LEFT ELEVATOR SHOWN
FITTING RIGHT ELEVATOR OPPOSITE
TYPICAL
CRACK ELEVATOR
DO SURFACE EDDY CURRENT INSPECTIONS OF THE FITTING RADIUS (8 LOCATIONS PER FITTING) FOR CRACKS. REPLACE CRACKED FITTINGS AND
REPEAT INSPECTIONS AT THE TIMES SHOWN IN
THIS SERVICE BULLETIN FWD TYPICAL ACTUATOR FITTING 1350358
FOUR LOCATIONS PER AIRPLANE Original Issue: April 19, 2007 Revision 3: November 24, 2009 777-55A0015 Copyright © Unpublished Work - See page 1 for details. BOEING PROPRIETARY - 9 of 36
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Commercial Airplanes 777 Service Bulletin Number: 777-55A0015 Original Issue: April 19, 2007 Revision 3: November 24, 2009 ATA System: 5527 SUBJECT: STABILIZERS - Elevator Attach Fittings - Elevator Actuator Fitting Assembly Inspection
1. PLANNING INFORMATION A. Effectivity
1. Airplanes This service bulletin is for the airplanes shown below.
Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP All 777-200 airplanes line number 1 through 40.-1 777-200, 777-200LR, 777-300, and 777-300ER airplanes line number 41 to 717.
-2 Airplane Models:
777-200, 777-200LR, 777-300, 777-300ER GroupVariable Number 1WA001 - WA017 1WA076 - WA080 1WA086 - WA087 2WA088 - WA093 1WA101 - WA104 1WA116 - WA117 2WA118 - WA119 1WA131 - WA135 2WA136 - WA137
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GroupVariable Number 1WA171 - WA173 2WA174 - WA175 1WA196 - WA197 2WA198 2WA206 - WA212 2WA221 - WA223 2WA231 - WA232 2WA241 - WA250 2WA261 - WA266 2WA281 - WA283 2WA301 - WA304 2WB001 - WB021 2WB031 - WB046 2WB051 - WB088 2WB101 - WB106 2WB121 - WB125 2WB131 - WB147 2WB151 - WB155 2WB161 - WB177 2WB181 - WB194 2WB201 - WB215 2WB231 - WB247 2WB271 - WB273 2WB276 - WB286 2WB291 - WB302 2WB306 - WB307 2WB311 - WB337 2WB341 - WB342 2WB366 - WB368 2WB371 - WB388 2WB406 2WB411 - WB413 2WB416 - WB439
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