### Commercial **Airplanes** 

# 777 Service Bulletin **ALERT Number: 777-55A0018**  Original Issue: July 27, 2011 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 1 of 38 4.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 2 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 18 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 18 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 20 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 21 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK. . . . . . . . . . . . . . . . . . . . . . . . . 31 FIGURE 2: 182W6401-2 OR 182W6401-301 INNER PIVOT PIN REWORK. . . . . . . . . . . . . . 35 APPENDIX A: HORIZONTAL STABILIZER TEMPORARY PIVOT PIN FABRICATION/INSTALLATION . 37

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 3 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 4 of 38 **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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 5 of 38**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** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. 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.
**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 6 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 7 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 8 of 38 **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 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 868.

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

Airplane Models: 777-200, 777-200LR, 777-300, 777-300ER, 777F **Group Variable Number**  1 WA001 - WA017 1 WA076 - WA080 1 WA086 - WA093 1 WA101 - WA104 1 WA116 - WA119

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 9 of 38**Group Variable Number**  1 WA131 - WA137 1 WA171 - WA175 1 WA196 - WA198 1 WA206 - WA212 1 WA221 - WA223 1 WA231 - WA232 1 WA241 - WA250 1 WA261 - WA266 1 WA281 - WA283 1 WA301 - WA304 1 WB001 - WB021 1 WB031 - WB046 1 WB051 - WB088 1 WB101 - WB106 1 WB121 - WB125 1 WB131 - WB148 1 WB151 - WB155 1 WB161 - WB177 1 WB181 - WB194 1 WB201 - WB215 1 WB231 - WB247 1 WB271 - WB273 1 WB276 - WB286 1 WB291 - WB302 1 WB306 - WB307 1 WB311 - WB337 1 WB341 - WB342 1 WB366 - WB368 1 WB371 - WB388 1 WB406 1 WB411 - WB413 1 WB416 - WB439 1 WB446 - WB453

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 10 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Group**  **Variable Number** 1 WB476 1 WB481 - WB484 1 WB501 - WB512 1 WB531 - WB537 1 WB551 - WB554 1 WB591 - WB597 1 WB601 - WB606 1 WB611 - WB622 1 WB631 - WB638 1 WB646 - WB649 1 WC051 - WC073 1 WC101 - WC104 1 WC111 - WC120 1 WC221 - WC224 1 WC241 - WC243 1 WC281 - WC290 1 WC301 - WC308 1 WC361 - WC364 1 WC371 - WC374 1 WC381 - WC395 1 WC441 1 WC446 - WC449 1 WC456 - WC459 1 WC486 - WC493 1 WC506 - WC508 1 WC521 - WC522 1 WC531 - WC536 1 WC546 - WC548 1 WC556 1 WC566 - WC567 1 WC571 - WC574 1 WC581 2 WD001 - WD002

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 11 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Group**  **Variable Number** 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 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 12 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Group**  **Variable Number** 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 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 13 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**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. **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. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**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** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 14 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Table 1: Horizontal Stabilizer Pivot Pin Replacement**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 750 days after the original issue 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 with new pivot pinsin accordance with paragraph 3.B., Work Instructions, PART 1. ORDo the pivot pin replacement with reworked pivot pins in accordance withparagraph 3.B., Work Instructions, PART 2. All airplanes.

**Group 1: Table 2: After Replacement 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 in accordance with paragraph 3.B.,Work Instructions, PART 1 or PART 2. Within 32,000flight cycles after accomplishment of the pivot pin replacement in accordance with paragraph 3.B.,Work Instructions, PART 1 or PART 2. Do the after replacement detailed and ultrasonic inspections in accordance with paragraph 3.B., Work Instructions, PART 3. All airplanes on which pivot pins have been replaced in accordance with paragraph 3.B., Work Instructions, PART 1 or 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. - - Repeat the after replace-ment detailed and ultrasonic inspections in 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 15 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Group 2:**  **Table 3: After Replacement 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 in accordance with paragraph 3.B.,Work Instructions, PART 1 or PART 2. Within 32,000flight cycles after accomplishment of the pivot pin replacement in accordance with paragraph 3.B.,Work Instructions, PART 1 or PART 2. Do the after replacement detailed and ultrasonic inspections in accordance with paragraph 3.B., Work Instructions, PART 3. All airplanes on which pivot pins have been replaced in accordance with paragraph 3.B., Work Instructions, PART 1 or 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. Within 12,000 flight cycles or within 3,000 days, whichever occurs first. - - Repeat the after replace-ment detailed and ultrasonic inspections in 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 16 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**• 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 or PART 2) (a) 5.50 22.00 4 PART 3 - After Re- placement Detailedand Ultrasonic Inspections (a) 9.50 (b) 38.00 (b) TOTAL FOR EACH AIRPLANE (a) This task includes Removal and Installation steps. (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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 17 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**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
**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 18 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT 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** 

$11,452.00 206 1 April 14, 2011 TOP KIT - 777 HORI- ZONTAL STABILIZER- PIVOT PIN - REPLACEMENT 005W3480-1 99 July 01, 2011

**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.
**Kit 005W3480-1 Notes**  **Existing Part Num- ber**  **Name QTY**  **New Part Number** (a) (c) 182W6401-1 Outer Pin - Pivot, Horizontal Stabilizer 2 182W6401-303 (a) (c) 182W6401-2, -301 Inner Pin - Pivot, Horizontal Stabilizer 2 182W6401-304

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 19 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT Kit 005W3480-1**  **Notes Existing Part Num-**  **ber Name**  **QTY New Part Number**  (b) 182W6402-1 Spacer - Pivot, Horizontal Stabilizer 1 182W6402-4 (b) 182W6402-2 Spacer - Pivot, Horizontal Stabilizer 2 182W6402-5 (b) 182W6402-3 Spacer - Pivot, Horizontal Stabilizer 1 182W6402-6 (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.

2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** (a) Primer 2 Oz. BMS10-79, Type III (BMS10-11, Type I optional) (a) Grease 2 Oz. BMS3-33 (a) Solid (Dry) Film Lubricant 2 Oz. BMS3-8 (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
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 (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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 20 of 38 **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. In addition, 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 21 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 22 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**

BLANK PAGE**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 23 of 38 **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. Do not intermix new pivot pins and reworked pivot pins on the same airplane during PART 1 or PART 2 pivot pin replacement. Intermixing is allowed if a pivot pin needs to be replaced during PART 3 inspections. 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 outer 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 outer pivot pins reworked in accordance with this service bulletin are reidentified as 182W6401-301SP. **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 and remove the following parts from the airplane. Refer to 777 AMM 55-17-01 as an accepted procedure for removal. **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.
**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. For pivot pin removal after PART 1 has been accomplished, get access and remove the following parts from the airplane. Refer to 777 AMM 55-17-01 as an accepted procedure for removal.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 24 of 38 **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 182W6401-303 2 Inner Pivot Pin 182W6401-304 3. For pivot pin removal after PART 2 has been accomplished, get access 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 182W6401-1SP 2 Inner Pivot Pin 182W6401-2SP or 182W6401-301SP **PART 1 - Pivot Pin Replacement with New Pivot Pins that have Improved Resistance to Corrosion (182W6401-303 outer pivot pin, 182W6401-304 inner pivot pin)**  1. Remove the existing horizontal stabilizer inner and outer pivot pins and spacers. Refer to the Removal steps as an accepted procedure. 2. Do the following for the Left Side horizontal stabilizer pivot joint: a. Replace the existing 182W6401-1 outer pivot pin with a new 182W6401-303 outer pivot pin. b. Replace the existing 182W6401-2 or 182W6401-301 inner pivot pin with a new 182W6401-304 inner pivot pin. c. 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. (1) 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. (2) 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. d. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 25 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**(1) 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. (2) 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. 3. Do the following for the Right Side horizontal stabilizer pivot joint: a. Replace the existing 182W6401-1 outer pivot pin with a new 182W6401-303 pivot pin. b. Replace the existing 182W6401-2 or 182W6401-301 inner pivot pin with a new 182W6401-304 pivot pin. c. 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 or other irregularity. (1) 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. (2) 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. d. 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 or other irregularity. (1) 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. (2) 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. 4. Install the horizontal stabilizer inner and outer pivot pins and spacers. Refer to the Installation steps as an accepted procedure. **PART 2 - Pivot Pin Replacement with Reworked Pivot Pins (Reworked in Accordance with PART 4)**  1. Remove the existing horizontal stabilizer inner and outer pivot pins and spacers. Refer to the Removal steps as an accepted procedure. 2. Do the following for the Left Side horizontal stabilizer pivot joint:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 26 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**a. 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. b. **Group 1:** Rework the existing 182W6401-2 or 182W6401-301 inner pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the inner pivot pin with a 182W6401-2SP or 182W6401-301SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework.

c. **Group 2:** 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. d. 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. (1) 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. (2) 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. e. 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. (1) 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. (2) 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. 3. Do the following for the Right Side horizontal stabilizer pivot joint:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 27 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**a. 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. b. **Group 1:** Rework the existing 182W6401-2 or 182W6401-301 inner pivot pin in accordance with PART 4 - Pivot Pin Rework or replace the inner pivot pin with a 182W6401-2SP or 182W6401-301SP inner pivot pin that has been reworked in accordance with PART 4 - Pivot Pin Rework.

c. **Group 2:** 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. d. 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 or other irregularity. (1) 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. (2) 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. e. 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 or other irregularity. (1) 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. (2) 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. 4. Install the horizontal stabilizer inner and outer pivot pins and spacers. Refer to the Installation steps as an accepted procedure. **PART 3 - After Replacement Detailed and Ultrasonic Inspections** 1. Remove the horizontal stabilizer inner and outer pivot pins. Refer to the Removal steps as an accepted procedure. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 28 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT 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. 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:** 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. 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 1, 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 27, 2011 777-55A0018 29 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT 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. 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 30 of 38 **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 31 of 38 **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 32 of 38 **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) 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 33 of 38 **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 34 of 38 **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 35 of 38 **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) 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 36 of 38 **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 37 of 38 **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 38 of 38 **BOEING SERVICE BULLETIN 777-55A0018 ALERT**  **ALERT**