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Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 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all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 1 of 36 6.0 ### Page 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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 BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 Summary ...................................................... 7 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 ### Page 4 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 4 of 36 BOEING SERVICE BULLETIN 777-55A0015 BLANK PAGE ### Page 5 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 5 of 36 ### Page 6 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: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 6 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 7 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 7 of 36 ### Page 8 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 8 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 9 (OCR) 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 ### Page 10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 10 of 36 BOEING SERVICE BULLETIN 777-55A0015 BLANK PAGE ### Page 11 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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 11 of 36 ### Page 12 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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 12 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 13 GroupVariable Number 2WB446 - WB453 2WB476 2WB481 - WB484 2WB501 - WB512 2WB531 - WB537 2WB551 - WB554 2WB591 - WB597 2WB601 - WB606 2WB611 - WB622 2WB631 - WB638 2WB646 - WB649 2WC051 - WC073 2WC101 - WC104 2WC111 - WC119 2WC221 - WC222 2WC241 - WC243 2WC281 - WC290 2WC301 - WC308 2WC361 - WC364 2WC371 - WC374 2WC381 - WC395 2WC441 2WC446 - WC449 2WC456 - WC459 2WC486 - WC493 2WC506 - WC508 2WC521 - WC522 2WC531 - WC536 2WC546 - WC548 2WC556 2WC566 - WC567 2WD001 - WD002 2WD011 - WD015 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 13 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 14 GroupVariable Number 2WD031 - WD036 2WD046 - WD049 2WD066 - WD067 2WD501 - WD507 2WD521 - WD538 2WD546 - WD552 2WD561 - WD572 2WD581 - WD594 2WD606 - WD609 2WD621 - WD632 2WD651 - WD659 2WD671 - WD675 2WD691 - WD706 2WD741 - WD748 2WD761 - WD770 2WD786 - WD788 2WD796 - WD802 2WD826 - WD829 2WD846 - WD849 2WD871 - WD872 2WD911 - WD912 2. Spares Affected None. B. Concurrent Requirements None. C. Reason 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 14 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 15 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. Revision 1 was sent to clarify the areas of the fitting to be inspected. Figures 1 and 2 were changed to show the inspection area. In addition, references to FAA NPRM 2007-NM-109-AD have been added. Revision 2 was sent to remove airplanes after line number 717 from the service bulletin effectivity. The inspections shown in this service bulletin are not necessary on airplanes line number 718 and on, which have redesigned elevator actuator fittings installed during production. Revision 3 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. 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. Boeing Service Related Problem (SRP) 777-SRP-55-0040 is related to this service bulletin. D. Description Get access to the elevator actuator fittings at left and right Elevator Stations 169.79 and 194.79. Do surface 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, Table 2. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 15 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 16 Airplanes line number 718 and on have redesigned elevator actuator fittings installed during production. Revision 3 - No more work is necessary on airplanes changed as shown in the original issue, Revision 1, or Revision 2 of this service bulletin. Continue to do repeat inspections as given in Revision 3. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 336, 346777-200 Group 2: Affected Maintenance Zones ZoneModel 336, 346777-200, 777-200LR, 777-300, 777-300ER E. Compliance Boeing recommends that the inspection given in this service bulletin be done at the times given in the table that follows: Table 1: Elevator Actuator Fitting Initial Inspection Compliance TimeAction (a)Condition Within 90 days after the original issue date of this service bulletin. Do a HFEC or dye-penetrant in- spection of the elevator actuator fittings for any crack as given in Paragraph 3.B., Part 1. All airplanes with 14,000 total flight- cycles or more as of the original is- sue date of this service bulletin Within 12 months after the original issue date of this service bulletin, or within 90 days after the air- plane reaches 14,000 total flight- cycles, whichever occurs first. Do a HFEC or dye-penetrant in- spection of the elevator actuator fittings for any crack as given in Paragraph 3.B., Part 1. All airplanes with 10,000 total flight- cycles or more, but less than 14,000 total flight-cycles, as of the original issue date of this service bulletin Before 10,000 total flight-cycles or within 12 months after the original issue date of this service bulletin, whichever occurs later. Do a HFEC or dye-penetrant in- spection of the elevator actuator fittings for any crack as given in Paragraph 3.B., Part 1. All airplanes with less than 10,000 total flight-cycles as of the original issue date of this service bulletin As given in Table 2Do a HFEC, dye-penetrant, or detailed inspection of uncracked elevator actuator fittings for any crack as given in Table 2. Fittings found not cracked during inspection BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 16 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 17 Table 1: Elevator Actuator Fitting Initial Inspection Compliance TimeAction (a)Condition Before further flight.Replace any cracked fitting with a new fitting of the same part number as given in Paragraph 3.B., Part 4. Fittings found cracked during inspec- tion As given in Table 2Do a HFEC, dye-penetrant, or detailed inspection of uncracked elevator actuator fittings for any crack as given in Table 2. Replaced cracked fitting with a new fitting of the same part number as given in Paragraph 3.B., Part 4. (a) Boeing Service Bulletin 777-55A0016 gives instructions to replace the existing elevator actuator fitting assemblies with a new and improved actuator fitting assemblies. As an alternative, accomplishment of Boeing Service Bulletin 777-55A0016 is terminating action for the inspection requirements as given in this service bulletin. Table 2: Elevator Actuator Fitting Repeat Inspections Repeat Interval (Not to Exceed) Compliance TimeAction (c)Condition -Within 1,200 flight- cycles after the ini- tial inspection given in Table 1. Do a HFEC, dye penetrant, or detailed inspection of the elevator actuator fit- tings for any crack as given in Para- graph 3.B., Part 2. Fittings previously inspected using HFEC as given in Ta- ble 1 -Within 1,000 flight- cycles after the ini- tial inspection given in Table 1. Do a HFEC, dye penetrant, or detailed inspection of the elevator actuator fit- tings for any crack as given in Para- graph 3.B., Part 2. Fittings previously inspected using dye penetrant as given in Table 1 -Within 10,000 flight- cycles after the fit- ting was replaced, if a new fitting was in- stalled. Do a HFEC, dye penetrant, or detailed inspection of the replaced fittings for any crack as given in Paragraph 3.B., Part 2. Fittings previously replaced with a new fitting of the same part number as given in Paragraph 3.B., Part 4, as given in Table 1 350 flight-cycles350 flight-cycles af- ter the last detailed inspection Do a detailed inspection of the un- cracked elevator actuator fittings for any crack as given in Paragraph 3.B., Part 2. (a) Fittings found not cracked during the repeat inspection 1,000 flight-cy- cles 1,000 flight-cycles after the last dye penetrant inspection Do a dye penetrant inspection of the uncracked elevator actuator fittings for any crack as given in Paragraph 3.B., Part 2. (a) 1,200 flight-cy- cles 1,200 flight-cycles after the last HFEC inspection Do a HFEC inspection of the un- cracked elevator actuator fittings for any crack as given in Paragraph 3.B., Part 2. (a) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 17 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 18 Table 2: Elevator Actuator Fitting Repeat Inspections Repeat Interval (Not to Exceed) Compliance TimeAction (c)Condition -Before further flight.Replace any cracked fitting with a new fitting of the same part number as giv- en in Paragraph 3.B., Part 4. Fittings found cracked during the repeat inspection (b)10,000 flight-cycles after the fitting was replaced, if a new fitting was installed. Do a HFEC, dye penetrant, or detailed inspection of the replaced fittings for any crack as given in Paragraph 3.B., Part 2. Replaced Fittings with a new fitting of the same part num- ber as given in Paragraph 3.B., Part 4 (a) Do any one of the optional detailed, dye penetrant, or HFEC inspections at the time and repeat interval shown. (b) Do repeated inspections of the replaced fittings at the intervals specified above for fittings found not cracked. (c) Boeing Service Bulletin 777-55A0016 gives instructions to replace the existing elevator actuator fitting assemblies with a new and improved actuator fitting assemblies. As an alternative, accomplishment of Boeing Service Bulletin 777-55A0016 is terminating action for the inspection requirements as given in this service bulletin. Federal Aviation Administration (FAA) Airworthiness Directive 2007-26-05, Amendment 39-15307 is related to this service bulletin. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. This SB has been approved by the FAA. In addition, the manager of the Seattle Aircraft Certification Office (ACO) approves the inspection procedures and methods with the corresponding compliance times, as well as the added optional replacement of the existing fittings with the new, improved fatigue details fittings per SB 777-55A0016 as terminating action for the inspection requirements, specified in Table 1 and Table 2 under Paragraph 1.E. "Compliance," of SB 777-55A0015, Revision 3 - Stabilizers - Elevator Attach Fittings - Elevator Actuator Fitting Assembly inspection as an AMOC to the inspection methods and corresponding compliance times specified in Table 1 and Table 2, under paragraph 1.E., "Compliance," of SB 777-55A0015, Revision Original Issue, dated April 19, 2007; required by paragraph (f) of AD 2007-26-05. All provisions of AD 2007-26-05 that are not specified referenced in the preceding sentence remain fully applicable and must be complied with. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 18 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 19 Furthermore, the manager of the Seattle Aircraft Certification Office (SACO) approves the incorporation of Boeing PRR 62777-59S as an AMOC to the inspection and replacement requirements of paragraph (f) of AD 2007-26-05. G. Manpower The table below shows an estimate of the task hours necessary to do this inspection for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The 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. Elapsed HoursTask HoursNumber of Persons Task 1.532Open Access 1.753.52Figure 1 1.532Close Access 4.759.5TOTAL FOR EACH AIRPLANE Elapsed HoursTask HoursNumber of Persons Task 1.532Open Access 1.753.52Figure 2 1.532Close Access 4.759.5TOTAL FOR EACH AIRPLANE NOTE: More time will be necessary for fitting replacement if cracks are found. H. Weight and Balance Changes None. I. Electrical Load Data Not changed. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 19 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 20 J. References 1. Existing Data: a. 777 Aircraft Maintenance Manual (AMM) 12-12-01, 27-31-09 , 27-31-10, 29-11-00 b. 777 Non-Destructive Testing (NDT) Manual, Part 6, 51-00-01 c. 777 Structural Repair Manual (SRM) Chapter 51 d. Component Maintenance Manual (CMM) 55-20-23, 55-20-24 e. Service Related Problem (SRP) 777-SRP-55-0040 f. Standard Overhaul Practices Manual (SOPM) 20-20-02 g. FAA AD 2007-26-05, Amendment 39-15307 h. Boeing Service Bulletin 777-55A0016 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. K. Publications Affected 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 20 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 21 2. MATERIAL INFORMATION A. Material - Price and Availability The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. B. Industry Support Information Boeing warranty remedies are available for 777 airplanes in warranty as of November 17, 2006. For inspection task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. If the condition described in this service bulletin is found during the inspection for airplanes in warranty as of that date and additional task hours and parts are required, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. Please refer to this service bulletin number and reference the airplane variable number in your purchase order. C. Parts Necessary For Each Airplane 1. Kits/Parts: None. 2. Parts and Materials Supplied by the Operator: NOTE: The parts that follow may be necessary if cracked fittings are found. The number in the QTY column is the maximum number of parts that may be necessary for one airplane. Group 1: NotesExisting Part NumberNameQTYPart Number (a)183W1300-1Outboard Elevator Actuator Fit- ting Assembly - Left Side 1183W1300-5 (b)183W1300-2Outboard Elevator Actuator Fit- ting Assembly - Right Side 1183W1300-6 (c)183W1300-3Inboard Elevator Actuator Fit- ting Assembly - Left Side 1183W1300-7 (d)183W1300-4Inboard Elevator Actuator Fit- ting Assembly - Right Side 1183W1300-8 (a) 183W1300-1 is optional to 183W1300-5. (b) 183W1300-2 is optional to 183W1300-6. (c) 183W1300-3 is optional to 183W1300-7. (d) 183W1300-4 is optional to 183W1300-8. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 21 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 22 Group 2: NotesExisting Part NumberNameQTYPart Number (a)183W1312-1Outboard Elevator Actuator Fit- ting Assembly - Left Side 1183W1312-5 (b)183W1312-2Outboard Elevator Actuator Fit- ting Assembly - Right Side 1183W1312-6 (c)183W1322-1Inboard Elevator Actuator Fitting Assembly - Left Side 1183W1322-5 (d)183W1322-2Inboard Elevator Actuator Fitting Assembly - Right Side 1183W1322-6 (a) 183W1312-1 is optional to 183W1312-5. (b) 183W1312-2 is optional to 183W1312-6. (c) 183W1322-1 is optional to 183W1322-5. (d) 183W1322-2 is optional to 183W1322-6. 3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 22 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 23 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: — Linear dimensions are in inches — Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch. — Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch — Angular tolerance is plus or minus 2 degrees — Hole dimensions for standard solid rivets are given in 777 SRM, Chapter 51 — Torque limits to tighten nuts and bolts are given in 777 SRM, Chapter 51. 4. These work instructions refer to procedures included on 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 "as given in" are included in the instruction, the procedure in the Boeing document must be used. 5. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 6. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 23 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 24 B. WORK INSTRUCTIONS PART 1 - INITIAL INSPECTION 1. Get access. Refer to PART 3 as an accepted procedure. 2. Do surface High Frequency Eddy Current (HFEC) or dye penetrant inspections of the elevator actuator fittings as given in Figure 1. 3. If any cracked fitting is found, replace the cracked fitting as given in PART 4. After fitting replacement, start to do inspections of any replaced fitting as given in PART 1 at the time given in Paragraph 1.E., Compliance. 4. Restore access. Refer to PART 5 as an accepted procedure. 5. Put the airplane back in a serviceable condition. Do repeat inspections of uncracked fittings as given in PART 2 at the times given in Table 2 of Paragraph 1.E., Compliance. PART 2 - REPEAT INSPECTION 1. Get access. Refer to PART 3 as an accepted procedure. 2. Do surface High Frequency Eddy Current (HFEC), dye penetrant, or detailed inspections of the elevator actuator fittings as given in Figure 2. 3. If any cracked fitting is found, replace the affected fitting as given in PART 4. After fitting replacement, start to do inspections of any replaced fitting as given in PART 1 at the time given in Paragraph 1.E., Compliance. 4. Restore access. Refer to PART 5 as an accepted procedure. 5. Put the airplane back in a serviceable condition. Do repeat inspections of uncracked fittings as given in PART 2 at the times given in Table 2 of Paragraph 1.E., Compliance. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 24 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 25 PART 3 - ACCESS 1. On the left horizontal stabilizer, remove and keep access panels 335EB, 335FB (or 335EXB), and 335RB (or 335RBX) for access to the elevator actuator fittings. 2. On the right horizontal stabilizer, remove and keep access panels 345EB, 345FB (or 345EXB), and 345RB (or 345RBX) for access to the elevator actuator fittings. WARNING: YOU MUST PREVENT ALL POSSIBLE OPERATION OF THE HORIZONTAL STABILIZER WHEN YOU WORK ON OR NEAR IT. THE HORIZONTAL STABILIZER MOVES QUICKLY AND WITH FORCE. IF THE STABILIZER MOVES WHEN PERSONS ARE IN THE TORSION BOX COMPARTMENT OR NEAR THE STABILIZER, YOU CAN CAUSE INJURY TO THEM. WARNING: MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF THE ELEVATOR SURFACES BEFORE YOU REMOVE HYDRAULIC PRESSURE TO THE PCUS. WHEN YOU REMOVE HYDRAULIC PRESSURE, THE SURFACE WILL LOWER SLOWLY. ACCIDENTAL MOVEMENT OF ELEVATOR SURFACES CAN CAUSE INJURIES TO PERSONNEL AND DAMAGE TO EQUIPMENT. 3. Refer to one of the following methods as an accepted procedure to prevent all possible operation of the horizontal stabilizer and the elevator assembly: NOTE: The procedure that follows is from 777 AMM 27-31-09. a. Do these steps to move the elevator up manually: (1) Depressurize the hydraulic system and reservoir. Refer to 777 AMM 29-11-00 as an accepted procedure. (2) Operate the control column several times to remove the remaining hydraulic pressure. (3) On the P61 panel, move the FLT CONTROL HYD VALVE POWER - TAIL switches to the SHUT OFF position. (4) Open these circuit breakers and install safety tags: Left Power Management Panel, P110 NameNumberColRow ELEV PCU RIB(BLK)/ROB(BYP)C2760927K Power Supply Assembly Center, M24301 NameNumberColRow ELEV PCUCBA7-C7A BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 25 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 26 Power Supply Assembly Left, M24101 NameNumberColRow ELEV PCU LIB (BLK) LOB (BYP)CBA7-L7A Power Supply Assembly Right, M24201 NameNumberColRow ELEV PCUCBA7-R7A (5) Operate the manual bypass valve on the two elevator Power Control Units (PCUs): (a) Install the elevator PCU bypass pin, SPL-1708, on the manual bypass valves on the two elector PCUs. (b) Push the trailing edge of the elevator up. NOTE: The elevator will only move slowly because of the resistance in the PCUs. (6) Install the rudder and elevator power control unit lock, SPL-1712, on one of the elevator PCUs. (7) Remove the elevator PCU bypass pin, SPL-1708, from the manual bypass valves. CAUTION: BEFORE YOU USE THIS PROCEDURE, MAKE SURE THAT THERE IS NO LOCK INSTALLED ON ANY OF THE ELEVATOR PCUS. THE PCUS CAN BE DAMAGED IF HYDRAULIC POWER IS SUPPLIED WHEN THE LOCKS ARE INSTALLED ON THEM. b. Do these steps to move the elevator up with hydraulic power: (1) Make sure the PRIMARY FLIGHT COMPUTER switch (on the overhead panel, P5) is in the AUTO position. (2) Move and hold the Captain's or the First Officer's control column full aft to put the elevators in the up position. (3) Open these circuit breakers and install safety tags: Left Power Management Panel, P110 NameNumberColRow ELEV PCU RIB(BLK)/ROB(BYP)C2760927K Power Supply Assembly Center, M24301 NameNumberColRow ELEV PCUCBA7-C7A BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 26 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 27 Power Supply Assembly Left, M24101 NameNumberColRow ELEV PCU LIB (BLK) LOB (BYP)CBA7-L7A Power Supply Assembly Right, M24201 NameNumberColRow ELEV PCUCBA7-R7A (4) On the P61 panel, move the FLT CONTROL HYD VALVE POWER - TAIL switches to the SHUT OFF position. (5) Depressurize the hydraulic system and reservoir. Refer to 777 AMM 29-11-00 as an accepted procedure. (6) Operate the control column several times to remove the remaining hydraulic pressure. (7) Release the control column. (8) Make sure that there is no elevator movement. WARNING: MAKE SURE THE CIRCUIT BREAKERS FOR THE PCUS ARE OPEN AND HYDRAULIC POWER FOR THE ELEVATOR PCUS IS REMOVED BEFORE YOU INSTALL THE SAFETY LOCKS. IF THE CIRCUIT BREAKERS FOR THE PCUS ARE CLOSED, THE ELEVATOR CAN FALL WHILE YOU INSTALL THE SAFETY LOCKS. IF HYDRAULIC POWER FOR THE PCUS IS ON, THE ELEVATOR CAN MOVE DOWN VERY FAST WHILE YOU INSTALL THE SAFETY LOCKS. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE EQUIPMENT. (9) Install the rudder and elevator power control unit lock, SPL-1712, on one of the elevator PCUs. PART 4 - FITTING REPLACEMENT 1. Remove the affected elevator. Refer to 777 AMM 27-31-10 as an accepted procedure. 2. Group 1: Replace any cracked fitting with a new fitting of the same part number as given in CMM 55-20-23 or an approved optional part number. 3. Group 2: Replace any cracked fitting with a new fitting of the same part number as given in CMM 55-20-24 or an approved optional part number. 4. Install the elevator. Refer to 777 AMM 27-31-10 as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 27 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 28 PART 5 - RESTORE ACCESS 1. Refer to the following steps an accepted procedure to restore access: NOTE: These steps are from 777 AMM 27-31-09. a. Remove the rudder and elevator power control unit lock, SPL-1712. b. Remove the safety tags and close these circuit breakers: Left Power Management Panel, P110 NameNumberColRow ELEV PCU RIB(BLK)/ROB(BYP)C2760927K Power Supply Assembly Center, M24301 NameNumberColRow ELEV PCUCBA7-C7A Power Supply Assembly Left, M24101 NameNumberColRow ELEV PCU LIB (BLK) LOB (BYP)CBA7-L7A Power Supply Assembly Right, M24201 NameNumberColRow ELEV PCUCBA7-R7A c. Pressurize the main hydraulic system. Refer to 777 AMM 29-11-00 as an accepted procedure. d. On the P61 panel, move the FLT CONTROL HYD POWER - TAIL switches to the NORM position. e. Fill the hydraulic reservoir as needed. Refer to 777 AMM 12-12-01 as an accepted procedure. 2. Install the access panels that were removed for access to the elevator actuator fittings. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3: November 24, 2009 28 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 29 (OCR) BOEING SERVICE BULLETIN 777-55A0015 SEE A SEE ® ELEV STA 194.79 ELEV STA 169.79 - SEE C SEE C > FWD LEFT ELEVATOR ASSEMBLY 1350109 FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION (SHEET 1 OF 4) Original Issue: April 19, 2007 Revision 3 November 24, 2009 BOEING PROPRIETARY - 777-55A0015 Copyright © Unpublished Work - See page 1 for details. 29 of 36 ### Page 30 FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION (SHEET 2 OF 4) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3 November 24, 2009 30 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 31 (OCR) BOEING SERVICE BULLETIN 777-55A0015 1.0 (TYPICAL) UPPER FLANGE (TYPICAL, 2 EDGE LOCATIONS PER FITTING) LOWER FLANGE SEE O FWD TYPICAL ACTUATOR FITTING FOUR LOCATIONS PER AIRPLANE (TYPICAL, 8 RADIUS LOCATIONS PER FITTING) 0.5 (TYPICAL, 8 LOCATIONS FWD SHOWN, UPPER FLANGE LOWER FLANGE OF FITTING 1454300 SIMILAR FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION (SHEET 3 OF 4) Original Issue: April 19, 2007 Revision 3 November 24, 2009 777-55A0015 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 36 ### Page 32 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY number shown below is the number of areas affected for each actuator fitting. There are a total of four affected actuator fittings on each airplane. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP For cracks at locations where the fitting transitions into the upper and lower flanges. Use surface HFEC, as given in 777 NDT, Part 6, 51-00-01, Procedure 1 or 2 or dye penetrant as given in SOPM 20-20-02. 8-Actuator FittingInspect1 For cracks at the fitting edge. Use surface HFEC, as given in 777 NDT, Part 6, 51-00-01, Pro- cedure 1 or 2 or dye penetrant as given in SOPM 20-20-02. 2-Actuator FittingInspect2 FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION (SHEET 4 OF 4) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3 November 24, 2009 32 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 33 (OCR) BOEING SERVICE BULLETIN 777-55A0015 SEE A SEE ® ELEV STA 194.79 ELEV STA 169.79 - SEE C SEE C • FWD LEFT ELEVATOR ASSEMBLY 1361642 FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION (SHEET 1 OF 4) Original Issue: April 19, 2007 Revision 3 November 24, 2009 BOEING PROPRIETARY - 777-55A0015 Copyright © Unpublished Work - See page 1 for details. 33 of 36 ### Page 34 FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION (SHEET 2 OF 4) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3 November 24, 2009 34 of 36 BOEING SERVICE BULLETIN 777-55A0015 ### Page 35 (OCR) BOEING SERVICE BULLETIN 777-55A0015 1.0 (TYPICAL) UPPER FLANGE ) (TYPICAL, 2 EDGE LOCATIONS PER FITTING) LOWER FLANGE SEE O FWD TYPICAL ACTUATOR FITTING FOUR LOCATIONS PER AIRPLANE (TYPICAL, 8 RADIUS LOCATIONS PER FITTING) 0.5 (TYPICAL, LOWER FLANGE OF FITTING 8 LOCATIONS FWD SHOWN, UPPER FLANGE 1454342 SIMILAR FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION (SHEET 3 OF 4) Original Issue: April 19, 2007 Revision 3 November 24, 2009 BOEING PROPRIETARY - 777-55A0015 Copyright © Unpublished Work - See page 1 for details. 35 of 36 ### Page 36 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY number shown below is the number of areas affected for each actuator fitting. There are a total of four affected actuator fittings on each airplane. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP For cracks at locations where the fitting transitions into the upper and lower flanges. Use surface HFEC as given in 777 NDT, Part 6, 51-00-01, Procedure 1 or 2, dye penetrant as given in SOPM 20-20-02, or a detailed inspec- tion 8-Actuator FittingInspect1 For cracks at the fitting edge. Use surface HFEC, as given in 777 NDT, Part 6, 51-00-01, Pro- cedure 1 or 2 or dye penetrant as given in SOPM 20-20-02. 2-Actuator FittingInspect2 FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION (SHEET 4 OF 4) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015Revision 3 November 24, 2009 36 of 36 BOEING SERVICE BULLETIN 777-55A0015 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. 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