### 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 1 of 36 6.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 2 of 36 **BOEING SERVICE BULLETIN 777-55A0015**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 20 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 20 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 20 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 21 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 22 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION. . . . . . . . . . . . . . . . . . 29 FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION. . . . . . . . . . . . . . . . . 33

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 3 of 36 **BOEING SERVICE BULLETIN 777-55A0015**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 4 of 36 **BOEING SERVICE BULLETIN 777-55A0015**

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### Commercial **Airplanes** 

# 777 Service Bulletin **Revision Transmittal Sheet 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 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 777-55A0015 Revision 3: November 24, 2009 5 of 365. 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, 2007 Original Issue: January 31, 2008 Revision 1: December 04, 2008 Revision 2: November 24, 2009 Revision 3:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 6 of 36 **BOEING SERVICE BULLETIN 777-55A0015**

### Commercial **Airplanes** 

# 777 Service Bulletin **Summary 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 **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 777-55A0015 Revision 3: November 24, 2009 7 of 36Federal 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 Hours**  **Total Task Hours Airplanes**  4.75 9.5 All - Initial Inspection 4.75 9.5 All - Repeat Inspection
**MATERIAL INFORMATION** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 8 of 36 **BOEING SERVICE BULLETIN 777-55A0015**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 9 of 36 **BOEING SERVICE BULLETIN 777-55A0015**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 10 of 36 **BOEING SERVICE BULLETIN 777-55A0015**

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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.
**DESCRIPTION CONFIGURATION**  **GROUP** 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 **Group Variable Number**  1 WA001 - WA017 1 WA076 - WA080 1 WA086 - WA087 2 WA088 - WA093 1 WA101 - WA104 1 WA116 - WA117 2 WA118 - WA119 1 WA131 - WA135 2 WA136 - WA137

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 11 of 36**Group Variable Number**  1 WA171 - WA173 2 WA174 - WA175 1 WA196 - WA197 2 WA198 2 WA206 - WA212 2 WA221 - WA223 2 WA231 - WA232 2 WA241 - WA250 2 WA261 - WA266 2 WA281 - WA283 2 WA301 - WA304 2 WB001 - WB021 2 WB031 - WB046 2 WB051 - WB088 2 WB101 - WB106 2 WB121 - WB125 2 WB131 - WB147 2 WB151 - WB155 2 WB161 - WB177 2 WB181 - WB194 2 WB201 - WB215 2 WB231 - WB247 2 WB271 - WB273 2 WB276 - WB286 2 WB291 - WB302 2 WB306 - WB307 2 WB311 - WB337 2 WB341 - WB342 2 WB366 - WB368 2 WB371 - WB388 2 WB406 2 WB411 - WB413 2 WB416 - WB439

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 12 of 36 **BOEING SERVICE BULLETIN 777-55A0015 Group**  **Variable Number** 2 WB446 - WB453 2 WB476 2 WB481 - WB484 2 WB501 - WB512 2 WB531 - WB537 2 WB551 - WB554 2 WB591 - WB597 2 WB601 - WB606 2 WB611 - WB622 2 WB631 - WB638 2 WB646 - WB649 2 WC051 - WC073 2 WC101 - WC104 2 WC111 - WC119 2 WC221 - WC222 2 WC241 - WC243 2 WC281 - WC290 2 WC301 - WC308 2 WC361 - WC364 2 WC371 - WC374 2 WC381 - WC395 2 WC441 2 WC446 - WC449 2 WC456 - WC459 2 WC486 - WC493 2 WC506 - WC508 2 WC521 - WC522 2 WC531 - WC536 2 WC546 - WC548 2 WC556 2 WC566 - WC567 2 WD001 - WD002 2 WD011 - WD015

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 13 of 36 **BOEING SERVICE BULLETIN 777-55A0015 Group**  **Variable Number** 2 WD031 - WD036 2 WD046 - WD049 2 WD066 - WD067 2 WD501 - WD507 2 WD521 - WD538 2 WD546 - WD552 2 WD561 - WD572 2 WD581 - WD594 2 WD606 - WD609 2 WD621 - WD632 2 WD651 - WD659 2 WD671 - WD675 2 WD691 - WD706 2 WD741 - WD748 2 WD761 - WD770 2 WD786 - WD788 2 WD796 - WD802 2 WD826 - WD829 2 WD846 - WD849 2 WD871 - WD872 2 WD911 - 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 777-55A0015 Revision 3: November 24, 2009 14 of 36 **BOEING SERVICE BULLETIN 777-55A0015**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 777-55A0015 Revision 3: November 24, 2009 15 of 36 **BOEING SERVICE BULLETIN 777-55A0015**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 Zone**  **Model** 336, 346 777-200 **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 336, 346 777-200, 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 Time**  **Action (a) Condition**  Within 90 days after the original issue date of this service bulletin.Do a HFEC or dye-penetrant inspection of the elevator actuator fittings for any crack as given in Paragraph 3.B., Part 1.All airplanes with 14,000 total flightcycles or more as of the original issue date of this service bulletin Within 12 months after the original issue date of this service bulletin,or within 90 days after the airplane reaches 14,000 total flightcycles, whichever occurs first.Do a HFEC or dye-penetrant inspection of the elevator actuator fittings for any crack as given in Paragraph 3.B., Part 1.All airplanes with 10,000 total flightcycles 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 inspection 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 2 Do 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 777-55A0015 Revision 3: November 24, 2009 16 of 36 **BOEING SERVICE BULLETIN 777-55A0015 Table 1: Elevator Actuator Fitting Initial Inspection**  **Compliance Time Action (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 inspection

As given in Table 2 Do 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 Time**  **Action (c) Condition** 

- Within 1,200 flight-cycles after the initial inspection given in Table 1. Do a HFEC, dye penetrant, or detailedinspection of the elevator actuator fittings for any crack as given in Paragraph 3.B., Part 2. Fittings previously inspectedusing HFEC as given in Table 1

- Within 1,000 flight-cycles after the initial inspection given in Table 1. Do a HFEC, dye penetrant, or detailedinspection of the elevator actuator fittings for any crack as given in Paragraph 3.B., Part 2. Fittings previously inspected using dye penetrant as given in Table 1

- Within 10,000 flight-cycles after the fitting was replaced, ifa 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. 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-cycles 350 flight-cycles af- ter the last detailed inspectionDo a detailed inspection of the uncracked 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-cycles 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-cycles 1,200 flight-cycles after the last HFEC inspectionDo a HFEC inspection of the uncracked 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 777-55A0015 Revision 3: November 24, 2009 17 of 36 **BOEING SERVICE BULLETIN 777-55A0015 Table 2: Elevator Actuator Fitting Repeat Inspections**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action (c)**  **Condition**

- Before further flight. Replace any cracked fitting with a newfitting of the same part number as given 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 newfitting of the same part number 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 777-55A0015 Revision 3: November 24, 2009 18 of 36 **BOEING SERVICE BULLETIN 777-55A0015**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 Hours Task Hours**  **Number of Persons**  **Task**
1.5 3 2 Open Access 1.75 3.5 2 Figure 1 1.5 3 2 Close Access 4.75 9.5 TOTAL FOR EACH AIRPLANE **Elapsed Hours Task Hours**  **Number of Persons**  **Task**
1.5 3 2 Open Access 1.75 3.5 2 Figure 2 1.5 3 2 Close Access 4.75 9.5 TOTAL 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 777-55A0015 Revision 3: November 24, 2009 19 of 36 **BOEING SERVICE BULLETIN 777-55A0015 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 777-55A0015 Revision 3: November 24, 2009 20 of 36 **BOEING SERVICE BULLETIN 777-55A0015 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:**
**Notes Existing Part Number**  **Name QTY**  **Part Number** (a) 183W1300-1 Outboard Elevator Actuator Fit- ting Assembly - Left Side 1 183W1300-5 (b) 183W1300-2 Outboard Elevator Actuator Fit- ting Assembly - Right Side 1 183W1300-6 (c) 183W1300-3 Inboard Elevator Actuator Fit- ting Assembly - Left Side 1 183W1300-7 (d) 183W1300-4 Inboard Elevator Actuator Fit- ting Assembly - Right Side 1 183W1300-8 (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 777-55A0015 Revision 3: November 24, 2009 21 of 36 **BOEING SERVICE BULLETIN 777-55A0015 Group 2:** 
**Notes Existing Part Number**  **Name QTY**  **Part Number** (a) 183W1312-1 Outboard Elevator Actuator Fit- ting Assembly - Left Side 1 183W1312-5 (b) 183W1312-2 Outboard Elevator Actuator Fit- ting Assembly - Right Side 1 183W1312-6 (c) 183W1322-1 Inboard Elevator Actuator Fitting Assembly - Left Side 1 183W1322-5 (d) 183W1322-2 Inboard Elevator Actuator Fitting Assembly - Right Side 1 183W1322-6 (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 777-55A0015 Revision 3: November 24, 2009 22 of 36 **BOEING SERVICE BULLETIN 777-55A0015 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 777-55A0015 Revision 3: November 24, 2009 23 of 36 **BOEING SERVICE BULLETIN 777-55A0015 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 777-55A0015 Revision 3: November 24, 2009 24 of 36 **BOEING SERVICE BULLETIN 777-55A0015 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**
**Name Number**  **Col Row**  ELEV PCU RIB(BLK)/ROB(BYP) C27609 27 K **Power Supply Assembly Center, M24301**
**Name Number**  **Col Row**  ELEV PCU CBA7-C 7 A

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 25 of 36 **BOEING SERVICE BULLETIN 777-55A0015 Power Supply Assembly Left, M24101** 
**Name Number**  **Col Row**  ELEV PCU LIB (BLK) LOB (BYP) CBA7-L 7 A **Power Supply Assembly Right, M24201**
**Name Number**  **Col Row**  ELEV PCU CBA7-R 7 A (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**
**Name Number**  **Col Row**  ELEV PCU RIB(BLK)/ROB(BYP) C27609 27 K **Power Supply Assembly Center, M24301**
**Name Number**  **Col Row**  ELEV PCU CBA7-C 7 A

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3: November 24, 2009 26 of 36 **BOEING SERVICE BULLETIN 777-55A0015 Power Supply Assembly Left, M24101** 
**Name Number**  **Col Row**  ELEV PCU LIB (BLK) LOB (BYP) CBA7-L 7 A **Power Supply Assembly Right, M24201**
**Name Number**  **Col Row**  ELEV PCU CBA7-R 7 A (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 777-55A0015 Revision 3: November 24, 2009 27 of 36 **BOEING SERVICE BULLETIN 777-55A0015 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**
**Name Number**  **Col Row**  ELEV PCU RIB(BLK)/ROB(BYP) C27609 27 K **Power Supply Assembly Center, M24301**
**Name Number**  **Col Row**  ELEV PCU CBA7-C 7 A **Power Supply Assembly Left, M24101**
**Name Number**  **Col Row**  ELEV PCU LIB (BLK) LOB (BYP) CBA7-L 7 A **Power Supply Assembly Right, M24201**
**Name Number**  **Col Row**  ELEV PCU CBA7-R 7 A 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 777-55A0015 Revision 3: November 24, 2009 28 of 36 **BOEING SERVICE BULLETIN 777-55A0015 FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION**  **(SHEET 1 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3 November 24, 2009 29 of 36 **BOEING SERVICE BULLETIN 777-55A0015 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 777-55A0015 Revision 3 November 24, 2009 30 of 36 **BOEING SERVICE BULLETIN 777-55A0015 FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION**  **(SHEET 3 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3 November 24, 2009 31 of 36 **BOEING SERVICE BULLETIN 777-55A0015**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  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 Fitting Inspect 1

For cracks at the fitting edge. Use surface HFEC, as given in777 NDT, Part 6, 51-00-01, Procedure 1 or 2 or dye penetrant as given in SOPM 20-20-02. 2
- Actuator Fitting Inspect 2

**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 777-55A0015 Revision 3 November 24, 2009 32 of 36 **BOEING SERVICE BULLETIN 777-55A0015 FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION**  **(SHEET 1 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3 November 24, 2009 33 of 36 **BOEING SERVICE BULLETIN 777-55A0015 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 777-55A0015 Revision 3 November 24, 2009 34 of 36 **BOEING SERVICE BULLETIN 777-55A0015 FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION**  **(SHEET 3 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 19, 2007 777-55A0015 Revision 3 November 24, 2009 35 of 36 **BOEING SERVICE BULLETIN 777-55A0015**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  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 SOPM20-20-02, or a detailed inspection 8
- Actuator Fitting Inspect 1

For cracks at the fitting edge. Use surface HFEC, as given in777 NDT, Part 6, 51-00-01, Procedure 1 or 2 or dye penetrant as given in SOPM 20-20-02. 2
- Actuator Fitting Inspect 2

**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 777-55A0015 Revision 3 November 24, 2009 36 of 36 **BOEING SERVICE BULLETIN 777-55A0015**