### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Number: 777-32-0083**  Original Issue: February 05, 2009 Revision 1: February 17, 2011 ATA System: 3211 **SUBJECT:** LANDING GEAR - Main Landing Gear - Retract Actuator Fuse Pin Inspection 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 1 of 30 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 2 of 30 **BOEING SERVICE BULLETIN 777-32-0083**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 15 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 18 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 18 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 FIGURE 1: LEFT MLG RETRACT ACTUATOR FUSE PIN INSPECTION . . . . . . . . . . . . . . . . 21 FIGURE 2: RIGHT MLG RETRACT ACTUATOR FUSE PIN INSPECTION . . . . . . . . . . . . . . . 23 FIGURE 3: LEFT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT. . . . . . . . . . . . . . 25 FIGURE 4: RIGHT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT. . . . . . . . . . . . . 28

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 3 of 30 **BOEING SERVICE BULLETIN 777-32-0083**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 4 of 30 **BOEING SERVICE BULLETIN 777-32-0083**

BLANK PAGE

### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Revision Transmittal Sheet**  **Number: 777-32-0083** Original Issue: February 05, 2009 Revision 1: February 17, 2011 ATA System: 3211 **SUBJECT:** LANDING GEAR - Main Landing Gear - Retract Actuator Fuse Pin Inspection and Replacement This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** No more work is necessary on the airplane(s) changed in accordance with the original issue of this service bulletin. **REASON FOR REVISION** This revision is sent to add an optional material for the Corrosion Inhibiting Material. These sections were changed: 1. In Paragraph 2.A., Material - Price and Availability, updated table to current standards. 2. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added BMS3-38 as optional to BMS3-27 in Part Number Specification column. 3. In Paragraph 3.A., General Information, added Note 5, 6, 8 and 9 to the note list. 4. In Figure 3, step 3, added BMS3-38 as optional to BMS3-27 in Identification column. 5. In Figure 3, step 7, added BMS3-38 as optional to BMS3-27 in Identification column. 6. In Figure 4, step 3, added BMS3-38 as optional to BMS3-27 in Identification column. 7. In Figure 4, step 7, added BMS3-38 as optional to BMS3-27 in Identification column. The data given in Information Notice 777-32-0083 IN 01 is included in this revision. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 5 of 30**REVISION HISTORY** February 05, 2009 Original Issue: February 17, 2011 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 6 of 30 **BOEING SERVICE BULLETIN 777-32-0083**

### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Summary**  **Number: 777-32-0083** Original Issue: February 05, 2009 Revision 1: February 17, 2011 ATA System: 3211 **SUBJECT:** LANDING GEAR - Main Landing Gear - Retract Actuator Fuse Pin Inspection and Replacement BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** Accomplishment of this service bulletin will find and replace 112W1769-1 Retract Actuator Fuse Pins. The 112W1769-1 Retract Actuator Fuse Pins have been found to crack and fail earlier than the previously determined safe life limit of the pins. A fractured Retract Actuator Fuse Pin can cause the main landing gear (MLG) to extend without restriction and attempt to lock into position under high dynamic loads. Unrestricted MLG extension could cause structural damage to the side and drag brace lock assemblies, leading to unlocked drag and/or side braces which could result in landing gear collapse during touchdown, rollout or taxi. One operator reported that a right MLG 112W1769-1 pin sheared during normal flight operations. The failure occurred on a pin with 10,874 flight cycles. The left MLG pin was also inspected and was found to be cracked. Examination of the sheared pin concluded that the cracking was due to fatigue. Three other pins that were reported to have cracks had between 10,000 and 11,000 flight cycles. This service bulletin provides instructions to inspect the left and right MLG for 112W1769-1 Retract Actuator Fuse Pins and to replace the affected pins with 112W1769-3 pins. Boeing Service Related Problem (SRP) 777-SRP-57-0226 is related to this service bulletin. Boeing Service Letter (SL) 777-SL-57-011 is related to this service bulletin. Boeing Fleet Team Digest Article (FTD) 777 FTD 57-08005 is related to this service bulletin. **ACTION** Get access to the left and right MLG Retract Actuator Fuse Pins. Do an inspection of the Retract Actuator Fuse Pins to identify the part number. If an affected pin is found, replace the pin. If an affected pin is not found, no further action is required at that pin location.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 7 of 30**EFFECTIVITY** 777-200 and 777-300 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. **COMPLIANCE** Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this service bulletin. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  3.00 4.50 All
**MATERIAL INFORMATION** Boeing and Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 8 of 30 **BOEING SERVICE BULLETIN 777-32-0083**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 9 of 30 **BOEING SERVICE BULLETIN 777-32-0083**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 10 of 30 **BOEING SERVICE BULLETIN 777-32-0083**

BLANK PAGE

### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Number: 777-32-0083**  Original Issue: February 05, 2009 Revision 1: February 17, 2011 ATA System: 3211 **SUBJECT:** LANDING GEAR - Main Landing Gear - Retract Actuator Fuse Pin Inspection and Replacement BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplanes shown below. Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.

**DESCRIPTION CONFIGURATION**  **GROUP** 777 Airplanes with line numbers 1-163.

- 1

Airplane Models: 777-200, 777-300 **Group Variable Number**  1 WA001 - WA017 1 WA076 - WA080 1 WA086 - WA093 1 WA101 - WA104 1 WA116 - WA119 1 WA131 - WA137 1 WA171 - WA175

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 11 of 30**Group Variable Number**  1 WA196 - WA198 1 WA206 - WA211 1 WA221 - WA223 1 WA231 - WA232 1 WB001 - WB014 1 WB051 - WB068 1 WB101 - WB104 1 WB121 - WB125 1 WB131 - WB133 1 WB151 - WB153 1 WB161 - WB169 1 WB181 - WB186 1 WB231 - WB234 1 WB271 - WB272 1 WB276 - WB286 1 WB306 - WB307 1 WB311 - WB313 1 WB336 1 WB371 1 WB501 - WB504 1 WB531 - WB534 1 WB551 - WB552 1 WB591 - WB592 1 WB601 2. Spares Affected None. **B. Concurrent Requirements** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 12 of 30 **BOEING SERVICE BULLETIN 777-32-0083 C. Reason**  Accomplishment of this service bulletin will find and replace 112W1769-1 Retract Actuator Fuse Pins. The 112W1769-1 Retract Actuator Fuse Pins have been found to crack and fail earlier than the previously determined safe life limit of the pins. A fractured Retract Actuator Fuse Pin can cause the main landing gear (MLG) to extend without restriction and attempt to lock into position under high dynamic loads. Unrestricted MLG extension could cause structural damage to the side and drag brace lock assemblies, leading to unlocked drag and/or side braces which could result in landing gear collapse during touchdown, rollout or taxi. One operator reported that a right MLG 112W1769-1 pin sheared during normal flight operations. The failure occurred on a pin with 10,874 flight cycles. The left MLG pin was also inspected and was found to be cracked. Examination of the sheared pin concluded that the cracking was due to fatigue. Three other pins that were reported to have cracks had between 10,000 and 11,000 flight cycles. This service bulletin provides instructions to inspect the left and right MLG for 112W1769-1 Retract Actuator Fuse Pins and to replace the affected pins with 112W1769-3 pins. Boeing Service Related Problem (SRP) 777-SRP-57-0226 is related to this service bulletin. Boeing Service Letter (SL) 777-SL-57-011 is related to this service bulletin. Boeing Fleet Team Digest Article (FTD) 777 FTD 57-08005 is related to this service bulletin. **D. Description** Get access to the left and right MLG Retract Actuator Fuse Pins. Do an inspection of the Retract Actuator Fuse Pins to identify the part number. If an affected pin is found, replace the pin. If an affected pin is not found, no further action is required at that pin location. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 731, 741 777-200, 777-300 **E. Compliance** Accomplish Part 1 and Part 2 as required in Table 1 below in accordance with Paragraph 3., Accomplishment Instructions. **NOTE:** 1. The conditions, actions and compliance times below are based on flight cycles on each pin since new, not flight cycles of the airplane on which the pin is installed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 13 of 30 **BOEING SERVICE BULLETIN 777-32-0083 Table 1: Inspection and Replacement of Retract Actuator Fuse Pin**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition**

- Within 6 months after the Date of the Original Issueof this Service Bulletin.Inspect the pin in accordance with Part 1 - MLG Retract Actuator Fuse Pin Part Number Inspection. All Airplanes

- - No further action is re- quired for that fuse pin location. (a) Condition 1: 112W1769-3 MLG Retract Actuator Fuse Pin Installed.

- Within 6 months after the Date of the Original Issueof this Service Bulletin.Replace the pin in accordance with Part 2 - MLG Retract Actuator Fuse Pin Replacement. (a) Condition 2A: 112W1769- 1 MLG Retract Actuator Fuse Pin installed with greater than 10,000 flight cycles (FC).

- Before 10,000 FC on the pin or within 12 months after the Date of the OriginalIssue of this Service Bulletin, whichever occurs later.Replace the pin in accordance with Part 2 - MLG Retract Actuator Fuse Pin Replacement. (a) Condition 2B: 112W1769- 1 MLG Retract Actuator Fuse Pin installed with 8,000 to 10,000 FC.

- Before 8,000 FC on the pin or within 24 months after the Date of the OriginalIssue of this Service Bulletin, whichever occurs later.Replace the pin in accordance with Part 2 - MLG Retract Actuator Fuse Pin Replacement. (a) Condition 2C: 112W1769- 1 MLG Retract Actuator Fuse Pin installed with less than 8,000 FC.

(a) The 112W1769-3 MLG Retract Actuator Fuse Pin is a safe life limited part. Refer to 777 MPD Section 9 for the safe life limits. **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 14 of 30 **BOEING SERVICE BULLETIN 777-32-0083 G. Manpower**  **Elapsed Hours Task Hours**  **Number of Per- sons**  **Task**
0.75 1.50 2 Open Access 0.25 0.25 1 FIGURE 1 0.25 0.25 1 FIGURE 2 0.50 0.50 1 FIGURE 3 0.50 0.50 1 FIGURE 4 0.75 1.50 2 Close Access 3.00 4.50 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  - 3628.0 - 2.7 All
**I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. Boeing Service Letter 777-SL-57-011 b. Boeing Service Related Problem (SRP) 777-SRP-57-0226 c. 777 Aircraft Maintenance Manual (AMM) 06-44-00, 32-00-15, 32-00-30, 32-11-01 d. 777 Fleet Team Digest (FTD) 57-08005 e. 777 Maintenance Planning Data (MPD) Section 9 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin
**Title Drawing Number**  Installation - Main Landing Gear 161W0000

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 15 of 30 **BOEING SERVICE BULLETIN 777-32-0083**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 or operators. **K. Publications Affected Chapter-Section** 

**Publication** 32-11 777 Illustrated Parts Catalog **L. Interchangeability and Intermixability of Parts** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 16 of 30 **BOEING SERVICE BULLETIN 777-32-0083 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown below. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The parts 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 RESPON DER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFOR**  **MATION**
**Unit Price as of the orignal issue date** **of this Service Bul letin (US Dollars)**  **ROLT as of the original**  **issues date of this Ser**  **vice Bulletin (Calendar**  **Days) Name**  **Part Number**

$769.00 588 MLG Retract Actuator Fuse Pin 112W1769-3 **B. Industry Support Information** Boeing warranty remedies are not available for the inspection, and/or repair 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.
**Notes Existing Part**  **Number Name**  **QTY New Part Number**  (a) (b) (c) 112W1769-1 MLG Retract Actua- tor Fuse Pin 2 112W1769-3 (a) Discard the existing part. (b) This part is used in production. (c) You cannot use the existing part to replace the new or changed part.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 17 of 30 **BOEING SERVICE BULLETIN 777-32-0083**2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** (a) Corrosion Inhibiting Material

- BMS3-27 (BMS3- 38 Optional) Pin, Cotter 2 BACP18BC03A12P (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 18 of 30 **BOEING SERVICE BULLETIN 777-32-0083 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. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Obey all of the warnings and cautions given in the specified manual sections. 4. 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 5. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 6. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 7. 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. 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. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 19 of 30 **BOEING SERVICE BULLETIN 777-32-0083 B. WORK INSTRUCTIONS**  1. Install the Main Landing Gear (MLG) downlock pins. Refer to 777 AMM 32-00-30 as an accepted procedure. 2. Install the MLG safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure. 3. Open the following access panels on the left and right wing. Refer to 777 AMM 06-44-00 as an accepted procedure. – 551DB - Inboard Fixed Trailing Edge Panel – 651DB - Inboard Fixed Trailing Edge Panel 4. Do Part 1 - MLG Retract Actuator Fuse Pin Part Number Inspection. a. Condition 1: 112W1769-3 MLG Retract Actuator Fuse Pin installed. (1) No further action is required for that fuse pin location. b. Condition 2: 112W1769-1 MLG Retract Actuator Fuse Pin installed. (1) Determine the total flight cycles on the MLG Retract Actuator Fuse Pin since new. (2) Do Part 2 - MLG Retract Actuator Fuse Pin Replacement within the compliance time in accordance with Paragraph 1.E., Compliance Condition 2A, 2B or 2C for that fuse pin location. (3) No further action is required for that fuse pin location. 5. Close the following access panels on the left and right wing. Refer to 777 AMM 06-44-00 as an accepted procedure. – 551DB - Inboard Fixed Trailing Edge Panel – 651DB - Inboard Fixed Trailing Edge Panel 6. Remove the MLG safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure. 7. Remove the Main Landing Gear (MLG) downlock pins. Refer to 777 AMM 32-00-30 as an accepted procedure. 8. Put the airplane back into serviceable condition. **Part 1 - MLG Retract Actuator Fuse Pin Part Number Inspection** 1. Inspect the MLG Retract Actuator Fuse Pins to determine the part numbers in accordance with FIGURE 1 for the left MLG and FIGURE 2 for the right MLG. As an alternative, a review of the maintenance or delivery records can be used if the part number of the installed MLG Retract Actuator Fuse Pin can be positively determined. **Part 2 - MLG Retract Actuator Fuse Pin Replacement** 1. Replace the MLG Retract Actuator Fuse Pin in accordance with FIGURE 3 for the left MLG and FIGURE 4 for the right MLG.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1: February 17, 2011 20 of 30 **BOEING SERVICE BULLETIN 777-32-0083 FIGURE 1: LEFT MLG RETRACT ACTUATOR FUSE PIN INSPECTION**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1 February 17, 2011 21 of 30 **BOEING SERVICE BULLETIN 777-32-0083 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** to determine the partnumber which is located on the head of the pin. 1 112W1769 Retract Actuator Fuse Pin Inspect 1

**FIGURE 1: LEFT MLG RETRACT ACTUATOR FUSE PIN INSPECTION (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1 February 17, 2011 22 of 30 **BOEING SERVICE BULLETIN 777-32-0083 FIGURE 2: RIGHT MLG RETRACT ACTUATOR FUSE PIN INSPECTION**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1 February 17, 2011 23 of 30 **BOEING SERVICE BULLETIN 777-32-0083 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** to determine the partnumber which is located on the head of the pin. 1 112W1769 Retract Actuator Fuse Pin Inspect 1

**FIGURE 2: RIGHT MLG RETRACT ACTUATOR FUSE PIN INSPECTION (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1 February 17, 2011 24 of 30 **BOEING SERVICE BULLETIN 777-32-0083 FIGURE 3: LEFT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1 February 17, 2011 25 of 30 **BOEING SERVICE BULLETIN 777-32-0083 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Refer to 777 AMM32-11-01 as an accepted procedure. Keep washers and nut. 1 112W1769-1 Retract Actuator Fuse Pin Remove 1

Refer to 777 AMM32-11-01 as an accepted procedure. A new or overhauled pin is acceptable. 1 112W1769-3 Retract Actuator Fuse Pin Install (New) 2

**FIGURE 3: LEFT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1 February 17, 2011 26 of 30 **BOEING SERVICE BULLETIN 777-32-0083 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** lightly coating the thread group of the pin and the washer faces. - BMS3-27 (BMS3-38 optional) Corrosion Inhibiting Material Apply 3

Tighten nut to 15-25 in-lbs over maximum run on torque. 1
- Nut Install (Kept) 4

to the nearest castellation to install the cotter pin. 1
- Nut Loosen 5

1 BACP18BC03A12P Cotter Pin Install (New) 6 Wipe off all excess material. - BMS3-27 (BMS3-38 optional) Corrosion Inhibiting Material Remove 7

**FIGURE 3: LEFT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1 February 17, 2011 27 of 30 **BOEING SERVICE BULLETIN 777-32-0083 FIGURE 4: RIGHT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1 February 17, 2011 28 of 30 **BOEING SERVICE BULLETIN 777-32-0083 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Refer to 777 AMM32-11-01 as an accepted procedure. Keep washers and nut. 1 112W1769-1 Retract Actuator Fuse Pin Remove 1

Refer to 777 AMM32-11-01 as an accepted procedure. A new or overhauled pin is acceptable. 1 112W1769-3 Retract Actuator Fuse Pin Install (New) 2

**FIGURE 4: RIGHT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1 February 17, 2011 29 of 30 **BOEING SERVICE BULLETIN 777-32-0083 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** lightly coating the thread group of the pin and the washer faces. - BMS3-27 (BMS3-38 optional) Corrosion Inhibiting Material Apply 3

Tighten nut to 15-25 in-lbs over max run on torque. 1
- Nut Install (Kept) 4

to the nearest castellation to install the cotter pin. 1
- Nut Loosen 5

- BACP18BC03A12P Cotter Pin Install (New) 6 Wipe off all excess material. - BMS3-27 (BMS3-38 optional) Corrosion Inhibiting Material Remove 7

**FIGURE 4: RIGHT MLG RETRACT ACTUATOR FUSE PIN REPLACEMENT (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 05, 2009 777-32-0083 Revision 1 February 17, 2011 30 of 30 **BOEING SERVICE BULLETIN 777-32-0083**