### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Number: 777-55A0018**  Original Issue: July 27, 2011 Revision 1: March 06, 2012 ATA System: 5510 **SUBJECT:** STABILIZERS - Horizontal Stabilizer - Pivot Pin - Inspection, Rework, and Replacement 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 1 of 47 4.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 2 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 9 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 22 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 27 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 28 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK. . . . . . . . . . . . . . . . . . . . . . . . . 38 FIGURE 2: 182W6401-2 OR 182W6401-301 INNER PIVOT PIN REWORK. . . . . . . . . . . . . . 42 FIGURE 3: 182W6403-1 ANTI-ROTATION PLATE REWORK [Group 1]. . . . . . . . . . . . . . . . 44 APPENDIX A: HORIZONTAL STABILIZER TEMPORARY PIVOT PIN FABRICATION/INSTALLATION . 46

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 3 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 4 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Revision Transmittal Sheet**  **Number: 777-55A0018** Original Issue: July 27, 2011 Revision 1: March 06, 2012 ATA System: 5510 **SUBJECT:** STABILIZERS - Horizontal Stabilizer - Pivot Pin - Inspection, Rework, and Replacement This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2011-NM-181-AD is related to this service bulletin. No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. No airplanes were added to the service bulletin effectivity. However, Group 1 from the original issue of this service bulletin has been divided into two groups. 777-200 and 777-300 airplanes, line numbers 423 through 868, which were included in Group 1 in the original issue of this service bulletin, have been moved to new Group 3. Group 1 now includes 777-200 and 777-300 airplanes line numbers 1 through 422. Airplane Group 2 has not been changed. **REASON FOR REVISION** This revision is sent to include a new top kit for 777-200 and 777-300 airplanes, line numbers 1 through 422. For these airplanes, new Top Kit 005W3480-2 includes new anti-rotation plates for use when accomplishing the Paragraph 3.B., PART 1 and PART 2 replacement. An alternative to rework existing anti-rotation plates has also been added as new Figure 3. These sections were changed: 1. In the BACKGROUND section of the Summary, the Summary Evaluation Table was added. 2. In the COMPLIANCE section of the Summary, reference to FAA NPRM 2011-NM-181-AD was added. 3. In Paragraph 1.A.1., Airplanes, the description of Group 1 was changed. A description of new Group 3 was added. 4. In Paragraph 1.C., Reason, a description of the changes in Revision 1 was added. 5. In Paragraph 1.D., Description, a "no more work" statement was added for Revision 1. Maintenance Zones were added for Group 3.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 5 of 476. In Paragraph 1.E., Compliance, reference to FAA NPRM 2011-NM-181-AD was added. Tables 1, 2 and 3 were changed in several places to specify the work in Paragraph 3.B., Work Instructions, PART 1 and PART 2, not PART 1 or PART 2. The Compliance Time grace period in Table 1 was changed to "within 750 days after the Revision 1 date of this service bulletin." Table 2 was marked as being applicable to Group 3. The data in the "Repeat Interval" column in Tables 2 and 3 was changed to add "after the most recent inspection". 7. In Paragraph 1.G., Manpower, the Task descriptions in the table have been changed due to changes in Paragraph 3.B., Work Instructions. 8. In Paragraph 1.J.1., Existing Data, reference to FAA NPRM 2011-NM-181-AD was added. 9. In Paragraph 2.A., Material - Price and Availability, new Top Kit 005W3480-2 was added. 10. In Paragraph 2.C.1., Kits/Parts, new Top Kit 005W3480-2 was added for Group 1 airplanes. Existing Top Kit 005W3480-1 was changed to be applicable to Group 2 and Group 3 airplanes. 11. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, Retention Pin 182W6401-5, Anti-Rotation Plate 182W6403-1, Anti-Rotation Plate 182W6403-301 and Nut 182W6404-5 were added. Conditions under which these parts may be needed were also added. 12. In Paragraph 2.C.3., Parts Modified and Reidentified, the anti-rotation plate was added for Group 1 airplanes. 13. In Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin, information for jacking and support of the horizontal stabilizer was added. 14. In Paragraph 3.A., General Information, a note that did not allow intermixing of new and reworked pivot pins on an airplane was deleted. A new note was added to specify that the pivot pins should only be removed from one side of the airplane at a time. 15. In Paragraph 3.B., Work Instructions, Step 1 was changed to specify removal of the load from the horizontal stabilizer pivot joint. 16. In Paragraph 3.B., Work Instructions, PART 1 and PART 2 were changed. PART 1, which previously showed only pivot pin replacement, now shows Left Side pivot pin replacement or rework. PART 2, which previously showed only pivot pin rework, now shows Right Side pivot pin replacement or rework. This reorganization of PART 1 and PART 2 results from adding the allowance to intermix new and reworked pivot pins during the initial replacement or rework, which was not allowed in the original issue of this service bulletin. 17. In Paragraph 3.B., Work Instructions, steps were added to PART 1 and PART 2 to remove and replace or rework the anti-rotation plates on Group 1 airplanes. The After-Replacement / Rework inspection instructions in PART 3 were changed to add applicability to new Group 3 and to add anti-rotation plate replacement or rework. 18. In FIGURE 1 and FIGURE 2, footnote (a) was changed. Dry film lubricant may have been previously removed when chrome plate was removed. 19. New FIGURE 3 was added for anti-rotation plate rework. The data given in Information Notice 777-55A0018 IN 01 is included in this revision. IN 01 was sent to advise operators that new or reworked anti-rotation plates would be necessary on line number 1 - 422 airplanes if new pivot pins are installed. IN 01 also advised operators of upcoming changes to horizontal stabilizer jacking equipment SPL-2037 (Part Number J55004-1), which is referred to in 777 AMM 55-17-01 for pivot joint disassembly.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 6 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**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** July 27, 2011 Original Issue: March 06, 2012 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 7 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 8 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Summary**  **Number: 777-55A0018** Original Issue: July 27, 2011 Revision 1: March 06, 2012 ATA System: 5510 **SUBJECT:** STABILIZERS - Horizontal Stabilizer - Pivot Pin - Inspection, Rework, and Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** This service bulletin gives instructions to replace the existing horizontal stabilizer pivot pins with new or reworked pivot pins that have improved resistance to corrosion. If the work given in this service bulletin is not done, horizontal stabilizer pivot pins with corrosion could eventually crack and fracture. A fractured horizontal stabilizer pivot pin may cause excessive horizontal stabilizer freeplay and structural damage significant enough to result in loss of control of the airplane. The left and right horizontal stabilizer pivot joints each contain inner and outer pivot pins, along with spacers, washers, and retaining hardware. These parts join the horizontal stabilizer to the section 48 stabilizer support bulkhead at body station 2370. Boeing has received several reports of horizontal stabilizer pivot pin corrosion damage on the outer diameter chrome surface. One operator sent a corroded pivot pin to Boeing for analysis. Upon close examination, Boeing found micro cracks in the chrome plating of the pivot pin. Some of the micro cracks extended into the base metal. Accomplishment of this service bulletin will remove the micro-cracking process condition found in existing horizontal stabilizer pivot pins and ensure that the pins are free of corrosion damage that could result in pivot pin fracture. Boeing Fleet Team Digest (FTD) article 777 FTD 55-10001 is related to this service bulletin. Boeing Service Related Problem (SRP) 777-SRP-55-0049 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 9 of 47**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., Compliance Yes AD Related Paragraph 1.H., Weight and Balance Changes No Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected Yes Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts Yes Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required

**ACTION (PRR 62777-78S)** Remove the horizontal stabilizer inner and outer pivot pins. Install new pivot pins that have improved resistance to corrosion. Alternatively, rework and re-install the existing pivot pins or install spare pivot pins that have already been reworked in accordance with this service bulletin. After replacement, do detailed and ultrasonic inspections of the horizontal stabilizer pivot pins. Accomplish all actions in accordance with paragraph 1.E., Compliance. **EFFECTIVITY** 777-200, 777-200LR, 777-300, 777-300ER, and 777F airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **COMPLIANCE** Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2011-NM-181-AD, is related to this service bulletin. Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the inspection and replacement procedures given in this service bulletin. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  9.50 38.00 All airplanes.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 10 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT MATERIAL INFORMATION**  Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. Operator Supplied Materials.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 11 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 12 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Number: 777-55A0018**  Original Issue: July 27, 2011 Revision 1: March 06, 2012 ATA System: 5510 **SUBJECT:** STABILIZERS - Horizontal Stabilizer - Pivot Pin - Inspection, Rework, and Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 62777-78S for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** 777-200 and 777-300 airplanes, line numbers 1 through 422.

- 1 777-200LR, 777-300ER, and 777F airplanes, line numbers 423 through 919. - 2
777-200 and 777-300 airplanes, line numbers 424 through 868.

- 3

Airplane Models: 777-200, 777-200LR, 777-300, 777-300ER, 777F **Group Variable Number**  1 WA001 - WA017 1 WA076 - WA080 1 WA086 - WA093

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 13 of 47**Group Variable Number**  1 WA101 - WA104 1 WA116 - WA119 1 WA131 - WA137 1 WA171 - WA175 1 WA196 - WA198 1 WA206 - WA212 1 WA221 - WA223 1 WA231 - WA232 1 WA241 - WA250 1 WA261 - WA266 3 WA281 - WA283 3 WA301 - WA304 1 WB001 - WB021 1 WB031 - WB046 1 WB051 - WB088 1 WB101 - WB106 1 WB121 - WB125 1 WB131 - WB138 3 WB139 - WB148 1 WB151 - WB155 1 WB161 - WB175 3 WB176 - WB177 1 WB181 - WB190 3 WB191 - WB194 1 WB201 - WB212 3 WB213 - WB215 1 WB231 - WB242 3 WB243 - WB247 1 WB271 - WB273 1 WB276 - WB286 1 WB291 - WB302 1 WB306 - WB307 1 WB311 - WB337

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 14 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Group**  **Variable Number** 1 WB341 - WB342 1 WB366 - WB367 3 WB368 1 WB371 - WB388 1 WB406 1 WB411 - WB413 1 WB416 - WB435 3 WB436 - WB439 1 WB446 - WB453 1 WB476 1 WB481 - WB484 1 WB501 - WB507 3 WB508 - WB512 1 WB531 - WB535 3 WB536 - WB537 1 WB551 - WB554 1 WB591 - WB595 3 WB596 - WB597 1 WB601 - WB606 1 WB611 - WB618 3 WB619 - WB622 1 WB631 - WB638 1 WB646 3 WB647 - WB649 1 WC051 - WC073 1 WC101 - WC104 1 WC111 - WC114 3 WC115 - WC120 3 WC221 - WC224 1 WC241 - WC242 3 WC243 1 WC281 - WC282 3 WC283 - WC290

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 15 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Group**  **Variable Number** 3 WC301 - WC308 3 WC361 - WC364 3 WC371 - WC374 3 WC381 - WC395 3 WC441 3 WC446 - WC449 3 WC456 - WC459 3 WC486 - WC493 3 WC506 - WC508 3 WC521 - WC522 3 WC531 - WC536 3 WC546 - WC548 3 WC556 3 WC566 - WC567 3 WC571 - WC574 3 WC581 2 WD001 - WD002 2 WD011 - WD018 2 WD031 - WD036 2 WD046 - WD055 2 WD066 - WD075 2 WD081 - WD088 2 WD091 2 WD096 2 WD101 - WD103 2 WD501 - WD513 2 WD521 - WD541 2 WD546 - WD554 2 WD561 - WD573 2 WD581 - WD599 2 WD606 - WD609 2 WD621 - WD632 2 WD651 - WD665

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 16 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Group**  **Variable Number** 2 WD671 - WD676 2 WD691 - WD709 2 WD741 - WD752 2 WD761 - WD771 2 WD786 - WD788 2 WD796 - WD813 2 WD826 - WD837 2 WD846 - WD861 2 WD871 - WD883 2 WD911 - WD915 2 WD921 - WD922 2 WD936 - WD939 2 WD946 - WD951 2 WD966 - WD970 2 WD981 - WD982 2 WD986 - WD987 2 WD996 2 WE001 - WE004 2 WE011 - WE012 2 WE021 - WE025 2 WE031 2 WE051 - WE052 2 WE071 2 WE081 - WE082 2 WE126 - WE133 2 WF001 - WF004 2 WF016 - WF020 2 WF031 - WF032 2 WF046 - WF054 2 WF076 - WF077 2 WF081 - WF088 2 WF096 - WF099 2 WF106 - WF107

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 17 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Group**  **Variable Number** 2 WF111 - WF112 2 WF121 2. Spares Affected Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for the recommended use. **B. Concurrent Requirements** None. **C. Reason** This service bulletin gives instructions to replace the existing horizontal stabilizer pivot pins with new or reworked pivot pins that have improved resistance to corrosion. If the work given in this service bulletin is not done, horizontal stabilizer pivot pins with corrosion could eventually crack and fracture. A fractured horizontal stabilizer pivot pin may cause excessive horizontal stabilizer freeplay and structural damage significant enough to result in loss of control of the airplane. The left and right horizontal stabilizer pivot joints each contain inner and outer pivot pins, along with spacers, washers, and retaining hardware. These parts join the horizontal stabilizer to the section 48 stabilizer support bulkhead at body station 2370. Boeing has received several reports of horizontal stabilizer pivot pin corrosion damage on the outer diameter chrome surface. One operator sent a corroded pivot pin to Boeing for analysis. Upon close examination, Boeing found micro cracks in the chrome plating of the pivot pin. Some of the micro cracks extended into the base metal. Accomplishment of this service bulletin will remove the micro-cracking process condition found in existing horizontal stabilizer pivot pins and ensure that the pins are free of corrosion damage that could result in pivot pin fracture. Boeing Fleet Team Digest (FTD) article 777 FTD 55-10001 is related to this service bulletin. Boeing Service Related Problem (SRP) 777-SRP-55-0049 is related to this service bulletin. Revision 1 is sent to include a new top kit for 777-200 and 777-300 airplanes, line numbers 1 through 422. For these airplanes, new Top Kit 005W3480-2 includes new anti-rotation plates for use when accomplishing the Paragraph 3.B., PART 1 and PART 2 replacement. An alternative to rework existing anti-rotation plates has also been added as new Figure 3. The data given in Information Notice 777-55A0018 IN 01 is included in Revision 1. IN 01 was sent to advise operators that new or reworked anti-rotation plates would be necessary on line number 1 - 422 airplanes if new pivot pins are installed. IN 01 also advised operators of upcoming changes to the SPL-2037 horizontal stabilizer jacking tool, which is referred to in 777 AMM 55-17-01 for pivot joint disassembly. Other changes have also been made as part of Revision 1. A detailed list of these changes is given under "Reason for Revision" in the Revision Transmittal Sheet Section of Revision 1 of this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 18 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT D. Description**  Remove the horizontal stabilizer inner and outer pivot pins. Install new pivot pins that have improved resistance to corrosion. Alternatively, rework and re-install the existing pivot pins or install spare pivot pins that have already been reworked in accordance with this service bulletin. After replacement, do detailed and ultrasonic inspections of the horizontal stabilizer pivot pins. Accomplish all actions in accordance with Paragraph 1.E., Compliance. Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1, 3:**
**Affected Maintenance Zones Zone**  **Model** 313, 314, 331, 341 777-200, 777-300 **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 313, 314, 331, 341 777-200LR, 777-300ER, 777F **E. Compliance** Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2011-NM-181-AD, is related to this service bulletin. **Table 1: Horizontal Stabilizer Pivot Pin Replacement or Rework**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 750 daysafter the Revision 1 date ofthis service bulletin. Before 16,000 total flight cycles or within 3,000 days after the date of issuance of the originalcertificate of airworthiness orthe original export certificate,whichever occurs first.Do the pivot pin replacement or rework in accordance with paragraph 3.B., Work Instructions, PART 1 and PART 2 All airplanes.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 19 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Group 1, 3:**  **Table 2: After Replacement / Rework**  **Inspections - 777-200 and 777-300 Airplanes. Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs First) Action**  **Condition**

- Within 6,000days after accomplishment ofthe pivot pin replacement or rework in accordance with paragraph 3.B.,Work Instructions, PART 1 and PART 2. Within 32,000flight cycles after accomplishment of the pivot pin replacement or rework in accordance with paragraph3.B., Work Instructions, PART 1 and PART 2. Do the after replacement/ rework detailed and ultrasonic inspections in accordance with paragraph 3.B., Work Instructions, PART 3. All airplanes on which pivot pins have been replaced or reworked in accordance with paragraph 3.B., Work Instructions, PART 1 and PART 2.

- Before further flight. Replace the pivot pin inaccordance with paragraph 3.B., Work Instructions, PART 3.Any crack, corrosion damage, or other irregularity found on a pivot pin during PART 3 inspections. Within 16,000 flight cycles or within 3,000 days, whichever occurs first, after the most recent inspection. - - Repeat the after replace- ment / rework detailed and ultrasonic inspectionsin accordance with paragraph 3.B., Work Instructions, PART 3.No crack, corrosion damage, or other irregularityfound during PART 3 inspections, or pivot pins that have been replaced.

**Group 2: Table 3: After Replacement** **/ Rework Inspections - 777-200LR, 777-300ER, and 777F Airplanes.**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs First)**  **Action Condition** 

- Within 6,000days after accomplishment ofthe pivot pin replacement or rework in accordance with paragraph 3.B.,Work Instructions, PART 1 and PART 2. Within 32,000flight cycles after accomplishment of the pivot pin replacement or rework in accordance with paragraph3.B., Work Instructions, PART 1 and PART 2. Do the after replacement/ rework detailed and ultrasonic inspections in accordance with paragraph 3.B., Work Instructions, PART 3. All airplanes on which pivot pins have been replaced or reworked in accordance with paragraph 3.B., Work Instructions, PART 1 and PART 2.

- Before further flight. Replace the pivot pin inaccordance with paragraph 3.B., Work Instructions, PART 3.Any crack, corrosion damage, or other irregularity found in a pivot pin during PART 3 inspections.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 20 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Group 2:**  **Table 3: After Replacement / Rework**  **Inspections - 777-200LR, 777-300ER, and 777F Airplanes. Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs First) Action**  **Condition** Within 12,000 flight cycles or within 3,000 days, whichever occurs first, after the most recent inspection. - - Repeat the after replace- ment / rework detailed and ultrasonic inspectionsin accordance with paragraph 3.B., Work Instructions, PART 3.No crack, corrosion damage, or other irregularityfound during PART 3 inspections, or pivot pins that have been replaced.

**F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task hours necessary to do the horizontal stabilizer pivot pin replacement 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**  4.00 16.00 4 Pivot Pin Replace- ment (PART 1 and PART 2) (a) 5.50 22.00 4 PART 3 - After Re- placement / ReworkDetailed and Ultrasonic Inspections (a) 9.50 (b) 38.00 (b) TOTAL FOR EACH AIRPLANE (a) This task includes Removal and Installation steps.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 21 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Elapsed Hours**  **Task Hours Number of Persons**  **Task** (b) Estimate assumes existing pivot pins are replaced with new pivot pins that have improved resistance to corrosion. If pivot pins are reworked in accordance with FIGURE 1 and FIGURE 2, more time will be required. **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. Engineering Change Memo PRR 62777-78S b. Boeing Service Related Problem (SRP) 777-SRP-55-0049 c. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-10-03, 20-10-04, 20-20-01, 20-30-02, 20-30-03, 20-42-03, 20-50-08, 20-50-10 d. 777 Aircraft Maintenance Manual (AMM) 55-17-01 e. 777 Fleet Team Digest (FTD) 55-10001 f. 777 Illustrated Parts Catalog (IPC) 55-10-00 g. 777 Non-Destructive Testing (NDT) Manual Part 4, 55-17-01 h. Boeing Process Specifications BAC5736 and BAC5882 i. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2011-NM-181-AD 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin This drawing was used to prepare this service bulletin. This drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. This drawing may not be applicable to all airplane configurations.
**Title Drawing Number**  Horizontal Stabilizer Top Instl 180W0000

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 22 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT K. Publications Affected**  1. Publications: **Chapter-Section**

**Publication** 55-10 777 Illustrated Parts Catalog 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. **L. Interchangeability and Intermixability of Parts** Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability information.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 23 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 24 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 **REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** 
**Unit Price as of the original issue** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **original issue date of this Ser** **vice Bulletin (Cal endar Days)**  **QTY Date**  **Name Kit Number** 

$12,731.00 265 49 Available TOP KIT - 777 HORI- ZONTAL STABILIZER- PIVOT PIN - REPLACEMENT 005W3480-1

$13,751.00 300 17 October 11, 2012TOP KIT - 777 HORIZONTAL STABILIZER- PIVOT PIN - REPLACEMENT 005W3480-2

17 November 8, 2012 16 December 10, 2012 **B. Industry Support Information** Boeing warranty remedies are not available for the inspection and replacement procedures given in this service bulletin. **C. Parts Necessary For Each Airplane** 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. **NOTE:** One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. 1.
2. For Group 1 airplanes, original Top Kit 005W3480-1 plus two 182W6403-301 Anti-rotation plates, is equivalent to new Top Kit 005W3480-2.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 25 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Kit 005W3480**  **Notes Existing Part**  **Number Name**  **QTY New Part Number**  **-2 -1**  Group 2 and Group 3 - TOP KIT - 777 HORIZONTALSTABILIZER - PIVOT PIN - REPLACEMENT . - 005W3480-1

Group 1

- TOP KIT - 777 HORIZONTALSTABILIZER - PIVOT PIN - REPLACEMENT - . 005W3480-2

(a) (c) 182W6401-1 OUTER PIN - PIV- OT, HORIZONTAL STABILIZER 2 2 182W6401-303

(a) (c) 182W6401-2, -301 INNER PIN - PIV- OT, HORIZONTAL STABILIZER 2 2 182W6401-304

(b) 182W6402-1 SPACER - PIVOT, HORIZONTAL STABILIZER 1 1 182W6402-4

(b) 182W6402-2 SPACER - PIVOT, HORIZONTAL STABILIZER 2 2 182W6402-5

(b) 182W6402-3 SPACER - PIVOT, HORIZONTAL STABILIZER 1 1 182W6402-6

(a) (c) 182W6403-1 ANTI-ROTATION PLATE - PIVOT, HORIZONTAL STABILIZER 2

. 182W6403-301

(a) Discard the existing part or rework the existing part in accordance with this service bulletin. (b) Discard the existing part or the existing part can be re-used if it is inspected (using detailed inspection methods) and found to be free of cracks, corrosion damage, or other irregularity. (c) You cannot use the existing part to replace the new part unless the existing part has been reworked in accordance with this service bulletin. If you use the existing part (without rework) to replace the new part, you cancel the effect of the change given in this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 26 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** (a) Primer 2 Oz. BMS 10-79, Type III (BMS10-11, Type I optional) (a) Grease 2 Oz. BMS 3-33 (a) Solid (Dry) Film Lubricant 2 Oz. BMS 3-8 (b) Retention Pin 2 182W6401-5 (d) Anti-Rotation Plate 2 182W6403-1 (c) Anti-Rotation Plate 2 182W6403-301 (b) Nut 2 182W6404-5 (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) If necessary, for use during pivot pin installation. (c) Group 1 only, if 182W6401-301SP or 182W6401-304 inner pivot pins are installed and the existing 182W6403-1 anti-rotation plate is not reworked in accordance with FIGURE 3 of this service bulletin. (d) Group 3 only, if reworked 182W6401-2SP inner pivot pins are installed.
3. Parts Modified and Reidentified The parts shown in the following table are modified and reidentified only if the rework given in this service bulletin is accomplished. The QTY is the number of parts necessary for each airplane.
**Notes New Part Number**  **Name QTY**  **Existing Part Number**  (a) (b) 182W6401-1SP Outer Pivot Pin 2 182W6401-1 (a) (b) 182W6401-2SP Inner Pivot Pin 2 182W6401-2

------------------------ ------------------------ ------------------------ ------ OR (a) (b) 182W6401-301SP Inner Pivot Pin 2 182W6401-301 (b) (c) 005W3480-4 Anti-Rotation Plate 2 182W6403-1 (a) Make the change in accordance with this service bulletin. (b) The "New Part Number" is the part number after the change is done in accordance with this service bulletin. Refer to SOPM 20-50-10 as an accepted procedure to apply Code M part mark. (c) Group 1 only, reworked in accordance with FIGURE 3 as an alternative to new Anti-Rotation Plate 182W6403-301.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 27 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**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 have been developed specifically for this service bulletin. However, operators may choose to install temporary pins in the horizontal stabilizer pivot joints while existing pivot pins are being reworked. Refer to Appendix A for fabrication and installation of temporary pins. Accomplishment of the modification in this service bulletin requires that the horizontal stabilizer be supported to remove the load from the pivot joint. The J55004-1 Horizontal Stabilizer Jack described in 777 AMM 55-17-01 is an example of an appropriate tool for this purpose. However, J55004-1 is only appropriate for airplanes line number 1 - 40. A horizontal stabilizer jacking tool for airplanes after line number 40 is currently being designed. 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: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 28 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT 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 and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 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. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 7. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 8. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 29 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**9. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. The removed part can be discarded if a new or serviceable part is installed. 10. Deleted. 11. The Work Instructions given in this service bulletin assume that 182W6401-1 outer pivot pins reworked in accordance with this service bulletin are reidentified as 182W6401-1SP. 12. The Work Instructions given in this service bulletin assume that 182W6401-2 inner pivot pins reworked in accordance with this service bulletin are reidentified as 182W6401-2SP. 13. The Work Instructions given in this service bulletin assume that 182W6401-301 inner pivot pins reworked in accordance with this service bulletin are reidentified as 182W6401-301SP. 14. The pivot pins should only be removed from one side of the airplane at a time. **B. WORK INSTRUCTIONS Removal**  **CAUTION:** THIS PROCEDURE ALLOWS INSTALLATION OF TEMPORARY PIVOT PINS WHILE REWORK IS BEING DONE ON EXISTING PIVOT PINS. TEMPORARY PIVOT PINS ARE NOT APPROVED FOR FLIGHT AND MUST BE MARKED AS TEMPORARY WHILE IN USE. IF TEMPORARY PIVOT PINS ARE INSTALLED, MAKE SURE THEY ARE REMOVED, AND NEW OR REWORKED PIVOT PINS INSTALLED, BEFORE FLIGHT. 1. For the initial pivot pin and spacer removal, get access, remove the load from the horizontal stabilizer pivot joint, and remove the following parts from the airplane. Refer to 777 AMM 55-17-01 as an accepted procedure. **NOTE:** If the existing pivot pins will be reworked, it is acceptable to install temporary pins while the rework is being done. Refer to Appendix A for fabrication and installation of temporary pins.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 30 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT More Data**  **Quantity per Airplane**  **Part Name Part Number** 
Refer to 777 IPC 55-10-00. 2 Outer Pivot Pin 182W6401-1 2 Inner Pivot Pin 182W6401-2 or 182W6401-301 1 Spacer 182W6402-1 2 Spacer 182W6402-2 1 Spacer 182W6402-3 2 Anti-Rotation Plate 182W6403-1 (Group 1 on- ly) or 182W6403-301 (Group 2 and Group 3) **PART 1 - Left Side Pivot Pin Replacement or Rework** 1. Remove the existing horizontal stabilizer inner and outer pivot pins and spacers. Refer to the Removal steps as an accepted procedure. 2. For the existing Left Side horizontal stabilizer pivot joint outer pin, do one of the following: a. Replace the existing 182W6401-1 outer pivot pin with a new 182W6401-303 outer pivot pin.

or b. Rework the existing 182W6401-1 outer pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the outer pivot pin with a 182W6401-1SP outer pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework. 3. **Group 1:** For the existing Left Side horizontal stabilizer pivot joint inner pin, do one of the following pin replacement steps (and the anti-rotation plate replacement step, as necessary): a. Replace the existing 182W6401-2 inner pivot pin with a new 182W6401-304 inner pivot pin. Also replace the existing 182W6403-1 anti-rotation plate with a 182W6403-301 anti-rotation plate. **NOTE:** As an alternative to the replacement of the 182W6403-1 anti-rotation plate, rework the existing 182W6403-1 anti-rotation plate in accordance with FIGURE 3 or replace the anti-rotation plate with a 005W3480-4 anti-rotation plate that has been reworked in accordance with FIGURE 3.

or b. Rework the existing 182W6401-2 inner pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the inner pivot pin with a 182W6401-2SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework.

or

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 31 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**c. Rework the existing 182W6401-2 inner pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework. Also replace the existing 182W6403-1 anti-rotation plate with a 182W6403-301 anti-rotation plate. **NOTE:** As an alternative to the replacement of the 182W6403-1 anti-rotation plate, rework the existing 182W6403-1 anti-rotation plate in accordance with FIGURE 3 or replace the anti-rotation plate with a 005W3480-4 anti-rotation plate that has been reworked in accordance with FIGURE 3.
4. **Group 2:** For the existing Left Side horizontal stabilizer pivot joint inner pin, do one of the following pin replacement steps (and the anti-rotation plate replacement step, as necessary): a. Replace the existing 182W6401-301 inner pivot pin with a new 182W6401-304 inner pivot pin.

or b. Rework the existing 182W6401-301 inner pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework.
5. **Group 3:** For the existing Left Side horizontal stabilizer pivot joint inner pin, do one of the following pin replacement steps (and the anti-rotation plate replacement step, as necessary): a. Replace the existing 182W6401-301 inner pivot pin with a new 182W6401-304 inner pivot pin.

or b. Rework the existing 182W6401-301 inner pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework.

or c. Replace the existing 182W6401-301 inner pivot pin with a 182W6401-2SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework. Also replace the existing 182W6403-301 anti-rotation plate with a 182W6403-1 anti-rotation plate. 6. Replace the existing 182W6402-1 spacer with a 182W6402-4 spacer. As an alternative to replacement, do a detailed inspection of the existing 182W6402-1 spacer for corrosion damage or other irregularity. a. If any corrosion damage or other irregularity is found, replace the existing 182W6402-1 spacer with a 182W6402-4 spacer or another serviceable 182W6402-1 spacer. Before installing another serviceable 182W6402-1 spacer, apply primer in accordance with PART 5 - Spacer Refinish.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 32 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**b. If no corrosion damage or other irregularity is found, the existing spacer can be re-installed. Before re-installing the existing spacer, apply primer in accordance with PART 5 - Spacer Refinish. 7. Replace the existing 182W6402-2 spacer with a 182W6402-5 spacer. As an alternative to replacement, do a detailed inspection of the existing 182W6402-2 spacer for corrosion damage or other irregularity. a. If any corrosion damage or other irregularity is found, replace the existing 182W6402-2 spacer with a 182W6402-5 spacer or another serviceable 182W6402-2 spacer. Before installing another serviceable 182W6402-2 spacer, apply primer in accordance with PART 5 - Spacer Refinish. b. If no corrosion damage or other irregularity is found, the existing spacer can be re-installed. Before re-installing the existing spacer, apply primer in accordance with PART 5 - Spacer Refinish. 8. Install the horizontal stabilizer inner and outer pivot pins and spacers. Refer to the Installation steps as an accepted procedure. Apply grease BMS 3-33 to the inner and outer diameters of the anti-rotation plate before installation. **PART 2 - Right Side Pivot Pin Replacement or Rework** 1. Remove the existing horizontal stabilizer inner and outer pivot pins and spacers. Refer to the Removal steps as an accepted procedure. 2. For the existing Right Side horizontal stabilizer pivot joint outer pin, do one of the following: a. Replace the existing 182W6401-1 outer pivot pin with a new 182W6401-303 outer pivot pin.

or b. Rework the existing 182W6401-1 outer pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the outer pivot pin with a 182W6401-1SP outer pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework. 3. **Group 1:** For the existing Right Side horizontal stabilizer pivot joint inner pin, do one of the following pin replacement steps (and the anti-rotation plate replacement step, as necessary): a. Replace the existing 182W6401-2 inner pivot pin with a new 182W6401-304 inner pivot pin. Also replace the existing 182W6403-1 anti-rotation plate with a 182W6403-301 anti-rotation plate. **NOTE:** As an alternative to the replacement of the 182W6403-1 anti-rotation plate, rework the existing 182W6403-1 anti-rotation plate in accordance with FIGURE 3 or replace the anti-rotation plate with a 005W3480-4 anti-rotation plate that has been reworked in accordance with FIGURE 3.

or

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 33 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**b. Rework the existing 182W6401-2 inner pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the inner pivot pin with a 182W6401-2SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework.

or c. Rework the existing 182W6401-2 inner pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework. Also replace the existing 182W6403-1 anti-rotation plate with a 182W6403-301 anti-rotation plate. **NOTE:** As an alternative to the replacement of the 182W6403-1 anti-rotation plate, rework the existing 182W6403-1 anti-rotation plate in accordance with FIGURE 3 or replace the anti-rotation plate with a 005W3480-4 anti-rotation plate that has been reworked in accordance with FIGURE 3.
4. **Group 2:** For the existing Right Side horizontal stabilizer pivot joint inner pin, do one of the following pin replacement steps (and the anti-rotation plate replacement step, as necessary): a. Replace the existing 182W6401-301 inner pivot pin with a new 182W6401-304 inner pivot pin.

or b. Rework the existing 182W6401-301 inner pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework.
5. **Group 3:** For the existing Right Side horizontal stabilizer pivot joint inner pin, do one of the following pin replacement steps (and the anti-rotation plate replacement step, as necessary): a. Replace the existing 182W6401-301 inner pivot pin with a new 182W6401-304 inner pivot pin.

or b. Rework the existing 182W6401-301 inner pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework.

or c. Replace the existing 182W6401-301 inner pivot pin with a 182W6401-2SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework. Also replace the existing 182W6403-301 anti-rotation plate with a 182W6403-1 anti-rotation plate. 6. Replace the existing 182W6402-3 spacer with a 182W6402-6 spacer. As an alternative to replacement, do a detailed inspection of the existing 182W6402-3 spacer for corrosion damage or other irregularity.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 34 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**a. If any corrosion damage or other irregularity is found, replace the existing 182W6402-3 spacer with a 182W6402-6 spacer or another serviceable 182W6402-3 spacer. Before installing another serviceable 182W6402-3 spacer, apply primer in accordance with PART 5 - Spacer Refinish. b. If no corrosion damage or other irregularity is found, the existing spacer can be re-installed. Before re-installing the existing spacer, apply primer in accordance with PART 5 - Spacer Refinish. 7. Replace the existing 182W6402-2 spacer with a 182W6402-5 spacer. As an alternative to replacement, do a detailed inspection of the existing 182W6402-2 spacer for corrosion damage or other irregularity. a. If any corrosion damage or other irregularity is found, replace the existing 182W6402-2 spacer with a 182W6402-5 spacer or another serviceable 182W6402-2 spacer. Before installing another serviceable 182W6402-2 spacer, apply primer in accordance with PART 5 - Spacer Refinish. b. If no corrosion damage or other irregularity is found, the existing spacer can be re-installed. Before re-installing the existing spacer, apply primer in accordance with PART 5 - Spacer Refinish. 8. Install the horizontal stabilizer inner and outer pivot pins and spacers. Refer to the Installation steps as an accepted procedure. Apply grease BMS 3-33 to the inner and outer diameters of the anti-rotation plate before installation. **PART 3 - After Replacement / Rework**  **Detailed and Ultrasonic Inspections** 1. Remove the horizontal stabilizer inner and outer pivot pins. Get access, remove the load from the horizontal stabilizer pivot joint, and remove the following parts from the airplane. Refer to 777 AMM 55-17-01 as an accepted procedure for removal.
**More Data Quantity per**  **Airplane Part Name**  **Part Number**
Refer to 777 IPC 55-10-00. 2 Outer Pivot Pin 182W6401-303 or 182W6401-1SP 2 Inner Pivot Pin 182W6401-304 or 182W6401-2SP or 182W6401-301SP 2. Do a detailed inspection of the outer pivot pins and inner pivot pins for cracks, corrosion damage, or other irregularity. 3. Do an ultrasonic inspection of the outer pivot pins for cracks in accordance with 777 NDT Part 4, 55-17-01. **NOTE:** Ultrasonic inspection of the outer pivot pins in accordance with 777 NDT Part 4, 55-17-01 can be done with the outer pivot pins installed or removed. Because the pivot pins need to be removed for detailed inspection, Boeing recommends that the ultrasonic inspection be done with the outer pivot pins removed. If removed, clean the inner and outer diameters of the outer pivot pins before inspection.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 35 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**4. If any crack, corrosion damage, or other irregularity is found on an outer pivot pin, replace it with a new or serviceable outer pivot pin with part number 182W6401-303 or 182W6401-1SP. Discard the damaged pin.
5. **Group 1, 3:** If any crack, corrosion damage, or other irregularity is found on an inner pivot pin, replace it with a new or serviceable inner pivot pin with part number 182W6401-304 or 182W6401-2SP or 182W6401-301SP. Discard the damaged pin. a. If a 182W6401-2SP inner pivot pin is replaced with a 182W6401-301SP or a 182W6401-304 inner pivot pin, also replace the existing 182W6403-1 anti-rotation plate with a 182W6403-301 anti-rotation plate. As an alternative, rework the existing 182W6403-1 anti-rotation plate in accordance with FIGURE 3 or replace the anti-rotation plate with a 005W3480-4 anti-rotation plate that has been reworked in accordance with FIGURE 3. b. If a 182W6401-301SP or a 182W6401-304 inner pivot pin is replaced with a 182W6401-2SP inner pivot pin, also replace the existing 182W6403-301 anti-rotation plate with a 182W6403-1 anti-rotation plate. 6. **Group 2:** If any crack, corrosion damage, or other irregularity is found on an inner pivot pin, replace it with a new or serviceable inner pivot pin with part number 182W6401-304 or 182W6401-301SP. Discard the damaged pin. 7. If no crack, corrosion damage, or other irregularity is found or damaged pins have been replaced, repeat the detailed and ultrasonic inspections in accordance with Paragraph 1.E., Compliance. 8. Install the horizontal stabilizer inner and outer pivot pins. Refer to the Installation steps as an accepted procedure. **PART 4 - Pivot Pin Rework** 1. Rework the 182W6401-1 outer pivot pin in accordance with FIGURE 1. If any crack is found during inspections required by FIGURE 1, discard the pin. 2. Rework the 182W6401-2 or 182W6401-301 inner pivot pin in accordance with FIGURE 2. If any crack is found during inspections required by FIGURE 2, discard the pin. 3. Make sure all reworked pivot pins are reidentified with an "SP" part number in accordance with Paragraph 2.C.3., Parts Modified and Reidentified. The "SP" part mark on a pivot pin will indicate that the pin has been shot peened. **PART 5 - Spacer Refinish** 1. For 182W6402-1 spacers: Manually apply wipe-on BMS10-79, Type III primer (F-19.451) or wipe-on BMS10-11, Type I primer (F-19.45) to the outer diameter, except no primer on the threads. Refer to BAC5882 as an accepted procedure for application of wipe-on BMS10-79, Type III or refer to BAC5736 as an accepted procedure for application of wipe-on BMS 10-11, Type I. 2. For 182W6402-2 spacers: Manually apply wipe-on BMS10-79, Type III primer (F-19.451) or wipe-on BMS10-11, Type I primer (F-19.45) to the outer diameter. Refer to BAC5882 as an accepted procedure for application of wipe-on BMS10-79, Type III or refer to BAC5736 as an accepted procedure for application of wipe-on BMS 10-11, Type I.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 36 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**3. For 182W6402-3 spacers: Manually apply wipe-on BMS10-79, Type III primer (F-19.451) or wipe-on BMS10-11, Type I primer (F-19.45) to the outer diameter. Refer to BAC5882 as an accepted procedure for application of wipe-on BMS10-79, Type III or refer to BAC5736 as an accepted procedure for application of wipe-on BMS 10-11, Type I. **Installation** 1. Install horizontal stabilizer pivot joint pins and installation hardware. Refer to 777 AMM 55-17-01 as an accepted procedure. Make sure to apply sufficient BMS3-33 grease to provide visible squeeze out of grease between components in the joints. 2. Return the airplane to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1: March 06, 2012 37 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK**  **(SHEET 1 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1 March 06, 2012 38 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK**  **(SHEET 2 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1 March 06, 2012 39 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each component.
**MORE DATA QTY**  **IDENTIFICA- TION**  **NAME TASK**  **STEP**
Refer to SOPM 20-30-02 as anaccepted procedure. - - Existing Chrome Plate Remove 1

(a)

- - Existing Solid(Dry) Film Lubricant Remove 2

Do a magneticparticle inspection of the pin. (b) - - Outer Pivot Pin Inspect 3

(c)

- - Outer Pivot Pin Machine 4 (d)

- - Outer Pivot Pin Heat Treat 5 (e)

- - Outer Pivot Pin Shot Peen 6 (f)

- F-15.34 Chromium Plate Apply 7 (g)

- - Outer Pivot Pin Grind 8 (h)

- BMS3-8 Solid Film Lubri- cant Apply 9 (i) 1 Oz. BMS10-79, Type III Primer Apply 10 BMS10-11, Type I (optional) (j)

- - Marking Apply 11 (a) If not removed during the previous step, remove existing solid film lubricant from the threads and inner diameter. Refer to SOPM 20-30-02 as an accepted procedure.(b) Refer to SOPM 20-20-01 as an accepted procedure. If any crack is found during magnetic particle inspection, discard the outer pivot pin. (c) Machine the outer diameter of the pin to the "before plating" diameter, as shown. Maintain surface finish of 63 Microinches Ra or better. Maintain 0.050 - 0.070 inch radius under the head as shown. (d) Stress relieve the outer pivot pin at 875 degrees F for 1-4 hours. Refer to SOPM 20-10-02 as an accepted procedure. (e) Shot peen the outer diameter of the pin. Refer to SOPM 20-10-03 as an accepted procedure. Intensity = 0.012A to 0.017A. Coverage = 2.0. Overspray allowed on all areas, except threads and inner diameter. Make sure to maintain the "before plating" diameter. (f) Apply Class 3 chrome plate (F-15.34) to the outer diameter of the pin. Refer to SOPM 20-42-03 as an accepted procedure.

**FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1 March 06, 2012 40 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICA-**  **TION NAME**  **TASK STEP**  (g) Grind the outer diameter of the pivot pin to meet the "after plating" dimension shown. Refer to SOPM 20- 10-04 as an accepted procedure. Make sure the final surface finish is 16 Microinches Ra or better. (h) Apply BMS3-8 solid film lubricant (F-19.10) to the threads and inner diameter. Refer to SOPM 20-50-08, Type 8. (i) Solvent clean the outer diameter of the pin. Refer to SOPM 20-30-03 as an accepted procedure. Manually apply wipe-on BMS10-79, Type III primer (F-19.451) or wipe-on BMS10-11, Type I primer (F-19.45) to the outer diameter. Refer to BAC5882 as an accepted procedure for application of wipe-on BMS10-79, Type III or refer to BAC5736 as an accepted procedure for application of wipe-on BMS 10-11, Type I. (j) Change the part number of the reworked outer pin to the new part number given in paragraph 2.C.3., Parts Modified and Reidentified. Refer to SOPM 20-50-10 as an accepted procedure to apply Code M part mark.

**FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1 March 06, 2012 41 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each component.
**MORE DATA QTY**  **IDENTIFICA- TION**  **NAME TASK**  **STEP**
Refer to SOPM 20-30-02 as anaccepted procedure. - - Existing Chrome Plate Remove 1

(a)

- - Existing Solid(Dry) Film Lubricant Remove 2

Do a magneticparticle inspection of the pin. (b) - - Inner Pivot Pin Inspect 3

**FIGURE 2: 182W6401-2 OR 182W6401-301 INNER PIVOT PIN REWORK (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1 March 06, 2012 42 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICA-**  **TION NAME**  **TASK STEP**  (c)

- - Inner Pivot Pin Machine 4 (d)

- - Inner Pivot Pin Heat Treat 5 (e)

- - Inner Pivot Pin Shot Peen 6 (f)

- F-15.34 Chromium Plate Apply 7 (g)

- - Inner Pivot Pin Grind 8 (h)

- BMS3-8 Solid Film Lubri- cant Apply 9 (i) 1 Oz. BMS10-79, Type III Primer Apply 10 BMS10-11, Type I (optional) (j)

- - Marking Apply 11 (a) If not removed during the previous step, remove existing solid film lubricant from the threads. Refer to SOPM 20-30-02 as an accepted procedure.(b) Refer to SOPM 20-20-01 as an accepted procedure. If any crack is found during magnetic particle inspection, discard the inner pivot pin. (c) Machine the outer diameter of the pin to the "before plating" diameter, as shown. Maintain surface finish of 63 Microinches Ra or better. Maintain 0.050 - 0.070 inch radius under the head as shown. (d) Stress relieve the inner pivot pin at 875 degrees F for 1-4 hours. Refer to SOPM 20-10-02 as an accepted procedure. (e) Shot peen the outer diameter of the pin. Refer to SOPM 20-10-03 as an accepted procedure. Intensity = 0.012A to 0.017A. Coverage = 2.0. Overspray allowed on all areas, except threads. Make sure to maintain the "before plating" diameter. (f) Apply Class 3 chrome plate (F-15.34) to the outer diameter of the pin. Refer to SOPM 20-42-03 as an accepted procedure. (g) Grind the outer diameter of the pivot pin to meet the "after plating" dimension shown. Refer to SOPM 20- 10-04 as an accepted procedure. Make sure the final surface finish is 16 Microinches Ra or better. (h) Apply BMS3-8 solid film lubricant (F-19.10) to the threads. Refer to SOPM 20-50-08, Type 8. (i) Solvent clean the outer diameter of the pin. Refer to SOPM 20-30-03 as an accepted procedure. Manually apply wipe-on BMS10-79, Type III primer (F-19.451) or wipe-on BMS10-11, Type I primer (F-19.45) to the outer diameter. Refer to BAC5882 as an accepted procedure for application of wipe-on BMS10-79, Type III or refer to BAC5736 as an accepted procedure for application of wipe-on BMS 10-11, Type I. (j) Change the part number of the reworked inner pin to the new part number given in paragraph 2.C.3., Parts Modified and Reidentified. Refer to SOPM 20-50-10 as an accepted procedure to apply Code M part mark.

**FIGURE 2: 182W6401-2 OR 182W6401-301 INNER PIVOT PIN REWORK (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1 March 06, 2012 43 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT This Figure applies only to: Group 1.** 

**FIGURE 3: 182W6403-1 ANTI-ROTATION PLATE REWORK (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1 March 06, 2012 44 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each component.
**MORE DATA QTY**  **IDENTIFICA- TION**  **NAME TASK**  **STEP** (a)

- - Anti-rotation Plate Clean 1 (b)

- - Anti-rotation Plate Machine 2

as shown.

- - Anti-rotation Plate Chamfer 3 Do a magneticparticle inspection of the part. (c) - - Anti-rotation Plate Inspect 4

(d)

- - Finish Apply 5 (e)

- - Marking Apply 6 (a) Clean the part as necessary to accomplish the rework. Refer to SOPM 20-30-03 as an accepted procedure.(b) Machine the outer diameter of the anti-rotation plate to the diameter shown. Blend new diameter into existing relief cut to create new 0.050 - 0.070 inch radius as shown. Break sharp edges 0.010 - 0.020 R after machining. Maintain surface finish of 125 Microinches Ra or better on all machined surfaces.(c) Refer to SOPM 20-20-01 as an accepted procedure. If any crack is found during magnetic particle inspection, discard the part. (d) Passivate the entire part. Refer to SOPM 20-30-03 or BAC5625, Method II as an accepted procedure. As an option, locally passivate only the newly machined areas of the part. (e) Change the part number of the reworked anti-rotation plate to the new part number given in Paragraph 2.C.3., Parts Modified and Reidentified. Refer to SOPM 20-50-10 as an accepted procedure to apply Code RO part mark.

**FIGURE 3: 182W6403-1 ANTI-ROTATION PLATE REWORK (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1 March 06, 2012 45 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**Fabricate temporary pins, as necessary, for installation in the horizontal stabilizer pivot joints while the inner and outer pivot pins are being reworked. Fabricate temporary pins from 150 ksi minimum 15-5PH stainless steel. Fabricate temporary pins to the dimensions shown in Illustration 1. Install the temporary pins as shown in Illustration 2. **NOTE:** TEMPORARY PINS ARE NOT APPROVED FOR FLIGHT.

**APPENDIX A: HORIZONTAL STABILIZER TEMPORARY PIVOT PIN FABRICATION/INSTALLATION (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1 March 06, 2012 46 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT NOTE:**  RETENTION BOLT: INSTALL ANY AVAILABLE 1/4 INCH BOLT, WASHERS, AND LOCK NUT TO ENSURE THE TEMPORARY PIN CANNOT MIGRATE OUT OF THE JOINT. IF BOLTS ARE NOT AVAILABLE, OTHER RETENTION METHODS THAT KEEP THE PIN FROM MIGRATING ARE ACCEPTABLE.

**APPENDIX A: HORIZONTAL STABILIZER TEMPORARY PIVOT PIN FABRICATION/INSTALLATION (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 Revision 1 March 06, 2012 47 of 47 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**